Aircraft Acquisition Technical Specifications Revised 15 Dec 25.pdf

U.S. Marshals Service (USMS) Justice Prisoner Air Transportation System (JPATS) Aircraft Technical Specifications for the Purchase of

One Boeing 737-700 or 737-800 Aircraft

Original Revision December 15, 2025

Table of Contents

1. General

2. Aircraft Requirements and Configuration

2.1. Airframe

2.2. Avionics

2.3. Software

2.4. Powerplant

2.4.1. Engines

2.4.2. Auxiliary Power Unit (APU)

2.5. Publications

2.6. Reports, Records, and Miscellaneous Documentation

3. JPATS Owned Boeing 737-400 Aircraft and Spare Parts Purchase Requirement

4. Deliverables

5. Pre-Award Inspection, Final Delivery / Inspection and Acceptance of the Aircraft

5.1. Pre-Award Inspection

5.2. Final Delivery / Inspection

5.3. Deliverables

5.4. Delivery Location

5.5. Other Final Delivery / Inspection Items and Acceptance Flight

5.6. Final Delivery / Inspection and Acceptance Flight Deficiencies

5.7. Termination for Cause

Appendix A: Airframe Information Appendix B: Powerplant Specifications Appendix C: Landing Gear Specifications Appendix D: Avionics Equipment List Appendix E: Software List Appendix F: Autoflight and Autothrottle System Software Options Appendix G: Common Display System Software Options Appendix H: Brake Temperature Monitoring System Software Options Appendix I: Air Temperature Measurement System Software Options Appendix J: Ground Proximity Warning System Software Options Appendix K: Ground Proximity Warning System Warning and Cautions Functionality Appendix L: Flight Management Computer Software Options Appendix M: Flight Control Computer Software

1. General

The primary mission of U.S. Marshals Service (USMS), Justice Prisoner Air Transportation System (JPATS) is the safe, secure, and efficient transportation of federal and non-federal prisoners and the provisioning of aircraft and flight crew for the support of other operational missions. Additional mission assignments include, but are not limited to, international flights in support of foreign extraditions, witness security and enforcement operations, strategic deployment of USMS and Special Operations Group personnel and equipment and other special operations assigned by the USMS or U.S. Attorney General.

JPATS has a requirement to purchase one (1) Boeing 737-700 or 737-800, transport category, narrow body, twin engine jet aircraft. This aircraft will be operated primarily from the JPATS Oklahoma City, Oklahoma operational site but may at times, based on particular mission demands, operate from other JPATS operational sites. The aircraft will be operated by JPATS as a Public Aircraft meeting the mandatory requirements of 14 CFR Part 91 for operations in the National Airspace System. JPATS will take delivery of the aircraft 12 weeks after contract award.

2. Aircraft Requirements and Configuration

The Contractor shall provide one (1) Boeing 737-700 or 737-800 aircraft that, at time of delivery:

2.1. Airframe

2.1.1. Is a large, transport category, narrow body, twin engine jet aircraft with a United States of America registration (“N” number) and a current and valid FAA issued Standard Airworthiness Certificate.

Note: The aircraft registration number must be changed prior to delivery.

JPATS will provide a reserved Special N-Number to the contractor at the time of contract award.

2.1.2. Meets all specifications of its original Type Certificate in accordance with 14 CFR Part 25.

2.1.3. Is currently being maintained and inspected on an approved, aircraft serial number specific, maintenance and inspection program.

2.1.4. Has not accumulated more than 40,000 cycles since new (CSN).

2.1.5. Is certified for day, night, Visual Flight Rules (VFR), Instrument Flight Rules (IFR) operations, and flights into known icing conditions.

2.1.6. Is “Stage 3” noise level compliant with maximum takeoff noise levels not exceeding those levels as prescribed in 14 CFR Part 36, Section B36.5 (d) of Appendix B and International Civil Aviation Organization (ICAO) Annex 16, Environmental Protection, Volume 1, Aircraft Noise, Third Edition, July 1993, Amendment 7, effective March 21, 2002, or later edition.

2.1.7. Has a minimum of 132 passenger seats installed. All installed seats shall be “Tourist Class” configuration and meet 14 CFR Part 121 standards for the carriage of passengers. Seat cushions, seat covers, and seat backs must be leather and conform to 14 CFR Part 121 burn certification criteria.

2.1.8. Is equipped with three (3) flushable lavatories; one located in the forward cabin, two located in the aft cabin, and configured for external servicing.

2.1.9. Is equipped with Boeing OEM self-contained, powered, forward air stairs at the L-1 door.

2.1.10. Has all hard time-controlled parts (defined as any part that requires maintenance at a predefined interval) and Life Limited Parts (LLP) that are associated with the airframe, appliances, and landing gear at “mid-life” or greater, meaning they have 50% or greater life remaining based on the interval specified by the manufacturer in terms of flight hours, flight cycles, or calendar months.

2.1.11. Has all hard time-controlled parts (defined as any part that requires maintenance at a predefined interval) and Life Limited Parts (LLP) serviceable and supported by appropriate certification documentation with either an EASA Form 1, FAA Form 8130-3, or CAA Form 1 with back-to-birth traceability for each landing gear installed.

2.1.12. Is in compliance with all applicable FAA issued Airworthiness Directives (AD) and manufacturer mandatory Service Bulletins (SB). Any repetitive (recurring) inspections that are associated with these ADs and SBs must not come due within 12 months of contract award unless recurring inspection interval is less than 12 months.

2.1.13. Is in compliance with all maintenance requirements from either a Manufacturer or FAA approved maintenance program.

2.1.14. Has no “Scheduled” Heavy Maintenance or Major Inspection (C Check or higher) within 12 months of aircraft delivery date.

2.1.15. Is equipped with emergency equipment and over water passenger operations equipment in accordance with 14 CFR Parts: 121.309, 121.310, 121.337, and 121.339.

2.1.16. Has a Maximum Takeoff Weight (MTOW) as follows:

• Boeing 737-700 aircraft must have a MTOW of 154,500 lbs.

• Boeing 737-800 aircraft must have a MTOW of 174,200 lbs.

