0 BY MAJOR REPAIR AND ALTERATION us Osean- ent or Tremont /fen (Airframe, Powerplant, Propeller, or Appliance) Newel Mitten AdenInlotretien OMB tee memo EV: W31/20.4 ElecircricTrecknehatet fl or FAA Usi Only INSTRUCTIONS: Print or type ail entries. See Title 14 CFR §43.9, Part 43 Appendix B, and AC 419.1 (or subsequent revision thereof) for instructions and disposition c4 this form. This won Is rethireid by Law (49 U.S.C. §44701). Failure to repot can ankh in a civil penalty for each such violation. (49 U.S.C. §48301(a)) 1. Aircraft Nationality and Registration Mark N908JE Senaf No. 20115 Make BOEING ode 727-31 eves 2. Owrer Name (As shown on registration certificate) JEGE INC Address (As shown on registration certificate) Arklent )02 FOULS HO ST E 202 Cry VetAfiNGTON Stew OE ip 11003.3742 Ceu try SA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial No. O lil AIRFRAME (As described in Item I above) 0 O POWERPLANT O O PROPELLER O APPLIANCE Two Manufacturer S ConfomiltyStetement A. Agencys Name and Address B. Kind Of Agency tams Bergen Ak ServkeASok•OMplen U. S. densidned wawa I Manufacturer Ads.“ SS Or I ma vein Foreman Commend mechanic C. Certificate No. Cry ft isethedels ore' FL x Cortietled Seater Stow SD4R514M Po 'POO Corr/ USA CSISCeleeMeireenteCeorperrat0IN D. I certify that the repair ancVor alteration made to the unit(s) identified in Om 5 above and described on the reverse or attachments hereto have been made In accordance vMh the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information famished herein is true and correct to the best 01 my knowledge. blended range fuel ow 14 CFR Part 43 O APP. 0 S Date of Authorized Incividual . /.....• ../ 4 :// David K. Crosby 15 JAN 2016 ov I for m to Service Pursuant to the authority g yen persons specified below, the u ' retied in rem 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration end is XIApproved I—Rejected BY FAA Fri Standards Inspector Manufacturer Maintenance Organization Pawns Approved by Canadian Depannuthr or Transport FM Designee X Repair Station Inspection Authorization 0010r (Speedy) Minato or Designation No. SD4R514M 7 4-iitu ate of Authorized Individual i / 92 a . 1 David K. Crosby 15 JAN 2016 FAA Form 337 (10/06) SDNY_GM_02759647 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246569 EFTA01331032

NOTICE Weight and balance or operating hmitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible AIM all previous alterations to assure continued conformity with the applicable airworthiness requirements. II Description of Work Accomplished fa more space is muffed. attach &rational sheets. Identity with aircraft nationaAty 811:1reptstration mark end date work competed) The following work was accomplished on Work Order 82484. N908JE 15 JAN 2016 Nationality and Registalion Mark Date INSTALLED: Aviation Communication & Surveillance Systems (ACSS) STC Number ST02406LA, entitled 'Installation of TCAS version 7.1 In accordance with FAA approved AML No. ST02406LA. dated February 06, 2012, or later FAA approved revision.' The following Aviation Communication & Surveillance Systems (ACSS) Traffic Collision Avoidance System (TCAS II) equipment andlor components were removed for modification: 1. RT-910 TCAS II Computer Unit (Change 7.0) PIN 4066010-913 The following Aviation Communication & Surveillance Systems (ACSS) Traffic Collision Avoidance System (TCAS II) equipment and/or components were installed after factory modification: 1. RT-910 TCAS II Computer Unit (Change 7.1) P/N 4066010.914 The above modified equipment and/or components was installed in accordance with ACSS TCAS II/2000 Change 7.1 AML STC Master Data List, Document No. 8900067-002 Revision E dated August 07, 2013 (FAA accepted on September 9, 2013 Los Angeles ACO) or later FAA approved revision, as listed on the FAA Approved Model List (AML), Document No. ST02406LA, dated September 25. 2013 or later approved revisions, and the ACSS Traffic Alert and Collision Avoidance System, System Description and Installation Manual, Pub. No. C15-3841.005, (ATA No. 34-43-00). Revision 004 dated 15 Oct 2013, Including Temporary Revision No. 8 dated 15 Jun 2011 or later appropriate revisions. The required FAA approved Airplane Flight Manual Supplement (AFMS), Spec. No.: 8008565-001. Rev. IR dated August 9, 2012 or later FAA approved revision has been inserted into the Airplane Flight Manual. The aircraft Weight & Balance change negligible and Equipment List amended. The electrical load was computed and found not to exceed 80% of the system output. Log book entry made. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (ICA) 14 CFR 425.1529 The Instructions for Continued Airworthiness are contained within the ACSS TCAS II/2000 Change 7.1 AML STC Instructions for Continued Airworthiness, Document Number 8008572-001 Revision B dated 18 April 2013 or later FAA accepted revision. END A00it cred Sheets Ate Atteehial FAA Form 337(10/06) SDNY_GM_02759848 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246570 EFTA01331033

-r BANYAN Federal Aviation Administration Aircraft Registration Branch AFS-750 PO Box 25504 Oklahoma City, OK 73125 Ann: Record Keeping Date: January 15, 2016 Subject: ,ubmIttal of FAA Form 337 for N311AG Boelna 727-31. SM 20115 for the installation of the AC S TCAS II Chance 7.1 IAW ACSS STC ST02460LA Enclosures: 1. Original FAA Form 337 for the Installation of ACSS STC No. ST02406LA. dated 15 JAN 2016. The above listed enclosures are being submitted as per 14 CFR 43, Appendix B paragraph (a)(3). Please contact myself with any questions or concerns. Banyan Air Service Fort Lauderdale Executive Airport • 5360 NW 20" Terrace • Ft. Lauderdale FL 33309 www.banyanair.com SDNY_GM_02759649 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024657I EFTA01331034

. . . • SDNY_GM_02759650 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246572 EFTA01331035

0 MAJOR REPAIR AND ALTERATION LIS Dopeerent . al !romantic., (Airframe, Poworplant, Propeller, or Appliance) Foilsniknoesa AAISSetteeen O M O 1.1 2 1 M 0,20 Douro* Troclong tivatw En: &'3t11014 l 0 saw OW INSTRUCTIONS: Pita or type at entries. See Title 14 CFR §43.9. Pad 43 Appen B. and AC 43.9-1 (or subsequent revision thereof) for insvuctions and disposition of this form. This report is required by law (49 U.S.C. $44701). Rause to report can result in a civil penalty for each such violation. (49 U.S.C. §46301(a)) 1. Aircraft Nationality and Registration Mark N908JE Serial No. 20115 Make BOEING Model 727-31 Series 2. Owner Name (As shown on registration coreficete) JEGE INC Address (As shown on registration certificate) maw iC0 Mout ROAD SUITE 202 CO, WILIMeTION 5.01• CE Zro 1010S.3712 Cava, U.ASTED STATES .. .. _ 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteraton Lint Make Model Senal No. El 0 AIRFRAME (As described in gem 1 above) El In POWERPLANT El O PROPELLER O D APPLIANCE Twee renureckcer 6. Conformity Statement AL Agency's Name and Address B. Kind ol Agency Nam BOCA AJRCRAFT PANNTENANCE LLC x U S. carlificaled Mechem I Mandecluter km.. sesAmicaT Yew.* I Foreign Cenfteled PiethenC C. Certificate No. Cer BOCA PATON Wee Ft Cenficated Rope., Saloon, A&P 2884154 re 31131 cc..„, wart° SMITS CertiScated Maintenance Orearrieben D. I certify triat the repair and/or alteration made to the unite idenblied in item 5 above and descnbeS on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my ItnoMedge. Extended range fuel per 14 CFR Part 43 O APP. 8 SignalureiDate honied Ike ma r /"/d) 7. Approval for Return to Service Pursuant to the wAhonly even persons specirted below, the unit identified In nem 5 was Inspected in the manner prescnbed by' the **nenestratorol the Federal Aviator, Administration arid Is nApproved illiejected BY FAA Fk. Standards Inspector Manufacturer Meinlonance Organization Per Aneovel by Caneden Deparenerd el Transport FAA Designee Repair Station X Inspecaon Authorization Other (Sneer)) Celli cote Or o. A&P/IA Designation N 3434119 win Aix.d incWidual 1/9/20/5- FAA Form 337 (10/06) Page I SDNY_Givl_02759651 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246573 EFTA01331036

NOTICE Weight and balance or operating limitation changes shell be entered in the appropriate sirens!? record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. S. Description of Week Accomplished of more space is required. attach additional shoots (dent h secret nationaiW and registration math and date ewe completed.) Milt2015 Nationality and Regolnition &lark Date REMOVED AVIATION COMMUNICATION AND SURVEILLANCE SYSTEMS (ACSS) TCAS SYSTEM PROCESSOR P/N 4066010-910 (S/N 91050384) AND ROUTED TO MANUFACTURER FOR INCORPORATION OF SERVICE BULLETIN 8008230-001, REVISION 02 (ATA SB 4066010-34-6036). REINSTALLED REPAIRED I MODIFIED TCAS PROCESSOR P/N 4066010.913 (SIN 91050384) AFTER INCORPORATION OF ACSS ATA SB 4066010-34-6036. PERFORMED OPERATIONAL TESTS WTTH NO NOTED DISCREPANCIES PER ACSS TCAS II SYSTEM DESCRIPTION AND INSTALLATION MANUAL (SDIM), ACSS PUB 0 CIS-3841-005 (ATA NO. 34-43-00). NO CREW OPERATIONAL PROCEDURES HAVE BEEN AFFECTED BY THIS SOFTWARE UPGRADE. MODIFICATION IS WITH REGARD TO PROCESSOR SOFTWARE ONLY AND THEREFORE: WEIGHT AND BALANCE IS NOT AFFECTED. ELECTRICAL LOAD IS NOT AFFECTED. CONTINUED AI WORTHINESS REQUIREMENTS ARE NOT AFFECTED. ALL WORK WAS PERFORMED AS PER FAA AD 2012.02-08. CAddltaUtiSh4)013 Are Attached FAA Form 337 (10/06) Page 2 SDNY_GM_02 759652 • SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246574 EFTA01331037

Mobile Repair Team • • • Boca0Aircraft NAAINTENJANJCE CRS# 380R5358 3300 Airport Road Hangar 2 Suite 121 Boca Raton. Florida. 33431 MOO . lirral tiber baKia43 ft /WWI** a - 3?CA &SC\ O ?Tc±-- 20i:C— werehistio o asks to oe PFIiirlifeil (--,D (ICs Ik-tcw I C- 7 C Cci\Air NE \ ete,,,t, Pe7Strirre Ars`rito ( VeTirilerff&) pi ee \I\ CA- N3 -N.... Cc, erO Tr, to S7 e erso sj A therized t rf c2 Ira ^spectionsand Appr ved or Reit f • 10 Service e 6rnp oyee @26117@italitcDr OCTIMillein J. C,S2 0rilik A •ri vi.‘ 0,,,.4 24 ,v• ,T., r) -z y S Le 5- V Authorization efrUtist Kousmg Adequate a imps and Equipment a Parts and Materials Available Technical Data Available Et' RSIA/OO.1 Copy AviaLabla Et- Destination: F.J6 Notes: Manager's / Lead's Signature Authorizing MRT Date. Form MRT 4/1/2011 SDNY_GM_02759653 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246575 EFTA01331038

• • • SDNYGM02759654 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246576 EFTA01331039

0 MAJOR REPAIR AND ALTERATION VS Deow's.sei of Ttetspalien (Airframe, Powerplant, Propeller, or Appliance) codonlAvisdea AdeSiatrulen romtApporWl OIM we z‘200:00 tirJOrSOF Enoric Treckna finest **flare 0* INSTRUCTIONS: Print or type as entries. See Title 14 CFR §43.9, Put 43 Amer* B. and AC 43.9.1 (or subsequent revision Owed) for inanabons and disposition of thi$ form This report is required by law (49 U.S.C. §44701). FaNure lo report can result in a civil penalty for each SuCh ViOlitiO . (49 U. S.C. 546301(e)) 1. Aircraft Nationality and Registration Mark N908JE Serial NO. 20115 make BOEING Model 727 Setts 31 2. Owner Name (As ShOWII on togivronon °Miyake) JEGE INC. AddreSS (As Shown on legtsinstiai cortMOAAM wow. 103 FOULK ROAD SUITE 202 tar WILMINGTON stew 0 to 19803-3742 Coat/ UNITEDSTATES 3. For FAA Use Only 4. Type S. Unit Identification Renew ARM Won Unil Make Model Serial No. Z O AIRFRAME (As dexROue on Item I above) O El POWERPLANT O O PROPELLER O O APPLIANCE rya Minufacturte 6. Conformity Statement A. Agency's Name and Address B. Kra al Agency woe FLIGHTSTAR AIRCRAFT SERVICES. 110. 06. coneested Necinent I Manutacturer Mises 8021FLIGHTLINE RD BLDG. 615 Fotiolati Girt kaki MOChark C. Certircate No. on JACKSONALE s FL i CertliCato0 nervier SIMON FOTR986N zy 32221 cater UNITED STATES CentkomaiminsenmotOrosnaMon 0. I certify trial the repair andfor alteration made to the WAS) have been made in accordance with the requirements of fuenished herein is 'rut and cared to the best of my knowledge. klenflflOO in item 5 above and deserted an the reverse or altativntelit here*, Part 43 al the U.S. Federal Alston Regulations and that the inforrnetlen Extended range fvel per 14 CFR Part 43 O App. B Sigr)ie Of Aulh5rnatO Individual t..., Act/. . - / PETER JACKSON 91482 MARCH 01, 2012 , e. , T. Approval for Return to Service Pursuant to Ow authority given persons specified beiow, the unit identified in item 5 was inspected in the manner pronatted by tie A0MiriSedlOf of Me Federal AvIEIPOO Administration and is gl Approved O Rejected BY FAA FR. 9landards Mamba Manufacturer Maintenance Organization Pence. APProved try Caliklen DepOrlfrent of Minivan FM Designee x Repair Station Inspection Authorization Other (Speofy) Onto:ale or Oesignation No. FOTR986N Si u ,tiol dAu honied Individual osa.4920 " PETER JACKSON 91482 MARCH 01. 2012 FAA Fun 337 uses) SDNY_GM_02759855 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246577 EFTA01331040

NOTICE Weight and balance or operating limitabon changes shah be entered in the appropriate aircraft record. An alteration must be compatible with at previous alterations to assure continued confomety with the applicable airworthiness requirements. S. Description of Work Accomplished (amore space is required. attach oddoonal sheets. Identify with aircraft national:I], and registration mark and date work comPieredl N908JE Stationary and Registration Mark W/O 21219 MARCH 01, 2012 Date 1. WR 25306: REPLACED RIGHT WING FRONT SPAR VERTICAL STIFFENER AT APPROX. W.S. 200 WITH PIN 65-16200-3M IAW BOEING 727 SRM 51-30-2 REV. 103. 2. N/R 25522: REPAIRED RIGHT HORIZONTAL STABILIZER REAR SPAR LOWER CHORD BETWEEN STAB. STA 56 TO 113, IAW COTNEY AEROSPACE DRAWING AL81.55.101 REV. IR. FAA FORM 8110-3 DATED FEBRUARY 03, 2012 ISSUED. MATERIAL USED: ANGLE; PM54-2304 7075-T6511, DIM. 4" X 55.75% ANGLE; AND10137-3001 7075-76511, DIM. 16.375" X 3.75', RADIUS BLOCK; 7075-T6, 0.125', DIM. 12.5' X 2'. 3. N/R 25523: REPLACED RIGHT HORIZONTAL STABILIZER VERTICAL STIFFENER ON AFT SPAR AT ELEV. STA 53.91 IAW BOEING DRAWING 65-16876. MATERIAL USED: EXTRUSION; BAC 1505-29222 707576511. 12.5' LONG. END K &Mb,* Meets Na Awned FAA Form 737 noes) SDNY_GM_02759656 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA (X1246578 EFTA01331041

