el, -- MAJOR REPAIR AND ALTERATION US Department Of Tm114104/111011 (Airframe, Powerplant, Propeller, or Appliance) FOsteral Aviation Adednitrallen OM No.21200020 Exp. 541/2011 Ettoternie TM:alp Wetter Ems. For FAA Use °My 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)) 1. Aircraft Nationality and Registration Mark UNITED STATES / N188TS Serial No. RK-244 'make RAYTHEON AIRCRAFT COMPANY Model 400A Series 2. owner Name (As shown on registration certificate) THORAIR LLC Address As shown on registration certificate) Address 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. ril I I AIRFRAME MYTHEOMARCROST COWAIN (As described in Item I above) RK.244 K POWERPLANT K n PROPELLER APPLIANCE Type 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 have been made In accordance with the requirements of furnished herein is true and Identified Part In Item 5 above and described on the 43 of the U.S. Federal Aviation Regulations reverse or attachments hereto and That the Information Extended range fuel per 14 CFR Part 43 App. B 10/04/2019 umTotemic. Pursuant to the authority g Administrator of the Federal i, rsons spec ' • .. , t e un Administreti• ' and is n leg I In Item 5 Approved vial nspected in the manner prescribed by the Rejected BY — Manufacturer Maintenance Organization — Persons Approved by Canadian Department of Transom' ____j FM RI Standards Inspector FM Designee MI  Repair Station pectIon Authorization Other (Specify) Certificate or Desi nation No. CRS# WC7R346J Signature/Da f Author ed Individual __ ...._--------- 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 FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE November 30, 2018 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MANE Textron Aviation 3. MODEL NO. N541000-004 4. TYPE Mkorst &*e. Propeller, ea) Forebody Assy S. NAME OF APPLICANT Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA SLREIffla NT-EO-1118-31 Rev. IR November 29, 2018 Engine Inlet Rivet Repair. --- 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 Pen 193. dots nand above and on 'Bathed appacsoie requirements of the AInvortnIness K Recommend wired bydrecelon of the AdrranIstralor end In accordance with conditions and Ilmitallons of appcdnMsent under 14 CFR sheds numbered _BA, have been emartned in accordance with established procedures all found es coos* et Standards Listed approval of these data these data I (We) Therefore FrA. Approve it SIGNATURE(S) OF DESIGNATED ENGINEERING RE PRESENTAttVE(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

e i (6, MAJOR REPAIR AND ALTERATION US Departalerd 0/ Trenelarlation (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation taimiwarzion Olaf NO. 2120-0920 SM Ent I QM O Ekciront Trackhg Haw For FAA thia Oral 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)) 1. Aircraft Nationakty and Registration Mark UNITED STATES / N188TS Serial No. RK-244 Make RAYTHEON AIRCRAFT COMPANY Model 400A Series a Owner Name (As shown on registration certa1cato THORAIR LLC Address As shown on registration certificate) At:keen 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. WI [j AIRFRAME RATIMONAMCIMFTCOSIMY (As described in Item I above) RK-244 K K POVVERPIANT PROPELLER I I APPLIANCE 11Y01 Manufacturer 6. Conformity Statement A. Agencys Name and Address B. Hind Of Agency sew Constant Aviation LLC U. S. CerWketed Mechanic 1 Manufacturer Newt I Portion Certificated Mechanic C. Certificate No. a, CLEVELAND suds OH Ceblitaied Re r PM/ Station CRS#WC7R346J zis 44143 c,,,,....., USA 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 Mfonnallon Wished herein is true and Extended per 14 APP. range fuel CFR Part 43 B K 10/04/2019 turn-Vs-Service Pursue Administrator I to the authority g nri of the Federal a ion Administrati end Is I in item 5 Approved Inspected In the manner prescribed by the Relected t..--- — FAA Fit. Standards Inspector Manufacturer Maintenance Organlzabon Persons Approved by Canadian Department 01 Transport BY FAA Designee M Repair Station i spection Authorization Other (Specify) Certificate or Designation No. CRS# WC7R346J Signature/Da AW d IndNidual .----------------- / 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 FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE November 30, 2018 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Textron Aviation S. MODEL NO. N541000-004 4. TYPE (Aber* Engine, People, art) Forebody Assy & NAME OF APPLICANT Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA & PENTIF(GM.PN 7. TITLE NT-EO-1118-31 Rev. IR November 29, 2018 — Engine Inlet Rivet Repair. Notes: 1) The structural approval is demonstrates subparagraph 2) This form constitutes substantiation data are approved herein. This the data listed above specified by paragraph and engineering data necessary for for the entire repair. —END aspects only of the above Ilsted only for the engineering data. It Indicates compliance only with the regulations listed below as 'Applicable Requirements." FAA approval of all the of compliance to necessary requirements 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 I n 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 1 of 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 Teatret Aviden 400A Alrenol Soorial Naait) 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 enge Int» forebody neemt*: The repair wil be accennistied on It» RH engen ijkt forelndy assembly (PIN: N541000-004. Sin. Ft0010) REGULATORY Aa ~d Pa MorinhaN Aa tasa /t~ clualcabeSMOZIFUFAI *pen/ b ~d to San, ~IS a I44JOR • - anion, D YES ISINO MMO 01160RO LU D YES NO ~We InhAeOreal O YES giro Pmbn OS Peperibiba • YES Ca NO Das tble EO signilkently aflect wenk beaam otiodural strengt eircraft perbmara peperplant opreten, light dandaddicre. or ober aineortiiness goalies? MAJOR ' . ' ... b YES /APK* OIO Cm tb EO be accompliihod by accepled paden a dementary operator» MINOR D YES I ? — II Pompen done, oe& Ibis EO special* affect inwort elt»? ' ~gr St MINOR !Duo assks. tE3 1/MOR O MNOR Ei STC (Ne ST02371LA) ~ISW Ballifo Clep D YES 0 NO MA ~COO NINA E3 YES 1:1 NO GENERAL Crimen UWAticivnnta repro 1: Oemaged Rivel Locatief, en RN Engte Wal eig, Motel Stan) remenitenyeas O YES 0 NO Resafidaterom 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& engerd ringt trem ceesenellen. dur Is Snot and 81104 at R stands WA P. Avabalumov ACIION DAM PrepreedEly 10/1/2019 ander' By 10/1/2019 Approved By ikowdbyPinUsa vinv• 1011/2019 >019.10.02 Wil.» mto Form No. NT.E0-01 I Ree A Page 1013 This Document h Unzontroted Onc• Ptt:lied EFTA00011677

