# rp._ aoEIND

October 4, 2012

M-7300-12-066 The Boeing Company

P.O. Box 3707

Seattle, WA 98 1 24- 2 207



# To : All Recipients of Boe i ng 737-600/700/800/900 (737NG) D626A001-CMR

Maintenance Planning Data (MPD) Document

Subject: Temporary Revision (TR) 09-039, da t ed 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 rev i sion of Document D626A001-CMR which is

published as Section 9 of the 737NG MPD

.

For this rev i sion, the following changes were added and approved by the Seattle FAA BASCO:

• Revised Section E.2 front matter by adding the regulation T i tle 14 CFR 

# § 25.951 requiring

the engine fuel suct i on feed test. Provided the background and technical reason why the

engine fuel suction feed test is a mandatory ma i ntenance 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 quant i ty requ i rement.

For a comp l ete list of revisions, p l ease refer to the revision log within the document.

Also enclosed is a copy of FAA Letter 140S-12-200

, Approval of A l ternative Method of

Comp l iance (AMOC).

If there are any questions or comments regarding this TR

, please submit them to the

undersigned.

Sincerely,

# ~;H:zJr--

Maintenance Programs Enginee ri ng

Commercial Av i at i on Services

The Boe i ng Company

206-766-3497

Enclosures: FAA Letter 140S-12-200

MPD Sect i on 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-lOOS737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-1737-600/700/700C/800/900/900ERMAINTENANCE PLANNING DATA (MPD) DOCUMENTSECTION 9AIRWORTHINESS LIMITATIONS (AWLs) ANDCERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)D626A001-CMRAUGUST 2012COMPILED AND PUBLISHED BY:MAINTENANCE PROGRAMS ENGINEERINGCOMMERCIAL AVIATION SERVICESBOEING COMMERCIAL AIRPLANE GROUPSEATTLE, WASHINGTONAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-2737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3TABLE OF CONTENTSREVISIONS .................................................................................................................................................................................................................................. 9.0-5LIST OF EFFECTIVE PAGES .................................................................................................................................................................................................... 9.0-37A. SCOPE................................................................................................................................................................................................................................... 9.0-39B. AWLS – STRUCTURAL INSPECTIONS................................................................................................................................................................................ 9.0-39C. AWLS – STRUCTURAL SAFE LIFE PARTS ........................................................................................................................................................................9.0-116D. AWLS – SYSTEMS ...............................................................................................................................................................................................................9.0-117E. AWLS – FUEL SYSTEMS .....................................................................................................................................................................................................9.0-118E.1 AWLS – FUEL TANK IGNITION PREVENTION ALIS ANDCDCCLS ........................................................................................................................... 9.0-121E.2 ENGINE FUEL SUCTION FEED SYSTEM.................................................................................................................................................................... 9.0-138F. AWLS – NITROGEN GENERATION SYSTEM ALIS AND CDCCLS.................................................................................................................................... 9.0-140G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS)........................................................................................................................................... 9.0-146H. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS.................................................................................................................... 9.0-159AUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALSEPTEMBER 1997Original Release.Submitted by: N. E. Hennigs (Boeing) Approved by: D. L Riggin (FAA)FEBRUARY 1998Added Note on Page 9.0-19 stating operatorsunder JAR 25 Regulations are not allowed toescalate CMR task intervals.Added one additional ATA 27 CMR that is applicable only to operators under JAR 25Regulations. See Page 9.3-4.Submitted by: N. E. Hennigs (Boeing) Approved by: D. L Riggin (FAA)MARCH 1998Changed statement on Page 9.0-9 Section A. Scope to include the 737-800.Clarified statements onPages 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 56-7BService Bulletin 73-016.Submitted by: N. E. Hennigs (Boeing) Approved by: D. L Riggin (FAA)AUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAAPRIL 1998Deleted 27-CMR-01. Subsequent qualification data has determinedthat the CMR is nolonger required.Added 251A4510-5 actuator to 27-CMR-02.Submitted by: N. E. Hennigs (Boeing) Approved by: D. L Riggin (FAA)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) Approved by: D. L Riggin (FAA)SEPTEMBER 1998Changed statement on Page 9.0-9, Section A. Scope to include the 737-700IGW.Submitted by: S. Pierini (Boeing) Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7JUNE 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 updatedinformation pertaining to damage tolerance based inspection program for the fuselage andempennage.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” tablesand included a column defining airplane applicability. Also moved these tables from the endof the document into Part B to be consistentwith the document format of the other Boeingairplane models. Revised threshold for PSE 53-40-16-2 from 75,000 flight cycles to 38,000flight cycles.Revised Table 9-2 by adding new PSE 55-20-09.Deleted “SPECIAL STRUCTURAL INSPECTIONS” paragraphs from Section B as servicebulletins will address these inspections.Revised the Life Limits in Section C forthe Main Landing Gear and Main Landing GearSupport Structure from 14,500 to 45,000 landings.Revised Page 9.0-52 by deleting statement prohibiting JAA member state registries fromescalating 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 wasomitted in error from an earlier revision.Submitted by: S. Pierini (Boeing)Approved by:JANUARY 2001Revised inspection thresholds listed forPSEs 57-20-02, 57-20-03, 57-20-09, and57-20-19 (Table 9-2) for airplanes, LineNumbers 740, 742, and 749 through 782.Submitted by: S. Pierini (Boeing)Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAJANUARY 2001R1Revised 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 airplanes740, 742,and 749through 782.Submitted by: S. Pierini (Boeing)Approved by:APRIL 2001Revised document to include the 737-900 airplane.Revised the “Threshold” column of Table 9-2to include 75,000 HRS for non-flight lengthsensitive entries. Revised Page 9.0-15 last paragraph.Removed reference to ED/AD and EDR/ADR,and replaced with “Baseline StructuresProgram”.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 changeis 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)Approved by:APRIL 2001R1Revised document to include 737-800 airplaneswith 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)Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9AUGUST 2001Revised document by adding a supplement inspection in Table 9-2 for PSEs57-20 -01/-02/-03/-04/-05 and -08 for airplanesL/N 961 and on with wing panel wear strips.Revised CMR 27-CMR-04 to 27-CMR-06 dueto a duplication with JAA 27-CMR-04.Submitted by: S. Pierini (Boeing)Approved by:DECEMBER 2001Revised document by updating the third paragraphin Section A on Page 9.0-15 that refers tothe document revision date and effective Line Numbers.Revised document by deletingstatement on Page 9.0-21 regarding the MPD publication dateof DTR Check Forms for the 737-800 and 737-900 winglet airplanes as publication has beenaccomplished.Revised document bychanging the applicability (model thresholds) in Table 9.2 for PSEs53-40-16-2 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)Approved by: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 airplanesincorporating Service Bulletin 737-57-1268.Submitted by: Gil Palafox (Boeing)Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAMAY 2002Revised document to reflect damage tolerance analysis based supplemental inspectionthresholds for horizontal stabilizer PSEs, including the 6 hinge elevator tab designincorporated at L/N 1175. All PSEs previously listed in Table 9-1 weremoved to Table 9-2.Table 9-1 has now been deleted. A conservative interim threshold of 16,000 cycles wasspecified for all horizontal stabilizer, elevator and elevator tab PSEs. These thresholds arecurrently the subject of Regulatory review and will be increased at the completion of thisreview.Revised CMRs 27-CMR-05 and 27-CMR-06 to beapplicable to L/Ns 596 to 1174 only. Inaddition, 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 tabdesign incorporated at L/N 1175 and on.Submitted by: S. Pierini (Boeing)Approved by: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 onlyapplicable to airplanes with specific fuel pumps.Added PSE 53-80-06-3 and PSE 53-80-07-3 to Table 9-2. These airworthiness limitationshave conservative interim intervals which are currently being evaluated by the FAA. Uponcompletion of the evaluation, the airworthinesslimitations will eitherbe deleted or modified.Submitted by:Larry Churchwell (Boeing)Approved by:OCTOBER 2002Added CMR 52-CMR-01 to perform a functionalcheck of the flight deck door locking andunlocking latch bolt mechanism on the decompression panel.Submitted by:Larry Churchwell (Boeing)Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11DECEMBER 2002Revised the maximum oil consumption rate of 0.250 gallons per hour for the Model 737-800with winglets and the Model 737-900 airplanes to 0.310 and 0.340 gallons per hourrespectively (Section D. AIRWORTHINESS LIMITATIONS – SYSTEMS).Revised Airplane Applicability for Rudder Check CMR No. 27-CMR-03 (L/Ns 1-1267airplanes that have not incorporated SB 737-27-1253).Added Rudder Check CMR No. 27-CMR-10 for airplanes L/Ns 1-1267 airplanes that haveincorporated SB 737-27-1253 and for airplane L/Ns 1268 and on.Revised CMR Nos. 27-CMR-07 and 27-CMR-08 byproviding the related MRB Item Numbers27-095 and 27-096, respectively.Submitted by:Larry Churchwell (Boeing)Approved by:MAY 2003Added paragraph for the maximum oil consumption rate for the CFM56-7B27A enginesinstalled 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)Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAAUGUST 2003Revised “A. Scope” paragraph to specify Aug 2003 revision and to delete statement “The FAAis considering issuance of an airworthiness directive to mandate these inspections for LineNumbers 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 pendingFAA resolution.Revised all the conservative temporary 16,000 flight cycle horizontal stabilizer thresholds (aslisted in Table 9-2) initiated in May 2002 as follows:Revised the incorrect threshold listing of 75,000cycles/75,000 hrs for PSE 53-80-05-1 to56,000 cycles.Revised threshold for PSE 55-10-08-5A from16,000 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 remaining16,000 cycles/75,000 hrs conservative interim thresholds to56,000 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 CabWindow, 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 Weblooking 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 56,000cycles following FAA review of the integrated bulkhead (FAA Project #TD6620SE-T) damagetolerance 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)Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13AUGUST 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 and57-20-09 to reflect the reworknecessitated by Service Bulletin 737-57-1275. The 10,000flight cycles or 10,000 flight hours thresholdswere increased to 30,000 flight cycles or 30,000flight 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 to27-097 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 (seeFAA Letter 120S-02-791 dated 09 September 2002).(Continued from previous page) (Continued from previous page)APRIL 2004Revised CMRs 28-CMR-01 and 28-CMR-02 to delete reporting requirements for inspectionresults.Added new CMR 28-CMR-03 to perform a functional check of the Center Tank Boost PumpAuto Shutoff System. This was added to comply with FAR 25.1309 by direction of FAAAircraft Certification Office.Submitted by: S. Pierini (Boeing)Approved by: A. Pasion (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-14737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAJULY 2004Revised the reference of Appendix B to the new DTR document, D626A001-DTR datedJuly 2004 on page 9.0-26.Revised PSEs 55-20-08 and 55-20-09 by adding reference thatthis task is applicable tooperators 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 Number737-55-1081.Revised Airplane Applicability to existing PSEs 57-20-03 to include 737-700 AirplanesL/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/N1545 and on with winglets.Revised CMRs 27-CMR-07 and 27-CMR-08 task descriptions to include reference toSB 737-55-1081.Revised CMR 52-CMR-01 to add related MRBRitem number 52-360 and added an airplanenote to specify which airplanes and Line Numbers are affected.Added Section G which contains new airline operator reporting requirements foruncontrollable high thrust failure conditions orassociated causal failures. This new sectionsupports wording which will be added to the 737NG Type Certificate Data Sheet statingoccurrences of these subject failure conditions may endanger the safe operation of theairplane and hence are reportable under 14CFR 121.703(c), 125.409 and 135.415. SectionG contains a listing of these failures. Reference Exemption No. 7968 "Partial Exemption from25.901(c) as it relates to uncontrollable high thrust.Submitted by: S. Pierini (Boeing)Approved by: Jeffrey E. Duven(FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-15AUGUST 2004Added paragraph on Page 9.0-27 titled "Special Structural Inspections". This is a specialinspection 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 1to 1388.Added PSE Nos 53-10-04-2a and 53-10-04-4a due to cab window forging material changesapplicable to L/N 1389 and On. (FAA Project TD7471SE-T).Revised PSE Nos. 53-10-04-6based on recent materialdata obtained from testing.Revised the language in Section D. “AIRWORTHINESS LIMITATIONS - SYSTEMS" toprovide clarification regarding special flightpermits for 737-900 airplanes and 737-800airplanes with winglets and to provide clarification regarding the applicable configuration for737-700IGW airplanes with CFM56-7B27A engines.Submitted by: S. Pierini (Boeing) Approved by: A. Pasion (FAA)DECEMBER 2004Added PSE 55-10-07-3 pertaining to the horizontal stabilizer side of body and bolts (FAAProject #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 requiredby Service Bulletin 737-53A1253.Submitted by: G. Palafox (Boeing) Approved by:MAY 2005Revised reference to D626A001-DTR revision date from "July 2004" to "December 2004" inparagraphs "Repeat Inspection Interval" and in"Reporting Results of Structural Inspections".Added additional Special Inspections that are required inspection of the Horizontal StabilizerFront Spar Attachment Bolts and Rear Spar Attachment Pins.Added PSE 55-10-05-3 for horizontal stabilizer rearspar terminal fitting, side of body pins.Submitted by: B. McLoughlin (Boeing) Approved by: Jeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-16737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAJULY 2005Revised reference to D626A001-DTR revision date from "December 2004" to "June 2005" inparagraphs "Repeat Inspection Interval" and in"Reporting Results of Structural Inspections".Revised Special Structural Inspections for theHorizontal Stabilizer Front Spar AttachmentBolts and Rear Spar Attachment Pins. Includedinspections 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 enginesCFM56-7B27A from 0.19 gallons per hour to 0.25 gallon per hour.Revised PSE 53-40-16-2 threshold from 65000 to 56000 due totypographical error.Submitted by: B. McLoughlin (Boeing)Approved by: Jeffrey E. Duven (FAA)NOVEMBER 2005Added heading for Engine Oil Consumption Limitation for clarity.Added Nitrogen Generation System Airworthiness Limitations, including inspection anddesign limitations.Submitted by: S. Pierini (Boeing) Approved by: A. Pasion (FAA)DECEMBER 2005Added new Fuel System Airworthiness Limitationssection which includes an inspection of thecenter 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) Approved by: Dorr Anderson (FAA)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) Approved by: A. Pasion (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-17MARCH 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) Approved by: A. Pasion (FAA)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 airplaneapplicability.Submitted by: G. Palafox (Boeing) Approved by: A. Pasion (FAA)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 LineNumber 1877 through 1980, 1982, and airplanesthat have incorporated Service Bulletin 737-28A1207.Added a functional check of the auxiliary fuel tank boost pump ground fault interrupter systemnumber 28-AWL-20. Applicable to 737-600,-700, -700C, -800, and -900 airplanes startingwith L/N 1978 and airplanes that haveincorporated Service Bulletin737-28A1201.Revised 28-AWL-07 to clarify bonding measurement location.Submitted by: S. Pierini (Boeing) Approved by: A. Pasion (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-18737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATANOVEMBER 2006Revised THRESHOLD airplane applicability to include 737-800 FPB (Flat PressureBulkhead).Revised REPEAT INSPECTION INTERVAL to change DTR Document revision date fromJune 2005 to November 2006.Revised document to includePSEs for the new -800 Flat Aft Pressure Bulkhead andassociated structural changes for units which incorporate this option. A conservative interimthreshold of 10,000 cycles was specified for these PSEs. Thesethresholds are currently thesubject 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 toreflect that most flights will be atfull cabin pressure of 8.35 PSID.Submitted by: S. Pierini (Boeing) Approved by: A. Pasion (FAA)NOVEMBER 2006R1Added text to A. Scope section in front matter, titled "Limitations Due to Increased CabinPressure". This is in reference to BBJ operators that incorporate SB 737-21-1149 to increasethe internal cabin pressure.Added Table 9-3 for BBJ operators that incorporate SB 737-21-1149 to increase the internalcabin pressure.Submitted by: S. Pierini (Boeing) Approved by: Phillip Forde forJeffrey E. Duven (FAA)MARCH 2007Removed -700C, -700IGW and -900ER in the textthroughout the document as it is called outin the Applicability section.Revised applicability ofindividual Airworthiness Limitations tasksto replace “737/-600/-700/-800/-900” with “All”.Revised 28-AWL-20 interval from 3 years to 1 year based on Ground fault interrupter relaysupplier reliability data, and task was changed fromFunctional to Operational. Also revisedapplicability to show new line position for production incorporation of the ground faultinterrupter relay. The applicability was changed from L/N 1978 to 2210.Submitted by: S. Pierini (Boeing) Approved by: Jeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-19MARCH 2007R1Added 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) Approved by: Jeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-20737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAMARCH 2007R2Revised A. Scope.Table 9-2, PSEs 57-20-04, 57-20-05, 57-20-16, 57-20-17, 57-20-29and 57-31-02 have anote 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, conservativeinspection threshold information that is provided in B. Introduction and by Flag Note forspecific 57-XX-XX PSEs in Table 9-2.Changed Special Structural Instructionsto 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 fromLocation Description“See Entry and DTRForm for PSE 53-30-04-3” and added “S-10L and S-10R, Sta 540 to 727 Upper FastenerRow, Upper Skin” to Location column.Revised PSE 53-40-16-3 to correct airplane applicability.Added PSE 53-40-19-3a, new landing gearsupport 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 57-20-09to change the effectivity/thresholds byeliminating the 30,000 cycle/30,000 flight hourthreshold for airplanes affected by ServiceBulletin 737-57-1275 (AD 2005-24-03).Added paragraph for the maximum oil consumption rate for the CFM56-7B engines installedon the model 737-900ER in (SectionD. AIRWORTHINESS LIMITATIONS - SYSTEMS).Added CMR 27-CMR-11 and 27-CMR-12, related to the 737-900ER airplanes.Submitted by: B. McLoughlin (Boeing) Approved by: Phillip Forde forJeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-21FEBRUARY 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 withwinglets installed due to re-design and material changes.Revised Section E. Exceptional Short-Term Extensions to clarify process and notificationrequirements.Revised the title of Section F. to readFuel System Airworthiness Limitations.Revised AWL 28-AWL-20 airplane Applicabilityfrom L/N 2210 and on to Airplanes 1981,2093, 2210 and on and airplanes thathave incorporated Service Bulletin737-28A1201 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, 2620and on.Revised 47-AWL-04 airplane applicability to include airplanes 2517, 2620 and on and revisedinterval 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 MaintenanceRequirements (CMRs) - Exception Short-TermExtensions to clarify processand 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 thatincorporated 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 haveincorporated SB 737-57-1298.Revised Section K. Reporting Uncontrollable High Thrust Failure Conditions to incorporate“Reporting Uncontrolled High Thrust FailureConditions” per FAR 121.703 and FAR 135.415.Submitted by: B. McLoughlin (Boeing)Approved by:Jeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-22737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAMARCH 2008Revised 28-AWL-01 to remove 36000FH task interval limitation based upon engineeringreview and operator maintenance practiceand removed body station and buttock line textand replaced with “per AMM 28-11-00”.Revised 28-AWL-03 to reflect the new maximum loop resistance values associated with thelightning protection of the unpressurized FQIS wire bundle installations so as to satisfy theAirworthiness Limitation Instructions required bySFAR 88. Also removed the joint resistancevalues and 36000FH task interval limitationbased upon engineering review and operatormaintenance 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 clarifyapplicability.