• e US Department MAJOR REPAIR AND ALTERATION Of Transportation Federal (Airframe, Powerplant, Propeller, or Appliance) Aviation Administration Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification So- r5DO- 1 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC43.9-1 (or subsequent revision thereof) for instructions a d 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 ea such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Boeing Model 727-100 Serial No. 20115 _ Nationality and Registration Mark USA N908JE 2. Owner Name (As shown on registration certificate) J.E.G.E, Inc. = N om Only 3. For FAA Use .. ..• • . OCT Tor, data identified here' pties atoverthInes reqiiFements is approved described aircraft, subject ntorrnity ,uthe dram 43, se 43.7. with applicable for the above I by a person 5 (-1 --f5V 0 — i T Date Sign of Inspector 4. Unit Identificati 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. BANYAN AIR SERVICE •VI NICS DIVISION U.S. Certificated Mechanic Radio Class 1,2,3 Limited Airframe Foreign Certificated Mechanic Certificated Repair Station 0 Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date . :,7fr/ C?-7---46 '&/-g_. <71, 0C)Z Signature of Authorized lndi .d4,31) ,/ eeZ Steve Ouellette ( 9/W_ 7. Approval for Return to Service Pursuant to the authority given personsRecified Federal Aviation Administration and is below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the APPROVED O REJECTED BY FAA Flt. Standards Inspector Manufacturer inspectfon Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group -b, Date of Approval or Rejection Der-0,57 _ ,,ao 6 Certificate or Designation No. SD4R514M Signatur ____ 0: thorized I idu d Ouellette ..______ Steve l FAA Form 337 (12-88) EFTA00277580

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.) The purpose of this 337 is for the work performect 1•1908JE under Banyan Air Service; Avionics Division work order #71301 completed on a2s/a6 A. Installed ari 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 AC43.13-1B, Chapter 7, sections 1-5, AC43.13-1B Chapterg,'Options,3-17, AC43.13-2A Chapter 1, AC43.13-2A Chapter 2, paragraphs 24 & 25 and the aircraft's maintenance manual. . 111W: C A functional test of the .ab6e/Aniprrient 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. The weight change is negligible. the equipment list was updated to reflect this change. E. Instructions for continued airworthiness is attached.. END K Additional Sheets are Attached EFTA00277581

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 EFTA00277582

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• APPLICATION REVISIONS . DESC. NEXT ASSY USED ON REV DESCRIPTION DATE APPROVED ST 3100 ASE SYSTEM BARON 95-B55 A BASELINE RELEASE 2002-10-16 K. FRANTZ B SEE DCN 00179 2002-10-25 K. FRANTZ ._,.... ALL SHEETS CARRY THE SAME REVISION LETTER UNLESS OTHERWISE SPECIFIED DIMENSIONING & TOLERANCING bkW ASME Y14.5M-1994 DIMENSIONS ARE IN INCHES STANDARD TOLERANCES: x = ±. .1 )(X= ± .02 )(XX= ± .010 e . AirCell, Inc. no d 1172 Century Drive ..._.7 Suite 280, Building B Louisville, CO 80027 APPROVED DATE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ST 3100 ASE SYSTEM PREPARED BY K. FRANTZ YEAR-M O-DA 2002-10-16 MECH DESIGN Z. HOH YEAR-MO-DA 2002-10-16 ELEC DESIGN B. SOUKUP YEAR-M O-DA 2002-10-16 TECH SUPPORT B. NIELSON YEAR-MO-DA 2002-10-16 SYSTEMS K. FRANTZ --\ YEAR-MO-DA 2002-10-16 ENGINEERING J. POLSON YEAR-MO-DA 2002-10-16 SIZE A - CAGE CODE 1NO67 DRAWING NUMBER . 820-10680-001 REV B FILE FORMAT: Microsoft Word 2000 SCALE: NONE WEIGHT: NA SH 1 of 8 FILENAME: 820-10680-001-B.doc • S a • • a a S S 699-10077: A-SIZE SPEC TEMPLATE.DOC EFTA00277584

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p p p p p p p. 9 p p p p p ) ) TABLE OF CONTENTS 1 GENERAL INFORMATION 3 1.1 SCOPE OF THIS DOCUMENT 3 1.2 TECHNICAL SUPPORT CONTACT INFORMATION 3 1.3 • GENERAL. NOTES 3 1.4 ADVISORIES 4 2 SYSTEM DESCRIPTION 4 2.1 TOP LEVEL SYSTEM CONFIGURATION 1 "4 2.2 OPERATION OF THE SYSTEM 6 OPERATIONAL TIME LIMITS AND SCHEDULED MAINTENANCE 7 4 UNSCHEDULED MAINTENANCE 7 4.1 TROUBLESHOOTING PROCEDURE 7 5 AIRWORTHINESS LIMITATIONS 7 FIGURES AND TABLES Table 2.1-1 System Component Definition 5 Figure 2.1-1 Block Diagram of ST 3100 ASE System 6 • AirCell, Inc. SIZE CAGE CODE DRAWING NUMBER REV e 1172 Century Drive A 1NQ67 820-10680-001 B Suite 280, Building B FILE FORMAT: Microsoft Word 2000 SH 2 of 8 Louisville, CO 80027 FILE NAME: 820.10680-001-B.doc 699.10077: A-SIZE SPEC TEMPLATE.DOC EFTA00277586

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GENERAL INFORMATION 1.1 SCOPE OF THIS DOCUMENT This manual defines the instructions for continued airworthiness (ICAW) for an AirCell_ 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] elf AirCell, Inc. 1172 Century Drive Suite 280, Building B Louisville, CO 80027 SIZE A CAGE CODE 1NC)67 DRAWING NUMBER 820-10680-001 REV B FILE FORMAT: Microsoft Word 2000 I SH 3 of 8 FILE NAME: 820-10680-001-B.doc 699-10077: A-SIZE SPEC TEMPLATE.DOC EFTA00277588

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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 gal 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. AirCell' AirCell, Inc. 1172 Century Drive Suite 280, Building B Louisville, CO 80027 SIZE CAGE CODE DRAWING NUMBER REV A 1NO67 820-10680-001 B FILE FORMAT: Microsoft Word 2000 SH 4 of 8 FILE NAME: 820-10680-001-B.doc 699-10077: A-SIZE SPEC TEMPLATE.DOC EFTA00277590

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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 Designatio n Description AirCell PN. Approved Alternate(s) AirCell PN of Alternate System Transceiver LRU ST 3100 ASE Transceiver 400-10680-001 none Transceiver :Mounting Tray LRU 3/8 ATR Width Mounting Tray 800007-1 3000 Series 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 Portable Coilcord ASE Handset Custom Retractable ASE Handset 400-10035-00X* 400-10015-00X* 400-10019-00X* Satellite ASE Antenna LRU 1600 MHz Satellite ASE Antenna, Patch Style 015-10306-001 1600 MHz Satellite ASE Antenna, Blade Style 015-10683-001 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. (MICA: 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: Microsoft Word 2000 I SH 5 of 8 FILE NAME: 820-10680-001-B.doc AAt4r4fAco" 699-1C077:A-SIZE SPEC TEMPLATE.DOC EFTA00277592

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ASE SATELLITE \/ ANTENNA I 0 p I I I I I I I I I I ) ) .44111 .\_ AIRCRAFT FUSELAGE ASE SYSTEM XCVR SAT ANTENNA ID AUX CNCTR NO CONNECTION SYS CNCTR ASE SYS HS CNCTR ASE SYS HS CNCTR 1=1--M120 ASE 5Y5 HS CNCTR D ASE SYS RS232 CNCTR ASE HANDSET CHANNEL ASE HANDSET CHANNEL Mffal ASE HANDSET CHANNEL TO AUDIO PANEL TO RS232 DATA TERMINAL TO AIRCRAFT POWER (2.8 Vdc) AIRCRAFT 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). 6N_j.ri•Celf 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: Microsoft Word 2000 SH 6 of 8 FILE NAME: 820-10680-001-B.doc 699-10077: A-SIZE SPEC T EMPLATE.D GC EFTA00277594

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3 OPERATIONAL TIME LIMITS AND SCHEDULED MAINTENANCE The ST 3100 system is designed and manufactured to be maintenance free after installation. As a 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 TROUBLESHOOTING PROCEDURE 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 clear, 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 Part 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. A7-frCelf 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: Microsoft Word 2000 SH 7 of 8 FILE NAME: 820-10680-001-B.doc uctict)ticccfoC 699-10377: A-SIZE SPEC TEMPLATE.DOC EFTA00277596

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t.d S • 0 P 9 P p p a a a a Appendix A ST 3100 ASE System Troubleshooting Procedure A tirr AirCell, Inc. kjell 1172 Century Drive Suite 280, Building B Louisville, CO 80027 SIZE A CAGE CODE 1NQ67 DRAWING NUMBER 820-10680-001 B F. FILE FORMAT: Microsoft Word 2000 I SH 8 of 8 FILE NAME: 820-10680-001-B.doc 68410077,S. SPEC TEMPLATE.DOC EFTA00277598

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TrCell' Symptom Possible Cause Discussion Verification Step(s) Symptom 1 Power is not available to ASE The handset display should always O 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 arc off, proceed to the next bullet in this list. If most handsets are illuminated, but one is not, then proceed to Symptom 2. (One or more suggests that there is a problem with O If all handset displays are dead, the problem is likely in the power system wiring handsets integrated in the input power to the ASE system. before the ASE transceiver. Visually check the system connections and the wiring system, no handset . In the event that the one or more 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 lines 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 ail connections are made in accordance (ASE 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 handset O If all system connections are correct, then switch the `dead' handset with a known good handset and retest the system. If the handset is still dead in the new location, then the handset is bad. Contact AirCell Technical Support for repair/replacement instructions. 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 harness to match the wiring diagram. • O If this procedure does not resolve the problem, contact AirCell Technical Support for additional guidance. A-1 ST 3100 ASE System Troubleshooting Procedure 820-10680-001, Rev B Ceti- IC tttik MiLttlettAdt EFTA00277600

