## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-1 

# 737-100/200/200C/300/400/500 AIRWORTHINESS LIMITATIONS (AWLs) AND CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

D6-38278-CMR

JULY 2011

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the d ocument and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, S eattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-1 0, MD-10, MD-11, MD-80, MD-88, MD-90, and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in conn ection with this document unless provided in writing by Boeing.

COMPILED AND PUBLISHED BY: MAINTENANCE PROGRAMS ENGINEERING COMMERCIAL AVIATION SERVICES BOEING COMMERCIAL AIRPLANE GROUP

A DIVISION OF THE BOEING COMPANY SEATTLE, WASHINGTON USA

This document has EAR data with an Export Control Classification Number (ECCN) of 9E991. Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An ex port license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individ ual responsibility to abide by all export laws.

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### TABLE OF CONTENTS

REVISIONS ...................................................................................................................... ............................................................................................................ 9.0-5

LIST OF EFFECTIVE PAGES ........................................................................................................ .............................................................................................9.0-11

A. SCOPE....................................................................................................................... ............................................................................................................ 9.0-13
B. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS) ............................................................................... .............................................................. 9.0-13

PAGE FORMAT: SYSTEMS MAINTENA NCE PROGRAM....................................................................................... .............................................................. 9.0-17

CERTIFICATION MAINTENANCE REQUIREMENTS TASKS................................................................................... ............................................................ 9.0-18

C. FUEL SYSTEMS AIRWORTHINESS LIMITATIONS...................................................................................... ........................................................................ 9.0-19

PAGE FORMAT: SYSTEMS AIRWORTH INESS LIMITATIONS .

................................................................................ ............................................................ 9.0-21
737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS ...................................... ...................... 9.0-22
737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS....................................... ........................ 9.0-32

D. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEMS ..................................................................... ................................................... 9.0-44

AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEM TASKS................................................................... ............................................ 9.0-45

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### REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL FEBRUARY 2003 Original Release - Added CMR 27-CMR- 01 applicable to airplanes accomplishing Service Bulletin 737-27-125 2 (737-100/200/200C) and 737-27-1255 (737-300/400/500). Submitted by: S. Pierini (Boeing) Approved by: (Seattle FAA ACO)

NOVEMBER 2004 Added CMR 52-CMR-01 to perform a function al check of the fligh t deck door locking and unlocking latch bolt mechani sm on the decompression panel. Deleted “RELATED MRBR ITEM NUMBER” colu mn as it is no longer necessary. Submitted by: G.Palafox(Boeing) Approved by:

MARCH 2006 Added Section “C” of Airworthiness Limitat ions to satisfy maintenance requirements introduced by 25.981 and Special Federal Aviation Regulation (SFAR) No. 88. Submitted by: Approved by:

MAY 2006 Revised AWL Revision Process paragraphs in the Applicability column of the AWL tables to include -100, -200, and -200C models. Revised the applicability of 28-AWL-05, 28-AWL-09, 28-AWL-14, 28-AWL-18, and 28- AWL-20 by adding the -200C model. Submitted by: Approved by:

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

REVISION AND REVISION DESCRIPTION APPROVAL SEPTEMBER 2006 Added a functional check of the center ta nk Fuel Boost Pump Auto Shutoff System Number 28-AWL-20. Applicable to 737-300/400/500 airplanes that have incorporated Service Bulletin 737-28A1216. Added a functional check of the auxiliary fuel tank Boost Pump Auto Shutoff System Number 28-AWL-21. Applicable to 737- 300/-400 airplanes wit h Boeing certified auxiliary fuel tanks installed, that have incorporated Service Bulletin 737-28A1216. Added a functional check of the center ta nk Fuel Boost Pump Auto Shutoff System Number 28-AWL-21. Applicable to 7371 00/-200 airplanes thathave incorporated Service Bulletin 737-28A1228. Added a functional check of the auxiliary fuel tank Boost Pump Auto Shutoff System Number 28-AWL-22. Applicable to 737-100/-200 airplanes with Boeing certified auxiliary fuel tanks installed, that have incorporated Service Bulletin 737-28A1228. Deleted the RELATED MRBR ITEM NUMBER column information from the PAGE FORMAT: SYSTEMS MAINTENANCE PROGRAM page since this information does not apply to this table. Revised 737-100/200 28-AWL-1 4 to indicate that a float assembly must be used. Submitted by: Approved by:

JUL 2011

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7 REVISION AND REVISION DESCRIPTION APPROVAL NOVEMBER 2007 Revised Section B. paragraph on Exceptional Short-Term Extensions to clarify process and notification requirements. Revised the first sentence of Section C. Airworthiness Limitations - Fuel Systems by adding “scheduled inspections and design limitations”, and revised the information on Exceptional Short-Term Extensions to clarify notification requirements. Revised the heading in Section C to read “Page Format: Fuel Systems Airworthiness Limitations" instead of “Page F ormat: Airworthiness Limitations”. For 737-100/200: Revised Airworthiness Limitation (AWL) 28-AWL-19 to add Ground Fault Interrupter (GFI) relays to the limitation that restricts resetting of fuel pump circuit breakers. Added new AWL 28-AWL-23, a yearly check of the Boost Pump GFI. This AWL is applicable to airplanes th at have incorporated Se rvice Bulletin 737-28A1212. For 737-300/400/500: Revised AWL 28-AWL-19 to add GFI relays to the limitation that restricts resetting of fuel pump circuit breakers. Added new AWL 28-AWL-22, a yearly check of the Boost Pump GFI. This AWL is applicable to airplanes thathave incorporated Servi ce Bulletin 737-28A1212. Submitted by: E. B. Lange (Boeing) Approved by: Phillip Forde (FAA)

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

REVISION AND REVISION DESCRIPTION APPROVAL MARCH 2008 Revised 28-AWL-01 to remove 36000F H task interval limitation based upon engineering review and operat or maintenance practice a nd removed body station and buttock line text and replace d with "per AMM 28-11-00". Revised 28-AWL-03 to reflect the new maximum loop resistance values associated with the lightning protection of th e unpressurized FQIS wire bund le installations so as to satisfy the Airworthiness Limitation Instruct ions required by SFAR 88. Also removed the joint resistance values and 36000FH task interval limitation base d upon engineering review and operator maintenance practice and removed -100 from the applicability column since this AWL does not apply to the 737-100. Revised 28-AWL-04 to remove -100 from the applicability column since this AWL does not apply to the 737-100. Revised 28-AWL-18 by replacing both Service Bulletin (SB) 737-28A1120 and Airworthiness Directive (AD ) 99-21-15 with su perseded SB 737-28A 1263 and AD 2007- 24-02. Also remove the following text "o r an additional Teflon sleeve" and "Non jacketed wiring and double sleeves". Submitted by: John Sabolchy (Boeing) Approved by: Dorr Anderson (FAA)

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D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9 REVISION AND REVISION DESCRIPTION APPROVAL MAY 2009 Added Section D. front matter for the Airw orthiness Limitations-Nitrogen Generation System (NGS) requirements and also added 47-AWL-01 thru 47-AWL-05 NGS tasks. These items apply to the 737-400 only. Revised 737 (12345) CMR tasks to be consis tent with AMOCs since December, 2008, including updating CMM references such as Vendor and Cage Code. Revised 28-AWL-02 (12345) by updating text in the task descri ption to clarify inspection requirements and location. Revised the task description of 28-AWL-03 (7 37-12345) by removing the statement "at side of body, and" to reflect the or iginal intent of the task requirement. Revised 28-AWL-04 (12345) by rewording text to clarify ta sk description requirements. Revised the Task Description for 28-AWL-05 toclarify the intent of the requirement and to provide the SWPM referenc e for installation requirements. Revised the Task Description for 28-AWL-06 (for 737-345) to clarify the party responsible for repair ing the Isolated Fuel Quantity Transmitter (IFQT). Revised the task description of 28-AWL-07, and -12 (737-12345) by adding text to provide an alternative to the identified CMM by using th e manufacture's production procedures. Revised 28-AWL-11 (737-12345) with updated F uel Tank Penetration text per the latest FAA AMOC 120S-09-230. Revised 28-AWL-17 (737-12345) resistance from "1 ohm" to "0.010 (10 milliohms)" to correct resistance between the pressure relief valve and the door. Revised 28-AWL-19 (737 -12345) by replacing the text "&" in the task description to "or" to clarify the intent of the task. Revised 28-AWL-20 by adding vendor C MM in task description for clarification. Added new AWL 28-AWL-23 (737-345), a yearly check to verify the continued functionality of the center tank fuel bo ost pump Power Failed On Protection System. Added new AWL 28-AWL-24, a yearly check to verify the continued functionality of the center tank fuel boost pump Power Failed On Protection System. Added new AWL 28-AWL-25 (737-12), a ye arly check to verify the continued functionality of the auxiliary tank fuel boost pump Power Failed On Protection System. Submitted by: John Sabolchy (Boeing) Approved by: Jeffrey E. Duven (Seattle FAA ACO)