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 theoriginal pumps.Revised 28-AWL-17 to change the fay surface bond limit call out for the pressure relief valvefrom 1 ohm or less to 0.010 ohm (10 milliohms) or less.Submitted by: J. Sabolchy (Boeing) Approved by: Dorr Anderson forJeffrey E. Duven (FAA)APRIL 2008Added information to Section B., AIRWORTHINESS LIMITATIONS – STRUCTURALINSPECTIONS regarding the conservative inspection threshold for the 737-900ER andfuselage 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 theWing-to-Body Fairing to Table 9-2, Airworthiness Limitations - Structural Inspections.Submitted by: J. Onorati (Boeing) Approved by: (Seattle FAA ACO)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-23JUNE 2008Revised applicability of 28-CMR-01 and 28-CMR-02 to indicate the task is applicable only tofuel pumps which are installed without Fuel Pump Ground Fault Interrupter.Submitted by: J. Onorati (Boeing) Approved by: (Seattle FAA ACO)FEBRUARY 2009Revised Section B. Introduction, to remove the conservative threshold for the Wing-to-Bodyfairings 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 areassessment of the fuselage and empennage items for the 737-900ER.Revised Tables 9-2 and 9-3 by adding note todeclare the operational limit imposed by sometasks pending validation,publication, andregulatory acceptance ofthe associated inspectionprocedures.Submitted by: R. Robinson (Boeing) Approved by: (Seattle FAA ACO)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-24737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAMARCH 2009Added information to Section A., SCOPE, and Section B., AIRWORTHINESS LIMITATIONS -STRUCTURAL INSPECTIONS to include applicability to the 737-900ER Boeing BusinessJet 3 (BBJ3).Added information to Section B., AIRWORTHINESS LIMITATIONS - STRUCTURALINSPECTIONS regarding the inspection threshold and specialized DTR Check Forms forAirworthiness Limitations pertaining to the wing of the 737-900ER (BBJ3) airplanes thatincorporated SB 737-21-1149.Added information to Flag Note for Table 9.2 AIRWORTHINESS LIMITATIONS -STRUCTURAL INSPECTIONS to incorporate the inspection threshold and specialized DTRCheck Forms pertaining to the wing of the 737-900ER (BBJ3) airplanes that incorporatedSB 737-21-1149.Revised Table 9.3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONSFOR AIRPLANES WITH SB 737-21-1149 to include applicability of select DTR Check Formsto model 737-900ER BBJ3.Added Principal Structural Elements (PSEs) andassociated DTR inspection details toTable 9.3 AIRWORTHINESSLIMITATIONS - SUPPLEMENTAL INSPECTIONS FORAIRPLANES WITH SB 737-21-1149 applicable to model 737-900ER BBJ3.Submitted by: R. Robinson (Boeing) Approved by: (Seattle FAA ACO)AUGUST 2009Added information regarding removal of excess sealant when performing inspections.Submitted by: J. Onorati (Boeing)SIGNATURE ON FILEFAA ACO8/21/2009REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-25SEPTEMBER 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 thathave escalated the Baseline Structures Program.Submitted by: R. Robinson (Boeing) Approved by: Kevin Hull (FAA ACO)SIGNATURE ON FILE10/6/2009NOVEMBER 2009Added information to Section A, SCOPE,AIRWORTHINESS LIMITATIONS-STRUCTURALINSPECTIONS, regarding the inspection thresholdsresulting from factory installation ofwinglets for the 737-700IGW airplanes.Revised Table 9-2 by adding and updating notes to declare operational limit imposed byfactory installed winglets for the 737-700IGW airplanes.Added paragraph to Section D, AIRWORTHINESS LIMITATIONS - SYSTEMS for themaximum oil consumption rate for the CFM56-7B27A Engines, with no auxiliary fuel tanksinstalled, for the 737-700IGW (BBJ) model.Submitted by: R. Robinson (Boeing)Approved by: Kevin Hull (FAA ACO)SIGNATURE ON FILE12/18/2009REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-26737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAJANUARY 2010Revised Paragraph A. Scope to update applicability statements to reference modelderivatives and to add the 737-900ER in the Table 9-2 reference.Revised paragraph in the Airworthiness Limitations - Structural Inspections introduction toremove inspection limitations for 737-900ER.Revised front matter section “Repeat Inspection Interval” to remove obsolete wordingregarding blank DTR forms.Revised Table 9-2 Airworthiness Limitations -Structural Inspections as a result of areassessment 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 DTRCheck Forms pertaining to the wing of the 737-900ER (BBJ3) airplanes that incorporatedSB 737-21-1149.Revised Table 9-2 to increase conservativethresholds on the flat pressure bulkhead PSEsfrom 10,000 cycles to 50,000 cycles.Deleted information to Flag Note 1 for Table 9-2 to remove the inspection threshold limitationsfor the 737-900ER wing.Revised Table 9-3 information inseveral ATA 53 PSEs to maintain consistency with similaritems in Table 9-2.Revised 26-CMR-02 to reference correct AMM task procedure.Submitted by: J. Onorati (Boeing)Approved by: (FAA ACO)SIGNATURE ON FILE04/28/2010MAY 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 todeclare the operational limit imposed by factory installed winglets for the 737-700C airplanes.Submitted by: R. Robinson (Boeing) Approved by:Boeing Aviation Safety Oversight Office(BASOO) NM-100BSIGNATURE ON FILE06/17/2010REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-27JULY 2010Revised the Life Limits in Section C forthe Main Landing Gear and Main Landing GearSupport Structure from 45,000 to 75,000 landings.Revised Airworthiness Limitations - Structural Safe Life Parts [1] to update documentD101A801-14 to document D101A805-14.Revised Airworthiness Limitations - Structural Safe Life Parts [2] to state the thresholdlimitation for the Hanger Link Pin (115A1610).Submitted by: R. Robinson (Boeing) Approved by: (Seattle FAA ACO)SIGNATURE ON FILE08/27/2010REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-28737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAAUGUST 2010Revised Section H. Airworthiness Limitations – Nitrogen Generation System ALIs andCDCCLs by adding the "Final Flammability Rule,Paragraph III (F), Section 7, ParagraphM25.4 (a)" clarifying the compliance measures provided in the subsequent AWLs.Revised 47-AWL-01 by updating the Applicability column to change the affected line numbersand include airplanes that have incorporated Service Bulletin 737-47-1002, by changing thetitle to replace FRS with NGS, by removing filament heating from the concern, by replacingthe text "per AMM 47-21-07" with"(refer to Boeing AMM 47-21-07)", by refining the necessaryconditions for maintenance of the bulkhead fitting and those corresponding maintenanceactions, and by adding a note to declare thatany change to the bulkhead fitting requiresapproval by the Seattle FAA ACO.Revised 47-AWL-02 and 47-AWL-04 by updating the Applicability column to include airplanesthat 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 haveincorporated Service Bulletin 737-47-1003, byreplacing 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 GenerationSystem Cross-Vent Check Valve.Added 47-AWL-07, a 6500 Flight Hour Inspection of the Nitrogen Generation System NEADistribution Ducting.Added 47-AWL-08, an identification of the maintenance standard forthe Nitrogen GenerationSystem and notice of potential future compliance requirements associated with decreasedaircraft descent rates.Submitted by: R. Robinson (Boeing) Approved by: Robert D. Breneman(FAA)SIGNATURE ON FILE10/04/2010REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-29FEBRUARY 2011Revised Section B by deleting the blank page following Figures 1 and 2.Revised Section B by moving the ThresholdAirplane Effectivity Line Number-specificinformation before the Figures to provide better data flow in the Threshold section.Revised paragraph in Section B by deleting incorrect page number references for thelocations of Figures 1 and 2.Revised Section E by adding Sections E. 1. AWLs – FUEL SYSTEMS ALIs AND CDCCLswhich 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 mayinclude OperationalChecks (OPCs) and by clarifying theusage of the term “maintenance” inCDCCLs.Revised the USE OF ALTERNATE TOOLS paragraph to specify conditions for permissibleuse of alternate tools, test equipment, or materials.Revised the EXCEPTIONAL SHORT-TERM EXTENSIONS paragraph by updating “FlightStandards Handbook 8300.10" to "Flight Standards Handbook 8900.1 FSIMS" to reflect thecurrent reference.Revised Section F. PAGE FORMAT: AWLs – FUEL SYSTEMS table by making it asubheading of Section E, adding Operational Check (OPC), and then relettering the followingheadings 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, and28-AWL-22 through 28-AWL-24 to clarify the airplane applicability.Revised 28-AWL-01 to clarify the inspectionrequired and added an inspection of the wiresleeving, 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 limitrequirements.(Continued on next page)Submitted by: Mark Arnold (Boeing)Approved by: Scott Fung forRobert D. Breneman(FAA)SIGNATURE ON FILE03/04/2011REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-30737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAFEBRUARY 2011, ContinuedRevised 28-AWL-04 to clarify which design features must be maintained, dependent on thedisruption of the ground path of each specified connector.Revised 28-AWL-05 by replacing "EMI" with "EME" and deleting "outside of the tank". Inaddition, specified that new wiring is to be within 6.5 inches of FQISwiring. Clarified wirespacing 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 andapplicable Component Maintenance Manual revision.Revised 28-AWL-07 to clarify this CDCCL isapplicable during installation of the Hot ShortProtector and defined the features to maintain during installation. Added reference toGoodrich CMM 28-41-24 for testing.Revised 28-AWL-09 to clarify that repair andoverhaul of the FQIS in-tank wire harnessesmust be Seattle FAA ACO approved and definedwhat design features must be maintainedwhen installing the FQIS spar penetration connector.Revised 28-AWL-10 to clarify what design features must be maintained if the bulkhead fittingis removed and replaced.Revised 28-AWL-11 to clarify what design features must be maintained if the bulkhead fittingor attached tubing is removed or replaced.Revised 28-AWL-12 to clarify the maintenance actions requiring approval by the Seattle FAAACO, 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 featuresmust be maintained during pump replacement.Revised 28-AWL-15 to define what design features must be met during float switchreplacement.Revised the title of 28-AWL-16 from "Fuel TankAccess Doors - Lightning Protection Bond" to“Fuel Tank Access Doors - Lightning Protection";clarified door position numbers that requiremaintenance action during fuel tank access door installation, and added requirements forwhen using a used gasket that is greater thanfive years old and the torque values wheninstalling fuel tank access doors.(Continued on next page)(Continued from previous page)(Continued from previous page)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-31FEBRUARY 2011, ContinuedRevised the title of 28-AWL-17 from "Surge Tank Access Doors (533BB and 633BB) -Lightning Protection Bond" to "Surge TankAccess Doors (533BB and 633BB) - LightningProtection", and added fastener and torque requirements.Revised 28-AWL-18 to clarify what must be accomplished prior to resetting the circuitbreaker(s) or GFIs.Revised 28-AWL-21 by adding "CDCCL" to theTask column. Clarified what design featuresmust be maintained when the Spar Valve adapterplate, Spar Valve index, Spar Valveactuator, Cross-feed Valve adapter plate, Cross-feed index plate, or Cross-feed Valveactuator is removed and replaced for 737-600, -700, -700C, -700IGW, -800, and -900airplanes starting with Line Numbers 1877 thru 1980, 1982, and airplanes that haveincorporated Service Bulletin 737-28A1207. Clarified what must be maintained when theadapter 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 Number1983 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 actuatorwas 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, instructionsto do an Engine Fuel Suction FeedOperational Test.Revised old Section J. PAGE FORMAT: CERTIFICATION MAINTENANCEREQUIREMENTS 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 to1174” to “Note” and added the following Applicability Note: “Applicable to 737-900 airplanes,L/N 683 to 1174, that have not incorporatedSB 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 moreapplicable instructions for the associated maintenance procedure.(Continued from previous page) (Continued from previous page)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-32737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAMARCH 2011Revised Section A. Scope by adding information on a production change that has beenincorporated to increase the thickness of the horizontal stabilizer inspar lower skin, whichaffects all 737-600/700/700C/800/900ER models.Revised Table 9-2 - Airworthiness Limitations - Structural Inspections by adding a flag note(<4>) to selected 55-10PSE items, which concerns the inspection threshold for airplanes witha redesigned horizontal stabilizer inspar lower skin.Revised subsections of Section E, INTRODUCTION and PAGE FORMAT: AWLs – FUELSYSTEMS by removing referencesto Operational Checks (OPCs) as a specific type ofAirworthiness Limitation (AWL).Revised Section E.2 – Other bydeleting the text referencing Title 14 Code of FederalRegulations § 25.1301(a) and § 25.1309(b) and replacing it with the following: “This sectionof the AWLs contains FAA-approved scheduled inspections and design limitations foroperators to incorporate into their maintenance program.”Revised 28-AWL-101 by changing the task type from an Operational Check (OPC) to anAirworthiness Limitation Instruction (ALI).Submitted by: Ryder Robinson(Boeing)Approved by: Robert D. Breneman(FAA)SIGNATURE ON FILE03/22/2011REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-33JUNE 2011Revised statement referring to DTR documentD626A001-DTR by removing revision date asthe Discrepant Structure Report Form canbe used from any DTR document revision.Revised flagnote descriptions in Table 9-2 toreplace "factory installed winglets" with"production installed winglets" for reference consistency.Revised text and organization in document Sections A and B (and elsewhere) to comply withFAA formatting specifications, including, but not limited to:Revised references to 737 Next Generationmajor models from "737-600/700/800/900" toread "737-600/700/700C/800/900/900ER" to include -700C and -900ER as specificconfigurations.Revised references to Federal Aviation Regulations (FARs) to more correctly cite the UnitedStates Code of Federal Regulations (CFR) Title 14.Revised Section A. SCOPE by relocating the document effectivity information for airplaneswith 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 conservativeinspection thresholds on certain structuralelements and airplanes that have incorporatedService Bulletin 737-21-1149 for Lower Cabin Altitude (LCA) to Section B.Added paragraph to Section B to address accountability for the cumulative operational usageof Removable Structural Components.Added paragraph to Section B to reference a new Appendix J to the MPD which contains theoriginal task intervals for scheduled maintenance items which now use intervals escalated bythe Industry Steering Committee but whichmust be reverted to meet Damage Tolerancerequirements.(Continued on next page)Submitted by: Ryder Robinson(Boeing)Approved by: Robert D. Breneman(FAA)SIGNATURE ON FILE07/13/2011REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-34737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAJUNE 2011, ContinuedRevised Table 9-2 by changing number and format ofitem flag "(1)" to "<5>" to distinguish themarker and maintain document consistency.Revised Table 9-3 by changing number and format ofitem flag "(1)" to "<2>" to distinguish themarker and maintain documentconsistency, and by eliminating applicability references to"BBJ (Boeing Business Jet)", which isnot a certified type designation.Revised Section B by eliminating requirements for removal of excess sealant for all airplanesexcept those modified for LCA and by adding and eliminating inspection requirements for thehorizontal 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 newcertification data regarding excess production sealant application and from a reassessment ofthe horizontal stabilizer damage tolerance analysis.(Continued from previous page)(Continued from previous page)JULY 2011Revised 47-AWL-02 to incorporate NGS performance features to show compliance with14 CFR 26.33.Submitted by: Mark Arnold(Boeing)Approved by: Ron Landes forRobert D. Breneman(FAA)SIGNATURE ON FILE07/29/2011REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-35AUGUST 2011Revised Section D. Airworthiness Limitations – Systems to arrange the limitations for affectedaircraft in numerical order of minor-model for ease of reference.Deleted 26-CMR-01 as all potentially affected aircraft have either demonstrated freedom fromthe design concern or have implemented repairs that impose alternate inspection limits, andtherefore 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 beingsubject to 26-CMR-01, now deleted. Also removed reference to Service Bulletin 737-57-1298as the bulletin was canceled prior to release.Deleted secondary listing of 27-CMR-04 from the end of the CMR Task Table andincorporated the maintenance requirement details and the accompanying Applicability Notewithin the primary listing.Submitted by: Ryder Robinson(Boeing)Approved by: Robert D. Breneman(FAA)SIGNATURE ON FILE09/30/2011OCTOBER 2011Revised Section B. AWLs - Structural Inspections by revising 737-IGW to 737-700IGW toprovide clarification that the IGW is a 737-700. Removed reference to winglet provisioningwhich clarifies that the limitation is against the wingleted aircraft. Removed reference to wingfrom conservative threshold limits since that analysis has been completed. Replacedreference to Note <5> with Note <1> to correspond to changes in Table 9-2. Revisedhorizontal stabilizer rear spar pin part numbers. Removed paragraph giving conservativeinspection thresholds for the 737-900ER with LCA modification.Revised Table 9-2 by removing flag <1> from PSEs57-10-01 through 57-70-01 to remove thelife limits for the LCA modification on the 737-900ER and the life limit for the wing for 737-700C and 737-700IGW aircraftwith production installed winglets.Revised Table 9-2, Note <1> with Note <5> wording "These PSE's require supplementalinspections only if the Baseline StructuresProgram has been escalated." Deleted Note <5>from the Notes list since it was moved to Note <1>. All previous Note <5> references wereupdated to Note <1> to realign for clarity.Submitted by: Ryder Robinson(Boeing)Approved by: Thomas A. Enyart(for Kevin Hull)(Los Angeles FAA ACO)SIGNATURE ON FILE11/4/2011REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-36737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATADECEMBER 2011Revised Table 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONSFOR AIRPLANES WITH SB 737-21-1149 to incorporate changes affected by excess sealantapplication.Submitted by: Teja Singh (Boeing)SIGNATURE ON FILEFAA BASOO01/5/2012AUGUST 2012Revised the title for Section E.2 from “AWLs – Other” to “ENGINE FUEL SUCTION FEEDSYSTEM”.Revised Section E.2 front matter by adding theregulation Title 14 CFR § 25.951 requiring theengine fuel suction feed test. Provided the background and technical reason why the enginefuel 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" tocover lower utilization operators and revise the center tank fuel quantity requirement. Addeda notation that the excess fuel can be transferredto the opposite main tank to avoid defueling.Added a notation that the APU may be used to start the engine. Added clarification that asuction fuel feed system failing the operationaltest must be repaired and successfully passthe operational test prior to further flight.Submitted by: Cassandra Ho(Boeing)SIGNATURE ON FILEFAA BASOO10/02/2012REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAUG 2012Section Page Date Section Page Date Section Page Date Section Page Date Section Page DateD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-37LIST OF EFFECTIVE PAGES737-600/700/700C/800/900/900ERMAINTENANCE PLANNING DATA9.0 1 AUG 20129.0 2 BLANK9.0 3 AUG 20129.0 4 BLANK9.0 5 AUG 20129.0 6 AUG 20129.0 7 AUG 20129.0 8 AUG 20129.0 9 AUG 20129.0 10 AUG 20129.0 11 AUG 20129.0 12 AUG 20129.0 13 AUG 20129.0 14 AUG 20129.0 15 AUG 20129.0 16 AUG 20129.0 17 AUG 20129.0 18 AUG 20129.0 19 AUG 20129.0 20 AUG 20129.0 21 AUG 20129.0 22 AUG 20129.0 23 AUG 20129.0 24 AUG 20129.0 25 AUG 20129.0 26 AUG 20129.0 27 AUG 20129.0 28 AUG 20129.0 29 AUG 20129.0 30 AUG 20129.0 31 AUG 20129.0 32 AUG 20129.0 33 AUG 20129.0 34 AUG 20129.0 35 AUG 20129.0 36 AUG 20129.0 37 AUG 20129.0 38 BLANK9.0 39 JUN 20119.0 40 JUN 20119.0 41 JUN 20119.0 42 OCT 20119.0 43 JUN 20119.0 44 JUN 20119.0 45 OCT 20119.0 46 OCT 20119.0 47 OCT 20119.0 48 OCT 20119.0 49 OCT 20119.0 50 OCT 20119.0 51 OCT 20119.0 52 OCT 20119.0 53 OCT 20119.0 54 OCT 20119.0 55 OCT 20119.0 56 OCT 20119.0 57 OCT 20119.0 58 OCT 20119.0 59 OCT 20119.0 60 OCT 20119.0 61 OCT 20119.0 62 OCT 20119.0 63 OCT 20119.0 64 OCT 20119.0 65 OCT 20119.0 66 OCT 20119.0 67 OCT 20119.0 68 OCT 20119.0 69 OCT 20119.0 70 OCT 20119.0 71 OCT 20119.0 72 OCT 20119.0 73 OCT 20119.0 74 OCT 20119.0 75 OCT 20119.0 76 OCT 20119.0 77 OCT 20119.0 78 OCT 20119.0 79 OCT 20119.0 80 OCT 20119.0 81 OCT 20119.0 82 OCT 20119.0 83 OCT 20119.0 84 OCT 20119.0 85 OCT 20119.0 86 OCT 20119.0 87 OCT 20119.0 88 OCT 20119.0 89 OCT 20119.0 90 OCT 20119.0 91 OCT 20119.0 92 OCT 20119.0 93 OCT 20119.0 94 OCT 20119.0 95 DEC 20119.0 96 DEC 20119.0 97 DEC 20119.0 98 DEC 20119.0 99 DEC 20119.0 100 DEC 20119.0 101 DEC 20119.0 102 DEC 20119.0 103 DEC 20119.0 104 DEC 20119.0 105 DEC 20119.0 106 DEC 20119.0 107 DEC 20119.0 108 DEC 20119.0 109 DEC 20119.0 110 DEC 20119.0 111 DEC 20119.0 112 DEC 20119.0 113 DEC 20119.0 114 DEC 20119.0 115 DEC 20119.0 116 JUN 20119.0 117 AUG 20119.0 118 MAR 20119.0 119 FEB 20119.0 120 JUN 20119.0 121 FEB 20119.0 122 FEB 20119.0 123 FEB 20119.0 124 FEB 20119.0 125 FEB 20119.0 126 FEB 20119.0 127 FEB 20119.0 128 FEB 20119.0 129 FEB 20119.0 130 FEB 20119.0 131 FEB 20119.0 132 FEB 20119.0 133 FEB 20119.0 134 FEB 20119.0 135 FEB 20119.0 136 FEB 20119.0 137 FEB 20119.0 138 AUG 20129.0 139 AUG 20129.0 140 FEB 20119.0 141 JUL 20119.0 142 JUL 20119.0 143 JUL 20119.0 144 JUL 20119.0 145 JUL 20119.0 146 JUN 20119.0 147 MAY 20039.0 148 FEB 20089.0 149 JUN 20119.0 150 MAR 20079.0 151 FEB 20119.0 152 AUG 20119.0 153 AUG 20119.0 154 AUG 20119.0 155 AUG 20119.0 156 AUG 20119.0 157 AUG 20119.0 158 AUG 20119.0 159 FEB 20119.0 160 FEB 2008AUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-38LIST OF EFFECTIVE PAGES737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATASection Page Date Section Page Date Section Page Date Section Page Date Section Page DateBLANKr{i-DDEING737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-39A. SCOPEThe 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 derivativeairplane certificationactivities with the U.S. Federal Aviation Administration (FAA).Accordingly, this FAA approvedAirworthiness Limitations (AWLs) and CertificationMaintenance Requirements (CMRs) document is cross-referenced in the Model 737 Type Certificate Data Sheet, A16WE. This document satisfies therequirements of United States Code of Federal Regulations (CFR) Title 14, 25.571 and 25.1529 and Advisory Circular (AC) 25-19 as the controllingdocument 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 CFRTitle 14, 43.16 and91.403 unless an alternative program has been FAA approved.AIRWORTHINESS LIMITATIONS (AWLs)The Airworthiness Limitations (Structural Inspections and Safe LifeLimitations) may only be revised with the approval of the Seattle FAA ACO.If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection must be approved by theSeattle FAA ACO.B. AWLs– STRUCTURALINSPECTIONSINTRODUCTIONThe scheduled maintenance requirements described in this section are applicable to all 737-600/700/700C/800/900/900ER airplanemodels and allderivatives. This section is also applicable to 737-700/700C/800/900ER aircraft that have winglets installed in the factory asidentified in Table 9-1.JUN 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-40737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAThe 737-600/700/800/900 Maintenance Review Board (MRB) Report outlines the initial minimum scheduled maintenance/inspection requirements(hereafter referred to asthe baseline program) for all structure, including all Principal StructuralElements (PSEs). This baseline program was developedin accordance with the guidelines of MSG-3 and satisfies requirements of CFR Title 14, 25.571 and 25.1529 by providing accidental, environmental, andfatigue damage detection opportunity for all PSEs. In order tofully comply with therequirements of CFRTitle 14, 25.571 thesupplemental structuralinspections defined herein, are required to be accomplished prior to the stated threshold. These supplemental inspections conducted in conjunction withthe 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 CPCPBasic Task at all initial andrepeat inspections unlessnoted otherwise. It is a requirement of this section that all structure identified in Section 3 ofthe 737-600/700/800/900 MRBReport be maintained with theuse 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 DOCUMENTaMODELLINE NUMBERSWINGWINGLET737-700b1545 and onYesNo737-700IGW3128 and onYesYes737-700C3346 and onYesYes737-800778 and onYesYes737-900ERAllYesYesa. Aircraft modified to install winglets via Supplemental Type Certificate (STC) are covered by information obtained from the STCholder; refer to the applicable STC holder’s Maintenance PlanningDocument Supplement for maintenance requirements in additionto those provided in this section.b. The 737-700 models that had winglets installed in production have a split certification responsibility. Refer to the applicable STCholder’s Maintenance Planning Document Supplement for maintenance requirements in addition to those provided in this section.JUN 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-41This section does not prohibit escalationof the baseline program. The baseline program defined in the MRB Report is intendedto serve as a guideline forestablishing initial inspection requirements for new operators’ maintenance programs. Initial adjustments may be necessary toaddress operational and/orenvironmental conditions unique to the operator. As operatingexperience is accumulated, additional adjustments may be made bythe operator withFAA Principal Maintenance Inspector (PMI) approval in accordance with CFR Title 14, Part 121 in order to maintain an efficient and effective maintenanceprogram.The fuselage and empennage structure of the 737-600/700/700IGW/800is not significantly modifiedfrom the 737-300/400/500 and is certified to CFR Title14, 25.571, Amendment 0. Although a damage tolerance analysis isnot required for certification of the fuselage and empennage,AC 91-56 does requirethat a supplemental structural inspection program (based on a damage tolerance assessment) be developed for structure certifiedto the early versions ofCFR Title 14, 25.571. The 737-700C and 737-900/900ERare 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, DTRCheck Form Title,Location, Inspection Zone, Airplane Applicability, and Threshold. Where there ismore than one listingfor a given PSE Number,the DTR Check Form Titleand Location are the unique identifiers. Airplane applicability aslisted 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 737-700Airplane greater than 155,000 lbs Maximum Taxi Weight)-800 - 737-800-800FPB - 737-800FPB (Flat Pressure Bulkhead)-900 - 737-900-900ER - 737-900ER (Extended Range)JUN 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-42737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAFor all model 737-600/700/700C/800/900ER airplanes Line Numbers 3624and on: A production change has been incorporated to increase the thicknessof the horizontal stabilizerinspar lower skin. At the timeof initial certification of thisproduction change, the Airworthiness Limitations for the horizontalstabilizer have been established by requiring a conservative inspection thresholdon 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 on: For those airplanesequipped with winglets as an original factory installation, atthe time of initial certification of the winglets, the Airworthiness Limitations for the horizontalstabilizer have been established by requiring a conservative inspection thresholdon an initial list of PSEs.The inspection threshold for the subject PSEs on the affected737-600/700/700C/800/900ER and 737-700IGW airplanes described above is 10,000 flightcycles or 20,000 flight hours, whichever occurs first. Operators are instructed to contact Boeing for FAA approved inspectionswhen airplanes reach theinspection threshold.The initial supplemental inspections must beaccomplished prior to the cycle and/or hour threshold listed (prior to the first occurring). Some items aresensitive to flight length and are identified by FLS (Flight Length Sensitive) in theThreshold column of the table. FLS itemsrequire both flight hours andflight cycles to determine the implementation threshold. Refer to Figures 9-1 and 9-2 (as directed by Table 9-2 for a given PSE) to determine the thresholdfor 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 appropriateflight 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 curve.Initial inspection (threshold) and intervals are measured in flight cycles or flight hours thata particular PSE detail has accumulated regardless of what theairframe as a whole has accumulated. Most PSE details have never been replaced and therefore haveaccumulated the same flightcycles and flight hoursas the airframe. Some PSE details are replaced, such as wheninstalling RemovableStructural Components(repairable/rotable/expendables) or installingused structural parts as a repair. In these cases the PSE details have accumulated flight cycles and flight hours that may bedifferent than the airframe.The operator must account for this in determining when inspectionsmust be done. In determining the PSE flight cycles or flight hours, operators may useprocesses defined in AC 120-93.OCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-43FIGURE 9-1. FLIGHT LENGTH SENSITIVE (FLS)THRESHOLD CURVE (75,000 FLIGHT CYCLE MAXIMUM)Refer to Table 9-2 for applicability

