Draft SOW w-Attachments.pdf

October 1, 2020

STATEMENT OF WORK/ TECHNICAL SPECIFICATIONS

LEASE WITH OPTION TO PURCHASE: BOEING 737-700 OR 737-800

JUSTICE PRISONER AND ALIEN TRANSPORTATION SYSTEM (JPATS)

OKLAHOMA CITY, OKLAHOMA

I. GENERAL

The primary mission of U.S. Marshals Service, Justice Prisoner and Alien Transportation System (JPATS) is the safe, secure and efficient transportation of federal and non-federal prisoners and the provision 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 for the Lease with Option to Purchase of one (1) Boeing 737-700 or 737-800, transport category, narrow body, twin engine jet aircraft.

(NOTE: Brand Name Requirement is based on pilot type certification, passenger seating, maintenance, repair parts and logistics support). This aircraft will be operated primarily from the JPATS Oklahoma City operational site but may at times, based on particular mission demands, operate from the JPATS Las Vegas operational site. The aircraft will be operated by JPATS as Public Use aircraft meeting the mandatory requirements of Title 14 CFR Part 91 for operations in National Airspace. The period of performance will be a Base period: October 1, 2021 through September 30, 2022, with four (4) Option Years. JPATS will have the option to purchase the aircraft at any time during the base period or the option years.

II. AIRCRAFT UTILIZATION

Based on current mission flying schedules, JPATS’ estimated utilization rate for the proposed aircraft is approximately 1290 flight hours or 900 takeoffs and landings (cycles) per year. “Flight Hour” by definition is “wheels off” during takeoff to “wheels on” during landing. The actual hours and cycles will vary due to scheduling demands. JPATS will pay a monthly firm-fixed price lease rate for the aircraft through the leasing period for unlimited use of the aircraft. If JPATS elects to purchase the aircraft (at a firm-fixed price) the monthly firm-fixed price lease rate will cease on effective date of the purchase.

III. AIRCRAFT REQUIREMENTS / CONFIGURATION

A. Aircraft / General: The Contractor shall provide one (1) aircraft that, at time of

Lease delivery:

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

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

3. Has a printed copy of a current, aircraft serial number specific, Airplane Flight Manual (AFM) with Performance Specifications and Systems Description and Operation in English print and United States measurement units.

4. Has a printed copy of a current, aircraft serial number specific, Flight Crew

Operating Manual (or equivalent) in English print and United States measurement units.

5. Has a printed copy of a current, aircraft serial number specific, Minimum

Equipment List in English print and United States measurement units.

6. Has two (2) printed current, aircraft serial number specific, Quick Reference

Handbooks (QRH) in English print and United States measurement units.

7. Has the current Weight and Balance Manual (if separate from the Airplane Flight

Manual) in English print and United States measurement units.

8. 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 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.

9. Is accompanied with a current aircraft serial number specific Layout of Passenger

Accommodations (LOPA) in English print and United States measurement units.

10. Is accompanied with a current aircraft serial number specific Emergency

Equipment Layout in English print and United States measurement units.

11. Is accompanied with current (within 12 calendar months) aircraft Equipment List in English print and United States measurement units.

12. 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.

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

14. Is accompanied by a current, aircraft serial number specific, maintenance and inspection status report (in a format acceptable to JPATS) in respect to the aircraft, including the AD and SB status of the airframe, appliances, engines, and APU; status of hard time components, alterations, major repairs (337s, STCs, Engineering Orders, etc.), and flight hour / flight cycle summary.

15. Has not accumulated, and will not accumulate, more than 40,000 total cycles since new (TCSN) during the contract period of performance (base year and option years).

16. Is certified for day, night, Visual Flight Rules (VFR), Instrument Flight Rules

(IFR) operations and flight into known icing conditions.

17. Is accompanied with appropriate documentation testifying that the aircraft has not sustained any substantial damage as defined by National Transportation Safety Board 49 CFR Subpart A, General 830.2.

18. Has all cockpit and cabin instrumentation, avionics, placards, gauges readable in the English language and in the United States measuring system.

19. Is “Stage 3” noise level compliant with maximum takeoff noise levels not exceeding those levels as prescribed in Title 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.

20. Is equipped with an Auxiliary Power Unit (APU) Model GTCP131-9B, Part

Number 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.

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

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

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

24. Has all Life Limited Parts (LLP) that are associated with the airframe, engines, APU, appliances, and landing gear at “mid-life” or greater meaning that 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 and the projected aircraft utilization identified in paragraph II.

