737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-100/200/200C/300/400/500

AIRWORTHINESS LIMITATIONS (AWLs) A

 CERTIFICATION MAINTENANCE REQUIREMENT

D6-38278-CMR

JUNE 2014

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matte

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 docu

information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Wa

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, MD-10

MD-88, MD-90, and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document 

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 export license may 

used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to a

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

THIS PAGE INTENTIONALLY LEFT BLANK

BLANK
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

TABLE OF CONTENTS

REVISIONS .......................................................................................................................................................................................LIST OF EFFECTIVE PAGES ...........................................................................................................................................................A. SCOPE..........................................................................................................................................................................................B. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS) ....................................................................................................

C. AIRWORTHINESS LIMITATIONS – SYSTEMS............................................................................................................................

C.1 FUEL SYSTEMS IGNITION PREVENTION ...........................................................................................................................C.2 NITROGEN GENERATION SYSTEM (NGS)..........................................................................................................................C.3 IMPACT-RESISTANT FUEL TANK ACCESS DOORS ...........................................................................................................

D. LIMIT OF VALIDITY (LOV)............................................................................................................................................................

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

THIS PAGE INTENTIONALLY LEFT BLANK

BLANK
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

REVISIONS

REVISION AND REVISION DESCRIPTION 

FEBRUARY 2003Original Release - Added CMR 27-CMR-01 applicable to airplanes accomplishing Service Bulletin 737-27-1252 (737-100/200/200C) and 737-27-1255 (737-300/400/500).

Submitted by: S. Pierini (Boeing) Approv

(Seattle 

NOVEMBER 2004Added CMR 52-CMR-01 to perform a functional check of the flight deck door locking and unlocking latch bolt mechanism on the decompression panel. Deleted “RELATED MRBR ITEM NUMBER” column as it is no longer necessary.

Submitted by: G.Palafox(Boeing) Approv

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

Submitted by: Approv

MAY 2006Revised 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: Approv

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

SEPTEMBER 2006Added a functional check of the center tank 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 with Boeing certified auxiliary fuel tanks installed, that have incorporated Service Bulletin 737-28A1216.

Added a functional check of the center tank Fuel Boost Pump Auto Shutoff System Number 28-AWL-21. Applicable to 737100/-200 airplanes that have 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-14 to indicate that a float assembly must be used.

Submitted by: Approv

REVISION AND REVISION DESCRIPTION 

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

NOVEMBER 2007Revised 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 Format: 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 that have incorporated Service 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 that have incorporated Service Bulletin 737-28A1212.

Submitted by: E. B. Lange (Boeing)

Approv

MARCH 2008Revised 28-AWL-01 to remove 36000FH task interval limitation based upon engineering review and operator maintenance practice and removed body station and buttock line text and replaced with "per AMM 28-11-00".Revised 28-AWL-03 to reflect the new maximum loop resistance values associated with the lightning protection of the unpressurized FQIS wire bundle installations so as to satisfy the Airworthiness Limitation Instructions required by SFAR 88. Also removed the joint resistance values and 36000FH task interval limitation based 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 superseded SB 737-28A1263 and AD 2007-24-02. Also remove the following text "or an additional Teflon sleeve" and "Non jacketed wiring and double sleeves".

Submitted by: John Sabolchy (Boeing)

Approv

REVISION AND REVISION DESCRIPTION 

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

MAY 2009Added Section D. front matter for the Airworthiness 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 consistent 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 description to clarify inspection requirements and location.Revised the task description of 28-AWL-03 (737-12345) by removing the statement "at side of body, and" to reflect the original intent of the task requirement.Revised 28-AWL-04 (12345) by rewording text to clarify task description requirements.Revised the Task Description for 28-AWL-05 to clarify the intent of the requirement and to provide the SWPM reference for installation requirements.Revised the Task Description for 28-AWL-06 (for 737-345) to clarify the party responsible for repairing 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 the manufacture's production 

procedures. Revised 28-AWL-11 (737-12345) with updated Fuel 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 CMM 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 boost 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 yearly check to verify the continued functionality of the auxiliary tank fuel boost pump Power Failed On Protection System.

Submitted by: John Sabolchy (Boeing)

Approv 

REVISION AND REVISION DESCRIPTION 

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

AUGUST 2010Revised Paragraph D. Airworthiness Limitations – 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 incorporated Service Bulletin 737-47-1004 or 737-47-1007.Revised 47-AWL-01 by updating the Task Description 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 the isolator hose and to replace "per" with "refer to".Revised 47-AWL-03, 47-AWL-04, and 47-AWL-05 by updating the Applicability column to read "Airplanes that have incorporated Service Bulletin 737-47-1005 or 737-47-1008.Revised 47-AWL-04 by replacing "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 the maintenance standard for the Nitrogen Generation System and notice of potential future compliance requirements associated with decreased aircraft descent rates.

Submitted by: John Sabolchy (Boeing)

Approv 

JULY 2011Revised 47-AWL-03 to incorporate NGS performance features to show compliance with 14 CFR 26.33.

Submitted by: Mark Arnold (Boeing)

Approv  

REVISION AND REVISION DESCRIPTION 

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

JULY 2012Added a new Section E. Limit of Validity (LOV) as required by Title 14 Code of Federal Regulations (CFR) Section 26.21 (Amendment 26-6).

Submitted by: Sheila Reilley (Boeing)

Approv 

AUGUST 2012Added heading for Section C.1, AWLs – Fuel System Ignition Prevention.Revised existing Section D title to make it a subheading of Section C to be consistent with other CMR documents.Added Section C.3, Impact-Resistant Fuel Tank Access Doors and 57-AWL-01 for the 737-100/200/200C and 57-AWL-01 for the 737-300 to verify the fuel tank access door is impact-resistant during installation of the fuel tank access doors.Revised Section E title, making it Section D, to be sequential in order following previous heading revisions.

Submitted by: Cassie Ho (Boeing)

JUNE 2014Revised Section A Scope to define FAA Oversight Office and replaced all references of "Seattle FAA ACO" with "FAA Oversight Office" throughout the entire document. Added information that the Airworthiness Limitations are approved by the FAA and required under the Title 14 CFR § 43.16 and § 91.403. Added new subparagraph "Airworthiness Limitations" to clarify that the Airworthiness Limitations can only be revised with the approval of the FAA Oversight Office.References to FAA regulations were changed to include "Title 14 CFR §" to accurately reflect FAA regulation citations throughout the document and for consistency.Revised Section C front matter with the following:Moved the first 2 paragraph under "Introduction" to the front matter for the Section C, "Fuel Systems Ignition Prevention".Added the information on FAA approved Airworthiness Limitations required under Title 14 CFR § 43.16 and § 91.403 to the "Introduction " subparagraph.

(Continued on next page)

Submitted by: Cassie Ho (Boeing)

REVISION AND REVISION DESCRIPTION 

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

JUNE 2014, ContinuedAdded reference to the SFAR 88 and Title 14 CFR 25.981 to the CDCCL paragraph under "Introduction" to specify that the CDCCL is required by these regulations. Also, clarified the word "maintenance" to include alterations.Deleted references to fuel tank ignition source prevention in the ALI paragraph under "Introduction" since the front matter is applicable to all systems inspection tasks under Section C.Moved the "Regulatory Agency Approval" to the after the "Introduction" subparagraph. Provides clarification that the operator not under the FAA jurisdiction should get the deviations from the AWL instructions from their local regulatory authority.Added "Accomplishment Instructions - General Information" to clarify the use of "in accordance with" and "refer to" verbiage when referencing other Instructions for Continued Airworthiness documents. Added reference to SWPM 20-20 for electrical bonding and grounding requirements.Revised "USE OF ALTERNATE TOOLS" to "USE OF ALTERNATE TOOLS OR EQUIVALENT TOOLS, TEST EQUIPMENT OR MATERIALS". Added clarification that the use of alternate or equivalent tools, test equipment, or materials that is outlined in the AWL and when CMM is cited as "in accordance with" and not "refer to" requires FAA Oversight Office approval.Revised the Exceptional Short-Term Extensions subparagraph, changing "fuel system AWL" to "system AWL" to apply the front matter to all AWLs under Section C. Revised "(e.g., a Principal Maintenance Inspector)" to "or a Principal Maintenance Inspector" and the Flight Standards Handbook reference from "8900.1" to "8900.1 FSIMS".Added new subparagraphs to Section C: "Definitions", to provide further clarification on accomplishment instructions, and "Supporting Documentation", to clarify that strict adherence to the methods, techniques and practices, as prescribed, is required to ensure the ALI or CDCCL is complied with.Revised Section C to replace the word "per" with "in accordance with" throughout the entire section.Revised the title for C.1 to remove "AWLs" from the title for consistency.

