EFTA Document EFTA01326943

UNITED STATES OF AMERICA DEPARTMENT OF TRANSPORTATION-FEDERAL AVIATION ADMINISTRATION STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND 2 MANUFACTURER AND MODEL 3 AIRCRAFT SERIAL 4 CATEGORY REGISTRATION MARKS Raytheon Aircraft NUMBER N188TS Company 400A RK-244 Transport 5 AUTHORITY AND BASIS FOR ISSUANCE This airworthiness certificate is issued pursuant to 49 PROT85. § 44704 and certifies that, as of the date of issuance, the aircraft to which issued has been inspected and found to conform to the type certificate therefor, to be in condition for safe operation, and has been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention on International Civil Aviation, except as noted herein. Exceptions: -Nonextoz/tt/Aem 6 TERMS AND CONDITIONS Unless sooner surrendered, suspended, revoked, or a termination date is otherwise established by the FAA, this airworthiness certificate is effective as long as the maintenance, preventative maintenance, and alterations are performed in accordance with Parts 21, 43, and 91 of the Federal Aviation Regulations, as appropriate, and the aircraft is registered in the United States. DATE OF ISSUANCE R3/06/2014 Arnold Wolfe,(52:, s4? C,),VAL_. FM REPRESENTATIVE Any alteration, reproduction, or misuse of this certificate may be punishable by a fine not exceeding $1,000 or imprisonment not exceeding 3 years or both. THIS CERTIFICATE MUST BE DISPLAYED IN THE AIRCRAFT IN ACCORDANCE WITH APPLICABLE FEDERAL AVIATION REGULATIONS. DESIGNATION NUMBER GL-25 FAA Form 8100-2 (04-11) Supersedes Previous Edition SOMIGM_02754903 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024 I 825 PROT0 PROT50 EFTA_0024 I 826 PROT1 0 MAJOR REPAIR AND ALTERATION US Otooftrroft a Triespalatten (Airframe, Powerplant, Propeller, or Appliance) Federal ANSI AtiniMalereen erra la 2, 204020 Err SOWOIS Ottarcedt RCN Maw foe MA Use Only INSTRUCTIONS: Print or type an entries. See Title 14 PROT86 §43.9. Pal 43 Amender It and AC 43.9.1 (or subsequent revision thereof) for Instructions and deposition of this form. This report is required by law (49 PROT87. g44701). FaIn to repx1 can resultant:we penally lot each such violation. (49 PROT88. 946301019 1. Aircraft Nationality and Registration Mew UNITED STATES / N188TS Sent No. RK-244 /flake RAYTHEON AIRCRAFT COMPANY Model 400A Series 2. owner Name (As shoal en regatrarion csrtMcate) THORAIR LLC Address (As shown on nyistration CV: ea) Amen PO BOX 2218 SANDUSKY Pa" OHIO re 44871-2218 Caret UNITED STATES 3. For FAA Use Only 4. Type 6. Unit Identilleadon - Reese Mention tall Mae Model Serial No. 7 in AIRFRAME PAYTMONeetts./teONAWe (As described M Item / show) me244 POWERPLANT O nPROPELLER APPLIANCE Typo arinurackar 8. Conformity Statement A. Agency's Name and Address B. Kind et Agency Nee. Constant Aviation LLC a a Caritated Methane Altai:barer ram 355 RICHMOND ROAD Folio CellicM•11A•shanle C. Catificate No. Ph CLEVELAND as. OH 7 Crallaslad Rasa Saari CRS#WC7R348J a 44143 ea ," USA Crailuad Maintananos Oraarristion D. I certify DUI the repair anaor alteration made to the unas have been made In accordance Wm the requremorks of furnished herein is true and correct to the best of my km i Warned In Plan 6 above and described on the reverse or attachments hereto Pad 43 al me U.S. Federal Aviation Regulatens and that the InfomiatIon Extended TIMO0 SI prir 14 PROT89 Put 43 App. 8 fid ar Silkily I Steven A. Watkins 10/04/2019 vat for RMiletitillervice Punsuanl to the authority Administrator of the Federal below. the wit in item 5 Adml end Is 1 eyed nnspected .n Inc manner prescribed by Inc Rejected BY - FAA Ft Standards Inspector Manufacturer Maintenance Organization - Pence* Areemed by Camden Deporiereal al Ming:toe - Other FM Designee MI Repair Staler) neaten Authorization (SPec4 Certi cat or DesVation No CRS# WC7R346J SIgnaturaTM 7 / *Mud David Kerr 10/04/2019 FAA Form 337 (10/06) Page I PROT51 EFTA_00241827 PROT2 NOTICE Weight and balance or operating limitabon changes shag be entered In the appropriate aircraft record_ M alteration must be compabble with all previous alterations to assure continued conformity with the eppricable airworthiness requirements. a. Description of Work Acton"liked pt mote apace brewer:oft attach plcStional sheets. Wen* wth aircraft nalicoally and regiftrallon ma* end dale were Cask* red) UNITED STATESMinn tOAW20I9 Plogioniay and Ribaeleslon Waal DMa 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 