25. Is powered by CFM56-7B24/B1 series engines (or International Aero Engines or Pratt & Whitney engines of equivalent thrust / performance).

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

27. Is accompanied by an on-wing Max Power Assurance Run sheet showing clear documentation of full rated thrust for the applicable installed engines with demonstrated EGT Margins of not less than 20 degrees for each installed engine.

This requirement must be current and valid and have been performed after the last flight of the previous operator and prior to the first flight by JPATS.

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

29. Is in compliance with all applicable published FAA 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.

30. Is in compliance with all calendar, flight hour, flight cycle maintenance inspections and events from either a Manufacturer or FAA approved maintenance program.

31. Has no “Scheduled” Heavy Maintenance or Major Inspection (C Check or higher) within 18 months of contract award.

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

33. Prefer aircraft with an Increased Gross Weight (IGW) Maximum Takeoff Weight

(MTOW) option as specified in Type Certificate Data Sheet A16WE.

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

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

36. Has a reinforced Flight Deck Door meeting the standards for a Title 14 CFR Part

121.313 commercial air carrier.

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

38. Has it’s appropriately assigned U.S. registration (“N”) number applied to the aircraft in accordance with Title 14 CFR Part 45.25 requirements.

39. Has each hard time controlled and life limited component serviceable and supported by appropriate installation certification documentation with either the EASA Form 1 or FAA Form 8130-3.

40. 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.

41. Is free of fuel, oil, hydraulic and pneumatic leaks. Any repair of leaks will have been permanent repairs.

42. Has a fuselage free of dents and abrasions.

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

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

45. Has the wing’s and stabilizer’s leading edges serviceable in accordance with

AMM limits (e.g. no significant hail or other foreign object damage).

46. Has wings free of fuel leaks as demonstrated by the Manufacturer’s relevant testing guidelines.

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

48. Is capable of allowing for loading and unloading of normal JPATS’ mission equipment and provisions in the lower cargo compartments without the use of external ground support equipment.

49. Has a Boeing OEM Nitrogen Generation System (NGS) installed.

50. Is equipped with single 24-volt nickel-cadmium rated 48-AH battery providing

RNP & other essential equipment 30-min standby power capability.

DESIREABLE: Boeing approved Dual Battery System; two 24 volt rated nickel-cadmium batteries (main and auxiliary) are installed in the electronics compartment. Two fully charged 48-AH batteries must have sufficient capacity to provide standby power for a minimum of 60 minutes.

51. Is equipped with a fixed permanently installed Emergency Locator Transmitter

(ELT).

B. Avionic/Navigation/Auto Flight System: In addition to the requirements of Paragraph

A the aircraft shall have, as a minimum, the following at the time of delivery to

JPATS:

1. Dual Flight Management Systems (FMS) with latest revision of OP Program U13.0. Navigation database subscription for the duration of the lease from the date of delivery for worldwide database navigation data conforming to WGS-84 coordinate system, such as the Jeppesen JEP 5, or equal. Additionally, the airport database will incorporate all airports with an instrument approach procedure (IAP) and a runway greater than 5,000 feet in length within the geographical area as defined by the Continental United States (CONUS), Alaska, Hawaii, Canada, Caribbean, Latin America and South America regions.

2. The FMS must be fully interfaced with and receive navigational data/inputs from a minimum of two (2) Inertial Reference Systems (IRS), two (2) Global Navigation Satellite Systems (GPS position updating systems), and a minimum of two (2) radio navigation systems.

3. Air Data Inertial Reference System (ARDIRS): dual ADIRUs (both IRS) with most current magnetic variation tables (MAG VAR EPOC) cited under AFM.

4. Dual Global Navigation Satellite System (GNSS) position updating system, capable of gaining operational approval to conduct Title 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.

5. Capable of navigating 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 Statement of Compliance in AFM/AFMS/POH or avionics operating manual.

6. 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.

NOTE: fill out TABLE-3 AUTHORIZED AIRPLANE(S), EQUIPMENT REFLECTING

III.B.1-6 RNP EQUIPAGE STATEMENT OF COMPLIANCE PUBLISHED IN AFM/

AFMS/STC OR AVIONICS OPERATOR MANUAL

7. Dual Flight Guidance/Autopilot System capable of meeting the required lateral and vertical RNAV/VNAV performance while coupled with FMS system.