(Continued on next page)

Continued from previous page Co

REVISION AND REVISION DESCRIPTION 

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

JUNE 2014, ContinuedRevised 28-AWL-18 for the 737-100/200/200C applicability to clarify that the AWL is 

applicable to 737-100/200/200C that have incorporated Service Bulletin 737-28A1263 but have not incorporated Service Bulletin 737-28A1273.Added 28-AWL-26 for the 737-100/200/200C to require the installation of the conduit liner and jacketed or shielded wiring when the pump wiring or wiring in the conduit is removed or replaced.Revised 28-AWL-18 for the 737-300/400/500 applicability to clarify that the AWL is 

applicable to 737-300/400/500 that have incorporated Service Bulletin 737-28A1263 but have not incorporated Service Bulletin 737-28A1273.Added 28-AWL-25 for the 737-300/400/500 to require the installation of the conduit liner and jacketed or shielded wiring when the pump wiring or wiring in the conduit is removed or replaced.Revised AWL 57-AWL-01 for both the 737-100/200/200C and 737-300 to add a reference to the Boeing AMM 28-11-11.

Continued from previous page Co

REVISION AND REVISION DESCRIPTION 

JUN 2014
Section Page Date Section Page Date Section Page Date Section Page Date 

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

LIST OF EFFECTIVE PAGES

 737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

1.0 1 JUN 20141.0 2 BLANK1.0 3 JUN 20141.0 4 BLANK1.0 5 JUN 20141.0 6 JUN 20141.0 7 JUN 20141.0 8 JUN 20141.0 9 JUN 20141.0 10 JUN 20141.0 11 JUN 20141.0 12 JUN 20141.0 13 JUN 20141.0 14 JUN 20141.0 15 JUN 20141.0 16 JUN 20141.0 17 JUN 20141.0 18 JUN 20141.0 19 JUN 20141.0 20 NOV 20071.0 21 JUN 20141.0 22 JUN 20141.0 23 JUN 20141.0 24 JUN 20141.0 25 MAY 20091.0 26 JUN 20141.0 27 JUN 20141.0 28 JUN 20141.0 29 JUN 20141.0 30 JUN 20141.0 31 JUN 20141.0 32 JUN 20141.0 33 JUN 20141.0 34 JUN 20141.0 35 JUN 20141.0 36 JUN 20141.0 37 JUN 20141.0 38 JUN 20141.0 39 JUN 2014

1.0 40 JUN 20141.0 41 JUN 20141.0 42 JUN 20141.0 43 JUN 20141.0 44 JUN 20141.0 45 JUN 20141.0 46 JUN 20141.0 47 JUN 20141.0 48 JUN 20141.0 49 JUN 20141.0 50 JUN 20141.0 51 JUN 20141.0 52 JUN 20141.0 53 JUN 20141.0 54 JUN 20141.0 55 AUG 20121.0 56 JUN 20141.0 57 JUN 20141.0 58 AUG 2012

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

A. SCOPE

The scheduled maintenance requirements described in this section result from airplane certification activities with the U.S. Fed

(FAA). Accordingly, this FAA approved Airworthiness Limitations (AWL) and Certification Maintenance Requirements (CMR) d

referenced in the Model 737-100/200/200C/300/400/500 Type Certificate Data Sheet. This document satisfies the requirement

Federal Regulations (CFR) § 25.571, § 25.1529 and Advisory Circular (AC) 25-19 as the controlling document for all 737-100/2CMRs. These maintenance actions are mandatory.These Airworthiness Limitations sections are FAA approved and specifies maintenance required under Title 14 CFR § 43.16 an

alternative program has been FAA Oversight Office approved.Where used in this document, the term “FAA Oversight Office” is defined as the FAA office that currently has oversight responsof the Boeing model 737-100/200/200C/300/400/500. At the time of publication, the FAA office with oversight responsibility for t

737-100/200/200C/300/400/500 is the FAA Boeing Aviation Safety Oversight Office (BASOO).

AIRWORTHINESS LIMITATIONSThe Airworthiness Limitations may only be revised with the approval of the FAA Oversight Office.If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection approved by the FAA Ov

be used.

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

B. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

CMR DEFINITIONAs defined by AC 25-19, a CMR is a required periodic task, established during the design certification of the airplane as an ope

certificate. CMRs usually result from a formal, numerical analysis conducted to show compliance with catastrophic and hazardAdditional notes concerning the definition of CMRs:1. A CMR is intended to detect safety-significant latent (hidden) failures that would, in combination with one or more specific f

hazardous or catastrophic failure condition.

2. It is important to note that CMRs are derived from a fundamentally different analysis process than the maintenance tasks a

the Maintenance Steering Group (MSG-3) Analysis associated with Maintenance Review Board (MRB) activities. MSG-3 A

maintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance before failure occurs (and are intended to prevent failures), as well as failure-finding tasks. CMRs, on the other hand, are ty

and exist solely to limit the exposure to otherwise hidden failures. Nevertheless, use of potential failure-finding tasks, such inspections, may also be appropriate.

3. CMRs are designed to verify that a certain failure has or has not occurred, and do not provide any preventative maintenanc

the failure clock to zero” for latent failures by verifying that the item has not failed, or caused repair if it has failed. Because t

failure is a key element in the calculations used in a safety analysis performed to show compliance with Title 14 CFR § 25.

time will have a significant effect on the resultant overall failure probability of the system. The CMR Task Interval should be 

hours, cycles, or calendar time, as appropriate.

4. The type certification process assumes that the airplane will be maintained in a condition of airworthiness with respect to its 

condition. The process described in AC 25-19 is not intended to establish normal maintenance tasks that should be define

Analysis process. Neither is this process intended to establish CMRs for the purpose of providing supplemental margins of late in the type design approval process.

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

5. CMRs should not be confused with required structural inspection programs and are to be developed by the type certificate 

inspection requirements for damage tolerance, as required by Title 14 CFR § 25.571 or § 25.1529, Appendix H25.4 (AirwortCMRs are to be developed and administered separately from any structural inspection programs.

CMR TYPESCMR Tasks are divided into two categories: 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 withou

FAA Oversight Office.

2. Two Star CMRs (**) – Task intervals may be adjusted in accordance with each operator’s approved escalation program or a

program in a like manner for any MRB Report task, but may not be deleted without prior FAA Oversight Office approval.

ESCALATION OF TWO STAR CMRs (**)All Two Star CMRs (**) can be managed and controlled the same as any MRB Report task; however, they can not be deleted f

without prior FAA Oversight Office approval. For operators with approved escalation practices or an approved reliability progra

analytical techniques are used to make adjustments to an operator’s maintenance program. It has been demonstrated that the maintenance program does not give rise to undue escalations; consequently, the escalation of Two Star CMR (**) intervals withmaintenance program will be properly managed by the operator subject to local regulatory authority approval.

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

EXCEPTIONAL SHORT-TERM EXTENSIONSSince CMR intervals are based on statistical averages and reliability rates, an exceptional short-term extension of 10% for each document may be made without jeopardizing safety. The local regulatory authority or a Principle Maintenance Inspector must cshort-term extensions before they take place using procedures established with the local regulatory authority in the operators’ mshort-term extension” process is applicable to CMR intervals. It should not be confused with the operator’s “short-term escalati

maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8900.1 FSIMS.The FAA Oversight Office has accepted that these exceptional short-term extensions may be granted without consultation with 1. The term “exceptional short-term extension” is defined as an increase in a CMR interval that may be needed to cover an un

situation. All CMRs listed in this document have been approved with an exceptional short-term extension of 10%.

2. Repeated use of extensions, either on the same airplane or on similar airplanes in an operator’s fleet, should not be used a

management practices. Exceptional short-term extensions must not be used for fleet CMR escalation.

3. After a CMR has experienced an exceptional short-term extension, the CMR interval will revert back to its interval listed in t

Oversight Office must approve, prior to its use, any desired extension not explicitly listed above.