CYCLES (X 1,000)01080907030504020604016014012010080607545FLIGHT HOURS (X 1,000)JUN 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-44737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAFIGURE 9-2. FLIGHT LENGTH SENSITIVE (FLS)THRESHOLD CURVE (56,000 FLIGHT CYCLE MAXIMUM)Refer to Table 9-2 for applicabilityFLIGHT HOURS (X 1,000)5601070305040206010080 14020604012033 759080

CYCLES (X 1,000)JUN 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-45REPEAT INSPECTION INTERVALThe supplemental structural inspection program uses the Damage Tolerance Rating (DTR)system to determine the inspections (andrepeat intervals)necessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that must beachieved for eachPSE. DTR Check Forms, which define the inspection options andthe required DTR are contained in D626A001-DTR.All PSEs that met the DTR requirement through the baseline programhave been evaluated for up to25% escalation of the baselineinspection flight cycleintervals. The additional supplemental inspections as a result of the escalation tothe baseline program are identified with Note <1> in Table 9-2. Thesenoted supplemental inspections must be accomplished prior to the given threshold if the baseline program is escalated by any amount. The 36,000 cycleinterval was not considered for escalation and is the maximum interval allowed for supplemental inspections. Where credit forthe baseline StructuresProgram is taken on a DTR Check Form, the DTR Check Form must be reevaluated and adjusted by the operator (to maintain total DTR equal to orgreater than the required DTR) upon any escalation of the baseline program. If the baseline program flight cycles are escalated beyond 25%, contact theSeattle FAA ACO.A repeat inspection interval for the fatigue inspection of a PSEis established from its DTR Check Form. Revision to the required DTR or the DTR curve isnot allowed without approval from the Seattle FAA ACO.Some structures and zonal MPD items have been escalated by theIndustry Steering Committee beyondthe initial repeat interval considered at the time ofthe initial aircraft certification. The intervals listed in Appendix J correspond to the original task intervals used in determining the DTR which satisfies 14CFR Part 25.571. As a result, prior to or at the threshold specified in Table 9-2, the items listed in Appendix J are requiredto be returned to the interval inthat appendix, rather than what is listed in Sections 2 and 3 of this MPD.OCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-46737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATASPECIAL STRUCTURAL INSPECTIONSThe following special inspections are required forhorizontal stabilizer front spar attachment bolts and rear spar attachment pins. These inspections maybe performed in conjunction with the referenced Section 2 Structural Maintenance Program inspections.Airplane Applicability:All 737-600/700/700C/800/900/900ER airplanes withhorizontal stabilizer front spar attachment bolt part numbers 180A1611-3 or180A1611-5 and horizontal stabilizer rear spar attachment pin part numbers 180A1612-3, 180A1612-4,180A1612-7 or180A1612-8.Task Description:Perform an internal detailed visual inspection of the plating on the horizontal stabilizer attachment bolts and pins for missing, crackedor flaking plating. If the plating is missing, cracked or flaking, prior to further flight replace with new parts or repair inaccordance with a method approvedby an Authorized Representative for the BCA Organization Designation Authorization who has been authorized to make those findings. ReferenceSection 2 - Structural Maintenance Program, MPD Item Number 55-070-01, 55-070-02, 55-110-01 and 55-110-02. Bolt and pin removal is required.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 accumulated from the time the newpart was installed. All otherparts shall be inspected at the specified aircraft threshold.Repeat:None.REPORTING RESULTS OFSTRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within ten (10) days directly to the Manager of the Seattle FAA ACO, the Transport AirplaneDirectorate, the FAA, and to Boeing Commercial Airplanes usingthe Discrepant Structure Report Form. Refer to D626A001-DTR forthe required reportform (any suitable alternative which contains the same information may be used).OCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-47737 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 forhire is prohibited; theseare commonly referred to as a Boeing Business Jet (BBJ). These aircraft may be modified with Service Bulletin (SB) 737-21-1149that increases themaximum 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, also require thesupplemental inspections identified in Table 9-3 of this section. These limitationsare permanent for the service life of theairplane, regardless of asubsequent reversion to any lower internal cabin pressure, or removal of SB 737-21-1149, and can only be changed by a completeengineering analysisapproved 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 tolerance analysis onlyaccounts for the specification maximum amount of sealant. The amount of sealant affects how much of the PSE structure is hidden for visual inspections.Excessive sealant (beyondspecification limits) on PSEstructure could affect the damage tolerance analysis results. Thereforesealant found to exceedthe dimension limits in AMM 51-31-00, figures 204 and 205, must beremoved to within specification for visual inspections priorto reaching the followingthresholds:1. A threshold of 28,000 cycles or 50,000 hours, whichever comesfirst, for baseline maintenance inspections (MPD Section 2 and3)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.OCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-48737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATATABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE # DTR CHECK FORM TITLE LOCATION ZONE REFAIRPLANEAPPLIC THRESHOLD52-21-04 Automatic Overwing Door Lower Frame at Stop/Guide Fitting 833/843832/842ALL 50000 Cycles52-32-01 Main Deck Cargo Door Cam Latch Support Fitting under Shear Clip 835 -700C 50000 Cycles<2>52-32-03 Main Deck Cargo Door Hinge to Skin Connection 835 -700C 50000 Cycles<2>52-48-04-2 Electronic Equipment Access DoorBounded by LBL 5.70,RBL 14.12, FrameSta 325.07 andSta 349.13117ALL 50000 Cycles53-10-03-1 Longitudinal Lap SpliceS-4L & S-4R,Sta 259.5 to 360 Upper Fastener Row, UpperSkin. 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 1016221/222231/232241/242-600/-700-700IGW-800-900-900ER50000 Cycles<2>53-10-03-1a Longitudinal Lap SpliceS-4R, Sta 259.5 to 360; S-8L, Sta 259.5 to 294.5, 350 to 360Upper 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 1016221/222231/232241/242-700C 50000 Cycles<2>53-10-03-2 Longitudinal Lap SpliceS-4L & S-4R, Sta 259.5 to 360Lower Fastener Row, Lower Skin221/222 -600/-700-700IGW-800-900-900ER50000 Cycles<2>53-10-03-2a Longitudinal Lap SpliceS-4R, Sta 259.5 to 360, S-8L, Sta 259.5 to 294.5, and 350 to360 Lower Fastener Row, Lower Skin221/222 -700C 50000 Cycles<2>53-10-03-3 Longitudinal Lap SpliceS-14L, Sta 259.5 to 294.5, 350to 360, Upper Row, Upper SkinS-14R, Sta 259.5 to 277, 344 to 360, Upper Row, Upper Skin221/222 ALL 50000 Cycles<2>OCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4953-10-03-4 Longitudinal Lap SpliceS-14L, Sta 259.5 to 294.5, 350to 360, Lower Row, Lower SkinS-14R, Sta 259.5 to 277, 344 to 360, Lower Row, Lower Skin221/222 ALL 50000 Cycles<2>53-10-03-5 Longitudinal Lap SpliceS-24L Sta259.5 to 334, & S-24R Sta 259.5 to 360Upper Fastener Row, Upper Skin112113/114117/118ALL 50000 Cycles<2>53-10-04-1 Cutout Crew Cab WindowsABPost211/212 L/N 1 to 1388 50000 Cycles<2>53-10-04-1a Cutout Crew Cab Windows(L/N 1389 & on) AB Post211/212 L/N 1389and on50000 Cycles<2>53-10-04-2 Cutout Crew Cab WindowsCD Post Leftand Right211/212 L/N 1 to 1388 50000 Cycles53-10-04-2a Cutout Crew Cab WindowsCDPost Left and Right211/212 L/N 1389and on50000 Cycles53-10-04-3 Cutout Crew Cab WindowsEF Post Left and Right211/212 ALL 50000 Cycles<2>53-10-04-4 Cutout Crew Cab Windows (L/N 1 to 1388) BD Sill Left and Right211/212 L/N 1 to 1388 50000 Cycles<2>53-10-04-4a Cutout Crew Cab Windows (L/N 1389 & on) BD Sill Left and Right211/212 L/N 1389and on50000 Cycles<2>53-10-04-5 Cutout Crew Cab WindowsPoint D Fitting Left and Right Side211/212 ALL 50000 Cycles<2>53-10-04-6 Cutout Crew Cabin WindowsX-750 Angle atB-D Sill Inner Chord Left and Right Sides ofthe Aircraft211/212 ALL 50000 Cycles<2>53-10-05-1 Crown Skin Panel - Fwd of Sta 259.5Longitudinal Splice at BL 0211/212 ALL 50000 Cycles<2>53-10-08-1 Crown Skin Panel Sta 259.5 to 360See Table Entry and DTR Form for PSE 53-30-01-2221/222 ALL<2>53-10-12-1 Cutout - Forward Access Door, Forward Edgeof CutoutSta 203.8, BL 16L to BL 16R112 -700C-700IGW50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-50737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-10-13-1 Cutout - Electronic Equipment DoorCutout Bounded by Stations323.7 & 351.2, and RBL 15.47and LBL 6.74117/118 ALL 50000 Cycles<2>53-10-14-4 Cutout - Fwd Entry Door FrameSta303.9 from S-11L to S-12L221ALL 50000 Cycles<2>53-10-14-5 Cutout - Fwd Entry Door FrameSta 303.9 from S-7L to S-11L and S-12L to S-13L221ALL 50000 Cycles<2>53-10-14-7 Fwd Entry Door Fwd Edge Frame Stops Stop Fittings at S-7 thru S-16221ALL 50000 Cycles<2>53-10-14-8 Fwd Entry Door Fwd Edge Frame Stops StopStraps at S-7 thru S-14221ALL 50000 Cycles<2>53-10-14-9 Fwd Entry Door Fwd Edge Frame Stops Stop Straps at S-15 and S-16221ALL 50000 Cycles<2>53-10-14-10 Fwd Entry Door Aft Edge Frame Stops S-15 and S-16 Tension Straps at Sta 351.2Frame Inner Chord 221 -600/-700-800-900-900ER50000 Cycles53-10-14-11 Fwd Entry Door Aft Edge Frame Stops AftFrame Stops @ Inner Flange Holes @ Approx. Sta 348.2(S-7 to S-14)221ALL 50000 Cycles53-10-14-12 Forward Entry Door CutoutLower Edge of Cutout Sta 303 to Sta 350 around and underScuff Plates Also PSE 53-10-15 Forward Galley Door Cutout117/221 ALL 50000 Cycles<2>53-10-15 Forward Galley Door CutoutSee Table Entry and DTR Form for PSE 53-10-14-12118/222 ALL<2>53-10-15-2 Forward Galley Door Surround Structure DoorStop Backup StructureForward Edge Frame at Stops #1, #2, #5, and #6 IntercostalTension Straps222ALL 50000 Cycles<2>53-10-15-4 Cutout Fwd Galley DoorSta 291.5 & Sta 328.5, S-8R to S-14R222ALL 50000 Cycles<2>53-10-18-1 Bulkhead, Sta 294.5Nose Wheel WellAft Bulkhead WL 172 Beam at BL 17115/116117/118ALL 50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5153-10-19-4 Nose Wheel Well Side and Top Panels Aft AccessCutout Forward Vertical Beam Sta 260, WL 170 toWL 184113/114115/116-600/-700-800-900-900ER50000 Cycles53-10-20-2 Nose Landing Gear Support Fittings Drag Brace Fittings, Sta 262, BL 16, WL 189.3 113/114115/116ALL 50000 Cycles<2>53-10-20-3 Nose Landing Gear Trunnion Support Fitting Inboard and Outboard Fitting Segments BS 294.5 WL 156.1BL 16113/114115/116ALL 50000 Cycles53-10-21-1 Air Stair Door Cutout Upper and Lower Sills Sta 303.8 to Sta 348 117 ALL 50000 Cycles53-10-21-4 Air Stair Door Cutout Forward andAft Edge Frames Sta 303.9 and 351.2 atLower Corners117 ALL 50000 Cycles<2>53-10-23-1 Forward Nose Wheel Well Cutout Outer Chord Sta 224.8 BL 8.45L 112/113114-700C-700IGW50000 Cycles<2>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 1016221/222231/232241/242ALL 50000 Cycles<2>53-30-01-4 Crown Skin Panel Sta 360 to 540 Antenna Cutouts at Sta 385, Sta 430, Sta 500A 231/232 ALL 50000 Cycles53-30-01-5 Satcom Aero-H Antenna Installation Sta 500 S-6/S-7 231/232 -600/-700-80050000 Cycles53-30-02-1 Fuselage Side Skin Panels BS360 to BS 540, S-14 to S-17 Also:PSE 53-60-02-1 Sta 727 to Sta 887117/118121/122125/126141/142191194195/196231/232241/242ALL 50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-52737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-30-02-4 Fuselage Side SkinPanels Under the Wing-toBody FairingBS 360 to BS 540, Under Wing-to-Body Fairing.Also: PSE 53-60-02-4, BS 727 to BS 887.121/122123/124125/126141/142143/144191/192194ALL 50000 Cycles53-30-04-1 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-10-03-1 231/232 -600/-700-700IGW-800-900-900ER<2>53-30-04-1a LongitudinalLap SpliceSee Table Entry and DTR Form for PSE 53-10-03-1a231/232 -700C<2>53-30-04-2 Longitudinal Lap SpliceS-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 887231/232241/242-600/-700-700IGW-800-900-900ER50000 Cycles<2>53-30-04-2a Longitudinal Lap SpliceS-4R, Sta 360 to540; S-7L, Sta 500 to540, Lower FastenerRow, 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 887231/232241/242-700C 50000 Cycles<2>53-30-04-3 Longitudinal Skin SpliceS-10L & S-10R,Sta 360-540 Upper Fastener Row, Upper Skin.Also: PSE 53-60-04-3 Sta 727 to 887231/232241/242-600/-700-700IGW-800-900-900ER50000 Cycles<2>53-30-04-3a Longitudinal Skin SpliceS-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 887231/232241/242-700C 50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5353-30-04-4 Longitudinal Lap SpliceS-10L and S-10R, Sta 360-540 Lower Fastener Row, LowerSkin. Also: PSE 53-60-04-4 Sta 727 to 887231/232241/242-600/-700-700IGW-800-900-900ER50000 Cycles<2>53-30-04-4a Longitudinal Lap SpliceS-10R Sta 360 - 540 Lower Fastener Row, Lower Skin. Also:PSE 53-60-04-4a, S-10L and S-10R, Sta 727 to 887231/232241/242-700C 50000 Cycles<2>53-30-04-5 Longitudinal Lap SpliceS-14L & S-14R, Sta 360 to 540 Upper Fastener Row, UpperSkin. Also: PSE 53-60-04-5 Sta 727 to 887231/232241/242-600/-700-700IGW-800-900-900ER50000 Cycles53-30-04-5a Longitudinal Lap SpliceS-14R, Sta 360to 540, S-14L, Sta 500 to 540, Upper FastenerRow, Upper Skin. Also:PSE 53-60-04-5a, S-14L & S-14R, Sta 727 to 887231/232241/242-700C 50000 Cycles53-30-04-6 Longitudinal Lap SpliceS-14L & S-14R, Sta 360 to 540 Lower Fastener Row, LowerSkin. Also: PSE 53-60-04-6 Sta 727 to Sta 887231/232241/242-600/-700-700IGW-800-900-900ER50000 Cycles<2>53-30-04-6a Longitudinal Lap SpliceS-14R, Sta 360to 540, S-14L, Sta 500 to 540, Lower FastenerRow, Lower Skin. Also:PSE 53-60-04-6a, S-14L & S-14R, Sta 727 to 887231/232241/242-700C 50000 Cycles<2>53-30-04-7 Longitudinal Lap SpliceS-24L & S-24R, Sta 360 to 540 Except at Cargo Door Cutout.Upper Fastener Row, Upper (Inner) Skin123/124125/126191ALL 50000 Cycles<2>53-30-04-8 Longitudinal Lap SpliceS-24L and S-24R, Sta 360 to 540 Except at Cargo Door Cutout.Lower Fastener Row, Lower (Outer) Skin123/124125/126191ALL 50000 Cycles53-30-05 Window BeltSee Table Entry and DTR Form for PSE 53-60-05-2231/232 ALLTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-54737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-30-08 Forward Cargo Door Surround Structure See Table Entry and DTR Form for PSE 53-60-08-8 122/124 ALL <2>53-30-08-1 Forward Cargo Door Surround Forward andAft Edge Frames at Sta 440 and 492.4 OuterChord Between S-17R and S-26R (Except at Door Stops andSills Location)122/124 ALL 50000 Cycles<2>53-30-08-2 Forward Cargo Door Surround Forward andAft Edge Frames at Sta 440 and 492.4 OuterChord at Door Stops Location andat Frame/Sill Intersections122/124 ALL 50000 Cycles<2>53-30-08-3 Forward Cargo Door Surround Forwardand Aft Edge Frame Inner Chords Between S-18Rand S-26R122/124 ALL 50000 Cycles<2>53-30-08-4 Forward Cargo Door Surround Structure Forward and Aft Edge Frame Inner Chords Between S-17Rand S-18R122 ALL 50000 Cycles<2>53-30-08-5 Forward Cargo Door Surround Structure Forwardand Aft Edge Frame Inner Chords at S-18R 122 ALL 50000 Cycles<2>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 847122/124142/144ALL 50000 Cycles<2>53-30-08-9 Forward Cargo Door Surround Structure Skin and Bearstrap atCorners of Cutout.See Table Entry and DTR Form for PSE 53-60-08-9.122/124142/144ALL53-30-08-10<1>Forward Cargo Door Surround Structure Upper Sill Outer ChordAlso: PSE 53-60-08 Aft Cargo Door Upper Sill122/124142/144ALL 50000 Cycles<2>53-30-08-11<1>Forward Cargo Door Surround Structure See Table Entry and DTR Form for PSE 53-60-08-11 122/124142/144-600/-700-700IGW-800/-900-900ER53-30-08-12 Forward Cargo Door Surround Structure LowerMain Sill Chords Between Sta 421 & 438 (-600) LowerMain Sill Chords Between Sta 461 and 478 (-700/-800) Also:PSE 53-60-08 Aft Cargo DoorSurround Structure Lower SillSta 807 to 827122/124142/144ALL 50000 Cycles<2>53-30-09-3 Forward Cargo Door Fittings and Stops at theForward and Aft Edge FramesBackup Fittings and Intercostals122ALL 50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5553-30-11-1 Wing to Body Lower Drag AngleBS 518 to BS 555 Above S-24125/126131/132191ALL 50000 Cycles<2>53-30-11-02 Wing to Body Upper Drag AngleBS 500D to 550 Between S-21 and S-22125/126131/132191ALL 50000 Cycles<2>53-30-11-03 Wing to Body Upper Drag AngleNear BS 540, Between S-21 and S-22125/126131/132191ALL 50000 Cycles<2>53-30-12-7 Floor Beam to Frame JointBS 360 to BS 500; S-17R to 18R121/122 700C 50000 Cycles<2>53-40-01-1 Crown Skin Panel Sta 540 to 727SeeTable Entry and DTR Form for PSE 53-30-01-2231/232241/242ALL<2>53-40-03-1 LongitudinalLap SpliceSee Table Entry andDTR Form for PSE 53-10-03-1231/232241/242-600/-700-700IGW-800-900-900ER<2>53-40-03-1a Longitudinal Lap SpliceSee Table Entry and DTR Form for PSE 53-10-03-1a231/232241/242-700C<2>53-40-03-2 LongitudinalLap SpliceSee Table Entry andDTR Form for PSE 53-30-04-2231/232241/242-600/-700-700IGW-800-900-900ER<2>53-40-03-2a Longitudinal Lap SpliceSee Table Entry and DTR Form for PSE 53-30-04-2a231/232241/242-700C<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-56737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-40-03-3 Longitudinal Skin SpliceS-10L andS-10R, STA 540 to 727 Upper Fastener Row,Upper Skin231/232241/242-600/-700-700IGW-800-900-900ER50000 Cycles<2>53-40-03-3a Longitudinal SkinSpliceSee Table Entry and DTRForm for PSE 53-30-04-3a231/232241/242-700C<2>53-40-04-1 Window Belt, Sta 540 to 727Stringer 11 and Stringer 13231/232241/242ALL 50000 Cycles53-40-04-2 Window Belt, Sta 540 to 727Between Windows, S-11 to S-13231/232241/242ALL 50000 Cycles53-40-07-2 Stringer Splice, Sta 663Spliceat Stringer 11 and Stringer 13231/232241/242ALL 50000 Cycles53-40-08-1 Keel Beam Chords, Stiffeners and Splice Keel Beam Side Panel Webs Sta 540 to Sta 663133/134139192/193ALL 50000 Cycles53-40-10-1 Stiffener Attachment to Floor Beam, Sta 727 LBL 45.5 & RBL 45.5 @ WL 202.6133/134 ALL 50000 Cycles<2>53-40-11-1 Stringer 18 Strap Side ofBodySta 717 to Sta 727133/134141/142ALL 50000 Cycles<2>53-40-12-1 Stringer 18A Chord and LinksSta 663 Link Lugs131/132133/134ALL 50000 Cycles<2>53-40-14-1 Frame Splice @ BS 540Inner Chord Between S-8 and S-9231/232 ALL 50000 Cycles<2>53-40-14-4 BS 540 BulkheadSkin at Outer Chord, S-9L to S-9R231/232 ALL 50000 Cycles53-40-15-1 BS 663 BulkheadOuter Chord Between S-8 and S-11231/232 ALL 50000 Cycles53-40-15-3 BS 663 BulkheadInner Chord Between S-10 and S-17 LH & RH231/232 ALL 50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5753-40-16-1a Aft Wheel Well Bulkhead Sta 727 Outer Chord S-21 to S-27 133/134141/142143/144193ALL 50000 Cycles<2>53-40-16-1b Aft Wheel Well Bulkhead Sta 727 Outer Chord S-21 to S-27 133/134141/142143/144193ALL 50000 Cycles<2>53-40-16-2 Wheel Well Aft Bulkhead Frame Inner Chord at Sta 727, WL 201 141/142 -600L/N 1-766-600L/N 767-1192-700L/N 1-766-700L/N 767-119234000 Cycles50000 Cycles27000 Cycles50000 Cycles53-40-16-2a Wheel Well Aft Bulkhead Frame Inner Chord at Sta 727, WL 201 141/142 -600/-700L/N 1193And On-700C-700IGW-800/-900-900ER50000 Cycles50000 Cycles53-40-16-3 Wheel Well Aft Bulkhead and Pressure Web,Sta 727Lower Frame Sta 727 133/134141/142-600/-700-700IGW-800/-900-900ER50000 Cycles<2>53-40-16-5 Aft Wheel Well Bulkhead and Pressure Web,Sta 727Frame Sta 727, S-9L to S-9R 241/242 ALL 50000 Cycles53-40-16-6 Aft Wheel Well Bulkhead Frame Sta 727 Sta 727 Between S-9 and S-10 241/242 ALL 50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-58737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-40-17-1 Side Strut Support Frame Sta 706Frame Inner & OuterChords and Fail-Safe Angle S-10 to S-13 241/242 ALL 50000 Cycles<2>53-40-18-2 Main Landing Gear Support Frame Sta 695 Stub Beam Upper Chord133/134241/242ALL 50000 Cycles<2>53-40-19-1 Main Landing Gear Support Frame Sta 716 Frame Inner Chord and Web at S-16133/134241/242ALL 50000 Cycles<2>53-40-19-2 Main Landing Gear Support Frame Sta 716 Stub Beam Upper Chord at Crease Beam Chord Attachment 133/134241/242ALL 50000 Cycles<2>53-40-19-3 Main Landing Gear Support Frame Sta 716Stub Beam Web at Floor Clip Attachment133/134241/242ALL 50000 Cycles<2>53-40-19-3a Main Landing Gear Support Frame STA 716 Horizontal Leg of Frame STA 716, BL 45.5 to BL 64.6133/134241/242ALL 50000 Cycles<2>53-40-21-2 Wheel Well Frame, Sta 685Frame Inner Chord S-13 to S-15133/134241/242ALL 50000 Cycles53-40-21-3 Wheel Well Frame Sta 685Frame Inner Chord S-17 to S-14133/134241/242ALL 50000 Cycles<2>53-40-21-4 Wheel Well Frame at Sta685Stub Beam Upper Chord133/134241/242ALL 50000 Cycles<2>53-40-22-1 Overwing Emergency Exit CutoutEdge Frame 616 Outer Chord and Skin Assembly betweenSTR 10 and STR 13231/232 -600 50000 Cycles<2>53-40-22-2 Overwing EmergencyExit Cutout (InspectionApplicable Only to 737-700/-700C/-700IGW Cumline Number 9 and on)Edge Frame Sta 616 Outer Chord, S-10 to S-13231/232 -700-700C-700IGW50000 Cycles<2>53-40-22-3 Overwing Emergency Exit Cutout SkinAssembly and Frame Outer Chord (InspectionApplicable Only to 737-800 Cumline Number 9and on and 737-900)Edge Frame 578 Near Stringer S-11 to S-13231/232 -800-900-900ER50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5953-40-22-4 Overwing Emergency Exit Cutout Forward and Aft Lower Door Corners Sta 616 and Sta 639 231/232 -600/-700-700C-700IGW50000 Cycles<2>53-40-22-5 Overwing Emergency Exit Cutout Upper Edgeof both Upper Cornersof Cutout from S-11 @Sta 616 to S-11 @ Sta 639231/232 -600/-700-700C-700IGW50000 Cycles<2>53-40-22-6 Overwing EmergencyExit Cutout - DoorCutouts CornersUpper Edge of Doors from S-11 @ Sta 578 to S-11 @ Sta 601and from S-11 @ Sta 616 to S-11 @ Sta 639231/232 -800-900-900ER50000 Cycles<2>53-40-22-7 Overwing Emergency ExitCutout Edge Frame Outer Chord Under Stop Backup Fittings at S-11and S-12231/232 ALL 50000 Cycles<2>53-40-22-8 Overwing Emergency Exit Cutout Both LowerCorners and Lower Edge of Cutout from S-14 @Sta 616 to S-14 at Sta 639231/232 -600/-700 50000 Cycles<2>53-40-22-8a Overwing Emergency Exit Cutout Both Lower Corners and Lower Edge of Cutout from S-14Sta 616 to S-14 Sta 639231/232 -700C-700IGW50000 Cycles<2>53-40-22-9 Overwing Emergency Exit CutoutAll Four Lower Corners (Intersection of Lower Sill and EdgeFrames 578, 601, 616, and 639) + SkinAssy over the LowerSills231/232 -800-900-900ER50000 Cycles<2>53-40-22-10 Overwing EmergencyExit Cutout Skin andFrame Assy Section@ Sta 616 and S-13Covered Region: Edge Frame 616 from S-13 to S-15 andEdge Frame 639 from S-10 to S-15231/232 -600/-700-700C-700IGW50000 Cycles<2>53-40-22-11 Overwing EmergencyExit Cutout Skin Assyand Frame Outer ChordDoor Edges at Sta 578 S-13 toS-15 and at Sta 601, 616 and639 S-10 to S-15231/232 -800-900-900ER50000 Cycles<2>53-40-22-12 Overwing Emergency Exit CutoutLower Aft Corner Frame 616 & 639 at Lower Sill231/232 -700C-700IGW50000 Cycles53-40-22-13 Overwing Emergency Exit CutoutLower Sill Inner Splice Strap231/232 -800-900-900ER50000 CyclesTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-60737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-40-22-20 Overwing EmergencyExit Cutout Structure(Inspection Applicable to 737-700 CumlineNumber 1 thru 6 Only)Sta 616 Skin Assembly under External (Boomerang) Doubler 231/232 -700 50000 Cycles<2>53-40-22-22 Overwing EmergencyExit Cutout Structure(Inspection Applicable to 737-800 CumlineNumber 7 and 8 Only)Sta 578, Sta 616 and Sta 639 Skin Assemblies under External(Boomerang) Doublers231/232 -800 50000 Cycles<2>53-40-23-1 Overwing Emergency Exit Door Stops andFittingsDoor Stops Attached to the Forward and Aft Door Edge Frames 231/232 ALL 50000 Cycles53-40-23-2 Overwing Emergency Exit Door Stops andFittingsDoor Stop Intercostals Between Sta 601 and Sta 616231/232 -800-900-900ER50000 Cycles53-40-23-3 Overwing Exit Door Stops and Fittings Door Stop Backup Fitting Attachment to Window Frames atS-11 and S-12231/232 -600/-700-800-900-900ER50000 Cycles<2>53-40-24-1 Pressure Deck Attachments to Rear SparExtensionBS 663133/134 ALL 50000 Cycles53-60-01-2 Crown Skin Panel Sta 727 to 887See Table Entry and DTR Form for PSE 53-30-01-2241/242 ALL<2>53-60-01-4 Crown Skin Panel Sta 727 to 887ADF Antenna Cutout Sta 727 + 9, RBL 5SATCOM Antenna Cutout Sta 747, STR-1241/242 ALL 50000 Cycles53-60-01-5 SATCOM Antenna Installation(Canadian Marconi and Honeywell)Section 46: Sta 767 between S-1 and S-2L241/242 ALL 50000 Cycles<2>53-60-01-6 SATCOM Antenna Installation (All except thosecovered by PSE 53-60-01-5)Section 46: Sta 767 between S-1 and S-2L241/242 ALL 50000 Cycles<2>53-60-02-1 Fuselage Side SkinPanelsSee Table Entry and DTR Form for PSE 53-30-02-1141/142194241/242ALL<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6153-60-02-4 Fuselage Side SkinPanels Under the Wing-toBody FairingSee Table Entry and DTR Form for PSE 53-30-02-4. 