rp._aoEIND 

October 4, 2012 

M-7300-12-066 

The Boeing Company 

P.O. Box 3707 

Seattle, WA 98124-2207 

To: All Recipients of Boeing 737-600/700/800/900 (737NG) D626A001-CMR 

Maintenance Planning Data (MPD) Document 

Subject: Temporary Revision (TR) 09-039, dated August 2012 to the Boeing 737NG 

MPD Document 

This letter transmits the enclosed TR 09-039 to the 737NG MPD. TR 09-039 contains the latest 

Federal Aviation Administration (FAA) approved revision of Document D626A001-CMR which is 

published as Section 9 of the 737NG MPD. 

For this revision, the following changes were added and approved by the Seattle FAA BASCO: 

• Revised Section E.2 front matter by adding the regulation Title 14 CFR § 25.951 requiring 

the engine fuel suction feed test. Provided the background and technical reason why the 

engine fuel suction feed test is a mandatory maintenance requirement. 

• Revised 28-AWL-1 01 to revise the interval to "7500 FH or 3 yrs, whichever occurs first" to 

cover lower utilization operators and revise the center tank fuel quantity requirement. 

For a complete list of revisions, please refer to the revision log within the document. 

Also enclosed is a copy of FAA Letter 140S-12-200, Approval of Alternative Method of 

Compliance (AMOC). 

If there are any questions or comments regarding this TR, please submit them to the 

undersigned. 

Sincerely, 

~;H:zJr-- Maintenance Programs Engineering 

Commercial Aviation Services 

The Boeing Company 

206-766-3497 

Enclosures: FAA Letter 140S-12-200 

MPD Section 9 TR 09-039 
U.S. Department 

of Transporlation 

Federal Aviation 

Administration 

OCT -2 2012 

In Reply 

Refer To: l40S-l2-200 

Mr. Douglas M. Lane 

ODA Deputy Lead Administrator 

Regulatory Administration 

Boeing Commercial Airplanes 

P.O. Box 3707, MC 03-56 

Seattle, WA 98124-2207 

Dear Mr. Lane: 

Transport Airplane Directorate 

Aircraft Certification Service 

1601 lind Avenue SW 

Renton, WA 98057 

Subject: Federal Aviation Administration (FAA) Approval of Alternative Method of 

Complianee (AMOC) to Airworthiness Direetives (AD) 2008-10-10 R1, AD 

2008-17-15, and AD 2011-18-03. 

Referenees: (1) AD 2008-10-10 R1, effeetive date January 27, 2010 

(2) AD 2008-17-15, effeetive date Oetober 2, 2008 

(3) AD 2011-18-03, effeetive date September 30, 2011 

(4) Boeing 737-6001700/700C/800/900/900ER Maintenanee Plarming Data 

(MPD) Doeument, Seetion 9, D626A001-CMR, dated August 2012 

The FAA has received your letter RA-12-03655, dated August 28,2012, requesting approval 

ofmr AMOC to the referenee (1) AD 2008-10-10 R1, referenee (2) AD 2008-17-15, and the 

referenee (3) AD 2011-18-03. 

AD 2008-10-10 Rl requires revising the Airworthiness Limitations (AWL) section of the 

Instructions for Continued Airworthiness (ICA) by incorporating new limitations for fuel 

tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This AD 

also requires an initial inspection to phase in certain repetitive AWL inspections, and repair 

if necessary. 

AD 2008-17-15 requires installing a hot short protector, support brackets, and equipment for 

the fuel quantity indicating system (FQIS) fuel densitometer. This AD also requires the 

revision of the AWLs section of the ICAs by incorporating AWL No. 28-AWL-07. This AD 

was issued to prevent the center tank densitometer from overheating and becoming a 

potential ignition source inside the center fuel tank. 
140S-12-200 2 

AD 2011-18-03 requires installation of an automatic shutoff system for the center tank fuel 

boost pumps in accordance with the accomplishment instructions of Boeing Service Bulletin 

737-28Al206 Rev 2. This AD also requires the revision of the AWLs section of the !CAs by 

incorporating AWL No. 28-A WL-23. This AD was issued to prevent center tank fuel pump 

operation with continuous low pressure, which could lead to sparks or overheating in the 

pump inlet creating a potential ignition source inside the center tank. 

You are requesting approval of the use of the reference (4) MPD document as an alternative 

method of compliance (AMOC) to the requirements of paragraph (g)(l ), (g)(2), (g)(3), (h)(l ), 

and (h)(2) oftl1e reference (1) AD; paragraph (g) of the reference (2) AD, and paragraph (k) of 

the reference (3) AD. 

Your proposal provides an acceptable level of safety as there have been no changes to 

subsection E "AWLs -FUEL SYSTEMS" since the previous December 2011 MPD revision, 

which was previously approved as an AMOC to the reference (1) AD and the reference (3) 

AD, and no changes to AWL No 28-A WL-07 of subsection E have been made since the 

February 2011 MPD revision, which is specified in paragraph (g) of the reference (2) AD. 

We have completed our review of your request and approve the use of section 9, subsection 

E of the reference (4) MPD document instead of the use of subsections E, F, and G of 

Boeing TR 09-020, dated March 2008, to the Boeing 737-600/700/700C/800/900/900ER 

MPD Document, D626A001-CMR Revision March 2008; or subsections E, F,"and G of 

section 9 of the Boeing 737-600/700/700C/800/900/900ER MPD Document, 

D626A001-CMR Revision September 2009, as an AMOC when complying with the 

requirements of paragraph (g)(l), (g)(2), (g)(3), (h)(l), and (h)(2) of the reference (1) AD 

2008-10-lORL 

We also approve the use of AWL No. 28-AWL-07 of subsection E, section 9 of the 

reference ( 4) MPD document as an AMOC when complying with the requirements of 

paragraph (g) of the reference (2) AD 2008-17-15, 

In addition, we approve the use of AWL No. 28-A WL-23, described as Center Tank Fuel 

Boost Pump Power Failed On Protection System, of subsection E, AWLs-Fuel Systems of 

the reference (4) document as an AMOC when complying with the requirements of 

paragraph (k) of the reference (3) AD 2011-18-03, 

In accordance with FAA Order 8110.103A, dated September 28, 2010, the following 

conditions apply: 

], All provisions of ADs 2008-10-10 Rl, 2008-17-15, and 2011-18-03 that are not 

specifically referenced above remain fully applicable and must be complied with 

accordingly. 

2. This approval is applicable only to Boeing Model737-600, -700, -700C, -800, and 

-900 series airplanes. 

3. This approval is transferable with airplane(s) to other operators. 
140S-12-200 3 

4. Before using this AMOC, notify your appropriate principal inspector, or lacking a 

principal inspector, the manager of the local flight standards district office/certificate 

holding district office. 

This AMOC only applies to the FAA ADs listed above. The FAA does not have the 

authority to approve this as an AMOC to any AD issued by another civil aviation authority 

(CAA). Approval of an AMOC to anotherCAA's AD must come from that CAA. 

Should you have any questions, please contact this office or Mr. Ansel James at telephone 

number (425) 917-6497, fax number (425) 917-6590, or e-mail at ansel.james.@faa.gov. 

Sincerely, 

t&-J~ Ross Landes 

Acting Manager, Seattle Aircraft 

Certification Office, ANM-lOOS 
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

737-600/700/700C/800/900/900ER

MAINTENANCE PLANNING DATA (MPD) DOCUMENT

SECTION 9

AIRWORTHINESS LIMITATIONS (AWLs) AND 

CERTIFICATION MAINTENANCE REQUIREMENTS (CM

D626A001-CMR

AUGUST 2012

COMPILED AND PUBLISHED BY:

MAINTENANCE PROGRAMS ENGINEERING

COMMERCIAL AVIATION SERVICES

BOEING COMMERCIAL AIRPLANE GROUP

SEATTLE, WASHINGTON

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

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TABLE OF CONTENTS

REVISIONS .......................................................................................................................................................................................LIST OF EFFECTIVE PAGES ...........................................................................................................................................................A. SCOPE..........................................................................................................................................................................................B. AWLS – STRUCTURAL INSPECTIONS.......................................................................................................................................C. AWLS – STRUCTURAL SAFE LIFE PARTS ................................................................................................................................D. AWLS – SYSTEMS .......................................................................................................................................................................

E. AWLS – FUEL SYSTEMS .............................................................................................................................................................

E.1 AWLS – FUEL TANK IGNITION PREVENTION ALIS AND CDCCLS ....................................................................................E.2 ENGINE FUEL SUCTION FEED SYSTEM.............................................................................................................................

F. AWLS – NITROGEN GENERATION SYSTEM ALIS AND CDCCLS.............................................................................................G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS) ....................................................................................................

H. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS.............................................................................

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REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

SEPTEMBER 1997Original Release.

Submitted by: N. E. Hennigs (Boeing) Appro

FEBRUARY 1998Added Note on Page 9.0-19 stating operators under JAR 25 Regulations are not allowed to escalate CMR task intervals.Added one additional ATA 27 CMR that is applicable only to operators under JAR 25 Regulations. See Page 9.3-4.

Submitted by: N. E. Hennigs (Boeing) Appro

MARCH 1998Changed statement on Page 9.0-9 Section A. Scope to include the 737-800.Clarified statements on Pages 9.0-10 and 9.0-14 about escalations.Updated airplane effectivity on Page 9.0-15.Updated Life Limits on Page 9.0-17.Deleted 38-CMR-01 due to redesigned component installed on delivered aircraft.Added 73-CMR-01 to remove the engine hydro mechanical unit for inspection per CFM 56-7B Service Bulletin 73-016.

Submitted by: N. E. Hennigs (Boeing) Appro

AUG 2012
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BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

APRIL 1998Deleted 27-CMR-01. Subsequent qualification data has determined that the CMR is no longer required.Added 251A4510-5 actuator to 27-CMR-02.

Submitted by: N. E. Hennigs (Boeing) Appro

JUNE 1998Changed statement on Page 9.0-9 Section A. Scope to include the 737-600.Updated Life Limits on Page 9.0.17.

Submitted by: N. E. Hennigs (Boeing) Appro

SEPTEMBER 1998Changed statement on Page 9.0-9, Section A. Scope to include the 737-700IGW.

Submitted by: S. Pierini (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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D626A001-CMR

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

JUNE 2000Revised document to include 737-700C airplane and 737-700IGW fuselage.Revised paragraph and paragraph order in Section B on Page 9.0-13 to provide updated information pertaining to damage tolerance based inspection program for the fuselage and empennage.Revised wording in second line of second paragraph on Page 9.0-17 to read “Note (1)” instead of “a note”.Revised titles and contents of the “Airworthiness Limitations - Structural Inspections” tables and included a column defining airplane applicability. Also moved these tables from the end of the document into Part B to be consistent with the document format of the other Boeing airplane models. Revised threshold for PSE 53-40-16-2 from 75,000 flight cycles to 38,000 flight cycles.Revised Table 9-2 by adding new PSE 55-20-09.Deleted “SPECIAL STRUCTURAL INSPECTIONS” paragraphs from Section B as service bulletins will address these inspections.Revised the Life Limits in Section C for the Main Landing Gear and Main Landing Gear Support Structure from 14,500 to 45,000 landings.Revised Page 9.0-52 by deleting statement prohibiting JAA member state registries from escalating CMR task intervals. This change coordinated between Boeing and the JAA.Revised the interval column for CMR 27-CMR-02 to reinstate the 4500 FH call out which was omitted in error from an earlier revision.

Submitted by: S. Pierini (Boeing) Appr

JANUARY 2001Revised inspection thresholds listed for PSEs 57-20-02, 57-20-03, 57-20-09, and 57-20-19 (Table 9-2) for airplanes, Line Numbers 740, 742, and 749 through 782.

Submitted by: S. Pierini (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

JANUARY 2001 R1Revised inspection thresholds listed for PSEs 57-20-02, 57-20-03, and 57-20-09 (Table 9-2) for airplanes, Line Numbers 742, 749, 750, 751, 754, 755, 759, 760, and 762 through 782. Revised the inspection thresholds listed for PSE 57-20-19 for airplanes 740, 742, and 749 through 782.

Submitted by: S. Pierini (Boeing) Appr

APRIL 2001Revised document to include the 737-900 airplane.Revised the “Threshold” column of Table 9-2 to include 75,000 HRS for non-flight length 

sensitive entries. Revised Page 9.0-15 last paragraph.Removed reference to ED/AD and EDR/ADR, and replaced with “Baseline Structures Program”.In Table 9-2:Deleted supplemental inspection requirement for Item 53-10-12-1.Revised threshold for 53-40-16-2 and added 53-40-16-2A.Revised threshold for 53-70-08-3.Added new section - Airworthiness Limitations - Systems.This section adds an airworthiness limitation for oil consumption on the 737-900. This change is due to oil tank quantities verses range capability.Added CMRs 27-CMR-04 and 27-CMR-05, related to the elevator tab.

Submitted by: S. Pierini (Boeing) Appr

APRIL 2001 R1Revised document to include 737-800 airplanes with full provisioning for winglets and 737-800 airplanes with winglets installation.Added CMR 33-CMR-01, related to the 737-800 airplanes with winglets.Revised applicability for oil consumption to add 737-800s with winglet provisions/installations.

Submitted by: S. Pierini (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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D626A001-CMR

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

AUGUST 2001Revised document by adding a supplement inspection in Table 9-2 for PSEs57-20 -01/-02/-03/-04/-05 and -08 for airplanes L/N 961 and on with wing panel wear strips.Revised CMR 27-CMR-04 to 27-CMR-06 due to a duplication with JAA 27-CMR-04.

Submitted by: S. Pierini (Boeing) Appr

DECEMBER 2001Revised document by updating the third paragraph in Section A on Page 9.0-15 that refers to the document revision date and effective Line Numbers.Revised document by deleting statement on Page 9.0-21 regarding the MPD publication date 

of DTR Check Forms for the 737-800 and 737-900 winglet airplanes as publication has been accomplished.Revised document by changing the applicability (model thresholds) in Table 9.2 for PSEs 

53-40-16-2 and 53-40-16-2a.Revised document by adding PSE 53-80-01-13 (applicable to L/N 1057 and on) to Table 9-2.

Submitted by: S. Pierini (Boeing) Appr

APRIL 2002Revised airplane applicability column in Table 9-2 for listing of PSEs 57-20-01, 02, 03, 04, 05, and 08 to provide coverage for airplanes incorporating Service Bulletin 737-57-1268.

Submitted by: Gil Palafox (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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D626A001-CMR

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

MAY 2002Revised document to reflect damage tolerance analysis based supplemental inspection thresholds for horizontal stabilizer PSEs, including the 6 hinge elevator tab design incorporated at L/N 1175. All PSEs previously listed in Table 9-1 were moved to Table 9-2. Table 9-1 has now been deleted. A conservative interim threshold of 16,000 cycles was 

specified for all horizontal stabilizer, elevator and elevator tab PSEs. These thresholds are 

currently the subject of Regulatory review and will be increased at the completion of this review.Revised CMRs 27-CMR-05 and 27-CMR-06 to be applicable to L/Ns 596 to 1174 only. In addition, provided MRB references (Item Nos. 27-095 and 27-097).Added new CMRs 27-CMR-07, 27-CMR-08 and 27-CMR-09 related to the new elevator tab design incorporated at L/N 1175 and on.

Submitted by: S. Pierini (Boeing) Appr

AUGUST 2002Deleted CMR No. 33-CMR-01 because it is now covered by the Maintenance Review Board (MRB) Report.Revised the airplane applicability for CMR Nos. 28-CMR-01 and 28-CMR-02, which are only applicable to airplanes with specific fuel pumps.Added PSE 53-80-06-3 and PSE 53-80-07-3 to Table 9-2. These airworthiness limitations have conservative interim intervals which are currently being evaluated by the FAA. Upon completion of the evaluation, the airworthiness limitations will either be deleted or modified.

Submitted by: Larry Churchwell (Boeing) Appr

OCTOBER 2002Added CMR 52-CMR-01 to perform a functional check of the flight deck door locking and unlocking latch bolt mechanism on the decompression panel.

Submitted by:Larry Churchwell (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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D626A001-CMR

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

DECEMBER 2002Revised the maximum oil consumption rate of 0.250 gallons per hour for the Model 737-800 with winglets and the Model 737-900 airplanes to 0.310 and 0.340 gallons per hour respectively (Section D. AIRWORTHINESS LIMITATIONS – SYSTEMS).Revised Airplane Applicability for Rudder Check CMR No. 27-CMR-03 (L/Ns 1-1267 airplanes that have not incorporated SB 737-27-1253).Added Rudder Check CMR No. 27-CMR-10 for airplanes L/Ns 1-1267 airplanes that have incorporated SB 737-27-1253 and for airplane L/Ns 1268 and on.Revised CMR Nos. 27-CMR-07 and 27-CMR-08 by providing the related MRB Item Numbers 27-095 and 27-096, respectively. 

Submitted by:Larry Churchwell (Boeing) Appr

MAY 2003Added paragraph for the maximum oil consumption rate for the CFM56-7B27A engines installed on the model 737-700IGW (BBJ) in (Section D. AIRWORTHINESS LIMITATIONS - SYSTEMS).Revised the following paragraph in (Section D. AIRWORTHINESS LIMITATIONS – SYSTEMS) to remove “models 737-800’s with winglets installed and 737-900 airplane” to “models listed above”.

Submitted by: Seb Pierini (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

AUGUST 2003Revised “A. Scope” paragraph to specify Aug 2003 revision and to delete statement “The FAA is considering issuance of an airworthiness directive to mandate these inspections for Line Numbers 1 through 1174.Added page for reference to the deletion of Table 9-1 on Page 9.0-28.Revised all Table 9-2 75,000 Flight Cycles Threshold items to 56,000 Flight Cycles pending FAA resolution.Revised all the conservative temporary 16,000 flight cycle horizontal stabilizer thresholds (as listed in Table 9-2) initiated in May 2002 as follows:Revised the incorrect threshold listing of 75,000 cycles/75,000 hrs for PSE 53-80-05-1 to 56,000 cycles.Revised threshold for PSE 55-10-08-5A from 16,000 cycles/75,000 hours to 36,000 cyclesRevised threshold for PSE 55-20-08 from 16,000 cycles/75,000 hours to 18,000 cycles.Revised threshold for PSE 55-20-09 from 16,000 cycles/75,000 hours to 18,000 cycles.Revised the remaining 16,000 cycles/75,000 hrs conservative interim thresholds to 56,000 cycles.Revised airplane applicability for PSE Nos. 53-10-04-1 from ALL to Airplane L/Ns 1 thru 1388.Added new PSE Nos. 53-10-04-1A for airplane L/N’s 1389 and on. New material on the Cab Window, AB Post forging materials being changed to 7050-T7452.Added new PSE Nos. 53-80-01-14 as an inspection plan for the BS 1016 Bulkhead Web looking for Oil Cans as part of FAA Project (#TD7774SE-T).Revised the conservative threshold for PSE Nos. 53-80-07-2 from 5000 cycles to 56,000 cycles following FAA review of the integrated bulkhead (FAA Project #TD6620SE-T) damage tolerance analysis. PSE Nos. 53-80-06-3 and 53-80-07-3 are deleted following a FAA review.

(Continued on next page)

Submitted by: S. Pierini (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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D626A001-CMR

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

AUGUST 2003, ContinuedRevised airplane applicability for PSE Nos. 55-20-08-1, 55-20-08-2, 55-20-09-1, 55-20-09-2, 55-20-12 and 55-20-12-1.Revised airplane applicability and changed thresholds for PSE Nos. 57-20-02, 57-20-03 and 57-20-09 to reflect the rework necessitated by Service Bulletin 737-57-1275. The 10,000 

flight cycles or 10,000 flight hours thresholds were increased to 30,000 flight cycles or 30,000 flight hours for Line Numbers 740, 752, 753, 756, 757, 758 and 761.Deleted Note (2) from the end of Table 9-2. as it is no longer necessary.Revised airplane applicability for CMR Nos. 27-CMR-03, 27-CMR-05, 27-CMR-06, 27-CMR-07, 27-CMR-08, and 27-CMR-10.Revise the “RELATED MRB ITEM NUMBER” for CMR Nos. 27-CMR-06 from 27-096 to 27-097 for 27-CMR-07 from 27-095 to 27-093 and 27-CMR-08 from 27-97 to 27-99.Deleted CMR No. 27-CMR-09 following fatigue test substantiation of bearing material (see FAA Letter 120S-02-791 dated 09 September 2002).

(Continued from previous page) (

APRIL 2004Revised CMRs 28-CMR-01 and 28-CMR-02 to delete reporting requirements for inspection results.Added new CMR 28-CMR-03 to perform a functional check of the Center Tank Boost Pump Auto Shutoff System. This was added to comply with FAR 25.1309 by direction of FAA Aircraft Certification Office.

Submitted by: S. Pierini (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

JULY 2004Revised the reference of Appendix B to the new DTR document, D626A001-DTR dated July 2004 on page 9.0-26.Revised PSEs 55-20-08 and 55-20-09 by adding reference that this task is applicable to operators that have not incorporated SB 737-55A1080.Revised PSEs 55-20-08-2, 55-20-09-2 and 55-20-12-1 to include SB Reference Number 737-55-1081.Revised Airplane Applicability to existing PSEs 57-20-03 to include 737-700 Airplanes L/N 1545 and on.Added new PSEs 57-20-03 for 737-700 Airplanes L/N 1545 and on with or without winglets.Revised existing PSEs 57-20-04 location description and/or Applicability.Added new PSEs 57-20-04 for 737-700 Airplanes L/N 1545 and on with or without winglets.Revised existing PSEs 57-20-05 location description and/or Applicability.Added new PSEs 57-20-05 for 737-700 Airplanes L/N 1545 and on with or without winglets.Revised Airplane Applicability to existing PSEs 57-20-29 to include Airplane 737-700 L/N 1545 and on with winglets.Revised CMRs 27-CMR-07 and 27-CMR-08 task descriptions to include reference to SB 737-55-1081.Revised CMR 52-CMR-01 to add related MRBR item number 52-360 and added an airplane note to specify which airplanes and Line Numbers are affected.Added Section G which contains new airline operator reporting requirements for uncontrollable high thrust failure conditions or associated causal failures. This new section supports wording which will be added to the 737NG Type Certificate Data Sheet stating occurrences of these subject failure conditions may endanger the safe operation of the airplane and hence are reportable under 14 CFR 121.703(c), 125.409 and 135.415. Section G contains a listing of these failures. Reference Exemption No. 7968 "Partial Exemption from 25.901(c) as it relates to uncontrollable high thrust.

Submitted by: S. Pierini (Boeing) Appr

(FAA

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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D626A001-CMR

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

AUGUST 2004Added paragraph on Page 9.0-27 titled "Special Structural Inspections". This is a special inspection and action requirement of Boeing SB 737-53-1256.Revised airplane applicability for PSE Nos. 53-10-04-2 and 53-10-04-4 for airplanes L/N 1 to 1388.Added PSE Nos 53-10-04-2a and 53-10-04-4a due to cab window forging material changes applicable to L/N 1389 and On. (FAA Project TD7471SE-T).Revised PSE Nos. 53-10-04-6 based on recent material data obtained from testing.

Revised the language in Section D. “AIRWORTHINESS LIMITATIONS - SYSTEMS" to provide clarification regarding special flight permits for 737-900 airplanes and 737-800 airplanes with winglets and to provide clarification regarding the applicable configuration for 737-700IGW airplanes with CFM56-7B27A engines.

Submitted by: S. Pierini (Boeing) Appro

DECEMBER 2004Added PSE 55-10-07-3 pertaining to the horizontal stabilizer side of body and bolts (FAA Project #TD8823SE-T).Deleted PSE 53-80-01-14 due to production changes to be accomplished to the bulkhead, through (FAA Project #TD7775SE-T). Prior airplane inspections will continue to be required by Service Bulletin 737-53A1253.

Submitted by: G. Palafox (Boeing) Appro

MAY 2005Revised reference to D626A001-DTR revision date from "July 2004" to "December 2004" in paragraphs "Repeat Inspection Interval" and in "Reporting Results of Structural Inspections".Added additional Special Inspections that are required inspection of the Horizontal Stabilizer Front Spar Attachment Bolts and Rear Spar Attachment Pins.Added PSE 55-10-05-3 for horizontal stabilizer rear spar terminal fitting, side of body pins.

Submitted by: B. McLoughlin (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

JULY 2005Revised reference to D626A001-DTR revision date from "December 2004" to "June 2005" in paragraphs "Repeat Inspection Interval" and in "Reporting Results of Structural Inspections".Revised Special Structural Inspections for the Horizontal Stabilizer Front Spar Attachment Bolts and Rear Spar Attachment Pins. Included inspections for L/N 1-1634 (Front Spar Bolts) and L/N 1-1724 (Rear Spar Pins).Deleted PSE 53-80-01-5 and replaced with PSE's 53-80-01-5A and 53-80-01-5B.Added PSE 53-80-01-14 for oil can inspection for Line Number 1756 and on at 36,000 cycles.Revised paragraph D. Airworthiness Limitation Systems for oil consumption on engines CFM56-7B27A from 0.19 gallons per hour to 0.25 gallon per hour.Revised PSE 53-40-16-2 threshold from 65000 to 56000 due to typographical error.

Submitted by: B. McLoughlin (Boeing) Appro

NOVEMBER 2005Added heading for Engine Oil Consumption Limitation for clarity.Added Nitrogen Generation System Airworthiness Limitations, including inspection and design limitations.

Submitted by: S. Pierini (Boeing) Appro

DECEMBER 2005Added new Fuel System Airworthiness Limitations section which includes an inspection of the center tank auto shutoff system.Deleted 28-CMR-03 and replaced it with 28-AWL-19 to support SFAR 88 requirements.

Submitted by: S. Pierini (Boeing) Appro

JANUARY 2006Added three new Airworthiness Limitations: 1. Hot Short Protection Design Limitation2. Motor Operated Valve Actuator Installation Limitation3. Motor Operated Valve Actuator Repair Limitation.

Submitted by: S. Pierini (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

MARCH 2006Added seventeen Fuel System Airworthiness Limitations to satisfy SFAR 88 requirements.Revised 28-AWL-21 to clarify bonding measurement location in Step 1.f.

Submitted by: G. Palafox (Boeing) Appro

MAY 2006Added Pump Power Failed On protection system inspection 28-AWL-23.Revised 47-AWL-01, 47-AWL-02, 47-AWL-03, and 47-AWL-04 to correct airplane applicability.

Submitted by: G. Palafox (Boeing) Appro

OCTOBER 2006Revised 28-AWL-21 to ensure that all motor operated valve configurations are addressed.Added new motor operated valve inspection number 28-AWL-24 applicable to airplanes Line Number 1877 through 1980, 1982, and airplanes that have incorporated Service Bulletin 737-28A1207.Added a functional check of the auxiliary fuel tank boost pump ground fault interrupter system number 28-AWL-20. Applicable to 737-600, -700, -700C, -800, and -900 airplanes starting with L/N 1978 and airplanes that have incorporated Service Bulletin737-28A1201.Revised 28-AWL-07 to clarify bonding measurement location.

Submitted by: S. Pierini (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

NOVEMBER 2006Revised THRESHOLD airplane applicability to include 737-800 FPB (Flat Pressure Bulkhead).Revised REPEAT INSPECTION INTERVAL to change DTR Document revision date from June 2005 to November 2006.Revised document to include PSEs for the new -800 Flat Aft Pressure Bulkhead and associated structural changes for units which incorporate this option. A conservative interim threshold of 10,000 cycles was specified for these PSEs. These thresholds are currently the subject of regulatory review and will be increased at the completion of this review.Revised the threshold for all fuselage and pressurized door structure (ATA 53 and 52, respectively) from 56,000 cycles to 50,000 cycles in response to regulatory guidance and to reflect that most flights will be at full cabin pressure of 8.35 PSID.

Submitted by: S. Pierini (Boeing) Appro

NOVEMBER 2006 R1Added text to A. Scope section in front matter, titled "Limitations Due to Increased Cabin Pressure". This is in reference to BBJ operators that incorporate SB 737-21-1149 to increase 

the internal cabin pressure.Added Table 9-3 for BBJ operators that incorporate SB 737-21-1149 to increase the internal cabin pressure.

Submitted by: S. Pierini (Boeing) Appro

 

MARCH 2007Removed -700C, -700IGW and -900ER in the text throughout the document as it is called out in the Applicability section.Revised applicability of individual Airworthiness Limitations tasks to replace “737/-600/-700/-800/-900” with “All”.Revised 28-AWL-20 interval from 3 years to 1 year based on Ground fault interrupter relay supplier reliability data, and task was changed from Functional to Operational. Also revised applicability to show new line position for production incorporation of the ground fault interrupter relay. The applicability was changed from L/N 1978 to 2210.

Submitted by: S. Pierini (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

MARCH 2007 R1Added 26-CMR-01 to perform a detailed inspection of the center wing rear spar vapor web (fiberglass panels only) from inside the main gear wheel well.

