EFTA00011669

OM No.21200020 Ettoternie TM:alp Wetter Ems. 541/2011 Exp. el, -- MAJOR REPAIR AND ALTERATION For FAA Use °My US Department Of Tm114104/111011 FOsteral Aviation (Airframe, Powerplant, Propeller, or Appliance) Adednitrallen INSTRUCTIONS: Pita or type all entries. See Title 14 CFR §43.9. Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructIons and disposition of tNs form. This report Is required by law (49 U.S.C. §44701). Failure to report can result Ina mil penally for each such violation. (49 U.S.C. §46301(a)) Nationality and Registration Mark Serial No. UNITED STATES / N188TS RK-244 1. Aircraft 'make Model Series RAYTHEON AIRCRAFT COMPANY 400A Name (As shown on registration certificate) Address As shown on registration certificate) Address 2. owner THORAIR LLC 04. SANDUSKY SUM OHIO re 44871-2218 cam/ UNITED STATES 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Untt Make Model Serial No. MYTHEOMARCROST COWAIN (As described in Item I above) RK.244 AIRFRAME ril I I ❑ POWERPLANT ❑ n PROPELLER Type APPLIANCE Manufacturer I Conformity Statement A. Agency's Name and Address B. Kind of Agency in Coastal'. Aviation LLC U. S. Genic/mad Mechanic I Idanufaclurer Meese Foreign Cerbhcated Ilechanic C. Certificate No. cis CLEVELAND sys OH 7 Conticaled Repair Station ai 44143 c.,,,,,,,, USA Certificated Maintenance organization CRS#WC7R346J D. I certify That the repair and/or alteration made to the una(s Identified In Item 5 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and That the Information furnished herein is true and Extended range fuel per 14 CFR Part 43 App. B 10/04/2019 umTotemic. Pursuant to the authority g i, rsons spec ' • .. , t e un nleg In Item 5 vial nspected in the manner prescribed by the Administrator of the Federal Administreti• ' and is I Approved Rejected — FM RI Standards Maintenance Organization — Persons Approved by Canadian Manufacturer Department of Transom' ____j Inspector BY MI Other (Specify) FM Designee ✓ Repair Station pectIon Authorization Certificate or Signature/Da f Author ed Individual Desi nation No. CRS# __ WC7R346J ...._--------- 10/04/2019 FAA Form 337 (10/06) Page I EFTA00011669 NOTICE Weight and balance or operating limitation changes shall be entered In the appropriate aircraft record. M alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished (Il more space is moulted. attach additional sheets. Identify mitt steal? nationally end registratIon m** end date work completed) UNITED STATESIMOSTS mov2019 Nationality and RegistraMn Mark Date Engine Inlet Rivet Repair Installed blind rivets in place of the damaged solid rivets on the lip of the right hand engine inlet forebody assembly part number 541000-004, serial number R0010, In accordance with nextant aerospace engineering order NT-EO-1118-31 rev IR dated 11/29/2018 with FM form 8110-3 dated 11/30/2018. Instructions for Continued Airworthiness: Follow the maintenance inspection practices in the aircraft maintenance manual. Inspection intervals shall remain as indicated in the aircraft maintenance manual or operators approved inspection program as appropriate. Weight and Balance unaffected. Reference Constant Aviation work order CCM-3160 END =Additional Sheets Arc Attached FAA Form 337 (10/06) Pagc 2 EFTA00011670 U.S. DEPARTMENT OF TRANSPORTAllON 1. DATE FEDERAL AVIATION ADMINISTRATION November 30, 2018 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MANE 3. MODEL NO. 4. TYPE Mkorst &*e. Propeller, ea) S. NAME OF APPLICANT Textron Aviation N541000-004 Forebody Assy Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA SLREIffla NT-EO-1118-31 Engine Inlet Rivet Repair. Rev. IR November 29, 2018 --- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval Is only for the engineering data. It Indicates the data listed above demonstrates compliance only vAth the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements." 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. e. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody May PIN N541000-004, SRN R0010 under Nextant Aerospace Work Order No.10585.1.1. 9. APPLICABLE REQUIREMENTS (UM speckle sections) CFR Title 14 Part 25.301(25-23), 25.303(25-23], 25.305(a)(bUcX25-23), 25.307(a125-231, 25.801[25-00), 25.603(aXbXc)(25-38), 25.605(a){25-00), 25.807(25-23), 25.809(eXbX25-00], 25.811(25-2n 25.813(aXbXcX25-00], 25.619[25-23]. and 25.625(a)(0XcX25-231. re. CERTFICATION - Under minority wired bydrecelon of the AdrranIstralor end In accordance with conditions and Ilmitallons of appcdnMsent under 14 CFR Pen 193. dots nand above and on 'Bathed sheds numbered _BA, have been emartned in accordance with established procedures all found es coos* et appacsoie requirements of the AInvortnIness Standards Listed ❑ Recommend approval of these data I (We) Therefore FrA. Approve these data it SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTAttVE(S) 12. DESIGNATION NUMBERS(S) I3. CLASSIFICATION(S) pre:7 4 Z.--; DERT-410115-CE Structures .-- FAA Form 8110.3 (03-10) SUPERSEOES PREVIOUS EDITION File Number. H18777-01 Page 1 of 1 EFTA00011671 EFTA00011672 i Olaf NO. 2120-0920 Ekciront Trackhg Haw Ent SMI OQM e (6, MAJOR REPAIR AND ALTERATION For FAA thia Oral US Departalerd 0/ Trenelarlation Federal Aviation (Airframe, Powerplant, Propeller, or Appliance) taimiwarzion INSTRUCTIONS: Print or type all entries. See Tide 14 CFR §43.9 Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for Instructions and disposition of this form. This report is required by law (49 U.S.C. §44701). Failure to report can result In a cNa penalty ler each such Notation. (49 U.S.C. §46301(a)) Nationakty and Registration Mark Serial No. UNITED STATES / N188TS RK-244 1. Aircraft Make Model Series RAYTHEON AIRCRAFT COMPANY 400A Name (As shown on registration certa1cato Address As shown on registration certificate) At:keen a Owner THORAIR LLC an SANDUSKY ham 011I0 za 44871-2218 cosier UNITED STATES 3. For FAA Uso Only 4. Type ill. Unit identrestIon Repair Alteration UM Make Model Serial No. [j AIRFRAME WI RATIMONAMCIMFTCOSIMY (As described in Item I above) RK-244 ❑ ❑ POVVERPIANT PROPELLER 11Y01 I I APPLIANCE Manufacturer 6. Conformity Statement A. Agencys Name and Address B. Hind Of Agency sew Constant Aviation LLC U. S. CerWketed Mechanic 1 Manufacturer Newt Portion Certificated Mechanic C. Certificate No. a, CLEVELAND suds OH I Ceblitaied RePM/ Station r zis 44143 c,,,,....., USA Certificated Maintenance Organization CRS#WC7R346J D. I certify that the repair and/or alteration made to the unit(s identified in Item 5 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Mfonnallon Wished herein is true and Extended range fuel per 14 CFR Part 43 ❑ APP. B 10/04/2019 turn-Vs-Service Pursue I to the authority g nri in item 5 Inspected In the manner prescribed by the Administrator of the Federal a ion Administrati end Is I Approved Relected t..--- FAA Fit. Standards Persons Approved by Canadian Manufacturer Maintenance Organlzabon Department 01 Transport Inspector BY — M i Other (Specify) FAA Designee Repair Station spection Authorization Certificate or Signature/Da AW d IndNidual Designation No. CRS# WC7R346J .----------------- / 10/04/2019 FAA Form 337(10/06) Page I EFTA00011673 NOTICE Weight and balance or operating limitation changes shall be entered ✓n the appropriate aircraft record. M alteration must be compatible with ail previous alienations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (f mote space Is reputed. attach additional sheets ;den* Mih sitar* nationality and regisfratton math and date soak completed) UNITED STATES! NIESTS IW04/2019 Nationality end Registration Mark Date Engine Inlet Rivet Repair Installed blind rivets in place of the damaged solid rivets on the lip of the right hand engine inlet forebody assembly part number 541000-004, serial number R0010, in accordance with nextant aerospace engineering order NT-ED-1118-31 rev IR dated 11/29/2018 with FM form 8110-3 dated 11/30/2018. Instructions for Continued Airworthiness: Follow the maintenance inspection practices in the aircraft maintenance manual. Inspection intervals shall remain as indicated in the aircraft maintenance manual or operators approved inspection program as appropriate. Weight and Balance unaffected. Reference Constant Aviation work order CCM-3160 END- FlAdditional Sheets Are Attached FAA Form 337 (10/06) Page 2 EFTA00011674 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE • 2. MAKE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION S. MODEL NO. 4. TYPE (Aber* Engine, People, art) & NAME OF APPLICANT November 30, 2018 Textron Aviation N541000-004 Forebody Assy Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA & PENTIF(GM.PN 7. TITLE NT-EO-1118-31 Engine Inlet Rivet Repair. Rev. IR November 29, 2018 — —END Notes: 1) The structural aspects only of the above Ilsted data are approved herein. This approval is only for the engineering data. It Indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements." 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. • a. PURPOSE OF DATA: Engineering data to support repair procedure for Textron 400A Forebody May PIN N541000-004, S/N R0010 under Nextant Aerospace Work Order No.10565.1.1. 9. APPLICABLE REOUREMENTS (LMIIPodfic MadanN CFR nee 14 Pad 25.301[25-23], 25.303(25.23], 25.305(a)(b)(cX25-23), 25.307(aX25-23), 25.801[25-00), 25.603(aXb)(c)[25-38], 25.605(a)(25-00), 25.807[25-23), 25.609(a)(bX25-001, 25.811[25-23), 25.613(eXbXcX25-00), 25.619[25-23), and 25.625(aXbXcX25-23). 10. CERTIFICATION - WON surely veiled byAvalon of the Adeninistrstor end In azeardance WM conekns end IrkatIons of appolnonent under I 4 CFR Pert 163. data bled above and cn attached thetas numbered N/A have been exalted In accordance wilh colablahed procedurea and found to complyv/4h aPIANON requarrmega of the AINronnIness Standards Listed p Recommend approval of these data I (We) Therefore El Approve Omni dale I I. SIGNATURES) OF DESIGNATED ENGINEERNO REPRESENTAT1VE(SI 12. DESIGNATION NU)eERS(S) 13. CLASSFICATION(S) ptridia ..----C.o. DENT-410115-CE Structures FM Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Flle Number H18777-01 Page 1of 1 EFTA00011675 S • • EFTA00011676 nextant aerospace • //gerMAGINED immer //Rang» I EO Ik NT-EO•1118-31 I Tine: Engine Intet Rivet Repelt ENGINEERING ORDER ARTICLE DESCRIPTION Locklithaageke Alrenol SoorialNaait) Teatret Aviden 400A See Rerrans onnette nier Mam Die purpose of Ibis EO is to am for te ins:asem "kid Sits gmt CR32124-XX)of »vroor-iet° lengt in pace of te damaged sol»rivet (PIN: MS20426AD5-XX)on tie RH enge Int» forebody neemt*: The repair wil be accennistied on It» engen ijkt forelndy assembly (PIN: N541000-004. Sin. Ft0010) REGULATORY Aa~dPaMorinhaN Aa tasa /t~ clualcabeSMOZIFUFAI*pen/ b~d toSan,~ISa I44JOR • - anion, MMO LU ~WeInhAeOreal Pmbn OSPeperibiba D YES ISINO 01160RO D YES NO O YES giro • YES Ca NO Das tble EO signilkently aflect wenk beaam otiodural strengt eircraft perbmara peperplant opreten, light dandaddicre. or ober .' MAJOR ... ' /APK* aineortiiness goalies? b YES OIO Cm tb EO be accompliihod by accepled paden a dementary operator»? MINOR — I D YES ~gr MINOR IIPompen done, oe& Ibis EO special* affect inwortelt»? ' St !Duo assks. ~ISW Ballifo Clep MA~COONINA tE3 1/MOR O MNOR Ei STC (Ne ST02371LA) D YES 0 NO E3 YES 1:1 NO GENERAL • CrimenUWAticivnnta repro 1: Oemaged Rivel Locatief, en RNEngte Wal eig, MotelStan) remenitenyeas Resafidaterom O YES 0 NO Het PM: N541000-004 SIN: R0010 Wtr. 10565.1.1 (Original WO. IR wit approval) 13003 (IR.1 WO) OberrytAex Proclise Specificeer:n: CA;1015 REVISION ~WIN OM CfACRPTION ECII k REV4E0 Iff IR I 1129018 kik" Proposal MA R Avahalumov IRA 1071/2019 Updated b gemme sper& engerdringt trem ceesenellen. dur Is Snot and 81104 at R stands WA P. Avabalumov ACIION DAM PrepreedEly 10/1/2019 ander' By 10/1/2019 ikowdbyPinUsa Approved By vinv• 1011/2019 >019.10.02 Wil.»mto Page 1013 Form No. NT.E0-01I Ree A This Document h Unzontroted Onc• Ptt:lied EFTA00011677 • • • EFTA00011678 nextant aerospace //fatMAGMED //U/da! //REBORN ENGINEERING ORDER EO a: NT.EO1118-31 Title: Engine Inlet Rivet Repair 1 PROCEDURES ITEM DISTRUCTIONS Visually rasped the engine inlet hp and barrel for any other damaged, missing a loose bsteners. 1 • If no addennal discrepancies are detected, calla° with repair as °dined below. CiEs•C« - If additional descepamies me rant canted Nettie Aerospace la depositors 00 Visualy inspect No engine roan es defined in Sib Task 724140420-801ofhi Mann Inlombonel LivE WtINTENANCE NVE MANUAL- FJ443AP 111030402 (blest re' ). C.A.C. 2 • If no additional cracrepanOes are detected. conatie with repair u coined below. e OSS • If Mai:anal durepancies me noted. corded Nettant Aerospace for deposition. 3 Locale damaged rivets as shown in Figure 1 end carefully and completely dal al the remaining hateier material. making sure not to damage, ably, a oversize the fastener hole. Prepare the holed the missing bsteners for instillation of Caiegyailax Riven RN CR3212-5.XX in feu of nominal solid rivets MS20426AD540C 41/2 • Prepare ham by aging and reaming to the required rivet Sae, as required, per ClwayMaa clocunent CA.1015 Cs4.c, 4 • Determine be correct gdp Sangth for to fasteners to be used. cabana Cherybax document CA-1015. 0.' • Using the manufacturers reornmended installation ton install Ne reel fasteners per ChemyMax dowdiest CA.1015. • Inspect the conedeted rivet set lo verify te lodeng coiled has been inserted and the stem has hazed flush with the rivet head. Refer to Chemyttix anseent CA-1015 Ix Inspection ad verification. -END • LAKTATIONS None INSTRUCTIONS FOR CONTINUING AIRWORTHINESS (ICA's) Follow the maintenance inspection practices in Ne aircraft rnslaenevce manual. Inspection intervals shall roman as indicated vita eircrin't marilenanco manual or waralas approved inspection program as appropnan COMPLIANCE AH.:RNI M0DEI ~AT ~TPA,» AlxaAfleB1W NIMILA San crIstAtall A t/uS8 13 lc 2•Vel DATE RSA WC7R346J 10/27 Page 2 ol 3 Form No. NT.E0-01I Rev A This Document is Unconuolled Once Printed EFTA00011679 • • • EFTA00011680 ry nextant aerospace //REINiAGiNED //RESULT //MORN ENGINEERING ORDER EO /: NT-E0:11111-31 I Title: Engine Inlet Rivet Repair • Figure 1: Damaged Rivet Location on RH Engine Inlet Up (Typical Shown) • Form No. NT•EOA1 I Rev A Page 3 ol 3 This Document Is Uncontrolled Once Printed EFTA00011681 S • • EFTA00011682 DNB ,40- 2120'0020 Elearerie Track0g Witco Exp. Pamela 0 US DepeVret MAJOR REPAIR AND ALTERATION For FAA Use Only of Tranwortefon (Airframe, Powerplant, Propeller, or Appliance) Wend Avliclon Adearileintlein INSTRUCTIONS: Print or type all entries. See Title 14 CFR §43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition oft* form. This report is required by law (49 U.S.C. §44701). Failure to report can result in a civil penalty lor each such violation. (49 U.S.C. §48301(a)) Nationality and Registration Mark Serial No. UNITED STATES / N188TS RK-244 1. Aircraft Make Model Series RAYTHEON AIRCRAFT COMPANY 400A Name (As shown on registration certificate) Address (As shown on registration certiecate) Address 2. Owner THORAIR LLC coy SANDUSKY SYS OH 2p 44871 Cathy UNITED STATES 3. For FAA Uso Only 4. Type 6. Unit identification Repair Alteration Unk Make Model Serial No. MOEN I MYPEOP.A0CRAFT COMM" m, AIRFRAME (As described in Men; 1 above) -1 POWERPLANT PROPELLER Type APPLIANCE Menet/were.. 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Now CONSTANT AVIATION U. & Caollkated Mechanic I Manufacturer Adana Foreign CatilloNed Mechank C. Certificate No. Ott CLEVELAND sew OR i Certificated Repair Stallion 10 44143 Candy UNITED STATES ♦ CalLated Maintenance Organ/wk., CRS# WC7R346J D. I certify that the repair andior alteration made to the unks Identified in Item 5 above and deathbed on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information furnished herein Is true and correct to the best of m knovA i • i i Extended range fuel Sign per 14 CFR Part 43 Am. B 10/7/2019 7. A • proval for Return to Service Pursuant to the authority paten persons specified below. the Lilt Wenn, In item 6 va tinspected In the mama prescribed by the Administrator of the Federal Aviation Administration and la I Approved Rigel:led --"' FAA Fit. Standards — — — Persons Approved by Canadian Manufacturer Maintenance OrgaNzatlon Depaitrnen1 of Transport Inspector BY = Other (Specify) FM Designee I Repair Station Inspection Authorization Certificate or ^ Signature) . e uthori ed Individual Designation No. C RS# ,,i WC7R346J 10/7/2019 FAA Form 337 (10/06) Page 1 EFTA00011683 NOTICE Weight end balance or operating Nmitallon changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished almore space is requirec( attach additional sheets. Mandy *eh thrash nationally and registration mark and date oak completed) mire, STATES /N1887/3 107/2019 Nationality and Registration Mark Date INSTALLATION OF ADS-B OUT ON PART 25 AIRCRAFT Complied with installation of BHE & Associates, LTD. STC# ST11216DS Installation of Automatic Dependent Surveillance-Broadcast Out on Part 25 Aircraft IAW BHE & Associates,LTD. Master Data List (MDL) number 584-00-0001 Rev.G. Dated 8/29/2019. Reference BHE & Associates, LTD. Aircraft Flight Manual Supplement (AFMS) Installation of ADS-B Out on Part 25 Aircraft. Report number 584-00-0046 Rev.C. Dated 5/4/2019. Reference BHE & Associates, LTD. Electrical Load Analysis (ELA) Installation of ADS-B Out on Part 25 Aircraft. Report number 584-00-0050 Rev.B. Dated 10/9/2018. Reference BHE & Associates, LTD. Instructions for Continued Airworthiness (ICA) Installation of ADS-B Out on Part 25 Aircraft. Report number 584-00-0047 Rev.D. Dated 3/19/2019. Weight and Balance: Reference calculated weight and balance dated 10/7/2019. Equipment List: Updated. Reference Work Order: CCM-R3160. END riAdditional Sheets Ne Attached FAA Form 337 (10/06) Page 2 EFTA00011684 vs/miaow (gamma etpartmeat IT'ramprtation Feetativiationiftfothistratlim Supplemental!)re Cergficate .9Ifiumbir ST11216DS MU traffic-aulaudto: BHE & Associates, Ltd. San Antonio, TX 78216 tert,fes doe for dap is the type asignfi r dejedfruandert aid Me limaationsaftatcotdiftims denybtr as Jpenfreanron meets de airavuotheartythetwas iltaft25 ?Pi/federal Aviation Regulations. Original Product — Type Ceniticate Number: Make: See attached AML Model: See attached AML See attached approved model list (AML) Description orlype Design Change: Installation of automatic dependent surveillance-broadcast (ADS-8) out on Part 25 aircraft, in accordance with Master Data List 584-00-0001, Revision IR, dated June 29, 2018 or later FM approved revision. For Instructions for Continued Airworthiness and Airplane Flight Manual Supplement reference the attached AML. Limitations and Conditions: 1. The installer must determine whether this design change is compatible with previously approved modifications. 2. If the holder agrees to permit another person to use this certificate to alter a product, the holder must give the other person written evidence of that permission. 3. See attached AML for additional limitations and conditions. 'flu a/41fmk.amide supporting eta wildis the 6ashforappronisiende fit nittsuntwifere4 saspellatid;andinrokeefora termination ate is oderwite ene6/10flay t6efiminu aide Fralreigratioll dIteladdrinu Date of Application: February 9. 2018 Date Reissued: Date of Issuance: June 29. 2018 Date Amended: roy Oben fiticitaial 3(9watt/re 9itk VT ORB Aviation Project ODA Administrator ODA-831473-SW Any alteration ot this cert.ficale is constable by a fine of not exCeedngS1.000. or imprisonment not exceeding 3 years. or bolt. Dies certificate may be transferred or made evade to third persons by licensing agreements en accordance with le CFR 21.47. Possession of this Supplemental Type Cerbncale (STC) document by persons otter pen the STC heeler does not commute rights to the design data nor to alter an aireaft aircraft engine, or propeller. The STCs supporting documentation (drawings. instructions, speofications, flight manual supplements. CC ) is the ptcperty of the STC holder. An SIC hotter who aeon a person to use the SIC to ate( an airaaft. airaaft engine, or propeller moat Mande that person Mm mitten permission acceptable tome FAA (Ref le CFR 21 120) FAA Form 8110-2 (5114) Page i of 2 EFTA00011685 SledStates ofilmen?a Department triansportation ediraf2viationAtfmtnistratthrt Supplemental75pe Certificate 1NSTRUCITONS The transfer endorsement below may be used to notify the appropriate FAA Aircraft Certification Office of the transfer of this Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him. Transfer Endorsement Transfer the ownership of Supplemental Type Certificate Number: ST11216DS To (Name and address of transferee) From (Name and address of grantor) Extent of Authority (if licensing agreement): One etransfer Signature ?grantor My alteration of this certificate is punishable by a fine of not exceerfing 51.000. or imprisonment not exceeding 3 years. or both. This certificate may be transferred or made available to third persons by licensing agreements in accordance with 14 CFR 21.47. Possession *falls Supplemental Type Certificate (STC) document by persons other than the SIC holder does not constitute rights to the design data nor to alter an aircraft. aircraft engine. or propeller. The Sits supporting documemadon (drevangs. instructions, specifications, flIgM manual supplements, etc.) is the property of the SIC holder. ,M STC holder who allows a parson to use the STC to alter an aircraft. aircraft engine. or propeller must provide That person with written permission acceptable to the FAA. (Ref. 14 CFR 21.120). FAA Form 8110-2 (5/14) Page 2 of 2 EFTA00011686 DocuSign Envelope ID: CFB828B5-6FE8-4C80-A4E3-5461F9B20045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR THE INSTALLATION OF ADS-B OUT ON PART 25 AIRCRAFT REPORT No. 584-00-0047 Revision D Date: 03/19/2019 NOTICE: The contents of this document are proprietary to BHE & Associates, Ltd. and shall not be disclosed, disseminated, copied, or used except for purposes expressly authorized in writing by BHE & Associates, Ltd. BHE & Associates, Ltd. San Antonio, TX 78216 USA CAGE: N/A Rerd By VLDRB, FSCM 47M27, Shl 1 of 39, 2019/Marl19 EFTA00011687 DocuSign Envelope ID: CFB628B5-6FES-4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS NOTICES AND SIGNATURES Notices: Note: Paragraphs and/or figure numbers followed by" I" indicate a change by latest revision. Approval Signatures: REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 2 of 36 Rem By VT-DRS. FSCM 471027, Sht 2 01 39. 2019/Mer/19 EFTA00011688 DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9820045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Record of Revisions - .. : -l7 - ..-:.4 t....... ... ., •-• 106 NIOtOY0 Revision Number" ri Ion of change . ' . Dats .- IR Initial Release 5/9/18 Page 8, Section 1.1 revised transponder and GPS part numbers. A 6/27/18 Page 10, Section 2 remove' light Hours' from Table 4 Page 4, Revised list of aircraft models in Introduction B Pages 9, 24-25, 28-29, Revised aircraft models 11/6/18 in Tables 3, 7, and 9. Pages 8 and 28, clarified wording for installation. Revised Table 3 on page 9 Revised Table 4 on page 10 Revised Table 5 on page 26 C Revised Table 6 on pages 27 & 28 1/18/19 Revised section 6.1.9 on page 31 Revised figures on pages 13 & 20, Added figures on pages 14, 17 & 18 Added STC number on page 4. D Added figure on page 24. 3(lcitict Revised form in Appendix C. REPORT No. 584-00-0047, Rev: D BHE & Associates. Ltd. Page 3 of 36 Rerd By VT-DRB, FSCM 471,0127, Sht 3 of 39, 2019/Mar/19 EFTA00011689 DocuSign Envelope ID: CFB62885-6FEB-4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS INTRODUCTION These Instructions for Continued Airworthiness (ICA) document have been developed using the guidelines in Appendix "H" of 14 CFR Part 25 as required by §FAR 21.50 and §25.1529. This document is designed to provide avionics and aircraft technicians with sufficient information to inspect, troubleshoot, adjust, repair, test, remove, and install ADS-B on the following Part 25 Aircraft. • Bombardier Inc. - CL-600-1A11, CL-600-2Al2, CL-600-2B16 (Challengers) • Gulfstream Aerospace -1125 Westwind Astra, Astra SPX, Gulfstream 100, G150 • Gulfstream - G-1159, G-1159A, G-1159B, G-IV, GV • Gulfstream - 200 • Sabreliner - NA-265-65, NA-265-70, NA-265-80 • Textron Aviation Inc. — 500. 550, S550, 560 (Citation) • Textron Aviation — 400, 400A (Beechjet) • Textron Aviation - 650 • Textron Aviation - HS.125 Series 700A, HS.125 Series 700B, BAe.125 Series 800A, BAe.125 Series 8006, Hawker 800XP, Hawker 750, Hawker 850XP, Hawker 900XP • Learjet - 60 (STC Aircraft) • Dassault Aviation — Falcon 10, Mystere-Falcon 50, Mystere-Falcon 20-05/D5fE5/F5, Mystere-Falcon 200, Mystere-Falcon 900 Table 1: Equipment Type Description New CPN Qty DO-260B ADS-B Out TOR-94 Transponder 622-9352-502 0, 1 or 2* TDR-94D Transponder 622.9210-502 0, 1 or 2* GPS1203C GPS Receiver 84327-50-XXXX 0 or 1 CI 429-200 GPS Antenna CI 429-200 0 or 1 GPS-40005 GPS Receiver 822-2189- 0, 1 or 2 004/005/006/007/010/011/100 *Either TOR-94 or TDR-94D will be installed. The above equipment is installed in accordance with FM Supplemental Type Certificate No. ST11216DS . See the List of Applicable Publications (LOAP) in Appendix A of this document. The publications listed in the LOAP constitute the required information essential for continued airworthiness for the aircraft. The documents contained in the LOAP are a necessary part of this ICA and the latest revision should be available to maintenance personnel when performing maintenance. The STC holder will continue to monitor changes to the ICA that were the basis of the supplementary ICA and provide revised supplemental ICA as necessary. The information in this document supplements or supersedes the original manufacturer's maintenance manual only in those areas listed. For limitations, procedures and other information not contained in this document, refer to the aircraft manufacturer's maintenance manuals, illustrated parts manuals and wiring diagrams or the vendor manuals as listed in the LOAP. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 4 of 36 Reid By VT-DRB, FSCM 47MZ7, Shl 4 of 39. 2019/Mar/19 EFTA00011690 Docu&an Envelope ID: CFB628B5-6FE841C8D-A4E3-5461F9B20045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS RECORD OF REVISIONS For continuous use of this document, this document must be maintained in current revision status. Each time the STC holder finds it necessary to revise this document; a revision will be distributed to all users of the STC. Revisions will be supplied to the customer by: a) E-mail with an attached PDF file, or b) Compact Disc (CD) via mail Changes to this document will be incorporated by an updated revision to the complete document. All pages will indicate the "new" revision level. Upon receipt of the new revision, the previous revision should be discarded and replaced with the updated, current, revision. Changes to this document will be listed in the revision block on page 3. It is the responsibility of the person(s) performing maintenance on the installed system to ensure that this document is current prior to performing this maintenance. The current revision number may be verified by contacting the STC holder, BHE & Associates. Report any discrepancies to the installation of this STC using the form in Appendix C of this document. Once filled out the form must be sent to both the ODA and the STC holder. Their addresses are as follows: ODA VT-DRB Aviation Consultants San Antonio, Texas 78216 STC Holder BHE & Associates Ltd. San Antonio, Texas 78216 REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 5 of 36 Rani By VT-ORB. FSCM 47M27. Sht 5 of 39, 2019/Marf19 EFTA00011691 DocuSign Envelope ID: CFB62885.6FE84C8Da4E3•5461F982D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS TABLE OF CONTENTS INTRODUCTION 4 RECORD OF REVISIONS 5 1 SYSTEM DESCRIPTION 8 1.1 GENERAL 2 AIRWORTHINESS LIMITATIONS 10 2.1 Inspection Intervals 10 2.2 Inspection Program 22 2.3 Inspection Method 22 2.4 Eddy Current Inspection 28 3 MAINTENANCE PRACTICES 29 3.1 Removal/Installation 29 3.2 Access Location 29 4 POWER DISTRIBUTION 30 4.1 Circuit Breakers by Bus 30 5 SYSTEM TROUBLESHOOTING 31 6 INSPECTION REQUIREMENTS 31 6.1 Scheduled Inspections and Maintenance Checks 31 6.2 Wiring 34 Appendix A — List of Applicable Publications Al Appendix B — Special Tools and Equipment B1 Appendix C — Discrepancy Reporting Form Cl REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 6 of 36 Red Ely VT-DRB, FS0.4 47k4Z7, sat 6 of 39. 2019,MartI9 EFTA00011692 DocuSign Envelope ID: CFEt628B5.6FE8-4C8D-A4E3-5461F9B20045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LIST OF FIGURES AND TABLES Table 1: Equipment 4 Table 2 Equipment List 8 Table 3 Equipment by Aircraft 9 Table 4 Inspection Intervals 10 Table 5 Manual List 28 Table 6 Access Panel Location 29 Table 7 Equipment Installation Locations by Aircraft 29 Table 8 New and Upgraded Equipment 30 Table 9 Maintenance Manual by Aircraft 33 REPORT No. 584-00-0047, Rev: D BHE 8 Associates, Ltd. Page 7 of 36 Red By VT•ORB. FSCM 47MZ7. Sht 7 of 39. 2019/Mar/19 EFTA00011693 DocuSign Envelope ID: CFB62895-6FES4C8D-ACE3-5461F9820045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 1 SYSTEM DESCRIPTION 1.1 GENERAL This STC will include installations and/or updates to equipment to allow for Automatic dependent surveillance —broadcast Out (ADS-B Out). ADS-B periodically broadcasts information about each aircraft, such as identification, current position, altitude, and velocity, through an onboard transmitter. The equipment list in Table 2 below details the equipment required for this installation. The TDR-94/94D Transponder(s) will be upgraded to part number 622-9352-502 (94) or 622- 9210-502 (94D), if not previously installed. The TDR-94/94D Transponder is an all solid-state, crystal-controlled receiver/transmitter. The transponder(s) will get the GPS information from either a newly installed Freeflight GPS1203C GPS receiver and dedicated GPS antenna; or, a GPS-4000S GPS receiver. Depending on the aircraft configuration, the GPS-4000/A/S may be previously installed. If the previously installed GPS- 4000/A/S is not a part number 822-2189-004/005/006/007/010/011/100 it will have to be upgraded to one of these part numbers. (Reference Tables shown on drawing 584-00-0004 for applicable GPS installation based on aircraft model) Wiring is added dependent on the installed or replaced GPS receiver(s), Transponder(s), and annunciator installed. (Reference Tables shown on drawing 584-00-0004 for applicable installations based on aircraft model and subsequent Wire Routing drawing 584-00-0005).See section 6.1.9 for details on inspection. An optional ADS-B Out annunciator can be installed to alert the pilot that the ADS-B function of the active transponder is not properly functioning. The ADS-B Out annunciator is required for all standalone GPS installations. Standalone means the GPS only provides data to the transponders. All 1203C installations and 4000S installations that only connect to the transponders are standalone. It can be installed as an option for installations where the 4000S is used for both ADS-B and FMS navigation. ((Reference Tables shown on drawing 584-00-0004 for applicable ADS-B Out Annunciator installation based on aircraft model) Table 2 E ul ment List Type Description New CPN 1 Qty DO-260B ADS-B Out TDR-94 Transponder 622-9352-502 0, 1 or 2* TDR-94D Transponder 622-9210-502 0, 1 or 2* GPS1203C GPS Receiver 84327-50-XXXX 0 or 1 CI 429-200 GPS Antenna CI 429-200 0 or 1 GPS-4000S GPS Receiver 822.2189- 0, 1or 2 004/005/006/007/010/011/100 •Either TDR-94 or TDR-94D will be installed. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 8 of 36 Red By VT-ORB. FSCM 471027, Snl 8 of 39. 2019/MartI9 EFTA00011694 DocuSign Envelope ID: CFB626B5-6FE8-4C80.A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Table 3 below lists the equipment being installed by aircraft. The aircraft will leave with updated TDR- 94s or 94Ds depending on the what transponder was already existing. Table 3 Equipment by Aircraft Transponder GPS , Aircraft Antenna Installed Installed/Retained/Replaced Installed/Replaced • I GPS-1203C or GPS- Learjet 60 TDR-94s or 94Ds CI 429-200 40005 Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, TDR-94s or 94Ds GPS-4000S N/A Gulfstream 100, G150 Gulfstream G-1159, GPS-1203C or GPS- TDR-94s or 94Ds CI 429-200 G-1159B, G-IV, GV 4000S Gulfstream G-1159A TDR-94s or 94Ds GPS-40005 N/A Gulfstream 200 TDR-94s or 94Ds GPS-4000S N/A GPS-1203C or GPS- Textron Aviation 500 TDR-94s or 94Ds CI 429-200 40005 Textron Aviation 550, GPS-1203C or GPS- TDR-94s or 94Ds CI 429-200 5550, 560 4000S GPS-1203C or GPS- Textron Aviation 400 TDR-94s or 94Ds CI 429-200 4000S Textron Aviation TDR-94s or 94Ds GPS-4000S N/A 400A GPS-1203C or GPS- Textron Aviation 650 TDR-94s or 94Ds CI 429-200 40005 Bombardier CL-600- 1A11 GPS-1203C or GPS- TDR-94s or 94Ds CI 429-200 CL-600-2Al2, CL- 40005 600-2616 Sabreliner NA-265- 65, TDR-94s or 94Ds GPS-40005 N/A NA-265-70, NA-265- 80 Textron Aviation HS.125 700A, GPS-1203C or GPS- TDR-94s or 94Ds CI 429.200 BAe.125 800A/800B, 40005 Hawker 800XP Textron Aviation 1-15.125 700B, TDR-94s or 94Ds GPS-4000S N/A Hawker 750/850XP/900XP Dassault Aviation Falcon 10, Mystere- Falcon 50, Mystere- Falcon 20- TDR-94s or 94Ds GPS-40005 N/A C5/D5/ES/FS, Mystere-Falcon 200, Mystere-Falcon 900 REPORT No. 584-00-0047, Rev: D BHE 8 Associates, Ltd. Page 9 of 36 Reid By VT-ORB, FSCM 47M27. SM 9 of 39. ₹019/Marl19 EFTA00011695 DowSign Envelope ID: CF862885-6FE8-4CSD-A4E3-5461F9S2D04S INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 2 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under 14 CFR §§43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. 2.1 Inspection Intervals The following items require high Frequency Eddie Current inspections including 2.0 inch detailed visual inspection around periphery of the installation. Inspections as listed in the table below. Table 4Inspection Intervals Inspection requirements are for AML fuselage modification Inspection In ervals (Flight Cycles) Detectable Crack Length (in.) Threshold Recurring Fwd bulkhead penetrations 4,000 4,000 0.200 GPS Antenna Installation 6,700 6,350 0.200 GPS Antenna Installation (See Note 1) 5,650 5,400 0.200 Note1: These intervals are applicable to the Textron Aviation Cessna 650 and all the Gulfstream Models The following images specify antenna installation and bulkhead feedthrough installation locations. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 10 of 36 Rerd By VT-DRB, FSCM 47MZ7, Sht 10 of 39. 2019iMar/19 EFTA00011696 DowSign Envelope ID: CFB62885-6FEB-4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS BOMBARDIER INC. CL-600-1A11 (CL-600), -2Al2 (CL-601), -2B16 (CL-601-3A VARIANT, CL-601-3R VARIANT, CL-604 VARIANT) ACCEFTAKE LOCATION TS IS FS FS FS TS rs Fs It FS 310.00 MOO 364.03 394 00 424 449.95 473.15 499.00 MAO 539.00 03 21°4° FS FS Fs IS FS FS Fs mos n 295.00 32140 343.00 379.00 441.50 494.00 513.00 is 25000 I FS 13600 • s' br 21130.22"D OO FS 193.00 Fs 19900 H00000 REPORT No. 584-00-0047, Rev: D BHE 8 Associates, Ltd. Page 11 of 36 Red By VT-ORB. FSCM 47M27, Shl l l of 39: 2019/Ma019 EFTA00011697 DocuSign Envelope ID: CFB62885-6FE8-4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS TEXTRON AVIATION 400 ACCEPTABLE LOCATION 17224 196.46 FS FS FS PS Fs PS 124.61 141.14 159.25 203.35 221.46 240.75 260.04 FS F'IIS FS FS FS FS FS FS FS 1:6534 13767 1220 6214 .35 212.40 231.42 25039 269.69 71.65 niD I PRESS BLPHD FS 20.2e 'Pi iirki FS FS 60.91 99.02 FS FS 6996 108.07 REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 12 of 36 Red By VT-DRB. FSCM 47MZ7, Snt 12 of 39. 2019/Mar/19 EFTA00011698 DocuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9B20045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS TEXTRON AVIATION INC. 550, S550, 560 ACCEPTABLE LOCATION ACCEPTABLE LOCATION FS FS FS 225.23 151.00 179.02 23 (560) FS FS FS FS FS 134.00 165.00 223.40 94.00 117.00 FWD PRESS FS BOOM 59 00 i FS 216.10 (560 ONLY) REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 13 of 36 Reel By VT-ORB, FSCM 47MZ7, Sht 13 of 39. 2019/Matil9 EFTA00011699 DoneSign Envelope ID: CF8628B5-6FE8-4C8D-A4E3-5461F962D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS TEXTRON AVIATION INC. 650 ACCEPTABLE LOCATION FS FS FS FS 172.00 202.00 261.00 288.76 FS FS FS FS 157.00 187.00 245 00 272.00 94.00 FWD I PRESS FS BLKHD I 58 00 REPORT No. 584-00-0047, Rev: D BHE 8 Associates, Ltd. Page 14 of 36 Red By VT-DRB, FSCM 47M27. SM 14 of 39. 2019iMari19 EFTA00011700 DocuSgn Envelope ID: CF862885-6FE8-4C8D-A4E3-5481F9820045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS TEXTRON AVIATION HS.125 SERIES 700A, BAe.125 SERIES 800A 8c 800B, HAWKER 800XP ACCEPTABLE LOCATION 163.3 3013 220.0 MO 171 M11O-1 201.0 202.3 FII J~p7III13 Ft }I I I 07 r-T T 1 '0 O O 000) 1 I I I - n. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 15 of 36 Rory By VT-ORB. FSCM 47MZ7. Sill 15 of 39. 2019/Mar/i9 EFTA00011701 DocuSign Envelope ID: CFB628B5-6FE8-4CEID-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LEARJET 60 ACCEPTABLE LOCATION 110.99 336.61 " 124.39 151.19 170,59 201.79 222.1 216.. F23 274.59 302.59 323.59 I 355.16 FS 110 F12 F14.4 Fl IS F200 F21A I . F25 137.79 164.59 184.99 1210.19 234.19 25059 2M29 3lel 4663 99.57 F11 f13 F 5 F17 F19 F21 F22 F24 Fe 197.50 1941 59.23 I 11 I 7523 r5 61.23 47.23 F3 33.3 F2 I I I 1 I I I I 0 orr0 1 I I I I I 1 I I I IL MI ' 70.59 Fl IA REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 16 of 36 Red By VT-DRB. FSCM 47MZ7, Sill 16 of 39, 2019/Marf19 EFTA00011702 DowSign Envelope ID: CFB62885-6FE8-4O3D-A4E3-5461F982DO45 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS GULFSTREAN/ G-1159, G-1 1598, G-IV ACCEPTABLE LOCATION FS FS 145.0 .0 193.0 FS FS '33.0 181.0 FS 63.0 FV4) PRESS BLKHD .1 I \ I- I-1 I 1 IAII- I 100 ...,•*#'....' I . I. I N _ I I I I ...1 I I 1 1 I H LEI REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 17 of 36 Ro(d By VT-DRS, FSCM 47M27. Ste 17 of 39. 2019/Mar/19 EFTA00011703 DocuSign Envelope ID: CF862885-6FE8-4C8D-A4E3-5461F9020045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS GULFSTREAN/ GV ACCEPTABLE LOCATION FS FS FS FS 157.' 181.0 205.0 229.0 FS FS FS FS 145.0 193.0 217.0 241.0 ES 63.0 I I FWD PRESS BUCK) I I 1 I I I I n 1 WL vzi 100 I i- I I I I I C -L p_ 1 I I\ - - I I .1_I J REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 18 of 36 Rerd By 1/7-DRB, FSCM 47M27. Shl 18 of 39. 2019/Mar/19 EFTA00011704 DocuSign Envelope ID: CFB628B5-6FEB4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS % ALTERNATE LOCATION (WL 0.0) SS 0 M 0 000 I I 0 I' I I III III III II I I I I II I I /1 / I II I I t i // // I I I I - -.L 7 -- LOOKING AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD (TEXTRON AVIATION 400) 1 REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 19 of 36 Red By VTORB, FSCM 47M27, Sht 19 of 39. 2019rMar/19 EFTA00011705 DocuSign Envelope ID: CFB62885-6FEB-4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS \-- TT I IF I. I I l l i ,II. -- -LL-,__LI LOOKING AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD (TEXTRON AVIATION INC. 500, 550, S550, 560) I REPORT No. 584.00-0047, Rev: D BHE & Associates, Ltd. Page 20 of 36 Reid By VT-DRB, FSCM 47MZ7, Sht 20 of 39, 2019/Mar/19 EFTA00011706 DocuSign Envelope ID: CFB629BS-6FEB4C80-A4E3-6461F9132D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (ALTERNATE LOCAnOIN i Vc CW1 7 47F WOMAN MOW rc-: -X+m 7:i-it r t-t,- 4* It i lit 44 a 41 ±:ii- 1 ±: :r . :* + r ,::l; O: ool: 1+4 1 ; • LI I ° .r*: 1 O :+: : . 4L+" il I iii+p /‘+/ t: I Pl ICIM I:1 1 ! I:l st t i , ,,,,.4,, • rs, • Lk' i _ 14+ 1 1 :+: V' +"\ In: Etifa : 4 -141?1 1-#11:4 ,42 HI i ifr: III. IA\ •'I4.44 0.1 ,...„ , * I : I I II:I I iiiIii Ii ,41i..., II o•r::1 I:I , fr, ; ID:''locq {s-4- IB+11:4:11 _ :oo I( !! I- : 1,1 +, ;;; I I I 1+7 +• II I ---t _EL LOOKING AFT AT FRO SCE OF FORWARD PRESSURE Bult01110 (LEARJET 60) REPORT No. 564.00-0047, Rev: D BHE & Associates. Ltd. Page 21 of 36 Refd By VT-DRB. FSCh147M27. Sht 21 of 39, 2019/Mar/19 EFTA00011707 DoeuSIgn Envelope ID: CFB62885-6FE84C8D-A4E3•5461F982D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 2.2 Inspection Program Perform additional fuselage modification inspections. 2.3 Inspection Method Inspect fuselage skin in the modification area, doubler fastener holes area, using high frequency eddy current inspection techniques, according to the intervals outlined in table 4. The detectable crack length for eddy current inspection techniques is 0.200'. For the fastener holes, the inspector should look for cracks on the surface of the skin and doubler around the fastener holes. REPORT No. 584-00-0047, Rev: BHE & Associates, Ltd. Page 22 of 36 Rerd By VT-ORB. FSCM 47M27. Sht 22 of 39. 2019/Mar/19 EFTA00011708 DocuSIgn Envelope ID: CF862885-6FES-4C813-A4E3-54619982D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS INSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS typical Instal14tic, shown, Innsspectiti ont:y#: tcvaltlienettatto i tauada Ealtaijiar" !lc re-412 • ..41:insiirat";:z4TTEraillirs.-:417.4e-tir4LW- st•-•*,:!;........... REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 23 of 36 Red By VT.ORB. FSCM 47M27, SM 23 of 39. 2019/Mar/19 EFTA00011709 Doc Sign Envelope ID: CF8628854IFE9-4C8D-A4E3-5481F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .INSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS •••• ...... ..... . ... I r-ftn2Critr e f.. wags*/ REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 24 of 36 Red By VTdMB, FSCM 47M27. SM 24 of 39. 2019/M8r/19 EFTA00011710 DocuSign Envelope ID; CFS62885-6FE8-4C80-ACE3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS INSPECTION AREA & METHOD GPS Antenna Typical Instk 0%; ,Ipes.49.*4; :Applicable to all ditenzia • AI EAT ;Xl g a fira s REPORT No. 584-00-0047, Rev: I) BHE & Associates, Ltd. Page 25 of 36 Red By VT DRB. FSCM 47M27, Slit 25 o139, 2019/Mar/19 EFTA00011711 DocuSign Envelope ID: CFB62865-6FE8-4C8D-A4E3-5461F9B2O045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LNSPECTION AREA & METHOD GPS ANTENNA Typiciiliris'tallati ii slio ii Inspections 'are applicable to all.azItepnainstallations REPORT No. 584.00-0047, Rev: D BHE & Associates, Ltd. Page 26 of 36 Reid By VT-ORB, ESCM 47A127. Sht 26 of 39. 2019/Mar/19 EFTA00011712 DocuS'gn Envelope ID: CFB628B5 6FE8.4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS DISPECTION AREA & METHOD GPS ANTENNA Typical lastallation shot% Intztectiotw ate applicable to all antenna ‘4=' . . !ta ins • j SAW& ,4,1". REPORT No. 584-00-0047, Rev: O SHE & Associates, Ltd. Page 27 of 36 Red By VT-ORB, FSCM 47MZ7, Sht 27 of 39, 2019/Meff19 EFTA00011713 DocuSign Envelope ID: CFB828B5-6FE8-4C8D-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 2.4 Eddy Current Inspection For eddy current inspection requirements and procedures, refer to the referenced documents in the table below for the different aircraft types. The following documents describe the various procedures and requirements for HF eddy current inspection including personnel, instrumentation, equipment setup and standardization, probes, special tools and equipment eddy current standards, and eddy current test procedures required by the Cessna Aircraft Company. The defects identified by this method are incipient fatigue or corrosion stress cracks in bores, machining radii, shoulders and countersunk holes, and in the actual skin. The direction of propagation defects are perpendicular to in-flight stresses in the case of fatigue stress cracks, or perpendicular to internal stresses for stress corrosion cracks. This method also detects minor corrosion-induced surface damage. Table 5 Manual List Document Aircraft Manual Number Non-Destructive Inspection NDI-2 Learjet 60 Manual (Chapter 3) Textron (Citation) Series 500 Non-Destructive 5056ND 500, 550, S550, 560 Testing Manual (Part 6, Chapter 20) Textron (Citation) Model 650 Non-Destructive 65ND 650 Testing Manual (Part 6, Chapter 20) Textron (Beechjet) Model 4001400A/400XP 128-590001-9C29 400, 400A Maintenance Manual (Chapter 20-80-03) Textron (Beechcraft) 125 Series 1-800, Hawker N/A HS.125 700A, Bae.125 800A, 750, 800, 800XP, 850XP, and (General Techniques Bae.125 8006, 900XP Non-Destructive Part 8) Hawker 800XP Testing Manual N/A Challengers Structural Repair Manual (Chapter 51) Gulfstream G-1159, G-1159B, G- Structural Repair Manual N/A IV, GV (Chapter 51) FAA APPROVED: IIIIIIIIII____ Project ODA Administrator VT DRB Aviation Consultants A Division of VT San Antonio Aerospace, Inc. I IIII”ISan Antonio, TX 78216 Date REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 28 of 36 Rerd By VT-DRB. FSCM 47MZ7. Sht 28 of 39. 2019/Mar/19 EFTA00011714 DocuSIgn Envelope ID: CF862885-6FE8-4C8Da4E3-5461F982D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 3 MAINTENANCE PRACTICES 3.1 Removal/Installation The following installation manuals contain complete, detailed instruction for the installation and removal of equipment. Installation locations for the equipment vary by aircraft, reference tables 6, 7 and 9 for more details on equipment locations and respective maintenance manuals. • Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor, document 86764, Installation Section • Collins GPS-4000( ) Global Positioning System Installation Manual, document 523-0780545, Installation Section. • TDR-94/94D ATC/Mode-S Transponder System (-5)O(), document 523-0821492, Installation Section 3.2 Access Location Refer to the Aircraft Maintenance Manuals listed in table 9 for additional details. Table 6 Access Panel Location Location of Access Access Panels Forward Nose Access Panels Nose Avionics Bay (Right & Left) Cabin EE Racks N/A Instrument Panel & Pedestal N/A Tail Avionics Bay Tail Access Panel Table 7 Equipment Installation Locations by Aircraft Aircraft Transponder Location GPS Location Nose (GPS-4000S) Learjet 60 Nose Cabin (1203C) Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, Nose Nose Gulfstream 100, 0150 Gulfstream 200 Nose Nose Gulfstream G-1159, G- RH EE Rack, Cabin RH EE Rack, Cabin 1159A, G-1159B, G-IV Gulfstream GV LH & RH EE Rack, Cabin LH & RH EE Rack, Cabin Textron Aviation 500, 550, Nose Nose S550,560 REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 29 of 36 Rerd By VT-DRB, FSCM 47M27, Sht 29 of 39, 2019iMar/19 EFTA00011715 DocuSign Envelope ID: CFB62885-6FE8-CC8D-A4E3-6461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Aircraft Transponder Location GPS Location Textron Aviation 400/400A Nose Nose Nose (GPS-4000S) Textron Aviation 650 Aft Cabin Cabin (1203C) Bombardier CL-600-1A11 Under Floor, Cabin Under Floor, Cabin CL-600-2Al2, CL-600-2B16 Sabreliner NA-265-65, Nose Nose NA-265-70, NA-265-80 Alternate: FWD EE Shelf Alternate: FWD EE Shelf Textron Aviation HS.125 700A/700B, BAe.125 . Nose Under Floor, Cabin 800A/800B, Alternate: AFT EE Shelf Alternate: AFT EE Shelf Hawker 750/800X131850X131900XP Dassault Aviation Falcon 10, Mystere-Falcon 20- 05/D5/E5/F5, Mystere- Nose Nose Falcon 200, Mystere-Falcon 900 Dassault Aviation Mystere- Nose Nose Falcon 50 Alternate: Aft Avionics Shelf 4 POWER DISTRIBUTION 4.1 Circuit Breakers by Bus There are multiple options for the installation, the table below shows the possible equipment part numbers that may have changed with this update and the associated electrical load. The following equipment part numbers may have changed with this update. Table 8 New and Upgraded Equipment Max Load in Equipment/System Model/Part Number ' Amps TDR-94 622-9352-502 1.79 TDR-94D 622-9210-502 1.79 GPS RECEIVER GPS1203C 84327-50-XXXX 0.179 822-2189- 0.56 GPS RECEIVER GPS-40005 004/005/006/007/010/011/100 REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 30 of 36 Rerd By VT-DRB, FSCM 47M27, Set 30 of 39, 2019fMar/19 EFTA00011716 DccuSign Envelope ID: CFB62885-6FE8-4C80-A4E34461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 5 SYSTEM TROUBLESHOOTING For troubleshooting information, refer to the following; Equipment Circuit Breaker Document GPS1203c ADS-B GPS Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor Collins GPS-40005 Global Positioning System Installation GPS 4000S ADS-B GPS Manual, document 523-0780545, Maintenance Section TDR-94/94D ATC/Mode-S Transponder System (-5XX), TDR-94D TDR Document Number 523-0821492, Maintenance Section 6 INSPECTION REQUIREMENTS 6.1 Scheduled Inspections and Maintenance Checks This section of the document contains information regarding Time Limits — Inspection and Maintenance Checks, Overhaul and Replacement Items and Inspection Requirements. 6.1.1 Time Limits — Inspection and Maintenance Checks Note: Recommended inspection/maintenance intervals do not guarantee that the item will function properly between inspection/maintenance checks. The inspection intervals are based on average usage and environmental conditions. Aircraft operated under extreme conditions, (extreme hot, extreme cold, high humidity, salty air, etc.) may require more frequent maintenance than the intervals specified in this document. The aircraft operator may perform more frequent inspection/maintenance checks based on his usage. 6.1.2 Visual Inspections The equipment necessary for conducting a visual inspection usually consists of a strong flashlight, a mirror with a ball joint, and a 2.5x — 4x magnifying glasses. A 10x magnifying glass is recommended for positive identification of suspected cracks. 6.1.3 Corrosion Treatment Before attempting a close, visual inspection of any selected part or structural area, it should be checked for signs of corrosion. Any corrosion found should be tested to discover its extent and severity. Heavy or severe corrosion requires immediate corrective action. If mild corrosion is present, it should be carefully, but completely, removed before continuing with preparations for the visual inspection. 6.1.4 Structural Failure Determination. The first step in a visual inspection should be an examination of the area for deformed or missing fasteners. These should be identified for subsequent replacement. A close examination for cracks in the surfaces of structural members should then be made with the aid of a flashlight. The majorities of cracks start at, and progress from, points of concentrated stress such as sharp corner cutouts and fastener holes. Cracks may also occur in sheet metal bend radii and similar places that were subjected to severe forming operations during manufacture. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 31 of 36 Red By VT•DRB. FSCM 471427, Stu 31 of 39, 2019/Mar/19 EFTA00011717 DocuSign Envelope ID: CFB628B5-6FE8-4C8Da4E3.5461F9B20045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 6.1.5 Cleaning of Structural Parts All parts of areas from which mild corrosion has been removed should be thoroughly cleaned using an approved solvent. (Metal conditioner should not be applied at this time as it may interfere with subsequent dye penetrant inspection.) 6.1.6 Cleaning Other Areas All other areas to be inspected should also be cleaned of any deposits that might hinder the discovery of existing surface flaws. The protective finish need not be removed. The cleaning should be performed using any approved solvent. For cleaning high heat-treat steel parts, or areas in which a high heat steel part is installed, use only the approved solvents. 6.1.7 Crack Detection Technique When looking for surface cracks, the inspector should point his flashlight towards himself and hold it at an angle of 5° - 45° to the surface. (See Figure 6) The extent of the crack may be traced by directing the beam at right angles to the crack. Never direct the light beam at such an angle that the reflected beam shines directly into the eyes. The proper procedure is to keep the eyes above the reflected beam. INCIDENT - EYE ABOVE FLASHLIGHT LIGHT BEAM REFLECTED / LIGHT BEAM REFLECTED LIGHT BEAM 5° TO 45° CRACK OPEN TO SURFACE FAYING SURFACES Figure 6 - Inspection for Cracks 6.1.8 Verification of cracks A lOx magnifying glass may be used to confirm the existence or extent of a suspected crack. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 32 of 36 RON By VT-ORB. FSCM 47M27. Sht 32 or 39: 2019/Mar119 EFTA00011718 DocuSign Envelope ID: CFB62855.6FE8.4C8D-A4E3-5461F982D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 6.1.9 Visual Wiring Inspection Perform visual inspections of the wiring. These visual inspections should be performed as part of the existing applicable inspection cycles, not to exceed 1200 hours. (Reference Tables shown on drawing 584-00-0004 for applicable installations based on aircraft model and subsequent Wire Routing drawing 584-00-0005) Refer to the pertinent Maintenance Document listed below: Table 9 Maintenance Manual by Aircraft Aircraft, - TCDS Model Maintenance Manual Learjet 60 60 P/N MM-103 Bombardier Inc CL-600- CL-600-1A11 PSP 601-2 1A11 Bombardier Inc CL- CL-600-2B12, CL-600- CL 604 AMM 6002Al2, CL-6002616 2616 Dassault Aviation Falcon Dassault Falcon 10 Falcon 10 10 Maintenance Manual Dassault Aviation Mystere-Falcon 20- Mystere Falcon 20- Dassault Fan Jet Falcon C5/D5/E5/F5, Mystere C5/D5/E5/F5 Maintenance Manual Falcon 200 Dassault Aviation Dassault Falcon 50/50EX Mystere Falcon 50 Mystere-Falcon 50 Maintenance Manual Dassault Aviation Mystere Falcon 900 Dassault Falcon 900 Mystere-Falcon 900 Maintenance Manual Galaxy/Gulfstream G100/Astra SPX P/N G100-1001-11-1 G100/SPX Galaxy/Gulfstream 1125 1125 Astra P/N 25W-1001-11-1 Astra Galaxy/Gulfstream 200, Gulfstream 200, G150 --------- Gulfstream G150 Gulfstream G-1159, G- G-1159B Gulfstream II 11596 G-1159, Maintenance Manual Gulfstream III Gulfstream G-1159A G-1159A Maintenance Manual Gulfstream IV Aircraft Gulfstream G-IV G-IV Maintenance Manual Gulfstream GV GV Gulfstream V Aircraft Maintenance Manual Textron (Citation) Model 500 Maintenance 500/550/S550 500/550/S550 Manual REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 33 of 36 Bern By VT-DRB, FSCM 47MZ7, Slit 33 of 39, 2019/Mar/19 EFTA00011719 DowSign Envelope ID: CFB62885-6FES-4C8D.A4E3-5461F982D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Textron (Citation) Model 560 Maintenance 560 560 Manual Textron (Citation) Model 650 Maintenance 650 650 Manual Textron (Beechjet) 400/400A P/N 128-590001-9C 400, 400A Textron (Beechcraft) 700A, 700,B AFMS-125-700 HS.125 700A, 700B Textron (Beechcraft) 800A, 800B AFMS-800 BAe 125 800A, 800B Textron (Beechcraft) 750 AFMS-800XP 750 Textron (Beechcraft) 800XP AFMS-800XP 800XP Textron (Beechcraft) 850XP AFMS-800XP 850XP Textron (Beechcraft) 900XP AFMS-800XP 900XP Sabreliner Aviation NA-265-70, NA-265-70, P/N SE 0405 MM NA-265-80 NA-265-80 Sabreliner Aviation NA-265-65 P/N SE 0303 MM NA-265-65 A "visual inspection" is defined as the process of using the eye, alone or in conjunction with various aids, as the sensing mechanism from which judgments may be made about the condition of a unit to be inspected. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight. A visual inspection may require the removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked. The inspection criteria provided below is intended as general guidance. Conduct special inspection as deemed appropriate by each operator based on aircraft experience. Any discrepancies found should be repaired. 6.2 Wiring The inspection criteria provided below is intended as general guidance. Special inspection should be conducted as deemed appropriate by each operator. My discrepancies found should be repaired. a. Wire/Wire Bundle — Inspect for: • Aluminum drill shavings, lint or dust on or inside wire bundles. Aluminum shavings can, with vibration or other motion, cut through wire insulation and provide a conductive path between wires in a bundle or to adjacent grounded structure. Lint and dust can accumulate on wire bundles and may, if subjected to overheated wires, ignite or possibly feed an electrical fire. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 34 of 36 Rerd By VT-DRB. FSCM 47MZ7. Sht 34 o139. 2019/Mar/19 EFTA00011720 DocuSign Envelope ID: CFB62885-6FE8-4C80-A4E3-5461F982D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS • Wire insulation that has become brittle. Wire may be more susceptible to cracking. Damaged insulation and/or exposed conductor material of wires. Cracked, chafed and cut insulation can provide a conductive path between wires in a bundle or to adjacent grounded structure. • Pinched wires can occur at wire clamps, connector backshell clamps, excessively tight cable ties, etc. • Inappropriatefimproper wiring repairs such as the use of duct tape, electrical tape, poor crimp splices, etc. • Wire insulation damage due to fluid leaks (i.e. fuel, hydraulic fluid, etc.) • Separation of electrical wires from hydraulic, fuel and oxygen lines. Ensure a minimum of 0.5-inch separation and any wiring routed within 2.0 inches must be clamped to provide separation. • Small bend radii of wire. Wiring subjected to excessively tight bend radii may sustain damage to the wire insulation. • Sagging wire bundles. Ensure bundles are not allowed to droop onto structure, components, cables, hoses, other bundles, etc. • Wire attached to the outside of a wire bundle using plastic ties instead of being installed under existing wire clamps. Can cause chafed and cut wire insulation. • Unsupported wires running into conduit or wire supported in such a way as to pull the wire against the side of the conduit entrance instead of into the center. Can cause chafed and cut wire insulation. • Proximity to high temperature equipment. Wiring shall be kept separate from high temperature equipment, such as resistors, exhaust stacks, heating ducts and deicers, to prevent wire insulation deterioration. • Wires with different insulation types should not be routed together, where possible. Certain wire insulations may be easily abraded by other types of wire insulation. b. Wire Harness Clamps — Inspect for: • Condition. Ensure any protective material on the wire clamp (i.e. rubber, plastic, etc.) is in serviceable and functional condition. Clamps should be secured to structure and wire bundle should be snug in clamp. • Ensure clamps are not installed over splices. c. Connectors — Inspect for: • Condition. Make sure connectors are free of corrosion, moisture, dust and metal shavings. Check for wom environmental seals, loose contact tension, proper contact locking, missing seal plugs, missing dummy contacts, etc. Drip loops should be maintained when connectors are below the level of the hamess and tight bends at connectors should be avoided or corrected. d. Backshells — Inspect for: • Condition: Wires may break at connector backshells due to excessive flexing, lack of strain relief or improper buildup. Loss of backshell bonding may also occur due to these and other factors. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 35 of 36 Rerd By VT-DRB, FSCM 47M27, Slit 35 o139, 2019/Mar/19 EFTA00011721 DoeuSign Envelope ID: CFB628B5-6FE8-4C8D-A4E3-6461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS e. Electrical Conduits and Sleeving — Inspect for: • Susceptibility to water/moisture entrance: Conduits should not be susceptible to the entrance of moisture. If moisture going into conduits and sleeving is unavoidable, provisions should be made in the lower portions of the conduit to drain any moisture and prevent accumulation. • Condition: Damage to sleeving and conduits, if not corrected, will often lead to wire damage. Make sure components are free from corrosion, moisture, dust, and metal shavings. Check that conduit is secured to structure. f. Terminations — Inspect for: • Condition: Terminal lugs and splices are susceptible to mechanical damage, corrosion, heat damage and chemical contamination. The buildup and nut torque on wire lugs is critical to their performance. Grounding Points — Inspect for: • Condition: Grounding points should be checked for security (i.e. tightness) condition of termination, cleanliness and corrosion. Any grounding points that have corroded or have lost their protective coating should be repaired and checked for proper resistance. CAUTION Use care when disturbing or removing wire harness/bundles to minimize the possibility of wire insulation damage or cracking. Care must be especially used in areas with severe moisture problems. During any repair, modification, or installation work in close proximity to wire bundles, mounts, connectors and systems, ensure that these areas are protected from and/or cleaned of metal shavings and debris. REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page 36 of 36 Reid By VT-DRB. FSCM 47A427. Sht 36 of 39. 2019/Maril 9 EFTA00011722 DocuSign Envelope ID: CFB62885-6FE8-4C8D-PAE3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Appendix A — List of Applicable Publications NOTE: The latest released revision of the publications listed in the LOAF' constitutes the required information essential for continued airworthiness for the aircraft. Document Title Document Number Airplane Flight Manual Supplement 584-00-0046 Master Data List (includes wiring diagrams, 584-00-0001 equipment installations and ground test) TDR-94/94D ATC/Mode-S Transponder System 523-0821492 (-5XX) Install Manual GPS-4000( ) Global Positioning System 523-0780545 Installation Manual Equipment Installation Manual for the FreeFlight 86764 System Model 1203C GPS/SBAS Sensor REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page Al of Al Red By VT-ORB. FSCM 47M27. Sht 37 of 3s. 2019/Mad19 EFTA00011723 DocuSign ErnieMpe ID: CFB62885-8FE8-4C8D-A4E3-S461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Appendix B — Special Tools and Equipment Transponders — Aeroflex IFR-6000 or equivalent test set. GPS — JCAir 429 or equivalent 429 Bus Reader GPS - Oscilloscope REPORT No. 584-00-0047, Rev: D BHE 8 Associates, Ltd. Page 61 of B1 Rerd By VT-DRB. FSCM 47MZ7, Sht 38 of 39. 2019/Marrt 9 EFTA00011724 DocuSign Envelope ID: CF8928856FE8-4C8D-A4E3.5461F9B20045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS Appendix C — Discrepancy Reporting Form This form to be used by aircraft owner operators and modification centers to report discrepancies with modifications and repairs approved by the ODA. DATE DISCREPANCY DISCOVERED: Self explanatory. DISCREPANCY: Describe the discrepancy In detail. RECOMMENDED CORRECTIVE ACTION: Describe what actions you recommend taking to correct the discrepancy. REPORTED BY: Self explanatory. COMPANY NAME: PERSON TO CONTACT: PHONE NUMBER: TITLE: Self explanatory. Date: Self explanatory. Signature: Please submit the completed form to the following contact: mim ilikiODA Unit San Antonio, TX 78216 Phone: Email: REPORT No. 584-00-0047, Rev: D BHE & Associates, Ltd. Page C1 of C1 Reid By VT-DRS, FSCM 47M27, Sht 39 of 39. 2019/Marf19 EFTA00011725 EFTA00011726 061B Na 21200020 Slecircnie Trackeo itenbee 5v: 5/30201e 0 MAJOR REPAIR AND ALTERATION For FM Use day US Cerviertem of Transprecen (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Acenhesealoa INSTRUCTIONS: Print or type all entries. See Tele 14 CFR §43.9. Part 43 Appendix 13, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. §44701). FaNure to report can result in a civil penalty for each such violation. (49 U.S.C. §46301(a)) Nationality and Registration Mark Senal No. USA/N493LX RK-244 1. Aircraft Make Model Senes Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration certificate) Address 2. owner Flight Options Cry Richmond Helpers State OH 20 44143.1453 Court,/ USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. minneeiriir (As described in Item 1 above) xx.h. O x AIRFRAME 0 POINERPU*17 IMI ni PROPELLER Type E El APPLIANCE Manufacturer B. Conformity Statement A. Agency's Name and Address B. Kind of Agency Nam Neeani Aerospace U. S. Certacated mechanic I mammon, Maine Foreign Certificated Mechanic C. Certificate No. Ce Cleveland sum OH x CerbeCeled Repair Station AI 44I43-1453 CoottY use Certificated Maintenance Organization CRS# 25NR667B D. I certify that the repair and/or alteration made to the unit(s) identified in tern 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is tree and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized lndivi Aer 14 CFR Part 43 App. B /2-1 -..110/- , 7. Approval fo - / - -.1 /Y Pursuant to the authority g'ven persons specified below, the unit Identified in item 5 was 'nspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is FlApproved Rejected fi FAA Flt. Standards PerSOM Approved by Canadian Manufacturer Maintenance Organization Inspector Department of Transport BY Other (Specify) FAA Designee Repair Station Inspection Authorization X Certificate or Signature/Date of Authorized Designation No. CRS# 25NR667B 7 -17-7/.7 FAA Form 337 (10/06) V- o/- zei/ EFTA00011727 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements 8. Description of Work Accomplished (if more Spaced required. attach additional sheets Identity kWh aircraft nationality and registration mark and date wan( comma fed ) N493&X 12/2912013 Nationality and Registration Mark Dale This 337 is amended 01APR2019 to correct a Typo in block 8. Installed New Pitot Probes in accordance with STC ST10959SC. Nextant Master Drawing List Document 373-00-0001 Rev CC EO24-11. Removed Pitot Probes Part Number PHi 100-MU-R-1 Removed Pitot Probes Part Number PH1100-MU-L-1 Installed Pitot Probes Part Number PH1100-MUR-EN Serial Number 1975803 Installed Pitot Probes Part Number PH1100-MUL-EN Serial Number 1728401 Leak Check carried ouit Beechcraft Aircraft Maintenance Manual Chapter 34-12-00-201 ICA Continue with Normal Hawker Beech Maintenance Practices for this area. END MAdditiOnal Sheets Are Attached AA Form 337 (10/06) Paec 2 EFTA00011728 DEPARTMENTOFTRANSPORTATION-FEDERALAVIATIONADMMISTRAMON STANDARD AIRWORTHINESS CERTIFICATE I NATICNALRY AND 2 MANUFACTUFtER AND MODEL 3 AIRCRAF7 SERIAL 4 C.ATEGORY REGISTRATON MARKS NUMMER Raytheon Aircraft N188TS Company 400A RK-244 Wansport AUTIORITY AND BASIS FOR ISSUANCE Tim~hem mikseIs MAO 'usunn 41U.S.C. I M704 and tet tra is ol te Medmumx.Im~I nebb kanel has teen Ameneel and bm& b con»4) heI. møta Sekt MOS wen In Si *nåml erd tes Sin Ikno b~n rimniner4 MinmokaNs memMmenve anti Mit areteliness ca as moMnI ty Ames t ts Con ca MAIMIOnn fid bonn, ememM mad Menn &menn -None- I TERMS AND CONOITIONS Inmm soner suemenel summint motet ora IsminIca dis b «bunne estitethof by I. FM, dIe annellinem~tale e &KM N losa as te munmmak penmee nallamict and~Sms are parmaIncondate w1Pon2I.43, and tiden NOS AvatmRimelann. As irs~ sd Man. N#4Iffld b elt Unnd Maks. )ATE OF ISSUANCE DESIGNATION NUMSER R3/06/2014 GL-25 44,111~.~01. 3 pts orket 14SCERIIRCATE RUST SE DISPLAYER NITE MIOIM1IR ACC0R0ANCE WRII APPLICISE KREML AMT>REGIAATOIS. A Fonn 1100.2 (04-11) Supersedes Previous EMMA FeoPn fttRAvi- EFTA00011729 EFTA00011730 UNITEDSTATESOFAMERICA DEPARTMENTOFTRANSPORTATION-FEDERAI. AVIATIONADMINISTRATION STANDARDAIRWORTHINESS CERTIFICATE I NATIONALITYAND 2 MANUFACTURER ANDMODEL 3 AIRCRAFTSERIAL 4 CATEGORY REG;STRATIONMARKS NUMBER RaytheonAircraft 188TS Company400A RK-244 Iransport 5 AUTHORITYANDBASISFORISSUANCE Thisaivotess cedifuteisissuedpursualto49U.S.C.§441d4 andcues that,asofte daleofissuance,theknit to vkh issuedhasbeenlispectedandfoundlacohfomitothetypecertificatetherefor,tobeinconk forsafeoperation, andhasbeen shoolomeethe(quires albaappliote(mottos:Pieandetaised oodeasprovided airworthiness byWavle) lhe Convention onloleminhalCidAndo, exceptasholedbait bagel: FS-'?SO "" -None- 6 TERMSANDCONDITIONS UtSSOOnef seehdered, reveled,OfalEnitatioodateisotherwise suspended, eslabishedte FAK,thisiirivofiess cetficale iseffectiveaslongasthemaillenance, mairdenarte, prevehlative andalleradolsareperformed inaccordancewit Pat 21,43,and 91oftheFederalAviationRegulations, asappropriate, andtheateisrelisletedihtoUtd States. DATEOFISSUANCE DESIGNATIONNUMBER R3/06/2014 GL-25 Ofmisuse Artyallergen,reprodudon, ofOilsrdicale maybepuhishab'byeafinerId weeding11,660 mririsonment hotexceerfn9 3 elfS aboth. THISCERTIFICATE MUSTBEDISPLAYEDINTHEAIRCRAFT INACCORDANCE VIITHAPPI(CA8LE FEDERALAVIATION REGULATIONS. FAAForm81002 (04.11)SupersedesPreviousEdition EFTA00011731 EFTA00011732 U S Department or Transportation Federal Aviation Administration October 9, 2018 Aircraft Registration Branch AFS-750 To whom it may concern: During review of AFS-750 records it was found that a discrepancy existed of the Airworthiness Certificate for N188TS, Make: Raytheon Aircraft Company, Model: 400A, Serial Number RK-244, it was noted that the Airworthiness Certificate registration number did not show the required Nationality letter "N". During inspection of the aircraft it was found that the original Airworthiness Certificate did in fact have the required Nationality letter. Made a copy of the original Airworthiness Certificate and forwarded to AFS-750. If you have any questions in this matter, please contact me at FAA PMI CLE FSDO EFTA00011733 I EFTA00011734 nefiee 2120-0020 Electnooe Trecbro Nine Erg 531/N18 MAJOR REPAIR AND ALTERATION For FAA Use Only US Department of Trarecolaeco (Airframe, Powerplant, Propeller, or Appliance) Federal Minion AenenIstratIon INSTRUCTIONS: Pnnt or type an entries. See Title 14 CFR §43.9. Pan 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for Instructions and disposition of this foam. This report is required by law (49 U.S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. 146301(a)) Nationality and Registration Mark Serial No. USA / N188TS RK-244 1. Aircraft make Model Series RAYTHEON AIRCRAFT COMPANY 400A Name (As shown on registration certificate) Address (As shown on registration certrficate) swan 2. Owner THORAIR LLC C.,/ SANDUSKY State OHIO Zp 44171-221$ Catrily UNITM STATES 3. For FM Use Only 4 Type 6. Unit Identification Repel Alteration Unit Make Model Serial No. RAMC°.MOW Call1en (As described in Item I above) ✓ AIRFRAME POWERPLANT X -- 7 [7 PROPELLER Type ri❑ APPLIANCE Manufacturer 6 Conformity Statement A. Agencys Name and Address B. Kind of Agency Ilsere Heston: Arnow* U. S. Certificated Mechanic J Manufacturer woes, :WO 0."s "eert Pain., r Foreign Certificated Mechanic C. Certificate No. cc, ciewiene sub ollb i• Cerlillaterl Repast StabOrt ye 44143 careen. united Stain Certificated Maintenance OrganizatiOn CRS# WC7R346J D. I certify that the repair and/of alteratIon made to the unit(s identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pan 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. EXtended range fuel per 14 CFR Part 43 App. B 0/06/2017 . crrova atom to ce Pursuant to the authority given persons specified below, the unit Idenrel in Item5 /122sinspeedct in the manner prescribed by the Administrator of the Federal Aviation Administration and 's I Approved Rejected ,--.—.0 Persons Approved by Canadian FM Flt. Standards Manufacturer Maintenance Org nization Inspector Department Of Transport BY ~I C Other (Specify) FAA Designee I Repair Station Inspection Authorization Certificate or Designation No. CRS# WC7R346J4 10/06/2017 FAA Form 337 (10/06) age EFTA00011735 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date sat completed) N18878 10/06/2017 Nationality and Registration Mark Date STC# ST02371LA Winglet Option Installation Installed Nextant Aerospace Winglets IAW Nextant Aerospace STC# ST2371LA amended date 3/10/2017, Master Data List# MDL-NXT-001 Rev J, dated 2/14/2017, and minor deviations IAW EO# NT-EO-0817-09 Rev A and NT-EO-1017-09 Rev IR. Removed Equipment Item Part Number Serial Number Left Wingtip Assembly 45A10552-001 Left Strobe/Position Light Assembly 45A88750-22 Wing Tip Lens 8888-170000-01 Right Wingtp Assembly 45A10552-002 Right Strobe/Position Light Assembly 45A88750-22 Wing Tip Lens 8888-170000-02 Tail Strobe Light 4588315-121 Tail Position Light 45A88754-11 Strobe Power Supply 01-790080-00 00575 Installed Equipment Item Part Number Serial Number Left Winglet Assembly NEXT-SA15250LA57-10001 S-NEXT-0001 Right Winglet Assembly NEXT-SA15250LA57-10002 S-NEXT-0001 Left Winglet Light Assembly 87-03916-001 00214 Right Winglet Light Assembly 87-03917-001 00216 Tail Strobe Cover Plate NX0047-3340-0101-001 Tail Position Cover Plate NX0047-3340-0102-001 ICA Follow the maintenance inspection practices in the Nextant Aerospace Instructions for Continued Airworthiness Document No. NX0047-ICA0-0101 Rev. A, dated 6/20/2016 or later FAA approved revisions. AFMS FAA Approved Airplane Flight Manual Supplement Document No. NX0047-AFMS-0101 Rev. IR, dated 3/10-2017 or later FAA approved revisions have been added to the Airplane Flight Manual Weight and Balance Reference Weight and Balance Report dated 10/06/2017 END FlAdditional Sheets Are Attached FAA Form 337 (10/06) Page 2 EFTA00011736 1aIrt 3tatrrir.i peparbnent of troantsporittiou - "cigi rdcrul (Affirztion iiitiotruttrur $uppinnental Qltrtificute Xenzhe ST02371LA g,444420,eiwawil, Nextant Aeros a LLC Richmond Heights, Ohio 44143 A../4404firiti4.04,2,0 (;" aro devOrnA.• A4e4g:toennaltilseeitodel4 deneraiennei ernaectanisreensi dereVeer od ifrowajeasestiowissnee6 eserotoeisreisam reyessiewswhO 19aeke 25* oyet4 Faival...4exmaw. ...94,64.4kni. *Certification basis is set forth on TCDS A I6SW and continuation sheets 3 and 4. araf tellvickae 4 / seb g.....stfrjeassrelicsondao.• Al6SW agaa• Beechcraft Corporation AlCedef 400A Sava-ohiv),AF,Trog'.ivr. Veer Alteration of a Beechcraft Corporation 400A airplane, to replace Pratt Whitney JT15D-5 series engines with Williams International F.144-3AP engines (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems (Config. A) and (tor) the installation of Nextarrt Winglets (Config. B), in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001, Revision Ilt dated 8/22/2011, or later FAA approved revisions and the appropriate FAA approved Airplane Flight Manual Supplement(s) for the applicable installed configuration(s): NXT I -AFMS, Rev IR, dated September 1.5, 2011 or later FAA approved revisions Confic. B: NX0047-AFMS-0101, Rev III, dated March 10, 2017 or later FAA approved revisions 51207Vi(711:104/ ffed.g.;:seaarand. The installation thould not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above-noted airplane models only. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give 'Mrs other person written evidence of that permission. (CONTINUED on page 3) .97Z ageterAra•mall* idryneronar dun weenie lg. k'tt)A. yieroaneenenoin e jot de.o4t-te Juvrevanse.tmonendtaraosts.4/^ a lawsresirays dole w theitsgm.YE eViii4e4.44 EgenadheErrhso(AA Alwree.olyx;thew...4,197,a44Theen. 244 0rffstieraim March 24, 2008 arehnseaSeesei. Ode Vei.l.gredrner.• September 27, 2011 .7173.14141 . • March 10, 2017 .4osestehiss. ore.44.4a5sse:sedmisie Manager, Propulsion Branch Los Angelus Aircraft Certification Office Arty aarnation of this costifrata is punishato 6y a fans of not EVANfily) 51.004 or islphsromar rot goodthe I Yoga w both Mt Porn t, te.f (10.40) Pegs a of • Rifts' eatific.... trip,k miffing(in acrordaricsteitfi filt22.47. EFTA00011737 EFTA00011738 ait/bat/tin Putterien ,Drparhnritt of Zgrzruspnrtritinit - gtheral Akan-firm Ahministratinit $upplrnwntal `Tut Certificate (Crutinuatitm Akeet) Are/dr ST02371LA ..ganeltruleet7J ernea;raitas 7traetiuteeelY • Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this alteration. • The new Vmca and Vmcg values are 94 KIAS and 93 KIAS respectively. • The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature of 77°F. • Approved engine fuels are: Grade Specification Jet A ASTM-D 1655 Jet A-1 ASTM-D 1655 • FAA accepted revisions of the Nextant Aerospace, LLC Instructions for Continued Airworthiness document must be made available to the operator with the installation of the STC configuration(s). o Config. NXT1-ICA, Revision IR, or later FAA accepted revisions. o Config. B: NX0047-ICAO-0101, Revision A, or later FAA accepted revisions. g.../OrpoM Sera, The certification basis for this modification is as follows: The original certification basis for the Hawker Beechcraft Model 400A airplanes identified on TCDS AI6SW, Revision 26, dated March 17, 2010: Pan 25 of the Federal Aviation Regulations effective February 1, 1965. as amended by 25-1 through 25-40, plus §§ 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41: §§ 25.29, 25.255, and 25.1353(c)(6) of Amendment 25-42; and §§ 25.361(b) and 25.1329(h) of Amendment 25-46. Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36.17; SFAR 27 effective February 1. 1974. as amended by 27-1 through 27.5; and Special Conditions No. 25-ANM-32 dated February 22, 1990 (High Altitude Operation at 45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy Protection). (See NOTE 12) Equivalent Safety Items (I) Out-of-trim characteristics FAR 25.255 (2) Pilot compartment view FAR 25.773(b)(2) (3) Passenger compartment door FAR 25.813(e) (4) Emergency cut marking FAR 25.811(d)(1) and 25.811(d)(2) Application for amended Type Certificate dated February 18, 1988. Jtry alteration of this certiftatte is punishable fy a fine of not akseefing $1,000, or imprisonment not woofing 3 years, or tot& ma tom •110-20.0-6•11 Page > of 4 his certificate may be transfermf in aa-ordance vita ffR 121.47. EFTA00011739 EFTA00011740 Alltittb "Mtn 2.nterics cpartunnt of Transportation - AchrraI cAfitatinn cAlintinistratbn $uppinnental `Crypt Griffin:dr (aradinuation *int) ifielenhie ST02371LA Regulation at a later amendments for components and areas affected by the change (Ref. FAA approved Compliance Check List): Subpart A - General: §§ 25.2(25-99) Subpart B - Flight: §§ 25.207(25-121), 25.255(25-42) Subpart C — Structure: §§ 25.571 (25-96) Subpart D - Design and Construction: §§ 25.603(25-46), 25.605(25-46), 25.611(25-123), 25.613(25-112), 25.625(25-72),25.832(25-72), 25.863(2546), 25.869(25-123), Subpart E — Powerplant: §§ 25.901(25-46), 25.903(25-100), 25.951(25-73), 25.961(25-57), 25.981(25-125), 25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25-42), 25.1045(25-57), 25.1091(25-100), 25.1093(25-72), 25.1103(25-46), 25.1141(25-115), 25.1143(25-57), 25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57), 25.1195(25-46), 25.1203(25-123), 25.1207(25-46). Subpart F — Equipment: §§ 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123), 25.1316(25-80), 25.1317(25-122), 25.1321(25-41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123), 25.1357(25-123), 25.1381(25-72), 25.1431(25-113),25.1438(25.41), Subpart G — Operating Limitations and Information: 4§ 25.1501(25.42), 25.1521(25-72), 25.1527(25-105), 25.1529(25-54), 25.1543(25-72), 25.49(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-72), 25.1583(25-105). Subpart H - Electrical Wiring interconnection Systems (EWIS): §§ 25.1701(25-123), 25.1703(25-123), 25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25-123), 25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(25-123), 25.1727(25-123), 25.1729(25-123), 25.1731(25-123), 25.1733(25-123). 14 CFR Part 34(34-3): 34.11 14 CFR Part 36 ( 36-28): 36.1-36.7, 36.101--36.105, 36.1501, 36.1581. The following Nextant Aerospace Continued Airworthiness Supplements are applicable to airplanes modified in accordance with this SIC: • Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved revisions. • EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXTI-EA-007 Rev A dated 8/24/11 or later FAA approved revisions. fisty etonstion of this cortificatoispanishafr ty a fins of not mutant; $1,004 or impironment not meeting 3 years, or 6oth. ran tar. •110-2 (10-641 Hoe 4 of • ?Fu certificate wiry ht trittufardin ocronforwe with Tilt21.47. EFTA00011741 EFTA00011742 Form Potressed Electronic Tracking Number 1 OW No 2120.0020 e2b/ G MAJOR REPAIR AND ALTERATION 11/30,/2007 U.S Detwomert ce Trongorubon (Airframe, Powerplant, Propeller, or Appliance For FAA Use Only Foam, Aviation AdoONstnelon INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (Or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As Mew,, On registration Certificate) Address (As shown on registration certificate) 2. owner Flight Options .LLC Address city Richmond Heiahts stow OH To 44143-1453 Country aL li 3. For FAA Use Only 4. ype 5. Unit Identification Repair Alt ration Unit Make Model Serial Number ❑ 0 AIRFRAME (As arescnbed in Item I above) 0 ❑ POWERPLANT PROPELLER 0 ❑ Type O ❑ APPLIANCE MillileligOf 8. Conformity Statement A. Agency's Name and Address B Kind of Agency Nama Constant Aviation O U.S. Certificated Mechanic O I PAartufaCturtot Address O Foreign Certificated Mechanic C. Certificate 140. Cry Cleveland stow. OH a Certificated Repair Station zip 44143-1453 country USA O Certificated Maintenance Organization CRS # WC7R346J D. I certify that the repair and/or alteration made to the unit(s) kilentilled in item 5 above and described on the reverse a attadvnents hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnShed herein is true and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized Inc% • per 14 CFR Part 43 ❑ 09/Sep/2017 App. 8 7. Approval for Return to Service Pursuant to the authority given persons specified below, the unt identified in item 5 was inspected in the manner prescnbed by the Aciminlyttele: el the Federal Aviation Administration and iS a APPROVED IN REJECTED FAA FR Standards Person Approved by Canadian Manufacturer Maintenance Organization Department of Transport Inspector BY Other (Specify) FM Designee X Repair Station Inspection Authorization Certificate or Signature/Date of Authorized Indwilua Designation No. 09/Sep/2017 WC7R346J FAA Form 337 (10-06) EFTA00011743 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished (If more space is required, attach additional sheets. !dentin/ with aircraft nationality and registration mark and date work completed.) N493LX 12/Sep/2017 Nationality and Registration Mark Date This is a revised FAA 337 to correct the Serial Numbers of the Engines that were installed by Nextant Aerospace CRS # 25NR667B on FAA 337 Dated 05/30/2013 Nextant Aerospace Completed STC # ST02371LA Removed Pratt and Whitney 1115D-5 Series Engines. Installed the Williams International F144-3AP Engines with Full FADEC and Associated Systems in accordance with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011of later FAA Approved revisions. Installed Left Engine Part Number. 111000-202 Serial No. 252767 Installed Right Engine Part Number 111000-202 Serial No. 252768 ICA AFM Supplement was installed on Aircraft. Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted revisions are included in the Aircraft Maintenance Records. Carried out Engine Ground Runs and System 0PS checks IAW Ground Test Plan 373-00-0024 Rev F. End ..‘ Additional Sheets Are Attached FAA Form 337 (10.06) EFTA00011744 UNITEDSTATESOFAMERICA OFTRANSPORTATION DEPARTMENT -FEDERALAVIATIONADMINISTRATION •STANDARDAIRWORTHINESS CERTIFICATE 1 NATIONALITYAND 2 MANUFACTURER ANDMODEL 3 AIRCRAFTSERIAL 4 CATEGORY REGISTRATIONMARKS NUMBER RaytheonAircraft 188TS Company400A RK-244 Transport 5 AUTHORITYANDBASISFORISSUANCE ThisaiNionhiness certificateisissuedpigswillroa9U.S,C.§44104andciffeastat asofhdaleofissuance, lbea'rrctal-toOld issuedhasbeeninspected andloth Iaconformlathebiaol2ftfolIOMeV, tobeIPcordonforsalepetal, nodhasbeen shownlomeetIla requirements ofdieapplicable orrhensineanddalliedairworthiness codeasprovided byAnnul Odle ConverEononInternationalCHilNation,min asnotedherein, Exceptions: -None- 6 TERMSANDCONDITIONS Nondateisotheneise Untasssoonersurt¢ndered,suspended,sevoked,oraIek eslablIshed byIliaFAn:Bilsainiiiness Lseffectiveasloll asIbemaintanance, [WPMMAIRIOPRO, anddetainsareperformed inaccolanoeMtParts21,43,and BiddleFedtialAviationReohlons,asappropriale, andtheairclAisROM IPtheAd Stales.' DATEOFISSUANCE DESIGNATIONNUMBER 83/06/2014 GL-25 Anyallemlion, reproduction, ormisusealibiscediNcele byahe nalBank)RN)arIMOSIONPIPOIReed4 maybepunishable 3yearsorbd. THISCERTIFICATEMUSTBEDSPLAYED INTHEAIRCRAFT INACCORDANCEWITHAPPLICABLE FEDERALAYIAi10N REGULATIONS, FM Form8100.2(04.11)SupersedesPreviousEdition EFTA00011745 4 4 EFTA00011746 UNITEDSTATESOFAMERICA DEPARTMENT OFTRANSPORTATION -FEDERALAVIATIONADMINISTRATION STANDARDAIRWORTHINESS CERTIFICATE 1 NATIONALITYAND 2 MANUFACTURERANDMODEL 3 AIRCRAFTSERIAL 4 CATEGORY REGISTRATIONMARKS Raytheon Aircraft NUMBER RK-244 Transport N49311 Company 400A 5 AUTHORITYANDBASISFORISSUANCE ThisainvotinessRite isissuedptusuardlole U,S.C.§,14iGitand cerUdestali asofIhedoleofissuance,theaircraft0 which issuedhasbeeninspected andteund0 coin to0e typecetterate086,0 heincondition foisaleoperation,Ed hosbeen shown0meth tecui:emeols oftheapplicable comprottenSiVe anddelailedaimodinesscedeasproxidedbyAnnexfttoIhe ConventionInternaennal CivilAden, exceptasnotedherein. Exceptions: *None* 6 TERMSANDCONDITIONS keg SeqrSUR ntlemtl,suspended,revoked,ora terminationdateisolheraiseeslebfshedbytheFAA,thleakwodhinessceAiticale iseffectiNaskingsthamaintenance,preventativemaiNenance,am fl2it Pot 21,43,Bed 91oftheFederalAeileenRedalions,a5 *ale, andto airCril DATEOFISSUANCE DESIGNATIONNUMBER 03/06/2014 DART833943g ofINSceititalemayhepunishablebyafinenotexceeding$1,069orimposoemeel a misuse Anyallelloo,reprodudoo, rotexceeding 3 parsorboth, THISCERTIFICATE INTHEAIRCRAFT MUSTBEDISPLAYED INACCORDANCE WITHAPPLICABLEFEDERAL AVIATION REGULATIONS. FAAForm8100.2041) SupersedesPreviousEdition EFTA00011747 I EFTA00011748 4/10/2014 Flight Standards District Office Great Northern Tech Bldg. II North Olmstead, Ohio 44070 Cleveland Flight Standards District Office: ThorAir LLC. would like to request a new airworthiness certificate for Serial number RK-244, Raytheon Aircraft Company 400A. The reason for requiring an airworthiness certificate change is a new registration number is being placed on the aircraft. Included with this letter is AC Forum 8050-64 issue date Apr 03, 2014 showing the change in registration number from N493LX to N18815. Signature of Owner: Title of Owner: President of ThorSpoft, Inc., ThorAir, LLC. It's Member EFTA00011749 EFTA00011750 FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved O.M.D. No.2'20-0018 Es notion Date 02/28/2013 0LI' S 0461€70171 APPLICATION FOR INSTRUCTIONS- PIN ea IYPe. Done 464 in shaded meat these we for FAA use only &AP °nye; only to en eunspize0 FAA REOOSON4live. II eddma,el ol "r4Hponalion U.S. AIRWORTHINESS space is (waned. use eaectunent Fn special Opt panne, complete Sect ens Federal AMARA CERTIFICATE I1 VI. end Vii es appecable Ameniurstion 1. REGISTRATION MARX 2. AIRCRAFT BUILDERS NAME nAm 3 AIRCRAFT MODEL DESIGNATION 4 YR. MFR. FM CCOiNG N493O( Raytheon Aircraft Co 400A 5. AIRCRAFT SERIAL NO, 6. ENGINE BUILDER'S NAME (MAW 7 ENGINE MODEL DESIGNATION RK-244 Williams International FJ44-3AP ai 8. POWER CP pew es s 9 PROPELLER [ULCERS NAME Fa/ 10. PROPELLER MODEL DESIGNATION 1999 It AIRCRAFT IS I( ac eropk*F41 2 N/A N/A IMPORT APPLICATION IS HEREBY MADE FOR Ommks ma/ I A I / STANDARD AIRMRTHINESS CERTIFICATE essen...”) I Im•-• I I00-00 I Iw000.0 Ill m-0-00, I Ice...n.1 I• 9. 03. I tom,- a SPECIAL AIRWCRTHIMESS CERTIFICATE Mom era HRH 7 PRIMARY 9 UGHT-SPORT Rom aHo I I AIITMIT• I I PamN‘PIFIRTIFR I I W074-STR-Conirtd I I G&W I I Lighter then At 2 LIMITED 1 CLASS I 5 PROyiSIONAL Awsue. emu 2 CUSS,' R 3 RESTRICTED Asa* Ammon, AMs amend, 1 4 AGR/CULTURE AN PEST CONTROL FOREST memo NassAmcM 2 5 AERIAL SURVEY PATROLLING 3 6 AERIAL ADVERTISING MATTER CONTROL 1 0 OTHER 6moel N 1 RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EMOTION 4 AIR RACING 5 CREW TRAINING 6 MARHET SURVEY § 0 TO SHOW COMPLIANCE WITH THE CFR 7 OPERATING MoMMYCS*9.41FIT BUILT AIRCRAFT EXPERIMENTAL antra smem(s) aBA Esisiing Myatt wilICIA en limning., pleura a do mimosa $1011 4 OPERATiNG 86 a re a amoesi s U614E-SPORT lIC °Ining POMEIV IION U9N-SINH 4gelP600. ."I sry tax1/31Oxial11011486, Mary finsotHress d airmailietaaa a 21 I90 UNMANNED 9A REVAK,.ma DEVELOPMENT IOC' I CREW TRAINING 9 AIRCRAFT 98 MARKET SURVEY I FERRY FLIGHT KR REPAIRS. ALTERATOG. PAAINTEWMCE OR STORAGE SPECIAL FLIGHT PERMIT wow. 2 EVACUATE FROM AREA OF IMPENDING DANGER 13 epreNen re eneA/Csa Irer corwAre OPERATION IN EXCESS Cf MAxaTUR4 CERTIFICATED TAKEOFF MIGHT Nam so 4. we 44•44.4.4.. en 44.44 440 3 4 DELIVERING OR EXPCRDNG I 6 I • I PRODUCTION FLIGHT TESTING 6 CUSTOMER DEMONSTRATION FLIGHTS cl a MULTIPLE AIRWORTHINESS CERTIFICATE p.m. ABOVE 1,1•16:MOOMMOM fl ees 'Gaffed,MOND* A. REGISTERED OMER Ma MomM confooled oat intate, IF DEALER. CIIECK HERE I NAME ThorAir LW MS. Sandusky. OH 44871 B. AIRCRAFT CERTIFIGATICR BASIS Himammo ems weawasse•me ga MOMM3) AIRCRAFT SPEOFICATKFI OR TYPE CERTIFICATE DATA SHEET Ira Ne am AIRWORTHINESS DIRECTIVES omenet emkmA Ma a•HammToemoot*, ..44.4.4.4 i 44.44.',1 1 0Me IMMO Wainer WMIONP in. Ss *MAP ow • /DMMm•Mitak.) A16SW Rev 28 Bi Weekly 2014 2/10/2014 - 02/23/2014 i ARCRAFT LISTING /camp normrts$ WA SUPPLEMENTAL TYPE CERTIFICATE 6/4me esnth 47c Accepome) Pi / See Attached Sheet in C AIRCRAFT OPERATION AND MAINTENANCE RECORDS 5 CHECK IF RECORDS IN TOTAL AIRFRAME HOURS EXPERIMENTAL OM.Y crorFANH to.. mw, 4n[strew, AAA/ X CCSIPUANCENAni 3 a4 / 14 CFR Ma 92417 8616.1 TTAF ` 40 WA d D. CERTIFICATON • I hereby <wily MAIM?* 14filitered arner (or his 4WD 8 MO Put deaf!m tam. that me anon Is nomoto In 16 FORM ANOKA ASWIliSrea en el accordines mils TM 49 01the WHO Stale. Cole 44101Is are [pica es FERMI Aselben RepAMICess. end the Ihe eircreA aiwarTness cwVcate Amsted DATE OF APPLICATION NAME AND TIRE 'Fin tn..) &GNAT 03/06/2014 Anton Koprivnik Agent A THE AIRCRAFT DESCRIBED ABOVE HAS SEEN INSPECTED AND FOUND MRAORTHY BY: 044.40•44. mos ovIr 24 Cam/ V. I N.INSPECTION 14 CFR Mel 121 CERTIFICATE HOLDER Pre 3 CERTIRCATED MECHANIC Mfrs 04.1400”421 CERTIFICATED REPAIR ARON IOW amen 2 CooMMI0 Mal 6 NO) AGENCY 5 AIRCRAFT MANUFACTURER MA* nine es fray VERIFICATION DATE TILE SIGNATURE Ossamtc sepszes,4 sea e.4414.44 / THE CERTIFICATE REQUESTED V. FM REPRESENTAITVE A I TIM :+m the rave 61404X4 ii1Seetion1 or W meets moan for 4 AMEMSMETIT OR MODIFICATION OFCURRENT AIRWORTHINESS CERTIFICATE B. Inspemon the spec* figt4 pemil Lwow Seam MI I FAA INSPECTCR FAA DESIGNEE Tros con04100 Dy MIN/CATION DATE MIOGIFS00 FAA INSPECT CFFICE SIGNATURE MP 03/06/2014 GL-25 4 DART833943 FM Form 8130-8 (4/11) NI PteirCUI Editions Superioded pt t i t s, 9 V C. 1.--• MAR 1 0 2014 CLE- EFTA00011751 A. IAANUFACTURER NAME ADDRESS §I B. PROOUCTON BASIS (OMCk Opplable Rehl I2 ; F OTHER: PRODUCTION CERTIFICATE (GMT ACAS OPMFMAt Noted TYPE CERTIFICATE C. GinQUANTITY OFCERTIFICATES REQUIRED FOR OPERATING NEEOS DATE OF APPLICATION NAME AND TITLE (MINNOW) SIGNATURE A. OESCRIPTON OF AIRCRAFT REGISTERED OAT ER ADDRESS BURGER (Mgee) MODEL SERIAL NJM BE R REGISTRATION NARK 8 OESCRIPTION OF FuGHT CUSTOMER DEMONSTRATION FUGHTS O fl ee ' *plait) VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER TIAN PRODUCTION FLIGHT TEST FROM TO VIA OEPARTURE DATE DURATION C CREW REQUIRED TO OPERAT E DE AIRCRAFT AND ITS EQUIPMENT 1 1 PILOT I 1 COP LOT I I FUGNTENGiNEER I I OTHER (Spay) D THE AIRCRAFT CCUNOT MEET THE APPLICABLE NRWORTNNESS REQUIREMENTS AS FOU.ONS: E TIE FOLLONNG RESI R CTIOW ARE CONSIDERED NECESSARY FOR SA.E OPERATION. (Use ran EHammy) F CERTIFCATIOI Ant" cm* Minim um roosono0 owmr (or Na KAM) of d out Seated Mom tot to *ar is registered Min tre FolengMaga. Adorn unman in accorcance win DM 49 ol ligo Urand Salm Can 4001olzo and migicabig Fail Mean Rogotallont AM MK Os Scut hog tomMonger) end is Nete Ice Om fltaN Onamect DATE NAME ANOMIE (PANHIM/ SIGNATURE A Operatng Lentaactm are Matkings In COnVerma WEIN CFR WOOF, Ott 0. Satomat <I Concenitg. FAA Ferro BI304 Meath when reptsmx0 R ta 1 As AppIcatle It RAO Airmeiness CelAcalica ke mom Mae a CononI CP6Mbrg Lm1444414 Allarated (Mach when resiroN as ...IZ;: / C. Gala. Drafting& Prows^ alt (AMacit step tequentn I. PreVous Afrovetrinela Certificate immg inMcorglarm VAR ec i , i IF CFR Swam 21.191 (0 CAR FOMM teutenno i s; 4 i 0 Curve Wotan ana Basra Mormon AvtAitei in Mar gi E AI Ito DAM AlieratK41. FM Fpm 337 (MmA men (man i J. Cycle' Meatiness CAMARA IssuedInMordants WO 14 CFR Anoka 21.183 (d) (dopy sow/ § / F ins itzpeceon ROCONOS in MVO Records K. Us(+l4p01ArgraElliolincal of Corpora FMForm 813615 MOO when rewind) FAA Form 8130-141111 Ai Provous Eddidif Superseded adman Formai -PDF Page 2 x2 AP. EFTA00011752 UNITEDSTATESOFAMERICA DEPARTMENT -FEDERALAVIATIONADMINIST OFTRANSPORTATION STANDARDAIRWORTHINESS CERTIFICATE 1 NATIONALITYAND 2 MANUFACTURER ANDMODEL 3 AIRCRAFTSERIAL 4 CATEGORY REGISTRATIONMARKS Raytheon Aircraft NUMBER N493LX Company 400A RK-244 Transport 5 AUTHORITYANDBASISFORISSUANCE This*Pitiless codhalaisWIpoollo49U.S.C,04164andcedesdel,asplatadalolImamIP *tall towhich issuedhasboaOdd andfoundlooordorm loth lypaceicolethlor, to6611109dliOriforsaleoperadoa, andhasteen showntomeettherequirempls alto app!icahlo and'Maki airworthiness comprehensive codaspro*byAmaxBlob Condo onIntomolipalC4 Nation,mantasrichhail Exceplions: *NONE* 6 TERMSANDCONDITIONS lints sow mended, sap*,'evoked,klerroirellori daleisotherwise Petted b le FAA,thisahodies Whale isPalmas lop ashmitenco, praventalio mite/a, widiPa4s21,43,and SIofat Red Ade R MORS,asa ro ' le,andthea DATEOFISSUANCE DESIGNATIONNUMBER 03 06 2014 DART833943GL AnyalvaOon,reproduction, ormisuseofINsCirliall) mayhopiste% byafoieriotova* 51,656imprisonmord°pooling3youscrbolt THISCERTIFICATEMUSTBEDISPLAYED INTHEAIRCRAFT INACCORDANCE WITHAPPLICABLEfE0ERAlAVIATION REGULATIONS, FAAForm810040411) SupersedesPreviousEdition EFTA00011753 I i EFTA00011754 ' UNITEDSTATESOFAMERICA DEPARTMENTOF TRANSPORTATION• FEDERALAVIATIONADMINISTRATION SPECIAL AIRWORTHINESSCERTIFICATE A CATEGORY/DESIGNATION ERrirtienta1 PURPOSE Market S:4rvq,‘ / Q MANU- NAME /4,,( N/A ,Y q w FACTURER ADDRESS/di/ d/WA. („% FROM r /7AVI,VeV'', \\\ C FLIGHT TO iii.,• , ' ‘ WAY' ' .. N- 493LX i; , t , SERIALNO. RK-244 U BUILDERRaytheonOki , raTt 'Cd.4, MO* 400A DATE OF ISSUANCEFe ‘,0".5/401‘41' /O,.MRY Aug/ 04 /2014 OPERATINGLIMITA S'Oe '\k -.: :5110:10,0 PARTOF THISCERTIFICATE E DESIGNATIONOR OFFICENO. DART833943GL Any alteration, reproduction or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 pars, or both. THIS CERTIFICATEMUST BE DISPLAYEDIN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLETITLE 14, CODE OF FEDERAL REGULATIONS(CFR). FAAFORM8130.7 (071041 SEEREVERSESIDE NSN; 0052.00.6934000 EFTA00011755 A Thisairworthinesscertificateis issuedundertheauthorityofPublicLaw104, 49UnitedSlatesCode" A (USC)44704andTitle14CodeofFederalRegulations(CFR), Theainuorthinessceifificaleauthorizesthemanufacturernamedonthereversesidetoconduct Ba productionflightests,andonlyproductionflightests,ofaircraftregisteredin hisname,Nopersonmay conductproductionflighttestsunderthiscertificate:(1)Carryingpersonsorpropel/ forcompensationor hire:and/or(2)Cryingpersonsnotessentialto thepurposeof theflight C airworthinesscethficateaulhonZesthe flightspecifiedonthereversesideforthepurposeshownin BlockA, ThisairworthinessceilificateceitiliesMalasof thedaleofissuance,theaircrafto whichissuedhas beeninspectedandfoundtomeetherequirementsof theapplicableCFR,Theaircraftdoesnotmeet therequirementsof theapplicablecomprehensive anddetailedairworthinesscodeasprovidedbyAnnex D 8 totheConventionOninternationalCivilAviation,NopersonmayoperatetheaircraftdescribedOnthe reverseside:(1)exceptin accordancewiththeapplicableCFRandin accordancewithconditionsand limitationswhichmaybeprescribedby theAdministratoraspartof thiscertificate;(2)overanyforeign countrywithouthespecialpermissionof thatcountry, Unlessoonersurrendered,suspended,orrevoked,thisairworthinesscertificateis effectiveforthe E durationandundertheconditionsprescribedin 14CFR,Part21,Section21,181or 21,217. EFTA00011756 ThorAire March 3, 2014 ThorAir, LLC. Sandusky, Oh Re: RK 244 - Agent Authorization To whom it may concern: This letter is to confirm that ThorAir, (IC, authorizes Nextant Aerospace, LLC, as ThorAir's agent for a Beechjet 400A, bearing serial number RK-244 and FAA Registration number N493LX, which is owned by ThorAir, LLC., and operated by ThorSport, Inc., for any and all authorized FAA actions needed. Sincerely, Thor ' By: M.%\ "ZY`WtS \A\AQO\U Notary's Official Signature Sworn and subscribed to me this day,3 of nx V1 2014 ThorAir • • Sandusky Ohio 44870 ThorAfr EFTA00011757 EFTA00011758 RK-244 STC list (03/05/2014) Reference 8130-6: Application for Standard Airworthiness Certificate Transport Category, dated March 6, 2014 Reference section III owners certification ST02371LA: Replacement of Pratt & Whitney JT15D-5 series engine with Williams International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems. ST10959SC: Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFIS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics System Company (UASC) Terrain Awareness Warning System (TAWS) ST03960AT: Installation of Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (WEAN), Astronics 115VAC 60Hz Cabin Inverter and Bonner LED Cabin Lighting System. ST01572WI: Installation of four (4) model 400A OEM seats, one (1) three-place divan, one (1) aft toilet, one (1) set of aft pocket door dividers, one (1) set of forward pocket door dividers and LED lighting. STC01794LA: Installation of Hawker 97650W0370 or 9750W0370-8 battery ST000812SE: Group airplane approval for Reduced Vertical Separation Minimum — (RVSM) EFTA00011759 _ EFTA00011760 EFTA00011761 EFTA00011762 *iiCa4117A SAC ?ROMA \O SER\ AL # MOOV_V EFTA00011763 EFTA00011764 EFTA00011765 EFTA00011766 FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE T2 Form Approved O.m.g. No. 2120.0018 I itaiion Dale 0228/2013 Ill 01 3 APPLICATION FOR INSTRUCTIONS - Print or type. Do not wille in shaded meat Mese re for FAA U S Department use only. Submit original only to an authorized FM Representative. If acklronal 0/ aTranspenal ion U.S. AIRWORTHINESS space is required. use rtectuneM For special tight permits complete Sections -1 3 -i Federal A laton AdmInIstr on CERTIFICATE II. 1/1 and VII as applicable. 22 N 1. REGISTRATION MARK 2. AIRCRAFT BUILOEI3'S NAME (owl 3. AIRCRAFT MODEL DESIGNATION 4. YR. MFR. FAA COOING a N493LX Raytheon Aircraft Co 400A 1999 a lir. Q a 5. AIRCRAFT SERIAL NO. B. ENGINE BUILDER'S NAME mew 7. ENGINE MODEL DESIGNATION u a I S RK-244 Williams International FJ44-3AP _p B. NUMBER OF ENGINES 9. PROPELLER BUILOEF7S NAME mar ID. PROPELLER MODEL DESIGNATION I AIRCRAFT IS fawn 2 ejohness) 2 N/A N/A IMPORT APPLICATION IS HEREBY MADE FOR Itasca wiplagge WM/ I A I ei STANDARD AIRWORTHINESS CERTIFICATE metre crecold I has, I I win,' I I awc I/Imams-Yr I I ....... I I.4,00. I Iona, 0 SPECIAL AIRWORTHINESS CERTIFICATE (Crectiarreeemram 7 PRIMARY 9 LIGHT-SPORT emisam I 1 AlMene I I Poser-Peradlule I I Weistit•ShisCentel I I GM.' I I LOW den At 2 LIMITED I CLASS I 5 PROVISIONAL Aeon On) 2 CLASS II G I AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING rt 3 RESTRICTED mama apeastrarl am ametothe 4 FOREST mem anstmerd 5 PATROLLING e WEATHER CONTROL g 0 OTHER (soeat) I RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION 3 4 AIR RACING 5 CREW TRAINING a MARKET SURVEY a 0 TO SHOW COMPLIANCE WITH THE CFR 7 OPERATING Porgy Conn) KIT BUILT AIRCRAFT 2 BA Existing aircraft MithOlA WI aiworminess centate & do not meal 5 I03.1 '2 r 4 EXPERIMENTAL (mare Ordestimal to OF MOWN° $ OPERATING Be °wary LIM-Sport Kiiitaft sr LIGHT-SPORT U ornicl WSW, ' PnAlAutt, Issued spacial 99M-sporl Meow ainvonhiness ai canters under 5 VAC UNMANED 9A RESEARCH MID DEVELOPMENT [ 9C I I CREW TRAINING 9 AIRCRAFT 90 MARKET SURVEY I FERRY FLIGHT FOR REPAIRS. ALTERATIONS. MANTENANCE OR STORAGE SPECIAL FLIGHT PERMIT promo 2 EVACUATE FROM AREA OF IIMENONG GANGER opnAbno No pantheon IMO 00TOIMI B Memo a w in mama mmart. sew 3 OPERATION IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT 4 DELIVERING OR EXPORTING 15 I I PRODUCTION FLIGHT TESTING e CUSTOMER DEMONSTRATION FLIGHTS CI, a MULTIPLE AIRWORTHINESS CERTIFICATE fa.* MOVE %Skied Opirailoisne•Starclair iv •Linfte 414:10600A01 A REGISTERED OWNER mu rem an ememir arms remserse) IF DEALER, CHECK HERE I NAME Flight Options LLC IIIIII Richmond Heights .OH 44143 Z 8 AIRCRAFT CERTIFICATION BASIS (ChM, •APraa, WOCA. Onie0. 1. 0 dent *I OJOS* 0 AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET ICA• ma and AIRWORTHINESS DIRECTIVES 403 /4,0 4 *a aapikwidei 404 we cowpwata awg•womerter P / mummer / eft railADSUPPLEMENT mile* In as assay sewn MOO IWO 0 OPON410/9 A16SW Rev 28 Bi Weekly 2013-25 12/02/2013 - 12/15/2013 0 P AIRCRAFT LISTING roraeraeamemOU SUPPLEMENTAL TYPE CERTIFICATE (LIS member -SA SIC bitsponffic i NM See attached sheet C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS i CHECK F RECORDS IN TOTAL AIRFRAME HOURS EXPERIMENTAL ONLY (Emu have sae armMIchime Sited 1 WITH 8581A3 3 a wend) i CFR /c.00t:memtion sec 91A17 TTAF 2.81 ö D. CERTIFICATION • I hereby centy Nal am Ms regtslarloviner(or Ns gentle! tie eirnalt deserted stove. that We amend repaired with Me Federal Aviation AtInintralam Iti imordaroa with Tele 49 el the UMW Sires Ca* 44101 ABS end swabs Federal Avietion Rogulatice, and that the Orereft has teen illSPOCIOd and is Arwonhy and OSP* for the altworthWess crater. reapeslot DATE OF APPLICATION SIG 12/29/2013 Agent A THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: Komar ma mammy Nall per it I1310.4oles/ 14 CFR put 121 CERTIFICATE HOLOER tom CERTIFICATED MECHANIC (61.0494:41• No) e CERTIFICATED REPAR $TATi N (OW CeMcate I se r3 2 cement ram 3 PM) Wt 2g tul AIRCRAFT MANUFACTURER ter•• reranMN C 5 3 A CC j V DATE TITLE SIGNATURE (Ora AU *roam WC* awe A aVII) I THE CERTIFICATE REQUESTED at > A I Tad that ma maul described n Seam I or VII more regurernents for 4 AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE P 'S z B. Impechan toter:mist No porta under Section VII FAA INSPECTOR FM DESIGNEE i2 was conducted by Zg W CERTIFICATE HOLDER UNDER 14 CFR pales 14 CFR Wit 121 OR 135 1a CFR 11 145 a nYr DATE MIDOIF SOO iF, OFFICE 9u 12/29/2013 CLE-25 s FAA Form B1306(4111) Al Previous &Mons EFTA00011767 EFTA00011768 A. MANUFACTURER NAME ADDRESS B. PRODUCTION BASIS (Chick appitsbis Mm) IR PRODUCTION CERTIFICATE (Give proxkottim Akar° number) ft TYPE CERTIFICATE SGG OTHER C GNE QUANTITY OF CERTIFICATES REQUIRED f OR OPERATING NEEDS DATE OF APPLICATION NAME AND TITLE (Prini of RPM SIGNATURE A DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRATION MARK B. DESCRIPTION OF FIGHT CUSTOMER DEMONSTRATION FLIGHTS 0 (Check 11morat4) FROM TO VIA DEPARTURE OATE DURATION C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EOUIPME NT I PILOT I I CO-PILOT I I FLIGHT ENGINEER I I OTHER (Specify) D THE AIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS. E. THE FOLLOWING RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATION eltadmmni dnecessory) F. CERTIFICATION - I Namby =try Meilen the recoteted =nor for his ageed)of Me aircraft described them: that the aiwah is mcistered math the Federal Atielign Adniftisvation in smorcteme mt. Tills 49 of the LISS Sates Code 44101 gun and applicable Federal Mallon Regattas. end that IM aircraft hes Wen =peeled end s safe for the NOV desated DATE NAME AND TITLE (NW Of RPM SIGNATURE A. Operating Limitations and MaikessnOmnpharce Wan 14 CFR Section 919. G. Steinman( of Colonnity. FAA Form 8130-9 (Mach whenmugs* f 4 APPlicable 14 Foreign Almmtniness Gerthcaban for Import Airat Opening LerMations Attached (Attach when spired) B. Cat I. Previous Arworehmen Cantata Issued in Accordance With C. bete Drarwma Phoiographa etc (Alfa, whin 0.9a0NO I 14 CFR Section 21.191 (a) CAR (Onginet MaCNKO I D. Caren) Segni and BNence Wormalion Available In Aircraft I J Current Airworthiness Cenfcate Issued n Accordance Wen E Major Rest and Maralion. FAA Form 337 (Minh when inured) 14 CFR Seelien 21.181 (a) (Copy egeeMNO I F. This inspecbon Recorded n Aumaft Records K Ufett-Spcs AraM Stmement of Compiarce. FAA Fran 8130-1S (AEW, when =NYS) FM Form 81304 (4111) Ap Previous Edabm Superseded Demonic Forms -PDF Page 2 Of 2 EFTA00011769 EFTA00011770 UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERIAL 4 CATEGORY REGISTRATION MARKS NUMBER Raytheon Aircraft N493LX RK-244 Transport Company 400A 5 AUTHORITY AND BASIS FOR ISSUANCE This airworthiness certificate is issued pursuant to 49 U.S.C. § 44704 and certifies that, as of the date of issuance, ircraft to which issued has been inspected and found to conform to the type certificate therefor, to be in condon for safe o 'on, and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as sided by Annex 8 to the Convention on International Civil Aviation, except as noted herein. Exceptions: *None* 6 TERMS AND CONDITIONS Unless sooner surrendered, sus /d, revoked, or a termination date is otherwise established by the FAA, this ainvottiness certificate is effective as long a rts 21, 43, and 91 of the Federal A DATE OF ISSUANC DESIGNATION NUMBER 12/29/2013 DART833943GL Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. EFTA00011771 S EFTA00011772 UNITED STATESOF AMERICA DEPARTMENTOF TRANSPORTATION• FEDERALAVIATIONADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A CATEGORY/DESIGNATION EXPERIMENTAL I' - PURPOSE RESEADIAJELOPOKX i 0 MANU. NAME //b, A .,:`,il4,,1,/ B - ADDRESSIIIOWAI)Vd1 FROM NAY i,kiA / - 1`, FLIGHT TO ilj r`4, I ,D N• 493L4 ;111 t ', , StRIALNO.RK- 244 BUILDER RaythemAihrifikpany 1.4 MODEL 4C0A DATE OF ISSUANCE K..8) '&311 /0 .