NOTE: This exceptional short-term extension listed above applies to airlines that fall under the U.S. FAA jurisdiction only. O

U.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

POST-CERTIFICATION CHANGES TO CMRsAny post certification changes to CMRs should be reviewed by the 737-100/200/200C/300/400/500 Certification Maintenance C

(CMCC) and approved by the FAA Oversight Office:1. Since the purpose of a CMR is to limit the exposure time to a given significant latent failure as part of an engineering analysis 

instances of a CMR task repeatedly finding that no failure has occurred may not be sufficient justification for deleting the tabetween repetitive performances of the CMR task. In general, * CMRs are not good candidates for escalation under an op

A * CMR task change or interval escalation can only be made if world fleet service experience indicates that certain assumfailure rates made early during the engineering analysis were overly conservative, and a re-calculation of system reliability 

certain components reveals that the * CMR task or interval may be changed.

2. The introduction of a new CMR or any change to an existing CMR should be reviewed by the same process used during in

important that operators be afforded the same opportunity to participate that they received during the original certification o

allow the operators to manage their own maintenance programs.

3. In the event that later data provides sufficient basis for relaxation of a CMR (less restrictive actions to be performed), the cha

an FAA Oversight Office approved change 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 

CMR document and enforced by an FAA Airworthiness Directive (AD).

5. After initial aircraft certification, the only basis for adding a new CMR is in association with the certification of design change

6. A new CMR created as part of a design change should be part of the approved data for that change and added to this CMR 

In the event that a CMR is revised, Boeing will document it by preparing a revision to this document that will be approved by the 

This revision will then be forwarded to all 737-100/200/200C/300/400/500 operators and the FAA Oversight Office.

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

PAGE FORMAT: SYSTEMS MAINTENANCE PROGRAM

COLUMN EXPLANATIONCMR ITEM NUMBER

Each task is given a unique CMR Item Number. The first and second digits are the ATA Chapter Num

TYPE CMR TYPE:

CMRs are categorized into one or two star CMRs based on whether or not they can be escalated by th

prior FAA Oversight Office approval.* Cannot be escalated or deleted without prior FAA Oversight Office approval.** Can be escalated based on the operator’s approved program for continued airworthiness based on  analysis and surveillance; however, these tasks cannot be deleted without prior FAA Oversight Offi

TASK TASK TYPES/CATEGORIES:

LU = LubricationSV = ServicingOP = Operational CheckVC = Visual CheckGV = General Visual Inspection

DI = Detailed InspectionFC = Functional CheckRS = RestorationDS = Discard

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

Applicable Airplane Model and Engine.

TASK DESCRIPTION

Description of the task to be performed.

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

CERTIFICATION MAINTENANCE REQUIREMENTS TASKS

CMR ITEM 

NUMBER TYPE TASK

CMR 

INTERVAL

APPLICABILITY

APL ENG TASK DESCRIPTIO

27-CMR-01 * FC 10000 HRS NOTE ALL Functionally check rudder main PCU Internal leaka

Applicability Note: Airplanes that have incorporateon the 737-100/200/200C or 737-27-1255 on the 7

52-CMR-01 * FC 3,000 FH NOTE ALL Perform a functional check of the locking and unlo

the flight deck door decompression panel.Applicability Note: Applicable to airplanes with the Door installed by the customer specific Boeing Ser

NOV 2007
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

C. AIRWORTHINESS LIMITATIONS – SYSTEMS

INTRODUCTIONThe airplane systems maintenance requirements described in this AWL document result from various 737-100/200/200C/300/4

activities with the FAA. This Airworthiness Limitations section is FAA-approved and specifies maintenance required under Title § 91.403 of the Federal Aviation Regulations, unless an alternative program has been FAA Oversight Office approved. The AWthe approval of the FAA Oversight Office. If the maintenance requirements cannot be accomplished due to repairs and/or modi

inspection, acceptable to the FAA Oversight Office, must be used.An AWL may be an Airworthiness Limitation Instruction (ALI) or a Critical Design Configuration Control Limitation (CDCCL).

CDCCLs are a means of identifying certain design configuration features intended to preclude a fuel tank ignition source for the 

airplane as required under Special Federal Aviation Regulation No. 88 (SFAR 88) - Fuel Tank System Fault Tolerance Evaluat

14 CFR § 25.981 - Fuel Tank Ignition Prevention. CDCCLs are mandatory and cannot be changed or deleted without the appro

Office. A critical fuel tank ignition source prevention feature may exist in the fuel system and its related installation or in system

were to develop, could interact with the fuel system in such a way that an unsafe condition would develop without this limitationconfiguration, methods, techniques, and practices as prescribed is required to ensure compliance with the CDCCL. Any use of or practices not contained in the applicable CDCCL must be approved by the FAA Oversight Office. For each CDCCL, the wor

maintaining any installation during alterations; therefore, adherence to the CDCCL is required during maintenance or alteration

ALIs identify inspection tasks that which must be done to maintain the design level of safety for the operational life of the airpla

condition. These ALIs are mandatory and cannot be changed or deleted without the approval of the FAA Oversight Office. Stric

techniques and practices as prescribed is required to ensure the ALI is complied with. Any use of methods, techniques or practALIs must be approved by the FAA Oversight Office.

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

REGULATORY AGENCY APPROVALAny deviations from the published AWLs instructions included in this document require approval from the FAA Oversight Officeunder the U.S. FAA jurisdiction only and to airplanes registered in the US. Operators who are not under the U.S. FAA jurisdictiform their own local regulatory agency for any deviations from the listed AWL instructions. AWL REVISION PROCESSIn the event that an AWL is revised, Boeing will prepare a revision to this document that will be approved by the FAA Oversight 

then be forwarded to all 737-100/200/200C/300/400/500 operators and the FAA Oversight Office.ACCOMPLISHMENT INSTRUCTIONS – GENERAL INFORMATIONThe listed AWLs may make reference to Instructions for Continued Airworthiness which are included in other Boeing document• When a document is cited using the words "in accordance with" in an airworthiness limitation, the cited document (or 

followed to ensure that the critical design feature is maintained. Any deviation from the cited document requires FAA Overs

• When a document is cited using the words "refer to" in an airworthiness limitation, the cited document (or document sectio

complying with the airworthiness limitation. An alternative procedure may be developed by an operator in accordanc

maintenance program/manual.

For electrical bonding and grounding requirements, refer to the Boeing Standard Wiring Practices Manual (SWPM) 20-20.

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

USE OF ALTERNATE ALTERNATE OR EQUIVALENT TOOLS, TEST EQUIPMENT OR MATERIALSFor AWLs which require use of certain tools, test equipment or material, the use of alternate or equivalent tools, test equipment approval from the FAA Oversight Office.The Component Maintenance Manuals (CMMs) listed in the AWLs as "in accordance with" and not "refer to" are currently FAA 

If the CMM allows the use of alternate or equivalent tools, test equipment or materials, use of an alternate or equivalent tool, tedoes not require further approval by the FAA Oversight Office.EXCEPTIONAL SHORT-TERM EXTENSIONSSince AWL intervals are based on estimations of the probability of an event, an exceptional short-term extension for each systedocument may be made without jeopardizing safety. The local regulatory authority or a Principle Maintenance Inspector must cshort-term extensions before they take place using procedures established with the local regulatory authority in the operators’ m

short-term extension” process is applicable to AWL intervals. It should not be confused with the operator’s “short-term escalatimaintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8900.1 FSIMS.The FAA Oversight Office has accepted that these exceptional short-term extensions may be granted without consultation with 1. The term “exceptional short-term extension” is defined as an increase in a system AWL interval that may be needed to cove

pected situation. All AWLs listed in this section have been approved with an exceptional short-term extension of 30 days.

2. Repeated use of extensions, either on the same airplane or on similar airplanes in an operator’s fleet, should not be used a

management practices. Exceptional short-term extensions must not be used for fleet AWL extensions.

3. After a system AWL has experienced an exceptional short-term extension, the AWL interval will revert back to its interval lis

FAA Oversight Office must approve, prior to its use, any desired extension not explicitly listed above. 