141/142143/144194ALL53-60-04-1 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-10-03-1 241/242 -600/-700-700IGW-800-900/-900ER<2>53-60-04-1a LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-10-03-1a 241/242 -700C <2>53-60-04-2 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-2 241/242 -600/-700-700IGW-800-900/-900ER<2>53-60-04-2a LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-2a 241/242 -700C <2>53-60-04-3 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-3 241/242 -600/-700-700IGW-800-900/-900ER<2>53-60-04-3a Longitudinal Skin Splice See Table Entry and DTR Formfor PSE 53-30-04-3a 241/242 -700C <2>53-60-04-4 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-4 241/242 -600/-700-700IGW-800-900/-900ER<2>53-60-04-4a LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-4a 241/242 -700C <2>53-60-04-5 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-5 241/242 -600/-700-700IGW-800-900/-900ER53-60-04-5a LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-5a 241/242 -700CTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-62737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-60-04-6 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-30-04-6 241/242 -600/-700-700IGW-800-900/-900ER<2>53-60-04-6a LongitudinalLap SpliceSee Table Entry and DTR Form for PSE 53-30-04-6a241/242 -700C<2>53-60-04-7 Longitudinal Lap SpliceS-23L & S-23R, Sta 727 to 887 Except at Cargo Door Cutout.Upper Fastener Row, Upper (Inner) Skin143/144 ALL 50000 Cycles<2>53-60-05-2 Window Belt Sta 727 to888Window Frames Also PSE 53-30-05 Sta 360 to 540. Also:PSE 53-70-09 Sta 888 to 927231/232241/242ALL 50000 Cycles53-60-08 Aft Cargo Door Surround StructureSee Table Entry and DTR Form for PSE 53-30-08-12142/144 ALL<2>53-60-08 Aft Cargo Door Surround StructureSee Table Entry and DTR Form for PSE 53-30-08-10142/144 ALL<2>53-60-08 Aft Cargo Door Surround StructureSee Table Entry and DTR Form for PSE 53-30-08-6142/144 ALL<2>53-60-08-1 Aft Cargo Door Surround StructureForward and Aft EdgeFrame Inner Chords between S-18Rand S-26R142ALL 50000 Cycles<2>53-60-08-2 Aft Cargo Door Surround StructureForward and Aft EdgeFrame Inner Chords between S-17Rand S-18R142ALL 50000 Cycles<2>53-60-08-3 Aft Cargo Door Surround StructureForward and Aft Edge Frame InnerChords at S-18R142/144 ALL 50000 Cycles<2>53-60-08-4 Aft Cargo Door Surround Forward and Aft EdgeFrames at BS 794.37 and 847Outer Chord Between S-16R & S-26R (Except at Door Stopsand Sills Location)142/144 ALL 50000 Cycles<2>53-60-08-5 Aft Cargo Door Surround Forward and Aft EdgeFrames at BS 794.37 and 847Outer Chord at Door Stops Location and at Frame/SillIntersections142/144 ALL 50000 Cycles<2>53-60-08-8 Aft Cargo Door Surround StructureForward and Aft Edge of Door Sta 794.4 and Sta 847 S-18R toS-25R. Also:PSE 53-30-08, Forward Cargo Door at Sta 440 & Sta 492.4122/124142/144ALL 50000 Cycles<2>53-60-08-9 Aft Cargo Door Surround StructureSkin and Bearstrap at Corners of Cutout. Also:PSE 53-30-08-9, Forward Cargo Door122/124142/144ALL 34000 CyclesTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6353-60-08-11 Aft Cargo Door Surround Structure Upper Sill Inner Chord. Also:PSE 53-30-08-11, Forward Cargo Door Upper Sill Inner Chord-600/-700-800-900/-900ER50000 Cycles<2>53-60-09-3 Aft Cargo Door Fittings and Stops at theForward and Aft Edge FramesBackup Fittings and Intercostals 142 ALL 50000 Cycles<2>53-60-12-3 Mid Exit Door Surround StructureUpper Main Sill, STA 727H to 727J-900ER 50000 Cycles53-60-13-1 Mid Exit Door Surround Door Stop FittingsAt BS 727H + 8.85” and BS 727I + 13.15”-900ER 50000 Cycles53-70-03-1 LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-10-03-1 241/242 -600/-700-700IGW-800-900/-900ER<2>53-70-03-1a LongitudinalLap Splice See Table Entry and DTR Form for PSE 53-10-03-1a 241/242 -700C <2>53-70-03-2 Longitudinal Lap Splice S-4L & S-4R, Sta 887-1016 Lower Fastener Row, Lower Skin 241/242 ALL 50000 Cycles<2>53-70-03-3 Longitudinal Lap Splice S-14L, Sta 888 to 947, 1006 to1016, Upper Row, Upper SkinS-14R, Sta 888 to 947, 996 to 1016, Upper Row, Upper Skin241/242 ALL 50000 Cycles53-70-03-4 Longitudinal Lap Splice S-14L, Sta 888 to 947, 1006 to1016, Lower Row, Lower SkinS-14R, Sta 888 to 947, 996 to 1016, Lower Row, Lower Skin241/242 ALL 50000 Cycles<2>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 ALL <2>53-70-07-3 Aft Entry Door, Forward Edge Frame DoorStop Backup StructureStops #1, #2, #6 and #7 241 ALL 50000 Cycles<2>53-70-07-4 Aft Entry Door Aft Edge Frame Door StopBackup IntercostalsStop Locations #1, #2, #6 and #7 241 ALL 50000 Cycles<2>53-70-07-5<1>Cutout, Aft Entry Door Surround Structure SkinAround Perimeter of Cutout 241 ALL 50000 Cycles53-70-07-6 Aft Entry Door Surround StructureLower Sill Scuff Plate Installation. Also:PSE 53-70-08-6, Aft Galley Door Surround Structure145/241 ALL 50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-64737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-70-07-11<1>Aft Entry Door Surround StructureUpper MainSill Inner Chord Sta 951.0 to 1006.Also: PSE 53-70-08, Aft Galley Door Surround Structure241ALL 50000 Cycles53-70-07-12 Aft Entry Door Surround StructureLower Main SillAlso: PSE 53-70-08-12, Aft Galley Door Surround Structure241ALL 50000 Cycles<2>53-70-08<1>Aft Galley Door Surround StructureSee TableEntry and DTR Form for PSE 53-70-07-11242ALL<2>53-70-08-3 Aft Galley DoorForward Edge Frame DoorStop Backup StructureStops #1, #2, #5 and #6242ALL 50000 Cycles<2>53-70-08-4 Aft Galley Door Aft Edge Frame Door StopBackup IntercostalsStops Locations #1, #2, #5 and #6242ALL 50000 Cycles<2>53-70-08-5<1>Cutout, Aft Galley Door Surround Structure SkinAround Perimeter of Cutout242ALL 50000 Cycles53-70-08-6 Aft Galley Door Surround StructureSee Table Entry and DTRForm for PSE 53-70-07-6146/242 ALL<2>53-70-08-12 Aft Galley Door Surround StructureLower Main Sill Outer ChordSee Table Entry and DTR Form for PSE 53-70-07-12242ALL 50000 Cycles<2>53-70-09 Window BeltSee Table Entry and DTR Form for PSE 53-60-05-2241/242 ALL53-80-01-2 Bulkhead Sta 1016Pressure Dome Webs Between Tear Straps311/312 ALL Except-800FPB-900ER50000 Cycles53-80-01-3 Bulkhead Sta 1016Pressure Dome Webs Between Tear Straps Lap Splice(Visible Row)311/312 ALL Except-800FPB-900ER50000 Cycles53-80-01-4 Bulkhead Sta 1016Web at Pressure Chord Adjacent to Stiffeners145/146241/242311/312ALL Except-800FPB-900ER50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6553-80-01-5A Bulkhead Sta 1016Web at Pressure Chord Between Stiffeners from S-5L to S-7Land S-5R to S-9R.241/242311/312ALL Except-800FPB-900ER50000 Cycles<2>53-80-01-5B Bulkhead Sta 1016Web at Pressure Chord Between Stiffeners Areas Outside ofS-5L to S-7L and S-5R to S-9R.145/146241/242311/312ALL Except-800FPB-900ER50000 Cycles<2>53-80-01-6 Bulkhead Sta 1016Web at Chord Splice Between S-1 and S-3, and between S-15and S-18145/146241/242311/312ALL Except-800FPB-900ER50000 Cycles<2>53-80-01-7 Bulkhead Sta 1016Pressure Dome Webs Lap Splice Under Stiffeners(Hidden Detail)145/146241/242311/312ALL Except-800FPB-900ER50000 Cycles<2>53-80-01-8 Bulkhead Sta 1016Pressure Dome Webs at Tear Straps311/312 ALL Except-800FPB-900ER50000 Cycles<2>53-80-01-9 Bulkhead Sta 1016Pressure Dome Webs at Lap Splice and Tear StrapIntersection311/312 ALL Except-800FPB-900ER50000 Cycles<2>53-80-01-11 Bulkhead Sta 1016Pressure Dome Webs atLap Splice/Tear Strap Junctions 311/312 ALL Except-800FPB-900ER50000 Cycles<2>53-80-01-13 Bulkhead Sta 1016Web at Chord Splice/Doubler Between S-1 and S-3311/312 ALLL/N 1057and on, Except-800FPB-900ER50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-66737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-80-01-14 No DTR Form - Perform Aft Side DetailedVisual Inspection of BS 1016 Bulkhead WebLooking for Oil Cans, Refer to Structural RepairManual Section 53-80-08 for Definition of OilCan. SRMs:737-600 - D634A220737-700 - D634A201737-700IGW - D634A330737-700C - D634A202737-800 - D634A210737-900 - D634A211Repeat Inspections Every 10000 Flight Cycles.Bulkhead Sta 1016311/312 ALLL/N 1756and on, Except-800FPB-900ER36000 Cycles53-80-02-1<1>Vertical Fin Front Spar Fitting, BulkheadAttachment - STA 1016Bulkhead Sta 1016241/242322ALLExcept-800FPB-900ER50000 Cycles53-80-02-1a Vertical Fin Front Spar Fitting BulkheadAttachment - Sta 1016Bulkhead Attachment @ Sta 1016241/242322-800FPB-900ER50000 Cycles<2>53-80-02-2 Vertical Fin Front SparFittingsSta 1016 Fitting Lugs241/242322ALL 50000 Cycles<2>53-80-03-1 Stringer Splice FittingsSta 1016, S-9Lto S-9R Forward and Aft of Bulkhead241/242311/312ALL 50000 Cycles<2>53-80-05-1 Jackscrew Fitting LugsBulkhead Sta 1088311/312 ALL 50000 Cycles<2>53-80-06-1 Vertical Fin Rear Spar Attachment Fittings Bulkhead Sta 1088311/312313/314323ALL 50000 Cycles<2>53-80-06-2 Vertical Fin Rear Spar Attachment Fittings Primary Lugs at Sta 1088311/312313/314323ALL 50000 CyclesTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6753-80-07-1 Bulkhead Sta 1156Outer Chord at Pivot Fitting Attachment313/314317/318ALLL/N 1 to119850000 Cycles<2>53-80-07-2 Integrated Bulkhead Sta 1156Web Inboard of Failsafe Strap,Above and Below Pivot FittingAttachment313/314317/318ALLL/N 1199and on50000 Cycles<2>53-80-08-1 Horizontal Stabilizer Pivot FittingSta 1156 Hinge Beam at Pivot Pin313/314 ALL 50000 Cycles<2>53-80-08-2 Horizontal Stabilizer Pivot PinsSta 1156 Pivot Pins313/314 ALL 50000 Cycles<2>53-80-10-1 Section 48 Skin Panels, Sta 1088 to 1156 Skin Panels at BS 1138 Cutout313/314 ALL 50000 Cycles53-80-14-4 Sta 1042 Bulkhead StrapsAft Horizontal Straps311/312 -800FPB-900ER50000 Cycles53-80-14-7 Sta 1042 Bulkhead IntercostalsSystem Penetrations in Horizontal Intercostals311/312 -800FPB-900ER50000 Cycles53-80-15-1 Sta 1042 Bulkhead Lugs, Links and FittingsBulkhead LugsBulkhead Beam End Lugs @ Sta 1042311/312 -800FPB-900ER50000 Cycles53-80-15-2a Sta 1042 Bulkhead Lugs, Links and FittingsEnd Beam LugsLug Attachment to Beam Hidden byattach fittings Lugs atRBL/LBL 10, 23 and WL 282, 269, and 256311/312 -800FPB-900ER50000 Cycles<2>53-80-15-2b Sta 1042 Bulkhead Lugs, Links, and FittingsEnd Beam Lug Attachment at Diagonal BeamLug Attachment to Beam Hidden byAttach Fittings and Strapsat WL 223311/312 -800FPB-900ER50000 Cycles<2>53-80-15-3 Sta 1042 Bulkhead Link FittingsLinkClevis Fittings at Sta. 1042311/312 -800FPB-900ER50000 Cycles53-80-15-4 Sta 1042 Bulkhead Lugs, Links, and FittingsLink Attach FittingsBulkhead Link Attach Fittings @ Sta 1042311/312 -800FPB-900ER50000 Cycles53-80-16-1 Sta. 1042 Bulkhead Chord SpliceSplice @ APU Cutout145/146241/242311/312-800FPB-900ER50000 CyclesTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-68737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-80-17-2 APU Inlet Cutout Enclosure Forward Panel Fasteners at visible locations common to the longerons and theSta 1016 T-Chord241/242 -800FPB-900ER50000 Cycles<2>53-80-17-3 APU Inlet Enclosure Installation - PressurePanelsVisible fastener locations commonto the Mid and Aft PressurePanels241/242 -800FPB-900ER50000 Cycles53-80-17-4 APU Enclosure Installation Pressure Panels Crack at fastener in hidden edge 241/242 -800FPB-900ER50000 Cycles<2>53-80-17-5 APU Enclosure Installation Pressure Panels Crack at mid pressure panel hidden by frame at fastener row 241/242 -800FPB-900ER50000 Cycles<2>53-80-17-6 APU Enclosure Installation Pressure Panels Crack at fastener in aft pressure panel hidden by BS 1030frame241/242 -800FPB-900ER50000 Cycles<2>53-80-17-7 APU Inlet Enclosure Installation - PressurePanelsForward Pressure Panel Fastener Row Hidden by Stiffener 241/242 -800FPB-900ER50000 Cycles<2>53-80-17-8 APU Enclosure InstallationStiffenersat Mid/Aft Panel Interface241/242 -800FPB-900ER50000 Cycles<2>53-80-18-1 Section 48 Longitudinal Lap Splices S-4 LapSplice, Sta 1016 to 1042Upper Fastener Row - Outer Skin145/146241/242-800FPB-900ER50000 Cycles<2>53-80-18-2 Section 48 Longitudinal Lap Splices S-4 LapSplice, Sta 1016 to 1042Lower Fastener Row - Inner Skin145/146241/242-800FPB-900ER50000 Cycles<2>53-80-18-5 Section 48 Longitudinal Lap Splices S-24 LapSplice, Sta 1016 to 1042Upper Fastener Row - Outer Skin145/146241/242-800FPB-900ER50000 Cycles<2>53-80-18-6 Section 48 Longitudinal Lap Splices S-24 LapSplice, Sta 1016 to 1042Lower Fastener Row - Inner Skin145/146241/242-800FPB-900ER50000 Cycles<2>53-80-18-7 Section 48 Butt Splice at S-9R and S-9LBS 1016 - BS 1042Upper Fastener Row in the Upper Skin and Lower FastenerRow in the Lower Skin145/146241/242-800FPB-900ER50000 Cycles<2>53-80-18-9 Section 48 Butt Splice at S-9R and S-9LBS 1016 - BS 1042Fastener row in strap common to Stringer 9 (upper skin,lower row)145/146241/242-800FPB-900ER50000 Cycles<2>53-80-18-10 Section 48 Butt Splice at S-9R and S-9LBS 1016 - BS 1042Fastener row in strap common to upper row of lower skin 145/146241/242-800FPB-900ER50000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6953-80-20-4 Side Skin Panel, Sta 1016 to 1042 S-9R toS-16R - APU Inlet CutoutForward Edge of APU Inlet Cutout 241/242 -800FPB-900ER50000 Cycles54-51-0154-51-0254-51-0354-51-0454-51-0554-51-0654-51-0754-51-0854-51-0954-51-15Strut to Wing Attachments Zone 431/441/434/444 430/440 ALL 56000 Cycles56000 Cycles56000 Cycles56000 Cycles56000 Cycles56000 Cycles56000 Cycles56000 Cycles56000 Cycles56000 Cycles54-51-10 Lower Spar Chord-Typical Exposed Detail Typical Lower Spar Chord Between Forward and Aft EngineMounts 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 Chords433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord at Fire Seal DepressorBracketNSTA 203.4 Left and Right Hand ChordsNSTA 207.8 Left and Right Hand Chords433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord - Bracket NSTA 218.0 Right Hand SideNSTA 216.0 Left Hand Side433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord at Frames with Brackets NSTA 222.6, Left and Right Hand ChordsNSTA 242.7, Left and Right Hand Chords433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord Aft Engine Mount Bulkhead 433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord, Web Only NSTA 224.7 – 231.8, Right Chord 433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord, Chord Only NSTA 224.7 – 231.8, Right Chord 433/443 ALL 56000 CyclesTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-70737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA54-51-10 Lower Spar Chord – Compression PadBracket, Horizontal LegNSTA 244.9 Left and Right Hand Chords 433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord – Compression PadBracket, Vertical LegNSTA 244.9 Left and Right Hand Chords 433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord – Typical Frame Detail,Vertical LegNSTA 209.0 – 212.3, 231.8 – 234.4 Left and Right HandChords433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord – Typical Frame Detail,Horizontal LegNSTA 209.0 – 212.3, 231.8 – 234.4 Left and Right HandChords433/443 ALL 56000 Cycles54-51-10 Lower Spar Chord Aft of Aft Engine Mount Bulkhead 433/443 ALL 56000 Cycles54-51-11 Fwd Engine Mount Bulkhead End Pad Bolt Holes (4 Locations) 433/443 ALL 56000 Cycles54-51-14 Mid Strut Bulkhead End Pad 433/443 ALL 56000 Cycles54-51-16 Side Skin Cutouts NSTA 270 and NSTA 252, Left and Right Sides 433/443 ALL 56000 Cycles54-51-16 Strut Side Skin NSTA Sta 222.6 Left and Right Sides and NSTA 242.7, Leftand Right Sides433/443 ALL 56000 Cycles54-51-17 Upper Spar Chord Typical Upper Spar Chord Between Forward and Aft EngineMountsNSTA 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 Chords433/443 ALL 56000 Cycles54-51-17 Upper Spar Chord Near Cutouts NSTA 200.9 – NSTA 211.5, Right ChordNSTA 213.6 – NSTA 225.2, Right ChordNSTA 226.1 – NSTA 233.6, Right Chord433/443 ALL 56000 Cycles54-51-17 Upper Spar, R1 – Fitting and Upper Spar WebJoints, Chord OnlyNear Cutouts – NSTA 200.9 – 211.5,NSTA 213.6 – 225.2,NSTA 226.1 – 233.6433/443 ALL 56000 Cycles54-51-17 Upper Spar, R1 – Fitting and Upper SparJoints, Web OnlyNear Cutouts – NSTA 200.9 – 211.5,NSTA 213.6 – 225.2,NSTA 226.1 – 233.6433/443 ALL 56000 Cycles54-51-17 Upper and Lower Spar Chords Splice to Fwd Engine Mount Bulkhead 433/443 ALL 56000 CyclesTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7154-51-17 Upper Spar ChordNSTA 222.6, Left and Right Hand ChordsNSTA 210.6, Left and Right Hand Chords433/443 ALL 56000 Cycles54-51-17 Upper Spar ChordNSTA 242.7, Left and Right Chords433/443 ALL 56000 Cycles54-51-17 R3/R4 First Fastener Row – Vertical Leg First Fastener Row Right and Left Hand Side433/443 ALL 56000 Cycles54-55-03 Forward Engine Mount HangerZone 413/414/423/424410/420 ALL 56000 Cycles54-55-05 Thrust Link AssemblyZone 415/416/425/426410/420 ALL 56000 Cycles54-55-06 Thrust Link PinZone 415/416/425/426410/420 ALL 56000 Cycles54-55-10 Aft Engine Mount AssemblyZone 415/416/425/426410/420 ALL 56000 Cycles54-55-11 Evener Bar Assembly – Outboard Lugs Zone 415/416/425/426410/420 ALL 56000 Cycles54-55-11 Aft Engine Mount Evener Bar – Mid Span Zone 415/416/425/426410/420 ALL 56000 Cycles54-55-13 Strut Attach Bolts (Forward and Aft Mounts) Zone 413/414/415/416/423/424/425/426410/420 ALL 56000 Cycles55-10-01-1 Horizontal StabilizerCenter Section Rear SparUpper ChordBL 1.3 Left and Right313/314 ALL 56000 Cycles<2> <3> <4>55-10-01-2 Horizontal StabilizerCenter Section Rear SparUpper ChordBL 2.7 to BL 6.7 Left and Right313/314 ALL 56000 Cycles<2> <3> <4>55-10-01-3 Horizontal StabilizerCenter Section Rear SparUpper ChordBL 8.1 to 19.7 Left and Right313/314 ALL 56000 Cycles<2> <3> <4>55-10-01-4 Horizontal StabilizerCenter Section Rear SparUpper ChordThrust Beam Attachment313/314 ALL 56000 Cycles<2> <3> <4>55-10-02-1 Horizontal Stabilizer Center SectionPivot FittingHinge House Pivot Lug313/314 ALL 56000 Cycles<2> <3> <4>55-10-02-2 Horizontal Stabilizer Center SectionPivot FittingLower Hinge Housing Lugs313/314 ALL 56000 Cycles<2> <3> <4>55-10-02-3 Horizontal StabilizerCenter Section ThrustLink FittingsClevis Lugs313/314 ALL 56000 Cycles<2> <3> <4>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-72737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA55-10-03-1 Horizontal Stabilizer Center SectionJackscrew FittingJackscrew Lugs 311/312 ALL 56000 Cycles<2> <3> <4>55-10-04-1 Horizontal StabilizerRear Spar Lower Chord Stab Sta 129.5 to 212.3332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-2 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 212.3 to 310.54.Forward Flange at and between ribs 332/342333/343ALL 56000 Cycles<2> <3> <4>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)332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-4 Horizontal StabilizerRear Spar Lower Chord Stab Sta 212.3 to 310.54. Chord web flange at the TE ribs/stiffeners332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-5 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 212.3 to 310.54. Web Flange between the TE ribs/stiffeners332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-6 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 310.54 to outboard tip. Forward flange at andbetween the ribs332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-7 Horizontal StabilizerRear Spar Lower Chord Stab Sta 310.54 to outboard tip. Aft flange at and between theribs332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-8 Horizontal Stabilizer Rear Spar Lower Chord Stab Sta 310.54 to outboard tip. Web flange at and betweenthe ribs332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-9 Horizontal StabilizerRear Spar Lower Chord Aft flange at thehinge, Stab Sta 242 to 247, Elev Sta 197 to203332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-10A Horizontal StabilizerRear Spar Upper Chord atSide-of-BodyUpper chord between terminal fitting fork (Lead crack abovethe bolt hole)332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-10B Horizontal StabilizerRear Spar Upper Chord atSide-of-BodyUpper Chord Between Terminal Fitting Fork (Lead crack belowbolt hole, Outboard 3 bolt hole locations)332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-10C Horizontal Stabilizer Rear Spar Upper Chord atSide-of-BodyUpper Chord Between Terminal Fitting Fork (Lead crack belowbolt hole, Inboard Bolt Location)332/342333/343ALL 56000 Cycles<2> <3> <4>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLICTHRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7355-10-04-11A Horizontal Stabilizer Rear Spar UpperChord Stab Sta 67.78 to Stab Sta 203.10 332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-11B Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 203.10 to Stab Sta 258.28. Skin Flanges. 