SIGNATURE ON FILE 8/13/2009

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

REVISION AND REVISION DESCRIPTION APPROVAL AUGUST 2010 Revised Paragraph D. Airworthiness Limi tations – Nitrogen Generation System tasks by updating the FAA regulations corresponding to the compliance measures provided in the subsequent AWLs. Revised 47-AWL-01 and 47-AWL-02 by updating the Applicability column to read “Airplanes that have incorp orated Service Bulletin 73 7-47-1004 or 737-47-1007. Revised 47-AWL-01 by updating the Task Descr iption by adding instructions and a Note to clarify the procedure and parameters for the maintenance action. Revised 47-AWL-02 by updating the Task Description to clarify the procedure and parameters for the maintenance action of th e isolator hose and toreplace "per" with "refer to". Revised 47-AWL-03, 47-AWL-04, and 47-AWL-05 by updating the Applicability column to read "Airplanes that haveincorporated Service Bulleti n 737-47-1005 or 737-47-1008. Revised 47-AWL-04 by replac ing "per Boeing AMM 47-43- 02" with "(refer to Boeing AMM 47-43-02)". Revised 47-AWL-05 by replacing "(ref AMM ATA 47-21-00)" with "(refer to Boeing AMM 47-43-02)". Added 47-AWL-06, an identification of th e maintenance standard for the Nitrogen Generation System and notice of potential future compliance re quirements associated with decreased aircraft descent rates. Submitted by: John Sabolchy (Boeing) Approved by: Robert D. Breneman (Seattle FAA ACO)

SIGNATURE ON FILE 12/15/2010

JULY 2011 Revised 47-AWL-03 to incorp orate NGS performance features to show compliance with 14 CFR 26.33. Submitted by: Mark Arnold (Boeing) Approved by: Ron Landes for Robert D. Breneman (Seattle FAA ACO)

SIGNATURE ON FILE 8/10/2011

JUL 2011Section Page Date Section Page Date Section Page Date Section Page Date Section Page Date

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D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-13 A. SCOPE
The scheduled maintenance re quirements described in this sect ion result from airplane certification activities with the U.S. Fe deral Aviation Administration (FAA). Accordingly, this FAA approved Cert ification Maintenance Requirements (CMRs) doc ument is cross-referenced in the Model 737-300/400/500 Type Certificate Data Sheet. Th is document satisfies the requirements of FAR 25.571, FAR 25.1529 and Advisory Circular (AC) 25 -19 as the controlling document for all 737-100/2 00/200C/300/400/500 CMRs . These maintenance actions are mandatory.

B. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)
CMR DEFINITION
As defined by AC 25-19, a CMR is a required periodic task, established du ring the design certificatio n of the airplane as an op erating limitation of the type certificate. CMRs usually result from a formal, numerical anal ysis conducted to show complianc e with catastrophic and hazardou s failure conditions. Additional notes concerning the definition of CMRs:
1. A CMR is intended to detect safety-significa nt latent (hidden) failures that would, in combination wit h one or more specific failures or events, result in a
hazardous or catastro phic failure condition.
2. It is important to note that CMRs are derived from a funda mentally different analysis proce ss than the main tenance tasks and intervals that result from the Maintenance Steering Group (MSG-3) Analysis associated with Maintenance Review Board (MRB) activities. MSG-3 Analysis acti vity produces maintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance tasks, which are performed before failure occurs (and are intended to prevent fa ilures), as well as failure-finding tasks. CMRs, on the other hand, are typically failure-finding tasks, and exist solely to limit the exposure to otherwise hidden failures. Nevertheless, use of po tential failure-finding tasks, suc h as functional checks and inspections, may al so be appropriate.
3. CMRs are designed to verify that a certain failure has or has not occu rred, and do not provide any preventati ve maintenance function. CMRs “restart the failure clock to zero” for latent failures by verifying that the item has not failed, or ca used repair if it has failed. B ecause the exposure time to a latent failure is a key element in the calculations used in a safety anal ysis performed to show complian ce with FAR 25.1309, limiting the exposure time will have a significant effect on the resultant overall failure probability of the system. The CMR Task Interval should be designat ed in terms of flight hours, cycles, or calendar ti me, as appropriate.

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

4. The type certification process assumes that the airplane will be maintained in a condition of airworthiness with respect to i ts certified or properly altered condition. The process described in AC 25-19 is not in tended to establish normal maintenanc e tasks that should be defined thro ugh the MSG-3 Analysis process. Neithe r is this process intended to establish CMRs for the purpose of providing supplemental margins of safe ty for concerns arising late in the type design approval process.
5. CMRs should not be confused with required structural inspection programs and are to be developed by the type certificate appl icant to meet the inspection requirements for dama ge tolerance, as required by FAR 25.571 or 25 .1529, Appendix H25.4 (Air worthiness Limitations s ection). CMRs are to be developed and administered separately from any structural inspection programs.

CMR TYPES

CMR Tasks are divided into two cate gories: One Star CMRs (*) and Two Star CMRs (**). They are defined as follows:
1. One Star CMRs (*) – The tasks and intervals specified are mandatory and cannot be changed, escalated, or deleted without the concurrence of the FAA Seattle ACO.
2. Two Star CMRs (**) – Task intervals may be adjusted in accordanc e with each operator’s approved escalation program or an approved reliability program in a like manner for any MRB Report task, but ma y not be deleted without prior Seattle FAA ACO approval.

ESCALATION OF TWO STAR CMRs (**)
All Two Star CMRs (**) can be managed an d controlled the same as any MRB Report task; however, they can not be deleted from an operator’s program without prior Seattle FAA ACO approval. For operators with approved escalation practices or an approved reliability program, d ata collection and analytical techniques are used to make adjust ments to an operator’s maintenance program. It has been demonstrated that the man agement of a maintenance program does not give rise toundue escalations; consequently, the escalat ion of Two Star CMR (**) intervals within an operator’s maintenance program will be properly managed by the op erator subject to local regu latory authority approval.

FEB 2003

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-15 EXCEPTIONAL SHORT-TERM EXTENSIONS

Since CMR intervals are based on statis tical averages and reliability rates, an exceptional short-term extension of 10% for eac h CMR listed in this document may be made without jeopardizing safety. The local regu latory authority (e.g. a PrincipleMaintenance In spector) mustconcur with any exceptional short-term extensionsbefore they take place using procedures esta blished with the local regulatory authority in th e operators’ manuals. The “exceptional short-term extension” process is applicable to CMR intervals. It should notbe confused with the operator’s “short-term escalation” program for normal maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8300.10.
The Seattle FAA ACO has accepted that th ese exceptional short-term exte nsions may be granted withoutconsultation with that off ice:
1. The term “exceptional short-term extension” is defined as an increase in a CMR interva l that may be needed to cover an uncont rollable or unexpected situation. All CMRs listed in this document have been approved with an ex ceptional short-term extension of 10%.
2. Repeated use of extensions, either on the sa me airplane or on similar airplanes in an operator’s fleet, should not be used asa substitute for good management practices. Exceptional short-term exte nsions must not be used for fleet CMR escalation.
After a CMR has experienced an exceptional short-term extension, the CMR interval will revert back to its interval listed in th is document. The Seattle FAA ACO must approve, prior to its use, any desired extension not explicitly listed above.
This exceptional short-term exte nsion listed above applies to air lines that fall under the United States FAA jurisdiction only. Operators who are not under the U.S. FAA jurisdiction should obtain interval exte nsion approvals from thei r local regulatory agency.

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

POST CERTIFICATION CHANGES TO CMRs
Any post certification changes to CMRs sh ould be reviewed by the 737-100/200/200C/300/400/500 Certifica tion Maintenance Coordin ation Committee (CMCC) and approved by the Seattle FAA ACO:
1. Since the purpose of a CMR is to limit the exposure time to a given significant lat ent failure as part of an engineering anal ysis of overall system reliability, instances of a CMR task repeatedly find ing that no failure has occurred may not be sufficient justification for deleting the ta sk or increasing the time between repetitive performances of the CMR task. In general, * CMRs are not good candidates fo r escalation under an operator’sreliability program. A * CMR task change or interval escalation can only be made if wor ld fleet service experience indic ates that certain assumptionsregarding component failure rates made early during the engineering analysis were overly conservative, and a re-calculation of system reliability w ith revised failure rates of certain components reveals that the * CMR task or interv al may be changed. 2. The introduction of a new CMR or any chan ge to an existing CMR should be reviewed by the same process used during initial cer tification. It is important that operators be affo rded the same opportunity to participate that they received during the original certification of the airplane, in order to allow the operators to manage their own maintenance programs.
3. In the event that later data provides sufficient basis for re laxation of a CMR (less restrictive actions to be performed), th e change may be documented by an Seattle FAA ACO approved ch ange to this CMR document.
4. If the requirements of an existing CMR must be increased (more restrictive actions to be performed), it will be implemented b y a change to this CMR document and enforced by an F AA Airworthiness Directive (AD).
5. After initial aircraft certification, th e only basis for adding a new CMR is in asso ciation with the certification of design changes. 6. A new CMR created as part of a design cha nge should be part of the app roved data for that change and added to this CMR docume nt.
In the event that a CMR is revised, Boeing will document it by preparing a revision to this document that will be approved by t he Seattle FAA ACO. This revision will then be forwarded to all 737-100/200/200C/300/400/500 operators and the Seattle FAA ACO offices.