NOTE: This exceptional short term extension listed above applies to airlines that fall under the U.S. FAA jurisdiction only. Opethe U.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

DEFINITIONSRemoved or Replaced: Defined as removal or replacement of a component, as well as partial removals.Disturbed: Defined as interference, movement or change to the arrangement or order of the referenced component.New wiring: Defined as any alteration that installs wiring that is added to the airplane after initial Airplane Airworthiness Certificadate that the AWL/CMR Document, D6-38278-CMR, was first incorporated into an operator's maintenance program, whichever 

Sealant: Defined as sealant type BMS 5-45 or equivalent in accordance with SRM 51-20-4 for 737-100/-200 and SRM 51-20-05 inside of fuel tank and sealant type BMS 5-95, or equivalent, in accordance with SRM 51-20-4 for 737-100/-200 and SRM 51-2for outside of the fuel tank.FAA Oversight Office: Defined as the FAA office that currently has oversight responsibility for the type certificate of the Boeing 

300/400/500 aircraft. At the time of publication, the FAA Oversight Office is the FAA BASOO.SUPPORTING DOCUMENTATIONStrict adherence to methods, techniques and practices as prescribed is required to ensure the ALI or CDCCL is complied with. manufacturer's maintenance procedures when performing maintenance that has an effect on an ALI or CDCCL. If operators do 

can increase the risk of an unsafe condition. Any use of methods, techniques or practices not contained in these ALIs or CDCC

the FAA Oversight Office.

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONS

COLUMN EXPLANATIONAWL NUMBER Each task is given a unique AWL Item Number. The first and second digits are the ATA Chapter NumbTASK ALI = Airworthiness Limitation Instruction. These tasks are inspections that should be performed at th

CDCCL = Critical Design Configuration Control Limitations

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

APPLICABILITY Airplane model applicability.TASKDESCRIPTION

Description of the task to be performed or critical design configurations aspects that cannot be changethe intent of the design.

MAY 2009
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

C.1 FUEL SYSTEMS IGNITION PREVENTION

This section contains an FAA-approved program of scheduled inspections and design limitations for operators to incorporate in

program for this type design to meet the standards and assumptions introduced by Title 14 CFR § 25.981 and Special Federal 

(SFAR 88). SFAR 88 – Fuel Tank System Fault Tolerance Evaluation Requirements and Title 14 CFR § 25.981 – Fuel Tank Ig

maintenance instructions and control limitations for certain fuel tank critical design configurations.

NOTE: The auxiliary fuel tank installation has been shown to comply with Title 14 CFR § 25.981 at Amendment 25-102.

Paragraph 2(a) of SFAR 88 and Paragraph (b) of the standard introduced by Title 14 CFR § 25.981 (Amendment 25-102) requholders of Type Certificates (TCs) and Supplemental Type Certificates (STCs) of large transport airplanes to conduct a safety r

systems. The purpose of the safety review is to identify design features that may result in development of ignition sources in th

AWLs are mandatory maintenance actions required to ensure that unsafe conditions identified by the SFAR 88 safety review dintroduced into the fuel tank system as a result of configuration changes, repairs, alterations, or deficiencies in the maintenance operational life of the airplane.

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

AWLs - FUEL TANK IGNITION PREVENTION

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

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 TankConcern: Potential for Wire Chafing and Arcing to Center Fuel TaPerform a detailed inspection of the wire bundles routed over the 

main deck floor boards in accordance with AMM 28-11-00 to detechafing, damage to the vapor barrier, and that the wire bundle is n

center fuel tank. If discrepancies are found repair in accordance w

Practices Manual (SWPM) D6-54446.Interval Note: Threshold for interval inspection is 10 years after in737-28-1208.

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 TaIf any maintenance is performed in the area under the floor board

verify the following:1. Maintain the existing wire bundle routing and clamping.2. Installation of any new wire bundles must be in accordance w

Practices Manual, D6-54446.

3. Perform a detailed inspection of the wire bundles routed on ma

tank and under the main deck floor boards in the areas of the detect damaged clamps, wire chafing, and that the wire bundl

surface of the center tank. If wiring discrepancies are found, reBoeing Standard Wiring Practices Manual, D6-54446.

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

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 LightnGround TerminationConcern: Potential for Lightning induced voltages on the FQIS wPerform the following functional check to ensure the integrity of thtermination:Verify the resistance of the shield to ground terminations at the spunpressurized area by making the following measurements using 906-10246-2 or 906-10246-3 in accordance with Boeing AMM 20accordance with the Boeing AMM if required.Perform a loop resistance measurement where the wire bundle eThe loop resistance shall not exceed 28 milliohms for Connector The loop resistance shall not exceed 28 milliohms for Connector The loop resistance shall not exceed 35 milliohms for Connector 

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 LightnGround Termination Concern: Potential for Lightning induced voltages on the FQIS wIf the FQIS wire bundle or the shield on the FQIS wire bundle is rthe following:1. Presence of shielded wiring.2. The shield ground is terminated in accordance with the Boein3. The installation is inspected as specified in 28-AWL-03. 

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

28-AWL-05 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Out-Tank Wiring Installa

Concerns: Potential for hot shorts and EMI induced voltages on thfuel tank.For airplanes incorporating Isolated Fuel Quantity Transmitter (IF1178, the FQIS wiring is defined as the wiring between the IFQT For airplanes not incorporating IFQT, the FQIS wiring is defined aindicators and the fuel tank.Routing and installation of any new wiring must use wire types BMBMS 13- 58, and not be within a 2-inch radius of the FQIS wiring. or brackets, a separation greater than 1⁄2 inch must be maintained This AWL is for design requirements.The installation is in accordance with 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 Concern: Potential for maintenance error during FQIS Indicator orepair. The design of the FQIS Indicators and the VTO Unit limits into the tank to preclude possible ignition source into the tank.Repair and overhaul of FQIS Indicators and VTO must be in accoComponent Maintenance Manual (CMM) 28-41-11 Revision 12, C

28-41-23 Revision 10, or later revisions of these CMMs that have Oversight Office.

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-07 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Hardw

Compensators) Concern: Potential for maintenance error during repair of in-tank compensators). Arc gaps may develop that could result in an igniThe dielectric of these components must be maintained to providvoltages that could be coupled on the FQIS wiring or onto the wirfuel tank if the shield or shield ground of the wiring is compromiseRepair and overhaul of FQIS tank units and compensators must b(V89305) Component Maintenance Manual (CMM) 28-40-25 Revi11, CMM 28-40-58 Revision 4, or later revisions of these CMMs t

FAA Oversight Office. The AC powered float switch on airplanes wfunction is not repairable.The manufacturer's production procedures for this component ma

identified CMM.

28-AWL-08 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Repair or Replacement 

Concern: Potential for error during repair or replacement of in-tandevelop that could result in an ignition source inside the fuel tank. a concern if the safe-side harness is compromised.Repair and overhaul of FQIS in-tank wire harness must be in acc20-14-12. Installation of FQIS in-tank wire harness must be in accordance wWire slack clearance between wires and structure must be greatefollowing 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 pou4. A continuous bead of sealant is applied around the entire peri

harness connector at the spar interface.

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

28-AWL-09 CDCCL N/A 737-100/200/200C 

airplanes that have 

incorporated 

Service Bulletin

737-29A1096

Lightning Protection – Hydraulic Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the infitting and the spar during a lightning strike event.The following design features must be maintained in accordance the bulkhead fitting is removed and replaced:1. Verify electrical fay surface bond from bulkhead fitting to struc

0.001 ohms (1 milliohm) or less,

2. Install fillet seal on the fitting to the tank wall interface outside 3. Install full bodied fillet seal encapsulating the fitting to the tank 

the tank.

4. Verify an electrostatic bonding jumper exists between the stru

Heat Exchanger inside the tank.

5. Verify electrical bond from structure to the Hydraulic Heat Exc

0.005 ohms (5 milliohms) or less if the bonding jumper was re

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 PenetrationConcern: Potential for arcing or sparking inside the tank at the infitting and the spar during a lightning strike event.The following features must be maintained in accordance with Bobulkhead fitting or attached tubing are removed and replaced: 1. Verify electrical fay surface bond from bulkhead fitting to struc

tank) is 0.0005 ohms (0.5 milliohms) or less.

2. Install full-bodied fillet seal encapsulating the bulkhead fitting 

interface inside and outside the tank.

3. Install full bodied fillet seal encapsulating the tubes to fitting jo

outside the tank.

4. Verify an electrostatic bonding jumper exists between the first 

bulkhead fitting, and the structure inside the tank.