2.1.17. Has the minimum number of flight attendant seats required by 14 CFR Part 121.

2.1.18. Has standard “airline” type and style galleys with service carts, coffee makers, and ovens installed.

2.1.19. Has “moon mat” installed in the cabin, galleys, and lavatories.

2.1.20. Has a reinforced Flight Deck Door meeting the standards for a 14 CFR Part 121.313 commercial air carrier.

2.1.21. Has a non-descript paint scheme with no logos from any previous operator visible.

2.1.22. Has its appropriately assigned U.S. registration (“N”) number applied to the aircraft in accordance with 14 CFR Part 45.25 requirements.

2.1.23. Has all impact structural damages (regardless of cause) permanently repaired in accordance the Manufacturer Structural Repair Manual (SRM) or other EASA / FAA-approved data. There shall be no temporary repairs, time-limited repairs or repairs requiring repetitive inspections.

2.1.24. Is free of fuel, oil, hydraulic, and pneumatic leaks. All repairs of leaks must be permanent repairs. The fuel tanks must have no leaks and demonstrated as follows:

• Refuel the left wing tank to a minimum of 8,000 pounds.

• Refuel the right wing tank to a minimum of 8,000 pounds.

• Refuel the center wing tank to a minimum of 15,000 pounds.

• After a minimum of 24 hours, the aircraft will be inspected for fuel leaks.

2.1.25. Has a fuselage free of dents and abrasions.

2.1.26. Has windows free from delamination, blemishes, crazing, and properly sealed with all window shades operating smoothly.

2.1.27. Has doors that are free moving, properly rigged, and with serviceable seals.

2.1.28. Has the wings and stabilizer’s leading edges serviceable in accordance with AMM limits (e.g. no significant hail or other foreign object damage).

2.1.29. Has horizontal stabilizer and empennage leading edges serviceable in accordance with AMM limits (e.g. no significant hail or other foreign object damage.)

2.1.30. Is equipped with a Boeing OEM Nitrogen Generation System (NGS) or a Special Federal Aviation Regulation (SFAR) 88 compliant Ignition Mitigation

Means (IMM) approved by the FAA as compliant with the FTFR requirements of 14 CFR 25.981(c) or 26.33(c)(2).

2.1.31. Is equipped with a dual (main and auxiliary) 48-AH battery installation.

2.1.32. Is equipped with a fixed permanently installed Artex B406-4 Series Emergency Locator Transmitter (ELT).

2.1.33. Has Boeing Service Bulletin 737-52-1159 embodied.

2.2. Avionics

2.2.1. Has all cockpit and cabin instrumentation, avionics, placards, and gauges readable in the English language and in the United States measuring system, except for all temperatures must be in Celsius. All engine, FMC, fuel, air, oil, oxygen, cabin pressurization, displays, and performance temperature indications in degrees Celsius and is compliant with the software configuration listed in Appendices F through M.

2.2.2. Is equipped with a Collins Avionics Suite, which consists of the following components:

• Weather Radar Receiver / Transmitter

• Passenger Address Amplifier

• VHF Transceivers

• DME Interrogators

• VOR / Marker Beacon Receivers

• Multi-Mode Receivers

• Transponders

• ADF Receiver(s), if equipped

• Low Range Radio Altimeter Receiver / Transmitters

• Communications Management Unit

• HF Transceiver(s)

2.2.3. Dual Flight Management System (FMS)

• Equipped with at least U13.0 FMS OPS Software.

• The FMS must be fully interfaced with and receive navigational data/inputs from a minimum of two (2) Inertial Reference Systems (IRS), two (2) Collins GLU-2100 Global Navigation Satellite Systems Multi-Mode Receiver (MMR) capable of Localizer Performance with Vertical Guidance capability for 3G MMR Space-Based Augmentation System (SBAS).

• Equipped with two (2) 176200-01-01 Flight Management Computers with the FMC performance parameters listed below and the software options listed in Appendix L.

Performance Parameters

RNP VRNP TIMER

Oceanic 10.0 400 60 S Enroute 2.00 400 30 S Terminal 1.00 400 10 S Approach 0.30 125 10 S

2.2.4. Equipped with two (2) FANS 1 Capable Multipurpose Control Display

Units (MCDU) P/N: 174101-03-03.

2.2.5. Equipped with two (2) Air Data Inertial Reference Units (ADIRU) P/N:

HG2050AC11 and Service Bulletin 737-34-2421 Revision 2 embodied.

2.2.6. Dual Global Navigation Satellite System (GNSS) position updating system, capable of gaining operational approval to conduct 14 CFR Part 97 instrument procedures within the U.S. National Airspace System (NAS) where domestic air traffic control (ATC) procedures are applied. Dual GNSS, compliant with latest version of TSO-C145, is compatible position source as paired with aircraft specific ADS-B OUT equipment indicated by OEM/STC/AFMS statement of compliance.

2.2.7. Capable of navigating Radius-to-Fix RNAV-1 Departure and Arrival Procedures, RNP-1 Departure and Arrival Procedures, RNAV-2 Q-Routes and T-Routes, RNP-10, RNP-4, and RNP-2 Domestic Offshore and Oceanic / Remote Enroute operations as cited by the Statement of Compliance in AFM / AFMS / POH or avionics operating manual.

2.2.8. Certified to execute RNP 0.3 Enroute and Terminal operations requiring RNAV(GPS) [GPS (RNP Approaches)] IAPs to LNAV / VNAV minima, and RNAV(RNP) [RNP-AR Approaches] IAPs to RNP 0.10 minima using Navigation Performance Scales AFDS guidance with an appropriate performance approval certification statement in the Aircraft Flight Manual (AFM), Pilots Operating Manual (POM), or aircraft approved avionics operating manual reflecting incorporation of Appendices F through M.

2.2.9. Equipped with three (3) digital VHF transceivers communication systems with a minimum of 760 channels with 8.33 KHZ spacing with three (3) Gables P/N: G7404-124 radio tuning panels with three VHF (1-2-3), two HF (1-2) and amplitude modulation (AM) switch functions in the cockpit.

2.2.10. Equipped with VHF #3 Collins Transceiver P/N: 822-1250-002 with Service Bulletin VHF-920-23-16 (Mod 16) embodied.

2.2.11. Equipped with three (3) AVTECH Audio Control Panels P/N: 5145-1-77.

2.2.12. Equipped with one (1) HF Communication System.

2.2.13. Equipped with an ICS-220A / IRT-2120 Iridium Communication System to include, as a minimum:

• Flightcrew SATVOICE calls through Cockpit Interphone system with MCDUs phone control interface functions.