332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-11C Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 203.10 to Stab Sta 258.28. Web Flange at rib andstiffener locations332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-11D Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 203.10 to Stab Sta 258.28. Web Flange between ribsand stiffeners332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-12A Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Tip. Forward Flange of the chord 332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-12B Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Tip. Aft Flange of the chord332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-13A Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Stab Sta 310.54. Web Flange at Rib andStiffener Locations332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-13B Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 258.28 to Stab Sta 310.54. Web Flange between Riband Stiffener Locations332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-13C Horizontal Stabilizer Rear Spar Upper Chord Stab Sta 310.54 to Tip. Web flange both at and betweenStiffeners/Ribs332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-20 Horizontal Stabilizer Rear SparWebStab Sta 83.5 to Stab Sta 184.7332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-21 Horizontal StabilizerRear Spar WebStab Sta 184.7 to Stab Sta 285.9332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-22 Horizontal StabilizerRear Spar WebStab Sta 285.9 to Stab Sta 310.5332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-04-23 Horizontal Stabilizer RearSpar WebStab Sta 310.5 to Outboard Tip; Locations between stiffeners 332/342333/343ALL 56000 Cycles<2> <3> <4>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-74737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA55-10-04-24 Horizontal Stabilizer RearSpar Web Stab Sta 310.5 to OutboardTip; At stiffener locations. 332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-05-1 Horizontal Stabilizer Rear Spar Upper andFailsafe Chord LugsAt the Side of Body 332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-05-2A Horizontal Stabilizer Rear Spar Upper ChordTerminal FittingSide-of-Body Terminal Fitting at the Inboard 3 Attach BoltLocations332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-05-2B Horizontal Stabilizer Rear Spar Upper ChordTerminal FittingSide-of-Body Terminal Fitting at the Outboard Attach BoltLocation332/342333/343ALL 56000 Cycles<3> <4>55-10-05-3 Horizontal Stabilizer Rear SparTerminal Fitting Side-of-Body Pins 332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-05-4 Horizontal StabilizerRear Spar Upper ChordTerminal FittingAt Terminal Fitting (common to Side of Body Rib Tension BoltHole)332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-05-5 Horizontal StabilizerRear Spar Lower Chord At the Side-of-Body (common to the end rib tension bolt hole) 332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-06-1 Horizontal StabilizerFront Spar Upper Chord Side-of-Body to Stab Sta 66.5331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-2 Horizontal Stabilizer FrontSpar Upper Chord Aft Flange, Stab Sta 66.5 to Stab Tip331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-3 Horizontal StabilizerFront Spar Upper Chord Forward Flange,Stab Sta 66.5 to Stab Tip331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-4A Horizontal Stabilizer Front Spar Upper Chord Web Flange, Stab Sta66.5 to Stab Sta 175.5 and Stab Sta258.28 to Stab Tip331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-4B Horizontal Stabilizer Front Spar Upper Chord Web Flange, Stab Sta 175.5 to Stab Sta 258.28331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-6A Horizontal Stabilizer Front Spar Lower Chord Forward flange, Stab Sta 66.50 to Stab Sta 175.50331/341332/342ALL 56000 Cycles<3> <4>55-10-06-6B Horizontal Stabilizer Front Spar Lower Chord Aft flange, Stab Sta 66.50 to Stab Sta 175.50331/341332/342ALL 56000 Cycles<2> <3> <4>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7555-10-06-7A Horizontal Stabilizer Front Spar Lower Chord Forward Flange, Stab Sta 175.50 to Stab Sta 258.28 331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-7B Horizontal Stabilizer Front Spar Lower Chord Aft Flange, Stab Sta 175.50to Stab Sta 258.28 331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-8A Horizontal Stabilizer Front Spar Lower Chord Forward Flange, Stab Sta 258.28 to Stab BL 281.81 (Tip) 331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-8B Horizontal Stabilizer Front Spar Lower Chord AftFlange, Stab Sta 258.28 to Stab BL 281.81 (Tip)331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-W1 Horizontal Stabilizer Front Spar WebStab Sta66.5 to Stab Sta 111.1331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-WS Horizontal Stabilizer Front SparWebWeb Splice at Stab Sta 111.1331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-W2 Horizontal StabilizerFront Spar WebStab Sta 111.1 to Stab Sta 175.5331/341332/342ALL 56000 Cycles<3> <4>55-10-06-W3 Horizontal StabilizerFront Spar WebStab Sta 175.5 to Stab Sta 258.28331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-06-W4 Horizontal Stabilizer Front Spar WebStab Sta 258.28 to Stab Tip331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-07-2 Horizontal StabilizerFront Spar Upper Chord Side of Body at the Front Spar Upper Chord331/341332/342ALL 56000 Cycles<3> <4>55-10-07-3 Horizontal Stabilizer Front Spar TerminalFittingSide-of-Body Bolts331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-07-4 Horizontal Stabilizer Front Spar Lower Chord Lower chord at end rib tension fitting installation bolt hole 331/341332/342ALL 56000 Cycles<2> <3> <4>55-10-08-1 Horizontal Stabilizer Elevator Hinge Ribs Hinge Plates at Elevator Sta 121 and 176333/343334/344ALL 56000 Cycles<2>55-10-08-2 Horizontal Stabilizer Elevator Hinge Ribs Hinge Plate at Elevator Station 213 and Sta 250333/343334/344ALL 56000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-76737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA55-10-08-3 Horizontal StabilizerTrailing Edge Hinge PlateLower Forward LugHinge Plate at ESTA 265 333/343334/344ALL 56000 Cycles<2>55-10-08-4 Horizontal Stabilizer Elevator Hinge Ribs Hinge Plate at Elevator Station 66333/343334/344ALL 56000 Cycles<2>55-10-08-5A Horizontal Stabilizer Elevator Hinge RibsTrailing Edge ClevisESTA 121 and 176333/343334/344ALL –L/N 1 to 21536000 Cycles<2>55-10-08-5B Horizontal Stabilizer Elevator Hinge RibsTrailing Edge ClevisESTA 121 and 176333/343334/344ALL –L/N 216 and on56000 Cycles<2>55-10-08-6 Horizontal Stabilizer ElevatorHinge Ribs Elevator Station 66333/343334/344ALL 56000 Cycles<2>55-10-08-7 Horizontal Stabilizer Elevator Hinge Ribs Elevator Station 213 and 250333/343334/344ALL 56000 Cycles<2>55-10-08-8 Horizontal Stabilizer ElevatorHinge Ribs Elevator Station 265333/343334/344ALL 56000 Cycles<2>55-10-08-9 Horizontal StabilizerTrailing Edge ElevatorHinge RibElevator Hinge Rib to Rear Spar Attachment at ElevatorStations 66 and 121333/343334/344ALL 56000 Cycles<2>55-10-8-10 Horizontal Stabilizer, Trailing Edge Hinge Ribto Rear Spar AttachmentESTA 176333/343334/344ALL 56000 Cycles<2>55-10-8-11 Horizontal Stabilizer Elevator Hinge Ribs Hinge Rib to Rear Spar Attachment,Elevator Stations 213, 250and 265333/343334/344ALL 56000 Cycles<2>55-10-8-13 Horizontal Stabilizer Elevator Hinge Ribs Hinge RibLower Chord and Upper Chord, Elevator Stations 66and 121333/343334/344ALL 56000 Cycles<2>55-10-8-14 Horizontal Stabilizer Elevator Hinge Ribs Elevator Hinge Rib Lower Chord and Upper Chord, ElevatorStation 176333/343334/344ALL 56000 Cycles<2>55-10-09-1 Horizontal Stabilizer UpperInspar Skin Side of Body to Stabilizer Sta 157.1332/342 ALL 56000 Cycles<2> <3> <4>55-10-10-1 Horizontal StabilizerLower Inspar Skin Side of Body to Tip332/342 ALL 56000 Cycles<3> <4>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7755-10-11-1 Horizontal StabilizerCenter Section Front SparUpper ChordSide of Body Clevis Lugs 313/314 ALL 56000 Cycles<2> <3> <4>55-10-12-1 Horizontal StabilizerCenter Section Rear SparLugsLower Pivot Fitting Lugs 313/314332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-12-2 Horizontal StabilizerCenter Section Rear SparUpper ChordSide of Body Lugs 313/314332/342333/343ALL 56000 Cycles<2> <3> <4>55-10-13-2 Horizontal StabilizerCenter Section Front SparUpper ChordThrust Beam to Spar Joint313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-1 Horizontal StabilizerCenter Section Primaryand Thrust BeamsUpper Primary Beam at Front and Rear Spar Joint313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-2 Horizontal StabilizerCenter Section Primaryand Thrust BeamsUpper Primary Beam at Front and Rear Spar Joint Platesand Angles313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-3 Horizontal StabilizerCenter Section Primaryand Thrust BeamsPrimary Beam Upper Chord at the Thrust Beam Joint313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-4 Horizontal Stabilizer Center SectionThrust BeamsBeam Chords at Front and Rear Spars313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-5 Horizontal Stabilizer Center SectionThrust BeamsFront and Rear Spar to Beam Splice Members313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-6 Horizontal Stabilizer Center SectionThrust BeamsChords at Thrust Beam Intersection Joint313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-7 Horizontal StabilizerCenter Section ThrustBeam IntersectionSplice Plates313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-8 Horizontal Stabilizer Center SectionThrust BeamsUpper Chord at Primary Beam Joint313/314 ALL 56000 Cycles<2> <3> <4>55-10-14-9 Horizontal StabilizerCenter Section PrimaryBeam Chord to Web AttachmentUpper Chord Sta 1216 to 1242313/314 ALL 56000 Cycles<2> <3> <4>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-78737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA55-20-05 Elevator Hinge FittingsAll Elevator Hinge Fittings334/344 ALL 56000 Cycles<2>55-20-06 Elevator Mast Arm AssemblyElevatorActuator Fitting Lug Face334/344 ALL 56000 Cycles<2>55-20-07 Elevator Horn Balance WeightSupport StructureElevator Station 260334/344 ALL 56000 Cycles55-20-08 Elevator Tab MastFittingBase of Clevis Leg, Attach Flanges and LugsNote: Applicable to -600/-700/-700C/-700IGW/-800L/N 1 to 1174 which have not incorporated Service Bulletin737-55A1080. AD 2003-03-22 mandates Service Bulletin737-55A1080 prior to 18000 Cycles.334/344 Note 18000 Cycles<2>55-20-08-1 183A8700 Hinge/Mast Arm FittingUpper FlangeFastener Hole 2 and 3334/344 -900 –L/N 683to 117456000 Cycles<2>55-20-08-2 183A8700 Hinge/Mast Arm FittingUpper FlangeFastener Hole 2 and 3Note: Applicable to L/N 596 and ALL 1175 and on, andL/N 1-1174 that have Incorporated SB 737-55A1080 orSB 737-55-1081.334/344 Note 56000 Cycles<2>55-20-09 Elevator Tab Hinge Fittings 183A4211Lug AssemblyBolts Between the Lug Assembly and the Elevator Rear SparFitting, Hinges 1 through 4Note: Applicable to -600/-700/-700C/-700IGW/-800L/N 1 to 1174 which have not incorporated Service Bulletin737-55A1080. AD 2003-03-22 mandates Service Bulletin737-55A1080 prior to 18000 Cycles.334/344 Note 18000 Cycles<2>55-20-09-1 183A8300 Bridge Fitting Upper/Lower Flange Upper/Lower Flange Joints – Hinges 2 and 2.5334/344 -900 –L/N 683to 117456000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7955-20-09-2 183A8300 Bridge Fitting Upper/Lower Flange Upper/Lower Flange Joints – Hinges 3 through 6Note: Applicable to L/N 596 and ALL 1175 and on, andL/N 1-1174 that have Incorporated SB 737-55A1080 orSB 737-55-1081.334/344 Note 56000 Cycles<2>55-20-12 183A1400 – Bracket Assy – Tab ControlMechanism, ElevatorLug Faces 334/344 -900 –L/N 683to 117456000 Cycles<2>55-20-12-1 183A1400 – Bracket Assy – Tab ControlMechanism, ElevatorLug FacesNote: Applicable to L/N 596 and ALL 1175 and on, andL/N 1-1174 that have incorporated SB 737-55A1080 orSB 737-55-1081.334/344 Note 56000 Cycles<2>55-30-03-2 Vertical Fin – Rear SparPrimary Chord from Fin Sta 73.4 to Tip323/324 -600/-700-800-900/-900ER56000 Cycles<2>55-30-03-2a Vertical Fin – Rear SparPrimaryChord Fin Sta 80 to the Fin Tip323/324 -700C-700IGW56000 Cycles<2>55-30-05-1<1>Vertical Fin – Closure RibPrimary Chord @ Forward End Fastener Location Common toRear Spar Terminal Fitting323/324 ALL 56000 Cycles55-30-05-2 Vertical Fin – Closure RibPrimary Chord at Front Spar323 -700C-700IGW56000 Cycles<2>55-30-06-1 Rudder Hinge RibsHinge Fitting Lugs at Rib Attachment Hinge #1, #2, #3, #4, #5,#6, #7, #7A and #8324ALL 56000 Cycles55-30-06-2<1>Rudder Hinge RibsHinge Ribs 1 thru 7A at Rear Spar Attachment324ALL 56000 Cycles55-40-05 Rudder Hinge FittingsAll Rudder Hinge Fittings325ALL 56000 Cycles<2>55-40-06 Rudder Actuator FittingsRudderStations 60.85 and 70.65325ALL 56000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-80737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA55-40-07 737NG Rudder Balance ArmDoubler Common to Failsafe Strap and Front Spar Chord325ALL 56000 Cycles57-10-01 Wing Center Section Upper Panel Typical andVent StringersStringers 1-13 and 15-21 from LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-1<2>57-10-02 Wing Center Section Upper Panel SpliceStringerStringer 14, LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-1<2>57-10-03 Wing Center Section Upper PanelFront SparUpper Chord, LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-1<2>57-10-04 Wing Center Section Upper PanelRear SparUpper Chord, LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-1<2>57-10-05-1 Double Plus Chord at Stub BeamStubBeam Interface atBS 639195/196 ALL 56000 cycles<2>57-10-05-2 Double Plus Chord at Stringer18A Interface Aft End of Upper Vert. Flange Radius at Vert. Flange/Horiz.Flange195/196 ALL 56000 cycles<2>57-10-05-3a Double Plus Chord Vert Flange at Stringer 18AInterfaceVertical Flange Between BS 639 and BS 663. Top of wing,aft of over wing exits195/196 All except900ER56000 cycles<2>57-10-05-3b Double Plus Chord Upper Vert Flange atBody Stringer 18A InterfaceVertical Flange Between BS 639 and BS 663. Top of wing,aft of over wing exits195/196 900ER56000 cycles<2>57-10-05-4 Double Plus Chord, Upper Horizontal Flange Front Spar to Rear Spar135/136195/196ALLFLS,Figure 9-2<2>57-10-05-5 Double Plus Chord,Upper Horizontal Flange atStub BeamsBS 559, 578, 597, 616, 639135/136 ALLFLS,Figure 9-2<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8157-10-06 Wing Center Section Upper PanelUpper Skin atFloor Beam Attachments, BL 0, BL 25, BL 45from Front Spar To Rear Spar131/132135/136ALLFLS,Figure 9-2<2>57-10-07-1 Wing Center Section Lower Panel TypicalStringersStringers 1-4 and 6-8 from LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-1<2>57-10-07-2 Wing Center Section Lower Panel TypicalStringersStringers 10-14, LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-1<2>57-10-07/08 Wing Center Section Lower Panel Skin Front Sparto Rear Spar, Side-of-Body to Side-of-Body131/132 ALLFLS,Figure 9-2<2>57-10-08 Wing Center Section Lower PanelSplice Stringers 5 and 9, LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-2<2>57-10-09 Wing Center Section Lower PanelRear Spar Chord, LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-2<2>57-10-10 Wing Center Section Lower PanelFront Spar Lower Chord, LBL 67.0 to RBL 67.0131/132 ALLFLS,Figure 9-1<2>57-10-11-1 Side-of-Body Splice, Lower SurfaceTee-Chord, Rear Spar to Front Spar, BBL 70.85192131/132531/631ALLFLS,Figure 9-2<2>57-10-11-2 Side-of-Body Splice, Lower SurfaceRear Sparto Front Spar, BBL 70.85, (Non-Hidden)192ALLFLS,Figure 9-2<2>57-10-11-3 Side-of-Body Splice, Lower SurfaceRear Spar to Front Spar, BBL 70.85, (Hidden)192ALLFLS,Figure 9-2<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-82737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA57-10-12 Wing Center Section Lower PanelLower Skin atKeel Beam Attach (Front Spar to Rear Spar) 192131/132ALLFLS,Figure 9-2<2>57-10-13 Wing Center Section Lower PanelLower Skin at Drain Installation between Stringer 7 andStringer 8 at LBBL 3.5192131/132ALLFLS,Figure 9-1<2>57-10-15 Wing Center Section Lower PanelLower Skinat Lower Beam Attachment(Front Spar to RearSpar)192131/132ALLFLS,Figure 9-2<2>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 Tank131/132133/134ALLFLS,Figure 9-1<2>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 Tank131/132133/134ALLFLS,Figure 9-1<2>57-10-18 Wing Center Section Rear Spar Keel BeamStiffenersLBL 6.2 and RBL 6.2131/132133/134ALL 56000 cycles<2>57-10-20 Side of Body SpliceUpper and Lower Rear SparBBL 70.85131/132531/631ALLFLS,Figure 9-2<2>57-10-21 Side of Body SpliceUpper and Lower Front SparBBL 70.85131/132531/631ALLFLS,Figure 9-2<2>57-10-23-1 Wing Center SectionFloor Beam Upper ChordBL 0 and BL 25 Floor Beams from BS 655 to BS 675, BL 0Floor Beam from BS 716 to BS 727B, and BL 45 Floor Beamfrom BS 685 to BS 716135/136137/138ALL 56000 cycles<2>57-10-23-2 Wing Center SectionFloor Beam Upper ChordBL 0, BL 25 and BL 45 Floor Beams from BS 569 to 655 andBL 25 Floor Beam from BS 685 to BS 727A135/136137/138ALL 56000 cycles57-10-23-3 Wing Center Section Floor Beam Lower ChordOver Pressure DeckBL 0, BL 25, and BL 45 Floor Beamsfrom BS 664 to BS 727B 137/138 ALL 56000 cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8357-10-23-4 Wing Center Section Floor Beam Lower Chord BL 0, BL 25 and BL 45 Floor Beams between BS 574 andBS 664135/136 ALL 56000 cycles<2>57-10-23-5 Wing Center Section Floor Beam Lower Chord BL 0, BL 25 and BL 45 Floor Beams between BS 540 andBS 574135/136 ALL 56000 cycles<2>57-10-25 Side of Body Rib Typical Web-to-Stiffener Details 131/132531/631ALL FLS,Figure 9-157-20-01-1 Lower Wing Panel, Typical Stringers Stringers2-4 and 10-13 from Rib 1 to 10; Non-hidden FairingAreas531/631532/632ALL FLS,Figure 9-1<2>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 Chord531/631532/632ALL FLS,Figure 9-1<2>57-20-01-3 Lower Wing Panel, Typical Stringers Stringers1-4 and 10-14 at Ribs 5 and 8. Locations hidden byseal pans and sealant.531/631532/632ALL FLS,Figure 9-1<2>57-20-01/57-20-02/57-20-03/57-20-04/57-20-05/57-20-08-1Lower Wing Panel Skin; Under the Flap TrackFairings and Nacelle FairingsSkin panel at Rub Strip locations, Rib 5 to 8, Rib 9 to 11 andRib 13 to 15531/631532/632ALL FLS,Figure 9-2<2>57-20-01/57-20-02/57-20-03/57-20-04/57-20-05/57-20-08-2Lower Wing Panel Skin Rib 1to 14, Externally Visible Areas, Front Spar to Rear Spar 531/631532/632ALL FLS,Figure 9-2TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-84737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA57-20-01/57-20-02/57-20-03/57-20-04/57-20-05/57-20-08-3Lower Wing Panel Skin Rib 1 to 27, Front Spar to Rear Spar, All Fairing Locationswhere the skin is not covered by Rub Strips or Fittings531/631532/632533/633534/634ALL FLS,Figure 9-257-20-01/57-20-02/57-20-03/57-20-04/57-20-05/57-20-08-4Lower Wing Panel Skin Rib 14-27, Externally Visible Areas, Front Spar to Rear Spar 532/632533/633534/634ALL FLS,Figure 9-257-20-02-1 Lower Wing Panel, Rail Stringers Stringer6 and 8 from Rib 1 to 19; Non-hidden Faired and NonFaired531/631532/632ALL FLS,Figure 9-1<2>57-20-02-2 Lower Wing Panel, Rail Stringers Stringer6 and 8 at Rib 5 and 8; Hidden under seal pans andsealant531/631532/632ALL FLS,Figure 9-1<2>57-20-02-3 Lower Wing Panel, Rail Stringers Stringer 8,between Rib 6 and 7, Hidden by Nacelle SupportStrut Attach Fitting532/632 ALL FLS,Figure 9-1<2>57-20-02-4 Lower Wing Panel, Rail Stringers Stringer6 and 8: From Rib 19 to 25, Non-Hidden 532/632533/633ALL FLS,Figure 9-1<2>57-20-02-5 Lower Wing Panel, Rail Stringers Stringer6 and 8 at Rib 22, Hidden by flange of Rib 22, shimsand sealant532/632533/633ALL FLS,Figure 9-1<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8557-20-03-1 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 1 to 10, Non-Hidden, without fairing 531/631532/632ALL FLS,Figure 9-2<2>57-20-03-2 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 1 to 10, Non-Hidden, under fairing 531/631532/632ALL FLS,Figure 9-2<2>57-20-03-3 Lower Wing Panel, Splice Stringers Stringers 5 and 9 at Rib 5 and 8, Hidden by seal pans andsealant531/631532/632ALL FLS,Figure 9-2<2>57-20-03-4 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 10 to 19, Except Areas ExternallyCovered by Rub Strips532/632 ALL FLS,Figure 9-2<2>57-20-03-5 Lower Wing Panel, Splice Stringers Stringers 5 and 9 from Rib 10 