0 MAJOR REPAIR AND ALTERATION US Ogionmel Farm Approwel OW No 21204020 1.2•20is 11 wt Paden; Mats oda. Us O.* at Three:ono, (Airframe, Powerplant, Propeller, or Appliance) net.ii Media Aciaanithatiee INSTRUCTIONS: Print or type all entries. See Trde 14 CFR 643.9, Part 43 Appendix 13, and AC 43 9-1 (or subsequent revision thereof) for instructions and disposition of this but This report is required by law (49 U.S.C. §44701). Faire to report can result in a ovil penalty for each such violation. (49 U.S.C. 448301(1)) 1. Aircraft Natiortady and Registration Man( USA N9C8JE Serial No. 20115 loam Boeing model 727 Series 31 2. Owner Name (As shown on regisuahon contain) JEGE INC Address (As sham on nesistration conical.) Amens 101 FOUI K an STF 2112 cry VVILhliNGTON sue DE_ 7. 19803-3742 coney ‘USA 3. Fa FAA Use Onty 4. Type S. Unit Identification Repair wierason Unit Make Model Sate No. • if AIRFRAME (As clescdbed M Rem/wow) O • POWERPLANT • • PROPELLER O O APPUANCE tyre lasnutaClurer it Conformity Statement A. Agency; Name aid Address El. Kind of Agency rem TIMM) u. S. Conf.:ow MeChenic I Manubicluart New 102 SE Academic Ave. Foreign Ceircaled meowno C. Certificate No. oil I eke City see Florida . / Cortriesise Reps, Station DU4R141M Class IV rr 32025 Owe, USA coneeter Mainianarek0Mtnawn D. Icor* Smith. repair anclior alteration made to the snit( ) identified in item S above and denoted 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 idonnation finished herein is true and correct to the best of my tnoweitge. Extended par 14 APP. range fat CFR Pan 43 • 8 Signs ate of A m671 A Gregory A. Christman - 28 FEB 09 7. Approval for Return to Service Pursuant Administrator to the authorey given persons below, the uNt Identified n dem 5 was inspected in the manner prescand by the of the Federal Adak., Administration and is 2 Approved O Rejected FM Fe Standards Inspector Manufacturer Maintenance Organization eenons Append by Deneefien Cepailement of Teensy:A BY FM Designee I Repair Inspection ArAlloriZatiOn Omer (SPIT*/ CerlifiCale Of Designation No DU4R141M Class n/ Sign I Anthony V. Baroni - 28 FEB 09 FAA Form 337 nom> SDNY_GM_02 759857 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246579 EFTA01331042

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft retold. An alteration must be compatible with all previous excretions to assure continued conformity with the applicable airworthiness requirements. 8. Descdpdon of Work ACC0Mplish0d (If mote space is required, reface addtional sheets Wen* with atone nationatty and registration mak and date work completed) USA N908JE Nationally and Registration Mark The following major modification was accomplished: February 28, 2009 Dale 1. N/R #31809 Accomplished Deactivation of Rogerson Auxiliary Fuel System installed under STC #SA2734VVE in accordance with Quiet Wing Technologies Inc. Modification instructions No. M727-3-2008 Revision NC dated 19 NOV 08. approved per FAA Form 8110-3 by DER Mark Ostendorf #DERT-605421-NM dated 12/23/08. Minor deviations accomplished per Modification Instructions JEGE 8727-100 dated.2-26-09. SUMMARY 1. All work accomplished IAW STC fiSA2734WE and Quiet Wing Technologies Mod M727-3-2008. 2. Records of all work accomplished is on file at this repair station under Service Order #185008. 3. All Repairs are permanent unless otherwise stated. end Additional Sheets Ate Attached FAA Form 337000N SDNY_GM_02759858 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246580 EFTA01331043

ffri Foe. Aocromi4 ow en. zizo-coth orthezoc Becoa,t Lapp Mover LiS owwwww MAJOR REPAIR AND ALTERATION ret MAUviiithe of TSAI:WIN/0+ (Airframe, Powerplant, Propeller, or Appliance) Iodeni ANsfion Adminiontion INSTRUCTIONS: Print or type all entries. See Title 14 CFR §43.9, Part 43 Appendix a and AC 43.9-1 the subsequent revision memo° for instructions and disposition of this form. This report is required by law (49 U.S.C. §44701). Failure to report can result In a civil penally for sad. such violation. (49 U.S.C. §46301(e)) Nationality and Registration Mark N908JE Serial No 20115 1. Aircraft Maly Boeing Model 727 Series -31 Name (As shown on tegistathon condicate) JEGE Inc Address (As shown on togishation certificate) mufti. 103 Foul( Rd Sle 202 2. Owner Gib WiminatOn sew DE at 19003,3742 coon USA 3. For FAA Us. Only 4. Type 5. Unit Identification Repair Alteration Unit make Model Sonar No. (As desated in Item 1 80010) 0 (Z AIRFRAME o O POWERPLANT E 0 PROPELLER APPLIANCE 0 0 Manulack4s, 9. Conformity Statement A. AgencYs MIMS and Address B Kind of Agency rithe FLIGHTSTAR AIRCRAFT SERVICES. INC. u. S. Certhcated Mechanic I manuthcesw sass BLDG. 815,6025 FLIGHTLINE RD. 44441;n Certificsiod medwic C. Certificate No. ok, JACKSONVILLE es., Fl., / Catecated Raper Sheen be 32221 c....„, USA Ceonciders meinuensnce Organization FOTR986N D. I certify that the repair oridlor alteration made to the unli(+) have been made in accordance well the requirements of Mnlshed heroin is Duo and correct to the best or my knowledge. identified in Mon 5 above end described on the reverse or attachments hereto Pari 43 of the U.S. Federal Aviation Regulations and that the information i Extended range fuel per 14 CFR Part 43 0 APP. B Signature/Dale of Author! ad Individual CHRIS ADAMS 30 JULY 2008 It 7. Approval for Return to Service Pursuant to the authority given persons specified below, the MN Identified in item 5 was nspected in the manner prescribed by the Administrator of the Federal Aviation Administration and Is IZ Approved L Rejected FAA FN. Standards InspectOr Manufacturer Maintenance Organization Persona approved bye:moan Desarvneri or Transport BY FM Designee x Repair Station Inspection Authorization Other (Spotty) Corti math or Designation No. FOTR986N Signature/Ciato of Authorized Individual CHRIS ADAMS 30 JULY 2008 Cej , l id FAA Form 337 tooth SDNY_GM_02 759659 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024658 I EFTA01331044

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft reCOnl. An alteration must be Compatible with all proWous alterations to assure contoured conformity with the applicable eiwnxthiness requirements. S. Oaticrlption of Work Accomplished (Il more space Is required, stla0 additional shoats. Identify mei aircraft nahenegity and repotratlon mark and dote work comaltfed) WIO 8181 N908JE Nationality ON Registration Mn Oats L0 JULY 2008 1. COMPLIED WITH DFDR 11 CHANNEL UPGRADE IAW MODIFICATION ORDER EMTEO 2.80158.801 REV. B. DATED 07-30-2008 . FAA FORM 8110-3 DATED 07.30.2008 ISSUED. ENO K Additional Shoots Ara Attached FAA Form 337 threat SDNY_GM102799660 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246582 EFTA01331045

0 MAJOR REPAIR AND ALTERATION U.S. Departmtel of (Airframe, Powerplant, Propeller, or Appliance) Transportation Federal Aviation Ad ma bin tin Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification INSTRUCTIONS: Print or all aeries. See FAR 43.9, FAR 43 Appendix B and AC 43.9.1 @shy:gas revision Chaco( for instructions and disposition of this form. This report is roquira q law (49 U.S.C. 1421). Ware to report can result ma cull penalty not to exceed $1,000 for cad. such vxdatan (Section 901 Federal Aviation Act of 1916). I. Aircraft Make BOEING MODEL 727-31 Serial No. 20115 Nationality and Registraioo Mark USA N908JE 2. Owner Name (As shoal on regisnatiOn eatificalc) WOE INC Address (as shown on registration certificate) 103 FOULK RD STE 202 WILMINGTON, DELAWARE 19803.3742 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make I Model I Serial No. Repair Alteration AIRFRAME )O( (As descriked in item I above) POWERPLANT PROM 1ER APPLIANCE Type Mumfaeturer 6. Caaferalty Statuses • A. Agency's Name and Addreu B Kind of Agency C. Certificate No. TIMCO 102 SE Academic Ave. Lake City, FL 32025 U.S. Certificated Mechanic DU4R141M CLASS IV Foreign Cenificated Mechanic X Certificated Repair Station Manufacturer D. I certify that the repair sad/or alteration made to the units identified in km 4 above end described on the reverse or attachment% Mato have been made in accordance with Migliternatt3 of Part 43 of the U.S. Fedend Aviation Regulations and that the information furnished herein is true and correct to the bat of my knowkdge. Date April 28, 2008 Sisputure of Authorixed Owen H. Pritchard Individual t Approval for Return To Service Pursuant Administrator BY to the authority given persons specified below, the unit identified in itan 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is 121 APPROVED 0 REJECTED FAA F1L Standards Inspolor Manufacturer Inspection /unhorizstion Other (%4c169 FAA Designee X Repair Station Person Approved by Transport Canada Ainuatinen Group Date olApproasi or Rejection April 28 2008 Certificate or Designation No. DU4R141M CLASS IV Signature Antb of 'vides! y V 7 WrE :;1. FAA Form 337 (12-88) Us. 00VEINMENT MINTING orna 1992.76-012.0157 SDNY_GM_02759661 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246583 EFTA01331046

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) Boeing Model 727-31 S/N 20115 Reg. No. N908JE Page 1 April 28, 2008 The following major repair was accomplished: 1. OPS #24157 Repaired frozen bolt at I/B elevator hinge of RJH horizontal stabilizer by removing .023" corrosion, HFEC, no cracks noted. Fabricated and installed I ea. bushing IAW TIMCO REO-L01064 Rev. IR dated 04/14/08 approved by FAA Form 8110-3 by Richard C. Saltivan #DERT-40157-CE dated Apr. 17, 2008. SUMMARY 1. All work accomplished JAW TIMCO REO and FAA Form 8110-3. 2. Records of all work accomplished is on file at this repair station under service order 185006. 3. Aircraft was weighed and Weight and Balance updated accordingly. 4. All repairs are permanent unless otherwise stated. -end-- C I Additional Sheets Are Attached * us GOWN*41DIT PIUN114O OPICE ISMI4S-0IMI SDNY_GM_02759662 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246584 EFTA01331047

0 US Oepanntert MAJOR REPAIR AND ALTERATION Or Transportation (Airframe, Powerplant, Propeller, or Appliance) Fount aviation ...... Form Approved OMB No. 2120.0020 For FAA Use Only Office IderlaheatiOn So- rs vo- i INSTRUCTIONS: Print or type a entries. See FAR 43.9. FAR 43 Append& B. and AC43.9-1 (or subsequent revision thereof) for Instructions disposition of this form. This report is required bylaw (49 U.S.C. 1421). Failure to report can result In a civil penalty not to exceed $1,000 for such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Boeing Model 727-100 Serial No. 20115 Nationally and Registration Mark USA N908.1E 2. Owner Name (As shown on registration minket.) J.E.G.E, Inc. Address (as shown on registration certificate) 103 Far* Road STE 202 Wkniegton, DE. 19803-3742 3. For FAA Use Only S.L.'. • . :"'::: • in de Idevaieti arwortors itzwirentwes e serrred bthe snow -.... spew c....... airersit OCT r diddr. 43-7 sa_f 5V 0- 1-7 el ite= Dim 4. Unit Identificat 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME '""'"'"""*"•(As described in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 8. Conformity Statement A Agency's Name and Address 8. Kind of Agency C. Certificate No. BANYAN AIR SERVICE AVIONICS DIVISION 1635 NW 51st Place Ft. Lauderdale, FL 33309 u.s. Certificated Mechanic Radio C SD4R514Mlass 1.2.3 Limited Airframe Foreign Certificated Mechanic 0 Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified In kern 4 above and described on the reverse or attachments hereto have been made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations arid that the information furnished herein is true and correct to the best of my knowledge. Date o f g OCT-4912 01004 Signature of Authorized Inch ( O Steve Ouellette 7. Approval for Return to Service Pursuant to the authority given personsSpecified below; the unit identified In Item 4 was inspected n the manner prescribed by the Administrator of the Federal Aviation Adrrinistration and Is Si APPROVED O REJECTED BY FAA Fit. Standards Inspect( Manufacturer inspection Authorization Other (Specify) FM Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Refection Oeneoc.;:goa4 Certificate or . lion No. Designa SD4 . 11.514M Signatur thodzed I -oZ -- • Steve Ouellette FAA Form 337 (12436) SDNYGA402759663 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EF1'A_00246585 EFTA01331048

NOTICE Weight and balance or operating limitation changes shall be entered In the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach edationat sheets Identify with aircraft nationality and registration mark and date work completed) The purpose of this 337 is for the work performe,on 119087E under Banyan Air Service; Avionics Division work order #71301 completed on A 02 3/46 A. Installed an AirCell Iridium ST-3100 P/N 400-10680-001 and removed a previously installed AirCell AGT.01 P/N 900001-2. Minor wiring changes were made at the mating connector IAW installation manual P/N 800-10680 Rev. B dated June 2005. B. The above installation was performed in accordance with AC43.13-IB, Chapter 7, sections 1-5, AC43.13-1B Chapter.11;sections 3-17, AC43.13-2A Chapter 1, AC43.13-2A Chapter 2, paragraphs 24 & 25 and the aircraft's maintenance manual. : A functional test of the aboVedquipment has been performed FAR25.B09 and FAR25 .1431 for proper operation and did not adversely affect any other aircraft systems. An electrical load analysis was conducted and it was confirmed that this installation would not exceed 80% of the generator output. D. A log book entry and equipment list was generated to reflect the above installation. The weight change is negligible. the equipment list was updated to reflect this change. E. Instructions for continued airworthiness is attached.. END O Additional Sheets are Attached SDNY_GM_02759664 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246586 EFTA01331049

Instruction for Continued Airworthiness for AirCell ST 3100 Aircraft Subscriber Equipment System Installed on Boeing 727-100 N908JE S/N 20115 Revision O. Dated: 9/17/2006 SDNY_GM_02759665 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246587 EFTA01331050

SDNY_GM_02759666 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246588 EFTA01331051

• APPLICATION REVISIONS DESC. NEXT ASSY USED ON REV DESCRIPTION DATE APPROVED ST 3100 ASE SYSTEM BARON 95-BSS A BASELINE RELEASE 2002-10-16 K. FRANTZ B SEE OEN 00579 2002.10-25 K. FRANTZ irniet ALL SHEETS CARRY THE SAME REVISION LETTER UNLESS OTHERWISE SPECIFED DIMENSIONING & TOLERANCINt LAW ASAE Y14.5M-1994 DIMENS/ONS ARE II IN STANDARD TOLERANCES. .% t ±. .1 X< = 1.02 YYJC = ± .010 • ir e AirCell, Inc. lir C 11 1172 Century Drive Suite 280, Building B Louisville, CO 80027 APPROVED DATE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ST 3100 ASE SYSTEM PREPARED BY K FRANTZ YEAR-MO-DA 2002-10-16 MECH DESIGN Z HOH YEAR-MO-DA 2002-10-16 ELEC DESIGN B. SOUKUP YEAR-MO-DA 2002-10-16 TECH SUPPORT B. NIELSON YEAR-MO-DA 2002-10-16 SYSTEMS K FRANTZ YEAR-MO-DA 2002-10-16 ENGINEER,* J. POISON YEAR-MO-DA 2002-10-16 SI2E A CAGE CODE 1NO67 DRAINING NUMBER . 820-10680-001 REV B FILE FORMAT: Microsoft Word 2000 SCALE: NONE WEIGHT: NA SH 1 of 8 FILENAME: 820.10680-001-B.doe 65010377, A.St71 SPEC TEMPLATE DOC SDNY_GM_02759667 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246589 EFTA01331052

SDNY_GM_02759668 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246590 EFTA01331053

ge e p e 9 ft ft ft ft ft ft ft ) ft ) ) ) TABLE OF CONTENTS 1 GENERAL INFORMATION 3 1.1 SCOPE Cc THIS DCCUP•ENT 3 1.2 TECI-MAL SLFPCRT CONTACT WORMATION 3 1.3 GENERAL NOTES 3 1.4 Acmsomes 4 2 SYSTEM DESCRIPTION 2.1 TCPLEVEL SYSTEM COVIGURATICN 2.2 OPERA1O4OF1HE SYSTEM 6 3 OPERATIONAL TIME LIMITS AND SCHEDULED MAINTENANCE 4 UNSCHEDULED MAINTENANCE 4.1 TRnan Fs-DOINGPRO:IMRE 5 AIRWORTHINESS LIMITATIONS 7 7 7 7 FIGURES AND TABLES Table 2.1-1 System Component Definition 6 Figure 2.1-1 Block Diagram of ST 3100 ASE System 6 AltrCelf AirCell, Inc. 1172 Century Drive Suite 280, Building B Louisville, CO 80027 SIZE A CAGE CODE 1NQ67 DRAWNG NUMBER 820-10680-001 REV B FILE FORMAT: Microsoft Word 2000 I SH 2 of 8 FILE NAME: 820.10680-001 43.doc ST EOM ASCE SPEC TEMPLATE DOC SDNY_GM_02 759669 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024659 I EFTA01331054