Submitted by: S. Pierini (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

MARCH 2007 R2Revised A. Scope.Table 9-2, PSEs 57-20-04, 57-20-05, 57-20-16, 57-20-17, 57-20-29 and 57-31-02 have a note added that clarifies the effectivity for winglet installations on the 737-700 and 737-800.This revision also consists of changes that are for the 737-900ER wing, conservative inspection threshold information that is provided in B. Introduction and by Flag Note for specific 57-XX-XX PSEs in Table 9-2.Changed Special Structural Instructions to Special Structural Inspections.Revised PSEs in Table 9.2 to include -900ER effectivity as appropriate.Revised PSE 53-10-12-1 DTR Check Form Title and Location Description.Revised PSE 53-30-04-3 to remove statement “Also: PSE 53-40-03-3 Sta 540 to 727”.Added PSE 53-30-08-11, new forward cargo door upper sill inspection.Revised PSE 53-40-03-3 to remove statement from Location Description “See Entry and DTR Form for PSE 53-30-04-3” and added “S-10L and S-10R, Sta 540 to 727 Upper Fastener Row, Upper Skin” to Location column.Revised PSE 53-40-16-3 to correct airplane applicability.Added PSE 53-40-19-3a, new landing gear support frame, Sta 716 inspection.Added PSE 53-60-08-11, new aft cargo door upper sill inspection.Added PSE 53-60-12-3 for new mid exit door surround upper main sill.Added PSE 53-60-13-1 for new mid exit door surround stop fittings.Revised PSEs 57-20-02, 57-20-03 and 57-20-09 to change the effectivity/thresholds by eliminating the 30,000 cycle/30,000 flight hour threshold for airplanes affected by Service Bulletin 737-57-1275 (AD 2005-24-03).Added paragraph for the maximum oil consumption rate for the CFM56-7B engines installed on the model 737-900ER in (Section D. AIRWORTHINESS LIMITATIONS - SYSTEMS).Added CMR 27-CMR-11 and 27-CMR-12, related to the 737-900ER airplanes.

Submitted by: B. McLoughlin (Boeing) Appro

 

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

FEBRUARY 2008Revised PSE 53-40-03-3 by adding the threshold of 50000 cycles.Revised PSE 53-80-01-14 airplane applicability from L/N 1057 and on to L/N 1756 and on.Added new PSE 57-20-29 applicable to airplanes 700/800 line numbers 2566 and on with winglets installed due to re-design and material changes.Revised Section E. Exceptional Short-Term Extensions to clarify process and notification requirements.Revised the title of Section F. to read Fuel System Airworthiness Limitations.Revised AWL 28-AWL-20 airplane Applicability from L/N 2210 and on to Airplanes 1981, 2093, 2210 and on and airplanes that have incorporated Service Bulletin 737-28A1201 and revised AMM reference from 28-22-00 to 28-22-41.Revised 47-AWL-01 and 47-AWL-02 airplane applicability to include airplanes 2517, 2620 and on.Revised 47-AWL-04 airplane applicability to include airplanes 2517, 2620 and on and revised interval from 9,675 Hrs to 22,500 Hrs.Added new 47-AWL-05 task for Lightning Protection Shields Addition around Flame Arrestor.Revised Section I. Certification Maintenance Requirements (CMRs) - Exception Short-Term Extensions to clarify process and notification requirements.Revised CMR 26-CMR-01 airplane applicability from L/Ns 2093, 2216 and on to airplanes L/Ns 2093, 2216 through 2218, with excluding airplane L/N 2285. Added note for airplane that incorporated SB 737-57-1298 to use CMR 26-CMR-02. Added new CMR 26-CMR-02 for airplane L/Ns 2285, 2319 and on and for airplanes that have incorporated SB 737-57-1298. Revised Section K. Reporting Uncontrollable High Thrust Failure Conditions to incorporate “Reporting Uncontrolled High Thrust Failure Conditions” per FAR 121.703 and FAR 135.415.

Submitted by: B. McLoughlin (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

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.Revised 28-AWL-06 to add an additional CMM reference 28-41-73 Rev 3 to task.Revised 28-AWL-07 applicability by adding "equipped with densitometer" to clarify applicability.Revised 28-AWL-08 to add revision levels to the CMM references.Revised 28-AWL-13 to add CMM numbers in order to include the airplanes delivered with the original pumps.Revised 28-AWL-17 to change the fay surface bond limit call out for the pressure relief valve from 1 ohm or less to 0.010 ohm (10 milliohms) or less.

Submitted by: J. Sabolchy (Boeing) Appro

 

APRIL 2008Added information to Section B., AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS regarding the conservative inspection threshold for the 737-900ER and fuselage skin under the wing-to-body fairings.Added PSE Item Numbers 53-30-02-4 and 53-60-02-4, Fuselage Side Skin Panels Under the Wing-to-Body Fairing to Table 9-2, Airworthiness Limitations - Structural Inspections.

Submitted by: J. Onorati (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

JUNE 2008Revised applicability of 28-CMR-01 and 28-CMR-02 to indicate the task is applicable only to fuel pumps which are installed without Fuel Pump Ground Fault Interrupter.

Submitted by: J. Onorati (Boeing) Appro

FEBRUARY 2009Revised Section B. Introduction, to remove the conservative threshold for the Wing-to-Body fairings for the 737-900ER.Revised title of "Special Structural Instructions" to "Special Structural Inspections".Revised Tables 9-2 and 9-3 Airworthiness Limitations - Structural Inspections as a result of a reassessment of the fuselage and empennage items for the 737-900ER.Revised Tables 9-2 and 9-3 by adding note to declare the operational limit imposed by some tasks pending validation, publication, and regulatory acceptance of the associated inspection procedures.

Submitted by: R. Robinson (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

MARCH 2009Added information to Section A., SCOPE, and Section B., AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS to include applicability to the 737-900ER Boeing Business Jet 3 (BBJ3).Added information to Section B., AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS regarding the inspection threshold and specialized DTR Check Forms for Airworthiness Limitations pertaining to the wing of the 737-900ER (BBJ3) airplanes that incorporated SB 737-21-1149.Added information to Flag Note for Table 9.2 AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS to incorporate the inspection threshold and specialized DTR Check Forms pertaining to the wing of the 737-900ER (BBJ3) airplanes that incorporated SB 737-21-1149.Revised Table 9.3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-21-1149 to include applicability of select DTR Check Forms to model 737-900ER BBJ3.Added Principal Structural Elements (PSEs) and associated DTR inspection details to Table 9.3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-21-1149 applicable to model 737-900ER BBJ3.

Submitted by: R. Robinson (Boeing) Appro

AUGUST 2009Added information regarding removal of excess sealant when performing inspections.

Submitted by: J. Onorati (Boeing)

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

SEPTEMBER 2009Revised Tables 9-2 and 9-3 to include reference to SB 737-53-1300.Revised Table 9-3 by adding note requiring supplemental inspections for certain PSEs that have escalated the Baseline Structures Program.

Submitted by: R. Robinson (Boeing) Appro

NOVEMBER 2009Added information to Section A, SCOPE, AIRWORTHINESS LIMITATIONS-STRUCTURAL 

INSPECTIONS, regarding the inspection thresholds resulting from factory installation of 

winglets for the 737-700IGW airplanes.Revised Table 9-2 by adding and updating notes to declare operational limit imposed by factory installed winglets for the 737-700IGW airplanes.Added paragraph to Section D, AIRWORTHINESS LIMITATIONS - SYSTEMS for the maximum oil consumption rate for the CFM56-7B27A Engines, with no auxiliary fuel tanks installed, for the 737-700IGW (BBJ) model.

Submitted by: R. Robinson (Boeing) Appr

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

JANUARY 2010Revised Paragraph A. Scope to update applicability statements to reference model derivatives and to add the 737-900ER in the Table 9-2 reference.Revised paragraph in the Airworthiness Limitations - Structural Inspections introduction to remove inspection limitations for 737-900ER.Revised front matter section “Repeat Inspection Interval” to remove obsolete wording regarding blank DTR forms.Revised Table 9-2 Airworthiness Limitations - Structural Inspections as a result of a reassessment of the wing and empennage items for the 737-900ER.Revised Table 9-2 by adding a note to declare the inspection threshold and specialized DTR Check Forms pertaining to the wing of the 737-900ER (BBJ3) airplanes that incorporated SB 737-21-1149.Revised Table 9-2 to increase conservative thresholds on the flat pressure bulkhead PSEs from 10,000 cycles to 50,000 cycles.Deleted information to Flag Note 1 for Table 9-2 to remove the inspection threshold limitations for the 737-900ER wing.Revised Table 9-3 information in several ATA 53 PSEs to maintain consistency with similar 

items in Table 9-2.Revised 26-CMR-02 to reference correct AMM task procedure.

Submitted by: J. Onorati (Boeing) Appr

MAY 2010Revised Paragraph A. Scope to include applicability to the 737-700C TC Winglet airplanes.Revised Table 9-2, Airworthiness Limitations – Structural Inspections, by updating Notes to declare the operational limit imposed by factory installed winglets for the 737-700C airplanes.

Submitted by: R. Robinson (Boeing) Appro

Boein(BAS

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

JULY 2010Revised the Life Limits in Section C for the Main Landing Gear and Main Landing Gear Support Structure from 45,000 to 75,000 landings.Revised Airworthiness Limitations - Structural Safe Life Parts [1] to update document D101A801-14 to document D101A805-14.Revised Airworthiness Limitations - Structural Safe Life Parts [2] to state the threshold limitation for the Hanger Link Pin (115A1610).

Submitted by: R. Robinson (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

AUGUST 2010Revised Section H. Airworthiness Limitations – Nitrogen Generation System ALIs and CDCCLs by adding the "Final Flammability Rule, Paragraph III (F), Section 7, Paragraph M25.4 (a)" clarifying the compliance measures provided in the subsequent AWLs.Revised 47-AWL-01 by updating the Applicability column to change the affected line numbers and include airplanes that have incorporated Service Bulletin 737-47-1002, by changing the title to replace FRS with NGS, by removing filament heating from the concern, by replacing the text "per AMM 47-21-07" with "(refer to Boeing AMM 47-21-07)", by refining the necessary conditions for maintenance of the bulkhead fitting and those corresponding maintenance actions, and by adding a note to declare that any change to the bulkhead fitting requires approval by the Seattle FAA ACO.Revised 47-AWL-02 and 47-AWL-04 by updating the Applicability column to include airplanes that have incorporated Service Bulletin 737-47-1003.Deleted 47-AWL-03 because it is no longer applicable to the subject airplanes.Revised 47-AWL-05 by updating the Applicability column to include airplanes that have incorporated Service Bulletin 737-47-1003, by replacing the text "per AMM 47-21-08" with "(refer to Boeing AMM 47-21-08)", and by adding the text "or reinstalled".Added 47-AWL-06, a 13,000 Flight Hour Operational Check of the Nitrogen Generation System Cross-Vent Check Valve.Added 47-AWL-07, a 6500 Flight Hour Inspection of the Nitrogen Generation System NEA Distribution Ducting.Added 47-AWL-08, 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: R. Robinson (Boeing) Appro

 

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

FEBRUARY 2011Revised Section B by deleting the blank page following Figures 1 and 2.Revised Section B by moving the Threshold Airplane Effectivity Line Number-specific information before the Figures to provide better data flow in the Threshold section.Revised paragraph in Section B by deleting incorrect page number references for the locations of Figures 1 and 2.Revised Section E by adding Sections E. 1. AWLs – FUEL SYSTEMS ALIs AND CDCCLs which contains the information formerly found in Section G (now reassigned) and E.2 AWLs – OTHER.Revised the INTRODUCTION subsection of Section E by adding specification that AWLs may include Operational Checks (OPCs) and by clarifying the usage of the term “maintenance” in 

CDCCLs.Revised the USE OF ALTERNATE TOOLS paragraph to specify conditions for permissible use of alternate tools, test equipment, or materials.Revised the EXCEPTIONAL SHORT-TERM EXTENSIONS paragraph by updating “Flight Standards Handbook 8300.10" to "Flight Standards Handbook 8900.1 FSIMS" to reflect the current reference.Revised Section F. PAGE FORMAT: AWLs – FUEL SYSTEMS table by making it a subheading of Section E, adding Operational Check (OPC), and then relettering the following headings accordingly.Revised AWLs by replacing the word "per" with "refer to", wherever applicable.Revised 28-AWL-07, 28-AWL-11, 28-AWL-15, 28-AWL-19, 28-AWL-20, and 28-AWL-22 through 28-AWL-24 to clarify the airplane applicability.Revised 28-AWL-01 to clarify the inspection required and added an inspection of the wire sleeving, if installed.Revised 28-AWL-02 to clarify which design features must be maintained.Revised 28-AWL-03 to clarify the functional check that must be performed and the ohm limit requirements.

(Continued on next page)

Submitted by: Mark Arnold (Boeing) Appr

  

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

FEBRUARY 2011, ContinuedRevised 28-AWL-04 to clarify which design features must be maintained, dependent on the disruption of the ground path of each specified connector.Revised 28-AWL-05 by replacing "EMI" with "EME" and deleting "outside of the tank". In addition, specified that new wiring is to be within 6.5 inches of FQIS wiring. Clarified wire spacing requirements and limitations for new and/or repaired/replaced wiring.Revised 28-AWL-06, 28-AWL-08, and 28-AWL-13 to clarify the component vendor and applicable Component Maintenance Manual revision.Revised 28-AWL-07 to clarify this CDCCL is applicable during installation of the Hot Short Protector and defined the features to maintain during installation. Added reference to Goodrich CMM 28-41-24 for testing.Revised 28-AWL-09 to clarify that repair and overhaul of the FQIS in-tank wire harnesses must be Seattle FAA ACO approved and defined what design features must be maintained when installing the FQIS spar penetration connector.Revised 28-AWL-10 to clarify what design features must be maintained if the bulkhead fitting is removed and replaced.Revised 28-AWL-11 to clarify what design features must be maintained if the bulkhead fitting or attached tubing is removed or replaced.Revised 28-AWL-12 to clarify the maintenance actions requiring approval by the Seattle FAA ACO, and to specify installation requirements that accompany those actions.Revised the title for 28-AWL-14 from "AC Fuel Pump Fault Current Bonding Strap Installation" to "AC Fuel Pump Fault Current Bonding Jumper Installation", replaced "straps" with "jumpers", and clarified what design features must be maintained during pump replacement.Revised 28-AWL-15 to define what design features must be met during float switch replacement.Revised the title of 28-AWL-16 from "Fuel Tank Access Doors - Lightning Protection Bond" to “Fuel Tank Access Doors - Lightning Protection"; clarified door position numbers that require maintenance action during fuel tank access door installation, and added requirements for when using a used gasket that is greater than five years old and the torque values when installing fuel tank access doors.

(Continued on next page)

(Continued from previous page) (

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

FEBRUARY 2011, ContinuedRevised the title of 28-AWL-17 from "Surge Tank Access Doors (533BB and 633BB) - Lightning Protection Bond" to "Surge Tank Access Doors (533BB and 633BB) - Lightning Protection", and added fastener and torque requirements.Revised 28-AWL-18 to clarify what must be accomplished prior to resetting the circuit breaker(s) or GFIs.Revised 28-AWL-21 by adding "CDCCL" to the Task column. Clarified what design features must be maintained when the Spar Valve adapter plate, Spar Valve index, Spar Valve actuator, Cross-feed Valve adapter plate, Cross-feed index plate, or Cross-feed Valve actuator is removed and replaced for 737-600, -700, -700C, -700IGW, -800, and -900 airplanes starting with Line Numbers 1877 thru 1980, 1982, and airplanes that have incorporated Service Bulletin 737-28A1207. Clarified what must be maintained when the adapter plate, index plate, or actuator is removed and replaced for 737-600, -700, -700C, 

-700IGW, -800,-900 airplanes; Line Number 1981, and airplanes starting with Line Number 1983 and on.Revised the title of 28-AWL-22 from "Motor Operated Valve (MOV) Actuator - Repaired" to "Motor Operated Valve (MOV) Actuator - Removed or Repaired" and added "if the actuator was removed or repaired" and Vendor Code V73760.Revised 28-AWL-24 to clarify the functional check that is required.Added AWL Number 28-AWL-101, instructions to do an Engine Fuel Suction Feed Operational Test.Revised old Section J. PAGE FORMAT: CERTIFICATION MAINTENANCE REQUIREMENTS by making it a subheading of the new Section G.Revised the Airplane Applicability for 27-CMR-05 and 27-CMR-06 from “-900 L/N 683 to 1174” to “Note” and added the following Applicability Note: “Applicable to 737-900 airplanes, L/N 683 to 1174, that have not incorporated SB 737-55-1081” to clarify airplane applicability.Revised 47-AWL-07 by changing AMM reference from 47-21-00 to 41-00-00 to provide more applicable instructions for the associated maintenance procedure.

(Continued from previous page) (C

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

MARCH 2011Revised Section A. Scope by adding information on a production change that has been incorporated to increase the thickness of the horizontal stabilizer inspar lower skin, which affects all 737-600/700/700C/800/900ER models.Revised Table 9-2 - Airworthiness Limitations - Structural Inspections by adding a flag note (<4>) to selected 55-10 PSE items, which concerns the inspection threshold for airplanes with 

a redesigned horizontal stabilizer inspar lower skin.Revised subsections of Section E, INTRODUCTION and PAGE FORMAT: AWLs – FUEL SYSTEMS by removing references to Operational Checks (OPCs) as a specific type of 

Airworthiness Limitation (AWL).Revised Section E.2 – Other by deleting the text referencing Title 14 Code of Federal Regulations § 25.1301(a) and § 25.1309(b) and replacing it with the following: “This section of the AWLs contains FAA-approved scheduled inspections and design limitations for operators to incorporate into their maintenance program.”Revised 28-AWL-101 by changing the task type from an Operational Check (OPC) to an Airworthiness Limitation Instruction (ALI).

Submitted by: Ryder Robinson (Boeing)

Appro 

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

JUNE 2011Revised statement referring to DTR document D626A001-DTR by removing revision date as the Discrepant Structure Report Form can be used from any DTR document revision.Revised flagnote descriptions in Table 9-2 to replace "factory installed winglets" with "production installed winglets" for reference consistency.Revised text and organization in document Sections A and B (and elsewhere) to comply with FAA formatting specifications, including, but not limited to:Revised references to 737 Next Generation major models from "737-600/700/800/900" to read "737-600/700/700C/800/900/900ER" to include -700C and -900ER as specific configurations.Revised references to Federal Aviation Regulations (FARs) to more correctly cite the United 

States Code of Federal Regulations (CFR) Title 14.Revised Section A. SCOPE by relocating the document effectivity information for airplanes with production installed winglets into a new Table 9-1 within Section B. AWLs - STRUCTURAL INSPECTIONS.Revised Section A. SCOPE by relocating information specific to airplanes with conservative inspection thresholds on certain structural elements and airplanes that have incorporated Service Bulletin 737-21-1149 for Lower Cabin Altitude (LCA) to Section B.Added paragraph to Section B to address accountability for the cumulative operational usage of Removable Structural Components.Added paragraph to Section B to reference a new Appendix J to the MPD which contains the original task intervals for scheduled maintenance items which now use intervals escalated by the Industry Steering Committee but which must be reverted to meet Damage Tolerance requirements. (Continued on next page)

Submitted by: Ryder Robinson (Boeing)

Appro 

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

AUG 2012
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

JUNE 2011, ContinuedRevised Table 9-2 by changing number and format of item flag "(1)" to "<5>" to distinguish the marker and maintain document consistency.Revised Table 9-3 by changing number and format of item flag "(1)" to "<2>" to distinguish the marker and maintain document consistency, and by eliminating applicability references to "BBJ (Boeing Business Jet)", which is not a certified type designation. Revised Section B by eliminating requirements for removal of excess sealant for all airplanes except those modified for LCA and by adding and eliminating inspection requirements for the horizontal stabilizer front spar attachment bolts and rear spar attachment pins.Revised Table 9.2 by incorporating new and revised Principal Structural Elements (PSEs) and associated inspections, DTR references, and threshold/interval data resulting from new certification data regarding excess production sealant application and from a reassessment of the horizontal stabilizer damage tolerance analysis.

(Continued from previous page) (

JULY 2011Revised 47-AWL-02 to incorporate NGS performance features to show compliance with 14 CFR 26.33.

Submitted by: Mark Arnold (Boeing)

Appr  

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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AUGUST 2011Revised Section D. Airworthiness Limitations – Systems to arrange the limitations for affected aircraft in numerical order of minor-model for ease of reference.Deleted 26-CMR-01 as all potentially affected aircraft have either demonstrated freedom from the design concern or have implemented repairs that impose alternate inspection limits, and therefore should only be subject to the requirements of 26-CMR-02.Revised 26-CMR-02 to extend the applicability to include aircraft formerly exempt by being subject to 26-CMR-01, now deleted. Also removed reference to Service Bulletin 737-57-1298 as the bulletin was canceled prior to release.Deleted secondary listing of 27-CMR-04 from the end of the CMR Task Table and incorporated the maintenance requirement details and the accompanying Applicability Note within the primary listing.

Submitted by: Ryder Robinson (Boeing)

Appr 

OCTOBER 2011Revised Section B. AWLs - Structural Inspections by revising 737-IGW to 737-700IGW to provide clarification that the IGW is a 737-700. Removed reference to winglet provisioning which clarifies that the limitation is against the wingleted aircraft. Removed reference to wing from conservative threshold limits since that analysis has been completed. Replaced reference to Note <5> with Note <1> to correspond to changes in Table 9-2. Revised horizontal stabilizer rear spar pin part numbers. Removed paragraph giving conservative inspection thresholds for the 737-900ER with LCA modification.Revised Table 9-2 by removing flag <1> from PSEs 57-10-01 through 57-70-01 to remove the life limits for the LCA modification on the 737-900ER and the life limit for the wing for 737-700C and 737-700IGW aircraft with production installed winglets.Revised Table 9-2, Note <1> with Note <5> wording "These PSE's require supplemental inspections only if the Baseline Structures Program has been escalated." Deleted Note <5> from the Notes list since it was moved to Note <1>. All previous Note <5> references were updated to Note <1> to realign for clarity.

Submitted by: Ryder Robinson (Boeing)

Appro  

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DECEMBER 2011Revised Table 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-21-1149 to incorporate changes affected by excess sealant application.

Submitted by: Teja Singh (Boeing)

AUGUST 2012Revised the title for Section E.2 from “AWLs – Other” to “ENGINE FUEL SUCTION FEED SYSTEM”.Revised Section E.2 front matter by adding the regulation Title 14 CFR § 25.951 requiring the engine fuel suction feed test. Provided the background and technical reason why the engine fuel suction feed test is a mandatory maintenance requirement.Revised 28-AWL-101 to revise the interval to "7500 FH or 3 yrs, whichever occurs first" to cover lower utilization operators and revise the center tank fuel quantity requirement. Added a notation that the excess fuel can be transferred to the opposite main tank to avoid defueling. Added a notation that the APU may be used to start the engine. Added clarification that a suction fuel feed system failing the operational test must be repaired and successfully pass the operational test prior to further flight.

Submitted by: Cassandra Ho  (Boeing)

REVISIONS

REVISION AND REVISION DESCRIPTION APPROVAL

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A. SCOPE

The information described in this section is for airplane models 737-600/700/700C/800/900/900ER and all derivatives.

The scheduled maintenance requirements described in this section result from all 737-600/700/700C/800/900/900ER and deriv

activities with the U.S. Federal Aviation Administration (FAA). Accordingly, this FAA approved Airworthiness Limitations (AWLs

Maintenance Requirements (CMRs) document is cross-referenced in the Model 737 Type Certificate Data Sheet, A16WE. This requirements of United States Code of Federal Regulations (CFR) Title 14, 25.571 and 25.1529 and Advisory Circular (AC) 25-document for all 737-600/700/700C/800/900/900ER AWLs and CMRs. These maintenance actions are mandatory.The Airworthiness Limitations Section is FAA approved and specifies maintenance required under Federal Aviation Regulation 

91.403 unless an alternative program has been FAA approved.AIRWORTHINESS LIMITATIONS (AWLs)The Airworthiness Limitations (Structural Inspections and Safe Life Limitations) may only be revised with the approval of the SeIf the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection must be approved by the 

B. AWLs – STRUCTURAL INSPECTIONS

INTRODUCTIONThe scheduled maintenance requirements described in this section are applicable to all 737-600/700/700C/800/900/900ER airp

derivatives. This section is also applicable to 737-700/700C/800/900ER aircraft that have winglets installed in the factory as id

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

The 737-600/700/800/900 Maintenance Review Board (MRB) Report outlines the initial minimum scheduled maintenance/inspe(hereafter referred to as the baseline program) for all structure, including all Principal Structural Elements (PSEs). This baselinin accordance with the guidelines of MSG-3 and satisfies requirements of CFR Title 14, 25.571 and 25.1529 by providing accidfatigue damage detection opportunity for all PSEs. In order to fully comply with the requirements of CFR Title 14, 25.571 the su

inspections defined herein, are required to be accomplished prior to the stated threshold. These supplemental inspections conthe baseline program found in the MRBR satisfy the certification requirements of CFR Title 14, 25.571 and 25.1529.The baseline program defines the inspection task as one that includes accomplishment of the CPCP Basic Task at all initial an

noted otherwise. It is a requirement of this section that all structure identified in Section 3 of the 737-600/700/800/900 MRB Reuse of a Corrosion Prevention and Control Program. The objective of the CPCP is to control corrosion to Level 1 or better.

TABLE 9-1 737 MODELS WITH PRODUCTION INSTALLED WINGLETS COVERED BY THIS DOCUM

MODEL LINE NUMBERS WING WIN

737-700b 1545 and on Yes 

737-700IGW 3128 and on Yes Y

737-700C 3346 and on Yes Y

737-800 778 and on Yes Y

737-900ER All Yes Y

a. Aircraft modified to install winglets via Supplemental Type Certificate (STC) are covered by information obtained from t

holder; refer to the applicable STC holder’s Maintenance Planning Document Supplement for maintenance requirements to those provided in this section.b. The 737-700 models that had winglets installed in production have a split certification responsibility. Refer to the appliholder’s Maintenance Planning Document Supplement for maintenance requirements in addition to those provided in this 

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This section does not prohibit escalation of the baseline program. The baseline program defined in the MRB Report is intended 

establishing initial inspection requirements for new operators’ maintenance programs. Initial adjustments may be necessary to 

environmental conditions unique to the operator. As operating experience is accumulated, additional adjustments may be mad

FAA Principal Maintenance Inspector (PMI) approval in accordance with CFR Title 14, Part 121 in order to maintain an efficient program.The fuselage and empennage structure of the 737-600/700/700IGW/800 is not significantly modified from the 737-300/400/500 

14, 25.571, Amendment 0. Although a damage tolerance analysis is not required for certification of the fuselage and empennathat a supplemental structural inspection program (based on a damage tolerance assessment) be developed for structure certifCFR Title 14, 25.571. The 737-700C and 737-900/900ER are certified to CFR Title 14, 25.571, Amendment 86.THRESHOLDTable 9-2 of this section defines the supplemental inspection implementation threshold. Each item is listed by PSE Number, D

Location, Inspection Zone, Airplane Applicability, and Threshold. Where there is more than one listing for a given PSE Number

and Location are the unique identifiers. Airplane applicability as listed is shown below.

ALL - 737-600/700/700C/700IGW/800/900/900ER

-600 - 737-600-700 - 737-700-700C - 737-700C (Convertible)-700IGW - 737-700IGW (Increased Gross Weight - Any 737-700 Airplane greater than 155,000 lbs Maximum T

-800 - 737-800-800FPB - 737-800FPB (Flat Pressure Bulkhead)-900 - 737-900-900ER - 737-900ER (Extended Range)

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

For all model 737-600/700/700C/800/900ER airplanes Line Numbers 3624 and on: A production change has been incorporated of the horizontal stabilizer inspar lower skin. At the time of initial certification of this production change, the Airworthiness Limita

stabilizer have been established by requiring a conservative inspection threshold on an initial list of PSEs.For all model 737-700C airplanes, Line Number 3346 and on, and all model 737-700IGW airplanes, Line Number 3128 and onequipped with winglets as an original factory installation, at the time of initial certification of the winglets, the Airworthiness Limit

stabilizer have been established by requiring a conservative inspection threshold on an initial list of PSEs.The inspection threshold for the subject PSEs on the affected 737-600/700/700C/800/900ER and 737-700IGW airplanes descr

cycles or 20,000 flight hours, whichever occurs first. Operators are instructed to contact Boeing for FAA approved inspections w

inspection threshold.The initial supplemental inspections must be accomplished prior to the cycle and/or hour threshold listed (prior to the first occur

sensitive to flight length and are identified by FLS (Flight Length Sensitive) in the Threshold column of the table. FLS items req

flight cycles to determine the implementation threshold. Refer to Figures 9-1 and 9-2 (as directed by Table 9-2 for a given PSE

for FLS items.Instructions for the use of FLS Threshold Curve:1. Determine, for each airplane, the accumulated flight cycles and flight hours.2. Enter the FLS threshold curve at the appropriate flight cycles and flight hours and plot point.3. The initial supplemental inspection must be accomplished before crossing into the shaded area on the FLS threshold curveInitial inspection (threshold) and intervals are measured in flight cycles or flight hours that a particular PSE detail has accumula

airframe as a whole has accumulated. Most PSE details have never been replaced and therefore have accumulated the same 

as the airframe. Some PSE details are replaced, such as when installing Removable Structural Components (repairable/rotablused structural parts as a repair. In these cases the PSE details have accumulated flight cycles and flight hours that may be di

The operator must account for this in determining when inspections must be done. In determining the PSE flight cycles or fligh

processes defined in AC 120-93.