to 19, Areas externally coveredby Rub Strips532/632 ALL FLS,Figure 9-2<2>57-20-03-6 Lower Wing Panel, Splice Stringers Stringers 5 and 9, From Rib 1 to 10, Areas Externally Coveredby Fairing Rub Strips531/631532/632ALL FLS,Figure 9-2<2>57-20-03/57-20-15Splice 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 ALL FLS,Figure 9-2<2>57-20-04-1 Front Spar Lower Chord(Skin Flange Inspections)Hidden: Rib 1-6, Rib 19 - 22Non-Hidden: Rib 1-5, Rib 19-22531/631532/632ALL FLS,Figure 9-2<2>57-20-04-2 Front Spar Lower Chord(Skin Flange Inspections)Rib 5 to 7 Non-Hidden 532/632 ALL FLS,Figure 9-2<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-86737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA57-20-04-3 Front Spar Lower Chord(Web Flange Inspections)Rib 1 to 19 and Rib 22 to 25 hidden by stiffeners, rib posts orfittings531/631532/632533/633534/634ALL FLS,Figure 9-2<2>57-20-04-4 Front Spar Lower Chord (Skin FlangeInspections)Hidden: Rib 6-19, Rib 22-25Non-Hidden: Rib 7-19, Rib 22-25532/632533/633534/634ALL FLS,Figure 9-2<2>57-20-04-5 Front Spar Lower Chord (Web FlangeInspections)Rib 1 to 19 Non-Hidden 531/631532/632ALL FLS,Figure 9-2<2>57-20-04-6 Front Spar Lower Chord(Web Flange Inspections)Rib 19 to Rib 22 Non-Hidden532/632 ALLFLS,Figure 9-2<2>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 ALLFLS,Figure 9-2<2>57-20-04-8 Front Spar Lower Chord(Web Flange Inspections)Rib 22 to Rib 25 Non-Hidden533/633534/634ALLFLS,Figure 9-2<2>57-20-04-9 Front Spar Lower ChordAt R7/R8 Nacelle Fitting Attachment532/632 ALLFLS,Figure 9-2<2>57-20-04-10 Front Spar Lower Chord, (Skin and WebFlange Inspections)Rib 25 to Rib 27, Dry Bay534/634 ALLFLS,Figure 9-2<2>57-20-04/57-20-05/57-20-16Spar 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 ALLFLS,Figure 9-2<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8757-20-04/57-20-05/57-20-16/57-20-17Spar Chords at Winglet Attach Fittings Winglet Attach Fittings at Rib 27534/634 ALLFLS,Figure 9-1<2>57-20-05-1 Rear Spar Lower Chord(Skin Flange Inspections)Rib 1 to 7 Non-Hidden531/631532/632ALLFLS,Figure 9-2<2>57-20-05-2 Rear Spar Lower Chord(Web Flange Inspections)Rib 1 to 14 Non-Hidden531/631532/632ALLFLS,Figure 9-2<2>57-20-05-3 Rear Spar Lower Chord(Web Flange Inspections)Rib 1 to 25 Hidden by stiffeners, rib posts or fittings.531/631532/632533/633534/634ALLFLS,Figure 9-2<2>57-20-05-4 Rear Spar Lower Chord(Skin Flange Inspections)Rib 7 to 14 Non-Hidden532/632 ALLFLS,Figure 9-2<2>57-20-05-5 Rear Spar Lower Chord (Skin FlangeInspections)Rib 1 to 22 Hidden by stiffeners and Rib 1 to 25 Hidden by ribposts or fittings.531/631532/632533/633534/634ALLFLS,Figure 9-2<2>57-20-05-6 Rear Spar Lower Chord (Skin FlangeInspections)Rib 14 to 22 Non-Hidden532/632 ALLFLS,Figure 9-2<2>57-20-05-7 Rear Spar Lower Chord (Web FlangeInspections)Rib 14 to Rib 22 Non-Hidden532/632 ALLFLS,Figure 9-2<2>57-20-05-8 Rear Spar Lower Chord(Skin and Web Flange Inspections)Rib 22 to Rib 25, Non-Hidden533/633534/634ALLFLS,Figure 9-1<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-88737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA57-20-05-9 Rear Spar Lower Chord(Skin Flange Inspections)Rib 22 to Rib 25, Partially Hidden by Stiffener 533/633534/634ALL FLS,Figure 9-1<2>57-20-05-10 Rear Spar Lower Chord(Skin and Web Flange Inspections)Rib 25 to Rib 27, Dry Bay 534/634 ALL FLS,Figure 9-2<2>57-20-06/07-1 Lower Skin Panel at Main Landing GearOutboard Support FittingsWSTA 180, 190, 228.25 and 253531/631532/632550/650560/660All except900ER56000 cycles<2>57-20-06/07-2 Lower Skin Panel at Main Landing GearOutboard Support FittingsWSTA 180, 190, 228.25 and 253531/631532/632550/650560/660900ER 56000 cycles<2>57-20-09 Skin at Nacelle Support Fitting Attachments Lower Skin at R2, R3 and R4 Nacelle Fitting Attachments 532/632 ALLFLS,Figure 9-2<2>57-20-10 Skin at Shear Tied Rib AttachmentsRib 14532/632 ALLFLS,Figure 9-1<2>57-20-12 Lower Wing Panel Under Flap Track Fittings Lower wing skin under forward and aft fittings at Rib 10 andRib 14532/632 ALLFLS,Figure 9-2<2>57-20-13-1 Upper Wing Panel Typical StringersTypical Stringers at Rib 5. Stringers hidden under seal pansand sealant.531/631532/632ALLFLS,Figure 9-157-20-13-2 Upper Wing Panel Typical StringersStringers 1-9and 15-21, Rib 1-21 and Rib 22 to Rib 25.531/631532/632533/633ALLFLS,Figure 9-1<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8957-20-13/57-20-14/57-20-15/57-20-16/57-20-17-1Upper Wing Panel at Side-of-Body Double PlusChordSkin-to-Plus Chord Attachments at BBL 70.85 Except locationscovered by 57-20-13/14/15/16/17-2131/132531/631ALLFLS,Figure 9-2<2>57-20-1357-20-1457-20-1557-20-1657-20-17-2Upper Wing Panel at Side-of-Body Double PlusChordSkin-to-Plus Chord Attachmentsat BBL 70.85 Splice Stringer14131/132531/631ALLFLS,Figure 9-2<2>57-20-15 Upper Wing Panel Splice StringerStringer14, Rib 12 to Rib 21. Locations adjacent tospar chords.532/632 ALLFLS,Figure 9-1<2>57-20-17-1 Rear Spar Upper Chord(Skin Flange Inspections)Rib 1 to 13 Non-Hidden531/631532/632ALLFLS,Figure 9-2<2>57-20-17-2 Rear Spar Upper Chord(Skin Flange Inspections)Rib 1 to 13 Hidden by stiffeners, rib posts or fittings.531/631532/632ALLFLS,Figure 9-2<2>57-20-17-3 Rear Spar Upper Chord(Web Flange Inspections)Rib 1 to 13 Non-Hidden531/631532/632ALLFLS,Figure 9-2<2>57-20-17-4 Rear Spar Upper Chord(Web Flange Inspections)Rib 1 to 13 Hidden by stiffeners, rib posts or fittings.531/631532/632ALLFLS,Figure 9-2<2>57-20-19 Wing Upper Skin Tab at R1 Nacelle Fitting Fasteners common to skin and R1Fitting.532/632ALL 56000 cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-90737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA57-20-22 Front Spar Web Crack – Typical Details Rib 1 to6 and Rib 7 to 27. Web at Stiffeners, Fittings, orBrackets531/631532/632533/633534/634ALL FLS,Figure 9-1<2>57-20-24-1 Outboard Wing Rear SparWeb Typical Details Rib 1-27531/631532/632ALLFLS,Figure 9-157-20-24-2 Outboard Wing Rear Spar Web Typical Details Rib1-27, (Hidden) Except Locations Covered by 57-20-24/25/26532/632533/633534/634ALLFLS,Figure 9-1<2>57-20-24/57-20-25/57-20-26Rear Spar Web at Trunnion Attachment,MLG and T.E. FittingsRib 1 to 27 Web at attachment to T.E. fittings551/651561/661571/671ALLFLS,Figure 9-1<2>57-20-29-1 Rib 25 Upper and Lower Horizontal Flange WBL 616.75533/633 -700, -800,-900ER withproductioninstalledwinglets perTable 9-1.FLS,Figure 9-2<2>57-20-29-2 Rib 27, Upper and Lower Rib Flange to SkinAttachmentsWBL 658.17, Front Spar toRear Spar534/634 -700, -800,-900ER withproductioninstalledwinglets perTable 9-1.FLS,Figure 9-1<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9157-20-29-3 Rib 27, Front and Rear Spar Tension Fittings WBL 658.17534/634 -700, -800,-900ER withproductioninstalledwinglets perTable 9-1.FLS,Figure 9-1<2>57-20-35/57-20-36/57-20-37/57-20-38/57-20-39Strut-to-Wing AttachmentsZones 431/441/434/444434/444431/441ALL 56000 cycles57-31-02-1 In-Spar Rib, Station 0, WingletTension BoltHoles common to Winglet Sta 0 Rib527/627 -800, -900ERwith productioninstalledwinglets perTable 9-1.FLS,Figure 9-1<2>57-31-02-2 In-Spar Rib, Sta 0, Bolt HolesLower Flange (FwdLower), Winglet common to Sta 0 Rib 527/627 -800, -900ERwith productioninstalledwinglets perTable 9-1.FLS,Figure 9-1<2>57-51-15 Inboard Actuator SupportFittingsMLG Support Structure / Fixed T.E.552/652 ALL 56000 Cycles57-51-16 Gear Beam Inboard SupportMLG Support Structure/Inboard Support Fitting551/651 ALL 56000 Cycles<2>57-53-01-1a No. 1 Support, Track AssyOutboard Flap,Outboard Track, WBL 357.7544/644 All except900ER56000 Cycles57-53-01-1b No. 1 Support, Track AssyOutboard Flap,Outboard Track, WBL 357.7544/644 900ER 56000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-92737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA57-53-02 Support, Forward Fitting AssyForward SupportFitting, Flap Tracks 1, 2 and 3, WBL 357.7,254 and 164544/644543/643542/642ALL 56000 Cycles57-53-03-1a No. 2 Support, Track AssyOutboard Flap,Inboard Track, WBL 254.0543/643 All except900ER56000 Cycles57-53-03-1b No. 2 Support, Track AssyOutboard Flap,Inboard Track, WBL 254.0543/643 900ER 56000 Cycles<2>57-53-06-1a No. 3 Support, Track AssyInboard Flap, Outboard Track, WBL 164542/642 All except900ER56000 Cycles57-53-06-1b No. 3 Support, Track AssyInboard Flap,Outboard Track, WBL 164542/642 900ER 56000 Cycles<2>57-53-09 No. 4 Support, Aft Link PinsInboard Flap, Inboard Track Aft Link, WBL 64541/641 ALL 56000 Cycles<2>57-53-10-1a No. 4 Support, Track AssyInboard Flap, Inboard Track, WBL 64541/641 All except900ER56000 Cycles57-53-10-1b No. 4 Support, Track AssyInboard Flap,Inboard Track, WBL 64541/641 900ER 56000 Cycles<2>57-53-11 No. 4 Support, Forward Fitting AssyInboardFlap, Inboard Track, WBL 64, Forward FittingPrimary Lug541/641 ALL 56000 Cycles<2>57-53-12-1 Front Spar, Inboard Main FlapFront Spar Upper Chord, away from rib,ITEF MFSTA 73 to 167 553/653 ALL 56000 Cycles57-53-12-2 Front Spar, Inboard Main FlapFront SparUpper and Lower Chord, at rib, ITEF MFSTA 73to 167553/653 ALL 56000 Cycles<2>57-53-12-3 Front Spar cutout, Inboard Main FlapFront SparCutout / Fitting, ITEF MFSTA 155553/653 ALL 56000 Cycles57-53-13-1 Rear Spar, Inboard Main FlapRear Spar Chord, at fitting inboard and outboard cutout, ITEFMFSTA 85 and 143553/653 ALL 56000 Cycles57-53-13-2 Rear Spar, Inboard Main FlapRear Spar Chord, at inboard and outboard pushrod cutout,ITEF MFSTA 91 and 149553/653 ALL 56000 CyclesTABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9357-53-13-3 Rear Spar, Inboard Main FlapRearSpar Upper Chord, away from rib, ITEF MFSTA 73 to 167 553/653 ALL 56000 Cycles57-53-13-4 Rear Spar, Inboard Main FlapRear Spar Upper Chord, at rib, ITEF MFSTA 73 to 167553/653 ALL 56000 Cycles<2>57-53-14 Upper Inspar Skin Panels, Inboard Flap Skin at Rear Spar chord, ITEF MFSTA 73 to 167553/653 ALL 56000 Cycles57-53-17 Inboard Torque Tube Rib, Inboard Flap Rib lower chord553/653 ALL 56000 Cycles<2>57-53-20 Torque Tube, Inboard FlapTorque Tube553/653 ALL 56000 Cycles57-53-21 Rear Spar, Inboard Main FlapAft Flap Track Support Assy, ITEF MFSTA 85 and 143553/653 ALL 56000 Cycles<2>57-53-22 No. 3 Carriage Assy, Inboard FlapCarriage plate, fwd and aft lug553/653 ALL 56000 Cycles<2>57-53-23-1 No. 4 Carriage Assy, Inboard FlapCarriage plate, fwd and aft lug553/653 ALL 56000 Cycles<2>57-53-23-2 No. 4 Carriage Assy, Inboard FlapCarriage plate, Torque Tube Attachment Hoop553/653 ALL 56000 Cycles57-53-23-3 No. 4 Carriage Assy, Inboard FlapCarriage plate, Upper Rub Pad Hole553/653 ALL 56000 Cycles57-53-24-1 No. 1 Carriage Assy, Outboard FlapOutboardCarriage Roller Boss, WBL 357.7567/667 ALL 56000 Cycles<2>57-53-24-2 No. 1 Carriage Assy, Outboard FlapOutboard Carriage Aft Bridge Support, WBL 357.7567/667 ALL 56000 Cycles<2>57-53-25-1 No. 2 Carriage Assy, Outboard FlapInboard Carriage Roller Boss, WBL 254567/667 ALL 56000 Cycles<2>57-53-25-2 No. 2 Carriage Assy, Outboard FlapInboard Carriage Aft Bridge Support, WBL 254567/667 ALL 56000 Cycles<2>57-53-26-1 Front Spar, Outboard FlapSpar upper and lower chord at ribs (spar hidden),Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327567/667 ALL 56000 Cycles<2>TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-94737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA57-53-26-2 Front Spar, Outboard FlapSpar upper andlower chord between ribs (front spar visible),Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327567/667 ALL 56000 Cycles<2>57-53-27-1 Rear Spar, Outboard FlapAft Flap Track Cutouts #2 and #3567/667 ALL 56000 Cycles<2>57-53-27-2 Rear Spar, Outboard FlapRearSpar upper and lower chord at ribs,Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327567/667 ALL 56000 Cycles<2>57-53-27-3 Rear Spar, Outboard FlapRearSpar upper and lower chord between ribs,Lower Chord WBL 254 to 358Upper Chord WBL 280 to 327567/667 ALL 56000 Cycles<2>57-53-29 Lower Skin, Outboard FlapFront and RearSpar lower chord skin interface, WBL 254 toWBL 358567/667 ALL 56000 Cycles<2>57-53-31 Front Spar Spigot Fitting, Outboard Flap Fwd Spigot Fitting, WBL 254 and 358567/667 ALL 56000 Cycles<2>57-53-32 Rear Spar Spigot Fitting, Outboard Flap Aft Spigot Fitting Assy, WBL 254 and 358567/667 ALL 56000 Cycles57-53-35 Aft Flap Track Support Ribs, Outboard Flap AftFlap Track Support Ribs #2 and #3 between WBL 254.0and 358.0.567/667 ALL 56000 Cycles57-70-01 Hinge / Actuator Fittings, Inboard Spoiler #6 Lugson the Hinge and Actuator fittings552/652 ALL 56000 Cycles<1> These PSEs require supplementalinspections 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 validated, published in the appropriatemanual, and accepted by the FAA.<3> The inspection threshold for the 737-700IGW and 737-700C horizontal stabilizer withproduction installed winglets is 10,000flight cycles or 20,000 flight hours,whichever occurs first. The published DTR Check Form for this PSEis not applicable to the 737-700IGW or the 737-700C with production installed winglets. ContactBoeing 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 or20,000 flight hours, whichever occurs first.This design change applies to all 737 minor models beginning atLine Number 3624. The published DTR Check Form for this PSE isnot applicable to airplanes witha redesigned horizontal stabilizer insparlower skin. Contact Boeing for the FAA-approved DTR Check Form when reaching this threshold.TABLE 9-2 AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSPSE #DTR CHECK FORM TITLELOCATIONZONE REFAIRPLANEAPPLIC THRESHOLDOCT 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-95TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE # DTR CHECK FORM TITLE LOCATIONZONEREFAIRPLANEAPPLIC THRESHOLD52-11-02 Main Entry Door See Table Entry and DTR Form for PSE 52-13-02-3737-700IGW737-800737-900ER52-13-02-3 Aft Entry DoorForward 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 Door737-700IGW737-800737-900ER28000 Cycles52-21-04 Automatic Overwing DoorLower Frame at stop/guide fitting737-700IGW737-800737-900ER28000 Cycles52-41-02-3 Forward Galley DoorSee Table Entry and DTR Form for PSE 52-13-02-3737-700IGW737-800737-900ER52-41-04-3 Aft Galley DoorSee Table Entry and DTR Form for PSE 52-13-02-3737-700IGW737-800737-900ER52-48-04-2 Electronic Equipment Access Door AluminumCasting OnlyBounded by LBL 5.70, RBL 14.12, frame STA 325.07 andSTA 349.13737-700IGW737-800737-900ER28000 Cycles53-10-02-1 Circumferential Skin Splice, STA 259.5 S-7L to S-14L,S-7R to S-14R both FWD and AFT Side of Joint737-700IGW737-800737-900ER28000 Cycles<1>53-10-03-1 Longitudinal Lap SpliceS-4L & S-4R, STA 259.5 to 360 Upper Fastener Row, UpperSkin. 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 1016737-700IGW737-800737-900ER28000 Cycles<1>53-10-03-2 Longitudinal Lap SpliceS-4L & S-4R, STA 259.5 to 360 Lower Fastener Row, Lower Skin737-700IGW737-800737-900ER28000 Cycles<1>DEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-96737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-10-03-3 Longitudinal Lap SpliceS-14L, STA 259.5to 294.5, 350 to 360, Upper Row, Upper Skin.S-14R, STA 259.5 to 277, 344 to 360, Upper Row, Upper Skin737-700IGW737-800737-900ER28000 Cycles<1>53-10-03-4 Longitudinal Lap SpliceS-14L, STA 259.5to 294.5, 350 to 360, Lower Row, Lower Skin.S-14R, STA 259.5 to 277, 344 to 360, Lower Row, Lower Skin737-700IGW737-800737-900ER28000 Cycles<1>53-10-03-5 Longitudinal Lap SpliceS-24L STA 259.5 to 334, & S-24R STA 259.5 to 360 UpperFastener Row, Upper Skin737-700IGW737-800737-900ER28000 Cycles<1>53-10-04-1 Cutout - Crew Cab WindowsAB Post737-700IGW737-800737-900ER28000 Cycles<1>53-10-04-2 Cutout - Crew Cab WindowsCD Post, Left and Right737-700IGW737-80028000 Cycles<1>53-10-04-2A Cutout - CrewCab WindowsSee Table Entry and DTR Form for PSE 53-10-04-2737-900ER 28000 Cycles<1>53-10-04-3 Cutout - Crew Cab WindowsEF Post, Left and Right737-700IGW737-800737-900ER28000 Cycles<1>53-10-04-4 Cutout - Crew Cab WindowsBD Sill Left and Right737-700IGW737-800737-900ER28000 Cycles<1>53-10-04-5 Cutout - Crew Cab WindowsPointD Fitting - Left and Right Side737-700IGW737-800737-900ER28000 Cycles<1>53-10-04-6 Cutout - Crew Cab WindowsX-750 Angle atB-D Sill Inner Chord Left and Right Sides ofthe Aircraft737-700IGW737-800737-900ER28000 Cycles<1>53-10-05-1 Crown Skin Panel - Fwd of STA 259.5 Longitudinal Splice at BL 0737-700IGW737-800737-900ER28000 Cycles<1>53-10-06-1 Section 41 Side Panel, Pan Door Cutout STA 216.2, WL 235.5737-900ER 28000 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9753-10-08-1 Crown Skin Panel STA 259.5 to 360 See Table Entry and DTR Form for PSE 53-30-01-2 737-700IGW737-800737-900ER<1>53-10-12-2 Cutout - Fwd Access Door, Aft Edge Frame,BS 219.8See Table Entry andDTR Form for PSE 53-10-23-1 737-700IGW737-800737-900ER53-10-13-1 Cutout - Electronic Equipment DoorCutoutBounded by Stations 323.7 & 351.2, and RBL 15.47 &LBL 6.74737-700IGW737-800737-900ER28000 Cycles<1>53-10-14-4 Cutout - FWD Entry Door FrameSTA 303.9 from S-11L to S-12L737-700IGW737-800737-900ER28000 Cycles<1>53-10-14-5 Cutout - FWD Entry Door FrameSTA 303.9 from S-7L to S-11L and S-12L to S-13L737-700IGW737-800737-900ER28000 Cycles<1>53-10-14-7 FWD Entry Door FWD Edge Frame Stops Stop Fittings at S-7 thru S-16737-700IGW737-800737-900ER28000 Cycles53-10-14-8 FWD Entry Door FWD Edge FrameStop Straps at S-7 thru S-14737-700IGW737-800737-900ER28000 Cycles<1>53-10-14-9 FWD Entry Door FWD Edge Frame Stops Stop Straps at S-15 and S-16737-700IGW737-800737-900ER28000 Cycles<1>53-10-14-10 FWD Entry Door Aft Edge Frame Stops S-15 and S-16 Tension Straps at STA 351.2 Frame Inner Chord737-700IGW737-800737-900ER28000 Cycles53-10-14-11 FWD Entry Door Aft Edge Frame Stops AftFrame Stops @ Inner Flange Holes @ Approx. STA 348.2(S-7 to S-14)737-700IGW737-800737-900ER28000 Cycles53-10-14-12 Forward Entry Door CutoutLower Edge ofCutout STA 303 to STA 350 around and underScuff Plates. Also:PSE 53-10-15 Forward Galley Door Cutout737-700IGW737-800737-900ER28000 Cycles<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-98737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-10-15 Forward Galley DoorCutout See Table Entry and DTRForm for PSE 53-10-14-12 737-700IGW737-800737-900ER<1>53-10-15-2 Forward Galley Door Surround Structure DoorStop Backup StructureForward Edge Frame at Stops #1, #2, #5, and #6 IntercostalTension Straps737-700IGW737-800737-900ER28000 Cycles<1>53-10-15-4 Cutout - FWD Galley Door STA 291.5 & STA 328.5, S-8R to S-14R 737-700IGW737-800737-900ER28000 Cycles<1>53-10-18-1 Bulkhead, STA 294.5Nose Wheel Well Aft Bulkhead WL 172 Beam at BL 17737-700IGW737-800737-900ER28000 Cycles<1>53-10-19-4 Nose Wheel Well Side and Top Panels Aft access Cutout forward Vertical Beam STA 260, WL 170 toWL 184737-700IGW737-800737-900ER28000 Cycles53-10-20-2 Nose Landing Gear Support FittingsDrag Brace Fittings STA 262, BL 16 WL 189.3737-700IGW737-800737-900ER28000 Cycles<1>53-10-20-3 Nose Landing Gear Trunnion Support Fitting Inboard and Outboard Fitting Segments BS 294.5, WL 156.1,BL 16737-700IGW737-800737-900ER28000 Cycles53-10-21-1 Air Stair Door CutoutUpper and Lower Sills STA 303.8 to STA 348 (Internal)737-700IGW737-800737-900ER28000 Cycles53-10-21-2 Air Stair Door CutoutUpper and Lower Sills STA 303.8 to STA 348 (External)737-700IGW737-800737-900ER28000 Cycles53-10-21-4 Airstair Door CutoutForward andAft Edge Frames STA 303.9 & 351.2 at LowerCorners737-700IGW737-800737-900ER28000 Cycles<1>53-10-23-1 Forward Nose Wheel Well CutoutForward Edge Frame - BS 224.8. Also:PSE 53-10-12-2 Fwd Access Door Aft Frame - BS 219.8737-700IGW737-800737-900ER28000 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9953-30-01-2 Crown Skin Panel, STA 360 to 540BS 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 Finas RequiredPSE 53-70-04-1 STA 887 to 1016 - Remove Dorsal Finas Required737-700IGW737-800737-900ER28000 Cycles<1>53-30-01-4 Crown Skin Panel, STA 360 to 540Antenna Cutouts at STA 385, STA 430, STA 500A737-700IGW737-800737-900ER28000 Cycles53-30-01-5 Satcom Aero-H Antenna InstallationSection 43 STA 500 S-6 to S-7737-700IGW737-80028000 Cycles53-30-02-1 Fuselage Side Skin PanelsBS 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 540Bilge Skin, S-24L to S-24RPSE 53-60-03-1 STA 727 to STA 887Bilge Skin, S-23L to S-23R737-700IGW737-800737-900ER28000 Cycles53-30-02-4 Fuselage Side Skin Panels Under the Wing-toBody FairingSTA 360 to STA 540. Also:PSE 53-60-02-4 STA 727 to STA 887737-700IGW737-800737-900ER28000 Cycles53-30-03-1 Fuselage Bilge Skin Panels, BS 360 to 540,S-24L to S-24RSee Table Entry andDTR Form for PSE 53-30-02-1737-700IGW737-800737-900ER53-30-03-5 Bilge Skin, STA 360 to STA 540VHF Antenna Hole Cutout. Also:PSE 53-60-03-6 STA 727 to 887737-700IGW737-800737-900ER28000 Cycles<1>53-30-04-1 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-10-03-1737-700IGW737-800737-900ER<1>53-30-04-2 Longitudinal Lap SpliceS-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 887737-700IGW737-800737-900ER28000 Cycles<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-100737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-30-04-3 Longitudinal Lap SpliceS-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 887737-700IGW737-800737-900ER28000 Cycles<1>53-30-04-4 Longitudinal Skin SpliceS-10L & S-10R,STA 360-540 Lower Fastener Row, Lower Skin.Also:PSE 53-60-04-4 STA 727 to 887737-700IGW737-800737-900ER28000 Cycles<1>53-30-04-5 Longitudinal Lap SpliceS-14L & S-14R, STA 360 to 540 Upper Fastener Row, UpperSkin. Also: PSE 53-60-04-5 STA 727 to 887737-700IGW737-800737-900ER28000 Cycles53-30-04-6 Longitudinal Lap SpliceS-14L & S-14R, STA 360 to 540 Lower Fastener Row, LowerSkin. Also: PSE 53-60-04-6 STA 727 to 887737-700IGW737-800737-900ER28000 Cycles<1>53-30-04-7 Longitudinal Lap SpliceS-24L & S-24R, STA 360 to 540 Except at Cargo Door Cutout.Upper Fastener Row. Upper (Inner) Skin737-700IGW737-800737-900ER28000 Cycles<1>53-30-04-8 Longitudinal Lap SpliceS-24L & S-24R, STA 360 to 540 Except at Cargo Door Cutout.Lower Fastener Row. Lower (Outer) Skin737-700IGW737-800737-900ER28000 Cycles<1>53-30-05-1 Window Belt STA 360 to 540 - Corners ofWindow FrameSee Table Entry andDTR Form for PSE 53-60-05-1737-700IGW737-800737-900ER53-30-05-2 Window Belt STA 360 to 540 - Window Frame See Table Entry and DTR Form for PSE 53-60-05-2737-700IGW737-800737-900ER53-30-05-3 Window Belt STA 360 to540 - SkinSee Table Entry and DTR Form for PSE 53-60-05-3737-700IGW737-800737-900ER53-30-07-1<2>BS 540 Circumferential SpliceLead Crack inSkin Splice Strap737-900ER 28000 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10153-30-08-1 Forward Cargo Door Surround Forward and AftEdge 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 andDTR Form for PSE 53-60-08-4737-700IGW737-800737-900ER<1>53-30-08-2 Forward Cargo Door Surround Forward and AftEdge Frames at STA 440 and 492.4.