• • • EFTA00011678

nextant aerospace ITEM //fatMAGMED //U/da! //REBORN EO a: NT.EO1118-31 DISTRUCTIONS Title: Engine Inlet Rivet Repair ENGINEERING ORDER 1 PROCEDURES 1 Visually rasped the engine inlet hp and barrel for any other damaged, missing a loose bsteners. • If no addennal discrepancies are detected, calla° with repair as °dined below. - If additional descepamies me rant canted Nettie Aerospace la depositors CiEs•C« 00 2 3 Visualy inspect No engine roan es defined in Sib Task 724140420-801of hi Mann Inlombonel LivE WtINTENANCE MANUAL- FJ443AP 111030402 (blest re' ). • If no additional cracrepanOes are detected. conatie with repair u coined below. • If Mai:anal durepancies me noted. corded Nettant Aerospace for deposition. NVE C.A.C. OSS e 41/ 2 Cs4.c, 0.' 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. 4 Prepare the holed the missing bsteners for instillation of Caiegyailax Riven RN CR3212-5.XX in feu of nominal solid rivets MS20426AD540C • Prepare ham by aging and reaming to the required rivet Sae, as required, per ClwayMaa clocunent CA.1015 • Determine be correct gdp Sangth for to fasteners to be used. cabana Cherybax document CA-1015. • 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,» t/uS8 13 San crIstAtall A RSA WC7R346J AlxaAfleB1W NIMILA lc 2•Vel DATE 10/27 Form No. NT.E0-01 I Rev A Page 2 ol 3 This Document is Unconuolled Once Printed EFTA00011679

• • • EFTA00011680

ry • • nextant aerospace //REINiAGiNED //RESULT //MORN EO /: NT-E0:11111-31 I Title: Engine Inlet Rivet Repair ENGINEERING ORDER Figure 1: Damaged Rivet Location on RH Engine Inlet Up (Typical Shown) Page 3 ol 3 Form No. NT•EOA1 I Rev A This Document Is Uncontrolled Once Printed EFTA00011681

S • • EFTA00011682

0 MAJOR REPAIR AND ALTERATION US DepeVret of Tranwortefon (Airframe, Powerplant, Propeller, or Appliance) Wend Avliclon Adearileintlein DNB ,40- 2120'0020 Exp. Pamela Elearerie Track0g Witco For FAA Use Only 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)) 1. Aircraft Nationality and Registration Mark UNITED STATES / N188TS Serial No. RK-244 Make RAYTHEON AIRCRAFT COMPANY Model 400A Series 2. Owner Name (As shown on registration certificate) THORAIR LLC Address (As shown on registration certiecate) Address 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. I-1 m, AIRFRAME MYPEOP.A0CRAFT COMM" (As described in Men; 1 above) MOEN POWERPLANT PROPELLER APPLIANCE Type 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 ♦ CalLated Certificated Repair Stallion CRS# WC7R346J 10 44143 Candy UNITED STATES Maintenance Organ/wk., 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 per 14 CFR Part 43 Am. B Sign 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 Administrator of the Federal Aviation Administration and la I Approved In the mama prescribed by the Rigel:led BY --"' FAA Fit. Standards Inspector — Manufacturer — — Maintenance OrgaNzatlon Persons Approved by Canadian Depaitrnen1 of Transport = FM Designee I ^ Repair Station Inspection Authorization Other (Specify) Certificate or Designation No. C RS# WC7R346J Signature) . e uthori ed Individual ,,i 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 al more 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 ST1 1 216DS MU traffic-au laud to: BHE & Associates, Ltd. San Antonio, TX 78216 tert,fes doe for dap is the type asign fi r dejedfruandert aid Me limaationsaftatcotdiftims denybtr as Jpenfreanron meets de airavuotheartythetwas iltaft25 ?Pi/federal Aviation Regulations. Original Product — Type Ceniticate Number: See attached approved model list (AML) Make: See attached AML Model: See attached 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 wild is the 6ashforappronisiende fit nittsuntwifere4 saspellatid; and inrokeefor a termination ate is oderwite ene6/10flay t6efiminu aide Fralreigratioll dIteladdrinu Date of Application: February 9. 2018 Date of Issuance: June 29. 2018 Date Reissued: 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 Supplemental 75 pe 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 - .. Revision Number" ri Ion : -l7 - ..-:.4 of change t....... ... ., •-• . ' 106 Dats.- NIOtOY0 . IR Initial Release 5/9/18 A 6/27/18 Page 8, Section 1.1 revised transponder and GPS part numbers. Page 10, Section 2 remove' light Hours' from Table 4 B Page 4, Revised list of aircraft models in Introduction Pages 9, 24-25, 28-29, Revised aircraft models in Tables 3, 7, and 9. Pages 8 and 28, clarified wording for installation. 11/6/18 C Revised Table 3 on page 9 Revised Table 4 on page 10 Revised Table 5 on page 26 Revised Table 6 on pages 27 & 28 Revised section 6.1.9 on page 31 Revised figures on pages 13 & 20, Added figures on pages 14, 17 & 18 1/18/19 D Added STC number on page 4. Added figure on page 24. Revised form in Appendix C. 3(lcitict 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- 004/005/006/007/010/011/100 0, 1 or 2 *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- 004/005/006/007/010/011/100 0, 1 or 2 •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 Aircraft Transponder Installed/Retained/Replaced GPS Installed/Replaced , Antenna Installed • I Learjet 60 TDR-94s or 94Ds GPS-1203C or GPS- 40005 CI 429-200 Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, Gulfstream 100, G150 TDR-94s or 94Ds GPS-4000S N/A Gulfstream G-1159, G-1159B, G-IV, GV TDR-94s or 94Ds GPS-1203C or GPS- 4000S CI 429-200 Gulfstream G-1159A TDR-94s or 94Ds GPS-40005 N/A Gulfstream 200 TDR-94s or 94Ds GPS-4000S N/A Textron Aviation 500 TDR-94s or 94Ds GPS-1203C or GPS- 40005 CI 429-200 Textron Aviation 550, 5550, 560 TDR-94s or 94Ds GPS-1203C or GPS- 4000S CI 429-200 Textron Aviation 400 TDR-94s or 94Ds GPS-1203C or GPS- 4000S CI 429-200 Textron Aviation 400A TDR-94s or 94Ds GPS-4000S N/A Textron Aviation 650 TDR-94s or 94Ds GPS-1203C or GPS- 40005 CI 429-200 Bombardier CL-600- 1A11 CL-600-2Al2, CL- 600-2616 TDR-94s or 94Ds GPS-1203C or GPS- 40005 CI 429-200 Sabreliner NA-265- 65, NA-265-70, NA-265- 80 TDR-94s or 94Ds GPS-40005 N/A Textron Aviation HS.125 700A, BAe.125 800A/800B, Hawker 800XP TDR-94s or 94Ds GPS-1203C or GPS- 40005 CI 429.200 Textron Aviation 1-15.125 700B, Hawker 750/850XP/900XP TDR-94s or 94Ds GPS-4000S N/A Dassault Aviation Falcon 10, Mystere- Falcon 50, Mystere- Falcon 20- C5/D5/ES/FS, Mystere-Falcon 200, Mystere-Falcon 900 TDR-94s or 94Ds GPS-40005 N/A 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 310.00 MOO 03 21°4° Fs mos n 295.00 32140 FS is 25000 I FS 13600 21130.22"D OO FS 193.00 Fs 19900 FS 364.03 FS Fs 343.00 379.00 FS 394 00 FS TS 424 449.95 473.15 rs Fs It 499.00 MAO 539.00 IS FS FS 441.50 494.00 513.00 • s' br 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 F'S FS .46 FS FS FS 17224 196 FS PS Fs PS 124.61 141.14 159.25 II FS 203.35 221.46 240.75 260.04 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 FS FS 60.91 99.02 FS FS 6996 108.07 'Pi iirki 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 59 00 FS FS FS 134.00 94.00 FWD 117.00 PRESS BOOM i FS FS 151 .00 179.02 FS 165.00 FS 225.23 23 (560) FS 223.40 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 FS 58 00 FS 94.00 FWD PRESS BLKHD FS FS 172.00 202.00 FS FS 157.00 187.00 ACCEPTABLE LOCATION FS FS 261.00 288.76 FS I 245 00 272.00 I 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 }I I I J~p7III13 171 07 M11O-1 MO FII 201.0 202.3 Ft r-T T 1 1'0IOIOI 000) - 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