FEB 2003

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

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COLUMN EXPLANATION

CMR ITEM NUMBER Each task is given a unique CMR Ite m Number. The first and second digits are the ATA Chapter Number.

TYPE CMR TYPE: CMRs are categorized into one or two star CMRs based on whether or not they ca n be escalated by the operator without prior Seattle FAA ACO approval. * Cannot be escalated or deleted without prior Seattle FAA ACO approval. ** Can be escalated based on the operator’s approved program for continued airworthiness based on continuous analysis and surveillance; however, these tasks cannot be deleted without prior Seattle FAA ACO approval.

TASK TASK TYPES/CATEGORIES: LU = Lubrication SV = Servicing OP = Operational Check VC = Visual Check GV = General Visual Inspection DI = Detailed Inspection FC = Functional Check RS = Restoration DS = Discard

CMR INTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.

APPLICABILITY APL ENG Applicable Airplane Model and Engine.

TASK DESCRIPTION Description of the task to be performed.

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CERTIFICATION MAINTENANCE REQUIREMENTS TASKS

CMR ITEM NUMBER TYPE TASK CMR INTERVAL APPLICABILITY APL ENG TASK DESCRIPTION

27-CMR-01 * FC 10000 HRS NOTE ALL Functionally check rudder main PCU Internal leakage in a loaded condition. Applicability Note: Airplanes that have incorporated Service Bulletins 737-27-1252 on the 737-100/-200/-200C or 737-27-1255 on the 737-300/400/500.

52-CMR-01 * FC 3,000 FH NOTE ALL Perform a functional check of the locking an d unlocking latch bolt mechanism on the flight deck door decompression panel. Applicability Note: Applicable to airplanes with the Enhanced Flight Deck Security Door installed by the customer sp ecific Boeing Service Bulletins.

NOV 2004

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-19 C. FUEL SYSTEMS AIRWORTHINESS LIMITATIONS

This section of the Airworthiness Limitationscontains an FAA approved program of sc heduled inspections and design limitations for operators to incorporate into their maintenance program for this type de sign to meet the new standards an d assumptions introduced by § 25.98 1 and Special Federal Aviation Regulation (SFAR) No. 88. SFAR 88 - Fuel Tank System Fault Tolerance Eva luation Requirements a nd Title 14 Code of Fed eral Regulations § 25.981 - Fuel Tank Ignition Prevention require maintenance instructions, and contro l limitations for certain fuel tank critica l design configurations.
Paragraph 2(a) of SFAR 88 requires certain design approval holders of Type Certificate s (TCs) and Supplementa l Type Certificate s (STCs) of large transport airplanes to conduct a safety revi ew of the fuel tank systems. The purpose of the safety review is to identify design features that may result in development of ignition so urces in the fuel tank systems. Fuel System Airworthiness Limitation (AWL) items are mandatory main tenance actions required to ensure that unsafe conditions identified by the SFAR 88 safetyreview do not occur or are notintroduced into the fuel tank system as a result of configuration changes, re pairs, alterations, or deficienci es in the maintenance program th roughout the operational life of the airplane. An AWL may be: an Airworthiness Limitation Instruction (ALI) or a Crit ical Design Configuration Control Limitation (CDCCL).

CDCCLs are a means of identi fying certain design configuration features intended to preclude a fuel tank ignition source for th e operational life of the airplane. CDCCLs are mandatory and cannot be changed or deleted wit hout the approval of the Seattle FAA ACO that is responsible for the airplane model Type Certificate, or applic able regulatory agency. A critical fuel tank ignition source prevention feature may exist in t he fuel system and its related installation or in systems that, if a failure condition were to dev elop, could interact with the fuel system in such a way thatan unsafe condition would develop without this limitat ion. Strict adherence to configuration, methods, techniques, and practices as prescribed is require d to ensure compliance with the CDCCL. Any use of parts, methods, techniques or practices not contained in the applicable CDCCL must be approved by the Se attle FAA ACO that is responsible for the airplane model Type Cer tificate, or applicable regulatory agency.
ALIs identify inspection tasks related to fuel tank ignition sourceprevention which must be done to maintain the design level of safety for the operational life of the airplane. These ALIs are mandat ory and cannot be changed or deleted without the approval of the Seattle FAA ACO tha t is responsible for the airplane model Type Certificate, or applicab le regulatory agency. Strict adherence to me thods, techniques an d practices as pres cribed is required to ensure the ALI is complied with. Any use of methods, techniques or practices not containe d in these ALIs must be approved by th e Seattle FAA ACO that is responsible for the airpla ne model Type Certificate, or applicable regulatory agency.

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

USE OF ALTERNATE TOOLS
For AWLs which require use of certain tools, use of alterna te tools requires prior approval from the Seattle FAA ACO.

EXCEPTIONAL SHORT-TERM EXTENSIONS

Since AWL intervals are based on estimations of the probability of an event, an exceptional short-term extension for each fuel system AWL listed in this document may be made without jeopardizin g safety. The local regulator y authority (e.g., a Principle Maintenance Inspector) mus t concur with any exceptional short-term extensionsbefore they take place using procedures esta blished with the local regulatory authority in th e operators’ manuals. The “exceptional short-term extension ” process is applicable to AWL intervals. It sh ould not be confused with the operator’s “short-term escalation” program for normal maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8300.10.
The Seattle FAA ACO has accepted that th ese exceptional short-term exte nsions may be granted without consultation with that off ice:
1. The term “exceptional short-term extension” is defined as an increase in a fuel system AWL interval that may be needed to cov er an uncontrollable or unexpected situation. All AWLs listed in this section have be en approved with an exceptional short-term extension of 30 days.
2. Repeated use of extensions, either on the sa me airplane or on similar airplanes in an operator’s fleet, should not be used asa substitute for good management practices. Exceptional short-term exte nsions must not be used for fleet AWL extensions.
After a fuel system AWL has experienced an exceptional short-term extension, the AWL interval will revert back to its interval listed in this document. The Seattle FAA ACO must approve, pr ior to its use, any desired extension not explicitly listed above.
This exceptional short term extension listed above applies to airlines that fall under the United States FAA jurisdiction only. Operators who are not under the U.S. FAA jurisdiction should obtain interval exte nsion approvals from their local regulatory agency.

REGULATORY AGENCY APPROVAL
Any deviations from the published AWLs in structions included in this document require a pproval from the Seattle FAA ACO. This applies to operators under the US FAA jurisdiction on ly and to airplanes registered in the US. All other operators should ob tain approval form thei r own local regulatory agency for any deviations from the listed AWL instructions.

NOV 2007

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-21 AWL REVISION PROCESS
In the event that an AWL is revised, Boeing will prepare a revision to this document that will be approved by the Seattle FAA A CO. This revision will then be forwarded to all 737-100/200/200C/300/400/500 operators and the Seattle FAA ACO.

PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONS

COLUMN EXPLANATION
AWL NUMBER Each task is given a unique AWL Item Number. The first and second digits are the ATA Chapter Number.

TASK ALI = Airworthiness Limitation Instruct ion. These tasks are inspections that shou ld be performed at the listed intervals. CDCCL = Critical Design Configuration Control Limitations
INTERVAL Task frequencies are spec ified in terms of a usage parameter such as flight hours, cycles or calendar time.
APPLICABILITY Airplane model applicability.

TASK DESCRIPTION Description of the task to be performed or critical design configurations aspects thatcannot be changed without violating the intent of the design.

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

28-AWL-01 ALI 10 YRS 737-100/200/200C airplanes that have incorporated Service Bulletin

737-28-1208 External Wires Over Center Fuel Tank Concern: Potential for Wire Chafing and Arcing to Center Fuel Tank Upper Panel. Perform a detailed in spection of the wire bundles routed over the center fuel ta nk and under the main deck floor boards per AMM 28 -11-00 to detect damaged c lamps, wire chafing, damage to the vapor barrier, and that the wire bundle is not in contact with surface of the center fuel tank. If discrepancies are found repair per the Boei ng Standard Wiring Practices Manual (SWPM) D6-54446. Interval Note: Threshold for interval inspection is 10 years after incorpora tion of Service Bulletin 737-28-1208.

28-AWL-02 CDCCL N/A 737-100/200/200C airplanes that have incorporated Service Bulletin

737-28-1208 External Wires Over Center Fuel Tank Concern: Potential for Wire Chafing and Arcing to Center Fuel Tank Upper Panel. If any maintenance is performed in the area under the floor boards and over the center fuel tank, verify the following: 1. Maintain the existing wire bundle routing and clamping. 2. Installation of any new wire bundles must be per Boeing Standard Wiring Practices Manual, D6-54446. 3. Perform a detailed inspection of the wire bun dles routed on main deck over the center fuel tank and under the main deck floor boards in the areas of the performed maintenance to detect damaged clamps, wire chafing, a nd that the wire bundle is not in contact with the surface of the center tank. If wiring discrepancies are found, re pair per the Boeing Standard Wiring Practices Manual, D6-54446.