SDNY GM 02759670 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246592 EFTA01331055

1 GENERAL INFORMATION 1.1 SCOPE OF THIS DOCUMENT This manual defines the instructions for continued airworthiness (ICAW) for an AirCelI 3000 Series Aircraft Subscriber Equipment (ASE) system. The manual is written to demonstrate compliance with FARs 23.1529 and 25.1529. Specifically, this manual defines the Instructions for the Model 3100 Satellite Telephone System (ST 3100). This manual is subdivided into sections to support the general operation, Inspection and maintenance of the ST 3100 system. Section 1 defines general information for the maintenance and airworthiness of the ASE system. Section 2 provides general Information on the configuration and operation of AirCell ASE systems. Section 3 presents a discussion of the scheduled maintenance and operational time limits for the system. Section 4 and Appendix A provide instructions for system operational checks, troubleshooting, unscheduled maintenance and component replacement. Section 5 provides a brief statement addressing airworthiness limitations for the ST 3100 system. 1.2 TECHNICAL SUPPORT CONTACT INFORMATION Technical support for AirCell products is available from 08:00 to 17:00 United States Mountain Time (Time Zone GMT —7 hours) Monday through Friday. The contact information for AirCell Technical Support is as follows: From a landline: Phone (in the US): 1.888.286.9876 (toll free) Phone (outside the US): 001.303.379.0278 (toll call) From an AirCell phone: From an Air Mode/AMPS phone (in the US): 611 (toll free) From a SAT Mode (Iridium) phone (worldwide): 2471 (toll free) Email: [email protected] Note: The toll free numbers for AirCell phones will only work for AirCell provided phones and services. 1.3 GENERAL NOTES • All pages in this document carry the same revision level. Revision status is indicated by a letter printed on each page of this manual. • The material in this manual is subject to change. Before planning or performing any installation or maintenance operation, check with AirCell Technical Support to verify that this manual is complete and has the latest revision. • AirCell, Inc. welcomes your comments, suggestions, and corrections concerning this manual. Please include in your correspondence the publication number, equipment part number, page or figure number, and a brief description of any problem or consideration you noted. Please send your comments to: AirCell, Inc. Corporate Publication Coordinator 1172 Century Drive Suite 280, Building B Louisville, Colorado 80027 [email protected] t kirrCelf AirCell, Inc. 1172 Century Drive Suite 280, Building B Louisville, CO 80027 SIZE CAGE CODE DRAWING NUMBER REV A 1NQ67 820-10680-001 B FILE FORMAT: Micro oft Word 2000 I SH 3 of 8 FILE NAME: 820-10680-001 -B.doc csioon kSZE SPEC TEURATE.DOC SDNY_GM 02759671 f 4 I I $ t G Q G i Q Q V ert V et a • a ot Se SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246593 EFTA01331056

SDNY GM 02759672 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246594 EFTA01331057

*) • • • • • 0, b ► 1.4 ADVISORIES WARNING Statements in this section contain critical safety information. Read these statements carefully before installing this unit. WARNING Observe standard safety precautions and wear safety glasses to prevent personal injury while performing maintenance on this unit in the aircraft. WARNING Shut off power before connecting or disconnecting the ST 3100 system, as voltage transients may damage the unit or the interface wiring. WARNING Components or subassemblies found in this unit may contain materials such as beryllium oxide, acids, lithium, radioactive material, mercury, etc. that can be hazardous to your health. If the component enclosure mat is broken, precautions must be taken against personal contact or inhalation in accordance with OSHA requirements 29CFR 1910.1000 or superseding documents. AirCell strongly discourages the opening or disassembly of sealed components. WARRANTY AND CERTIFICATIONS Any alteration of this product voids the FAA or FCC certification and the AirCell warranty. 2 SYSTEM DESCRIPTION The ST 3100 ASE system provides access to a range of two way communication options from an aircraft, including voice and data applications. With the ST 3100 system these services are available when the aircraft is in the air or on the ground. The AirCell satellite mode communications link Is provided using the 1600 MHz Iridium LEO (Low Earth Orbit-485 miles altitude) satellite network, which provides coverage from the ground up over the entire surface of the earth. 2.1 TOP LEVEL SYSTEM CONFIGURATION The ST 3100 system consists of a number of primary system components. The heart of the system is the ST 3100 ASE Transceiver, which includes internal electronics to support operation in the Iridium satellite network. Other system components include the externally mounted antenna, a low loss coaxial cable, and various user interfaces including multiple ASE handsets (up to 9), an RS-232 data port, and an audio panel interface. AirCelf AirCell, Inc. 1172 Century Drive Suite 280, Building B Louisville, CO 80027 SIZE CAGE CODE DRAWNG NUMBER REV A 1NQ67 820-10680-001 B FILE FORMAT: Micro oft Word 2000 I SH 4 of 8 FILENAME: 820-10680-001•Eldoc CGS XOTT. A. SIZE SPEC TONI-Alt 1:QC SDNY_GM_02759673 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246595 EFTA01331058

SDNY_GM_02759674 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246596 EFTA01331059

• *4_,,,..Transceivet The primary components of an ASE system include Line Replaceable Units (LRUs) and AirCell specified assemblies (such as coaxial cables or wiring harnesses) that are manufactured or purchased by the system installer. A list of the LRUs and specified assemblies is provided in Table 2.1.1, and a representative block diagram is provided In Figure 2.1-1 to demonstrate the interconnection of a typical ST 3100 system. For detailed information on the system components, please refer to ST 3100 ASE System installation manual (AirCell document 800-10680). or contact AirCell Technical Support for assistance. Table 2.1.1 System Component Definition System Component Designatlo n Description AirCell PH. Approved Alternate(s) AirCall PH of Alternate System Transceiver tRU ST 3100 _ASE Transceiver 400-10680-001 none : Mounting Tray LRU 3/8 ATR Wen Mounting Tray 800007.1 3000 Seder Mounting Rails 151.10689.001 System Wiring Harness Specified Assembly 26 wire System Harness NA ASE Handset LRU Flush Mount ASE Handset 400-10001.10x' Standard ASE Handset Podable Colic:ad ASE Handset Custom Retracted° ASE Handset 400-10035-001C 400-10015-00r 400-10019-COr Satellite ASE Antenna LRU _ 1600 MHz Satelte ASE Antenna, Patch Style 015-10306-001 1600 MHz Satellite ASS Antenna. Blade Styx 015-10683-601 Satellite Channel Coaxial Cable Specified Assembly Low Loss Coaxial Cable NA (vendor item)" • 'X' designates the color of the ASE handsets. The system coaxial cable Is a required item that is not provided by AirCell. The system Installer will need to purchase this Item from an approved vendor as defined later in this document. 1172 Century Drive 4Airrce •e AirCell, Inc. il Suite 280, Building B Louisville, CO 80027 SIZE A CAGE CODE 1NQ67 DRAWING NUMBER 820-10680-001 REV B FILE FORMAT: Microsoft Word 2000 SH 5 of 8 FILE NAME: 820-10680-001-B.doc Mixon. xsai SPEC TDAPLATE SDNY_GM_02759675 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 t • (4 ee (4 9 4! • ar ai a ai EFTA_00246597 EFTA01331060

SONY GM 02759676 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246598 EFTA01331061

6 0 0 0 0 0 p I I p p p I I I p If I p p I \-I ME SATEUJ1E AHIDMA FUSELAGE ME SYSITU %OR SAT AN1D1NA MIX ENGIRD NO COWECTION SYS DIOR AM SYS HS CNCIR ASE 'wow CHANNEL ASE SYS HS Oat CI MED ASE HANDSET CANNEL ASE SYS HS CN ] AN HANDSET CHANNEL CD TO AUDIO PANEL ASE SYS RS232 OCT, O TO 1.5.23.2 DATA TERMNAL TO NRCRAFt PMER (28 We) AtrotArr FUSELAGE Figure 2.1-1 Block Diagram of ST 3100 ASE System Note: Each 'Handset Channel' listed above is capable of supporting up to 3 ASE handsets, making it possible to integrate up to 9 handsets in the ST 3100 system. 2.2 OPERATION OF THE SYSTEM The user interface and operation of the ST 3100 system is designed to be very similar to the operation of a terrestrial cellular or PCS phone. Some key features of the ST 3100 system are as follows: • The system will power up when the avionics master switch for the aircraft Is powered on. The AirCell system Is always on when the avionics master Is powered on. • ' The Satellite mode network provides coverage anywhere on (or above) the surface of the earth with a clear view of the sky in all directions. • To place a call from the system handset, the user must verify that the system is 'in service'. SAT mode calls are typically dialed as international long distance calls (00 + country code + phone number). After dialing, the user must press the " SND key on the handset, and the phone call will proceed as a typical cellular or PCS call. At the completion of a call, the user may press the " END key to terminate the call. • The user may receive Incoming (ground to air) phone calls depending on the in service condition. The user can answer these calls by pressing the ' SND ' key on the handset. • Data calls can be made from Air to Ground over the ST system by connecting a Data Terminal Equipment device (such as a PC) to the RS-232 port of the system. The ST system has a built in modem function, so some user setup of the DTE will be required. More detailed operating Instructions are provided for this system in the ST 3100 User's manual (AirCell document 810-10680). cifinCell. AirCell, Inc. 1172 Century Drive Suite 280, Building B Louisville, CO 80027 SIZE A CAGE CODE 1NQ67 DRAWING NUMBER 820-10680-001 REV B FILE FORMAT: Micro oft Word 2000 SH 6 of 8 FLE NAME: 820-10880.00143.doc OPYKOn A.SLZE5PFC lEMPLATEDOC SDNY_GM_02759677 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246599 EFTA01331062

SDNY_GM_02759678 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 002466((1 EFTA01331063

3 OPERATIONAL TIME LIMITS AND SCHEDULED MAINTENANCE The ST 3100 system is designed and manufactured to be maintenance free after installation. Asa result of this design, there are no operational time limits or periodic maintenance checks or procedures that must be performed for the system. Inspections and/or system verification checks are only required In the event of a system failure (On Condition), as defined in Section 4 of this document. As an option, the system operator may perform a visual inspection of the various system components at the aircraft annual inspection, or other periodic maintenance Interval as defined by the aircraft manufacturer. 4 UNSCHEDULED MAINTENANCE The ST 3100 system is designed for "On Condition" maintenance only. In the event of a system failure, the system user/aircraft operator is advised to follow the troubleshooting procedure defined in Appendix A of this manual. After performing the basic procedure, the user will either have returned the system to normal operation, or should contact AirCell technical support for additional guidance. Note that, in the process of performing the troubleshooting procedure, authorized field service personnel are permitted to perform repairs to wiring harnesses, RF cable assemblies, mounting interfaces, or (with prior approval from AirCell Technical Support) to remove and replace any of the primary system Line Replaceable Units (LRUs). AirCell does not, under any circumstances, authorize field repair or subassembly level maintenance on any LRU. Sealed LRUs should always be returned to the AirCell FAA Repair Station for evaluation and repair. 4.1 TROUBLESHOODNG RROCEDLRE Appendix A provides a guide to identify simple problems that may be identified and/or resolved with simple field inspection and test processes. It is advised that the procedure in this appendix should be performed before contacting AirCell Technical Support for additional instruction. No specialized tools or equipment are required to perform this procedure. In the event that a step in this procedure is not dear, or the results of a procedure are not conclusive, the test operator should feel free to contact Technical Support for assistance., 5 AIRWORTHINESS LIMITATIONS The AirCell ST 3100 ASE system is a non-critical communications system. In accordance with FAR 23.1529 (with Pan 23 Appendix G) and FAR 25.1529 (with Part 25 Appendix H) this system has no Airworthiness Limitations for either Part 23 or Part 25 aircraft. The airworthiness limitations section is FAA approved and specifies maintenance required under Sections 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been approved. AIrCell, Inc. SIZE CAGE WOE DRAWING NUMBER REV AirCell 1172 Century Drive A 1NQ67 820-10680-001 B Suite 280, Building B FILE FORMAT: Micro oft Word 2000 SN 7 of 8 Louisville, CO 80027 FILE NAME: 820.10680-0014.doc WMCOTT. A.SZE WIC TEMPIATEOCC SDNY_GM_02759679 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246601 EFTA01331064

SDNY_GM_02759680 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246602 EFTA01331065

4./ 0 • • I p • 9 p p b ) ) ) ) ) ) ) ) ) ) ) ) ) ) ) Appendix A ST 3100 ASE System Troubleshooting Procedure AirC iv. ell AirCell, Inc. 1172 Century Drive SIZE A CAGE CODE 1NQ67 DRAWING MJ!,16ER 820-10680-001 REV B Suite 280, Building B FILE FORMAT: Microsoft Word 2000 SH 8 of 8 Louisville, CO 80027 I FILE NAME: 820.10680401-B.doc ter1.1077). SZE SPEC TENRATE DOC SDNY_GM_02759681 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246603 EFTA01331066

SDNY GM 02759682 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246604 EFTA01331067

AirCell Symptom Possible Caine Discussion Verification Step(s) Symptom I Power is not available to ASE The handset display should always CI Verify that the aircraft power system (master avionics switch) is on. Handset Display is System be illuminated when power is O Verify that the ASE system circuit breaker is closed. not illuminated applied to the ASE transceiver. Because the failure of a handset display is unlikely, a 'dead' display O Visually inspect the displays of all installed handsets in the system. If all handsets are off, proceed to the next bullet in this list. If most handsets arc illuminated, but one is not, then proceed to Symptom 2. (One or more suggests that there is a problem with O Wall handset displays are dead, the problem is likely in the power system wiring handsets integrated in system, no handset the input power to the ASE system. In the event that the one or more before the ASE transceiver. Visually check the system connections and the wiring , harness leads between the transceiver and the aircraft power system. Repair or displays are handset display(s) are not reconnect any obvious problems. illuminated) illuminated, the user/operator should verify that aircraft power is on and O If needed, ring out the power lints per the system wiring diagram. Repair any broken wires or rework to match the system wiring diagram. available to the ASE transceiver. O If this procedure does not resolve the problem, contact AirCell Technical Support for additional guidance. Symptom 2 Handset Display is Bad connection or faulty wiring between handset and In a system with multiple handsets, if some handsets are operating and O Some ASE systems integrate multiple handsets. If more than one handset is • installed on the system, check the display on all handsets. If only one of multiple not illuminated transceiver• some arc not, then it is likely that either the handset is bad or the handsets is not illuminated, then the problem is either a bad handset or in the handset connection! wiring harness between that handset cradle and the transceiver. wiring between the handset and the O Perform a visual inspection to verify that all connections arc made in accordance (ASS System has or transceiver is faulty. with the system wiring diagram. Correct any obvious problems. multiple handsets, and the displays of most handsets are on, but one handset is not Bad hand set O If all system connections arc correct, then switch the 'dead' handset with a known good handset and retest the system. lithe handset is still dead in the new location, then the handset is bad. Contact AirCell Technical Support for repair/replacement instmetions. illuminated.) O If the known good handset is now dead, then the problem is in the system wiring/connections between the handset and the transceiver. Ring out the lines per the system wiring diagram. Specifically check for 9V power and ground leads on the HS power line from the transceiver system connector. Repair any broken wires or rework the system wiring hamar to match the wiring diagram. 0 If this procedure does not resolve the problem, contact AirCell Technical Support for additional guidance. 8 I -o c (0 C9I a-1 aC 06. tr) cc a. cc 0 c4 0 0 A-1 o_ 0 ST 3100 ASE System );.• •• ;a, *. Troubleshooting Procedure 820-10680-001, Rev B • c73 i • hn-ftteittilt. tit EFTA01331068