5. Verify electrical bond from the structure (wing front spar, in-tan

the bulkhead fitting is 0.010 ohms (10 milliohms) or less. 

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-11 CDCCL N/A All Lightning, Fault Current or Hot Short Protection – Fuel Tank Pene

Concern: Potential for arcing or sparking inside the tank at a conduinterface as a result of electrical fault currents or lightning strike ev

within the ground electrical path.Any alteration, design change or repair involving new penetrationrepair with fasteners, adding a bracket, bulkhead fitting or equipmfeatures of the existing equipment penetrations (such as fuel meavalves, fueling manifold, fuel temperature sensor, and motor operplate) requires approval by the FAA Oversight Office or an AuthorBoeing Commercial Airplanes Delegated Compliance OrganizatioHowever, any alteration, design change or repair involving new paccomplished in accordance with an FAA-approved Boeing StrucBoeing Service Bulletin is not subject to this requirement for addit

28-AWL-12 CDCCL N/A All AC and DC Electrical Fuel Tank Pump Maintenance

Concern: Potential for maintenance error during pump overhaul. ignition source prevention means (i.e., flame arrestor, thermal fuse

means, etc.) that must be maintained if pump is overhauled. Repair and overhaul of fuel pumps must be in accordance with EMaintenance Manual (CMM) 28-20-37 Revision 10, Argo-Tech (V7, CMM 28-20-5 Revision 6, CMM 28-20-07 Revision 1, or later rhave been approved by the FAA Oversight Office.The manufacturer's production procedures for this component maidentified CMM.

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

28-AWL-13 CDCCL N/A All AC Fuel Pump Fault Current Fay Surface Bond Installation 

Concern: Potential for fault current path through the pump housin

Electrical faults internal to the fuel pump motor impeller are by deimpeller assembly to the bonding straps on the front face of the mstructure outside the tank. The fay surface bond ensures that faustructure outside the tank until the circuit breaker and/or GFI has the pump.The following features must be maintained during pump replacemAMM-28-22-41:1. Installation of the pump fault current faying surface bond.2. Verify Motor Impeller bonding resistance to structure is 0.0002 

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 InstallationConcern: Potential for wire chafing and arcing to conduit inside tassemblies in fuel tank 1 and 2 are not repairable to the initial macenter tank and Boeing auxiliary tank (if installed) Float Switch aninitial manufactured standards. (Refer to Boeing AMM 28-21-71)During float switch replacement, a new float switch assembly musa new float switch assembly and liner system must be used for cetank (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 inside the tank at the intetank structure as a result of a direct strike or conducting currents The following features must be maintained during center fuel tank accordance with Boeing AMM 28-11-31: Verify presence of a phenolic strip positioned around the outermomates with the wing skin inside the tank.Connect the bonding jumper to the door and verify the resistance is 0.010 ohms (10 milliohms) or less.

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-16 CDCCL N/A All Main Fuel Tank Access Doors – Lightning Protection Bond

Concern: Potential for arcing or sparking inside the tank at the intetank structure as a result of a direct strike or conducting currents The following features must be maintained during main (wing) fueaccordance with Boeing AMM 28-11-11: Verify presence of a phenolic strip positioned around the outermomates with the wing skin inside the tank, and apply grease or antsides of the knitted aluminum mesh gasket. Install the prepared kbetween the outside face of the door and the wing skin to establisbetween the access door and the wing skin using the clamp ring specified in Boeing AMM 28-11-11.Note: Not applicable to Surge Tank Access Doors with the NACA Relief Valve. 

28-AWL-17 CDCCL N/A All Surge Tank Access Doors – Lightning Protection Bond

Concern: Potential for arcing or sparking inside the tank at the intetank structure as a result of a direct strike or conducting currents During surge tank access door installation, perform the following Boeing AMM 28-11-11:Clean the countersinks on the door. If the Pressure Relief Valve maintain the electrical fay surface bond between the pressure relohms (10 milliohms) or less in accordance with Boeing AMM 28-1removed and replaced, maintain the following electrical bonds in 28-13-31/401:Verify the electrical bond from the flame arrestor to the door asse(10 milliohms) or less. If the air vent scoop of the Type II flame ar

maintain the following electrical bonds in accordance with Boeing Verify the electrical bond from the flame arrestor to the door asse(10 milliohms) or less.Install door using the same part number conductive fasteners and Boeing AMM.

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

28-AWL-18 CDCCL N/A 737-100/200/200C 

airplanes that have 

incorporated 

Service Bulletin 

737-28A1263, but 

have not 

incorporated 

Service Bulletin 

737-28A1273

Fuel Boost Pump Wires in Conduit Installation – In-Fuel TankConcern: Potential for the boost pump wiring to chafe and arc in ignition source in the fuel tank.The boost pump wires that are in the conduits in the fuel tanks hato protect from wire chafing in accordance with the Service Bullet2007-24-02). The wiring also has a jacket to provide chafing protEnsure the following condition exists when replacing pump wiring - Jacketed wiring and a Teflon sleeve.The Teflon sleeve is not repairable. Whenever the wiring in condnew Teflon sleeve must be installed.

28-AWL-19 CDCCL N/A All Resetting of Tripped Fuel Pump Circuit Breakers or Ground Fault 

Concern: Potential for arcing or sparking inside the tank between housings and outside the tank between pump wiring and structure Verify it is safe to reset the circuit breaker(s) or GFIs by following troubleshooting procedures. Fault(s) that resulted in circuit breakeand 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 TConcern: The IFQT is designed to limit the voltage, current, and pwiring and components to intrinsically safe levels in order to preclsource within the fuel tank. IFQT installed as specified in FAA AD The IFQT is repairable only by Goodrich (89305) in accordance w

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

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 the center tank fuel pumps has the potenti

sources developing at the pump inlet due to either frictional heatinFOD contacting the pump rotating elements, rotating elements cojournal bearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit co

to 15 seconds.The following test is required in order to protect against latent fauFunctionally check the center tank fuel boost pump automatic shuAMM 28-22-0.

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 poten

sources developing at the pump inlet due to either frictional heatinFOD contacting the pump rotating elements, rotating elements cojournal bearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit co

to 15 seconds.The following test is required in order to protect against latent fauFunctionally check the auxiliary tank fuel boost pump automatic s

with AMM 28-22-0.

28-AWL-23 ALI 1 YR 737-100/200 

airplanes that have 

incorporated 

Service Bulletin

737-28A1212

Boost Pump Ground Fault Interrupter (GFI)Concern: Potential for pump housing burn-through, either internal result of major arcing due to electrical failure (i.e., damaged elector leadwire to housing/end cap shorting).The GFI is designed to detect electrical faults and open the circuithrough.The following maintenance check is required in order to ensure cGFI circuit:Operational check the GFI of all AC fuel tank boost Pumps in acc

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

28-AWL-24 ALI 1 YR 737-100/200/200C 

airplanes that have 

incorporated 

Service Bulletin

737-28A1227

Center Tank Fuel Boost Pump Power Failed On Protection SysteConcern: Dry running the center tank fuel pumps has the potentisources developing at the pump inlet due to either frictional heatinFOD contacting the pump rotating elements, rotating elements cojournal bearings due to bearing contamination or failure.The power failed on protection system is installed and designed isingle failure (i.e. wiring faults or a welded fuel pump control relaywhen the associated fuel pump control switch is positioned to OFThe following test is required in order to protect against latent fauVerify continued functionality of the center tank fuel boost pump PSystem in accordance with AMM 28-22-0.

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 SystConcern: Dry running the auxiliary tank fuel pumps has the potensources developing at the pump inlet due to either frictional heatinFOD contacting the pump rotating elements, rotating elements cojournal bearings due to bearing contamination or failure.The power failed on protection system is installed and designed isingle failure (i.e. wiring faults or a welded fuel pump control relaywhen the associated fuel pump control switch is positioned to OFThe following test is required in order to protect against latent fauVerify continued functionality of the auxiliary tank fuel boost pump System in accordance with AMM 28-22-0.

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-26 CDCCL N/A 737-100/200/200C 

airplanes that have 

incorporated 

Service Bulletin 

737-28A1273.