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‘4110 46P 4019 -.4m! VaY INV 10, INF 4mY 441,,w 400.4, WINO mi, wut:.‘soilmOlpf wov011OtiOWWW 14104rOVINVOtiOVIOU Symptom Possible Cause • Discussion Verification St,9(s) Symptom 3 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 (3B). 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. 0 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. 0 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 3B. No Satellite mode signal Possible Cause 3B There is a problem with the Satellite RF channel. • • Verification Test 3B O While the aircraft is on the ground, perform a visual inspection of the 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 are 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 EFTA00277602

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--tt US Department MAJOR REPAIR AND ALTERATION 0f Transportation (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Administration Form Approved OMB No. 2120-0020 For FA Use Only Office IdentificatioA (5O-rspo- iq INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC43.9-1 (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 727-100 Serial No. 20115 Nationality and Registration Mark USA N908JE 2. Owner Name (As shown on registration certificate) J.E.G.E, Inc. Address (as shown on registration certificate) 103 Foulk Road STE 202 Wilmington, DE. 19803-3742 3. For FAA Use Only -,i-c:;;;:.,:•• _ •*4-4 .:, 4. Unit identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. 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 Class Limited Airframe Foreign Certificated Mechanic El Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) *dentified 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 October 10, 2006 Signature of Authorized Indivi Steve Ouellette c.- ---- 7. Approval for Return to Service Pursuant to the authority given persons s• • cified below, Federal Aviation Administration and is e. APPROVED the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the O REJECTED BY FAA Fit. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection October 10, 2006 Certificate or Designation No. SD4R514M Signature of orized Ind* - I Steve Ouellette FAA Form 337 (12-88) EFTA00277604

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) The purpose of this 337 is for the work performed on N908JE 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. 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. Instructions for Continued Airworthiness is "on condition only." END Additional Sheets are Attached EFTA00277605

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 MODEL 727-31 TYPE (A irPlane. Radio, Helicopter, etc) Airplane NAME OF APPLICANT Banyan Air Services LIST OF DATA IDENTIFICATION TITLE DER Services Drawing: 2006-173-1 _ Rev. I/R -i.'...- *-::-i:Dtd. 27-Sep-06 END END • Iridium Antenna END END END Effectivity: S/N: 20115, T/N: N908JE Installation STA 515 - BTWN S-2R & END END END END END_ _ _ _ _ _ ___ 98-11-03 RI. Certification to FAR 25.571, may be required. Per Advisory Circular 25.1529-1 Repairs on Transport Category Airplanes, of the structure must be performed before of the above listed data are approved design data and is not installation approval. info) aircraft model and serial number listed Approved structural analysis on file Services, Inc. office in Birmingham Serial No. 20115 S-3R . END_ END Note: This aircraft is effected fatigue evaluation Continued Airworthiness and fatigue Notes: by AD of structure of Structural evaluation . only for more valid for the based on FAA FL. or DER 727.-31 Damage - tolerance and Instructions for; the damage tolerance 4/11/2003. . herein. This approval below at DER Services office AL. 1) The structural aspects is only for the engineering (Ref. 8110.45 8/30/02 2) This approval is 3) This approval is in Ft. Lauderdale, Model No. PURPOSE Approve data for low profile antenna installation (structural aspects only, Static Analysis) OF DATA APPLICABLE REQUIREMENTS (LIST SPECIFIC SECTIONS) CAR 4b.200, 4b.201, 4b.202, 4b.260, 4b301, 4b302, 4b303, 4b.306 CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with condition and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. Recommend approval of these data I (We) Therefore pi Approve these data SIGNATURES) OF DESIGNATED ENGINEERING REPRESENTIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) Robert J. Belgau DERT-510024-CE Structures — , FAA FORM 8110-3 (11-70) SUPERSEDES PREVIOUS EDITION DER SERVICES PROJECT NO. F2006-173 EFTA00277606

- a EFTA00277607

8 7 6 5 4 3 2 1 D C -o B A GENERAL NOTES: 1. FABRICATE PART(s) AS SHOWN. 2. BEFORE INSTALLATION OF DOUBLER, ROLL TO MATCH AIRCRAFT MOLD LINE RADIUS. 3. BREAK ALL SHARP EDGES .0201.030 R. 4. TREAT ALL REWORKED AREAS USING ALODINE 1201S (PER MIL-C-5541, CLASS 1A) AND TVVO (2) COATS OF EPDXY POLYAMIDE PRIMER (PER MIL-P-233377, TYPE I). 5. FINISH ALUMINUM PARTS USING ALODINE 1201S AND TWO (2) COATS OF EPDXY PRIMER. 6. MAINTAIN MINIMUM 2D + 1/16" EDGE DISTANCE FOR ALL FASTENERS ON DETAILS; MINIMUM 2D EDGE DISTANCE ON ASSEMBLY. 7, ALL FASTENERS ARE TO BE INSTALLED IN TRANSITION-FIT HOLES. HOLE TOLERANCE PER NAS618. 8. ALL FASTENER LENGTHS ARE TO BE VERIFIED FOR TOLERANCE PRIOR TO INSTALLATION. 9. INSTALL ALL PARTS AND THREADED FASTENERS WET USING PR1436G TYPE III SEALANT ON ALL FAYING SURFACES. 10. RESTORE ORIGINAL FINISH PER B727 M.M. 51-21. 11. PROTECT REWORKED AREA AGAINST CORROSION PER B727 SRM, CHAPTER 51-10-2. 12. REFERENCE 8727 S.R.M, CHAPTER 51-30 FOR FASTENER REMOVAL AND INSTALLATION PROCEDURES. S - 3R STA 510 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. STA 515.00 S - 2R EXISTING BONDED STRAPS (REF) DESCRIPTION DATE APPROVED I/R INITIAL RELEASE 09-27-2006 EXISTING FUSELAGE SKIN (REF) NAS 1097AD4 - 2 FASTENER CODES ITEM DESCRIPTION K LU K itj NASI097AD4 (TY'P 50 PLS) x 64510428AD 3 (TYP 8 PLS) x STA 520 50 COUNTERSUNK RIVET OPL 8 RIVET - NUTPLATE MS20426AD3- 2 QPL 4 4 SCREW MS24694C55 OPL 3 4 NUTPLATE NAS 1 473A3 QPL 2 1 1 1 DOUBLER - INTERNAL L1 CPS-IRIDIUM ANTENNA 567- 1575-109 0.050" 2024-T3 00 -A -250/5 QPL QPL ITEM QTY NAME PART NUMBER MATERIAL MIL-SPEC VENDOR Ports List CRAVING CREATED FCN, BANYAN AIR SERVICE CRAVING SIZE, B DATE APPROVED 09-27-2006 lJ DER SERVICES 2100 kV 6.311 STREET, Suitt C-I09, FT. LAITIRDAI.E rl. =9. (9509TI.3B32, FAX(954)971-3059 nes date Is provided as • CONFIDENTIAL AND PRIVILEGED 00C(JMENTOebecin BANYAN AIR SERVICE & DER 5•M ass. My oN use of raproductco *afoul the expnrssed tten coneare of DER Sareloatbaxpassly latedcius. My M4064 of 0is docurnerd incluctify INN not Potted IS) rasldabon In pen riOsoul send.n consent ci DER Son nee Is expressly Portirkeen. This aporovei Es Pew] upon AN. mod sr-esti@ ID DER Servicsrs torn BANYAN AIR SERVICE al So. Offs of nsporl corrphillon. My iddlaccial data Mich Osamu reale:is. may mull b afnenftn; 0r COnctoslco(s) expressed haneln UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES UNSPECIFIED TOLERANCE FRACTIONS ANGLES DECIMALS DRAVN BTU W.D.OLIVERI CHECKED BY' R.J.BELGAU STRESS BY' W.D.OLIVERI ±1/32 .15 MACH. .2 FORMED .X ± .1 .XX t .03 .XXX_ t .010 APPROVED BY. R.J.BELGAU 8 7 5 4 3 TITLE IRIDIUM ANTENNA INSTALLATION STA 515 - BTWN S-2R & S-3R A/C Typr BOEING T'G 2006-173-1 N.A. REV I/R Nod No ' 727-31 TAIL No. r N908JE PROJ 2006-173 -SCALE. SERIAL No 20115 STRL INSTL SHEET 1 OF 3 2 1 D C 4- B A EFTA00277608

J EFTA00277609

8 7 6 5 4 3 2 STA 510 EXISTING FUSELAGE SKIN (REF) VIEW LOOKING UP SOME STRUCTURE REMOVED FOR CLARITY 01.00 CONNECTOR CUTOUT IN SKIN STA 520 IRIDIUM ANTENNA INSTALLATION @ STA 515.00 - BTWN S-2R & S-3R EXISTING BONDED STRAPS (REF) EXISTING BONDED STRAPS (REF) TN. deer b prose.. as • COW IDENTIX. AND PFUYILED0ED DOCUMENT between BANYAN AIR SERVICE DER SerrIces. My Other use or (spend ucton ecnotrt De esOreesslawrInen mos. of DER SessIcse N.sweaty MPMM. My ndsyse of Pis Ovarrent bOumrq (bvl rot ernlletl b) qv...Jon b pert with. written consent of DER Se.. M -Drew lortedden. T. *pus.* Is based v.n dab ft.., sessiebb lo DER Sen.. Rom BANYAN AIR SERVICE al be SIR ot report corrode., My ...Ye/ dale. eh. becomes rear.. may row. In •^r•ran5 eye con:Susie*/ bIreesedb... 4 4 EXISTING BONDED STRAPS (REF) EXISTING FUSELAGE SKIN (REF) SECTION A-A D C 4- DER SERVICES ,'),`." 2006-173-1 2700 N.W. 62/10 STREET, 6us C-109, FT. LAUDERDALE. R 33XS. (554) 571.3832. FAX (M.) . 7 14.0 B SIZE DRAWN BY, W.D.OLIVERI REV UR SERIAL No. . 20115 SCALE 3= 4 SWET 2 OF 3 8 I 7 I 6 5 4 3 2 B A EFTA00277610