59.23 7523 r5 61.23 47.23 F3 33.3 F2 I I DocuSign Envelope ID: CFB628B5-6FE8-4CEID-A4E3-5461F9B2D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS LEARJET 60 110.99 " 124.39 151.19 170,59 201.79 222.1 FS Fl 137.79 110 F12 F14.4 99.57 164.59 184.99 1210.19 F11 f13 F 5 Fe 197.50 I 1941 1 1 1 I I I I I I I I I I 1 I I I 70.59 Fl IA ACCEPTABLE LOCATION 336.61 F23 216.. 274.59 302.59 323.59 I 355.16 IS F200 F21A I . F25 3 234.19 25059 2M29 lel 4663 F17 F19 F21 F22 F24 I 0 orr0 1 IL MI ' 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 IAII- 100 ...,•*#'....' I I . I. I N _ I I I I I ...1 I 1 1 I H .1 I \ I- I-1 I 1 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.' 181.0 205.0 229.0 145.0 193.0 217.0 241.0 FS FS FS FS WL 100 C ES 63.0 FWD PRESS BUCK) vzi I I I I 1 I I I I n 1 I I i- I I I I -L p_ - - I I .1_I J 1 I I\ 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 % 1 (WL 0.0) I' 000 I I 0 0 I I III -- - SS 0 M III III I I I I II I I /1 / I I I II t i // // I I I I -.L 7 ALTERNATE LOCATION LOOKING AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD (TEXTRON AVIATION 400) II 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 I \-- TT IF I. I Il l i I ,II. -- -LL-,__LI LOOKING AFT AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD (TEXTRON AVIATION INC. 500, 550, S550, 560) 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