SDNY_GM_02759684 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246606 EFTA01331069

viiv vs sew wwwwwww ur sir er var vs se is se it IP ler vb 1St IP eV nil WI le1 k irCe1F Symptom Possible Cause Discussion VerificationStep(*) Symptom 1 Handset Display is illuminated and display indicates no signal for Satellite (SAT) mode. Possible Cause 3A System antenna does not have Line of Sight (LOS) view to satellite. The ST 3100 transceiver operates in Satellite (SAT) mode. When in coverage the ST system should detect and register for SAT mode service. If the system does not register, then it is likely that either the antenna does not have a LOS to a satellite (3A), or there is a problem with the RF channel in the aircraft (38). In this condition, it is unlikely that there is a problem with the system transceiver, Verification Test 3A O Verify that the system SAT antenna has a clear LOS to the sky in all directions. A clear LOS is defined to exist when there are no obstructions (such as buildings, trees, vehicles etc) that are higher than 30 degrees above aircraft horizon in any direction. This should never be a problem in flight. O Use the handset to enter the SAT lock mode (FCN, 3, 3) keys on the handset. The handset will display the word "IRIDIUM" when the SAT mode is locked. O Once the LOS has been established the system should register on the SAT network within 60 seconds. The system is registered when the "NO SVC" indicator is not visible on the handset display. O If the "NO SVC" indicator extinguishes, then the SAT mode is engaged, and the problem is resolved. The user may choose to make a test call and verify the operation the system. O If the-NO SVC" indicator stays illuminated, then the system cannot register, and it is likely that there is an installation or equipment problem. Either contact AirCell Technical Support for additional guidance, or proceed to Verification Test 38. No Satellite mode signal Possible Cause 3D There is a problem with the Satellite RF channel. Verification Test 3D O While the aircraft is on the ground, perform a visual inspection orate ASE system satellite antenna. Verify that the antenna is installed to the aircraft fuselage in accordance with the system antenna installation drawings. Verify the mechanical integrity of the antenna, and that the antenna is reasonably free of dirt, oil, ice and other undesired coatings. O Visually inspect the RF satellite channel, including the coaxial connections to the antenna and the system transceiver. Inspect the coaxial connectors to verify that they are connected in accordance with the system wiring diagram, and that they arc not damaged. Look for breaks, kinks or other damage to the coaxial cable. 0 The user is authorized to correct installation errors (such as cabling errors), or to repair minor damage (such as broken coaxial connections, damaged coaxial cables, etc). The user is not authorized to open or modify sealed LRUs. O If these steps do not resolve the problem, contact AirCell Technical Support for additional guidance. Other conditions For all other conditions, contact AirCell Technical Support for guidance. A-2 ST 3100 ASE System Troubleshooting Procedure 820-10680-001, Rev B Ql OO v) cc w < a_ cc Lu C Lu U Lu 0 O I- I-U Lu cTo' D EFTA01331070

SDNYGM_02759686 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246608 EFTA01331071

0 a osarenant MAJOR REPAIR AND ALTERATION nmortation For Powerplant, Propeller, or Appliance) Ask., So- Fs AdISIMMIOn Forrn Approved OMB No. 2120-0020 For FM Use Only Office klentificalion DO- iq INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC43.9-1 (or subsequent revision theme° for inalnadtkaa and diseosltion of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1.000 breach such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Boeing Model 727-100 Serial No. 20115 Nationally and Registration Mark USA N908JE 2. Owner Name (As shown on registmeon certificate) J.E.G.E, Inc. Address (as shown on registration certificate) 103 Foot Ftoad STE 202 INihnington, DE. 198033742 3. For FM Use Only .., 4. Unit identification S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME ►all (As described in Hem 1 War POWERPLANT PROPELLER APPLIANCE Type Manures:haw 6. Conformity Statement A. AgenCits Name and Address B. Kind of Agency C. Certificate No. BANYAN AIR SERVICE AVIONICS DIVISION 1635 NW 51st Place Ft Lauderdale, FL 33309 U.S. Certificated Mechanic Radio C SDIR514M lass1.2,3 Limited Airframe Foreign Certificated Mechanic 0 Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unk(s) Identified ki kern 4 above and described on the reverse or attachments hereto have been made in accordance wan the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein S true and coned to the best of my knowledge. Date October 10. 2006 Signature of Authorked c_Inr2a2,__ Steve Ouellette 7. Approval for Return to Service Pursuant to the authority given pensoressecified below, the unk identified in kern 4 was inspected in the mater coescralial by the Administrator of the Federal Aviation Administration and SO APPROVED O REJECTED BY FM Ft. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FM Designee X Repair Station Person Approved by Transport Carlin AIWOrthilltin Grow Dab c4Approval or ion Reject Da October 10, 2006 Certificate or 0esienston No. SD4R5I4M sian2re:TrIzed I I Steve Ouellette - e--- FAA Fam 337 (1248) SONY_GM_02 759687 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246609 EFTA01331072

NOTICE • Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An Operation must be compatible with eh pmvious alterations to assure continued conformity with the applicable ainvorthlness requirements. 8. Description of Work Accomplished (// mole space is required. Witch edthtionsi sheets Identify Sin aircraft natiOnelity and registradan mark and date work completed) The purpose of this 337 is for the work performed on N908Th under Banyan Air Service; Avionics Division work order #71301 completed on October 4, 2006. A. Installed an AirCell Iridium Antenna P/N S67-1575-109 in accordance with DER Services drawing number 2006-173-1 approved per FAA form 8130-3 signed by Robert Belgau DERT designation number DERT-510024-CE. B. The above installation was performed in accordance with AC43.13-1B, Chapter 7, sections 1-5, AC43.13-1B Chapter 11, sections 3-17, AC43.13-2A Chapter 1, AC43.13-2A Chapter 3, paragraphs 43 & 44 and the aircraft's maintenance manual. A log book entry and equipment list was generated to reflect the above installation. The weight change is negligible. the equipment list was updated to reflect this change. D. Instructions for Continued Airworthiness is "on condition only." Additional Shies are Attached SDNY_GM_02759688 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246610 EFTA01331073

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE October 07,2006 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Boeing 172731E TYPE Airplane mil e"*A•sw macww al N a AME nyan OF APPLICANT B Air Service LIST OF DATA IDENTIFICATION TITLE DER Services Drawing: 2006-173-1 . Rev. UR tr.:. Dtd. 27-Sep-06 END END ____ Effectivity: S/N: 20115, T/N: N908JE Iridium Antenna Installation STA 515 - BTWN S-2R & S-3R END END END END END END END END END END Note: This aircraft is effected by AD 98-11-03 RI. Certification to FAR 25.571, Damage - tolerance and fatigue evaluation of structure may be required. Per Advisory Circular 25.1529-I Instructions for Continued Airworthiness of Structural Repairs on Transport Category Airplanes, the damage tolerance and fatigue evaluation of the structure must be performed before 4/11/2003. Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering design data and is not installation approval. (Ref. 8110.45 8/30/02 for more info) 2) This approval is valid for the aircraft model and aerial amber listed below 3) This approval is based on FAA Approved structural analysis on file at DER Services Office in Ft. Lauderdale, FL. or DER Services, Inc. office in Birmingham AL. Model No. 727-31 Serial No. 20115 PURPOSE Approve data for low profile antenna installation (structural aspects only, Stalls Analysis) OF DATA APPLICABLE REQUIREMENTS (LIST SPECIFIC SECTIONS) CAR 46.200, 46.201, 4b.202, 4b.260, 4b301, 46.302,46.303, 4L106 CERTIFICATION - trader antbotity vested by dirt-thee of the Administrator ad is accadaace with coadidos sod limitation of sppolatrant oder Part IS) of the Federal Mimics Repletion, data listed been tanated In accordance wltb established proudest sad toad to comply with applicable regainmeas of the Fatal Aviation Repletion O Reamstend approval of these data I (We) Therefore iril Approve these data SIGNATVRUS) Or DESIGNATED ENGINEERING REPRESENTWEW) DESIGNATION MAIDENS) CLASSIFICATIONS) -rid, esen---(•••-•- Robert J. Belgau DEBT-510024-CF. Structures IAA FORM II 14.311i.n)strrascou PittViOUS tOrrilXv DER SERVICES PROJECT NO. F2066-173 SDNY_GM_02759689 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246611 EFTA01331074

SDNY_GM_02759690 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002466 I 2 EFTA01331075

en •er Cg 8 7 6 5 4 3 I 2 D C 8 A GENERAL NOTES: 1. FABRICATE PART(s) AS SHOWN. 2. BEFORE INSTALLATION OF DOUBLER. ROLL TO MATCH AIRCRAFT MOLD UNE RADIUS. 3. BREAK AU. SHARP EDGES .020/.030 R. 4. TREAT ALL REWORKED AREAS USING ALODINE 1201S (PER MIL-C-5541. CLASS 1A) AND TWO (2) COATS OF EPDXY POLYAMIDE PRIMER (PER MIL-P-233377, TYPE I). 5. FINISH ALUMINUM PARTS USING ALODINE 120IS AND TWO (2) COATS OF EPDXY PRIMER. 6. MAINTAIN MINIMUM 2D • 1/16' EDGE DISTANCE FOR AU. FASTENERS ON DETAILS; MINIMUM 2D EDGE DISTANCE ON ASSEMBLY. 7. ALL FASTENERS ARE TO BE INSTALLED IN TRANSITION-FIT HOLES. HOLE TOLERANCE PER RAVINE 8. ALL FASTENER LENGTHS ARE TO BE VERIFIED FOR TOLERANCE PRIOR TO INSTALLATION. (REF) S - 3R --- STA 510 STA 515.00 S - 2R 9. INSTALL ALL PARTS AND THREADED FASTENERS WET USING PRIAM TYPE III SEALANT ON ALL FAYING SURFACES. 10. RESTORE ORIGINAL FINISH PER 9727 M.M. 51-21. 11. PROTECT REWORKED AREA AGAINST CORROSION PER 8727 SRM, CHAPTER 5140-2. 12. REFERENCE 8727 S.R.M. CHAPTER 51.30 FOR FASTENER REMOVAL AND INSTALLATION PROCEDURES. 13. REINSTALL ALL ADJACENT STRUCTURE REMOVED TO FACILITATE ANTENNA INSTALLATION. 14. BEAD SEAL ANTENNA WITH PRC 1422 SEALENT. 15. REVISE AIRCRAFT RECORDS TO REFLECT INSTALLATION. liitss scat NA EXISTING BONDED STRAPS VR DESCRIPTION INITIAL RELEASE 09-27-200T{(4,42az DATE APPROVED 50 COUNTERSUNK RIVET NAS I 097AD4 -2 EXISTING FUSELAGE SKIN (REF) FASTENER CODES ITEM DESCRIPTION saananstrel•Wa telASANOONAIPUN .--- STA 520 OP L OPL OPL OPL OPL OPL 8 4 4 1 RIVET - NUTPLATE SCREW NUTPLATE DOUBLER - INTERNAL LI CPS-IRIDIUM ANTENNA ITEM Ott ITS20426A03- 2 4 .3 2 MS24694C55 NAS1473A3 0.050" 2024-T3 00-A-25015 D C 4- 8 567-1575-109 PART NUMBER NAME MATERIAL MIL-SPEC VENDOR Ports List BANYAN AIR SERVICE SAMOA MANI 802bra MO P/SAY02 OCCJIDA SAAAAAN Al- ORAIVIC• OM Ns /anew an , WAYS —ft •••001......s • Ca losm•army @SSA A.600a. as a —AV we •PO I•al. WI OA••• S•••• ••••• .. NAAA/AAO Atari seorvic• ••• Poo era SY Fmoun AA amith Sr. re ...CMS_ gs'atiNINSEP UNSPEEISIED TOLERANCE LIT Mit orICHA 09-27 2006 a DER OW la tin ~SERVICESI 100 IRIDIUM ANTENNA INSTALLATION STA 515 SINN S-2R 8 S.3R FOLIOS NCLES !I/32 8 7 5 IECDIALS A Si t 43 Tu. t AI 4 MAW m W.D.OUVERI sacs IPA R.J.BELGAU miss to W.D.OUVERI ammo rn R.J.BELGAU Ait NT. BOEING stt w.. 727-3f us. w N902KIE stRAL IA .20115 r 2006-173-1 0. 3J g 2006-173 nt NA. no fir 3- 1 av !TR STRL INSTL 1 3 2 A N at C in I. Lri O ri z O vi • ri cri 0 R re <9 cc cc 0 EL 0 O cc o_ 0 V) EFTA01331076

SDNY_GM_02759692 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246614 EFTA01331077

8 7 6 5 4 3 2 C 4 a A STA 510 EXISTING FUSELAGE SKIN (REF) x4 STA 515 A 01.00 CONNECTOR CUTOUT IN SKIN 0 0 • 0 0 0 0 0 0 • •••• • o • • • r • • ° ea f a • • • • .. • • • • • it • 0_1_ • 0 • 0 • 0 • 0 A -I VIEW LOOKING UP SOME STRUCTURE REMOVED FOR CLARITY 4 STA 520 IRIDIUM ANTENNA INSTALLATION @ STA 515.00 - BTWN S-2R 8 S-3R EXISTING BONDED STRAPS (REF) EXISTING BONDED STRAPS (REF) - S - 2R LBL 12 - S - 3R Tins roe... •CoW001.6.NOMPAIMICDOCCOMPThano. an AN OMR • 01111.... As. es se glea. Ow 6.. ..•••• • Ca *tan as, lie% saminitaarretwa frea. emeid Op talon on am man OM Wows Sauey wan an W ream.. is. gab ninimio•00.6,420 RAY no Om off miner% fa. manors shale...a/ de. •••••••••••3 IMMWA 8 I 7 5 4 EXISTING BONDED STRAPS (REF) EXISTING FUSELAGE SKIN (REF) SECTION A-A DER SERVICES ir 2006-173-1 rt lailiatia FL la •••••••• ONINSWHINO MIA B W.D.OUVERI OR swot or 20115 KA13•4 I, wit 2 If 3 3 I 2 1 D C 4- a A 8i r-r at E,4 C tn (13 ri c cri 00 r-: (n cc C9 cc CL LLI 0 0 w H U cc a_ 0 H U tn EFTA01331078

SDNY_GM_027596. SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002466 I 6 EFTA01331079

a O a 0.75 O, 0.00 0.38 1.13 1.50 1.88 2.25 ! MINI i i iiiqi i .. il ii i i i 4.50 O I it " I I I 4.88 O 5.25 O O O O to Oft t tit. 5.83 O O O I. O .._ I j.! I iiti i 6.00 lit' .0, q, 1 i ri 1 ,:' ,.., z 0 Jo) 0 Ei OK% °WM (7 ill va 2.83 O 3.00 3.38 ---O 3.75 4.13 XV a 0, 4- O O SDNY_GM_02759695 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246617 EFTA01331080

, SDNY_GM_02759696 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 002466 I8 EFTA01331081

0 ._ us Depactran MAJOR REPAIR AND ALTERATION or Trainecetarthe Faders (Airframe, Powerplant, Propeller, or Appliance) Awoke, MminIstnalon Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification So- re) Do - /7 INSTRUCTIONS: Print or type all enures. See FAR 43.9. FAR 43 Appendix B. and AC43.9-1 (or subsequent revision thereof) for instructions and C0SP0SIt0rl of this them. This report is required by law (49 U.S.C. 1421). Faure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act o(1958). 1. Aircraft Make Boeing Model 727-100 Serial No. 20155 Nationafity and Regisbabort Mark USA N908JE 2. Owner Name (As shown on registratlan cerfAkate) J.E.G.E. Inc. • Address (as shown on rogistrstion certificate) 103 Pout Road. Ste 202 Wimington, DE. 19803-3742 3. For FAA Use Only 4. Unit Identification s. Type Unit Make Model Serial No. Repair Alteration AIRFRAME """""•"'s(At 0. deserted Mir 1 above POWERPLANT PROPELLER APPLIANCE Type Manufacturer IL Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. BANYAN AIR SERVICE AVIONICS DIVISION 1635 NW 51st Place Ft. Lauderdale, FL 33309 U.S. Certificated Mechanic Radio Cl SD4R514M ass 1,2,3 Limited Airframe Foreign Certificated Mechanic 0 Certifkated Repair Station Manufacturer D.1 certify that the repair andkit alteration made to the unit(s) lammed in Kern 4 above and described on the reverse or attachments hereto have been made in accordance %Nth the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is We and coned to the best of my knowledge. Date • 8 November 2004 Signature of Autheria2.3.1 .4 _,./2 : x i / et_ Zoe/ Steve Ouellette 7. Approval for Return to Service Pursuant to the authority given persons specified below, the unit identified in Item 4 was Inspected In the manner prescnbed by the Administrator of the Federal Aviation Administration and is APPROVED O REJECTED BY FAA Fit. Standards inspector Manufacturer inspection Amthorlzabon Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Atheorthiness Group Date of App oval or Rejection 19 November 2004 Certificate or Designation No. 9D4R314M Signature of Authorized Individual d2l egit u t_ .... .... ) Steve Ouellette FAA Form 337 02-88) SOFIY_GM_02 759897 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246619 EFTA01331082