8. Three (3) digital VHF transceivers communication systems with a minimum of

760 channels with 8.33 KHZ spacing. Desire three each radio tuning panels equal to GABLES 07404-24 with three VHF (1-2-3), two HF (1-2) and amplitude modulation (AM) switch functions in cockpit.

9. Prefer Audio Control Panel (ACP) equal to AVTECH 5145-1-77 with VHF 1-3, HF 1-2, INT, CABIN, PA, SAT 1-2 switch and call light functions.

10. OPTIONAL: One (1) HF transceiver communication system with SELCAL that satisfies one of two long range communication systems (LRCS) supporting Air Traffic Services (ATS) communication, if second ATS communication system meets SATVOICE equipage description under item III.B.11 below.

11. Iridium SATVOICE (satellite voice communication system) to include, as a minimum:

(a) Flightcrew SATVOICE calls through Cockpit Interphone system with

MCDU’s phone control interface functions.

(b) Cabin SATVOICE calling through wireless handset system

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

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.

(d) 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).

(e) FLIGHT DECK ANNUNCIATION. Alerting associated with non-normal conditions (such as failures) of the airborne SATVOICE system must comply with the appropriate part of Title 14 of the Code of Federal Regulations (14 CFR) 25.1322/1302. REF: AC20-150( ) paragraph 8 meeting all aural and visual crew alerts; airborne system failure detection; call ID termination or connection failure indications.

(f) Prefer 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).

12. Aircraft Data Link System at a minimum ACARS management unit interfacing with Aircraft Condition Monitoring System (ACMS) software functions and Digital Flight Data Acquisition Unit (DFDAU) reporting functionality. with SOC indicating

NOTE: fill out TABLE-4 AIRCRAFT DATALINK SOC REFLECTING AIRCRAFT

DATALINK INTEROPERABILITY / SUBNETWORK / PERFORMANCE EQUIPAGE

DATA SUMMARY.

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

14. One (1) Enhanced Ground Proximity Warning System (EGPWS) with low level wind shear detection meeting the requirement of Title 14 CFR Part 121.358.

15. Class A TAWS conforming to TSO-C151b dated Dec. 17, 2002.

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

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

18. OPTIONAL: Two (2) digital ADF navigation systems. ADF#1 providing input to Standby RMI in addition to normal input presented on cockpit displays.

19. Two (2) Mode S Transponder systems under 1090ES equipment installation mandate 14CFR 91.225 without temporary exemption restriction (must have

SBAS MMR’s) including AFM/AFMS/STC performance compliance statement under 14CFR 91.227 meeting the latest TSO C166b (DO-260B / Version 2) standard.

20. 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.

21. Two (2) Radio Altimeter systems.

22. One (1) Solid State Digital Flight Data Recorder which complies with Title 14

CFR Part 121.343 and 131.344 including Part 121 Appendix B and M as applicable.

23. Quick-Access Recorder (QAR) conforming to the USMS Flight Operations Quality Assurance (FOQA) program. The current program hardware accepted QAR is the L3 Micro QAR combined with the Honeywell Digital Flight Data Acquisition Unit (DFDAU) P/N 967-0212-002 utilizing 737-5 data frame for QAR readouts. Prefer a QAR light indicator on AFT Overhead Panel that illuminates when QAR is full.

24. One (1) Digital Cockpit Voice Recorder that records all flightcrew SATVOICE, HF, VHF interphone, and cockpit area communications including datalink messages in crash survivable memory.

25. Cockpit Configuration: FMS SW, EFIS and Standby options affording

(a) Flight Path Vector (FPV button) & Vertical Situation Display (VSD) controlled by Center (CTR) switch options enabled on EFIS Panel Controls,

(b) PFD Split axis command bars, Navigation Performance Scales (NPS) and (Integrated Approach Navigation (IAN) - optional) Flight Director indications,

(c) PLI pop-up, Airspeed Indication low airspeed alert option enabled, angle of attack,

(d) ND Map, Expanded & Center Map modes – TRK up orientation,

(e) V1 aural enabled (if Look Ahead Terrain Alerting callout is functional),

(f) Integrated Standby Flight Display (THALES AVIONICS CI6221KA01) or comparable with ILS/GS deviation indications from MMR#1, and MAG HDG from ARIRU#1 or automatic TRUE HDG in Polar regions.

IV Maintenance / Logistics Support

NOTE: Applicable during the lease period only. JPATS will assume all maintenance responsibility should the option to purchase be exercised.