; '' locq 1 • 'I 4. 44 * ID: o•r:: I:I IB+11:4:11-4- {s _ :oo I ( !! ;;; + • ---t DocuSign Envelope ID: CFB629BS-6FEB4C80-A4E3-6461F9132D045 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS CW1 747F (ALTERNATE LOCAnOIN WOMAN MOW rc-: -X+ 7:i m -it r t-t,- 4* i Vc It ilit a ±:ii- ±: :r 44 1 4 1 1 ; • + r . :* /‘+/ t: I LI I ° :+: : . 4L+" .r*: 1 O Pl ICIM I:1 1 ! I:l stt i , ,42 HI i In: Etifa : 4 -141?1 1-#11:4 I : I I II:I I Iiiiii il I iiii+pool: 1+4 ,:l:; O: 0.1 ifr: III. II IA\ ,...„ ,,,,. 4,, • rs, • Lk' i _ 14+ 1 1 :+: V' +"\ , fr, I ,41 i i..., , _EL LOOKING AFT AT FRO SCE OF FORWARD PRESSURE Bult01110 (LEARJET 60) I- I : +, 1,1 II I I I 1+7 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, Innsspectitiont:y#: tcvaltlienettatto i tau ada Ealtaijiar" !lc • ..41:insiirat";:z4TTEraillirs.-:417.4e-tir4LW-re--412 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 g a • AI EAT ;Xl 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 Aircraft Manual Document Number Learjet 60 Non-Destructive Inspection Manual NDI-2 (Chapter 3) Textron (Citation) 500, 550, S550, 560 Series 500 Non-Destructive Testing Manual 5056ND (Part 6, Chapter 20) Textron (Citation) 650 Model 650 Non-Destructive Testing Manual 65ND (Part 6, Chapter 20) Textron (Beechjet) 400, 400A Model 4001400A/400XP Maintenance Manual 128-590001-9C29 (Chapter 20-80-03) Textron (Beechcraft) HS.125 700A, Bae.125 800A, Bae.125 8006, Hawker 800XP 125 Series 1-800, Hawker 750, 800, 800XP, 850XP, and 900XP Non-Destructive Testing Manual N/A (General Techniques Part 8) Challengers Structural Repair Manual N/A (Chapter 51) Gulfstream G-1159, G-1159B, G- IV, GV Structural Repair Manual N/A (Chapter 51) IIIIIIIIII____ FAA APPROVED: 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 Nose Avionics Bay Forward Nose Access Panels (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 Learjet 60 Nose Nose (GPS-4000S) Cabin (1203C) Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, Gulfstream 100, 0150 Nose Nose Gulfstream 200 Nose Nose Gulfstream G-1159, G- 1159A, G-1159B, G-IV RH EE Rack, Cabin RH EE Rack, Cabin Gulfstream GV LH & RH EE Rack, Cabin LH & RH EE Rack, Cabin Textron Aviation 500, 550, S550,560 Nose Nose 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 Textron Aviation 650 Aft Cabin Nose (GPS-4000S) Cabin (1203C) Bombardier CL-600-1A11 CL-600-2Al2, CL-600-2B16 Under Floor, Cabin Under Floor, Cabin Sabreliner NA-265-65, NA-265-70, NA-265-80 Nose Alternate: FWD EE Shelf Nose Alternate: FWD EE Shelf Textron Aviation HS.125 700A/700B, BAe.125 . 800A/800B, Hawker 750/800X131850X131900XP Nose Alternate: AFT EE Shelf Under Floor, Cabin Alternate: AFT EE Shelf Dassault Aviation Falcon 10, Mystere-Falcon 20- 05/D5/E5/F5, Mystere- Falcon 200, Mystere-Falcon 900 Nose Nose Dassault Aviation Mystere- Falcon 50 Nose Nose 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 Equipment/System Model/Part Number ' d Amp Max Loa s in TDR-94 622-9352-502 1.79 TDR-94D 622-9210-502 1.79 GPS RECEIVER GPS1203C 84327-50-XXXX 0.179 GPS RECEIVER GPS-40005 822-2189- 004/005/006/007/010/011/100 0.56 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 GPS 4000S ADS-B GPS Collins GPS-40005 Global Positioning System Installation Manual, document 523-0780545, Maintenance Section TDR-94D TDR TDR-94/94D ATC/Mode-S Transponder System (-5XX), 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. FLASHLIGHT INCIDENT - LIGHT BEAM 5° TO 45° EYE ABOVE REFLECTED / LIGHT BEAM REFLECTED LIGHT BEAM FAYING SURFACES CRACK OPEN TO SURFACE 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- 1A11 CL-600-1A11 PSP 601-2 Bombardier Inc CL- 6002Al2, CL-6002616 CL-600-2B12, CL-600- 2616 CL 604 AMM Dassault Aviation Falcon 10 Falcon 10 Dassault Falcon 10 Maintenance Manual Dassault Aviation Mystere-Falcon 20- C5/D5/E5/F5, Mystere Falcon 200 Mystere Falcon 20- C5/D5/E5/F5 Dassault Fan Jet Falcon Maintenance Manual Dassault Aviation Mystere-Falcon 50 Mystere Falcon 50 Dassault Falcon 50/50EX Maintenance Manual Dassault Aviation Mystere-Falcon 900 Mystere Falcon 900 Dassault Falcon 900 Maintenance Manual Galaxy/Gulfstream G100/SPX G100/Astra SPX P/N G100-1001-11-1 Galaxy/Gulfstream 1125 Astra 1125 Astra P/N 25W-1001-11-1 Galaxy/Gulfstream 200, Gulfstream G150 Gulfstream 200, G150 --------- Gulfstream G-1159, G- 11596 G-1159, G-1159B Gulfstream II Maintenance Manual Gulfstream G-1159A G-1159A Gulfstream III Maintenance Manual Gulfstream G-IV G-IV Gulfstream IV Aircraft Maintenance Manual Gulfstream GV GV Gulfstream V Aircraft Maintenance Manual Textron (Citation) 500/550/S550 500/550/S550 Model 500 Maintenance 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) 560 560 Model 560 Maintenance Manual Textron (Citation) 650 650 Model 650 Maintenance Manual Textron (Beechjet) 400, 400A 400/400A P/N 128-590001-9C Textron (Beechcraft) HS.125 700A, 700B 700A, 700,B AFMS-125-700 Textron (Beechcraft) BAe 125 800A, 800B 800A, 800B AFMS-800 Textron (Beechcraft) 750 750 AFMS-800XP Textron (Beechcraft) 800XP 800XP AFMS-800XP Textron (Beechcraft) 850XP 850XP AFMS-800XP Textron (Beechcraft) 900XP 900XP AFMS-800XP Sabreliner Aviation NA-265-70, NA-265-80 NA-265-70, NA-265-80 P/N SE 0405 MM Sabreliner Aviation NA-265-65 NA-265-65 P/N SE 0303 MM 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, equipment installations and ground test) 584-00-0001 TDR-94/94D ATC/Mode-S Transponder System (-5XX) Install Manual 523-0821492 GPS-4000( ) Global Positioning System Installation Manual 523-0780545 Equipment Installation Manual for the FreeFlight System Model 1203C GPS/SBAS Sensor 86764 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: Signature: Self explanatory. Date: Self explanatory. 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

0 US Cerviertem MAJOR REPAIR AND ALTERATION of Transprecen (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Acenhesealoa 061B Na 21200020 5v: 5/30201e Slecircnie Trackeo itenbee For FM Use day 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)) 1. Aircraft Nationality and Registration Mark USA/N493LX Senal No. RK-244 Make Raytheon Aircraft Company Model 400A Senes 2. owner Name (As shown on registration certificate) Flight Options Address (As shown on registration certificate) Address 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. O x AIRFRAME minneeiriir (As described in Item 1 above) xx.h. 0 POINERPU*17 IMI ni PROPELLER E El APPLIANCE Type 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 CRS# 25NR667B AI 44I43-1453 CoottY use Certificated Maintenance Organization 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 Aer 14 CFR Part 43 App. B Signature/Date of Authorized lndivi /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 fi Rejected FAA Flt. Standards Inspector Manufacturer Maintenance Organization PerSOM Approved by Canadian Department of Transport BY FAA Designee X Repair Station Inspection Authorization Other (Specify) Certificate or Designation No. CRS# 25NR667B Signature/Date of Authorized 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 Raytheon Aircraft NUMMER N188TS Company 400A RK-244 Wansport AUTIORITY AND BASIS FOR ISSUANCE Tim ~hem mikse Is MAO 'usunn 41 U.S.C. I M704 and tet tra is ol te Med mumx. Im ~I nebb kanel has teen Ameneel and bm& b con» 4) he I. møta Sekt MOS wen In Si *nåml erd tes Sin Ikno b ~n rimniner4 Min mokaNs memMmenve anti Mit areteliness ca as moMnI ty Ames t ts Con ca MAIMIOnn fid bonn, emem M 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 w1 Pon2I.43, and tiden NOS Avatm Rimelann. As irs~ sd M an. N#4Iffld b elt Unnd Maks. )ATE OF ISSUANCE R3/06/2014 GL-25 44,111~.~01. 3 pts orket 14SCERIIRCATE RUST SE DISPLAYER NITE MIOIM1 IR ACC0R0ANCE WRII APPLICISE KREML AMT> REGIAATOIS. A Fonn 1100.2 (04-11) Supersedes Previous EMMA DESIGNATION NUMSER FeoPn fttRAvi- EFTA00011729