3 • EFTA00277611

8 7 6 5 4 3 2 1 - 0 B 01.62 FASTENER PATTERN (TYP 6 PLS) 00.20 ANTENNA MOUNT HOLE (TYP 4 PLS) 01.00 CONNECTOR CUTOUT ITEM 2 / DOUBLER FABRICATION USE NUTPLATE AS PATTERN FOR RIVET HOLES. (TYP 8 PLS) R 0.25 4.50 0 0 0 0 0 (TYP 4 PLS) 4.13 0 0 0 3.66 O O O 3.19 3.19 O o 2.72 -0 0 0 ( 0 o o o 2.24 Ck O o 1.78 0 1.38 o O ED O o 0 O 1.29 O 0.84 O O O O O O 0 0.38 O 0.00 o CO tO CI O W. to Cl CD CO 1O cn O CO LO C') O cr) t•- e ill CO N CO CD 0, cO CV CO O o o o cNi N (vi ri 4 4 4 4- B A A This data le ortroldid ae • CONFIDENTIAL AND PRA/ILEDDED DOCUMENT betetern BANYAN AiR SERVICE DERE...Mon. Any caw, ow or reproduction without the eapreesed rattan oznunt of DER BeMc.e4 expreeffy forbidden. Any mg.*. of AN 6:.O...nt I:Coelho (but not United quotation in pert without written coreenl of DER Serelpe b eefe...fY forbidden. Thts *pommel Is bawl upon date mad. sysliftes to DER Sonia. eon BANYAN AIR SERVILE el Ow erne of 1900 etelpfli3on. Any edditionei date. which becomes eveiletie, rney refue tr. emending tne oonclusicn(s) freereased herein. DER SERVICES NQG 2006-173-1 2700 N.W. 132.3 STREET. &Ate C-I09, FT. LAUDERDALE. FL. 11309. (p 6e) 971-3832. FAX (964)971-3059 SIZE ERAVN BY. REV W.D.OLIVERI l/R SERIAL No. .2O 1 1 5 SCALE 0.5 = 1 S ET 3 C.F 3 8 7 6 5 fi 4 3 2 EFTA00277612

EFTA00277613

• , C US Department MAJOR REPAIR AND ALTERATION Of Transportation Federal (Airframe, Powerplant, Propeller, or Appliance) Aviation Administration Form Approved OMB No. 2120-0020 For FA Use Only Office Identification SO- (3 DO -17 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC43.9-1 (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 727-100 Serial No. 20155 Nationality and Registration Mark USA N908JE 2. Owner Name (As shown on registration certificate) J.E.G.E. Inc. Address (as shown on registration certificate) 103 Foulk Road, Ste 202 Wilmington, DE. 19803-3742 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. 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 C SD4R514M Class 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 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 8 November 2004 Signature of Authoriz_e_ii.i l icyl . 7 .2; /d -‘,/ e Steve Ouellette 7. Approval for Return to Service Pursuant to the authority Federal Aviation Administration given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the and is II APPROVED II REJECTED BY FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection 19 November 2004 Certificate or Designation No. SD4R514M Signature of _---) _ Authorized Individual Steve Ouellette C FAA Form 337 (12-88) EFTA00277614

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.) 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 K Additional Sheets are Attached G' fin Og(10.b ffL, EFTA00277615

' . 0 ••--- . -I US Department MAJOR REPAIR AND ALTERATION Of Transportation Federal (Airframe, Powerplant, Propeller, or Appliance) Aviation Administration Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification 5a — r 51)6-1 7 INSTRUCTIONS: Print or type all entries. 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 $1,000 for each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make Boeing Model 727-100 Serial No. 20115 Nationality and Registration Mark USA N908JE 2. Owner Name (As shown on registration certificate) J.E.G.E, Inc. - Address (as shown on registration certificate) 103 Foulk Road STE 202 Wilmington, DE. 19803-3742 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. 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 M Radio C SD4R514 lass 1,2,3 Limited Airframe Foreign Certificated Mechanic a Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of 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 7 . 1/6/1•1/9e-:-/ a 4:2 C7 (71 Signature of Authori 4i .s.Jualit ‘C Steve Ouellette 7. Approval for Return to Service Pursuant to the authority given personsirfi ci ed below, the Federal Aviation Administration and is APPROVED unit identified in item 4 was inspected in the manner prescribed by the Administrator of the • REJECTED BY FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection / / r Ahi/6Arc e__c72O) C Certificate or Designation No. SD4R5 14M Signature o d Indivi Steve Ouellette FAA Form 337 (12-88) EFTA00277616

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.) 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 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 *Ay K Additional Sheets are Attached EFTA00277617

pniteb tutes jArrirriCn Prpartrrttnt of Zrartsportation - grbrral czAfliatinn cAbmirtistration , upialentenial `Tuve Certificate t.471 teinh.fe ST09951SC e°rl teak 1,:s,tezeti/o . SIP Technical Services, Inc. 10107 McAllister Freeway San Antonio, TX 78216 cu.-44,1 dead; ejange art de; *//ze tleJe 7y r1.4 a‘e.it,72/<cikelled/f bre dindal4vzs rz./sticevu‘4.-ivz.s . dercAr ens .yieceAdife., ,eevinee4s de izievz-c-vakeaeJis "e9ece.:vnuva.4.t ei4:7tr."/ 4b c/a; Civil Air Refez44iva.s. 6isr:;th2aigivekcl n'iv0cale A3WE ,d&zZe.- Boeing .A6esehi.• 727-100 Series .gesc. , 04"evz c>4.F1//ze Wiazife. - 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. eindg7cyzeit a..s.• Compatibility of this design change with previously approved modifications must be determined by the installer. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission. ce,-10cate and14 6:- .111/2/2O/66.iip ektet tcs/ficiza 9ga Jarre feei .1‘.4.3/2eze, reecch geeicv , a te..rmZaaleiva eizhr c3 cae.e<av:se e...ilae°4‘ede;/ dt; .../ge/z71.44e:stkzkv, €/° ev -a, '._/gotallevt.AeGitzikeafinciliark. :gale e3:rev/i&alei -vz, .• August 02, 2001 Lale 9/4,sa.z/ue ..December 13, 2002 :2ale rez,...uaed; gale ez,,vezaeAl.• (Sign ture) ces Co er, Spe ial Ce cation Office South4vest Region (Title) Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. FAA Form 8110-2(10-68) Page 1 of 2 This certificate may be transferred in accordance with FAR 2I.47. EFTA00277618

. . EFTA00277619

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 #. N908.TE SERIAL #. 20115 M This supplement must be attached to the FAA Approved Airplane Flight Manual when the Universal Avionics System Corporation UNS-1D+ Flight Mana•ement System (FMS) is .in§talled in accordance with field approved 337 dated 1Voll (2200 )4' . 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 '.'Pl‘ge 1 of 9 EFTA00277620

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 Table of Contents Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 SECTION PAGE GENERAL 3 LIMITATIONS 3 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 3 PERFORMANCE 6 Revision 0 All Date: NOV 8 2004 RECORD OF REVISIONS Pages Description Initial Release Rev. 0 Approved . NOV 8 71104 Pige 2 of 9 EFTA00277621

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 SECTION 1- GENERAL 1. INSTALLATION DESCRIPTION. Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 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 FMS'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 Operator's Manuals as applicable. The FMS's contain software SCN 802/902 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: VFR/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 FAA 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 FAA approved version. This does not constitute an operational approval. Date: NOV 8 2004 Rev. 0 Page 3 of 9 EFTA00277622

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-senSor 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 an 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 EFTA00277623

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 SECTION 11-- LIMITATIONS (cont.) Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 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 p'arameters are referenced to Magnetic North, and operation of the aircraft is limited to latitudes between N730and S600, 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: NCV 8 2004 Rev. 0 Page 5 of 9 EFTA00277624

Banyan Air 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 Amps 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). Date: NOV 8 2004 Rev. 0 Page 6 of 9 EFTA00277625

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 (EFI) 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 GPS-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 2004 Rev. 0 Page 7 of 9 EFTA00277626

Banyan Air Service Avionics Division 1635 NW 51st Place Ft. Lauderdale, FL 33309 SECTION IV - NORMAL PROCEDURES (cont) c. Approach Operations (cont.) Flight Manual Supplement UNS-1D+ FMS N908JE BOEING 20115 LOC, B/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 `NAV'- 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: NOV 8 2004 Rev. 0 '' 'Page 8 of 9 EFTA00277627

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-Glideslope 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 Page 9 of 9 EFTA00277628

••• • EFTA00277629

. • • 0 . US Department MAJOR REPAIR AND ALTERATION Of Transportation (Airframe, Powerplant, Propeller, or ApplianCe) Federal Aviation Administration Form Approved OMB No. 2120-0020 For FAA Use Only i Office Identification • - 1- • •• , INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC43.9-1 (or subsequent revision thereof) for instructions and -,I 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 O. Aircraft Make Boeing Model ; , 727-100 i Serial No. 20115 Nationality and Registration Mark USA N908JE . 2. Owner Name (As shown on registration certificate) J.E.G.E, Inc. - Address (as shown on registration certificate) 103 Foulk Road STE 202 Wilmington, DE. 19803-3742 3. For FAA Use Only Tri't data identified h plies airworthines n..quirements is described aircraft. subj conformity lutorized In FAR 43, s on 43.7. OCT 11 7004 d-e/ is FM the applicable tot the by a above person 5 0 - r-.5 DO- 1 . - Inspector Date nature 4. Unit Identifi atio 5. Type ry- Unit Make Model Serial No. Repair Alteration •• ••.i • ,..• AIRFRAME (As described in Item 1 above) -s.-4. POWERPLANT .i t---,-• PROPELLER APPLIANCE Type Manufacturer 6. 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 Class 1,2,3 —.... Limited Airframe Foreign Certificated Mechanic Certificated Repair Station r Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date /fA//44/16eW paC3 O Signature of Authori c di ' lual Ouellette — Steve , 7. Approval for Return to Service • Pursuant to the authority given persons specified below, Federal Aviation Administration and is APPROVED the unit identified in item 4 was inspected in the manner prescribed by the Administrator of thil.. REJECTED _ I BY FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) ..... FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection /9 A/47/ 106e2C_c:7,.: Certificate or Designation No. SD4R514M Signature of Aut • d Indio' . . Steve Ouellete ----_ —. FAA Form 337 (12-88) EFTA00277630