MAGUS:nal Sews NO needled FM Form 337 (10/06) Page 2 PROT52 EFTA 00241828 PROT3 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION POMMSTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE November 30, 2018 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MARE Textron Aviation 1 MODEL NO. N541000-004 4. TYPE Meal &pia Papaw. MO Forebody Assy &NAME OF APPLICANT Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA IL ICENTIREATION 7 TIRE NT-E0-1118-31 Rev. IR November 29, 2018 Engine Inlet Rivet Repair. data are approved herein. This the data listed above specified by paragraph and engineering data necessary for for the entire repair. --END Notes: 1) The structural aspects only of the above listed approval Is only for the engineering data. It Indicates demonstrates compliance only with the regulations subparagraph listed below as "Appicabie Requirements." 2) This form constitutes FAA approval of as the substantiation of compliance to necessary requirements s Pun Pose or OATA: Englneedng data to support repair procedure for Textron 400A Forebody Assy P/N N541000-004, SIN R0010 under Nextant Aerospace Work Order No.10565.1.1. a APFUCMAI REQUIREMENTS (UM spa seated) PROT90 Tide 14 Part 25.301(25-23], 25.303(25-23], 25.305(eXbXcX25-231, 25.307(aX25-23], 25.801(25-00], 25.803i0b)(cX25-38], 25.605(8)(25-00], 25.807(25-23), 25.609(aXbX25-00), 25.611(25-23), 25.613(aXb)(cX25-00], 25.61%25-23], and 25.625(eXbXcX25-231 10. CERTIRCATION - Under Son Pan la on few above end an nelleen teginimmla el InAlmomnies o Recommend veMed by Senn of the AdmInIetralet end Pt manna MM co,20a4 end emtetione of spinning order 14 CM ached inn illabtal a MVO ben eurrinod In scan:Ince et nalbtolietl teoceOns ale lowellocanolyMe Sunders Used. op/Novel of then dale then dela I OW Trenrere 0 APProve II. SIONATUREMICF DESIGNATED ENE4NEERND RE pRESENTATNEMI 12. DESIGNATION NUIMERS1M 13. CUSSFICATIONNI 0 0j24.4":"...,7: Paul Nodding DERT-410115-CE StrurAures FAA Form 8110-3 (01101 SUPERSEDES PREVIOUS EDITION File Number: H18777-01 Page 1011 PROT53 EFTA_00241829 PROT4 PROT54 EFTA_0024 I 830 PROT5 • nextant aerospace //elimaaRel0 /AMU //RUJORN EO t HM0.111841 I Title: Engine Inlet Rivet Repair ENGINEERING ORDER ARTICLE DESCRIPTION fficlotWodl."401 Team &Won 100A Mast snomen:3 See Ramona - 1 - 711 - Ds parpote cilia E0 Pio aloe for Na raulato of PM web (PM (R7212-540t)of mpqpiste lerpeti• pace d Pe dyne* NM Met (PM: 1620426A0540() al M seine ktel kxstotfastoenet The regal's' te Owomphhed en OM Fal /pre PIN forecdy mean* (RN 1154100X01. Sett R0010). REGULATORY •••••••••pithsoolleaan oar citeilluandllialt Oa erpaanapkid to dIatchomarim 10.6:4 OYES ONO maw OYES 0 NZI let OYES ONO kip.* lerbibtred OYES 0 PO PeWoveliloistIsperesallos OYES ONO Dom ON EOPpleconey Yed might. tudana. tad stremb. Writ ;stoma. Lowniant aorta ION dnledwa a Mc airtellisse aempR OYES MICR ONO pale Cal It El) be exargished bp:aped palm or elarbropereket? MINOR OYES • AP312 • O NO Seism*? MeN,Meld INIWC9r•MONefedeinaltiness7 IMJOR ta iis MINOR ONO Ones IS NAM 0 MCA 0 STC (NI STOWILA 1 towns hiss Dap OYES ONO FMAlffl0VIL ION Elms O mo GENERAL IMIINIONSIO RPM I:O~RIvM Waft m RN Emise MitIM (TwINISbaw) esamstueepas 0 YES 0 NO IleSallainras Met PM N541000004 WI 80010 WO. 10S65 I. i ppm! WO. R we amoval). IOOW (R.1 W0) OperiMes Proms Smdketax CA.1015 REWSION sta. tan Iteran1P. NM INaalaa IR 11129/40l$ Mel Prcpaal NM P. Pmbelimoy RI 10/1/2019 UpiSled b remwe wok number DUMP itm dectike. three is mixt and $110.3 N M Meth NYi P. Awhalsnav Acta. w r MN Remade), P. Awhatheav fall/2019 COaoad By K. Ifenefripi ION/2019 AWInd al , DbakInismd P. Awhelam Pinkhas AYSIIMMOV MII..... , . eve by Mir ION/2019 201t10010•1110 4CW ram No. NT.EOOI IRIPA Pas t 03 This Coconut Is Unconerolf *0 Ono Printed PROT55 EFTA_00241831 PROT6 PROT56 EFTA_0024 I 832 PROT7 nextant aerospace Natinuato //NW //WOW I E0 IfT.E0•1118-31 I Title: Engine Inlet Rivet Repair ENGINEERING ORDER PROCEDURES MN INAPUVO4 Fla 1 Veually inspett the trgle Se! Sp and barrel la arty otw damaged, nisang et loose banners. - II ao *Maw! draepandes are deteceet ecetnue MI Well IS C4101100 bib. - II iaS36:444 descepron we rcte canted Nutt,* ABIOGDOCS ingetabIt / 1414 2 VisuallyAmpect ihe arra rotor a deined in Sub T ask 724t-20420401 a/ Inman Inlemelimel LYE MANTENAACE 144NUAL -F.144-34P III poem reaskin) • II no allialel dscrepaxies wa dettete4 COMMA at remints Sinai toot - Indto,. ones:* se MK COMM Nubia Myopia lonfospilica CO 3 Longs dareplilvats MIMI, in Fgt., I and worn ovkanplably dill cal to teak., tamale men'. makog sure not lo Sage, gin OrPIRIZI ile Welt( kit pill it O 4 F'pacee be lidos alio wissirg Winn tor WY/ion albatrAlax Nat PR4CR3212-5.XX in lau of ncortai sold Nees MS2042104:64X - PinPern hobiby ay 444 mop 13 IS nawbed *MO" at NOM. per Chanyt tenni CA.1015 • Disinvie be careel avie lievei Ix tie anus 13 Is int slam Cheaytka cloosrent CA.1015 • Usip Os aianufullenea nasnandad inalahlte WI Intl tin eimi issianes per OweiyMax (band CA-1015 • Inspect the cargaled MIS loyally to bdiro ether hat bum Woad end Ihe stem has Wad Mt ugh Ito Oat head. Reba Carnytter donna CavIOIS ler Impede. raid tartan. AA .4 4 '••tc., lag -80 - LIMITATIONS Rene INSTRUCTIONS FOR CONTINUING AIRWORTHINESS RCA's) Mow Pt rairisike brredke pylon ii MSS nulnlenence ranuat In pedal .*wis shdl Wein as iniceled in be simnel inanionwics mina °rowan 44444ofilipstkai pommel 42,4044• COMPLIANCE tIMPAR WW1 GP aer 410 A AfOVEMOIMNI)31 N.1,88 7:5 /MOM IOW MAIM itg 2.446/ no OTIAWalsOialla*MOESVRoea..."0.6•100 ook4 /i• 1 14~' CRS, WC7R346J OAT fo/t/i1 En Ma NT4041 /R. A Paget d3 This Neuman. Uncontrolled Once Printed PROT57 EFTA_00241833 PROT8 PROT58 EFTA_00241834 PROT9 nextant aerospace II NSMASIID MOW //MORN ENGINEERING ORDER EO k NT-E0-1118-31 Tttle: Ina Inlet Repair I Figure 1: Damaged Rivet Location on RH Engine Inlet Up (Typical Shown) P. 3 cI3 Form No. NT.E0-01 f Roy A Thls Docua*nl Is Unconirollod Once Prmied PROT59 EFTA_00241835 PROT10 PROT60.914 EFTA_00241836 PROT11 0 MAJOR REPAIR AND ALTERATION US Oen... Tninportallon Powerplant, Propeller, Appliance) now, 21204020 Es 501/201S Ibeeeee TnadneMetiew MAIM OM/ al (Airframe, or foists, Avilitlaa AdministeSs INSTRUCTIONS: Print or typo all entries. See Title 14 PROT91 gag. Pet 43 Appends 8, and AC 43.9.1 (or subsequent revision thereon for instructions and disposition or INS form. This repel Is required by law (49 PROT92. §41701). Failure to report can result in a civil penalty for each such Nankin. (49 PROT93. §46301(a)) 1. Aircraft Nationally and Registration Mak UNITED STATES / N188TS Serial No. RK-244 !make RAYTHEON AIRCRAFT COMPANY Model 400A Series 2. Owner Name (As shown as registabon caracole) THORAIR LLC Address (As shown on roghbation certificate) Anus PO 80X 22i0 VI SAPOUSXY saw OH 29 14$11 Cony VNITE0 STATES 3. For FAA Use Only 4. 5. Unit Idendfication (Mt Make Model Serial No. Revak Alteration ii pi AIRFRAME MYIIIIECOMIKOVIT CCIONIf (As Omaha in Man :above) RK-2.11 POWERPLANT PROPELLER APPLIANCE Tee Manaiaret 6. Conformity Statement A. Agency's Mane and Address B. KM of Agency Mao WOW, MAYEN U. S. Garaged Mechanic rasnasons, Ado.. 300110•00.1000 Foreign canelcated Mechanic _j C. Certificate No. oar CUEVEI/J0 Ss OH Centres:4 now Stinson CRS# WC7R346J 2* 411411 ow" WNW STATES Z C•finteled Mantionanca Oryanizaton II I codify Met the repair andlet eleretton made to In unigs have been made h =men* with the requirements of furnished Meath tme and eared le the ow et my ko0.04.106. bandied In MITI 5 above and described on the reverse or SttlidifTWES hereto Pad 43 of the U.S. Federal Aviation Regttatkas and that Vie Information ended range bal Ext per 14 PROT94 Pad 43 App. B K Slonare/DetedAul . r #4, Ryan M Landes 10/7/2019 7. proval for Return to Service Pursuant to the authority gNen person speeded below, the wit Wenrtil Adrfilitistr atOr of the Federal ANation Administration and Is j In hem 6 Approved knpected In the mane( presorted by the Relecied BY - FM Fe. Standards Inspector - Manufachrer - Maintenance Organization Palmas Apiroved by Calm oepartmeni or Tramped r ......., FM Designee 7 Repair Station Inspection Authorizalion (Spray) Cerlificat or Designation No. CRS# WC7R346J SIgnatur died IndMduai David Kerr 10/7/2019 FAA Form 337 (10/06) Page I SDNYGivi02754915 EFTA_00241837 PROT12 NOTICE iveighr end balance or operating Nmitafion changes she, be entered In the appropriate aircraft recent M Salon must bbl compatible with aff previous alterations to EISSUM continued conformity will the applicable airworthiness requIreinent*. O. Description of Work ACCOMPlithel pf move sate is Mend. attach 80010701 sheet Wen* hen arced a:steamily and registration met* and date nor* cempreted) UNITEDSTATES/NIWTS 1017/2019 Nalknalltyars3 Raglatelkat Mark Data 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 1dditional Sheets