(Outer Chord at Door Stops Location and atFrame/Sill Intersections)See Table Entry andDTR Form for PSE 53-60-08-5737-700IGW737-800737-900ER<1>53-30-08-3 Forward Cargo Door Surround (Forward andAft Edge Frame Inner Chords Between S-18Rand S-26R).See Table Entry andDTR Form for PSE 53-60-08-1737-700IGW737-800737-900ER<1>53-30-08-4 Forward Cargo Door Surround Structure(Forward and Aft Edge Frame Inner ChordsBetween S-17R and S-18R)See Table Entry andDTR Form for PSE 53-60-08-2737-700IGW737-800737-900ER<1>53-30-08-5 Forward Cargo Door Surround Structure(Forward and Aft Edge Frame Inner Chords atS-18R)See Table Entry andDTR Form for PSE 53-60-08-3737-700IGW737-800737-900ER<1>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 DoorSkin Splices at BS 794.4and 847737-700IGW737-800737-900ER28000 Cycles<1>53-30-08-7 Forward Cargo Door Surround Structure(Forward and Aft Edge of Door STA 440 andSTA 492.4 S-18R to S-25R)See Table Entry andDTR Form for PSE 53-60-08-7737-700IGW737-800737-900ER<1>53-30-08-8 Forward Cargo Door Surround Structure(Forward and Aft Edge of Door STA 440 andSTA 492.4 S-18R to S-25R)See Table Entry andDTR Form for PSE 53-60-08-8737-700IGW737-800737-900ER<1>53-30-08-9 Forward Cargo DoorSurround Structure Skin and Bearstrap at Corners of CutoutSee Table Entry and DTRForm for PSE 53-60-08-9737-700IGW737-800737-900ER53-30-08-10 Forward Cargo Door Surround Structure Upper Sill Outer Chord. Also:PSE 53-60-08-10 Aft Cargo Door Upper Sill737-700IGW737-800737-900ER28000 Cycles<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-102737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-30-08-11 Forward Cargo Door SurroundStructure Upper Sill Inner Chord 737-700IGW737-800737-900ER28000 Cycles<1>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 MainSill STA 807 to 827737-700IGW737-800737-900ER28000 Cycles<1>53-30-09-1 Forward Cargo Door Stops (Forward and AftEdge of Forward Cargo Door)See Table Entry andDTR Form for PSE 53-60-09-1737-700IGW737-800737-900ER53-30-09-3 Forward Cargo Door Fittings and Stops at theForward and Aft Edge Frames (Backup Fittingsand Intercostals)See Table Entry andDTR Form for PSE 53-60-09-3737-700IGW737-800737-900ER<1>53-30-11-1 Wing to Body Lower Drag AngleBS 518 to BS 555 above S-24737-700IGW737-800737-900ER28000 Cycles<1>53-30-11-2 Wing to Body Upper Drag AngleNear BS 540, Between S-21 and S-22737-700IGW737-800737-900ER28000 Cycles<1>53-30-11-3 Wing to Body Upper Drag AngleNear BS 540, Between S-21 and S-22737-700IGW737-800737-900ER28000 Cycles<1>53-40-01-1 Crown Skin Panel STA540 to 727See Table Entry and DTR Form for PSE 53-30-01-2737-700IGW737-800737-900ER<1>53-40-02-2<2>Section 44 Side Panel, Circumferential Skin STA 540 toSTA 727, S-14 to S-17737-900ER 28000 Cycles53-40-03-1 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-10-03-1737-700IGW737-800737-900ER<1>53-40-03-2 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-30-04-2737-700IGW737-800737-900ER<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10353-40-03-3 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-30-04-3737-700IGW737-800737-900ER<1>53-40-04-1 Window Belt, STA 540 to 727Stringer 11 and Stringer 13737-700IGW737-800737-900ER28000 Cycles53-40-04-2 Window Belt, STA 540 to 727Between Windows S-11 to S-13737-700IGW737-800737-900ER28000 Cycles53-40-06-5<2>Circumferential Skin Splice, STA 727 Circumferential Skin Splice at BS 727737-900ER 28000 Cycles53-40-07-1<2>Stringer Splice STA 663Splice at Stringer 11737-700IGW737-800737-900ER28000 Cycles<1>53-40-07-2 Stringer Splice STA 663Splice at Stringer 11 and Stringer 13737-700IGW737-800737-900ER28000 Cycles53-40-08-1 Keel Beam Chords, Stiffeners, and Splice Keel Beam Side Panel Webs STA 540 to STA 663737-700IGW737-800737-900ER28000 Cycles53-40-10-1 Stiffener Attachment to Floor BeamSTA 727 LBL 45.5 & RBL 45.5 @ WL 202.6737-700IGW737-800737-900ER28000 Cycles<1>53-40-11-1 Stringer 18 Strap Side of BodySTA 717 to STA 727737-700IGW737-800737-900ER28000 Cycles<1>53-40-12-1 Stringer 18A Chord and LinksSTA 663 Link Lugs737-700IGW737-800737-900ER28000 Cycles<1>53-40-13-1 Pressure Deck Web and StiffenersSTA 663.75 to STA 727737-700IGW737-800737-900ER28000 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-104737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-40-14-1 Frame Splice @ STA 540Inner Chord between S-9 and S-10737-700IGW737-800737-900ER28000 Cycles<1>53-40-14-4 BS 540 BulkheadSkin at Outer Chord, S-9L to S-9R737-700IGW737-800737-900ER28000 Cycles53-40-14-5 BS 540 BulkheadPicklefork Fitting, S-17 and Below737-700IGW737-800737-900ER28000 Cycles53-40-15-1 BS 663 BulkheadOuter Chord Between S-8 and S-11737-700IGW737-800737-900ER28000 Cycles53-40-15-3 BS 663 BulkheadInner Chord between S-9 and S-17, LH & RH737-700IGW737-800737-900ER28000 Cycles<1>53-40-15-4 BS 663 BulkheadPicklefork Fitting, S-17 and Below737-700IGW737-800737-900ER28000 Cycles53-40-16-1A Aft Wheel Well Bulkhead STA 727Lower Chord, S-21 to S-27737-700IGW737-800737-900ER28000 Cycles<1>53-40-16-1B Aft Wheel Well Bulkhead STA 727Lower Chord, S-21 to S-27737-700IGW737-800737-900ER28000 Cycles<1>53-40-16-2 Wheel Well Aft BulkheadFrame Inner Chord at STA 727, WL 201737-700IGW737-80012700 Cycles53-40-16-2A Wheel Well Aft BulkheadFrame Inner Chord at STA 727, WL 201737-900ER 28000 Cycles53-40-16-3 Wheel Well Aft Bulkhead and Pressure Web,STA 727Lower Frame STA 727737-700IGW737-800737-900ER28000 Cycles53-40-16-5 Aft Wheel Well Bulkhead and Pressure Web,STA 727Frame STA 727, S-9L to S-9R737-700IGW737-800737-900ER28000 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10553-40-16-6 Aft Wheel Well Bulkhead Frame, STA 727 STA 727 between S-9 to S-10737-700IGW737-800737-900ER28000 Cycles<1>53-40-17-1 Side Strut Support Frame STA 706Frame Inner &Outer Chords and Fail-Safe Angle S-10 to S-13737-700IGW737-800737-900ER28000 Cycles<1>53-40-17-2 High Part of the Transition in the Frame SeeTable Entry andDTR Form for PSE 53-40-17-1737-700IGW737-800737-900ER<1>53-40-17-4 Crown Skin at Frame STA 706See Table Entry and DTR Form for PSE 53-30-01-2737-700IGW737-800737-900ER<1>53-40-18-1 Main Landing Gear Support Frame, STA 695 Inner Chord at Crease Beam STA 695737-900ER 28000 Cycles<1>53-40-18-2 Main Landing Gear Support Frame, STA 695 Stub Beam Upper Chord737-700IGW737-800737-900ER28000 Cycles<1>53-40-19-1 Main Landing Gear Support Frame, STA 716 Frame Inner Chord and Web at S-16737-700IGW737-800737-900ER28000 Cycles<1>53-40-19-2 Main Landing Gear Support Frame, STA 716 StubBeam Upper Chord at Crease Beam Chord Attachment737-700IGW737-800737-900ER28000 Cycles<1>53-40-19-3 Main Landing Gear Support Frame, STA 716 Stub Beam Web at Floor Clip Attachment737-700IGW737-800737-900ER28000 Cycles<1>53-40-19-3A Main Landing Gear Support Frame, STA 716 See Table Entry and DTR Formfor PSE 53-40-19-3737-700IGW737-800737-900ER<1>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 andDTR Form for PSE 53-40-21-1737-700IGW737-800737-900ERTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-106737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-40-21-1 Wheel Well Frame, STA 685Outer Chord Splice Angle, S-9 to S-10. Also:PSE 53-40-20-3, Framesat STA 559 (BBJ2)Frames at STA 559, STA 578, and STA 601 (BBJ)737-700IGW737-800737-900ER28000 Cycles53-40-21-2 Wheel Well Frame, STA 685Frame Inner Chord S-13 to S-15737-700IGW737-800737-900ER28000 Cycles53-40-21-3 Wheel Well Frame, STA 685Frame Inner Chord S-17 to S-14737-700IGW737-800737-900ER28000 Cycles<1>53-40-21-4 Wheel Well Frame, at STA 685Stub Beam Upper Chord737-700IGW737-800737-900ER28000 Cycles<1>53-40-22-2 Overwing Emergency Exit CutoutEdge Frame STA 616 Outer Chord, S-10 to S-13737-700IGW 28000 Cycles<1>53-40-22-3 Overwing Emergency Exit Cutout SkinAssembly & Frame Outer ChordEdge Frame 578 near Stringer S-11 to S-13737-800737-900ER28000 Cycles<1>53-40-22-4 Overwing EmergencyExit Cutout (Inspectionapplicable only to BBJ 1 Lower Sill Inner SpliceStrap STA 616 and STA 639).See Table Entry and DTR Form forPSE 53-40-22-13 - BBJ2737-700IGW<1>53-40-22-5 Overwing Emergency Exit CutoutUpper Edge and Both Upper Corners of Cutout from S-11 @STA 616 to S-11 @ STA 639737-700IGW 28000 Cycles<1>53-40-22-6 Overwing Emergency Exit Cutout - DoorCutouts CornersUpper Edge of Doors from S-11 @ STA 578 to S-11 @ STA 601and from S-11 @ STA 616 to S-11 @ STA 639737-800737-900ER28000 Cycles<1>53-40-22-7 Overwing Emergency Exit CutoutEdge Frame Outer Chord under stop backup fittings at S-11and S-12737-700IGW737-800737-900ER28000 Cycles<1>53-40-22-8A Overwing Emergency ExitCutoutBoth Lower Corners and Lower Edge of Cutout from S-14STA 616 to S-14 STA 639737-700IGW 28000 Cycles<1>53-40-22-9 Overwing Emergency Exit CutoutAll Four LowerCorners (intersection of lower sill and edge frames578, 601,616 and 639) + Skin Assy over the Lower Sills.737-800737-900ER28000 Cycles<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10753-40-22-10 Overwing Emergency Exit CutoutSkin and Frame Assy. Section @ STA 616 &S-13Covered Region: Edge Frame 616 from S-13 to S-15 and EdgeFrame 639 from S-10 to S-15737-700IGW 28000 Cycles<1>53-40-22-11 Overwing Emergency Exit CutoutSkin Assy and Frame Outer ChordDoor Edges at STA 578 S-13 toS-15 and at STA 601, 616, and639 S-10 to S-15737-800737-900ER28000 Cycles<1>53-40-22-12 Overwing Emergency ExitCutout Lower Aft Corner Frame 616 and 639 at Lower Sill.Also: Frames 578 and 601 for BBJ2 and BBJ3.737-700IGW737-800737-900ER27000 Cycles53-40-22-13 Overwing Emergency Exit CutoutLower Sill Inner Splice Strap atBS 578, 601, 616, and 639. Also:PSE 53-40-22-4 Frame 616 and639 on the BBJ(737-700IGW)737-800737-900ER26700 Cycles<1>53-40-23-1 Overwing Emergency Exit Door Stopsand FittingsDoor Stops attached to the Forward and Aft Door Edge Frames737-700IGW737-800737-900ER28000 Cycles53-40-23-2 Overwing Emergency Exit Door Stopsand FittingsDoor Stops Intercostals between STA 601 and 616737-800737-900ER28000 Cycles53-40-23-3 Overwing Emergency Exit Door Stopsand FittingsDoor Stops Backup Fitting Attachment to Window Frames at S-11and S-12 at BS 616 for (BBJ) or BS 578 (BBJ2)737-700IGW737-800737-900ER28000 Cycles<1>53-40-24-1 Pressure Deck Attachment to Rear SparExtensionBS 663737-700IGW737-800737-900ER28000 Cycles53-60-01-2 Crown Skin Panel STA727 to 887See Table Entry and DTR Form for PSE 53-30-01-2737-700IGW737-800737-900ER<1>53-60-01-4 Crown Skin Panel STA 727 to 887ADF Antenna Cutout STA 727 + 9, RBL 5SATCOM Antenna CutoutSTA 747, STR-1737-700IGW737-800737-900ER28000 Cycles53-60-01-5 SATCOM Antenna Installation(Canadian Marconi and Honeywell)Section 46: STA 767 between S-1 and S-2L737-700IGW737-80028000 Cycles<1>53-60-01-6 SATCOM Antenna Installation (all exceptthose covered by PSE 53-60-01-5)Section 46: STA 767 between S-1 and S-2L737-700IGW737-80028000 Cycles<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-108737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-60-02-1 Fuselage Side Skin Panels (BS 727 to BS 887,S-14 to S-23)See Table Entry andDTR Form for PSE 53-30-02-1 737-700IGW737-800737-900ER53-60-02-2 Fuselage Side Skin Panels (BS 727 to BS 887,S-14 to S-23)See Table Entry andDTR Form for PSE 53-30-02-1 737-700IGW737-800737-900ER53-60-02-3 Fuselage Side Skin Panels (BS 727 to BS 887,S-14 to S-23)See Table Entry andDTR Form for PSE 53-30-02-1 737-700IGW737-800737-900ER53-60-02-4 Fuselage Side Skin Panels Under the Wing-toBody FairingSee Table Entry andDTR Form for PSE 53-30-02-4 737-700IGW737-800737-900ER53-60-03-1 Fuselage Bilge Skin Panels (BS 727 to 887,S-23L to 23R)See Table Entry andDTR Form for PSE 53-30-02-1737-700IGW737-800737-900ER53-60-03-6 Fuselage Bilge Skin Panels (BS 727 to 887,VHF Antenna Hole Cutout).See Table Entry andDTR Form for PSE 53-30-03-5737-700IGW737-800737-900ER<1>53-60-04-1 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-10-03-1737-700IGW737-800737-900ER<1>53-60-04-2 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-30-04-2737-700IGW737-800737-900ER<1>53-60-04-3 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-30-04-3737-700IGW737-800737-900ER<1>53-60-04-4 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-30-04-4737-700IGW737-800737-900ER<1>53-60-04-5 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-30-04-5737-700IGW737-800737-900ERTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10953-60-04-6 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-30-04-6737-700IGW737-800737-900ER<1>53-60-04-7 Longitudinal Lap SpliceS-23L & S23R, STA 727 to 887 except at Cargo Door Cutout.Upper Fastener Row,Upper (Inner) Skin. Also: PSE 53-70-03-5STA 887 to 1016737-700IGW737-800737-900ER28000 Cycles<1>53-60-05-1 Window Belt STA 727 to 888Corners of Window Frame. Also:PSE 53-30-05-1 STA 360 to 540PSE 53-70-09-1 STA 888 to 927737-700IGW737-800737-900ER28000 Cycles53-60-05-2 Window Belt STA 727 to 888Window Frames. Also:PSE 53-30-05-2 STA 360 to 540PSE 53-70-09-2 STA 888 to 927737-700IGW737-800737-900ER28000 Cycles53-60-05-3 Window Belt STA 727 to 888Skin. Also:PSE 53-30-05-3 STA 360 to 540PSE 53-70-09-3 STA 888 to 927737-700IGW737-800737-900ER28000 Cycles53-60-08-1 Aft Cargo Door Surround StructureForward and Aft Edge Frame inner Chords betweenS-18R & S-26R. Also: PSE 53-30-08-3 Forward Cargo Door737-700IGW737-800737-900ER28000 Cycles<1>53-60-08-2 Aft Cargo Door Surround StructureForward and Aft Edge Frame Inner Chords betweenS-17R & S-18R. Also: PSE 53-30-08-4 Forward Cargo Door737-700IGW737-800737-900ER28000 Cycles<1>53-60-08-3 Aft Cargo Door Surround StructureForward and Aft Edge Frame Inner Chords at S-18R. Also:PSE 53-30-08-5 Forward Cargo Door737-700IGW737-800737-900ER28000 Cycles<1>53-60-08-4 Aft Cargo Door Surround Forward and AftEdge Frames at BS 794.37 and 847Outer Chord Between S-16R and S-26R (Except at Door Stopsand Sill Location). Also:PSE 53-30-08-1 Forward Cargo Door, STA 440 and STA 492.4,S-17R to S-26R737-700IGW737-800737-900ER28000 Cycles<1>53-60-08-5 Aft Cargo Door Surround Forward and AftEdge Frames at BS 794.37 and 847Outer Chord at Door Stops Location and at Frame/SillIntersections. Also:PSE 53-30-08-2 Forward CargoDoor, STA 400 & STA 492.4737-700IGW737-800737-900ER28000 Cycles<1>53-60-08-6 Aft Cargo Door Surround Structure(Skin Splice at S-23R BS 794.4 and 847)See Table Entry andDTR Form for PSE 53-30-08-6737-700IGW737-800737-900ER<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-110737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-60-08-7 Aft Cargo Door Surround StructureForward 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 492.4737-700IGW737-800737-900ER21600 Cycles<1>53-60-08-8 Aft Cargo Door Surround StructureForward 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 492.4737-700IGW737-800737-900ER21600 Cycles<1>53-60-08-9 Aft Cargo Door Surround StructureSkin and Bearstrap at Corners of Cutout.Also: PSE 53-30-08-9 Forward Cargo Door Surround Structure737-700IGW737-800737-900ER24000 Cycles53-60-08-10 Aft Cargo Door Surround Structure(Upper Sill Outer Chord)See Table Entry and DTR Form for PSE 53-30-08-10737-700IGW737-800737-900ER<1>53-60-08-11 Aft Cargo Door Surround StructureUpper Sill Inner Chord737-700IGW737-800737-900ER28000 Cycles53-60-08-12 Aft Cargo Door Surround Structure(Lower Main Sill Chords Between STA 807and 827)See Table Entry and DTR Form for PSE 53-30-08-12737-700IGW737-800737-900ER<1>53-60-09-1 Aft Cargo Door StopForward and Aft edges of Aft Cargo Door. Also:PSE 53-30-09-1 Forward Cargo Door737-700IGW737-800737-900ER28000 Cycles53-60-09-3 Aft Cargo Door Fittings and Stops at theForward and Aft Edge FramesBackup Fittings and Intercostals. Also:PSE 53-30-09-3 Forward Cargo Door737-700IGW737-800737-900ER28000 Cycles<1>53-60-12-2 Mid Exit Door Surround Structure Skin andBearstrapBetween BS 727H + 8.85” and BS 727I + 13.15”737-900ER 28000 Cycles53-60-12-3 Mid Exit Door Surround Structure Upper MainSillSTA 727H to STA 727J737-900ER 28000 Cycles53-60-12-5 Skin Lap Splice, Lower Row at S-10L toS-10R, Mid Exit Door Surround - Section 46Between BS 727G and BS 727K737-900ER 28000 Cycles53-60-12-6 Skin Lap Splice, Lower Row at S-14 to S-14,Mid Exit Door Surround - Section 46Between BS 727G and BS 727K737-900ER 28000 Cycles53-60-13-1 Mid Exit Door Stop FittingsBS 727H + 8.85” and BS 7271 + 13.15”737-900ER 28000 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11153-70-03-1 Longitudinal Lap SpliceSee Table Entry andDTR Form for PSE 53-10-03-1737-700IGW737-800737-900ER<1>53-70-03-2 Longitudinal Lap SpliceS-4L & S-4R, STA 887-1016 Lower Fastener Row, Lower Skin737-700IGW737-800737-900ER28000 Cycles<1>53-70-03-3 Longitudinal Lap SpliceS-14L, STA 888 to 947, 1006 to 1016, Upper Row, Upper Skin.S-14R, STA 888 to 947, 996 to 1016 Upper Row, Upper Skin737-700IGW737-800737-900ER28000 Cycles<1>53-70-03-4 Longitudinal Lap SpliceS-14L, STA 888 to 947, 1006 to 1016, Lower Row, Lower Skin.S-14R, STA 888 to 947, 996 to 1016 Lower Row, Lower Skin737-700IGW737-800737-900ER28000 Cycles<1>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 andDTR Form for PSE 53-60-04-7737-700IGW737-800737-900ER<1>53-70-04-1 Crown Skin Panel STA 887to 1016See Table Entry and DTR Form for PSE 53-30-01-2737-700IGW737-800737-900ER<1>53-70-07-3 Aft Entry Door, Forward Edge Frame DoorStop Backup StructureStops #1, #2, #6 and #7737-700IGW737-800737-900ER28000 Cycles<1>53-70-07-4 Aft Entry Door, Aft Edge Frame Door StopBackup IntercostalsStops Locations #1, #2, #6 and #7737-700IGW737-800737-900ER28000 Cycles<1>53-70-07-5 Cutout, Aft Entry Door Surround Structure Skin Around Perimeter of Cutout. Also:PSE 53-70-08-5 Aft Galley Door737-700IGW737-800737-900ER28000 Cycles<1>53-70-07-6 Aft Entry Door Surround StructureLower Sill Scuff Plate Installation. Also:PSE 53-70-08-6 Aft Galley Door737-700IGW737-800737-900ER28000 Cycles<1>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 Door737-700IGW737-80014200 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-112737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-70-07-11A Cutout, Aft Entry Door SurroundStructure Upper Main Sill Inner ChordSTA 951 to STA 1006 737-900ER 14200 Cycles<1>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 Door737-700IGW737-800737-900ER28000 Cycles<1>53-70-08-3 Aft Galley Door Forward Edge Frame DoorStop Backup StructureStops #1, #2, #5 and #6 737-700IGW737-800737-900ER28000 Cycles<1>53-70-08-4 Aft Galley Door Aft Edge Frame Door StopBackup IntercostalsStop Locations #1, #2, #5 and #6 737-700IGW737-800737-900ER28000 Cycles<1>53-70-08-5 Cutout, Aft Galley Door Surround Structure(Skin around Perimeter of Cutout)See Table Entry andDTR Form for PSE 53-70-07-5 737-700IGW737-800737-900ER<1>53-70-08-6 Aft Galley DoorSurround Structure See Table Entry and DTR Formfor PSE 53-70-07-6 737-700IGW737-800737-900ER<1>53-70-08-11 Aft Galley Door Surround Structure See TableEntry and DTR Form for PSE 53-70-07-11 737-700IGW737-80053-70-08-11A Cutout, Aft Galley Door SurroundStructure Upper Main Sill Inner ChordSTA 951 to STA 1006 737-900ER 14200 Cycles53-70-08-12 Aft Galley Door Surround Structure(Lower Main Sill Inner and Outer Chord)See Table Entry and DTR Form for PSE 53-70-07-12737-700IGW737-800737-900ER<1>53-70-09-1 Window Belt STA 888 to 927 – Corners ofWindow FrameSee Table Entry andDTR Form for PSE 53-60-05-1737-700IGW737-800737-900ER53-70-09-2 Window Belt STA888 to 927– Window Frame SeeTable Entry andDTR Form for PSE 53-60-05-2737-700IGW737-800737-900ER53-70-09-3 Window Belt STA 888 to927 – SkinSee Table Entry and DTR Form for PSE 53-60-05-3737-700IGW737-800737-900ER53-80-01-1 Bulkhead STA 1016Pressure Chord737-700IGW737-80028000 CyclesTABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11353-80-01-2 Bulkhead STA 1016Pressure Dome Webs between Tear Straps737-700IGW737-80028000 Cycles53-80-01-3 Bulkhead STA 1016Pressure Dome Webs between Tear Straps Lap Splice(Visible Row)737-700IGW737-80028000 Cycles<1>53-80-01-4 Bulkhead STA 1016Web at Pressure Chord Adjacent to Stiffeners737-700IGW737-80028000 Cycles<1>53-80-01-5A Bulkhead STA 1016Web at Pressure Chord Between Stiffeners, Str 5L to 7L andStr 5R to 9R737-700IGW737-80028000 Cycles<1>53-80-01-5B Bulkhead STA 1016Web at PressureChord Between Stiffeners, Areas Outsideof Str 5L to 7L and Str 5R to 9R737-700IGW737-80028000 Cycles<1>53-80-01-6 Bulkhead STA 1016Web at Chord Splice Between S-1 and S-3, and between S-15and S-18737-700IGW737-80028000 Cycles<1>53-80-01-7 Bulkhead STA 1016Pressure Dome Webs Lap Splice Under Stiffeners(Hidden Detail)737-700IGW737-80028000 Cycles<1>53-80-01-8 Bulkhead STA 1016Pressure Dome Webs at Tear Straps737-700IGW737-80028000 Cycles<1>53-80-01-9 Bulkhead STA 1016Pressure Dome Webs at Lap Splice and Tear Strap Intersection737-700IGW737-80028000 Cycles<1>53-80-01-11 Bulkhead STA 1016Pressure Dome Webs atLap Splice and Tear Strap Junctions737-700IGW737-80028000 Cycles<1>53-80-01-12 Bulkhead STA 1016Pressure Dome Webat Tear Strap between Stiffeners737-700IGW737-80028000 Cycles<1>53-80-01-13 Bulkhead STA 1016Web at Chord Splice/Double between S-1 and S-3737-700IGW737-800L/N 1057 and On,Except -800FPB28000 Cycles<1>53-80-02-1A Vertical Fin Front Spar Fitting, BulkheadAttachment - STA 1016Bulkhead Fittings @ STA 1016737-900ER 28000 Cycles<1>53-80-02-2 Vertical Fin Front Spar Fittings – STA 1016 Fitting Lugs737-900ER 28000 Cycles<1>53-80-03-1 Stringer Splice FittingsSTA 1016, S-9L to S-9R Forward