€XPIRYJan 12.2014 OPERATINGLIMITATIO,i' At,' 08';20B,igE PARTOF THISCERTIFICATE E "D'ESIGNATIONOR OFFICE NO. DART833943a Any alteratio •production or misuse of this cetficale may be punishable by a fine not exceeding $1,000 or imprison • 1 not exceeding 3 years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN A9i 'DANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (CFR). FAA FORM 8130.7 (07(041 SEEREVERSESIDE NSW. 005240.6914000 EFTA00011773 Thisairworthiness certificateis issuedundertheauthorityofPublicLaw104.6,49UnitedStatesCode A (USC)44704andTitle14CodeofFederalRegulations(CFR). Theairworthinesscertificateauthorizesthemanufacturernamedonthereversesidetoconduct productionflighttests,andonlyproductionflightests,ofaircraftregistereind hisname,Nopersonmay B conductproduction:lightestsunderthiscertificate:(1)Carryingpersonsorproperlyforcompensationor hire:and/or(2)Crying personsnotessentiatol thepurposeof theflight. Thisairworthiness certificateauthorizestheflightspecifiedonthereversesideforthepurposeshownin BlockA. Thisairworthiness certificateceitifiesthatasof thedateofissuance,theaircraftowhichissuedhas beeninspectedandfoundtomeetherequirementsoftheapplicableCFR,Theaircraftdoesnotmeet therequirements of theapplicablecomprehensive anddetailedairworthinesscodeasprovidedbyAnnex 9 totheConventionOninternationalCivilAviation.Nopersonmayoperatetheaircraftdescribedonthe reverseside(1)exceptin accordancewiththeapplicableCFRandin accordancewithconditionsand limitationswhichmaybeprescribedbytheAdministrator aspartof thiscertificate;(2)overanyforeign countywithouthespecialpermissionof thatcountry. Unlessoonersurrendered, suspended,orrevoked,thisairworthiness certificateiseffectiveforthe E durationandundertheconditionsprescrib 14CFR, edin Part21,Section21.181or 21.217. EFTA00011774 RK 244 STC list (12-26-2013) Reference 8130-6: Application for Standard Airworthiness Certificate Transport Category, dated December 26, 2013 Reference section ill owners certification ST02371LA: Replacement of Pratt & Whitney JT15D-5 series engine with Williams International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems. ST10959SC: Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFIS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics System Company (UASC) Terrain Awareness Warning System (TAWS) ST03960AT: Installation of Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (WLAN), Astronics 115VAC 60Hz Cabin Inverter and Bonner LED Cabin Lighting System. ST01572WI: Installation of four (4) model 400A OEM seats, one (1) three-place divan, one (1) aft toilet, one (1) set of aft pocket door dividers, one (1) set of forward pocket door dividers and LED lighting. STC01794LA: Installation of Hawker 97650W0370 or 9750W0370-8 battery ST000812SE: Group airplane approval for Reduced Vertical Separation Minimum — (RVSM) EFTA00011775 EFTA00011776 Cleveland. Ohio 44143 aLti Options December 26, 2013 Nextant Aeros ace, LLC Cleveland, Ohio 44143 Attention: Re: RK-244 — Agent Authorization To whom it may concern: This letter is to confirm that Flight Options, LLC ("FO") authorizes Nextant Aerospace, LLC, as FO's agent, for a Beechjet 400A, bearing serial number RK-244 and FM Registration Number N493LX (also identified as a "Nextant 400XT"), which is owned by FO, for any and all authorized FAA actions in regards to: Airworthiness Classification Experimental X Airworthiness Classification Standard Sincerely, Flight Options, LLC By: Vice President, Administration & Contracts Ma_ Notary's Officio" &Ina-Cure Siam ana subscx tbez1 4-o Pt -141 do. 2 G, ckC bef-,e.,nt•er O4 2_01 3 bl EFTA00011777 EFTA00011778 EFTA00011779 I EFTA00011780 Riff', Apotral Electronic Trackin9 Number 0 MAJOR REPAIR AND ALTERATION ovs Ne 2l mono itt3orzoci7 US Mammon a (Airframe, Powerplant,Propeller, or Appliance) Trarapanalkin For FAA Use Only Fedni Aviation AchninIstratreri INSTRUCTIONS: Pant or type all entries. See FAR 43.9. FAR 43 Appendix 8. and AC 429-1 (or subsequent revision thereof) for instructors and disposition of this form. This report is required by law (49 U.S.C. 1421). Faiture to report can result in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1955) Nationality and Registration Mark Serial No RK-244 N493LX 1. Aircraft Make Model Soles Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner Flight Options .LLC Address Cry Richmond Heights state. OH Zip 44143-1453 co.ty USA 3. For FAA Use Only 4. Typo 5. Unit Identification Repair Alteration Unit Make Model Senal Number 0 ►1 AIRFRAME (As descnbect in gem 1 above) a P0WERPLANT III ❑ a PROPELLER Type ❑ O APPLIANCE lilanyfanser 6. Conformity Statement A. Agency's Name and Address 8 Knd of Agency Nerve Nextant Aerospace O u.S. Certificated Mechanic O 'Manufacturer Address O Foreign Centticated Mechanic C. Certificate No. City Cleveland stn. OH 0 Certificated Repair Station Zip 44143-1453 cony USA O Certificated Maintenance Organization CRS # 25NR667B D. I candy that the repair smiler alteration made to the unit(s) Identiaed in item 5 above and described on the reverse or attachments hereto have been made n accordance with the requiements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of ray knowledge. Extended range fuel per 14 CFR Part 43 Apo. Et 11 05/30/2013 7. Approval for Return to Service Pursuant to the authority given persons speared ['Sow, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is El APPROVED ❑ REJECTED FAA Fit Standards Manufacturer Maintenance Organization [Person Approved Department of by Canadian Transport Inspector BY other (SPearY) FAA Designee X Repair Station Inspection Au •rization i Certificate or Designation No. CRS it 25NR667B 05/30/2013 FAA Form 337 (1006) EFTA00011781 EFTA00011782 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued conformity with the applicable airworthiness requirements 8. Description of Work Accomplished (If more space is required, attach additional sheets. !den* with aircraft nationality and registration mark and date work completed) N493LX 05/30/2013 Nationality and Registration Mark Date Part I of 3 The Following Equipment was removed along with Associated Hardware. EFD-871 622-9345-203 Electronic Flight Display EFD-871 622.9345.203 Electronic Flight Display MFD-871 622-9434-213 Multi Function Display ICU-85 622-6189-002 Internal Compensation Unit ICU-85 622-6189-002 Internal Compensation Unit AHC-SSE 622-9336-400 Attitude/Heading Computer AHC-85E 622-9336-400 Attitude/Heading Computer SDU-6408 622-9735-001 Sensor Display Unit SDU-6408 622-9735-001 Sensor Display Unit DCP-5000 822-1028-011 Display Control Panel DCP-5000 822.1028.011 Display Control Panel ARP-851 622-9500-011 Altitude Reference Panel ARP-851 622-9500.011 Altitude Reference Panel AAP-851 822.0328.011 Altitude Awareness Panel AAP-851 822-0328-011 Altitude Awareness Panel CHP-850 622-7397-002 Course Heading Panel DBU-4100 822-0014-002 Data Base Unit DAU-650 622-9344-101 Data Acquisition Unit SDD-640A 622-9347-001 Sensor Display Driver IOC-4000 ( 4) 622-9814-514 Card Assembly MDC-4000 622-9818-751 Maintenance Computer CSU-4000 (2) 822.0049-002 Configuration Strapping Unit FMC-5000 (4) 822-0891-008 Flight Management Computer PWR-4000 (4) 622-9945-021 !APS Power Card GPS•4000 822-0931-003 GPS Receiver Mounts 622-9430-002 EFD /MFD Mounts EFB Electronic Flight Bag Mounting El Additional Sheets Are Attached Form 337 (10-06) EFTA00011783 EFTA00011784 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 5/30/2013 Nationality and Registration Mark Date Page 2 of 3 Installed the Following Equipment along with Associated Hardware. Model Part Number Description Weight Arm CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 DCU-3001C 822-2362.003 Data Concentrator Unit 5.0 325 DCU-3001C 822-2362-003 Data Concentrator Unit 5.0 325 ECU-3000 822-1200-209 External Compensation Unit 0.40 57.5 ECU-3000 822.1200-209 External Compensation Unit 0.40 57.5 FSU-5010 822-1543.101 File Server Unit (1" ins) 6.5 60.83 ECU-3000 822-1200.998 File Server Unit (1st IRS) 0.40 57.5 AFD-3010E 822-1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753.416 Adaptive Flight Display 12.90 89.2 AF0-3010E 822-1753-416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753-416 Adaptive Flight Display 12.90 89.2 IMT-3010 822-1140.401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 10852801Y00 Fuel Quantity Conditioner 0.90 324 PC920-2A2000PH-2A1 Fuel Flow Conditioner 1.10 325 GPS-40005 822-2189-004 GPS Receiver 6.0 37 Cl 429-410 GPS Antenna 1.0 166.14 Amp Cluster N241100-002 DC Voltmeter 1.5 97.4 373-93-1501-1 Speed Switch (2) 0.25 89.2 DBU-5010E 822-3000-202 Data Base Unit 1.60 134.5 PS-835D 501-1228.004 Power Supply 12.5 52.9 MMT-5000 822-1811-003 File Server Unit Rack 0.30 57.5 MMT-3010 (2) 822-1290-003 AHS Mounting Rack 1.80 57.5 XM WR-1000 822-2031-002 XM Weather 1.5 41.0 CHP-3010 822-1280.003 Course Heading Panel 1.30 92.5 Options Configuration Module. OCM-4100 822-1463-228 0.30 57.5 WAAS/LPV Options Configuration Module. OCM-4100 822-1463.228 0.30 57.5 WAASAPV Additional Sheets Are Attached Form 337 (10.06) EFTA00011785 EFTA00011786 NOTICE Weight and balance or operating limitation changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 05/30/2013 Nationality and Registration Mark Date Page 3 of 3 Model Part Number Description Weight Arm CSU-4100 (2) 822-1364-002 Configuration Strapping Unit 1.60 55.7 MDC-3110 822-1987.006 Maintenance Data Computer 0.80 55.7 FMC-6000 (2) 822-0868-123 Flight Management Computer 1.90 55.7 ADC-850D (2) 822-0389-468 Air Data Computer 5.30 60.83 AHC-3000A (2) 822-1378-001 Attitude Heading Computer 4.80 57.5 DCP-3030 (2) 822-1828-002 Display Control Panel 1.90 89.96 PWR-4000 (4) 622-9945-022 IAPS Power Card 1.3 55.0 IOC-4100 (4) 822-1362-511 Input/output Concentrator 0.8 55.0 LT-4001-010 Master Caution Panel 1.3 87.0 Rev. Panel 373-91-3203.1 Pilot Reversion Panel 0.2 88.0 Rev. Panel 373-91-3203-3 Co-pilot Reversion Panel 0.2 88.0 9-PED 373-91-3203.9 9-Pedestal Panel 1.8 92.89 345-6196 ELT Switch 0.2 88.0 Annunciator Led-42-12-8B-E0Y47 AUX BATT (1/2) Annunciator 0.05 88.0 Annunciator (2) Led-40-18-88-E0Y4S Pull Up/ Terrain Annunciator 0.05 88.0 Annunciator 2-F840231 Terrain Inhibit/ Terrain Fail 0.05 88.0 In Accordance with SIC ST10959SC. See Attached Copy AFM Supplement, Nextant Aerospace Doc. No. 373.00.0023 Rev IR Dated 09/02/2011or later FAA approved revision, installed on Aircraft. Equipment Pilot Guides are Installed in the Aircraft as Portable Document Format (.pdf) via supplied I-Pad. NOTE: Portable electronic devices used to store required aircraft records required by Part 91.9 are considered Electronic Flight Bags (EFB) per FAA Advisory Circular AC 120-768 par 4-g. Commercial operators are required to obtain authorization for their use from their managing Flight Standards District Office. Instructions for Continued Airworthiness (ICA) Ref Nextant Aerospace Document 373-00-0002.Rev C or Later are included in the Aircraft Maintenance Records Carried out System Ground Test Plan PAW Master Drawing List (MDL) 373.00.004 Rev C. Carried out Hawker Beechcraft Service Bulletin 34-3431Reduced Vertical Separation Minimum (RVSM) Airframe Inspection / Modification. Performed FAR 91.411Inspection per Part 43 appendix "E" Pitot Static & FAR 91.413 Inspection per Part 43 appendix "F" Transponder System checks. ❑ Additional Sheets Are Attached Form 337 (10.06) EFTA00011787 EFTA00011788 *atm of 4\ nterica department of eafrartsportation Ifeberal (Ablation glibministration $upplerttental Type Certificate ACIalate ST10959SC .121, an.1.456%4 Nextant Aeros ace LLC Richmond Heights, OH 44143 arA4A 44,a; donjs414,A 4ye diainfr44 / 40avnneediclavle /.4 dovialani azulawelaivo rRJ rataSewitereen nwv/4i airnaam trytabetneaht marl 25 944 Federal Aviation Jigewana.J. (See Pages 3 and 4 for complete certification basis.) eini‘sezeilierka• 4,eg;n4jetatin./YimaGe Al 6SW ../44. Hawker Beechcraft Corp. ,.#r61. 400A gieW.)7/w tyriffifs 91474 KZ/7r Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EMS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics Systems Company (UASC) Terrain Awareness Warning System (TAWS) in accordance with Nextant Aerospace LLC Master Drawing List Doc. No. 373.00.0001 Revision W, dated March 29, 2012, or later FAA approved version. Sintelalsiinss andriaisiast: 1) The installer must determine whether this design change is compatible with previously approved modifications. 2) If the holder agrees to permit another person to use this certificate to alter a product, the holder must give that person written evidence of that permission. . 3) For aircraft equipped with Pratt & Whitney al 5D Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00.0008 Revision IR, dated 10/19/2009, or later FAA approved version, is required on board the modified aircraft. cete94'eare and 4 invites? a/a 0444' Ai a Au) wiaatvs,.....4.4 S'ent t...41..vtentseired wt.itar.a.‘ei vvend re a keetaisaloin cotto twe serwe:m ma < 4. 4A .4144,4x4,474v r724 .9;eArat lenearaectleM gia.4./yrrearairen June 26, 2008 glao freV.1.31/..1 g4.4. elt;vacar..t October 19.2009 afflealb2(' September 26, 2011; April 05, 2012 Manager, Systems and Flight Test Branch Chicago Aircraft Cenitication Office (Tirle) Any .notation or (big JS poroshata., OY . floe of not ovcoodino .1.J.O. or Joprison.0.1 .0C •mcoOdinq 1 year., or Opt.. Fmk rot.. 4110-2110.641 PAGE I of 4 P&G'S This NY be trans:oared Ja accorderce .Jco fa 21.42. EFTA00011789 EFTA00011790 jfintieb Stales of ,Aintrita !el:ointment of 2granisportation - ebernt Ablation ,2\botinisfration Supplemental `Type Tertifirate (Cartiinuation $ijeet) Aa,724/e ST I 0959SC Pako>44.saonoo• October 19, 2009 Date Amended: September 26, 2011; April 05, 2012 gleadeal OesetWAISAYIJ 7ISVialeArk 4) For aircraft equipped with Williams FJ44-3AP Engines, those engines must be installed under STC ST0237ILA. 5) For aircraft equipped with Williams FJ44-3AP Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373.00.0023 Revision IR, dated September 2, 2011, or later FAA approved version, is required on board the modified aircraft. 6) Aircraft must have previously qualified for Operations in Reduced Vertical Airspace via: RK-I thru RK-I 17 and RK-I 19 thru RK-I39, Hawker Beechcraft Service Bulletin No. 34-3431. RK-118, RIC-140 thru RK-224, Hawker Beechcraft Service Bulletin Nos. 34-3228 and 34-3431. RK-225 thru RK-299, Hawker Beechcraft Service Bulletin No. 34-3431. RK-300 and after as original equipped from Hawker Beechcraft. 7) For aircraft equipped with Universal Avionics Systems Corporation (UASC) TAWS FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0036 Revision IR, approved March 28, 2012, or later FAA approved version, is required on board the modified aircraft. 8) For aircraft with Collins Proline 21 FMS-6100 LPV Approach enabled FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0032 Revision IR, approved March 28,2012, or later FAA approved version, is required on board the modified aircraft. tifeaeAaten Suit: Based on 14 CFR §p 1.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Hawker Beechcraft 400A aircraft is as follows: a. The type certification basis for the Hawker Beechcraft 400A aircraft is shown on TCDS Al 6SW for parts not changed or not affected by this change. b. The certification basis for the parts changed or affected by this change since the reference date of application, September 29, 2009, is based on TCDS A I6SW and §§ 14 CFR Part 25 as shown on page 4 of 4 of this STC. • Any alser [son of chis cerCIfjcace is pvnishable 0y 4 Zito or hot eeeoedin0 01.000. or inpeJsohosoc not extooding J years. or both. FAA ram IIIO-0.1110-PII PACE 3 of 4 PAGES This ces(iIi4Ate *my be Cron*****SO' An sccordance .lth FAA L.U. EFTA00011791 I EFTA00011792 !lulled *alto of /mtrica pepartment of Eransportatiott - geberal jAbiation cAbministration Supplemental Igp Tertificate ((Continuation Ace° Paie4 rAvacteres October 19. 2009 Date Amended: September 26, 2011; April 05, 2012 Based on 14 CFR §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the baseline Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFIS) with Rockwell Collins FMS-6100 modification was determined to be TCDS A I6SW and the following later regulations: Amdt.[24-4) Amdt(25.23) Amdt.(25.38J Amdi.)25-401 Amdt.I25-41) 25.771 (Le) 25.301; 25.303: 25.581; 25.1309 25.901 (b)(1Xi); 25.1549 25.1321 (aX6)(e)(e): 25.607: 25.611. 25.773 (eXtiXe)(cXeNn: (1)(bXe) 25.1131;25.1333 (a)(1)(1)(d) 25.1322 Amdt.[25-421 Amdt.125-46) Amdt.(25.54) Amdl.(25.72J Amdt.125.801 25.1501 25.603; 25.605: 25.613; 25.1529 25.307;25.571, 25.1307 25.1316 25.1329(N (OK): 25.1351 (a)(1)(d): 25.1381; 25.1521 (a)(c); 25.1543(6); 25.1581: 25.1563 (a) Am& (25-86) Andt[25.90J Amdt.12541) Amdl.125-1021 Amdt.(25-105) 25.305 25.1303 25.561 25.981 (a)(b) 25.1585(a) Amdt.(25.108J Arndt 125-1091 Amdi.(25-1 131 Amdt (25-122) Amdl.(25.123J 25.1325 (d) 25.1323 (aX060 25.869 ('X4):25.1431 25.1317 (a)(bXe) 25.1353 (aXc) Based on 14 CFR §§ 21 115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Collins Proline 21 FMS-6100 with LPV Approach enabled and UASC TAWS was determined to be TCDS A I6SW and the following later regulations: Amdt (Original) Amdt.(24-4) Amdt.(2S-23) Amdi.(25.38) Amdl [25.40) 25.601, 25.605, 25.609, 25.771 (a) 25.301; 25.303; 25.305, 25.603, 25.1322, 25.1585 (a) 25.613. 25.1301, 25.307, 25.561(c); 25.1583(e) 25.1357, 25.1381. 25.607; 25.611, 25.1307 25.1525, 25.1541, 15.1581 Amdt.(25•41) Amdt.(25-42) Amdt.(25-46) Amdt(25.54) Amdt.(25-72) 25.1309 (a)(b)(c)(6)(eXg) 25.1501 25.777(a0(c) 25.1529 25.869(a)(1) 25.1351 (a)(1) Amdt.(25-102) Amdt.[25-1 13) Amdt.[25.123] 25.98 1(a)(b) 25.1431(a) 25.1153 (aXe) - END - A y elu at on of C J* cort• Mktg is pimp& 'DM by s fine at not *Ambling $1.000, or Jowlsoewnt tun •xcentiao 3 yens, or Ugh. !AA 400.4 $110.1-1110.0!1 IPla 4 of 0 MASS This c•rt4 ('care 'Ay be transferred in ACCOt011AC• with FAA 21.4/. EFTA00011793 EFTA00011794 Form Approved Electronic Tracking Number OMB No. 21200720 0 MAJOR REPAIR AND ALTERATION itranwr u.SOccrartment or Tcansporodon (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only ROHR Aviation A/mnions:in INSTRUCTIONS: Pnnt or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.91 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not 10 exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Alrcraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration cemecate) Address (As shown on registration certificate) 2. Owner Flight Options .LLC ra mo ss city Richmond Heights slew OH zip 44143-1453 canny USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number El El AIRFRAME (As descnbed in Item I ahove) ❑ O POWERPLANT PROPELLER 0 ❑ Typo ❑ APPLIANCE 0 manitock_tor G. Conformity Statement A. Agency's Name and Address B. Kind of Agency name Nextant Aerospace O U.S. Certificated Mechanic O1Manufacturer AROMA O Foreign Certificated Mechanic C. Certificate No city Cleveland slaw. OH C Certificated Repair Station Zip 44143-1453 campy USA O Certificated Maintenance organization CRS # 25NR667B O. I certify that the repair and/or alteration made to the unit(s) identified in tern 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized Individ per 10 CFR Part 43 05/30/2013 App. B 0 7. Approval for Return to Service Pursuant to the authority given persons speofied below, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is El APPROVED El REJECTED FAA Flt standards Organization I Person Approved by Canadian Manufacturer Maintenance Department of Transport inspector BY Other Specify) FAA Designee X Repair Station Inspection Autftrization Certificate or Signature/Date of Authorized Individual Designation No. 05/30/2013 CRS # 25NR667B FAA Form 337 (10.06) EFTA00011795 EFTA00011796 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 05/30/2013 Nationality and Registration Mack Date Nextant Aerospace Completed STC tt ST02371LA Removed Pratt and Whitney JT15D-5 Series Engines . Installed the Williams International FJ44-3AP Engines with Full FADEC and Associated Systems in accordance with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011of later FAA Approved revisions. Installed Left Engine Part Number. 111000-202 Serial No. 252757 Installed Right Engine Part Number 111000-202 Serial No. 252758 ICA AFM Supplement was installed on Aircraft. Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted revisions are included in the Aircraft Maintenance Records. Carried out Engine Ground Runs and System OPS checks IAW Ground Test Plan 373-00-0024 Rev F. End ❑ Additional Sheets Are Attached FAA Form 337 (ro.os) EFTA00011797 EFTA00011798 }lidkit Alnico erAciericii Pepin.Intent of ZIrmispectrdinit - jliederid cAbintion i*ittriiriotration $upplemental Tuve Certifiaxte ACeenz4/, ST02371LA Yt, rfiriVcale'Akira Nextant Ados ace LLC Richmond Heights, Ohio 44143 /4 ) /Lair liar a. /4 Ow devrAfr alfriSearndastenal cre3 dowlakiw cerrelconait4J. erreArei reet9freheemorniter4 riecemitarthew rwatimervai tegnarl 25 * teen ..greverea47.4iw -94,144*."0. *Certification basis is set forth on TCDS A l6SW and continuation sheets 3 and 4. ifgviriteaordra' *to WreiViartrivi‘rcero.• A 1GSW Hawker Beechcraft 400A Nvo*afeiis ifira Our Meir Replacement of Pratt &, Whitney 5D-5 series engine with Williams International FJ44-3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems, in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001, Revision 1R dated 8/22/2011, or later FAA approved revisions and FAA Approved Airplane Flight Manual Supplement, NXTI-AFMS, Rev IR, dated September 15, 2011 or later FAA approved revisions. Nextant Aerospace, LLC Instructions for Continued Airworthiness document NXT1-ICA, Revision IR, or later FAA accepted revisions must be provided with this STC. ..Weetheaivto rriorteewrieliw.i: The installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above-noted airplane models only. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. (CONTINUED on page 3) gai ereVetakt ecoriall.irwrevar ata ele.it;aA onewoorararre-evnertia At Oat/the JItneerteleredJaOrneedretwevie.v.a. knieririzaiva Abe Ai careciari evireteddevel. ./Mteire:OrrIcv, eyeafei Rielerrat6thierleiva ..egedieritealredicva fkia,/eryacre4;v:. March 24, 2008 ame/kwavien.. September 27, 2011 14.raterneleil.- &itroit Manager, Propulsion Branch Los Angeles Aircraft Certification Office (Time) Any alteration of this atiffrate it panisfiable by a fine of no: excetelloyi $1,004 or iiniultonment not taccediv 3 years, or Gotta YM rem 0110.2(10.4i) Pegs r of 4 Vic certificate nay de trainfeired moat:met n1(0)1(.4.21.47 EFTA00011799 EFTA00011800 INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Regional Office of the transfer of this Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him. TRANSFER ENDORSEMENT Transfer the ownership of the Supplemental Type Certificate Number to Paine of transferee) Oteritrss of transfer) tecum(vr an!itrrei) (ail Sr•14 daZip rile) from (name ofgrantor)(Pr(nt or we), (fiffiress ofgrantot) OrlimbentnIscrert) tic% Seal andZip roe) Extent of Authority (if licensing agreement): Date of Transfer: Signature of grantor an MO Pagc2 or 4 EFTA00011801 EFTA00011802 puttee Plates WI Anterior .Bcpairtnient of Zikantepartation - lfebernt Abintiou Pt bmirtistrtttiorr $upplartentai Zgin Tertifirate (ffinutinuntion $11291) Afeeenie/< ST02371LA -2reintrakiinr analifoncerdeanix (conitnan(1 • Nextant Aerospace, LLC, "Installation of Rockwell Collins Pro Line 21," Amended STC ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this alteration. • The new Vince and Vmcg values arc 94 KIAS and 93 K1AS respectively. • The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature of 77°F. • Approved engine fuels are: Grade Specification Jet A ASTM-D 1655 Jet A-1 ASTM-D 1655 Wee49catkew,....fiani The certification basis for this modification is as follows: The original certification basis for the Hawker Beecheraft Model 400A airplanes identified on TCDS AI6SW, Revision 26, dated March 17, 2010: Part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by 25.1 through 25.40, plus §§ 25.1335, 25.135I(d), 25.1353(c)(5), and 25.1447 of Amendment 25.41; §§ 25.29, 25.255, and 25.1353(0(6) of Amendment 25.42; and §§ 25.361(b) and 25.132900 of Amendment 25.46. Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36-17; SPAR 27 effective February 1, 1974, as amended by 27-I through 27-5: and Special Conditions No. 25-ANM-32 dated February 22, 1990 (High Altitude Operation at 45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy Protection). (See NOTE 12) Equivalent Safety Items: (I) Out.of-trim characteristics § 25.255 (2) Pilot compartment view § 25.773(b)(2) (3) Passenger compartment door § 25.813(c) (4) Emergency exit marking §§25.811(d)(1) and 25.811(d)(2) Application for amended Type Certificate dated February 18, 1988. Regulation at a later amendments for components and areas affected by the change (Ref. FAA approved Compliance Check List): Subpart A - General: 25.2(25.99) Subpart 11— Flight: 25.207(25-121), 25.255(25.42) Subpart C Structure: 25.571 (25-96) pay dimwit of the attfwan is pialisha64 by a fine of not cowling $1,000, or neprinament not aim% 3 pan, or boa PM Pons 0310.2110-6I) sego ) of 4 ?hit certificate nay ds traurfirraf in anonfann with TRIL21.47. EFTA00011803 EFTA00011804 palish Stoles 01A tunics Peparfutent of Zrattoporintion - jliehertti cAbintiott Jtlbritittistrrttirm $upplartental Zglat Tertifiatte (clantinuation $beet) ./rande.# ST02371LA WeriaAniaimegade:s iconloaraesed Subpart D —Design and Construction: 25.603(25-46), 25.605(25-46), 25.611(25-123), 25.613(25-112), 25.625(25-72), 25.832(25-72), 25.863(25-46), 25.869(25.123), Subpart E — Powernlant: 25.901(25.46), 25.903(25-100), 25.951(25-73), 25.961(25-57), 25.981(25-125), 25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25.42), 25.1045(25-57), 25.1091(25400), 25.1093(25-72, 25.1103(25.46), 25.1141(25-115), 25.1143(25-57), 25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57), 25.1195(25.46), 25.1203(25-123), 25.1207(25.46). Subpart F —Equipment: 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123), 25.1316(25-80), 25.1317(25-122), 25.1321(25-41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123), 25.1357(25-123), 25.1381(25-72), 25.1431(25-113), 25.1438(25-41), Subpart G— Operating Limitations and Information: 25.1501(25.42), 25.1521(25-72), 25.1527(25- 105), 25.1529(25-54), 25.1543(25-72), 25.1549(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-72), 25.1583(25-105). Subpart H- Electrical Wiring interconnection Systems (EWIS): 25.1701(25-123), 25.1703(25-123), 25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25423), 25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25423), 25.1725(25-123), 25.1727(25-123), 25.1729(25-123), 25.1731(25-123), 25.1733(25-123). 14 CFR Part 34 (34-3): 34.11 14 CFR Part 36 (36-28): 36.1-36.7, 36.101--36105, 36.1501, 36.1581. The following Nextant Aerospace Continued Airworthiness Supplements are applicable to airplanes modified in accordance with this STC: • Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved revisions. • EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXTI-EA-007 Rcv A dated 8/24/11 or later FAA approved revisions. -END- Any iteration of this artyieate is punishable by a fine of not evettfing ii,00cs or implisonntent not mere% 3 years, or both PM Pons 1110-2(10-40 Pogo 4 at 4 This syndicate may be transtetriin acrodance nib TAR,21.47. EFTA00011805 EFTA00011806 Font amens Electronic Tracking Number 0m8 No 2t204:020 0 MAJOR REPAIR AND ALTERATION it nor2037 u S oessani or (Airframe, Powerplant,Propeller, or Appliance) Tissoananon For FAA Um Only Paws minion ministration INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43 9.1 (or subsequent revision thereof) for instructions and dispositio of this form This report is required by law (49 V.S.C. 1421). Failure to report can result in a civil penalty not to exceed 51.000 for each such 'elation (Section 901 Federal Aviation Ad 1958) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Senes Raytheon Aircraft Company 400A Name (As ShOwn on tegistrabOn certificate) Address (As shown on registration certificate) 2. Owner Flight Options .LLC Metes, City Richmond Heinfits swe.OH zip 44143-1453 coulee USA 3. For FAA Use Only 4. Type S. Unit Identification Repair PAeratiOn Unit Make Mood Serial Number AIRFRAME (As described in Item I above) El El • O POWERPLANT ID O PROPELLER Typo O O APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B K no of Agency Nara Nextant Aerospace 0 U.S. Certificated Mechanic 0 Manufacturer moms 0 Foreign Certificated Mechanic C. Certificate No. cry Cleveland slate OH El Certificated Repair Station zo 44143-1453 Country USA 0 Certificated Maintenance Organization CRS # 25NR667B D. I certify that Ihe repair and/or allerabon made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U S Federal Aviation Regalabons and that the information furnished herein is true and correct to the best of my knowledge - Extended range fuel Per 14 CFR Part 43 2/29/2013 App. B MI 7. Approval for Return t lett / Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is .. APPROVED El REJECTED FAA Flt Standards Organization i Person ApprOved by Canadian Manufacturer Maintenance Department of Transport Inspector BY Other (SPecif0 FAA Designee X Repair Station Inspection Authorization Certificate or Designation No. /29/2013 CRS # 25NR667B FAA Form 337 (teat) EFTA00011807 EFTA00011808 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed N493LX 12/29/2013 Nationality and Registration Math Date Installed the following In-Flight Entertainment System in accordance with STC # ST03960AT and in accordance with Nextant Aerospace Master Drawing List DB1002067. Revision F.05 Dated: October 9, 2013. Installed Bonner Cabin LED Lighting System without the Venue System in accordance with NX330-1304002. Rev B Dated October 17, 2013. Ref. drawing for parts list. ICA Requirements. Ref FAA Order 8100.17 Page 7-5 and 7-6 Use FM publications such as AC 43.13.1, Acceptable Methods, Techniques, and Practices—Aircraft Inspection and Repair. and AC 43.13-2, Acceptable Methods, Techniques, and Practices—Aircraft Alterations; part 43 appendix D; or other applicable aviation standards. Installed Iridium Sat Comm (Cockpit Phone only) and Broadband Internet System with Aircell Axxess II and ATG 4000 in Accordance with DB 1001013. Rev E ICA for Aircell System Ref to Nextant Aerospace Document No DB1105003. Rev A dated September 22 2011 or later FM Accepted Revisions The following manuals contain complete detailed maintenance instructions and should be consulted for all maintenance activities not covered within this ICA: Aircell Axxess II Installation Manual 012004 Revision E, dated March 2010 or later applicable revision Aircell ATG-4000 Installation Manual D13485 Revision B Dated November 2009 or later applicable revision Aircell Axxess II WLAN AFM Supplement DB1002072 Rev IR dated March 22 2012 for the has been Installed in the AFM Installed the Astronics DC-AC 115 VAC Power Supply in Accordance with DB1002067 Rev F.04 Dated 10/9/2013 This is Located under the Seat Divan ICA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No DB1108018 Rev IR Date 9/22/2011 or later FAA Accepted Revision. Aircraft Flight Supplement DB1109012 has been installed on the Aircraft See Current Weight and Balance Dated: December 29, 2013 End ❑ Additional Sheets Are Attached FAA Form 337 (io.os) EFTA00011809 • EFTA00011810 Vniteb 'take of ;America gleporiment of ligrattoportation geberal cMialion cabrninistration $upplementat Type Tertificate Actinetede4 ST03960AT .71;5 fernAvA' 44"a Nextant Aerospace LLC West Palm Beach, FL 33406 reehAm ten/ee rieenfe 4, Or /me eAlikes/9- dravethyyreetafe/ end at, etw'rerhiw4 Awe/erna>;v7J acyrise se4 VerseAtif"wen ineet zee felivideiVtinkl esyntinview/3 r/ !Arne 25 Vier Federal Aviation .92,1”42vawa. Sfironetrity4n1- • , ;fie KvOrrelo •AC0,6- AI 6SW ..41 60A Hawker Beechcraft Corporation Sea: 400A fiskle.s0/eisss el gs>ir . iiSlsises War.' Installation of Rockwell Collins Venue In-Flight Entertainment(1FE), Aircell Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (W LAN) Astronics 115VAC 60HZ Cabin Inverter, and Emteq LED Cabin Lighting System in accordance with Nextant Aerospace LLC, Master Drawing List DB1002067, Revision E, dated January 26, 2012, or later FAA approved revision. ,9ramArhiv., 4welfenaiv,J.• This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated, unless it is determine by the installer that the interrelationship between this change and any other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. ..We3 ovietrain twee'Or ay/Are/49 44/et avtii nt; etzyteretet.Ateeentteas 4. *Or/ foyhl Jitemfeeireet. Jeninena e n rime re re beziniiseekvs etr* hl reeete,:le estireifiVergy /4 .4 1,4,,,:viderv/re r//6 ....XsArset fleas/4w fate re/:waved: 0.4 July 28, 2012 -eget rAwerewee March 22, 2012 ewe sowitiveAv6.- Atlanta Aircraft Certification Office My sitoraclon of this corcilicsfe is ounissablo Dye lino of hoc osensitno 12,000, or Imprisonment not excee0ing J ye***, or moth. VAL fwm 8110-2(10-fel MGt I of 1 YMCAS This cora/leaf* se/ N csonstfrzoii In se,ezdan.• mach PAR 21.4.. EFTA00011811 EFTA00011812 VolItb *tato of America pepartnunt of transportation - Xeherni Pkbintion ptbministrntion $upptententnl Zype Certificate (Tantinuation $beet) tfriteregett ST03960AT When the Rockwell Collins Venue system is installed Airplane Flight Manual Supplement, DB1106015, Revision A, dated March 22, 2012, or later FAA approved revision, is required. When the Aircell Axxess II system is installed Airplane Flight Manual Supplement, DB1002072, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. When the Astronics Cabin Inverter system is installed Airplane Flight Manual Supplement, DB1109012, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. This system is intended to provide internet connection and email services to the airplane's cabin using portable electronic devices (PEDs). Any other intended function of this equipment will require a re- examination of the certification basis. When the Rockwell Collins Venue system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1002068, Rev IR, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Aircell Axxess II system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DBII05003, Rev A, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Astronics Cabin Inverter system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB I 108018, Rev IR, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Emteq LED Cabin Lighting system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1108019, Rev IR, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. Any alteration of this ooze ion* purdahs)) • by • flea at net trend nq 11,000, or ltprlsonwent not arcabffir4 l years, or both. MA it 1110-2-1(10-49) PAGE 2 or 3 PAGES This entificat• way b transforrect in •ccoraanc• with PAR 22.17. EFTA00011813 EFTA00011814 Alates of ,America peoartment of grzinsportation - geberat Ablation Administration $upplemental `Type Tertificate (Tantirtuation Sheet) A rtaidede ST03960AT enr/Veleedava The Certification Basis for this installation is per Type Certificate Data Sheet Al6SW original Certification Basis, Federal Aviation Regulation (FAR), Part 25 as amended by Amendment 25-1 through 25.40 plus FAR 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; FAR 25.29, FAR 25.255, and FAR 25.1353(e)(6) of Amendment 25-42; and FAR 25.361(b) and 25.1329(h) of Amendment 25-46. In addition the following specified rules amendment levels were used for this installation. 25.571 25.1353(aXc) 25.1357 25.1431 25.1529 [25.541 _ [25.123] [25-1231 [25-113] [25-541 (1Indicates amendmen level Any alt aaaaa on or this corellicett is punishable by • Tins of not enabling 53,000, Or laprisonnent not intending 1 years, or both. FAA EOM 0110-2-2(20-01 AWL 3 of 3 PAGES This certificate nay be transfersest in accordance with FAR 11.4r. EFTA00011815 MS EFTA00011816 ram Append Elect/oat Trackirg Number ore tie 21204020 0 MAJOR REPAIR AND ALTERATION 11/30,2t03 u s orsemieni al hasp:dam (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only F000.11 AARIOA AdwANtratlen INSTRUCTIONS: RIM of type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.9.1 (or subsequent revision thereof) for Instructions and disposition of this form. This report is required by law (40 U.S.C. 1424 Failure to report can result Mach& penalty not to exceed 61800 for each such violation (Section 901 Federal Aviation Act 1958) NationaRy and Registration Mark Serial No. N493LX RK244 I. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration cerfifiCate) Flight Options, LLC 2. Owner cityHichmOnd Heights sue:Ohio 4944143-1453 ciairoa.8 3. For FAA Use Only 4. Type 6. Unit IdeMlfic alien Repel/ Alteration Und Make Model Serial Number El el AIRFRAME (As describer:1ln ken l above) ii POWERPLANT 0 El PROPELLER 0 rye. O D APPLIANCE Nara...over 6. Conformity Statement A. Agency's Name and Address B. KIM of Agency Na Avi _ i n CI U.S. Certificated Mechanic 0 IManufacturer Aa&es 0 Foreign Certificated Mechanic C. Certificate No. cityCleveland swoOhio 0 Certificated Repair Station CRS#WC7R34OJ zo44135 courevOnited States CI Certificated Maintenance Organization D. I certify that the repak andiOI alteration made to the unit(s) Identified in item 5 above and described on the rover c or Mtn:laments hereto have been made In accordance with the requirements of Pen 43 of the U.S. Federal Aviation Regulations and that the information furnished heroin Is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 Date: December 30, 2013 App. 8 ill Service Pursuant to the authority given persons spooned below, the unit Idea tn item 6 W3S inspected In the manner presorted by the Administrator of the Federal Aviation Administration end is El APPROVED II REJECTED FM Fa Standards Organization I Person Approved by Canadian Manufacturer IAMMenance Department of Transport Inspector BY other moon FM Designee X Repair Station Inspection Authorization CerOlicate or SignauxerDate el Onlonolion No. Date: December 30 , 2013 CRSHWC7R346J FAA Form 337 node EFTA00011817 EFTA00011818 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft reCOM. An alteration must be compatible will, allprevious alterations to assure continued conlomety with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. identify with eircrak nationality and registration mark and dale work completed) N493LX 12/30/2013 Nationality and Registration Mark Dale ACCOMPLISHED INTERIOR REFURBISHMENT/MODIFICATION AND 3 PLACE DIVAN INSTALLATION THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN REFURBISHED: RepalMed, recovered control columns with Mane Bed( Leather Accordance with BeedVel 400A AMM 20-70.00-701. 25.0040-001 Removed and Replaced Glare shield and Eyebrow panel material with Matte Sack Leather In Accordance with Becch)et 400A AMM 20-60-00.201. Removed and Replaced Cockpit Sidewal malarial MU Mane Black Leather In Accordance with Beet:lel 400A AMM 20.80-00.201. Removed and replaced Pitc1Seal Pad Number TAWII00PM000I Serial Number 82. Foam and recovered with Garen Sheepskin Oak and Excel Cappucdno Leather. Removed and replaced Co-Pilot Seat Part Number TABH100CM00.01 Serial Number 248, Foam and recovered w.thCarrell Sheepskin Oak and Excell Cappuccino Leather. Removed and Replaced Loll Hand #4 Passenger Seal Pad Number 2524.014(-530A) Serial Number 990719.4 Foam and recovered with Townsend Leather (Heritage Brown) Removed and replaced Right Hand #5 Passenger Seal Part Number 2524.014(-530B) Serial Number 990426-7 Foam and recovered with Townsend Leatherpleriinge Brown) Removed arid Replaced Left Hand 03 Passenger Seal Pan Number 2524.014(5306)Sedal Number 03061845 Foam and recovered with Townsend Leather (Heritage Brown) Removed and replaced Right Hand S7 Passenger Seat Pan Number 2524-014(530A) Serial Number 030708.2 Foam and recovered with Townsend Leather (Heritage Brown) DIE FOLLOWING MANUALS AND APPROVED DATA HAVE OLEN UTILIZED FOR OASIS OF REFURBISHMENT. Skendla Flammability Test S254978 as approved by FM t)EIT Jane Mersa* (DERY 832780-CE) on FM form 8110-3 dated 4/23/2013 Flame Out Elam/1180'4y Test 4351 as approved by FM DER Herb Reed II (DERT-230293.CE) on FM Form 8110-3 dated 12/23/2013. Skandla Flammability Test Report IP 22081 Rev A as approved by FM DER and Faberslein( DERY-832780-CE) on FM Form 8110-3 dated 05/02/2013. Three Place Divan installation: Installed (3) ptace divan part Number 32.03913(MOVOT123.K02 S/N 003702 In Accordance Men Aviation Fabricators SIC/ STOI572W1 and Skandia Rammila test report 5254978 per Jane Bibeisleln FM DER (DERV-832780-CE) dated 4/23.2013 THE FOLLOWING INTERIOR ITEMS HAVE BEEN MODIFIED: UR Golly Assy, RM Galley May, Divan Amy. LM Galley Assy and install per Deka G drawing DGD-GW1.101 Rev 0, DGD-CAOI -101 E0 E- t. LfH Galley Install DGO-CA01-501 Rev EO A-1. DGOCA0t-501 Rev IR as approved on FAA formal 10-3 pm FAA DER Donald Geese* (DERT-750135-SW) dated March 25 2013. RA4 Galley Assy and Install per Della G drawings DGD-CA02-101 Rev B. OGLICA02-501 Rev IR as approved on FM /OM 8110-3 by FM DER Donald Geese* (DERT-750135-SW) dated March 25. 2013 Divan Assy per Delta G drawings OCID-CA09-101 Rev C and DGD-CA09-101 E0 0-1 as approved on FM form 8110.3 per FM DER Donald Giuospk (DERT 750135-SW) dated March 25. 2013, Month Kit Sfdewa0 esay &arena 2553-0038 RCN C. Bonner sldeledge any *away 25324)032 Rev C Bonner Ka Foldout Table assy drawings 2553.0041 Rev C and 2553-0040 Rev EL Bonner XTI finer Kit Ina drawing 2553-0037 Rev C as approved on FAA form 8110.3 per Stephen Formes DERT-230238-CE dated Dec 20, 2013. INSTRUCTIONS FOR CONTINUEDAIRWORTHINESS. THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE. THERE ARE NO ADDITIONAL INSPECTIONS REQUIRED. CONTINUE TO INSPECT JAW MANUFACTURERS MBA, SRIL OR CMM AS APPLICABLE AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER -END--- O Additional Sheets Are Attached FAA Form 337 (1008) EFTA00011819 EFTA00011820 U.S. DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION Dec 26, 2013 STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL TYPE (Airplane. Radio. Helicopter, NAME O APPLICANT Beeehcraft Corporation 400A eta) AIRPLANE NEXTANT Aerospace Cleveland OH. LIST OF DATA IDENTIFICAITON TITLE REPORT: RKG3282 BEECHJET 400A INTERIOR STRUCTURAL SUBSTANTIATION Rev. IR, 8-28-2013 2553-0037 BEECHJET 400A Rev C, dated 8-30-2013 XTI LINER KIT INSTL. Beechjet 400A, Aircraft Serial No. RK-244 Certification Bases for this aircraft modification is per Type Certificate Number A I GSW Revision 28 dated April 12,2013 PURPOSE OF DATA DESCRIBE AND SHOW VERIFICATIONS FOR NEXTANT INTERIOR INSTALLATION ON BEECHJET 400A, AIRCRAFT SERIAL NO. RK-244 APPLICABLE REQUIREMENTS ( List spec* sections) 14 CFR Part 25 §.301, 303, 305, 307a), 365, 561, 571,601, 603, 605, 609, 613 CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Pan 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I 01413 Therefore O Recommend approval of these data 0 Approve these data SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) DERT-230238-CE STRUCTURES AND DAMAGE TOLERANCE CPO 961.613 FAA Form 8110-3 OO0) SUPERSEDES PREVIOUS EDITOR EFTA00011821 EFTA00011822 FamAprons:1 Electronic Tracking Number OMB No. 2120-0020 le MAJOR REPAIR AND ALTERATION 11/30/8:07 NS Droorintro of Trampoutto (Airframe, Powerplant,Propeller, or Appliance) For FAA Use Only Fees Aviation Administraton INSTRUCTIONS: Prialor type all entries. See FAR 43.9. FAR 43 Appendix 8. and AC 43.9-1 (or subsequent revision (recto') for instructions and disposition of this form. This report is required Dy taw (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 91,000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Ma* Serial No. RK 244 N493LX 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner Flight Options .LLC 00°t°'° coy Richmond Heights sets OH re 44143-145 cater USA 3. For FAA Use Only 4. Type 5. U it Identification Repair Minden Unit Make Model Serial Number I gii AIRFRAME (As described in Item 1 above) POVVERPIANT o 0 PROPELLER ;pit APPLIANCE n ii MonufrOuree 6. Conformity Statement A. Agencys Name and Address B. Knd of Agency Norte Nextant Aerospace O U.S. Certificated Mechanic Cl /Manufacturer Andrea O Foreign Certificated Mechanic C. Certificate No. City Cleveland see. OH SI Certificated Repair Station Ze 44143-1453 country USA O Certificated Maintenance Organization CRS # 25NR667B D. I certify that the repair anclior alteration made to the unit(s) identi ed in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 10 CFR Part 43 12/29/2013 App. B MI prove or'eum o / Pursuant to the authority given persons specified below, the unit idenUSed in dem 5 was inspected in the manner presort ed by the Administrator of the Federal Aviation Administration and is rj APPROVED ❑ REJECTED FAA Flt Standards I Person Approved by Canadian Manufacturer Maintenance Or oepanment of Transposed Inspector BY Other (Specify) FAA Designee X Repair Station Inspection Authorization Certificate or Designation No. 2129/2013 CRS # 25NR667B FAA Form 337 (10.06) EFTA00011823 EFTA00011824 NOTICE Weight and balance or operating limitation changes shall be enteredin the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Installed the following In-Flight Entertainment System in accordance with STC # ST03960AT and in accordance with Nextant Aerospace Master Drawing List D81002067. Revision F.05 Dated: October 9, 2013. Installed Bonner Cabin LED Lighting System without the Venue System in accordance with NX330-1304002. Rev B Dated October 17, 2013. Ref. drawing for parts list. ICA Requirements. Ref FM Order 8100.17 Page 7-5 and 7-6 Use FM publications such as AC 43.13-1, Acceptable Methods, Techniques, and Practices—Aircraft Inspection and Repair, and AC 43.13-2, Acceptable Methods, Techniques, and Practices—Aircraft Alterations; part 43 appendix 0; or other applicable aviation standards. Installed Iridium Sat Comm (Cockpit Phone only) and Broadband Internet System with Aircell Axxess II and ATG 4000 in Accordance with DB 1001013. Rev E ICA for Aircell System Ref to Nextant Aerospace Document No DB1105003. Rev A dated September 22 2011 or later FM Accepted Revisions The following manuals contain complete detailed maintenance instructions and should be consulted for all maintenance activities not covered within this ICA: Aircell Axxess It Installation Manual D12004 Revision E, dated March 2010 or later applicable revision Aircell ATG-4000 Installation Manual D13485 Revision B Dated November 2009 or later applicable revision Aircell Axxess II WLAN AFM Supplement D61002072 Rev IR dated March 22 2012 for the has been Installed in the AFM Installed the Astronics DC-AC 115 VAC Power Supply in Accordance with DB1002067 Rev F.04 Dated 10/9/2013 This is Located under the Seat Divan ICA for Astronics 115 VAC Cabin Inverter Ref to Nextant Aerospace Report No DB1108018 Rev IR Date 9/22/2011 or later FM Accepted Revision. Aircraft Flight Supplement DB1109012 has been installed on the Aircraft See Current Weight and Balance Dated: December 29, 2013 End ❑ Additional Sheets Are Attached FAA Form 337 (10-06) EFTA00011825 EFTA00011826 Vniteb *oho of L•ttrica !epartment of Zranzportation geberal crtbiation Abministratian $uppietrtental Mgpe Certificate Afarland ST03960AT 0 .14) tree/nia• Ammo/4 Nextant Aerospace LLC 3800 Southern Blvd. West Palm Beach, FL 33406 ere/Au ea* nefeente la dr fir s eieureArzeanvivivertnee/ Arhi /.4^ elnerAtteeveht eseVite arrAr rlJ 4fierVetareprea meet* hie tretoevareaJ erree:rementi ri e 044'25 Ver Federal Aviation ifoyereekaMJ. Cseritenreivat A6:Matee t 6sw SAC -* Hawker Beechcraft Corporation sea. 400A cZetierffr/Ova r/Fp://r Fyn c ellar Installation ofRockwell Collins Venue In-Flight Entertainment(IFE), AffCelI Axxess Cabin II Iridium Phone and High Speed Internet System with Wireless Local Area Network (WLAN) Astronics I I 5VAC 60HZ Cabin InVerter, and Emteq LED Cabin Lighting System in accordance with Nextant Aerospace LLC, Master Drawing List DB1002067, Revision E, dated January 26, 2012, or later FAA approved revision. 2::rnzahma nwawaivr.i.• This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated, unless it is determine by the installer that the interrelationship between this change and any other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. terhAYEAT envne.g. ,sewterfaye reitik erAhie evrerreveAt4entzereas a.. *Irv/ tea/e, Jetterseiregi Jatonexted AN:rine/re to 4vrtifiver/eivA o&* rJ et4reelm eV/Ma:an• ery de r/66. .rnOnse,/tedrireivs ,./UneiltifeakivA. Over etwAve44-4. July 28, 2012 Ode erAsJoreott.- Ode rAuftern re March 22, 2012 0404* at/tenni- Manager Atlanta Aircraft Certification Office Any Alcoration of tbla CerellIcare Is poninablt by a Ilo et net exceeding 13,000. or imprisonment nee stcnOlzq J )sirs, or Sorb. TAS. Iran MG— 1 of 2 PAGta This costa:Scare sky 000no ferrod In acCergen,e wIcA IAR 14.4,. EFTA00011827 EFTA00011828 3ilnilebStafeo of America . !epartment of granepartation - Ofeberal Abiatiart Abministration Supplemental. 'Tut Tertifirate ( cintinuation *feet) A1/402,60ST03960AT When the Rockwell Collins Venue system is installed Airplane Flight Manual Supplement, DB1106015, Revision A, dated March 22, 2012, or later FAA approved revision, is required. When the A ircell Axxess II system is installed Airplane Flight Manual Supplement, DB1002072, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. When the Astronics Cabin Inverter system is installed Airplane Flight Manual Supplement, DB1109012, Revision IR, dated March 22, 2012, or later FAA approved revision, is required. This system is intended to provide Internet connection and email services to the airplane's cabin using portable electronic devices (PEDs). Any other intended function of this equipment will require a re- examination of the certification basis. When the Rockwell Collins Venue system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1002068, Rev III, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Aircell Axxess II system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1105003, Rev A, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Astronics Cabin Inverter system is installed Instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1108018, Rev lit, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. When the Emteq LED Cabin Lighting system is installed instructions for Continued Airworthiness (ICA), Nextant Aerospace Document No. DB1108019, Rev iR, dated September 22, 2011, or later FAA accepted revisions must be made available to the operator at the time of installation. My alteration of this coiCitiCOM is ponishible by a rine of not •XMMISM r1.000. or SePrisorrtent not exceeding l press, or both. tilt row 1110-2-1110-0i Mt 2 of 3 outs This certificatebey be transferred In ICCOrdlnef rich FM 2l.47. EFTA00011829 EFTA00011830 giliien Atated of ?merlon pepartment of ' :transpartation - Offeberal cAbiation cataninistration Supplemental Type Certificate (Continuation Ant) A/14022,4 4 ST03960AT % ,4:1 oteleiva .954re,i4.• The Certification Basis for this installation is per Type Certificate Data Sheet Al 6SW original Certification Basis, Federal Aviation Regulation (FAR), Part 25 as amended by Amendment 25-1 through 25-40 plus FAR 25.1335, 25.1351(d), 25.1353(c)(5), and 25.1447 of Amendment 25-41; FAR. 25.29, FAR 25.255, and FAR 25.1353(c)(6) of Amendment 2542; and FAR 25.361(b) and 25.1329(h) of Amendment 25-46. In addition the following specified rules amendment levels were used for this installation. 25.571 25.1353(We) 25.1357 25.1431 25.1529 125-541 [25-1231 [25-1231 [25-1131 125.541 [..] Indicates amendmcn level END— Any alteration of this certificate is punishable by a fins of not exceeding 41.000, or Itearlsonnant not exceeding A years, or both. FAA Fon. 0110-Z-1110-6U ME 3 of 3 PAGES This Certificate may ae transferred in teceordence with FAR 22.17. EFTA00011831 EFTA00011832 Nextant Aeros ace LLC Report No: DB1002067 Revision F.05 est Palm Beach FL 33406 Master Drawing List Document Number: DB1002067 Revision: F.0510/1812013 In-Flight Entertainment HAWKER BEECHCRAFT 400A Aircraft FAA STC ST03960AT Approved By Date 1-4-2013 Page 1 of 7 EFTA00011833 EFTA00011834 O Fttri ',waved Etecironic Tracking Number OMB No 2120.0020 MAJOR REPAIR AND ALTERATION 11/1C/2007 u.5 Onsarymor or (Airframe, Powerplant, Propeller, or Appliance) rrompxv,43n For FAA Use Only Fedni Aviation Adralniftrittlen INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.91 (or subsequent revision thereof) (Or instructions and disposition of this form. This report is required by law (49 U.S C. 1421). Failure to report can result in a civil penally not to exceed 51,000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Ser,es Raytheon Aircraft Company 400A Name (As shown on registrabon ceraate) Address (As shown on registration centhcate) 2. owner Flight Options .LLC Add"" c ty Richmond Heigbts slaw. OH 7.,9 44143-1453 county USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration lint Make Model Serial Number 0 :I AIRFRAME . (As descnbed in (tern 1above) ❑ O POWERPLANT Ell ❑ PROPELLER Type APPLIANCE • ID manatee( 6. Conformity Statement A. Agency's Name and Address 8 Kind of Agency tin Nextant Aerospace O U.S. certificated Mechanic O Manufacturer Address O Foreign Certificated Mechanic C. Cendicate No. Coy Cleveland sum OH 0 Certificated Repair Station zip 44143-1453 duality USA O Certificated Maintenance Organization CRS # 25NR6678 0. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 or the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best o(m knowled•0 Extended range fuel per 14 CFR Pan 43 APP. B 1:3 12/29/2013 7. Approval for Return to rvtce Pursuant to the authOnly given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is El APPROVED ❑ REJECTED FAA FR Standards Organization I Person Approved by Canadian Manufacturer Maintenance Department of TranSperl Inspector BY Otner (Specify) FAA Designee X Repair Station Inspection Authorization „iv Certificate or Designation No 12129/2013 CRS # 25NR6678 FAA Form 337 (10-06) EFTA00011835 EFTA00011836 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Upper Aft Baggage Panel od Modified Baggage Ceiling Panel to Accommodate the Engine FADEC wire harness. 1. Fabricated two panel pieces, N251103-001 and N251103.002. 2. Installed N251103-001 to existing baggage compartment structure 128.440095.1 using two screws and install N251103-002 as shown with a trim to fit honeycomb piece fabricated from interiors using potted inserts. 3. Attached honeycomb baggage panel to N251103-001 in upper aft baggage area using three 4055-21 Camloc quarter- turn fasteners and 214.16D receptacles. Secured N251203-002 to existing upper aft baggage panel with two Camloc 40S5-21 quarter - turn fasteners and 214-16D receptacles. See attached FAA Form 8110-3 Signed by DERT-410115-CE on February 12, 2013 using Nextant Aerospace Engineering Order EO 029. Rev E Dated February 8. 2013 ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures for this Area End ❑ Additional Sheets Are Attached FAA Form 337 (10.06) EFTA00011837 EFTA00011838 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION February 12, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2 MAKE 3. MODEL NO. 4. TYPE (Aircraft Engine. Propeller, etc ) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Richmond Heights, Ohio LIST OF DATA 8 IDENTIFICATION 7 TITLE EO 029 Upper Aft Baggage Panel Mod. Rev. E February 8, 2013 ----- --------------------------------- END------------ ------------------ Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements." 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. e. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List SpeCiat sections) CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23), 25.307(a)[25-23], 25.562(c)[25-23), 25.601[25.00], 25.603(a)(b)(c)[25-38), 25.605(a)[25-00), 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)(25-00), 25.619[25-23], 25.625(a)(b)(c)[25-23), and 25.789[25-32]. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183. data listed above and on attached sheets numbered NIA_ have been examined In accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. ❑ Recommend approval of these data I (We) Therefore a Approve these data in DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION FsIe Number. H13107-O6 Page 1of 1 EFTA00011839 EFTA00011840 Form Apprcacd Electronic Tracking Number OMB no 2120-0O20 MAJOR REPAIR AND ALTERATION limoacor U.S Onedrrentol (Airframe, Powerplant,Propeller, or Appliance) Transponason For FAA Use Only Federal Aviation darndinrstion INSTRUCTIONS: Pont or type an entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a cave penalty not to exceed 61,000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Regstration Mark Serial No. RK 244 N493LX 1. Aircraft Series Make Model Raytheon Aircraft Company 400A Name (As shown on registration cerbticate) Address (As shown on r ;strewn cerbtkate 2. Owner Flight Options .LLC Armen car Richmond Heieht§ State OH to 94143-1453 county OA 3. For FAA Use Only 4. Type S. Unit Identification Repair Alteration Unit Make Model Serial Number ❑ 0 AIRFRAME (As described in item I above) O POWERPLANT El ❑ O PROPELLER Typo APPLIANCE ❑ 0 Mandacttser 6. Conformity Statement A. Agency's Name and Address B Kind of Agency Name Nextant Aerospace El U.S. Certificated Mechanic a Manufacturer Address Cl Foreign Certificated MechaniC C. Certificate No. City Cleveland Suite. OH 0 Certificated Repair Station zp 44143-1453 county USA ID Certificated Maintenance Organization CRS # 25NR667B D. I Certify that the repair andror alteration made to the und(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pad 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 0 12/29/2013 APP. CI 7. Approval for Return to S ice Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescnbed by the Administrator of the Federal Aviation Administration and is ii.2 APPROVED 0 REJECTED FAA Flt Standards I Person Approved by Canadian Manufacturer Maintenance Organization Department of Transport inspector BY Other (Specify) FM Designee X Repair Station Inspection Authorization • Certificate or Designation NO. 12/29/2013 CRS # 25NR6678 FAA Form 337 (1ODO) EFTA00011841 EFTA00011842 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and dale work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Installed New Pitot Probes in accordance with STC ST10159SC. Nextant Aerospace Master Drawing List Document 373-00.0001Rev CC EO24-11 Removed Pitot Probes Part Number PH1100-MU-R-1 Removed Pitot Probes Part Number PH1100-MU-L-1 Installed Pitot Probes Part Number PH1100-MUR-EN Serial Number 1975803 Installed Pitot Probe Part Number PH1100-MUL-EN Serial Number 1728401 Leak Check carried out IAW Beechcraft Aircraft Maintenance Manual Chapter 34-12.00-201. ICA Continue with Normal Hawker Beech Maintenance Practices for this Area End ❑ Additional Sheets Are Attached FAA Form 337 pace) EFTA00011843 EFTA00011844 Form /owned Electronic Tracking Number 06,18 N. 2i204020 0 MAJOR REPAIR AND ALTERATION ii3Or2C07 v s owinnint ot (Air(rame, Powerplant, Propeller, or Appliance) Transatmen For FAA Use Only Federal Aviation Administration INSTRUCTIONS Print or type all entries. See FAR 43 9, FAR 43 Appendix B. and AC 43.9.1 (or subsequ nt revision there* fOr InStruetiOnS and disposition of this form. This report is required by law (49 U.S.C. 1421) Failure to report can result in a civil penally not O exceed $1,000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX I. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner AdCMCS2 Flight Options .LLC City Richmond Heights sta. OH zc 44143-1453 comity Na 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Senal Number ili ❑ AIRFRAME (As desciibed in item 1above) O POWERPLANT 0 . O PROPELLER Type ❑ O APPLIANCE Man&Dela, 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name Nextant Aerospace ID U.S. Certificated Mechanic 0 I Manufacturer Address 0 Foreign Certificated Mechanic C. Certificate No. City Cleveland sup.. OH 0 Certificated Repair Station zip 44143-1453 Cutory USA El Ceti/leafed Maintenance Organization CRS # 25NR6676 O. I certify that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the 'Over e or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and trat the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 12/29/2013 App. B 0 7. Approval for Return t 'ervice Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescn bed by the Administrator of the Federal Aviation Administration and is 0 APPROVED 0 REJECTED FAA Flt Standards Organization I Person Approved by Canadian Manufacturer Maintenance Department of Transport Inspector BY Other (Specify) FM Designee X Repair Station Inspection Authorization Certificate or Design lion No. 12129/2013 CRS # 25NR6676 FAA Form 337 (10.06) EFTA00011845 EFTA00011846 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and dale work completed) N493LX 12/29/2013 Nationality and Registration Mark Date Provisions for 19107 in Cockpit Sidewall at FS122.735 Added Mount provisions for J9107 in bracket assy. 45A88588-3 at Flight Station 122.735 provided in Structure Repair Manual Document 53-20.05-001. Use receptacle MS3470W18. See attached FAA Form 8110-3 Signed By DERT-410115-CE Dated December 28, 2012 using Nextant Aerospace Engineering Order 115-12 Rev C, Dated November 27, 2012 for details. ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End ❑ Additional Sheets Are Attached FAA Form 337 (to-067 EFTA00011847 EFTA00011848 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION December 28, 2012 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft. Engine, Propeller, etc.) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Richmond Heights, Ohio LIST OF DATA 0 IDENTIFICATION 7 DILE EO 115-12 Mount Provisions for J9107. Rev. C November 27, 2012 --------------- -------- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed ' below as "Applicable Requirements." 2) This form constitutes FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. s. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25-23), 25.305(a)(b)(c)[25-23), 25.307(a)125-231, 25.601[25.00), 25.603(a)(b)(c)[25-38], 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25- 00), 25.619(25-23), and 25.625(a)(b)(c)[25-23]. 10. CERTIFICATION - Under authority vested by drectica of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Pad 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and (cord to comply with applicable requirements of the Airworthiness Standards Listed. 0 Recommend approval of these data . .. I (we) Therefore El ApprOvatheSe data it. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVEIS) 12. DESIGNATION NUMBERS(S) 13. CLASSiFICATiONIS) DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number. H12740.03 Page 101 EFTA00011849 EFTA00011850 Form APPrOvatl Elect(WIC Tracking Number OMB No. 212043020 0 MAJOR REPAIR AND ALTERATION 11nolcor u s ceprvurenter Tiensevuoce (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Fodonl Aviation Anniniornion INSTRUCTIONS: Print or lype all entries. See FAR 43.9, FAR 43 Appendix 8, and AC 43 9.1 (or subsequent revision thereof) for instructions and disposition of this loan. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 31000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on re istration certificate 2. Owner Flight Options .LLC Addf05f City Richmond Heights site. OH zp 44143-1453 Cony USA 3. For FAA Use Only 4. Type 6. Unit Identification Repair Alteration Unit Make Model Serial Number 0 0 AIRFRAME (As described in pem 1above) O POWERPLANT li Ill PROPELLER 0 Typt El O APPLIANCE Manigactortv 6. Conformity Statement A Agency's Name and Address B. K nd of Agency wens Nextant Aerospace 0 U.S. Certificated Mechanic a IManufacturer Address 0 Foreign Certificated Mechanic C. Cenificate No. Cali Cleveland sin. OH 0 Certificated Repair Station zip 44143-1453 cairn USA 0 Certificated Maintenance Organization CRS # 25NR667B D. I certify that the repair and/or alteration made to the wigs) identified in item 5 above and described on Ihe reverse or attachments hereto have been made in accordance vith the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 App. 8 ❑ 12/29/2013 Pursuant to the authority given persons pecifed below, the unit identified in item 5 was inspected In the manner prescribed by the Administrator of the Federal Aviation Administration and Is CI. APPROVED ❑ REJECTED FAA Flt Standards I Person Approved by Canadian Manufacturer Maintenance Organization Department of Transport Inspector BY Oder (Specify) FAA Designee X Repair Station Inspection Authorization Certificate or Designation No. 12/29/2013 CRS # 25NR6676 FAA Form 337 (10.06) EFTA00011851 EFTA00011852 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. lden ify with aircraft nationality and registration ma* and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Title: Ice Detector Master Caution / Master Warning Light on Constantly Re-Installed the previously removed components ( Ref S/B 30-2600, Rev 2) 1.) Isolation Relay 1(255 P/N: 50-380048-1 2.) Diode CR654, P/N: 132408-22 3.) Ground stud GS151A P/N: M535206-246 (Stud may be marked GS152) As shown in chapter 30-01-01-01 of AMM. 4.) Wire number corrections on wiring diagram 30-01-01-01 Page 1 correct drawing errors on original drawing. Inspect, verify and correct wiring per EO corrections on EO page 2 See attached FAA Form 8110-3 signed by Daniel Buzz DERT-230019-CE. Dated 8/13/2012 using Nextant Aerospace Engineering Order EO 0130 Rev D. Dated 7/18/2012 ICA Weight and Balance Changes are Negligible Continue to Use Existing Beechjet 400/400A Maintenance Manuals Inspection Procedure for this Area END ❑ Additional Sheets Are Attached FAA Form 337 (r0-06) EFTA00011853 I EFTA00011854 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION 8.13.2012 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS . AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MOOEL NO. 4. TYPE (Airplane. Radio. Heecopter. S. NAME OF APPLICANT — liwker Eleechcraft 400A etc) Nextant Aerospace LLC S/N RK-244 Only Airplane LIST OF DATA B. IDENTIFICATION 7. TITLE Nextant Aerospace Engineering Order Document 130-12 Ice Detector MCiVIW Light On Constantly dated 7-18-12 Rev. D ------------- ------------ ......________ ----- ----- This approval is for the electrical systems aspects only. B. PURPOSE OF DATA Support major alteration to aIre aft Hawker Eleechcraft 400A RK-244 Only. 9. APPLICABLE REQUIREMENTS (flu SPeriCC stations) 14 CFR 25.1301(a) (Dire] Note: Comphance has been found to the amendment levels indicated on Hawker Beechczaft TCOS Revision 26 Part 25 Amendment 25.1 through 25-40 to the above applicable requirements. 10. CERTIFICATION - Linder aulh why vested by direction of Ilia Administrator and in accordance vMhconditions and limitations of appointment under 14 CFR Pat1183 of the Federal Aviation Regulations. data listed above and on attached sheets numbered &a have bawl examined in accordance with established procedures and round to comply with applicable requirements of the Airworthiness Standards listed. I (We) Therefore approve these date. . It. SIUNATUR 4GNATE E I E RI REPRESENTATNE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIRCATILMIS) CERT-230019-CE Systems and Equipment ..'AA Form 81104 (03710) SUPERSEDES PREVIOUS EDITION GPO 901.813 EFTA00011855 EFTA00011856 Form Approved Electronic Tracking Number ORS No. N20-0020 MAJOR REPAIR AND ALTERATION timOr2tW u.S oreartivent or TIIIMPC41•11}1 (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Federal Aviation reaveritration INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition Of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not 10 exceed 51.000 for eaCh such icilabon (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX I. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on regishation oendicafe) Address (As shown on registration certificate) 2. owner Flight Options .LLC A6Sress City Richmond Heiaht state. OH zip 44143-1453 country USA 3. For FAA Use Only 4. Typo 5. Unit Identification Repair Mention Unit Make Model Serial Number h.e. ❑ AIRFRAME (As descnbed in (ern t above) ❑ O POWERPLANT 0 O PROPELLER Typo APPLIANCE 0 . Man./acts,: G. Conformity Stat moat A. Agency's Name and Address B. Kind of Agency Nanie Nextant Aerospace O U.S. Certificated Mechanic 0 Manufacturer Meese O Foreign Certificated Mechanic C. Certificate No. city Cleveland State OH ISI Certificated Repair Station zo 44143-1453 Courtry USA CI Certificated Maintenance Organization CRS # 25NR6678 D. I certify that the repair anchor alteration made to the unit(s) Identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 App. II 0 12/29/2013 prove or tum l': crir ce Pursuant to the authority given persons specified below, the unit Identified in item 5 was inspected in the manner prescribed by the Admi ist,ator of the Federal Aviation Administration and is 0 APPROVED 0 REJECTED FM Fit Standards I Person Approved by Canadian Manufacturer Maintenance Organization Department of Transport Inspector BY Other Specify) FM Designee X Repair Station inspection Authorize% on Certificate or Designation No. 12/29/2013 CRS # 25NR667B FAA Form 337 00-00 EFTA00011857 EFTA00011858 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Antenna Repair Patch After removing the forward lower "L" Band Antenna, Instead of removing the Antenna doubler and filling the connector hole with a coin patch and installing nut plate plugs P/N. DB1105020-189-25, the antenna repair doubler P/N. DB104042.001 was installed on the existing antenna doubler and two coin repair patches P/n. DB1104042-002 were installed, one on top of the other to allow for a flush skin repair. The existing nut plate holes were filled with 4 screws P/N. AN525-10R7. See Attached FAA Form 8110-3 signed by DERT-410115-CE dated August 15, 2012 using Nextant Aerospace Engineering Order 139-12 Rev C Dated August 03,1111Mails. ICA Weight and Balance change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End ❑ Additional Sheets Are Attached FAA Form 337 po-orn EFTA00011859 EFTA00011860 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION August 15, 2012 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft. Engine. Propeller, etc) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Richmond Heights, Ohio LIST OF DATA 8 IDENTIFICATION 7 TITLE EO 139-12 Antenna Repair Patch (L-Band Antenna Moved). Rev. C ' August 3, 2012 --------- ----------------- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements.' 2) This form does not constitute FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. The electrical requirements are not included in this approval and require separate approval. B. PURPOSE OF DATA: Engineering data in support of FAA STC ST03960AT. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23), 25.307(a)[25-231, 25.365(a)(b)(c)(d)(f)(g)[25-00], 25.562(c)(25-23], 25.601[25-00], 25.603(a)(b)(c)[25.38), 25.605(a)(25-00), 25.607[25-23], 25.609(a)(b)125-00), 25.611[25-23], 25.613(a)(b)(c)[25-00), 25.619[25-23], 25.625(a)(b)(c)[25-23), and 25.789[25-32). 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with cor.011ons and limitations of appointment under 14 CFR Pan 183. data listed above and on attached sheets numbered N/A . have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. ❑ Recommend approval of these data I (We) Therefore El Approve these data II. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATNE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATIONS) DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION Fite Number. H12418.02 Page 1of 1 EFTA00011861 EFTA00011862 ram AProved Electronic Tracking Number OMB No. 21204020 le MAJOR REPAIR AND ALTERATION 11/302007 vs oriparinem or Tamperiewn (Airframe, Powerplant,Propeller, or Appliance) For FAA Use Only Fulmer Aviation noeniseetion INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Apperdx B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (40 U.S.C. 1421). Failure tO report can result in a cinf penalty net to exceed 81.000 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Model Make Series Raytheon Aircraft Company 400A Name (As shown on reels:tattoo certificate) Address (As shown on tegisfration certificate) 2. Owner neoresi Flight Options .LLC City Richmond Heights sure. OH zo 44143-1453 cumin USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number ❑ E4 AIRFRAME (Asdescribed in MOM I Mon) ❑ D PONIERPLANT • O PROPELLER Type APPLIANCE El • meoracmar 6. Conformity Statement A. Agency's Name and Address 8. Kind of Agency Rae Nextant Aerospace O U.S. Cenincated Mechanic CI IManufacturer Address O Foreign Certificated Mechanic C. Coruscate No. City Cleveland slaw OH 0 Certificated Repair Station zip 44143-1453 Country USA O Certificated Maintenance Organization CRS # 25NR667B 0. i certify that the repair and/or alteration made to the unit(S) Identified in Kern 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 12/29/2013 APP. B 0 Pursuant to the authority given persons pecified below. The unit identified in Item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Admnistration and is 111 APPROVED 0 REJECTED FAA Fit Standards i Person Approved by Canadian Manufacturer Maintenance Organization Department of Transport Inspector BY Other (Specify) FM Designee X Repair Station Inspection Authorization CedifiCete or Designation No. 12/29/2013 CRS # 25NR667B FAA Form 331 (10-os) er' EFTA00011863 EFTA00011864 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Title: Pedestal cover extension Modification After STC modification of pedestal per 373-94-1000_B, existing pedestal close out tray needs to be extended to cover appropriate areas. Modification of the close out tray is required. Modify the pedestal close out tray per drawing NX25 - 10002. See attached FAA Form 8110-3 signed by DERT - 410115-CE. Dated 11/8/2013 using Nextant Aerospace Engineering Order EO 1018 Rev F. Dated 10/9/2013 ICA Weight and Balance Changes are Negligible Continue to Use Existing Beechjet 400/400AMaintenance Manuals Inspection Procedure for this Area END ❑ Additional Sheets Are Attached FAA Form 337 (10-06) EFTA00011865 EFTA00011866 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION November 8, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aimsft. Engine, Properler, eft) 5. NAME Of APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Cleveland, Ohio LIST OF DATA 8 IDENTIFICATION 7 TIP E EO 1018 Pedestal Cover Extension Modification. Rev. F October 9, 2013 — -------------- ---- — Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements? 2) This form constitutes FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. B. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specilic sections) CFR Title 14 Part 25.301(25.23), 25.303[25-23), 25.305(a)(b)(c)(25-23], 25.307(a)[25-23), 25.562(c)(25-23), 25.601(25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00), 25.607(25-23), 25.609(a)(b)[25-00), 25.611[25-23], 25.613(a)(b)(c)(25-00), 25.619(25.23), 25.625(a)(b)(c)125-23), and 25.789[25-32). 10. CERTIFICATION - Under authority vested by direction of the Administrate( and In accordance with conditions and lirnotati5ns of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered Nth have teen examined in accordance with established procedures and found to comply with applicable requirements of the ArnvonhMess Standards Listed. ❑ Recommend approval of these data I (We) Therefore 0 Approve these data 11. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number H13817.04 Page 1of 1 EFTA00011867 I EFTA00011868 Form Approved Electronic Tracking Number OMB No. 2120-0020 0 MAJOR REPAIR AND ALTERATION lino/mg Deparment of TrarreonatIon (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Ayarwal Aviation Aahaduration INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this loon. This report is required by law (49 U. S.C. 1421). Failure to report can result in a civil penalty not to exceed 51,000 for each such violation (Section 901 Federal Aviation Act 1959) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on rogiSfrafion certificate) Address (As shown on registration certificate) 2. Owner Flight Options .LLC Adere6s cry Richmond Heights site OH tip 44143.1453 coowy USA 3. For FAA Use Only 4. Typo 5. Unit Identification Repair Alteration Unit Make Model Serial Number 0 0 AIRFRAME (As described in Nem 1 above) IE POWERPLANT Ill • PROPELLER 0 Type APPLIANCE ❑ O manufacturer' 6. Conformity Statement A. Agencys Name and Address B. Kind of Agency Nana Nextant Aerospace CI u.s. Certificated Mechanic O I Manufacturer Patron O Foreign Certificated Mechanic C. Certificate No. cry Cleveland State. OH B Certificated Repair Station tip 44143-1453 Country USA O Certificated Maintenance Organization CRS # 25NR667B D. I certify that the repair and/Or alteration made to the unit(s) identified in item 5 above and described on tne reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 12/29/2013 APP. B El 7. Approval for Return to Service Pursuant to the authority given persons specified below, the unit identified in item 5 was Inspected In the manner presalbecl by the Administrator of the Federal Aviation Administration and is Ell APPROVED ❑ REJECTED FAA Flt Standards Organization I Person Approved by Canadian Manufacturer Maintenance Department of Transport Inspector BY Other (Specify) FM Designee X Repair Station InsPeCtiOn Authorization Certificate or Designation No. 12/29/2013 CRS # 25NR667B FAA Form 337 (10.06) EFTA00011869 EFTA00011870 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N49311 12/29/2013 Nationality and Registration Mark Date DEACTIVATE CLOCKS For Pilots Clock Deactivation: I.) Removed PLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load side wires. 2.) At Radio Junction Box: a.) disconnected wire W78-I9 from 393IJ25 PIN R & S. b.) Spliced wire W78-19 from pin R with 3931322 wire W71-3 (20) pin D•. For Co-Pilots Clock Deactivation: 4.) Removed COPLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load side wires. 5.) At Radio Junction Box: a.) disconnected wire W78.45 from 39311B1 3931R3 pin 3. b.) cap and stowed wire. c.) Installed jumper from pin 3 to 3931.122 pin F* (splice with wire W71-4 (20)) 6.) Tested all WOW interface circuits at #1 & #2 DCU, #1 & #2 DCP,01 & #2 PFD,tiI & #2 MFD, DAU, #1 &#2 ADC, #1 & #2 GPS, #1 & #2 FSU, #1 & #2 TDR. 7.) Changed power wiring for ELT from #2 Clock to #2 Audio panel. Disconnected wire from inline fuse ELTFI feed side and connected to Audio power input 2350P4 pin 8 (spliced with wire W965.019 (20)). Tested ELT. This removal was electrically approved by FAA DERT-230019-CE using a FAA 8110-3 Dated November 15, 2013 Using Nextant Engineering order 1165 Rev B Dated 11/13/2013 End ❑ Additional Sheets Are Attached FAA Form 337 (1005) EFTA00011871 EFTA00011872 V.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION 11.15-2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Airplane, Radio. Helicopter, 5. NAME OF APPLICANT -. Hawker Beechcraft 400A etc.) Nextant Aerospace LLC \ SIN RK-244 Only Airplane LIST OF DATA G. IDENTIFICATION 7. TITLE Nextant Aerospace Engineering Order Document EO 1165 Deactivate Clocks dated 11.13.13 Rev. B - END This approval is for the electrical systems aspects onty. 8. PURPOSE OF DATA Support major alteration to aircraft Hawker Beechcraft 400A RK-244 Only. 9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR 25.1301(a) pig' Note: Compliance has been found to the amendment levels indicated on Hawker Beechcraft 400A TCDS Revision 26 Part 25 Amendment 25- 1 through 25-40 to the above applicable requirements. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Pan 183 of the Federal Aviation Regulations. data listed above and on attached sheets numbered WA have been examined In accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. I (We) Therefore approve these data. 11. SIGNATURES I N ING REPRESENTATNE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-230019-CE Systems and Equipment 1-AA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION GPO 90t413 EFTA00011873 EFTA00011874 C Form Appnarod Electronic Tracking Number om8 No.21204020 MAJOR REPAIR AND ALTERATION I 1r30,2C07 •piinment el Trans T portaarn (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Federal Aviation Administration INSTRUCTIONS: Print or type 31entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S C. 1421). Failure to report can result In a civil penalty not to exceed $1,030 for each such violation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Bones Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on regtsfration certificate) 2. Owner AnSress Flight Options .LLC Gila Richmond Heights sin OH zip 44143-14U Camay USA 3. Far FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number ... AIRFRAME (As described in Item 1above) 0 0 O POWERPLANT ❑ PROPELLER o TWO APPLIANCE • U Mania:Leer 6. Conformity Slat mont A. Agency's Name and Address B. K nd of Agency Wits Nextant Aerospace 0 u.S. CerbliCaMd Mechanic 0 I Manufacturer Melon 0 Foreign Ceetbealed Mechanic C. Certificate NO. City Cleveland Stati OH 0 Certificated Repair Station co 44143-1453 cowry USA 0 Certificated Maintenance Organization CRS # 25NR667B D. !certify that the repair and/Or alteration made to the rings) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furniihed herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 ❑ 12/29/2013 APP. B Pursuant to the authonly given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is El APPROVED 0 REJECTED FM Fit Standards Person Approved by Canadian Manufacturer Maintenance Organization Department of Transport Inspector av Other (Specify) FAA Designee X Repair Station inspection Authorization Cenificace Or Designation No 2/29/2013 CRS # 25NR667B FAA Form 337 (10-06) EFTA00011875 EFTA00011876 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (It more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date TITLE: Aircraft Windshield Sealing Process Deviation: Allow Deviation from AMM 56-10-00-201 for the sealing of the aircraft windshield process. Temporary fasteners are not necessary during the sealing of the windshield. Original & typical bolts for installation may be used during the process, to keep retainers and shims in place during the entire sealing & installation of the windshield. After proper sealing time had elapsed, torqued bolts for installation of windshield per AMM. See attached FM Form 8110-3 Signed By DERT-410115-CE Dated June 12, 2013 using Nextant Aerospace Engineering Order 1257, Rev. A, Dated May 21, 2013 for details. ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End ❑ Additional Sheets Are Attached FAA Form 337 (10-08) EFTA00011877 EFTA00011878 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION June 12, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft Engine. Propene( eta) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Richmond Heights, Ohio LIST OF DATA 6 IDFNTIRCATION 7 TITLE EC 1257 Aircraft Windshield Sealing Process Deviation. Rev. A May 21, 2013 ------- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements." 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. 8. PURPOSE OF DATA: Engineering data in support of major repair to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23), 25.303[25-23), 25.305(a)(b)(c)(25-23], 25.307(a)[25-23], 25.601[25-00), 25.603(a)(b)(c)(25-38], 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)[25-00), 25.611[25-23), 25.613(a)(b)(c)(25- 00], 25.619[25-231, and 25.625(a)(b)(c)125-231. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with condelices and limitations of appointment under 14 CFR Part 183: data listed above and on attached sheets numbered _Ha_ have been examined in accordance with established procedures and found to comply with applicable requirements of the Ainvorthiness standards Listed. ❑ Recommend approval of these data I (We) Therefore i015 Approve these data II. SIGNATURES) OF DESIGNATED ENGINEERING REPRESENTATIVES) 12. DESIGNATION NUMBERS(S) 13. CIASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number. H13367-01 Page 1oft EFTA00011879 EFTA00011880 FormApprond Electronic Tracking Number OMB No. 2i2043020 e MAJOR REPAIR AND ALTERATION iti3OIXOT u.s oepavvent or (Airframe, Powerplant,Propeller, or Appliance) Truirexitatien For FAA Use Only Folond AvlatIon Adonlnistration INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix 9. and AC 43.94 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 V $ C. 1421). Failure to report can result in a Civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act 1958) Nationally and Registration Mark Serial No. RI< 244 N493LX t. Aircraft Model Make Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration certificate) *guess t . Owner Flight Options .LLC Ci:y Richmond Heights Mete OH zp 44143-1453 CoJtry USA 3. For FAA Use Only 4. Typo 5. U It Identification Repair Alteration Unit Make Model Serial Number El AIRFRAME (As descnbed in Item I above) El POWERPLANT MI • l: PROPELLER Typo 0 El APPLIANCE manure:firer 6. Conformity Statement A. Agency's Name and AddreSS It Kmd of Agency mete Nextant Aerospace O U.S. Certificated Mechanic O I Manufacturer mons O Foreign Certificated Mechanic C. Certificate No. City Cleveland state. OH 0 Certificated Repair Station zo 44143.1453 cmintry USA O Certificated Maintenance Organization CRS # 25NR667B 0. I certify that the repair andror ateraten made to the twigs) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pad 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 2/29/2013 App. B 0 7. Approval for Return (Service Pursuant to the authority given pe sons specified below. the unit identified in item 5 was inspected in the manner prescribed by the AdMiNStrator of the Federal Aviation Administration and is 121 APPROVED ❑ REJECTED FAA FR Standards Manufacturer Maintenance Organization I Person Approved by Canadian Inspector Department of Transport BY Other (Specify) FAA Designee X Repair Station Inspection Authorization Certificate or Designation No. • • /2013 CRS # 25NR667B FAA Form 337 no-06) EFTA00011881 EFTA00011882 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registratkin mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Requested for use of new processes & materials for the removal and installation of Main & Side Windscreen, deviation from HBC AMM When performing the removal and installation of the windscreen and/or cockpit side windows, the following deviations from the HBC AMM are allowed & recommended: 1. During the removal & installation of the main windscreen, reference FO-AMMS document, chapter 56-10-01 for the main windscreen installation using AVDEC materials. This document correctly defines the processes and materials to be used for the removal and installation of the main windscreen. 2. During the removal and installation of the cockpit side windows, reference Flight Options FO-AMMS Document, chapter 56-10-10 & 56-10-11 for the replacement of the side window inner rubber gasket. This document correctly defines the processes and materials to be used for the replacement of the cockpit side windows inner rubber gasket. NOTE: TG8498 & HT3935-7 may not be used on exterior surfaces unless sealant is to be painted after curing for protection against UV light. PERMISSIBLE TO PAINT OUTER WINDSHIELD RETAINER WITH Chevron White JET GLO, CM0570513 (Sherwin-Williams) This Alteration was FAA Approved by FM DERT-410115-CE using an FM Form 8110-3 dated December 28, 2013. Using Nextant Aerospace Engineering Order 1303 Rev B Dated November 13, 2013 ICA Continue with Normal Hawker Beech Maintenance manual Inspection Requirements for this Area End ❑ Additional Sheets Are Attached FAA Form 337 (10-06) EFTA00011883 EFTA00011884 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION December 28, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft. Engine. Propeller, etc.) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Richmond Heights, Ohio LIST OF DATA 8 IDENTIFICATION 7 TITLE EO 1303 Process & Material Deviation for the Removal and Installation of the Main & Side Rev. B Windscreens. November 13, 2013 -- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements? 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. B. PURPOSE OF DATA. Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244. 9. APPLICABLE REQUIREMENTS (Ust specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)125-231, 25.562(c)[25-231, 25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23), 25.613(a)(b)(c)[25-00], 25.619[25-23], 25.625(a)(b)(c)(25-23], and 25.789[25-32]. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183. data listed above and on attached sheets numbered N/A , have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. 0 Recommend approval of these data I (We) Therefore 0 Approve these data 11. SIGNATURE $ OF DESIGNATED ENGINEERING REPRESENTATn/E(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Fie Number H13949.01 Page tof EFTA00011885 EFTA00011886 Fool Approved Electronic Tracking Number 04/43 No. 21200020 0 MAJOR REPAIR AND ALTERATION 1traOrau37 u.s cworwienice TranNonsoan (Airframe, Powerplant,Propeller, or Appliance) For FAA Use Only Fetal Aviation Aomiresuation INSTRUCTIONS: Print or types. entries. Sec FAR 43.9. FAR 43 Appendix B. and AC 43.91 (or subsequent revision thereof) for instructions and disposition or this form. This report is required by law (49 U.S.C. 1421). Fa •i'e to report can result in a OM penally not to exceed S1.000 ror each such violation (Section 901 Federal Aviation Act 1956) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Mcdel Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on regisfra bon certificate) 2. Owner Flight Options .LLC Address Crly Richmond Heights Slate OH zip 44143-1453 cowry USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number AIRFRAME (As descnbed in Item I above) 0 POWERPLANT Ill El ❑ PROPELLER Tyco ❑ 0 APPLIANCE M-sgVactwer 6. Conformity Statement A. Agency's Name and Address e. Kind of Agency Name Nextant Aerospace O U.S. Certificated Mechanit O Manufacturer Address O Foreign Cenneated Mechanic C. Certificate No. City Cleveland Stale. OH CB Certificated Repair Station Zip 44143-1453 count USA O Certificated Maintenance Organization CRS it 25NR667B D. I certify that the repair and/or aileratlon made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of P rt 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my know: dge. Extended range fuel per 14 CFR Part 43 12/29/2013 App. S ❑ Pursuant to the authonty given persons specified below, the unit Identified in item 5 was inspected in the manner prescnbed by the Administrator of the Federal Aviation Administration and is 9 APPROVED 0REJECTED FAA FR Standards Person Approved by Canadian inspector Manufacturer Maintenance Organization Departing/Mot Transport BY Other tSpeci6r) FM Designee X Repair Station Inspection Authorization Certificate or Designation No. 12/29/2013 CRS # 25NR667B FAA Form 337 (10-06) EFTA00011887 EFTA00011888 NOTICE Weight and balance or operating limitation changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Title : Replace MD-302 with Round Style Standby Gauges Aircraft with MD302 digit SAM instruments must be reverted back to using round standby gauges until issues are resolved. Modified Instrument Panel (373-92-4110-14) to allow the installation of the original round standby gauges per drawing NX311-10007-03 Rev A Fabricated round indictor subpanel per drawing NX311-10007-01 Rev B Installed instruments into subpanel and install subpanel into main instrument panel per drawing NX311-10007. See Attached 8110-3 DERT 410115-CE dated November 8, 2013 per Nextant Aerospace EO 1543 Rev D dated October 23, 2013 End ❑ Additional Sheets Are Attached FAA Form 337 110.06) EFTA00011889 EFTA00011890 U.S. DEPARTMENT OF TRANSPORTATION t. DATE FEDERAL AVIATION ADMINISTRATION November 8, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft. Engine. Propeller. efc) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Cleveland, Ohio LIST OF DATA 6 IDENTIFICATION 7 MI E EO 1543 Replace MD-302 With Round Style Gauges. Rev. D October 23, 2013 ---- ------------------ END-- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements." 2) This form does not constitute FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. The electrical requirements are not included in this approval and require separate approval. a. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23), 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.562(c)[25-23], 25.601[25-00), 25.603(a)(b)(c)[25-38], 25.605(a)[25-00), 25.607(25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25.00], 25.619[25-23], 25.625(a)(b)(c)[25-23], and 25.789[25-32). IC. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered N!A have been examined in accordance wth estatished procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. 0 Recommend approval of these data I (We) Therefore )4 Approve these data i 1. SIGNATURE S OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION File Number. I413818-01 Paget off EFTA00011891 EFTA00011892 FanMarano I Electronic Tricking Number 2120-ccdo 0 MAJOR REPAIR AND ALTERATION ENO waocco7 U.SOnertrrient of (Airframe, Powerplant, Propeller, or Appliance) rimironifion For FAA Use Only Foam Aviation ArtninIstration INSTRUCTIONS: Print or typo ail entries. See FAR 419, FAR 43 Appenox B. and AC 43 9.I (or subseccent ression thereof)or instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1954) Nationality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner Aram" Flight Options .LLC city Richmond Heights Stale. OH 7.0 44143-1453 cvisdry USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number • 111 AIRFRAME (As described in Item 1 above) • • POWERPLANT PROPELLER Typo APPLIANCE II . Vardatheor 6. Conformity Statement A. Asiencys Name and Address 8. Kind of Agency Name Nextant Aerospace CI U.S. Certificated Mechanic O (Manufacturer Address O Foreign Certificated Mechanic C. Certificate No. Cry Cleveland Sara. OH 0 Certificated Repair Station iv 44143-1453 Ccuray USA O Certificated MaiMenance Organization CRS # 25NR667B D. I certify that the repair arilror alteration made to the unri(S) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 12/29/2013 App. 8 INI Pursuant to the authOrity given persons pecilled below. the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 0 APPROVED ❑ REJECTED FAA Flt Standards 1 i Person Approved by Canadian Manufacturer Maintenance Organization DeparUnent of Transport Inspector BY Other (Specify) FAA Designee X Repair Station Inspection Authorization Certificate or Designation No 12/29/2013 CRS # 25NR667B FAA Form 337 it 0-06) EFTA00011893 EFTA00011894 NOTICE Weight and balance or operating limitation changes shall be entered in the appropfiate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Spoiler Linkage Closeout Modification Modified the Cockpit Floor Close out Panels Part Number: LH 45A30839-7 (Pilots) and Part Number: RH 45A30839-7 ( Co-Pilots) . Installed Nextant Aerospace Closeout Panel Part Number NX532- 1004-1 between these Panels to allow room for the New Throttle Quadrant to fit under the Center Pedestal This Alteration was FAA Approved by FAA DERT-410114-CE using a FAA 8110-3 Dated December 28, 2013 using Nextant Aerospace Engineering Order 1563 Rev. B Dated December 24, 2013 ICA Continue with Normal Hawker Beech Maintenance Manual Inspection Requirements for this Area End ❑ Additional Sheets Are Attached FAA Form 337 (lam EFTA00011895 I EFTA00011896 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION December 28, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 1. MODEL NO. 4. TYPE (Aircraft Engine, Pnopetter. etc.) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LLC Corporation Cleveland, Ohio LIST OF DATA 8 IDENTIFICATION 7 TITLE EO 1563 Spoileron Linkage Closeout Modification. Rev. B December 24, 2013 Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements." 2) This constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. 8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25.23), 25.305(a)(b)(c)(25-23J, 25.307(a)(25-23], 25.601[25-00], 25.603(a)(b)(c)[25-381, 25.605(a)(25.00), 25.607[25-231, 25.609(a)(b)[25-00], 25.611(25-23), 25.613(a)(b)(c)[25- 00], 25.619[25-231, and 25.625(a)(b)(c)(25-231. 10. CERTIFICATION • Under authority vested by drection of the Administrator and in accordance with conitions and irmitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. ❑ Recommend approval of these data I (We) Therefore 0 Approve these data 11. SIGNATURE OF DESIGNATED ENGINEERING REPRESENTATIVES) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICAT/ON(S) DERT-410115-CE Structures FAA Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Fite Number. H13950-0I Pageioll EFTA00011897 I EFTA00011898 IC"' AOItte.Orl Electronic Tracking' Number OW No 2120-0020 le MAJOR REPAIR AND ALTERATION 11/3C/2007 u S Deeinmem re (Airframe, Powerplant,Propeller, or Appliance) soopooion For FAA Use Only Federal Aviation Administration INSTRUCTIONS: Print or type a'l entnes See FAR 43.9. FAR 43 Appendix 8. and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result In a civil penalty not to exceed 51.000 for each such vitiation (Section 901 Federal Aviation Act 1958) Nationality and Registration Mark Sena' No. RK 244 N493LX 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As ShOwn on registration certificate) 2. Owner Flight Options .LLC Addre ss City Richmond Heights sow. OH tip 441431453 couroy USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number CI AIRFRAME (As described in Item 1above) ❑ O POWERPLANT O ❑ PROPELLER TIP° O O APPLIANCE Manufactory • 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Nome Nextant Aerospace O U.S. Cenificaled Mechanic O Manufacturer Address O Foreign Certificated Mechanic C. Certificate No. City Cleveland sole OH II9 Certificated Repair Station 21p 44143-1453 cony USA O Cedaficated Maintenance Organization CRS # 25NR6676 D. I certify that the repair and/or alteration made to the und(s) identified in dem 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pail 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 12/29/2013 App. 8 ❑ Pursuant to the authority given persons specified below, the unit identified in item 5 was iispected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 0 APPROVED O REJECTED FAA FR Standards Organization I Person Approved by Canadian Manufacturer Maintenance Department of Transport Inspector BY Other (Specify) FAA Designee X Repair Station Inspection Authorization Certificate or Designation No. 12/29/2013 CRS # 25NR6676 FAA Form 337 (0046) EFTA00011899 EFTA00011900 NOTICE Weight end balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued confomety with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12/29/2013 Nationality and Registration Mark Date Nextant Aerospace Carried out a Repair to the Horizontal Stabilizer Ribs Using Nextant Aerospace Kit Part Number NXK-128-6200 Rev B. Dated July16. 2012. The following Ribs were replaced. NXR-45A21112-007 Rib — H Stab Cant STA 13.779. NXR-45A21113-007 Rib — H Stab Cant STA 29.921. NXR-45A21101-021 Rib — H Stab Cant STA 46.063. NXR-45A21116-007 Rib — H Stab Cant STA 62.205 NXR-45A21117-007 Rib — H Stab Cant STA 78.346 The following Ribs were not Replaced as there was not Damaged. NXR128-620020-001 NXR128-620020-002 This Kit was FAA Approved by DER-T 410115-CE Structures on an FAA 8110-3. Dated June 12, 2013. Using Nextant Aerospace Engineering Drawing NXR-128-6200 Rev B Dated July 16.2012 END ❑ Additional Sheets Are Attached FAA Form 337 (10.06) EFTA00011901 EFTA00011902 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION June 12, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aircraft, Engine, Propeller, etc) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aeiospace LLC Corporation Richmond Heights. Ohio LIST OF DATA 6 IDENTIFICATION 7 TfTLE NXR-128-6200 Kit — Horizontal Stabilizer Rib Replacement Installation Instructions. Rev. B July 16, 2012 NXR-45A21112-007 Rib - H Stab Cant STA 13.779. Rev. C July 13, 2012 NXR-45A21113-007 Rib — H Stab Cant STA 29.921. Rev. B July 13, 2012 NXR-45A21114.007 Rib — H Stab Cant STA 46.063. Rev. B July 13. 2012 NXR-45A21115-007 Rib — H Stab Cant STA 46.063. Rev. C July 13, 2012 NXR-45A21101.021 Rib Assy — H Stab Cant STA 46.063. Rev. A July 19. 2012 NXR-45A21116-007 Rib — H Stab Cant STA 62.205. Rev. B July 13, 2012 NXR-45A21117-007 Rib — H Stab Cant STA 78.346. Rev. B July 13, 2012 e. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on Hawker Beechcraft 400A, S/N RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25-23), 25.305(a)(b)(c)(25-23), 25.307(a)(25-23), 25.601[25-00], 25.603(a)(b)(c)125-381, 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)(25-00), 25.611(25-23), 25.613(a)(b)(c)(25- 00), 25.619[25-23], and 25.625(a)(b)(c)(25-23]. 10. CERTIFICATION • Under authority vested by direction of the Administrator and in accordance with conditions and tirnitatians of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered .,..2_ have been examined in accordance with established procedures and found to comply mm applicable requirements of the seaworthiness Standards Listed. O Recommend approval of these data I (We) Therefore 0 Approve these data 1I. SIGNATURE S OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number H13370-01 Page 1 of 2 EFTA00011903 EFTA00011904 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION June 12, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO 4. TYPE (Aircraft Engine, Propetter. etc.) 5. NAME OF APPLICANT Hawker Beechcraft 400A Aircraft Nextant Aerospace LW Corporation Richmond Heights, Ohio LIST OF DATA 8 IDENTIFICATION 7 TIT' E ---------- ------------ --- --------------------------------- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements' 2) This form constitutes FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. 8. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on Hawker Beechcraft 400A, S/N RK-244. 0. APPLICABLE REQUIREMENTS (List spectic sections) CFR Title 14 Part 25.301(25-23], 25.303[25-23), 25.305(a)(b)(c)[25-23), 25.307(a)[25.23], 25.601[25-00], 25.603(a)(b)(c)[25-38), 25.605(a)(25.00], 25.607[25-23], 25.609(O1:0[25-00], 25.611(25-23), 25.613(a)(b)(c)[25- 00], 25.619[25-23], and 25.625(a)(b)(c)[25-23). 10. CERTIFICATION • Under authority vested by direction of the Administrator and in accordance with conditions and 5mitations of appointment under 14 CFR Part 163. data listed above and on attached sheets numbered ...7,_ have been examined in accordance wdh established procedures and found to comply mlh applicable requirements of the Airworthiness Standards Usted. • Recommend approval of these data I (We) Therefore i, Approve these data It. SIGNATURES OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERSIS) 13 CLASSIFICATION(S) DERT-410115-CE Structures • FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION File Number 1113370.01 Page 2 of 2 EFTA00011905 I EFTA00011906 Form APProved Electronic Tracking Number OMB No. 2120-0020 0 MAJOR REPAIR AND ALTERATION 11M0f2007 he ovolownot (Airframe, Powerplant, Propeller, or Appliance) Timmy/woo For FAA Use Only Federal Ai/1HW Adrairdallntkia INSTRUCTIONS: Print or type all entries. See FAR 43.9 FAR 43 Appendix B, and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result In a civil penalty not to exceed 31,000 for each such 10latiOn (Salon 901 Federal Aviation Act 1958) Nationality and Registration Mark Serial No. N493LX RK244 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration cerfrfiCate) Address As shown on registration certificate Flight Options, LLC 2. Owner cayRichmond Heights swoOhio zo44143-1453 ecitritryUSA 3. For FAA Use Only 4. Type 5. Unit Identification Repar Alteration Unit Make Model Serial Number • 1 AIRFRAME (As described in Item 1 above) POWERPLANT • O PROPELLER Trim ❑ APPLIANCE 0 Menulectirer IL Conformity Statement A. Agency's Name and Address B. K rid of Agency rwooConstant Aviation O U.S. Certificated Mechanic O I Manufacturer Add. O Foreign Certificated Mechanic C. Certificate No. cisCleveland swoOhio El Certificated Repair Station CRS#WC7R346J 444135 canyUnited States O Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the wit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Anabon Regulations and that the information furnished herein is true and correct to the best of m Extended range fuel per 14 CFR Part 43 ❑ Date: December 30, 2013 App. 8 to Service Pursuant to the authority given pe sons specified below, the unit identi ed in item S was Inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is irl APPROVED ❑ REJECTED FM Fit Standards Person Approved by Canadian Manufacturer Maintenance Orgarizatica Department of Transport Inspector BY Other (Specify) FM Designee X Repair Staten Inspection Authorization Certificate or Signature/Date • Designation No. Date: December 30 , 2013 CRS#WC7R346J FAA Form 337 (lo-os) EFTA00011907 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12130/2013 Nationality and Registration Mark Date ACCOMPLISHED INTERIOR REFURBISHMENT/MODIFICATION AND 3 PLACE DIVAN INSTALLATION THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN REFURBISHED: Repainted, recovered control Ocrumns with Matte Black Leather Accordance with Beechjet 400A AMM 20-70-00.701, 25-00430-001 Removed and Replaced Glare sHeld and Eyebrow panel material with Matte Black Leathern Accordance with Beechjet 400A AMM 20.60.00.201 Removed and Replaced Cor-kpl Sidewise material with Matte Black Leather in Accordance with Beechjet 400A AMM 20-60-00-201. Removed and replaced Pilot Seat Pan Number TABHIOOPM0001 Serial Number 62, Foam and recovered with Garrett Sheepskin Oak and Excel' Cappuccino Leather. Removed and replaced Co-Pilot Seat Part Number TABH100CM00-01 Serial Number 248. Foam and recovered with Garrett Sheepskin Oak and Excel' Cappuccino Leather. Removed and Replaced Lett Hard /Xs Passenger Seat Part Number 2524-014(-530A) Serial Number 990719.4 Foam and recovered with Townsend Leather (Heritage Brown) Removed and replaced Right Hand #5 Passenger Seat Pan Number 2524.014(4308) Serial Number 990426-7 Foam and recovered with Townsend LeaMer(Hertlage Brown) Removed and Replaced Left Hand 88 Passenger Seat Part Number 2524-014(530B)Serial Number 030818-6 Foam and recovered with Townsend Leather (Heritage Brown) Removed and replaced Right Hand *7 Passenger Seat Pal Number 2524-014(530A) Serial Number 030708-2 Foam and recovered with Townsend Loather (lenlage Brown) THE FOLLOWING MANUALS AND APPROVED DATA HAVE BEEN UTILIZED FOR BASIS OF REFURBISHMENT: Skandia Flammability Test S254978 as approved by FAA DER Jane Biberstein (DERV 832780-CE) on FM form 8110-3 dated 412312013. Flame Out Flammability Test 4311 as approved by FM DER Herb Reed II (GERT-230293-CE) on FM Form 8110-3 dated 12/23/2013. Skandia Flammabitly Test Report TP 22681 Rev A as approved by FM DER Jane Biberstein( DERV-832780-CE) on FM Form 8110-3 dated 05/02/2013. Three Place Divan installation: Installed (3) place divan part Number 32-0396(A6OPT)7123.K02 S/N 003702 In Accordance with Aviation Fabricators STCIST01572VVI and Skandia FlammiNity test report 5254976 per Jane Biberstein FM DER (DERY-832780-CE) dated 4/23-2013 THE FOLLOWING INTERIOR ITEMS HAVE BEEN MODIFIED: LM Gaily Assy. FUH Galley Assy, Divan Assy. LIM Galley Assy and Install per Delta G drawing OGO-CA01-101 Rev 0, DGD-CA01-101 E0 E-1, UH Galley Install DGD.CA01-501 Rev EO A-1, DGD-CA01-501 Rev IR as approved on FM form 8110-3 per FM DER Donald Mimeo (DERT-750t35-SW) dated March 25 2013. RM Galley Assy and Install per Delta G drawings DGD-CA02.101 Rev 8, DGD-CA02-501 Rev IR as approved on FM form 8110-3 by FM DER Donald Gillespie (DERT-750135SW) dated March 25. 2013, Divan Any per Delta G draynngs DGD-CA09.101 Rev C and OGOGA09-101 E0 D-1 as approved on FM form 6110-3 per FM DER Donald Gillespie (DERT 750135-SW) dated March 25, 2013, Bonner Kit Sideway assy drawing 2553-0036 Rev C, Bonner Sideledge assy drawing 2532-0002 Rev C, Bonner Kit Foldout Table assy «manes 2553.0041 Rev C and 2553-0040 Rev B. Bonner XTI liner Kit knit drawing 2553.0037 Rev C as approved on FM form 8110-3 per Stephen Forness DERT-230238-CE dated Dec 26. 2013. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE. THERE ME NO ADDITIONAL INSPECTIONS REQUIRED. CONTINUE TO INSPECT lAW MANUFACTURERS ANN, SRM, OR CMM AS APPLICABLE AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER END— El Additional Sheets Are Attached FAA Form 337 (10-06) EFTA00011908 U.S. DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION Dec 26, 2013 STATEMENT OF COMPLIANCE Willi THE FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE MODEL TYPE (Airplane. Radio. Helicopter. NAME OF APPLICANT Beechcrall Corporation 400A etc.) AIRPLANE NEXTANT Aerospace Cleveland OH. LIST OF DATA IDENTIFICAITON TITLE REPORT: RKG3282 BEECHJET 400A INTERIOR STRUCTURAL SUBSTANTIATION Rev. IR, 8-28-2013 2553-0037 BEECHJET 400A Rev C, dated 8.30.2013 XTI LINER KIT INSTL. Beechjet 400A, Aircraft Serial No. R K-244 Certification Bases for this aircraft modification is per Type Certificate Number Al 6SW Revision 28 dated April 12,2013 PURPOSE OF DATA DESCRIBE AND SHOW VERIFICATIONS FOR NEXTANT INTERIOR INSTALLATION ON BEECRIET 400A, AIRCRAFT SERIAL NO. RK-244 APPLICABLE REQUIREMENTS ( Ust specific sections) 14 CFR Part 25 §.301, 303, 305, 307a), 365, 561, 571, 601, 603, 605, 609.613 CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations ofappointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. l(11AB Therefore ■ Recommend approval of these data H Approve these data SIGNATURE(S) Or DI s IGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) DERT-230238-CE STRUCR/RES AND DAMAGE TOLERANCE FAA Form 8110-3 (I I.70j surrasmrs PREVIOUS EDITION GPO 901 • 61) EFTA00011909 EFTA00011910 products engineering services, inc. STRUCTURAL ANALYSIS REPORT Forward Calley Cabinet Modifications - Beechcraft Model 400A, RK-244 & RK-305 Document No: 313-ST-001 Revision IR PREPARED BY: Date: December 24, 2013 APPROVED BY: APPROVED BY: Manager - Design Engineering President THIS DOCUMENT CONTAINS INFORMATION OF A PROPRIETARY NATURE AND SHALL NOT BE TRANSMITTED, REVEALED, OR DISCLOSED TO ANYONE WITHOUT THE EXPRESS WRITTEN PERMISSION OF LEE PRODUCTS ENGINEERING SERVICES, INC. ADDITIONALLY, USE OF THE INFORMATION IS PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY LEE PRODUCTS ENGINEERING SERVICES, INC. EFTA00011911 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE ii REVISION RECORD Revision Date Description Approval IR 12/24/13 Initial Release See Cover Sheet EFTA00011912 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE iii TABLE OF CONTENTS 1. INTRODUCTION 1 2. REFERENCES 2 2.1 CONSTANT AVIATION DRAWINGS 2 2.2 APPLICABLE SUPPLIER DRAWINGS (AVIATION FABRICATORS) 2 2.3 APPLICABLE LPESI REPORTS 2 2.4 APPLICABLE GOVERNMENT DOCUMENTS 2 3. CERTIFICATION BASIS 2 4. DESCRIPTION 3 4.1 GENERAL 3 4.2 RH FORWARD GALLEY ASSY & INSTL 3 4.3 RH FORWARD DIVAN MODIFICATION 4 4.4 LH FORWARD GALLEY ASSY & INSTL 5 4.5 LH AFT LAVATORY EXTENSION 7 5. STRUCTURAL SUBSTANTIATION 7 5.1 LH FORWARD GALLEY ASSY & INSTL 7 6. CONCLUSION 8 APPENDIX A A.1 EFTA00011913 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 1 1. INTRODUCTION The purpose of this report is to demonstrate the structural substantiation to applicable 14 CFR Part 25 regulations as they relate to the installation and modification of various interior cabinets on Beechcraft Model 400A, S/N's RK- 244 and RK-305, for a FAA Form 337 major alteration, performed by Constant Aviation at their Cleveland, OH facility. The installations consist of the replacement of new RH and LH forward galleys, and modification to the existing closet frame, an extension of the aft lavatory, and a modification to the side-facing divan with the manufacturer's approval. Everything except the new LH forward galley has been accomplished on a previous modification as documented in LPESI Report 222-ST-001. Therefore, only the new galley will be discussed and analyzed in this report. The floorplan for the two (2) Beechcraft Model 400A aircraft is as shown below. VA • P• s• way nom to. I IIVX ISM II CO RIO Figure 1-1 — Floorplan EFTA00011914 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 2 2. REFERENCES 2.1 Constant Aviation Drawings ,v Drawing Np. Rev. Title ... NXT0213-01 IR LH Galley Assembly NXT0213-02 IR LH Galley Installation NXT0213-05 IR Weight Placard Installation NXT0313-01 IR RH Galley Assembly NXT0313-02 IR RH Galley Installation NXT0313-03 IR Divan Assembly NXT0313-07 IR 4" Lay Ext 2.2 Applicable Supplier Drawings (Aviation Fabricators) Drawipg ri9. Rev. . Titla. D-10666 A 3 Place Divan Installation (STC ST01572WI) 2.3 Applicable LPESI Reports Drawing itch . iNvi Titlp ., 222-ST-001 B Miscellaneous Cabinet Modifications - Beechcraft Model 400A 2.4 Applicable Government Documents Document. ,,:,.R64,:. i, Titi#, . .i: ‹, 14 CFR Part 25 See Airworthiness Standards: Transport Category Sect. 3 Airplanes ANM-115-09-017 1/28/10 Interaction of Interior Structures, Including Seats 3. CERTIFICATION BASIS The Beechcraft Model 400A certification basis is defined Type Certificate Data Sheet (TCDS) A16SW, Rev. 28, the Certification Basis is 14 CFR Part 25 dated February 1, 1965, including Amendments 25-1 through 25-40. The individual 14 CFR Part 25 subparagraphs that will be discussed herein are: 25.301(a)(b)(c) Loads (Amdt. 25-23) 25.303 Factors of Safety (Amdt. 25-23) 25.305(a)(b) Strength and Deformation (25-23) 25.307(a) Proof of Structure (Amdt. 25-23) EFTA00011915 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 3 25.341(c) Gust Loads (No Amdt.) 25.561(a)(b)(c) Emergency Landing Loads - General (Amdt 25-23) 25.601 Design and Construction - General (No Amdt.) 25.603(a)(b) Materials and Workmanship (Amdt. 25-38) 25.605 Fabrication Methods (No Amdt.) 25.607(a)(b) Fasteners (Amdt. 25-23) 25.609(a)(b) Protection of Structure (No Amdt.) 25.613(a-e) Materials Strength Properties ... (No Amdt.) 25.625(a)(b)(c) Fitting Factors (Amdt. 25-23) 25.787(a)(b) Stowage Compartments (Amdt. 25-38) 25.789 Retention of Items of Mass ... (Amdt. 25-32) 4. DESCRIPTION 4.1 General The modification of the Model 400A aircraft consists of replacing the existing RH and LH forward cabinets with new assemblies, modifying the RH forward 3- place side-facing divan by refurbing the divan, and modifying the existing LH aft lavatory cabinet by extending its cabinet structure to close out the area around it. All but the new LH galley are previously installed and certified on previous 400A aircraft, and analyzed in LPESI Report 222-ST-001. 