Fuel Boost Pump Wires in Conduit Installation - In Fuel TankConcern: Potential for the boost pump wiring to chafe and arc to tignition source in the fuel tank. The boost pump wires that are in thave incorporated a conduit liner to protect from wire chafing. The (grounded at both ends) that is monitored by the GFI for an additpump power wire short within the conduit.The following design features must be verified when the pump wiis removed or replaced (refer to Boeing AMM 28-22-41):1. Jacketed and shielded (grounded at both ends) wiring is insta2. A Convoluted Conduit Liner is installed.NOTE: The above requirement applies to the following Fuel BooMain Tank No. 1 AFT Fuel Boost PumpCenter Tank LEFT Fuel Boost PumpCenter Tank RIGHT Fuel Boost PumpMain Tank No. 2 AFT Fuel Boost Pump

737-100/200/200C MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYS

AWL 

NUMBER TASK INTERVAL APPLICABILITY TASK DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

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 and Arcing to Center FuePerform a detailed inspection of the wire bundles routed on matank and under the main deck floor boards in accordance with damaged clamps, wire chafing, damage to the vapor barrier, acontact with surface of the center fuel tank. If discrepancies arwith the Boeing Standard Wiring Practices Manual, D6-54446. Interval Note: Threshold for initial inspection is 10 years after i

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 and Arcing to Center FueIf any maintenance is performed in the area under the main decenter fuel tank, verify the following:1. Maintain the existing wire bundle routing and clamping.2. Installation of any new wire bundles must be in accordance 

Wiring Practices Manual, D6-54446.

3. Perform a detailed inspection of the wire bundles routed on 

fuel tank and under the main deck floor boards in the areas maintenance to detect damaged clamps, wire chafing, and 

in contact with the surface of the center tank. If wiring discin accordance with the Boeing Standard Wiring Practices M

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

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 LighGround TerminationConcern: Potential for Lightning induced voltages on the FQIS Perform the following functional check to ensure the integrity o

ground termination:Verify the resistance of the shield to ground terminations at the unpressurized area by making the following measurements usN 906-10246-2 or 906-10246-3 in accordance with Boeing AMRestore the bonds as specified in the Boeing AMM if required.The loop resistance shall not exceed 28 milliohms for ConnectThe loop resistance shall not exceed 28 milliohms for ConnectThe loop resistance shall not exceed 35 milliohms for Connect

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 LighGround Termination Concern: Potential for Lightning induced voltages on the FQIS If the FQIS wire bundle or the shield on the FQIS wire bundle ithe following:1. Presence of shielded wiring.2. The shield ground is terminated in accordance with the Boe3. The installation is inspected as specified in 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 InstRequirement Concerns: Potential for hot shorts and EMI induced voltages oharness to enter the fuel tank. The FQIS wiring is defined as thFuel Quantity Transmitter (IFQT) and the fuel tank.Routing and installation of any new wiring must use wire types BMS 13-58, and not be within a 2-inch radius of the FQIS wirin

clamps or brackets, a separation greater than 1⁄2 inch must be This AWL is for design requirements.The installation is in accordance with SWPM 20-10-11.

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

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) – Isolated Fuel Quanti

Concern: The IFQT is designed to limit the voltage, current, anwiring and components to intrinsically safe levels in order to pr

ignition source within the fuel tank. IFQT installed as specified The IFQT is repairable only by Goodrich (89305) in accordanc

28-AWL-07 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Ha

Compensators) Concern: Potential for maintenance error during repair of in-tancompensators). Arc gaps may develop that could result in an tank. The dielectric of these components must be maintained voltages that could couple onto the FQIS wiring between the IF

shield ground is compromised. Repair and overhaul of FQIS tank units and compensators mu

manufacturer Component Maintenance Manual (CMM) 28-40-2Revision Number 11, or 28-40-58 Revision Number 4 as applicCMMs that have been approved by the FAA Oversight Office.The manufacturer's production procedures for this component the identified CMM.

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-08 CDCCL N/A All Fuel Quantity Indicating System (FQIS) – Repair or Replacem

Concern: Potential for error during repair or replacement of in-tmay develop that could result in an ignition source inside the furequired for airplanes with IFQT in case the FQIS wiring betwecompromised.Repair and overhaul of FQIS in-tank wire harness must be in a

20-14-12. Installation of FQIS in-tank wire harness must be in accordancDuring installation of the harness, verify the following:For airplanes with rectangular bussing plug, tighten the mounti65 – 90 pound-inches.For airplanes with circular bussing plug:- On the receptacle for the No. 1 or the No. 2 Tank, tighten th325 – 350 pound-inches.- On the receptacle for the center tank, tighten the receptacle 100 – 150 inch-pounds.A thin layer of sealant is present around the joint between the r

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 structure must be gre

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

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 fitting and the spar during a lightning strike event.The following design features must be maintained in accordancIf the bulkhead fitting is removed and replaced:1. Verify electrical fay surface bond from bulkhead fitting to st

0.001 ohms (1 milliohm) or less,

2. Install fillet seal on the fitting to the tank wall interface outsi3. Install full bodied fillet seal encapsulating the fitting to the ta

the tank,

4. Verify an electrostatic bonding jumper exists between the s

Heat Exchanger inside the tank, and

5. Verify electrical bond from structure to the Hydraulic Heat E

0.005 ohms (5 milliohms) or less if the bonding jumper was 

28-AWL-10 CDCCL N/A 737-300/400/500 

airplanes that have 

incorporated 

Service Bulletin 

737-28A1174

Lightning Protection – Engine Fuel Feed Line Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the fitting and the spar during a lightning strike event.The following features must be maintained in accordance with bulkhead fitting or attached tubing are removed and replaced: 1. Verify electrical fay surface bond from bulkhead fitting to st

(0.5 milliohms) or less,

2. Install full-bodied fillet seal encapsulating the fitting to the ta

outside the tank,

3. Install full-bodied fillet seal encapsulating the tubes to fitting 

outside the tank, 

4. Verify an electrostatic bonding jumper exists between first t

bulkhead fitting and the mating tube inside the tank, and

5. Verify electrical bond from the structure (wing front spar, in

with the bulkhead fitting is 0.010 ohms (10 milliohms) or les

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-11 CDCCL N/A All Lightning, Fault Current or Hot Short Protection – Fuel Tank Pe

Concern: Potential for arcing or sparking inside the tank at a costructure interface as a result of electrical fault currents or light

insufficient bonding within the ground electrical path.Any alteration, design change or repair involving new penetratirepair with fasteners, adding a bracket, bulkhead fitting or equi

features of the existing equipment penetrations (such as fuel mvalves, fueling manifold, fuel temperature sensor, and motor opadaptor plate) requires approval by the FAA Oversight Office o

(AR) of the Boeing Commercial Airplanes Delegated Complian

However, any alteration, design change or repair involving new accomplished in accordance with an FAA-approved Boeing StruBoeing Service Bulletin is not subject to this requirement for ad

28-AWL-12 CDCCL N/A All AC and DC Electrical Fuel Tank Pump Maintenance

Concern: Potential for maintenance error during pump overhaignition source prevention means (i.e., flame arrestor, thermal retention means, etc.) that must be maintained if pump is overRepair and overhaul of Fuel Pumps must be in accordance witComponent Maintenance Manual (CMM) Numbers 28-20-37 RRevision Number 7, 28-20-5 Revision Number 6, 28-20-07 Rev

or later revisions of these CMMs that have been approved by tThe manufacturer's production procedures for this component 

the identified CMM.

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

28-AWL-13 CDCCL N/A All AC Fuel Pump Fault Current Fay Surface Bond Installation 

Concern: Potential for fault current path through the pump hous

Electrical faults internal to the fuel pump motor impeller are by dimpeller assembly to the bonding straps on the front face of the 

structure outside the tank. The fay surface bond ensures that 

structure outside the tank until the circuit breaker and/or GFI hfrom the pump.The following features must be maintained during pump replacBoeing AMM 28-22-41:1. Installation of the pump fault current faying surface bond.2. Verify Motor Impeller bonding resistance to structure is 0.00

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 InstallationConcern: Potential for wire chafing and arcing to conduit insid

assemblies in Fuel Tank 1 and 2 are not repairable to the initiacenter tank and Boeing auxiliary tank (if installed) Float Switch 

the initial manufactured standards (refer to Boeing AMM 28-21During float switch replacement, a new float switch assembly mand a new float switch and liner system must be used for cente

(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 inside the tank at the 

the tank structure as a result of a direct strike or conducting cuThe following features must be maintained during center fuel taaccordance with Boeing AMM 28-11-31:Verify presence of a phenolic strip positioned around the outer

mates with the wing skin inside the tank.