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FIGURE 9-1. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE (75,000 FLIGHT CYC

Refer to Table 9-2 for applicability

CYCLES (X 1,000)

0

10

8090703050402060

40 60 80 100 120 140 

75

45

FLIGHT HOURS (X 1,000)

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FIGURE 9-2. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE (56,000 FLIGHT CYC

Refer to Table 9-2 for applicability

FLIGHT HOURS (X 1,000)

56

0

10703050402060

20 40 60 80 

100 120 33 75

90

80

CYCLES (X 1,000)

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REPEAT INSPECTION INTERVALThe supplemental structural inspection program uses the Damage Tolerance Rating (DTR) system to determine the inspection

necessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that mPSE. DTR Check Forms, which define the inspection options and the required DTR are contained in D626A001-DTR.

All PSEs that met the DTR requirement through the baseline program have been evaluated for up to 25% escalation of the basintervals. The additional supplemental inspections as a result of the escalation to the baseline program are identified with Note noted supplemental inspections must be accomplished prior to the given threshold if the baseline program is escalated by any 

interval was not considered for escalation and is the maximum interval allowed for supplemental inspections. Where credit for 

Program is taken on a DTR Check Form, the DTR Check Form must be reevaluated and adjusted by the operator (to maintain greater than the required DTR) upon any escalation of the baseline program. If the baseline program flight cycles are escalateSeattle FAA ACO.A repeat inspection interval for the fatigue inspection of a PSE is established from its DTR Check Form. Revision to the requirenot allowed without approval from the Seattle FAA ACO.Some structures and zonal MPD items have been escalated by the Industry Steering Committee beyond the initial repeat intervthe initial aircraft certification. The intervals listed in Appendix J correspond to the original task intervals used in determining th

CFR Part 25.571. As a result, prior to or at the threshold specified in Table 9-2, the items listed in Appendix J are required to bthat appendix, rather than what is listed in Sections 2 and 3 of this MPD.

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SPECIAL STRUCTURAL INSPECTIONSThe following special inspections are required for horizontal stabilizer front spar attachment bolts and rear spar attachment pins

be performed in conjunction with the referenced Section 2 Structural Maintenance Program inspections.Airplane Applicability: All 737-600/700/700C/800/900/900ER airplanes with horizontal stabilizer front spar attachment bolt pa

180A1611-5 and horizontal stabilizer rear spar attachment pin part numbers 180A1612-3, 180A1612-4, 180A1612-7 or 180A16

Task Description: Perform an internal detailed visual inspection of the plating on the horizontal stabilizer attachment bolts and 

or flaking plating. If the plating is missing, cracked or flaking, prior to further flight replace with new parts or repair in accordanc

by an Authorized Representative for the BCA Organization Designation Authorization who has been authorized to make those Section 2 - Structural Maintenance Program, MPD Item Number 55-070-01, 55-070-02, 55-110-01 and 55-110-02. Bolt and pin 

Threshold: 36,000 total aircraft flight cyclesIf any of the subject parts have been replaced with a new part; the threshold for the new part is considered the cycles accumulapart was installed. All other parts shall be inspected at the specified aircraft threshold. Repeat: None.REPORTING RESULTS OF STRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within ten (10) days directly to the Manager of the Seattle FAA ACODirectorate, the FAA, and to Boeing Commercial Airplanes using the Discrepant Structure Report Form. Refer to D626A001-Dform (any suitable alternative which contains the same information may be used).

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737 LOWER CABIN ALTITUDE MODIFICATION - BOEING SB 737-21-1149Certain 737-700IGW/800/900ER airplanes are utilized for private use, where carriage of persons or property for compensation 

are commonly referred to as a Boeing Business Jet (BBJ). These aircraft may be modified with Service Bulletin (SB) 737-21-1

maximum operating cabin pressure from 8.35 psi to 8.99 psi. Operators of BBJ airplanes that have incorporated SB 737-21-1149, in addition to the all previously cited structural inspections

supplemental inspections identified in Table 9-3 of this section. These limitations are permanent for the service life of the airplasubsequent reversion to any lower internal cabin pressure, or removal of SB 737-21-1149, and can only be changed by a compapproved by the manager of the FAA Los Angeles Aircraft Certification Office (ACO).It has been discovered that production sealant application has exceeded specification limits in some locations and the damage 

accounts for the specification maximum amount of sealant. The amount of sealant affects how much of the PSE structure is hiExcessive sealant (beyond specification limits) on PSE structure could affect the damage tolerance analysis results. Therefore 

the dimension limits in AMM 51-31-00, figures 204 and 205, must be removed to within specification for visual inspections prior thresholds:1. A threshold of 28,000 cycles or 50,000 hours, whichever comes first, for baseline maintenance inspections (MPD Section 2 

2. The threshold for each PSE inspection listed in Tables 9-2 and 9-3Refer to AMM 51-31-00 for sealant removal and application.

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TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

52-21-04 Automatic Overwing Door Lower Frame at Stop/Guide Fitting 833/843

832/842

52-32-01 Main Deck Cargo Door Cam Latch Support Fitting under Shear Clip 835 52-32-03 Main Deck Cargo Door Hinge to Skin Connection 835 

52-48-04-2 Electronic Equipment Access Door Bounded by LBL 5.70, RBL 14.12, Frame Sta 325.07 and 

Sta 349.13

117 

53-10-03-1 Longitudinal Lap Splice S-4L & S-4R, Sta 259.5 to 360 Upper Fastener Row, Upper 

Skin. Also: PSE 53-30-04-1 Sta 360 to 540 PSE 53-40-03-1 Sta 540 to 727PSE 53-60-04-1 Sta 727 to 887PSE 53-70-03-1 Sta 887 to 1016

221/222231/232241/242

53-10-03-1a Longitudinal Lap Splice S-4R, Sta 259.5 to 360; S-8L, Sta 259.5 to 294.5, 350 to 360 

Upper Fastener Row, Upper Skin. Also:PSE 53-30-04-1a, S-4R, Sta 360 to 540PSE 53-30-04-1a, S-7L, Sta 500 to 540PSE 53-40-03-1a, S-4L & S-4R, Sta 540 to 727PSE 53-60-04-1a, S-4L & S-4R, Sta 727 to 887PSE 53-70-03-1a, S-4L & S-4R, Sta 887 to 1016

221/222231/232241/242

53-10-03-2 Longitudinal Lap Splice S-4L & S-4R, Sta 259.5 to 360 

Lower Fastener Row, Lower Skin

221/222 

53-10-03-2a Longitudinal Lap Splice S-4R, Sta 259.5 to 360, S-8L, Sta 259.5 to 294.5, and 350 to 

360 Lower Fastener Row, Lower Skin

221/222 

53-10-03-3 Longitudinal Lap Splice S-14L, Sta 259.5 to 294.5, 350 to 360, Upper Row, Upper Skin

S-14R, Sta 259.5 to 277, 344 to 360, Upper Row, Upper Skin

221/222 

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53-10-03-4 Longitudinal Lap Splice S-14L, Sta 259.5 to 294.5, 350 to 360, Lower Row, Lower Skin

S-14R, Sta 259.5 to 277, 344 to 360, Lower Row, Lower Skin

221/222 

53-10-03-5 Longitudinal Lap Splice S-24L Sta 259.5 to 334, & S-24R Sta 259.5 to 360

Upper Fastener Row, Upper Skin

112

113/114 117/118

53-10-04-1 Cutout Crew Cab Windows AB Post 211/212 

53-10-04-1a Cutout Crew Cab Windows (L/N 1389 & on) AB Post 211/212 

53-10-04-2 Cutout Crew Cab Windows CD Post Left and Right 211/212 

53-10-04-2a Cutout Crew Cab Windows CD Post Left and Right 211/212 

53-10-04-3 Cutout Crew Cab Windows EF Post Left and Right 211/212 53-10-04-4 Cutout Crew Cab Windows (L/N 1 to 1388) BD Sill Left and Right 211/212 

53-10-04-4a Cutout Crew Cab Windows (L/N 1389 & on) BD Sill Left and Right 211/212 

53-10-04-5 Cutout Crew Cab Windows Point D Fitting Left and Right Side 211/212 

53-10-04-6 Cutout Crew Cabin Windows X-750 Angle at B-D Sill Inner Chord Left and Right Sides of 

the Aircraft

211/212 

53-10-05-1 Crown Skin Panel - Fwd of Sta 259.5 Longitudinal Splice at BL 0 211/212 53-10-08-1 Crown Skin Panel Sta 259.5 to 360 See Table Entry and DTR Form for PSE 53-30-01-2 221/222 

53-10-12-1 Cutout - Forward Access Door, Forward Edge 

of Cutout

Sta 203.8, BL 16L to BL 16R 112 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

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53-10-13-1 Cutout - Electronic Equipment Door Cutout Bounded by Stations 323.7 & 351.2, and RBL 15.47 

and LBL 6.74

117/118 

53-10-14-4 Cutout - Fwd Entry Door Frame Sta 303.9 from S-11L to S-12L 221 53-10-14-5 Cutout - Fwd Entry Door Frame Sta 303.9 from S-7L to S-11L and S-12L to S-13L 221 

53-10-14-7 Fwd Entry Door Fwd Edge Frame Stops Stop Fittings at S-7 thru S-16 221 

53-10-14-8 Fwd Entry Door Fwd Edge Frame Stops Stop Straps at S-7 thru S-14 221 

53-10-14-9 Fwd Entry Door Fwd Edge Frame Stops Stop Straps at S-15 and S-16 221 

53-10-14-10 Fwd Entry Door Aft Edge Frame Stops S-15 and S-16 Tension Straps at Sta 351.2 Frame Inner Chord 221 53-10-14-11 Fwd Entry Door Aft Edge Frame Stops Aft Frame Stops @ Inner Flange Holes @ Approx. Sta 348.2 

(S-7 to S-14)

221 

53-10-14-12 Forward Entry Door Cutout Lower Edge of Cutout Sta 303 to Sta 350 around and under 

Scuff Plates Also PSE 53-10-15 Forward Galley Door Cutout 

117/221 

53-10-15 Forward Galley Door Cutout See Table Entry and DTR Form for PSE 53-10-14-12 118/222 

53-10-15-2 Forward Galley Door Surround Structure Door 

Stop Backup Structure

Forward Edge Frame at Stops #1, #2, #5, and #6 Intercostal Tension Straps

222 

53-10-15-4 Cutout Fwd Galley Door Sta 291.5 & Sta 328.5, S-8R to S-14R 222 

53-10-18-1 Bulkhead, Sta 294.5 Nose Wheel Well Aft Bulkhead WL 172 Beam at BL 17 115/116

117/118

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

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53-10-19-4 Nose Wheel Well Side and Top Panels Aft Access Cutout Forward Vertical Beam Sta 260, WL 170 to 

WL 184

113/114115/116

53-10-20-2 Nose Landing Gear Support Fittings Drag Brace Fittings, Sta 262, BL 16, WL 189.3 113/114

115/116

53-10-20-3 Nose Landing Gear Trunnion Support Fitting Inboard and Outboard Fitting Segments BS 294.5 WL 156.1 

BL 16

113/114115/116

53-10-21-1 Air Stair Door Cutout Upper and Lower Sills Sta 303.8 to Sta 348 117 53-10-21-4 Air Stair Door Cutout Forward and Aft Edge Frames Sta 303.9 and 351.2 at 

Lower Corners

117 

53-10-23-1 Forward Nose Wheel Well Cutout Outer Chord Sta 224.8 BL 8.45L 112/113 

114

53-30-01-2 Crown Skin Panel Sta 360 to 540 BS 360-540, S-10L to S-10R Also:

PSE 53-10-08-1 Sta 259.5 to 360PSE 53-40-01-1 Sta 540 to 727PSE 53-60-01-2 Sta 727 to 887PSE 53-70-04-1 Sta 887 to 1016

221/222231/232241/242

53-30-01-4 Crown Skin Panel Sta 360 to 540 Antenna Cutouts at Sta 385, Sta 430, Sta 500A 231/232 53-30-01-5 Satcom Aero-H Antenna Installation Sta 500 S-6/S-7 231/232 53-30-02-1 Fuselage Side Skin Panels BS 360 to BS 540, S-14 to S-17 Also:

PSE 53-60-02-1 Sta 727 to Sta 887 

117/118121/122125/126141/142

191194

195/196231/232241/242

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-30-02-4 Fuselage Side Skin Panels Under the Wing-toBody Fairing BS 360 to BS 540, Under Wing-to-Body Fairing. Also: PSE 53-60-02-4, BS 727 to BS 887. 121/122 123/124

125/126141/142143/144191/192

194

53-30-04-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 231/232 

53-30-04-1a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1a 231/232 

53-30-04-2 Longitudinal Lap Splice S-4L & S-4R, Sta 360-540 Lower Fastener Row, Lower Skin. 

Also: PSE 53-40-03-2 Sta 540 to 727 PSE 53-60-04-2 Sta 727 to 887

231/232241/242

53-30-04-2a Longitudinal Lap Splice S-4R, Sta 360 to 540; S-7L, Sta 500 to 540, Lower Fastener 

Row, Lower Skin. Also:PSE 53-40-03-2a, S-4L & S-4R, Sta 540 to 727PSE 53-60-04-2a, S-4L & S-4R, Sta 727 to 887

231/232241/242

53-30-04-3 Longitudinal Skin Splice S-10L & S-10R, Sta 360-540 Upper Fastener Row, Upper Skin. 

Also: PSE 53-60-04-3 Sta 727 to 887 

231/232241/242

53-30-04-3a Longitudinal Skin Splice S-10R, Sta 360-540 Upper Fastener Row, Upper Skin. Also:

PSE 53-40-03-3a, S-10L & S10-R, Sta 540 to 727PSE 53-60-04-3a, S-10L & S-10R Sta 727 to 887

231/232241/242

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-30-04-4 Longitudinal Lap Splice S-10L and S-10R, Sta 360-540 Lower Fastener Row, Lower 

Skin. Also: PSE 53-60-04-4 Sta 727 to 887

231/232241/242

53-30-04-4a Longitudinal Lap Splice S-10R Sta 360 - 540 Lower Fastener Row, Lower Skin. Also:

PSE 53-60-04-4a, S-10L and S-10R, Sta 727 to 887

231/232241/242

53-30-04-5 Longitudinal Lap Splice S-14L & S-14R, Sta 360 to 540 Upper Fastener Row, Upper 

Skin. Also: PSE 53-60-04-5 Sta 727 to 887

231/232241/242

53-30-04-5a Longitudinal Lap Splice S-14R, Sta 360 to 540, S-14L, Sta 500 to 540, Upper Fastener 

Row, Upper Skin. Also:PSE 53-60-04-5a, S-14L & S-14R, Sta 727 to 887

231/232241/242

53-30-04-6 Longitudinal Lap Splice S-14L & S-14R, Sta 360 to 540 Lower Fastener Row, Lower 

Skin. Also: PSE 53-60-04-6 Sta 727 to Sta 887

231/232241/242

53-30-04-6a Longitudinal Lap Splice S-14R, Sta 360 to 540, S-14L, Sta 500 to 540, Lower Fastener 

Row, Lower Skin. Also:PSE 53-60-04-6a, S-14L & S-14R, Sta 727 to 887

231/232241/242

53-30-04-7 Longitudinal Lap Splice S-24L & S-24R, Sta 360 to 540 Except at Cargo Door Cutout. 

Upper Fastener Row, Upper (Inner) Skin 

123/124125/126

191

53-30-04-8 Longitudinal Lap Splice S-24L and S-24R, Sta 360 to 540 Except at Cargo Door Cutout. 

Lower Fastener Row, Lower (Outer) Skin

123/124125/126

191

53-30-05 Window Belt See Table Entry and DTR Form for PSE 53-60-05-2 231/232 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-30-08 Forward Cargo Door Surround Structure See Table Entry and DTR Form for PSE 53-60-08-8 122/124 

53-30-08-1 Forward Cargo Door Surround Forward and Aft Edge Frames at Sta 440 and 492.4 Outer 

Chord Between S-17R and S-26R (Except at Door Stops and Sills Location)

122/124 

53-30-08-2 Forward Cargo Door Surround Forward and Aft Edge Frames at Sta 440 and 492.4 Outer 

Chord at Door Stops Location and at Frame/Sill Intersections

122/124 

53-30-08-3 Forward Cargo Door Surround Forward and Aft Edge Frame Inner Chords Between S-18R 

and S-26R

122/124 

53-30-08-4 Forward Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords Between S-17R 

and S-18R

122 

53-30-08-5 Forward Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords at S-18R 122 

53-30-08-6 Forward Cargo Door Surround Structure Skin Splice at S-24R, BS 440 & 492.4. Also:

PSE 53-60-08 Aft Cargo Door Splices at BS 794.4 and 847

122/124142/144

53-30-08-9 Forward Cargo Door Surround Structure Skin and Bearstrap at Corners of Cutout.

See Table Entry and DTR Form for PSE 53-60-08-9.

122/124142/144

53-30-08-10

<1>

Forward Cargo Door Surround Structure Upper Sill Outer Chord 

Also: PSE 53-60-08 Aft Cargo Door Upper Sill

122/124142/144

53-30-08-11

<1>

Forward Cargo Door Surround Structure See Table Entry and DTR Form for PSE 53-60-08-11 122/124

142/144

53-30-08-12 Forward Cargo Door Surround Structure Lower Main Sill Chords Between Sta 421 & 438 (-600) Lower 

Main Sill Chords Between Sta 461 and 478 (-700/-800) Also:PSE 53-60-08 Aft Cargo Door Surround Structure Lower Sill Sta 807 to 827 

122/124142/144

53-30-09-3 Forward Cargo Door Fittings and Stops at the 

Forward and Aft Edge Frames

Backup Fittings and Intercostals 122 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-30-11-1 Wing to Body Lower Drag Angle BS 518 to BS 555 Above S-24 125/126

131/132

191

53-30-11-02 Wing to Body Upper Drag Angle BS 500D to 550 Between S-21 and S-22 125/126

131/132

191

53-30-11-03 Wing to Body Upper Drag Angle Near BS 540, Between S-21 and S-22 125/126

131/132

191

53-30-12-7 Floor Beam to Frame Joint BS 360 to BS 500; S-17R to 18R 121/122 

53-40-01-1 Crown Skin Panel Sta 540 to 727 See Table Entry and DTR Form for PSE 53-30-01-2 231/232

241/242

53-40-03-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 231/232

241/242

53-40-03-1a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1a 231/232

241/242

53-40-03-2 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-2 231/232

241/242

53-40-03-2a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-2a 231/232

241/242

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-40-03-3 Longitudinal Skin Splice S-10L and S-10R, STA 540 to 727 Upper Fastener Row, 

Upper Skin

231/232241/242

53-40-03-3a Longitudinal Skin Splice See Table Entry and DTR Form for PSE 53-30-04-3a 231/232

241/242

53-40-04-1 Window Belt, Sta 540 to 727 Stringer 11 and Stringer 13 231/232

241/242

53-40-04-2 Window Belt, Sta 540 to 727 Between Windows, S-11 to S-13 231/232

241/242

53-40-07-2 Stringer Splice, Sta 663 Splice at Stringer 11 and Stringer 13 231/232

241/242

53-40-08-1 Keel Beam Chords, Stiffeners and Splice Keel Beam Side Panel Webs Sta 540 to Sta 663 133/134

139

192/193

53-40-10-1 Stiffener Attachment to Floor Beam, Sta 727 LBL 45.5 & RBL 45.5 @ WL 202.6 133/134 53-40-11-1 Stringer 18 Strap Side of Body Sta 717 to Sta 727 133/134

141/142

53-40-12-1 Stringer 18A Chord and Links Sta 663 Link Lugs 131/132

133/134

53-40-14-1 Frame Splice @ BS 540 Inner Chord Between S-8 and S-9 231/232 53-40-14-4 BS 540 Bulkhead Skin at Outer Chord, S-9L to S-9R 231/232 53-40-15-1 BS 663 Bulkhead Outer Chord Between S-8 and S-11 231/232 53-40-15-3 BS 663 Bulkhead Inner Chord Between S-10 and S-17 LH & RH 231/232 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-40-16-1a Aft Wheel Well Bulkhead Sta 727 Outer Chord S-21 to S-27 133/134

141/142143/144

193

53-40-16-1b Aft Wheel Well Bulkhead Sta 727 Outer Chord S-21 to S-27 133/134

141/142143/144

193

53-40-16-2 Wheel Well Aft Bulkhead Frame Inner Chord at Sta 727, WL 201 141/142 

53-40-16-2a Wheel Well Aft Bulkhead Frame Inner Chord at Sta 727, WL 201 141/142 

53-40-16-3 Wheel Well Aft Bulkhead and Pressure Web, 

Sta 727

Lower Frame Sta 727 133/134

141/142

53-40-16-5 Aft Wheel Well Bulkhead and Pressure Web, 

Sta 727

Frame Sta 727, S-9L to S-9R 241/242 

53-40-16-6 Aft Wheel Well Bulkhead Frame Sta 727 Sta 727 Between S-9 and S-10 241/242 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-40-17-1 Side Strut Support Frame Sta 706 Frame Inner & Outer Chords and Fail-Safe Angle S-10 to S-13 241/242 

53-40-18-2 Main Landing Gear Support Frame Sta 695 Stub Beam Upper Chord 133/134

241/242

53-40-19-1 Main Landing Gear Support Frame Sta 716 Frame Inner Chord and Web at S-16 133/134

241/242

53-40-19-2 Main Landing Gear Support Frame Sta 716 Stub Beam Upper Chord at Crease Beam Chord Attachment 133/134

241/242

53-40-19-3 Main Landing Gear Support Frame Sta 716 Stub Beam Web at Floor Clip Attachment 133/134

241/242

53-40-19-3a Main Landing Gear Support Frame STA 716 Horizontal Leg of Frame STA 716, BL 45.5 to BL 64.6 133/134

241/242

53-40-21-2 Wheel Well Frame, Sta 685 Frame Inner Chord S-13 to S-15 133/134

241/242

53-40-21-3 Wheel Well Frame Sta 685 Frame Inner Chord S-17 to S-14 133/134

241/242

53-40-21-4 Wheel Well Frame at Sta 685 Stub Beam Upper Chord 133/134

241/242

53-40-22-1 Overwing Emergency Exit Cutout Edge Frame 616 Outer Chord and Skin Assembly between 

STR 10 and STR 13

231/232 

53-40-22-2 Overwing Emergency Exit Cutout (Inspection 

Applicable Only to 737-700/-700C/-700IGW Cumline Number 9 and on)

Edge Frame Sta 616 Outer Chord, S-10 to S-13 231/232 

53-40-22-3 Overwing Emergency Exit Cutout Skin 

Assembly and Frame Outer Chord (Inspection Applicable Only to 737-800 Cumline Number 9 and on and 737-900)

Edge Frame 578 Near Stringer S-11 to S-13 231/232 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-40-22-4 Overwing Emergency Exit Cutout Forward and Aft Lower Door Corners Sta 616 and Sta 639 231/232 53-40-22-5 Overwing Emergency Exit Cutout Upper Edge of both Upper Corners of Cutout from S-11 @ 

Sta 616 to S-11 @ Sta 639

231/232 

53-40-22-6 Overwing Emergency Exit Cutout - Door 

Cutouts Corners

Upper Edge of Doors from S-11 @ Sta 578 to S-11 @ Sta 601 and from S-11 @ Sta 616 to S-11 @ Sta 639

231/232 

53-40-22-7 Overwing Emergency Exit Cutout Edge Frame Outer Chord Under Stop Backup Fittings at S-11 

and S-12

231/232 

53-40-22-8 Overwing Emergency Exit Cutout Both Lower Corners and Lower Edge of Cutout from S-14 @ 

Sta 616 to S-14 at Sta 639

231/232 

53-40-22-8a Overwing Emergency Exit Cutout Both Lower Corners and Lower Edge of Cutout from S-14 

Sta 616 to S-14 Sta 639

231/232 

53-40-22-9 Overwing Emergency Exit Cutout All Four Lower Corners (Intersection of Lower Sill and Edge 

Frames 578, 601, 616, and 639) + Skin Assy over the Lower Sills

231/232 

53-40-22-10 Overwing Emergency Exit Cutout Skin and 

Frame Assy Section @ Sta 616 and S-13

Covered Region: Edge Frame 616 from S-13 to S-15 and Edge Frame 639 from S-10 to S-15

231/232 

53-40-22-11 Overwing Emergency Exit Cutout Skin Assy 

and Frame Outer Chord

Door Edges at Sta 578 S-13 to S-15 and at Sta 601, 616 and 639 S-10 to S-15

231/232 

53-40-22-12 Overwing Emergency Exit Cutout Lower Aft Corner Frame 616 & 639 at Lower Sill 231/232 53-40-22-13 Overwing Emergency Exit Cutout Lower Sill Inner Splice Strap 231/232 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-40-22-20 Overwing Emergency Exit Cutout Structure 

(Inspection Applicable to 737-700 Cumline Number 1 thru 6 Only)

Sta 616 Skin Assembly under External (Boomerang) Doubler 231/232 

53-40-22-22 Overwing Emergency Exit Cutout Structure 

(Inspection Applicable to 737-800 Cumline Number 7 and 8 Only)

Sta 578, Sta 616 and Sta 639 Skin Assemblies under External (Boomerang) Doublers

231/232 

53-40-23-1 Overwing Emergency Exit Door Stops and 

Fittings

Door Stops Attached to the Forward and Aft Door Edge Frames 231/232 

53-40-23-2 Overwing Emergency Exit Door Stops and 

Fittings

Door Stop Intercostals Between Sta 601 and Sta 616 231/232 

53-40-23-3 Overwing Exit Door Stops and Fittings Door Stop Backup Fitting Attachment to Window Frames at 

S-11 and S-12

231/232 

53-40-24-1 Pressure Deck Attachments to Rear Spar 

Extension

BS 663 133/134 

53-60-01-2 Crown Skin Panel Sta 727 to 887 See Table Entry and DTR Form for PSE 53-30-01-2 241/242 

53-60-01-4 Crown Skin Panel Sta 727 to 887 ADF Antenna Cutout Sta 727 + 9, RBL 5

SATCOM Antenna Cutout Sta 747, STR-1

241/242 

53-60-01-5 SATCOM Antenna Installation 

(Canadian Marconi and Honeywell)

Section 46: Sta 767 between S-1 and S-2L 241/242 

53-60-01-6 SATCOM Antenna Installation (All except those 

covered by PSE 53-60-01-5)

Section 46: Sta 767 between S-1 and S-2L 241/242 

53-60-02-1 Fuselage Side Skin Panels See Table Entry and DTR Form for PSE 53-30-02-1 141/142

194

241/242

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-60-02-4 Fuselage Side Skin Panels Under the Wing-toBody Fairing See Table Entry and DTR Form for PSE 53-30-02-4. 141/142 143/144

194

53-60-04-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 241/242 

53-60-04-1a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1a 241/242 

53-60-04-2 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-2 241/242 

53-60-04-2a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-2a 241/242 

53-60-04-3 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-3 241/242 

53-60-04-3a Longitudinal Skin Splice See Table Entry and DTR Form for PSE 53-30-04-3a 241/242 

53-60-04-4 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-4 241/242 

53-60-04-4a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-4a 241/242 

53-60-04-5 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-5 241/242 

53-60-04-5a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-5a 241/242 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-60-04-6 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-6 241/242 

53-60-04-6a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-6a 241/242 

53-60-04-7 Longitudinal Lap Splice S-23L & S-23R, Sta 727 to 887 Except at Cargo Door Cutout. 