• Cabin SATVOICE calling through wireless handset system.

• Call management programming system with ability to setting up and receiving SATVOICE calls within level of Priority, Preemption and Precedence (PPP) feature consistent with the table below:

Priority Level Application Category SATVOICE

Emergency

(Highest) Safety of Flight

Distress and Urgency

Inflight Emergency, Rapid Descent, Urgent Sidestep for Weather

Operational High

(2nd Highest) Safety of Flight

Flight Safety Altitude Request, ATC Clearance /

Instruction

Operational Low

(3rd Highest) Safety of Flight

Regularity of Flight, Meteorological, Administrative

Air Traffic Information Service, AOC, Redispatch, Maintenance

Non-Operational (Lowest) Non-Safety

Related

Official Correspondence

GOV Cabin User Phone Calls

For single-channel systems, if the satellite voice channel is in use for a lower priority call and the aircraft receives a higher priority call, the satellite voice equipment or network should clear the channel and accept the higher priority call. For multi-channel systems, if all available channels are in use, the equipment should preempt the channel supporting the lowest priority call in favor of the higher priority call. If SATVOICE resources are shared on the aircraft (e.g. for cabin use), the satellite voice equipment must provide the flight crew the means to preempt those resources at any time. The equipment may provide the means for preemption of resources when the flight crew makes a call.

• Audio Management System: Call alert notification, audio listen through cockpit interphone system providing full-duplex voice capability via hand, boom, and oxygen mask microphones for both pilots and any additional flight crewmember (e.g. jumpseat position).

• Flight Deck Annunciation: Alerting associated with non-normal conditions (such as failures) of the airborne SATVOICE system must comply with the appropriate part of 14 CFR 25.1322 / 1302. Reference: AC20-150() Paragraph 8 meeting all aural and visual crew alerts; airborne system failure detection; call ID termination, or connection failure indications.

• Two Independent Service Line Growth – One used for company datalink / tracking, other used for normal voice/data transmissions (total of three SATVOICE / DATA channels 1- ATS / 2-DATA / 3-GOV duty- Medical Voice / Data mix).

2.2.14. An Aircraft Data Link System that, as a minimum, has a Collins CMU- 900 Communication Management Unit (CMU) P/N: 822-1239-151, with Core 16 Software P/N: 831-6605-016, that interfaces with Aircraft Condition Monitoring System (ACMS) software functions and Digital Flight Data Acquisition Unit (DFDAU) reporting functionality. DATA LINK SOC REPORT: In addition to the avionics equipment list, appropriate to offeror configuration, a data link equipage report must include Statement of Compliance (SOC) summary.

2.2.15. Eqipped with a Rockwell Collins WXR-2100 MultiScan Weather Radar System.

2.2.16. One (1) Predictive Windshear Radar system meeting the requirement of 14 CFR Part 121.357 fully interfaced with TAWS mapping for auto tilt functions.

2.2.17. One (1) Enhanced Ground Proximity Warning System (EGPWS) with low level wind shear detection meeting the requirement of 14 CFR Part

121.358 and CDS Software integration enabling peaks and obstacle depiction and alerts. Smart 500 callout in addition to standard FAA Mode 6 callout alerts. Reference Appendix J and K for additional requirements.

2.2.18. Two (2) digital VHF, VOR / Beacon navigation receivers providing NAV-1 data on Standby RMI / DME indicator in addition with normal NAV-1 and NAV-2 on cockpit displays.

2.2.19. Distance Measuring Equipment (DME) Interrogator with Nav-1 and Nav- 2 and autotune channeling functions.

2.2.20. Equipped with two (2) Collins GLU-2100 MMRs P/N: 822-2532-100.

2.2.21. Equipped with two (2) Collins TPR-901 Transponders P/N: 822-1338- 205.

2.2.22. Is compliant with 14 CFR 91.225 Automatic Dependent Surveillance- Broadcast (ADS-B) Out Equipment and Use without any exemptions or restrictions.

For a 1090ES equipment installation required by 14 CFR 91.225 without temporary exemption restriction and must include an AFM / AFMS / STC performance compliance statement under 14 CFR 91.227 meeting the latest TSO C166b (DO-260B / Version 2) standard.

2.2.23. Traffic Collision Avoidance System (TCAS) II system that meets latest revision of TSO C–119b (Version 7.1), integrated into cockpit display and warning advisory system.

2.2.24. Equipped with two (2) Collins Low Range Radio Altimeter (LRRA) Receiver / Transmitters P/N: 822-0334-004.

2.2.25. Equipped with one (1) Solid State Digital Flight Data Recorder which complies with 14 CFR Part 121.343 and 131.344 including Part 121 Appendix B and M as applicable.

2.2.26. Has Supplemental Type Certificate (STC) ST02706AT embodied for the installation of the L-3 Comm. Corp. micro Quick-Access Recorder (QAR).

2.2.27. Equipped with Honeywell Digital Flight Data Acquisition Unit (DFDAU) P/N: 967-0212-002 with the following software installed:

Software Software Part Number DFDAU Mandatory (DB) 998-2512-504

DFDAU 429 BROADCAST DB 998-2513-504

ACMS SYSTEM/APPL SW 998-2361-509

2.2.28. One (1) Digital Cockpit Voice Recorder that records all flight crew

SATVOICE, HF, VHF, interphone, and cockpit area communications including datalink messages in crash survivable memory.

2.2.29. Equipped with Thales Avionics Integrated Standby Flight Display (ISFD) P/N: C16221KA02 or P/N: C16786HA02 with ILS / GS deviation indications from MMR #1, and MAG HDG from ARIRU #1 or automatic TRUE HDG in Polar regions.

2.2.30. Equipped with Gables ATC / TCAS Control Panel P/N: G6992-240.

2.2.31. Equipped with two (2) Stall Management Computers P/N: 285A1010-9.

2.2.32. Equipped with Mode Control Panel (MCP) P/N: 822-1567-101, P/N: 822-

1567-102, P/N: 822-1567-103, P/N: 822-1567-104, or P/N: 4082260-939.

2.3. Software

2.3.1. Is compliant with the software configuration listed in Appendices F through M.

2.3.2. Is accompanied with a current Software Configuration List that includes the software listed in Appendix E: Software List.