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-16 CDCCL N/A All Main Fuel Tank Access Doors – Lightning Protection Bond

Concern: Potential for arcing or sparking inside the tank at the 

the tank structure as a result of a direct strike or conducting cuThe following features must be maintained during main (wing) installation in accordance with Boeing AMM 28-11-11:1. Apply anti-corrosion compound to both sides of the knitted 

and install the greased aluminum mesh gasket between the wing skin. Due to the countersink, the aluminum mesh will and establish the electrical conductivity between the accesusing the clamp ring and fasteners torqued to the value spe28-11-11.

Note: Not applicable to Surge Tank Access Doors with the NAPressure Relief Valve. 

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

28-AWL-17 CDCCL N/A All Surge Tank Access Doors – Lightning Protection Bond

Concern: Potential for arcing or sparking inside the tank at the 

the tank structure as a result of a direct strike or conducting cuDuring surge tank access door installation, perform the followinBoeing AMM 28-11-11:Clean the countersinks on the access door. If the Pressure Relief Valve is removed and replaced, maintain 

between the pressure relief valve and the door 0.010 ohms (10 

accordance with Boeing AMM 28-13-41.If the Type I Flame Arrestor is removed and replaced, verify the arrestor to the door assembly is 0.010 ohms (10 milliohms) or AMM 28-13-31.If the Air Vent Scoop of the Type II Flame Arrestor is removed following electrical bonds in accordance with Boeing AMM 28-1. Prepare the electrical fay surface from the upper surface of 

lower surface of the air vent scoop.

2. Before the surface is sealed, verify the electrical surface bo

to the air vent scoop is 0.0025 ohms (2.5 milliohms) or less

3. After the surface is sealed, verify the electrical bond from th

assembly is 0.010 ohms (10 milliohms) or less.

Install the door using the same part number conductive fastene

in the Boeing AMM.

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

28-AWL-18 CDCCL N/A 737-300/400/500 

airplanes that have 

incorporated 

Service Bulletin 

737-28A1263, but 

have not 

incorporated 

Service Bulletin 

737-28A1273

Fuel Boost Pump Wires In Conduit Installation – In Fuel TankConcern: Potential for the boost pump wiring to chafe and arc ignition source in the fuel tank. The boost pump wires that are have incorporated a Teflon sleeve to protect from wire chafing Service Bulletin 737-28A1263 (FAA AD 2007-24-02). The wirichafing protection. Ensure the following condition exists when replacing pump wir- Jacketed wiring and a Teflon sleeve.The Teflon sleeve is not repairable. Whenever the wiring in conew Teflon sleeve must be installed.

28-AWL-19 CDCCL N/A All Resetting of Tripped Fuel Pump Circuit Breakers or Ground Fa

Concern: Potential for arcing or sparking inside the tank betwehousings and outside the tank between pump wiring and structzones.Verify it is safe to reset the circuit breaker(s) or GFIs by followitroubleshooting procedures. Fault(s) that resulted in circuit brea

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 Pump Automatic Shutoff SystemConcern: Dry running the center tank fuel pumps has the potesources developing at the pump inlet due to either frictional heFOD contacting the pump rotating elements, rotating elements hot journal bearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit condition to 15 seconds.The following test is required in order to protect against latent fFunctionally check the center tank fuel boost pump automatic with AMM 28-22-00.

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

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 SystemConcern: Dry running the auxiliary tank fuel pumps has the posources developing at the pump inlet due to either frictional heFOD contacting the pump rotating elements, rotating elements hot journal bearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit condition to 15 seconds.The following test is required in order to protect against latent fFunctionally check the auxiliary tank fuel boost pump automati

with AMM 28-22-00.

28-AWL-22 ALI 1 YR 737-300/400/500 

airplanes that have 

incorporated 

Service Bulletin 

737-28A1212

Boost Pump Ground Fault Interrupter (GFI)Concern: Potential for pump housing burn-through, either interas a result of major arcing due to electrical failure (i.e., damage

windings or leadwire to housing/end cap shorting).The GFI is designed to detect electrical faults and open the cirthrough.The following maintenance check is required in order to ensure GFI circuit:Operational check the GFI of all AC Fuel Tank Boost Pumps in 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 Sys

Concern: Dry running the center tank fuel pumps has the pote

sources developing at the pump inlet due to either frictional heFOD contacting the pump rotating elements, rotating elements hot journal bearings due to bearing contamination or failure.The power failed on protection system is installed and designesingle failure (i.e. wiring faults or a welded fuel pump control relwhen the associated fuel pump control switch is positioned to OThe following test is required in order to protect against latent fVerify continued functionality of the center tank fuel boost pumSystem in accordance with AMM 28-22-00.

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

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 SConcern: Dry running the auxiliary tank fuel pumps has the posources developing at the pump inlet due to either frictional heFOD contacting the pump rotating elements, rotating elements hot journal bearings due to bearing contamination or failure.The power failed on protection system is installed and designesingle failure (i.e. wiring faults or a welded fuel pump control relwhen the associated fuel pump control switch is positioned to OThe following test is required in order to protect against latent fVerify continued functionality of the auxiliary tank fuel boost pu

System in accordance with AMM 28-22-00.

28-AWL-25 CDCCL N/A 737-300/400/500 

airplanes that have 

incorporated 

Service Bulletin 

737-28A1273

Fuel Boost Pump Wires in Conduit Installation - In Fuel TankConcern: Potential for the boost pump wiring to chafe and arc ignition source in the fuel tank. The boost pump wires that are have incorporated a conduit liner to protect from wire chafing. (grounded at both ends) that is monitored by the GFI for an adpump power wire short within the conduit.The following design features must be verified when the pump conduit is removed or replaced (refer to Boeing AMM 28-22-001. Jacketed and shielded (grounded at both ends) wiring is in2. A Convoluted Conduit Liner is installed.NOTE: The above requirement applies to the following Fuel BMain Tank No. 1 AFT Fuel Boost PumpCenter Tank LEFT Fuel Boost PumpCenter Tank RIGHT Fuel Boost PumpMain Tank No. 2 AFT Fuel Boost Pump

737-300/400/500 MAINTENANCE PLANNING DATA – AIRWORTHINESS LIMITATIONS – FUEL SYST

AWL NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

C.2 NITROGEN GENERATION SYSTEM (NGS)

The following list of AWLs (ALIs and CDCCLs) contains FAA approved scheduled inspections and design limitations for operat

maintenance program for this type design to meet the requirements for the introduction of Flammability Reduction Means (FRM

System (NGS). The FAA Final Flammability Rule, E8-16084, requires maintenance instructions and control limitations for cert

configurations. Title 14 CFR § 25.981 also requires AWLs to preclude ignition sources inside the fuel tank that may be introduc

E8-16084, Final Flammability Rule, Paragraph III(F), Section 7, Identification of Airworthiness Limitations: Paragraph M25.4(a) 

to comply with Paragraph M25.1, airworthiness limitations must be identified for all maintenance or inspection tasks required to components within the FRM that are needed to meet Paragraph M25.1. NGS AWLs are mandatory maintenance actions that en

that arise due to NGS failures do not occur or are not introduced into the airplane as a result of configuration changes, repairs, in the NGS maintenance program throughout the operational life of the airplane.

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

AWLs – NITROGEN GENERATION SYSTEM

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) Distributi

Concern: Potential for arcing or sparking inside the tank at the intefitting and the spar during a lightning strike event.The following must be maintained if the bulkhead fitting is removed (refer to Boeing AMM 47-21-07):1. Install the same part number bulkhead fitting.2. Verify electrical fay surface bond from the bulkhead fitting to th

the tank is 0.0005 ohms (0.5 milliohms) or less.

3. Install fillet seal on both the inside and outside surfaces of the 

perimeter of the bulkhead fitting and jam nut.

Note: The bulkhead fitting is a special part which has an integral f this part requires approval by the FAA Oversight Office.