EFTA00011730

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAI. AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE I NATIONALITY AND REG;STRATION MARKS 188TS 2 MANUFACTURER AND MODEL Raytheon Aircraft Company 400A 3 AIRCRAFT SERIAL NUMBER RK-244 5 AUTHORITY AND BASIS FOR ISSUANCE This aivotess cedifute is issued pursual to 49 U.S.C.§441d4 and cues that, as of te dale of issuance, the knit to vkh issued has been lispected and found la cohfomi to the type certificate therefor, to be in conk for safe operation, and has been shoo lo meet the (quires alba appliote (mottos:Pie and detaised airworthiness oode as provided by Wavle) lhe Convention on loleminhal Cid Ando, except as holed bait bagel: -None- FS-'?SO "" 4 CATEGORY Iransport 6 TERMS AND CONDITIONS UtSSOOnef seehdered, suspended, reveled, Of a lEnitatioo date is otherwise eslabished te FAK, this iirivofiess cetficale is effective as long as the maillenance, prevehlative mairdenarte, and alleradols are performed in accordance wit Pat 21, 43, and 91 of the Federal Aviation Regulations, as appropriate, and the ate is relisleted ih to Utd States. DATE OF ISSUANCE DESIGNATION NUMBER R3/06/2014 GL-25 Arty allergen, reprodudon, Of misuse of Oils rdicale may be puhishab'e by a fine rId weeding 11,660 mririsonment hot exceerfn9 3 elfS aboth. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE VIITH APPI(CA8LE FEDERAL AVIATION REGULATIONS. FAA Form 81002 (04.11) Supersedes Previous Edition 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

US Department MAJOR REPAIR AND ALTERATION of Trarecolaeco (Airframe, Powerplant, Propeller, or Appliance) Federal Minion AenenIstratIon nefiee 2120-0020 Erg 531/N18 Electnooe Trecbro Nine For FAA Use Only 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)) 1. Aircraft Nationality and Registration Mark USA / N188TS Serial No. RK-244 make RAYTHEON AIRCRAFT COMPANY Model 400A Series 2. Owner Name (As shown on registration certificate) THORAIR LLC Address (As shown on registration certrficate) swan C.,/ SANDUSKY State OHIO Zp 44171-221$ Catrily UNITM STATES 3. For FM Use Only 4 Type 6. Unit Identification Unit Make Model Serial No. Repel Alteration  RAMC°. MOW Call1en (As described in Item I above) AIRFRAME POWERPLANT X -- 7 [7 PROPELLER ri❑ APPLIANCE Type 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 Pa in., r Foreign Certificated Mechanic C. Certificate No. cc, ciewiene sub ollb i • Cerlillaterl Repast StabOrt CRS# WC7R346J ye 44143 careen. united Stain Certificated Maintenance OrganizatiOn D. I certify that the repair and/of alteratIon have been made in accordance furnished herein is true and correct EXtended range fuel made to the unit(s identified in item 5 above and described on the reverse or attachments hereto with the requirements of Pan 43 of the U.S. Federal Aviation Regulations and that the information to the best of my knowledge. 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 Administrator of the Federal Aviation Administration and 's I in Item5 1/22sinspeed Approved ct in the manner prescribed by the Rejected ,--.—.0 FM Flt. Standards Inspector Manufacturer Maintenance Org nization Persons Approved by Canadian Department Of Transport BY ~I C Other (Specify) FAA Designee I Repair Station Inspection Authorization Certificate Designation or 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 Left Wingtip Assembly Left Strobe/Position Light Assembly Wing Tip Lens Right Wingtp Assembly Right Strobe/Position Light Assembly Wing Tip Lens Tail Strobe Light Tail Position Light Strobe Power Supply Installed Equipment Item Left Winglet Assembly Right Winglet Assembly Left Winglet Light Assembly Right Winglet Light Assembly Tail Strobe Cover Plate Tail Position Cover Plate Part Number 45A10552-001 45A88750-22 8888-170000-01 45A10552-002 45A88750-22 8888-170000-02 4588315-121 45A88754-11 01-790080-00 Part Number NEXT-SA15250LA57-10001 NEXT-SA15250LA57-10002 87-03916-001 87-03917-001 NX0047-3340-0101-001 NX0047-3340-0102-001 Serial Number 00575 Serial Number S-N EXT-0001 S-NEXT-0001 00214 00216 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 - "cigirdcrul (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.tmonendtar aosts.4/^ a lawsresirays dole w theitsgm.YE eViii4e4.44 EgenadheErrhso (AA Alwree.olyx;thew...4,197,a44Theen. 244 0rffstieraim Ode Vei.l.gredrner.• March 24, 2008 September 27, 2011 arehnseaSeesei. .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 trittufard in ocronforwe with Tilt21.47. EFTA00011741

EFTA00011742

e2b MAJOR REPAIR AND ALTERATION G1 / U.S Detwomert ce (Airframe, Powerplant, Propeller, or Appliance Trongorubon Foam, Aviation AdoONstnelon Form Po tressed OW No 2120.0020 11/30,/2007 Electronic Tracking Number For FAA Use Only 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) 1. Aircraft Nationality and Registration Mark N493LX Serial No. RK 244 Make Raytheon Aircraft Company Model 400A Series 2. owner Name (As Mew,, On registration Certificate) Flight Options .LLC Address (As shown on registration certificate) 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 K 0 AIRFRAME (As arescnbed in Item I above) 0 K POWERPLANT 0 K PROPELLER O K APPLIANCE Type Millilelig Of 8. Conformity Statement A. Agency's Name and Address B Kind of Agency Nama Constant Aviation Address Cry Cleveland stow. OH zip 44143-1453 country USA O U.S. Certificated Mechanic O I PAartufaCturtot O Foreign Certificated Mechanic C. Certificate 140. a Certificated Repair Station CRS # WC7R346J O Certificated Maintenance Organization 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 per 14 CFR Part 43 K App. 8 Signature/Date of Authorized Inc% • 09/Sep/2017 7. Approval for Return to Service Pursuant to the authority given persons specified below, the un Aciminlyttele: el the Federal Aviation Administration and iS t identified a in item APPROVED 5 was IN inspected in the manner prescnbed by the REJECTED BY FAA FR Standards Inspector Manufacturer Maintenance Organization Person Approved by Canadian Department of Transport FM Designee X Repair Station Inspection Authorization Other (Specify) Certificate or Designation No. WC7R346J Signature/Date of Authorized Indwilua 09/Sep/2017 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 Nationality and Registration Mark 12/Sep/2017 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 9/15/2011 of 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