2.3.3. Is accompanied with a physical and electronic copy of the software listed in Appendix E: Software List.

2.4. Powerplant

2.4.1. Engines

• Are equipped with the appropriate engine package for the aircraft being offered:

o Boeing 737-700 aircraft must have CFM56-7B24/B1 engines installed.

o Boeing 737-800 aircraft must have CFM56-7B26 engines installed.

• Has a minimum of 5,000 cycles remaining prior to any scheduled shop visit (scheduled off-wing maintenance) with any recurring inspections identified.

• Is accompanied by an on-wing Max Power Assurance Run sheet showing clear documentation of full rated thrust for each engine installed with demonstrated EGT Margins of not less than 20 degrees. This requirement must be performed after the last flight of the previous operator and prior to the first flight by JPATS.

• Has a minimum of 120 flight days of engine trend data.

• Has engines eligible for enrollment in an “industry standard” Power by the Hour engine maintenance program.

• Has each hard time-controlled part (defined as any part that requires maintenance at a predefined interval) and life limited parts (LLP) serviceable and supported by appropriate installation certification documentation with either an EASA Form 1, FAA Form 8130-3, or CAA Form 1.

• Has back-to-birth traceability for each engine installed.

• Is accompanied with a Mini Pack, for each engine installed, that, as a minimum, includes the following documents:

o FAA Form 8130-3 o FAA Form 337 o Life Limited Parts (LLP) Status o Current Status of Airworthiness Directives o Current Status of Service Bulletins o Engine Test Cell Data o Borescope Report o QEC Inventory Report

2.4.2. Auxiliary Power Unit (APU)

• Is equipped with APU Model GTCP131-9B P/N: 3800702-1 and is suitable for providing ground electrical power and self-contained engine starts. It must be capable of supplying electrical power to the aircraft’s electrical system while airborne and running two environmental systems, simultaneously, for ground heating or cooling of the aircraft.

• Has each hard time-controlled part (defined as any part that requires maintenance at a predefined interval) and life limited parts (LLP):

o At “mid-life” or greater, meaning they have 50% or greater life remaining based on the interval specified by the manufacturer in terms of APU Hours or APU Cycles.

o Serviceable and supported by appropriate installation certification documentation with either an EASA Form 1, FAA Form 8130-3, or CAA Form 1.

• Has back-to-birth traceability.

• Is accompanied with a Mini Pack, that, as a minimum, includes the following documents:

o FAA Form 8130-3 o FAA Form 337 o Life Limited Parts (LLP) Status o Current Status of Airworthiness Directives o Current Status of Service Bulletins o APU Test Cell Data o Borescope Report o QEC Inventory Report

2.5. Publications

2.5.1. Has a printed and electronic copy of the current, aircraft serial number specific, Boeing Airplane Flight Manual (AFM) with Performance Specifications and Systems Description and Operation in English print and United States measurement units (except Temperature in degrees C).

2.5.2. Has a printed and electronic copy of the current, aircraft serial number specific, Flight Crew Operating Manual (or equivalent) in English print and United States measurement units (except Temperature in degrees C).

2.5.3. Has two (2) printed and an electronic copy of the current, aircraft serial number specific, Quick Reference Handbooks (QRH) in English print and United States measurement units (except Temperature in degrees C).

2.5.4. Is accompanied with documentation and manuals for the operation of the aircraft flight systems (e.g. FMS, TCAS, etc.) that are not addressed in the current, aircraft serial number specific, Flight Crew Operating Manual.

2.5.5. Has the current Weight and Balance Manual (if separate from the Airplane Flight Manual) in English print and United States measurement units.

2.5.6. Has a printed and electronic copy of the current, aircraft serial number specific, Minimum Equipment List (MEL) in English print and United States measurement units.

2.5.7. Is accompanied with all data packages for all installed STCs, major repairs, and alterations.

2.5.8. Is accompanied with, as a minimum, an electronic copy of the following manuals:

• Aircraft Maintenance Manual (AMM)

• Aircraft Illustrated Parts Catalog (AIPC)

• Wiring Diagram Manual (WDM)

• Fault Isolation Manual (FIM)

• Structural Repair Manual (SRM)

• Airworthiness Limitations – Line Number Specific (AWLLNS)

• Special Compliance Items / Airworthiness Limitations (SCIAWL)

• Task Cards (TASK)

2.6. Reports, Records, and Miscellaneous Documentation

2.6.1. Is accompanied with a current (within 12 calendar months) and valid (meeting FAA standards) Weight and Balance report in English print and US measurement units accomplished in accordance with the applicable manufacturer’s weight and balance manual. At a minimum, the report will provide the aircraft’s configuration at weighing, empty weight, weight and moment for each gear, basic empty weight, and basic empty weight present of MAC.

2.6.2. Is accompanied with a current aircraft serial number specific Layout of Passenger Accommodations (LOPA) in English print and United States measurement units.

2.6.3. Is accompanied with a current aircraft serial number specific Emergency Equipment Layout in English print and United States measurement units.

2.6.4. Is accompanied with a current Aircraft Equipment List in English print and United States measurement units. Prior to aircraft delivery, the Contractor must complete Appendix D: Avionics Equipment List.

2.6.5. Is accompanied with a current, aircraft serial number specific, maintenance and inspection status report (in a format acceptable to JPATS).

2.6.6. Is accompanied with the following reports, current at the time of delivery:

• Airworthiness Directive Status for the:

o Airframe, o Engines, o Auxiliary Power Unit (APU), o Landing Gear, and o Appliances.

• Service Bulletin Status for the:

o Airframe, o Engines, o Auxiliary Power Unit (APU), o Landing Gear, and o Appliances.

• Hard Time-Controlled Component Status

• Instructions for Continued Airworthiness (ICA) Status

• Supplemental Type Certificate (STC) List

• Major Repairs and Alterations List

• Landing Gear Life Limited Parts (LLP) Status

• Engine Life Limited Parts (LLP) Status

• Auxiliary Power Unit (APU) Life Limited Parts (LLP) Status

• Flight Hour and Flight Cycle Status

• Dent and Buckle Report

• Electrical Load Analysis (ELA) with Coordination Sheet including all associated aircraft alterations.