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. i• f rr. Description of Work Accomplished • (lf more space is 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 under Banyan Air Service, Avionics Division work order #68062. A. Installed an Artex ELT406-2HM 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. 1 f. r • L. I • .; B. The above installation Aidsi3e&efe,din.iccofdanceX4h. 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 213,7AZ,431172A7Chapter 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 are Attached EFTA00277631

0 US Department MAJOR REPAIR AND ALTERATION Of Transportation (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Administration Form Approved OMB No. 2120-0020 For FAA Use Only .. Office Identification . - - _ INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC43.9-1 (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). . 11. Aircraft Make Boeing Model 727-100 Serial No. 20155 Nationality and Registration Mark USA N908JE 2. Owner Name (As shown on registration certificate) J.E.G.E. Inc. Address (as shown on registration certificate) 103 Foulk Road, Ste 202 Wilmington, DE. 19803-3742 - 3. For FAA Use Only NOV Tr': data identified herei complies the applicable ainvorthines rLquicements d is approv for the above described aircraft, sub' conformity s n by a person authorized in FAR 43, s on 43.7. 8 2004 Ter, . , ., e) — f-S720 --/ 7 . Date Startatura FAA Inspector - 4. Unit Identificat 0 5. Type Unit Make Model Serial No. Repair Alteration . , AIRFRAME (As described in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. 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 C SD4R514M Class Limited Airframe Foreign Certificated Mechanic Certificated Repair Station 0 Manufacturer , D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and . correct to the best of my knowledge. Date 5 ). A /0,-/e-A1,46-2 ,,, e (-1 V Signature of Au .er Indivi , Steve Ouellette 7. Approval for Return to Service Pursuant to the authority given personsAoecified below, Federal Aviation Administration and is x APPROVED the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the III REJECTED BY FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection n X/1/ - - o 76)- Certificate or Designation No. SD4R514M Signature of Authorized Indivi ual Steve Ouellette 1 -7 — FAA Form 337 (12-88) • EFTA00277632

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. 0. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and 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 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 • • •v-inc .q)4:11 A'A4 tit3O 0 Additional Sheets are Attached EFTA00277633

NOV. NV. 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.: A/yog-j-t--- REGISTRATION NO.: c90 /A-5— 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 Manual. APPROVED: S. Frances Cox, Manager Special Certification Office Federal Aviation Administration Ft. Worth, Texas 76193-0190 DATE: October 25, 2004 Page 1 of 9 EFTA00277634

• EFTA00277635

NOY. 8. 2004 9:50AM PYKA AEROSPACE NO. 2146 P. 4 Doc. No. 7280-FM-001, Rev A Issue 092401 S.I.P. Technical Services Inc 10107 McAllister Freeway San Antonio, TX 78216 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 EFTA00277636

• 1 tat EFTA00277637

NOV. 8. 2004 9:51AM PYKA AEROSPACE NO. 2146 P. 5 Dot. 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 5 2. Cold Temperature Operations 5 3. Systems Test 5 4. Pop-Up Terrain Display 6 5. System Annunciators 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 ff CTION V - PERFORMANCE 10 SECTION VI - WEIGHT AND BALANCE 10 TAWS System AFM Supplement for Boeing 727-100 FAA APPROVED Date: October 25, 2004 Page 3 of EFTA00277638

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, NOV. 8. 2004 9:51AM PYKA AEROSPACE Na 2146 P. 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 1 — GENERAL 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. I, 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 3-1) view provides no attitude information. To avoid giving unwanted terrain alerts, the TAWS terrain alerts must be inhibited by pressing the TERR INHIB 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 Air 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 EFTA00277640

3 r EFTA00277641

NOV. 8.2004 9:51AM PYKA AEROSPACE NO. 2146 P. 7 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 1. Operation All aircraft crew interface is conducted through the Universal Avionics display, either multi- function display (MFD) or FMS control display unit (CDU), and system annunciator switches. TAWS terrain information may be presented on either an MFD 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 barb-corrected altitude as the reference for Forwared 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 Alert (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 crew 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 FAIL or TERR 1NOP 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 Illuminated BELOW G/S Annunciator Illuminated G/S INHIBIT Annunciator Illuminated TERR INHIBIT Annunciator Illuminated FAA APPROVED Date: October 25, 2004 Page 5 of 9 EFTA00277642

. EFTA00277643

C. 2.;04 is PYKA NO. 2146 P. 8 Doe. No. 7280-1, . 1, Rev A TAWS System Issue 092401 AFM Supplement for S.I.P. Technical Services Inc. Boeing 727.100 10107 McAllister Freeway San Antonio, TX 78216 SECTION III - NORMAL PROCEDURES(Continued) GPWS FAIL Annunciator GPWS TEST Annunciator Illuminated Illuminated TAWS Terrain Display Test Image (Colored Bars) Aurel Annunciations "TERRAIN, TERRAIN" "PULL UP, PULL UP" "DON'T SINK" "SINK RATE" "GLIDESLOPE" "TOO LOW TERRAIN" "TOO LOW GEAR" "TOO LOW FLAPS" "FIVE HUNDRED" Once the test is complete, TAWS will reboot. During this time the GPWS 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 cancel 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 CDU. 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 annunciated 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 warning). YELLOW threat "stars" on the TAWS display indicate a Terrain Caution(60-second warning) FAA APPROVED Date: October 25, 2004 Page 6 of 9 EFTA00277644

_ "••••• ••••• EFTA00277645

NOV. 8. 2004 9:52AM PYKA AEROSPACE NO. 2146—P. 9" Doc. No. 7280-FM-001, Rev A TAWS System Issue 092401 AFM Supplement for S.I.P. Technical Services Inc. Boeing 727-100 10107 McAllister Freeway San Antonio, TX 78216 SECTION 1.1 1 PROCEDURES Continued 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 annunciator 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 armunciator/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 EFTA00277646

• EFTA00277647

NOY. 8. 2004 9:53AM PYKA AEROSPACE N0. 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 SECTION UI - NORMAL PROCEDURES (Continuedi 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 INOP 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 database 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 INHIB 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 DRIB is active. FAA APPROVED Date: October 25, 2004 Page 8 of 9 EFTA00277648

EFTA00277649

NOV. 8.2004 9:53AM 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 1. Circuit Breakers The TAWS system is protected by the following tip-five circuit breakers: NAME GPWS TAWS System AFM Supplement for Boeing 727-100 LOCATION AMPS BUS P-18 5 28 VDC Ess. 2. Use of TERR INHIB switch. The Terrain Awareness Display inhibit switch (TERR INHIB) must be placed in the INHIB position in the following conditions: 1-Whenever the FMS in the Dead Reckoning (DR) mode 2-Within 15 nm 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 TERR 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," "SINKRATE" 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 EFTA00277650

I I EFTA00277651

NOV. 8. 2004 9:53AM PYKA AEROSPACE NO. 2146—P. 12 Doc. No. 7280-FM-001, Rev A Issue 092401 S.LP. Technical Services Inc. 10107 McAllister Freeway San Antonio, TX 78216 TAWS System AFM Supplement for Boeing 727-100 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" aurel annunciation, SECTION V - PERFORMANCE No change to basic Airplane Flight Manual. SECTION VI - WEIGHT AND B4LANCE Refer to applicable weight and balance document. FAA APPROVED Date: October 25, 2004 Page 10 of 9 EFTA00277652

• EFTA00277653

MAJOR REPAIR AND ALTERATION US Department 01 transportation (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Administration Form Approved OMB No. 2120-0020 For FAA Use On y Office Identification _ 50-r-37,0- r7 INSTRUCTIONS: Print or type all entries. See FAR 43.9 Appendix B, and AC 43.9-.1 (or subsequent revision thereof) for instruc • ns 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 727-31 Serial No. 20115 Nationality and Registration Mark U.S.A. N908JE 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 Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind 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 X ---, Certificated Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and desc . ed on tti reverse o attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Ra ulation4 and that th information ) furnished herein is true and correct to the best of my knowledge. \ \ Date 6/12/02 Signature of Authorized Individual ' Christopher Houseworth. Inspector. \ i• \ _, I 7. Approval for Return to Service Pursuant Administrator BY, to the authority given of the Federal Aviation persons specified below, the unit Administration and is identified in item 4 was inspected in the manndr pr cribed by the 0 REJECTED ,..., CI APPROVED FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Airworthiness Group Date of Approval or Rejection 6/12/02 • Certificate or Designation No. EYKR782D Signature of Authorized Individual .- C.. - . John K. Urso. Inspector. -- ' & 6 1 FAA Form 337 (12-88) EFTA00277654

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 accomplished.) N908JE, BOEING 727-31, S/N 20115, W.O. 18046 REFERENCE F.A.A. FORM 337 DATED 7/2/01 INSTALLING A UNIVERSAL AVIONICS CORP. UNS-ID FLIGHT MANAGEMENT SYSTEMS (FMS) WITH INTEGRAL GPS SENSORS. RECONFIGURED AIRCRAFT WIRING TO PROVIDE V-NAV DISPLAY INFORMATION ONLY, FROM THE EXISTING # I AND # 2 UNS-ID FLIGHT MANAGEMENT SYSTEMS. THIS MODIFICATION AS ACCOMPLISHED PER THE FOLLOWING JET AVIATION DRAWINGS, WHICH ARE SUBSTANTIATED BY F.A.A. FROM 8110-3 RESPECTIVELY: WIRING DRAWINGS: • B727-16236-410, REV A, DATED 4/16/02, SHEETS 1 THRU 5, TITLED - NO. 1 FLIGHT MANAGEMENT SYSTEM. • B727-I6236-411, REV A, DATED 4/16/02, SHEETS 1 THRU 5, TITLED - 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 2001 WITH NO DISCREPANCIES NOTED. AN EMI TEST, REPORT NO.: B727-16236-080 REV IR, SHEETS 1 OF 5, DATED 06/19/2001, WAS CONDUCTED AND THE INSTALLED EQUIPMENT DOES NOT INTERFERE WITH ANY OTHER INSTALLED EQUIPMENT. MAGNETIC DIRECTION INDICATORS WERE CHECKED FOR ACCURACY AND COMPENSATED AS NECESSARY PER AC 43.13-1B, CHAPTER 12, SECTION 3, PARAGRAPH 12- 37 AND AC 43.13-2A, CHAPTER 2 PARAGRAPH 23f. A LOGBOOK ENTRY REFLECTING THIS INSTALLATION WAS COMPLETED PER F.A.R. 43.9 AND ENTERED INTO THE AIRCRAFT LOGBOOK. THE REQUIRED F.A.A. APPROVED FLIGHT MANUAL SUPPLEMENT DOC NUMBER B727-16236-100, REV A, SHEETS 1 THRU 9, DATED 5/8/02 HAS BEEN INSERTED INTO THE AIRCRAFT FLIGHT MANUAL. END K Additional Sheets Are Attached -A- U.S. G. P.O 1990-761-753 EFTA00277655