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION -FEDERAL AVIATION ADMINISTRATION • STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND REGISTRATION MARKS 188TS 2 MANUFACTURER AND MODEL Raytheon Aircraft Company 400A 5 AUTHORITY AND BASIS FOR ISSUANCE This aiNionhiness certificate is issued pigswill ro a9 U.S,C.§ 44104 and ciffeas tat as of h dale of issuance, lbe a'rrctal to-Old issued has been inspected and loth Ia conform la the biao l2ftfolIO MeV, to be IP cordon for sale petal, nod has been shown lo meet Ila requirements of die applicable orrhensine and dallied airworthiness code as provided by Annul Odle ConverEon on International CHil Nation, min as noted herein, Exceptions: 3 AIRCRAFT SERIAL NUMBER RK -244 4 CATEGORY Transport -None- 6 TERMS AND CONDITIONS Untasssoonersurt¢ndered,suspended,sevoked,oraIek Non date isotheneise eslablIshed by Ilia FAn:Bils ainiiiness Ls effective as loll as Ibe maintanance, [WPM MAIRIOPRO, and detains are performed in accolanoe Mt Parts 21, 43, and Biddle Fedtial Aviation Reohlons, as appropriale, and the airclAis ROM IP the Ad Stales. ' DATE OF ISSUANCE 83/06/2014 DESIGNATION NUMBER GL-25 Any allemlion, reproduction, or misuse alibis cediNcele maybe punishable by a he nal Bank) RN) ar IMOSIONPIPOIReed4 3 years or bd. THIS CERTIFICATE MUST BED SPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AYIAi10N REGULATIONS, FM Form 8100.2 (04.11) Supersedes Previous Edition EFTA00011745

4 4 EFTA00011746

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION -FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND REGISTRATION MARKS N49311 5 AUTHORITY AND BASIS FOR ISSUANCE 2 MANUFACTURER AND MODEL Raytheon Aircraft Company 400A 3 AIRCRAFT SERIAL NUMBER RK -244 4 CATEGORY Transport This ainvotiness Rite is issued ptusuardlo le U,S.C. §,14iGit and cerUdes tali as of Ihe dole of issuance, the aircraft 0 which issued has been inspected and teund 0 coin to 0e type cetterate 086,0 he in condition foi sale operation, Ed hos been shown 0 meth tecui:emeols of the applicable comprottenSiVe and delailed aimodiness cede as proxided by Annex ft to Ihe Convention Internaennal Civil Aden, except as noted herein. Exceptions: *None* 6 TERMS AND CONDITIONS keg SeqrSUR ntlemtl,suspended,revoked,ora terminationdateisolheraiseeslebfshedbytheFAA,thleakwodhinessceAiticale is effectiN asking sthamaintenance,preventativemaiNenance,am fl2 it Pot 21,43, Bed 91 of the Federal Aeileen Re dalions,a5 *ale, and to airCril DATE OF ISSUANCE DESIGNATION NUMBER 03/06/2014 DART833943g Any allelloo, reprodudoo, a misuse of INS ceititale may he punishable by a fine not exceeding $1,069 or imposoemeel rot exceeding 3 pars or both, THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. FAA Form 8100.2 041) Supersedes Previous Edition 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 0 APPLICATION FOR LI' S 0461€70171 U.S. AIRWORTHINESS ol "r4Hponalion Federal AMARA CERTIFICATE Ameniurstion 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 space is (waned. use eaectunent Fn special Opt panne, complete Sect ens I1 VI. end Vii es appecable a i 1. REGISTRATION MARX N493O( 2. AIRCRAFT BUILDERS NAME nAm Raytheon Aircraft Co 3 AIRCRAFT MODEL DESIGNATION 400A 4 YR. MFR. 1999 FM CCOiNG 5. AIRCRAFT SERIAL NO, RK-244 6. ENGINE BUILDER'S NAME (MAW Williams International 7 ENGINE MODEL DESIGNATION FJ44-3AP 8. POWER CP pew s 9 es 2 PROPELLER [ULCERS NAME Fa/ N/A 10. PROPELLER MODEL DESIGNATION It AIRCRAFT IS I( ac eropk*F41 N/A IMPORT R 1 N § d APPLICATION IS HEREBY MADE FOR Om mks 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 5 PROyiSIONAL 1 CLASS I Awsue. emu 2 CUSS,' 1 AGR/CULTURE AN PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING 3 RESTRICTED Asa* Ammon, A Ms amend, 4 FOREST memo NassAmcM 5 PATROLLING 6 MATTER CONTROL 0 OTHER 6moel 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 a Esisiing Myatt wilICIA en limning., pleura a do mimosa $1011 4 antra smem(s) re a amoesi s BA OPERATiNG 86 a °Ining POMEIV U614E-SPORT lIC IION U9N-SINH 4gelP600. ."I sry tax1/31Oxial11011486, Mary finsotHress airmailietaaa a 21 I90 9 UNMANNED 9A REVAK,. ma DEVELOPMENT IOC' I CREW TRAINING AIRCRAFT 98 MARKET SURVEY I FERRY FLIGHT KR REPAIRS. ALTERATOG. PAAINTEWMCE OR STORAGE SPECIAL FLIGHT PERMIT wow. 2 EVACUATE FROM AREA OF IMPENDING DANGER 13 epreNen re eneA/Csa Irer corwAre Nam so 4. we 44•44.4.4.. en 44.44 440 3 OPERATION IN EXCESS Cf MAxaTUR4 CERTIFICATED TAKEOFF MIGHT 4 DELIVERING OR EXPCRDNG I 6 I • I PRODUCTION FLIGHT TESTING 6 CUSTOMER DEMONSTRATION FLIGHTS cl a MULTIPLE AIRWORTHINESS CERTIFICATE p.m. ABOVE 1,1•16:MOOMMOM fl ees 'Gaffed, MOND* i Pi in 5 X d A. REGISTERED OMER Ma Mom M confooled oat intate, IF DEALER. CIIECK HERE I NAME ThorAir LW MS. Sandusky. OH 44871 B. AIRCRAFT CERTIFIGATICR BASIS Him ammo ems we awasse• me ga MOMM3) i AIRCRAFT SPEOFICATKFI OR TYPE CERTIFICATE DATA SHEET Ira Ne am 44.44.',1 A16SW Rev 28 1 AIRWORTHINESS DIRECTIVES omen et emkm A Ma a• Hamm Toe moot*, ..44.4.4.4 0 Me IMMO Wainer WMIONP in. *M Ss AP ow • / DM Mm•Mitak.) Bi Weekly 2014 2/10/2014 - 02/23/2014 ARCRAFT LISTING /camp normrts$ WA / SUPPLEMENTAL TYPE CERTIFICATE 6/4 me es nth 47c Accepome) See Attached Sheet C AIRCRAFT OPERATION AND MAINTENANCE RECORDS / CHECK IF RECORDS IN CCSIPUANCENAni 14 CFR Ma 92417 TOT AL AIRFRAME HOURS 8616.1 TTAF 3 EXPERIMENTAL OM.Y crorFANH to.. mw, 4n [strew, AAA/ a4` 40 WA D. CERTIFICATON • I hereby <wily MAIM?* accordines mils TM 49 01the WHO Stale. aiwarTness cwVcate Amsted 14filitered arner (or his 4WD 8 MO Put deaf! m tam. that me anon Cole 44101 Is are [pica es FERMI Aselben RepAMICess. end the Ihe eircreA Is nomoto In 16 FORM ANOKA ASWIliSrea en el DATE OF APPLICATION 03/06/2014 NAME AND TIRE 'Fin tn..) Anton Koprivnik Agent &GNAT N. INSPECTION AGENCY VERIFICATION A THE AIRCRAFT DESCRIBED ABOVE HAS SEEN INSPECTED AND FOUND MRAORTHY BY: 044.40•44. mos ovIr 24 Cam/ V. I 2 14 CFR Mel 121 CERTIFICATE HOLDER Pre CooMMI0 Mal 3 CERTIRCATED MECHANIC Mfrs 04.1400”421 6 CERTIFICATED REPAIR ARON IOW amen NO) 5 AIRCRAFT MANUFACTURER MA* nine es fray DATE TILE SIGNATURE V. FM REPRESENTAITVE MIN/CATION Ossamtc sepszes,4 sea e.4414.44 / THE CERTIFICATE REQUESTED A I TIM :+m the rave 61404X4 ii1Seetion 1 or W meets moan for 4 AMEMSMETIT OR MODIFICATION OFCURRENT AIRWORTHINESS CERTIFICATE B. Inspemon the spec* figt4 pemil Lwow Seam MI Tros con04100 Dy I FAA INSPECTCR FAA DESIGNEE DATE 03/06/2014 MIOGIFS00 CFFICE GL-25 4 FAA INSPECT SIGNATURE DART833943 MP FM Form 8130-8 (4/11) NI PteirCUI Editions Superioded pt t it s, 9 V C. 1.--• MAR 1 0 2014 CLE- EFTA00011751

