Aircraft Technical Specifications with Attachments.pdf

January 1, 2021

AIRCRAFT TECHNICAL SPECIFICATIONS

PURCHASE OF AIRCRAFT: 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 to Purchase one (1) or two (2) 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/These 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. JPATS will take delivery of the aircraft 12 weeks after contract award.

II. AIRCRAFT UTILIZATION

Based on current mission flying schedules, JPATS’ estimated utilization rate for each of 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.

III. AIRCRAFT REQUIREMENTS / CONFIGURATION

A. Aircraft / General: The Contractor shall provide one (1) or two (2) aircraft that, at time of 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 more than 40,000 total cycles since new (TCSN).

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. Aircraft must be equipped with a minimum of two (2) flushable lavatories; one located in the forward cabin and one located in the aft cabin, configured for external servicing. JPATS prefers aircraft equipped with three (3) flushable lavatories; one located in the forward cabin and two located in the aft cabin, configured for external servicing.

23. At a minimum, aircraft must be OEM pre-wired for self-contained, powered, forward air stairs at the L-1 door. JPATS prefers aircraft already equipped with self-contained, powered, forward air stairs at the L-1 door.

24. Has all time controlled parts (any part that requires maintenance at a predefined interval) and Life Limited Parts (LLP) that are associated with the airframe, APU, 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.

25. Is powered by CFM56-7B24/B1 series engines when installed on a 737-700 aircraft or powered by CFM56-7B26 series engines when installed on a 737-800 aircraft.

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 18 months of contract award unless recurring inspection interval is less than 18 months.

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, FAA Form 8130-3 or CAA Form 1.

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. JPATS prefers a Boeing approved Dual Battery System; two 24 volt rated nickel-cadmium batteries (main and auxiliary) 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 System (FMS)

(a) Prefer Dual Flight Management Systems (FMS) with latest revision of OP

Program U13.0 (minimum of 10.8A required).

(b) 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.

(c) Must be equipped with two (2) Flight Management Computers Part Number 176200-01-01.

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

3. 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.

4. 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.

5. 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 III.B.24 Cockpit Configuration.

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

7. 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.

8. 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.

9. 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.10 below.

10. 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).

11. 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. DATA LINK SOC REPORT: In addition to avionics equipment list, appropriate to offeror aircraft configuration, a data link equipage report must include Statement of Compliance (SOC) summary.

12. 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.

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

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

15. 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.

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

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

18. 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.

19. Prefer 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.

20. Two (2) Radio Altimeter systems.

21. 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.

22. 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.

23. 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.

24. 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 (Prefer 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.

V. DELIVERABLES

Table No. 2 – Deliverables Per Aircraft Purchased

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), Delivered with aircraft

No.

Due Date and flight hour / flight cycle summary.

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 Packs 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 at the time of purchase.

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 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 specifications 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.

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 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 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 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 must be 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 #1) and the Boeing 737 Next Generation Series Change of Operator Demonstration Profile (Attachment #2). 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.

ATTACHMENTS:

Attachment #1 – Boeing Post Delivery 737NG Flight Profile (63 Pages)