'f Apr-19-02 08:08A N J Curran 352 243 1011 P_O2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE April 19, 2002 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Boeing MODEL NO. 727-31 TYPE (Airplane, Radio. Helicopter. etc) Airplane NAME OF APPLICANT Jet Aviation Associates West Palm Beach, FL LIST OF DATA IDENTIFICATION TITLE B727-16236-410, Revision A, dated April 16, 2002 B727-16236-411, 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 N908JE. APPLICABLE REQUIREMENTS (List specific sections) CFR TITLE 14, CHAPTER 1, SUBCHAPTER C FAR 25.581 (a)(b)(1) FAR 25.1329 (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 25.1357 (a)(c)(d)(e) FAR 25.1309 (a)(b)(c)(d)(e)(g) FAR 26.1381 (a)(b) FAR 25.1322 (b)(c) FAR 25.1431 (al(b)(c) CERTIFICATION - under authority vcsted by direction data limed above and on attached shirts numbered NONE have tithe Administrator and to accordance with conditions and Limitations or appointment under Part 18.1 or the Federal Aviation Regulations. been examined in accordance with established procedures and found to comply with applicable requirements or the Federal Aviation these data & Equipment Aspects, Design Approval Only, Does Not Constitute Installation Approval) Rezulations. II Recommend approval of I (We) Therefore El Approve these data (Systems SIGNATUR . 0 DESIGN ED NGIN ' REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATIONS) ‘44661--- DERT-510087-NM Systems & Equipment Nor an J. an FAA Form 8110-3 (11-70) SUPERSEDES PREVIOUS EDITION GPO 901-613 FILENAME: SC-727-FMS-REVA.DOC EFTA00277656

lot • I EFTA00277657

Jet Aviation Associates Ltd. Bldg. 1515 Perimeter Rd. Palm Beach Int'l 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.: N908JE SERIAL NO.: 20115 WITH DUAL UNIVERSAL AVIONICS FLIGHT MANAGEMENT SYSTEMS (UNS1-D) INSTALLED This supplement must be attached to the FAA 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 VOR/DME from the Collins No. 1 and No. 2 VOR/DME systems in accordance with manufacture's Installation and Checkout Manual No. 34-60-09, Rev. 2, dated August 15, 1997 or later approved revision and FAA Form 337, dated June 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: iriz Federal Aviation Administration Flight Standard District Office - 17 1050 Lee Wagener Blvd. Ft. Lauderdale, Florida 33315 FAA Approved Date: June 21, 2001 Revision A, Dated: 5/ Page 1 of 9 EFTA00277658

1 p EFTA00277659

MAJOR REPAIR AND ALTERATION US Dopartment . of Transportation ‘ (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation • Administration Form Approved OMB No. 2120-0020 For FAA Use Only OffiQeldentificatjon, 7 SDU7 .604 6s 3 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 727-31 Serial No. 20115 Nationality and Registration Mark U.S.A. N908JE 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 Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. JET AVIATION ASSOCIATES LTD. 1515 PERIMETER RD. WEST PALM BEACH. FL. 33406 U.S. Certified Mechanic CRS AIRFRAME RADIO LIMITED EYKR782D 1,3. 1,2,3. ENG. -Foreign Certified Mechanic ---, X Certificated Repair Station Manufacturer A/F & D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date 1/14/02 Signature of Authorized Individual , ,i John K. Urso. Inspector. x,I.Z.-- L/C-6 -- , 7. Approval for Return to Sery Pursuant Administrator BY to the authority given persons specified below, the unit of the Federal Aviation Administration and is identified in item 4 Was inspected in the manner prescribed by the K REJECTED Cs APPROVED FM Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Airworthiness Group Date of Approval or Rejection 1/14/02 Certificate or Designation No. EYKR782D Signature of Authorized Individual Ronald K. Bystrom. Manager Quality Assurance. 11-V. FAA Form 337 (12-88) EFTA00277660

NOTICE Weisht.andtalanca Or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all prev7ous 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 accomplished.) BOEING 727-31, S/N 20115, N9081E,'W/O 17454. ACCOMPLISHED AN ALTERATION TO THE CABIN INTERIOR FURNISHING ARRANGEMENT PREVIOUSLY INSTALLED UNDER PAGE AVJET STC SA3137SO, DATED 1/17/92, BY REMOVING THE FOLLOWING INTERIOR FURNISHINGS: DESCRIPTION POSITION P/N S/N F.S. R/H O/B AFT FACING SEAT. FORWARD SALON 303413-2 4350 401.94 R/H 1/B AFT FACING SEAT. FORWARD SALON 303413-10 4351 401.94 FORWARD R/H TABLE AND PEDESTAL FORWARD SALON A727-2531-001 NSN 438.50 UH AFT FACING SEAT CENTER LOUNGE 303413-1 4354 732.00 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 1/2/02, SHEETS I & 2, TITLED - MINOR DEVIATION TO STC SA3137SO, 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 IAW AC43.13-1B, CHAPTER 10, SECTION 2 AND AC 43.13-2A, CHAPTER 1 PARAGRAPH 9. THERE ARE NO FLIGHT MANUAL SUPPLEMENTS OR COCKPIT PROCEDURAL CHANGES REQUIRED FOR THIS ALTERATION. END K Additional Sheets Are Attached * U.S. G. P.O 1990-761-753 EFTA00277661

MAJOR REPAIR AND ALTERATION US Department (Airframe, Powerplant, Propeller, or Appliance) of Transportation Federal Aviation Administration Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification dift ---( 1 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 727-31 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 19803-3742 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item I above) X POWERPLANT PROPELLER APPLIANCE Type 1 / 1 1 _ Manufacturer 61 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 that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date 08/01/01 _ Signature of Authorized Gary K Palmer Individual 7. Approval for Return to Service Pursuant Administrator BY to the authority given of the Federal Aviation persons specified below, the unit Administration and is identified in item 4 was inspected in the manner prescribed by the 0 REJECTED ►4, APPROVED FAA Flt. Standards Inspector Manufacturer X Inspection Authorization Other (Specify) FAA Designee Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection 08/01/01 Certificate or Designation No. 84544584IA Signature of Authorized Individual _. Gary K Palmer FAA Form 337 (12-88) EFTA00277662

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. Li B. Description of Work Accomplished (If more space is required, attach additional sheets, identify with aircraft nationality and registration mark and date work accomplished.) Fireblocked and upholstered existing, one (1) cabin single chair (Erda SIN 4359) in Townsend: Leather Lambskin Paris Alligator Embossed/Tipped Gold/Black, leather and two (2) cabin chairs (Erda S/N 4357 and 4358) in Clarence House: 10379B1S-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 S/N 4354) and one (1) three section divan (Dettmers S/N 520, 521, and 522) in Geltman Ind.: Tiburon Tweed, fabric and one (1) divan (Dettmer SIN 516) in Clarence House: 10379BIS-37 Velours Mohair, fabric. D.E.R. Identification 65624-01. Fireblocked and upholstered existing six (6) single cabin seats (Erda S/N 4350, 4351, 4352, 4353, 4355, 4356), one (1) LH forward sidefacing divan (Dettmers S/N 517), and two (2) 3-place reclining divans (Dettmers S/N 518 and 519) in Old Weavers: EA81340013 Alfa Check, fabric and ETS J. Tassin S.A.: Mastic #19075, leather. D.E.R. Identification 66059- 01. All materials meet FAR 25.853(a) Appendix F, Part l(a)(1)(ii). 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 burn tests are documented on S.A.I.'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 compliance 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 SLO2300-28 seat recline Hydrolok and 6 each P.L. Porter SLO2300-21 divan recline Hydrolok. Hydroloks were replaced using standard interior practices. Installed Erda Hydro Legrest P/N 302617-3 and mechanical control single P/N MC15-36 on two (2) cabin single seats Erda seat S/N 4360 and 4361 in accordance with Erda drawing 302617 Rev B. Attached: FAA approved Townsend: Leather Lambskin Paris Alligator Embossed/Tipped Gold/Black, feather and Clarence House: 10379BIS-37 Velours Mohair, fabric. Test Plan #7428, form FAA 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 FAA 8110-3 dated 06/20/01, Judy Johnson, DERY-405020-CE. identification 64318-01. Attached: FAA approved Geltman Ind.: Tiburon Tweed, fabric and Clarence House: 10379B1S-37 Velours Mohair, fabric. Test Plan #7722, form FAA 8110-3 dated 07/12/01, Donna J. Parrish, DERY-410100-CE. Identification 65624-01. Attached: FAA approved Old World Weavers: EA81340013 Alfa Check, fabric and ETS J. Tassin S.A.: Mastic #19075, leather. Test Plan #7759, form FAA 8110-3 dated 07/24/01, Donna J. Parrish, DERY-410100-CE. Identification 66059-01. Attached: Aircraft Belts, Inc.: Certification/Packing List, work order number 0046395 consisting of 11 sheets. Attached: FAA form 8130-3 from P.L. Porter Controls, Inc.: SLO2300-21 and SLO2300-28 Hydrolocs tracking number 7723, 6751, 7176, 6759, 9495, 7367, 7368, and 9292. Pertinent data on file at International Jet Interiors, Inc. under W.O.#: 01119. Customer to install seats and divans in aircraft. Log entry has been made. END DI Additional Sheets Are Attached * U.S. G.P.O 1990-761-753 EFTA00277663