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-23 28-AWL-03 ALI 10 YRS 737-200/200C airplanes that have incorporated Service Bulletin

737-28-1178 Fuel Quantity Indicating System (FQIS) – Out-Tank Wiring Lightning Shield to Ground Termination Concern: Potential for Lightning induced voltages on the FQIS wiring to enter the fuel tank. Perform the following functional check to ensure the integrity of the FQIS wiring shield to ground termination: Verify the resistance of the shield to ground terminations at the spar penetration in the unpressurized area by making the following measurements using a Loop Resistance Tester P/N 906-10246-2 or 906-10246-3 per Boeing AMM 20 -55-54. Restore the bonds per the Boeing AMM if required. Perform a loop resistance measurement wh ere the wire bundle enters the fuel tank. The loop resistance shall not exceed 28 milliohms for Connector D884 (Left Main Tank). The loop resistance shall not exceed 28 milliohms for Connector D888 (Right Main Tank). The loop resistance shall not exceed 35 milliohms for Connector D886 (Center Main Tank).

28-AWL-04 CDCCL N/A 737-200/200C airplanes that have incorporated Service Bulletin

737-28-1178 Fuel Quantity Indicating System (FQIS) – Out-Tank Wiring Lightning Shield to Ground Termination Concern: Potential for Lightning induced voltages on the F QIS wiring to enter the fuel tank. If the FQIS wire bundle or the shield on the FQIS wire bundle is repaired or replaced, verify the following: 1. Presence of shielded wiring. 2. The shield ground is termina ted per the Boeing SWPM 20-10-15. 3. The installation is inspected per 28-AWL-03. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-05 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Out-Ta nk Wiring Installation Separation Requirement Concerns: Potential for hot shorts and EMI induced voltages on the FQIS wiring to enter the fuel tank. For airplanes incorporating Isol ated Fuel Quantity Transmitter (I FQT) Service Bulletin 737-28- 1178, the FQIS wiring is defined as the wiring between the IFQT and the fuel tank. For airplanes not incorporating IFQT, the FQIS wiring is defined as the wiring between the indicators and the fuel tank. Routing and installation of any new wiring mustuse wire types BMS 13-48, BMS 13-60 or BMS 13- 58, and not be within a 2-inc h radius of the FQIS wiring. Under single failures of clamps or brackets, a separation grea ter than 1⁄2 inch must be maintained from the FQIS wiring. This AWL is for de sign requirements. The installation is per SWPM 20-10-11.

28-AWL-06 CDCCL N/A 737-100/200/200C airplanes that Service Bulletin 737-28-1178 is not applicable to (Airplanes with Electronic VTO Units) Fuel Quantity Indicating System (FQIS) – Indicator and VTO Unit Repair Concern: Potential for main tenance error during FQIS Indicator or Volumetric Top-Off (VTO) Unit repair. The design of the FQIS Indicators and t he VTO Unit limits the voltage, current and power into the tank to preclude possible ignition source into the tank. Repair and overhaul of FQIS Indicators and VT O must be per Goodrich (V89305) Component Maintenance Manual (CMM)28-41-11 Revision 12, CMM 28-41-13 Revision 11, 28-41-23 Revision 10, or later revisions of these CMMs that have been ap proved by the Seattle FAA ACO. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-25 28-AWL-07 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Hardware (Tank Units and Compensators) Concern: Potential for maintena nce error during repair of in- tank hardware (tank units and compensators). Arc gaps may develop that could result in an ignition source inside the fuel tank. The dielectric of these componen ts must be maintained to provide lightning protection for voltages that could be coupled on the FQIS wiring or onto the wiring between the IFQT and the fuel tank if the shield or shield ground of the wiring is compromised. Repair and overhaul of FQIS tank units and compensators must be per Goodrich (V89305) Component Maintenance Manual (CMM) 28-40-25 Revision L, CMM 28-41-05 Revision 11, CMM 28-40-58 Revision 4, or later revisions of th ese CMMs that have been approved by the Seattle FAA ACO. The AC powered float switch on airplanes with Volumetric Top-Off (VTO) function is not repairable. The manufacturer's production procedures for this component may be used as an alternate to the identified CMM.

28-AWL-08 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Rep air or Replacement of In-Tank Wire Harness Concern: Potential for error during repair or replacement of in-tank wire harness. Arc gaps may develop that could result in an ignit ion source inside the fuel tank. For airplanes with IFQT this is a concern if the safe-side harness is compromised. Repair and overhaul of FQIS in-tank wire ha rness must be per Boeing SWPM 20-14-12. Installation of FQIS in-tank wire harness must be per Boeing AMM 28-41-101. Wire slack clearance between wires and stru cture must be greater than 0.12 5 inches. Verify the following when installing the spar penetration receptacle: 1. The mounting area is free of primer or paint. 2. A new O-ring is installed. 3. The receptacle mounting screws are tightened to 65 to 90 pound-inches. 4. A continuous bead of seal ant is applied around the entireperimeter of the internal tank harness connector at the spar interface. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-09 CDCCL N/A 737-100/200/200C airplanes that have incorporated Service Bulletin

737-29A1096 Lightning Protection – Hydrau lic Line Fuel Tank Penetration Concern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting and the spar duri ng a lightning strike event. The following design features mu st be maintained per Boeing AMM 29-11-53 if the bulkhead fitting is removed and replaced: 1. Verify electrical fay surface bond from bu lkhead fitting to structure outside the tank is 0.001 ohms (1 milliohm) or less, 2. Install fillet seal on the fitting to the tank wall interface outside the tank. 3. Install full bodied fillet seal encapsulating the fitting to the tank wall interface inside the tank. 4. Verify an electrostatic bonding jumper exists between the structure and the Hydraulic Heat Exchanger inside the tank. 5. Verify electrical bond from structure to the Hydraulic Heat Exchanger inside the tank is 0.005 ohms (5 milliohms) or less if the bonding jumper was removed and replaced.

28-AWL-10 CDCCL N/A 737-100/200/200C airplanes that have incorporated Service Bulletin

737-28A1174 Lightning Protection – Engine Fuel Feed Line Tank Penetration Concern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting and the spar dur ing a lightning strike event. The following features must be ma intained per Boeing AMM 28-22-142 if the bu lkhead fitting or attached tubing are removed and replaced: 1. Verify electrical fay surface bond from bulkhead fitting to struct ure (wing front spar, out-tank) is 0.0005 ohms (0.5 milliohms) or less. 2. Install full-bodied fi llet seal encapsulating the bulkhead fi tting to the wing front spar interface inside and outside the tank. 3. Install full bodied fillet seal encapsulating the tubes to fitting joints interface inside and outside the tank. 4. Verify an electrostatic bonding jumper exists between the first tube mating with the bulkhead fitting, and the structure inside the tank. 5. Verify electrical bond from the structure (wing front spar, in-tank) to first tube mating with the bulkhead fitting is 0.010 ohms (10 milliohms) or less. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-27 28-AWL-11 CDCCL N/A All Lightning, Fault Current or Hot Short Protection – Fuel Tank Penetrations Concern: Potential for arcing or sparking inside the tank at a conductive metal-to-ground structure interface as a result of electrical faultcurrents or lightning strike events due to insufficient bonding within the ground electrical path. Any alteration, design change or repair involving new penetrations of the fuel tanks (such as a repair with fasteners, adding a bracket, bulkhead fitting or equipment) or change to the design features of the existing equipm ent penetrations (such as fuel measuring sticks, sump drain valves, fueling manifold, fuel temperature sensor, and motor operated fuel shutoff valve adaptor plate) requires approval by the Seattle FAA ACO or an Authorized Repres entative (AR) of the Boeing Commercial Airplanes Delegated Compliance Organization (BDCO). However, any alteration, design change or repair involving new penetrations of the fuel tanks, accomplished in accordance with an FAA-approved Boeing Structural Repair Manual (SRM) or Boeing Service Bulletin is not subject to this requirement fo r additional approval.

28-AWL-12 CDCCL N/A All AC and DC Electrical Fuel Tank Pump Maintenance Concern: Potential for maintenance error during pump overhaul. Fuel pump designs contain ignition source prevention means (i .e., flame arrestor, thermal fu ses, materials, leadwire retention means, etc.) that must be main tained if pump is overhauled. Repair and overhaul of fuel pumps must be per Eaton (VK2523) Component Maintenance Manual (CMM) 28-20-3 7 Revision 10, Argo-Tech (V59875) CMM 28-20-1 Revision 7, CMM 28- 20-5 Revision 6, CMM 28-20-07 Revision 1, or later revisions of these CMMs that have been approved by the Seattle FAA ACO. The manufacturer's production procedures for this component may be used as an alternate to the identified CMM. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-13 CDCCL N/A All AC Fuel Pump Fault Current Fay Surface Bond Installation Concern: Potential for fa ult current path through the pump housing to structure inside the tank. Electrical faults internal to th e fuel pump motor impeller are by design routed through the motor impeller assembly to the bonding straps on the front face of the motor impeller assembly to structure outside the tank. The fay surface bond ensures that fault currents are conducted to structure outside the tank until the circuit breake r and/or GFI has had timeto remove power from the pump. The following features must be maintained during pum p replacement per Boeing AMM-28-22-41: 1. Installation of the pump fault current faying surface bond. 2. Verify Motor Impeller bonding resistance to structure is 0.0002 ohms (0.2 milliohms) or less.