Upper Fastener Row, Upper (Inner) Skin

143/144 

53-60-05-2 Window Belt Sta 727 to 888 Window Frames Also PSE 53-30-05 Sta 360 to 540. Also:

PSE 53-70-09 Sta 888 to 927

231/232241/242

53-60-08 Aft Cargo Door Surround Structure See Table Entry and DTR Form for PSE 53-30-08-12 142/144 

53-60-08 Aft Cargo Door Surround Structure See Table Entry and DTR Form for PSE 53-30-08-10 142/144 

53-60-08 Aft Cargo Door Surround Structure See Table Entry and DTR Form for PSE 53-30-08-6 142/144 

53-60-08-1 Aft Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords between S-18R 

and S-26R

142 

53-60-08-2 Aft Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords between S-17R 

and S-18R

142 

53-60-08-3 Aft Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords at S-18R 142/144 

53-60-08-4 Aft Cargo Door Surround Forward and Aft Edge 

Frames at BS 794.37 and 847

Outer Chord Between S-16R & S-26R (Except at Door Stops and Sills Location) 

142/144 

53-60-08-5 Aft Cargo Door Surround Forward and Aft Edge 

Frames at BS 794.37 and 847

Outer Chord at Door Stops Location and at Frame/Sill Intersections

142/144 

53-60-08-8 Aft Cargo Door Surround Structure Forward and Aft Edge of Door Sta 794.4 and Sta 847 S-18R to 

S-25R. Also: PSE 53-30-08, Forward Cargo Door at Sta 440 & Sta 492.4

122/124142/144

53-60-08-9 Aft Cargo Door Surround Structure Skin and Bearstrap at Corners of Cutout. Also: 

PSE 53-30-08-9, Forward Cargo Door

122/124142/144

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-60-08-11 Aft Cargo Door Surround Structure Upper Sill Inner Chord. Also:

PSE 53-30-08-11, Forward Cargo Door Upper Sill Inner Chord

53-60-09-3 Aft Cargo Door Fittings and Stops at the 

Forward and Aft Edge Frames

Backup Fittings and Intercostals 142 

53-60-12-3 Mid Exit Door Surround Structure Upper Main Sill, STA 727H to 727J 

53-60-13-1 Mid Exit Door Surround Door Stop Fittings At BS 727H + 8.85” and BS 727I + 13.15” 

53-70-03-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 241/242 

53-70-03-1a Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1a 241/242 

53-70-03-2 Longitudinal Lap Splice S-4L & S-4R, Sta 887-1016 Lower Fastener Row, Lower Skin 241/242 53-70-03-3 Longitudinal Lap Splice S-14L, Sta 888 to 947, 1006 to 1016, Upper Row, Upper Skin 

S-14R, Sta 888 to 947, 996 to 1016, Upper Row, Upper Skin

241/242 

53-70-03-4 Longitudinal Lap Splice S-14L, Sta 888 to 947, 1006 to 1016, Lower Row, Lower Skin 

S-14R, Sta 888 to 947, 996 to 1016, Lower Row, Lower Skin 

241/242 

53-70-04-1 Crown Skin Panel Sta 887 to 1016 See Table Entry and DTR Form for PSE 53-30-01-2 241/242 53-70-07-3 Aft Entry Door, Forward Edge Frame Door 

Stop Backup Structure

Stops #1, #2, #6 and #7 241 

53-70-07-4 Aft Entry Door Aft Edge Frame Door Stop 

Backup Intercostals

Stop Locations #1, #2, #6 and #7 241 

53-70-07-5 

<1>

Cutout, Aft Entry Door Surround Structure Skin Around Perimeter of Cutout 241 

53-70-07-6 Aft Entry Door Surround Structure Lower Sill Scuff Plate Installation. Also:

PSE 53-70-08-6, Aft Galley Door Surround Structure

145/241 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-70-07-11 

<1>

Aft Entry Door Surround Structure Upper Main Sill Inner Chord Sta 951.0 to 1006. 

Also: PSE 53-70-08, Aft Galley Door Surround Structure

241 

53-70-07-12 Aft Entry Door Surround Structure Lower Main Sill

Also: PSE 53-70-08-12, Aft Galley Door Surround Structure

241 

53-70-08 

<1>

Aft Galley Door Surround Structure See Table Entry and DTR Form for PSE 53-70-07-11 242 

53-70-08-3 Aft Galley Door Forward Edge Frame Door 

Stop Backup Structure

Stops #1, #2, #5 and #6 242 

53-70-08-4 Aft Galley Door Aft Edge Frame Door Stop 

Backup Intercostals

Stops Locations #1, #2, #5 and #6 242 

53-70-08-5 

<1>

Cutout, Aft Galley Door Surround Structure Skin Around Perimeter of Cutout 242 

53-70-08-6 Aft Galley Door Surround Structure See Table Entry and DTR Form for PSE 53-70-07-6 146/242 

53-70-08-12 Aft Galley Door Surround Structure Lower Main Sill Outer Chord

See Table Entry and DTR Form for PSE 53-70-07-12

242 

53-70-09 Window Belt See Table Entry and DTR Form for PSE 53-60-05-2 241/242 

53-80-01-2 Bulkhead Sta 1016 Pressure Dome Webs Between Tear Straps 311/312 

53-80-01-3 Bulkhead Sta 1016 Pressure Dome Webs Between Tear Straps Lap Splice 

(Visible Row)

311/312 

53-80-01-4 Bulkhead Sta 1016 Web at Pressure Chord Adjacent to Stiffeners 145/146

241/242311/312

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-80-01-5A Bulkhead Sta 1016 Web at Pressure Chord Between Stiffeners from S-5L to S-7L 

and S-5R to S-9R.

241/242311/312

53-80-01-5B Bulkhead Sta 1016 Web at Pressure Chord Between Stiffeners Areas Outside of 

S-5L to S-7L and S-5R to S-9R.

145/146241/242311/312

53-80-01-6 Bulkhead Sta 1016 Web at Chord Splice Between S-1 and S-3, and between S-15 

and S-18

145/146241/242311/312

53-80-01-7 Bulkhead Sta 1016 Pressure Dome Webs Lap Splice Under Stiffeners 

(Hidden Detail)

145/146241/242311/312

53-80-01-8 Bulkhead Sta 1016 Pressure Dome Webs at Tear Straps 311/312 

53-80-01-9 Bulkhead Sta 1016 Pressure Dome Webs at Lap Splice and Tear Strap 

Intersection

311/312 

53-80-01-11 Bulkhead Sta 1016 Pressure Dome Webs at Lap Splice/Tear Strap Junctions 311/312 53-80-01-13 Bulkhead Sta 1016 Web at Chord Splice/Doubler Between S-1 and S-3 311/312 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-80-01-14 No DTR Form - Perform Aft Side Detailed 

Visual Inspection of BS 1016 Bulkhead Web Looking for Oil Cans, Refer to Structural Repair Manual Section 53-80-08 for Definition of Oil Can. SRMs:737-600 - D634A220737-700 - D634A201737-700IGW - D634A330737-700C - D634A202737-800 - D634A210737-900 - D634A211Repeat Inspections Every 10000 Flight Cycles.

Bulkhead Sta 1016 311/312 

53-80-02-1 

<1>

Vertical Fin Front Spar Fitting, Bulkhead Attachment - STA 1016

Bulkhead Sta 1016 241/242

322

53-80-02-1a Vertical Fin Front Spar Fitting Bulkhead 

Attachment - Sta 1016

Bulkhead Attachment @ Sta 1016 241/242

322

53-80-02-2 Vertical Fin Front Spar Fittings Sta 1016 Fitting Lugs 241/242

322

53-80-03-1 Stringer Splice Fittings Sta 1016, S-9L to S-9R Forward and Aft of Bulkhead 241/242

311/312

53-80-05-1 Jackscrew Fitting Lugs Bulkhead Sta 1088 311/312 53-80-06-1 Vertical Fin Rear Spar Attachment Fittings Bulkhead Sta 1088 311/312

313/314

323

53-80-06-2 Vertical Fin Rear Spar Attachment Fittings Primary Lugs at Sta 1088 311/312

313/314

323

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-80-07-1 Bulkhead Sta 1156 Outer Chord at Pivot Fitting Attachment 313/314 

317/318

53-80-07-2 Integrated Bulkhead Sta 1156 Web Inboard of Failsafe Strap, Above and Below Pivot Fitting 

Attachment

313/314 317/318

53-80-08-1 Horizontal Stabilizer Pivot Fitting Sta 1156 Hinge Beam at Pivot Pin 313/314 53-80-08-2 Horizontal Stabilizer Pivot Pins Sta 1156 Pivot Pins 313/314 53-80-10-1 Section 48 Skin Panels, Sta 1088 to 1156 Skin Panels at BS 1138 Cutout 313/314 53-80-14-4 Sta 1042 Bulkhead Straps Aft Horizontal Straps 311/312 

53-80-14-7 Sta 1042 Bulkhead Intercostals System Penetrations in Horizontal Intercostals 311/312 

53-80-15-1 Sta 1042 Bulkhead Lugs, Links and Fittings 

Bulkhead Lugs

Bulkhead Beam End Lugs @ Sta 1042 311/312 

53-80-15-2a Sta 1042 Bulkhead Lugs, Links and Fittings 

End Beam Lugs

Lug Attachment to Beam Hidden by attach fittings Lugs at 

RBL/LBL 10, 23 and WL 282, 269, and 256

311/312 

53-80-15-2b Sta 1042 Bulkhead Lugs, Links, and Fittings 

End Beam Lug Attachment at Diagonal Beam

Lug Attachment to Beam Hidden by Attach Fittings and Straps at WL 223

311/312 

53-80-15-3 Sta 1042 Bulkhead Link Fittings Link Clevis Fittings at Sta. 1042 311/312 53-80-15-4 Sta 1042 Bulkhead Lugs, Links, and Fittings 

Link Attach Fittings

Bulkhead Link Attach Fittings @ Sta 1042 311/312 

53-80-16-1 Sta. 1042 Bulkhead Chord Splice Splice @ APU Cutout 145/146

241/242311/312

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-80-17-2 APU Inlet Cutout Enclosure Forward Panel Fasteners at visible locations common to the longerons and the 

Sta 1016 T-Chord

241/242 

53-80-17-3 APU Inlet Enclosure Installation - Pressure 

Panels

Visible fastener locations common to the Mid and Aft Pressure Panels

241/242 

53-80-17-4 APU Enclosure Installation Pressure Panels Crack at fastener in hidden edge 241/242 53-80-17-5 APU Enclosure Installation Pressure Panels Crack at mid pressure panel hidden by frame at fastener row 241/242 53-80-17-6 APU Enclosure Installation Pressure Panels Crack at fastener in aft pressure panel hidden by BS 1030 

frame

241/242 

53-80-17-7 APU Inlet Enclosure Installation - Pressure 

Panels

Forward Pressure Panel Fastener Row Hidden by Stiffener 241/242 

53-80-17-8 APU Enclosure Installation Stiffeners at Mid/Aft Panel Interface 241/242 

53-80-18-1 Section 48 Longitudinal Lap Splices S-4 Lap 

Splice, Sta 1016 to 1042

Upper Fastener Row - Outer Skin 145/146

241/242

53-80-18-2 Section 48 Longitudinal Lap Splices S-4 Lap 

Splice, Sta 1016 to 1042

Lower Fastener Row - Inner Skin 145/146

241/242

53-80-18-5 Section 48 Longitudinal Lap Splices S-24 Lap 

Splice, Sta 1016 to 1042

Upper Fastener Row - Outer Skin 145/146

241/242

53-80-18-6 Section 48 Longitudinal Lap Splices S-24 Lap 

Splice, Sta 1016 to 1042

Lower Fastener Row - Inner Skin 145/146

241/242

53-80-18-7 Section 48 Butt Splice at S-9R and S-9L 

BS 1016 - BS 1042

Upper Fastener Row in the Upper Skin and Lower Fastener Row in the Lower Skin

145/146241/242

53-80-18-9 Section 48 Butt Splice at S-9R and S-9L 

BS 1016 - BS 1042

Fastener row in strap common to Stringer 9 (upper skin, lower row)

145/146241/242

53-80-18-10 Section 48 Butt Splice at S-9R and S-9L 

BS 1016 - BS 1042

Fastener row in strap common to upper row of lower skin 145/146

241/242

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-80-20-4 Side Skin Panel, Sta 1016 to 1042 S-9R to 

S-16R - APU Inlet Cutout

Forward Edge of APU Inlet Cutout 241/242 

54-51-0154-51-0254-51-0354-51-0454-51-0554-51-0654-51-0754-51-0854-51-0954-51-15

Strut to Wing Attachments Zone 431/441/434/444 430/440 

54-51-10 Lower Spar Chord-Typical Exposed Detail Typical Lower Spar Chord Between Forward and Aft Engine 

Mounts NSTA 203.6 – 209.9 Left and Right Hand ChordsNSTA 212.3 – 222.0 Left and Right Hand ChordsNSTA 224.7 – 231.8 Left Hand ChordNSTA 234.4 – 240.4 Left and Right Hand ChordsNSTA 234.5 – 250.6 Left and Right Hand Chords

433/443 

54-51-10 Lower Spar Chord at Fire Seal Depressor 

Bracket

NSTA 203.4 Left and Right Hand ChordsNSTA 207.8 Left and Right Hand Chords

433/443 

54-51-10 Lower Spar Chord - Bracket NSTA 218.0 Right Hand Side

NSTA 216.0 Left Hand Side

433/443 

54-51-10 Lower Spar Chord at Frames with Brackets NSTA 222.6, Left and Right Hand Chords

NSTA 242.7, Left and Right Hand Chords

433/443 

54-51-10 Lower Spar Chord Aft Engine Mount Bulkhead 433/443 54-51-10 Lower Spar Chord, Web Only NSTA 224.7 – 231.8, Right Chord 433/443 54-51-10 Lower Spar Chord, Chord Only NSTA 224.7 – 231.8, Right Chord 433/443 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

54-51-10 Lower Spar Chord – Compression Pad 

Bracket, Horizontal Leg

NSTA 244.9 Left and Right Hand Chords 433/443 

54-51-10 Lower Spar Chord – Compression Pad 

Bracket, Vertical Leg

NSTA 244.9 Left and Right Hand Chords 433/443 

54-51-10 Lower Spar Chord – Typical Frame Detail, 

Vertical Leg

NSTA 209.0 – 212.3, 231.8 – 234.4 Left and Right Hand Chords

433/443 

54-51-10 Lower Spar Chord – Typical Frame Detail, 

Horizontal Leg

NSTA 209.0 – 212.3, 231.8 – 234.4 Left and Right Hand Chords 

433/443 

54-51-10 Lower Spar Chord Aft of Aft Engine Mount Bulkhead 433/443 54-51-11 Fwd Engine Mount Bulkhead End Pad Bolt Holes (4 Locations) 433/443 54-51-14 Mid Strut Bulkhead End Pad 433/443 54-51-16 Side Skin Cutouts NSTA 270 and NSTA 252, Left and Right Sides 433/443 54-51-16 Strut Side Skin NSTA Sta 222.6 Left and Right Sides and NSTA 242.7, Left 

and Right Sides

433/443 

54-51-17 Upper Spar Chord Typical Upper Spar Chord Between Forward and Aft Engine 

MountsNSTA 200.9 – 211.5 Left ChordsNSTA 213.6 – 225.2 Left ChordsNSTA 226.1 – 233.6 Left ChordsNSTA 236.3 – 241.8 Left and Right Chords

433/443 

54-51-17 Upper Spar Chord Near Cutouts NSTA 200.9 – NSTA 211.5, Right Chord

NSTA 213.6 – NSTA 225.2, Right ChordNSTA 226.1 – NSTA 233.6, Right Chord

433/443 

54-51-17 Upper Spar, R1 – Fitting and Upper Spar Web 

Joints, Chord Only

Near Cutouts – NSTA 200.9 – 211.5,NSTA 213.6 – 225.2, NSTA 226.1 – 233.6

433/443 

54-51-17 Upper Spar, R1 – Fitting and Upper Spar 

Joints, Web Only

Near Cutouts – NSTA 200.9 – 211.5,NSTA 213.6 – 225.2, NSTA 226.1 – 233.6

433/443 

54-51-17 Upper and Lower Spar Chords Splice to Fwd Engine Mount Bulkhead 433/443 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

54-51-17 Upper Spar Chord NSTA 222.6, Left and Right Hand Chords

NSTA 210.6, Left and Right Hand Chords

433/443 

54-51-17 Upper Spar Chord NSTA 242.7, Left and Right Chords 433/443 

54-51-17 R3/R4 First Fastener Row – Vertical Leg First Fastener Row Right and Left Hand Side 433/443 

54-55-03 Forward Engine Mount Hanger Zone 413/414/423/424 410/420 

54-55-05 Thrust Link Assembly Zone 415/416/425/426 410/420 

54-55-06 Thrust Link Pin Zone 415/416/425/426 410/420 54-55-10 Aft Engine Mount Assembly Zone 415/416/425/426 410/420 

54-55-11 Evener Bar Assembly – Outboard Lugs Zone 415/416/425/426 410/420 54-55-11 Aft Engine Mount Evener Bar – Mid Span Zone 415/416/425/426 410/420 54-55-13 Strut Attach Bolts (Forward and Aft Mounts) Zone 413/414/415/416/423/424/425/426 410/420 

55-10-01-1 Horizontal Stabilizer Center Section Rear Spar 

Upper Chord

BL 1.3 Left and Right 313/314 

55-10-01-2 Horizontal Stabilizer Center Section Rear Spar 

Upper Chord

BL 2.7 to BL 6.7 Left and Right 313/314 

55-10-01-3 Horizontal Stabilizer Center Section Rear Spar 

Upper Chord

BL 8.1 to 19.7 Left and Right 313/314 

55-10-01-4 Horizontal Stabilizer Center Section Rear Spar 

Upper Chord

Thrust Beam Attachment 313/314 

55-10-02-1 Horizontal Stabilizer Center Section 

Pivot Fitting

Hinge House Pivot Lug 313/314 

55-10-02-2 Horizontal Stabilizer Center Section 

Pivot Fitting

Lower Hinge Housing Lugs 313/314 

55-10-02-3 Horizontal Stabilizer Center Section Thrust 

Link Fittings

Clevis Lugs 313/314 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

55-10-03-1 Horizontal Stabilizer Center Section 

Jackscrew Fitting

Jackscrew Lugs 311/312 

55-10-04-1 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 129.5 to 212.3 332/342

333/343

55-10-04-2 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 212.3 to 310.54. Forward Flange at and between ribs 332/342

333/343

55-10-04-3 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 212.3 to 310.54. Aft flange at and between ribs 

(except area covered by 55-10-04-9)

332/342333/343

55-10-04-4 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 212.3 to 310.54. Chord web flange at the TE ribs/

stiffeners

332/342333/343

55-10-04-5 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 212.3 to 310.54. Web Flange between the TE ribs/

stiffeners

332/342333/343

55-10-04-6 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 310.54 to outboard tip. Forward flange at and 

between the ribs

332/342333/343

55-10-04-7 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 310.54 to outboard tip. Aft flange at and between the 

ribs

332/342333/343

55-10-04-8 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 310.54 to outboard tip. Web flange at and between 

the ribs

332/342333/343

55-10-04-9 Horizontal Stabilizer Rear Spar Lower Chord Aft flange at the hinge, Stab Sta 242 to 247, Elev Sta 197 to 

203

332/342333/343

55-10-04-10A Horizontal Stabilizer Rear Spar Upper Chord at 

Side-of-Body

Upper chord between terminal fitting fork (Lead crack above the bolt hole)

332/342333/343

55-10-04-10B Horizontal Stabilizer Rear Spar Upper Chord at 

Side-of-Body

Upper Chord Between Terminal Fitting Fork (Lead crack below bolt hole, Outboard 3 bolt hole locations)

332/342333/343

55-10-04-10C Horizontal Stabilizer Rear Spar Upper Chord at 

Side-of-Body

Upper Chord Between Terminal Fitting Fork (Lead crack below bolt hole, Inboard Bolt Location)

332/342333/343

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

55-10-04-11A Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 67.78 to Stab Sta 203.10 332/342

333/343

55-10-04-11B Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 203.10 to Stab Sta 258.28. Skin Flanges. 332/342

333/343

55-10-04-11C Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 203.10 to Stab Sta 258.28. Web Flange at rib and 

stiffener locations

332/342333/343

55-10-04-11D Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 203.10 to Stab Sta 258.28. Web Flange between ribs 

and stiffeners

332/342333/343

55-10-04-12A Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Tip. Forward Flange of the chord 332/342

333/343

55-10-04-12B Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Tip. Aft Flange of the chord 332/342

333/343

55-10-04-13A Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Stab Sta 310.54. Web Flange at Rib and 

Stiffener Locations

332/342333/343

55-10-04-13B Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Stab Sta 310.54. Web Flange between Rib 

and Stiffener Locations

332/342333/343

55-10-04-13C Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 310.54 to Tip. Web flange both at and between 

Stiffeners/Ribs

332/342333/343

55-10-04-20 Horizontal Stabilizer Rear Spar Web Stab Sta 83.5 to Stab Sta 184.7 332/342

333/343

55-10-04-21 Horizontal Stabilizer Rear Spar Web Stab Sta 184.7 to Stab Sta 285.9 332/342

333/343

55-10-04-22 Horizontal Stabilizer Rear Spar Web Stab Sta 285.9 to Stab Sta 310.5 332/342

333/343

55-10-04-23 Horizontal Stabilizer Rear Spar Web Stab Sta 310.5 to Outboard Tip; Locations between stiffeners 332/342

333/343

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

55-10-04-24 Horizontal Stabilizer Rear Spar Web Stab Sta 310.5 to Outboard Tip; At stiffener locations. 332/342

333/343

55-10-05-1 Horizontal Stabilizer Rear Spar Upper and 

Failsafe Chord Lugs

At the Side of Body 332/342

333/343

55-10-05-2A Horizontal Stabilizer Rear Spar Upper Chord 

Terminal Fitting

Side-of-Body Terminal Fitting at the Inboard 3 Attach Bolt Locations

332/342333/343

55-10-05-2B Horizontal Stabilizer Rear Spar Upper Chord 

Terminal Fitting

Side-of-Body Terminal Fitting at the Outboard Attach Bolt Location

332/342333/343

55-10-05-3 Horizontal Stabilizer Rear Spar Terminal Fitting Side-of-Body Pins 332/342

333/343

55-10-05-4 Horizontal Stabilizer Rear Spar Upper Chord 

Terminal Fitting

At Terminal Fitting (common to Side of Body Rib Tension Bolt Hole)

332/342333/343

55-10-05-5 Horizontal Stabilizer Rear Spar Lower Chord At the Side-of-Body (common to the end rib tension bolt hole) 332/342

333/343

55-10-06-1 Horizontal Stabilizer Front Spar Upper Chord Side-of-Body to Stab Sta 66.5 331/341

332/342

55-10-06-2 Horizontal Stabilizer Front Spar Upper Chord Aft Flange, Stab Sta 66.5 to Stab Tip 331/341

332/342

55-10-06-3 Horizontal Stabilizer Front Spar Upper Chord Forward Flange, Stab Sta 66.5 to Stab Tip 331/341

332/342

55-10-06-4A Horizontal Stabilizer Front Spar Upper Chord Web Flange, Stab Sta 66.5 to Stab Sta 175.5 and Stab Sta 

258.28 to Stab Tip

331/341332/342

55-10-06-4B Horizontal Stabilizer Front Spar Upper Chord Web Flange, Stab Sta 175.5 to Stab Sta 258.28 331/341

332/342

55-10-06-6A Horizontal Stabilizer Front Spar Lower Chord Forward flange, Stab Sta 66.50 to Stab Sta 175.50 331/341

332/342

55-10-06-6B Horizontal Stabilizer Front Spar Lower Chord Aft flange, Stab Sta 66.50 to Stab Sta 175.50 331/341

332/342

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

55-10-06-7A Horizontal Stabilizer Front Spar Lower Chord Forward Flange, Stab Sta 175.50 to Stab Sta 258.28 331/341

332/342

55-10-06-7B Horizontal Stabilizer Front Spar Lower Chord Aft Flange, Stab Sta 175.50 to Stab Sta 258.28 331/341

332/342

55-10-06-8A Horizontal Stabilizer Front Spar Lower Chord Forward Flange, Stab Sta 258.28 to Stab BL 281.81 (Tip) 331/341

332/342

55-10-06-8B Horizontal Stabilizer Front Spar Lower Chord Aft Flange, Stab Sta 258.28 to Stab BL 281.81 (Tip) 331/341

332/342

55-10-06-W1 Horizontal Stabilizer Front Spar Web Stab Sta 66.5 to Stab Sta 111.1 331/341

332/342

55-10-06-WS Horizontal Stabilizer Front Spar Web Web Splice at Stab Sta 111.1 331/341

332/342

55-10-06-W2 Horizontal Stabilizer Front Spar Web Stab Sta 111.1 to Stab Sta 175.5 331/341

332/342

55-10-06-W3 Horizontal Stabilizer Front Spar Web Stab Sta 175.5 to Stab Sta 258.28 331/341

332/342

55-10-06-W4 Horizontal Stabilizer Front Spar Web Stab Sta 258.28 to Stab Tip 331/341

332/342

55-10-07-2 Horizontal Stabilizer Front Spar Upper Chord Side of Body at the Front Spar Upper Chord 331/341

332/342

55-10-07-3 Horizontal Stabilizer Front Spar Terminal 

Fitting

Side-of-Body Bolts 331/341

332/342

55-10-07-4 Horizontal Stabilizer Front Spar Lower Chord Lower chord at end rib tension fitting installation bolt hole 331/341

332/342

55-10-08-1 Horizontal Stabilizer Elevator Hinge Ribs Hinge Plates at Elevator Sta 121 and 176 333/343

334/344

55-10-08-2 Horizontal Stabilizer Elevator Hinge Ribs Hinge Plate at Elevator Station 213 and Sta 250 333/343

334/344

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

55-10-08-3 Horizontal Stabilizer Trailing Edge Hinge Plate 

Lower Forward Lug

Hinge Plate at ESTA 265 333/343

334/344

55-10-08-4 Horizontal Stabilizer Elevator Hinge Ribs Hinge Plate at Elevator Station 66 333/343

334/344

55-10-08-5A Horizontal Stabilizer Elevator Hinge Ribs 

Trailing Edge Clevis

ESTA 121 and 176 333/343

334/344

55-10-08-5B Horizontal Stabilizer Elevator Hinge Ribs 

Trailing Edge Clevis

ESTA 121 and 176 333/343

334/344

55-10-08-6 Horizontal Stabilizer Elevator Hinge Ribs Elevator Station 66 333/343

334/344

55-10-08-7 Horizontal Stabilizer Elevator Hinge Ribs Elevator Station 213 and 250 333/343

334/344

55-10-08-8 Horizontal Stabilizer Elevator Hinge Ribs Elevator Station 265 333/343

334/344

55-10-08-9 Horizontal Stabilizer Trailing Edge Elevator 

Hinge Rib

Elevator Hinge Rib to Rear Spar Attachment at Elevator Stations 66 and 121

333/343334/344

55-10-8-10 Horizontal Stabilizer, Trailing Edge Hinge Rib 

to Rear Spar Attachment

ESTA 176 333/343

334/344

55-10-8-11 Horizontal Stabilizer Elevator Hinge Ribs Hinge Rib to Rear Spar Attachment, Elevator Stations 213, 250 

and 265

333/343334/344

55-10-8-13 Horizontal Stabilizer Elevator Hinge Ribs Hinge Rib Lower Chord and Upper Chord, Elevator Stations 66 

and 121

333/343334/344

55-10-8-14 Horizontal Stabilizer Elevator Hinge Ribs Elevator Hinge Rib Lower Chord and Upper Chord, Elevator 

Station 176

333/343334/344

55-10-09-1 Horizontal Stabilizer Upper Inspar Skin Side of Body to Stabilizer Sta 157.1 332/342 55-10-10-1 Horizontal Stabilizer Lower Inspar Skin Side of Body to Tip 332/342 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

55-10-11-1 Horizontal Stabilizer Center Section Front Spar 

Upper Chord

Side of Body Clevis Lugs 313/314 

55-10-12-1 Horizontal Stabilizer Center Section Rear Spar 

Lugs

Lower Pivot Fitting Lugs 313/314

332/342333/343

55-10-12-2 Horizontal Stabilizer Center Section Rear Spar 

Upper Chord

Side of Body Lugs 313/314

332/342333/343

55-10-13-2 Horizontal Stabilizer Center Section Front Spar 

Upper Chord

Thrust Beam to Spar Joint 313/314 

55-10-14-1 Horizontal Stabilizer Center Section Primary 

and Thrust Beams

Upper Primary Beam at Front and Rear Spar Joint 313/314 

55-10-14-2 Horizontal Stabilizer Center Section Primary 

and Thrust Beams

Upper Primary Beam at Front and Rear Spar Joint Plates and Angles

313/314 

55-10-14-3 Horizontal Stabilizer Center Section Primary 

and Thrust Beams

Primary Beam Upper Chord at the Thrust Beam Joint 313/314 

55-10-14-4 Horizontal Stabilizer Center Section 

Thrust Beams

Beam Chords at Front and Rear Spars 313/314 

55-10-14-5 Horizontal Stabilizer Center Section 

Thrust Beams

Front and Rear Spar to Beam Splice Members 313/314 

55-10-14-6 Horizontal Stabilizer Center Section 

Thrust Beams

Chords at Thrust Beam Intersection Joint 313/314 

55-10-14-7 Horizontal Stabilizer Center Section Thrust 

Beam Intersection

Splice Plates 313/314 

55-10-14-8 Horizontal Stabilizer Center Section 

Thrust Beams

Upper Chord at Primary Beam Joint 313/314 

55-10-14-9 Horizontal Stabilizer Center Section Primary 

Beam Chord to Web Attachment

Upper Chord Sta 1216 to 1242 313/314 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

55-20-05 Elevator Hinge Fittings All Elevator Hinge Fittings 334/344 

55-20-06 Elevator Mast Arm Assembly Elevator Actuator Fitting Lug Face 334/344 

55-20-07 Elevator Horn Balance Weight 

Support Structure 

Elevator Station 260 334/344 

55-20-08 Elevator Tab Mast Fitting Base of Clevis Leg, Attach Flanges and Lugs

Note: Applicable to -600/-700/-700C/-700IGW/-800 L/N 1 to 1174 which have not incorporated Service Bulletin 737-55A1080. AD 2003-03-22 mandates Service Bulletin 737-55A1080 prior to 18000 Cycles.