(jv C - . MAJOR REPAIR AND ALTERATION U.S. Dc.-partinalt of (Airframe, Powerplant, Propeller, or Appliance) Transportation Federal Aviation Administration s ... Form Approved OMB No. 2120-0020 For FAA Use Only : Office Identification tlae) F5 De - t f--"--(--_ INSTRUCTIONS: Print or tspe all entries. See FAR 43.9, FAR 43 Appendix B , and AC43.9-1 (or subsequent revision thereof for instructions and disposition of this form. This report is required' by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed S1,900 for each such violation (Section 901 Federal Asia tion Act of 1958). . . i. Aircraft • Make Boeing . Model 727-31 • Serial No.201 15 ' Nationality and Registration Mark N908JE . 2. Owner . Name (As shown . TEGR INC_ on registration certificate). . Addri s (as shown, on registration certifikmte) . 103 FOULKRD STE 202 - WILMINGTON DE. 19803-3742 _ 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration ' AIRFRAME — above) )O - (As described in item 1 ^ . POWERPLANT • s PROPELLER . . APPLIANCE Type . . . Manufacturer 6. Conformity Statement A Agency's Name and- Address B Kind of Agency - C. Certificate:No. - TIMCO Lake City Municipal Airport Lake City, FL 32025 . U.S_CertificatxxiModianic ' DU4R141M Foreign Certificated- Mechanic X Certificated Repair Station .. . Manufacturer . ' D. I certify that accordance with- the repair and/or alteration ill, tiv-rnPnts of Part 43 of made to the units the U.S. Federal -on-the informatices been made in the best of my knowlees identified in item-4 4 •e, and described Aviation Regulaticess andthatthe restat. oraltaeiuencut. hereto have furnished herein. istrue and ccarectto , Date August 1, 2001 . Signature of Authorized Individnal Owen H. Pritchard II I. Approval- for Return- To-Sery cc Pursuant Administrator BY to the authority given persons of the Feclizal Aviatioa specified below, the unit identified Administration and is El APPROVED in item 4 was inspected in the manner prescribed by the D REJECTED FAA Flt.. Standards Inspector Manufacturer Inspection Authorization , Other (Specify! . FAA Designee X Repair Station - • Person- Approved by Transport Canada .. Aim() • .....4. Group - Data of Approval or Rejection August 1, 2001 Certificate or Designation Na • DU4R141M ' Signatu c • 1 / L. Palm Authorized Ind' y • ual 0 IIIIIP, On FAA Form 337 (12-88) EFTA00277664

NOTICE • Weight andbalance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued con fomity 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 data work*Cornpleted_) BOEING SIN 20115 REG. NO. N908JE Page 1 August 1, 2001 The following major repairs were accomplished: NR# 27754 Repaired delaminated R/H Mid Flap Trailing Edge wedge by removing the delaminated section and fabricating and installing a new T/E wedge and strips IAW TIMCO REO-L00464 dated 7/17/01 FAA Form 8110-3 approved by DER Richard C. Saltivan DER # DERT-405157-CE dated June 19, 2001. NR# 27918 Repaired the delaminated and corroded Left Hand Inboard Mid Flap bottom upper Rock-shield panel by removing Rock-shield and corrosion, treated and primed area to be bonded,. impregnated fiberglass overlays as required, applied conductive coating and installed panel IAW B727 SRM 5-7-50-2, 51-40-8, MM 51-20-0 & SB 727-32-247 R1 dated June 5, 1981. SUMMARY 1. All work accomplished IAW Boeing SRM, TIMCO REO, FAA Form 8110-3 and Service Bulletin. 2. Records of all work accomplished is on file at this repair station under work order 185003. 3. Aircraft Weight and Balance updated accordingly. end Ei Additional Sheets Are Attached *- U.S. GOVERNMEqF PRLNTLVG OFFICE: 1992-769-012160157 EFTA00277665

(tt'' • MAJOR REPAIR AND ALTERATION US Department of Transportation (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Administration Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification 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 727-31 Serial No. 20115 Nationality and Registration Mark U.S.A. N908JE 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 ino data identified herein with described aircraft, subject try aPPlovad, linverthines requirements J Ufilterini 3' s 431. i i the applicabl: brthte person :above by 1 7- SO —rD ,e)- Date , ire A Inspector 4. Unit Identifica 99) 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type ' Manufacturer ... 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. JET AVIATION ASSOCIATES LTD. 1515 PERIMETER RD. WEST PALM BEACH. FL. 33406 U.S. Certified Mechanic CRS AIRFRAME RADIO LIMITED EYKR782D 1,3. 1,2,3. ENG. Foreign Certified Mechanic x Certificated Repair Station Manufacturer AfF & D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date -71WO / Signature of Authorized Individ I John K. Urso. Inspector. C.- ,a441 --- 7. Approval for Return to Servl Pursuant Administrator BY to the authority given of the Federal Aviation persons specified below, the unit Administration and is identified in item 4 was inspected in the manner prescribed by the a APPROVED M REJECTED Fit. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA FAA Designee X Repair Station Person Approved by Transport Airworthiness Group Date of Ap royal or Rejection p 7/2 1—/&/ Certificate or Designation No. EYKR782D Signature of Authorized Individual Ronald K. Bystrom. Manager Quality Assurance FAA Form 337 (12-88) EFTA00277666

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 accomplished.) AIRCRAFT: BOEING, TYPE: 727-31, S/N 20115, DATE: 06/14/2001, W.O. 16236, PAGE 1 OF 2 INSTALLED A SINGLE EVENTIDE AVIONICS ARGUS 5000/CE MOVING MAP DISPLAY SYSTEM (TSO C113). THIS MODIFICATION WAS COMPLETED USING JET AVIATION DRAWING NO. B727-16236-270, ARGUS 5000 C/E MOVING MAP DISPLAY, REV. A, DATED 06/19/01. REFERENCE FAA FORM 8110-3, DATED 6/20/01, BY SYSTEMS AND EQUIPMENT DER NO. DERT-510087-NM. THE EXISTING LASERTRAK WIRING WAS RE-BUSSED DUE TO RELOCATION OF LASERTRAK C.D.I. THIS MODIFICATION WAS COMPLETED USING JET AVIATION DRAWING NO. 34-61-32-1, LAZERTRAK SYSTEM MODIFICATION, REV IR, DATED 5/24/01. THE STRUCTURAL INSTALLATION OF THE ARGUS:5(104/GFAMDVAIO MAP,DISPLAY nsum AND THE RELOCATION OF THE LASERTRAK C.D.I. WAS COMPLETED USING JgTANTIM , 1'413119ff,ING:N9:1372-7-1p31V-i1270, ARGUS 5000/CE MOVING MAP EQUIPMENT INSTALLATION, REV. IR, DATED 05d9'/OrREff itEN r 41,0,-5115AIED 06/03/2001, BY STRUCTURES DER NO. DERT-810028-NE. 7110 A can, &A — THE EVENTIDE AVIONICS ARGUS 5000/CE MOVING MAP DISPLAY IS A PICTORIAL NAVIGATION INSTRUMENT, WHICH PROVIDES VISUAL REFERENCE OF AIRCRAFT POSITION RELATIVE TO LANDING FACILITIES, NAVIGATIONAL AIDS AND SPECIAL USE AIRSPACE. THE ARGUS 5000/CE RECEIVES GEODETIC POSITION AND OTHER NAVIGATION INFORMATION FROM THE NO. 1 UNS-ID FMS THROUGH AN EVENTIDE AVIONICS ARINC 419/429 ADAPTER UNIT AND THE AIRCRAFT'S NO. 3 HONEYWELL "LASERREF' INERTIAL REFERENCE SENSOR (IRS) DIRECTIONAL HEADING SYSTEM WHICH, PROVIDES MAP GRAPHICS AND BEARING ORIENTATION. THE FOLLOWING SWITCHES ARE LOCATED ON P16 FORWARD CONTROL STAND, BELOW THE ARGUS 5000/CE MOVING MAP DISPLAY: ARGUS INFO MOMENTARILY DEPRESSING THE ARGUS INFO ILLUMINATED (BLUE) SWITCH BRINGS UP INFORMATION ABOUT MAP OBJECTS ON THE ARGUS 5000/CE MOVING MAP DISPLAY. IF THE ARGUS INFO SWITCH IS PUSHED IN FOR 1 SECOND, THE ARGUS 5000/CE WILL RETURN TO THE MAP DISPLAY IN THE SAME MODE AND AT THE SAME RANGE SET, WHEN INFO WAS ENTERED. ARGUS SEL MOMENTARILY DEPRESSING THE ARGUS SEL ILLUMINATED (BLUE) SWITCH CYCI RS THE ARGUS 5000/CE DISPLAY THROUGH THE VARIOUS MAP OBJECTS. ARGUS TEST MOMENTARILY DEPRESS THE ARGUS TEST SWITCH TO ENABLE DISPLAY SIMULATION TEST. THE ARGUS 5000/CE MOVING MAP DISPLAY IS APPROVED FOR IFR ENROUTE NAVIGATION ONLY WHEN RECEIVING NAVIGATION INFORMATION FROM AN IFR APPROVED GPS, LORAN, OR OTHER LONG-RANGE NAVIGATION SYSTEM. THE ARGUS 5000/CE DATABASE MUST BE CURRENT (NOT EXPIRED). THE ARGUS 5000/CE IS APPROVED FOR USE AS A SUPPLEMENTAL NAVIGATION DISPLAY FOR VFR AND IFR OPERATIONS BUT IS LIMITED TO THE APPROVAL OF THE LORAN C OR GPS NAVIGATION SYSTEM. THE ARGUS 5000/CE MOVING MAP DISPLAY HAS BEEN SHOWN TO MEET THE CRITERIA OF FAA rso-c113, AIRBORNE MULTIPURPOSE ELECTRONIC DISPLAYS, AND HAS BEEN PREVIOUSLY INSTALLED UNDER EVENTIDE INC. FAA APPROVED STC SA0054NY, IN AN AIRCRAFT AND MEETS THE FAA REQUIREMENTS FOR OPERATION IN THE AIRCRAFT DURING INSTRUMENT FLIGHT AND CAN BE USED AS A REQUIRED INSTRUMENT. THE NEW EQUIPMENT AND. ASSOCIATED SYSTEMS WERE FUNCTIONALLY TESTED PER EVENTIDE AVIONICS INSTALLATION MANUAL NO. 5003, REVISION 03.07, DATED JULY 10, 1995 WITH NO DISCREPANCIES. AN EMI TEST, REPORT NO.: B727-16236-080 REV IR, SHEETS 5, DATED 06/19/01 WAS CONDUCTED AND THE INSTALLED EQUIPMENT DOES NOT INTERFERE WITH ANY OTHER INSTALLED EQUIPMENT. MAGNETIC DIRECTION INDICATORS WERE CHECKED FOR ACCURACY AND COMPENSATED AS NECESSARY PER AC 43.13-1B, CHAPTER 12, SECTION 3, PARAGRAPH 12- 37 AND AC 43.13-2A, CHAPTER 2 PARAGRAPH 23f. THE STATIC LOADING OF THE INSTALLED EQUIPMENT MEETS THE REQUIREMENTS OF AC 43.13-2A, CHAPTER 1, PARAGRAPH 3 AND WAS FOUND TO MEET THE REQUIREMENTS OF PARAGRAPH 2. MATERIALS AND PRACTICES COMPLY WITH PARAGRAPHS 4 THROUGH 12. THE ELECTRICAL LOAD ANALYSIS UPDATE REPORT NO. B727-I6236-041, REV IR, SHEETS 1 THRU 21, DATED 06/11/2001 WAS COMPLETED IN ACCORDANCE WITH AC43.13-1B, CHAPTER 11, SECTION 3, PARAGRAPH 11-37. 1S] Additional Sheets Are Attached * U.S. G.P.O 1990-761-753 EFTA00277667