28-AWL-14 CDCCL N/A 737-200/200C airplanes that have incorporated Service Bulletin 737-28A1141 or

737-28A1192 Fueling Float Switch System Installation Concern: Potential for wire chafing and arcing to conduit inside the tank. The float switch assemblies in fuel tank 1 and 2 are not repairable to the initial ma nufactured standards. The center tank and Boeing auxiliary tank (if installed) Float Switch and Liner are not repairable to the initial manufactured standards. (Refer to Boeing AMM 28-21-71) During float switch replacement, a new float switch assembly must be used in Tanks 1 and 2, and a new float switch assembly and liner system must be used for center and Boeing auxiliary fuel tank (if installed) as applicable.

28-AWL-15 CDCCL N/A All Center Fuel Tank Access Doors – Lightning Protection Bond Concern: Potential for arcing or sp arking inside the tank at the int erface between the door and the tank structure as a result of a direct stri ke or conducting currents through the wing skin. The following features must be main tained during ce nter fuel tank access door installation per Boeing AMM 28-11-31: Verify presence of a phenolic strip positioned around the outermost periph ery of the door that mates with the wing skin inside the tank. Connect the bonding jumper to the door and verify the resistance between the door and structure is 0.010 ohms (10 milliohms) or less. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-29 28-AWL-16 CDCCL N/A All Main Fuel Tank Access Doors – Lightning Protection Bond Concern: Potential for arcing or sp arking inside the tank at the int erface between the door and the tank structure as a result of a direct stri ke or conducting currents through the wing skin. The following features must be m aintained during main (wing) fu el tank access door installation per Boeing AMM 28-11-11: Verify presence of a phenolic strip positioned around the outermost periph ery of the door that mates with the wing skin inside the ta nk, and apply grease or anti-c orrosion compound to both sides of the knitted aluminum me sh gasket. Install th e prepared knitted aluminum mesh gasket between the outside face of the door and the wing skin to establish the electrical conductivity between the access door and the wing skin using the clamp ring and fasten ers torqued to that specified in Boeing AMM 28-11-11. Note: Not applicable to Surge T ank Access Doors with the NACA Vent Scoop a nd Pressure Relief Valve.

28-AWL-17 CDCCL N/A All Surge Tank Access Doors – Lightning Protection Bond Concern: Potential for arcing or sp arking inside the tank at the int erface between the door and the tank structure as a result of a direct stri ke or conducting currents through the wing skin. During surge tank access do or installation, perform th e following actions per Boeing AMM 28-11-11: Clean the countersinks on the door. If the Pressure Relief Va lve is removed and replaced, maintain the electrical fay surfac e bond between the pressure relief valve and the door 0.010 ohms (10 milliohms) or less per Boeing AMM 28-13-41. If the Flame Arrestor is removed and replaced, maintain the following electri cal bonds per Boein g AMM 28-13-31/401: Verify the electrical bond from the flame ar restor to the door assembly is 0.010 ohms (10 milliohms) or less. If the air vent scoop of the Type II flame arrestor is removed and replaced, maintain the following electrical bonds per Boeing AMM 28-13-31: Verify the electrical bond from the flame ar restor to the door assembly is 0.010 ohms (10 milliohms) or less. Install door using the same part number conductive fasteners and torque to that specified in the Boeing AMM. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-18 CDCCL N/A 737-100/200/200C airplanes that have incorporated Service Bulletin

737-28A1263 Fuel Boost Pump Wires in Cond uit Installation – In-Fuel Tank Concern: Potential for the boost pump wiring tochafe and arc in the co nduit and provide an ignition source in the fuel tank. The boost pump wires thatare in the conduits in the fuel tank s have incorporated a Teflon sleeve to protect from wire chafing per Service Bulleti n 737-28A1263 (FAA AD 2007-24-02). The wiring also has a jacket to provide chafing protection. Ensure the following condition exists wh en replacing pump wiring or wiring conduit: - Jacketed wiring and a Teflon sleeve. The Teflon sleeve is not repairab le. Whenever the wir ing in conduit or the conduit is removed, new Teflon sleeve must be installed.

28-AWL-19 CDCCL N/A All Resetting of Tripped Fuel PumpCircuit Breakers or Grou nd Fault Interrupters (GFIs) Concern: Potential for arcing or sparking ins ide the tank between fuel pumps and fuel pump housings and outside the tank be tween pump wiring and structure in flammable leakage zones. Verify it is safe to reset the circuit brea ker(s) or GFIs by fo llowing the applicable OEM troubleshooting procedures. Fault(s) that resulted in circuit breaker or GFI trip must be isolated and corrected prior to reset.

28-AWL-20 CDCCL N/A 737-200/200C airplanes that have incorporated Service Bulletin

737-28-1178 Fuel Quantity Indicating System (FQIS) – Isolated Fuel Quantity Transmitter (IFQT) Concern: The IFQT is des igned to limit the voltage, curren t, and power on the FQIS fuel tank wiring and components to intrinsically safe levels in order to preclude the potential of an ignition source within the fuel tank. IF QT installed per FAA AD 99-03-04. The IFQT is repairable only by Goodrich (89305) per their CMM 28-41-91.

28-AWL-21 ALI 1 YR 737-100/200 airplanes that have incorporated Service Bulletin

737-28A1228 Center Tank Fuel Boost Pump Automatic Shutoff System Concern: Dry running th e center tank fuel pumps has the potential for single failure ignition sources developing at the pump inlet du e to either frictio nal heating or sparking as a result of FOD contacting the pump rotating elements, rotati ng elements contacting stationary parts, or hot journal bearings due to bearing contam ination or failure. The automatic shutoff system is installed and designed to limit co ntinuous dry running condition to 15 seconds. The following test is requ ired in order to protect against latent faults: Functionally check the center tank fuel boost pump automatic shutoff system per AMM 28-22-0. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-31 28-AWL-22 ALI 1 YR 737-100/200 airplanes with Boeing certified Auxiliary fuel tanks that have incorporated Service Bulletin

737-28A1228 Auxiliary Tank Fuel Boost Pump Automatic Shutoff System Concern: Dry running the auxiliary tank fuel pumps has the pot ential for single failure ignition sources developing at the pump inlet du e to either friction al heating or sparking as a result of FOD contacting the pump rotating elements, rotati ng elements contacting stationary parts, or hot journal bearings due to bearing contam ination or failure. The automatic shutoff system is installed and desi gned to limit continuousdry running condition to 15 seconds. The following test is requ ired in order to protect against latent faults: Functionally check the auxiliary tank fuel boost pump automatic shutoff system per AMM 28-22-0.

28-AWL-23 ALI 1 YR 737-100/200 airplanes that have incorporated Service Bulletin

737-28A1212 Boost Pump Ground Fa ult Interrupter (GFI) Concern: Potential for pump housing burn-through, either internal or external to the fuel tank, as a result of major arcing due to electrical failure (i.e., damaged electrical connector, stator windings or leadwire to housing/end cap shorting). The GFI is designed to detect electrical faults an d open the circuit prior to pump housing burnthrough. The following maintenance check is required in order to ensure continue d functionality of the GFI circuit: Operational check the GFI of all AC fu el tank boost Pump s per AMM 28-22-41.

28-AWL-24 ALI 1 YR 737-100/200/200C airplanes that have incorporated Service Bulletin

737-28A1227 Center Tank Fuel Boost Pump Po wer Failed On Protection System Concern: Dry running th e center tank fuel pumps has the po tential for single failure ignition sources developing at the pump inlet du e to either friction al heating or sparking as a result of FOD contacting the pump rotating elements, rotating elements contacting stationary parts or hot journal bearings due to bearing contam ination or failure. The power failed on protection system is installed and designed in order to protect against a single failure (i.e. wiring faults or a welded fuel pump control relay) keep ing power on the pump when the associated fuel pump co ntrol switch is positioned to OFF. The following test is requ ired in order to protect against latent faults: Verify continued functionality of the center tank fuel boost pu mp Power Failed On Protection System per AMM 28-22-0. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-25 ALI 1 YR 737-200/200C airplanes with Auxiliary fuel tanks that have incorporated Service Bulletin

737-28A1227 Auxiliary Fuel Tank Boost Pump Power Failed On Protection System Concern: Dry running the au xiliary tank fuel pumps has the potential for single failure ignition sources developing at the pump inlet due to either frictio nal heating or sparking as a result of FOD contacting the pump rotating elements, rotati ng elements contacting stationary parts or hot journal bearings due tobearing contamina tion or failure. The power failed on protection system is installed and designed in order to protect against a single failure (i.e. wiring faults or a welded fuel pu mp control relay) keeping power on the pump when the associated fuel pump cont rol switch is positioned to OFF. The following test is requ ired in order to protect against latent faults: Verify continued functionality of the auxiliary tank fuel boost pump Power Failed On Protection System per AMM 28-22-0. 737-100, -200, -200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-33 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

28-AWL-01 ALI 10 YRS 737-300/400/500 airplanes that have incorporated Service Bulletin

737-28-1208 External Wires Over Center Fuel Tank Concern: Potential for Wire Chafing an d Arcing to Center Fu el Tank Upper Panel. Perform a detailed inspection of the wire bundles routed on ma in deck over the center fuel tank and under the main deck floor boards per AM M 28-11-00 to detect damaged clamps, wire chafing, damage to the vapor barr ier, and that the wire bundle is not in contact with surface of the center fuel tank. If discrep ancies are found, repair pe r the Boeing Standard Wiring Practices Manual, D6-54446. Interval Note: Threshold for initial inspection is 10 years after incorporation of Service Bulletin 737-28-1208.