2.6.7. Is accompanied with an editable electronic copy of the aircraft’s maintenance and inspection program.

2.6.8. Is accompanied with all historical records.

2.6.9. Is accompanied with The Loading System Substantiation (Engineering Report) Document / envelope / LOPA combination for Narrow Body aircraft.

3. JPATS Owned Boeing 737-400 Aircraft and Spare Parts Purchase Requirement

The Contractor must provide JPATS with an offer to purchase a JPATS owned Boeing 737-400 aircraft and spare parts. To assist in determining the value for the purchase of the aircraft and all spare parts, JPATS will provide the following documents:

• Maintenance Status Report

• Engine LLP Report

• APU Mini Pack

• Landing Gear Mini Pack and LLP Report

• Avionics Inventory

• STC List

• Out of Cycle Maintenance Requirements Report

• Part List

The Contractor must be aware JPATS owned Boeing 737-400 aircraft will be sold in an “AS IS, WHERE IS” condition and JPATS reserves the right to either accept or reject the Contractor’s offer. If JPATS elects to accept the Contractor’s offer, the funds due to JPATS will offset the purchase price of the Contractor’s aircraft, and the Contractor can anticipate the JPATS owned Boeing 737-400 aircraft will be ready for pickup not earlier than twenty-eight (28) days after JPATS final acceptance of the Contractor’s aircraft.

4. Deliverables

Item Number Description Due Date

A Boeing 737-700 or 737-800 aircraft that meets the requirements of this Technical Specifications Document.

12 Weeks After

Award

2 All publications listed in Section 2.5 At Delivery

3 A physical and electronic copy of all software listed in Appendix E.

At Delivery

An EASA Form 1, FAA Form 8130-3, or CAA Form 1 for each hard time-controlled part and life limited part (LLP) installed on the aircraft, engine, APU, or landing gear.

At Delivery

5 Back-to-birth traceability for each landing gear installed on the aircraft.

At Delivery

6 Back-to-birth traceability and mini packs for each engine and APU installed on the aircraft.

At Delivery

7 All reports, records, and documentation listed in Section 2.6.

At Delivery

5. Pre-Award Inspection, Final Delivery / Inspection and Acceptance of the Aircraft

5.1. Pre-Award Inspection

After all Offers have been evaluated and an Apparent Successful Offeror has been determined, the Apparent Successful Offeror will be notified to present the aircraft for a pre-award inspection. This inspection will take place not later than 14 days after notification at a location determined by the Offeror within the Continental United States (CONUS). A period of up to three (3) days will be required for the pre-award inspection. The purpose of this pre-award inspection is to determine if the condition of the aircraft is as presented in the Offeror’s proposal. If the aircraft is found to not meet all of the requirements as detailed in the Aircraft Technical Specifications and as presented in the Offeror’s proposal, the Government will then determine if those items not meeting the Aircraft Technical Requirements can be corrected prior to Final Delivery/Inspection of the aircraft (within 12 weeks after contract award). If the Government determines they can, then award will be made to the Apparent Successful Offeror and the Contractor shall bring the aircraft up to the technical requirements prior to final delivery/inspection and acceptance by the Government. If the Government determines the aircraft requires extensive repairs/modifications and cannot reasonably become “Acceptable” within 12 weeks after contract award, the aircraft will be determined to be “Unacceptable” and the offer will not be further evaluated, nor considered for award. The Government plans to utilize an independent third-party expert(s) to assist with this pre-award inspection.

5.2. Final Delivery / Inspection

The Contractor shall configure the aircraft for final delivery/inspection and acceptance not later than twelve (12) weeks after award. The aircraft shall be delivered in an airworthy condition, in good working order, condition and appearance, with all pilot reported discrepancies and deferred maintenance items cleared, clean by commercial airline standards, and ready for flight with all of the aircraft equipment, components, and systems operating within limits specified in the appropriate aircraft maintenance manual and functioning in accordance with their intended use. There shall be no “on-watch” conditions, special callouts, special repetitive inspections, deferred maintenance, special waivers, or exemptions in effect on the Airframe, any Engine, the APU, or any part. The aircraft shall be in full compliance with the rules and regulations of the FAA and the applicable Type Certificate Data Sheets. Each AD issued by the FAA and with a compliance date on or prior to Delivery shall be complied with.

The Government will perform a Final Delivery/Inspection of the aircraft to verify that the aircraft complies with all of the technical specifications of the Contract and to ensure all of the findings from the pre-award inspection have been corrected to the full satisfaction of the Government. The Government will have seven (7) calendar days to conduct this inspection. During the Final Delivery / Inspection, the Government will document any findings where the aircraft or deliverables do not meet the contract requirements. The contractor will be required to correct any findings within five (5) calendar days. The Government plans to utilize an independent third-party expert(s) to assist with this inspection.

5.3. Deliverables

In addition to the aircraft, during the Final Delivery / Inspection, and acceptance process, the Contractor must provide all contract deliverables as identified in Section 4. All flight deck presentations, placards, cockpit indications and gages and associated navigational equipment/instruments and manuals and supporting documentation all in the English language and U.S. standard measurement system.

5.4. Delivery Location

The aircraft final delivery / inspection and acceptance shall be at the Contractor’s designated location within the continental United States.

5.5. Other Final Delivery / Inspection Items and Acceptance Flight

5.5.1. The delivery and inspection process will include a Maximum Power Assurance run on each installed engine in accordance with the appropriate aircraft maintenance manual, to include associated documentation, a chip detector inspection, and an evaluation of the cruise and take-off trend analysis followed by an Acceptance Flight. These will be done at the Contractor’s expense and shall be overseen by JPATS representatives.

5.5.2. Utilizing an independent third-party expert at JPATS expense, JPATS will ensure each engine receives an external inspection and a full internal borescope inspection of the engine’s entire gas path resulting in a video borescope record of each installed engine with a written borescope report detailing the internal health of the engines to include the fan, compressor, combustion and turbine sections of the engine. JPATS will provide a copy of the borescope inspection reports to the Contractor. This borescope will be accomplished during the seven (7) calendar day inspection. Note: Full gas path borescope inspection will be reviewed by independent third-party propulsion engineer prior to engine acceptance.