An Method FM Form 337 (10/06) Page 2 PROT61 EFTA 0024I838 PROT13 athee.s.tan efistries /Department efrrampottalint I;21,11cationflivithirtrathn Supplemental Type Cergficate Nailer. ST11216DS 7birenafrateivaedterBHE & Associates, Ltd. 12002 Warfield St. Suite 250 San Antonio, TX 78218 real per tbar at clap is the type juiptfintiefaffenag quad an' Me /inniations onaramennas dm:fitter specified Sena sear tie Onntuteineanrganratenis gifint25 itieFederal Aviation Regulations. Original Product - Tape Ct-rlilicate Numlict: Make: See attached AML Model: See attached AML See attached approved model list (AML) Description of 'Fyn Deakin Clamp:: Installation of automatic dependent surveillance-broadcast (ADS-B) out on Part 25 aircraft in accordance with Master Data List 584-00-0001, Revision IR, dated June 29. 2018 or later FAA approved revision. For Instructions for Continued Airworthiness and Airplane Flight Manual Supplement reference the attached AML Limitations and Conditions: I 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 pemaission 3. See attached AML for additional limitations and conditions. centfirate and's& supporting data guild is tie earn forappanniderrosoin in Oa unistsurmakrel, suspended snimiafroror a termination fate 4.r allientire andlisitify tendril-mi./Snuffing/tie falinnOnntion indinnairat iota Date of Application: February 9. 2018 Daic or lase:mem Junc 24. 2018 Dam kcissucd: Dow Am-acted: illy /Dina ion tit fidunnistrotar Seraame lit4 VT ORB Aviation Project ODA Administrator ODA-831473-SW My alwaecn of this certecate is eyeshade by a an al nal mewing 51.000. a Iftnicemaril not exceeding 3 yen a torn Pas cormcze may be transfeed or made evadable to third persons by brewing agreements er acepowee with IC PROT95 2147. Possession ulna Supplemental Type Ceder-roe (STC) OeCofrenl by persons order than the STC holier does net cortabbste rights to the design data nor to altar an small aroatl signs. of propeller The STC, supporting documented:a (dramoos. Aetna:We speokatons. figM manual supplements. etc) is the property of nit SIC homer An STC holier who least • person buying STC war an arrcraft awes ,none. ce propener must prove that pe so yam tynnen purression accepts* to the FAA. IRS 14 PROT96 21.120). FAA Form 5110-2 (914) Page 1 o12 PROT62 EFTA_00241839 PROT14 thuitiatatts °amnia apartment 17fransportathn FeafrativiattS/larministration Supplemental 7)Te Cent/lc-ate INSTRUCTIONS The transfer endonernent below may be toed to notify dw appropnne FAA Aixereft Certifieatial Office ache [mien of this Supplernmul Type Cartgkate. The MA will reissue the certificate m the nose of the transfereeand leeward 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): eau itraalit *mama Irina: My alleradon e this conthstia 4 punishable by a Me Of flat exceeding 51.000. of Imprisonment not escaertrg 3 yaws. a bath this certificate may be Rfingerred de made AMAMI 30 two Mein by Witernents In accordance with Id CPR 2147. Possession of this Supplemental Type CeMcra (STC) Saturnine by persons at than the STC hart& does not con:A/luta rights 10 the design data nor to stem an stvel, Srget engine. or propeller. The STCh supeoceng eleceneetehen (dnawrtos, ireeeeekee. weeneelehe fight manual supthements, etc) is the property of the STC toblet. M SIC maw wow stows a person lo use the STC b alter an aitheft. shalt engine, a propeller must prova Mt person with erten Permission acceptable to the FM (Ref. II PROT97 21.1201. FAA Form 8110.2(5114) Paget Of 2 SDNY_GM_O2754918 EFTA_00241840 PROT15 DocuSign Envelope a CFB621313.543FE8-4C8D.A4E34461F9B213045 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 Pero By VT-DRB. FSCM 47MZ7, Snt 1 o139. 2019fMatf19 PROT63 EFTA 00241841 PROT16 DocuSgn Envetope CFS82885-6FES4C8D-A4E3-5461F9820045 NOTICES AND SIGNATURES Notices: Note: Paragraphs andror figure numbers followed by' i" indicate a change by latest revision. Approval Signatures: NAME SIGNATURE Prepared by: R. Zamora See rev IR Checked by: M. Graham See rev IR Approved by: M. Graham See rev IR REPORT No. 584-00-0047, Rev: D Page 2 of 36 Red By VT.DRB. FSCM 471127. Sit 2 01 39, 201944.1a/f19 PROT64 EFTA 00241842 PROT17 DocuSign Envelope ID: CFI36211185-6FE8-4C8D-A4E3-5461F9820045 Record of Revisions Revision Number Description of change - . .s. - RevislOn . Date Approved IR Innis] Release 5/9/18 MG A Page 8, Section 1.1 revised transponder and GPS part numbers. Page 10, Section 2 remove 'Flight Hours' horn Table 4 6727/18 MG 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. 