28-AWL-02 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletin

737-28-1208 External Wires Over Center Fuel Tank Concern: Potential for Wire Chafing an d Arcing to Center Fu el Tank Upper Panel If any maintenance is performed in the area under the main deck floor boards and over the center fuel tank, verify the following: 1. Maintain the existing wire bundle routing and clamping. 2. Installation of any new wire bundles mu st be per Boeing Standard Wiring Practices Manual, D6-54446. 3. Perform a detailed inspection of the wire bundles routed on main deck over the center fuel tank and under the main deck floor boards in the areas of t he performed maintenance to detect damaged clamps, wire chafing, and that the wire bundle is not in contact with the surface of the center tank. If wirin g discrepancies are found, repair per the Boeing Standard Wiring Practices Manual, D6-54446.

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-03 ALI 10 YRS 737-300/400/500 airplanes that have incorporated Service Bulletins 737-28-1175 or 737-28-1183 or

737-28-1186 Fuel Quantity Indicating System (FQIS) – Out-Tank Wiring Li ghtning Shield to Ground Termination Concern: Potential fo r Lightning induced voltages on th e FQIS wiring to enter the fuel tank. Perform the following functional check to ensure the integrity of the FQIS wiring shield to ground termination: Verify the resistance of the shield to ground terminations atthe spar penetration in the unpressurized area by making the following measurements us ing a Loop Resistance Tester P/ N 906-10246-2 or 906-10246-3 per Boeing AMM 20-55-54. Restore the bonds per the Boeing AMM if required. The loop resistance shall not exceed 28 milliohms for Connector D884 (Left Main Tank). The loop resistance shall not exceed 28 milliohms for Connector D888 (Right Main Tank). The loop resistance shall not exceed 35 milliohms for Connector D886 (Center Main Tank).

28-AWL-04 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletins 737-28-1175 or 737-28-1183 or

737-28-1186 Fuel Quantity Indicating System (FQIS) – Out-Tank Wiring Lightning Shield to Ground Termination Concern: Potential fo r Lightning induced voltages on the FQIS wiring to enter the fuel tank. If the FQIS wire bundle or the shield on the FQIS wire bundle is repaired or replaced, verify the following: 1. Presence of shielded wiring 2. The shield ground is termina ted per the Boein g SWPM 20-10-15 3. The installation is inspected per 28-AWL-03.

28-AWL-05 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletins 737-28-1175 or 737-28-1183 or

737-28-1186 Fuel Quantity Indicating System (FQIS) – Out-Tank Wiring Installation Separation Requirement Concerns: Potential for ho t shorts and EMI induced voltages on the IFQT safe-side wire harness to enter the fuel tank. The FQIS wiring is defined as the harness between the Isolated Fuel Quantity Transmitter (IFQT) and the fuel tank. Routing and installation of any new wiring mustuse wire types BMS 13-48, BMS 13-60 or BMS 13-58, and not be within a 2-inch radius of the FQIS wiring. Under single failures of clamps or brackets, a separation greater than 1⁄2 inch must be maintained from FQIS wiring. This AWL is for design requirements. The installation is per SWPM 20-10-11. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-35 28-AWL-06 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletins 737-28-1175 or 737-28-1183 or

737-28-1186 Fuel Quantity Indicating System (FQIS) – Isol ated Fuel Quantity Transmitter (IFQT) Concern: The IFQT is designed tolimit the voltage, current, an d power on the FQIS fuel tank wiring and components to intrinsically safe lev els in order to preclud e the potential of an ignition source within th e fuel tank. IFQT installed per FAA AD 99-03-04. The IFQT is repairable only by Goodri ch (89305) per their CMM 28-41-91.

28-AWL-07 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Hardware (Tank Units and Compensators) Concern: Potential for maintenance error during repair of in-tank hardware (tank units and compensators). Arc gaps may develop that could result in an ignition source inside the fuel tank. The dielectric of thes e components must be mainta ined to protect from lightning voltages that could couple ontothe FQIS wiring between the IFQT and the tank if the wire shield ground is compromised. Repair and overhaul of FQIS tank units and compensators must be per the manufacturer Component Maintenance Manual (CMM) 28-40-25 Revision L, 28 -41-05 Revision Number 11, or 28-40-58 Revision Number 4 as applicable or later revisions of these CMMs that have been approved by the Seattle FAA ACO. The manufacturer's production procedures for this component may be used as an alternate to the identified CMM. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-08 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Repa ir or Replacement of In-Tank Wire Harness Concern: Potential for error duri ng repair or replacement of in-tank wire harness. Arc gaps may develop that could result in an ignition source inside the fuel tank . This CDCCL is also required for airplanes with IFQT in case the FQIS wiring between the IFQT and the fuel tank is compromised. Repair and overhaul of FQIS in-tank wire harness must be per Boeing SWPM 20-14-12. Installation of FQIS in-tankwire harness must be per Bo eing AMM 28-41-44. During installation of the harness, verify the following: For airplanes with rectangular bu ssing plug, tighten the mounting screws to a torque of 65 – 90 pound-inches. For airplanes with ci rcular bussing plug: - On the receptacle for the No. 1 or the No. 2 Ta nk, tighten the receptacle nut to a torque of 325 – 350 pound-inches. - On the receptacle for th e center tank, tighten the receptacle nut to a torque of 100 – 150 inch-pounds. A thin layer of sealant is presen t around the joint between the receptacle and the bulkhead on the inside of the tank. - Apply a continuous bead of sealant to the joint. - Make sure the bead fully seals the joint. Wire slack clearance between wires and stru cture must be greate r than 0.125 inches. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-37 28-AWL-09 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletin

737-29A1096 Lightning Protection – Hydraulic Line Fuel Tank Penetration Concern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting and the spar duri ng a lightning strike event. The following design features must be maintained per Boeing AMM 29-15-04. If the bulkhead fitting is removed and replaced: 1. Verify electrical fay surface bond from bulkhead fitting to stru cture outside the tank is 0.001 ohms (1 milliohm) or less, 2. Install fillet seal on the fitting to the tank wall interface outside the tank, 3. Install full bodied fillet seal encapsulating the fitting to the tank wall interface inside the tank,
4. Verify an electrostatic bonding jumper exists between the structure and the Hydraulic Heat Exchanger inside the tank, and 5. Verify electrical bond from structure to the Hydraulic Heat Exchanger inside the tank is 0.005 ohms (5 milliohms) or less if the bonding jumper was removed and replaced.

28-AWL-10 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletin

737-28A1174 Lightning Protection – Engine Fu el Feed Line Tank Penetration Concern: Potential for arcing or sparking inside the tank at th e interface between the bulkhead fitting and the spar during a lightning strike event. The following features must be maintained per Bo eing AMM 28-22-15 if the bulkhead fitting or attached tubing are re moved and replaced: 1. Verify electrical fay surface bond from bulkhead fitting to structure is 0.0005 ohms (0.5 milliohms) or less, 2. Install full-bodied fillet seal encapsulating the fitting to the tank wall interface inside and outside the tank, 3. Install full-bodied fillet seal encapsulating the tubes to fitting joints interface inside and outside the tank, 4. Verify an electrostatic bonding jumper exists be tween first tube mating wit h the bulkhead fitting and the mating tube inside the tank, and 5. Verify electrical bond from th e structure (wing front spar, in-tank) to first tube mating with the bulkhead fitting is 0.010 ohms (10 milliohms) or less. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-11 CDCCL N/A All Lightning, Fault Current or Hot Short Protection – Fuel Tank Penetrations Concern: Potential for arcing or sparking insi de the tank at a conductive metal-to-ground structure interface as a result of electrical fa ult currents or lightning strike events due to insufficient bonding within the ground electrical path. Any alteration, design change or re pair involving new penetrationsof the fuel tanks (such as a repair with fasteners, adding a bracket, bulkhead fitting or equipment) or change to the design features of the existing equipment penetratio ns (such as fuel measur ing sticks, sump drain valves, fueling manifold, fuel temperature sensor, and motor operated fu el shutoff valve adaptor plate) requiresapproval by the Seattle FAA ACO or an Authorized Representative (AR) of the Boeing Commercial Airplanes De legated Compliance Organization (BDCO). However, any alteration, design change or repair in volving new penetration s of the fuel tanks, accomplished in accordance with an FAA-approved Boeing Structural Repair Manual (SRM) or Boeing Service Bulletin is not subject to this requirement for additional approval.