Attachment #2 – 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

GND Ground

GRD Ground

G/S Glideslope

GW Gross Weight

HDG Heading

HF High Frequency

HUD Heads Up Display

HYD Hydraulics

Hz Hertz

IAS Indicated Airspeed

IAN Integrated Approach Navigation

IDG Integrated Drive Generator

IGN Ignitor

ILS Instrument Landing System

INBD Inboard

IND Indicator

INOP Inoperative

INSTR Instrument

INT Intermittent

IRS Inertial Reference System

ISFD Integrated Standby Flt Display

KG Kilogram

KIAS Knots Indicated Airspeed

KT Knots

L Left

LAS Load Alleviation System

LBS Pounds

LE Leading Edge

LGTU Landing Gear Transfer Unit

LNAV Lateral Navigation

LOC Localizer

LRRA Low Range Radar Altimeter

MAC Mean Aerodynamic Chord

MASI Mach/Airspeed Indicator

MCT Maximum Continuous Thrust

MCP Mode Control Panel

MIC Microphone

MMO Maximum Mach Operating Speed

NAV Navigation

ND Navigation Display

ND Nose Down

NDB Non-directional Beacon

NO. Number

NU Nose Up

O2, OXY Oxygen

OAT Outside Air Temperature

OUTBD Outboard

P Pressure

PA Passenger Address

PA Pressure Altitude

PCU Power Control Unit

PFD Primary Flight Display

PG Page

PIDS Primary Ice Detection System

POS Position

P/RST Press/Reset

REV B D541A015-2 6

PSEU Proximity Sys. Electronic Unit

PSI Pounds per Square Inch

PTU Power Transfer Unit

PWS Predictive Wind Shear

PCU Power Control Unit

PFD Primary Flight Display

PG Page

PIDS Primary Ice Detection System

POS Position

P/RST Press/Reset

PSI Pounds per Square Inch

PTU Power Transfer Unit

PWS Predictive Wind Shear

Q Quantity

QRH Quick Reference Handbook

R Right

REV Reverse

RMI Radio Magnetic Indicator

RPM Revolutions Per Minute

RTO Rejected Take-Off

RUD Rudder

RVSM Reduced Vertical Separation Minimums

SAC Single Annular Combustor

SAT Static Air Temperature

S/B Speedbrakes

SFP Short Field Performance

SEC Second

SLFPM Sea Level Feet Per Minute

SOV Shut-Off Valve

SPD Speed

SPSEU Supplemental Proximity Sensing Electronic Unit

STAB Stabilizer

STBY Standby

SS Stick-Shaker

SYS System

T Temperature

TAI Thermal Anti-Ice

TA/RA Traffic Advisory/ Resolution Advisory

TAS True Airspeed

TAT Total Air Temperature

TCAS Traffic Collision Avoidance System

TFC Traffic

TMD Thrust Mode Display

TOGA Take-Off Go-Around

V Volts

VHF Very High Frequency

VLE Maximum Landing Gear Extended Speed

VMO Maximum Velocity Operating Speed

VNAV Vertical Navigation

VOR VHF Omni-Directional Range

VS Vertical Speed

WAI Wing Anti-Ice

WT Weight

WTRIS Wheel-To-Rudder Interconnect

WX, WXR Weather Radar

CHAPTER 1

PREFLIGHT

REV B D541A015-2 7

TABLE of CONTENTS

FLIGHT PROFILE

COCKPIT LIGHTING

STANDBY POWER

ENG/APU OVERHEAT & FIRE WARNING

APU START

NORMAL ELECTRICAL POWER

CAB/UTL & IFE/PASS SEAT

WHEEL WELL FIRE WARNING

CARGO FIRE

FUEL, CENTER FUEL BOOST PUMP AUTO SHUT OFF AND MASTER CAUTION

HYDRAULICS

BRAKE ACCUMULATOR

ASPIRATED TAT (AS REQUIRED)

PNEUMATICS

AIR CONDITIONING -600/700/700C

RECIRC & GASPER FANS -600/700/700C (AS INSTALLED)

AIR CONDITIONING -800/900

RECIRC FANS –800/900

PACK HIGH FLOW

EQUIPMENT COOLING

PRESSURIZATION

WINDOW HEAT

WING ANTI-ICE

INSTRUMENT SWITCHING

IRS SWITCHING

VHF NAV SWITCHING

DISPLAY SELECT PANEL

ENGINE DISPLAY CONTROL PANEL

ENGINE EEC

REV B D541A015-2 8

CONTENTS (Cont’d)

REINFORCED COCKPIT DOOR

FLIGHT CONTROLS

OXYGEN, INTERPHONE, PA

COMMUNICATIONS

INTERTIAL REFERENCE SYSTEM (IRS)

NAVIGATION

AUTOPILOT DISCONNECTS

EXTERIOR LIGHTS

INSTRUMENTS & FURNISHINGS

COCKPIT VOICE RECORDER (CVR)

FLIGHT MANAGEMENT SYSTEM (FMS)