§I IF; 2 A. IAANUFACTURER NAME ADDRESS B. PROOUCTON BASIS (OMCk Opplable Rehl PRODUCTION CERTIFICATE (GMT ACAS OPMFMAt Noted TYPE CERTIFICATE OTHER: C. GinQUANTITY OFCERTIFICATES REQUIRED FOR OPERATING NEEOS DATE OF APPLICATION NAME AND TITLE (MINNOW) SIGNATURE VII. SPECIAL FLIGHT PERMIT PURPOSES OTHER TIAN PRODUCTION FLIGHT TEST 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) 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 CCU NOT MEET THE APPLICABLE NRWORTNNESS REQUIREMENTS AS FOU.ONS: E TIE FOLLONNG RES I R CTIOW ARE CONSIDERED NECESSARY FOR SA.E OPERATION. (Use ran E Hammy) F CERTIFCATIOI Ant" cm* Minim um roosono0 owmr (or Na KAM) of d out Seated Mom tot to *ar is registered Min tre Foleng Maga. Adorn unman in accorcance win DM 49 ol ligo Urand Salm Can 4001 olzo and migicabig Fail Mean Rogotallont AM MK Os Scut hog tom Monger) end is Nete Ice Om fltaN Onamect DATE NAME ANOMIE (PAN HIM/ SIGNATURE R ta a brg as ...IZ;: ec i , i s; 4 gi § 1 A Operatng Lentaactm are Matkings In COnVerma WEIN CFR WOOF, Ott As AppIcatle 0. Satomat <I Concenitg. FAA Ferro BI304 Meath when reptsmx0 It RAO Airmeiness CelAcalica ke mom Mae (Mach when resiroN a CononI CP6M A Lm1444414 llarated / C. Gala. Drafting& Prows^ alt (AMacit step tequentn i I. PreVous Afrovetrinela Certificate immg in Mcorglarm VAR IF CFR Swam 21.191 (0 CAR FOMM teutenno i 0 Curve Wotan ana Basra Mormon AvtAitei in Mar E FM F Alie AI Ito DAM ratK41. Fpm 337 (MmA men (man i J. Cycle' Meatiness CAMARA Issued In Mordants WO 14 CFR Anoka 21.183 (d) (dopy sow/ / F ins itzpeceon ROCONOS in MVO Records K. Us(+l4p01 ArgraElliolincal of Corpora FM Form 813615 MOO when rewind) FAA Form 8130-141111 Ai Provous Eddidif Superseded adman Formai -PDF Page 2 x2 AP. EFTA00011752

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION -FEDERAL AVIATION ADMINIST STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND REGISTRATION MARKS N493LX 2 MANUFACTURER AND MODEL Raytheon Aircraft Company 400A 3 AIRCRAFT SERIAL NUMBER RK-244 4 CATEGORY Transport 5 AUTHORITY AND BASIS FOR ISSUANCE This *Pitiless codhala is WI pool lo 49 U.S.C, 04164 and cedes del, as plata dalo ol Imam IP *tall to which issued has boa Odd and found lo oordorm loth lypa ceicole thlor, to 66 11109dliOri for sale operadoa, and has teen shown to meet the requirempls alto app!icahlo comprehensive and 'Maki airworthiness coda as pro* by Amax Blob Condo on Intomolipal C4 Nation, mantas rich hail Exceplions: *NONE* 6 TERMS AND CONDITIONS lints sow mended, sap*, 'evoked, klerroirellori dale is otherwise Petted b le FAA, this ahodies Whale is Palmas lop as h mitenco, praventalio mite/a, widiPa4s21,43,and SI of at Red Ade R MORS, as a ro ' le, and the a DATE OF ISSUANCE DESIGNATION NUMBER 03 06 2014 DART833943GL Any alvaOon, reproduction, or misuse of INs Cirliall) may ho piste% by a foie riot ova* 51,656 imprisonmord °pooling 3youscrbolt THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE fE0ERAl AVIATION REGULATIONS, FAA Form 81004 0411) Supersedes Previous Edition EFTA00011753