28-AWL-12 CDCCL N/A All AC and DC Electrical Fuel Tank Pump Maintenance Concern: Potential for maintenance error during pump overhaul. Fuel pump designs contain ignition source prevention means (i.e., flame arrestor, thermal fuses, materials, leadwire retention means, etc.) that must bemaintained if pump is overhauled. Repair and overhaul of Fuel Pumps must be per the manufacturer’s Component Maintenance Manual (CMM) Numbers 28-20-37 Revision Number 10, 28-20-1 Revision Number 7, 28-20-5 Revision Number 6, 28-20-07 Revision Number 1, as applicable, or later revisions of these CMMs that have been approved by the Seattle FAA ACO. The manufacturer's production procedures for t his component may be us ed as an alternate to the identified CMM. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-39 28-AWL-13 CDCCL N/A All AC Fuel Pump Fault Current Fay Surface Bond Installation Concern: Potential for fault current path throu gh the pump housing to structure inside the tank. Electrical faults internal to the fu el pump motor impeller are by de sign routed through the motor impeller assembly to the bonding straps on the front face of th e motor impeller assembly to structure outside the tank. The fay surface bond ensures that fault currents are conducted to structure outside the tank until the circuit breaker and/or GFI has had time to remove power from the pump. The following features must be maintaine d during pump replacement per Boeing AMM 28-22-41: 1. Installation of the pump fault current faying surface bond. 2. Verify Motor Impeller bonding resistance to structure is 0.0002 ohms (0.2 milliohms) or less.

28-AWL-14 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletins 737-28A1141 or

737-28A1192 Fueling Float Switch System Installation Concern: Potential for wire chafing and arcing to conduit insidethe tank. The float switch assemblies in Fuel Tank 1 and 2 are not repairable to the initial manufactured standards. The center tank and Boeing auxiliary tank (if installed) Float Switch and Liner are not repairable to the initial manufactured standards (refer to Boeing AMM 28-21-71). During float switch replacement, a new float switch assembly must be used in Tanks 1 and 2, and a new float switch and liner system must be used for center and Boeing auxiliary fuel tank (if installed) as applicable.

28-AWL-15 CDCCL N/A All Center Fuel Tank Access Doors – Lightning Protection Bond Concern: Potential for arcing or sparking insidethe tank at the interface between the door and the tank structure as a result of a direct stri ke or conducting currents through the wing skin. The following features must be maintained during center fuel tank access door installation per Boeing AMM 28-11-31: Verify presence of a phenolic st rip positioned around the outermos t periphery of the door that mates with the wing skin inside the tank. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-16 CDCCL N/A All Main Fuel Tank Access Doors – Lightning Protection Bond Concern: Potential for arcing or sparking insid e the tank at the interface between the door and the tank structure as a result of a direct stri ke or conducting currents through the wing skin. The following features must be maintained during main (wing) fuel tank access door installation per Boeing AMM 28-11-11: 1. Apply anti-corrosion co mpound to both sides of the knitted aluminum mesh gasket, and install the greased aluminum mesh gasket between the clamp ring and the lower wing skin. Due to the countersink, the aluminum mesh will contact the access door and establish the electrical conductivity between the access door and the wing skin using the clamp ring and fasteners torqued to the value specified in Boeing AMM 28-11-11. Note: Not applicable to Surge Tank Access Doors with the NACA Vent Scoop and Pressure Relief Valve. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-41 28-AWL-17 CDCCL N/A All Surge Tank Access Doors – Lightning Protection Bond Concern: Potential for arcing or sparking insid e the tank at the interface between the door and the tank structure as a result of a direct stri ke or conducting currents through the wing skin. During surge tank access door installation , perform the following actions per Boeing AMM 28-11-11: Clean the countersinks on the access door. If the Pressure Relief Valve is removed and replac ed, maintain the electrical fay surface bond between the pressure relief valve and the door 0.010 ohms (10 milliohms) or less per Boeing AMM 28-13-41. If the Type I Flame Arrestor is removed and replaced, verify the electrical bond from the flame arrestor to the door assembly is 0.010 ohms (10 milliohms) or less per Boeing AMM 28-13-31. If the Air Vent Scoop of the Type II Flame Arrestor is removed and replaced, maintain the following electrical bonds per Boeing AMM 28-13-31: 1. Prepare the electrical fay surface from the up per surface of the door assembly to the lower surface of the air vent scoop. 2. Before the surface is sealed, verify the el ectrical surface bond from the door assembly to the air vent scoop is 0.0025 ohms (2.5 milliohms) or less. 3. After the surface is sealed, verify the elect rical bond from the air vent scoop to the door assembly is 0.010 ohms (10 milliohms) or less. Install the door using the same part number con ductive fasteners and torque to that specified in the Boeing AMM.

28-AWL-18 CDCCL N/A 737-300/400/500 airplanes that have incorporated Service Bulletin

737-28A1263 Fuel Boost Pump Wires In Conduit Installation – In Fuel Tank Concern: Potential for the boost pump wiring to chafe and arc in the conduitto provide an ignition source in the fuel tank. The boost pump wires that are in the conduits in the fuel tanks have incorporated a Teflon sleeve to protect from wire chafing per Boeing Service Bulletin 737- 28A1263 (FAA AD 2007-24- 02). The wiring also has a jacket to provide chafing protection. Ensure the following condition exists when replacing pu mp wiring or wiring conduit: - Jacketed wiring and a Teflon sleeve. The Teflon sleeve is not repairable. Whenever the wiring in cond uit or the conduit is removed, new Teflon sleeve must be installed. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

28-AWL-19 CDCCL N/A All Resetting of Tripped Fuel Pump Circuit Bre akers or Ground Fault Interrupters (GFIs) Concern: Potential for arcing or sparking ins ide the tank between fuel pumps and fuel pump housings and outside the tankbetween pump wiring and st ructure in flammable leakage
zones. Verify it is safe to reset the circuit breaker(s) or GFIs by following the applicable OEM troubleshooting procedures. Fault(s) that resulted in circuit breaker or GFI trip must be isolated and corrected prior to reset.

28-AWL-20 ALI 1 YR 737-300/400/500 airplanes that have incorporated Service Bulletin

737-28A1216 Center Tank Fuel Boost Pu mp Automatic Shutoff System Concern: Dry running the center tank fuel pu mps has the potential for single failure ignition sources developing at the pump inlet due to either frictional hea ting or sparking as a result of FOD contacting the pump rotating elements, rota ting elements contacting stationary parts, or hot journal bearings due to bear ing contamination or failure. The automatic shutoff system is installed and designed to limit co ntinuous dry running condition to 15 seconds. The following test is required in order to protect against latent faults: Functionally check the center tank fuel boost pump automatic shutoff system per AMM 28-22-00.

28-AWL-21 ALI 1 YR 737-300/400 airplanes with Boeing certified auxiliary fuel tanks installed, that have incorporated Service Bulletin

737-28A1216 Auxiliary Tank Fuel Boost Pump Automatic Shutoff System Concern: Dry running the auxiliary tank fuel pumps has the potential for single failure ignition sources developing at the pump in let due to either frictional heati ng or sparking as a result of FOD contacting the pump rotating el ements, rotating elements contacting stationary parts, or hot journal bearings due to be aring contamination or failure. The automatic shutoff system is installed and designed to limit co ntinuous dry running condition to 15 seconds. The following test is required in orde r to protect against latent faults: Functionally check the auxiliary tank fuel boost pump automatic shutoff system per AMM 28-22-00. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAY 2009

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-43 28-AWL-22 ALI 1 YR 737-300/400/500 airplanes that have incorporated Service Bulletin

737-28A1212 Boost Pump Ground Fa ult Interrupter (GFI) Concern: Potential for pump housing burn-through, either internal or external to the fuel tank, as a result of major arcing due to electrical fa ilure (i.e., damaged electr ical connector, stator windings or leadwire to housing/end cap shorting). The GFI is designed to dete ct electrical faults and open the ci rcuit prior to pump housing burnthrough. The following maintenance check is requ ired in order to ensure co ntinued function ality of the GFI circuit: Operational check the GFI of all AC Fuel Tank Boost Pumps per AMM 28-22-41.