JPATS Responsibilities:

1. JPATS will be responsible to perform all Line Maintenance and Line Servicing maintenance inspection and repairs to include the associated logistics requirements. This will be performed by a Title 14 CFR Part 145 Certificated Repair Station (CRS) under a separate contract. All maintenance will be performed on this lease aircraft without discrimination when compared to the aircraft currently owned and operated by JPATS.

Maintenance, inspection and repairs will be to a Title 14 CFR Part 91 standard. JPATS will utilize the policies and procedures detailed in the USMS General Maintenance Manual (GMM) (See Attachment #1) in the performance of these Line Maintenance and Line Servicing responsibilities.

2. JPATS will be responsible to utilize the JPATS Daily Flight Log Books, FAA

Form 337, and contract maintenance providers Routine and Non-Routine Work Order Forms for documenting maintenance, inspections and repairs of this aircraft made during the period of this lease.

3. JPATS will be responsible to make all appropriate entries into the Aircraft, Engine, and APU Permanent Historical Records for all applicable maintenance, inspections, and repairs of this aircraft made during the period of this lease.

4. JPATS will be responsible for utilizing Contractor supplied “approved data” in performance of Line Maintenance and Line Servicing to include but not limited to Aircraft Maintenance Manuals (AMM), Illustrated Parts Catalogs (IPC), Structural Repair Manual (SRM), and Wiring Diagram Manual

(WDM).

5. JPATS will be responsible for the acquisition of all parts, materials, consumables, free stock, and lubricants required for Line Maintenance and Line Servicing in maintaining the aircraft in a safe airworthy condition as detailed in the maintenance and inspection program as well as to correct pilot reported discrepancies (PIREPS). All parts purchased will be done so utilizing acquisition policies and procedures of the aforementioned Title 14 CFR Part 145 CRS using their Approved Vendor List of certified vendors.

All parts installed will have FAA Forms 8130-3 or EASA Form 1 attached and will have “birth” traceability when appropriate.

6. JPATS will be responsible for all costs in connection with or related to the use, movement and operation of the Aircraft. Such costs include but are not exclusive of the costs of flight crews, cabin personnel, fuel, oil, storage, landing and navigation fees, airport charges, passenger services and any and all other mission related expenses.

7. JPATS will be responsible for the accomplishment of FAA issued

Airworthiness Directives (AD) with a compliance date falling within the period of this lease, base year and option years, that can be performed at a

Line Maintenance level and do not exceed $25,000 in total cost. ADs that cannot be performed at a Line Maintenance level or exceed $25,000.00 in cost are determined to be “Heavy Maintenance” and the Contractor shall be responsible.

8. JPATS will be responsible for the accomplishment of contractor provided manufacturer issued Mandatory Service Bulletins (SB) issued and with a compliance date falling within the period of this lease, base year and option years, that can be performed at a Line Maintenance level and do not exceed $25,000 in total cost. SBs that cannot be performed at a Line Maintenance level or exceed $25,000 in cost are determined to be “Heavy Maintenance” and the Contract shall be responsible.

Contractor Responsibilities:

1. The Contractor will be responsible to perform all “Scheduled” Heavy Maintenance to include scheduled Major Inspections; C Checks or higher, to include “Non-Routine” Discrepancies identified during the heavy maintenance or major inspections. These Heavy Maintenance events and Major Inspections will be performed by a Title 14 CFR Part 145 Certificated Repair Station (CRS) to a Title 14 CFR Part 91 standard, as a minimum.

NOTE: JPATS defines Heavy Maintenance as any maintenance event to include maintenance, inspection, repair, alteration, or overhaul, whether scheduled or unscheduled, that exceeds the capabilities of mechanics in a typical line maintenance environment; for reasons such as; but not limited to, lack of proper facilities (hangar), lack of specialized / unique tooling, support equipment, special tools, test sets, or fixtures. Scheduled Heavy Maintenance is normally associated with a Major Inspection such as an aircraft C Check or above.

JPATS further defines “Heavy Maintenance” as all scheduled checks at the

C-check level or higher; all major repairs, alterations and inspections as defined by Title 14 CFR Part 1.1; engine, APU, and landing gear changes or engine, APU, and landing gear repairs requiring approved data at the Component Maintenance Manual (CMM) level, vice Aircraft Maintenance Manual (AMM) level; or when structural repairs are estimated to require 100 man-hours or more to accomplish.