4.2 RH Forward Galley Assy & Instl The NXT0313-01 RH forward galley assembly (installed per NXT0313-02) is the same as that previously installed on other Model 400A aircraft. An illustration of the galley in Figure 4-1. EFTA00011916 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 4 Figure 4-1 - RH Forward GalleyAssy (Contact Pad on Upper Area Not Shown) The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP- 501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. The RH forward galley is installed between the existing RH forward structural partition (which separates the flight deck with the cabin) forward of it and the 3-place side-facing divan immediately aft of it. The lower wider section of the cabinet also encloses the aircraft's air conditioning evaporator mounted separately to the floor structure underneath. 4.3 RH Forward Divan Modification The NXT0313-03 3-place side-facing divan assembly consists of new drawer and fascia door panels onto the existing structural divan frame (Aviation Fabricators D-10666 STC'd Installation Kit - STC ST01572WI). It has also been installed in previous Model 400A aircraft, and analyzed in LPESI Report 222-ST-001. An illustration of the divan assembly is provided in Figure 4-2. EFTA00011917 Lee Products Engineering Services, Inc. 313-5T-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 5 Figure 4-2 — RH Forward Divan Mod The divan closeout panels are manufactured from strong lightweight 0.50- inch thick ATR-FP-501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. The STC'd divan frame installation consists of a structural frame (bottom only - no seat backs, cushions form the divan backs), restraint systems consisting of lap belts and shoulder harnesses for all three (3) seated positions, and a D-106699 floorboard modification installation underneath the divan. The frame installed in eight (8) places into the existing cabinet "Brownline" seat track extrusions (inboard and outboard). 4.4 LH Forward Galley Assy & instl The NXT0213-01 LH forward galley assembly is a traditional aircraft galley and is located between the flight deck and the entry door, directly aft of the existing LH forward structural partition (bulkhead). The new galley replaces an existing galley of similar design and the same size. In fact, this new galley assembly is the same as previously installed in other Model 400A aircraft, and analyzed in LPESI Report 222-ST-001, except for a minor change to the upper forward portion of the cabinet. As can be seen in a comparison of the galley illustrations below and Fig. 4-3 of 222-ST- 001, the change consists of eliminating the small recessed condiment tray drawer and extending (down) the existing compartment to compensate. The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP- 501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. An illustration of the LH forward galley is provided in Figure 4-3. EFTA00011918 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 6 I Figure 4-3 - LH Forward Galley Assy The LH forward galley is installed per NXT0213-02 and is installed utilizing the same existing installation attachments - five (5) screw/insert attachments into the existing partition and four (4) floor attachments (2 into the existing seat track and 2 into existing floorboard mounts, and is the same as the previous NXT0313-05 installation analyzed in LPESI Report 222-ST-001. The empty cabinet weights 86.15 pounds (less than the 90.61 pound galley analyzed in LPESI Report 222-ST-001) and the total placarded content weight (Ref. NXT0213-05) of 141.0 pounds (only 1.0 pound more than the 222-ST-001 analyzed galley). Therefore, the total installation weight of the NXT0213-02 galley is 3.46 pounds lighter than that analyzed in LPESI Report 222-ST-001, and is therefore structurally substantiated by comparison. EFTA00011919 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 7 4.5 LH Aft Lavatory Extension The NXT0313-07 LH aft lavatory modification consists of augmenting the toilet cabinet with new panels and compartments between the existing cabinet and the RH aft partition. An illustration of the modification to the aft lavatory is shown in Figure 4-4 (new components in gray). , --7.-zit:Z-7XL It tl FWD Mgr Figure 4-4 — LH Aft Lavatory Extension This is the same as previously analyzed in LPESI Report 222-ST-001. 5. STRUCTURAL SUBSTANTIATION The structural analysis will be generated using traditional means based on conservative assumptions. In determining the Margin of Safety (MS), the resulting analytical result will be subtracted from 1.0 so that any MS greater than 0.0 is considered a positive margin. Also, MS's greater than 3.0 will be listed as "+Ample". 5.1 LH Forward Galley Assy & Instl The critical loadings for the LH forward galley are the 9.0g forward and 3.5g side load conditions. However, since the new galley weighs 3.5 pounds less than the previously analyzed galley, is of similar shape and design, includes that same installed equipment, and utilizing the same aircraft attachment points, the new galley assembly and installation is therefore structural substantiated by comparison. EFTA00011920 Lee Products Engineering Services, Inc. 313-ST-001 REV. IR STRUCTURAL ANALYSIS REPORT PAGE 8 The largest placarded drawer is the top, center drawer in the lower section of the galley, which is placarded for 45.0 pounds. The drawer is restrained by a standard Actron paddle latch, P/N A23511-1S. The applied load to the latch is (the drawer itself + hardware is 5.0 pounds): Applied Load = (5.0 lbs + 45.0 Ibs) x 3.5g x 1.15ff = 201.3 pounds The minimum load rating for the A23511 paddle latch by its manufacturer is 225.0 pounds. The resulting margin of safety is: M.S. = 225.0 lbs / 201.3 Ibs) - 1.0 = +0.12 6. CONCLUSION Based on the above structural analysis, the new cabinets and modification and their installations, listed in Sect. 2.1, into the aircraft have been shown to be compliant with the applicable 14 CFR Part 25 regulations, as defined in Sect. 3 with positive margins of safety. EFTA00011921 4 3 2 004Oda ITN 0001:04•009 ba Weed, Oaten(' • OWSOITSOCOOn osoOpyry /it Oaten Pa met) Oftmermo wan covelannla O Ott @deaf* =1- Imailtatoe, gat •Oneirtil 4211041.4vOltarano wan, Su, SiMO Sal fl tt O. OMIT .00.1.C. D 1.73 0-12 100. ten a OLCS.ORTIP BASIC PART 511.0905R A 2951$ .301 39040. .00 X 94 th• .20 ROT A nsie nal STRUCTURAL ANALYSIS REPORT C C lams aose ad A ISM son Nuo 0.40 not WOWS .4••• B.. ito DASH Na A oat noos Beata s1 I— 1 .44 45' .9381101 —]A 1.50 41* .5 45- V XIIN3ddV A 2'3511 .7 .13 NONE •9 .75 45' B I *23510 seed() It SAM POT Oa BOLT IIATCRIAL LETTER Lee Products Engineering Services, Inc. 9 41904.599. NO A f at RR lWeiaw ,O4T m2041,149 4' IV RN Ople u laXONOL5 A23511 .3 $ e ewe enemewei A vitthit° n. sorrow of uomm male. Px,vows now as to O WRAC! OP Oa I* 0 ,11.0401000 • ft wnall Mitt /0 Lai O• sceerAMINITSINSOOVAN.,4114CaiK 61 =0, I %S Henn:- ate ▪ taibic ramighwa Mat Oat la NIL •••0.CCIRO 4.4=95.TolIGHANAVICA UST 091/4TEALIt Rom) ••••••• cosh.Inman dthi %Welt% s Si PMTS. trilats3 a-weans to A Marl' 00.? • OD rSO MOTO3 •" .t.=•••• 00 SOY OCAS •Orr rem an-- SNOOP .00, A .OtanSeli .0.0•04 on elin.ot flange. 4••••• HIM Nat 04.1.1COMO . - • W. eleC• t Iwo. ...Gia✓ worts nt man Ontala STOMP LATCH k:78;;: ft 7 : 1::are els • San 10.11. MIS 1.1100. WA, AST •••• —.CATION PS. of Oat if are palm. tam ASS'Y. A23 511 SMOGS 4 3 2 1 EFTA00011922 U. S. DEPARTMENT OF TRANSPORTATION - t.DA it FEDERAL AVIATION ADMINISTRATION STATEMENT Of COMPLIANCE WITH AIRWORTHINESS STANDARDS 4/23/2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2.MAKE S.MODEL NO. 4.TyPE(4SPIAFt. Engintt Propeler. eta) 5.NAME OF APPLICANT Raytheon 400A Airplane Constant Aviation-CLM . . LIST OF DATA 6.IDENTIFICATION 7,TITLE • Design Data 5254976 Skandia, Inc. Flammability. Test Results Rev NC Bunsen Burner Testing Test Specimen P/N's Cont. 25 (represents main entry door trim) 27 (represents upper med surround) 28 (represents lower med, lower.Med surround, lh aft blkhd) 29 (represents pax seat back shrouds, arms, crash pad) 30 (represents'seat shrouds) 31 (represents entry Steps, cockpit ped step) 33 (represents cntrt coltimn boots, rudder boots) 34 (repreientsckpt defog vent closeout) 35 (represents table shrouds) 36 (represents dado and aircelltloSeout) 39 (represents crew seats) Notes: 1) Work accomplished under Skandia Inc. WO # /54976-13, Ref Document ID 9365(). 2) Flammability tettimitnessing only, does not constitute installation approval of materials. 3) IAW Skandia. Flammability.Streamfine Testing Test Plan 21306, Rev IR, Dated 11/03/11 Page 2 8,PURPOSE OF DATA Demonstration of Compliance with material flammability regtilrenients for S/NRK;244 Q.APPLICAEILE REQUIREMENTS (Llsl specific sections) 14 CFR.Pert 25:853(a) Arndt 25-116 Appendix F Patti (a)(1)(6 Amdt 25-111 14 CFR Pert 25.853 (a)Amdt 25, 116 ApPenflixF Part I (p)(1)(ii) 14 CFR Part 25.855 (d).8met 25-118 Appendix F Part I (6) ., • 10.CERTIFICATION. under authority vested by direction of the Administrator snd in accordance withrOnditione and 5i-ribbons of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered I — -1— have been examined In accordance with established protedures and found to comply with appliCable requirement's of the AinmorthlRess Standards listed.. • I (We) Therefore •,0 Recommend . approval of these data E.w.: Approve these data 11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE %DESIGNATION NUMBER(S) 13.CLASSIFICATION(S) DERV-832780-CE' Structural Special FAA—Form 8110-3 COMO-SUPERSEDES PREVIOUS.EDITION EFTA00011923 I i EFTA00011924 U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMNISTRATION March 25, 2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MOOD- NO. 4. TYPE ~ant Rathq tiolicopfix etc) 5. NAME OF APPLICANT Beechjet 400A AIRPLANE Constant Aviation Cleveland, Ohio UST OF DATA B. IDENTIFICATION 7 ITTI F Document No. DGD-CA08-501 REV: IR ARMREST RH INSTL Dated: 6/13/12 DGD-CA09.101 REV; C DIVAN ASSY Dated: 1/25113 OGD-CA09-101 EO: D-1 DIVAN ASSY Dated: 2/28/13 DGD-CA13-101 REV: IR CARD TABLE ASSY Dated: 2/28/13 DGD-CA14-101 REV: IR LAV CLOSET FRAME MOD Dated: 1/31/13 ------ End of Data --- NOTES: 1. This approval is for Beechjet model 400A (Nextant 400XT variant) SIN RK-244 only. 2. This approval is for the structural design aspects only on the above listed date and does not constitute an Installation approval. 3. Approval is only for regulations specified in the "Applicable Requirements" block. Compliance with additional regulations not listed herein may be required. This form does not constitute FAA approval of all engineering design data for the entire alteration. Additional 8110-3 approvals may be necessary for Damage Tolerance, Flammability, Mechanical Systeme, Electrical, Weight & Balance, as well as other disciplines. 4. For certification basis, refer to TC data sheet No. Al 6SW 5. Structural Approvals are provided separately. 8. PURPOSE OF DATA approval To provide type data fo FAA approval of structure in support of a return to service on S/N RK•244. This is for design data only on a major alteration and is not an Installation approval. 9. APPLICABLE REQUIREMENTS (List specific sections) Amdt 14 CFR Part 25.601 Amdt 25-0, 25.603(a)(b), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0, 25.611, Amdt 25-23, 25.613 (1)(b)(c) 25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (s)(6)(rXdXeX 1) Amdt 25-32, 25.789 Amdt 25.32 limitations of appointment urger 14 CFR 10. CERTIFICATION - Under authority vested by Erection of the Administrator and In acc0rdenCe with conditions and and found to comply Pad 183, data Mod above and on attached sheets numbered N/A have been examined In accordance with established procedures with applicable requirements of the Aknorthiness Standards Listed. ❑ Recommend approval of teem data I (We) Therefore 0 Approve Mese data 12. DESIGNATION NUIABERDIS) 13. Ct scSIFICATION(S) !IlaPRESENTATIVE(S) STRUCTURAL DERT-750135-SW FMForm 8110-3 (03n o)SuPERSEDES PREVIOUS EDITION EFTA00011925 EFTA00011926 13DLG-CON-0325E U.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS March 25, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (AI/plane, Rs:No, HeScepter, at' 5. NAME OF APPLICANT Beechjet 4OOA AIRPLANE Constant Aviation Cleveland, Ohio LIST OF DATA 0 IDENTIFICATION 7 TITI F Document No. DGD-CA01-SS-07 SUBSTANTIATION ANALYSIS of the Intenor on an Hawker Boochcratt 400A Aircraft REV: IR Dated: 3/6/13 ---------- End of Data NOTES: 1. This approval Is for Beechiet model 40DA (Nextant 400XT variant) SIN RK-244 only. 2. This approval Is for the structural design aspects only on the above listed data and does not constitute an installation approval. 3. Approval is only for regulations specified In the "Applicable Requirements" block. Compliance with additional regulations not listed herein may be required. This form does not constitute FAA approval of all engineering design data for the entire alteration. Additional 8110.3 approvals may be necessary for Damage Tolerance, Flammability, Mechanical Systems, Electrical, Weight & Balance, as well as other disciplines. 4. For certification basis, refer to TC data sheet No. A18SW B. PURPOSE OF DATA Structural substantiation In support of FAA Form 337 for aircraft SIN RK-244. This approval is for design data only on a major alteration and is not an Installation approval. 9. APPLICABLE REQUIREMENTS Wit speck sections) 14 CFR Pert 25.30I(Amdt. 25-23), .303IAmdt. 25-23),...30S(s)(b)LAmdt. ES-23)..307lAmdt 25-231,.34t (Arndt. 25-0), .361'Arndt. 25-231, .6011Amdt.25-01, .603(eXb)lArndt.25-381,.605lAmdt.23-01,.609[Arndt.23-0],.611fAmdt.25-231,.613(eXbXc)lAmdl.2S-Ob.625 'Arndt. 25- 23], .785(O(bXc)(d)(e)(BlAmdt. 25-32), .78700iAmdt 25-32),.789lAmdt. 25,32] 10. CERTIFICATION - Under authority vested by direction of the Administrator and In accordance with conditions end Inflations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered _ NA have been examined in accordance with established procedures and found to comply with aPPlicable requkemertS Ot the Any:tininess Standards Listed. . Recommend approval of these date I (We) Therefore g.i Approve these dee !I'M, • • ENTATIvE(S) 12. DESIGNATIoN NUmBERS(S) 13. CLASSIFICATIONS1 DERT-75O135-SW STRUCTURAL FAA Form 8110-3 (mate SUPERSEDES PREVIOUS EDITION EFTA00011927 EFTA00011928 13DLG-CON-0325B V.S. DEPARTMENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADIANISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS March 25, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Aaptano. Radio, Itkopter. ac) 5. NAME OF APPLICANT Beechjet 400A AIRPLANE Constant Aviation Cleveland, Ohio UST OF DATA 6 IDFNTIFICATION 7 TITLE Document No. DGD-CA02.1O1 REV: B RH GALLEY ASSY Dated: 1(25/13 DGD-CA02-501 REV: IR RH GALLEY INSTL Dated: 6/13/12 DGD-CA13-501 REV: IR CARD TABLE INSTL Dated: 12/21/12 DGD-CA13-501 £0: A-1 CARD TABLE INSTL Dated: 2/28/12 DGD-CA04.1O1 REV: IR SIDE LEDGE ASSY Dated: 6/13/12 ------ End ofData --- NOTES: 1. This approval is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only. 2. This approval is for the structural design aspects only on the above fisted data and does not constitute an Installation approval. 3. Approval le only for regulations specified In the "Applicable Requirements" block. Compliance with additional regulations not listed herein may be required. This form does not constitute FAA approval of all engineering design data for the entire alteration. Additional 81104 approvals may be necessary for Damage Tolerance, Flammability, Mechanical Systems, Electrical, Weight & Balance, as well as other disciplines. 4. For certification basis, refer to TC data sheet No. A165W S. Structural Approvals are provided separately. 8. PURPOSE OF DATA To provide type data fo FM approval of structure in support of a return to service on S/N RK-244. This approval Is for design data only on a major alteration and is not an Installation approval. 9. APPLICAI3LE REQUIREMENTS (List spec& sections) 14 CFR Part 25.601 Arndt 25-0, 25.603(004, Amdt 25-38, 25.605 Amdt 25-0, 25.609 Arndt 254, 25.6111 Amdt 25.23, 25.613 (a)(b)(c) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (a)(bXcXdXeXf) Amdt 25-32,25.789 Amdt 2542 10. CERTIFICATION - Under authority vested by direction of the Administraior and in ecoontanee vilth condbons and limitations of appointment under 14 CFR Part 183. date listed Stove and on attached sheets numbered N/A htwo been examined in accordance with established procedures and found to comply with applicable requirements of the Nninwthiness Standards Listed, U Recommend approval of those data I (we) Therefore tlif Approve these data !IMISPRESENTATNE(S) 12. DESIGNATION NUMBERS(S} 13. CLASSIF1CATION(S) DERT-750135-SW STRUCTURAL FM Form 8110-3 (03!10) SUPERSEDES PREVIOUS EDITION EFTA00011929 EFTA00011930 13DLG-CON-0325A U.S. DEPAarruENT OF TRANSPORTATION 1. DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS March 25.2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE 3. MODEL NO. 4. TYPE (Afro/amt. R.d Hata(et. oft) & NAME OF APPLICANT Beechjet 400A AIRPLANE Constant Aviation Cleveland, Ohio LIST OF DATA 6 TIFNTIFiCATKIN 7 TiTLE Document No. OGD-CA01-101 REV: D LH GALLEY ASSY Dated: 3/5/13 000-CA01.101 EO: E-1 LH GALLEY ASSY Dated: 3/6/13 DGD-CA01-501 REV: IR LH GALLEY INSTL Dated: 6/13/12 CGD-CA01-501 EO: A-1 LH GALLEY INSTL Dated: 1/29/13 DOD-CA01-501 EO: A-2 LH GALLEY INSTL Dated: 3/5/13 ----- End of Data ----- NOTES: 1. This approval Is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only. 2. This approval is for the structural design aspects only on the above listed data and does not constitute an Installation approval. 3. Approval is onlyfor regulations specified in the "Applicable Requirements" block. Compliance with additional regulations not listed herein may be required. This form does not constitute FAA approval of ail engineering design data for the entire alteration. Additional 8110-3 approvals may be necessary for Damage Tolerance, Flammability, Mechanical Systems, Electrical, Weight & Balance, as well as other disciplines. 4. For certification basis, refer to TC data sheet No. A16SW S. Structural Approvals are provided separately. 8. PURPOSE OF DATA To provide type data for FAA approval of structure in support of a return to service on S/N RK-244. This approval Is for design data only on a major alteration and is not an installation approval. 9. APPLICABLE REQUIREMENTS (LIN NAOS marina) 14 CFR Part 25.601 Arndt 25-0, 25.603(06), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0,25.611, Arndt 25-23, 25.613 (a)(bXe) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Arndt 25-23, 25.785 (a)(b)(e)(dXeXf) Amdt 25-32, 25.789 Amdt 25-32 10. CERTIFICATION - Under authenly vested by direction of the Administrator end h accordance with comfit:Ins and Imitations of appointment under 14 CFR Pan 183. data 'sled above and on attached sheets numbensd WA have been examined In accordance with astatoshed procedures and found to tarn* with applicable requiroments of the Airworthiness Standards Listed. ❑ Recommend approval al these data I (We) Therefore CE3Approv. these data 1 U RE OF DESIGNAT D ENGiNEERING REPRESENTATNE(S) 12. DESIGNATION NuMBERS(S) 13. CLASSIFICATION(SI CERT-750135-SW STRUCTURAL FAA Form 81104 (03/10) SUPERSEDES PREVIOUS EDITION EFTA00011931 EFTA00011932 Aviation Fabricators n e Clinton, Missouri 64735 Report # AF-475FTP August 09, 2010 Rev (A) Functional Test Procedure for STC # ST01572W1 Hawker Beechcraft Cabin Configuration Applicable Aircraft Model: Hawker Beechcraft 400, 400A EFTA00011933 . . Aviation Fabricators. Inc. AF-475FTP ' 08-0940 Clinton, Missou►i 64735 Rev (A) Page 2 of 4 Revision Log Date Rev Pages Description Approved by 08-09-10 A 1 -Added model 400A G.R. Lowe III -Changed data list # to AF-475MDL EFTA00011934 Aviation Fabricators Inc. Clinton, MO. 64735 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS For Interior Cabin Configurations Document No.: AF-528 Revision "IR" Revision Date: 11121111 Applicable to: Hawker Beechcraft model 400A Modified by FAA STC ST01572WI The information in the Instructions (or Continued Airworthiness is FM accepted material and complies with 14 CFR 25.1529, Instructions for Continued Airworthiness. It supersedes or adds to that provided in the Maintenance Manual for the Hawker Beechcraft 400A Aircraft, only where covered in the items contained herein. For limitations and procedures not contained in the Supplement, consult the Component Maintenance Manual, or other approved airplane data. Page 1of 16 EFTA00011935 aRIFABAt AVIATION FABRICATORS Fax 571 * 00-3 70a Nov 7, 2012 CERTIFICATE OF CONFORMANCE This certifies that Aviation Fabricators, Divan, 3 Place with stowage provisions, Beechjet, part number, 32-0396(A60P)T1≥3.K-02, serial number, 003702, was manufactured in, or determined to be in conformity to anc with approved design data and is in a condition for safe operation for installation on aircraft. Vice-President Aviation Fabricators • Central Airmotive . _ EFTA00011936 ) REVISION PAGE Document Title: Instructions for Continued Airworthiness Prepared By: Todd Ponue Reviewed By: Jeffrey R. Lowe Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of revisions and the effective pages will be listed below. Log of Revisions REV. EFFECTED DESCRIPTION DATE APPROVED NO. PAGE(S) BY All Initial Release 11/21/11 JRL IR Per the requirement of Appendix H of 14 CFR Part 25 paragraph 1-125.1 (c), the changes made to the ICA by the applicant will be distributed via mail by means of paper copy Page 2 of 15 EFTA00011937 ICA Document No.: AF-528 1101011 Revision (IR) Clinton, MO. 64735 Dale: November 21, 2011 TABLE OF CONTENTS DESCRIPTION PAGE REVISION PAGE 2 TABLE OF CONTENTS 3 ABBREVIATIONS AND DEFINITIONS 4 1.0 INTRODUCTION 5 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 9 3.0 DIMENSION AND ACCESS. 11 4.0 LIFTING AND SHORING 11 5.0 LEVELING AND WEIGHING 11 6.0 TOWING AND TAXIING 11 7.0 PARKING AND MOORING 11 8.0 PLACARDS AND MARKINGS 12 9.0 SERVICE INFORMATION 13 10.0 AIRWORTHINESS LIMITATIONS 15 11.0 TROUBLESHOOTING INFORMATION 15 Page 3 of 16 EFTA00011938 1 REVISION PAGE Document Title: Instructions for Continued Airworthiness Prepared By: Reviewed By: Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of revisions and the effective pages will be listed below. Log of Revisions REV. EFFECTED DESCRIPTION DATE APPROVED NO. PAGE(S) BY All Initial Release 11/21/11 JRL IR Per the requirement of Appendix H of 14 CFR Part 25 paragraph H25.1 (c), the changes ) made to the ICA by the applicant will be distributed via mail by means of paper copy Page 2 of 15 EFTA00011939 I c. ICA Document No.: AF-528 Revision (IR) n on, . Date: November 21, 2011 TABLE OF CONTENTS DESCRIPTION PAGE REVISION PAGE 2 TABLE OF CONTENTS 3 ABBREVIATIONS AND DEFINITIONS 4 1.0 INTRODUCTION 5 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 9 3.0 DIMENSION AND ACCESS' 11 4.0 LIFTING AND SHORING 11 5.0 LEVELING AND WEIGHING 11 6.0 TOWING AND TAXIING 11 7.0 PARKING AND MOORING 11 8.0 PLACARDS AND MARKINGS 12 9.0 SERVICE INFORMATION 13 10.0 AIRWORTHINESS LIMITATIONS 15 11.0 TROUBLESHOOTING INFORMATION 15 Page 3 of 16 EFTA00011940 ICA Document No.: AF-528 Revision (IR) n on, MO. 64735 Date: November 21, 2011 ABBREVIATIONS AND DEFINITIONS Abbreviations Definitions AML FAA Approved Model List (AML) Detailed An intensive examination of a specific Item, installation or assembly Inspection (DET) to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an Intensity deemed appropriate. Inspection aids such as mirrors, magnifying tenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required. FAA Federal Aviation Administration FAA MIDO FAA Manufacturing Inspection District Office General Visual A visual examination of an interior or exterior area, installation or Inspection (GVI) assembly to detect obvious damage, failure or irregularity. This level of Inspection Is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the Inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. ICA Instructions for Continued Airworthiness Special Detailed An Intensive examination of a specific Item, Installation , or Inspection (SDI) assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. STC Supplemental Type Certificate Page 4 of 15 EFTA00011941 ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 1.0 INTRODUCTION The purpose of this Maintenance Manual Supplement and Instructions for Continued Airworthiness (ICA) is to provide the maintenance technician with the information necessary to ensure the continued airworthiness of the Aviation Fabricators cabin configuration, per installation number 400-3, when installed in the aircraft passenger cabin in accordance with Aviation Fabricators design data included on Master Data List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI. Modifications to an aircraft obligates the operator to include the maintenance Information provided by this document into the operators aircraft Maintenance Manual and operator's aircraft scheduled maintenance program. This document defines supplementary maintenance operations and frequencies recommended by Aviation Fabricators Inc., to ensure the aircraft's airworthiness. The information contained herein addresses the requirements specified in 14 CFR 25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane Maintenance Manual only in those areas listed as pertains to the installation of divan assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manual. DATA All information to support the continued airworthiness of this modification is contained in: STC ST01572WI. Master Data List: AF-475MDL. Installation: 3 Place Divan (Ref. Installation number 400-3), Installation Instructions D-10666 for P/N 32-0396K-X Parts: P/N 32-0396K-X, 3 Place Divan Installation The new divan assembly (with restraint system) is a self contained complete assembly that mounts to the existing seat track, using standard fittings, in accordance with FAA approved floor plans. The (restraint system) seat belts are attached to the seat track with typical tie down fittings and the inertia reel shoulder harness is bolted to the divan frame on the outboard side using standard aircraft hardware. Design Change Control All data and changes to the parts and assemblies will be tracked per Master Data List AF- 475MDL Rev C or later FM approved revision. Applicable Aircraft Beechjet 400A Page 6 of 16 EFTA00011942 ICA Document No.: AF-528 Revision (IR) Tinton, MO. 64735 Date: November 21, 2011 ABBREVIATIONS AND DEFINITIONS Abbreviations Definitions AML FM Approved Model List (AML) Detailed An intensive examination of a specific Item, installation or assembly Inspection (DET) to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required. FM Federal Aviation Administration FAA MIDO FM Manufacturing inspection District Office General Visual A visual examination of an interior or exterior area, installation or Inspection (GVI) assembly to detect obvious damage, failure or irregularity. This level of inspection Is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of Inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. ICA Instructions for Continued Airworthiness Special Detailed An Intensive examination of a specific item, Installation , or Inspection (SDI) assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. STC Supplemental Type Certificate Page 4 of 15 EFTA00011943 ICA Document No.: AF-528 Revision (IR) Clinton, MO. Date: November 21, 2011 1.0 INTRODUCTION The purpose of this Maintenance Manual Supplement and Instructions for Continued Airworthiness (ICA) is to provide the maintenance technician with the information necessary to ensure the continued airworthiness of the Aviation Fabricators cabin configuration, per installation number 400-3, when installed in the aircraft passenger cabin in accordance with Aviation Fabricators design data included on Master Data List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI. Modifications to an aircraft obligates the operator to include the maintenance Information provided by this document into the operators aircraft Maintenance Manual and operator's aircraft scheduled maintenance program. This document defines supplementary maintenance operations and frequencies recommended by Aviation Fabricators Inc., to ensure the aircraft's airworthiness. The information contained herein addresses the requirements specified in 14 CFR 25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane Maintenance Manual only in those areas listed as pertains to the installation of divan assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manual. DATA All information to support the continued airworthiness of this modification is contained in: STC ST01572WI. Master Data List: AF-475MDL. Installation: 3 Place Divan (Ref. installation number 400-3), Installation Instructions D-10666 for P/N 32-0396K-X Parts: P/N 32-0396K-X, 3 Place Divan Installation The new divan assembly (with restraint system) is a self contained complete assembly that mounts to the existing seat track, using standard fittings, in accordance with FAA approved floor plans. The (restraint system) seat belts are attached to the seat track with typical tie down fittings and the inertia reel shoulder harness Is bolted to the divan frame on the outboard side using standard aircraft hardware. Design Change Control All data and changes to the parts and assemblies will be tracked per Master Data List AF- 475MOL Rev C or later FAA approved revision. Applicable Aircraft Beechjet 400A Page 5 of 15 EFTA00011944 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 3 Place Divan P/N 32-0396K-X (Top not shown for clarity) WWII" WI W>C0.101RR KOT nO MO UMIfI / infa p I falliew II N letWOCOITIAMT ...IVA YAW &W INNrani LOCMOIOISKWIWitatil intOTIA40 I nil FOOT ATTACHMENT TODIVPN rat no A...nova PIX4 "War" NS1nailMINI 'In WC.101/21t Wit* 01 FOOT AlTPCaCENT ...0 CKWIll FOOTA1TACWASIT TO TRACK ISO WAIN,11, Figure 1.0A Page 6 of 15 EFTA00011945 ICA Document No.: AF-528 11.111.11 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 Inertia Reel Attachment DIVAN FRAME NUT WASHER INERTIA REEL BOLT Figure 1.0B Seat Belt Attachment SEAT BELT TIE DOWN FITTING SEAT TRACK REF Figure 1.0C Page 7 of 15 EFTA00011946 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 3 Place Divan P/N 32-0396K-X (Top not shown for clarity) FOOTATTACHMENT TO DIVAN °err TOMMIADAMOICCI >RCS 1.0=Erall FOOT ATTPV0MTMCKWn4 GAP FOOT ATTPCHMENr TOTRICK main AUCOrilt Figure 1.0A Page 6 of 15 EFTA00011947 ICA Document No.: AF-528 Revision (IR) 1 1 1Inton, 101 . 11 473 Date: November 21, 2011 Inertia Reel Attachment Figure 1.0B Seat Belt Attachment Figure 1.0C Page 7 of 15 EFTA00011948 ICA Document No.: AF-528 Revision (IR) n on, MO. 84735 Date: November 21, 2011 SEAT BOTTOM ASSEMBLY NALL auguiousssguiLieugeme Figure 1.0D Page 8 of 15 EFTA00011949 A ti r r ICA Document No.: AF-528 Revision (IR) nton, MO. 64735 Date: November 21, 2011 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 1. To comply with14 CFR 25.1529, continue the new divan assembly (with restraint system) on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for cabin section inspections. a. The new cabin configuration components require no service other than inspection at normal inspection interval of 200 hours. b. The safety belts require no service other than inspection at normal inspection interval of every 200 hours. c. Perform a detailed visual inspection of each passenger seat bottom and back cushions and covering of all cabin interior components to detect apparent or obvious defects or irregularities. On the cushion assembly, check for cracks and punctures within a 4" diameter circle. The cushion assembly can have no more than three defects found within the 4" diameter circle. If a cushion develops a "lump", check to see if there are no more than two lumps within a 4" diameter circle. Any damage to the cushions outside of the described limits will require them to be replaced. Visually inspect the covering assemblies for holes, punctures, and tears. If the damage to the covering is holes smaller than /12 " in diameter or a cut at a maximum of 2" in length then the covering is satisfactory. The sewing of the cover assemblies is not to exceed 1" tearing. Any damage to the covering assemblies outside of the described limits will require them to be replaced. d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and deformation. Damaged conditions could be detected as a crack at the edge of the tube or along the length of the tubes or as a crack, tear or cut found on the seat bottom or back diaphragm. Visually inspect all hardware for excessive wear before and after installation. Replace the seat back and bottom diaphragm if two cracks or deformations are found with a 4" diameter circle. If a tear or cut is found with a maximum of 6", replace the diaphragm. There shall be no broken tubes. There shall be no sharp corners, edges, or protrusions that may Injure passengers. Replace the tubes if they are bent in such a way that they are more than 2" off center. Replace the seat tubes if crack length is found to be .125" or greater. Replace the tube if a dent is found running longer than 3". Replace the seat tubes if deformation is greater than .25" the overall thickness of the tube diameter. Cracked or broken fasteners or fittings are to be replaced with new immediately. Page 9 of 15 EFTA00011950 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64736 Date: November 21, 2011 SEAT BOTTOM ASSEMBLY CUSHION ASSEMBLY REFFRFN0F Figure 1.0D Page 8 of 16 EFTA00011951 A a r ICA Document No.: AF-528 Revision (IR) nton, MO. 4736 Date: November 21, 2011 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 1. To comply with14 CFR 25.1529, continue the new divan assembly (with restraint system) on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for cabin section inspections. a. The new cabin configuration components require no service other than inspection at normal inspection interval of 200 hours. b. The safety belts require no service other than inspection at normal inspection interval of every 200 hours. c. Perform a detailed visual inspection of each passenger seat bottom and back cushions and covering of all cabin interior components to detect apparent or obvious defects or irregularities. On the cushion assembly, check for cracks and punctures within a 4" diameter circle. The cushion assembly can have no more than three defects found within the 4" diameter circle. If a cushion develops a "lump", check to see if there are no more than two lumps within a 4" diameter circle. Any damage to the cushions outside of the described limits will require them to be replaced. Visually inspect the covering assemblies for holes, punctures, and tears. If the damage to the covering is holes smaller than '/Z' in diameter or a cut at a maximum of 2" in length then the covering is satisfactory. The sewing of the cover assemblies is not to exceed 1" tearing. Any damage to the covering assemblies outside of the described limits will require them to be replaced. d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and deformation. Damaged conditions could be detected as a crack at the edge of the tube or along the length of the tubes or as a crack, tear or cut found on the seat bottom or back diaphragm. Visually inspect all hardware for excessive wear before and after installation. Replace the seat back and bottom diaphragm if two cracks or deformations are found with a 4" diameter circle. If a tear or cut is found with a maximum of 6", replace the diaphragm. There shall be no broken tubes. There shall be no sharp corners, edges, or protrusions that may Injure passengers. Replace the tubes if they are bent in such a way that they are more than 2" off center. Replace the seat tubes if crack length is found to be .125" or greater. Replace the tube if a dent Is found running longer than 3". Replace the seat tubes if deformation is greater than .25" the overall thickness of the tube diameter. Cracked or broken fasteners or fittings are to be replaced with new immediately. Page 9 of 16 EFTA00011952 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 For repair or replacement of damaged or broken parts or assemblies contact Aviation Fabricators Inc. 2. Inspection Time Limit for the cabin configuration installations: 200 +1- hour inspection for the new cabin configuration components Task Schedule Date Mech Insp Code AFI-100 a. Inspect for damage to upholstery. AFI-101 b. Inspect safety belts for wear, cuts, fraying, damage, and deterioration. AFI-102 c. Inspect safety belt attachment fittings for wear and damage AFI-103 d. Inspect foot fittings for damage, security, and function. AFI-104 e. Inspect seat frame for damage, and corrosion. AFI-105 f. Inspect overall seat for fit and function. A. The new divan assembly and restraint system are on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for passenger seats. Page 10 of 15 EFTA00011953 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 3.0 DIMENSION AND ACCESS: The installation of this cabin configuration does not change the dimensions of the aircraft or alter the access to any existing aircraft system. 4.0 LIFTING AND SHORING No change. 5.0 LEVELING AND WEIGHING Divan Maximum Allowable Seat Weight = 80 lbs w/ Seat Bottom Upholstery Base Weight of Divan Assembly w/ Restraint System = 50 lbs (includes empty drawer weight) 6.0 TOWING AND TAXIING No change. 7.0 PARKING AND MOORING No change. Page 11 of 16 EFTA00011954 ICA Document No.: AF-528 Revision (IR} non, MO. 64735 Date: November 21, 2011 For repair or replacement of damaged or broken parts or assemblies contact Aviation Fabricators Inc. 2. Inspection Time Limit for the cabin configuration installations: 200 +1- hour inspection for the new cabin configuration components Task Schedule Date Mech Insp Code AFI-100 a. Inspect for damage to upholstery. AFI-101 b. Inspect safety belts for wear, cuts, fraying, damage, and deterioration. AFI-102 c. Inspect safety belt attachment fittings for wear and damage AFI-103 d. Inspect foot fittings for damage, security, and function. AFI-104 e. Inspect seat frame for damage, and corrosion. AR-105 f. Inspect overall seat for fit and function. A. The new divan assembly and restraint system are on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for passenger seats. Page 10 of 16 EFTA00011955 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 3.0 DIMENSION AND ACCESS: The installation of this cabin configuration does not change the dimensions of the aircraft or alter the access to any existing aircraft system. 4.0 LIFTING AND SHORING No change. 5.0 LEVELING AND WEIGHING Divan Maximum Allowable Seat Weight = 80 lbs w/ Seat Bottom Upholstery Base Weight of Divan Assembly w/ Restraint System = 50 lbs (includes empty drawer weight) 6.0 TOWING AND TAXIING No change. 7.0 PARKING AND MOORING No change. Page 11 of 16 EFTA00011956 ICA Document No.: AF-528 Revision (IR) Clinton, O. 84735 Date: November 21, 2011 8.0 PLACARDS AND MARKINGS Three (3) placards are required in conjunction with this modification: 1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be installed in plain view of the seat occupants on the forward divider. LIFE VEST LOCATED IN UNDER SEAT COMPARTMENT PIN 1S•0288 FASTEN SEATBELTANO SMOULDER HARNESS FOR TAXI. TAKEOFF AND LANDING P/N 32-0377-20 Figure 8.0A 2. A placard stating "to install harness over seat occupant's fwd shoulder" is sewn on to restraint system part numbers 3088-7-061-2396 and should be legible and easily viewed by the seat occupant. Figure 8.0B Page 12 of 16 EFTA00011957 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 9.0 SERVICE INFORMATION Typical Passenger Seating Service Instructions: A. Upholstery Cleaning: Service Instructions 1. Remove seat back and seat bottom cushion assemblies from the interior seating components. 2. Clean the cushions in accordance with instructions issued by the company responsible for the upholstery covering so that knowledge of the upholstery material's fire retardant properties are known and will not be compromised. 3. Clean and inspect restraint system for damage, fraying, cuts or seam deterioration. 4. Inspect all attachment fittings and replace if necessary. 5. Inspect overall interior component for fit and function. Typical Maintenance Instructions: Divan Assembly The divans are self contained complete assemblies that mount to the existing aircraft cabin seat track using standard fittings in accordance with approved floor plans. Refer to Figure 1.0A. Divan Installation Installation of the divan requires aligned the feet on the existing seat track and -attaching the divan legs using standard hardware. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Divan Removal Removal of the divan requires loosening the attaching hardware and lifting the divan from its location on the seat track. The feet will be slid forward or aft to the end of the seat track or a gap in the track for their removal. Cushions Seat back and seat bottom cushion assemblies are removed by simply pulling the cushion inboard away from the Velcro on the sidewall or up away from the Velcro on the pan of the divan assembly, respectively. All covering and upholstery materials must comply with 14 CFR 25.853 as stated on the Finish Materials Listing AF-476. The cushion design and layout were determined & manufactured by the seat installer to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for Cushion Assembly Reference for basic assemblies. Page 13 of 16 EFTA00011958 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 8.0 PLACARDS AND MARKINGS Three (3) placards are required in conjunction with this modification: 1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be installed in plain view of the seat occupants on the forward divider. UFE VEST LOCATED IN UNDER SEAT COMPARTMENT PIN 15.0288 FASTEN SEATBELT AND SHOULDER HARNESS FOR TAXI TAKEOFF AND LANDING 35.6 PIN 32-0377-20 Figure 8.0A 2. A placard stating "to install harness over seat occupant's fwd shoulder is sewn on to restraint system part numbers 3088-7-061-2396 and should be legible and easily viewed by the seat occupant. illitaill KIrILIZI nnmrunuu • fOISLROWINIllf Figure 8.0B Page 12 of 16 EFTA00011959 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 84735 Date: November 21, 2011 9.0 SERVICE INFORMATION Typical Passenger Seating Service Instructions: A. Upholstery Cleaning: Service Instructions 1. Remove seat back and seat bottom cushion assemblies from the interior seating components. 2. Clean the cushions in accordance with instructions issued by the company responsible for the upholstery covering so that knowledge of the upholstery material's fire retardant properties are known and will not be compromised. 3. Clean and inspect restraint system for damage, fraying, cuts or seam deterioration. 4. Inspect all attachment fittings and replace if necessary. 5. Inspect overall interior component for fit and function. Typical Maintenance Instructions: Divan Assembly The divans are self contained complete assemblies that mount to the existing aircraft cabin seat track using standard fittings in accordance with approved floor plans. Refer to Figure 1.0A. Divan Installation Installation of the divan requires aligned the feet on the existing seat track and -attaching the divan legs using standard hardware. Refer to Installation Instruction drawing O-10666 for complete installation details and hardware part numbers. Divan Removal Removal of the divan requires loosening the attaching hardware and lifting the divan from its location on the seat track. The feet will be slid forward or aft to the end of the seat track or a gap in the track for their removal. Cushions Seat back and seat bottom cushion assemblies are removed by simply pulling the cushion inboard away from the Velcro on the sidewall or up away from the Velcro on the pan of the divan assembly, respectively. All covering and upholstery materials must comply with 14 CFR 25.853 as stated on the Finish Materials Listing AF-476. The cushion design and layout were determined & manufactured by the seat installer to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for Cushion Assembly Reference for basic assemblies. Page 13 of 16 EFTA00011960 ICA Document No.: AF-528 Revision (IR) Clinton, M0. 647 Date: November 21, 2011 Inertia Reel Inertia reel removal is accomplished by loosening attaching hardware and removing from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.08. Seat Belt Seat belt and removal is accomplished by loosening attaching hardware and removing from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0C. B. RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations and requirements apply to the Aviation Fabricators' interior cabin configuration. Page 14 of 15 EFTA00011961 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Date: November 21, 2011 10.0 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FM approved. There are no new (or additional) Airworthiness Limitations associated with this equipment and /or installation. 11.0 TROUBLESHOOTING INFORMATION Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan installation that is required beyond the information found on the installation drawing D-10666. For replacement pads or repair of damage parts: Contact Aviation Fabricators at Troubleshooting this installation should only be accomplished by FM approved repair stations with the appropriate ratings or appropriately rated operator/individuals, with required test equipment and service data. Page 16 of 15 EFTA00011962 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64736 Date: November 21, 2011 Inertia Reel Inertia reel removal is accomplished by loosening attaching hardware and removing from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0B. Seat Belt Seat belt and removal is accomplished by loosening attaching hardware and removing from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0C. B. RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations and requirements apply to the Aviation Fabricators' interior cabin configuration. Page 14 of 15 EFTA00011963 ICA Document No.: AF-528 Revision (IR) Clinton, MO. 64735 Dale: November 21, 2011 10.0 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FM approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are no new (or additional) Airworthiness Limitations associated with this equipment and /or installation. 11.0 TROUBLESHOOTING INFORMATION Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan installation that is required beyond the information found on the installation drawing D-10666. For replacement parts or repair of damage parts: Contact Aviation Fabricators at Troubleshooting this installation should only be accomplished by FAA approved repair stations with the appropriate ratings or appropriately rated operator/individuals, with required test equipment and service data. Page 15 of 15 EFTA00011964 U. S. DEPARTMENT OF TRANSPORTATION 1.DATE FEDERAL AVIATION ADMINISTRATION $/02/2013 STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2.MAKE 3.MODEL NO. 4.TYPE(AiVane• Engine. PrOplber. etc) 5.NAME OF APPLICANT Raytheon 400A Airplane Constant Aviation-CLM LIST OF DATA 6,IDENTIFICATION 2.TITLE TP 22681 Skandia, Inc. Flammability Test Report Rev A Oil Burner Testing and Vertical Burner Testing Dated 05/02/2013 Notes: 1) Work accomplished under Skandia Inc. WO # 254987-13, Ref Document ID 93685. 2) Flammability test witnessing only, does not constitute installation approval of the materials. 8.PURPOSE OF DATA Demonstration of compliance with material flammability requirements for S/N RK-244 9.APPLICABLE REQUIREMENTS (Ust specific sections) 14 CFR Part 25.853 (a) Amdt 25.116 Appendix F Part I (a)(1)(ii) 14 CFR Part 25.853 (c) Amendment 25-116 Appendix F Part II 10.CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered have been examined in accordance with established procedures and found to comply with applicable requirements of the Ainvorthiness Standards listed. O Recommend approval of these data I ( ) Therefore `?.{ECApprove these data 11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE 12.DESIGNATION NUMBER(S) 13.CLASSIFICATION(S) I ERY-83278O-CE Structural Special FAA Forni 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION EFTA00011965 - EFTA00011966 D Q co a FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE 0 Form Approved O.M.B. No.2120-0018 Expiration Dam 02/28/2013 L. a U.S Deparonen APPLICATION FOR U.S. AIRWORTHINESS INSTRUCTIONS • Print or type. Do net wraci n shaded cent then are for FM use only &lam* colonel only Man aL4hOrited FM Remesentalive If additional a PJ bTrenStaaratten space a reparad, use indented For Wool Pahl permits ccmplete Sections Federal !Mallon CERTIFICATE IL W. and VII as coolIcable. 0 ANnuNarstion I. REGISTRATION NARK 1 ARCRAF I OuiLOER'S NAME Pam/ 3. AIRCRAFT MODEL DESIGNATION 4. YR MFR. FM CODING I. AIRCRAFT N493LX Raytheon Aircraft Co 400A 1999 5. A.RCRAFT SERIAL NO. 6. ENGINE SULZER'S NAME (5 7. ENGINE MODEL DESIGNATION RK-244 Williams International FJ44-3AP DESCRIPTION B. HOMER OF ENGINES 9 PROPELLER BURGERS NAME Plate 10. PROPELLER WOa DESIGNATION It AIRCRAFT IS nentia emmicaan 2 N/A N/A I IMPORT APPUCATION IS HEREBY MADE FOR **a eforese.4...) I A I STA/COMO AIRWORTHINESS CERTiFICATE (woo sematm/ I I 'Knit I I mol l I maeoll I I ^AA"' I I ce's's" . I I Nato' I I ob'm B I SPEOAL AIIMORTFINESS CERTIFICATE cora swoon io•NI 7 PRIMARY 9 LIGHT-SPORT «—t,-, I Inman, I fr oar-Paractsa I_ I Weigi-Stetanved I I Oder !keret Wan Air 2 UNITED 1 CLASS I 5 MORMON/M. 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OR STORAGE SPECIAL FLIGHT PERMIT !MOW. 2 EVACUATE FROM AREA OF IMPENDINGDAN3ER 0440.001b be P:04444084 namaereis OPERATIONIN EXCESS OF MAXIMUM CERTIFICATED TAKECCF HEIGHT 8 S•ex. VI a• vw es 4wecrat el town. lag 3 4 CEUVEMNG OR EXPORTING 16 I I PRODUCTION FIGHT TESTING 6 CUSTOMER DEMONSTRATOR RAMS CI 6 MULTIPLE mRACRTHMESS CERTIFICATE gemMOstainmaid Oessorrarramesser astma,a melema/ A REGETERED OWNER ma sin COIRCIAtt/Intia feifelnii IF DEALER. CHECK HERE--ss I NAME F igh Options LLC Richmond Heights .OH 44143 8 AIRCRAFT CERTIFICATION OASIS tOmm aeons.macs ramemec. ems. a$ evanesce AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA sasEET crass se and AIRWORTHINESS ORECTIVES ensecti444amaessam es ammeemei melee es 4004, i /imamno/ / ano wAD SOOWEAMMT~YAPnes ilsesety same n fl eas al4•044444 N/A Bi Weekly 2013-22 10/21/2013 - 11/03/2013 ft AIRCRAFT LISTWG (Caaeme e. 1003 SUPPLEMENTAL TYPE CERTIFICATE AMranks&lath SIC Acarnembel N/A N/A E at C. AIRCRAFT OPERATION AND WuNTENANCE RECORDS ii CHECK IF RECORDS IN TOTAL AIRFRAME HOURS EXPERIMENTAL ONLY myna., /*wa s" pi ati. saw 1 I COMPUANCE MATH nrage) art, clat91.417 TTAF 8578.62 3 <e 14.82 li 0. CERTIFICATION slant, e•My Malian we mastered caws (or Ns gen° of Ma Mutt dsunbad Raw DIM We Washis rageletinld Yana* Federal Ablation AcireNstralcet In aceardwo6 `IS TIO• 49 al MA Urges Man CRCs 411011St RN WRNS Feel* Aviation Recatatons. SCout the ' alretalhaess canifiona racemrsIed. DATE OF APPUCATON 1 /18/2013 illibila Agent A THE NRCRAFT CESCRO3E0 ABOVE HAS BEEN INSPECTED ANI)FOUNO SCOW/ BY: Crew we NeartstaY 14 CFR pwl 121 CERTIFICATE MADERO" I CERTIFICATED MECHANIC gos Cameos on CERTIFICATED REPAIR STATION (C.