RVSM ALTIMETER

STALL WARNING TEST

MACH AIRSPEED WARNING TEST

REV B D541A015-2 9

S ta ndby C om pas s

A D F/V

O R -D

M E

Tra nsp onder

C om m unic at io ns

E ng A cc el

/D ec el

Fuel C ro ss fe ed

C ru is e

Tri m

A P U S ta rt a nd E le ct ri ca l

C ruise D ata

A uto Isobaric P ressure

Autopilot Flight

Director System

Weather Radar

Windshield

& Foot Air

Window Heat

Alt Alerts

TCAS

10,000 ft

7 - CRUISE

6 - CLIMB

8 - DESCENT

5-TAKEOFF

1-PREFLIGHT

2-ENGINE START

3-AFTER START

4-TAKEOFF

Flight Director System

For safety, limit testing below 10,000 ft

8 – DESCENT

(continued)

Coupled Approach

Bold items–Pilot (with SO coordination)

Italic items–SO (with pilot coordination)

Tactile & Audible

Engine Vibration

Cabin Climb Rates

Eng/Wing Anti-Ice

Pressurization/Pneumatics

APU Fire Warning Switch Shutdown

Pressurization

Descent

C onfig ura tio n W ar nin g

9 – LOW ALTITUDE

10 – APPROACH

& LANDING

11 – TAXI IN & SHUTDOWN

15,000 ft

Fuel Suction Feed, Inertial

System

Autobrake System, Marker

Beacon, GLS (O), Autoland, EGPWS, HUD (O)

10,000 ft

Engine Icing Idle

A lte rn at e Fla ps

Engine Approach Idle

Landing Gear

Manual Extension

Max Reverse Thrust

E N G

IN

E H

IG

H S

TA

G E

P ack H igh Flow

R ecirc Fan &

O verboard E xhaust

Trim A ir

U nbalanced P ack Tem p

A uto M ax P ress

C abin Leak

S ingle P ack and C rossbleed

M anual O

Alternate Gear/LGTU

APU Bleed

A uto sl at

/P

TU

S pee dbra ke s

P A C K H ig h F lo w

In hib it

REV B D541A015-2 10

COCKPIT LIGHTING

Operate interior lighting controls with windshield blackout panels installed:

Capt's & F/O's MAIN PANEL, BACKGROUND, AFDS FLOOD, OUTBD DU, INBD DU, UPPER DU, LOWER DU, WXR, AISLE

STAND FLOOD & PANEL, DOME, CIRCUIT

BREAKER FLOOD, OVERHEAD PANEL,

COMPASS LIGHT

Operate HUD Lighting Controls (As installed)

All lighting controls rotate freely and extinguish at the

OFF position.

Floods dim appropriately and illuminate the appropriate panel correctly.

DUs reduce to minimum intensity.

Individual panels are balanced.

LIGHTS switch 'TEST', 'DIM' & 'BRT' Ensure appropriate lights illuminate at the correct intensity, jewels are properly labeled, all bulbs function.

GRD PWR switch 'OFF' Verify the following lights function:

Capt's MAIN PANEL

Capt's Display Select Panel

Capt's Clock

BACKGROUND flood (fixed)

Standby Instruments and Communication

Engine Control Panel

Fire Control Panel

Cargo Fire Detector Fault Light

Aisle stand equipment powered by STBY POWER

Emergency Exits, DOME

REV B D541A015-2 11

STANDBY POWER

BAT switch 'ON'

STANDBY POWER switch 'AUTO'

EMER EXIT LIGHTS switch 'ARMED'

GRD PWR switch 'OFF' Emergency Exit lights illuminate.

BAT DISCHARGE, MASTER CAUTION(s) & ELEC light illuminates (25 sec delay).

DC METERS selector 'BAT' & ‘AUX BAT' Battery and AUX BAT are 22 to 26 VDC negative amps.

DC & AC METERS selectors 'STBY PWR' Standby power is 22 to 26 VDC, 110 to 120 VAC & 390 to 410 Hz.

EMER EXIT LIGHTS switch 'OFF' Emergency Exit lights extinguish.

STANDBY POWER switch ‘OFF’ STANDBY PWR OFF, MASTER CAUTION(s) & ELEC lights illuminate.

DC METERS selector ‘BAT BUS' Battery is 22 to 26 VDC.

DC & AC METERS selectors 'STBY PWR' Verify AC & DC voltmeters indicate 0 volts.

Engine 1 & 2 Start levers 'CUTOFF' Verify ENG VALVE CLOSED & SPAR VALVE

CLOSED lights are illuminated dim.