2. The Contractor will be responsible for the accomplishment of “Unscheduled”

Heavy Maintenance on the aircraft, engines, and APU. When such heavy maintenance was a direct result of the actions, or inactions, on the part of JPATS employees, or the employees of JPATS Line Maintenance Contractor, reimbursement for this maintenance will be made to the Contractor as an Over and Above effort under a separate Contract Line Item Number (CLIN).

NOTE: JPATS defines Heavy Maintenance as any maintenance event to include maintenance, inspection, repair, alteration or overhaul, whether scheduled or unscheduled, that exceeds the capabilities of mechanics in a typical line maintenance environment; for reasons such as; but not limited to, lack of proper facilities (hangar), lack of specialized / unique tooling, support equipment, special tools, test sets, or fixtures. Scheduled Heavy Maintenance is normally associated with a Major Inspection such as an aircraft C Check or above.

JPATS further defines “Heavy Maintenance” as all scheduled checks at the

C-check level or higher; all major repairs, alterations and inspections as defined by Title 14 CFR Part 1.1; engine, APU, and landing gear changes or engine, APU, and landing gear repairs requiring approved data at the Component Maintenance Manual (CMM) level, vice Aircraft Maintenance Manual (AMM) level; or when structural repairs are estimated to require 100 man-hours or more to accomplish.

JPATS will reposition the aircraft for any heavy maintenance event under the following conditions: 1) JPATS has pilots available; 2) The aircraft is signed off as “airworthy” in the JPATS flight log the day of the reposition flight; 3) The reposition is within the 48 contiguous U.S.; 4) All fuel costs will be the responsibility of the Lessor; 5) JPATS pilots will not perform any Functional Check Flights (FCF) required after heavy maintenance; and 6) JPATS pilots will not perform any required test flights after heavy maintenance.

3. The Contractor will be responsible for “off-wing” engine maintenance such as an engine shop visit. When the “off-wing” maintenance or engine shop visit was the direct result of actions, or inactions, on the part of JPATS employees, or the employees of JPATS Line Maintenance Contractor, reimbursement will be made to the Contractor as an Over and Above effort under a separate Contract Line Item Number (CLIN).

4. The Contractor will be responsible to secure a serviceable replacement engine to be utilized by JPATS in keeping the aircraft in revenue service in the event an installed engine must be removed for scheduled maintenance or an unscheduled failure such as FOD damage.

5. When the Aircraft or Engine undergoes any scheduled or unscheduled Heavy maintenance exceeding five (5) days during any month during the Lease Term, the monthly lease rate will abate on a daily basis commencing on the sixth (6th) day after aircraft is removed from revenue service and ending on such date as the Aircraft is airworthy and returned to JPATS. No abatement shall apply in the event that the Heavy Maintenance event is required solely as a result of JPATS’ operation of the Aircraft and unrelated to ordinary wear and tear or latent defects.

6. The Contractor shall ensure that all Heavy Maintenance to the Aircraft is accomplished at an FAA Certificated Repair Station (CRS) utilizing the Repair Station Manual (RSM) and approved data. The CRS shall provide a complete record of all work performed and execute an appropriate return to service.

7. The Contractor shall provide a certificate of insurance or documentation evidencing the insurance of the Aircraft.

8. The Contractor shall be responsible to identify, track and document all maintenance events performed as well as communicate to JPATS all scheduled maintenance and inspections coming due during the duration of this lease with at least a 30-day lead time. The Contractor will do this by utilizing an automated maintenance and inspection tracking program. This program will be in the contractor’s format and be common to the aviation industry. As a minimum, its format and content must meet a Title 14 CFR Part 91 standard. Note: The Contractor shall provide designated JPATS employees access to the electronic database which tracks and schedules maintenance.

9. The Contractor shall be responsible to provide JPATS at time of aircraft delivery “approved data” for the performance of Line Maintenance and Line Servicing to include; but not limited to, all required Aircraft Maintenance Manuals (AMM), Illustrated Parts Catalogs (IPC), Structural Repair Manual (SRM), and Wiring Diagram Manual (WDM).

V. DELIVERABLES

Table No. 2 - Deliverables

Item No.

Due Date

1. Large Transport Category, Narrow Body, Twin Engine Jet Aircraft (Oklahoma City, Oklahoma)

12 weeks after contract award

2. Airplane Flight Manual (AFM) (with Performance Specifications and Systems Description and Operation) in English print and U.S. measurement system.

Delivered with aircraft

3. Manufacturer Flight Crew Operating Manual (or equivalent) in English print and United States measurement units specific to the aircraft serial number.

