el, -- MAJOR REPAIR AND ALTERATION US Department

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 WetterEms. 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 ❑ POWERPLANT ❑ 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 7Conticaled 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 ❑ 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:74 Z.--; .--DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEOES PREVIOUS EDITION File Number. H18777-01 Page 1 of 1 EFTA00011671 EFTA00011672 ei (6, MAJOR REPAIR AND ALTERATION US Departalerd 0/ Trenelarlation (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation taimiwarzion Olaf NO. 2120-0920 SMEnt I QMO 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[jAIRFRAME RATIMONAMCIMFTCOSIMY (As described in Item I above) RK-244 ❑ ❑ 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 ❑ 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» MINORD 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 41/2Cs4.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 vatinspected 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 fir 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" riIon : -l7 - ..-:.4 of change t.......... ., •-• . ' 106Dats.- 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- 4000SCI 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- 4000SCI 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"DOO 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 I245 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 FII201.0 202.3 Ft r-T T 1 1'0IOIOI000) - 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 II I I III I 1 III 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 1IL 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 III 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 II III -- - SS 0 M III III II IIII II /1 / II III ti //// IIII -.L 7ALTERNATE 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 Illi I ,II.---LL-,__LILOOKING 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 CW1747F (ALTERNATE LOCAnOIN WOMAN MOW rc-:-X+ 7:im -itrt-t,-4* i Vc It ilita±:ii- ±: :r44 141 1 ; • + r .:* /‘+/ t: I LI I ° :+: : . 4L+" .r*:1 O PlICIM I:1 1 ! I:l stti, ,42 HI i In: Etifa :4-141?1 1-#11:4 I: II II:I I Iiiiiiil I iiiii+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 III II 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 itau ada Ealtaijiar" !lc • ..41:insiirat";:z 4TTEraill irs.-: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-ftn2Critref.. 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=' . . !tains • 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 ManualN/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. IIIII”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 750/800X1 31850X131900XP 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 Avi