NOTICE Weight and balance or operating limitation changes shall be entered In the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (II more space is required, attach additional sheets Identify with aircraft nationality end registration mark and date work completed) The purpose of this 337 is for the FAA approval of the new flight manual supplement on N908JE under Banyan Air Servive, Avionics Division work order #68062. A. Removed existing TDR-94 transponders P/N 622-9210-003 and routed to the manufacture for upgrade to P/N 6252-9210-007 to provide flight ID. System ground and flight checked good. B. The weight & balance is not affected and equipment list was updated. C. Instructions for continued airworthiness are "on condition only". END O Additional Sheets are Attached SDNY_GM_02759698 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246620 EFTA01331083

0 - - US Deponmem MAJOR REPAIR AND ALTERATION a Federal (Airframe, Powerplant, Propeller, or Appliance) A,&gon AdmiNstraban Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification f 1 50 •3/4 1451)6P-47 ! INSTRUCTIONS: Print or type all obits. See FAR 43,9, FAR 43 Appendix B. and AC43.9-1 (or subsequent revision thereof) for Instructions a disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report Can result in a Civil penalty not to exceed 31.000 for each such violation (Section 901 Federal Aviation Act of 1958). I. Aircraft Make Boeing Model 727-100 Senal No. 20115 Natlonaity and Registration Mark USA N908JE 2. Owner Name (As shown on registration certificate) J.E.G.E, Inc. • Address (as shown on registrallon certificate) 103 Folk Road STE 202 Wilmingten, DE. 19803-3742 -- 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair il terabon • AIRFRAME •m1-----"(AS described in Item 1 abover--- --- el POWERPLANT PROPELLER Type APPLIANCE Manufacturer 6. Confomilty Statement A Agency's Name and Address B. Kind Of Agency C. Certificate No. BANYAN AIR SERVICE u.S. Certificated Mechanic AVIONICS DIVISION Foreign Certificated Mechanic SD4R514M Radio Class 1.2,3 1635 NW 51st Place I81 Certificated Repair Station Limited Airframe Ft. Lauderdale, FL 33309 Manufacturer 0. I certify that the repair ancllor alteration made to the unit(s) identified In item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein Is true and correct to the best of my knowledge. Date / ar A‘l/eifrilge? a '°‘71 signature of Author iduaadail. Steve Ouellette . 7. Approval for Return to Servile 1 Pursuant to the authority given persons Federal Aviation Administration and is cified below, the unit Identified in item 4 was inspected in the manner prescribed by the Administrator of the APPROVED O REJECTED BY FAA Ft Standards Inspector Manufacturer inspection Authorization Other (Specify) FM Designee X Repair Station Pilsen Approved by Transport Canada Ainvorthiness Group Dale of Approval or Refection , /9 ferewisel_ace Certificate or Designation No. SD4R514M Signature win /* II '''''' Steve Ouellette FM Form 337 (12-83) SONY_GM_02 759699 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246621 EFTA01331084

NOTICE ' Weight and balance or operating limitation changes shall be entered In the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. O. Dinalotion of Work Accomplished (It more space is required, attach wititional sheets. Identity with aircraft flattened), and registration mark and date week completed.) The purpose of this 337 is for the work performed on N908JE under Banyan Air Service, Avionics Division work order #68062. A. Installed a Universal Avionics Systems Corp. Terrain Avoidance and Warning System in accordance with SIP Technical Services, Inc. data list 7280-DL-001-501, Rev. H dated December 5,2002 or later. (STC# ST09951SC) B. The above installation was performed in accordance with AC43.13-1B, Chapter 7, sections 1-5, AC43.13-1B Chapter 11, sections 3-17, AC43.13-2A Chapter 1, AC43.13-2A Chapter 2, paragraphs 24, 25, and 28, AC25-23 and the aircraft's maintenance manual. C. A functional test of the above equipment has been performed FAR25.1309 and FAR25 1431 for proper operation and did not adversely affect any other aircraft systems. An electrical load analysis was conducted and it was confirmed that this installation would not exceed 80% of the generator output. D. A log book entry and equipment list was generated to reflect the above installation. A weight & balance was calculated. An FAA approved flight manual supplement provided with the above STC, Document No. 7280-FM-001, dated December 13, 2002 or later E. Instructions for continued airworthiness provided by SIP Technical Services Report No. 7280-ICA-001 Rev. F dated June 6, 2002. END O Addilional Sheets are Attached SDNY_GM_02759700 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246622 EFTA01331085

!tuna ,tate• Of eetencriut ptpartment of Zaransparintion - gehrrnl cikbizition jktiministralion Supplemental Egpr aertifirate &-iftesah• award/0 ST09951SC SIP Technical Services, lac. 10107 McAllister Freeway San Antonio, TX 78216 era 4u ea or., b. a yr , .4.9.A. GMerowasis, sear assi sznetena4 ZZONA•aJ 44000S01 07,0r4 46 sabsbablefibeiki yerabiwaseisti ivegiwit 4b 1/c& Civil Air Sacjiaral.r. ektouregkv&e., .Fif/se KelOoszie ./Ifiest4e: A3wE ada.4.. Boeing -0 -4•441: 727-100 Series giosootavb ("rem atogw, War Installation of a Universal Avionics Systems Corporation Terrain Awareness and Warning System in accordance with SIP Technical Services, Data List 7280-DL-001-501, Revision H, dated December 5, 2002, or later FAA approved revision. FAA approved Airplane Flight Manual Supplement Document Number 7280-FM-001, dated December 13, 2002, or later FAA approved revision is required. Siouratavw resireassia4nS. Compatibility of this design change with previously approved modifications must be determined by the installer. If the bolder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. 82.3 Kra // that" andh& JOISWee41, data rairket t‘t iftweVa.b syrbata-osvas:b 6. viren.a Jae...staved Ja4neneed nrchetaia, a knasinalien W.4 I cawrae intateW4. 44 aiiauh,:serato, 044 .3i.t4e,ae l../Sevialeys ../erkstoeVeciZievs. Sate cideesivs4Pbalebvs August 02, 2001 Sale oeisia4.44r :December 13, 2002 eee:i.kteae.- gek amended.. (ml.) Mr ai ion of this certificate is p bisbthla by s 1455 or not racemi,y Q. 000, or opt rower, PM Son 1110.3(10-4•I Paha l a 29 I fl air, or both. s certificate soy he traiarare0 to scnrdsacs with OA 22.57. SDNY_GM_02759701 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246623 EFTA01331086

SDNY_OM_02759702 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246624 EFTA01331087

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 FAA APPROVED • AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BOEING 727-100 WITH UNIVERSAL AVIONICS SYSTEMS CORPORATION DUAL MULTISENSOR UNS-ID+ FLIGHT MANAGEMENT SYSTEMS • REG IL N908TE SERIAL #. 20115 This supplement must be attached to the FM Approved Airplane Flight Manual when the Universal Avionics System Corporation UNS-1D+ Flight Manitgement System (FMS) is „installed in accordance with field approved 337 dated eV:: /la/ (21O(-)le . The information contained herein supplements or supersedes the basic manual only in those areas listed herein. For limitations, procedures, and performance information not contained in this supplement; consult the basic Airplane Flight Manual. FAA APPROVED Gary Justice Principal Avionics Inspector Federal Aviation Administration Flight Standards District Office #17 Ft. Lauderdale, FL 33315 Date: NOV 8 2004 Rev. 0 VFilige 1 of 9 SDNY_GM_02759703 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 002436625 EFTA01331088

4 Banyan Air Service Flight Manual Supplement Avionics Division UNS-1D+ FMS 1635 NW 51st Place N908JE BOEING 20115 Ft. Lauderdale, FL 33309 Table of Content' SECTION PAGE GENERAL 3 LIMITATIONS 3 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 3 PERFORMANCE 8 Revision 0 Ail Date: NOY 8 2004 Pages RECORD OF REVISIONS Description Initlal Release Rev. 0 Approved . NOV 8 2001 *Et: O. Page 2 of 9 SDNY GM_02 759704 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246626 EFTA01331089

Banyan Air Service Flight Manual Supplement Avionics Division UNS-1D. FMS 1635 NW 51st Place N908JE BOEING 20115 Ft. Lauderdale, FL 33309 SECTION I - GENERAL 1. INSTALLATION DESCRIPTION. The Universal Avionics Systems Corporation dual FMS's use inputs from their integral GPS Receivers, Navigation Receivers and DME Transceivers to provide a blended position for navigation. Each FMS contains an Internal TSO C129a GPS sensor (GNSS 2400), which is cross-wired to the other FMS such that both systems have GPS 1 and GPS 2 data as inputs. The EMS's receive air data parameters from an Air Data Computer. A Data Transfer Unit (DTU100) is used to load periodic navigation data base updates via zip disks. The systems provide navigation and steering data to the flight director/autopilot system. Refer to the appropriate Operators Manuals as applicable. The FMS's contain software SCN 8021902 which provides capability for point-to-point navigation, as well as SIDs, STARs, holding patterns and GPS approaches. These SCN's comply with requirements of TSOs C115b and C129a Class Al when interfaced to the internal GPS sensors which are TSO C129a Class Al/B1/C1 certified The UNS- 1D+ FMS may contain either a GLONASS sensor or a GPS sensor, depending on hardware configuration. Lateral and Vertical deviations are provided for En Route, Terminal Area and Approach operations, including GPS overlay approaches. Approaches may be FCS coupled both laterally and vertically. Multi-Mission search patterns are available with SCN 902. 2. LATERAL NAVIGATION APPROVALS. Provided the FMS multi-sensor navigation system is receiving usable signals, it has been demonstrated capable of and has been shown to meet the accuracy specifications of: VER/IFR En Route domestic, Terminal and Instrument Approach (LOC, BC, GPS and GPS-overlay NDB, VOR, VOR-DME and RNAV) operations within the U.S.National Airspace System using the WGS-84 coordinate reference datum in accordance with the criteria of Advisory Circular AC 20-130A and AC 25-15. Satellite navigation data is based upon use of only the Global Positioning System (GPS) operated by the United States. Additionally, Russian GLONASS satellites provide increased accuracy but are not used for integrity or Receiver Autonomous Integrity Monitoring (RAIM) calculations or predictions. The dual FMS installation with dual internal GPS sensors, as installed, complies with the requirements of FM Notice 8110.60 for GPS primary means of Class II navigation in oceanic and remote airspace (including NAT MNPS in accordance with AC 120-33 and 91-49), when used in conjunction with the Universal Flight Planning Program, PN 10751 with SCN 24.0 or later FM approved version. This does not constitute an operational approval. Date: NOV 8 2004 Rev. 0 Page 3 of 9 SDNY_GM_02759705 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246627 EFTA01331090

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 SECTION I — GENERAL (cont.) Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 RNP- Approvals The dual multi-sentor FMS installation integrates dual GPS sensors and complies with equipage and accuracy requirements of FAA Order 8400.12A paragraph 12b(4), for operations in RNP-10 airspace. This does not constitute en operational approval. This installation also complies with equipage and accuracy requirements of AC 90- 96 paragraph 7b(1), 7d(3)(a) 2, 7d(3)(e) for BRNAV (RNP-5) when operating in Class I airspace, without time limits. The table details time limitations placed on RNP-10 and BRNAV operations with minimum sensors in NAV mode. Sensors Available RNP-10 Limitations RPN-5 (BRNAV) Limitations minimum dual FMS's required) (minimum single FMS required 1 GPS only N/A No time limitation when used in Conjunction with UFP VOR/DME only N/A No time limitation DME/DME only N/A No time limitation 3. VERTICAL NAVIGATION APPROVAL The dual Flight Management Systems, as installed, meet the requirements for VFR/IFR En Route, Terminal Area and Approach VNAV operations in accordance with the criteria of AC 20-129 and AC 90-97, paragraph 7.a (2). SECTION II — LIMITATIONS 1. The FMS Operator's Manual, Report Nos. 2423sv802/902 Dated 9/16/03 (or later revision) must be available to the flight crew whenever navigation is predicated upon the use of the Universal Avionics Flight Management System. 2. The system must utilize software version SCN 802/902.X, where X represents FAA approved minor changes. 4. IFR En Route and Terminal navigation are prohibited unless the pilot verifies the currency of the database or verifies each selected Waypoint for accuracy by reference to current approved data. Date: NOV 8 2004 Rev. 0 • Page 4 of 9 SDNY_GM_02759706 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246628 EFTA01331091

Banyan Air Service Flight Manual Supplement Avionics Division UNS-1D+ FMS 1635 NW 51st Place N908..IE BOEING 20115 Ft. Lauderdale. FL 33309 SECTION II - LIMITATIONS (cont) 4. Instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the FMS database. The FMS database must incorporate the current update cycle. a. Instrument approaches must be conducted in the Approach-mode, and GPS Integrity monitoring (when using GPS for approach guidance) must be available at the Final - Approach Fix, as indicated to the pilot by the 'GPS INTEG' amber annunciator being off. b. When an alternate airport is required by the applicable operating rules, it must be served by an approach based on other than GPS navigation, the aircraft must have.. operational equipment capable of using that navigation aid, and the required navigation aid must be operational. c. GPS can only be used for approach guidance if the reference coordinate datum system for the approach is WGS-84 or NAD 83. d. GPS will remain selected for all GPS approaches and any approach with a 'G" suffix to the approach identifier in the navigation database. GPS will be deselected for any pilot-defined VOR or VOR/DME' RNAV approaches. e. Pilot-defined IFR approaches must be defined using Waypoint coordinates from FMS's navigation data base. f. The FMS's are approved for pilot-defined VFR approaches as a VFR pilot aid only. NOTE: All sensors remain selected for VFR approaches. 5. When operating in other than oceanic and remote regions, the aircraft must have other approved navigation equipment installed and operating appropriate for the route of flight. 6. Displayed FMS navigation parameters are referenced to Magnetic North, and operation of the aircraft is limited to latitudes between N730 and 860o, unless magnetic variation is manually entered by the flight crew. 7. When using VNAV, the Altimeter on each pilot's panel must be used as the altitude reference for all operations. 8. ' Fuel display parameters are advisory only and do not replace primary fuel quantity or fuel flow gauges for fuel load and range planning. SECTION III - EMERGENCY PROCEDURES NO CHANGE TO AFM. Date: NC V 8 2004 Rev. 0 7 4 Page 5 ors SDNY_GM_02759707 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246629 EFTA01331092

Banyan Alr Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 SECTION IIIA - ABNORMAL PROCEDURES 1. If 'GPS RAIM' becomes unavailable (as indicated by a Message and 'GPS INTEG' (amber annunciation), continue navigating using the GPS equipment or revert to an alternate means of navigation appropriate to the route and phase of flight, as necessary. When continuing to use GPS navigation, position should be verified every fifteen minutes using another IFR-approved navigation system. 2. Should an FMS system component fail, in most cases the CDU will go blank or the 'FMS MSG' light will flash. Depressing the MSG key will display the Message Page, which will indicate the component which has failed. 3. If sensor information is intermittent or lost, utilize remaining operational navigation equipment as required. 3. The FMS and associated components are protected by the following circuit breakers: C/B Name Amos Location Bus FMS No. 1 5 Pilot 28VDC Avionics Bus No. 1 (Triple-Fed) FMS No. 2 5 Copilot 28VDC Avionics Bus No. 2 (L GEN) FMS DTU 1 Pilot 28VDC Avionics Bus No. 1 (Triple-Fed) SECTION IV - NORMAL PROCEDURES 1. OPERATION Normal operating procedures are outlined in the FMS Operator's Manual, Report No. 2423sv802/902. 2. NAVIGATION DATABASE VERIFICATION. After power-on self tests have been completed, the INITIALIZATION page will appear. The term 'NAV DATABASE EXPIRES' followed by a date will be displayed. If the actual date is later than that which is displayed, the FMS will notify the pilot with a 'DATABASE EXPIRED'-message. Refer to the Operator's Manual for navigation database update instructions. 3. SYSTEM ANNUNCIATORS Each FMS has the following annunciations presented on the Universal Electronic Flight Instrument (EFI) displays (refer to the EFI Operator's Manual, as applicable) : MSG Illuminates and flashes in conjunction with the CDU to indicate a message is to be acknowledged on the MESSAGE page. SXTK Illuminates to indicate that selected crosstrack is active. FHDG Illuminates to indicate that the FMS is in Heading sub-mode. APPR Illuminates to indicate that an Approach has been activated. GPS INTEG Illuminates to indicate GPS Integrity is outside of the allowable limit for phase of flight (2.0nm En Route, 1.0 nm Terminal and Approach transition, and 0.3 nm Final Approach segment). NOV 8 2004 Date: Rev. 0 Page 6 of 9 SDNY_GM_02759708 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246630 EFTA01331093