334/344 

55-20-08-1 183A8700 Hinge/Mast Arm Fitting 

Upper Flange

Fastener Hole 2 and 3 334/344 

55-20-08-2 183A8700 Hinge/Mast Arm Fitting 

Upper Flange

Fastener Hole 2 and 3Note: Applicable to L/N 596 and ALL 1175 and on, and L/N 1-1174 that have Incorporated SB 737-55A1080 or SB 737-55-1081.

334/344 

55-20-09 Elevator Tab Hinge Fittings 183A4211 

Lug Assembly

Bolts Between the Lug Assembly and the Elevator Rear Spar Fitting, Hinges 1 through 4Note: Applicable to -600/-700/-700C/-700IGW/-800 L/N 1 to 1174 which have not incorporated Service Bulletin 737-55A1080. AD 2003-03-22 mandates Service Bulletin 737-55A1080 prior to 18000 Cycles.

334/344 

55-20-09-1 183A8300 Bridge Fitting Upper/Lower Flange Upper/Lower Flange Joints – Hinges 2 and 2.5 334/344 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

55-20-09-2 183A8300 Bridge Fitting Upper/Lower Flange Upper/Lower Flange Joints – Hinges 3 through 6

Note: Applicable to L/N 596 and ALL 1175 and on, and L/N 1-1174 that have Incorporated SB 737-55A1080 or SB 737-55-1081.

334/344 

55-20-12 183A1400 – Bracket Assy – Tab Control 

Mechanism, Elevator

Lug Faces 334/344 

55-20-12-1 183A1400 – Bracket Assy – Tab Control 

Mechanism, Elevator

Lug FacesNote: Applicable to L/N 596 and ALL 1175 and on, and L/N 1-1174 that have incorporated SB 737-55A1080 or SB 737-55-1081.

334/344 

55-30-03-2 Vertical Fin – Rear Spar Primary Chord from Fin Sta 73.4 to Tip 323/324 

55-30-03-2a Vertical Fin – Rear Spar Primary Chord Fin Sta 80 to the Fin Tip 323/324 

55-30-05-1 

<1>

Vertical Fin – Closure Rib Primary Chord @ Forward End Fastener Location Common to 

Rear Spar Terminal Fitting

323/324 

55-30-05-2 Vertical Fin – Closure Rib Primary Chord at Front Spar 323 55-30-06-1 Rudder Hinge Ribs Hinge Fitting Lugs at Rib Attachment Hinge #1, #2, #3, #4, #5, 

#6, #7, #7A and #8

324 

55-30-06-2

<1>

Rudder Hinge Ribs Hinge Ribs 1 thru 7A at Rear Spar Attachment 324 

55-40-05 Rudder Hinge Fittings All Rudder Hinge Fittings 325 

55-40-06 Rudder Actuator Fittings Rudder Stations 60.85 and 70.65 325 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

55-40-07 737NG Rudder Balance Arm Doubler Common to Failsafe Strap and Front Spar Chord 325 

57-10-01 Wing Center Section Upper Panel Typical and 

Vent Stringers

Stringers 1-13 and 15-21 from LBL 67.0 to RBL 67.0 131/132 

57-10-02 Wing Center Section Upper Panel Splice 

Stringer

Stringer 14, LBL 67.0 to RBL 67.0 131/132 

57-10-03 Wing Center Section Upper Panel Front Spar Upper Chord, LBL 67.0 to RBL 67.0 131/132 

57-10-04 Wing Center Section Upper Panel Rear Spar Upper Chord, LBL 67.0 to RBL 67.0 131/132 

57-10-05-1 Double Plus Chord at Stub Beam Stub Beam Interface at BS 639 195/196 

57-10-05-2 Double Plus Chord at Stringer 18A Interface Aft End of Upper Vert. Flange Radius at Vert. Flange/Horiz. 

Flange

195/196 

57-10-05-3a Double Plus Chord Vert Flange at Stringer 18A 

Interface

Vertical Flange Between BS 639 and BS 663. Top of wing, aft of over wing exits

195/196 

57-10-05-3b Double Plus Chord Upper Vert Flange at 

Body Stringer 18A Interface

Vertical Flange Between BS 639 and BS 663. Top of wing, aft of over wing exits

195/196 

57-10-05-4 Double Plus Chord, Upper Horizontal Flange Front Spar to Rear Spar 135/136

195/196

57-10-05-5 Double Plus Chord, Upper Horizontal Flange at 

Stub Beams

BS 559, 578, 597, 616, 639 135/136 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

57-10-06 Wing Center Section Upper Panel Upper Skin at Floor Beam Attachments, BL 0, BL 25, BL 45 

from Front Spar To Rear Spar

131/132135/136

57-10-07-1 Wing Center Section Lower Panel Typical 

Stringers

Stringers 1-4 and 6-8 from LBL 67.0 to RBL 67.0 131/132 

57-10-07-2 Wing Center Section Lower Panel Typical 

Stringers

Stringers 10-14, LBL 67.0 to RBL 67.0 131/132 

57-10-07/08 Wing Center Section Lower Panel Skin Front Spar to Rear Spar, Side-of-Body to Side-of-Body 131/132 

57-10-08 Wing Center Section Lower Panel Splice Stringers 5 and 9, LBL 67.0 to RBL 67.0 131/132 

57-10-09 Wing Center Section Lower Panel Rear Spar Chord, LBL 67.0 to RBL 67.0 131/132 

57-10-10 Wing Center Section Lower Panel Front Spar Lower Chord, LBL 67.0 to RBL 67.0 131/132 

57-10-11-1 Side-of-Body Splice, Lower Surface Tee-Chord, Rear Spar to Front Spar, BBL 70.85 192

131/132531/631

57-10-11-2 Side-of-Body Splice, Lower Surface Rear Spar to Front Spar, BBL 70.85, (Non-Hidden) 192 57-10-11-3 Side-of-Body Splice, Lower Surface Rear Spar to Front Spar, BBL 70.85, (Hidden) 192 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

57-10-12 Wing Center Section Lower Panel Lower Skin at Keel Beam Attach (Front Spar to Rear Spar) 192

131/132

57-10-13 Wing Center Section Lower Panel Lower Skin at Drain Installation between Stringer 7 and 

Stringer 8 at LBBL 3.5

192

131/132

57-10-15 Wing Center Section Lower Panel Lower Skin at Lower Beam Attachment (Front Spar to Rear 

Spar)

192

131/132

57-10-17-1 Wing Center Section Rear Spar Typical Web 

(Crack Initially Hidden)

LBBL 70.85 to RBBL 70.85 Web Common to Fuel Tank 131/132

133/134

57-10-17-2 Wing Center Section Rear Spar Typical Web 

(Non-Hidden Locations)

LBBL 70.85 to RBBL 70.85 Web Common to Fuel Tank 131/132

133/134

57-10-18 Wing Center Section Rear Spar Keel Beam 

Stiffeners

LBL 6.2 and RBL 6.2 131/132

133/134

57-10-20 Side of Body Splice

Upper and Lower Rear Spar

BBL 70.85 131/132

531/631

57-10-21 Side of Body Splice

Upper and Lower Front Spar

BBL 70.85 131/132

531/631

57-10-23-1 Wing Center Section

Floor Beam Upper Chord

BL 0 and BL 25 Floor Beams from BS 655 to BS 675, BL 0 Floor Beam from BS 716 to BS 727B, and BL 45 Floor Beam from BS 685 to BS 716

135/136137/138

57-10-23-2 Wing Center Section

Floor Beam Upper Chord

BL 0, BL 25 and BL 45 Floor Beams from BS 569 to 655 and BL 25 Floor Beam from BS 685 to BS 727A

135/136137/138

57-10-23-3 Wing Center Section Floor Beam Lower Chord 

Over Pressure Deck

BL 0, BL 25, and BL 45 Floor Beams from BS 664 to BS 727B 137/138 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

57-10-23-4 Wing Center Section Floor Beam Lower Chord BL 0, BL 25 and BL 45 Floor Beams between BS 574 and 

BS 664

135/136 

57-10-23-5 Wing Center Section Floor Beam Lower Chord BL 0, BL 25 and BL 45 Floor Beams between BS 540 and 

BS 574

135/136 

57-10-25 Side of Body Rib Typical Web-to-Stiffener Details 131/132

531/631

57-20-01-1 Lower Wing Panel, Typical Stringers Stringers 2-4 and 10-13 from Rib 1 to 10; Non-hidden Fairing 

Areas

531/631532/632

57-20-01-2 Lower Wing Panel, Typical Stringers Stringers 1-4 and 10-14 from Rib 1 to 15; Non-hidden, 

Adjacent to a Spar Chord

531/631532/632

57-20-01-3 Lower Wing Panel, Typical Stringers Stringers 1-4 and 10-14 at Ribs 5 and 8. Locations hidden by 

seal pans and sealant.

531/631532/632

57-20-01/57-20-02/57-20-03/57-20-04/57-20-05/

57-20-08

-1

Lower Wing Panel Skin; Under the Flap Track Fairings and Nacelle Fairings

Skin panel at Rub Strip locations, Rib 5 to 8, Rib 9 to 11 and Rib 13 to 15

531/631532/632

57-20-01/57-20-02/57-20-03/57-20-04/57-20-05/

57-20-08

-2

Lower Wing Panel Skin Rib 1to 14, Externally Visible Areas, Front Spar to Rear Spar 531/631

532/632

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

57-20-01/57-20-02/57-20-03/57-20-04/57-20-05/

57-20-08

-3

Lower Wing Panel Skin Rib 1 to 27, Front Spar to Rear Spar, All Fairing Locations 

where the skin is not covered by Rub Strips or Fittings

531/631532/632533/633534/634

57-20-01/57-20-02/57-20-03/57-20-04/57-20-05/

57-20-08

-4

Lower Wing Panel Skin Rib 14-27, Externally Visible Areas, Front Spar to Rear Spar 532/632

533/633534/634

57-20-02-1 Lower Wing Panel, Rail Stringers Stringer 6 and 8 from Rib 1 to 19; Non-hidden Faired and NonFaired 531/631 532/632 57-20-02-2 Lower Wing Panel, Rail Stringers Stringer 6 and 8 at Rib 5 and 8; Hidden under seal pans and 

sealant

531/631532/632

57-20-02-3 Lower Wing Panel, Rail Stringers Stringer 8, between Rib 6 and 7, Hidden by Nacelle Support 

Strut Attach Fitting

532/632 

57-20-02-4 Lower Wing Panel, Rail Stringers Stringer 6 and 8: From Rib 19 to 25, Non-Hidden 532/632

533/633

57-20-02-5 Lower Wing Panel, Rail Stringers Stringer 6 and 8 at Rib 22, Hidden by flange of Rib 22, shims 

and sealant

532/632533/633

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

57-20-03-1 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 1 to 10, Non-Hidden, without fairing 531/631

532/632

57-20-03-2 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 1 to 10, Non-Hidden, under fairing 531/631

532/632

57-20-03-3 Lower Wing Panel, Splice Stringers Stringers 5 and 9 at Rib 5 and 8, Hidden by seal pans and 

sealant

531/631532/632

57-20-03-4 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 10 to 19, Except Areas Externally 

Covered by Rub Strips

532/632 

57-20-03-5 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 10 to 19, Areas externally covered 

by Rub Strips

532/632 

57-20-03-6 Lower Wing Panel, Splice Stringers Stringers 5 and 9, From Rib 1 to 10, Areas Externally Covered 

by Fairing Rub Strips

531/631532/632

57-20-03/

57-20-15

Splice Stringers at Chordwise Skin Splices (Upper and Lower Panel)

Lower Stringer 9 (Rib 17 to 18), Lower Stringer 5 (Rib 18 to 19) and Upper Stringer 14 (Rib 19 to 20)

532/632 

57-20-04-1 Front Spar Lower Chord 

(Skin Flange Inspections)

Hidden: Rib 1-6, Rib 19 - 22Non-Hidden: Rib 1-5, Rib 19-22

531/631532/632

57-20-04-2 Front Spar Lower Chord 

(Skin Flange Inspections)

Rib 5 to 7 Non-Hidden 532/632 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

57-20-04-3 Front Spar Lower Chord 

(Web Flange Inspections)

Rib 1 to 19 and Rib 22 to 25 hidden by stiffeners, rib posts or fittings

531/631532/632533/633534/634

57-20-04-4 Front Spar Lower Chord (Skin Flange 

Inspections)

Hidden: Rib 6-19, Rib 22-25Non-Hidden: Rib 7-19, Rib 22-25

532/632533/633534/634

57-20-04-5 Front Spar Lower Chord (Web Flange 

Inspections)

Rib 1 to 19 Non-Hidden 531/631

532/632

57-20-04-6 Front Spar Lower Chord

(Web Flange Inspections)

Rib 19 to Rib 22 Non-Hidden 532/632 

57-20-04-7 Front Spar Lower Chord 

(Web Flange Inspections)

Rib 19 to Rib 22 Hidden by stiffeners, rib posts, or fittings. 532/632 

57-20-04-8 Front Spar Lower Chord 

(Web Flange Inspections)

Rib 22 to Rib 25 Non-Hidden 533/633

534/634

57-20-04-9 Front Spar Lower Chord At R7/R8 Nacelle Fitting Attachment 532/632 

57-20-04-10 Front Spar Lower Chord, (Skin and Web 

Flange Inspections)

Rib 25 to Rib 27, Dry Bay 534/634 

57-20-04/57-20-05/

57-20-16

Spar Chords at Chordwise Skin Splices (Upper and Lower Panel)

Front Spar Lower Chord (Rib 17 to 18), Rear Spar Lower Chord (Rib 18 to 19) and Front Spar Upper Chord (Rib 19 to 20)

532/632 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

57-20-04/57-20-05/57-20-16/

57-20-17

Spar Chords at Winglet Attach Fittings Winglet Attach Fittings at Rib 27 534/634 

57-20-05-1 Rear Spar Lower Chord 

(Skin Flange Inspections)

Rib 1 to 7 Non-Hidden 531/631

532/632

57-20-05-2 Rear Spar Lower Chord 

(Web Flange Inspections)

Rib 1 to 14 Non-Hidden 531/631

532/632

57-20-05-3 Rear Spar Lower Chord 

(Web Flange Inspections)

Rib 1 to 25 Hidden by stiffeners, rib posts or fittings. 531/631

532/632533/633534/634

57-20-05-4 Rear Spar Lower Chord 

(Skin Flange Inspections)

Rib 7 to 14 Non-Hidden 532/632 

57-20-05-5 Rear Spar Lower Chord (Skin Flange 

Inspections)

Rib 1 to 22 Hidden by stiffeners and Rib 1 to 25 Hidden by rib posts or fittings.

531/631532/632533/633534/634

57-20-05-6 Rear Spar Lower Chord (Skin Flange 

Inspections)

Rib 14 to 22 Non-Hidden 532/632 

57-20-05-7 Rear Spar Lower Chord (Web Flange 

Inspections)

Rib 14 to Rib 22 Non-Hidden 532/632 

57-20-05-8 Rear Spar Lower Chord

(Skin and Web Flange Inspections)

Rib 22 to Rib 25, Non-Hidden 533/633

534/634

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

57-20-05-9 Rear Spar Lower Chord

(Skin Flange Inspections)

Rib 22 to Rib 25, Partially Hidden by Stiffener 533/633

534/634

57-20-05-10 Rear Spar Lower Chord

(Skin and Web Flange Inspections)

Rib 25 to Rib 27, Dry Bay 534/634 

57-20-06/07-1 Lower Skin Panel at Main Landing Gear 

Outboard Support Fittings

WSTA 180, 190, 228.25 and 253 531/631

532/632550/650560/660

57-20-06/07-2 Lower Skin Panel at Main Landing Gear 

Outboard Support Fittings

WSTA 180, 190, 228.25 and 253 531/631

532/632550/650560/660

57-20-09 Skin at Nacelle Support Fitting Attachments Lower Skin at R2, R3 and R4 Nacelle Fitting Attachments 532/632 

57-20-10 Skin at Shear Tied Rib Attachments Rib 14 532/632 

57-20-12 Lower Wing Panel Under Flap Track Fittings Lower wing skin under forward and aft fittings at Rib 10 and 

Rib 14

532/632 

57-20-13-1 Upper Wing Panel Typical Stringers Typical Stringers at Rib 5. Stringers hidden under seal pans 

and sealant.

531/631532/632

57-20-13-2 Upper Wing Panel Typical Stringers Stringers 1-9 and 15-21, Rib 1-21 and Rib 22 to Rib 25. 531/631

532/632533/633

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

57-20-13/57-20-14/57-20-15/57-20-16/

57-20-17-1

Upper Wing Panel at Side-of-Body Double Plus Chord

Skin-to-Plus Chord Attachments at BBL 70.85 Except locations covered by 57-20-13/14/15/16/17-2

131/132531/631

57-20-1357-20-1457-20-1557-20-16

57-20-17-2

Upper Wing Panel at Side-of-Body Double Plus Chord

Skin-to-Plus Chord Attachments at BBL 70.85 Splice Stringer 14

131/132531/631

57-20-15 Upper Wing Panel Splice Stringer Stringer 14, Rib 12 to Rib 21. Locations adjacent to 

spar chords.

532/632 

57-20-17-1 Rear Spar Upper Chord 

(Skin Flange Inspections)

Rib 1 to 13 Non-Hidden 531/631

532/632

57-20-17-2 Rear Spar Upper Chord 

(Skin Flange Inspections)

Rib 1 to 13 Hidden by stiffeners, rib posts or fittings. 531/631

532/632

57-20-17-3 Rear Spar Upper Chord 

(Web Flange Inspections)

Rib 1 to 13 Non-Hidden 531/631

532/632

57-20-17-4 Rear Spar Upper Chord 

(Web Flange Inspections)

Rib 1 to 13 Hidden by stiffeners, rib posts or fittings. 531/631

532/632

57-20-19 Wing Upper Skin Tab at R1 Nacelle Fitting Fasteners common to skin and R1 Fitting. 532/632 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

57-20-22 Front Spar Web Crack – Typical Details Rib 1 to 6 and Rib 7 to 27. Web at Stiffeners, Fittings, or 

Brackets

531/631532/632533/633534/634

57-20-24-1 Outboard Wing Rear Spar Web Typical Details Rib 1-27 531/631

532/632

57-20-24-2 Outboard Wing Rear Spar Web Typical Details Rib 1-27, (Hidden) Except Locations Covered by 57-20-24/25/

26

532/632533/633534/634

57-20-24/57-20-25/

57-20-26

Rear Spar Web at Trunnion Attachment, MLG and T.E. Fittings

Rib 1 to 27 Web at attachment to T.E. fittings 551/651

561/661571/671

57-20-29-1 Rib 25 Upper and Lower Horizontal Flange WBL 616.75 533/633 

57-20-29-2 Rib 27, Upper and Lower Rib Flange to Skin 

Attachments

WBL 658.17, Front Spar to Rear Spar 534/634 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

57-20-29-3 Rib 27, Front and Rear Spar Tension Fittings WBL 658.17 534/634 

57-20-35/57-20-36/57-20-37/57-20-38/

57-20-39

Strut-to-Wing Attachments Zones 431/441/434/444 434/444

431/441

57-31-02-1 In-Spar Rib, Station 0, Winglet Tension Bolt Holes common to Winglet Sta 0 Rib 527/627 57-31-02-2 In-Spar Rib, Sta 0, Bolt Holes Lower Flange (Fwd Lower), Winglet common to Sta 0 Rib 527/627 

57-51-15 Inboard Actuator Support Fittings MLG Support Structure / Fixed T.E. 552/652 

57-51-16 Gear Beam Inboard Support MLG Support Structure/Inboard Support Fitting 551/651 

57-53-01-1a No. 1 Support, Track Assy Outboard Flap, Outboard Track, WBL 357.7 544/644 

57-53-01-1b No. 1 Support, Track Assy Outboard Flap, Outboard Track, WBL 357.7 544/644 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

57-53-02 Support, Forward Fitting Assy Forward Support Fitting, Flap Tracks 1, 2 and 3, WBL 357.7, 

254 and 164

544/644543/643542/642

57-53-03-1a No. 2 Support, Track Assy Outboard Flap, Inboard Track, WBL 254.0 543/643 

57-53-03-1b No. 2 Support, Track Assy Outboard Flap, Inboard Track, WBL 254.0 543/643 57-53-06-1a No. 3 Support, Track Assy Inboard Flap, Outboard Track, WBL 164 542/642 57-53-06-1b No. 3 Support, Track Assy Inboard Flap, Outboard Track, WBL 164 542/642 

57-53-09 No. 4 Support, Aft Link Pins Inboard Flap, Inboard Track Aft Link, WBL 64 541/641 

57-53-10-1a No. 4 Support, Track Assy Inboard Flap, Inboard Track, WBL 64 541/641 57-53-10-1b No. 4 Support, Track Assy Inboard Flap, Inboard Track, WBL 64 541/641 

57-53-11 No. 4 Support, Forward Fitting Assy Inboard Flap, Inboard Track, WBL 64, Forward Fitting 

Primary Lug

541/641 

57-53-12-1 Front Spar, Inboard Main Flap Front Spar Upper Chord, away from rib, ITEF MFSTA 73 to 167 553/653 

57-53-12-2 Front Spar, Inboard Main Flap Front Spar Upper and Lower Chord, at rib, ITEF MFSTA 73 

to 167

553/653 

57-53-12-3 Front Spar cutout, Inboard Main Flap Front Spar Cutout / Fitting, ITEF MFSTA 155 553/653 

57-53-13-1 Rear Spar, Inboard Main Flap Rear Spar Chord, at fitting inboard and outboard cutout, ITEF 

MFSTA 85 and 143

553/653 

57-53-13-2 Rear Spar, Inboard Main Flap Rear Spar Chord, at inboard and outboard pushrod cutout, 

ITEF MFSTA 91 and 149

553/653 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

57-53-13-3 Rear Spar, Inboard Main Flap Rear Spar Upper Chord, away from rib, ITEF MFSTA 73 to 167 553/653 

57-53-13-4 Rear Spar, Inboard Main Flap Rear Spar Upper Chord, at rib, ITEF MFSTA 73 to 167 553/653 

57-53-14 Upper Inspar Skin Panels, Inboard Flap Skin at Rear Spar chord, ITEF MFSTA 73 to 167 553/653 57-53-17 Inboard Torque Tube Rib, Inboard Flap Rib lower chord 553/653 

57-53-20 Torque Tube, Inboard Flap Torque Tube 553/653 57-53-21 Rear Spar, Inboard Main Flap Aft Flap Track Support Assy, ITEF MFSTA 85 and 143 553/653 

57-53-22 No. 3 Carriage Assy, Inboard Flap Carriage plate, fwd and aft lug 553/653 

57-53-23-1 No. 4 Carriage Assy, Inboard Flap Carriage plate, fwd and aft lug 553/653 57-53-23-2 No. 4 Carriage Assy, Inboard Flap Carriage plate, Torque Tube Attachment Hoop 553/653 

57-53-23-3 No. 4 Carriage Assy, Inboard Flap Carriage plate, Upper Rub Pad Hole 553/653 

57-53-24-1 No. 1 Carriage Assy, Outboard Flap Outboard Carriage Roller Boss, WBL 357.7 567/667 

57-53-24-2 No. 1 Carriage Assy, Outboard Flap Outboard Carriage Aft Bridge Support, WBL 357.7 567/667 

57-53-25-1 No. 2 Carriage Assy, Outboard Flap Inboard Carriage Roller Boss, WBL 254 567/667 

57-53-25-2 No. 2 Carriage Assy, Outboard Flap Inboard Carriage Aft Bridge Support, WBL 254 567/667 57-53-26-1 Front Spar, Outboard Flap Spar upper and lower chord at ribs (spar hidden), 

Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327

567/667 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

57-53-26-2 Front Spar, Outboard Flap Spar upper and lower chord between ribs (front spar visible),

Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327

567/667 

57-53-27-1 Rear Spar, Outboard Flap Aft Flap Track Cutouts #2 and #3 567/667 

57-53-27-2 Rear Spar, Outboard Flap Rear Spar upper and lower chord at ribs, 

Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327

567/667 

57-53-27-3 Rear Spar, Outboard Flap Rear Spar upper and lower chord between ribs, 

Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327

567/667 

57-53-29 Lower Skin, Outboard Flap Front and Rear Spar lower chord skin interface, WBL 254 to 

WBL 358

567/667 

57-53-31 Front Spar Spigot Fitting, Outboard Flap Fwd Spigot Fitting, WBL 254 and 358 567/667 57-53-32 Rear Spar Spigot Fitting, Outboard Flap Aft Spigot Fitting Assy, WBL 254 and 358 567/667 

57-53-35 Aft Flap Track Support Ribs, Outboard Flap Aft Flap Track Support Ribs #2 and #3 between WBL 254.0 

and 358.0.

567/667 

57-70-01 Hinge / Actuator Fittings, Inboard Spoiler #6 Lugs on the Hinge and Actuator fittings 552/652 

<1> These PSEs require supplemental inspections only if the Baseline Structures Program has been escalated.

<2> No airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures are val

manual, and accepted by the FAA.

<3> The inspection threshold for the 737-700IGW and 737-700C horizontal stabilizer with production installed winglets is 10,000 fligh

whichever occurs first. The published DTR Check Form for this PSE is not applicable to the 737-700IGW or the 737-700C with pr

Boeing for the FAA-approved DTR Check Form when reaching this threshold.

<4> The inspection threshold for airplanes with a redesigned horizontal stabilizer inspar lower skin is 10,000 flight cycles or 20,000 fl

This design change applies to all 737 minor models beginning at Line Number 3624. The published DTR Check Form for this PS

a redesigned horizontal stabilizer inspar lower skin. Contact Boeing for the FAA-approved DTR Check Form when reaching this 

TABLE 9-2 AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

PSE # DTR CHECK FORM TITLE LOCATION ZONE REF

OCT 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

52-11-02 Main Entry Door See Table Entry and DTR Form for PSE 52-13-02-3 

52-13-02-3 Aft Entry Door Forward and Aft Edge of Door Skin and Beams. Also:

PSE 52-41-02-3 Forward Galley DoorPSE 52-41-04-3 Aft Galley DoorPSE 52-11-02 Main Entry Door

52-21-04 Automatic Overwing Door Lower Frame at stop/guide fitting 

52-41-02-3 Forward Galley Door See Table Entry and DTR Form for PSE 52-13-02-3 52-41-04-3 Aft Galley Door See Table Entry and DTR Form for PSE 52-13-02-3 

52-48-04-2 Electronic Equipment Access Door Aluminum 

Casting Only

Bounded by LBL 5.70, RBL 14.12, frame STA 325.07 and STA 349.13

53-10-02-1 Circumferential Skin Splice, STA 259.5 S-7L to S-14L, S-7R to S-14R both FWD and AFT Side of Joint 

53-10-03-1 Longitudinal Lap Splice S-4L & S-4R, STA 259.5 to 360 Upper Fastener Row, Upper 

Skin. Also:PSE 53-30-04-1 STA 360 to 540PSE 53-40-03-1 STA 540 to 727PSE 53-60-04-1 STA 727 to 887PSE 53-70-03-1 STA 887 to 1016

53-10-03-2 Longitudinal Lap Splice S-4L & S-4R, STA 259.5 to 360 Lower Fastener Row, Lower Skin 

DEC 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-10-03-3 Longitudinal Lap Splice S-14L, STA 259.5 to 294.5, 350 to 360, Upper Row, Upper Skin.

S-14R, STA 259.5 to 277, 344 to 360, Upper Row, Upper Skin

53-10-03-4 Longitudinal Lap Splice S-14L, STA 259.5 to 294.5, 350 to 360, Lower Row, Lower Skin. 