28-AWL-23 ALI 1 YR 737-300/400/500 airplanes that have incorporated Service Bulletin

737-28A1227 Center Tank Fuel Boost Pump Power Failed On Protection System Concern: Dry running the center tank fuel pumps has the potential for single failure ignition sources developing at the pump inle t due to either frictional heatin g or sparking as a result of FOD contacting the pump rotating elements, rotating elements contacting stationary parts or hot journal bearings due to be aring contamination or failure. The power failed on protection system is insta lled and designed in order to protect against a single failure (i.e. wiring faults or a welded fuel pump control relay) keep ing power on the pump when the associated fuel pump cont rol switch is po sitioned to OFF. The following test is required in orde r to protect against latent faults: Verify continued functionality of the center tank fuel boost pump Power Failed On Protection System per AMM 28-22-00.

28-AWL-24 ALI 1 YR 737-300/400/500 airplanes with Auxiliary fuel tanks that have incorporated Service Bulletin

737-28A1227 Auxiliary Fuel Tank Boost Pump Power Failed On Protection System Concern: Dry running the auxiliary tank fuel pumps has the potential for single failure ignition sources developing at the pump inle t due to either frictional heati ng or sparking as a result of FOD contacting the pump rotating elements, rota ting elements contacting stationary parts or hot journal bearings due to be aring contamination or failure. The power failed on protection system is insta lled and designed in orde r to protect against a single failure (i.e. wiring faults or a welded fuel pump control relay) keep ing power on the pump when the associated fuel pump cont rol switch is po sitioned to OFF. The following test is required in order to protect against latent faults: Verify continued functionality of the auxiliary tank fuel boost pump Power Failed On Protection System per AMM 28-22-00. 737-300, -400, -500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEMS
The following list of AWLs (ALIs and CDCCLs) contains FAA approved scheduled inspections and design limitations for operatorsto incorporate into their maintenance program for this type design to meet the requirements for the introduction of Flammability Reduction Means (FRM) Nitrogen Generation System (NGS). The FAA Final Flammability Rule, E8-16084, requires maintenance instructions and control limitations for certain NGS critical design configu rations. 

### § 25.981 also requires AWLs to preclude ignition sources inside the fuel tank that may be introduced by the addition of NGS.
E8-16084, Final Flammability Rule, Paragraph III(F), Section 7, Identification of Airworthiness Limitations: Paragraph M25.4(a) requires that if FRM is used to comply with Paragraph M25.1, airworthiness limitations must be identified for all ma intenance or inspecti on tasks required t o identify failures of components within the FRM that are needed to meet Paragraph M25.1. NGS AW Ls are mandatory maintenance actions that ensure that unsafe conditions that arise due to NGS failures donot occur or are not introduced into the airplane as a result of configuration changes, repai rs, alterations, or deficiencies in the NGS maintenance program throughout the operational life of the airplane.

AUG 2010

## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-45 AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEM TASKS

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

47-AWL-01 CDCCL N/A Airplanes that have incorporated

Service Bulletin 737-47-1004 or

737-47-1007 Lightning Protection – NGS Nitrogen Enriched Air (NEA) Distribution Line Fuel Tank Penetration Concern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting and the spar during a lightning strike event. The following must be maintained if the bulkhead fi tting is removed and re placed or re-installed (refer to Boeing AMM 47-21-07): 1. Install the same part number bulkhead fitting. 2. Verify electrical fay surface bond from the bulk head fitting to the rear spar structure inside the tank is 0.0005 ohms (0.5 milliohms) or less. 3. Install fillet seal on both the inside and outside surfaces of the rear spar around the perimeter of the bulkhead fitting and jam nut. NOTE: The bulkhead fitting is a special part whic h has an integral flame a rrestor. Any change to this part requires approval by the Seattle FAA ACO.

47-AWL-02 CDCCL N/A Airplanes that have incorporated

Service Bulletin 737-47-1004 or

737-47-1007 Lightning Protection – NGS NEA Distr ibution Line Fuel Tank Penetration Concern: Potential for arcing, sparking or filament heating inside the tank at the interface between the dielectric isolator hose and the NEA tubing during a lightning strike event. The NGS installation is designed to prevent lightning currents from entering the center wing fuel tank by adding a dielectric isolator hose in the wheel well at the rear spar bulkhead fitting in the NEA distribution line. The isolator hose must be maintained if the dielectric isolator hose or attached tubing are removed and replaced or reinstalled (refer to Boeing AMM 47-21-00 and AMM 47-21-07).

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

47-AWL-03 CDCCL N/A Airplanes that have incorporated

Service Bulletin 737-47-1005 or

737-47-1008 Nitrogen Generation System (NGS) – Flam mability Exposure and Performance Concern: Airplane alterations may impact the performance of the NGS and hence the flammability of the Center Wing Fuel Tank. Background: The NGS is designed toprovide the proper level of nit rogen to the center wing tank in order to reduce the flammability exposure by reducing the oxygen content of the ullage. The flammability exposure is also affected by the temperature of the fuel. The following are critical features of the airplane that, if altered, can negatively affect t he performance of the NGS which in turn may increase the center fuel tank flammability exposure beyond the limits of 14 Code of Federal Regulations, Section 25.981 at Amendment 25-125, utilizing the equivalent level of safety finding described in FAA Memorandum PS05-0177-P-2. 1. Transferring air (20.9% oxygen) to the center fuel tank will dilute the nitrogen rich atmosphere created by the NGS in the fuel tank. Some Auxiliary Fuel Tank installations transfer air to the center wing tank as part of venting and fuel transfer. 2. NGS performance depends on bleed air pressure in the bleed air cross-over manifold supplied by the engines. 3. Certification of the NGS depends on the inherent flammability of the center fuel tank without NGS installed. Center tank flammability is a direct function of fuel tank temperature. Any heat sources around the tank, heat sources introduced into the tank (such as warm fuel or new heat exchangers), or changes that would cause heat to be retained (such installation of blankets adjac ent to tank walls) could affect fuel tank flammability in a negative manner. CDCCL: Any design change that affects the vent system by adding air to the center tank, reduces the bleed pressure in the cross-over manifold during any phase of flight or ground operations, or adds any heat to the center wing fuel tank or increases heat retent ion of the center wing fuel tank is not allowed without an FAA approved analysis to show that the change , or combination of changes, does not affect the NGS performance per the requirements of 14 CFR Section 25.981(b), Amendment 25-125 utilizing the equivalent level of safety finding described in FAA Memorandum PS05-0177-P-2 See Boeing AMM Chapter 28 for a description of the Fuel System. See Boeing AMM Chapter 47 for a description of the NGS. AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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## 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENANCE REQUIREMENTS

D6-38278-CMR BOEING PROPRIETARY - Copyright (c) - Unpublished Wo rk - See title page for details Page 9.0-47 47-AWL-04 ALI 22,500 FH Airplanes that have incorporated

Service Bulletin 737-47-1005 or

737-47-1008 Nitrogen Generation System – Thermal Swit ch Functional and Operational Check Concern: Latent Failure of the Thermal Switch removes a layer of protection against fuel tank ignition by hot bleed air. The NGS uses engine bleed air from the engine bleed system cross -over manifold to generate nitrogen to reduce the flammability of the center fuel tank. The NGS has features to prevent directly feeding hot bleed air into the fuel tank . The Thermal Switch provides a redundant backup to the NGS controller to protect the Air Separa tion Module (ASM) and prev ent hot bleed air from entering the fuel tank. The Therma l Switch backup feature is a latent (not detected) failure and must be tested to maintain certification of the NGS. Perform a functional and operational check of th e Thermal Switch to en sure integrity of the Thermal Switch (refer to Boeing AMM 47-43-02).

47-AWL-05 ALI 14,500 FH Airplanes that have incorporated

Service Bulletin 737-47-1005 or

737-47-1008 Nitrogen Generation System – NEA Distribution Ducting Inspection Concern: The NEA Distribution Syst em ducting outside the fuel ta nk may fail latently allowing NEA to leak without reaching th e fuel tank, resulting in the fuel tanknot reaching required inert levels. Inspect the NEA distribution lines from the ASM to the fuel tank rear spar for damage and leaks (refer to Boeing AMM ATA 47-21-00).

47-AWL-06 CDCCL N/A Airplanes that have incorporated

Service Bulletin 737-47-1005 or

737-47-1008 Industry Fleet Average Flammability Exposure Concern: NGS performance is dep endent on industry descent times. Industry efforts to reduce descent time may result in NGS performanc e that does not meet FAA requirements. Fleet Average flammability exposure for the fuel tanks with flammability reduction of this airplane type must be maintained in accordance with 14 CFR Part 25, Appendix M. Boeing will monitor U.S. descent statistics and, if necessary to maintain compliance, will publish service information. If Boeing publishes such service information, this CDCCL requires either that operators implement these FAA-approved design changes or that operators implement ot her design changes or operational procedural changes approved by th e Seattle FAA ACO to maintain compliance with 14 CFR Part 25, Appendix M. NOTE: This CDCCL does not require individual operators to monitor descent rates of their fleets. Boeing will monitor U.S. descent statistics and provide any needed service instructions to operators. To prevent increasing flammability exposure above permissible levels, this CDCCL requires operators to in corporate future Boeing pu blished service instructions denoted to maintain compliance with this CDCCL, or other approved actions, within the compliance times stated in the service instructions. AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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