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 SECTION IV - NORMAL PROCEDURES (cont) 4. AIRCRAFT INTEGRATION a. Universal Avionics EFI display of FMS information Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 1) FMS information is displayed on the Universal Electronic Flight Instrument (ER) displays. The associated EFI Control Panel provides control of each display. See the appropriate Operator's Manual, as applicable, for each EFI display system. 2) Lateral deviation display scaling meets with requirements of TSO C129a and AC 20-130A (5.0 nm full scale for En Route, 1.0 nm for Terminal operations, and 0.3 nm for Approach operations). 3) b. En Route and Terminal Area Flight Control System Operation 1) With 'FMS'-mode selected by using the EFI Control Panel, the respective FMS information can be presented as Flight Director steering commands by pressing the [NAV] button of the FCP-65 Flight Control Panel. 2) With reasonable navigation data being displayed, the steering information can be Autopilot-coupled, to the pilot's or copilot's Flight Director system, by pressing the 'AP ENGAGE' - button on the APP-65A Autopilot Control Panel. c. Approach Operations NOTE: ILS approaches can be retrieved from the Jeppesen database and linked to the flight plan, but cannot be armed or activated as FMS approaches. The FMS can be used to provide navigation up to the final approach course, at which point the EFI must be changed to display raw ILS data which can be coupled to the Flight Control System (FCS). NOTE: GPS will remain selected for GPS and CPS-overlay approved approaches from the navigation database, as well as pilot-defined VFR approaches. Refer to Operator's Manual, Section V, Approach Procedures. Date: NOV 8 2000 Rev. 0 ):11Y, Page 7 of 9 SDNY GM 02759709 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024663 I EFTA01331094

Banyan Air Service Flight Manual Supplement Avionics Division UNS-1D+ FMS 1635 NW 51st Place N908JE BOEING 20115 Ft. Lauderdale, FL 33309 SECTION IV - NORMAL PROCEDURES (cont) c. Approach Operations (cont.) LOC, I3/C, GPS, NDB, RNAV, VOR, VOR/DME, and VFR approaches may be linked into the flight plan and then laterally and vertically coupled to the FCS as follows: 1) Approach Transition: When an entire approach transition (e.g., procedure turn, DME arc, etc.) is to be flown, first arm the approach on the FMS (ARM APPR). If the FMS is not armed manually it will arm automatically at 30nm from the airport. With the desired DIRECT TO or FROM/TO Waypoints selected, or the desired FMS Heading selected with INTERCEPT ACTIVE, select FCS 'NAY- mode by pressing the [NAV] button of the appropriate FCP-65 Flight Control Panel. When the FMS . has automatically activated the approach, denoted by the 'APPR' annunciator displayed in the associated EFI display, press the [APPR) button of the Flight Control Panel. When the FCS has captured the "APPR" — mode, a white "VNAV" will appear on the PFD and a white VN on the ADI signifying the 'arming' of the VNAV mode. The "VNAV- and 'VN" annunciation will turn to green in color when the FCS has captured the VNAV glideslope. See the EFI operator's manual for specific display annunciations. Continue monitoring both lateral and vertical deviations throughout the duration of the approach. If required, initiate 'Missed Approach Procedures' as described in the Universal Avionics Operator's Manual. 2) Heading Vectors: If given heading vectors by ATC to the final approach course, manually activate the approach on FMS NAV page 1/3. The FMS will enter the 'FHDG" mode, the EFI display will now display final approach course data, and the INTERCEPT prompt on Nav page 1/3 will be active. When cleared to intercept final, press the INTERCEPT line select key to intercept final. Ensure that commanded heading mode is canceled. Select [APPR) on the FCS Flight Control Panel to capture and track the final approach lateral and vertical information. NOTE: Guidance is provided to the runway threshold or missed approach point. It is the pilot's responsibility to level out at MDA if the runway environment is not in sight. Date: Rev. 0 NOV 8 2004 • Page 8 of 9 SDNY_GM_02759710 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246632 EFTA01331095

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale. FL 33309 SECTION IV - NORMAL PROCEDURES (cont) Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 3) Press the APP-65A Autopilot Control Panel [AP ENG]-button to couple the AP to the selected FD. The Autopilot will track pseudo-Localizer and pseudo-Glidesbpe signals from the FMS. b. Advanced Approach Operations 1) Advanced approaches may be identified in the data base by the prefix "A° to the approach listed in the 'ARRIVAL' page and in the navigation data base They are characterized by course changes on the final approach segment of greater than 6 degrees and/or having multiple flight path angles. To avoid excessive deviations from course and flight path, these approaches may need to be flown in FCS [NAV) mode until on the final leg of the approach. Select FCS (APPR] sequencing the final waypoint to engage vertically. c. Vertical Navigation 1) Vertical Navigation (VNAV) information is displayed on the EFI display and is available for enroute, terminal or approach descents. Pitch steering commands for enroute and terminal VNAV operations are not provided to the Flight Control System. SECTION V - PERFORMANCE DATA NO CHANGE TO AFM. Date: NOV 8 2004 Rev. 0 Rage 9 of 9 SONY_GM_02759711 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246633 EFTA01331096

coos SDNY_GM_02759712 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246634 EFTA01331097

C . US Department MAJOR REPAIR AND ALTERATION Ot Transportation Anon (Airframe, Powerplant, Propeller, or Appliance) kelaton AOrrinistration Form Approved OMB No. 2120-0020 For FAA Use Only Office Identificabon INSTRUCTIONS: Print Print or type all entries. See FAR 43.9, FAR 43 Appendix B. and AC43.9-1 (or subsequent evision thereof) for instructions and ...a i disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can resutt in a civil penally not to exceed 51.000 for each such. violation (Section 901 Federal Aviation Act of 1958} 1 -71 : 11. Alreraft Make Boeing Model 727-100 Serial No. 20115 Nationality and Registration Mark USA N908JE i i2. Owner Name (As shown on registration certificate) J.E.G.E. Inc. Address (as Mown on registration certificate) .. 103 Foulk Road STE 202 Wfirringlon, DE. 19803-3742 3. For FAA Use Only Tr, data denoted .x...24 tz, M ilt: rsortilints racluirement• il desentood real subfoct =Say bf • person wrerizea tr. FAR C. al. OCT I 9 7004 ,A, , 5° - Fs Do-17 ggMsnFMbUQS Os I 4. Unit Identify atb 5. Type Unit Make Model Serial No. Repak Alteration 1 . ? , AIRFRAME '"•"--'---(As described in Item 1 above)^•^•^---^rrear *"si POWERPLANT .i ffPROPELLER r APPLIANCE Type •• Manufacturer 8. Conformity Statement A. Agency's Name and Address B. Kind of AgenCY C. Certificate No. BANYAN AIR SERVICE u S Certificated Mechanic AVIONICS DIVISION Foreign Certificatedmechanic SD4R514M Ftadio Class 1,2,3 1635 NW 51st Place ra Certificated Repair Station Limited Airframe Ft. Lauderdale, FL 33309 Manufacturer D. I Certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been. made In accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein Is true and correct to the best cdnY knoMedge. ' Date ty,) ; a vg. se ,..200 %zr frf die Signature of A=arral 6,2 zado, _ , .A. 'r-- . Steve Gluellette• . 7. Approval for Return to Sera* • 'pursuant to the authority given persorts specified below, the unit identified in item 4 was Inspected in the manner prescribed by the Administrator or to& Federal Aviation Administration and is APPROVED O REJECTED :Ety FAA Fit. Standards Inspector Manufacturer Inspection Authorization Other (Specify) ..t- FAA Designee X Repair Stadal Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection /9 AA4,041/1"X. a ct / • Certificate or Designation No. SD4R314M Signature of Au U I ' I Stave Ousileili FAA Form 337 (124e) SDNY_GM_02759713 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246635 EFTA01331098

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be ...,ompatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. I ra. Description of Work Accomplished 1 id more space ls required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed) The purpose of this 337 is for the work performed on N908JE undo Banyan Air Service, Avionics • Division work order #68062. A. Installed an Artex ELT406-2Hivl per Artex installation document number 570.5000, Rev. A, dated 12/10/02 mounted in unpressurized aft compartment. The antenna is mounted in the aft tail section. A remote switch is mounted in cockpit in the copilot's insrtument panel. An aural activation monitor is mount within the vacinity of the ELT per the installation document listed above. • B. The above installation WaikkiredinIceordancemith AC43.13-1B, Chapter 7, sections 1-5, AC43.13-1B Chapter 11, sections 3-17, AC43.13:2A Chapter 1, AC43.13-2A Chapter 2, paragraphs 24, 25, an—d78;76-C43:T3,-2ATChapter 3; paragraph 38 and the aircraft's maintenance manual. C. A functional test of the above equipment has been performed FAR25.1309 and FAR25 .1431 for proper operation and did not adversely affect any other aircraft systems. An electrical load analysis was conducted and it was confirmed that this installation would not exceed 80% of the generator output. D. A log book entry and equipment list was generated to reflect the above installation. No Weight and balance was generated as the aircraft was weighed. E. Instructions for continued airworthiness is a battery due time change. This due date is reflected on the log book entry. Annual inspection is required per FAR 91-207 (d). END 0 Additional Sheets am Attached SDNY_GM_02759714 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246636 EFTA01331099

a us Drotirtintira MAJOR REPAIR AND ALTERATION or Trareportran (Airframe, Powerplant, Propeller, or Appliance) Fedani Artiftil Aterdnisinakm Form Approved OMB No. 2120-0020 For FAA Use Only office Idenb5cabon . INSTRUCTIONS: Print or type al entries. See FAR 43.9, FAR 43 Appendix B. and AC43.9-1 (or subsequent °vision thereof) for instructions and ;disposition of this tone. This report S required by law (49 U.S.C. 1421). Failure to report can result Ma civil penalty not to exceed 51.000 for each such. iiridation (Section 901 Federal Aviation Act of 1958). it. Aircraft Make Boeing Model 727-100 Serial No. 20155 Nationality and RegStration Mark ii USA N9081E • 2. Owner Name (As shown on legislation certificate) J.E.G.E. Inc. ' Address (as shown on ripiStration certificate) • 103 Fouls Road, Ste 202 Wilmington. OE. 19803-3742 3. For FAA Use Only Tn-, data elcnbatil canoes the Waage° at mammas is for the Move by • elniOn described Octet corionnity iri FAR 4.1, 43.T NO0uthar2004 -r-svo-f 7 Mee 4. Unit IdentifIcatc 5 Type Unit Make Model Serial No. Rep* AllareUdl .' 'AIRFRAME CI (As described In Item 1 above . POWERPLANT . i PROPELLER APPLIANCE Type Manufacturer t Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. BANYAN AIR SERVICE AVIONICS DIVISION 1635 NW 51st Place Ft. Lauderdale, FL 33309 U.S. Certificated Mechanic SOIR514M Radio Class 1,2.3 Foreign Certificated Mechanic 0 Certificated Repair Station Limited Aidrame Manufacturer 0.1certify that the repair and/or alteration made to the unit(s) identified in tern 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the Information furnished herein is true and correct to the best of my knowtedge. Date I .44.05.466-4 ,,,,74/09- Signature of rodi c..._ Steve Ouellette 7. Approval for Return to Service Pursuant Feder to the authority given persons s I Aviation Administration and is below, the unit Identified in Item 4 was inspected in the manner prescribed by the Administrator of the APPROVED Q REJECTED BY FAA Flt. Standards inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Ainvorthiness Group Date cf Approval cc Rejection /9 j (4gs , see e e . - 2 2 , / Certificate or Designation No. SD4R514M Signature of Authorized Indi ' ual Steve Ouellette FAA Fenn 337 (12-88) SDNY_GM_02759715 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246637 EFTA01331100

NOTICE Weight and balance or operating limitation changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 0. Description of Work Accomplished al more space is required, attach additional sheets. ideMily with aircraft nationality and registration mark and dale work completed) The purpose of this 337 is for the FAA approval of the new flight manual supplement on N908JE under Banyan Air Servive, Avionics Division work order #68062. A. Removed existing UNS-1D Flight Management System (FMS) control display/computer units and routed to the manufacture for upgrade to UNS-1D+. Reinstalled UNS-1D+ FMS CDU computers. System ground checked good. B. A flight manual supplement has been generated, approved and incorportated into the existing flight manual. A weight & balance and equipment list update are not required. END .z. vum 44.3 akcpc,A PIP i.S70 O Additional Sheets are Attached SDNY_GM_02759716 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 I EFTA_00246638 EFTA01331101

NOV. 8.2004 9:50AM PYKA AEROSPACE NO. 2146 P. 3 Doc. No. 7280-FM-001, Rev A Issue 092401 S.I.P. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 TAWS System AFM Supplement for Boeing 727-100 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT UNIVERSAL AVIONICS TERRAIN AWARENESS WARNING SYSTEM (TAWS) AIRPLANE MAKE: BOEING AIRPLANE MODEL: 727-100 AIRPLANE SERIAL NO.: /1/7013—C REGISTRATION NO.: (-90 //6" This supplement must be attached to the FAA Approved Airplane Flight Manual when the airplane is modified by the installation of a Universal Avionics Terrain Awareness Warning System (TAWS) in accordance with FAA STC number ST09951SC. The information contained herein supplements or supersedes the basic Airplane Flight Manual only in those areas listed herein. For limitations, procedures, and performance information not contained in this document, consult the basic Airplane Flight Manuel APPROVED: 1--f-1,/gern yR S. Frances Cox, Manager Special Certification Office Federal Aviation Administration Ft. Worth, Texas 76193-0190 DATE October 25, 2004 Page 1 of 9 SDNY_GM_02759717 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246639 EFTA01331102

SDNY_GM_02759718 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246640 EFTA01331103

NOV. 14 4 Doc. No. 7280-FM-001, Rev A Issue 092401 Si.?. Technical Services Inc 10107 McAllister Freeway San Antonio, pc 76216 LOG OF REVISIONS TAWS System AFM Supplement for Boeing 727.100 REv, DESCRIPTION REVISED PAGES APPRD. By DATE IR New supplement All S. Frances Cox 12-13-2002 A Allow use of CDU or MFD display. Format and editorial corrections throughout. All See cover page 10.25.2004 FAA APPROVED Date: October 25, 2004 Page 2 of 9 SDNY_GM_02759719 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024664I EFTA01331104

i SDNY_GM_02759720 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246642 EFTA01331105

NOV. 8. t 4 9: 1A/1, 'YKA A A NI. i4 Doc. No. 7280-FM-001, Rev A Issue 092401 S.I.P. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 TABLE OF CONTENTS SECTION PAGE SECTION I - GENERAL 4 SECTION II - LIMITATIONS 4 SECTION III — NORMAL PROCEDURES 5 1. Operation 2. Cold Temperature Operations 5 3. Systems Test S 4. Pop-Up Terrain Display 6 5. System Anntmciators 7 SECTION IV — EMERGENCY/ABNORMAL PROCEDURES 9 EMERGENCY PROCEDURES 9 ABNORMAL PROCEDURES 9 1. Circuit Breakers 9 2. Use of TERR INHIBIT switch 9 3. Response to TAWS Warnings 9 4. Response to Glideslope Deviation Alerts 9 5. Use of Flap Override Switch 10 SECTION V - PERFORMANCE 10 SECTION VI - WEIGHT AM) BALANCE 10 TAWS System AFM Supplement for Boeing 727-100 FAA APPROVED Date: October 25, 2004 Page 3 of 9 SDNY_GM_02759721 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFFA_00246643 EFTA01331106

SDNY_GM_02759722 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246644 EFTA01331107