S-14R, STA 259.5 to 277, 344 to 360, Lower Row, Lower Skin

53-10-03-5 Longitudinal Lap Splice S-24L STA 259.5 to 334, & S-24R STA 259.5 to 360 Upper 

Fastener Row, Upper Skin

53-10-04-1 Cutout - Crew Cab Windows AB Post 

53-10-04-2 Cutout - Crew Cab Windows CD Post, Left and Right 

53-10-04-2A Cutout - Crew Cab Windows See Table Entry and DTR Form for PSE 53-10-04-2 

53-10-04-3 Cutout - Crew Cab Windows EF Post, Left and Right 

53-10-04-4 Cutout - Crew Cab Windows BD Sill Left and Right 

53-10-04-5 Cutout - Crew Cab Windows Point D Fitting - Left and Right Side 

53-10-04-6 Cutout - Crew Cab Windows X-750 Angle at B-D Sill Inner Chord Left and Right Sides of 

the Aircraft

53-10-05-1 Crown Skin Panel - Fwd of STA 259.5 Longitudinal Splice at BL 0 

53-10-06-1 Section 41 Side Panel, Pan Door Cutout STA 216.2, WL 235.5 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-10-08-1 Crown Skin Panel STA 259.5 to 360 See Table Entry and DTR Form for PSE 53-30-01-2 

53-10-12-2 Cutout - Fwd Access Door, Aft Edge Frame, 

BS 219.8

See Table Entry and DTR Form for PSE 53-10-23-1 

53-10-13-1 Cutout - Electronic Equipment Door Cutout Bounded by Stations 323.7 & 351.2, and RBL 15.47 & 

LBL 6.74

53-10-14-4 Cutout - FWD Entry Door Frame STA 303.9 from S-11L to S-12L 

53-10-14-5 Cutout - FWD Entry Door Frame STA 303.9 from S-7L to S-11L and S-12L to S-13L 

53-10-14-7 FWD Entry Door FWD Edge Frame Stops Stop Fittings at S-7 thru S-16 

53-10-14-8 FWD Entry Door FWD Edge Frame Stop Straps at S-7 thru S-14 

53-10-14-9 FWD Entry Door FWD Edge Frame Stops Stop Straps at S-15 and S-16 

53-10-14-10 FWD Entry Door Aft Edge Frame Stops S-15 and S-16 Tension Straps at STA 351.2 Frame Inner Chord 

53-10-14-11 FWD Entry Door Aft Edge Frame Stops Aft Frame Stops @ Inner Flange Holes @ Approx. STA 348.2 

(S-7 to S-14)

53-10-14-12 Forward Entry Door Cutout Lower Edge of Cutout STA 303 to STA 350 around and under 

Scuff Plates. Also:PSE 53-10-15 Forward Galley Door Cutout

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-10-15 Forward Galley Door Cutout See Table Entry and DTR Form for PSE 53-10-14-12 

53-10-15-2 Forward Galley Door Surround Structure Door 

Stop Backup Structure

Forward Edge Frame at Stops #1, #2, #5, and #6 Intercostal Tension Straps

53-10-15-4 Cutout - FWD Galley Door STA 291.5 & STA 328.5, S-8R to S-14R 

53-10-18-1 Bulkhead, STA 294.5 Nose Wheel Well Aft Bulkhead WL 172 Beam at BL 17 

53-10-19-4 Nose Wheel Well Side and Top Panels Aft access Cutout forward Vertical Beam STA 260, WL 170 to 

WL 184

53-10-20-2 Nose Landing Gear Support Fittings Drag Brace Fittings STA 262, BL 16 WL 189.3 

53-10-20-3 Nose Landing Gear Trunnion Support Fitting Inboard and Outboard Fitting Segments BS 294.5, WL 156.1, 

BL 16

53-10-21-1 Air Stair Door Cutout Upper and Lower Sills STA 303.8 to STA 348 (Internal) 53-10-21-2 Air Stair Door Cutout Upper and Lower Sills STA 303.8 to STA 348 (External) 53-10-21-4 Airstair Door Cutout Forward and Aft Edge Frames STA 303.9 & 351.2 at Lower 

Corners

53-10-23-1 Forward Nose Wheel Well Cutout Forward Edge Frame - BS 224.8. Also:

PSE 53-10-12-2 Fwd Access Door Aft Frame - BS 219.8

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-30-01-2 Crown Skin Panel, STA 360 to 540 BS 360-540, S-10L to S-10R. Also:

PSE 53-10-08-1 STA 259.5 to 360PSE 53-40-01-1 STA 540 to 727PSE 53-40-17-4 STA 706PSE 53-60-01-2 STA 727 to 887 - Remove Dorsal Fin 

as RequiredPSE 53-70-04-1 STA 887 to 1016 - Remove Dorsal Fin as Required

53-30-01-4 Crown Skin Panel, STA 360 to 540 Antenna Cutouts at STA 385, STA 430, STA 500A 

53-30-01-5 Satcom Aero-H Antenna Installation Section 43 STA 500 S-6 to S-7 

53-30-02-1 Fuselage Side Skin Panels BS 360 to 540, S-14 to S-24. Also:

PSE 53-60-02-1 STA 727 to 887, S-14 to S-23PSE 53-30-03-1 STA 360 to STA 540 Bilge Skin, S-24L to S-24R

PSE 53-60-03-1 STA 727 to STA 887 Bilge Skin, S-23L to S-23R

53-30-02-4 Fuselage Side Skin Panels Under the Wing-toBody Fairing STA 360 to STA 540. Also: PSE 53-60-02-4 STA 727 to STA 887 53-30-03-1 Fuselage Bilge Skin Panels, BS 360 to 540, 

S-24L to S-24R

See Table Entry and DTR Form for PSE 53-30-02-1 

53-30-03-5 Bilge Skin, STA 360 to STA 540 VHF Antenna Hole Cutout. Also:

PSE 53-60-03-6 STA 727 to 887

53-30-04-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 

53-30-04-2 Longitudinal Lap Splice S-4L & S-4R, STA 360-540 Lower Fastener Row, Lower Skin. 

Also:PSE 53-40-03-2 STA 540 to 727PSE 53-60-04-2 STA 727 to 887

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-30-04-3 Longitudinal Lap Splice S-10L & S-10R, STA 360-540 Upper Fastener Row, Upper Skin. 

Also:PSE 53-40-03-3 STA 540 to 727PSE 53-60-04-3 STA 727 to 887

53-30-04-4 Longitudinal Skin Splice S-10L & S-10R, STA 360-540 Lower Fastener Row, Lower Skin. 

Also:PSE 53-60-04-4 STA 727 to 887

53-30-04-5 Longitudinal Lap Splice S-14L & S-14R, STA 360 to 540 Upper Fastener Row, Upper 

Skin. Also: PSE 53-60-04-5 STA 727 to 887

53-30-04-6 Longitudinal Lap Splice S-14L & S-14R, STA 360 to 540 Lower Fastener Row, Lower 

Skin. Also: PSE 53-60-04-6 STA 727 to 887

53-30-04-7 Longitudinal Lap Splice S-24L & S-24R, STA 360 to 540 Except at Cargo Door Cutout. 

Upper Fastener Row. Upper (Inner) Skin

53-30-04-8 Longitudinal Lap Splice S-24L & S-24R, STA 360 to 540 Except at Cargo Door Cutout. 

Lower Fastener Row. Lower (Outer) Skin

53-30-05-1 Window Belt STA 360 to 540 - Corners of 

Window Frame

See Table Entry and DTR Form for PSE 53-60-05-1 

53-30-05-2 Window Belt STA 360 to 540 - Window Frame See Table Entry and DTR Form for PSE 53-60-05-2 53-30-05-3 Window Belt STA 360 to 540 - Skin See Table Entry and DTR Form for PSE 53-60-05-3 

53-30-07-1

<2>

BS 540 Circumferential Splice Lead Crack in Skin Splice Strap 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-30-08-1 Forward Cargo Door Surround Forward and Aft 

Edge Frames at STA 440 and 492.4. (Outer Chord Between S-17R and S-26R; except at Door Stops and Sills Location)

See Table Entry and DTR Form for PSE 53-60-08-4 

53-30-08-2 Forward Cargo Door Surround Forward and Aft 

Edge Frames at STA 440 and 492.4. (Outer Chord at Door Stops Location and at Frame/Sill Intersections)

See Table Entry and DTR Form for PSE 53-60-08-5 

53-30-08-3 Forward Cargo Door Surround (Forward and 

Aft Edge Frame Inner Chords Between S-18R and S-26R).

See Table Entry and DTR Form for PSE 53-60-08-1 

53-30-08-4 Forward Cargo Door Surround Structure 

(Forward and Aft Edge Frame Inner Chords Between S-17R and S-18R)

See Table Entry and DTR Form for PSE 53-60-08-2 

53-30-08-5 Forward Cargo Door Surround Structure 

(Forward and Aft Edge Frame Inner Chords at S-18R)

See Table Entry and DTR Form for PSE 53-60-08-3 

53-30-08-6 Forward Cargo Door Surround Structure Skin Splice at S-24R, BS 440 & 492.4. Also:

PSE 53-60-08-6 Aft Cargo Door Skin Splices at BS 794.4 and 847

53-30-08-7 Forward Cargo Door Surround Structure 

(Forward and Aft Edge of Door STA 440 and STA 492.4 S-18R to S-25R)

See Table Entry and DTR Form for PSE 53-60-08-7 

53-30-08-8 Forward Cargo Door Surround Structure 

(Forward and Aft Edge of Door STA 440 and STA 492.4 S-18R to S-25R)

See Table Entry and DTR Form for PSE 53-60-08-8 

53-30-08-9 Forward Cargo Door Surround Structure Skin and Bearstrap at Corners of Cutout

See Table Entry and DTR Form for PSE 53-60-08-9

53-30-08-10 Forward Cargo Door Surround Structure Upper Sill Outer Chord. Also:

PSE 53-60-08-10 Aft Cargo Door Upper Sill

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-30-08-11 Forward Cargo Door Surround Structure Upper Sill Inner Chord 

53-30-08-12 Forward Cargo Door Surround Structure Lower Main Sill Chords between STA 461 & 478. Also:

PSE 53-60-08-12 Aft Cargo Door Surround Structure Lower Main 

Sill STA 807 to 827

53-30-09-1 Forward Cargo Door Stops (Forward and Aft 

Edge of Forward Cargo Door)

See Table Entry and DTR Form for PSE 53-60-09-1 

53-30-09-3 Forward Cargo Door Fittings and Stops at the 

Forward and Aft Edge Frames (Backup Fittings 

and Intercostals)

See Table Entry and DTR Form for PSE 53-60-09-3 

53-30-11-1 Wing to Body Lower Drag Angle BS 518 to BS 555 above S-24 

53-30-11-2 Wing to Body Upper Drag Angle Near BS 540, Between S-21 and S-22 

53-30-11-3 Wing to Body Upper Drag Angle Near BS 540, Between S-21 and S-22 

53-40-01-1 Crown Skin Panel STA 540 to 727 See Table Entry and DTR Form for PSE 53-30-01-2 

53-40-02-2

<2>

Section 44 Side Panel, Circumferential Skin STA 540 to STA 727, S-14 to S-17 

53-40-03-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 53-40-03-2 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-2 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-40-03-3 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-3 

53-40-04-1 Window Belt, STA 540 to 727 Stringer 11 and Stringer 13 

53-40-04-2 Window Belt, STA 540 to 727 Between Windows S-11 to S-13 

53-40-06-5

<2>

Circumferential Skin Splice, STA 727 Circumferential Skin Splice at BS 727 

53-40-07-1

<2>

Stringer Splice STA 663 Splice at Stringer 11 

53-40-07-2 Stringer Splice STA 663 Splice at Stringer 11 and Stringer 13 

53-40-08-1 Keel Beam Chords, Stiffeners, and Splice Keel Beam Side Panel Webs STA 540 to STA 663 53-40-10-1 Stiffener Attachment to Floor Beam STA 727 LBL 45.5 & RBL 45.5 @ WL 202.6 

53-40-11-1 Stringer 18 Strap Side of Body STA 717 to STA 727 

53-40-12-1 Stringer 18A Chord and Links STA 663 Link Lugs 

53-40-13-1 Pressure Deck Web and Stiffeners STA 663.75 to STA 727 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-40-14-1 Frame Splice @ STA 540 Inner Chord between S-9 and S-10 

53-40-14-4 BS 540 Bulkhead Skin at Outer Chord, S-9L to S-9R 

53-40-14-5 BS 540 Bulkhead Picklefork Fitting, S-17 and Below 53-40-15-1 BS 663 Bulkhead Outer Chord Between S-8 and S-11 53-40-15-3 BS 663 Bulkhead Inner Chord between S-9 and S-17, LH & RH 

53-40-15-4 BS 663 Bulkhead Picklefork Fitting, S-17 and Below 

53-40-16-1A Aft Wheel Well Bulkhead STA 727 Lower Chord, S-21 to S-27 

53-40-16-1B Aft Wheel Well Bulkhead STA 727 Lower Chord, S-21 to S-27 

53-40-16-2 Wheel Well Aft Bulkhead Frame Inner Chord at STA 727, WL 201 

53-40-16-2A Wheel Well Aft Bulkhead Frame Inner Chord at STA 727, WL 201 

53-40-16-3 Wheel Well Aft Bulkhead and Pressure Web, 

STA 727

Lower Frame STA 727 

53-40-16-5 Aft Wheel Well Bulkhead and Pressure Web, 

STA 727

Frame STA 727, S-9L to S-9R 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-40-16-6 Aft Wheel Well Bulkhead Frame, STA 727 STA 727 between S-9 to S-10 

53-40-17-1 Side Strut Support Frame STA 706 Frame Inner & Outer Chords and Fail-Safe Angle S-10 to S-13 

53-40-17-2 High Part of the Transition in the Frame See Table Entry and DTR Form for PSE 53-40-17-1 

53-40-17-4 Crown Skin at Frame STA 706 See Table Entry and DTR Form for PSE 53-30-01-2 

53-40-18-1 Main Landing Gear Support Frame, STA 695 Inner Chord at Crease Beam STA 695 53-40-18-2 Main Landing Gear Support Frame, STA 695 Stub Beam Upper Chord 

53-40-19-1 Main Landing Gear Support Frame, STA 716 Frame Inner Chord and Web at S-16 

53-40-19-2 Main Landing Gear Support Frame, STA 716 Stub Beam Upper Chord at Crease Beam Chord Attachment 

53-40-19-3 Main Landing Gear Support Frame, STA 716 Stub Beam Web at Floor Clip Attachment 

53-40-19-3A Main Landing Gear Support Frame, STA 716 See Table Entry and DTR Form for PSE 53-40-19-3 

53-40-20-3 Wheel Well Frames, STA 559 (BBJ2), 

STA 559, 578, & 601 (BBJ). (Splice Angle Between S-9 to S-10).

See Table Entry and DTR Form for PSE 53-40-21-1 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-40-21-1 Wheel Well Frame, STA 685 Outer Chord Splice Angle, S-9 to S-10. Also:

PSE 53-40-20-3, Frames at STA 559 (BBJ2)

Frames at STA 559, STA 578, and STA 601 (BBJ)

53-40-21-2 Wheel Well Frame, STA 685 Frame Inner Chord S-13 to S-15 53-40-21-3 Wheel Well Frame, STA 685 Frame Inner Chord S-17 to S-14 

53-40-21-4 Wheel Well Frame, at STA 685 Stub Beam Upper Chord 

53-40-22-2 Overwing Emergency Exit Cutout Edge Frame STA 616 Outer Chord, S-10 to S-13 53-40-22-3 Overwing Emergency Exit Cutout Skin 

Assembly & Frame Outer Chord

Edge Frame 578 near Stringer S-11 to S-13 

53-40-22-4 Overwing Emergency Exit Cutout (Inspection 

applicable only to BBJ 1 Lower Sill Inner Splice Strap STA 616 and STA 639).

See Table Entry and DTR Form for PSE 53-40-22-13 - BBJ2 

53-40-22-5 Overwing Emergency Exit Cutout Upper Edge and Both Upper Corners of Cutout from S-11 @ 

STA 616 to S-11 @ STA 639

53-40-22-6 Overwing Emergency Exit Cutout - Door 

Cutouts Corners

Upper Edge of Doors from S-11 @ STA 578 to S-11 @ STA 601 and from S-11 @ STA 616 to S-11 @ STA 639

53-40-22-7 Overwing Emergency Exit Cutout Edge Frame Outer Chord under stop backup fittings at S-11 

and S-12

53-40-22-8A Overwing Emergency Exit Cutout Both Lower Corners and Lower Edge of Cutout from S-14 

STA 616 to S-14 STA 639

53-40-22-9 Overwing Emergency Exit Cutout All Four Lower Corners (intersection of lower sill and edge frames 

578, 601, 616 and 639) + Skin Assy over the Lower Sills.

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

ZONE

 REF

DEC 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

53-40-22-10 Overwing Emergency Exit Cutout 

Skin and Frame Assy. Section @ STA 616 & S-13

Covered Region: Edge Frame 616 from S-13 to S-15 and Edge Frame 639 from S-10 to S-15

53-40-22-11 Overwing Emergency Exit Cutout 

Skin Assy and Frame Outer Chord

Door Edges at STA 578 S-13 to S-15 and at STA 601, 616, and 

639 S-10 to S-15

53-40-22-12 Overwing Emergency Exit Cutout Lower Aft Corner Frame 616 and 639 at Lower Sill. 

Also: Frames 578 and 601 for BBJ2 and BBJ3.

53-40-22-13 Overwing Emergency Exit Cutout Lower Sill Inner Splice Strap at BS 578, 601, 616, and 639. Also: 

PSE 53-40-22-4 Frame 616 and 639 on the BBJ (737-700IGW)

53-40-23-1 Overwing Emergency Exit Door Stops 

and Fittings

Door Stops attached to the Forward and Aft Door Edge Frames 

53-40-23-2 Overwing Emergency Exit Door Stops 

and Fittings

Door Stops Intercostals between STA 601 and 616 

53-40-23-3 Overwing Emergency Exit Door Stops 

and Fittings

Door Stops Backup Fitting Attachment to Window Frames at S-11 and S-12 at BS 616 for (BBJ) or BS 578 (BBJ2)

53-40-24-1 Pressure Deck Attachment to Rear Spar 

Extension

BS 663 

53-60-01-2 Crown Skin Panel STA 727 to 887 See Table Entry and DTR Form for PSE 53-30-01-2 

53-60-01-4 Crown Skin Panel STA 727 to 887 ADF Antenna Cutout STA 727 + 9, RBL 5

SATCOM Antenna Cutout STA 747, STR-1

53-60-01-5 SATCOM Antenna Installation 

(Canadian Marconi and Honeywell)

Section 46: STA 767 between S-1 and S-2L 

53-60-01-6 SATCOM Antenna Installation (all except 

those covered by PSE 53-60-01-5)

Section 46: STA 767 between S-1 and S-2L 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-60-02-1 Fuselage Side Skin Panels (BS 727 to BS 887, 

S-14 to S-23)

See Table Entry and DTR Form for PSE 53-30-02-1 

53-60-02-2 Fuselage Side Skin Panels (BS 727 to BS 887, 

S-14 to S-23)

See Table Entry and DTR Form for PSE 53-30-02-1 

53-60-02-3 Fuselage Side Skin Panels (BS 727 to BS 887, 

S-14 to S-23)

See Table Entry and DTR Form for PSE 53-30-02-1 

53-60-02-4 Fuselage Side Skin Panels Under the Wing-toBody Fairing See Table Entry and DTR Form for PSE 53-30-02-4 53-60-03-1 Fuselage Bilge Skin Panels (BS 727 to 887, 

S-23L to 23R)

See Table Entry and DTR Form for PSE 53-30-02-1 

53-60-03-6 Fuselage Bilge Skin Panels (BS 727 to 887, 

VHF Antenna Hole Cutout).

See Table Entry and DTR Form for PSE 53-30-03-5 

53-60-04-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 53-60-04-2 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-2 53-60-04-3 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-3 53-60-04-4 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-4 53-60-04-5 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-5 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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D626A001-CMR

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53-60-04-6 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-30-04-6 

53-60-04-7 Longitudinal Lap Splice S-23L & S23R, STA 727 to 887 except at Cargo Door Cutout. 

Upper Fastener Row, Upper (Inner) Skin. Also: PSE 53-70-03-5 STA 887 to 1016

53-60-05-1 Window Belt STA 727 to 888 Corners of Window Frame. Also: 

PSE 53-30-05-1 STA 360 to 540PSE 53-70-09-1 STA 888 to 927

53-60-05-2 Window Belt STA 727 to 888 Window Frames. Also:

PSE 53-30-05-2 STA 360 to 540PSE 53-70-09-2 STA 888 to 927

53-60-05-3 Window Belt STA 727 to 888 Skin. Also:

PSE 53-30-05-3 STA 360 to 540PSE 53-70-09-3 STA 888 to 927

53-60-08-1 Aft Cargo Door Surround Structure Forward and Aft Edge Frame inner Chords between 

S-18R & S-26R. Also: PSE 53-30-08-3 Forward Cargo Door

53-60-08-2 Aft Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords between 

S-17R & S-18R. Also: PSE 53-30-08-4 Forward Cargo Door

53-60-08-3 Aft Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords at S-18R. Also:

PSE 53-30-08-5 Forward Cargo Door

53-60-08-4 Aft Cargo Door Surround Forward and Aft 

Edge Frames at BS 794.37 and 847

Outer Chord Between S-16R and S-26R (Except at Door Stops and Sill Location). Also:PSE 53-30-08-1 Forward Cargo Door, STA 440 and STA 492.4, S-17R to S-26R

53-60-08-5 Aft Cargo Door Surround Forward and Aft 

Edge Frames at BS 794.37 and 847

Outer Chord at Door Stops Location and at Frame/Sill Intersections. Also:PSE 53-30-08-2 Forward Cargo Door, STA 400 & STA 492.4

53-60-08-6 Aft Cargo Door Surround Structure 

(Skin Splice at S-23R BS 794.4 and 847)

See Table Entry and DTR Form for PSE 53-30-08-6 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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DEC 2011
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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-60-08-7 Aft Cargo Door Surround Structure Forward and Aft Edge of Door STA 794.4 and STA 847, 

S-18R to S-25R. Also:PSE 53-30-08-7 Forward Cargo Door at STA 440 and STA 492.4

53-60-08-8 Aft Cargo Door Surround Structure Forward and Aft Edge of Door STA 794.4 and STA 847, 

S-18R to S-25R. Also:PSE 53-30-08-8 Forward Cargo Door at STA 440 and 492.4

53-60-08-9 Aft Cargo Door Surround Structure Skin and Bearstrap at Corners of Cutout.

Also: PSE 53-30-08-9 Forward Cargo Door Surround Structure

53-60-08-10 Aft Cargo Door Surround Structure 

(Upper Sill Outer Chord)

See Table Entry and DTR Form for PSE 53-30-08-10 

53-60-08-11 Aft Cargo Door Surround Structure Upper Sill Inner Chord 

53-60-08-12 Aft Cargo Door Surround Structure 

(Lower Main Sill Chords Between STA 807 and 827)

See Table Entry and DTR Form for PSE 53-30-08-12 

53-60-09-1 Aft Cargo Door Stop Forward and Aft edges of Aft Cargo Door. Also:

PSE 53-30-09-1 Forward Cargo Door

53-60-09-3 Aft Cargo Door Fittings and Stops at the 

Forward and Aft Edge Frames

Backup Fittings and Intercostals. Also:PSE 53-30-09-3 Forward Cargo Door

53-60-12-2 Mid Exit Door Surround Structure Skin and 

Bearstrap

Between BS 727H + 8.85” and BS 727I + 13.15” 

53-60-12-3 Mid Exit Door Surround Structure Upper Main 

Sill

STA 727H to STA 727J 

53-60-12-5 Skin Lap Splice, Lower Row at S-10L to 

S-10R, Mid Exit Door Surround - Section 46

Between BS 727G and BS 727K 

53-60-12-6 Skin Lap Splice, Lower Row at S-14 to S-14, 

Mid Exit Door Surround - Section 46

Between BS 727G and BS 727K 

53-60-13-1 Mid Exit Door Stop Fittings BS 727H + 8.85” and BS 7271 + 13.15” 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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DEC 2011
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D626A001-CMR

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53-70-03-1 Longitudinal Lap Splice See Table Entry and DTR Form for PSE 53-10-03-1 

53-70-03-2 Longitudinal Lap Splice S-4L & S-4R, STA 887-1016 Lower Fastener Row, Lower Skin 

53-70-03-3 Longitudinal Lap Splice S-14L, STA 888 to 947, 1006 to 1016, Upper Row, Upper Skin.

S-14R, STA 888 to 947, 996 to 1016 Upper Row, Upper Skin

53-70-03-4 Longitudinal Lap Splice S-14L, STA 888 to 947, 1006 to 1016, Lower Row, Lower Skin.

S-14R, STA 888 to 947, 996 to 1016 Lower Row, Lower Skin

53-70-03-5 Longitudinal Lap Splice (S-23L and S-23R, 

STA 887 to 1016, Upper Fastener Row, Upper (Inner) Skin)

See Table Entry and DTR Form for PSE 53-60-04-7 

53-70-04-1 Crown Skin Panel STA 887 to 1016 See Table Entry and DTR Form for PSE 53-30-01-2 

53-70-07-3 Aft Entry Door, Forward Edge Frame Door 

Stop Backup Structure

Stops #1, #2, #6 and #7 

53-70-07-4 Aft Entry Door, Aft Edge Frame Door Stop 

Backup Intercostals

Stops Locations #1, #2, #6 and #7 

53-70-07-5 Cutout, Aft Entry Door Surround Structure Skin Around Perimeter of Cutout. Also:

PSE 53-70-08-5 Aft Galley Door

53-70-07-6 Aft Entry Door Surround Structure Lower Sill Scuff Plate Installation. Also:

PSE 53-70-08-6 Aft Galley Door

53-70-07-11 Cutout, Aft Entry Door Surround Structure Upper Main Sill Inner Chord STA 951 to STA 1006. 

Also: PSE 53-70-08-11 Aft Galley Door

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-70-07-11A Cutout, Aft Entry Door Surround Structure Upper Main Sill Inner Chord STA 951 to STA 1006 

53-70-07-12 Cutout, Aft Entry Door Surround Structure Lower Main Sill - Inner and Outer Chord. Also:

PSE 53-70-08-12 Aft Galley Door

53-70-08-3 Aft Galley Door Forward Edge Frame Door 

Stop Backup Structure

Stops #1, #2, #5 and #6 

53-70-08-4 Aft Galley Door Aft Edge Frame Door Stop 

Backup Intercostals

Stop Locations #1, #2, #5 and #6 

53-70-08-5 Cutout, Aft Galley Door Surround Structure 

(Skin around Perimeter of Cutout)

See Table Entry and DTR Form for PSE 53-70-07-5 

53-70-08-6 Aft Galley Door Surround Structure See Table Entry and DTR Form for PSE 53-70-07-6 

53-70-08-11 Aft Galley Door Surround Structure See Table Entry and DTR Form for PSE 53-70-07-11 

53-70-08-11A Cutout, Aft Galley Door Surround Structure Upper Main Sill Inner Chord STA 951 to STA 1006 

53-70-08-12 Aft Galley Door Surround Structure 

(Lower Main Sill Inner and Outer Chord)

See Table Entry and DTR Form for PSE 53-70-07-12 

53-70-09-1 Window Belt STA 888 to 927 – Corners of 

Window Frame

See Table Entry and DTR Form for PSE 53-60-05-1 

53-70-09-2 Window Belt STA 888 to 927– Window Frame See Table Entry and DTR Form for PSE 53-60-05-2 

53-70-09-3 Window Belt STA 888 to 927 – Skin See Table Entry and DTR Form for PSE 53-60-05-3 

53-80-01-1 Bulkhead STA 1016 Pressure Chord 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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D626A001-CMR

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

53-80-01-2 Bulkhead STA 1016 Pressure Dome Webs between Tear Straps 

53-80-01-3 Bulkhead STA 1016 Pressure Dome Webs between Tear Straps Lap Splice 

(Visible Row)

53-80-01-4 Bulkhead STA 1016 Web at Pressure Chord Adjacent to Stiffeners 

53-80-01-5A Bulkhead STA 1016 Web at Pressure Chord Between Stiffeners, Str 5L to 7L and 

Str 5R to 9R

53-80-01-5B Bulkhead STA 1016 Web at Pressure Chord Between Stiffeners, Areas Outside 

of Str 5L to 7L and Str 5R to 9R

53-80-01-6 Bulkhead STA 1016 Web at Chord Splice Between S-1 and S-3, and between S-15 

and S-18

53-80-01-7 Bulkhead STA 1016 Pressure Dome Webs Lap Splice Under Stiffeners 

(Hidden Detail)

53-80-01-8 Bulkhead STA 1016 Pressure Dome Webs at Tear Straps 

53-80-01-9 Bulkhead STA 1016 Pressure Dome Webs at Lap Splice and Tear Strap Intersection 

53-80-01-11 Bulkhead STA 1016 Pressure Dome Webs at Lap Splice and Tear Strap Junctions 53-80-01-12 Bulkhead STA 1016 Pressure Dome Web at Tear Strap between Stiffeners 

53-80-01-13 Bulkhead STA 1016 Web at Chord Splice/Double between S-1 and S-3 

L/N 

Ex

53-80-02-1A Vertical Fin Front Spar Fitting, Bulkhead 

Attachment - STA 1016

Bulkhead Fittings @ STA 1016 

53-80-02-2 Vertical Fin Front Spar Fittings – STA 1016 Fitting Lugs 53-80-03-1 Stringer Splice Fittings STA 1016, S-9L to S-9R Forward and Aft of Bulkhead 

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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 REF

DEC 2011
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BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

53-80-13-2 STA 1042 Bulkhead Web ECS Duct Cutout 

53-80-14-1 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Vertical Beams

Vertical Beam at Horizontal Beam Splice 

53-80-14-3 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Horizontal Intercostals

See Table Entry and DTR Form for PSE 53-80-14-4 

53-80-14-4 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Horizontal Intercostals

STA 1042 Bulkhead Beams, Aft Horizontal Straps 

53-80-14-7 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Horizontal Intercostals

STA 1042 Bulkhead Beams, System Penetrations in Horizontal Intercostals

53-80-15-1 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Beam Lugs

STA 1042 Lugs, Links & Fittings - Bulkhead Beam End Lugs 

53-80-15-2A 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Lug Fittings

STA 1042 Lugs, Links & Fittings - Bulkhead Beam End Lugs Hidden By Attach (Clamshell) Fittings (RBL/LBL 10 & 23, WL 282, 269, and 256)

53-80-15-2B 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Lug Fittings

STA 1042 Lugs, Links & Fittings - Bulkhead Beam End Lugs Hidden By Attach (Clamshell) Fittings (WL 223)

53-80-15-3 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Beam Links

STA 1042 Lugs, Links & Fittings - Link Clevis Fittings 

53-80-15-4 737-900 BBJ3 LCA STA 1042 Pressure 

Bulkhead Attach Fittings

STA 1042 Lugs, Links & Fittings - Fwd Link Attach Fittings 

53-80-16-1 STA 1042 Bulkhead Chord Splice STA 1042 Bulkhead Fittings, APU Chord Splice Fitting 

53-80-17-2 737-900 BBJ3 LCA APU Inlet Enclosure APU Inlet Cutout Enclosure - Forward Pressure Panel, Visible 

Fastener Locations

53-80-17-3 APU Inlet Cutout Enclosure Installation Middle and Aft Pressure Panels, Visible Fastener Locations 

53-80-17-4 737-900 BBJ3 LCA APU Inlet Enclosure APU Inlet Cutout Enclosure - Mid Pressure Panel, Hidden by 

Stiffener

53-80-17-5 737-900 BBJ3 LCA APU Inlet Enclosure APU Inlet Cutout Enclosure - Mid Pressure Panel Hidden by 

STA 1030 Frame

53-80-17-6 APU Enclosure Installation Pressure Panels APU Inlet Enclosure - Aft Pressure Panel Hidden by STA 1030 

Frame

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

PSE # DTR CHECK FORM TITLE LOCATION

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D626A001-CMR

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

53-80-17-7 APU Enclosure Installation: Forward Pressure 

Panels

APU Inlet Enclosure - Fwd Pressure Panel Hidden by Stiffener 

53-80-17-8 APU Enclosure Installation: Stiffener at 

Fwd/Mid Pressure Panel Interface

APU Inlet Enclosure - Fwd/Mid Panel Interface Stiffener 

53-80-17-10 APU Enclosure Installation: Stiffener at Mid 

Pressure Panel

Section 48, RHS Only 

53-80-18-1 Section 48 Longitudinal Lap Splice Longitudinal Skin Lap Splices, Section 48, S-4 Lap, Upper Row, 

Outer Skin

53-80-18-2 Section 48 Longitudinal Lap Splice Longitudinal Skin Lap Splices, Section 48, S-4 Lap, Lower Row, 

Inner Skin

53-80-18-5 Section 48 Longitudinal Lap Splice Longitudinal Skin Lap Splices, Section 48, S-24 Lap, Upper Row, 

Outer Skin

53-80-18-6 Section 48 Longitudinal Lap Splice Longitudinal Skin Lap Splices, Section 48, S-24 Lap, Lower Row, 

Inner Skin

53-80-18-7 Section 48 Butt Splice at S-9R and S-9L Longitudinal Skin Butt Splice, Section 48, Upper and Lower 

Rows, Skin

53-80-18-8 Section 48 Butt Splice at S-9R and S-9L See Table Entry for DTR Form for PSE 53-80-18-7 

53-80-18-9 Section 48 Butt Splice at S-9R and S-9L Longitudinal Skin Butt Splice, Section 48, Upper Row, 

Splice Strap

53-80-18-10 Section 48 Butt Splice at S-9R and S-9L Longitudinal Skin Butt Splice, Section 48, Lower Row, 

Splice Strap

53-80-20-4 Side Skin Panel, STA 1016 to 1042 APU Inlet Cutout 53-80-21-1 Section 48, Side Skin Panel Side Skin Panel, STA 1016 to 1042 

<1> No airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures are valid

manual, and accepted by the FAA.