I i EFTA00011754

' UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION • FEDERAL AVIATION ADMINISTRATION SPECIAL AIRWORTHINESS CERTIFICATE A CATEGORY/DESIGNATION ERrirtienta 1 PURPOSE Market S:4rvq,‘ / Q w MANU- FACTURER NAME /4,,(( N/A q ,Y ADDRESS/di/id/WA. („% C FLIGHT FROM r /7 AVI,VeV'', \\\ TO iii ' ‘ WAY' ' U .,• , N- 493LX i; , t , .. SERIAL NO. RK-244 BUILDER RaytheonOki , raTt 'Cd.4, MO* 400A E DATE OF ISSUANCEFe ‘,0".5/401‘41' /O,.MRY Aug/ 04 /2014 OPERATING LIMITA S'Oe '\k -.: :5110:10,0 PART OF THIS CERTIFICATE DESIGNATION OR OFFICE NO. 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 CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE TITLE 14, CODE OF FEDERAL REGULATIONS (CFR). FAA FORM 8130.7 (071041 SEE REVERSE SIDE NSN; 0052.00.6934000 EFTA00011755

A A This airworthiness certificate is issued under the authority of Public Law 104, 49 United Slates Code" (USC) 44704 and Title 14 Code of Federal Regulations (CFR), aB The ainuorthiness ceifificale authorizes the manufacturer named on the reverse side to conduct production flight tests, and only production flight tests, of aircraft registered in his name, No person may conduct production flight tests under this certificate: (1) Carrying persons or propel/ for compensation or hire: and/or (2) Crying persons not essential to the purpose of the flight C airworthiness cethficate aulhonZes the flight specified on the reverse side for the purpose shown in Block A, D This airworthiness ceilificate ceitilies Mal as of the dale of issuance, the aircraft to which issued has been inspected and found to meet the requirements of the applicable CFR, The 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, No person may operate the aircraft described On the reverse side: (1) except in accordance with the applicable CFR and in accordance with conditions and limitations which may be prescribed by the Administrator as part of this certificate; (2) over any foreign country without the special permission of that country, E Unless sooner surrendered, suspended, or revoked, this airworthiness certificate is effective for the duration and under the conditions prescribed in 14 CFR, Part 21, Section 21,181 or 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

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EFTA00011762

*iiCa4117A SAC ?ROMA \O SER\ AL # MOOV_V EFTA00011763

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EFTA00011766

FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved O.m.g. No. 2120.0018 itai ion Dale 0228/2013 T2 I 0 1 3 U S Department aTranspenal Federal A AdmInIstr APPLICATION FOR ion U.S. AIRWORTHINESS laton CERTIFICATE on Ill INSTRUCTIONS - Print or type. Do not wille in shaded meat Mese re for FAA it use only. Submit original only to an authorized FM Representative. If acklronal 0/ -1 space is required. use rtectuneM For special tight permits complete Sections 3 -i II. 1/1 and VII as applicable. 22 ilr. Q 1. REGISTRATION MARK N493LX 2. AIRCRAFT BUILOEI3'S NAME (owl Raytheon Aircraft Co 3. AIRCRAFT MODEL DESIGNATION 400A 4. YR. MFR. 1999 N FAA COOING a a a u a I S 5. AIRCRAFT SERIAL NO. RK-244 B B. ENGINE BUILDER'S NAME mew Williams International 7. ENGINE MODEL DESIGNATION 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 (Crectiarreeem ram 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 5 PROVISIONAL I CLASS I Aeon On) 2 CLASS II r G I AGRICULTURE AND PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING t 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 ' EXPERIMENTAL BA Existing aircraft MithOlA WI aiworminess centate & do not meal 5 I03.1 2 r 4 Ordesti (mare mal to OF MOWN° $ OPERATING Be °wary LIM-Sport Kiiitaft sr U ai LIGHT-SPORT ornicl WSW, ' PnAlAutt, Issued spacial 99M-sporl Meow ainvonhiness canters under 5 VAC 9 UNMANE D 9A RESEARCH MID DEVELOPMENT [ 9C I I CREW TRAINING AIRCRAFT 90 MARKET SURVEY I FERRY FLIGHT FOR REPAIRS. ALTERATIONS. MANTENANCE OR STORAGE SPECIAL FLIGHT PERMIT promo 2 EVACUATE FROM AREA OF IIMENONG GANGER B opnAbno No pantheon IMO 00TOIMI Memo a w in mama m mart. 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 41 4:10600A01 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 P 0 A16SW / AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA SHEET ICA• ma and mummer Rev 28 / AIRWORTHINESS DIRECTIVES 403/4,0 4 *a aapikwidei 404 we cowpwata awg•womerter eft rail ADSUPPLEMENT mile* I n as assay sewn MOO IWO 0 OPON410/9 Bi Weekly 2013-25 12/02/2013 - 12/15/2013 P AIRCRAFT LISTING roraeraeamemOU NM i SUPPLEMENTAL TYPE CERTIFICATE (LIS member-SA SIC bitsponffic See attached sheet C. AIRCRAFT OPERATION AND MAINTENANCE RECORDS i 1 /c.00t:memtion CHECK F RECORDS IN WI 91 TH A i CFR sec 17 TOTAL AIRFRAME HOURS TTAF 8581A3 3 EXPERIMENTAL ONLY (Emu have sae arm MI chime Sited a wend) 2.81 ö D. CERTIFICATION • I hereby centy Nal am imordaroa with Tele 49 el the UMW Sires altworthWess crater. reapeslot Ms regtslarloviner(or Ns gentle! tie eirnalt deserted stove. that We amend Ca* 44101 ABS end swabs Federal Avietion Rogulatice, and that the repaired with Me Federal Aviation AtInintralam Iti Orereft has teen illSPOCIOd and is Arwonhy and OSP* for the DATE OF APPLICATION 12/29/2013 Agent SIG A THE AIRCRAFT DESCRIBED ABOVE HAS BEEN INSPECTED AND FOUND AIRWORTHY BY: Komar ma mammy Nall per it I1310.4oles/ I 3 se r W 2g 2 14 CFR put 121 CERTIFICATE HOLOER tom cement ram 3 CERTIFICATED MECHANIC (61.0494:41• No) e CERTIFICATED RE PAR $TATi N (OW CeMcate PM) t tul C 3 A CC 5 AIRCRAFT MANUFACTURER ter • • reran MN j V DATE TITLE SIGNATURE at (Ora AU *roam WC* awe A aVII) I THE CERTIFICATE REQUESTED > P A I Tad that ma maul described described n Seam I or VII more regurernents for 4 AMENDMENT OR MODIFICATION OF CURRENT AIRWORTHINESS CERTIFICATE 'S z 2 B. Impechan toter:mist No porta under Section VII was conducted by FAA INSPECTOR FM DESIGNEE Zi W g CERTIFICATE HOLDER UNDER 14 CFR pales 14 CFR Wit 121 OR 135 1a CFR 11 145 nYr a iF, 9u s DATE 12/29/2013 MIDOIF SOO OFFICE CLE-25 FAA Form B1306(4111) Al Previous &Mons EFTA00011767

EFTA00011768