MK 8.2004 0:514.M PYKA AEROSPACE h0. 2146 6 Doe. No. 7280-FM-001, Rev A Issue 092401 S.I.P. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 SECTION - GENERAL TAWS System AFM Supplement for Boeing 727-100 This Supplement provides general information for the Enhanced Ground Proximity Warning System installation. The aircraft is equipped with a Universal Avionics TAWS system. The system uses inputs from the air data computer No. 1, navigation receiver No. 1, radio altimeter, and the Universal Avionics UNS-1 Flight Management System (FMS) , and an internal terrain database to provide basic GPWS alerts and terrain alerts The TAWS alerts provide the crew with aural and visual indications of possible inadvertent flight into terrain. TAWS alerts are generated if one or a combination of the airplane's: 1) vertical speed, 2) rate of closure to terrain, 3) accumulated altitude loss, 4) airspeed, flap and /or gear configurations or 5) glideslope deviation is unsafe given the airplane's radar altitude and phase of flight. Terrain alerts are generated by comparing aircraft position and altitude to the EGPWS terrain database. This system also provides "Flight Plan Look Ahead" terrain alerts and warnings by comparing the FMS flight plan to the terrain database SECTION II — LIMITATIONS The TAWS display will be used for situational awareness only. Navigation must not be predicated upon the use of the TAWS. The 3-D view provides no amuck information. To avoid giving unwanted terrain alerts, the TAWS terrain alerts must be inhibited by pressing the TERR INHIEI switch when landing at airports that are not included in the airport database or when landing at an airport other than the airport in the FMS flight plan. Deviation from Aix Traffic Control Clearances is authorized to the extent necessary to comply with TAWS warning. The use of terrain awareness warning and terrain display function is prohibited during QFE operations. The current local altimeter setting must be entered in the pilot's altimeter for proper terrain alerting. The TAWS database and alerting algorithms do not account for man made obstructions FAA APPROVED Date: October 25, 2004 Page 4 of 9 SDNY_GM_02759723 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246645 EFTA01331108

SDNY_GM_02759724 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246646 EFTA01331109

NOY. 8.2004 3'514M PYKA AEROSPACE NO. 214 6 Doc. No. 7280-FM-001, Rev A Issue 092401 S.I.P. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 TAWS System AFM Supplement for Boeing 727-100 SECTION III — NORMAL PROCEDURES I. Operation All aircraft crew interface is conducted through the Universal Avionics display, either multi- function display (MFD) or FMS control display unit (CD11), end system annunciator switches. TAWS terrain information may be presented on either an MTID or a CDU. The TAWS requires inputs from the following systems, radio altimeter, air data computer, VHF navigation receiver, FMS, gear position and flap position. 2. Cold Temperature Operations TAWS uses baro-corrected altitude as the reference for Fonvansd Looking Terrain Alerts (FLTA). TAWS does NOT compensate the baro altitude input for non-standard temperature lapse rates that may be encountered in extreme cold conditions, causing degraded FLTA operation. Basic ground proximity warning modes (1 through 6), as well as Premature Descent Alen (PDA), are radio altitude based and not affected. In extreme cold conditions, the aircraft will be operating at a lower altitude than indicated, thus resulting in TAWS alerts being delayed or missing. The color-banding on the TAWS display will be offset by the cold temperature altitude error. When operating into and out of airports where cold temperatures exist, the aew should be aware of the difference between the indicated baro altitude and the true altitude and the effect this has on FLTA and the terrain display. To determine the effect on FLTA warnings consult the Airman's information Manual Chapter 7 paragraphs 7.2.3d and 7-2-3e. 3. System Tests BUILT IN TEST TAWS has a Built-In-Test (BIT) function which includes Power-Up Self Tests, Initiated Tests and Continuous Tests. Where there has been degradation in capabilities that result in TAWS being unavailable, BIT annunciates the fact to the flight crew via a GPWS FAR. or TERR MOP Lamp. PRE-FLIGHT TESTS A TAWS Self Test should be conducted prior to each flight. Momentarily press the GPWS TEST annunciator. The following indications confirm proper TAWS operation: PULL-UP Annunciator Illuminated TERR Annunciator ➢luminated BELOW G/S Annunciator ➢luminated G/S INHIBIT Annunciator Illuminated TERR INHIBIT Annunciator Illuminated FAA APPROVED Date: October 25, 2004 Page 5 of 9 SDNY_GM_02759725 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246647 EFTA01331110

SDNY_GM_02759726 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246648 EFTA01331111

hil4. 4.2404 • PYKA AEROSih.E Doc. No. 7280-1 (it , Rev A Issue 092401 S.I.P. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 SECTION IIT — NORMAL PROCEDURES iCcatinuedi GPWS FAIL Annunciator GPWS TFST Annunciator illuminated Illuminated NO.2146 P. 8 TAWS Terrain Display Test Image (Colored Bars) Awe! Amtunciarions "TERRAIN, TERRAIN" "PULL UP, PULL UP" "DON'T SThlE" "SINK RATE" "GUDESLOPE" "TOO LOW TERRAIN" "TOO LOW GEAR" "TOO LOW FLAPS" "ME HUNDRED" TAWS System AFM Supplement for Boeing 727-100 Once the test is complete, TAWS will reboot During this time the Greys FAIL and TERR INOP annunciators will remain lit and a TAWS FAIL message will be generated on the MFD until the system is operational. (approx one min) NOTE: As a result of pressing the GPWS TEST annunciator again within five seconds of initiating this test, the test will canal and the TAWS computer will continue to operate without rebooting. 4. Pop-Up Terrain Display In the event of terrain alert, the map view of the TAWS display will "pop-up" on the MFD or CD1J. Pressing any function key on the display will remove the pop-up and revert to the selected display function. Prospective terrain conflicts are depicted by a star shaped Terrain Threat Symbol. Both Warnings and Cautions are annunciate(' with this symbol. Terrain warnings are a flashing red symbol while Terrain cautions are depicted by a flashing yellow symbol. Terrain threats along the flight plan are depicted by a white symbol and represent the predicted first point of conflict between the flight plan and terrain RED threat "stars" on the TAWS display indicate a Terrain Alert (30-second wanting). YELLOW threat "stars" on the TAWS display indicate a Terrain Caution(60-second waning). FAA APPROVED Date: October 25, 2004 Page 6 of 9 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 91101 SONY_GkL02759727 15, and 17 EFTA_00246640 EFTA01331112

sj SDNYGM02759728 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246650 EFTA01331113

NOV. 8.2004 9:52AM PYKA AEROSPACE ti0 2146—P. 9 Doc. No. 7280-FM-001, Rev A Issue 092401 S.I.P. Technical Services Inc 10107 McAllister Freeway San Antonio, TX 78216 sEall)N III - NORMAL PROCEDURES1Coneinaedi TAWS System AFM Supplement for Boeing 727.100 WHITE advisory alert " stars" on the TAWS display indicate a flight plan terrain conflict. These alerts are annunciated by a "star" on the display shortly after a VNAV altitude is entered into the flight plan or when a procedure (STAR or approach) containing altitudes is linked to the flight plan Flight plan terrain advisories do not require immediate action but indicate that adhering to the flight plan as entered will cause a future terrain alert. Waypoints and altitudes should be checked for accuracy. 5. System Annunciators The following system annunciators are provided for the system; A. PULL UP Red PULL UP annunciators are located on the Captain's and First Officer's instrument panel. This annunciator illuminates whenever TAWS has detected terrain in the aircraft's immediate flight path The annunciator will remain illuminated until the terrain has been cleared. Aural annunciations of "TERRAIN, TERRAIN, PULL UP" or "PULL UP, PULL UP" are also provided whenever the red PULL UP annunciator illuminates. B. BELOW GS Amber BELOW GS annunciators are located on the Captain's and First Officer's instrument panel. This armtmciator illuminates on approach whenever the TAWS has detected that the aircraft is at least 1.3 dots below the glideslope. This annunciator remains illuminated until the aircraft has returned to within less than one dot of the glideslope. Aural warnings of "GLIDESLOPE-GLIDESLOPE-GLIDESLOPE" sound until the aircraft has returned to within less than one dot below the glidepath The aural annunciation may be canceled by pressing the BELOW GS anntraciator/switch. However, the BELOW GS annunciators will remain illuminated. If the aircraft goes below the glideslope after the aural warning and light annunciation has gone out, the light and aural warning will again sound. C. GPWS FAIL Amber GPWS FAIL annunciators are located on the Captain's and First Officer's instrument panel. This annunciator illuminates if the TAWS has failed. FAA APPROVED Date: October 25, 2004 Page 7 of 9 SONY GM_027 59729 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFM_00246651 EFTA01331114

SDNY_GM_02759730 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246652 EFTA01331115

NOV. 8.2004 9:53AM PYKA AEROSPACE NO. 2146 P. 10 Doc. No. 7280-FM-001, Rev A Issue 092401 S.I.P. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 SECTIONH7 - NORMAL PROCEDURESiContinuedi D. GPWS TEST TAWS System AFM Supplement for Boeing 727-100 GPWS TEST switches are located on the Captain's and First Officer's instrument panel shared with the GPWS FAIL annunciator. This switch is utilized to perform a self-test of the TAWS system. E. TERR Amber TERR annunciators are located on the Captain's and First Officer's instrument panel. The "TERRAIN, TERRAIN" aural warning paired with a visual alert is indication of reduced terrain clearance. F. TERR INOP Amber TERR LNOP annunciators are located on the Captain's and First Officer's instrument panel. This annunciator illuminates when the terrain function is inhibited by TERR INHIB switch, terrain datah.lte is invalid or failed, terrain alert function is inoperative due to hardware failure or lack of a required input such as position or altitude. G. TERR LNILIB Blue TERR INHIB annunciator/switch is located on the Captain's instrument panel adjacent to the TERR INOP annunicator. This annunciator/switch is illuminated white visible only when the TERR INHIB is active. FAA APPROVED Date: October 25, 2004 Page 8 of 9 SDNY_GM_02759731 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246653 EFTA01331116

SDNY_GM_02759732 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246654 EFTA01331117

NOv. 8.2004 9:530. PYKA AEROSPACE NO. 2146—P. 11 Doc. No. 7280-FM-001, Rev A Issue 092401 S.1.P. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 SECTION IV -EMERGENCY/ABNORMAL PROCEDURES EMERGENCY PROCEDURES No change to basic Airplane Flight Manual ABNORMAL PROCEDURES TAWS System AFM Supplement for Boeing 727-100 1. Circuit Breakers The TAWS system is protected by the following trip-free circuit breakers: NAME JACATION AMPS BUS GPWS P-18 5 28 VDC Ess. 2. Use of TERR INB1B switch. The Terrain Awareness Display inhibit switch (TERR WHIR) must be placed in the INHIB position in the following conditions: 1-Whenever the FMS in the Dead Reckoning (DR) mode 2-Within 15 nrn of approach or landing at an airport not contained in the TAWS database. NOTE: When an off airport landing is required the FLTA and PDA functions should be inhibited by activation of the TEAR INHIB switch. 3. Response to TAWS Warnings When an aural 'TERRAIN, TERRAIN, PULL UP" or a red PULL UP warning light annunciates, execute a positive pull up maneuver, apply maximum rated thrust, and ascend to at least the best climb angle until the warning ceases. Notify ATC if action requires deviation of ATC cleared flight plan. When an aural "CAUTION TERRAIN", "TOO LOW TERRAIN," "SINICRATE" "DONT SINK," "'TOO LOW FLAPS" or 'TOO LOW GEAR" caution annunciates, initiate corrective action to remove the cause of the warning. 4. Response to Glideslope Deviation Alerts When the BELOW GS annunciator illuminates and an aural "GLIDESLOPE" annunciation alert occurs, initiate corrective action to fly the airplane back to the glideslope centerline. To inhibit the "GLIDESLOPE" annunciation on back course approaches, select the BELOW GS warning light/switch. The glideslope inhibit function is only available below 2000 ft AOL when the BELOW GS annunciator illuminates. FAA APPROVED Date: October 25, 2004 Page 9 of 9 SDNYGPA02759733 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246655 EFTA01331118

SDNY_GM_02759734 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246656 EFTA01331119

NOV. 8. 2004 9:530 FYKA AF.;O5:1ACi. NC. [ <16 12 Doc. No. 728O-FM-OO1, Rev A Issue O924O1 S.I.F. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 TAWS System AFM Supplement for Boeing 727-1OO SECTION IV — EMERGENCY/ABNORMAL PROCEDURES (Continued) 5. Use of Flap Override Switch When landing with less than normal flaps, the FLAP OVERRIDE switch should be usesd to prevent the `TOO LOW FLAPS" turn] annunciation. SECTION V - PERFORMANCE No change to basic Airplane Flight Manual. SECTION VT - WEIGHT AND BALANCE Refer to applicable weight and balance document. FAA APPROVED Date: October 25, 2OO4 Page 10 of 9 SDNY_GM_02759735 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246657 EFTA01331120

SDNY GM 02759736 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246658 EFTA01331121

0 MAJOR REPAIR AND ALTERATION al instsatiktn (Airframe, Powerplant, Propeller, or Appliance) resew mtrallOn emo AtImbilll Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification .51, - r-s pc, - /7 INSTRUCTIONS: and disposition 81.000for each Rim or type all entries. See FAR 43.9 Appendix B, and AC 419-1 (or subsequent revision thereof) tor' of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make BOEING Model 727.31 Serial No. 20115 Nationality and Registration Mark U.S.A. N908.1E 2. Owner Name (As shown on registration certificate) JEGE INC Address (As shown on registration certificate) 103 FOULK RD STE 202 WILMINGTON DE 19803-3742 3. For FAA Use Only 4. Unit Identification 5. Type UM Make Model Serial No. Repair Alteration AIRFRAME As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A Agency& Name and Address B. Kmd of Agency C. Certificate No. JET AVIATION ASSOCIATES LTD. 1515 PERIMETER RD. WEST PALM BEACH. FL 33406 U.S. Certified Mechanic CRS EYKR782D AIRFRAME 1,3. RADIO 1,2,3. LIMITED A/F &ENG Foreign Certified Mechanic T i c Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unh( ) idenfilied in item 4 above and have been made in accordance with the requirements of Pan 43 of tine and that e U.S. Federal Aviation on 11! reverse A \attachments hereto ' information furnished herein is (rue and correct to the best of my knotiledge. Date 6/12/02 Signature of Authorized Individual 1 Christoptia Hoeseuorth Inspector. , 7. Approval for Return to Service \ Pursuant Admini BY . to the authority given persons specified below, the unit dentilied in item 4 was inst3ected m the bY6 trator of the Federal Aviation Administration and is 0 APPROVED 0 REJECTED FAA R. Standards Inspector Manufacturer Inspection Authorization Other (Spear) FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Refection 6/12/02 Certificate or Designation No. EYKR782D Signature of Authorized Individual k ' John K. Urso. Inspector., -;l" , -: L us` I ' 6 FAA Form 337 risen / SDNY_GM_027 59737 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246659 EFTA01331122

rr NOTICE Weight and balance or operating lirritation donor* shall be entered in the appropriate aircraft record. An alteration must be soaped :de with all previous alterations to assure continued conformity wIth the applicable altwortNness requirements. 8. Description of Work Accomplished (If more space Is required. attach additional sheers, Identify with aircraft nationality and registratim mark and date work accomplished) N9081E. BOEING 727-31, S/N 20115. W.O. 18046 REFERENCE F.A.A. FORM 337 DATED 7/2A)1 INSTALLING A UNIVERSAL AVIONICS CORP. UNS-I 19 FLIGHT MANAGEMENT SYSTEMS (FMS) WITH INTEGRAL GPS SENSORS. RECONFIGURED AIRCRAFT WIRING TO PROVIDE V-NAV DISPLAY INFORMATION ONLY. FROM THE EXISTING a 1 AND it 2 UNS-I D FLIGHT MANAGEMENT SYSTEMS. MS MODIFICATION AS ACCOMPLISHED PER THE FOLLOWING JET AVIATION DRAWINGS. WHICH ARE SUBSTANTIATED BY FAA FROM 8110-3 RESPECTIVELY: WIRING DRAWINGS. • BM-16236-410, REV A. DATEDawe SHEETS I THRU 5. TITLED - NO. I FLIGHT MANAGEMENT SYSTEM. • B727-16236.411. REV A, DATED/1/16/0Z SHEETS I THEW 5.1TfLED - NO. 2 FLIGHT MANAGEMENT SYSTEM. REFERENCE F.A.A. FORM 8110-3 DATED 4/19/02 BY SYSTEMS AND EQUIPMENT DER NO. DERT510087-NM. ACCOMPLISHED OPERATIONAL CHECKS PER UNIVERSAL AVIONICS CORP. RETURN TO SERVICE MAINTENANCE AND CHECKOUT PROCEDURES MANUAL NO. 34-60-21. DATED 19 MARCH 200) writ NO DISCREPANCIES NOTED. AN EMI TEST. REPORT NO.: 8727.16236-080 REV IR. SHEETS I OF 5. DATED 06/19/2001. WAS CONDUCTED AND THE INSTALLED EQUIPMENT DOES NOT INTERFERE WITH ANY CANER INSTALLED EQUIPMENT. MAGNETIC DIRECTION INDICATORS WERE CHECKED FOR ACCURACY AND COMPENSATED AS NECESSARY PER AC 43.13- I II, CHAPTER 12. SECTION 3, PARAGRAPH 12- 37 AND AC 43.I3-2A. CHAPTER 2 PARAGRAPH 23f. A LOGBOOK ENTRY REFLECTING THIS INSTALLATION WAS COMPLETED PER FAR. 43.9 AND ENTERED INTO THE AIRCRAFT LOGBOOK. THE REQUIRED F.A.A. APPROVED FLIGHT MANUAL SUPPLEMENT DOC NUMBER B727-16236100, REV A. SHEETS 1 THRU 9. DATED 5/8/02 HAS BEEN INSERTED INTO THE AIRCRAFT FLIGHT MANUAL END K Additional Sheets Are Attached * U.S. G.P.O 1990-761-753 SDNY_GM_02759738 - SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246660 EFTA01331123