<2> These PSE's require supplemental inspections only if the Baseline Structures Program has been escalated.

TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITH SB 737-

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

C. AWLs – STRUCTURAL SAFE LIFE PARTS

ITEM LIFE LIMIT

Nose Landing Gear 75,000 Landings 

 Except Aft Lock Link (162A2115-2) 4,200 LandingsMain Landing Gear 75,000 LandingMain Landing Gear Support Structure 75,000 Landings [1] This value is based on analysis contained in document D101A805-14.[2] Except 115A1610 MLG Beam Support (Hanger link) pin (45,000 Landings).

NOTE: The following drawings contain a complete listing of 737-600/700/700C/800/900/900ER safe life parts:

161A0002, 737-X Main Landing Gear Component Interchangeability List

162A0002, 737-X Nose Landing Gear Safe Life Component List115A0007, 737 Trailing Edge Component Life Limited List

JUN 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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D. AWLs – SYSTEMS

ENGINE OIL CONSUMPTION LIMITATIONThe approved maximum oil consumption rate for the CFM56-7B engine installed on the model 737-700IGW (BBJ) with winglets 

have been established as 0.290 gallons per hour.The approved maximum oil consumption rate for the CFM56-7B27A engines installed on the model 737-700IGW (BBJ) without auxiliary tanks has been established as 0.25 gallons per hour.

The approved maximum oil consumption rate for the CFM56-7B engines installed on the model 737-800 with winglets has been 0.310 gallons per hour.The approved maximum oil consumption rate for the CFM56-7B engines installed on the model 737-900 airplane has been est

per hour.The approved maximum oil consumption rate for the CFM56-7B engines installed on the model 737-900ER aircraft with wingletanks has been established as 0.330 gallons per hour, and for aircraft without winglets and with no auxiliary fuel tanks has been 

0.340 gallons per hour.Operation of these specific airplane models, configured as described, with an engine oil consumption rate higher than these limas allowed under a special flight permit authorized under 14 CFR 21.197 and 21.199.

AUG 2011
D626A001-CMR

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

E. AWLs – FUEL SYSTEMS

INTRODUCTIONThe airplane systems maintenance requirements described in this section of the AWL document result from various 737 airplan

the FAA. These maintenance requirements are required under the Code of Federal Regulations (CFR) 43.16 and 91.403. The with the approval of the Seattle FAA Aircraft Certification Office (ACO). If the maintenance requirements cannot be accomplish

modifications, an alternate inspection, acceptable to the Seattle FAA ACO, 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. CDCCLs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO that is respo

model Type Certificate, or applicable regulatory agency. A critical fuel tank ignition source prevention feature may exist in the fuinstallation or in systems that, if a failure condition were to develop, could interact with the fuel system in such a way that an undevelop without this limitation. Strict adherence to configuration, methods, techniques, and practices as prescribed is required tthe CDCCL. Any use of parts, methods, techniques or practices not contained in the applicable CDCCL must be approved by t

responsible for the airplane model Type Certificate, or applicable regulatory agency. For each CDCCL, the word "maintenanceinstallation during alterations; therefore, adherence to the CDCCL is required during maintenance or alterations.ALIs identify inspection tasks related to fuel tank ignition source prevention which must be done to maintain the design level of 

life of the airplane. These ALIs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO 

airplane model Type Certificate, or applicable regulatory agency. Strict adherence to methods, techniques and practices as pre

ensure the ALI is complied with. Any use of methods, techniques or practices not contained in these ALIs must be approved by is responsible for the airplane model Type Certificate, or applicable regulatory agency.

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D626A001-CMR

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

USE OF ALTERNATE TOOLSThe Component Maintenance Manuals (CMM) listed in the AWLs are currently Seattle FAA ACO approved. If the CMM allows 

equivalent tools, test equipment or materials, use of an alternate or equivalent tool, test equipment or material does not require 

Seattle FAA ACO or local Regulatory Agency. For inside of the tank, use sealant type BMS 5-45 or equivalent per SRM 51-20-

use sealant type BMS 5-95 or equivalent per SRM 51-20-05.EXCEPTIONAL SHORT-TERM EXTENSIONSSince AWL intervals are based on estimations of the probability of an event, an exceptional short-term extension for each fuel sdocument may be made without jeopardizing safety. The local regulatory authority (e.g. a Principle Maintenance Inspector) muexceptional short-term extensions before they take place using procedures established with the local regulatory authority in the “exceptional short-term extension” process is applicable to AWL intervals. It should not be confused with the operator’s short-tnormal maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8900.1 FSIMS.The Seattle FAA ACO has accepted that these exceptional short-term extensions may be granted without consultation with tha1. The term “exceptional short-term extension” is defined as an increase in a System AWL interval that may be needed to cov

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

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.

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

Seattle FAA ACO must approve, prior to its use, any desired extension not explicitly listed above.This exceptional short term extension listed above applies to airlines that fall under the United States FAA jurisdiction only. Opthe U.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

REGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval from the Seattle FAA ACO. Th

under the US FAA jurisdiction only and to airplanes registered in the US. All other operators should obtain approval form their ofor 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 Seattle FAA AC

be forwarded to all 737-600/700/700C/800/900/900ER operators and the Seattle FAA ACO.PAGE FORMAT: AWLs – FUEL SYSTEMS

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

CDCCL = Critical Design Configuration Control Limitation

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

APPLICABILITY Airplane model applicability.DESCRIPTION Description of the task to be performed or critical design configurations aspects that cannot be changed without vi

the design.

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

E.1 AWLs – FUEL TANK IGNITION PREVENTION ALIs AND CDCCLs

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

maintenance program for this type design to meet the new standards and assumptions introduced by § 25.981 and SFAR 88. 

System Fault Tolerance Evaluation Requirements and Title 14 Code of Federal Regulations § 25.981 – Fuel Tank Ignition Prev

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

Paragraph 2(a) of SFAR 88 requires certain design approval holders of Type Certificates (TCs) and Supplemental Type Certific

transport airplanes to conduct a safety review of the fuel tank systems. The purpose of the safety review is to identify design fe

development of ignition sources in the fuel tank systems. Fuel System AWLs are mandatory maintenance actions established ito ensure that unsafe conditions identified by the SFAR 88 safety review do not occur or are not introduced into the fuel tank sy

configuration changes, repairs, alterations, or deficiencies in the maintenance program throughout the operational life of the air

AWL Number Task Interval Applicability Description

28-AWL-01 ALI 10 YR ALL External Wires Over Center Fuel Tank

Concern: Potential for Wire chafing and arcing to Center Fuel Tank Upper Perform a detailed inspection of the wire bundles routed over the center fufloor boards to detect damaged clamps, wire chafing, and that the wire busurface of the center fuel tank (refer to Boeing AMM 28-11-00).Inspect the sleeving over the wire bundles if installed for sign of visible dainspect the wiring for chafing if the sleeving was damaged.Repair any discrepancies found (refer to Boeing SWPM D6-54446 20-10-

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-02 CDCCL N/A ALL External Wires Over Center Fuel Tank 

Concern: Potential for Wire chafing and arcing to Center Fuel Tank Upper If any maintenance is performed in the area over the center fuel tank and 

verify the following in the affected areas where maintenance was perform

1. Maintain the existing type design configuration.2. Wire bundles clamps are not damaged.3. Wires are not chafed.4. Wire bundles are not in contact with the surface of the center fuel tan

Repair any discrepancies found (refer to Boeing SWPM D6-54446 20-10-

28-AWL-03 ALI 10 Yrs ALL Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning Shie

Concern: Potential for Lightning induced voltages on the FQIS wiring to ePerform the following functional check to ensure the integrity of the FQIS win the unpressurized area using a Loop Resistance Tester P/N 906-10246

AMM 05-55-54):1. The loop resistance shall not exceed 0.138 ohm (138 milliohms) for C

Tank without Densitometer) Wire Bundle W1140.

2. The loop resistance shall not exceed 0.063 ohm (63 milliohms) for Co

with Densitometer) Wire Bundle W1140.

3. The loop resistance shall not exceed 0.138 ohm (138 milliohms) for C

Tank without Densitometer) Wire Bundle W1138.

4. The loop resistance shall not exceed 0.063 ohm (63 milliohms) for Co

Tank with Densitometer) Wire Bundle W1138.

5. The loop resistance shall not exceed 0.040 ohm (40 milliohms) for Co

without Densitometer) Wire Bundle W7580.

6. The loop resistance shall not exceed 0.040 ohm (40 milliohms) for Co

with Densitometer) Wire Bundle W7580.

Restore the bonds if the measured loop resistance value is greater than th

(refer to Boeing AMM 05-55-54).

AWL Number Task Interval Applicability Description

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

28-AWL-04 CDCCL N/A ALL FQIS – Out Tank Wiring Lightning Shield to Ground Termination

Concern: Potential for lightning induced voltages on the FQIS wiring to en

If maintenance is performed in the unpressurized zone that disconnects oto ground path, then after restoration, perform the bond check for the type 

below:1. For side of body FQIS connectors D39915, D39916, D4850P, and Ho

connectors D13836 and D13834 that use the connector's backshell fo

to structure:If any of the following maintenance is performed:A. Loosening and/or tightening the coupling ring of the connector.B. The shield terminal lug is removed and reinstalled to the backshe

connectors D39915, D39916, and D4850P).

Then verify the following:A. For connectors D39915, D39916 and D4850P, the resistance from 

structure shall be no greater than 3.0 milliohms (0.003 ohm) (refe

B. For connectors D13836 and D13834, the resistance from the con

be no greater than 3.0 milliohms (0.003 ohm) (refer to Boeing SW

2. For tank side FQIS connectors D11312, D11314 and D11316 that use 

for shield ground path to structure: If the shield pigtail terminal lug to ground stud is removed and reinstais repaired:Then verify the following:A. The resistance from the shield pigtail terminal lug to the ground st

1.0 milliohm (0.001 ohm) (refer to Boeing SWPM 20-20-00).

If any FQIS wire bundle in the unpressurized zone is replaced or the FQIS (except as noted above), then that particular wire bundle shall be inspected per AWL 28-AWL-03 (refer to Boeing AMM 05-55-54).

AWL Number Task Interval Applicability Description

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-05 CDCCL N/A ALL FQIS – Out Tank Wiring Installation Separation Requirement 

Concerns: Potential for hot shorts and Electromagnetic Effects (EME) induenter the tank.The following applies to any new wiring that is installed within 6.5 inches odefined as any wiring that is added to the airplane, excluding repair or rep1. Must use wire types BMS 13-48, BMS 13-60 or BMS 13-58.2. The wiring must not be installed within a two-inch radius of the FQIS 

3. Under single failure of any clamp or bracket, a minimum 1⁄2 inch separ

be maintained.

The following applies to repair or replacement of existing wiring that is ins

FQIS wiring:1. Maintain existing wire routing and wire type (refer to Boeing SWPM 2

substitutes).

NOTE: Refer to the Wire Diagrams to identify FQIS wiring.

28-AWL-06 CDCCL N/A ALL FQIS – Repair of Processor Unit 

Concern: Potential for maintenance error during FQIS processor repair.The FQIS processor is designed to limit the levels of energy, voltage, curr

FQIS circuit to intrinsically safe levels in order to preclude the potential of 

fuel tank.Repair and overhaul of FQIS processor unit must be per the Goodrich (V8and IPC 28-41-87 Revision 1 or CMM 28-41-73 Revision 3 and IPC 28-41that have been approved by the Seattle FAA ACO.

AWL Number Task Interval Applicability Description

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

28-AWL-07 CDCCL N/A Airplanes

L/N 1767 and on 

equipped with 

densitometer, or 

airplanes that have 

incorporated 

Service Bulletin 

737-28A1221

FQIS – Installation of Center Fuel Tank Hot Short Protector (HSP)Concern: Potential for wire to wire hot short voltages on the center tank fuenter the fuel tank. This is applicable to airplanes with optional densitomeThe FQIS HSP is designed to prevent wire to wire external hot short voltawhere it may cause an ignition. The following features must be maintaine(refer to Boeing AMM 28-41-24):1. The electrical bonding resistance between the loose end of each bon

web, prior to attachment of the two bonding jumpers to the HSP, is 0.or less.

2. The electrical bonding resistance between each jumper lug and the H

or less.

3. The electrical bonding resistance between the HSP and the spar web 

or less.

4. Sealant is applied on the fastener heads and mating components of t

protect the bond.

5. The electrical bonding resistance between each HSP connector (D13

the HSP is 0.003 ohm (3.0 milliohms) or less.

The HSP unit is not repairable. A new unit must be used if the HSP has fCMM 28-41-24 for testing).

28-AWL-08 CDCCL N/A ALL FQIS – Repair of In-Tank Hardware (Tank Units, Compensators and Dens

Concern: Potential for maintenance error during repair of in-tank hardware densitometers). Arc gaps may develop that could result in an ignition souRepair and overhaul of FQIS tank units, compensators and densitometers (V89305) CMM 28-41-76 Revision 1, or CMM 28-41-75 Revision 0, or CMrevisions that have been approved by the Seattle FAA ACO.

AWL Number Task Interval Applicability Description

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-09 CDCCL N/A ALL FQIS – Repair or Replacement of In-Tank Wire Harness

Concern: Potential for error during repair or replacement of in-tank wire hacould result in an ignition source inside the fuel tank.Repair of the FQIS in-tank wire harness must be approved by the Seattle The following design feature must be maintained when installing the FQIS Boeing AMM 28-41-44):1. Wire slack clearance between wires and structure must be a minimum The following design features must be maintained when installing the FQI(refer to Boeing AMM 28-41-42):1. New O-ring is installed.2. The Jam Nut is tightened to a torque of 325 - 350 inch-pounds (37 - 43. The electrical fay surface bond between the spar connector and the s

(1 milliohm) or less.

4. Sealant is applied around the connector inside and outside the fuel ta

28-AWL-10 CDCCL N/A ALL Lightning Protection – Hydraulic Line Fuel Tank Penetration

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

spar during a lightning strike event.The following design features must be maintained if the bulkhead fitting is 

Boeing AMM 29-11-04):1. The electrical fay surface bond from the bulkhead fitting to the spar o

(1 milliohm) or less.

2. A fillet seal is applied on the fitting to the tank wall interface outside th3. Sealant is applied, encapsulating the fitting to the tank wall interface 4. An electrostatic bonding jumper exists between the structure and the H

the tank.

5. The electrical bonding resistance between the structure and the Hydr

tank is 0.0025 ohm (2.5 milliohms) or less if the bonding jumper was 

AWL Number Task Interval Applicability Description

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D626A001-CMR

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

28-AWL-11 CDCCL N/A Airplanes 

L/N 1498 and on, 

or airplanes that 

have incorporated 

Service Bulletin 

737-28-1225

Lightning Protection – Engine Fuel Feed Line Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface b

spar during a lightning strike event.The following design features must be maintained if the bulkhead fitting o

replaced (refer to Boeing AMM 28-22-15):1. The electrical fay surface bond between the bulkhead fitting and the s

0.0005 ohm (0.5 milliohms) or less.

2. Sealant is applied, encapsulating the fitting to the tank wall interface 3. Sealant is applied, encapsulating the first fitting to the tube interface i

4. A fillet seal is applied between the jam nut and the spar outside the ta5. An electrostatic bonding jumper exists between the spar and the first 

fitting inside the tank.

6. The electrical bonding resistance from the spar to the first tube matin

the tank is 0.010 ohm (10 milliohms) or less if the tube bonding jumpe

28-AWL-12 CDCCL N/A ALL Lightning, Fault Current or Hot Short Protection – Fuel Tank Penetrations

Concern: Potential for arcing or sparking inside the tank at a conductive m

as a result of electrical fault currents or lightning strike events due to insufelectrical path.Any alteration, design change, or repair involving new penetrations to the 

fasteners, adding a bracket, bulkhead fitting or equipment) or change to tequipment penetrations (such as fuel measuring sticks, sump drain valves

sensor, and motor operated fuel shutoff valve adaptor plate) requires appElectrical bonding of fittings and brackets and/or cap sealing of fasteners interface to structure inside and/or outside the fuel tank will be required.

AWL Number Task Interval Applicability Description

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-13 CDCCL N/A ALL AC and DC Electrical Fuel Tank Pump Maintenance

Concern: Potential for maintenance error during pump overhaul. Fuel puprevention means (i.e., flame arrestor, thermal fuses, materials, leadwire maintained if pump is overhauled. Repair and overhaul of AC Fuel Pumps must be per the Crane (V81982) CMM 28-22-06 Revision 6, CMM 28-22-08 Revision 4, CMM 28-22-09 Revbeen approved by the Seattle FAA ACO.Repair and overhaul of DC Fuel Pump must be per the Intertechnique (VFor a later revision that has been approved by the Seattle FAA ACO.

28-AWL-14 CDCCL N/A ALL AC Fuel Pump Fault Current Bonding Jumper Installation

Concern: Potential for fault current path through the pump housing to strufaults internal to the fuel pump motor impeller are by design routed througthe bonding jumpers on the front face of the motor impeller assembly to sbonding jumpers ensure that fault currents are conducted to structure outs

and/or GFI has had time to remove power from the pump.The following design features must be maintained during pump replaceme

1. Two fay sealed bonding jumpers are installed between the pump mot

the spar.

2. The electrical bonding resistance between the motor impeller end-ca

(0.4 milliohm) or less.

28-AWL-15 CDCCL N/A Airplanes 

L/N 928 and on,

or airplanes that 

have incorporated 

Service Bulletin 

737-28A1142.

Fueling Float Switch System InstallationConcern: Potential for wire chafing and arcing to conduit inside the tank. 

Tank 1 and 2 are not repairable to the initial manufactured standards. Thare not repairable to the initial manufactured standards.The following design features must be met during float switch replacemenAMM 28-21-71):1. A new float switch assembly must be used for Fuel Tank 1 or Fuel Ta

2. A new float switch and liner system must be used for the center fuel t

AWL Number Task Interval Applicability Description

FEB 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

28-AWL-16 CDCCL N/A ALL Fuel Tank Access Doors – Lightning Protection

Concern: Potential for arcing or sparking inside the tank at the interface bestructure as a result of a direct strike or conducting currents through the w

The following design features must be maintained during fuel tank access 

AMMs 28-11-11 and 28-11-31): 1. For doors installed at door position numbers other than 531AB, 631AB

632AB, verify presence of a phenolic strip positioned around the outer

mates with the wing skin inside the tank.

2. For 737-900ER airplanes with machined style impact-resistant doors, 

631AB, 531BB, 631BB, 532AB, and 632AB, verify presence of a phenoutermost periphery of the door that mates with the wing skin inside th

3. A corrosion-free access door, clamp ring, and lower wing skin electric4. A new knitted aluminum mesh gasket is installed. If a new gasket is n

meeting the following criteria may be installed:a. No fastener holes are torn.b. Gasket is not elongated or out of shape.c. Gasket rubber seals around the inner and outer periphery must b

0.015 inches thick.

d. No more than 10% of strands in all three layers are broken throug

NOTE: A gasket not meeting Items a through c criteria may be used for a 5. Grease or anti-corrosion compound is applied to both sides of the knit

required for a new knitted aluminum mesh gasket that is less than five NOTE: If the new knitted aluminum mesh gasket is greater than five 

date, de-grease and re-impregnate with 0.5-1 ounce of MILgrease, or anti-corrosion compound BMS 3-38 (CorBan 27L before installation.

6. The knitted aluminum mesh gasket is installed between the outside fa

to establish the electrical conductivity between the access door and the 

and fasteners torqued to 35 ±5 in-lb (4 ±1 N-m) for all doors except 73resistant doors. For machined impact-resistant doors installed on 737±1 N-m).

NOTE: Not applicable to Access Doors 533BB and 633BB (Surge Tank A

Vent Scoop and Pressure Relief Valve).

AWL Number Task Interval Applicability Description

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-17 CDCCL N/A ALL Surge Tank Access Doors (533BB and 633BB) – Lightning Protection

Concern: Potential for arcing or sparking inside the tank at the interface bstructure as a result of a direct strike or conducting currents through the w

During surge tank access door installation, perform the following actions (28-13-41, and 28-13-31): Clean the countersinks on the door.If the pressure relief valve is removed and replaced, verify the electrical fapressure relief valve and the door is 0.010 ohm (10 milliohms) or less (refIf the upper duct of the flame arrestor is removed and replaced, verify the AMM 28-13-31):1. The sealed electrical fay surface bond between the flame arrestor an

vent stack is 0.010 ohm (10 milliohms) or less, and

2. The sealed electrical fay surface bond between the flange on the low

on the upper duct is 0.010 ohm (10 milliohms) or less.

Install door using the BACB30LH3-10 conductive fasteners torqued to 35 

substitution is allowed.

28-AWL-18 CDCCL N/A ALL Resetting of Tripped Fuel Pump Circuit Breakers or Ground Fault Interrup

Concern: Potential for arcing or sparking inside the tank between fuel pumoutside the tank between pump wiring and structure in flammable leakage To reset the circuit breaker(s) or GFIs, the following must be performed:1. Accomplish the troubleshooting procedures (refer to Boeing Fault Iso2. The fault(s) that resulted in circuit breaker or GFI tripping must be isol

AWL Number Task Interval Applicability Description

FEB 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

28-AWL-19 ALI 1 YR Airplanes 

L/N 1494 and on, 

or airplanes that 

have incorporated 

Service Bulletin 

737-28A1206.

Center Tank Fuel Boost Pump Automatic Shutoff SystemConcern: Dry running the center tank fuel pumps has the potential for sin

developing at the pump inlet due to either frictional heating or sparking as (FOD) contacting the pump rotating elements, rotating elements contactinbearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit continuous 

15 seconds.The following test is required in order to protect against latent faults:Functionally check the center tank fuel boost pump automatic shutoff syst28-22-00).

28-AWL-20 ALI 1 YR Airplanes L/N 1981, 

2093, 2210 and on, 

or airplanes that 

have incorporated 

Service Bulletin

737-28A1201.

Boost Pump Ground Fault Interrupter (GFI)Concern: Potential for pump housing burn-through, either internal or exte

major arcing due to electrical failure (i.e., damaged electrical connector, s

housing/end cap shorting).The GFI is designed to detect electrical faults and open the circuit prior to following maintenance check is required in order to ensure continued funcOperationally check the GFI of all AC Fuel Tank Boost Pumps (refer to Bo

AWL Number Task Interval Applicability Description

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-21 CDCCL N/A See Description. Motor Operated Valve (MOV) Actuator – Lightning and Fault Current Prot

Concern: Potential for arcing or sparking inside the fuel tank at a conduct

interface as a result of lightning or electrical fault current event.

Applicability: 737-600/700/700C/700IGW/800/900 airplanes starting with 

or airplanes that have incorporated Service Bulletin 737-28A1207.The following design features must be maintained during actuator, index p(refer to Boeing AMM 28-22-11 or 28-22-21):1. Maintain the following if the Spar Valve adapter plate is removed and 

a. The electrical bonding resistance between the adapter plate and 

(0.5 milliohm) or less.

b. A fillet seal is applied around the periphery of the adapter plate ac. The four bolts that attach the adapter plate to the spar inside the 

sealed, and fillet seal is applied around the edge of the hole and adapter plate inside the tank.

d. The sealed electrical fay surface bond between the serrated mat

and the adapter plate. The index plate screws are wet installed u

e. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

f. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

g. The electrical bonding resistance between the loose end of the b

stiffener, prior to attachment of the bonding jumper to the actuato

(1.5 milliohms) or less.

h The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

i. The electrical bonding resistance between the FQIS outermost s

spar is 0.007 ohm (7.0 milliohms) or less.

(Continued on next page)

AWL Number Task Interval Applicability Description

FEB 2011
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D626A001-CMR

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

28-AWL-21,

Continued

MOV Actuator – Lightning and Fault Current Protection, Continued2. Maintain the following if the Spar Valve index plate is removed and re

a. The sealed electrical fay surface bond between the serrated mat

and the adapter plate. The index plate screws are wet installed u

b. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

c. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

d. The electrical bonding resistance between the loose end of the b

stiffener, prior to attachment of the bonding jumper to the actuato(1.5 milliohms) or less.

e. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

f. The electrical bonding resistance between the FQIS outermost s

spar is 0.007 ohm (7.0 milliohms) or less.

3. Maintain the following If the Spar Valve actuator is removed and repla

a. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

b. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

c. The electrical bonding resistance between the loose end of the b

stiffener, prior to attachment of the bonding jumper to the actuato(1.5 milliohms) or less.

d. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

e. The electrical bonding resistance between the FQIS outermost s

spar is 0.007 ohm (7.0 milliohms) or less.