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 accomplished.) AIRCRAFT: BOEING, TYPE: 727-31, SIN 20115, DATE: 06/1442001, W.O. 16236, PAGE 2 OF 2 AIRCRAFT METAL WORK INVOLVING METAL REPAIR OR ALTERATION COMPLIES WITH AC43.13-1B, CHAPTER 4, SECTIONS 1, 2, 3 AND 4, CHAPTER 6, SECTIONS 3 AND 8. HARDWARE AND MATERIALS USED IN THE INSTALLATION CONFORM TO AC43.13-1B, CHAPTER 7, SECTIONS 1- 5 AS APPLICABLE. CIRCUIT BREAKERS, SWITCHES AND CONNECTORS ARE OF THE TYPE RECOMMENDED BY THE AIRCRAFT MANUFACTURER OR ARE MIL SPEC APPROVED FOR AIRCRAFT USE AND MEET THE REQUIREMENTS OF AC43.13-1B, CHAPTER 11, SECTION 4. ELECTRICAL/ELECTRONIC WIRING WAS SELECTED AND INSTALLED IAW AC43.13-1B, CHAPTER 11, SECTIONS 5-8, 13, 15, 17-19 AND AC43.13-2A CHAPTER 2, PARAGRAPHS 21, 22 & 27. ROUTING, LACING AND TYING COMPLIES WITH AC43.13-1B, CHAPTER 11, SECTIONS 9-12. WIRE MARKING COMPLIES WITH AC43.13-1B SECTION 16. ELECTRONIC EQUIPMENT INSTALLATION COMPLIES WITH THE AIRCRAFT AND EQUIPMENT MANUFACTURER'S INSTRUCTIONS AND AC43.13-2A, CHAPTER 2, PARAGRAPHS 21 THROUGH 26 AND CHAPTER 3, PARAGRAPH 44. 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 IAW AC43.13-1B, CHAPTER 10, SECTION 2 AND AC 43.13-2A, CHAPTER 1 PARAGRAPH 9. MAINTENANCE FOR CONTINUED AIRWORTHINESS IS OUTLINED IN EVENTIDE AVIONICS DRAWING NO. 14O003, REV. B, DATED JUNE JUNE 4, 1999, AND STATES THAT THE ARGUS 5000/CE MOVING MAP DISPLAY SYSTEM IS "ON CONDITION". THE REQUIRED F.A.A. ARPROVED FLIGHT MANUAL SUPPLEMENT DOC NUMBER B727-16236-I01, REV IR, PAGES 1 THRU 6 DATED JiJ lie 2 00 I HAS BEEN INSERTED INTO THE AIRCRAFT FLIGHT MANUAL. END K Additional Sheets Are Attached * U.S. G.P.O 1990-761-753 EFTA00277668

. AI as EFTA00277669

• Jet Aviation Associates Ltd. Bldg. 1515 Perimeter Rd. Palm Beach Int'l Airport West Palm Beach, FL 33406 FAA CRS EYKR782D Document No. B727-16236-101 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.: N908JE SERIAL NO.: 20115 WITH A. SINGLE EVENTIDE AVIONICS ARGUS 5000/CE MOVING MAP DISPLAY This supplement must be attached to the FAA approved Airplane Flight Manual when the airplane is modified by the installation of a single Eventide Avionics Argus 5000/CE Moving Map Display receiving navigation inputs from the No. 1 UNS-1D Flight Management System (FMS) in accordance with manufacture's Installation Manual No_ 50 3 Revision 03.07, dated July 10, 1995 or later approved revision and FAA Form 337, dated "7/ 7 O/ 1 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: Federal Aviation Administration Flight Standard District Office - 17 1050 Lee Wagener Blvd. Ft. Lauderdale, Florida 33315 FAA Approved Date: JUN 2 1 2001 Page 1 of 6 EFTA00277670

• 6 EFTA00277671

O-01 08:53 Jet Aviation ,Jun -20-01 08:03A N 3 Curran 352 243 1011 P-02 P _ 02 C DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAI. AVIATION REGULATIONS DATI:. 06/20/2001 • •I AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Boeing MODEL NO. • 727-31 TYPE (Alt-Mane. Radio. Helicopter. etc) Airplane NAME OF APPLICANT Jet Aviation Associates West Palm Beach, FL LIST OF DATA IDENTIFICATION TITLE B727-16236-270, Revision A, dated 06/19101 ARGUS 5000/CE MOVING MAP DISPLAY • PURPOSE OF DATA In support of major alteration to.Boe-ing 727-31, serial number 20115, registration number N905.1E. APPLICABLE REQUIREMENTS (List specific sections) FAR 25.869 (a)(4) FAR 25.1431 (a)(b)(c) FAR 25.1301 (a)(b)(c)(d) FAR 25.1529 FAR 25.1309 (a)(b)(g) FAR 25.1581 (a)(b)(d) FAR 25.1351 (a) FAR 26.1357 (a)(c) CERTIFICATION -'Witt ratthont• .vault by ain-criaa Isla loud obwre AuK1006 al/talked OK'd, ..00t Iscrrsi 'WINE of tart- AitagigolfiltOr slid it, WroidliaCe 1.101 tau:gime, aid tiviii.O•As of tippAix1Ann I grfttles, Fan ISJ if the Finlitral Ariati.• Kepis hods, hare bora tisairrid no stionti.or ...III, ntsobik lord prolletturn and hoad no cn..pty will. applicable mtikeoph-xti ei Ow I edc.1 .4.'114. these data & Equipment Aspects. Desi/a Approval Only. Does Plot ('osassita he Installation Approval) Rtptatanwl a Recommend approval of I (We) Therefore L] Approve these ties (Systems SI GNATILIKEIS) N El) ENG) NG REPRESENTATIVEISI DESIGNATION NOM BER(SI CLANSIFIE •rtnhts €40---- DERT-510087-NM Systems & Equipment an — FAA Form 8110-3 n i-70) SUPERSETWC PREVIOUS EDITION CiPO 9O1-613 FLLENAIME: SC-127-NCINGMAP_ADOC EFTA00277672

..I EFTA00277673

k 4 71& . JEF NIf/R11-10111 JET AVIATION ASSOCIATES, LTD 1515 PERIMETER ROAD PALM BEACH INT'L AIRPORT WEST PALM BEACH, FLORIDA 334O6-1493 561-233-7262 FAX 561 -233-7279 CRS-EYKR782O MODIFICATIO\ DAWING PROPRIETARY NOTES Ths drcrwlng contoins specifications and/or data. technical materiel, proprietary designs and information that ere the sate property of JET AVIATION ASSOCIATES. LTD. to be held and treated by its recipient on o confidential basis and is not to be shown or disclosed to any unauthorized organization or person without the written authorization of JET AVtATION ASSOCIATES. LTD. TITLE: LASERTRAK SYSTEM MODIFICATION PAGE: 1 OF 1 DWG NO.: 34-61-32-1 REASON: RE-BUSS LASERTRAK INSTRUMENT LIGHTING FROM CENTER PANEL TO CAPTAINS INSTRUMENT PANEL DUE TO RELOCATION OF INSTRUMENT A NOTES: 1. AIRCRAFT WIRING INSTALLATION CHAPTER 11, SECTIONS 2. ALL WIRE PER MIL 3. ALL SHIELDED WIRE 4. ALL WIRE 20 AWG 5. ALL CIRCUIT BREAKERS 6. ALTERNATE TWISTED TRIPLE TWISTED: • . TWISTED PAIR: 7. LOWER CASE LEITERS 8. THIS MODIFICATION SYSTEM PER THE I REGARDING THE LASERTRAK DWG. 34-61-32. TO THE ORIGINAL ITAPT BRGAIST IND. i H I INSTR LTS{ ci tI rr, i L .A.,__. __...y__. _ _.•\„,.._ LOC: CAPT. INSTR. PANEL rIASERTRAK CDI I I- I H IT ) INSTR LTS { I i I I ...- LOC: CAPT. INSTR. PANEL IAW FM A.C. 43.13-1B, 1, AND 3-20. -W-22759 UNLESS SHIELDED. PER MIL- C-27500TG. UNLESS SPECIFIED OTHERWISE. PER MS36574. WIRE COLORS MAY BE SUBSTITUTED: PRIMARY SUB LASERTRAK PAGE AVJET DWG. 33-11-11 RED (R) WHITE (W) BLUE (B) BLUE (B) YELLOW (Y) ORANGE (0) RED (R) WHITE (W) BLUE (B) BLUE (B) ARE SHOWN UNDERLINED. I.E. ci. DRAWING ONLY CHANGES THE EXISTING WIRING SHOWN, FOR ALL OTHER INFORMATION SYSTEM REFER TO ORIGINAL PAGE THIS MODIFICATION DRAWING SHALL BE ATTACHED PAGE AVJET DRAWING FOR REFERNCE. 09504 20 „T, I-- 20 ill — 019 -20 — — —5 ----018-20---o M • D9315 D9315 1 20 } 09315-9-20 Q SYMBOL AND NUMBER REFERS TO PARTS LIST ITEM NUMBER. A SYMBOL AND NUMBER REFERS TO INSTALLATION NOTES. O SYMBOL AND LETTER REFERS TO LIKE LETTER IN SYMBOL ON THIS DWG. NO. =DC GND GROUND NOTES: { -D> =SHLD GND NEW WIRE WIRE TYPE NOTES: -C> =AC GND --I> =CHASSIS GND REMOVED WIRE EXISTING WIRE (* ) (_ - - -) ( ) /G. SCALE: NONE SER. NO.: 20115 PREPARED BY: G.L. KARR APPROVED BY: T. JARDINE 1 A/C MODEL: 727-100 REG. NO.: N908JE DATE: 05/24/01 DATE: 05/24/01 EFTA00277674