FUEL SHUTOFF VALVES BUS

c/b OPEN (P6-3:C6)

Verify engine SPAR VALVE operates on back up battery and charger system.

Engine 1 & 2 Start Levers 'IDLE' Verify SPAR VALVE CLOSED lights are extinguished

& ENG VALVE CLOSED lights are illuminated bright.

(cont’d on next page)

REV B D541A015-2 12

STANDBY POWER, cont’d

Engine 1 & 2 Fire Warning switches ‘PULL’ Verify SPAR VALVE CLOSED & ENG VALVE

CLOSED lights are illuminated dim.

Engine 1 & 2 Fire Warning switches ‘RESET’ Verify SPAR VALVE CLOSED lights are extinguished

& ENG VALVE CLOSED lights are illuminated bright.

Engine 1 & 2 Start Levers 'CUTOFF' Verify SPAR VALVE CLOSED & ENG VALVE

CLOSED lights are illuminated dim.

FUEL SHUTOFF VALVES BUS

c/b CLOSED (P6-3:C6)

GROUND SERVICE switch 'ON' Normal equipment cooling blower runs.

Passenger cabin lights illuminate.

DC METERS selector to 'BAT' & ‘AUX BAT’ Battery and AUX BAT are 24 to 28 VDC positive amps.

Remove the ground power cord Ground Service switch trips off.

Battery is 22 to 26 VDC discharging.

Fwd and Aft Overhead GEAR green lights illuminated.

FUEL CROSSFEED selector 'OPEN' Crossfeed VALVE OPEN light illuminates bright and then dim.

FUEL CROSSFEED selector 'CLOSE' Crossfeed VALVE OPEN light illuminates bright and then extinguishes.

REV B D541A015-2 13

STANDBY POWER, cont’d

L IRS MODE selector 'ATT' ON DC, MASTER CAUTION(s) & IRS lights illuminate.

ECS warning horn sounds (20 sec delay).

STANDBY POWER switch 'AUTO' STANDBY PWR OFF light extinguishes.

L IRS ON DC light extinguishes.

ECS warning horn stops.

Capt's OUTBD, Capt’s INBD (if FMC is powered) &

CTR UPPER displays illuminate within 3 minutes (1.5 minutes norm).

PSEU interface to air mode

((FFWWDD EE BBAAYY))

'CDS FAULT' message changes to

'DSPLY SOURCE' when in air mode.

DC & AC METERS selector 'STBY PWR' Standby power is 22 to 26 VDC, 110 to 120 VAC, 390 to 410 Hz.

REV B D541A015-2 14

STANDBY POWER, cont’d

Equipment on Standby Power

(others, as installed)

Verify the following items: (As installed)

Capt's Clock (illuminated) Interphone and PA

Capt's OUTBD DU VHF Comm 1

Capt's INBOARD DU NAV 1 Control

Capt's Display Select Panel ADF 1

Engine Control Panel IFF No. 1

CTR UPPER DU ATC No. 1

Fuel Quantity Indicators Cargo Fire Detector Fault Light

Capt's EFIS Control Panel F/O Clock (no light)

Standby ADI/ILS Pressurization, Manual Mode

Standby Altimeter Vibrator Capt's Audio Control Panel

Standby Compass and Light

Enter a heading on the IRS Control

Panel

Verify that the Capt’s flight instruments and Standby RMI align to the selection.

(30 seconds delay)

PSEU interface to ground mode 'DSPLY SOURCE' message changes to 'CDS FAULT'

STANDBY POWER switch 'BAT' Standby powered equipment remains operative.

STANDBY POWER switch 'AUTO'

L IRS MODE selector 'OFF'

REV B D541A015-2 15

ENG/APU OVERHEAT & FIRE WARNING

ENG 1 & 2 OVHT DET switches

LOOP 'A'

FAULT/INOP AND OVHT/FIRE TEST

switch hold at 'FAULT/INOP' until responses are verified

FAULT, APU DET INOP, MASTER CAUTION(s), &

OVHT/DET lights illuminate.

FAULT/INOP AND OVHT/FIRE TEST

switch hold at 'OVHT/FIRE' until responses are verified

Master FIRE WARN, MASTER CAUTION(s), & OVHT/DET lights illuminate.

ENGINE 1, ENGINE 2 & APU FIRE WARNING switches illuminate.