Delivered with aircraft

4. A printed copy of a current, aircraft serial number specific, Minimum Equipment List in English print and United States measurement units.

Delivered with aircraft

5. Manufacturer Quick Reference Handbooks (QRH) or equivalent in English print and U.S. measurement system.

Delivered with aircraft

6. Manufacturer Weight and Balance Manual (if separate from the Airplane Flight Manual) in English print and U.S. measurement system.

Delivered with aircraft

7. 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 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

Delivered with aircraft

8. Current Aircraft Layout of Passenger Accommodations (LOPA) in English print and U.S.

measurement system

Delivered with aircraft

9. Current Aircraft Equipment List in English print. Delivered with aircraft

10. 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.

Delivered with aircraft

11. A current status report in respect to the aircraft, including the AD and SB status of the airframe, appliances, engines, and APU; status of hard time components, alterations, major repairs (337s / STCs), and flight hour / flight cycle summary.

Delivered with aircraft

No.

Due Date

12. Approved data to include all Aircraft Maintenance Manuals, Illustrated Parts Catalogs, Structural repair manuals and Wiring Diagrams STC, Engineering Orders, etc. for accomplishment of Line Maintenance and Line Servicing

Delivered with aircraft

13. An editable digital and physical copy of the aircraft’s maintenance and inspection program.

Delivered with aircraft

14. All applicable burn certification documentation Delivered with aircraft

15. Current EASA Form 1 and / or FAA Form 8130-3 for each engine, APU, landing gear, and all Hard Time and / or life limited components.

Delivered with aircraft

16. Instructions for Continued Airworthiness (ICAs) for all aircraft, engine, and appliance alteration and / or repair.

Delivered with aircraft

17. Engine Mini Pack with an up to date Life Limited Parts List.

Delivered with aircraft

18. APU Mini Pack with an up to date Life Limited Parts List.

Delivered with aircraft

19. Physical copy of all software installed. Delivered with aircraft

20. Previous 120 flight days of engine trend data Delivered with aircraft

21. Current Electrical Load Analysis (ELA) with

Coordination Sheet and all associated aircraft alterations.

Delivered with aircraft

Note: All deliverables shall be presented with a printed physical copy and an editable digital copy.

All historical records shall be delivered to JPATS if the option to purchase is exercised.

VI. PRE-AWARD INSPECTION, FINAL DELIVERY/INSPECTION AND

ACCEPTANCE OF THE AIRCRAFT

A. 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 technical requirements as detailed in the Statement of Work and as presented in the Offeror’s proposal, the Government will then determine if those items not meeting the 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, 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 their contracted maintenance provider or a third-party expert to assist with this pre-award inspection.

B. 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 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 with 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 requirements 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 their contracted maintenance provider or an independent third-party expert to assist with this pre-award inspection.

C. Deliverables --In addition to the aircraft, during the Final Delivery/Inspection, and acceptance process, the Contractor must provide all contract deliverables as identified in this Statement of Work, Table 1, Deliverables (Items 2-21). 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.

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

E. Other Final Delivery/Inspection Items & Acceptance Flight –

(a) 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.

(b) 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.

(c) 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.

(d) The Final Delivery/Inspection process will also include an Acceptance Flight.

This Acceptance Flight is meant to demonstrate the takeoff and landing capabilities and the en route 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 "jump" seat 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 (Attachment #2) and the Boeing 737 Next Generation Series Change of Operator Demonstration Profile (Attachment #3). The Acceptance Flight shall be for a duration not to exceed 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 reposition 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 flight logbook.

(e) 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.

F. Final Delivery/Inspection & 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.

G. 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.

TABLE 3 – AUTHORIZED AIRPLANE(S), EQUIPMENT

Airplane M/M/S

Long-Range Navigation Systems

(LRNS)

Navigation Specification(s)

Additional Capabilities

Limitations RNP Time

Limits Manufacturer Model/HW Part #

Software Part/Ver#

B-737-700ER A-RNP/RNP-1/

RNP-2/ RNP-4/

RNP-10/

RNP APCH/

RNP AR APCH

RF No Lateral Offset

B-737-800

A-RNP/RNP-1/

RNP-2/ RNP-4/

RNP-10/

RNP APCH/

RNP AR APCH

FRT/TOAC/

Offset

GUIDANCE & APPROVAL SOURCE:

Flight Operations Group, Performance Based Navigation (PBN)