(Continued on next page)

AWL Number Task Interval Applicability Description

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-21,

Continued

MOV Actuator – Lightning and Fault Current Protection, Continued4. Maintain the following if the Cross-feed Valve Adapter Plate is remov

a. The electrical bonding resistance between the adapter plate and 

(0.5 milliohm) or less.

b. A fillet seal is applied around the periphery of the adapter plate a

c. The four bolts that attach the adapter plate to the spar inside the 

sealed, and fillet seal is applied around the edge of the hole and adapter plate inside the tank.

d. The sealed electrical fay surface bond between the serrated mat

and the adapter plate. The index plate screws are wet installed u

e. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

f. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

g. The electrical bonding resistance between the loose end of the b

prior to attachment of the bonding jumper to the actuator, is 0.00

h. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

5. Maintain the following if the Cross-feed Index Plate is removed and re

a. The sealed electrical fay surface bond between the serrated mat

and the adapter plate. The index plate screws are wet installed u

b. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

c. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

d. The electrical bonding resistance between the loose end of the b

prior to attachment of the bonding jumper to the actuator, is 0.00

e. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

(Continued on next page)

AWL Number Task Interval Applicability Description

FEB 2011
737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

D626A001-CMR

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

28-AWL-21,

Continued

MOV Actuator – Lightning and Fault Current Protection, Continued6. Maintain the following If the Cross-feed Valve Actuator is removed an

a. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

b. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

c. The electrical bonding resistance between the loose end of the b

prior to attachment of the bonding jumper to the actuator, is 0.00

d. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

Applicability: 737-600/700/700C/700IGW/800/900 airplanes; Line NumbeLine Number 1983 and on.

The following design features must be maintained during actuator, index replacement (refer to Boeing AMM 28-22-11 or 28-22-21):

1. Maintain the following if the adapter plate is removed and replaced:

a. The electrical bonding resistance between the adapter plate and 

(0.5 milliohm) or less.

b. A fillet seal is applied around the periphery of the adapter plate ac. The four bolts that attach the adapter plate to the spar inside the 

sealed, and fillet seal is applied around the edge of the hole and adapter plate inside the tank.

d. The sealed electrical fay surface bond between the serrated mat

and the adapter plate. The index plate screws are wet installed u

e. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

f. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

g The electrical bonding resistance between the loose end of the b

prior to attachment of the bonding jumper to the actuator, is 0.00

h. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

(Continued on next page)

AWL Number Task Interval Applicability Description

FEB 2011
D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

28-AWL-21,

Continued

MOV Actuator – Lightning and Fault Current Protection, Continued2. Maintain the following if the index plate is removed and replaced:

a. The sealed electrical fay surface bond between the serrated mat

and the adapter plate. The index plate screws are wet installed u

b. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

c. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

d The electrical bonding resistance between the loose end of the b

prior to attachment of the bonding jumper to the actuator, is 0.00

e. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

3. Maintain the following if the actuator is removed and replaced:

a. The sealed electrical fay surface bond between the mating surfa

index plate. The actuator screws are wet installed using same se

b. The electrical bonding resistance between the actuator upper ho

attachment of the bonding jumper and electrical connector, is 0.0

c. The electrical bonding resistance between the loose end of the b

prior to attachment of the bonding jumper to the actuator, is 0.00

d. The electrical bonding resistance between the actuator upper ho

bonding jumper terminal (using a sealed electrical bond) is 0.001 

28-AWL-22 CDCCL N/A Airplanes 

L/N 1877 and on,

or airplanes that 

have incorporated 

Service Bulletin 

737-28A1207.

MOV Actuator – Removed or RepairedConcern: Potential for arcing or sparking inside the fuel tank at a conduct

interface as a result of lightning or electrical fault current event. An electr

shaft is intended to disconnect the output shaft electrically from the motor 

ground path structure.To verify the integrity of the electrical isolation feature, conduct the followi

removed or repaired (refer to ITT (V73760) CMM 28-20-21):A Dielectric Strength test on the completed actuator assembly shall be peRMS, 60 Hz for one (1) minute between any mounting foot of the actuator shall be no evidence of disruptive discharge in the form of leakage curren

3000V test is a bench test only and must not be performed on the aircraft

AWL Number Task Interval Applicability Description

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28-AWL-23 ALI 1 YR Airplanes 

L/N 1973 and on, 

or airplanes that 

have incorporated 

Service Bulletin 

737-28A1248.

Center Tank Fuel Boost Pump Power Failed On Protection SystemConcern: Dry running the center tank fuel pumps has the potential for sin

developing at the pump inlet due to either frictional heating or sparking as pump rotating elements, rotating elements contacting stationary parts, or contamination or failure.The power failed on protection system is installed and designed in order t(i.e., wiring faults or a welded fuel pump control relay) keeping power on tpump control switch is positioned to OFF. The following test is required in order to protect against latent faults:Verify continued functionality of the center tank fuel boost pump Power FaBoeing AMM 28-22-00).

28-AWL-24 ALI 6 YR Airplanes 

L/N 1877 - 1980, 

1982, or airplanes 

that have 

incorporated 

Service Bulletin 

737-28A1207.

MOV Actuator – Lightning and Fault Current ProtectionConcern: Potential for arcing or sparking inside the fuel tank at a conduct

interface as a result of lightning or electrical fault current event.Perform the following functional check to ensure the integrity of the Spar Vpath (refer to Boeing AMM 28-22-11):1. The electrical bonding resistance between the actuator connector flan

electrical connector and the bonding jumper disconnected, is 0.010 o

2. The electrical bonding resistance between the actuator upper housin

jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 millio

3. The electrical bonding resistance between the outermost FQIS shield 

with the actuator electrical connector disconnected, is 0.014 ohm (14 

Restore the bonds if the measured resistance is greater than the maximu

SWPM 20-20-00).

AWL Number Task Interval Applicability Description

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

E.2 ENGINE FUEL SUCTION FEED SYSTEM

This section contains an FAA approved program of scheduled inspections for operators to incorporate into their maintenance p

to meet Title 14 CFR § 25.951.The 737NG Engine Fuel Suction Feed System was type certificated as being compliant to Title 14 CFR § 25.951(b) when perfo

operations. The Engine Fuel Suction Feed System AWL results from service experience of loss of fuel system suction feed cathe engine fuel feed system. The AWL is required maintenance needed to detect and correct failure of the Engine Fuel Suction 

the possibility of engine flameout resulting from air ingestion into the Engine Fuel Suction Feed System during low fuel level opinoperative.The Engine Fuel Suction Feed System AWL is mandatory maintenance to ensure that the system retains the performance of th

Feed System required by Title 14 CFR § 25.951(b) that arise due to air leaks in the Engine Fuel Suction Feed System do not reboth engines.

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AWL Number Task Interval Applicability Description

28-AWL-101 ALI 7500 FH or 

3 YRS, 

whichever 

occurs first

ALL Engine Fuel Suction Feed Operational Test

An Engine Fuel Suction Feed Operational Test must be accomplished sucindividually. This test is required in order to protect against engine flameo(refer to Boeing AMM 28-22-00):1. Each engine (fuel system) to be tested must meet the following Fuel 

Procedural Limitations listed below.A. Fuel Tank Quantity – Engine No. 1

I. The Center Tank Fuel Quantity must not exceed 3000 lbs (13II. The Main Tank No. 1 Fuel Quantity must be between 1870 lbNOTE: Excess fuel can be transferred to Main Tank No. 2.

B. Fuel Tank Quantity – Engine No. 2

I. The Center Tank Fuel Quantity must not exceed 3000 lbs (13II. The Main Tank No. 2 Fuel Quantity must be between 1870 lbNOTE: Excess fuel can be transferred to Main Tank No. 1.

C. Test Procedural Limitations:

I. The Fuel Cross-Feed Valve must be CLOSED.II. The APU Selector Switch must be OFF.III. The Idle Engine Warm-up time of minimum two minutes with 

IV. Idle Engine Suction Feed (Boost Pump OFF) operation of miNOTE: The APU may be used to start the engines, provided th

procedural limitations are met.

2. The test is considered a success if engine operation is maintained du

engine parameters (N1, N2, and Fuel Flow) do not decay relative to thON.

3. An Engine Fuel Suction Feed System that fails the operational test m

pass the Engine Fuel Suction Feed Operational Test prior to further f

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

F. AWLs – NITROGEN GENERATION SYSTEM ALIs AND CDCCLs

The following list of AWLs contains FAA approved scheduled inspections for operators to incorporate into their maintenance pr

to meet the requirements for the introduction of the Nitrogen Generation System (NGS). The FAA Final Flammability Rule, E8-

maintenance instructions and control limitations for certain NGS critical design configurations. § 25.981 (d) also requires AWLs inside the fuel tank that may be introduced by the addition of NGS.E8-16084, Final Flammability Rule, Paragraph III(F), Section 7, Identification of Airworthiness Limitations: Paragraph M25.4(a) 

Reduction Means (FRM) is used to comply with Paragraph M25.1, AWLs must be identified for all maintenance or inspection ta

failures of components within the FRM that are needed to meet Paragraph M25.1. NGS AWLs are mandatory maintenance ac

unsafe conditions that arise due to NGS failures do not occur or are not introduced into the airplane as a result of configuration 

alterations, or deficiencies in the NGS maintenance program throughout the operational life of the airplane.See Section E for the definition of an ALI or CDCCL.

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AWL Number Task Interval Applicability Description

47-AWL-01 CDCCL N/A All airplanes

L/N 1820, 1831, 1935 and on.

All airplanes that have 

incorporated Service Bulletin 

737-47-1002.

Lightning Protection – Nitrogen Generation System (NGS) Nitroge

Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the inteand the spar during a lightning strike event.The following must be maintained if the bulkhead fitting is removed 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 t

tank is 0.0005 ohm (0.5 milliohm) or less,

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

of the bulkhead fitting and jam nut, and

4. Verify electrical bond from structure to first tube mating with th

(100 milliohms) or less.NOTE: The bulkhead fitting is a special part which has an i

change to this part requires approval by the Seattle 

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

47-AWL-02 CDCCL N/A All airplanes

L/Ns 1820, 1831, 2517, 2620 

and on.

All airplanes that have 

incorporated

 Service Bulletin 

737-47-1003.

Nitrogen Generation System (NGS) – Flammability Exposure and Concern: Airplane alterations may impact the performance of the the Center Wing Fuel Tank.Background: The NGS is designed to provide the proper level of order to reduce the flammability exposure by reducing the oxygen flammability exposure is also affected by the temperature of the fufeatures of the airplane that, if altered, can negatively affect the pemay increase the center fuel tank flammability exposure beyond thRegulations, Section 25.981 at Amendment 25-125, utilizing the edescribed in FAA Memorandum PS05-0177-P-2.1. Transferring air (20.9% oxygen) to the center fuel tank will dil

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

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

by the engines.

3. Certification of the NGS depends on the inherent flammability 

NGS installed. Center tank flammability is a direct function of sources around the tank, heat sources introduced into the tanheat exchangers), or changes that would cause heat to be retblankets adjacent to tank walls) could affect fuel tank flamma

CDCCL: Any design change that affects the vent system by addinbleed pressure in the cross-over manifold during any phase of flig

any heat to the center wing fuel tank or increases heat retention o

allowed without an FAA approved analysis to show that the chang

not affect the NGS performance per the requirements of 14 CFR S125 utilizing the equivalent level of safety finding described in FAA See Boeing AMM Chapter 28 for a description of the Fuel Systema description of the NGS.

AWL Number Task Interval Applicability Description

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47-AWL-03

DELETED

ALI 1200 FH All airplanes 

L/N 1820 and 1831

Nitrogen Generation System – Functional Check Performance InsConcern: Latent failure of the Hollow Fiber Membranes that make 

(ASMs) will reduce the percentage of nitrogen in the nitrogen enricfuel tank.Perform the ASM inspection listed in Boeing AMM 47-00-00:1. Measure the oxygen concentration of the NEA at the output of 

00-00).

2. Verify the NEA purity is in the satisfactory zone (shaded area) 

published in Boeing AMM 47-00-00.

If the nitrogen content is not satisfactory, troubleshoot per Boeing and perform the recommended repairs per Boeing AMM 47-00-00

47-AWL-04 ALI 22500 FH All airplanes 

L/N 1820, 1831, 2517, 2620 

and on.

All airplanes that have 

incorporated Service Bulletin

737-47-1003.

Nitrogen Generation System – Thermal Switch Functional and OpConcern: Latent failure of the Thermal Switch removes a layer of pby hot bleed air.The NGS uses engine bleed air from the bleed system cross-over reduce the flammability of the center fuel tank. The NGS has featu

bleed air into the fuel tank. The Thermal Switch provides a redundprotect the Air Separation Module (ASM) and prevent hot bleed aiThermal Switch backup feature is a latent (not detected) failure ancertification of the NGS.Perform a functional and operational test of the thermal switch to e

switch (refer to Boeing AMM 47-43-02).

AWL Number Task Interval Applicability Description

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

47-AWL-05 CDCCL N/A All Airplanes 

L/N 1820, 1831, 1935 

and on.

All airplanes that have 

incorporated Service Bulletin 

737-47-1003.

Lightning Protection – FRS NEA Distribution Line Fuel Tank LightConcern: Potential for arcing, sparking or filament heating inside the bulkhead fitting and the spar during a lightning strike event.The following features must be maintained if the upper or lower ligreplaced or reinstalled (refer to Boeing AMM 47-21-08):1. Install Upper Lightning Shield sealed electrical fay surface bo

stiffener sealed electrical fay surface bond to Rear Spar Web

2. Verify Upper Lightning Shield bonding resistance to Rear Spa

(1.0 milliohms) or less.

3. Install Lower Lightning Shield sealed electrical fay surface bo

rivet bond to stiffener, and stiffener sealed electrical fay surfa

4. Verify Lower Lightning Shield bonding resistance to Rear Spa

(1.5 milliohms) or less.

47-AWL-06 ALI 13,000 FH All Airplanes 

L/N 1820, 1831, 2517, 2620 

and on.

All Airplanes that have 

incorporated Service Bulletin 

737-47-1003.

Nitrogen Generation System – Cross-Vent Check Valve – OperatiConcern: The Cross-Vent Check Valve may fail open, latently allotank, diluting the nitrogen rich environment created by the NitrogeOperationally check the Cross-Vent Check Valve by accessing the the valve opens and closes (refer to Boeing AMM 47-00-00).

47-AWL-07 ALI 6,500 FH All Airplanes 

L/N 1820, 1831, 2517, 2620 

and on.

All Airplanes that have 

incorporated Service Bulletin 

737-47-1003.

Nitrogen Generation System – NEA Distribution Ducting InspectioConcern: The NEA Distribution System ducting outside the fuel tanleak without reaching the fuel tank, resulting in the fuel tank not re

Inspect the NEA distribution lines from the ASM to the fuel tank rea

to Boeing AMM 47-00-00).

AWL Number Task Interval Applicability Description

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D626A001-CMR

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NOTE: SHADED AWLs HAVE BEEN DELETED.

47-AWL-08 CDCCL N/A All Airplanes 

L/N 1820, 1831, 2517, 2620 

and on.

All Airplanes that have 

incorporated Service Bulletin 

737-47-1003.

Industry Fleet Average Flammability ExposureConcern: NGS performance is dependent on industry descent tim

descent time may result in NGS performance that does not meet FFleet Average flammability exposure for the fuel tanks with flammamust be maintained in accordance with 14 CFR Part 25, Appendix descent statistics and, if necessary to maintain compliance, will pupublishes such service information, this CDCCL requires either th

approved design changes or that operators implement other desigprocedural changes approved by the Seattle Aircraft Certification 14 CFR Part 25, Appendix M.NOTE: This CDCCL does not require individual operators to mon

fleets. Boeing will monitor US descent statistics and provinstructions to operators. To prevent increasing flammabpermissible levels, this CDCCL requires operators to incopublished service instructions denoted to maintain complother approved actions, within the compliance times state

AWL Number Task Interval Applicability Description

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

SELECTION OF CMRsIn order to grant operators of the 737-600/700/700C/800/900/900ER airplane an opportunity to participate in the evaluation and 

integrated process with MRBR tasks and intervals, a Certification Maintenance Coordination Committee (CMCC) was convene

737-600/700/700C/800/900/900ER CMRs. The CMRs listed in this document are the result of applying the CMCC process as 

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

performed before failure occurs (and are intended to prevent failures), as well as failure-finding tasks. CMRs, on the other 

tasks only, and exist solely to limit the exposure to otherwise hidden failures. Although CMR tasks are failure-finding tasksfinding tasks, such as functional checks and 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 maintenan

the failure clock to zero” for latent failures by verifying that the item has not failed, or cause repair if it has failed. Because tfailure is a key element in the calculations used in a safety analysis performed to show compliance with CFR Title 14, limiti

have a significant effect on the resultant overall failure probability of the system. The CMR task interval should be designa

cycles, or calendar time, as appropriate.

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

condition. The process described in AC 25-19 is not intended to establish normal maintenance tasks that should be defineanalysis process. Also, this process is not intended to establish CMRs for the purpose of providing supplemental margins olate in the type design approval process.

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

requirements for damage tolerance, as required by CFR Title 14, Appendix H25.4 (Airworthiness Limitations section). CMRadministered 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

Seattle FAA ACO.

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

program in a like manner for any MRB Report task, but may not be deleted without prior Seattle FAA ACO 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 Seattle FAA ACO approval. For operators with approved escalation practices or an approved reliability program, d

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.

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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 (e.g. a Principle Maintenance Inspector) mu

exceptional short-term extensions before they take place using procedures established with the local regulatory authority in the “exceptional short-term extension” process is applicable to CMR intervals. It should not be confused with the operator’s “short-for normal maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8300.10.

The Seattle FAA ACO has accepted that these exceptional short-term extensions may be granted without consultation with tha1. 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.

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

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

This exceptional short-term extension listed above applies to airlines that fall under the United States FAA jurisdiction only. Op

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

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POST-CERTIFICATION CHANGES TO CMRsAny post-certification changes to CMRs should be reviewed by the 737-600/700/700C/800/900/900ER CMCC and approved by 

1. Since the purpose of a CMR is to limit the exposure time to a given significant latent failure as part of an engineering analy

reliability, instances of a CMR task repeatedly finding that no failure has occurred may not be sufficient justification for deletitime between repetitive performances of the CMR task. In general, * CMRs are not good candidates for escalation under aprogram. A * CMR task change or interval escalation can only be made if world fleet service experience indicates that cert

component failure rates made early during the engineering analysis were overly conservative, and a re-calculation of syste

failure rates of 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 oallow the operators to manage their own maintenance programs.

3. In the event that later data provide sufficient basis for relaxation of a CMR (less restrictive actions to be required), the change 

FAA ACO 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 

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 revision will then be forwarded to all 737-600/700/700C/800/900/900ER operators and the Seattle FAA ACO offices.

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

T

YP

E K

AS

T

EXAMPLE ILLUSTRATING FORMAT

12000 HRS

SYSTEM.

29-CMR-02 * O 29-130 P ALL ALL Operationally check CENTER HYDRAULIC ISOLATIO

ITEM 737-600/700/700C/800/9

CMR

NUMBER ITEM

MRB

RELATED

NUMBER

APL ENG TASK DESCRIPTION

APPLICABILITY

INTERVAL

CMR

CERTIFICATION MAINTENANCE REQU

G95488

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PAGE FORMAT: CERTIFICATION MAINTENANCE REQUIREMENTS 

COLUMN EXPLANATIONCMR ITEM NUMBER Each task is given a unique CMR Item Number. The first and second digits are the ATA Chapter Number.TYPE CMR TYPE

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

* Cannot be escalated or deleted without prior Seattle ACO approval.** Can be escalated based on the operator’s approved program for continued airworthiness based on continuo

 surveillance; however, these tasks cannot be deleted without prior Seattle FAA ACO approval.

RELATED MRBR ITEM NUMBER

This column is for the related MRBR item number, if there is an applicable MRBR item number. Not all CMRs h

MRBR item number.

TASK MSG-3 TASK CATEGORIES

OP = OPERATIONAL CHECKFC = FUNCTIONAL CHECK

A failure finding task to determine if an item is fulfillinrequire quantitative tolerances.A quantitative check to determine if one or more func

limits.

CMR INTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles and calendar time.APPLICABILITY APL ENG Applicable Airplane Model and Engine.

AIRPLANEALL = All Airplanes

ENGINEALL = All Engines

TASK DESCRIPTION Description of the task to be performed.

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

CERTIFICATION MAINTENANCE REQUIREMENT TASKS

CMR

ITEM

NUMBER

T

YPE

RELATED 

MRBR 

ITEM 

NUMBER

T

A

S

K

CMR 

INTERVAL

APPLICABILITY

737-600/700/700C/800/9

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

26-CMR-01

DELETED

* DI 560 CYC

90 Days

Note

L/N 2093, 

2216

through 

2318 

(Exclude 

2285)

Note

All Perform a detailed inspection of the Center Wing R

near the stiffening beads on the fiberglass panels frInterval Note: Whichever comes first.Perform the task per AMM 05-41-01-211-801.For applicable airplanes that have replaced the fibe737-57-1298, perform 26-CMR-02 instead of this C

26-CMR-02 * DI 5500 CYC

24 MO

Note

L/N 2093, 

2216

and on

All Perform a detailed inspection of the Center Wing R

the fiberglass panel between the vertical structural inside the main gear wheel well.Interval Note: Whichever comes first.Perform the task per AMM 05-41-01-211-802.

27-CMR-01

DELETED

* FC Note Note All Perform a Functional Check of the Horizontal Stabi

Backlash.Interval Note: First inspection at 2000 FH and everAirplane Note: Applicable to airplanes equipped wi

27-CMR-02 * 27-108 RS 4,500 FH Note All Remove the Horizontal Stabilizer Trim Actuator for r

Secondary Brake.Applicability Note: For 251A4510-4 Actuator, RestoStabilizer Trim Actuator Brakes. For 251A4510-5 A

Secondary Brake. 

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27-CMR-03 * 27-044 FC 8,000 FH Note All Perform a Functional Check of the Main Rudder Pow

a loaded condition.NOTE: Applicable to Airplane Line Numbers 1 - 59

incorporated Service Bulletin SB 737-27-1

27-CMR-04 27-194 OP 20,000 FH Note All Perform an Operational Check of the Spoiler Mixer 

NOTE: This CMR is ONLY applicable to aircraft o

Registries.

27-CMR-05 * 27-095 IN 2,000 CYC

4,000 FH

Note All Detail Visual Inspection of the Elevator Tab Rods, T

NOTE: Applicable to 737-900 airplanes, L/N 683 t

incorporated SB 737-55-1081.

27-CMR-06 * 27-097 FC 2,000 CYC

4,000 FH

Note All Perform a Functional Check of the Elevator Tab Fre

NOTE: Applicable to 737-900 airplanes, L/N 683 t

incorporated SB 737-55-1081.

27-CMR-07 * 27-093 IN 2,000 CYC

4,000 FH

Note All Detail Visual Inspection of the Elevator Tab Rods, T

NOTE: Applicable to L/N 596 and 1175 and on, an

1174 that have incorporated SB 737-55A1

27-CMR-08 * 27-099 FC 2,000 CYC

4,000 FH

Note All Perform a Functional Check of the Elevator Tab Fre

NOTE: Applicable to L/N 596 and 1175 and on, an

1174 that have incorporated SB 737-55A1

27-CMR-09

DELETED

* DS 2 Years L/N 1175 

And On

All Discard the Elevator Tab Hinge Bearings (6 per sid

Interval Note: This CMR is temporary based on Fawill be deleted or permanent based on results.

CMR

ITEM

NUMBER

T

YPE

RELATED 

MRBR 

ITEM 

NUMBER

T

A

S

K

CMR 

INTERVAL

APPLICABILITY

737-600/700/700C/800/9

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

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737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

27-CMR-10 * 27-047 FC 10,000 FH Note

*

All Perform a Functional Check of the Main Rudder Pow

a loaded condition.NOTE: Applicable to Airplane Line Numbers 596 a

thru 595 and 597 thru 1267 that have inco

27-CMR-11 * 27-026 LU Note 900ER All Lubricate the aileron tab hinge bearing and rod end 

Interval Note: Airplanes using BMS 3-33 Grease, in(whichever comes first).Airplanes not using BMS 3-33 Grease, interval is 3comes first).Perform the task per AMM 12-22-11.

27-CMR-12 * 27-033 FC 8,000 FH

24 Months

Note

900ER All Perform a functional check of the aileron tab freepla

Interval Note: Whichever comes first.Perform the task per Boeing Service Bulletin 737-27revision.

28-CMR-01 * N/A IN Note Note All Perform a Detail Visual Inspection of the following i

for signs of Fuel Leaks, Heat Discoloration, or DamElectrical Connector, and Wire Insulation.If any discrepancy is detected, prior to further flightor serviceable Fuel Pump and perform an Insulation Interval Note: 5,000 FH or 18 Months (whichever coby CMR 28-CMR-02. (The interval for this task is aCMR 28-CMR-02.)Airplane Note: This CMR is only applicable to the foare installed without fuel pump ground fault interrup6, 60B92404-7 and Override Pumps 60B89004-10, 

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D626A001-CMR

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

28-CMR-02 * N/A FC Note Note All Perform an Insulation Resistance Test on all of the 

If any resistance measurement is less than or equareplace the Fuel Pump with a new or serviceable FResistance Test.Interval Note: If all resistance measurements are grepeat this test at 5,000 FH or 18 Months (whicheve

measurements are greater than 1 megohm, but one Repeat the Visual Inspection, 28-CMR-01, and the 500 FH for the affected Fuel Pumps, or replace the serviceable Fuel Pump and repeat the Insulation RAirplane Note: This CMR is only applicable to the foare installed without fuel pump ground fault interrup6, 60B92404-7 and Override Pumps 60B89004-10, 

28-CMR-03

Replaced by 

28-AWL-19.

* N/A FC 1 Year Note All Perform a Functional Check of the Center Tank Bo

Airplane Note: Applicable to Airplane Line Numberhave incorporated Boeing Service Bulletin 737-28A

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D626A001-CMR

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

33-CMR-01

DELETED

* N/A IN 2 Weeks -800 with 

winglets

Perform a General Visual Inspection of the TranspaForward Leading Edge of the Winglet, LH and RH.Visually inspect each lens for the following:Crazing - Lens should not exhibit a network of the cClarity - Lens should be transparent and clear. Lenor opaque in appearance.Cracking - Lens should not have cracks.Blistering or Bubbling - Lens should not contain air Small Bubbles in lens or coating that do not appear is allowed. The appearance of a few small bubbles manufacturing process and is considered normal.Peeling or Flaking - Lens coating should not peel oDiscoloration - Lens should not exhibit signs or yellSurface Deterioration - Lens should be smooth and not exhibit signs of physical deterioration such as amatte finish, erosion, physical deformation or irreguthe lens surface is allowed if there is not large quanscratches.The General Visual Inspection should reveal no optof the above conditions exist remove and replace thmanual. Ensure the position and anti-collision lightimaintenance manual.

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D626A001-CMR

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

DEFINITIONS:Appearance: The Aspect of visual experience by which things are recognized.Clarity: The characteristic of a transparent body whereby distinct high contrast images or high contrast objects are observable thro

Crazing: Network of apparent fine cracks on or beneath the surface of materials such as in transparent plastics, glazed ceramics, gTranslucent: Transmitting light diffusely, but not permitting a clear view of objects beyond the specimen and not in contact with it.

Distortion: Defect in an image forming system whereby the image is not the shape of an ideal image of the object. For example, A 

through a window having non-planar surfaces may appear to have bends in it.Matte: Lacking luster or gloss. Synonymous with “Flat” in paint terminology. 

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

52-CMR-01 * 52-360 FC 3,000 FH Note All Perform a Functional Check of the Locking and Unlo

Flight Deck Door Decompression Panel.Airplane Note: Applicable to airplane L/N 1221 and new flight deck security door installed by the customBulletins.

73-CMR-01 * N/A RS 300 FH -800 Note Remove the Left/Right Engine Hydro Mechanical U

Bulletin CFM 56-7B 73-016.Applicability Note: Applicable to Engine Hydro MecP/N 1853M56P04 or P/N 1853M56P05.

78-CMR-01 ** 78-110 OP 5,000 FH All All Perform an Operational Check of the Engine T/R S

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D626A001-CMR

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

H. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS

Title 14 Code of Federal Regulations sections 121.703 and 135.415 state that “each certificate holder shall report any failure, m

aircraft, system, component, or powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or de

may endanger the safe operation of an aircraft.” Section 125.409 also requires reporting of failures, malfunctions, or defects. Ifailure or malfunction will be obvious, but there are some failure modes related to uncontrolled high thrust that are reportable bu

following information is provided, as required by FAA Exemption No. 7968 to assist the operators in identifying reportable malfuuncontrolled high thrust.The FAA has concluded that the loss of capability to control thrust due to a failure of the engine thrust control system may endaincludes any malfunctions having one or more of the following characteristics.• Auto-acceleration or uncommanded thrust change to higher power• Stuck thrust lever above idle power• Inability to reduce thrustAlthough some of these incidents may not appear to be safety related, documenting the events is important to ensure the presemaintained and/or to identify failure conditions that must be corrected.

When filing a report of such an event with the FAA, the operator is requested to include in the description of the event one or m

phrases:• “thrust control”• “no response to thrust lever’• “auto-acceleration’• “uncontrolled high thrust”

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

737-600/700/700C/800/900/900ER MAINTENANCE PLANNING D

In addition, the following information should be included in the report:• Event description• Flight crew action• Maintenance action• List of affected or removed componentsReports should be submitted to the local representative of the FAA Administrator that handles the appropriate reporting respons

and 135.415. In addition to filing reports with the FAA, it is recommended that a copy be sent to Boeing and to the engine man

FEB 2008