47-AWL-02 CDCCL N/A Airplanes that 

have incorporated 

Service Bulletin 

737-47-1004 or 

737-47-1007

Lightning Protection – NGS NEA Distribution Line Fuel Tank PeneConcern: Potential for arcing, sparking or filament heating inside th

the dielectric isolator hose and the NEA tubing during a lightning sThe NGS installation is designed to prevent lightning currents from tank by adding a dielectric isolator hose in the wheel well at the reNEA distribution line. The isolator hose must be maintained if the d

attached tubing are removed and replaced or reinstalled (refer to BAMM 47-21-07).

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

47-AWL-03 CDCCL N/A Airplanes that 

have incorporated 

Service Bulletin 

737-47-1005 or 

737-47-1008

Nitrogen Generation System (NGS) – Flammability Exposure and Concern: Airplane alterations may impact the performance of the Nof the Center Wing Fuel Tank.Background: The NGS is designed to provide the proper level of nin order to reduce the flammability exposure by reducing the oxygeflammability exposure is also affected by the temperature of the fu

features of the airplane that, if altered, can negatively affect the peturn may increase the center fuel tank flammability exposure beyoSection 25.981 at Amendment 25-125, utilizing the equivalent leveFAA Memorandum PS05-0177-P-2.1. Transferring air (20.9% oxygen) to the center fuel tank will dilut

atmosphere created by the NGS in the fuel tank. Some Auxiliatransfer air to the center wing tank as part of venting and fuel t

2. NGS performance depends on bleed air pressure in the bleed 

supplied by the engines.

3. Certification of the NGS depends on the inherent flammability o

without NGS installed. Center tank flammability is a direct functemperature. Any heat sources around the tank, heat sources (such as warm fuel or new heat exchangers), or changes that w

retained (such installation of blankets adjacent to tank walls) co

flammability in a negative manner.

CDCCL: Any design change that affects the vent system by adding 

the bleed pressure in the cross-over manifold during any phase of adds any heat to the center wing fuel tank or increases heat retentis not allowed without an FAA approved analysis to show that the changes, does not affect the NGS performance as specified in the Section 25.981(b), Amendment 25-125 utilizing the equivalent leveFAA Memorandum PS05-0177-P-2.See Boeing AMM Chapter 28 for a description of the Fuel Systemfor a description of the NGS.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

47-AWL-04 ALI 22,500 FH Airplanes that 

have incorporated 

Service Bulletin 

737-47-1005 or 

737-47-1008

Nitrogen Generation System – Thermal Switch Functional and OpConcern: Latent Failure of the Thermal Switch removes a layer of 

ignition by hot bleed air.The NGS uses engine bleed air from the engine bleed system cronitrogen to reduce the flammability of the center fuel tank. The NG

directly feeding hot bleed air into the fuel tank. The Thermal Switcto the NGS controller to protect the Air Separation Module (ASM) a

entering the fuel tank. The Thermal Switch backup feature is a late

must be tested to maintain certification of the NGS.Perform a functional and operational check of the Thermal Switch 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 InspectioConcern: The NEA Distribution System ducting outside the fuel tan

to leak without reaching the fuel tank, resulting in the fuel tank not Inspect the NEA distribution lines from the ASM to the fuel tank re(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 ExposureConcern: NGS performance is dependent on industry descent timedescent time may result in NGS performance that does not meet FFleet Average flammability exposure for the fuel tanks with flamma

type must be maintained in accordance with Title 14 CFR Part 25, 

monitor U.S. descent statistics and, if necessary to maintain compinformation. If Boeing publishes such service information, this CDoperators implement these FAA-approved design changes or that design changes or operational procedural changes approved by th

maintain compliance with Title 14 CFR Part 25, Appendix M.

Note: This CDCCL does not require individual operators to monito Boeing will monitor U.S. descent statistics and provide any n operators. To prevent increasing flammability exposure abo CDCCL requires operators to incorporate future Boeing pub

 denoted to maintain compliance with this CDCCL, or other a compliance times stated in the service instructions.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

C.3 IMPACT-RESISTANT FUEL TANK ACCESS DOORS

INTRODUCTIONThe 737 Fuel Tank Access Doors are compliant with FAA Title 14 CFR § 25.963. Specifically, the 737 Impact-Resistant Acces

Title 14 CFR § 25.963(e)(1) which requires that all covers located in an area where experience or analysis indicates a strike is analysis or tests to minimize penetration and deformation by tire fragments, low energy engine debris, or other likely debris.For the 737-100/200: A design change at Line Number 1523 incorporated a physical feature which prevents non-impact-resistinstalled at locations that require impact-resistant doors. Airplane Line Numbers 1-1456 and 1486 do not have these physical f

Numbers 1-1456 and 1486 were retrofitted with impact-resistant access doors via Service Bulletins 737- 28A1064 and 737-28A

bulletins also required that the impact-resistant doors be stenciled “IMPACT-RESISTANT DOOR”. Additionally, the adjacent lostenciled “CAUTION: INSTALL ONLY IMPACT-RESISTANT DOOR AT THIS LOCATION”.All 737-200 airplanes after Line Number 1486 have a physical feature which prevents non-impact-resistant doors from being inrequire impact-resistant doors.For the 737-300: A design change for 737-300 airplanes at Line Number 1506 and on (excluding L/N 1508) incorporated a ph

prevents non-impact-resistant doors from being installed at locations that require impact-resistant doors. Airplane Line Numbe

not have these physical features. Airplane Line Numbers 1001-1505 and 1508 were retrofitted with impact-resistant access doo28-1081. This service bulletin also required that the impact-resistant doors be stenciled “IMPACT-RESISTANT DOOR”. Additiowing surface is stenciled “CAUTION: INSTALL ONLY IMPACT-RESISTANT DOOR AT THIS LOCATION”.All 737-300 airplanes after Line Number 1508 and all 737-400/500 airplanes have a physical feature which prevents non-impac

installed at locations that require impact-resistant doors.Boeing chose to use a CDCCL for the AWL of the Impact-Resistant Fuel Tank Access Doors. CDCCLs are commonly used anto define a design feature that must be maintained throughout the life of the airplane.

AUG 2012
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

737-100/200/200C MPD – AWLs – STRUCTURES

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

57-AWL-01 CDCCL N/A L/Ns 1-1456 

and 1486

Impact-Resistant Fuel Tank Access DoorsConcern: A potential exists for non-impact-resistant doors to be insimpact-resistant doors. A high energy impact on a non-impact-resicause a fuel leak, and in the presence of an ignition source, may r

Immediately prior to the installation of each of the Fuel Tank Acces7404R, 7205L, 7405R, 7206L, 7406R, 7207L, 7407R, 7208L, and 1. Verify that the fuel tank access door is impact-resistant. Impact

that are flat and a smooth inner surface. Doors with rounded estiffening ribs on the inner surface are not impact-resistant (ref28-11-11).

JUN 2014
737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENAN

D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-300 MPD – AWLs – STRUCTURES

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

57-AWL-01 CDCCL N/A L/Ns 1001 - 1505

and 1508

Impact-Resistant Fuel Tank Access DoorsConcern: A potential exists for non-impact-resistant doors to be insimpact-resistant doors. A high energy impact on a non-impact-resicause a fuel leak, and in the presence of an ignition source, may r

Immediately prior to the installation of each of the Fuel Tank Accesand 7404R, perform the following:1. Verify that the fuel tank access door is impact-resistant. Impact

that are flat and a smooth inner surface. Doors with rounded estiffening ribs on the inner surface are not impact-resistant (refAMM 28-11-11).

JUN 2014
D6-38278-CMR

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-12345 AIRWORTHINESS LIMITATIONS/CERTIFICATION MAINTENA

D. LIMIT OF VALIDITY (LOV)

This section provides the Limit of Validity (LOV) in accordance with the requirements of Title 14 CFR § 26.21 (Amendment 26-6

the establishment of an airplane level limit of validity of the engineering data that supports the structural maintenance program period of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demonstrated that will not occur in the airplane. The LOVs listed in the following table support operator compliance with Title 14 CFR Sections 121

737-100/200/200C/300/400/500.

LIMIT OF VALIDITY FOR THE 737100/200/200C/300/400/500

MODEL FLIGHT CYCLE LOV FLIGHT HOUR LOV

737-100,-200,-200C

Line Numbers 1 - 291 34,000 34,000

737-200,-200C,-300,-400,-500

Line Numbers 292 - 2565 75,000 100,000

737-300,-400,-500

Line Numbers 2566 - 3132 85,000 100,000

AUG 2012