11/6118 MG 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 MG D Added STC number on page 4. Added figure on page 24. Revised form form in Appendix C. 3(14lict SHE & Associates, ltd. Page 3 of 36 Red By VT.DREI. FSCM 47M27. Sht 3 of 39. 2019/Mar/19 PROT65 EFTA 00241843 PROT18 DowSign Envelope ID: CF862885-6FE8-4080-a4E3-5481F9620045 INTRODUCTION These Instructions for Continued Airworthiness (ICA) document have been developed using the guidelines in Appendix 'if of 14 PROT98 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-600.2816 (Challengers) Gulfstream Aerospace -1125 Westwind Astra. Astra SPX. Gulfstream 100, 0150 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, 5550, 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 800B, Hawker 800XP. Hawker 750, Hawker 850XP. Hawker 900XP Learjet - 60 (STC Aircraft) Dassault Aviation - Falcon 10, Mystere-Falcon 50, Mystere-Falcon 20-05/D5/E5/F5, Mystere-Falcon 200. Mystere-Falcon 900 Table 1: Equipment Type Description New CPN I 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-40005 GPS Receiver 822-2189- 004/005/006/007/010/011/100 0, 1 or 2 *Either TDR-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: BHE 8 Associates, Ltd. Page 4 of 36 Rye By VT-DRB. FSCM 476.127, SIB 4 a/ 39, 2019/MarD9 PROT66 EFTA 00241841 PROT19 DocuSign Envelope ID: CFS62885SFE8-4C8O-A4E3-5461F9B2D045 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-ORB Aviation Consultants 9800 John Saunders Rd San Antonio, Texas 78216 STC Holder BHE & Associates Ltd. 12002 Warfield Suite 250 San Antonio, Texas 78216 Page 5 of 36 Rah By VT-DRS. FSC51 47127. Sht 5 of 39. 2019fhtall 9 PROT67 EFTA 00241845 PROT20 Dzoof$Ign Envelope ID: CFB628B5-6FE8-4080•A4E3-5461F992D045 TABLE OF CONTENTS INTRODUCTION 4 RECORD OF REVISIONS 5 1 SYSTEM DESCRIPTION 8 1.1 GENERAL 8 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: 0 Page 6 of 36 fiord By VT-OR13, FSCM 47M27, SIM 6 of 39, 2019/Mar/IS PROT68 EFTA 00241846 PROT21 DoteSign Envelope ID: CR3628115,6FE8-4C8ETME3.5461F9432O04S 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 BHE 8. Associates, Ltd. Page 7 of 36 Red By VT-ORB, FSCM 47MI7. Sht 7 of 39. 2019thlar/19 PROT69 EFTA_0024 I 847 PROT22 DozeSon Envelope ID: CF8132885-6FE8-4C80-A4E3-503IFOBADO4S 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-40005 GPS receiver. Depending on the aircraft configuration, the GP$-4000/A/S may be previously installed. If the previously installed GPS- 4000/NS is not a part number 822-2189-004/005/006/007/010/011/100 it will have to be upgraded to one of these part numbers. (Reference Tables shown on drawing 584-00-0004 for applicable GPS installation based on aircraft model) Wiring is added dependent on the installed or replaced GPS receiver(s). Transponder(s), and annunciator installed. (Reference Tables shown on drawing 584.00.0004 for applicable installations based on aircraft model and subsequent Wire Routing drawing 584-00-0005).See section 6.1.9 for details on inspection. An optional ADS-B Out annunciator can be installed to alert the pilot that the ADS-B function of the active transponder is not properly functioning. The ADS-B Out annunciator is required for all standalone GPS installations. Standalone means the GPS only provides data to the transponders. All 1203C installations and 4000S installations that only connect to the transponders are standalone. It can be installed as an option for installations where the 4000S is used for both ADS-B and FMS navigation. ((Reference Tables shown on drawing 584-00.0004 for applicable ADS-B Out Annunciator installation based on aircraft model) Table 2 E ui ment List Type Description New CPN Qty DO-260B ADS-B Out TDR-94 Transponder 622-9352-502 0, 1 or 2* TDR-94D Transponder 622.9210.502 0, 1 or 2* GPSI203C GPS Receiver 84327-50-XXXX 0 or 1 CI 429.200 GPS Antenna CI 429.200 0 or 1 GPS-40005 GPS Receiver 822.2189- 004/005/006/007/010/011/100 0, 1 or 2 *Either TDR-94 or TDR-94D will be installed. REPORT No. 584-00-0047. Rev: D BHE 8 Associates. Ltd. Page 8 of 36 Rom By VT-ORB. FSCM 47MZ7, SN 8 of 39. 