Apr -19-02 08:08A N 3 Curran 352 243 1011 P . 02 DEPARTMENT OF 11LAREP0RTAT ION FEDERAL AVIATION ADMDFISTRATI0N STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE Apri119, 2002 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Boeing MODEL NO. 727-31 TYPE (Airplane. Radio. NA:copier. <IC) Airplane NAMEOF APPLICANT Jet Aviation Associates West Palm Beach, FL UST OF DATA IDENTIFICATION TITLE 8727.16236410, Revision A, dated April 16, 2002 0727.16236.411, Revision A. dated April 16, 2002 NO. 1 FLIGHT MANAGEMENT SYSTEM NO. 2 FLIGHT MANAGEMENT SYSTEM PURPOSE OF DATA in support of major alteration to Boeing 727-31. serial number 20115, registration number N9OSJE. APPLICABLE REQUIREMENTS (List specific sections) CFR TITLE 14. CHAPTER 1, SUBCHAPTER C FAR 25.681 (a)(b)(1) FAR 26.1329 (h) FAR 25.1529 FAR 25.869 (a)(4) FAR 25.1351 (a) FAR 25.1581 (a)(b)(d) FAR 25.1301 (a)(b)(c)(d) FAR 25.1367 (a)(c)(d)(e) FAR 25.1309 (a)(b)(c)(d)(e)(g) FAR 26.1381 (a)(b) FAR 26.1322 (b)(c) FAR 25.1431 (aKb)(c) CERTIFICATION - u..........rn ........ st feecciWe tia WM ant ad co sinthed YIN enacted NOM In. dd. A4LE.L.ARRER4 inconte...eD ...s• L no I...RR. RE oflacasto ...D.P." bin ma'am' is monism. Rub alablitbed procedens obiCowed ft amply' nii animal. dem & Eq.Ipmat REPK0'. DaliK APPreval thily. Dom NM COMOIDR Me( 41. Fete A..... 141.4 .••••• retektanet day rs., Afloat. lesiollAtios Appretsh KflaaAn 0 Rwomtnegid appnwsl .thew I W) Therefore ILI Appnn that data (Spleen tiGNAT1nt 'MGM CO EI RIPIRESOCCAlinai OCSIGNATIOM HUMIICINCCI CLASSOICATI0Nis• L. _ie./A__ DERT-510087-NIYI Systems & Equipment No an J. an FAA Form /*P0) sun/LS/DES PRZYIOUSEDmoN GP0001-433FIENAME30727414CREYADOC SDNY_GM_02759739 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024()661 EFTA01331124

SDNY_GM_02759740 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246662 EFTA01331125

Jet Aviation Associates Ltd. Bldg. 1515 Perimeter Rd. Palm Beach Intel Airport West Palm Beach, FL 33406 FAA CRS EYKR782D Document No. B727-16236-100 AFM Supplement to The Boeing Company 727-31 Serial No. 20115 FAA Form 337 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BOEING 727-31 REGISTRATION NO.: N9013JB SERIAL NO.: 20115 WITH DUAL UNIVERSAL AVIONICS FLIGHT MANAGEMENT SYSTEMS (UNS1-D) INSTALLED This supplement must be attached to the FM approved Airplane Flight Manual when the airplane is modified by the installation of dual Universal Avionics Systems Corp. (UASC) (UNS-1D) Flight Management Systems (FMS), with Frequency Management via a UASC Radio Tuning Unit (RTU), receiving navigation inputs from Triple Honeywell Inertial Reference Sensors (IRS), dual internal GPS sensors, and VORIDME from the Collins No. 1 and No. 2 VORIDME systems in accordance with manufacture's InstalatIon and Checkout Manual No. 34-60-09, Rev. 2, dated August 15, 1997 or later approved revision and FAA Form 337, dated ,f une 26, 2001. The information contained herein supplements or supersedes the basic manual only in those areas listed herein. For limitations, procedures, and performance information not contained in this supplement, consult the appropriate basic Airplane Flight Manual. FAA Approved: 'Or c7 . ' Cif, Federal Aviation Administration Flight Standard District Office -17 1050 Lee Wegener Blvd. Ft. Lauderdale, Florida 33315 FAA Approved Date: June ;1.2001 Revision A. Dated: 5/3 ,:.n> Page 1 of 9 SDNY_GM_02759741 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246663 EFTA01331126

SDNY_GM_027.742 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246664 EFTA01331127

f i g , US Orartrnre of Tansp3rwlon Federal Fede AdenletIstrallon MAJOR REPAIR AND ALTERATION . (Airframe, Powerplant, Propeller, or Appliance) Aviation Form Approved OMB No. 2120-0020 For FAA Use Only Officeldenlifisation , . Eri-k- 1.3U^37 INSTRUCTIONS: and disposition $1,000 Print or type all entries. See FAR 43.9 Appendix B. and AC 43.9-1 (or subseque t revision thereof) for Instructions of this form. This report is required by law (49 U.S.C. 1421). Failure to report can re ult in a civil penalty not to exceed for each such violation (Scotian 901 Federal Aviation Act of 1958). 1. Aircraft Make BOEING Model 727-31 Serial No. 20115 Nationality and Registration Mark U.S.A. N908.TE 2. Owner Name (As shown on registration certificate) JEGE INC. Address (As shown on registration certificate) 103 FOIE-ICRD. STE 2O2 WILMINGTON DE. 19803-3742 3. For FAA Use Only 4. Unit Identification 6. TYPO Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer . 6. Conformity Statement A. Moneys Name and Address B. Kind of Agency C. Certificate No. JET AVIATION ASSOCIATES LTD. 1516 PERIMETER RD. WEST PALM BEACH. FL 33406 U.S. Certified Mechanic CRS EVICR782D AIRFRAME O. RADIO 1,2,3. i METED A/F It ENG Foreign Certified Mechanic x Certificated Repair Station Manufacturer D. I certify have furnished that the repair and/or alteration made to the wafts) identified in item 4 above and described on the reverse or attachments hereto been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information herein is true and COrTett to the best of my knowledge. Date Signature of Authorized Individual 1/14/02 John K. Ursa. Inspector. L44 114.— 7. Approval for Return to Sera Pursuant Administrator BY to the authority given of the Federal Aviation persons specified below, the unit dentilied in item 4 As inspected In the manner prescribed by the Administration and is ig) APPROVED DI REJECTED FAA Fit. Standards Inspector Manufacturer Inspection Authorization Other (Sadly) FM Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection 1/14/02 Certificate or Designation No. EVICR782D Signature of Authorized Individual Ronald K. Bystrom. Manager Quality Assurance. FAA Form 337 (1288) SDNY_GM_02759743 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0O246665 EFTA01331128

NOTICE Weashland balance or operating amitalion changes shall be entered in the appropriate aircraft record An alteration must be compatacfir With al:previous alterations to assure continued contumely with the applicable ainvorthiness requirements. 8. Description of Work Accomplished (If more space is requited, attach adirdonal sheets, Identify with aircraft nationality and mgistration MEM and date note accomplished.) BOEING 727-31, S/N 20115. N908.1E: W/O 17454. ACCOMPLISHED AN ALTERATION TO THE CABIN INTERIOR FURNISHING ARRANGEMENT PREVIOUSLY INSTALLED UNDER PAGE AVJET STC SA3137S0, DATED 1/17/92, BY REMOVING THE FOLLOWING INTERIOR FURNISHINGS: DESCRIPTION POSMON P/N S/N F.S. WIT 0/B AFT FACING SEAT. FORWARD SALON 303413-2 4350 401.94 R/H VB AFT FACING SEAT. FORWARD SALON 303413-10 4351 401.94 FORWARD RAI TABLE AND PEDESTAL FORWARD SALON A727-2531-001 NSN 438.50 LH AFT FACING SEAT CENTER LOUNGE 3034131 4354 73200 COFFEE TABLE AND PEDESTAL CENTER LOUNGE 727-2535-003 NSN 772.50 THIS ALTERATION WAS ACCOMPLISHED PER JET AVIATION DRAWING B727-17454-200, REV IR, DATED 1/2102, SHEETS I & 2, TITLED - MINOR DEVIATION TO STC SA3137S0, THE LIMITED 727-100 GENERAL ARRANGEMENT. REFERENCE F.A.A. FORM 8110 DATED 1/6/02 BY STRUCTURES D.E.R. NO. DERT-810028-NE. A LOGBOOK ENTRY REFLECTING THIS INSTALLATION WAS COMPLETED PER F.A.R. 43.9 AND ENTERED INTO THE AIRCRAFT LOGBOOK. THE EQUIPMENT LIST WAS AMENDED AND THE NEW WEIGHT AND BALANCE WAS COMPUTED AND ENTERED IN THE AIRCRAFT RECORDS TAW AC43. I3-1B, CHAPTER TO, SECTION 2 AND AC 43.I3-2A, CHAPTER 1 PARAGRAPH 9. THERE ARE NO FLIGHT MANUAL SUPPLEMENTS OR COCKPIT PROCEDURAL CHANGES REQUIRED FOR THIS ALTERATION. END O Additional Shoots Am AttaOhod * U.S. G.P.O 1990.781.753 SDNY_GM_02759744 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00246666 EFTA01331129

le MAJOR REPAIR AND ALTERATION US T Otp.vtraceni (Airframe, Powerplant, Propeller, or Appliance) olranoccetabca Federal Minion AderisisbaGen Form Approved OMB No. 2120-0020 For FAA Use Only Office IVtifictlion INSTRUCTIONS:' Print or type all entries. See FAR 43.9 Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Boeing Model 72731 Serial No. 20115 Nationality and Registration Mark N908JE 2. Owner Name (As shown on registration certificate) JEGE Inc. Address (As shown on registration certificate) 103 Foulk RD STE 202 Wilmington, DE 198034742 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME As descnbed in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type / f I Manufacturer 6! Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Gary K Palmer 6 Hyacinth Lane Holbrook, NY 11741 X U.S. Certified Mechanic #84544584AP Foreign Certified Mechanic Certificated Repair Station Manufacturer D. I certify Nat the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date 08/01/01 Signature of Authorized Gary K Palmer Individual 7. App oval for Return to Service Pursuant Administrator BY to the authority given persons specified below, the unit dentified in item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is 0 APPROVED ID REJECTED FAA Ft Standards Inspector Manufacturer X Inspection Authorization Other (Snooty) FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Dale of Approval or Rejection 08/01/01 Certificate or Designation No. 84544584W of Authorized Individual x , Gary K Palmer ----Y.-42i Gary ern' 331 (12438) SDNY_GM_02759745 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246667 EFTA01331130

NOTICE ^%. Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. B. Description of Work Accomplished (If more space is required, attach additional sheets, Identify with aircraft nationality and registration math and date work accomplished.) Firebtocked and upholstered existing, one (1) cabin single chair (Erda SIN 4359) in Townsend: Leather Lambskin Pads Alligator Embossed/Tipped Gold/Black, leather and two (2) cabin chairs (Erda S/N 4357 and 4358) in Clarence House: 1037901S-37 Velours Mohair, fabric. D.E.R. Identification 62326-01. Fireblocked and upholstered existing, two (2) cabin single chair (Erda SIN 4360 and 4361) in Old World Weavers: Edmond Petit FMPOO 10004 Zoom, fabric. D.E.R. Identification 64318-01. Fireblocked and upholstered existing, one (1) cabin single seat (Erda 5/14 4354) and one (1) three section divan (Dettmers S/N 520, 521, and 522) in Gellman Ind.: Tiburon TWeed, fabric and one (1) divan (Deitmer SIN 516) in Clarence House: 10379MS-37 Velours Mohair, fabric. D.E.R Identification 65624-01. Fireblocked and upholstered existing six (6) single cabin seats (Erda SIN 4350, 4351, 4352, 4353, 4355, 4356), one (1) LH forward sidefacing divan (Dettmers SIN 517), and two (2) 3-place reclining divans (Detainers S/N 518 and 519) in Old Weavers: EA81340013 Alfa Check, fabric and ETS J. Tessin SA.: Mastic #19075, leather. D.E.R. Identification 65059- 01. All materials meet FAR 25.853(a) Appendix F, Part l(aX1)(ifi. Aircraft seat cushions have been fireblocked as per the requirements of FAR 25.853(c) Appendix F, Part II. Amendment 25 - 83. Results of sample bum tests are documented on SAL's Test Plan #7428, #7617, #7722, and #7759 and on attached DER approved 8110-3, Identification 62326-01, 64318-01, 65624-01, and 66059-01. Seat cushions have been tagged as being in comp5ance with the applicable regulatory requirements. Aircraft seatbelts were sent to Aircraft Belts. Inc. Repair Station YB1R632K for rewebbing, work order number 0046395 and reinstalled on the seats and divans. Replaced 19 each P.L. Porter 5102300-28 seat recline Hydrolok and 6 each P.L Porter 5102300-21 divan recline Hydrolok. Hydroloks were replaced using standard interior practices. Installed Erda Hydro Legrest PIN 302617-3 and mechanical control single P/N MC15-36 on two (2) cabin single seats Erda seat SIN 4360 and 4361 in accordance with Erda drawing 302617 Rev B. Attached: FAA approved Townsend: Leather Lambskin Paris Alligator Embossed/ Tipped Gold/Black, leather and Clarence House: 10379015-37 Velours Mohair, fabric. Test Plan #7428, form FM 8110-3 dated 04/16/01, Judy Boggs, DERY-405020-CE. Identification 62326-01. Attached: FAA approved Old World Weavers: Edmond Petit FMPOO 10004 Zoom, fabric. D.E.R. Identification 64318-01. Test Plan #7617, form FM 8110-3 dated 06/20/01, Judy Johnson, DERY-405020-CE. Identification 64318-01. Attached: FM approved Gellman Ind.: Tiburon Tweed, fabric and Clarence House: 10379BIS-37 Velours Mohair, fabric. Test Plan #7722. form FM 8110.3 dated 07/12/01, Donna J. Parrish, DERY-410100-CE. Identification 65624-01. Attached: FAA approved Oki World Weavers: EA81340013 Alfa Check, fabric and ETS J. Tessin SA: Mastic #19075, leather. Test Plan #7759, fowl FM 8110-3 dated 07/24/01, Donna J. Parish, DERY-410100-CE. Identification 66059-01. Attached: Aircraft Belts, Inc.: CertificalloniPaddng List, work order number 0046395 consisting of 11 sheets. Attached: FAA form 8130-3 from P.L. Porter Controls, Inc.: 5102300-21 and 5102300-28 Hydrolocs tracking number 7723, 6751, 7176. 6759, 9495, 7367, 7368, and 9292. Pertinent data on file at International Jet Interiors, Inc. under W.0.#: 01119. Customer to install seats and divans In aircraft. Log entry has been made. EN 0 Additional Sheets Are Attached * U.S. G.P.O 1990461453 SDNY_GM_02759746 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00246668 EFTA01331131