A-RNP Advanced Required Navigation Performance [REF: AC90-105(), Appx H] A-RNP qualification per AC20-138() in AFM or other OEM documentation includes functional capability of performing:

1. Scalability,

2. Radius to Fix (RF)

3. Parallel Offset

4. Fixed Radius Transition (FRT)

5. Time of Arrival Control (TOAC)

RNP-1 Aircraft with a Statement of Compliance (SOC) with RNP 1 criteria in accordance with AC 20-138( ). [REF: AC90-105(), appx C]

RNP-2 Aircraft with an SOC with RNP 2 criteria in accordance with AC 20-138( ) [REF: AC90-105(), appx E]

RNP-4 Aircraft with an SOC with RNP 4 criteria in accordance with AC 20-138( ) [REF: AC90-105(), appx F]

RNAV/RNP-10

https://www.faa.gov/about/office_org/headquarters_offices/avs/offices/afx/afs/afs400/afs410/pbn/

Aircraft with an SOC with RNP 10 criteria in accordance with AC 20-138( ) [REF: AC90-105(), appx G]

RNP APCH Aircraft with a statement from the manufacturer documenting compliance with the criteria in AC 20-138( ) [REF: AC90-105(), appx A]

RNP AR APCH

Aircraft with a SOC meeting criteria AC20-138( ) and documentation in AFM, AFMS, POH, or avionics operating manual meeting the performance and functional requirements of AC90-101( ) with identification of optional capabilities (e.g., RF legs and RNP missed approaches) defined under Appendix 2 Aircraft Qualification criteria.

TABLE 4 - AIRCRAFT DATALINK SOC

AIRCRAFT ELIGIBILITY = INTEROPERABILITY / SUBNETWORK / PERFORMANCE

INTEROP

Designator

AFM SOC

SUBNETWORK

Designator

AIRCRAFT PERFORMANCE

Allocated Rate (sec)

Rqrd COMM Perf

CPDLC ‐ RCP

(130 / 240 / 400)

Rqrd SURV Perf

ADS‐C ‐ RSP

(160 / 180 / 400)

FANS 1/A+

with

AUTOMATION

VDL M0/A 240 RCP 180 RSP

VDL M2 240 RCP 180 RSP

HFDL 400 RCP 400 RSP

SATCOM (SBD) 240 RCP 180 RSP

ACARS ATS

VDL M0/A N/A N/A

VDL M2 N/A N/A

HFDL N/A N/A

SATCOM (SBB) N/A N/A

SOW ATTACHMENTS:

Attachment #1 – USMS General Maintenance Manual (GMM) (298 pages)

Attachment #2 – Boeing Post Delivery 737NG Flight Profile (63 Pages)

Attachment #3 - Boeing 737 Next Generation Series Change of Operator Demonstration Profile (61 pages)

CAGE Code 81205

Post Delivery 737NG Flight Profile

DOCUMENT NUMBER: RELEASE/REVISION: RELEASE/REVISION DATE:

D541A015-2 REV B OCTOBER 2017

CONTENT OWNER:

Flight Crew Operations (9R-TE-TGXX)

All revisions to this document must be approved by the content owner before release.

The information contained herein is the property of The Boeing Company and shall not be reproduced or disclosed in whole or in part or used for any purpose except when the user possesses direct, written authorization from

The Boeing Company.

REV B D541A015-2 2

PROPERTY OF THE BOEING COMPANY

Table of Contents

TITLE PAGE

TABLE OF CONTENTS 2

1 PURPOSE AND SCOPE 3

2 GLOSSARY 4

CHAPTER 1 PREFLIGHT 7

CHAPTER 2 ENGINE START 50

CHAPTER 3 AFTER ENGINE START 51

CHAPTER 4 TAXI 52

CHAPTER 5 TAKEOFF 53

CHAPTER 6 CLIMB 54

CHAPTER 7 CRUISE 55

CHAPTER 8 DESCENT 56

CHAPTER 9 LOW ALTITUDE 57

CHAPTER 10 APPROACH AND LANDING 58

CHAPTER 11 TAXI IN AND SHUTDOWN 59

ACTIVE PAGE RECORD 60

REVISION RECORD 61

REV B D541A015-2 3

1. PURPOSE AND SCOPE

This is a Boeing 737 post delivery flight profile that outlines information on what to check to assess airplane operation following heavy maintenance, modification, or long term storage. It is intended to provide information to flight crews already trained in proper flight testing procedures and techniques. This information may help evaluate proper airplane systems function, airworthiness, and conformity to type design. This document is intended to be used only as a guide and is not designed to satisfy regulatory requirements. Any use of this document outside this intended function and/or by crews that are not highly experienced in performing these types of tests is strongly discouraged. Boeing does not endorse or recommend using this document to conduct any flight test.