2019N.1419 PROT70 EFTA 00241848 PROT23 ()cooSign Envelope ID: CF/352885-6FE84C80-A4E3-9461F9820045 Table 3 below lists the equipment being installed by aircraft. The aircraft will leave with updated TOR- 94$ or 94Ds depending on the what transponder was already existing. Table 3 E ul ment by Aircraft Aircraft Transponder Installed/Retained/Replaced. GPS Installed/Replaced Antenna Installed Learjet 60 TDR-94s or 94Ds GPS-1203C or GPS- 40005 CI 429-200 Gulfstream Aerospace 1125 Westwind Astra, Astra SPX, Gulfstream 100, G150 TOR-94s or 94Ds GPS-4000S N/A Gulfstream G-1159, G-11598, G-IV, GV TOR-94s or 9413s GPS-1203C or GPS- 40005 CI 429.200 Gulfstream G-11594 GPS-4000S N/A Gulfstream 200 GPS-40005 N/A Textron Aviation 500 GPS- 1203C or GPS- 40005 CI 429-200 Textron Aviation 550, 5550, 560 GPS-1203C or GI'S- 40005 CI 429.200 Textron Aviation 400 GPS-1203C or CPS- 4000S CI 429-200 Textron Aviation 400A GPS-4000S N/A Textron Aviation 650 GPS-1203C or GPS- 4000S CI 429-200 Bombardier CL-600- 1411 CL-600-2Al2, CL- 600.2816 CPS-1203C or CPS- 40005 CI 429.200 Sabreliner NA-265- 65, NA-265-70, NA-265- 80 GPS-4000S N/A Textron Aviation HS.125 700A, BAe.125 800A/800B, Hawker 800XP GPS-1203C or GPS- 40005 CI 429-200 Textron Aviation HS.125 7008, Hawker 750/850XP/900XP GPS-40005 N/A Dassault Aviation Falcon 10, Mystere- Falcon 50, Mystere- Falcon 20- C5/D5/E5/F5, Mystere-Falcon 200, Mystere-Falcon 900 TOR-94s or 94DS GPS-40005 N/A Page 9 of 36 Red By VT.DRB. FSCP..1 44127. Slit 9 of 39. 2019rtcladi9 PROT71 EFTA 00241849 PROT24 DoomSign Enveleft ID: CFB628B5-6FE8-4C8D-ME3-5461F9620005 2 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under 14 PROT99 H43.16 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 4 Ins ion 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. Page 10 of 36 Rerd By Vf -ORB. FSCM 47MV. Sol 10 of 39: 2019/Marf19 PROT72 EFTA_0024 I 850 PROT25 I 58 I ti00-V.L.43 cr) C co H H n -O O n H H 3D C 3D -O 3D 3D -O Vf • 1 OD LD I - cn P 2lc) co -4 CD - L'S I_a r - 1000O3 I ,41.3 DocuSign Envelope ID: CFB628135-6FEB-4C8D-A4E3-5461F9820045 BOMBARDIER INC. CL-600-1A11 (CL-600), -2Al2 (CL-601), -2B16 (CL-601-3A VARIANT, CL-601-3R VARIANT, CL-604 VARIANT) ACC DOABLE LOCATION TS CS OM USW 0t 47115 SAO 5300 55 rs mm no O MO r'S na rs 29100 I 1":* IS r'S a AS AS 4513▪ 0 T REPORT No. 584.00.0047, Rev: D SHE & Associates, Ltd. Page 11 01 36 Reid By VT-ORB. FSCM 471427, Shill al 39. 2019;161mM PROT26 c581 ti:00-V.Ld3 cn C co H H ITI -o 3D H H 3D C 3D-O 3D G.) -O 0 LO cn P 'O im O su -4 g DowSion Envelope ID: CF862885-6FE8-4030-41E3-548iF9821)045 20.20 TEXTRON AVIATION 400 ACCEPTABLE LOCA11ON IS FS 172.24 196.41 FS [repeated 7 times] 124.61 141 14 71.65 FS 203.35 221.46 240.75 26404 FS [repeated 3 times] 11734 13747 1503.20 266.1 18 S 4 212.40 231. FS 42 250.39 269.69 Ft I FS PRESS WOO I F L js is I 80.91 I 99.02 FS FS 88 96 106.07 :0: 0 hrt , litu REPORT No. 584.00.0047, Rev: D Page 12 of 36 Red By VT-DRB. FSCM 4714Z7, SIR 12 o139. 2019/Man19 PROT27 V) DocuSign Envelope ID: CFB62885-SFE8-9C8D-A4E3-5461F9B2D045 C £ SS I PZOCV.L43 O3 t. O 73 0 0 70 73 V) SO lO N p ,G) U E Ca ) O.; lea TEXT -PON AVIATION INC. 550, S550, 560 ACCEPTABLE LOCATION FS 59.00 FS FS 151.00 179.02 Fs F5 FS Fs 134.00 165.00 94.00 FWD 117.00 PRESS I BLKHD r _I 1 FS 225.23 23 (560) FS 223.40 , id? , FS 216.10 (560 ONLY) Page 13 of 36 Redd By VT-ORB, FSCM 47PAZ7, Ste 13 01 39, 2019/Mar/19 PROT28 V't DaceSoon Envelope ID: CF8628854FE/54C8D-A4E3-5461F902D045 C tgi? I ti00-V1-13 co n H ITl -0 0 0 C ITl po -0 po -0 : 3/4400 .93 cn P :4 0_ it, FS 58.00 TEXTRON AVIATION INC. 650 FS 94.00 PRESS 8VHD FS FS 172.00 202.00 FS FS 157.00 187.00 FS FS 261.00 288.76 I FS 00 272.00 I i C: 1 0 1 I I i M l ill I ha SHE 8 Associates. Ltd. Page 14 of 36 Red By VT-DRB, FSCM 47M27, Snt 14 of 39. 2019/Mer/19 PROT29 558 I ti:00-V.L.43 C rn H H -o 0 H nr" H rn 0 0 rn 70 -o 7s G) ,z) -o 1) cn P 2 ,G) co cp_ I_a DocuSign Envelope ID: CFB6288543FE8AC8D-A4E3-5461F9B20045 TEXTRON AVIATION HS.125 SERIES 700A, BAe.125 SERIES 800A & 800B, HAWKER 800XP 67.0 1800 2043 224 • ra MA •I0 11; I Ur 241 Sn • 2822 FICIA ;II ET- (71 1.10 10I0I I I i 1) - 1 I irl n I1 14 n 101.0 two own simony O i l I I I rT 6 - r - - 1 - - _Cr BHE & Acanriates, Ltd. Page 15 of 36 Reid By VT-ORB. FSCM 47MZ7. Sht 15 of 39. 2019/Mar/19 PROT30 cn C co rn H H n -o 7o 0 H rn n H rn 0 31 ci rn 73 -o 73 -o to Co L0 Cn P IC) O CU 958 1 ti00-V.Ld3 33491 DocuSign Envelope ID: CF862885-6FE8-4C8D-A4E3-5461F982OO45 LEARJ ET 60 110.99 17 124.39 151.19 17549 20 .79 232.1 2 274.51 302.59 323.5 r3.3 9 305.11 137.79 FIO r 2 99 F144 Fl p.59I209 F-21 I ;23 90 .57 r• F. 144.59 till 1210.19 197.59 F1S 2 r19 246.59 T3INS1 341143 F204 1 r23 rt4 20.39 riI REPORT No. 584-00.0047, Rev: D Page 16 of 36 Reed By VT-ORB. FSCM 47M27. Sol 16 of 39. 