• Cfnea• H 2 cantariel 3 6 Ab ) ill 5 AIRCRAFT MANLIFACTURER patesere rem/ i DATE TITLE SIGNATURE tow ALL aeons• MomM.,4 ova) ,s THE CERTIFICATE REQUESTED V. FAA REPRESENTATIVE A. I And Mat re Sand demoted inSan I cc VII mow raparemerts rim 4 /JAEsfwENT CR IAOCCICATICN OF CURRENT MRIACRTHINESS CERTif iCATE avower., for a special not pooh weer Section VII FM INSPECTOR FM DESIGNEE .as conned Dr CERTIFICATE HOLDER UNCER 14 CFR 65 14 CF 121 OR 135 14 II DATE meCOFSDO CERTIFICATION OFFICE 11/16/2013 CLE-25 FAA Form 81304 (4J11) AI P 'anus Editions Stpetseded Electronic Format -PO F RECtIvED DEC 1 a 2013 CLE — 01.22 EFTA00011967 EFTA00011968 A. MAMJFACTURER NAME *OGRESS au i8 9. PRODUCTION SASS (C.hecR makes (MN PRODUCTION CERTS1CATE (Caro induCann can/tka nprnaO t )1 TYPE CERTIFICATE 9 C OTHER C. GM QUANTITY OF CERTIFICATES REQUIRED FOR OFERATIM3 NEEDS DATE OF APPLICATION NAME ANC% TILE (AM or WM SIGNATURE A DESCRIPTION OF AIRCRAFT REGISTERED OANER ADDRESS EIULCIER NON MODEL SERIAL NUMBER REGSTRATION MARK H E. DESCRIPTION OF FLIGHT CuS7CatFR DEMONSTRATION FLIGHTS C) act II ar~e) FROM 70 k VIA DEPARTURE DATE DURATION C. CREW REQUIRED TO OPERATE THE AIRCRAFT AHD ITS EOUPMENT I I PILOT I I COPILOT I ll FUGHT ENGINEER I I O71-IER(Sact/H D. THE AIRCRAFT DOES NOT MEET THE APPUCABLE NRWORTHNESS REQUIREMENTS AS FOLLOWS: • 2 1 O I 2 iZ E. THE FOLLOWINGRESTRICTK)NS ARE CONSIDERED NECESSARY FOR SAFE OPERATION-. (Use onacnrneni a necessary) I g g F. CERTIFICATION • i hereby unly ow $ an roe nagmenal wince Mr his gat 44 the ~all ~abedMoat OW 1119 Wain li tasleffee mil Me Federal Ayaldin ~eleance,In acmrclance rain Tale 49 of me Unted Swiss Code 44101 mag erd applKetae Federal Anegan Resat" and mat roe awal has canins:main arc s saM by MeMN detwited. DATE tom4E AM) TITLE (Peal a lyta) SIGNATURE ir A OPelead Written. nO Mallngs In Cotriplancie Ma 14 CPR anion 919. G. Seamen ol Conaway. FAA Form 81309 (Mach .tenrequWo VII. AIRWORTHINESS AeNtolatile It Foreign Anvorthiness Centation Tor Irian Mend (Meta whenrecl~) a ^Mane Maclied 0CCUMENTATION I FAAltaGNEE I. PnaMme ~eau Cartkam issued a Abadan. WM C. DMA Ortharga ~cgs" em. One& when ~era i le cat agago 21.191 (a) cm conrai attach:di l D. Carat ~IF« aid Enna Wormann Mama in Mcrae us* or*) J. Cunard Pirercaemes Graeae leased in Aacrilence WM E Marx RONK imil Mermen FM Form337 (Meal when ragweed) 1 la caR sock", 21.191 (a) tconschm K. ØØ Alma awns% ol Ccerørecte. FAA Form 60015 (Mach / F. Trn inseam« Recorder, n Aircraft Records whenMON« FM Form 91304 VIII 1) All Previous Eagle SuNKII40400 Electronic Format -PDF Poii• 2 2 EFTA00011969 EFTA00011970 UNITEDSTATESOFAMERICA DEPARTMENT OFTRANSPORTATION .FEDERALAVIATIONADMINISTRATION SPECIAL AIRWORTHINESSCERTIFICATE A CATEGORYIDESIGNATION EVERIEITA. PURPOSE RESEW & COMMENT,,,:A‘ B MANU- NAME /f/VA.J;-,(-1--1;11\ . FACTURER ADDRESS 8d,Nti(Al \'4, ‘ c FLIGHT FROM II/AVM* AI`A TO Iii '11,0 I r, ) \ E' ',.!,! ., n N. 4.91IX III '')-,;v,-- - --n--) SERIAL NO. R-241 u ' BUILDER Raytheon Ater4facip* IA MODEL OA DATE OF ISSUANCE tiorO\ \ Ili /0 ;E:X,FAY Jan 12. 2014 OPERATINGLIMITKONNIPIi1820134t PARTOF THISCERTIFICATE E ' ' li ' DESIGNATION OROFFICENO. DART833943GL Any alteration,reproductionor misuse of this certificatemay be punishableby a fine not exceeding$1,000 or imprisonmentnot exceeding3 years, or both. THIS CERTIFICATEMUST BE DISPLAYEDIN THE AIRCRAFT IN ACCORDANCEWITH APPLICABLETITLE 14, CODE OF FEDERALREGULATIONS(CFR). FAA FORM 5130.7 (MN} SEEREVERSESIDE NSN. 0052.004914000 EFTA00011971 A Thisairworthinesscertificateis issuedundertheauthorityofPublicLaw104.6,49UnitedStalesCode A (USC)44704andTitle14Codeof FederalRegulations(CFR). Theairworthinesscertificateauthorizesthemanufacturernamedonthereverseside0 conduct 0 productionflight!et, andonlyproductionflighttests,ofaircraftregisteredin hisname.Nopersonmay w conductproductionflightestsunderthiscertificate:(1)Cagingpersonsorpropertyforcompensation or hire:and/or0 Carryingpersonsnotessentialto thepurposeof theflight r Thisairworthinesscertificateauthorizesthe flightspecified.onthereversesidefor thepurposeshownin v BlockA, Thisairworthinesscertificatecertifiesthatasof thedateofissuance,theaircraftowhichissuedhas beeninspectedandfoundtomeetherequirements°title applicableCFR.Theaircraftdoesnotmeet therequirementsof theapplicablecomprehensive anddetailedairworthinesscodeasprovidedbyAnnex D 6 totheConventionOnInternationalCivilAvialion.Nopersonmayoperatetheaircraftdescribedonthe reverseside:(1)exceptin accordancewiththeapplicableCFRandin accordancewithconditionsand limitationswhichmaybeprescribedby theAdministratoraspartof thiscertificate;(2)overanyforeign countrywithouthespecialpermissionof thatcountry. Unlessoonersurrendered,suspended,orrevoked,thisairworthinesscertificateis effectiveforthe E durationandundertheconditionsprescribedin 14CFR,Part21,Section21,161or 21.217. EFTA00011972 ' UNITEDSTATESOF AMERICA ' DEPARTMENTOF TRANSPORTATION .FEDERALAVIATIONADMINISTRATION SPECIALAIRWORTHINESSCERTIFICATE A CATEGORY/DESIGNATION ' EXPERIMENTAL MANU• NAME PURPOSE B FACTURER NIA ADDRESS NIA Research and Development p • FROM C FLIGHT TO ON:A \ D N•493LX BUILDER SERIAL NO, RK2 MODEL44 400A 4\\ 0\ EXPIRY MAY12012013 OPERATING DATE 1 1. Raytheon Aircraft Company ARE DATEOFISSUANC PART OF THIS CERTI NomRi2013 E DESIGNATIO OR OFFICE U ATIONS NO, DARF-400148•CE CERTIFICATE Any alteration,reproductiono misuseof this certi ie may be punishableby a fine not exceeding$1,000or IN imprisonmentnot exceeding3 years,or both,THIS MUSTBE DISPLAYEDIN THE AIRCRAFT ACCORDANCEWITHAPPLICABLETITLE14, CODEOFFEDERALREGULATIONS(CFR), FAA Form813P 04120111Nous Edition01104MaybeUseduntilDepleted SEEREVERSESIDENSN:00524493400 EFTA00011973 c A Thisairworthiness certificateisissuedundertheauthorityofPublicLaw104.6,49UnitedSlatesCode n (USC)44704andTitle14CodeofFederalRegulations(CFR). Theairworthiness certificateauthorizesthemanufacturer namedonthereversesidetoconduct productionfighttests,andonlyproductionflightests,ofaircraftregisteredinhisname,Nopersonmay B conductproductionflightestsunderthiscertificate(1)Carryingpersonsorpropertyforcompensation or hire:andlor(2)Carryingpersonsnotessentialtothepurposeoftheflight. ftThisairworthiness certificateauthorizestheflightspecifiedonthereversesideforthepurposeshownin v BlockA. Thisairworthiness certificatecodifiesthatasofthedateofissuance,theaircraftto whichissuedhasbeen inspectedandfoundtomeetherequirements oftheapplicableCFR.Theaircraftdoesnotmeethe requirements of theapplicablecomprehensive anddetailedairworthiness codeasprovidedbyAnnex8 to D theConventionOnInternationalCivilAviation,Nopersonmayoperatetheaircraftdescribedonthe reverseside(1)exceptin accordancewiththeapplicableCFRandin accordancewithconditionsand limitationswhichmaybeprescribedbytheFMaspartofthiscertificate;(2)overanyforeigncountry withoutthespecialpermissionofthatcountry. Unlessoonersurrendered, certificateiseffectiveforthe suspended,orrevoked,thisairworthiness E durationandunderthecondnionsprescribedin 14CFR,Pad21,Section21.181or21.211. EFTA00011974 U.S.Oepartment of Transportation Federal Aviation MO WM 0404140 Ohio 44070 Administration EXPERIMENTAL OPERATING LIMITATIONS For Research and Development (R&D) REG. NO. MAKE: MODEL SERIAL NO: N4931X Raytheon Aircraft Co 400A RK - 244 THESE OPERATING LIMITATIONS SHALL BE ACCESSIBLE TO THE PILOT 1. No person may operate this aircraft unless the FAA Form 8130-7, Special Airworthiness Certificate. is displayed at the cabin or cockpit entrance and visible to passengers or flight crew members. 2. No person may operate this aircraft for other than the purpose of Research and Development to accomplish the flight operation outlined in the applicant's program letter Dated November 13.2013, which describes compliance withl4 CFR 21.193 (d) and made available to the pilot in command of the aircraft In addition, this aircraft shall be operated in accordance with applicable.air traffic and general operating rules of 14 CFR part 91,and all additional limitalionsherein prescribed under the provisions of 14 CFR 91.319 (i). 3. R&D flights must be conducted IAW Nextant Aerospace's Program Letter Dated November 13. 2013, within the geographical area described In the program letter. R&D Rights will be conducted In North America 4. Except for takeoffs and landings, this arcraft must not be operated over densely populated areas or in congested airways. 5. This aircraft must not be operated unless it is maintained and Inspected in accordance with the appropriate military technicalpublIcations and/a manufacturer's recommendation. The owner/operator must select, establish, identify, and use an inspection program set forth in 14 CFR 91.409 (e), (f),(g), and (h). This inspection program must be recorded in the aircraft maintenance records. 6. The Pilot In Command of this aircraft must hold an appropriate category/Gass rating. If required for the type of aircraft to be flown, the Pilot In Command also must hold either an appropriate type rating or a Letter of Authorization issued by an FM Flight Standards Operations Inspector. 7. This aircraft may be operated under VFR, day and/or night. 8. The Aircraft may be operated under IFR, and must be properly equipped for instrument flight in accordance with 14 CFR 91.205. 9. No person may operate this aircraft for carrying persons or property for compensation or hire. 10. No person may be carried in this aircraft during flight unless that person is essential to the purpose of the flight. 11. The Pilot In Command of this aircraft must advise each passenger of the experimentalnature of this arcraft, And explain that It does not meet the certification requirements of a standard certified aircraft. • 12. This Aircraft must contain the Beech Model 400A Flight Manual with Nextant 400XT AFM Section Insert, Placards, markings, etc. (or other operating instructions developed for an STC modification), as required by14 CFR 91.9. 13. This Aircraft is Prohibited from Aerobatic Flight , that is an Intentional Maneuver involving an Abrupt change in the Aircrafts attitude, an abnormal attitude, or abnormal acceleration not necessary for normal flight, unless part of show compliance flight testing 14. This aircraft shall not be used for glider towing, banner towing, or intentionalparachute jumping. Page 102 EFTA00011975 EFTA00011976 of Transportation Federal Aviation Administration 15. No person shall operate this aircraft unless within the preceding 12 Calendar months it has had a condition inspection performed in accordance with 14 CFR Part 43, appendix D,or other FAA approved programs, and was found to be in a condition for safe Operation. This inspection will be recorded in the aircraft maintenance records. 18. FAA•certificated Repair Stations and FM - Certified mechanics with appropriate ratings, as authorized by 14 CFR 43.3 may perform inspections required by these limitations. 17. Inspections shall be recorded in the aircraft maintenance records showing the following or a similarly worded statement: "I certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of 14 CFR part 43, appendix D,or other FAA approved programs and found to be In a condition for safe operation." The entry will Include the aircraft's totaltime-in-service, and the name, signature, certificate number, and type of certificate held by the person performing the inspection. 18. If the aircraft, engine, or propeller operating limitations are exceeded, an appropriate entry will be made In the aircraft records. 19. This aircraft must not be operated unless it is maintained and inspected in accordance with the requirements of 14 CFR Part 43. 20. This aircraft must display the word `EXPERIMENTAL"In accordance with 14 CFR 45.23(b). 21. The Pilot In Command of this aircraft must notify air traffic control of the experimental nature of this aircraft when operating into or out of airports with operating control bra The Pilot In Command must plan routing that will avoid densely populated areas and congested airways when operating VER. 22. This aircraft does not meet the requirements of the applicable, comprehensive, and detailed AInvorthIness code as provided by Annex 8 of the International Convention of Civil Aviation. The Owner/Operator of this aircraft must obtain written permission from another country's Civil Airworthiness Authority (CAA) prior to operating this aircraft in or over that country. That written permission must be carried aboard the aircraft together with the U.S. airworthiness certificate and, upon request, be made available to an FAA inspector or the CAA in the country of operation. 23. Aicraft instruments and equipment installed and used under 14 CFR 91205 must be inspected and maintained in accordance with the requirements of 14 CFR parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the Aircraft Maintenance records. 24. Application must be made to the geographically responsible FSDO or MO for any revision to these operating limitations. 25. 14 CFR 47.45 requires that the FM Aircraft Registry must be notified within 30 days of any change it the aircraft registrant's address. Such notification Is to be made by submitting Aeronautical Center Form 8050-1, Aircraft Registration Application, to AFS•750 in Oklahoma City, OK. 26. Condition Inspections must be performed in Accordance with 14 CFR Part 43 Appendix D at least every 100 Hrs Flight Hours. This Inspection must be performed by an FM Certified Mechanic with the Appropriate Ratings as deemed in 14 CFR. 43.3 27. The Special Airworthiness Certificate and Operation Limitations will eerie on. Jan 12.2014 Designated Airworthiness Representative DART833943GL Issued at Cuyahoga Airport Date Issued: November18 2013 Page 2 c42 EFTA00011977 EFTA00011978 nextant aerospace Quality Assurance Department To: Federal Aviation Administration Date: November 13, 2013 Flight Standards District Office North Olmsted, Ohio 44070 From: Chief Inspector Nextant Aerospace Subject: FAA Program letter for Beech let 400A, Serial number RK-244, Registration Number N493LX. Ref: FAA order 8130.2G 1. Registered Owner: Flight Options LLC. Address: Richmond Heights, Ohio 44143 2. Aircraft Description: Twin Engine Light let a. Registration: N493LX b. Aircraft Builder Raytheon Aircraft Co c. Year mfg.: 1999 d. Aircraft Serial Number: RK-244 e. Aircraft Model Designation: Beech Jet 400A 3. The program purpose for the aircraft will be used To complete the flight performance profile in Research & Development Category in support of FAA Project SA 152501A-7 (Replacement of Wingtips) 4. Program Duration a. List the estimated flight hours required for program: 20 Hrs b. Number of flights: 20 c. Number of days: 60 S. Describe the areas over which the flights to be conducted and address of base operation: The base of operation is Cuyahoga County Airport, 355 Richmond, Cleveland, Ohio. Flights will be conducted in North America. 6. Describe the aircraft configuration: This Aircraft is a standard Beech let 400A with new Williams F144-3AP engines and upgraded avionics with full authority digital engine controls (FADEC) a. Maintenance Program 1. Hawker Beechcraft Maintenance Manual Chapter 5 Rev C22 or later with the exception of the .1115D Engines. 2. Williams International recommended FJ44 3A Maintenance manual (FADEC maintenance is covered in 71.00.00 of this manual) 3. Maintenance Requirements for the Throttle Quadrant is addressed in the Instructions for Continued Airworthiness on the FJ44-3AP STC. Nextant Aerospace 202 A Tel Work Cell '4'Spt& EFTA00011979 EFTA00011980 Cleveland. Ohio 44143 aLitOptions November 13, 2013 Nextant Aerospace, LLC Cleveland, Ohio 44143 Attention: Re: RK-244 — Agent Authorization To whom it may concern: This letter is to confirm that Flight Options, LLC (TO") authorizes Nextant Aerospace, LLC, as FO's agent, for a Beechjet 400A, bearing serial number RK-244 and FAA Registration Number N493LX (also identified as a "Nextant 400XT'), which is owned by FO, for any and all authorized FAA actions in regards to: X Airworthiness Classification Experimental Airworthiness Classification Standard Sincerely, Flight Options, LLC By: Vice President, Administration & Contracts EFTA00011981 :I•1A1 1: • EFTA00011982 FAA FORM 1030-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Fpm Approved O.M.O. No. 2120-0018 Expiration Date 02/28/2013 aU.S. Cepartmem APPLICATION FOR U.S. AIRWORTHINESS INSTRUCTIONS • Prim or Iwo Do nol rote in shaded arms; Mese are for FAA molly. Sutom cripnal otmr a en eufacrized FM Repfeientatne. If edclOomil a Transponaton Space is motive& use ailachnent. For special IIHM permits complete Sections Federal Aviation CERTIFICATE H. A. and Alas applicable Adirealsrratioe I REGISTRATION MARK 2. AIRCRAFT MOLDERS NAME mum 3. AIRCRAFT MOOELDESGNATION 4. YR MFR. FM COOING e N493LX Raytheon Aircraft Co 400A 1999 t 0 * r 5 AIRCRAFT SERIAL NO. S ENGINE BUILDER'S NAME Ago.) 7. ENGINE MODEL OESIGNATION gi RK244 Williams International FJ44.3AP • 8. NUMBER OF ENGINES 9 PROPELLER BUILDERS NAME MAN ID PROPELLER MOOEL DESIGNATION II. AIRCRAFT IS farm moomsam 2 N/A N/A IMPORT APPUCATION IS HEREBY MACE FOR. Momoorrim on) I A l STANDARD NROORTIMIESS CERTIFICATE roses *wpm Hama Honor, I I I I roarrem I [morn. Hamm. I lona 8 re SPECIAL MFMORTICESS CERTINCATE Moo refierme Arm/ 7 PRIAMM 9 UGHT-SPCRT limas Caw I IN/Hanel I loompParadue I I WeIgHtellarotrc4 I 1 Cider I I Utter Mari M 2 UNITED 1 CLASS 5 PROVISIONAL Room oleo 2 CLASS II 1 AGRICULTURE AND PEST CONTROL 2 AEFOAL SURVEY 3 AERIM.A0VERMING ig 3 RESTRICTED Mcrae 4 5 PATROLLING 6 HEATHER CONTROL to 44 <40:1•000) FOREST 0$0.4 ten."4"; ubrr 0 OTHER (40/4240 g I I RESEARCH AND CEVELCPMENT 2 AMATEUR BUILT 3 EXHH/TION 4 AIR RACING S CREW BINNING 6 MARKET SURVEY 0 TO SHOW COMPLIANCE VAN THE CFR 7 OPERATING Morro Crown KIT MKT AIRCRAFT I OA EMOTE aMmill*Mota an armorinns cortfale II 00 nol noel 6103.1 4 EXPERIMENTµ nmcompramoN get rem romum e OPERATIC 58 OPROUBUDIGpoil Kt-tun UGHT4PC111 u ec OPTION 1911-sped HICAPIT *PAP WOO 5911-spat allegory almannona a cerMeate untie 621.190 UMMNMED 9A RESEARCH AND DEVELOPMENT ICI I CREW TRAINING 9 AIRCRAFT 96 MARKET SURVEY I FERRY FLIGHT FOR REP...MS.ALTERATION& MAINTENANCE CR STORAGE SPEOAL FLIGHT PERMIT mops 2 EVACUATE FROM AREA OF IMPENDING DANGER wersoo re re mower oaf ammo OPERATION IN EXCESS OF MAXJMUM CERTIFICATED TAKEOFF WEIGHT 8 mom me. oval motes* inform HIN 3 4 DEUVERING OR EXPORTING I 5 I I PROCUCTIONCL4HT TESTING 6 CUSTOMER CEMONSTRATIONFUGHTS CI 6 MULTIPLE AIRWORTHINESS CERTIFICATE KAM MOM Moron Oiwatim on lanOwe a bile•raniffitaal A REGISTEREDCOTNER Hs was , mita a rose nommor IF DEALER. CHECK HERE o I NM* F ight Options.LLC Flight Options LLC , Richmond Heights .OH 44143 B AIRCRAFT CERTIFICATION 8ABG rtmempoommuar mamma Sr, n **gat AIRCRAFT SPECIFICATION CR TYPE CERTIFICATE DATA SHEET rom rie ma ACVORTMNESS ORECTIVES (Owl delloWeormOs ii• erreraloomeerwmormeree A•VOiLl ion 1 AD Si,. -Van. 'VW miss If or o mmymno O ordinee as W itooleeerf N/A Bi-Weeky 2013-09, 04/22/2013 - 05/05/2013 i NRCRAFT LISTING (G.........e.nw SUPPLEMENTAL TYPE CERTIFICATE ON east elnen Sit N/A N/A § is C. NRCRAFT OPERATION MID MAINTENANCE RECORDS CAECK IF RECORDS IN TOTAL AIRFRAME CURS EXPERIAMMTAL ONLY oa gmmeem f same resimaimmoray COMPLIANCE WIN 3 Pommel 14 CFR maion 91.417 8563.80 i D. CERTIRCATION - Mersey wiry Minim Me regtsond maw (of Pis mere) of fl ame deemed atom out me a cart is roomers wfl um Femme miafion Auffirientlen In accordant* am Title 49 of to vow Stain Coo:lan), rt)aa and swears Feciend Amato Regutataro and mat lie wenn has Wen is eimilby WV* aP* MoKorinests cenlftele DATE OF APPLICATION 05/13/2013 A THE AIRCRAFT OESCREIEDMIOVE § § 2 Iii CFR =121 CERTIFICATE HOLDEROm I al 'CERTIFICATED MECRANICIG•• Gesture no, I 0 I I CERTIFICATED REPAIR STATION min comm. u i AIRCRAFT MANUFACTURER (ava nava weary 5 qe 5 DATE I WILE I SIGNATURE a ttatax rt Awns taco HMO A Mee) THE CERTIFICATE REQUESTED A. I lino Mal ins Wine dilated In Salon Ice VII meets refoiterrors to 14 MIENINENT OR MODIFICATION OF CURRENT NRW3RTHWESS CERTIFICATE ; (I A B. IrdPr-Sen Tor a Medial WY pWT1 Lwow Sprain VII FM INSPECTOR FM DESIGNEE was conducted by. I A, " DATE MICOSSOO 5 OFFICE fl /1400/40 ct-91T 4 u FAA Fern 81304 (4/11) Al Preview Etna Superseded Msdronic Tama -POF Page 1 o12 EFTA00011983 r EFTA00011984 A. MANUFACTURER NAME ADDRESS VI. PRODUCTION Et PRODUCTION BASIS (CAM M0MS* amp FLIGHT TESTING PRODUCTION CERTIFICATE 1Gw Skis cetelicettinai) .. TYPE CERTIFICATE OTHER C. GIVE OLLANNTY OF CERTIFICATES REWIRED FOR OPERATING NEEDS DATE OF APPLICATOR I NAME ANO TITLE (PAM MK*) SIGNATURE A DESCRIPTION OF MRCRAFT REGISTERED OWNER ADDRESS BUIDER (444/g) MODEL SERIAL NUMBER REGISTRATION MARK B. DESCRIPTION OF RIGHT CUSTOMER DEMONSTRATION FLIGHTS CI COMM arpiest, VLL SPECIAL. ruGHT PERMIT PURPOSES OTHER THAN PRODUCTION WONT TEST FROM TO VIA OEPARTURE DATE DURATION G CREW REWIRED TO OPERATE THE MRCRAFT ANDITS EOUIPMENT I I PILOT I i COPILOT I I FLIGHT ENGINEER I I oTHERmixtoM O. THE AIRCRAFT DOES NOT MEET THE APPLICABLE ARWORTHWESS REOUREMENTS AS FOLLOWS: E TIE FOU.OWNO RESTRICTIONS ARE CONSIDERED NECESSARY FOR SAFE OPERATOR Ma artaconenr.r moues) F. CERTIFICATION • 1 nints own& ita I inn ronmerse comer (or PM onov) ol to ICS emoted sten TM et glenA Is recitietedweh re Feces& Aeatt:c AOrtmusilon In KC0nlarballMI. TIN 49 d Me UMW gabs Cods 44101 AM Old Opplane F.dfl ANSIRegal** anent Os eaten ras omen (Assam AN o d. b. so fir easerisol DATE NAME AND TITLE (HMI Or Wee SIGNATURE cam Unallons end Morkims In Complisnes W0114 CFR Seclion 919. EL Stammers of CoMonons, FAA Fpm 8,30.9 (Attach twee i 'Quince a "°°"" m Apro )t Forolr Akoortinom Owilkslon fix loomNana 3 4.4 man Atm' rogue') ..4 g Y El. Curia Camel° Lieritefens Aliened 3_ I Ewa* Mvoltenrs semen Ai Accordsnas Win E tf c oga. Dr.&Arcs. 12744O3rXim. etc lath rinuiroal X 14 CFR SICEcti hi. 3 a) CAR (EloGolM(mown i ll 1 D. Omen: weiM re4 BOOM Ink/motion Awilatle in Aktran At z ..%). J Carp' ANAIEhnenCe.SMSIved in AtEcedanCe Wm V E. Majot Eepal and Minton. FAA Form 337 (ARM MenIMMO Iv Id CFR Swim 2.I.Fit (of 1 (Cary Onto* ic F. Ms iromraon Ftscanol In Moan Recant N. UV-Sport Alrcret SUOMMI ciCarolarcoo. FM Form 813013 Mach Men nequeed) FAA Form 61304 (4111) MI Pnwians Edlli0ni gnomons(' Eiscimoic Formal -POF Page 2 of 2 EFTA00011985 EFTA00011986 UNITEDSTATESOFAMERICA DEPARTMENT OFTRANSPORTATION • FEDERALAVIATIONADMINISTRATION SPECIALAIRWORTHINESSCERTIFICATE A CATEGORY/DESIGNATIONEXPERIMENTAL PURPOSE Research and Development MK. NAME NIA st a FACTURER ADDRESS NIA FROM et C FLIGHT TO ,, D N. 4931,X SERIALNO.RK244 BUILDER Raytheon Company MODEL OA DATEOFISSUANCE mAymoi3 EXPIRY NOV11612013 OPERATINGLIMITATIONSDATE AREPARTOFTHISCERTIFICATE E DESIGNATIONOROFFICENO. DARF-400148•CE Any alteration,reproductionor misuseof this cerii cafemay be perishableby a fine not exceeding$1,000or imprisonmentnot exceeding3 years,or both.THISCERTIFICATEMUSTBE DISPLAYEDIN THEAIRCRAFT IN ACCORDANCEWITHAPPLICABLETITLE14, CODEOFFEDERALREGULATIONS{CFR), FAAForm 8130.1(4412011)PreviousEdition01104MaybeUsedold Depleted SEEREVERSESIDENSM 0052.00.693.4000 EFTA00011987 A Thisairworthiness certificateis issuedundertheauthoriryofPublicLaw104.5,49UnitedSlatesCode PI (USC)44184andTile14CodeofFederalRegulations(CFR). Theairworthinesscertificateauthorizesthemanufacturer namedonthereversesidetoconduct fightests,andonlyproductionlight tests,ofaircraftregisteredinhisname.Nopersonmay D production w conductproductionflightestsunderthiscertificate(1)Carryingpersonsor propertyforcompensation or hire:andfor(2)Carryingpersonsnotessentialtothepurposeofthenight. r Thisairworthiness certificateauthorizesthelightspecifiedonthereversesideforthepurposeshownin v BlockA, Thisairworthinesscertificatecertifiesthatasofthedaleofissuance,theaircraftto whichissuedhasbeen inspectedandfoundtomeetherequirements oftheapplicableCFR.Theaircraftdoesnotmeethe requirements oftheapplicablecomprehensive codeasprovidedbyAnnex8 to and detailedairworthiness D theConventionOnInternationalCivilAviation.Nopersonmayoperatetheaircraftdescribedonthe reverseside(1)exceptin accordance withtheapplicableCFRandinaccordancewithcondonsand limitationswhichmaybeprescribedbytheFM aspadofthiscertificate;(2)overanyforeigncountry withoutthespecialpermissionof thatcountry, c Unlessoonersurrendered,suspended, ofrevoked,thisairworthiness certificateiseffectiveforthe in durationandundertheconditionsprescribedin14CFR,Part21,Section21.181or21.217. EFTA00011988 mato STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY NC 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERIAL 4 CATEGORY REGISTRATION MARKS NUMBER Raytheon Aircraft Co. N493LX 400A RK-244 Transport 5 AUTHORITY AND BASIS FOR ISSUANCE This eawonhasess cenAcate is issued pagan to the Federal Avtation Ad of 19SI) and cents, the, es a the date of deemd& the simnel to shish weed Ms been inspected and found to conleem to the type corshcato Monitor, to be In condbon to safe operation and has been enhan to rneel the re:we-rents of the applicable comprehensive and detailed einvonNness code as prove:kid by Anneal° the Convention on Intemallenal CM AWtbn• except as noted lea Escepbons: None TEWASANO CONDITIONS Unless sooner stnendered. suspended. teroked. at a terrnInahcn data N othanvise establoshect by the Adadnistrelor. this einirenhiness Cette:000 b elleCIMI BO Bee es the maintenance. preventatse men•Mend. and alterations are Paired In adadane *RI Fans 2I. 43. and 91 of Me Fathom, A registered Yl Sr UMW States. DATE OF ISSUANCE DESIGNATION NUMBER R 10/01/1999 AEA-FSCO-23 My Menlo% repoduceon. a Meese of Ithoelitcate may be paetheble Menne not exceeding SIAM et lepreonmeini not 11$014.910 3 semisweet. THIS CERTIFICATE MUST BE DISPLAYED M THE SAGAMI IN ACCORDANCE tMTH AMICABLE FEDERAL AVIATION REGULATIONS. FAA Farm 4100-2 (108) EFTA00011989 - EFTA00011990 Cleveland, Gala 44143 eit Options May 8.2013 VIA HAND DELIVERY Nextant Aerospace, LLC Cleveland, Ohio 44143 Attention: Re: RK-244 — Agent Authorization Ladies and Gentlemen: This letter is to confirm that Flight Options. LLC ("Flight Options") authorizes Nextant Aerospace, LLC, as Flight Options' agent, for a Beechjet 400A, bearing serial number RK-244 and FAA Registration Number N493LX, which is owned by Flight Options, for any and all authorized FAA actions. Sincerely. FLIGHT OPTIONS LLC Vice President of Whole Aircraft Acquisitions and Sales STATE OF OHIO tty Camm. ExpteS APIS a 2016 511-41.3 EFTA00011991 EFTA00011992 U.S. Department of Transportation Federal Aviation Administration EXPERIMENTAL OPERATING LIMITATIONS PURPOSE Research and Development Raytheon Aircraft MAKE MODEL 400A Company SERIAL REGISTRATION N493LX RK244 NUMBER I ) No person may operate this aircraft unless FAA Form 8130-7 is displayed at the cabin or cockpit entrance and is visible to passengers or flightcrew members. 2) No person may operate this aircraft for other than the purpose of RESEARCH AND DEVELOPMENT to accomplish the flight operation outlined in the program letter, dated May 13, 2013, which describes compliance with 14 CFR §21.193(d) and has been made available to the pilot-in-command of the aircraft. In addition, this aircraft must be operated in accordance with applicable air traffic and general operating rules of 14 CFR Part 91, and all additional limitations herein prescribed under the provisions of 14 CFR § 9I.319(i). 3) All flights must be conducted within the 48 contiguous United States of America, except for takeoffs and landings, this aircraft must not be operated over densely populated areas or in congested airways except when otherwise directed by Air Traffic Control or in an emergency situation. 4) N/A 5) N/A 6) N/A 7) This aircraft must not be operated unless it is inspected and maintained in accordance with appropriate military technical publications and/or manufacturer's recommendations. The owner/operator must select, establish, identify, and use an inspection program as set forth in 14 CFR §91.409(e), (0, (g) and (h). This inspection program must be recorded in the aircraft maintenance records. 8) The Pilot in Command of this aircraft must hold an appropriate category/class rating. If required for the type of aircraft to be flown, the Pilot in Command must also hold either an appropriate type rating or a letter of authorization issued by an FAA Flight Standards Operations Inspector. 9) N/A 10) N/A II) This aircraft may be operated under IFR, and must be properly equipped for instrument flight in accordance with 14 CFR § 91.205. All test maneuvers must be conducted during day Visual Meteorological Conditions (VFR). 12) No person may operate this aircraft for carrying persons or property for compensation or hire. 13) No person may be carried in this aircraft during flight unless that person is essential to the purpose of the flight. 14) N/A 15) The pilot in command of this aircraft must advise each passenger of the experimental nature of this aircraft, and explain that it does not meet the certification requirements of a standard certificated aircraft. 16) This aircraft must contain the placards, markings, etc., (or other operating instructions developed for an STC modification) as required by 14 CFR §91.9. Total Pages: 3 EFTA00011993 EFTA00011994 EXPERIMENTAL OPERATING LIMITATIONS PURPOSE Research and Development Raytheon Aircraft MAKE MODEL 400A Company SERIAL REGISTRATION N493LX RK244 NUMBER Page 2 of 3 17) This aircraft is prohibited from aerobatic flight; that is, an intentional maneuver involving an abrupt change in the aircraft's attitude, an abnormal attitude, or abnormal acceleration not nectssary for normal flight. I 8) This aircraft may conduct acrobatic flight in accordance with 14 CFR § 91.303. Aerobatics must not be attempted until sufficient flight experience has been gained to establish that the aircraft is satisfactorily controllable and in compliance with 14 CFR § 91.319(b). Acrobatic maneuvers intended to be performed must be satisfactorily accomplished and recorded in the aircraft records during the flight test period. I 9) N/A 20) This aircraft must not be used for glider towing, banner towing, or intentional parachute jumping. 21) No person must operate this aircraft unless within the preceding 12 calendar months it has had a condition inspection performed in accordance with the scope and detail of 14 CFR part 43 appendix D, or other FAA- approved programs and was found to be in a condition for safe operation. This inspection will be recorded in the aircraft maintenance records. 22) FAA-certificated repair stations and FAA-certificated mechanics with appropriate ratings as authorized by 14 CFR §43.3 may perform inspections required by these operating limitations. 23) Inspections must be recorded in the aircraft maintenance records showing the following or a similarly worded statement: "I certify that this aircraft has been inspected on (insert date) in accordance with the scope and detail of 14 CFR part 43, appendix D, or other FAA-approved programs, and was found to be in a condition for safe operation." The entry will include the aircraft total time-in-service, and the name, signature, certificate number and type of certificate held by the person performing the inspection. 24) If aircraft, engine, or propeller operating limitations are exceeded, an appropriate entry will be made in the aircraft records. 25) This aircraft must not be operated unless it is maintained and inspected in accordance with the requirements of 14 CFR Part 43. 26) This aircraft must display the word EXPERIMENTAL in accordance with 14 CFR §45.23(b). 27) The pilot-in-command of this aircraft must notify Air Traffic Control of the experimental nature of this aircraft when operating into or out of airports with operating control towers. The pilot in command must plan routing that will avoid densely populated areas and congested airways when operating VFR. 28) This aircraft does not meet the requirements of the applicable, comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention on International Civil Aviation (ICAO). The owner/operator of this aircraft must obtain written permission from another country's Civil Airworthiness Authority (CAA) prior to operating this aircraft in or over that country. That written permission must be carried aboard the aircraft together with the U. S. airworthiness certificate, and upon request, be made available to an FAA inspector or the CAA in the country of operation. 29) Aircraft instruments and equipment installed and used under 14 CFR §91.205 must be inspected and maintained in accordance with the requirement!: of parts 14 CFR parts 43 and 91. Any maintenance or inspection of this equipment must be recorded in the aircraft maintenance records. 30) Application must be made to the geographically responsible MIDO (Cleveland, OH MIDO) for any revision to these operating limitations. 31) 14 CFR § 47.45 requires that the FAA Aircraft Registry must be notified within 30 days of any change in the aircraft registrant's address. Such notification is to be made by submitting Aeronautical Center Form 8050-I to AFS-750 in Oklahoma City, Oklahoma. 32) Condition inspections must be performed in accordance with 14 CFR part 43, appendix D at least every 100 flight hours. The inspections must he performed by an FAA-certificated mechanic with appropriate ratings as definntl in 14 r.pp x dl EFTA00011995 EFTA00011996 EXPERIMENTAL OPERATING LIMITATIONS PURPOSE Research and Development Raytheon Aircraft MAKE MODEL 400A Corn . any SERIAL REGISTRATION N493LX RK244 NUMBER Page 3 of 3 33) Familiarization flights must be conducted only over sparsely populated areas. If aerobatics are involved, the applicant must inform the local FAA office and additional limitations may be imposed as necessary. III.igna u e DARF-400148-CE May 20.2013 EFTA00011997 . EFTA00011998 nextant aerospace Quality Assurance Department To: Federal Aviation Administration Date: May 13, 2013 Flight Standards District Office North Olmsted, Ohio 44070 From: Director of Quality Assurance Nextant Aerospace Subject: FAA Program letter for Beech Jet 400A, Serial number RK244, Registration Number N493LX Ref: FAA order 8130.2G 1. Registered Owner: Flight Options RC . Address: Richmond Heights, Ohio 44143 2. Aircraft Description: Twin Engine Light Jet a. Registration: N493LX b. Aircraft Builder Raytheon Aircraft Co c. Year mfg.: 1999 d. Aircraft Serial Number: RK244 e. Aircraft Model Designation: Beech let 400A 3. The program purpose for the aircraft will be used To complete the flight performance profile in Research & Development Category in support of FAA Project SA 15250LA-T (Replacement of Wingtips) 4. Program Duration a. List the estimated flight hours required for program: 300 Hrs b. Number of flights: 100 c. Number of days: 180 S. Describe the areas over which the flights to be conducted and address of base operation: The base of operation is Cuyahoga County Airport, 355 Richmond, Cleveland, Ohio. Flights will be conducted in North America. 6. Describe the aircraft configuration: This Aircraft is a standard Beech Jet 400A with new Williams F144-3AP engines and upgraded avionics with full authority digital engine controls (FADEC) a. Maintenance Program 1. Hawker Beechcraft Maintenance Manual Chapter S Rev C22 or later with the exception of the 1T150 Engines. 2. Williams International recommended F144 3A Maintenance manual (FADEC maintenance is covered in 71-00-00 of this manual) 3. Maintenance Requirements for the Throttle Quadrant is addressed in the instructions for Continued Airworthiness on the F144-3AP STC. enior Inspector Nextant Aerospace EFTA00011999 . . • • EFTA00012000 LOG BOOK ENTRY from Designated Airworthiness Representative (DAR) REGISTRATION AIRCRAFT SERIAL No. TT/TSN LANDINGS/CYCLES NUMBER MAKE/MODEL • Raytheon Aircraft Company RK244 N493LX 8563.8 7115 400A I find that the aircraft meets the requirements for the certification requested and have issued a Special Airworthiness Certificate dated May 20, 2013 for the purpose of Research and Development. Limitations dated May 20. 2013 and issued with this certificate must be complied with. The aircraft must be maintained in accordance with manufacturers requirements unless another FAA approved maintenance program is utilized. Issuance of this certificate does not eliminate or replace any required maintenance requirements. The Special Airworthiness Certificate has been issued as required to support Research and Development flight-testing as defined in/th app icant's program letter. The Standard Airworthiness Certificate dated R 19p111999 has been superseded. 4/5/ 20 2.013 Date EFTA00012001 EFTA00012002 Foon Soo/own Electronic Tracking Number OW) No 2120-0O20 le MAJOR REPAIR AND ALTERATION itsodusi u 5 Oesenrnont or • Trantpeeltavan lAcINal Aviation Achninilanakai (Airframe, Powerplant,Propeller, or Appliance) For FAA Use Only INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B, and AC 43.91 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty nor to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1958) NatiOnality and Registration Mark Serial No RK-244 N493LX 1. Aircraft Make model Series Raytheon Aircraft Company 400A Name (As Shown on registration certificate) Address (As shown on registration certificate) 2. Owner Flight Options .11O Ancireas cry Richmond Heiohts slew OH z,,, 44143-14 Country USA 3. For FAA Use Only 4. Type S. Unit Identification Repair Alteration Unit Make Model Serial Number 0 El AIRFRAME (AS described in Item I above) O POVVERPLANT CI ❑ O PROPELLER Type O O APPLIANCE tasrvisaune 6. Conformity Statement A. AgenCYS Name and Address Et Kind of Agency Nanny Nextant Aerospace I O U.S. Cenelicated Mechanic O Manufacturer Armrest O Foreign Certificated Mechant C. Certificate No. Cq Cleveland sure. OH 0 Certificated Repair Station zu 44143.1453 Country USA O Certificated maintenance Organization CRS # 25NR667B D. I certify that the repair and/or alteration made to the unit(s) Identified in item 5 above and descnoed on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 APP. B 0 05/30/2013 7. Approval for Return to Service Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in me manner prescribed by the Administrator of the Federal Aviation Administration and is esAPPROVED 0 REJECTED FAA Flt Standards Organization I Person Apart/wed by Canadian Manufacturer Maintenance Department of Transport Inspector BY • Certificate or Designation No. FM Designee X Repair Station Inspection Authorization Other Specify) CRS # 25NR667B 05/30/2013 EFTA00012003 lb • EFTA00012004 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration math and date work completed.) N493LX 05/30/2013 Nationality and Registration mark Date Part I of 3 The Following Equipment was removed along with Associated Hardware. EFD-871 622.9345-203 Electronic Flight Display EFD-871 622.9345.203 Electronic Flight Display MFD-871 622.9434.213 Multi Function Display ICU-85 622-6189-002 Internal Compensation Unit ICU-85 622-6189-002 Internal Compensation Unit AHC-85E 622.9336-400 Attitude/Heading Computer AHC-85E 622-9336-400 Attitude/Heading Computer SDU-640B 622-9735-001 Sensor Display Unit SDU-640B 622.9735-001 Sensor Display Unit DCP-5000 822-1028.011 Display Control Panel DCP-5000 822-1028.011 Display Control Panel ARP-851 622.9500-011 Altitude Reference Panel ARP-851 622.9500-011 Altitude Reference Panel AAP-851 822-0328-011 Altitude Awareness Panel AAP-851 822.0328.011 Altitude Awareness Panel CHP-850 622-7397-002 Course Heading Panel DBU-4100 822-0014-002 Data Base Unit DAU-650 622-9344.101 Data Acquisition Unit SDD-640A 622-9347-001 Sensor Display Driver IOC-4000 ( 4) 622-9814-514 Card Assembly MDC-4000 622-9818-751 Maintenance Computer CSU-4000 (2) 822-0049-002 Configuration Strapping Unit FMC-5000 (4) 822-0891-008 Flight Management Computer PWR-4000 (4) 622.9945.021 lAPS Power Card GPS-4000 822-0931-003 GPS Receiver Mounts 622-9430-002 EFD /MFD Mounts EFB Electronic Flight Bag Mounting 0 Additional Sheets Are Attached Form 337 (10.C6) EFTA00012005 • • • EFTA00012006 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality end registration mark and date work completed.) N493LX 5/30/201 Nationality and Registration Mark Date Page 2 of 3 Installed the Following Equipment along with Associated Hardware. Model Part Number Description Weight Arm CCP-3000 822-1746.002 Cursor Control Panel 2.60 90.0 CCP-3000 822-1746-002 Cursor Control Panel 2.60 90.0 DCU-3001C 822-2362-003 Data Concentrator Unit 5.0 325 DCU-3001C 822-2362.003 Data Concentrator Unit 5.0 325 ECU-3000 822-1200-209 External Compensation Unit 0.40 57.5 ECU-3000 822-1200.209 External Compensation Unit 0.40 57.5 FSU-5010 822.1543.101 File Server Unit (1° IFIS) 6.5 60.83 ECU-3000 822-1200.998 File Server Unit (1st IFIS) 0.40 57.5 AFD-3010E 822-1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822-1753.416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822.1753-416 Adaptive Flight Display 12.90 89.2 AFD-3010E 822.1753-416 Adaptive Flight Display 12.90 89.2 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 INIT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 IMT-3010 822-1140-401 AFD Mounting Rack 4.40 85.0 10852801Y00 Fuel Quantity Conditioner 0.90 324 PC920-2A2000PH-2A1 Fuel Flow Conditioner 1.10 325 GPS-4000S 822-2189-004 GPS Receiver 6.0 37 CI 429-410 GPS Antenna 1.0 166.14 Amp Cluster N241100-002 DC Voltmeter 1.5 97.4 373-93-1501-1 Speed Switch (2) 0.25 89.2 DBU-5010E 822-3000-202 Data Base Unit 1.60 134.5 PS-8350 501-1228-004 Power Supply 12.5 52.9 MMT-5000 822-1811-003 File Server Unit Rack 0.30 57.5 MMT-3010 (2) 822-1290-003 AHS Mounting Rack 1.80 57.5 XM WR-1000 822-2031-002 XM Weather 1.5 41.0 CHP-3010 822-1280-003 Course Heading Panel 1.30 92.5 Options Configuration Module. OCM-4100 822-1463.228 0.30 57.5 WAAS/LPV Options Configuration Module. OCM-4100 822-1463-228 0.30 57.5 WAAS/LPV El Additional Sheets Are Attached Form 337 (10.06) EFTA00012007 S • • EFTA00012008 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (II more space is required, attach additional sheets. Identity with aircraft nationality and registration mark and date work completed.) N493LX 05/30/2013 Nationality and Registration Mark Date Page 3 of 3 Model Part Number Description Weight Arm CSU-4100 (2) 822.1364.002 Configuration Strapping Unit 1.60 55.7 MDC-3110 822.1987.006 Maintenance Data Computer 0.80 55.7 FMC-6000 (2) 822.0868.123 Flight Management Computer 1.90 55.7 ADC-850D (2) 822.0389.468 Air Data Computer 5.30 60.83 AHC-3000A (2) 822-1378.001 Attitude Heading Computer 4.80 57.5 DCP-3030 (2) 822-1828-002 Display Control Panel 1.90 89.96 PWR-4000 (4) 622-9945-022 IAPS Power Card 1.3 55.0 IOC-4100(4) 822-1362-511 Input/output Concentrator 0.8 55.0 LT-4001.010 Master Caution Panel 1.3 87.0 Rev. Panel 373-91-3203-1 Pilot Reversion Panel 0.2 88.0 Rev. Panel 373-91-3203-3 Co-pilot Reversion Panel 0.2 88.0 9-PED 373-91-3203-9 9-Pedestal Panel 1.8 92.89 345.6196 ELT Switch 0.2 88.0 Annunciator led-42-12-BB-E0Y47 AUX BATT (1/2) Annunciator 0.05 88.0 Annunciator (2) Led-40-18-BB-E0Y45 Pull Up/ Terrain Annunciator 0.05 88.0 Annunciator 24840231 Terrain Inhibit/ Terrain Fail 0.05 88.0 In Accordance with STC ST109595C. See Attached Copy MM Supplement, Nextant Aerospace Doc. No. 373.00-0023 Rev IR Dated 09/02/2011or later FAA approved revision, installed on Aircraft. Equipment Pilot Guides are Installed in the Aircraft as Portable Document Format (.pdf) via supplied I-Pad. NOTE: Portable electronic devices used to store required aircraft records required by Part 91.9 are considered Electronic Flight Bags (EFB) per FAA Advisory Circular AC 120-768 par 4-g. Commercial operators are required to obtain authorization for their use from their managing Flight Standards District Office. Instructions for Continued Airworthiness (ICA) Ref Nextant Aerospace Document 373-00-0002.Rev C or Later are included in the Aircraft Maintenance Records Carried out System Ground Test Plan PAW Master Drawing List (MDL) 373.00.004 Rev C. Carried out Hawker Beechcraft Service Bulletin 34-3431 Reduced Vertical Separation Minimum (RVSM) Airframe Inspection / Modification. Performed FAR 91.411Inspection per Part 43 appendix "E" Pitot Static & FAR 91.413 Inspection per Part 43 appendix "F" Transponder System checks. ❑ Additional Sheets Are Attached Form 337 0046) EFTA00012009 • • EFTA00012010 11,1Ra "lain of Jkinerira • Pepartment of Zranspotintion getter:II (Ablation cAbministrution $uppientental 'ape Certificate ../fianZies ST I 0959SC arletecalei 44.444.4relk• Nextant Aeros ace LLC Richmond Heights, Of! 44143 &WOW 44114 ereir 6 414 *WO eie441/444AretiliWIfiedaletede 44 da.M74/4AVO emaneavaaesoa 44-9,4erai 044-454e4arnev• .444ev‘O 4wr i„e„-..044.„wan...4 *end 25 ./4,4 Federal Aviation Avast (See Prima 3 and 4 for complete certification basis.) oniadail- sc;n4;474,44;ney, Al 6SW ./E0.4. Hawker Beechcraft Corp. ..sgedi 4O0A givertythao rano ntiosYlier Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFTS) with Rockwell Collins FMS-6100, Localizer Performance with Vertical Guidance (LPV) approach capability and Universal Avionics Systems Company (UASC) Terrain Awareness Warning System (TAWS) in accordance with Nextant Aerospace LLC Master Drawing List Doc. No. 373-00-0001 Revision W, dated March 29, 2012, or later FAA approved version. • 24.n.r.gaivm ebuilf;v344.;viu : 1) The installer must determine whether this design change is compatible with previously approved modifications. 2) If the holder agrees to permit another person to use this certificate to alter a product, the holder must give that person written evidence of that permission. . 3) For aircraft equipped with Pratt & Whitney JTISD Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0008 Revision IR, dated 10/19/2009, or later FAA approved version, is required on board the modified aircraft. erehAe".44 cad a- ar da, 4, AA tryserisslawnetha rim ryl revie AvaLeiArroaoreei why...need envsione tv a kaniaer.44va dale resenr4ht 44144444441454 43rR .4444;s41,44.7494 la; Alevre 4.444.444,4 ./11.404sim4.14n4.4.4a Para eAreeesetm • June 26, 2008 Paleets...4.10eni: gaze r/e....‘;w&-.4 October 19, 2009 512/P OrnelleAl : September 26, 2011; April 05,2012 anger, ys ems all g Chicago Aircraft Certification Office • (lisle) Any *1CCCCCJon of this eertitlwce Jr pleas n0 a1,ON. Or S00041K AOt Oxe010anp l yllerS. of both. TM Parw 1110.1110.0/1 O is coral lats. n4y aft trans need In neerderee win IM 1.4 . EFTA00012011 0 • 0 EFTA00012012 ilnifebikafee Of America • Pepartment of Zrunsportzation - 1:cberal cAbiation crthntiliistrittion Supplemental `Type Qlertificate (Continuation $lieet) te/ rande, ST I 0959SC rAswenen• October 19.2009 Date Amended; September 26, 2011; April 05.2012 Monlerlavio andrinsetaavki nevrawedi: 4) For aircraft equipped with Williams FJ44-3AP Engines, those engines must be installed under SIC ST0237ILA. 5) For aircraft equipped with Williams FJ44-3AP Engines FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0023 Revision IR, dated September 2, 2011, or later FAA approved version, is required on board the modified aircraft. 6) Aircraft must have previously qualified for Operations in Reduced Vertical Airspace via: RK- I thru RK- I 17 and RK-I 19 thru RK-I39, Hawker Beechcraft Service Bulletin No. 34.3431. RK-I 18, RK-140 thru RK-224, Hawker Bccchcraft Service Bulletin Nos. 34-3228 and 34-3431. RK-225 thru RK-299, Hawker Beechcraft Service Bulletin No. 34-3431. RK-300 and after as original equipped from Hawker Beechcraft. 7) For aircraft equipped with Universal Avionics Systems Corporation (UASC) TAWS FAA approved • Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373-00-0036 Revision IR, approved March 28, 2012, or later FAA approved version, is required on board the modified aircraft. 8) For aircraft with Collins Proline 21 FMS-6100 LPV Approach enabled FAA approved Airplane Flight Manual Supplement, Nextant Aerospace LLC Doc. No. 373.00-0032 Revision IR, approved March 28,2012, or later FAA approved version, is required on board the modified aircraft. Based on 14 CFR §§2 1.1 15 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Hawker Beechcraft 400A aircraft is as follows: a. The type certification basis for the Hawker Beechcraft 400A aircraft is shown on TCDS Al6SW for parts not changed or not affected by this change. b. The certification basis for the parts changed or affected by this change since the reference date of application, September 29, 2009, is based on TCDS A I6SW and §§ 14 CFR Part 25 as shown on page 4 of 4 of this STC. • Any ale &&&&& on of rerun Cleo is Duo aneela by a Gn0 of not *needing Si .000. Or inparsonmene Trot OACOOd.no 1 yo00. Or bOth. "a Man 4110.14(10431 PAU 3 of 4 eAGLI Th is certificate way be cransfyi red f., accordance Win FAA 11.0. EFTA00012013 • • • EFTA00012014 Janda Slake of America • Department of Zgransportntion - federal Abiation Atiministration $uppiettuntal 'Type aertificatt (a:Continuation $hnt) gkr4, ViAkanot October 19, 2009 Date Amended: September 26, 2011; April 05. 2012 Based on 14 CFR §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the baseline Installation of Rockwell Collins Pro Line 21 Electronic Flight Instrument System (EFTS) with Rockwell Collins FMS-6100 modification was determined to be TCDS Al6SW and the following later regulations: Amda 124-4] MOORS-23) Amdt(25-310 Amck.(25-40] Amd1.125-411 25.771 (a.e) 25.301; 25.303; 25.581; 25.1309 25.901 (b)0X0; 25.1549 25.1321 (a0(b)(c)(c); 25.607; 25.611, 25.773 00(bXeXdflg); (4X6X0 25.1331; 25.1333 (aX1X2Xd) 25.1322 Mndt.(25-42) Amd1425-46] Ai/Mt(2544) Amdi.125-721 Am0112540) 25.1501 25.603; 25.605; 25.613; 25.1529 25.307; 25.571. 25.1307 25.1316 25.1329(h) NO; 23.1351MOM 25.1381; 25.1521 (.Xc); 25.1543 (b); 25.1581; 25.1583 (a) Amdt425.861 Amd1425.901 Amdtl25.91) Amett25-102) Amdt[25.105J 25.305 25.1303 25.561 25.981 (a(6) 25.1585 (o) Amdt425.108) Amdl.(25.109] Amdc.(25-113) Amdi425-1221 Amc11425-1231 • 25.1325 00 25.1323 (a)(1)(g) 25.869 (aX4); 25.1431 25.1317 (aX6)(e) Based on 14 CFR §§ 21 115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the Collins Proline 21 FMS-6100 with LPV Approach enabled and UASC TAWS 25.1353 (aXM was determined to be TCDS Al6SW and the following later regulations: AmattOriginali Amdr[24-41 Amd1.(25-23) Amdt.(25.381 Amdl.(25.401 25.601. 25.605. 25.609. 25.771 (a) 25.301; 25.303; 25.305. 25.603. 25.1322, 25.1585 (a) 25.613.25.1301, 25.307, 25.561(c); 25.1583(O 25.1357. 25.1381. 25.607; 25.611. 25.1307 25.1525, 25.1541, 1S.1581 Ainc1i125-411 Aindi.(25-421 Amdt125-46) Amdl.(25-541 Amdt.(25-72) 25.1309 (a)(b)(401)(aXa) 25.1501 25.777(a)(c) 25.1529 25469(a)(1) 25.1351 (a)(1) Amdr(25-102) Amdt.P5-113i A=0(25-1231 25.981(aXb) 25.14310) 25.1353 (aXe) - END - • Any &&&&&& On of t • COrtifiene II poniSOSO by • fPM 0f not ontoolling SI.000, or I ptiSASS not •44•003n9 3 Hero. or both. FAA Mom 4110.2.1110.401 PS 4 Of 4 SOS Thin cortirIsto My M trensferrod in accordence .ith DA 21.17. EFTA00012015 • • • EFTA00012016 Form Approved Electronic Tracking Number omen° 2120-0O20 0 MAJOR REPAIR AND ALTERATION 11/30,2007 U.S OOPWITIAI Of trenwraln-m (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Naomi Aviation AtIrnialcustron INSTRUCTIONS: Print or type alt entries. See FAR 43.9 FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition Of this fOrm. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act 1958) Nabonality and Registration Mark Serial No. RK 244 N493LX 1. Aircraft Make Model Series Raytheon Aircraft Company 400A Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner Flight Options .LLC Address CT). Richmond Heights slaw. OH zip 4414 -14 Country 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number 0 el AIRFRAME (As described in hem t above) • POWERPLANT 0 O PROPELLER 0 Type APPLIANCE 0 . stmeeaurer 6. Conformity Statement A. Agencys Name and Address B. Kind of Agency rim. Nextant Aerospace O U.S. Certificated Mechanic O IManufacturer Adores, O Foreign Certificated Mechanic C. Certificate No. City Cleveland sta. OH 0 Certificated Repair Station zip 44143-1453 Cotrey USA O Certificated Maintenance Organization CRS # 25NR667B D. I certify that the repair and/or Migration made to the unit(s) identified in item S above and described on the rever e or attachments hereto have been made in accordance with the requirements of P rt 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized Individ per 14 CFR Part 43 05/30/2013 App. 6 El 7. Approval for Return to Service Pursuant to the authonty given persons specified below. the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is ®APPROVED 0 REJECTED FM Fit Standards Person Approved by Canadian Manufacturer Maintenance Organization Department of Transport Inspector BY Other (Specify) FAA Designee X Repair Station Inspection Authorization i Certificate or Signature/Date of Authorized Individu. Designator NO 05/30/2013 CRS # 25NR667B FAA Form 337 0-061 EFTA00012017 EFTA00012018 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable ainvorthtness requirements. 8. Description of Work Accomplished (11more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 05/30/2013 Nationality and Registration Mark Date Nextant Aerospace Completed STC # ST02371LA Removed Pratt and Whitney JT15D-5 Series Engines . Installed the Williams International FJ44-3AP Engines with Full FADEC and Associated Systems in accordance with Nextant Aerospace MDL -NXT-001 Rev IR Dated 08/22/2011 or later FAA approved revisions, and FAA Approved AFM Supplement NXT-1-AFMS Rev IR dated 9/15/2011 of later FAA Approved revisions. Installed Left Engine Part Number. 111000-202 Serial No. 252757 Installed Right Engine Part Number 111000-202 Serial No. 252758 ICA AFM Supplement was installed on Aircraft. Nextant Aerospace Instructions for Continued Airworthiness Document NXT-ICA Rev IR or later FAA accepted revisions are included in the Aircraft Maintenance Records. Carried out Engine Ground Runs and System OPS checks SAW Ground Test Plan 373.00-0024 Rev F. End ❑ Additional Sheets Are Attached FAA Form 337 (10-06) EFTA00012019 l EFTA00012020 }loath Slake 01,P1merico Pepiirtmettt of "Mri iapnr ha lion - Athena cAb in tint' cainiiiiiistration $uppinnental Tut antificate -4400 fi ST02371LA 97L YlerrAWne.weee'n' Nextant Aeros ace, LLC Richmond Heights, Ohio 44143 er4eed /414 tArel /4 jfr o eirtifra/Se e'h/ Fara' /4 Atekheem andeanr44im& erre/fre rrevvtv//temonmed.' /4 aewer/41;orvat terthwtevno•°Mad 25* oth -9,7viprzteathiv: -93efideravv. *Certification basis is set forth on Tan A I6SW and continuation sheets 3 and 4. .6:10.4.4101flotet Wee/r/ea/n./Kmres,".. Al 6SW Hawker 13eechcraft 400A Stverfer4kn gam Ylis t refe.wyn.Replacement of Pratt & Whitney JT15D-5 series engine with Williams International F144.3AP engine (TCDS E3GL) with Full Authority Digital Engine Control (FADEC) and associated systems, in accordance with Nextant Aerospace Master Drawing List No.: MDL-NXT-001, Revision IR dated 8/22/2011, or later FAA approved revisions and FAA Approved Airplane Flight Manual Supplement, NXTI-AFMS, Rev IR, dated September IS, 2011 or later FAA approved revisions. Nextant Aerospace, LLC Instructions for Continued Airworthiness document NXT1-ICA, Revision IR, or later FAA accepted revisions must be provided with this STC. Smitrom, anatvraimo.. The installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of that aircraft. The approval of this modification applies to the above-noted airplane models only. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. (CONTINUED on page 3) Sot ewhiecalo emal/h arvyralearts riala reufrofis /4 irmajfice twravertraketemaria as eleclteethe Ornrenalreaffireonselerierweverviev a 4werrihthive dale' As ederrot;to evireadeal, ,Arketiteow/c,eyeen Fetrieredfitvideen dgriorriredretheva givenc4flactwiew, March 24, 2008 .02/4 mti.senvi• k4seAunonen.- 51 September 27, 2011 ebvemaremi.- frithierriev. (Signature) Manager, Propulsion Branch Los Angeles Aircraft Certification Office (Title) Any eremites? of Mu certificate it punishable by a fine of not tweeting 31,004 or imprisonment not weeding 3 years, or froth. FAA ran 0110-200•441 Pete 1 at 4 .7du eratferace may Sc transfenvi arronfaure ',nth fillt,27.47. EFTA00012021 EFTA00012022 INSTRUCTIONS: The transfer endorsement below may be used to notify the appropriate FAA Regional Office of the transfer of this Supplemental Type Certificate. The FAA will reissue the certificate in the name of the transferee and forward it to him. TRANSFER ENDORSEMENT Transfer the ownership of the Supplemental Type Certificate Number to (frame of transferee) attains of transfer) Oliallite andlora) (CYcz Shut, andLiptak) from (Name ofgran tor)(Trint or type)_ (Address ofgrantor) Patokr /al I aft) (plat Pete, endZiprah) Extent of Authority (if licensing agreement): Date of Transfer: Signature of grantor an ink) Past 2 of 4 EFTA00012023 EFTA00012024 puilrb Auden (Of cAnterirn Prinirltitent of Vint ttoportn tion - gebertil cabintioat cAbmittiotra Non $upplatuntal Ewe Tertificate (Cfontinuation $liget) Afeeenie/< ST02371LA ..Waterrthirm3 ammo/la:ono. loomammeil • Nextant Aerospace, LLC, "Installation ofRockwell Collins Pro Line 21," Amended STC ST10959SC, dated September 26, 2011 or later FAA approved revisions is required as part of this alteration. • The new Vmca and Vmeg values arc 94 KIAS and 93 K1AS respectively. • The new engine minimum rated thrust is 3,031 lb at sea level, flat rated to an ambient temperature of 77°F. • Approved engine fuels are: Grade Specification Jet A ASTM-D 1655 Jet A-I ASTM-D 165.5 rerlejeeethewSewth The certification basis for this modification is as follows: The original certification basis for the Hawker Beechcraft Model 400A airplanes identified on TCDS Al6SW, Revision 26, dated March 17, 2010: Part 25 of the Federal Aviation Regulations effective Febmary I, 1965, as amended by 25.1 through 25-40, plus §§ 25.1335, 25.1351(d), 25. I353(cX5), and 25.1447 of Amendment 25.41; §§ 25.29, 25.255, and 25.1353(eX6) of Amendment 25.42; and §§ 25.361(b) and 25.1329(h) of Amendment 25-46. Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36-17; SPAR 27 effective Febmary 1, 1974, as amended by 27.1 through 27-5; and Special Conditions No. 25-ANM-32 dated Febmary 22, 1990 (High Altitude Operation at 45,000 feet), and Special Conditions No. 25-ANM-33 dated June 18, 1990 (Lightning and Radio Frequency Energy Protection). (Sec NOTE 12) Equivalent Safety Items: (1) Out-of-trim characteristics § 25.255 (2) Pilot compartment view § 25.773033(2) (3) Passenger compartment door § 25.813(e) (4) Emergency exit marking §§ 25.811(d)(1) and 25.811(d)(2) Application for amended Type Certificate dated February 18, 1988. Regulation at a later amendments for components and areas affected by the change (Ref. FAA approved Compliance Check List): Subpart A - General : 25.2(25.99) Subpart B — Flight: 25.207(25-121), 25.255(25.42) Subpart C — Structure: 25.571 (25-96) piny dictation of tfiu marmite is ponisfrabb by a fine of not crow% 31,004 or imprisonment not eventing 3 rue or 6oth. FM roes M20-2110-411 Pete t of a 'MOeategete may fre tmeilerreltit °creamy with f:P4t21.47. EFTA00012025 EFTA00012026 Nuittb "hilts Of America Pepartment of transportation - geberni ciliation cAbmittistrntion „Sup-plartental Type Certificate (gartfinurdion $ipet) Afeednlei, ST02371LA free4eathen Sera /conk:tam, Subpart D —Design and Construction: 25.603(25.46), 25.605(25-46), 25.611(25-123), 25.613(25-112), 25.625(25-72), 25.832(25-72), 25.863(25.46), 25.869(25.123), Subvert E — Powernlant: 25.901(25.46), 25.903(25-100), 25.951(25.73), 25.961(25-57), 25.981(25-125), 25.994(25-57), 25.997(25-57), 25.1013(25-72), 25.1019(25-57), 25.1021(25.57), 25.1043(25-42), 25.1045(25-57), 25.1091(25-100), 25.1093(25-72, 25.1103(25.46), 25.1141(25-115), 25.1143(25-57), 25.1163(25-57), 25.1165(25-72), 25.1181(25-115), 25.1183(25-101), 25.1185(25-94), 25.1189(25-57), 25.1195(25.46), 25.1203(25-123), 25.1207(25-46). Subvert/ — Equivalent& 25.1301(25-123), 25.1305(25-115), 25.1307(25-72), 25.1309(25-123), 25.1316(25-80), 25.1317(25-122), 25.1321(25.41), 25.1331(25-41), 25.1351(25-72), 25.1353(25-123), 25.1357(25-123), 25.1381(25-72), 25.1431(25-113), 25.1438(25-41), Subpart G — Operating Limitations and Information: 25.1501(25.42), 25.1521(25-72), 25.1527(25- 105), 25.1529(25-54), 25.1543(25-72), 25.1549(25-40), 25.1551(25-72), 25.1557(25-72), 25.1581(25-n), 25.1583(25-105). Subpart H - Electrical Wiring interconnection Systems (EWIS): 25.1701(25-123), 25.1703(25-123), 25.1705(25-123), 25.1707(25-123), 25.1709(25-123), 25.1711(25-123), 25.1713(25-123), 25.1715(25-123), 25.1717(25-123), 25.1719(25-123), 25.1721(25-123), 25.1723(25-123), 25.1725(25-123), 25.1727(25-123), 25.1729(25-123), 25.1731(25-123), 25.1733(25-123). 14 CFR Part 34 (34-3): 34.11 14 CFR Part 36 (36-28): 36.I--36.7, 36.101-36.105, 36.1501, 36.1581. The following Noxtant Aerospace Continued Airworthiness Supplements are applicable to airplanes modified in accordance with this STC: • Master Minimum Equipment List document No. MMEL Rev. 8, dated 02/21/2011 or later FAA approved revisions. • EWIS (Electrical Wiring Interconnection Systems) Inspection Procedure/Report No. NXTI-EA-007 Rev A dated 8/24/11 or later FAA approved revisions. -END- Any titivation of this entifstote is pintisita64 ky a fine of no ttrutatto $3.000, or imprisonment not to-ceding 3 years, or 6otk ma Foxe 6110.2420.481 Part • 04 4 ihiscertifiSote may 6: tmofertain areortanee with Tfilt,21.47. EFTA00012027 EFTA00012028 Form Approved Electorsic Tracking Natter 420 OM No 21200020 US Dispartinent MAJOR REPAIR AND ALTERATION 11/302301 For FAA Use Only at nainert1140 (Airframe, Powerplant, Propeller, or Appliance) Want Aviation Administration INSTRUCTIONS: Print or type all entries. See Title 14 CFR §43.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report Is required by law (49 U S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. §46301(a)) Nationality and Registration Mark Serial No. USA, N493LX RK-244 1. Aircraft Make RAYTHEON AIRCRAFT COMPANY Model Series ICAO AIRCRAFT ADDRESS CODE:51416115 400A Not Applicable Name (As shown on registration certificate) Address (As shown on registration certificate) FLIGHT OPTIONS LLC At:Cross 2. Owner FLIGHT OPTIONS LLC City RICHMONO HEIGHTS State OHIO Le 44143.1453 3. For FAA Use Only 4. Type 6. Unit Identification Repair Alteration Unit Make Model Serial No. ❑ ril AIRFRAME (As describedIn Item I above) 0 ❑ POWERPLANT 0 IN PROPELLER Type 0 ❑ APPLIANCE Manufacturer 6. Conformity Statement A. Agencys Name and Address B. Kind of Agency Hem. me U. S. Certificated Mechanic Manufacturer Adams Foreign Certificated Mechanic C. Certificate No. City Blichantica Style NY Cedificated Repair Station DJFA206D rip 13101 USA x Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the unit s) identified in item 5 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel Signature/Date of per 14 CFR Part 43 APP. (3 ❑ . rove or 0 0Service Pursue t to the authority given persons specified below, the unit Identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and Is L Approved Rejected D FAA Fit. Standards X Persons Approved by Canadian Manufacturer Maintenance Organization Department of Transport Inspector BY Other (Specify FAA Designee Repair Station Inspection Authorization Certificate or Signature/Date of Autho Designation No. DJFA 206D FAA Form 337 rio-os) EFTA00012029 EFTA00012030 NOTICE Weight and balance or operating limitation changes shallbe entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Work Accomplished (If more space is required, attach additional sheets Identify with aircraft nationality and registration math and date work completed.) USA N493LX 4/3/2012 Nationality and Registration Mark Date Removed EFB Mount Assembly that was previously installed under Engineering Order M25-10/05-011. The aircraft weight and balance has been updated. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: None END Additional Sheets Are Attached AA Form 337 no-as EFTA00012031 EFTA00012032 UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONAUTY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERtAL 4 CATEGORY REGISTRATION MARKS NUMBER Raytheon Aircraft Co. N493LX 400A RK-244 Transport 5 AUTHORITY AND BASS FOR ISSUANCE Thy almorthIrtess terra la Issued pursuant to Coi Federal /widen Act of1 958 end coreDea that. as of Ihe dabs of tuuance. the Omit to ittah Issued has been Inspected end toad to =don to Ou type corticate Nervfot, to Debt:I:neon for sate operettas end has been ahem to meet the 13(grernents of the appkable comprehensive end detailed atm.:stings' code seen: toed by Marox no the Convandon on ~aeon& tDMI Avtatkai. except es noted herein. ecoepeons: None 5 TERMS MD CONDMONS Unless *toner riumerared, stoponded. mob& or e torrnhattri date Is °View» oatab i by ITO Attnertseator, this idnecelhbeta Cereksto ta effectNe es Iona as the mal pre-rental:ye rnatitamance, and alterallona are performed In accordance oil Parts 21. 43. end 91 of the Foam: Airtet)on Redutothra te. and the a-YtTelbrotl-ktared h Pe Ulled Stem. DATE OP ISSUANCE DESIGNATION NUMBER R 10/01/1999 AEA-FSDO-23 My ~an norcducart. or raw of Cia cerCt•uu may he swittable Dye Pie sol escorstsp 11,000 a bralkeresnt nut n¢eedh+p3 ras or tat THIS CERTIFICATE aftt8T 88 DISPtAYED N THE AIRCRAFT P4 ACCORDANCE WITH APFUCABLE FEDERAL AYIATION REGULATIONS. FAA Form 81004 (3-08) EFTA00012033 II 4 EFTA00012034 ENGINEERING ORDER Aircraft Type Aircraft Number Serial Number Station Engineering Order Number Revision Numbe Date Page 1 of: M25-10/05-011 Original 10-19-2005 1 E NG I NE ER I NG ORDE R T I TL E Electronic Flight Bag Mount Installation — Beechjet 400 Fleet Effectivity: Aircraft serial numbers RK-123 and after To install a fabricated mount assembly near the co-pilots map light Description: rheostat to hold the electronic flight bag computer Accompanying Work Compliance Instructions Form. DER approved Engineering Documents:. Directive EDW01-5. FAA forms 337 and 8110-3, Reason: For the effective aircraft to obtain a paperless cockpit environment Prepared By Date Keith Gawsyszawski 10-19.2005 Quality Assurance Date Robert Beaumont ;eta -- Approved By Date Todd Hattaway Regulat • ry Compliance Major Repair ❑ Minor Repair FAA Approval (E) Yes ❑ No Weight Arm Weight & Balance Affected (E) Yes ❑ No 4 lb increase 108 Parts Required Equipment List Update Yes, FG3500-400N, EFB mount assembly, 4 each AN3-5A bolts, 4 each NAS1149F0363P ❑ yes 18) No washers, 1 each -11 placard Drawings Required RVSM Status Affected Yes, 1175TA, rev A. 5245D, rev B, 5244FC, ❑ Yes No rev B (included in the Engineering Directive) Publications Affected AD List Affected None ❑ yes No Estimated Cost Estimated Labor Hours $176.00 4.0 hours Distribution Remarks I References The planning department shall add this EO to a Z000000 Maintenance Planning scheduled work order whenever an effective aircraft Maintenance is located at one of the Raytheon dedicated Quality Assurance maintenance facilities and adequate down time Operations permits. Procurement Priority Code (check all that apply) Aircraft Manufacturer Federal Aviation Administration ❑ Urgent IZ Mandatory ❑ Attrition FO-09 GMIVI Revision 1 0912005 EFTA00012035 EFTA00012036 ' .i sirr iZadrizia WORK COMPLIANCE INSTRUCTIONS .__--— 0...0,0— -- Page: Aircraft Number: Station: Work Order # Effectivity 1 of 2 RK-123 and after 0 Enginee ing Order Number: 0 Fleet Campaign Directive Number: OR M25-10/05-011 T I T L E Electronic Flight Bag (EFB) Mount Installation Procedures For Flight Options, LLC., Beechjet 400A's Item Work Description Mechanic Inspected Document the maintenance action on a Flight Options maintenance transaction report form FO-501 with the following statement in the 01 discrepancy side: 'Accomplishment of Flight Options EO M25-10/05-011 Installation of the Electronic FlightBag, FG3500 mount assembly is due' 07 Remove electrical power from aircraft and disconnect main aircraft battery. Loosen the upper glare shield and right side cover (which contains the 03 reading fight and air-cell phone assemblies) by removing the mounting screws and separating the Velcro strips. : Remove the three screws and 90 degree cover panel form the aft edge of cr 04 the right side cover panel and discard. With the glare shield and right side cover disconnected, locate the pre- .-- existing fastener holes located on the shelf just below the copilots windshield and temporarily install the Electronic Flight Bag (EFB) mount 05 assembly using the four AN3-5A bolls and NAS1149F0363P plain . a rtt washers (included In the kit) to the pre-existing fastener holes. Snug but do not tighten bolts at this time. Adjust the position of the EFB mount assembly to provide sufficient - 06 clearance between the existing ashtray and the EFB mount thumbscrew. When proper clearance Is achieved in step five. (thumbscrew does not 07 touch the ashtray when rotated), tighten mounting bolts to 22 to 28 inch pounds (AMM Chap 20). Reinstall the right side panel. Trim the aft edge of the panel as necessary to provide clearance between the panel and the 1175TA bracket, as 08 identified in engineering Directive EDW01-5, figure 2, on page 3. Trim .. leather covering as necessary and secure with adhesive (contact cement or equivalent). e Verify condition of Velcro on the upper glareshield and right side panel for 09 hn. proper security. Secure as necessary. _ 10 Install the EFB computer (Fujitsu) into the holder bracket. „.. ?am With the EFB mount installed, loosen the thumbscrew knob on the mount 11 assembly % to one full turn maximum (do not allow the lioldlt arm to separate from the mechanical stop pin In the drawing number 1175 mount bracket). With the EFB mount assembly arm loose; verify the co-pilots control column and wheel does not come in contact with the EFB mount assembly using the following procedure: Perform this task by moving the control column full travel forward and aft and rotating the control wheel full 12 left and right while also rotating the EFB mount assembly in all possible configurations. Verify that the EFB mount assembly does not make contact with any part of the control yoke and wheel. If contact does not occur, proceed to step 17 and N/A and initial blocks 13 through 16. Form Completed By: Date: Log Page: F0-10 GMM Revision 1 0912005 EFTA00012037 EFTA00012038 .. ---...--- nrcria WORK COMPLIANCE INSTRUCTIONS Page. Aircraft Number. Station: Work Order # Effectivity 2 of 2 RK-123 and after El Engineering Order Number: 0 Fleet Campaign Directive Number: OR M25-10/05-011 T I TLE Electronic Flight Bag (EFB) Mount Installation Procedures For Flight Options, LLC., Beechjet 400A's Item Work Description Mechanic Inspected If contact occurs, remove the mount assembly 'Hold-It' arm, identified in figure 2 of engineering directive EDW01-5, page 3, by completely 13 removing the thumbscrew. Take note not to lose the wedge shaped bushing located in the eye of the 'Hold-It' ann which supplies the locking feature of the mount assembly. Locate the small Allen type set screws and adjust as necessary to move 14 the arm towards the more vertical position. Make''/. turn adjustments at a time. Reinstall the 'Hold-Ir arm assembly, taking note to install the wedge bushing with the tapered end first into the eye of the arm assembly and tighten the thumbscrew. Caution: Make sure the mechanical stop pin 15 located on the drawing number 1175 mount bracket fits within the machined slot on the inside part of the eye portion of the "Hold-It' arm assembly. 16 Repeat steps 10 through 14 until proper clearance between the control yoke and the EFB is achieved. After the final adjustments are made to the Allen type set adjustment 17 screws, apply a small amount of Loctite 242 to the screw threads to secure from loosening. 18 Resecure the upper glareshleld to the right side panel by reinstalling the mounting screws and resecurinq the Velcro strips. i-4 19 Attach the power plug to the EFB computer. .4 Install the fabricated ' -11' placard as stated in the engineering directive 20 EDW01.5, page 2, to the right cockpit side wan panel just below the side window. 21 Reconnect the main aircraft battery. Secure as necessary. Complete the corrective action side of the Flight Options aircraft maintenance transaction form FO-501 with the fonowing statement: 22 'Complied with Flight Options EO M25-10/05-011. installation of the ri." Electronic Flight Bag assembly FG3500-400N in accordance with DER .. approved Engineering Directive EDW01-5, see FM form 8110-3 dated 8- 12-05 and Flight Options Work Compliance InsDuchene. ;As,• Complete the accompanying Engineering Directive checklist on page 2 and the previously FM field approved form 337 by completing blocks 6 and 7 in its entirety. When completed, forward one copy of the 337 and 23 the complete Engineering Directive package and Form 8110-3 to the 'Duality Assurance Department in Binghamton. New York and one copy of the FM form 337 and 8110-3 to the local Flight Standards District Office via US mail within two business days after completion of the installation. —END— -- t, . 7414 ili‘C.: t Form Completed By: Date: Log Page: FO-10 OMM Revision 1 09/2005 EFTA00012039 EFTA00012040 Form Awrovoti Eisaron'c 'finking Number OMB No. 2120-C020 0 US Ciepailmant MAJOR REPAIR AND ALTERATION I U30/2007 or FAA Us* Only al WardpOrtalion (Airframe, Powerplant, Propeller, or Appliance) Fodor& Aviation Administratinn INSTRUCTIONS: Print a type di entries See Title 14 CFR §43.9, Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. §46301(a)) Nationality and Registration Mark Serial No. N493LX RK-244 1. Aircraft Make Model Series HAWKER BEECHCRAFT CORP BEECHJET 400A Name (As shawl on registration certificate) AddreSS (As shown on registration certificate) FLIGHT OPTIONS LLC Marta 2. Owner SHMITKA AIR INC Oty Fddwriond itakifits Sale OH SOUTHEASTERN MILLS INC IT AL rip 14142.1453 County USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. Er. O AIRFRAME (As described in Item 1 above) 0 POWERPLANT ill III PROPELLER Type APPLIANCE Ill ❑ Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Mn kkaki O00ons. U.0 U. S. Certificated Mechanic I Manufacturer Aden, 27 Umr 0utr•StitoII Foreign Certificated mermanc C. Certificate No. Cky Mara Stow NY Certificated Repair Station DJFA206D rip 13104 Corny USA PC Cenificaled maintenance Organization D. I certify that the repair and/or alteration made to the unit s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 App. B 7. Approva or Return to Service Pursuant to the authority given persons specified below, the unit identified in dem 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is Approved EiRejected FAA Fit. Standards X Persons Approved by Canadian Manufacturer Maintenance Organization Inspector Department of Transport BY Other (Specify) FLIGHT OPTIONS FAA Designee Repair Station Inspection Authorization 135 AIR CARRIER CERTIFICATE Certificate or Designation No. DJFA 206D FAA Form 337 poem EFTA00012041 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. B. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark end date work completed.) USA N493LX SN-244 4/11/2011 Nationality and Registration Mark Date REPAIRED LEFT FUSELAGE SKIN ABOVE PYLON IAW US TECHNICAL EO6110 227227. 8110-3 DATED MARCH 27, 2011. (WORK ORDER # 227277 SQ-208) WEIGHT AND BALANCE NEGLIGIBLE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: FOLLOW NORMAL MAINTENANCE PRACTICES FOR THE LT AFT FUSELAGE SKIN ASSEMBLY REPAIR AS CALLED OUT IN THE BEECHJET 400A MAINTENANCE MANUAL XXXXXXXXXXXUXXXXX)OOOO(XXXXXXXX)O(XXXXXXXXXXXJOOOOO(XXXXXXXXXXXXXYJCXXXXXX EFTA00012042 Fenn Approved Searle Tracking Number OW) No. 2120-CO2O 0 US OlOattnienl MAJOR REPAIR AND ALTERATION itiPlarit7 Fee FAA Unlit* or litany:anew (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Administration INSTRUCTIONS: Print or bre all fl ies. See Title 14 CFR §43.9. Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. §46301(a)) Nationality and Registration Mark Serial No. N493LX RK-244 Make Model Series HAWKER BEECHCRAFT CORP BEECHJET 400A Name (As shown on registration certificate) Address (As shown on registration certificate) FLIGHT OPTIONS LLC Mani 2. Owner SHMITKA AIR INC City Itrearnand Heights Stale OH SOUTHEASTERN MILLS INC ET Al Zip 4042.1453 County USA 3. For FAA Use Only - 4. Type - - 5. Unit Identification • Repair Alteration Unit Make Model Serial No. O AIRFRAME (As described in Item 1 above) B e 0 O POWERPLANT 0 0 PROPELLER Type O APPLIANCE 0 Manufacturer 6. Conformity Statement A Agency's Name and Address B. Kind of Agency Notre Fitoctivent tic U. S. Certificated mechanic I Manufacturer Address 27 SWOOP. Subs Foreign Certificated mechanic C. Certificate No. City Einonsonn SW* NY - Certificated Repair Station DJFA206D Vp 13104 Corny USA Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the unit s) Identified In item 5 above and deserted on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulatio s and that the information furnished herein is true and correct to the best of my knowledge. . . .. Extended range fuel per 14 CFR Part 43 it App. B • 7. Appro for Return to Service Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is KApproved :7 :Rejected • FAA Flt. Standards X Persons Approved by Canadian Inspector Manufacturer Maintenance Organization Department of Transport BY Other (Specify) FLIGHT OPTIONS FAA Designee Repair Station Inspection Authorization 135 AIR CARRIER CERTIFICATE FAA Form 337 riootR EFTA00012043 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality end registration mark and da e work completed.) USA N493LX SN-244 3/8/2011 Nationality and Registration Mark Date REPAIRED LEFT ELEVATOR IAW US TECHNICAL EO5770 226648. 8110-3 DATED APRIL 19 2010 (WORK ORDER # 227277 SQ-97) WEIGHT AND BALANCE NEGLIGIBLE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: FOLLOW NORMAL MAINTENANCE PRACTICES FOR THE ELEVATOR AS CALLED OUT IN THE BEECHJET 400A MAINTENANCE MANUAL XXXXXXXXXXXXXXXXXXXXXXXXXX)0000000(XXXXXXXXXXXXXXW)000000(XXXXXXXXWXX EFTA00012044 Form Approved Flectonic Tracking Nome el MAJOR REPAIR AND ALTERATION ore No. 2129.0320 I 1/30r2037 US lfr Cocoas-lent For FAA Use CMly ct TransP0nEOP (Airframe, Powerplant, Propeller, or Appliance) Fedora, Aviation Administration INSTRUCTIONS: Print °inn: all Writs. See Title 14 CFR §43.9, Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U S.C. §44701). Failure to report can result in a civil penalty for each such violation. (49 U.S.C. §46301(a)) Nationality and Registration Mark Serial No. N493LX RK-244 1. Aircraft Make Model Series HAWKER BEECHCRAFT CORP BEECHJET 400A Name (As shown on registration certificate) Address (As shown on registration certificate) SHMITKA AIR INC ET-AL Addma 2. Owner SOUTHEASTERN MILLS INC C/0 FLIGHT OPTIONS LW ca Renmore Hoehn Shoo ON ASCENT I I LW Zip 44142.1451 Country USA PRIME TIMEASSOCIATES LIC 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No • AIRFRAME (As described in Item I above) Er ❑ • POWERPLANT 0 • PROPELLER Type O APPLIANCE El Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Name Flirt (Mims. LLC U. S. Certificated Mechanic I Manufacturer Addams 27 Link Din Suite a Foreign Certificated Mechanic C. Certificate No. city ano/WNW Sur NV Certificated Repli‘ Station DJFA206D Zas 13604 Cony uta X Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the unit s) Identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pan 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel Signature/Date of Authorized IndiVidual per 14 CFR Part 43 App. B /49 "'' I 9 -.26 /e) . pprova r eturn to Service Pursuant to the authority given persons specified below, the unit identif . in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is Approved —LRejected FAA Flt. Standards X Persons Approved by Canadian Inspector Manufacturer Maintenance Organization Department Transport BY Other (Specify) FLIGHT OPTIONS FAA Designee Repair Station Inspection Authorization 135 AIR CARRIER CERTIFICATE Certificate or Si nature/Date of Authorized Individual Designation No. DJFA 2O6D FAA Form 337(,008) EFTA00012045 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) USA N493LX SN-244 10/19/2010 Nationality and Registration Mark Date SUBSTITUTED FASTENERS IN H-STAB LOWER SKIN PER EO5938 2272771FAD FROM US TECHNICAL 8110-3 DATED 10/18/2010 WEIGHT AND BALANCE NEGLIGIBLE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: NORMAL MAINTENANCE PRACTICES FOR THE HORIZONTAL STABILIZER ASSEMBLY AS CALLED OUT IN THE BEECHJET 400A MAINTENANCE MANUAL XXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXWXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXX EFTA00012046 form Approved ElettfOtt Tracking lOwnber ORD No. 21204020 0 2/20/2011 MAJOR REPAIR AND ALTERATION For FAA Usti0nly US Department otTrwnocnaton (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Administration INSTRUCTIONS: Print or type all entries. See Title 14 CFR §43.9. Part 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for Instructions and disposition of this form. This report Is required by law (49 U.S.C. §44701). Failure to report can result in a chill penalty for each such violation. (49 U.S.C. §48301(a)) Nationality and Registration Mark Serial No. USA N493LX RK - 244 1. Aircraft Make Model Series RAYTHEON AIRCRAFT COMPANY BEECHJET 400A Name (As shown on registration certificate) Address As shown on : • istration certificate) AIR GHISLAINE INC Address 2. Owner stale OHIO SOUTHEASTERN MILLS INC Co RICHMOND HEIGHTS ASCENT II LLC PAP 44143-1453 Canto USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. III ig AIRFRAME (As descnoed in Item 1 above) . O POWERPLANT In In PROPELLER Type D Et APPLIANCE manufacturer 6. Conformity Statement A Agency's Name and Address B. Kind of Agency Nam Fl IGHT OPTIONS I I C U. S Certificated Mechanic I Manufacturer mew 27 LINK DRIVE SUITE B Foreign Certificated Mechanic C. Certificate No. tab' niNSHAPiATON ewe NY Certificated Repair Sleben rs. 13904 Cowry USA / Certificated Maintenance Organization DJFA 206 D D. I certify that the repair andlor alteration made to the unit(s) Identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information furnished herein is true and correct to the best of my knov.ledge. Extended range fuel Signature/Date of Authorized Individual per 14 CFR Part 43 App. B et 0 7. Approval for Return to Service Pursuant to the authority g ten persons specified below, the unit Identified in item 5 was nspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is E Approved D Rejected FAA Flt. Standards Persons Approved by Canadian 1 Maintenance Organization I Manufacturer Department 0 Transport Inspector BY Other (Specify) FAA Designee Repair Station Inspection Authorization Certi icate or Signature/Date of Authorized Individual Designation No DJFA 206 D a-7-)/0 orm 377 .10 55; EFTA00012047 , EFTA00012048 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with ail previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished almore space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) USA N493LX FEB 04 2010 Nationality and Registration Mark Oate ACCOMPLISHED INSTALLATION OF MAIN LANDING GEAR HEAT SHIELD COVER KIT 128-1002-0001 SERIAL NUMBER 137 AS DESCRIBED IN ENGINEERING ORDER EO M32-10/08.023. ALL WORK ACCOMPLISHED I/ANV HBC MAIN LANDING GEAR HEAT SHIELD COVER KIT 128-1002-0001 SERIAL NUMBER 137 AND ENGINEERING ORDER M32-10/08-023 REV. A DATED 11-13-08. WEIGHT AND BALANCE NEGLIGIBLE. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: INSPECT THE HEAT SHIELD BLANKETS AND COVERS IIIVW FLIGHT OPTIONS INSPECTION PROGRAM OR THE MANUFACTURES INSPECTION PROGRAM AS APPROPRIATE. END D Additional Sheets Are Attached FAA Form 337 mum EFTA00012049 EFTA00012050 («TED STATES OF AMERICA DEPARTMENT OF TRANSPORTATIO N-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFI 1 NATIONALITYAND CATE 2 MANUFACTURER AND MCGEE REGISTRATION MAWS 3 ~CRAFT SERIAL 4 CATEGORY NUMBER .ty, !"`1':-4 7 -:err.: '7'. Co. 11 :4931:: ga; Tgre-rnert 6 AUTNORRY MID BASIS FOR ISSUANCE Thlo brontroas retkable hand pinuu dbEls fornrrironAd of 1968 old broth hard hoe Os Imp~ corm est r of be fa of 199Ancr anl MUM Enna:tom lo Ty bee torkslo ~doh b MINN90 area b mul81. niquIrsenb WIN opple to In carbon for SO ~Or rbo comprobonota and Ward otrop hoe alin on Irdonoronal cm AS troo4 cor r pro0040 by Ara • b iho Oserflon «CS as ~el barb Escloptiort Hon? 8 TERMS AND CONDITIONS Unkba agnet aunendaried. aulpengeO, molte d. Or a twolnation dab O WfrMls inee or!~ aaata4r long at 034 ~Manna •••• by the Admlniatrator. INY alreenfleona and 91 of Po Fodor Aviation Reauttgona, maintenance, and snore am pertonned n accorbanba Win Pans 21. 43. ond M olfcrtalrmrlorocl b M United SUS GATE OF ISSUANCE FMRE DUE DESIGNATION NUMBER 10/01/199? Any Sen. ogeOduCtlan. Or gang he 401~»may ba puNYlYN by • Ina not nogg THIS CERTIFICATE MUST BE °GRATED N % 11.000 r THE ~RIFT IN Arymanobt WITH APPLICABLE Saberant eg ~gang 3 yearn r toet. FEDERAL AVIATION REGULATIONS MA Fans 81004 (308) umlED STATES OF ~RICA DEPART MENT OF TRAN SPORTATION —FEDERAL AVIAT ION ADMINISTRATION STANDARD AIRWORTHINESS CER I. IMTIDNALITYNIp TIFICATE 2 144NUFACTUREA AMR MODEL • OBECOSTRATION MARRS 3 AmicstArr SCRIM. CATEGoar RAYTHEON AIRCRAFT COMPANY N79STA 400A `5 to' AUTHORITY AND OASIS FOR ISSUANCE RK-244 TRANSPORT orronrnerartralo earl Purina to • area fa *fin ogre hag son & Ina Fang& AnatOn Act ot ItiSS IMO Cowle .rtypeaod and hawk] IQ contotre to s g Maciata Col alumna& Wm OINC•140^ and has Ow Won a Me NO* 4:011.1•414 urofoc lo Is In conen root IM tIlOv.~1,13 Of ins sortie on 10f se worry by 41•1•11110 ow Cors cornAssAansoye an0 0415380 sonh on on Ingenabonal Crra AnanOn. agog os coco ~MOM r •04•0 Pina NCNE 6 Trim 5n0 CONORGNS onto ~nip •••••• ••••• moo görg70,71bani cen.scate oink. ns .1NO 4I•3 01 • usmånaton 0411.4 Olhers.•• as kw, do the egubt.shee by Its Aenianraglet 11u• 0 mentenanCe• 13•••rontam• mantanarc• I.CCOrSDAC•wel•••fll 1 43 analll ono imenorni all 0•00•1141d an ot ma agatwarAnabon oproonT Sue goo/psis and In* Won fl196 • ~1.11f138UMN0 • DATE OF ISSUANCE FAA -AESEN ATI K-10/01/99 ; If DESIGNATION ~ABER Ally anambOniagettuch On. 0t m cal.may beProhare tor hoon ACE—FSDC)--07 ,pro or ban. DNS CERTIFICA cormara SUM~soarer MUST BE DISPLAYED IN THE not exciorr93 onATION REGULATIONS AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL 4. Form 81C-2 (ago o U.S 0.100311X19 889438 EFTA00012051 EFTA00012052 SIAM OF MJERICA ADMINISTRATION NSPORTATIOK-FED ETIAL AVIATION EISSANTNENT OF THA S CERTIFICATE STANDARD AIRWORTHINES 3 AnIt.AArt Spun. I CATEGORY t mAKTFACRIRCA »zo mODEL. 1RASER I NATIONALITY NED SEGSPRATION Maki MPANY RAYTHEON AIRCRAFT CO RK-244 TRANSPORT 11793TA 400A M LIAlstile BASIS ton eatiOCE ~Ma riatelliitiflaYo --:. S. ALJTWORITO MAD otalAYOrer Ap 01 Igi4 ar0 to a s condiron be NIS I Slue Durward To Sa Feal oysters to ma iypb ~La ~tot fM Yn10MNee I GAMIN d by Oculderal ontitnrstall Slob as tart Inspects, wry lour Isltie cosign/1es~ arel A stall s ortach GISMO NA tro ricistatrass W us itysp its boon Sow n 10 mops 'gen ~sin 0pefie0n and nai CM1 ARMS^ tre0Opl ad tto Corwenvon an Ifeanmepo oroROPO by ~MI Sco Exonaorts: NONE py OIa AdnlnCtnwl. Ste T EONS AND CONISTi oNS onletren• altaplOtteO rtve kat CI s ternnallan S. Y PRONNOO eI Una some: Awrimiend, suw ande st nCa. ISO nerehCan re ats K tenp .n 1M sorsimonsa pesetzlittatt insratra : tY/C ryslo nld ARIUS*. fl Se NSW akworah sett Perireitr A 'Oats as ASOropeate. Rid 21.4. t °Ss Fasterantia SST accordant*...SP/JR SWIM DESIGNATION NUMBER VE DATE OF LSSIMNde ACE-PSI:0-07 emnol excipoiling 3 R-10 01/99 mik a may to NS Y • SO NA osstrAro SI .000. et+nwneonm E WIT H APP LICABLE FEDERAL Any elltrAbOrt, riPrO dUCI A2/1 .O/ T IN ACC ORD ANC ED IN, THE AC/CRAF S CEATINCesTE tAVST PE DISPLAY Pin, Os ADS THI W1ATION REO yIAT ION S. .• . - * V.B. o.no:tine 889058 • t: ." . -2414~:44, EFTA00012053 z EFTA00012054 ' • C C-A.A-Xdaa rt- cri-10 Forth Approved OMB No. 2120-0020 e MAJOR REPAIR AND ALTERATION • For FAA Use Only a (Airframe, Powerplant, Propeller, or Appliance) Office Identification „Mk Federal Aviadon Administration Ch-C4 ' PS00 -23 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model Beechcraft 400A 1. Aircraft Serial No. Nationality and Registration Mark RK-244 N793TA Name (As shown on registration certificate) Address (As shown on registration certificate) 2. owner NORTH CHANNEL LLC C Fll h ns LLC ET-AL Richmond Heights H 43-1494 3. For FM Use Only THE TECHNICAL DATA IDENTIFIED HEREIN HAS BEEN FOUND TO COMPLY WITH APPLICAB ftWORTHINESS REQUIREMENTS AND IS HEREBY APPROVED FOR USE ONLY ON THE A @IB A RCRATT, SUBJECT TO litINSPECTION1Y-A-PERSON- IN-14-CFR PART-43:7:-- APPROVING INSPECTOR 3 0 JUN 2004 OA FcTICI 91 War 4. Unit Identifies 6. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item 1above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. B. Kind of Agency C. Certificate No. x U.S. Certificated Mechanic earjaHauji „ Foreign Certificated Mechanic ?/O .2 7 7 it252 VS' - icturtond rz ts, 0" 44143 Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pan 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date Signature of Authorized Individual /2- —02 .:9--017 ------ tz_____-- 7. Approval for Return To Service Pursuant to the authority given persons specified below the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is X APPROVED 0 REJECTED FM Flt. Standards Other (Specify) Manufacturer Inspection Authorization Inspector BY ll Transport i il i O da , t Alkei to FM Designee Repair Station Person Approved by Canada Airworthiness Group flee Date of Approval or Rejection Certificate or Sig Designation No. I,2 98- O11 CA2006is FM Fenn MT MA% EFTA00012055 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed ) Installed the following equipment In Beechcraft 400A SIN RK-244: Equipment Install Manual Maintenance Manual Pilot's Guide 009-18001.001 009-18000-001 TAWS 8000 (Class B) N/A Current Revision Current Revision Installed Goodrich Avionics Systems Landmark TAWS8000 system (TSO-C151a Class B) using Flight Options LLC electrical drawing 400-3446-20-01 and applicable manufacturers installation manuals listed above. This installation includes the optional Terrain Display function. FAA Approved Flight Manual SupplernenialoliA4i0iii6ist,oe,thrOci (Cid rithccaft when the Class B TAWS 8000 system is in use: • ' .• '• The TAWS 8000 system has been previously approved for multiple Beechjet aircraft under STC ST01881CH-D, with the Terrain Display function enabled. This installation has been inspected and found to conform to the operational and technical characteristics of STC ST01881CH-13 with minor deviations in location of switching relays and wiring interface points as depicted on Flight 0plionSiLLC drawing 400-3446-20-01. Similarity to STC ST01881CH-D is the basis for this request for field approval. Using the respective manufacturer's instructions for post-installation ground tests. performed operational checks on all systems. The systems performed to manufacturer's specifications and no interference to existing aircraft systems was noted. In addition to specific instructions contained in the manufacturer's installation manual(s) noted above, all physical mounting considerations were made with reference to AC 43.I3.2A. Chapter I. Chapter 2. Chapter 3, and Chapter II as they apply to this installation. Regarding attachment to additional structure all alterations were inspected to comply with the aircraft manufacturer's structural repair and alteration specifications. In addition to specific instructions contained in the manufacturer's installation manual(s) noted above, wire bundles were fabricated using MIL-SPEC, Teful wire, that meets the acceptability requirements of AC43.13-1B, Chapter I I, Section 7, Paragraph 11-85 (a) and/or (b). paragraph 11.88. and paragraph 11.89. All wiring was masked in accordance with AC43.B-18, Chapter I I, Section 16, Pam. 11.206. 11.207, 11.208 (a) and/or (b) and 11.210 (a) and (b). Individual wires were formed into bundles by lacing and tying using the techniques described in AC43.I3-1B, Chapter II, Section 12, paragraph 11.158 (a) and (b). Cables were routed and secured in the aircraft using AC43.13-18. Chapter I I, Section 8, Para.11-96. (a) through (gg) as a guide. An electrical load analysis was performed per AC43 13-1B Chapter II Section 3 Paragraph 36. The maximum probable continuous electrical load does not exceed 80% of the generator(s) output capacity. All compasses aboard this aircraft were checked for accuracy on completion of this installation. The aircraft equipment list and weight and balance were updated instructions for continued aliworifftness (ICA) for thls aircraft alteration and Interfacing components are as follows; (1) Introththtion to the aircraft altered is explained above. (2) Description of the major alteration is explained above. —(3) —Demotion Information is described In Um doeurrientallstod above for each particular.product ----- (4) servicing, (8) Diagram, and icciii platy. (9) Ssrasiess iir ements, (10) Application of protective treatment') (11) Data, (12) LIM of Special Tools (14) Recommended Overhaul Periods. and (15) Airworthiness limitation section are not applicable. (5) Maintenance, (6) troubleshooting Information (7) Removal and Replacement, and (13) for commuter category alrenift of the products listed, will be IAW the appropriate and current manufacturers Installation manuals. (16) Revision wilt be in accordance with the manufacturers' maintenance manuals and submitted to the local FSDO. Antennas and other parts and materials Installed such as wiring, circuit breakers, switches, annunciators, clamps, doublers, shelves, and racks will be Inspected In conjunction with the Raytheon Sectchjet 400A Phase C Inspection program, for condition, *acuity of attachment evidence of damage, and normal operation IAW FAR 25.1529 and/or applicable manufacturers service instructions n Additional Sheets Are Attached 'U.S GPO 1994-568-012/00019 EFTA00012056 JAN 03 2005. • • Form Approved OMB No. 2120-0020 0 MAJOR REPAIR AND ALTERATION , us Dem-wont For FAA Use Only (Airframe, Powerplant, Propeller, or Appliance) FM.* Avision Office Identification .11-2- Mimi*Aram 4 C-74 - FS Da —2 3 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix 8, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model Beechcraft 400A 1. Aircraft Serial No. Nationality and Registration Mark RK-244 N793TA Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner NORTH CHANNEL LLC CIO Flight ions LLC ET-AL Richmond Heights OH 44143-1494 3. For FAA Use Only .._...._ _ 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item t above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer S. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Lynn H. Huyen X U.S. Certificated Mechanic Foreign Certificated Mechanic A8P 278825845 c mon ag b 43-14114 Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the uniqs identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date Signature of Authorized Individual /*, -.2.2- - 0 9/ .7_______---- 7. Approval for Return To Service Pursuant to the authority g yen persons specified below the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is I213 APPROVED 0 REJECTED FM Rt. Standards Other ( Inspector Manufacturer Inspection Authorization BY i FM Designee Repair Station Certificate or Person Appro by Transport Canada invort ness Grou S Iee Date of Approval Rejection Designation No. FOAfilan SA NMI EFTA00012057 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) Removed existing MK-VI GPWS system in conjunction with installation of new TAWS (EGPWS) system reference FM form 337 dated 12-22-O4. Aircraft weight and balance and equipment list data have been revised. END 0 Additional Sheets Are Attached *U.S.GPO:1994-568-012/00019 EFTA00012058 Form Approved OMB No. 2120-0020 0 MAJOR REPAIR AND ALTERATION For FAA Use Only (Airframe, Powerplant, Propeller, or Appliance) US Copan:nen 0 Office Ffiderol Mutton Aclairattation 0 t5'.--- 7/31.'-- FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for INSTRUCTIONS: Print or type all entries. See FAR 43.9. by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not is require d instructions and disposition of this form. This repod n Federal Aviation Act of 1958). to exceed 24.000 for each such violation (Sectio 901 Model Make 400A BEECHJET 1. Aircraft Nationality and Registration Mark Serial No. RK244 N793TA Address As shown on istration certificate) Name (As shown on registration certificate) 2. Owner FLIGHTOPTIONS I NO H S.. OHIO 44143 3. For FAA Use On y 4. Unit Identification 6. Type Model Serial No. Repair Alteration Unit Make ' x (As descnbedin "ern 1 AIRFRAME POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Con ormity Statement C. Certificate No. B. Kind of Agency A. Agency's Name and Address U.S. Certificated Mechanic MPLETIONS INC. Foreign Certificated Mechanic R4GR031Y HI 4143 X Certificated Repair Station LEVELANCL Manufacturer and described on the reverse or attachments I certify that the repair andior alterati on made to the units identified in item 4 above l Aviation Regulations and that the D. the requirements of Part 43 of the U.S. Federa hereto have been made in accordance with to the best of my knowle dge. information furnished herein is true and correct fA rized Indiv' ual Date 12-10-2004 7. Approval for Return To Se ce by the item 4 was inspected in the manner prescribed s specified•below the unit identified in Pursuant to the authority given person O REJEC TED Administration and is l2; APPROVED Administrator of the Federal Aviation Other (Specify) FAA FIL Manufacturer Inspection Authorization Standards BY Person Approved by RECEIVED FAA Designee X Repair Station Transp ort Certificate or Signature of Authorized Individual DEC 16 2004 Date of Approval or Rejection Designation No. 12-10-2004 R4GRO31Y ellr atite-- f AA Filar, 317 o,N EFTA00012059 NOTICE aircraft record. An alteration must be Weight and balance or operating limitation changes shall be entered in the appropriate alterations to assure continued conformity with the applicable airworthines s requirements. compatible with all previous 8. Description of Work Accomplished mark and date work completed.) (If more space is required, attach additional sheets. Identify with aircraft nationality and registration AIRCRAFT: BEECHJET 400A N793TA RK-244 FORM FABRICATED AND INSTALLED THE FOLLOWING USING APPROVED DER DRAWINGS SEE FAA 8110-3 DATED 12-08-2004 1) Ft/H Galley 2) a) Assembly drawing #36G-200A006 b) Installation drawing #36G-200F006 those prescribed by the There are no additional inspections required for continued airworthiness other than aircraft manufacturer during regular inspections. END 0 Additional Sheets Are Attached •11.S.GP(11994-568-012/00019 EFTA00012060 Form Approved 0 OMB No. 2120-0020 us c.vikvvnevii MAJOR REPAIR AND ALTERATION For FAA Use Only a Federal Aviation Administration (Airframe, Powerplant, Propeller, or Appliance) _I Q OffArAliFS no INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result . it penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 123 Make Model RAYTHEON 400A 1. Aircraft Serial No. Nationality and Registration Mark RK-244 USA N793TA Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner SAMAIR INC ET-AL WICHITA, KS 67207 3. For FAA Use Only THE TECHN CAL DATA IDENTIFIED HEREIN HAS BEEN FOUND TO COMPLY WITH APPLICABL NYORTHtNESS REQUIREMENTS AND IS HEREBY APPROVED FOR USE ONLY ON TH BJECT TO CONFOR ITY INSPECTION BY A PERSON IN 14 CFR PART 43.7. APPROVING INSPECTOR DATE K.°1-2-S103 AEA FSDO 23 4. Unit Identificall ype Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item 1 above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. STEPHEN J. MAIDEN X U.S. Certificated Mechanic C/O FLIGHT OPTIONS LLC Foreign Certificated Mechanic A 297605039 Certificated Repair Station RICHMOND HEIGHTS, OH 44143 Manufacturer D. I certify that the repair and/or alteration made to the unit(s identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requi ements of Part 43 of the U.S. Federal Aviation Regulations and Mat the information furnished herein is true and correct to the best of m knowledge. Date JUNE 10, 2003 7. Approval for Ret n To ice Pursuant to the authority given persons specified below the unit identified in m 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is jn APPROVED 0 REJECTED FAA Flt. Standards Other (Specify) OPTIONS FLIGHT SUPPORT, Manufacturer Inspection Authorization Inspector INC., dibia FLIGHT OPTIONS BY FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection Certificate or Designation No. JUNE 10, 2003 KEITH GAWSYSZAWSKI DJFA206D FM Form 31? mig EFTA00012061 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatiblewitlzall previous alterations to assure continued conformity with the applicable ainvorthiness requirements. 8 Description'9trork Accomplished (If more spaceis required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) INSTALLED ROCKWELL COLLINS, INC., SUPPLEMENTAL TYPE CERTIFICATE #ST00881WI-D, MODIFICATION OF COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 6.04a RECEIVER TRANSMITTER TO A COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 7 TCAS II RECEIVER TRANSMITTER IN ACCORDANCE WITH COLLINS INSTALLATION INSTRUCTIONS AS LISTED ON AML tt ST00881WI-D. AIRCRAFT FLIGHT MANUAL SUPPLEMENT INSERTED INTO AIRCRAFT FLIGHT MANUAL. NO CHANGE TO WEIGHT AND BALANCE. O Additional Sheets Are Attached *U.S.GPO:1994-568-012/CO019 EFTA00012062 1 3 JUN 2003 Form Approved O OMB No. 2120-0020 US Department MAJOR REPAIR AND ALTERATION For FAA Use Only rd (Airframe, Powerplant, Propeller, or Appliance) Office Identification :31-f— Falderal Aviation Administration INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or stiCAgrESIX) instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result 23111 penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model RAYTHEON 400A 1. Aircraft Serial No. Nationality and Registration Mark RK-244 USA N793TA Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner SAMAIR INC ET-AL WICHITA, KS 67207 3. For FAA Use On y 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item 1above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Stephen J. Maiden X U.S. Certificated Mechanic C/O FLIGHT OPTIONS LLC Foreign Certificated Mechanic A297605039 Certificated Repair Station RICHMOND HEIGHTS, OH 44143 Manufacturer ' ' D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requ' information furnished herein is true arid correct to t Date 10 June, 03 7. Pursuant to the authority g ven persons specified below, the unit identified in it 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is X) APPROVED O REJECTED FAA Flt. Standards Manufacturer Inspection Authorization Other (Specify) FLIGHT OPTIONS LLC BY CERTIFICATE AGENCY AIR Inspector Person Approved by Transport FAA Designee Repair Station Canada Airworthiness Grow Date of Approval or Rejection Certificate or Designation No. fu tad to too DJFA206D FM?cal 33? IOW EFTA00012063 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. rict a -9 i; 8. Destflpli of Work Aecomplished (If more spacriseequired, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) INSTALLED ROCKWELL COLLINS, INC., SUPPLEMENTAL TYPE CERTIFICATE #ST00881WI-D, MODIFICATION OF COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 6.04a RECEIVER TRANSMITTER TO A COLLINS TCAS II SYSTEM INSTALLATION WITH COLLINS TTR-920 CHANGE 7 TCAS II RECEIVER TRANSMITTER IN ACCORDANCE WITH COLLINS INSTALLATION INSTRUCTIONS AS LISTED ON AML # ST00881WI-D. AIRCRAFT FLIGHT MANUAL SUPPLEMENT INSERTED INTO AIRCRAFT FLIGHT MANUAL. NO CHANGE TO WEIGHT AND BALANCE. END 0 Additional Sheets Are Attached *U.S.GPO:1994-568-012/00019 EFTA00012064 r Satiltbinalto of Amnia Pepartment of transportation — Aebtral tAbintion Abministralints $upplemental Jgpe Tertifirate ../14;9a 0./e ST00881INI.D .ffa trinVeale. t;hoowlie Rockwell Collins, Inc. 400 Collins Road NE, MS 164.100 Cedar Rapids, IA 52498 rerlOns arc/46 refer res a, r/rwirrsi rfc 46Arreverionoarekne en 46 Snarteivra orairavnAiievpo derOr a.; bynee.Aftherevr nonAs t neivreedionmaree:vwennia Val • erst.4:: • derpottr/tivar. niaseetliteduce Vienckdres 1:24”4.- • •See attached FAA Approved Model List (AML) • No. ST0088IWI-D for list of approved airplane models and applicable airworthiness regulations. Sive.soraiv. rtf4r: Modification of Collins TCAS 11 or TCAS 94 (TCAS II) system installation with Collins TTR-920 Change 6.04a Receiver Transmitter to a Collins TCAS II or TCAS 94 (TCAS II) system installation with Collins TTR-920 or Collins 17R-921 or Cellists TTR-4000 Change 7.0 TCAS 11Receiver Transmitter and optional TPR-901 in accordance with Collins Installation Instructions as listed on AML No. ST0088IWID, Revision -, or later FAA approved revisions. 5Saoardshei ( 0 Approval of this change in type design applies to the above model aircraft only. (2) Compatibility of this design change with previously approved modifications must be determined by the installer. (3) A copy of this Certificate and FAA Approved Model List (AML) No. ST00881WI-D issued June 30, 2000, or later FAA approved revision, must be maintained as pan of the permanent records for the modified aircraft. (4) Prior installation and approval of a Collins TTR-920 Change 6.04a Receiver Transmitter is a prerequisite to this STC. (5) If the holder agrees to permit another person lo use this certificate to alter the product, the holder shall give the other person written evidence of that pennission. .974, sada. .isenvevt&to ar/er rey(oriU Lf. ho.h‘l At, evreresiafattesentetU es 10e/ sena atenstAnet Jet.irina neater' Pe a AryesentieniVi Ate 0.l esCinvtvde nrferAitastafr ,,,Z1Lreereateer/re Vide !Rea- .1/4 ,-vtetwain . June 29, 2000 firor:• trtwr«l. !Alt e/ti.i.tuageo June 30, 2000 fere.o syno-sated. July 14, 2000, December I, 2000 11111111- Administrator, DAS-500864-CE My •iteronon of tai. tertifiCott le penialible by • tine of sot exteallO9 $1.000. Or Oar @Omen, aet OflteillIsfr J rears. Or boa. IAA r0t. $110-2110-44) Via I TOD Noy be into rrrrr to error et wf t0 PM 73.• . EFTA00012065 1 EFTA00012066 Avionics Cerblicalkan Center Rockwell Collins May 14, 2003 WO030737.DOC Fli ht O lions Cleveland, OH 44143 Tel: (216) 797-3500 Attention: Mr. Jody Kremsreiter/ Mr. Richard Fine (Collins on-site) Subject: STC ST00881WI-D Modification of Collins TCAS II System Installation with Collins TTR-920 Change 6.04a Receiver Transmitter and TPR-900 Mode S to a Collins TCAS II System Installation with Collins TTR-920, Collins TTR-921 or Collins TTR-4000 Change 7.0 TCAS II Receiver Transmitter and optional TPR-901 in Part 25 Aircraft Dear Mr. Kremsreiter: Enclosed is a compact disk with one copy each of the following FAA approved STC data: 1. STC ST00881WI-D Certificate, dated December 1, 2000. 2. FAA Approved Model List (AML) Number ST00881WI-D, amended April 15, 2003. 3. Drawing Index 992-4358-001. Revision M. 4. One copy of each drawing listed on Drawing Index 992-4358-001. 5. Airplane Flight Manual Supplement, ACC-00-105, Revision -. This letter is our authorization for Flight Options to use this STC as basis for the installation of our equipment in our at lanes based on the following model and serial numbers provided by Mr. of Rockwell Collins. EFTA00012067 '1 EFTA00012068 Flight Options WO030737.DOC STC ST00881WI-D May 14, 2003 Page 2 STC ST00881WI-D Model MSN MSN 400A RK006 RK248 RK016 RK252 RK022 RK257 RK027 RK260 RK030 RK264 RK031 RK265 RK045 RK268 RK062 RK271 RK093 RK273 RK146 RK274 RK161 RK276 RK168 RK279 RK178 RK282 RK180 RK284 RK186 RK289 RK189 RK292 RK195 RK295 RK198 RK297 RK201 RK301 RK202 RK305 RK209 RK307 RK222 RK310 RK230 RK317 RK234 RK324 RK237 RK327 RK239 RK328 RK244 RK334 RK245 Please return a record of any additional aircra (s) to me for installations performed using this STC. My fax number is Collins needs to receive this data before we can authorize additional installations. EFTA00012069 % % a ..) EFTA00012070 ••• Flight Options WO030737.DOC STC ST00881WI-D May 14, 2003 Page 3 Flight Options is responsible for the regulatory approval of any deviations from STC ST00881WI-D. Instructions explaining how to access the data on the CD have been inserted inside the jewel case. Customer satisfaction is important to us, and we would appreciate your input. Please corn lete and return the enclosed questionnaire or email me at nd let us know how we can best serve you. We trust this data will fulfill your installation requirements. However, if you have any questions, please call me at Collins Avionics Certification Center /pah Enclosure EFTA00012071 EFTA00012072 ee US DoPan:mon 0 MAJOR REPAIR AND ALTERATION (Airframe, Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 For FAA Use Only Federal /Melton Arh ienn Admkdstrallon INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 or subsequent revision for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 31,000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model Beechjet 400A 1. Aircraft Serial No. Nationality and Registration Mark RK- .214 4 USA N 793T/) Name (As shown on registration certificate) Address (As shown on registration certificate) Sitni AL.e TP C 2. Owner er-At_ coicitarf, KS (.7. 1 °2 3. For FAA Use Only The data identified herein complied with applicable airworthines - The above described aircraft subject to conformity inspected - - ----- a - - --- --- ' This approval is ontifor this'aircraftmakerm Date Approving Inspector tr i m - 12002 4. Unit Identification 6. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item 1above) X POWERPLANT 71 • PROPELLER • Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Keith Gawsyszawski X U.S. Certificated Mechanic i i Foreign Certificated Mechanic AP 287603483 Richmond Hts., ON 44143 Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requrements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date April 5, 2002 7. Approval for Return To Service Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 00 APPROVED U REJECTED FM Fit. Standards Other (Specify) Manufacturer ,K., Inspection Authorization Inspector BY FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection Certificate or Designation No. 44 4,1 ?00?- iv,-1.1374.93A3P1 PMNoto EFTA00012073 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) 1. Removed existing Tail Navigation Light Assembly including the rubber shock mount. 2. Installed Whelen Engineering, Inc. Model 70805-01 Tail Position Light Assembly in accordance with part number 04-0112558-00 instruction sheet to include installation procedures and drawing number 70805. 3. The light assembly will be operationally tested under Flight Options Continuous Airworthiness Maintenance Program under Phases IC, 9C and I7C. 4. Weight and Balance change found negligible. END-- Additional Sheets Are Attached *U.S.GPO:1994-568-012/00019 EFTA00012074 'arm Approved PO CO U.S. Department MAJOR REPAIR AND ALTERATION OMB No. 2120-0020 For FAA Use Only (Airframe, Powerplant, Propeller, or Appliance) of Transportation Federal Malkin Office Identification Administration Li W!? Mt- INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed S1,000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model I. Aircraft RAYTHEON AIRCRAFT 400A Serial No. Nationality and Registration Mark RK-244 USA N793TA Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner KETTLER ROBERT, MICHELS PIPELINE CONSTRUCTION INC, SOUTHEASTERN MILLS WICHITA KS 67207-1315 INC, REI AIR LLC, ET-AL 3. For FAA Use Only 4. Unit Identification S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT • PROPELLER TYPe APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address 8. Kind of Agency C. Certificate No. RAYTHEON AIRCRAFT SERVICES us. Certificated Meclunie CRS-XA14605K Foreign Certificated Mechanic LIMITED AIRFRAME X Certificated Repro Station SAN ANTONIO TEXAS 78216 Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best ofm knowled Date 12-10-01 Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected 'n the manner prescribed by the Administrator of the Federal Aviation Administration and is Pi APPROVED 0 REJECTED FAA Fit- Standards Manufacturer Inspection Authorization Other (Specify) BY Inspector FAA Designee x Repair Station Person Approved by Transport • a Airworthiness Grou Date of Approval or Rejection Certificate or Desisnation No. 12-10-01 CRS-XA14605K FAA Form 337 (12.81) EFTA00012075 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (Ifmore space is required, attach additionalsheets. !den* with aircraft nationality andregistration mark and date work completed.) MAKE: RAYTHEON 400A S/N: RK-244 REG: N793TA DATE: 12-10-01 ALL SEVEN CABIN SEATS AND THE LAVATORY SEAT WERE FIREBLOCKED IN ACCORDANCE WITH FAR 25.853 (a) APPENDIX F PART I (a) (1) (ii) AND FAR 25.853 (c) APPENDIX F PART II AMENDMENT 25-83. THE FIREBLOCKING WAS ACCOMPLISHED IN ACCORDANCE WITH THE SKANDIA INC. TEST PLAN #8335 REV. IR DATED 12-04-01, REFERENCE THE FORM 8110-3 DATED 12-04-01 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERY-410100-CE, STRUCTURAL SPECIAL. SEE THE FORM 8110-3 DATED 10-09-01 AS REFERENCE FOR THE FIREBLOCKING FLAMMABILITY TEST RESULTS OF THE SEATS THAT WAS PREVIOUSLY TESTED AND APPROVED ON THE SKANDIA INC. TEST PLAN #8118 REV. IR DATED 10-01-01 FOR P/N 8118-1 AND 8118-2 ONLY, APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERY-410100-CE, STRUCTURAL SPECIAL. END El Additional Sheets Are Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 EFTA00012076 Form Approved MAJOR REPAIR AND ALTERATION OMB No. 2120.0020 0 I Department (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only el Federal Transportation Aviation Office Identification Administration .9-7 9 a -, INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such vjolation (Section 901 Federal Aviation Act of I9581. Make Model I. Aircraft RAYTHEON AIRCRAFT 400A Serial No. Nationality and Registration Mark RK-244 USA N793TA Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner ICEITLER ROBERT, MICHELS PIPELINE CONSTRUCTION INC, SOUTHEASTERN MILLS WICHITA KS 67207-1315 INC, REI AIR. LLC, ET-AL 3. For FAA Use Only 4. Unit Identification S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER Type ' APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. RAYTHEON AIRCRAFT SERVICES U.S. Certifkated Mechanic CRS-XA14605K Foreign Certificated Mechanic LIMITED AIRFRAME - X Certific thated Repair Station SAN ANTONIO TEXAS 78216 Mara a:rum RADIO CLASS 1,11,III D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of m knowled e. Date 12-10-01 Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is l7 APPROVED 0 REJECTED FAA Fit Standards Manufacturer Inspection Authorization Other (Specify) BY Inspector FAA Designee x Repair Station Pawn Approved by Transport Canada Airworthiness Group Date of Approval or Rejection Certificate or Designation No. 12-10-01 CRS-XA14605K FAA Form 317 (12.88) EFTA00012077 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (if more space is required attach additional sheets. Men* with aircraft nationally andregistration mark and date work completed) MAKE: RAYTHEON 400A SIN: RK-244 REG: N793TA DATE: 12-10-01 MODIFIED THE EXISTING RIGHT HAND FORWARD GALLEY/CLOSET CABINET IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #528-2526-001 REV. A DATED 07-27-00, REFERENCE THE FORM 8110-3 DATED 12-07-01 APPROVED DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-405126-CE, STRUCTURAL. THE MODIFICATION CONSISTED OF INSTALLING ELECTRICAL PROVISIONS FOR A MAPCO, CUP HOLDERS AND LIGHTING IN THE FORWARD SECTION OF THE BAGGAGE CABINET. THE ELECTRICAL WIRING FOR THE GALLEY/CLOSET CABINET WAS INSTALLED IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #RAS-73-0112 REV. ER DATED 12-05-01, REFERENCE THE FORM 8110-3 DATED 12-07-01 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-710137-SW, SYSTEMS AND EQUIPMENT. THE MODIFIED GALLEY/CLOSET CABINET HAS A NEW WEIGHT OF 84.5 Lbs. AND A MOMENT OF 12844.0. THE WEIGHT AND BALANCE FORM AND THE EQUIPMENT LIST HAVE BEEN REVISED AND BOTH FORMS HAVE BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END Ei Additional Sheets Me Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 EFTA00012078 Form Approved egp/ 1) MAJOR REPAIR ANDALTERATION OMB No. 2120-0020 US. Department (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only of Transportation Office Idenfification Federal Aviation .....Nca-207 p t. AdmInistntIon INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 51,000 for each such *lotion (Section 901 Federal Aviation Act of 19581. Make Model 1. Aircraft RAYTHEON AIRCRAFT 400A Serial No. Nationality and Registration Mark RK-244 USA N793TA Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner KETTLER ROBERT, MICHELS PIPELINE CONSTRUCTION INC, SOUTHEASTERN MILLS WICHITA KS 67207-1315 INC, REI AIR LLC, ET-AL 3. For FAA Usc Only 4. Unit Identification S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPFI 1 Pla. Wile APPLIANCE Manufacturer 6. Conformity Statement A. Agencys Name and Address B. Kind of Agency C. Certificate No. RAYTHEON AIRCRAFT SERVICES U.S Certificated Mechanic CRS-XAI4605K Foreign Catikated MeCtiallk 1115 PAUL WILKINS ROAD LIMITED AIRFRAME X Certificated Repafr Station SAN ANTONIO TEXAS 78216 Mandsctunt D. I certify that the repair and/or alteration made to the unit( ) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information tbmished herein is true and correct to the best of m Date 12-10-01 Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is la APPROVED III REJECTED FAA Mt. Standards Manufacturer Inspection Authorization Other (Specify) BY Inspector FAA Designee x Repair Station Person Approved by Transport Date of Approval or Rejection Certificate or Desinnation No. 12-10-01 CRS-XA14605K FAA Form 337 (1243s) EFTA00012079 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be ' compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished #fmore space it required. attach additional sheets. Identify with aircraft nationally and registration mark and date work completed) MAKE: RAYTHEON 400A S/N: RIC-244 REG: N793TA DATE: 12-10-01 FABRICATED AND INSTALLED A NEW THE LIFE VEST CONTAINER IN THE TOILET CABINET IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #562-3832-001 REV. IR DATED 08-22-00, REFERENCE THE FORM 8110-3 DATED 12-07-01 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #DERT-405126-CE, STRUCTURAL. THE LIFE VEST CONTAINER WAS FABRICATED USING AAR COMPOSITES FLAT NOMEX PANEL P/N ATR-FP-251F2, REFERENCE THE FORM 8110-3 DATED 07-01-99 APPROVED BY DESIGNATED ENGINEERING REPRESENTATIVE, #CHI-410, STRUCTURAL SPECIAL. THE MODIFICATION OF THE CONTAINER WAS FOR THE INSTALLATION OF A NEW EASTERN AERO MARINE LIFE VEST, P/N PO1074-113. THE WEIGHT CHANGE IS NEGLIGIBLE. THE EQUIPMENT LIST HAS BEEN REVISED TO REFLECT THE NEW LIFE VEST AND HAS BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END El Additional Sheets Am Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 EFTA00012080 ••• 0 I Form Approved OMB No. 2120-0020 e'z,-. us oepaiment MAJOR REPAIR AND ALTERATION .. For FAA Use Only "le errnhnscxxiatan .......„„n Federal Million (Airframe, Powerplant, Propeller, or Appliance) ftb oge; ' c'ethisro Op INSTRUCTIONS: Print or type all entries. See FAR 43.9 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model RAYTHEON 400A 1. Aircraft Serial No. Nationality and Registration Mark RK-244 N793TA Name (As shown on registratkin certificate) Address (As shown on registration certificate) 2. Owner AIRCAP LLC WICHITA, KS 67207-1315 3. For FAA Use On y THE DATA IDENTIFIED HEREIN COMPLIES WITH APPLICAB AIRWORTHINESS REQUIREMENTS AND IS APPROVED ONLY FOR THE ABOVE DESCRIBED AIRCRAFT SU d CT T C NFO TY INSPECTION BY A PERSON AUTHORIZED IN FAR 43.7 APR 0 4 2000 DATE DPA-FSDO 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As describedin Item 1 above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. U.S. Certified Mechanic Elliott Aviation Foreign Certified Mechanic X Certificatedted Repair Station CGHR812C Moline, IL 61266-0100 Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date 3/29/2000 7. Approv Pursuant to the authority given persons specified below, the unit dentified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 03 APPROVED 0 REJECTED Other (Specify) FAA Fit. Standards Manufacturer Inspection Authorization Inspector BY Person Approved by Transport FAA Designee X Repair Station Airworthiness Group Da e of Approval or Rejection Certificate or Siaillilli Designation No. ft 9/ 90D0 CGHR812C FAA Form 337 (1zes) EFTA00012081 NOTICE be compatible entered in the appropriate aircraft record. An alteration must Weight and balance or operating limitation changes shall be ble airwort hiness require ments. with the applica with all previous alterations to assure continued conformity 8. Description of Work Accomplished accomplished) with aircraft nationality endregistration mark and date work (if more space is required, attach additional sheets, Identify CABIN DISPLAY MODEL 2700. 1. INSTALLED PENNY & GILES PASSENGER DIGITAL AFT OF DATUM WAS FLUSH MOUN TED IN THE FWD RH CLOSET/GALLEY CABINET AT 152.0 INCHES 2. THE CABIN DISPLAY CABIN ET. THE UNIT WILL DISPLAY SION HARNESS LOCATED IN THE FACING AFT. CONNECTED UNIT TO FACTORY PROVI N. THE DISPLA Y IS FAA/P MA CERTI FIED. THE CABIN INFOR MATIO TEMPERATURE, TRUE AIRSPEED, ALTITUDE AND E.TA 2700-0 03-026 REV 0 DATED DECEM BER INSTALLATION MANUAL P/N DISPLAY WAS INSTALLED IN ACCORDANCE WITH B&D 19,1996. 11-107 AND FAR DANCE WITH AC43.13-1B SECTION 8 PARAGRAPH 3. PERFORMED EMI INTERFERENCE TEST IN ACCOR 23.1309 AND 23.1431. TO REFLECT THIS LIST AND AIRFRAME LOGBOOKS WERE REVISED 4. WEIGHT AND BALANCE DATA, EQUIPMENT INSTALLATION. REMENTS OF 14 IONAL MAINTENANCE IS REQUIRED BEYOND THE REQUI 5. FOR THE ABOVE INSTALLED SYSTEM NO ADDIT E MAINTENANCE AND ALTER ATION S PER THE FOLLOWING CFR PART 91 SUBPART E MAINTENANCE, PREVENTATIV INSTALLATION MANUAL• REV 0 DATED DECEMBER 19,1996 (1) B&D INSTALLATION MANUAL P/N 2700-003-026 ESS CHECKLIST 5. INSTRUCTIONS FOR CONTINUED AIRWORTHIN (1) INTRODUCTION-REF THIS 337 FORM BLOCK 1 (2) DESCR IPTION -REF THIS 337 FORM BLOCK 8 337 FORM BLOCK 8 (3) CONTROL OPERATION INFORMATION- REF THIS (4) SERVING INFORMATION-NOT APPLIC ABLE BLOCK 8 (5) MAINTENANCE INSTRUCTIONS-REF THIS 337 FORM BLOCK 8 N- REF THIS 337 FORM (6) TROUBLESHOOTING INFORMATIO VAL AND REPLA CEMEN T-REF THIS 337 FORM BLOCK 8 (7) REMO (8) DIAGRAMS- NOT APPLICABLE ABLE (9) SPECIAL INSPECTION REQUIREMENTS-NOT APPLIC ABLE PROTE CTIVE TREAT MENTS -NOT APPLIC (10) APPLICATION OF • (11) DATA-NOT APPLICABLE (12) LIST OF SPECI AL TOOLS -NOT APPLIC ABLE ANALYSIS-NOT APPLICAPLE (13) COMMUTER CATERGORY NC- ELECTRICAL LOAD (14) NO ADDIT IONAL OVERH AUL TIME LIMITA TIONS APPLICABLE (15) AIRWORTHINESS LIMITATIONS SECTION-NOT WITH A A LETTER WILL BE SUBMITTED TO THE LOCAL FSDO (16) REVISION-IF A REVISION TO THIS ICA IS NECESSARY ED ICA. COPY OF THE REVISED FM FORM 337 AND REVIS END ❑ Additional Sheets Are Attached * U.S. G.P.O 1990-761-753 EFTA00012082 • APR 2 1 MI I Form Approved OMB No. 2120-0020 US Department MAJOR REPAfR AND ALTERATION For FAA Use Only of TronsporisSan (Airframe, Powerplant, Propeller, or Appliance) Fodor& Aviation Atm Idettny i lliefl- AdmInistraUon -FSDO INSTRUCTIONS: Print or type all entries. See FAR 43.9 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model BEECH 400A 1. Aircraft Serial No. Nationality and Registration Mark RK-244 N793TA Name (As shown on registration certificate) Address (A wn n strafion certificate) AIRCAP LLC 2. Owner WITCHA KS 67207-1315 3. For FAA Use On y 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME As described in Item 1 above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Con ormity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. U.S. Certified Mechanic Elliott Aviation Foreign Certified Mechanic • . X Certificated Repair Station CGHR812C • Moline, IL 61266-0100 Manufacturer D. I certify that the repair and/or alteration made to the unit(s) Identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date Si 4/14/00 7. Appro Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and Is IEJ APPROVED ID REJECTED FAA Ft Standards Other (Specify) Manufacturer Inspection Authorization Inspector BY Person Approved by Transport FAA Designee X Repair Station Canada Airworthiness Group Date of Approval or Rejection Certificate or 4/14/00 Designation G No. C FAA Form 337 OM) EFTA00012083 EFTA00012084 NOTICE tible in the appropriate aircraft record. An alteration must be compa Weight and balance or operating limitation changes shall be enteredapplicable airworthiness requirements. with the with all previous alterations to assure continued conformity B. Description of Work Accomplished plished.) with aircraft nationality and registration mark and date worn accom (If more space is required, attach additional sheets, Identify 400A, RK-244, N793TA, 4/14100 ers request. te a complete refurbishment of the interior per the custom Removed all the interior and the cabinetry items to facilita panels, the d. Recovered the cabin headliner, the left and right hand window Removed all the finishes and material's as require DA. # 12777, with Douglas Interior products: Fabric, DEF 9135, PN 04, Ivory, emergency exit panel and the cabin door upper panel approved by #45065-00 and the form 8110-3, Both dated 03/03/00 and s & REF # 402396-402545. See the bum test report WO the left and right hand drink ledge consoles with Roger D.E.R. #DERY 405020-CE, Structural special. Recovered 7- treatment #SKEP41539. See the burn test report WO #4648 n: Fabric, FRET #9103-05, Baroque, Treated at Skandia, REF ral special. ed by Judy Boggs, D.E.R. #DERV — 405020-CE structu 00 and the FORM 8110-3, both dated 04-13-00 and approv c pecan, Part #CL- y seat with leather Townsend leather. Leather, Classi Recovered both crew seats, seven cabin seats, the lavator ed Judy Boggs, -00 and the form 8110-3, both dated 03-01.00 and approv by with 17, D/L #11428. See the bum test report WO# 44969 of the left hand partitlan and both game table inserts D.E.R. 5020-CE structural special. The lower door panel , aft side -00 dated 03/01/00 and approved by Judy leather pecan, TF-17 D/L 11429.See bum test report Wo # 44969 panels partition, the outboard side of the aft stub partition. the three Boggs DER # DERV 405020-CE. Recovered the aft right hand int closet/galley cabinet with aircraft interior products, fabric, grospo #440, of the aft baggage compartment and the Inside of the fwd 06-24-99 and #SKFP15268, see the bum test report WO#35268 dated beige, lot #8817-8824, treated at Skandia, Ref. Treatment D.E.R. #CHI-410, Structural special. Cut, fitted, surged and the form 8110.3 dated 07-16.99, both approved by r. ultra area using aircraft interior products, CTM Pattern N installed new carpet throughout the cockpit and cabin D.E.R. form 8110-3 both dated 3-03-00 and approved b suede 034. See the burn test report #AIP stock and the out to crew seat restraint systems. Both restraint systems were sent #60-572, structures (interiors).. Removed the pilot and copilot by Am- nt systems P/N 504246-401-2291 after work was accomplished Am Safe, Inc. for rework. Installed both crew seat restrai all cabin seat belt from Am-Safe, Inc. Removed the lavatory seat and Safe, Inc. Reference both 8130-3 Forms dated 04-07-00 and all cabin seat s, Inc. for rewebbing. Installed the rewebbed lavatory seat assemblies and inertia reels. Sent all out to Belt Maker t, fwd and ork, WO #31888R. The galley/closet, upright storage cabine belt assemblies and inertia reels, see the certification paperw Veneer., t was covered with Carl F. Booth & Co. Waterfall Buginga aft bulkheads, game tables, drink ledges and the vanity cabine D.E.R. #DERY405020-CE, for the flammability ed by reference the burn test report #22702 dated 04-15-00 approv llardance ili ew with FAR 25.853 (a) appendix F part I (a) were firebloc requirements. All seven cabin seats and the lavatory seat with the 25-83. The fireblocking was accomplished in accordance (1) (II) and FAR 25.85) (c) appendix F part II amendment , reference the form 8110-3 dated 04-13-00 approved by Skandia, Inc. test plan #5880 Rev. new dated 04-13-00, 09 R2 the FM Form 337 dated 0414-00. Complied with AD 7408- D.E.R. #DERY-405020-CE, structural special. Reference s as ed with paper or linen waste receptacles by installing placard Transport category that have one or more lavatories equipp fe inc. nt system does not apply due to aircraft belts being AM-Sa required by this AD. AD 98-25-10R1 Aircraft Belts, Inc. Seat restrai of the been inspected in accordance with the current maintenance rules aircraft seat belts. The work performed on this aircraft has e t is approved for return to service. Weigh and balance chang Federal Aviation Regulations and for the work performed this aircraf negligible. END Q Additional Sheets Are Attached * U.S. G.P.O 1990-791-753 Form Approved MAJOR REPAIR AND ALTERATION OMB No. 2120-0020 uSOeparonent of Transportatfon (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Federal Aviation - Office Identification Administration roue- ce- 00b-61 ofr INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions ) and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each violation (Section 901 of Federal Aviation Act of 1958). Make Model Raytheon 400A 1. Aircraft Serial No. Nationality and Registration Mark RK-244 N428HR Name (As shown on registration certificate) dd vin on registration certificate) See Attached Copy . . 2. Owner Wichita, KS 67201 3. For FAA Use Only 4. Unit Identification S. Typo Und Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1above) X C) POWERPLANT C..i --: •-•C --- .: C.") Z.• • •..et.. 8 1r/ PROPELLER - -I a -t cc Type APPLIANCE —"" rn 00 •• Manufacturer 0 crt 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Kenneth W. Chitty X U.S. Certificated Mechanic 454944057 101 S. Webb Foreign Certificated Mechanic P.O. Box 2902 Certified Repair Station Witchita, Ks 67201-2902 Manufacturer D. I certify that the repair and/or alteration made to the unit(s Identified in item 4 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my know edge. Date Signature of A 03-06-00 7. Approval for Retu Pursuant o the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 031 APPROVED 0 REJECTED FAA Fit Standards Manufacturer X Other (Specify) Inspection Authorization Inspector BY FAA Designee Person Approved by Transport Repair Station Canada Airworthiness Grou • Date of Approval or Rejection Certificate or Signature of 03-06-00 Designation No. 454944057 FAA Form 337 (12-88) EFTA00012085 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If mom space is required, attach additional shoots. Identify with aircraft nationality and registration mark and date 1•.a& completed.) Installed Dog Harness P/N CS-H-1 in accordance with Aerodesign Engineering Report 1912-1 Rev.IR, 6-9-96, ( Faa Form 8110-3 dated 03-03-2000 is the Approved Data ) "Structual Substantiation, Restraint Harness for a Dog, installed into an Aircraft." This installation meets FAR 25.853b-2 Flammability requirements. This harness will be stored with the NC loose equipment and a copy of the Engineering report will be placed in the Flight Manual, instructions are in paragraph 3.0 No Weight & Balance change. END ❑ Additional Sheets are Attached EFTA00012086 UNITEDSTATESOF 規钢獻 DEPARTMENTOF TRA料SPORTATION-FEDERAL AVIATIONADMINISTR盯ION STANDARDAIRWORTHINESSCERTIFICATE NATO世AL耐AND 2. 咽剮鄲TURER ANDh ODEL 3．觫CRAFT SERIAL ． CATEGORY REGISTRATION'ARKS NU nER 暇黷蠟珊蒸戀鱗p轄Y N79n; 瞧 R和244 曬 5. AUTHORITY AND BASIS FOR ISSUANCE Thisairworthinessceft翱郎鯽ed puts ant to theFederal Aviation Act of 195 and certifies that, as of the dateo fissuance, the . a rcraft to which issued has been inspected and found to confofm to the type cectitate therC拖r,to be in condition for safe ope昭(ion:and has been sl own to meet the requirements of the applicable compreheilsive and detaited aim°rthiness code as provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein, Exceptions ' 體齲 6 TERMS AND CONDITIONS Unless sooner surrendefed, suspended, revoked, or a termina∥on date is otherwise甾伍廿ishedby the Admin trator, this 胖onihinesscerl'kale Ise什ectiveas long as the maintenance．preventat e maintenance, and alle藺o鷓are perlorrned in accordance with Parts21．43．. d91of theFederalAviatio fifiequ •lions,as appropriate,and the aircraft is registered in theUnited States, DATE OF ISSUANCE DESIGNATION NUMBER 可 璁囔鋤囤7 Any alteration,reprodu ion, or misuseof this cerlilicate may be punishable by a line not exceedingSi, 0,o imprisonment not exceeding 3．… years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS,I . ; FAA Form 81昤2 眸) . *U.S,G.P.0:1 8 66S028 EFTA00012087 1 0 f. $ ' EFTA00012088 UNITEDSTATESOF AMERICA DEPARTMENTOF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARDAIRWORTHINESSCERTIFICATE 1 NATIONALITYAND 2 3 AIRCRAFTSERIAL 4 CATEGORY ' REGISTRATIONMARYS 11711.dUNIAiiirRALFT COMPANY NUMBER N4281IR 4001 RK-244 TRANSPOR 5 AUTHORITYAND BASIS FOR ISSUANCE Thisairwortiness certificateis issuedpursuanttote FederalAviation Act of 1958andcertifies that,asof thedateof issuance,the aircraft to which issued has been inspected and lound to conform to the type certificate therefor, to be in condition for safe operation, and has been shown to meet the requirementsof the applicable comprehensiveand detailedairworthinesscode as providedby Annex 8 to the Convention on International Civil Aviation,except as noted herein. Exceptions: NONE 6 TERMSAND CONDITIONS Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, this airworthiness certificate is effective as long as the maintenance,preventativemaintenance,and alterations are performed in accordancewith Parts21,43,and 91of theFederalAvialionRegulations,as appropriate,and the aircraft is registeredin theUnited Stales. DATE OF ISSUANCE DESIGNATIONNUMBER 10-01-99 MIR CE-50115, Any alteralion,reproduction, or misuseof thiscerhlicate may be punishableby a finenot exceedingS1,000,or imprisonmentnotexceeding 3 years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATIONREGULATIONS. • 668.228 *U,S, GOVERNMENTPRINTINGOFFICE:1R31 FAA Form 8100.2(8.,s2) EFTA00012089 $ EFTA00012090 1-orm Approved Or ? fol -11 MAJOR REPAIR AND ALTERATION OMB No. 2120-0020 US Department of Transportation (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Went Aviation Office identification Administration SW FSDO 17 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix 8, and AC 43.9-1 (or subsequen revision thereof) for Instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of1959). Make Model 1. Aircraft RAYTHEON 400A Serial No. Nationality and Registration Mark RK-244 USA N428HR Name (As shown on registration certificate) Address (As shown on registration certificate) 2. Owner RAYTHEON AIRCRAFT COMPANY WICHITA, KANSAS 67201-0085 3. For FAA Uso Only 4. Unit Identification 5. Typo Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement I-A, Agency's Name and Address 8. Kind of Agency C. Certificate No. RAYTHEON AIRCRAFT SERVICES U.S. Dedicated Mechanic CRS-XA14605K Foreign Certificated Mechanic LIMITED AIRFRAME SAN ANTONIO TEXAS 78216 X Certificated Repair Station Manufacturer RADIO CUSS I,II,III D. I certify that the repair and/or alteration made to the und(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information furnished herein is true and correct to the best of my knowledge. Date 12-22-99 7 , Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is fP APPROVED 0 REJECTED FAA Rt. Standards Manufacturer Inspection Authorization Other (Specify) BY Inspector FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Gro • Date of Approval or Rejection Certificate or Designation No. 12-22-99 CRS-XA14605K FAA Form 337 (1248) EFTA00012091 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allprevious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (Ifmore space is required, attach additional sheets. Identtot with aircraft nationally and registration mark and date kettlecompleted.) MAKE: RAYTHEON 400A Wit RK-244 REG: N428HR DATE: 12-22-99 INSTALLED AN ALLIEDSIGNAL FLITEFONE VI AIRBORNE RADIOTELEPHONE SYSTEM CONSISTING OF THE FOLLOWING EQUIPMENT: MOD/MFG DESCRIPTION WEIGHT ARM RT-18D REC/TRANSMITTER WRACK 400-0125-2000 7.8 47.8 WH-I0 HANDSET 400-0123-112 1.5 106.3 WH-IO HANDSET W/CORD 400-0123-112 2.5 252.0 AT-462 ANTENNA 121-014378-01 0.5 365.1 THE ALLIEDSIGNAL FLITEFONE VI SYSTEM WAS INSTALLED IN ACCORDANCE WITH THE BEECH AIRCRAFT CORPORATION DWG. #128-340675, REV. ORIGINAL, DATED 11-13-95 AND THE CHANGE ORDER #G76866 DATED 10-11-96. THE ELECTRICAL WIRING FOR THIS INSTALLATION WAS INSTALLED IN ACCORDANCE WITH THE BEECH AIRCRAFT CORPORATION DWG. 128-340606 REV. A DATED 10-27-94. A FUNCTIONAL TEST OF THE EQUIPMENT HAS BEEN PERFORMED IN ACCORDANCE WITH FAR 25.1301, FAR 25.1309 AND CHECKED IN ACCORDANCE WITH FAR 25.1431 FOR OPERATING SATISFACTORILY AND DID NOT ADVERSELY AFFECT OTHER COMPONENTS INSTALLED IN THE AIRCRAFT. THE ALLIEDSIGNAL FLITEFONE VI OPERATORS MANUAL P/N: 006-08834.0000 AND THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS DOC. #FF VI-ICA-RK-244 DATED 12-22-99 HAVE BEEN INSERTED IN THE AIRCRAFT AS PART OF THE AIRCRAFT'S PERMANENT RECORDS. THE AIRCRAFT WEIGHT AND BALANCE FORM AND EQUIPMENT LIST HAVE BEEN REVISED TO REFLECT THIS MODIFICATION AND BOTH FORMS HAVE BEEN INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END- ❑ Additional Sheets Are Attached * U.S. GOVERNMENT PRINTING OFFICE: 1992-769-012/60157 EFTA00012092 RAYTHEON AIRCRAFT SERVICES ,SAN ANTONIO, TX. PAGE 1 OF 2 DOCUMENT NO. FF VI-ICA-RK-244 DATE: 12-22-99 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR A BEECHCRAFT MODEL 400A WITH AN ALLIEDSIGNAL FLITEFONE VI AIRBORNE RAD IOTELEPHONE SYSTEM I. INTRODUCTION: THIS MAJOR ALTERATION TO THIS AIRCR AFT OBLIGATES THE AIRCRAFT OPERATOR TO INCLUDE THE FOLLOWING MAINTENANCE INFORMATION PROVIDED BY THIS DOCUMENT IN THE OWNER/OPERATOR'S AIRCRAFT MAINTENANCE MANU AL AND THE OWNER/OPERATOR'S AIRCRAFT SCHEDULED MAINTENANCE PROGRAM. 2. DESCRIPTION: THE ALLIEDSIGNAL FLITEFONE VI AIRBO RNE RADIOTELEPHONE SYSTEM CONSISTS OF A RECEIVER/TRANSMITTER INCLUDING ITS MOUNTING RACK , TWO HANDSETS INCLUDING MOUNTING RACKS, TWO RETRACT CORDS, AN ANTENNA, ASSOCIATED WIRING, AND ANY RELATED HARDWARE. THE BASIC RADIOTELEPHONE SYSTEM IS A MOBILE COMMUNICA TION SYSTEM FOR AIRCRAFT. IT OPERATES IN A FREQUENCY RANGE BETWEEN 454.675 - 454.975 Mhz 13 CHANNELS TO RECEIVE AND 459.675 - 459.975 Mhz 13 CHANNELS TO TRANSMIT. 3. CONTROL, OPERATION INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI INSTALLATION MANU REV. E, REPORT 1362, BASIC ISSUE DATED SEP. 1/90 AL, AND THE ALLIEDSIGNAL FLITEFONE VI OPERATOR'S MANUAL P/N 006-08834-0000. 4. SERVICING INFORMATION: THE ALLIEDSIGNAL FLITE FONE VI AIRBORNE RADIOTELEPHONE SYSTEM IS ON CONDITION AND THERE IS NO PERIODIC, PREVENTIVE , OR SCHEDULED MAINTENANCE REQUIRED FOR CONTINUED OPERATION OF THIS SYSTEM. 5. MAINTENANCE INSTRUCTIONS: THE SCHED ULED MAINTENANCE TASKS REQUIRED BY THIS MODIF TO BE ADDED TO THE AIRCRAFT OWNER/OPERATO ICATION RS APPROPRIATE AIRPLANE MAINTENANCE PROGR FOLLOWS: AM AS a. PERFORM, ON AT LEAST AN ANNUAL BASES, A PERIODIC INSPECTION OF THE EQUIPMENT RACK, EQUIPMENT MOUNTINGS, ASSOCIATED WIRING, CABLE S, CONNECTORS, HARDWARE, ANTENNA AND RELATED AIRCRAFT STRUCTURE FOR INTEGRITY, SECURITY, WEAR, CHAFFING, AND ETC.. SPECIAL ATTENTION SHOULD BE GIVEN TO THE AIRCRAFT PRIMARY STRUCTURE WITH REGARDS TO FATIGUE STRESS CRACKING, CORROSION, AND ETC.. AND 6. TROUBLESHOOTING INFORMATION: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI AIRBORNE SYSTEM MAINTENANCE MANUAL P/N 150-1364-000 RADIOTELEPHONE REV. E, DATED SEP. 90 OR LATER REVISION. 7. REMOVAL AND REPLACEMENT INFORMATIO N: REFERENCE THE ALLIEDSIGNAL FLITEFONE VI RADIOTELEPHONE SYSTEM MAINTENANCE MANU AIRBORNE AL P/N 150-1364-000 REV. E, DATED SEP. 90 OR LATER REVISION. SHOULD IT BECOME NECES SARY TO REMOVE THE FLITEFONE VI, SECURE THE CABLES AND WIRING, COLLAR THE APPLICABLE ASSOCIATED CIRCUIT BREAKERS, PLACARD THE AIRCRAFT HAS BEEN REMOVED, REVISE THE WEIGHT & BALANCE THAT THE UNIT AND THE EQUIPMENT LIST AND MAKE A LOGBO THE UNIT HAS BEEN REMOVED FOR SERVICE, OK ENTRY REFER TO 91.213 OF TITLE 14 OF THE CODE OF REGULATIONS AND/OR THE AIRCRAFT'S MEL. FEDERAL 8. DIAGRAMS: THERE ARE NO ACCESS PLATE S THAT NEED TO BE REMOVED FOR INSPECTION. 9. SPECIAL INSPECTION REQUIREMENTS: SPECIAL INSPECTION REQUIREMENTS ARE NOT APPLICABLE 10. APPLICATION OF PROTECTIVE TREAT MENTS: APPLICATION OF PROTECTIVE TREAT APPLICABLE. MENTS ARE NOT 11. DATA: INSTALLATION REQUIREMENTS MAY BE FOUND WITHIN THE ACCEPTED INDUSTRY CONTAINED WITHIN AC 43.13-1B CHAPTERS 4, 6, PRACTICES 7, 11, AND 12, AND IN ACCORDANCE WITH CHAPTERS 1, 2, 3, II, AND 13. AC 43.13-2A EFTA00012093 %a EFTA00012094 "RAYTHEON AIRCRAFT SERVICES PAGE 2 OF 2 • SAN ANTONIO, TX. DOCUMENT NO. FF VI-ICA-RK-244 DATE: 12-22-99 12. LIST OF SPECIAL TOOLS: SPECIAL TOOLS ARE NOT REQUIRED. 13. FOR COMMUTER CATEGORY AIRCRAFT: NOT APPLICABLE, THIS AIRCRAFT NOT COMMUTER CATEGORY AIRCRAFT a ELECTRICAL LOADS: THE RAYTHEON AIRCRAFT SERVICES ELECTRICAL LOAD ANALYSIS DOCUMENT REV. DATED AND THE RAYTHEON AIRCRAFT SERVICES EMI/RFI GROUND TEST PROCEDURES DOCUMENT N REV. DATED HAVE BEEN PLACED IN THE AIRCRAFT AS PART OF THE AIRCRAFT's PERMANENT RECORDS. b. METHODS OF BALANCING FLIGHT CONTROLS: N/A TO THIS INSTALLATION c. IDENTIFICATION OF PRIMARY AND SECONDARY STRUCTURES: N/A TO THIS INSTALLATION d. SPECIAL REPAIR METHODS APPLICABLE TO THE AIRPLANE: N/A TO THIS INSTALLATION 14. RECOMMENDED OVERHAUL PERIODS: THERE ARE NO ADDITIONAL OVERHAUL TIME LIMITATIONS. IS. AIRWORTHINESS LIMITATION SECTION: THERE ARE NO ADDITIONAL AIRWORTHINESS LIMITATION S. 16. REVISION: THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CHECKLIST (ICA) MAY BE REVISED BY SUBMITTING A LETTER TO THE LOCAL FSDO WITH A COPY OF THE REVISED FAA FORM 337 AND REVISED ICA. THE FAA INSPECTOR ACCEPTS THE CHANGE BY SIGNING BLOCK 3 AND INCLUDING THE FOLLOWING STATEMENT: "THE ATTACHED REVISED/NEW INSTRUCTIONS FOR CONTINUED AIRWORTHI NESS (DATE ) FOR THE ABOVE AIRCRAFT OR COMPONENT MAJOR ALTERATION HAVE BEEN ACCEPTED BY THE FAA, SUPERSEDING THE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (DATE )." ONCE THE REVISION HAS BEEN ACCEPTED, A MAINTENANCE RECORD ENTRY WILL BE MADE, IDENTIFYING THE REVISION, ITS LOCATION AND DATE OF THE FORM 337. 17. ASSISTANCE: NOT APPLICABLE. 18. IMPLEMENTATION AND RECORD KEEPING: a. FOR MAJOR ALTERATIONS PERFORMED IN ACCORDANCE WITH FAA FIELD APPROVAL POLICY, THE OWNER/OPERATOR OPERATING UNDER PART 91 IS RESPONSIBLE FOR ENSURING THAT THE ICA IS MADE PART OF THE APPLICABLE SECTION 91.409 INSPECTION PROGRAM FOR THEIR AIRCRAFT. THIS IS ACCOMPLISHED WHEN A MAINTENANCE ENTRY IS MADE IN THE AIRCRAFT'S MAINTENAN CE RECORD IN ACCORDANCE WITH SECTION 43.9. THIS ENTRY RECORDS THE MAJOR ALTERATION AND IDENTIFIES THE ORIGINAL ICA LOCATION (e.g., BLOCK 8 OF FAA FORM 337) ALONG WITH A INSPECTION /MAINTENANCE REQUIREMENTS. b. FOR MAJOR ALTERATIONS PERFORMED IN ACCORDANCE WITH A FIELD APPROVAL ON AIR CARRIER AIRCRAFT, THE AIR CARRIER OPERATOR IS RESPONSIBLE FOR ENSURING THAT THE ICA IS MADE PART OF THE APPLICABLE INSPECTION/MAINTENANCE PROGRAM FOR THEIR AIRCRAFT. IF A PROCEDURE IS NOT CURRENTLY INCLUDED IN THE OPERATOR'S MANUAL TO INCORPORATE ICA, THIS PROCESS WILL NEED TO BE APPROPRIATELY ADDRESSED (i.e. THE OPERATOR SUBMITS A REVISION TO ITS MAINTENANCE PROGRAM TO THE APPLICABLE CERTIFICATE-HOLDING DISTRICT OFFICE (CHDO). a FOR AIRCRAFT INSPECTED UNDER AN APPROVED AIRCRAFT INSPECTION PROGRAM (AAIP), THE OPERATOR WILL SUBMIT A CHANGE TO THE CHDO IN ACCORDANCE WITH SECTION 135.419B. d. FOR AIR CARRIER AIRCRAFT INSPECTED USING AN ANNUAL 100 HOUR INSPECTION PROGRAM, A REFERENCE TO NEW ICA WILL BE MADE IN THE AIRCRAFT'S MAINTENANCE RECORD IN ACCORDANCE WITH SECTION 43.9. THIS ENTRY RECORDS THE MAJOR ALTERATION AND IDENTIFIES THE ORIGINAL ICA LOCATION (e.g., ICA ARE LOCATED/ATTACHED TO BLOCK 8 OF FAA FORM 337). IN ADDITION, THE OPERATOR WILL REQUEST A REVISION TO THE OPERATOR'S OPERATIONS SPECIFICATIONS, ADDITIONAL MAINTENANCE REQUIREMENTS, WHICH INCORPORATES THE ICA INTO THE INSPECTION PROGRAM. EFTA00012095 EFTA00012096 ea MAJOR REPAIR AND ALTERATION Form Approved OMB No. 2120-0020 KS. Deputnient (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only of I/deb:oration federal Aviation Admmoration 02pe tdentification gene bYV FSDO 17 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC 43.9-1 (or subsequen revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a dvii penalty not to exceed 51000 for each such violation (Section 901 Federal Aviation Act of 1958). Make Model 1. Aircraft RAYTHEON 400A Serial No. Nationality and Registration Mark RK-244 USA N428HR Name (As shown on registration certificate) Address As shown on registration certificate) 2. Owner RAYTHEON AIRCRAFT COMPANY WICHITA, KANSAS 67201-0085 3. For FAA Uso Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. RAYTHEON ALRCRAFT SERVICES U.S. Certificated Mechanic CRS-XA14605K Foreign Certificated Mechanic X certificated Repairstation LIMITED AIRFRAME SAN ANTONIO TEXAS 78216 RADIO CLASS MUM Manufacturer D. I net* that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that attachments hereto the information furnished herein is true and correct to the best of my knowledge. Date 12-22-99 Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected In the manner prescribed by the Administrator of the Federal Aviation Administration and is 0 APPROVED 0 REJECTED FAA Rt. Standards Manufacturer Inspection Authorization Other (SIKCifY) BY Inspector FM Designee x Repair Station Person Approved by Transport I Canada Airworthin - p • Date of Approval or Rejection Certificate or 12-22-99 Designation No. CRS-XA14605K FAA Form 337 (I2-8e) EFTA00012097 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with allpmvious alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (It more space is required, attach additionalsheets Identify with aircraft nationality and registration mark and date work completed.) NINCE: RAYTHEON 400A S/N: RK-244 REG: N428HR DATE: 12-22-99 INSTALLED A SUNDSTRAND MIC-VI GROUND PROXIMITY WARNING SYSTEM CONSISTING OF THE FOLLOWING EQUIPMENT: MOD/MFG DESCRIPTION P/N WEIGHT ARM MK-VI GPWS COMPUTER 965-0686-020 4.2 33.1 ADC-500 CONVERTER 500-8020 2.3 38.2 BRACKET & PLATE 0.5 36.1 WIRING & CONNECTOR 3.5 54.0 THE SUNDSTRAND MK-VI GPWS SYSTEM WAS INSTALLED IN ACCORDANCE WITH THE STC #SA3322SO ISSUED 09-18-92 AND REISSUED 10-04-95 AND THE HANGER ONE MASTER DRAWING LIST #11892-GPWS, REV. D DATED 03-22-93. THE ELECTRICAL WIRING WAS INSTALLED IN ACCORDANCE WITH THE RAYTHEON AIRCRAFT SERVICES DWG. #RAS-67-9917 REV. IR DATED 11-05-99, REFERENCE THE FORM 8110-3 DATED 11-23-99 APPROVED BY ROBERT M. HURLEY, DESIGNATED ENGINEERING REPRESENTATIVE #DERT-710137-SW, SYSTEMS AND EQUIPMENT. A FUNCTIONAL TEST OF THE EQUIPMENT HAS BEEN PERFORMED IN ACCORDANCE WITH FAR 25.1301, FAR 25.1309 AND CHECKED IN ACCORDANCE WITH FAR 25.1431 FOR OPERATING SATISFACTORILY AND DID NOT ADVERSELY AFFECT OTHER COMPONENTS INSTALLED IN THE AIRCRAFT. THE SUNDSTRAND MK-VI GPWS APPROVED FLIGHT MANUAL SUPPLEMENT, REV. B DATED 03-30-93 HAS BEEN INSERTED IN THE SUPPLEMENT SECTION OF THE AIRCRAFT FLIGHT MANUAL AND THE GPWS PILOT'S GUIDE P/N 060-4087-000 REV. A DATED 10-96 HAS BEEN INSERTED IN THE AIRCRAFT AS PART OF THE AIRCRAFTS PERMANENT RECORDS. THE AIRCRAFT WEIGHT AND BALANCE FORM AND THE EQUIPMENT LIST WERE REVISED TO REFLECT THIS MODIFICATION AND BOTH FORMS WERE INSERTED IN THE AIRCRAFT FLIGHT MANUAL. END— D Additional Sheets Are Attached * U.S. GOVERNMENT PRINTING OFFICE: '992-769-012,60157 EFTA00012098 tad Ztatta Drxrim Beparanutt of transportation—fuleral 2thation Sadminisattion *upplemental tgpe Certificate c../Yetzinkit- SA3322SO al rcs, Inc. Fulton County Airport-Brown Eteld Atlanta, Georgia 30336 .gatiZadLa.7 .,.4w,a(4/i02.erirvA-fefe,i/owthns idoedmiXearnitalthn444;td.oniefedin;a .d.. A. ;a4,0friatadifenowoneater aaizaameraiemena-ari 25 . Federal Aviation a r ze.ama. iternsia e—peeareA.L.Snee...- Al6SW ate: Beech „ea 400A -44 ale-a9/47/ 5-Sesrv 4 k 2r: Installation of a Sundstrand MK VI GPAYWn necordance with ranger One. Drawing List No. 11892-GPWS, Rev. B, dated September 17, 1992, or I/16;r FAA Approved revision. Seciiim-44andLrea:rnad: This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will produce no adverse effect upon the airworthiness of that aircraft. FAA Approved Airplane Flight Manual Supplement, dated September 18, I992, is a required part of this STC. wasaxeitseesandiefry4eWores:rdir eataithukte,oPS‘leitis-r.Wren ,a1,44esasrarre.esess,.e:tv.#4-4wesatias- ir e ;:s4rai tars,z..1;:w COP S.2 2neiuIenx/Zon. August 5, 1992 October 4, 1995 September 18, 1992 Associate Manager, ACE-116A Atlanta Aircraft rertifititinn Offira (Title) Any alteration of this en:Orate is punishable by a fine of not exceeding ;1,000, or imprisonment not exceeding 3 years, or both. This route nay be transferred in accordance with FAR 21.17. CAA rota 6110-2 110-60) EFTA00012099 4- EFTA00012100 I II IV I L-I JJI~t- i1N_INV L_ .L - DWG. LIST NO. 11892- GPWS DATE 9/1/92 REV. D DATE 3/22/93 ET 1 OF 1 SYSTEM SUNDSTRAND MK- VI GPWS . AIRCRAFT TYPE BEECHJET 400E F. A. A. PROJECT NO.CE- 115A- 2970 STC SA 3 -3 2 2S0 DATED 9/18/92 REVISION DRAWING NO. TITLE SHTS PAGE LTR DATE EO/REMAR . TRI- 92- 108 9 - 2 - 92 STRUCTURAL SUBSTANIATION REPORT GPWS AFMS B 3/22/93 AIRPLANE FLIGHT MANUAL SUPPLEMENT S 060- 3942 6/92 INSTALLATION DESIGN GUIDE 11892- 2 A 3/22/93 INSTALLATION PROCEDURES 11892- 3 A 3 / 2 2/93 BLOCK DIAGRAM 1 1 11892- 4 D 3/22/93 WIRING DIAGRAMS ° 2 182 11892- 5 8 - 29- 92 PARTS LIST & GENERAL NOTES 11892- 6 8 - 29- 92 GPWS MOUNTING PLATE 11892- 7 8 - 31 - 92 ADC-S00 MOUNTING PLATE 11 '- 8 8 - 29- 92 SUPPORT BRACKET 892-1 A 3/22/93 GROUND TEST PROCEDURES 060- 3956- 000 D 9/17/92 FLIGHT TEST PROCEDURES 500- 8000- RO 8/29/92 DESIGN SPECIFICATIONS ADC-S00 .. . EFTA00012101 , •d a EFTA00012102 U.S DEPARTMENT OF TRANSPORTATION DATE FEDERAL AVIATION ADMINISTRATION 11)23/99 STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION HAKE MODEL NO. TYPE Muria Rodeo.Idelmopstr. NAME OF APPLICANT toc.I Beech 400A Airplane Raytheon Aircraft Services LIST OF DATA - - ' IDENTIFICATION TITLE " Raytheon Drawings RAS-67.9917 Sundstrand Mk-VI Ground Pro>amrty Warning Sys Rev IR Dated 11/05/99 Note: This approval is for the Electrical aspects of the engineering design data only, and is not installation approval. Approval for aircraft SIN RK-244 only. Approval for GPWS is for only the minor deviations to FAA STC SA3322SO. . After modification is complete, perform EMURFI test In accordance with Raytneon report RAS-GF-9714, EMI/RF1 Test Procedure. PURPOSE OF DATA In support of a modification to install a GPWS in serial number RK-244. APPUCAS LE REOUIREMENTS(ArtspeoficcaA) FAR 25.1301 a,b,c FAR 25.1359 d FAR 25.1431 c CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations ofappointment under Pan 183 ofthe Federal Aviation Regulations, dam listed above and on attached sheets numbered None have beat examined in accordance with established procedures and found requirements ofthe Federal Aviation Regulations. to comply with applicable 70W Therdore ❑ Rccommead approval of That data ra Approve these this SIGNATURE(SI OF DESIGNATED ENGINEERING R AWES) DESIGNATION NUMBERS(E) CLASSIFICATIONS) DERT-710137-SW Systems & Equipment FAA Form 8110-3 (i1.70)9SEPMCESPRETICUS ENRON OFOreal 11 - 23-99 13:SS RECEIVED FRO14:512 989-2998 P.03 EFTA00012103 t EFTA00012104 Form Approved . O.M.B. No.21208018 INSTRUCTIONS - Print or type. Do not write in shaded areas: these are for FM 0 APPLICATION FOR useonly. Submit original only to an authorized FM Representative. II additional LLSDeporimcre AIRWORTHINESS spacers required. use an attachment For special fight penes compete Sectaans of tonsponalicn II and VI or VII as applicable Federal Arlation CERTIFICATE Administration 1REGISTRATION MARK 2AIRCRAFT BUILDERS NAILS (Make) 3. AIRCRAFT MODEL DESIGNATION 4.YR. MFR FM CODING N428HR RAYTHEON AIRCRAFT COMPANY 400A 1999 7,s I.AIRCRAFT cc 1 0 5. AIRCRAFT SERIAL NO. 6. ENGINE BUILDERS NAME WNW 7. ENGINE MODEL DESIGNATION DESCRIPTION RK-244 Pratt & Whitney Canada JT15I3-5 tif --; // L S 8. NUMBER OF ENGINES 9. PROPELLER BUILDERS NAME (Mike) 10. PROPELLER MODEL DESIGNATION 11. AIRCRAFT LS (Check tI apptitable) 2 N/A N/A (IMPORT APPLICATION IS HEREBY MADE FOR: (Check applicable awns ) A 1 X STANDARD AIRWORTHINESS CERTIFICATE (Indkate category) I Th)RMAI I I Inure t (ACROBATIC x (TRANSPORTI I GLIDER I BALLOON B SPECIAL AeftWOFITHINESS CERTIFICATE (Clerk Aapropda Ferns) 2 LIMITED II. CERTIFICATION REQUESTED 5 1 CLASS I PROVISIONAL (Mc:rate doss) 2 CLASS II 1 AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEYING 3 AERIAL ADVERTISING RESTRICTED (indicate opention(s) to 3 4 FOREST (Wida(e conservation) be conducted) 5 PATROLLING 6 WEATHER CONTROL 7 CARRIAGE OF CARGO 0 OTHER (Spear) 1 RESEARCH AND DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION EXPERIMENTAL flmacare operation(4) 4 to be Conducted) 4 RACING 5 CREW TRAINING MKT. SURVEY 0 TO SHOW COMPLIANCE WITH FAR I FERRY FLIGHT FOR REPAIRS. ALTERATIONS. MAINTENANCE OR STORAGE SPECIAL FLIGHT PERMIT ancricale 8 00rvattbn to be conducted. then 2 EVACUATE FROM AREA OF IMPENDING DANGER complete Section VI or Fil as 3 OPEAT)ON IN EXCESS OF MAXIMUM CERTIFICATED TAKE-OFF WEIGHT apµcaNe on testae side) 4 DELIVERING OR EXPORT 15 I IPROCIUCTION FLIGHT TESTING 6 CUSTOMER DEMONSTRATION FLIGHTS C a Mu TIPLE AIRWORTHINESS CERTIFICATE (Check ASOVE Reftrided O0mM:on- and 'Standard' orUnided.'as eppdcab/ej A. REGISTERED OWNER (As shorm on cerlificata olaircraft registration) IF DEALER. CHECK HERE --ilt NAME X ADDRESS RAYTHEON AIRCRAFT COMPANY P.O. BOX 85 WICHITA, KS 87201 B. AIRCRAFT CERTIFICATION BASIS (Check opStobte Web and compkfa eerns as indkated) ttL OWNER'S CERTIFICATION AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET (Give No. AIRWORTHINESS DIRECTIVES (Cheek if ea applicable AD3 complied *In x and Redsios No.) A16SW, Ray. 19 end 94P X latest AD No.) ISSUE 99-20 AIRCRAFT LISTING (Ohre Pogo nyndelfFP SUPPLEMENTAL TYPE CERTIFICATE (UR number cresol STCIncorporafed) N/A N/A C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS CHECK IF RECORDS IN TOTAL AIRFRAME HOURS EXPERIMENTAL ONLY (Enter hours dorm Ono° last ceiocato X COMPLIANCE WM BAO 3 issued cr renewed) FAR 91.4. 141. 417 N/A • D. CERTISCATON — I hereby certify that I am the registered owner (of his agent) A lho aircraft 'Ulan/eft above: mat the alrOaft Is registered with the Federal Aviaron Admindballan Si accordance wen Section 501 of the Federal A/Saban Act of 1958. and appncobie Federal Adelson ReguiXions: and that the aircraft has been Inspected and Is elnyorthy and estable for the any:farness ceralkato requested. DATE OF APPLICATION 1041-99 Eugene Hainstock —Administrative Staff CIA A. THE AIRCRAFT OFftauRFD ABOVE WS BEEN INSPECTED AND FOUND AIRWORTHY BY: (Complete This Sec on • FAR PART 121 OR 127 CERTIFICATE HOLDER (GA* CERTIFICATED MECHANIC (Gore - 2 Certaata Ab.) CERTIFICATED REPAIR STATION (Gem CertAcare is 0g ga 3 Certificate No) 6 No) a4 AIRCRAFT MANUFACTURER (We name or fend ic 5 DATE TITLE SIGNATURE (alearALL riPPitable bodes inilems A andB) X THE CERTIFICATE REQUESTED A. lend that Ow aircraft des/Abed In Scram I or VII meets requirements for: 4 AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHWESS CERTIFICATE p. B. Inspection for a special permit under Section VII FAA INSPECTOR I FM DESIGNEE V i g c DATE was conducted by: DISTRICT OFFICE : I , . ... • R UNDER: 1 iFAR 65 I !AR 121.127 OR 135 I FM INSPECTOR SIGNATURE I FAR 145 >iE g V 10-01.99 4 1 CE-43 FAA Form 81304 ii1481SUPERSEDES PREVIOUS EDITION GP0:1910241472/ta913 EFTA00012105 EFTA00012106 A. MANUFACTURER . . . . NAME ADDRESS VI. PRODUCTION B. PRODUCTION BASIS (Check •Plattable Kern) PRODUCTION CERTIFICATE (GMpultrodon cetera,. number) TYPE CERTIFICATE ONLY PUSHY TESTING APPROVED PRODUCTION INSPECTION SYSTEM C. GIVE QUANTITY OF CERTIFICATES REOUIRED FOR OPERATING NEEDS ► e DATE OF APPLICATION NAME AND TITLE CAW or twe) SIGNATURE A. DESCRIPTION OF AIRCRAFT REGISTERED OWNER ADDRESS BUILDER (Make) MODEL SERIAL NUMBER REGISTRATION MARK B. ESCRIPTION OF FLIGHT CUSTOMER DEMONSTRATION FLIGHTS 0 (CUM if afanItafW) FROM TO VIA DEPARTURE DATE DURATION TEST C. CREW REQUIRED TO OPERATE THE AIRCRAFT AND ITS EQUIPMENT I (CO-PILOT I (NAVIGATOR I I °MIER (SP°611) JIPILOT D. TNCAIRCRAFT DOES NOT MEET THE APPLICABLE AIRWORTHINESS REQUIREMENTS AS FOLLOWS: E. THE FOLLOWING RESTRICODNS ARE CONSIDERED NECESSARY FOR SAFE OPERATION Rise attachment dnecessary) .. . VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER THAN PRODUCTION FLIGHT F. CERTIFICATION — I hereby certify lhal 18m tie nelstered war far Ns agent) of the *wail drambed above; that the aircraft is regtstered with the Federal Waton Administration in awYclance with Saloon 501 of the Federal Avtadon Ad of 1958. and applicaSe Federal Anadon Regutsticets; and that the airodft has been inspected and is aim:My lot the fliaM desoted. DATE NAME AND TITLE (Print 0" IMO SIGNATURE X A. Operating Umnations and Marldngs In Compliarde wits FM 91.9 G. Statement of cord:miry FAA Form 8130-9 (Attach *hen feedred) 91.34-9 as AMatcatdo VIE AIRWORTHINESS H. Foreign AnwortNneSS Certificate." for Import Agoraft B. °snail Operating UredaticoS Attached (Attach WWI /MAW DOCUMENTATION C. Data. Drawn. Photographs. etc (Attached whoa muffed) I. PreviousMu:manes& Condole Issued in ACCOfd&ICO VAIII X D. Current Weght are, Balance Inftemation Avaitatle In Alrcran FAR CAR (OrIghalAttached) (FAA use only) E. Mater Remy and mieratren. FAA Conn 337 (Attached Men rewind) X J. Current /Unworthiness Cerlifcale Issued in Accordance with X F. This Inspection Recorded In Mersa Regards FAR 21.183 MI oaf 183 31 (Copy *P.M..) OF R . AEDT .Ortik.T__ESAMERICA DEPARTMENT OF TRANSPORTATION-FEDER FE AL AVIATION ADMINISTRATION 4 STANDARDAIRWORTHINESSCERTIFICATE 1 NATIONALITYAND 2 MANUFACTURERANDMODEL 3 AIRCRAFTSERIAL 4 CATEGORY REGISTRATIONMARKS RAYTHEONAIRCRtFTCOMPANY NUMBER N428FIR 400A R(.244 TRANSPORT 5 AUTHORITYAND BAS S FOR ISSUANCE This amorthinesscerlilicale is issuedpursuant tote FederalAviation Act 011958and cerlifies that,as of thedateol issuance,the aircraft to which issued has been inspected and boundto conform to the type cedificale therefor, to be in condition for safe operation. and has been shown io meet the requirements of the applicable comprehensiveand detailed airworthinesscode as provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein, Exceptions. NallE 6 TERMSAND CONDITIONS Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the Administrator, this airworthiness certficate is effective as long as the maintenance,preventativemaintenance,and alterations are performed in accordancewithParis2 4 n i1. r : . , . 10 . • .11 orahistegisIeredintheUded Slates, DATE OF ISSUANCE DESIGNATIONNUMBER 10-01-9R '•IR CE 01157 Any alteration,reproduclion,or misuse° I iscera icatemay be punishableby a fine notexceeding $1,000,or imprisonmentnot exceeding3 years, or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS, FAA Form8100-2(a421 U.S.GOVERNMENTPRINTINGOFFICE;1591••658.225 EFTA00012107 • • • I, 4 • EFTA00012108 I Coming • Pmr1 2-E .-E Canada Transports Canada Form TorrtwuFre 24-0078 3 Oemrmate Re, No . N•ee Menem do bees C-- 77 CANADA AUTHORIZED RELEASE CERTIFICATE - BON DE SORTIE AuTORtSé SEE BLOCK 5 4 Organ:ma • Otgantuee 5 Work OrmoConvaclavom . Son oe tnwancenlrablackee O Pratt & Whitney Canada ~mum. es Lens.l«....... IA U...len••••••• C.••••• Longueutl, Quebec 14G 1A1 P.0.14000014605 0 In 7 Desenotton 5 PM No • 6r de meta 9 Eicaly • kammstnlé • 10 Ory - Ore 11. Sometteleb No • area54MA» 12. 5141usAtIork • CimAravai FREE TURBINE 3030100 VARIOUS 1 PCE-3A0256 MANUFACTURED TURBOFAN IT15D-3 13 Recasts • Remarepn CANADIAN TYPE APPROVAL E-II, FAA TYPE CERTIFICATE E25F.A. THIS ENGINE CONFORMS TO ITS UNTIED STATES TYPE DESIGN (TYPE CERTIFICATE NUMBER E23EA) AND IS IN CONDTTION FOR SAFE OPERATION. THIS ENGINE HAS BEEN SUBJECTED BY THE MANUFACTURER TO A FINAL OPERATION CHECK AND IS INA PROPER STATE OF AIRWORTHKESS. 14 New Pats • Pietas newts: AVM Cruses Set 19 Used Pans • Pieces usagets • CAR $71.10.14awmtnem• Reuse Nat* CANNY. 561 MC 571 10 - CertalCVM apt mbalenanoe Cana« mal he pan(%) idencrel nose. OMNI el o eat cereTié ewe Is Dell 001W la ger...le) enedut Cerat.ect mat the maintenance &pealed abet* Ns been II cal emAll pa la Meanenee Spécae DAM • Tel Menke speo5rO as Week 13. Ni (Nt) been tad s. actawrece We-Mete a» 13. a Conn !ha pene are m •0:4541.InCt mil te MOON* stantlanf a fl eck& conlormemoni an normes ee ningabk4 Enmeaciu•MAnipeate in ~Mace mM me ~Over' »nlµale(s) COMOMemede Mix 43-0491 ee of ~men Emil as .meeesse Speeded In DIM 4050mblet. Mens. anemmt sp5364.11es ease 13.1a Mamie *Wen eats ass »itn ow itsvOniwnell t.OneeP1CO Penceofes et an resetinents se nar~wit 13, me on a) n tare) skates foe scree. Ie rose en stew» ele It Ides) petals) eel atatnée. .4.4. I6 Agreed Rel Na • Ref etautOrdalayi 20 Smtelum 21. ApplOvol RH. NM • RH omnonsabon I DOT APPROVAL 4 . 5/II It Dale 22 Nome Mud or twintiodi - Rem telsetysegrapSewleVaorna) 23 Da I H AY 1 8 1999 - • IOSIaler n1413100.53.41/10Ck apply witri applcoNe leamal data Le entepeur eed winger Tedmea.45116 levee It. eennkneetkiqueS permeates. USERRNSTALLER RESPONSIBIUTIES RESPONSABILITES DE VUSAGERINIONTEUR R erporunt b welerstano tbe: M exillenOr 01 Ihel ~anent am eon not Morwicaly conittvle »Mary 10 a en moommi de ben eoropmeom ea de pin $0n toltelee CO emareent no cambia pat forttn•ent NeWIMPWmNyCNJsstMtly. Macneaton elmteder la péceNoMpOuntleasenkee. Van me user/Mama worts in 5000nUnCe int the moon*. segUNICAS 011,PiroOrlhuneoS Au:betty 0•11eren101an Lemma tusnedironlesleusel DavaNe confmrémenl Dux stletnrill name 43me autord0 Ge V{ AO•OtOOnelb kanConly or e» oxavry speoCed in lay. 10 rs C•51.2•31 net the vse*MitsPee eat...es MI Miner ~natal.. *nee we 13010M6 de tuna,» munte ILI pu 1. t tN elItolel eue tutageraonteuNeute) MoCiálhaeSt AJR104ity meets Mrlskompanenhiasteakkes from Me Amm>115.5ms ~Mayel ON country eyries Mum. eue sms Monk Co nemfaiNdd ample les Mon/CONTosanlidenserreks de TaufOnk de et Po* I, nawyeaté insane a la cant. Sinernenls 14 and IT CO nol ce•••11Mle Mu:Mon ~MAIM in aO cnes the Mrs. itenneal ~mamma mead Les Otace10.2 Mmausenl n.m. eases II el le ne =Moen: pal taw cenAcmon de ~thee En INA 1~1 COS, a imeinlenenee instatelmn cenecaten nun» n accordance in. tne national semeebon by IN temps k ~set leampue C. ratan& at 03Mena one anikaten Mks menenenee !rose seta let Yemenite», before me wean may be ilswn lb;1enittlet ~a -ea. par Anapedmanieugevie). awe eve ratTond Mane elematt. store osseoel EFTA00012109 1z c.}ci, E -taansaort II:2:ft Form FONMASed 24-0078 3. CtrufcaN Ref No • N•41'Orem< du DCA AUTHORIZED RELEASE CERTIFICATE - BON DE SORTIE AUTORISE SEE BLOCK 5 42 $work OtdecCenbaellletre44 • Ban 0•1244oVentrautaate :t at Whitney Canada ..........,.........,•................<—.... Longueuil, uebee 4 1A1 P.O. 1 4000016693 B Pan Ho • Woe ate 9 Elabery-A44416146 • 10 Oty • COO II. Sonaltflatch Na - IP de sea 12. StOnsiWork• ElaUtrovoi 3030100 VARIOUS 1 PCE4A0257 MANUFACTURED FREE TURBINE TURBOFAN 11-15D-5 5PPROVAL &I I, FAA TYPE CERTIFICATE EISEA. 'ORMS TO ITS UNITED STATES TYPE DESIGN (TYPE CERTIF/CATE NUMBER E2SEA) AND IS IN CONDITION FOR SAFE OPERATION. AIRWORTHINESS. SEEN SUBJECTED BY 11W MANUFACTURER TO A FINAL OPERATION CHECK AND IS IN A PROPER STALE OF veil: A'44 C14440 5.11 12 Used Pans. Rtees 03.12642 . CAR 571.10- AlartlerstACe ReAsse M de N C1442,561 MC 571.10- CerlAcacon Nutt rrainlyatinCe Ote6144 ito.e. mot es l ess send* cue 4 mu para(s) tdet41 14S) 4 44cl Cented mot the manienance tended Rene has been u est one* quo ta onanlenruxe sptelfate el444. a Ail etA 13. has 0441 been said S. evIremeni spear; A Ia ease 13, a lontl el6 portormed 4 accordance wrin The raptcattle slanctods enema* Cordceintowne sox not444 de Annaba/a 4 woos:lanes ea% be consoveRswispeattIE oontoinitisem aux &ages cc ot 3eSveddieseet FAcept as amines* Wedded 4 Mock app1Cabt S. 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