5.5.3. Utilizing an independent third-party expert at JPATS expense, JPATS will ensure the APU receives an external inspection and a full internal borescope inspection of its entire gas path resulting in a video borescope record with a written borescope report detailing the internal health of the APU to include the compressor, combustion, and turbine sections. JPATS will provide a copy of the borescope inspection report to the Contractor.

This borescope will be accomplished during the seven (7) calendar day inspection.

5.5.4. Utilizing an independent third-party expert at JPATS expense, JPATS will observe the accomplishment of AMM Task 72-21-02-200-801-F00 on each engine. All unserviceable discrepancies must be corrected and any findings that result in a continue-in-service limit, or equivalent, will not be accepted.

After the reinstallation of the fan blades, AMM Task 71-00-00-700-814-F00, Test 7 – Vibration Survey, must be accomplished and each engine must be less than or equal to 1.0 units.

5.5.5. The Final Delivery / Inspection process will also include an Acceptance Flight. This Acceptance Flight is meant to demonstrate the takeoff, landing, and the enroute characteristics of the proposed aircraft. It shall be performed by pilots provided by the Contractor; however, a JPATS pilot shall sit in the center cockpit jumpseat on the flight deck during this acceptance flight as the official Government observer. This Acceptance Flight shall be in accordance with the Boeing Post Delivery 737NG Flight Profile and the Boeing 737 Next Generation Series Change of Operator Demonstration Profile. The Acceptance Flight shall be for a duration of approximately two hours and shall take place at the Delivery Location. All costs and expenses associated with this flight shall be the sole responsibility of the Contractor.

The operating parameters of each engine noted during the take-off power check shall be recorded. An Acceptance Flight will be deemed successful if all aircraft systems are fully operational and function properly during the flight, and the aircraft exhibits an acceptable level of trim, stability, maneuverability, and controllability as determined by the JPATS pilot. Any inoperative or improperly functioning component or system discovered during the acceptance flight shall be documented by the JPATS pilot in the applicable logbook.

5.5.6. After the Acceptance Flight, the Contractor shall perform an inspection of each magnetic chip detector on the installed engines as witnessed by a JPATS representative.

5.6. Final Delivery / Inspection and Acceptance Flight Deficiencies

The Contractor shall correct all deficiencies within three (3) calendar days from the date it receives the Government's notice to correct deficiencies, or in a time frame agreed to by the Contracting Officer, prior to a final determination of acceptance by the Government.

5.7. Termination for Cause

If, after this final delivery / inspection process, it is determined by the Government that any proposed aircraft is not acceptable or is unavailable for delivery on the required delivery date, the Government may terminate for cause this contract in whole or in part at no cost to the Government.

Appendix A: Airframe Information

Model:

Registration Number:

Serial Number:

Line Number:

Variable Number:

Date of Manufacture:

Time Since New (TSN):

Landings (Cycles) Since New (CSN):

Maximum Fuel Capacity (Pounds):

Maximum Fuel Capacity (US Gallons):

Maximum Takeoff Weight (Pounds):

Maximum Taxi / Ramp Weight (Pounds):

Maximum Landing Weight (Pounds):

Maximum Zero Fuel Weight (Pounds):

Maximum Certified Takeoff and Landing Altitude:

Total Passenger Seats:

Total Flight Attendant Seats:

Maximum Certified Passenger Seats:

Color of Exterior:

Date Last Painted:

Number of Lavatories:

Location of Lavatories:

Noise Level Compliant Stage:

Date Last C Check (or equivalent) was completed:

Airframe Hours Last C Check (or equivalent) was completed:

Airframe Landing (Cycles) Last C Check (or equivalent) was completed:

Date Next C Check (or equivalent) is Due:

Airframe Hours Next C Check (or equivalent) is Due:

Airframe Landing (Cycles) Next C Check (or equivalent) is Due:

Appendix B: Powerplant Specifications

#1 Engine Manufacturer:

Part Number:

Serial Number:

Series:

Time Since New (TSN):

Cycles Since New (CSN):

Last Overhaul Completion Date:

Last Overhaul Completion Hours:

Last Overhaul Completion Cycles:

Time Since Overhaul (TSO):

Cycles Since Overhaul (CSO):

Last Performance Restoration Completion Date:

Last Performance Restoration Completion Hours:

Last Performance Restoration Completion Cycles:

Last In-Shop Repair Completion Date:

Last In-Shop Repair Completion Hours:

Last In-Shop Repair Completion Cycles:

Time Since Repair (TSR):

Cycles Since Repair (CSR):

Airframe Installation Date:

Airframe Installation Hours:

Airframe Installation Cycles:

#2 Engine Manufacturer:

Part Number:

Serial Number:

Series:

Time Since New (TSN):

Cycles Since New (CSN):

Last Overhaul Completion Date:

Last Overhaul Completion Hours:

Last Overhaul Completion Cycles:

Time Since Overhaul (TSO):

Cycles Since Overhaul (CSO):

Last Performance Restoration Completion Date:

Last Performance Restoration Completion Hours:

Last Performance Restoration Completion Cycles:

Last In-Shop Repair Completion Date:

Last In-Shop Repair Completion Hours:

Last In-Shop Repair Completion Cycles:

Time Since Repair (TSR):

Cycles Since Repair (CSR):

Airframe Installation Date:

APU

Manufacturer:

Part Number:

Serial Number:

Series:

Time Since New (TSN):

Cycles Since New (CSN):

Last Overhaul Completion Date:

Last Overhaul Completion Hours:

Last Overhaul Completion Cycles:

Time Since Overhaul (TSO):

Cycles Since Overhaul (CSO):

Last In-Shop Repair Completion Date:

Last In-Shop Repair Completion Hours:

Last In-Shop Repair Completion Cycles:

Time Since Repair (TSR):

Cycles Since Repair (CSR):

Airframe Installation Date:

Appendix C: Landing Gear Specifications

Nose Landing Gear Manufacturer:

Part Number:

Serial Number:

Time Since New (TSN):

Cycles Since New (CSN):

Last Overhaul Completion Date:

Last Overhaul Completion Hours:

Last Overhaul Completion Cycles:

Time Since Overhaul (TSO):

Cycles Since Overhaul (CSO):

Next Due Overhaul Date:

Next Due Overhaul Cycles:

Airframe Installation Date:

Left Main Landing Gear Manufacturer:

Part Number:

Serial Number:

Time Since New (TSN):

Cycles Since New (CSN):