2019iMart19 PROT31 L 58 I ti:00-V1.43 cr) C co n H H ITl 0 H n 0 3D -o 6) -o Vf CO 1n oz lc) SD -4 ca CD_ ,.(f, I_a FRCSs FS FS 145.0 .0 193.0 133.0 rs 1:10 DowSign Envelope ID: CFB62885-6FE8-403D-A4E3-5461F9B2D045 GULFSTREAM G-1159, G-1 159B, G-IV Fs 63.0 BU010 L - P\ - I I I I t _ _ _LS 1 I REPORT No. 584.00-0047. Rev: D BHE 8. Associates. Ltd. Page 17 of 36 Ftefd By \MORD FSCM 47MZ7, Shl 17 of 39, 2019IMart19 PROT32 cn C co H H -to 3D n H IT IT 3D C IT 3D -0 3D -0 Ln 2 3 : D cn oz O co NNAy 858I ti:00-V.Ld3 DocuSion Enveboe ID: CFB62885-6FE8-4C8D-A4E3-5481F9132D045 GULFSTREAM GV FS [repeated 4 times] 157.. S 181.0 205.0 229.0 FS 145.0 1.3.1 I 193.0 217I.0 241.0 FS I FS I FS I FS 63.0 FWD 8U1HO - -Jill T1 n PRESS I 1 I 1 [repeated 5 times] 11 1 1 11 i a .• a =II 1 r- ie a 1 l 'P.41 I I i 100 - a_ 1 II I I. i i i i 1 I i (:( I [repeated 4 times] I I I I I II II - I--i - 1 _i_ p_ _p_ i i I [repeated 5 times] BHE 8 Associates. Ltd. Page 18 of 36 Reid By 1/7-DRB, FSCM 41M17, SIR 18 of 39.201911Am/19 PROT33 6 g2 I VZOCVJ.d3 (r) C co n H rT -0 0 n H rT H 73 ;a -o 73 Gl 73 -0 I O I-' IE E a E.: DoctiSign Envelops I0: CFB628B5GFE8-4C8D-A4E.95461F9B2D045 r " ri- --- - : T -"- -- I, I II I I I. I I i I ll II / (gggli Ott OO III ( ( OOO t I i -ID,- -144- I Itl--=:-- 1 ii n I III I 1 \''\ II III I III II /: N I I I I I I I I i I li N I II i ii \t i l! III I I I I I 117 1 I I I V H[L LOOKING AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD (TEXTRON AVIATION 400) BRE & Associates, Ltd. Page 19 o136 Reif By VT-DRB, FSCM 471.427, Sht 19 of 39. 20i9ThAv/I9 PROT34 V) DowSipn Envelope ID: CFB628B5-6FE8-4C8D-A4E3-5461F9E2D045 C Co .93 to LOOKING AFT AT FWD SIDE OF FORWARD PRESSURE BULKHEAD ZCI (TEXTRON AVIATION INC. 500, 550, S550, 560) O 0 1,1 I-4 IJ 00 O Page 20 of 36 Raid By VT-DREI, FSCM 47MZ7, SM 20 of 39, 2019/Marit9 PROT35 I9SIKOCV.L.43 in C L1.0:1 0 73 0 73 70 70 DD ,93 O 2 0.1 CL it GocuSIgn Envelope ID. CFB62885-6FE8-4C8D-A4E3-5461F9B20045 CAL1191tOOE WAD* , ay.; , .-r4 .17ir ,t, tit tel l ti: tS -it tj.t 41_ rir si ti I • • rh I Tteirh rfi 4. 4 LI 0 oi pp I: 0 j j gMET:EfiftlEF ! I I ' I I I I I le l : I It 4 11\ I I:1 II ;T+4 I: rh 1 44 fprim. -*-174-ditrati- +. 4 41 +. ifolCatshig{q- I I III I I I I 2: -1-r= - 0 '....thrietiz r-fit ii-711 i+ E-- I I I I LOOKIC SIT AT FOB SEC OF TOIFORD NOM MOEN (LEARJET 60) REPORT No. 584.00.0047, Rev: D Page 21 of 36 Rohl By VT-DRB, FSCM 47MV. Sht 21 o139, 2019A1ail19 PROT36 DocuSIgn Enveope ID. CFB628B5-6FEB-4C8D-A4E3-5461F962D045 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. Page 22 of 36 Red By VT-ORB. FSCM 47MZ7.Sht 22 of 39.201917.18:119 PROT73 EFTA 00241862 PROT37 DocuSIgn Envelope ID: CFB8288543FES4C80.04E3•5461F9B20045 LNSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS typical InstaIlation,shtnvg kspcctions applicable to all PadttatilWiiiitailkiiciai: Ni• "19,4 pcction NefirdSi Eint lldthiS2t11 411Vtigta l l j cry of installation LiNs. tra alit SHE & Associates. Ltd. Page 23 of 36 Red By VTCRB, FSCM 47M27, Shl 23 of 39. 2019/M91119 SDNYGtv1_02754941 EFTA_00241863 PROT38 (locoSago Envelope ID: CF862885-43FE8-4C6D-A4E3-5461F91320045 INSPECTION AREA & METHOD FWD BULKHEAD PENETRATIONS BHE 8 Associates. Ltd. Page 24 of 36 Reid By VT.DRB. FSCPA 47MZ7. $01 24 o139. 20194Am/19 PROT74 EFTA 00241864 PROT39 DocuSign Envelope III CF13628B5-6FE8-4CBD-A4E3-5461F9432D045 INSPECTION AREA & METHOD GPS Antenna Typical Installation sbown"Inspections are applicable to all antenna installations REPORT No. 584-00-0047, Rev: 0 Page 25 of 36 ReRI By VT-ORB. FSCM 47M27. SM 25 of 39. 2019iMarti 9 PROT75 EFTA 00241865 PROT40 DocuSogn Envelope ID: CFI362895-6PE8-4C6D-ME3-5461F9620045 INSPECTION AREA & METHOD GPS ANTENNA Typical InstallatiOnshOlit; Inspections arc applicable to all. antenna installations 1111544 ,ta, "fa Learthiz..4 al. i.ioziqnrr.-:z BHE 8 Aqsartates, Ltd. Page 26 of 36 Red By VT-DRB, FSCM 47M/7. She 26 of 39. 20150.ierng PROT76 EFTA_00241866 PROT41 FInfogign Envelope ID: CFB62/995-6903-4C8D-A4E3-546199820045 INSPECTION AREA & METHOD GPS ANTENNA Typical. Installation shown. 100;eetions are 4P01FOle !P. 01 WAAPP1Ps101019FIL ifFcz4R#tioxi:Aita,,o-ilmer tit 93-7.!,....E94..._ . Nif ts. rotr., T -9,:'' 'z realel_.. 4 I ..9.4-# -3.143_. Pat atijt lin g tet0 3 F RICWS4 W i Paa t4 CRIW4 S A4 T J ' 4 4 arcnlnd kmia tle.il. .. 