Because this document is only a guideline based on representative Boeing Production Flight Test Procedures, it is not specific to any model or configuration. Tests identified in this document may not apply to all model airplanes. Conversely, this profile may not accommodate all possible airplane configurations or modifications. As such, the information in this document will not specifically address airplanes that have undergone modification, repair, and/or maintenance due to service bulletin incorporation or compliance with airworthiness directives, or any other changes or modifications due to installation of additional equipment, such as by STC.

Therefore, tolerances, limitations, and specific procedures for performing each test or maneuver are not provided. All flight and maintenance personnel should refer to operations manuals and maintenance manuals specific to the airplane for this information and it is the responsibility of the operator to prepare a detailed plan of test prior to flight.

An in-depth understanding of airplane systems operation and the ability to recognize the appropriate outcome of tests or checks is critical to proper use of this document and are keys to a safe and efficient flight test. For certain checks, the inability to recognize system malfunctions may result in structural failure and/or loss of airplane control; conditions which may be beyond the capability of inexperienced and untrained flight crews and/or test pilots.

The pilot in command is responsible for the safe operation and control of the airplane. If an abnormal or emergency situation occurs, all testing should be discontinued and the appropriate non-normal checklist accomplished. The pilot in command may then determine if further testing is possible or appropriate.

Any time the cabin altitude is raised above 10,000 feet, all personnel should be seated.

Supplemental oxygen shall be made available and readily accessible. It is recommended that operators limit participation to minimum crew. It will be the responsibility of individual operators to determine the environmental conditions and requirements necessary for testing. In general, all checks should be conducted in day, VMC.

CAUTION: The checks outlined in this document are in addition to the normal operating procedures contained in the approved FAA Flight Manual and the appropriate Boeing Operations Manual. System failures during certain maneuvers may place the airplane outside its approved operating envelope. ONLY HIGHLY EXPERIENCED, PROPERLY

TRAINED CREWS SHOULD BE AT THE CONTROLS WHILE PERFORMING THE

MANEUVERS OUTLINED IN THIS DOCUMENT.

This document is not kept up to date and notification of revision is not provided.

REV B D541A015-2 4

2. GLOSSARY

AC Alternating Current

ADF Automatic Direction Finder

ADI Attitude Direction Indicator

ADIRU Air Data Inertial Reference Unit

AIL Aileron

AGL Above Ground Level

AFDS Automatic Flight Director System

ALT Altitude

ALTN Alternate

AND Airplane Nose Down

ANU Airplane Nose Up

A/P Auto Pilot

APU Auxiliary Power Unit

A/T Auto Throttle

ATC Air Traffic Control

ATT Attitude

ARR Arrival

AUTO Automatic

AVM Airborne Vibration Monitor

BBJ Boeing Business Jet

BRT Bright

CAA Civil Aviation Authority

CAPT Captain

C/B Circuit Breaker

CDU Control Display Unit

CLB Climb

CMD Command

COMM Communication

CON Continuous

COND Condition

CONFIG Configuration

CONT Continuous

CP Control Panel

CRZ Cruise

CTR Center

CTRL Control

CWS P,R Control Wheel Steering Pitch, Roll

DAC Double Annular Combustor

DC Direct Current

DEP Departure

DES Descent

DIR INTC Direct-Intercept

DME Distance Measuring Equipment

DN Down

DU Display Unit

E & E Electrical/Electronic

ECS Environmental Control System

EEC Engine Electronic Control

EFIS Electronic Flight Instrument System

EGT Exhaust Gas Temperature

ELEC Electric

ENG Engine

EXT Extend

Fxx Flap position xx

FAA Federal Aviation Administration

(USA)

FAC Final Approach Course

FCC Flight Control Computer

F/D Flight Director

FF Fuel Flow rate

FMA Flight Mode Annunciator

FMS Flight Management System

FL Flight Level

REV B D541A015-2 5

FLT Flight

F/O First Officer

FPM Feet Per Minute

FREQ Frequency

FSEU Flap-Slat Electronics Unit

FT Feet

FU Fuel Used

FWD Forward

GA Go-around

GEN Generator

GLS GNSS Landing System

GNSS Global Navigation Satellite Sys