Last Overhaul Completion Date:

Last Overhaul Completion Hours:

Last Overhaul Completion Cycles:

Time Since Overhaul (TSO):

Cycles Since Overhaul (CSO):

Next Due Overhaul Date:

Next Due Overhaul Cycles:

Airframe Installation Date:

Right Main Landing Gear Manufacturer:

Part Number:

Serial Number:

Time Since New (TSN):

Cycles Since New (CSN):

Last Overhaul Completion Date:

Last Overhaul Completion Hours:

Last Overhaul Completion Cycles:

Time Since Overhaul (TSO):

Cycles Since Overhaul (CSO):

Next Due Overhaul Date:

Next Due Overhaul Cycles:

Airframe Installation Date:

Appendix D: Avionics Equipment List

Rack Nomenclature Part Number Serial Number

E1-1

EGPWS Computer A/T Computer

IFSAU

FSEU

FCC-A

TCAS Computer

E1-2

DME-1

ATC-1

#1 VOR / Marker Beacon Receiver

#1 MMR

E1-3

AACU

PA AMP

#1 VHF COMM

E1-4

#2 VOR / Marker Beacon Receiver

#2 MMR

FCC-B

Wing to Body Wheel Overheat Detector

E1-5

#2 VHF COMM

ATC-1

DME-2

E2-1

WHCU-2 Left Front WHCU-1 Right Side

APU GCU

#1 GCU

#1 TRU

Main Battery Charger

E2-2

Engine / APU Fire Detector Module

#1 Cabin Pressure Controller

APU Start Converter Unit

Static Inverter APU Start Power Unit

E3-1

ADF-2

#2 CDS DEU

#1 CDS DEU

ADF-1

LRRA-1

Rack Nomenclature Part Number Serial Number

E3-2

LRRA-2

DFDAU

Engine AVM Engine Accessory

Unit Audio Entertainment

SMYD #2

SMYD #1

E3-3

#1 CMU

#2 CMU & APM

#3 VHF COMM

Auxiliary Battery

Charger SATCOM (if installed) SATCOM (if installed)

E4-1

Air Conditioning Relays

Cabin Temperature Controller

REU

#2 Cabin Pressure

Controller SELCAL Decoder

Brake Temperature Monitor (if installed)

HGS Computer

E4-2

AUDIO Ent Mux (if installed)

Auto Speed Brake Accessory Unit

WHCU-3 Right Front WHCU-4 Left Side

#3 TRU

#2 TRU

BPCU

#2 GCU

E5-2

#1 ADIRU

#1 FMC

FMC Switch #2 FMC Switch #1

FMC #2

#2 ADIRU

Rack Nomenclature Part Number Serial Number

E6-1 CVR

E6-2 #1 HF-COMM

#2 HF-COMM

E6-3 APU ECU

Nomenclature Part Number Serial Number Mode Control Panel

Left MCDU Right MCDU

ELT

Appendix E: Software List

Component Software Software Part Number

FCC OPS

DFDAU

DFDAU Mandatory (DB)

DFDAU 429 BROADCAST

DB

ACMS SYSTEM/APPL SW

ACMS DB

DEU CDS

OPS

OPC

Database "DUDB"

FMCS

OPS

OPC

MEDB

ACARS Datalink Database

Perf Defaults Database

APU ECU OPS

#1 Engine EEC Software #2 Engine EEC Software

MCDU

OPS

OPC

Mode

MMR OPS

OSS

ACARS System Configuration

Core Software

CMPART

IOPART

ANPROC

ACRASP DB

VMDTA

TCHDTA

ATSDTA

AOCDTA

Appendix F: Autoflight and Autothrottle System Software Options

ATA System 22-11 Digital Flight Control System

Option Required Acceptable Disabled Autoflight – Alert – 900 / 200 Feet – Enable X

Autoflight – Glideslope Capture Prior to Localizer Capture – Inhibit X

Autoflight – Control Wheel Steering Reversion in Approach Mode – Enable X

Autoflight – Flight Director Takeoff Mode Heading Select – Enable X

Autoflight – Go-Around Roll Mode – LNAV – Enable X Autoflight – Control Wheel Steering Warning –

Enable X Autoflight – Airspeed Deviation Warning – Enable X

Mode Control Panel (MCP) – With Speed and Altitude Intervention – Installation X

Autoflight – Autopilot Operation with One IRU Inoperative – Enable X

Autoflight – Roll Command Alerting System (RCAS) X ATA System 22-31 Autothrottle System

Option Required Acceptable Disabled Autothrottle – FMCS – Takeoff Profile Thrust

Reduction Altitude – Enable X

Appendix G: Common Display System Software Options

ATA System 31-61 Engine Indicating

Option Required Acceptable Disabled Upper Engine Display – Fuel Totalizer – Enable X

Upper Engine Display – (DOT) ACARS Messages – Enable X

Upper Engine Display – Double Derate Indication – Enable X

Control Surface Position Indication – System Display – Enable X

Upper Engine Display Selectable Compacted Engine Format – Enable X

Engine Oil Quantity Display – Percent – Enable X Upper Engine Display Full-Time Engine Fuel Flow

Display – Enable X Upper Engine Display (DOT) ATC Message ACARS

Generated – Enable X Common Display System (CDS) – Protected Mode

ATN/CPDLC – Enable X

ATA System 31-62 Flight and Navigation Displays

Option Required Acceptable Disabled PFD / ND Format – Over-and-Under Engine

Presentation – Enable X Flight Director Command Display – Split Axis –

Enable X Attitude Comparator Flashing ADI – Enable X

Radio Altitude – Below ADI – Enable X Display of Round Dial and Digital Radio Altitude –

ADI – Enable X ILS Localizer Deviation Expanded Scale – Autopilot or Flight Director Mode – Enable X V1 Aural Callout – Flight Deck – Enable X

Rising Runway Displayed on ADI – Enable X TCAS Resolution Advisory – VSI – Enable X

Single Channel Autopilot Annunciation – Above ADI

– Enable X

80-Knot Setting – Mach Airspeed Indicator – Enable X VNAV Speed Bands – Enable X

Navigation Performance Scales – Enable X Horizon Line Heading Scale – Enable X

REF Flap/Speed Annunciation – Enable X PFD – Baro Minimums Pointer – Displayed on Selection of Radio Altitude Minimums – Enable X