4-41 4 1.4L,4,1" ajcyjnia*FipeirIdt, ygSyt ,t<ti . z...4_,.. Tellie, .1:.! - - zPrr .rpil*:;-: - ..As= a'l. Page 27 of 36 Reid By VT-DRB, FSCM 479427. SN 27 of 39. 20191.4aill9 PROT77 EFTA 00241867 PROT42 DowSIgn Envelops ID: CF1352193.543FES-4C80-A4E3-546 I F9B2D045 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) 650 Model 650 Non-Destructive Testing Manual 65ND (Part 6, Chapter 20) Textron (Beechjet) 400, 400A Model 400/400N400XP Maintenance Manual 128-590001-9C29 (Chapter 20-80-03) Textron (Beechcraft) HS.125 700A. Bae.125 800A. Bae.125 8008, Hawker 800XP 125 Series 1-800, Hawker 750, 800, 800XP, 850XP. and 900XP Non-Destructive Testing Manual N/A (General Techniques - Part B) Challengers Structural Repair Manual N/A (Chapter 51) Gulfstream G-1159, 6-11598,6- IV, GV Structural Repair Manual N/A (Chapter 51) Oscars' 91, FAA APPROVED: 405,106FIC36743,- Danyl Seow, Project ODA Administrator VT DRB Aviation Consultants A Division of VT San Antonio Aerospace, Inc. 9800 John Saunders Rd, San Antonio, TX 78216 Date 3/21/2019 Vant SW" I Page 28 of 36 ROM By VT.C4iS FSCM 47127. SM 28 of 39. 2019/MaTh9 PROT78 EFTA_00241868 PROT43 DowSign Envelope ID: CF9628BS6FE8-4C8D-ME3-9461F9132D045 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 (-5XX), document 523-0821492, Installation Section 3.2 Access Location Refer to the Aircraft Maintenance Manuals listed in table 9 (or 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. 6150 Nose Nose Gulfstream 200 Nose Nose Gulfstream G-1159, G- 1159A, G-11598, 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 Page 29 of 36 Reid By VT-DRS. FSCIA 471.427. Sht 29 of 39. 2019Staf/19 PROT79 EFTA 00241869 PROT44 DecoSign Envelope ID: CFB628435-6FE8-4C8D-A4E3-5461F9820045 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-600-2816 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/7006, BAe.125 , 800A/800B, Hawker 750/800XP/850XP/900XP 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 • Max Load in Amps 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 Page 30 of 36 Read By VT-DRB, FSCM 47M27, Set 30 o139. 2019!Mar/19 PROT80 EFTA 00241570 PROT45 DocuSgn Envelope ID: CF862885-6FE8-4C80-A4 E3-546 I F9B2D045 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-94194D ATCIMode-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 Page 31 of 36 Reid By VT-DREI, FSCIA 47W7. Shl 31 of 39. 2019iMat/19 PROT81 EFTA_00241 I PROT46 DocuSign Envelope ID: CFB62885-6FE8-4C80-A4E3-5461F9920045 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 FAYING SURFACES EYE ABOVE REFLECTED LIGHT BEAM REFLECTED LIGHT BEAM CRACK OPEN TO SURFACE Figure 6 - inspection for Cracks 6.1.8 Verification of cracks A 10x magnifying glass may be used to confirm the existence or extent of a suspected crack. Page 32 of 36 Rord By VT.098. FSCM 47MZ7. SM 32 of 39. 2019/Maff 19 PROT82 EFTA 00241872 PROT47 DocuSign Envelope ID: CFB628B5-6FES4O9O.AcES5461F962O045 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 Learjet 60 60 P/N MM-103 Bombardier Inc CL-600- 1A11 CL-600-1A11 PSP 601-2 Bombardier Inc CL- 6002Al2, CL-6002B16 CL-600-2B12, CL-600- 2816 CL 604 AMM Dassault Aviation Falcon 10 Falcon 10 Dassault Falcon 10 Dassault Aviation Mystere-Falcon 20- C5/D5/E5/F5, Mystere Falcon 200 Mystere Falcon 20- C5/D5/E5/F5 Dassault Fan Jet Falcon Dassault Aviation Mystere-Falcon 50 Mystere Falcon 50 Dassault Falcon 50/50EX Dassault Aviation Mystere-Falcon 900 Mystere Falcon 900 Dassault Falcon 900 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- 1159B G-1159, G-1159B Gulfstream II Gulfstream G-1159A G-1159A Gulfstream Ill Gulfstream G-IV G-IV Gulfstream IV Aircraft Gulfstream GV GV Gulfstream V Aircraft 500/550/S550 500/550/S550 Model 500 Maintenance Manual Page 33 of 36 Res By VT-ORB. FSCAI 47M27. Sht 33 of 39. 2019/Mar/I9 PROT83 EFTA_0024 I 873 PROT48 DowSkr Envelope ID: CFB62841.543FEB-4C80-ME3-5461F96213045 560 560 Model 560 Maintenance Manual 650 650 Model 650 Maintenance Manual Textron (Beechjet) 400, 400A 400/400A P/N 128-590001-9C HS.125 700A, 700B 700A, 700B AFMS-125-700 BAe 125 800A. 8008 800A. 800B AFMS-800 750 750 AFMS-800XP 800XP 800XP AFMS-800XP 850XP 850XP AFMS-800XP 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 nspection" 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. Any discrepancies found should be repaired. a. WireNVire 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. Page 34 of 36 Red By VT-DRB. FSCM 47IAZ7. Shl 34 of 39. 2019:Mar/19 PROT84 EFTA 00241x74 PROT49