ENG 1 OVERHEAT & ENG 2 OVERHEAT lights illuminate.

The fire warning bell sounds in the cockpit.

The APU fire warning horn sounds in the wheel well.

The APU FIRE warning light flashes in the wheel well.

Capt's Master FIRE WARN switch PUSH

Verify that the FIRE WARN lights and bell cancel.

The APU fire warning horn cancels and the APU FIRE warning light illuminates steady in the wheel well.

switch release

ENG 1 & 2 OVHT DET switches

LOOP 'B'

(cont’d on next page

REV B D541A015-2 16

ENG/APU OVERHEAT & FIRE WARNING, cont’d

FAULT/INOP AND OVHT/FIRE TEST

switch hold at 'FAULT/INOP'

Same indications as above.

FAULT/INOP AND OVHT/FIRE TEST

switch hold at 'OVHT/FIRE'

Same indications as above.

F/O's Master FIRE WARN switch PUSH Same indications as above.

ENG 1 & 2 OVHT DET switch 'NORMAL' switch hold at 'FAULT/INOP'

Same indications as above.

FAULT/INOP AND OVHT/FIRE TEST

switch hold at 'OVHT/FIRE'

Same indications as above.

BELL CUTOUT switch PUSH Same indications as above.

Engine 1 & 2 and APU Fire Warning switches

PULL

Verify locks are released.

Engine 1 & 2 and APU Fire Warning switches

RESET

ENGINES EXT TEST switch hold at '1' L, R & APU extinguisher test lights illuminate.

ENGINES EXT TEST switch hold at '2' L, R & APU extinguisher test lights illuminate.

REV B D541A015-2 17

APU START

NOTE: The start cycle may take as long as 120 seconds.

All FUEL PUMP switches 'ON'

DC METERS selector 'BAT' & ‘AUX BAT' (as equipped)

AC METERS selector 'APU GEN'

BUS TRANSFER switch 'OFF'

GEN 1, GEN 2 & APU GEN switches 'ON'

All WINDOW HEAT & PROBE HEAT switches

'ON'

All HYD PUMP switches 'ON'

(Resets IDG fields)

APU switch 'START' and release to 'ON' APU initiates a start sequence.

Verify ‘AUX BAT' indicates 0 amps. (As installed)

Monitor starter engage and cutout on DC ammeter.

APU generator output at idle is 110 to 120 VAC, and 390 to 410 Hz.

Verify the following lights are illuminated:

Left & Right TRANSFER BUS OFF, SOURCE

OFF, GEN OFF BUS, and APU GEN OFF

BUS.

REV B D541A015-2 18

NORMAL ELECTRICAL POWER

Left APU GEN switch 'ON' APU GEN OFF BUS light is extinguished.

Left GEN OFF BUS light illuminated.

Left SOURCE OFF & TRANSFER BUS OFF lights extinguished.

Right TRANSFER BUS OFF, SOURCE OFF and

Right GEN OFF BUS lights are illuminated.

Single Bat Config: 'BAT,' 22 to 26 VDC, negative amps.

Dual BAT Config: ‘BAT’ and ‘AUX BAT,’ 24 to 28

VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

TR 1 is 22 to 30 VDC, positive amps.

TR 2 & 3, 0 VDC, 0 amps

‘B’ Electric Pump LOW PRESSURE light is extinguished.

BUS TRANSFER switch 'AUTO' Right TRANSFER BUS OFF light is extinguished.

TR 3, 2 & 1, 22 to 30 VDC.

Battery Charger starts a charge cycle.

Single Bat Config: ‘BAT,’ 24 to 32 VDC, positive amps.

Dual Bat Config: ‘BAT’ and ‘AUX BAT,’ 24 to 32 VDC, positive amps.

Right APU GEN switch 'ON' Right SOURCE OFF light is extinguished.

All buses and equipment are powered.

BUS TRANSFER switch 'OFF' No change should occur.

REV B D541A015-2 19

NORMAL ELECTRICAL POWER, cont’d

Left APU GEN switch 'OFF' Left TRANSFER BUS OFF & SOURCE OFF, MASTER CAUTION(s) and ELEC light illuminate.

‘A’ Electric Pump LOW PRESSURE light is extinguished.

Si…