31-62 Flight and Navigation Displays (Continued)

Option Required Acceptable Disabled PFD – Landing Altitude Reference Bar – Enable X PFD – Ground Speed Displayed Below Airspeed

Tape When Mach Number Is Not Displayed – Enable

X

PFD – Angle of Attack Display - Round Dial – Enable X

Manually Tuned VOR Selected Course Lines Displayed – Enable X

Map Mode Orientation – Track Up – Enable X Range Arcs – Enable X

TCAS 3-Nautical-Mile Range Ring – Enable X Vertical Situation Display – Enable X

Map Display – FMC and ADIRU Position Differences

– Exceedance Displayed – Enable X

Map Display – ADF Pointers – Enable (if ADF installed) X

Appendix H: Brake Temperature Monitoring System Software Options

ATA System 32-46 Brake Temperature Monitoring System

Option Required Acceptable Disabled Brake Temperature Monitoring System (BTMS) X

Appendix I: Air Temperature Measurement System Software Options

ATA System 34-12 Air Temperature Measurement System

Option Required Acceptable Disabled Dual Aspirated TAT Probe (for FMC) –

Installation X

Appendix J: Ground Proximity Warning System Software Options

ATA System 34-46 Enhanced Ground Proximity Warning System

Option Required Acceptable Disabled EGPWS – Enhanced Ground Proximity Warning

System – Smart 500 Callout – Enable X EGPWS – Altitude Callouts – Mode 6 Menu

Selections – Enable X EGPWS – Bank Angle Callout (Standard Option 1) –

Enable X Standard Volume for Altitude Callouts – Enable X

EGPWS – Peaks and Obstacles – Enable X Runway Awareness and Advisory System (RAAS) –

Enabled X

Appendix K: Ground Proximity Warning System Warning and Cautions Functionality

GPWS Indications Light / Message (ON) Light / Message (OFF) Aural Sound from

Speakers Amber GPWS INOP light;

cyan TERR TEST on the displays

Amber GPWS INOP The two amber BELOW

G/S lights GLIDESLOPE

The two amber BELOW G/S lights

Red PULL UP message on Capt’s and F/O’s displays;

TERR FAIL on the displays

Cyan TERR TEST on the displays PULL UP

Red PULL UP message on Capt’s and F/O’s displays

Red WINDSHEAR message on Capt’s and

F/O’s displays

Two tone siren

WINDSHEAR,

WINDSHEAR

Red WINDSHEAR message on Capt’s and

F/O’s displays; TERR FAIL on the displays

Red PULL UP message on Capt’s and F/O’s displays;

red TERRAIN message and test pattern on the displays

TERRAIN, TERRAIN –

PULL UP

Red PULL UP message on Capt’s and F/O’s displays;

red TERRAIN message and test pattern on the displays

Amber TERRAIN message on Capt’s and F/O’s displays; red PULL UP message on Capt’s and F/O’s displays; amber

TERRAIN changes to red OBSTACLE; red

OBSTACLE changes to amber

OBSTACLE, OBSTACLE –

GPWS Indications (Continued) Light / Message (ON) Light / Message (OFF) Aural Sound from

Speakers

Amber OBSTACLE on Capt’s and F/O’s PFD

AIR SPEED LOW

SINK RATE

PULL UP

TERRAIN

PULL UP

DON’T SINK, DON’T SINK

TOO LOW TERRAIN

TOO LOW GEAR

TOO LOW FLAPS

TOO LOW TERRAIN

GLIDESLOPE

APPROACHING

MINIMUMS

MINIMUMS

FIVE HUNDRED

FIFTY

FORTY

THRITY

TWENTY

TEN

Two tone siren

WINDSHEAR,

WINDSHEAR

TOO LOW TERRAIN

CAUTION TERRAIN

CAUTION TERRAIN

TERRAIN, TERRAIN –

PULL UP

CUATION OBSTACLE

CAUTION OBSTACLE

OBSTACLE, OBSTACLE –

Appendix L: Flight Management Computer Software Options

ATA System 34-60 Flight Management Computer

Option Required Acceptable Disabled FMCS – Runway Distance Remaining – Units of

Feet – Enable X FMCS – Speed and Altitude Intervention – Enable X FMCS – Vertical Navigation Profile – VNAV ALT –

Enable X FMCS – Alternate Destinations – Enable X FMCS – Quiet Climb System – Enable X

FMCS – Airline Operational Communications Data Link (AOC DL) – Enable X

FMCS – FANS 1 Capable Multipurpose Control Display Units (MCDU) – Installation X

FMCS – Default DME Update OFF – Enable X FMCS – Air Traffic Services (ATS DL) – Enable X

FMCS – Quick Reference Handbook Takeoff Speeds – Enable X

FMCS – Abeam Waypoints – Enable X FMCS – Message Recall – Enable X

FMCS in FAA Flight Rules – Enable X FMCS – Color CDU/MCDU Operation – Enable X

FMCS – Entry of Gross Weight on PERF INIT Page

– Disable X

FMCS – Integrated Approach Navigation (IAN) – Enable X

FMCS – Missed Approach in Cyan Until Active – Enable X

FMCS – Geometric Path Descent – Enable X FMCS – Fixed Percentage Takeoff Derates – Inhibit X

FMCS – QNH/QFE Selectable Reference for Takeoff and Landing – Enable X

FMCS – Engine Out Standard Instrument Departures (SID) – Enable X

FMCS – Flight Number Entry on the Route Page – Enable X

FMCS – Required Navigation Performance (RNP) Default Value – Revision X

FMCS – Common VNAV – Enable X Additional Control Display Unit (CDU) FIX Pages –

Enable X FMCS Speed Propagation From the Cruise Page to the Descent Page X FMCS – Takeoff Thrust Automatic Selection –

Enable X

34-60 Flight Management Computer (Continued)

Option Required Acceptable Disabled FMCS – Intent Data Transmitted to ACARS –

Enable X FMCS – Takeoff Runway Disagree Alert X

Appendix M: Flight Control Computer Software

Flight Control Computer Software Software Part Number

FCC A OPS

2270-COL-AC2-22 (Collins)

2216-HNP-03B-10

(Honeywell)

FCC B OPS

2270-COL-AC2-22 (Collins)

2216-HNP-03B-10

(Honeywell)