♦. EFTA00277675

ty DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE June 3, 2001 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Boeing MODEL NO. 727-31 TYPE (Airplane, Radio, Helicopter,etc.) Airplane _ NAME OF APPLICANT Jet Aviation Associates- WPB LIST OF DATA IDENTIFICATION TITLE B727-16236-1270 B727-16236-1331 •• Argus 5000/CE Moving Map Equipment Installation Sht 1-5, Rev IR Aircell Equipment Installation, Sht 1-6, Rev IR Note: 1. This approval is for structural aspects only. 2. This approval is based on drawing review and inspection. 3. After the alteration, the aircraft must be returned to service by FAA authorized personnel. PURPOSE OF DATA To approve structural aspects of a major alteration to Boeing 727-31, S/N: 20115 APPLICABLE REQUIREMENTS (List specific sections) FAR 25.301 25.303 25.305(a) 25.307(a) 25.321(a) 25.561 25.601 25.603 25.605(a) 25.609 25.611 25.613 25.789 CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions under Part 183 of the Federal Aviation Regulations,data listed above and on attached sheets numbered in accordance with established procedures and found to comply with applicable requirements of the Federal Recommend approval of these data. I ( X Therefore Approve these data. and limitations of appointment 0 have been examined Aviation Regulations. SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) David E. Haralson Jr-;.,:ie. iici-ez.— DERT-810028-N E Structural FAA Form 8110-3 (11-70) SUPERSEDES PREVIOUS EDMON ER01207.doc EFTA00277676

id EFTA00277677

Q-• O MAJOR REPAIR AND ALTERATION US t Departmen of Transportation (Airframe, Powerplant, Propeller, or Appliance) Federal Aviation Administration F o r m Approved OMB No. 2120-0020 For FAA Use Only Office Identification 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 727-31 Serial No. 20115 Nationality and Registration Mark U.S.A. N908JE 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 crv3 data Identified heroin compile* ainevorthinee requirements is approved described aircraft. Contor -uthorized in FAR 43, s on 43.7. JUN t 1 20P1 , or* the applicable for the above by a person - 1 7 50- SR) Date ginnfett of FAA inspector 4. Un Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer ,,. 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. JET AVIATION ASSOCIATES LTD. 1515 PERIMETER RD. WEST PALM BEACH. FL. 33406 U.S. Certified Mechanic CRS AIRFRAME RADIO LIMITED EYKR782D 1,3. 1,2,3. Foreign Certified Mechanic x Certificated Repair Station Manufacturer AF &ENG, D. I certify that the repair and/or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date -7/0 ) . Signature of Authorized Individual /L.- t 35-- John K. Urso. Inspector. eA— 7. Approval for Return to Se ce Pursuant Administrator BY to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is 0 APPROVED K REJECTED Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA FAA Designee X Repair Station Person Approved by Transport Airworthiness Group Date of Appr val r Rejection 9 - . /. Certificate or Designation No. EYKR782D Signature of Authorized Individual Ronald K. Bystrom. Manager Quality Assuranc .//' FAA Form 337 (12-88) EFTA00277678

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with afl 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 accomplished.) AIRCRAFT: BOEING, TYPE: 727-31, S/N 20115, DATE: 06/14/2001, W.O. 16236, PAGE 1 OF 2 REMOVED THE EXISTING NO. 1 AND 2 HONEYWELL NZ-920 FMS SYSTEMS AND THE DL-900 DATA LOADER UNIT, AND INSTALLED DUAL UNIVERSAL AVIONICS CORP. UNS-ID FLIGHT MANAGEMENT SYSTEMS (FMS) WITH INTEGRAL GPS SENSORS, A UNIVERSAL AVIONICS CORP. RADIO TUNING UNIT (RTU), AND A UNIVERSAL AVIONICS CORP. DTU-100 DATA TRANSFER UNIT (DTU). THIS MODIFICATION WAS COMPLETED USING ita AVIATION DRAWING NO. B727-16236-410, NO. 1 FLIGHT MANAGEMENT SYSTEM, REV IR, DATED 04/10/01 AND B727-16236-411, NO.2 FLIGHT MANAGEMENT SYSTEM, REV. IR, DATED 04/15/01. THE RTU WAS INSTALLED USING JET AVIATION DRAWING NO. B727-16236-293, FLIGHT MANAGEMENT SYSTEM RADIO TUNING UNIT, REV IR, DATED 04/16/01. REFERENCE FAA FORM 8110-3 DATED 05/29/2001 BY SYSTEMS AND EQUIPMENT DER NO. DERT-510087-NM. crli Mr" 25,4+ 11,313;i ts:;::, sC r..:•, ,d,3 orb FOi tno ---, ,,Avfnft= 2t Inc dirlartrup11 THE STRUCTURAL INSTALLATION OF EACH FMS, THE DTU;`' irrtintlIT WEItte9y1P4t7TgRy, .IL7T AVIATION DRAWING NO. B727-16236-1410, DUAL FMS W/RTU EQUIPMENT INSTALLATIONS, REV. IR, DATED 05/1'7/91, cg FAA FORM 8110-3, DATED JUNE I, 2001 BY STRUCTURES DER NO. DERT-810028,- ANTENNAS WER AILED USING JET AVIATION DRAWING NO. B727-16236-144I, GPS ANTENNA INSTALLATI REV. A, DATED 05/29/01, REFERENCE FAA FORM 8110- 3, DATED 6/18/01 BY STRUCTURES DER NO. DERT-510024-CE. THE UNS-1D SYSTEMS RECEIVE BARO-CORRECT1ED ALTITUDE AND TAS INFORMATION FROM THE NO. 1 AND NO.2 AIR DATA COMPUTERS RESPECTIVELY, VOR/DME BEARING AND DISTANCE INFORMATION FROM THE NO. I AND NO.2 COLLINS VIR-432 AND DME-442 SYSTEMS, AND CROSS SIDE GPS INFORMATION AS WELL AS EACH UNITS INDEPENDENT GPS SENSOR DATA, FUEL FLOW DATA FROM THE AIRCRAFT FUEL FLOW SYSTEM AND IRS INFORMATION FROM THE EXISTING NO. 1, 2, AND 3 HONEYWELL "LASERREF" SYSTEMS. THE UNS-ID FMS HAS BEEN PREVIOUSLY INSTALLED UNDER UNIVERSAL AVIONICS SYSTEMS CORP. FAA APPROVED STC SA5072NM, IN AN AIRCRAFT AND CERTIFIED FOR VFR AND IFR NAVIGATION WHICH QUALIFIES THIS INSTALLATION AS A "FOLLOW ON" INSTALLATION PER AC 20-130A. THE UNS-1D FMS SYSTEMS HAVE BEEN SHOWN TO MEET ALL OF THE REQUIREMENTS OF AC-20-130A FOR VFR-IFR NAVIGATION ENROUTE, TERMINAL, OVER WATER AND IN REMOTE AREAS, AND FOR NON-PRECISION APPROACHES. THE NO.1 AND 2 FMS SYSTEMS ARE DIGITALLY INTEGRATED TO THE EXISTING HONEYWELL FIVE-TUBE ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS). THE PILOT AND COPILOT'S EFIS SYMBOL GENERATOR'S HAVE HONEYWELL SERVICE BULLETIN A21-2000-028 AND THE MULTI-FUNCTION GENERATOR HAS HONEYWELL SERVICE BULLETIN A21-2000-029 TO INCORPORATE NON-PRECISION GPS SCALING VIA GAMA ARINC 429 LRN INTERFACE WHICH MEETS REQUIREMENTS OF TSO C129A AND AC 20-130A. THE FMS SYSTEMS ARE CROSS-COUPLED TO EITHER THE PILOT OR COPILOT EFIS FOR DISPLAY AND NAVIGATION. THE EFIS CONVERTS THE DIGITAL TO ANALOG OUTPUTS AND PROVIDES ALL LATERAL STEERING TO THE AUTOPILOT AND FLIGHT DIRECTOR SYSTEM. VERTICAL NAVIGATION (VNAV) FROM EITHER FMS SYSTEM IS NOT DISPLAYED OR COUPLED IN THIS INSTALLATION. THE FOLLOWING REQUIRED ANNUNCIATORS FOR THE FMS SYSTEMS ARE DISPLAYED ON THE EFIS DISPLAYS: FMS MSG INDICATES A MESSAGE IS TO BE ACKNOWLEDGED ON THE MSG PAGE. (COLOR: AMBER) LOCATED ON EADI. XTK SELECTED CROSSTRACK IS ACTIVE. (COLOR: CYAN) LOCATED ON EHSI. WPT INDICATES WAYPOINT ALERT TWO MINUTES PRIOR TO WAYPOINT IN EN ROUTE MODE, AND 15 SECONDS PRIOR IN APPROACH MODE. WHEN THIS ANNUNCIATOR FLASHES, IT INDICATES THAT AN UPCOMING VERTICAL FLIGHT PATH ANGLE (FPA) CHANGE IS WITHIN TWO MINUTES. (COLOR: AMBER) LOCATED ON EHSI. APP AN APPROACH HAS BEEN ACTIVATED. (COLOR: CYAN) LOCATED ON EHSI. El Additional Sheets Are Attached * U.S. G.P.O 1990-761-753 EFTA00277679