and Aft of Bulkhead737-700IGW737-800737-900ER28000 Cycles<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-114737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA53-80-13-2 STA 1042 Bulkhead WebECS Duct Cutout737-900ER 28000 Cycles53-80-14-1 737-900 BBJ3 LCA STA 1042 PressureBulkhead Vertical BeamsVertical Beam at Horizontal Beam Splice737-900ER 28000 Cycles53-80-14-3 737-900 BBJ3 LCA STA 1042 PressureBulkhead Horizontal IntercostalsSee Table Entry andDTR Form for PSE 53-80-14-4737-900ER53-80-14-4 737-900 BBJ3 LCA STA 1042 PressureBulkhead Horizontal IntercostalsSTA 1042 Bulkhead Beams, Aft Horizontal Straps737-900ER 28000 Cycles53-80-14-7 737-900 BBJ3 LCA STA 1042 PressureBulkhead Horizontal IntercostalsSTA 1042 Bulkhead Beams, SystemPenetrations in HorizontalIntercostals737-900ER 28000 Cycles53-80-15-1 737-900 BBJ3 LCA STA 1042 PressureBulkhead Beam LugsSTA 1042 Lugs, Links & Fittings - Bulkhead Beam End Lugs737-900ER 28000 Cycles53-80-15-2A 737-900 BBJ3 LCA STA 1042 PressureBulkhead Lug FittingsSTA 1042 Lugs, Links & Fittings - Bulkhead Beam End LugsHidden By Attach (Clamshell) Fittings (RBL/LBL 10 & 23,WL 282, 269, and 256)737-900ER 28000 Cycles<1>53-80-15-2B 737-900 BBJ3 LCA STA 1042 PressureBulkhead Lug FittingsSTA 1042 Lugs, Links & Fittings - Bulkhead Beam End LugsHidden By Attach (Clamshell) Fittings (WL 223)737-900ER 28000 Cycles<1>53-80-15-3 737-900 BBJ3 LCA STA 1042 PressureBulkhead Beam LinksSTA 1042 Lugs, Links & Fittings - Link Clevis Fittings737-900ER 28000 Cycles53-80-15-4 737-900 BBJ3 LCA STA 1042 PressureBulkhead Attach FittingsSTA 1042 Lugs, Links & Fittings - Fwd Link Attach Fittings737-900ER 28000 Cycles53-80-16-1 STA 1042 Bulkhead Chord SpliceSTA 1042 BulkheadFittings, APU Chord Splice Fitting737-900ER 28000 Cycles53-80-17-2 737-900 BBJ3 LCA APU Inlet Enclosure APU Inlet Cutout Enclosure - Forward Pressure Panel, VisibleFastener Locations737-900ER 28000 Cycles<1>53-80-17-3 APU Inlet Cutout Enclosure Installation Middle and AftPressure Panels, Visible Fastener Locations737-900ER 28000 Cycles53-80-17-4 737-900 BBJ3 LCA APU Inlet Enclosure APU Inlet Cutout Enclosure - Mid Pressure Panel, Hidden byStiffener737-900ER 28000 Cycles<1>53-80-17-5 737-900 BBJ3 LCA APU Inlet Enclosure APU Inlet Cutout Enclosure - Mid Pressure Panel Hidden bySTA 1030 Frame737-900ER 28000 Cycles<1>53-80-17-6 APU Enclosure Installation Pressure Panels APU Inlet Enclosure - Aft Pressure Panel Hidden by STA 1030Frame737-900ER 28000 Cycles<1>TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11553-80-17-7 APU Enclosure Installation: Forward PressurePanelsAPU Inlet Enclosure - Fwd Pressure Panel Hidden by Stiffener 737-900ER 28000 Cycles<1>53-80-17-8 APU Enclosure Installation: Stiffener atFwd/Mid Pressure Panel InterfaceAPU Inlet Enclosure - Fwd/Mid Panel Interface Stiffener737-900ER 28000 Cycles<1>53-80-17-10 APU Enclosure Installation: Stiffener at MidPressure PanelSection 48, RHS Only737-900ER 28000 Cycles53-80-18-1 Section 48 Longitudinal Lap SpliceLongitudinal Skin Lap Splices, Section 48, S-4 Lap, Upper Row,Outer Skin737-900ER 28000 Cycles53-80-18-2 Section 48 Longitudinal Lap SpliceLongitudinal Skin Lap Splices, Section 48, S-4 Lap, Lower Row,Inner Skin737-900ER 28000 Cycles<1>53-80-18-5 Section 48 Longitudinal Lap SpliceLongitudinal Skin Lap Splices, Section 48, S-24 Lap, Upper Row,Outer Skin737-900ER 28000 Cycles<1>53-80-18-6 Section 48 Longitudinal Lap SpliceLongitudinal Skin Lap Splices, Section 48, S-24 Lap, Lower Row,Inner Skin737-900ER 28000 Cycles<1>53-80-18-7 Section 48 Butt Splice at S-9R and S-9L Longitudinal Skin Butt Splice, Section 48, Upper and LowerRows, Skin737-900ER 28000 Cycles<1>53-80-18-8 Section 48 Butt Splice at S-9R and S-9LSee Table Entry for DTR Formfor PSE 53-80-18-7737-900ER<1>53-80-18-9 Section 48 Butt Splice at S-9R and S-9L Longitudinal Skin Butt Splice, Section 48, Upper Row,Splice Strap737-900ER 28000 Cycles<1>53-80-18-10 Section 48 Butt Splice at S-9R and S-9L Longitudinal Skin Butt Splice, Section 48, Lower Row,Splice Strap737-900ER 28000 Cycles<1>53-80-20-4 Side Skin Panel, STA 1016 to 1042APU Inlet Cutout737-900ER 28000 Cycles53-80-21-1 Section 48, Side Skin PanelSide Skin Panel, STA 1016 to 1042737-900ER 28000 Cycles<1> No airplane may be operated beyond the stated threshold (oroperational limit) until the applicable inspection procedures are validated, published in the appropriatemanual, and accepted by the FAA.<2> These PSE's require supplemental inspections only ifthe Baseline Structures Program has been escalated.TABLE 9-3 AIRWORTHINESS LIMITATIONS - SUPPLEMENTAL INSPECTIONS FOR AIRPLANES WITHSB 737-21-1149PSE #DTR CHECK FORM TITLELOCATIONZONEREFAIRPLANEAPPLIC THRESHOLDDEC 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-116737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAC. AWLs– STRUCTURAL SAFE LIFE PARTSITEM LIFE LIMITNose Landing Gear75,000 Landings[1]Except Aft Lock Link (162A2115-2)4,200 LandingsMain Landing Gear75,000 LandingsMain Landing Gear Support Structure75,000 Landings[2][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 containa complete listing of 737-600/700/700C/800/900/900ER safe life parts:161A0002, 737-X Main Landing Gear Component Interchangeability List162A0002, 737-X Nose Landing Gear Safe Life Component List115A0007, 737 Trailing Edge ComponentLife Limited ListJUN 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-117D. AWLs– SYSTEMSENGINE OIL CONSUMPTION LIMITATIONThe approved maximum oil consumption rate for the CFM56-7B engine installed on the model 737-700IGW (BBJ) with winglets and noauxiliary fuel tankshave 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 winglets,and with 0 to 5auxiliary 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 established as0.310 gallons per hour.The approved maximum oil consumption rate for the CFM56-7B engines installed on the model 737-900 airplane has been establishedas 0.340 gallonsper hour.The approved maximum oil consumption rate for the CFM56-7B engines installed on the model 737-900ER aircraft with winglets andno auxiliary fueltanks has been established as 0.330 gallonsper hour, and for aircraft without winglets and with no auxiliary fuel tanks has been established as0.340 gallons per hour.Operation of these specific airplane models, configured as described, with an engineoil consumption rate higher than these limits is not authorized, exceptas allowed under a special flight permit authorized under 14 CFR 21.197 and 21.199.AUG 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-118737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAE. AWLs– FUEL SYSTEMSINTRODUCTIONThe airplane systems maintenancerequirements described in thissection of the AWL document result from various 737 airplane certification activities withthe FAA. These maintenance requirements are required under the Code of Federal Regulations (CFR) 43.16 and 91.403. The AWLs may only be revisedwith the approval of the Seattle FAA Aircraft Certification Office (ACO). If the maintenance requirements cannot be accomplished due to repairs and/ormodifications, an alternate inspection, acceptable to the Seattle FAA ACO, must be used.An AWL may be an Airworthiness Limitation Instruction (ALI) or aCritical 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 operational life of theairplane. CDCCLs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO that is responsiblefor the airplanemodel Type Certificate, or applicable regulatory agency. A critical fuel tank ignition source prevention feature may exist in the fuel system and its relatedinstallation or in systems that, if a failure condition were to develop,could interact with the fuelsystem in such a way thatan unsafe condition woulddevelop without this limitation. Strict adherence to configuration, methods, techniques, and practices as prescribed is required to ensure compliance withthe CDCCL. Any use of parts, methods, techniques or practices not contained in the applicable CDCCL mustbe approved by the Seattle FAA ACO that isresponsible for the airplanemodel Type Certificate, or applicable regulatory agency. For each CDCCL, the word "maintenance" includes maintaining anyinstallation during alterations; therefore, adherence to the CDCCL is required during maintenance or alterations.ALIs identify inspection tasks related tofuel tank ignition source prevention which must be done to maintain the design levelof safety for the operationallife of the airplane. These ALIs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO that is responsible for theairplane model Type Certificate, or applicable regulatory agency. Strict adherence to methods, techniques and practices as prescribed is required toensure the ALI is complied with. Any use ofmethods, techniques or practices not contained in these ALIs must be approved by the Seattle FAA ACO thatis responsible for the airplane model Type Certificate, or applicable regulatory agency.MAR 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-119USE OF ALTERNATE TOOLSThe Component Maintenance Manuals (CMM) listed in the AWLs are currently Seattle FAA ACO approved.If the CMM allows the use ofalternate orequivalent tools, test equipment or materials, use of an alternate or equivalent tool, test equipment or material does not require further approval by theSeattle FAA ACO or local Regulatory Agency. For inside of the tank, use sealant type BMS 5-45 or equivalent per SRM 51-20-05.For outside of the tank,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 ofan event, an exceptional short-term extension for each fuelsystem AWL listed in thisdocument may be made without jeopardizing safety. The local regulatory authority (e.g. a Principle Maintenance Inspector) mustconcur with anyexceptional short-term extensions before they take place using procedures established with the local regulatory authority in the operators’ manuals. The“exceptional short-term extension” process is applicable to AWL intervals. It should not be confused with the operator’s short-term escalation” program fornormal 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 that office:1. The term “exceptional short-term extension” is defined as an increase in a System AWL interval that may be needed to cover anuncontrollable orunexpected situation. All AWLs listed in this section have been approved with an exceptional short-term extension of 30 days.2. Repeated use of extensions, either on the same airplane or on similar airplanes in an operator’s fleet, should not be used asa substitute for goodmanagement practices. Exceptionalshort-term extensions must not beused for fleet AWL extensions.After a fuel system AWL has experienced an exceptional short-term extension, the AWL interval will revert back to its intervallisted in this document. TheSeattle FAA ACO must approve, prior to its use,any desired extension notexplicitly listed above.This exceptional short term extension listed above applies to airlines that fall under the UnitedStates FAA jurisdiction only.Operators who are not underthe U.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.FEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-120737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAREGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval from the Seattle FAA ACO. This applies to operatorsunder the US FAA jurisdiction only and to airplanes registered in the US. All other operators should obtain approval form their own local regulatory agencyfor any deviations from the listed AWL instructions.AWL REVISION PROCESSIn the event that an AWL is revised, Boeing will prepare a revision tothis document that will be approved by the Seattle FAA ACO. This revision will thenbe forwarded to all 737-600/700/700C/800/900/900ER operators and the Seattle FAA ACO.PAGE FORMAT: AWLs – FUEL SYSTEMSCOLUMNEXPLANATIONAWL NUMBER Each task is given a unique AWL Item Number.The first and second digits are the ATA Chapter Number.TASKALI = Airworthiness Limitation Instruction. These tasks are inspections thatshould be performed at the listed intervals.CDCCL = Critical Design Configuration Control LimitationINTERVALTask 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 violating the intent ofthe design.JUN 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-121E.1 AWLs – FUEL TANK IGNITION PREVENTION ALIs AND CDCCLsThis section of AWLs contains an FAA-approved program of scheduled inspections and design limitations for operators to incorporate into theirmaintenance program for this type design tomeet the new standards and assumptions introduced by § 25.981 and SFAR 88. SFAR 88– Fuel TankSystem Fault Tolerance Evaluation Requirements and Title 14 Code of Federal Regulations § 25.981 – Fuel Tank Ignition Prevention require maintenanceinstructions and control limitations for certain fuel tankcritical design configurations.Paragraph 2(a) of SFAR 88 requires certain design approval holders of Type Certificates (TCs)and Supplemental Type Certificates (STCs) of largetransport airplanes to conduct a safety review of the fuel tank systems. The purpose of the safety reviewis to identify designfeatures that may result indevelopment of ignition sources in the fuel tank systems. Fuel System AWLs are mandatory maintenance actions established in accordance with § 25.981to ensure that unsafe conditions identifiedby the SFAR 88 safety review do not occur or are not introduced into the fuel tanksystem as a result ofconfiguration changes, repairs, alterations, or deficienciesin the maintenance program throughout the operational life of theairplane.AWL Number Task Interval ApplicabilityDescription28-AWL-01 ALI 10 YRALL External Wires Over Center Fuel TankConcern: Potential for Wire chafing and arcing to Center Fuel Tank Upper Panel.Perform a detailed inspection of the wire bundles routedover the center fuel tank and under the main deckfloor boards to detect damaged clamps, wire chafing, and that the wire bundles are not in contact with thesurface 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 damage, remove the sleeving andinspect the wiring for chafing if the sleeving was damaged.Repair any discrepancies found (referto Boeing SWPM D6-54446 20-10-11).FEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-122737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-02 CDCCL N/AALL External Wires Over Center Fuel TankConcern: Potential for Wire chafing and arcing to Center Fuel Tank Upper Panel.If any maintenance is performed in the area over thecenter fuel tank and under the main deck floor boards,verify the following in the affected areas where maintenance was performed (refer to Boeing AMM 28-11-00):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 withthe surface of the center fuel tank.Repair any discrepancies found (referto Boeing SWPM D6-54446 20-10-11).28-AWL-03 ALI 10 YrsALL Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring to enter the fuel tank.Perform the following functional check to ensure the integrity of the FQIS wiring shield to ground terminationsin the unpressurized area using a Loop Resistance Tester P/N 906-10246-2 or 906-10246-3 (refer to BoeingAMM 05-55-54):1. The loop resistance shall not exceed 0.138 ohm (138 milliohms) for Connector D11312 (Left MainTank without Densitometer) Wire Bundle W1140.2. The loop resistance shall not exceed 0.063 ohm (63 milliohms) for Connector D11312 (Left Main Tankwith Densitometer) Wire Bundle W1140.3. The loop resistance shall not exceed 0.138 ohm (138 milliohms) for Connector D11314 (Right MainTank without Densitometer) Wire Bundle W1138.4. The loop resistance shall not exceed 0.063 ohm (63 milliohms) for Connector D11314 (Right MainTank with Densitometer) Wire Bundle W1138.5. The loop resistance shall not exceed 0.040 ohm (40 milliohms) for Connector D11316 (Center Tankwithout Densitometer) Wire Bundle W7580.6. The loop resistance shall not exceed 0.040 ohm (40 milliohms) for Connector D11316 (Center Tankwith Densitometer) Wire Bundle W7580.Restore the bonds if the measuredloop resistance value is greater than the maximum allowed value(refer to Boeing AMM 05-55-54).AWL Number Task Interval ApplicabilityDescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12328-AWL-04 CDCCL N/AALL FQIS – Out Tank Wiring Lightning Shield to Ground TerminationConcern: Potential for lightninginduced voltages on the FQIS wiring to enter the fuel tank.If maintenance is performed in the unpressurized zonethat disconnects or opens an FQIS wire bundle shieldto ground path, then after restoration, perform thebond check for the type of ground path opened as listedbelow:1. For side of body FQIS connectors D39915,D39916, D4850P, and Hot Short Protector (HSP)connectors D13836 and D13834 that use theconnector's backshell for shield ground pathto 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 backshell of the connector (applicable toconnectors D39915, D39916, and D4850P).Then verify the following:A. For connectors D39915, D39916 and D4850P, the resistance from the shield terminal lug to airplanestructure shall be no greater than 3.0 milliohms(0.003 ohm) (refer to Boeing SWPM 20-20-00).B. For connectors D13836 and D13834, the resistance from the connector backshell to the HSP shallbe no greater than 3.0 milliohms (0.003ohm) (refer to Boeing SWPM 20-20-00).2. For tank side FQIS connectors D11312, D11314 andD11316 that use a shield pigtail and ground studfor shield ground path to structure:If the shield pigtail terminal lug to ground studis removed and reinstalled, or the ground studis repaired:Then verify the following:A. The resistance from the shield pigtail terminal lug to the ground stud bracket shall be no greater than1.0 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 wire bundle's shield is repaired(except as noted above), then that particular wire bundle shall be inspected using the Loop Resistance Testerper AWL 28-AWL-03 (refer toBoeing AMM 05-55-54).AWL Number Task Interval ApplicabilityDescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-124737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-05 CDCCL N/AALL FQIS – Out Tank Wiring Installation Separation RequirementConcerns: Potential for hot shortsand Electromagnetic Effects (EME) induced voltages on the FQIS wiring toenter the tank.The following applies to any new wiring that is installedwithin 6.5 inches of FQIS wiring. New wiring isdefined as any wiring that is added to the airplane,excluding repair or replacement of existing wiring.1. Must use wire types BMS 13-48, BMS 13-60 or BMS 13-58.2. The wiring must not be installed withina two-inch radius of the FQIS wiring.3. Under single failure of any clamp or bracket, a minimum 1⁄2 inch separation from the FQIS wiring mustbe maintained.The following applies to repair or replacement of existing wiring that is installed within 6.5 inches ofFQIS wiring:1. Maintain existing wire routing and wire type (refer to Boeing SWPM 20-00-13 for wire typesubstitutes).NOTE: Refer to the Wire Diagrams to identify FQIS wiring.28-AWL-06 CDCCL N/AALL FQIS – Repair of Processor UnitConcern: Potential for maintenance error during FQIS processor repair.The FQIS processor is designed to limit the levels ofenergy, voltage, current, and power allowed within theFQIS circuit to intrinsically safe levels in order to preclude the potential of an ignition source within anyfuel tank.Repair and overhaul of FQIS processor unit mustbe per the Goodrich (V89305) CMM 28-41-87 Revision 2and IPC 28-41-87 Revision 1 or CMM 28-41-73 Revision3 and IPC 28-41-73 Revision 0, or later revisionsthat have been approved by the Seattle FAA ACO.AWL Number Task Interval ApplicabilityDescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12528-AWL-07 CDCCL N/A AirplanesL/N 1767 and onequipped withdensitometer, orairplanes that haveincorporatedService Bulletin737-28A1221FQIS – Installation of Center Fuel Tank Hot Short Protector (HSP)Concern: Potential for wire to wire hot short voltages onthe center tank fuel quantity densitometer wiring toenter the fuel tank. This is applicable to airplanes with optional densitometer installed.The FQIS HSP is designed to prevent wire to wire external hot short voltages fromentering the fuel tankwhere it may cause an ignition. The following features must be maintained during installation of a HSP(refer to Boeing AMM 28-41-24):1. The electrical bonding resistance between the loose end of each bonding jumper lug and the sparweb, prior to attachment of the two bonding jumpers to the HSP, is 0.002 ohm (2.0 milliohms)or less.2. The electrical bonding resistance between each jumper lug and the HSP is 0.001 ohm (1.0 milliohm)or less.3. The electrical bonding resistance between the HSPand the spar web is 0.0025 ohm (2.5 milliohms)or less.4. Sealant is applied on the fastener heads and matingcomponents of the two bonding jumper lugs toprotect the bond.5. The electrical bonding resistance between eachHSP connector (D13834 and DI3836) backshell andthe HSP is 0.003 ohm (3.0 milliohms) or less.The HSP unit is not repairable. A new unit must beused if the HSP has failed (refer to Goodrich (V89305)CMM 28-41-24 for testing).28-AWL-08 CDCCL N/A ALL FQIS – Repair of In-Tank Hardware(Tank Units, Compensators and Densitometers)Concern: Potential for maintenance error during repair of in-tank hardware (tank units, compensators anddensitometers). Arc gaps may develop that could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS tank units, compensators and densitometers must be per the Goodrich(V89305) CMM 28-41-76 Revision 1,or CMM 28-41-75 Revision 0, or CMM 28-40-59 Revision E, or laterrevisions that have been approved by the Seattle FAA ACO.AWL Number Task Interval ApplicabilityDescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-126737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-09 CDCCL N/AALL FQIS – Repair or Replacement of In-Tank Wire HarnessConcern: Potential for error during repair or replacement of in-tank wire harness. Arc gaps may develop thatcould result in an ignition source inside the fuel tank.Repair of the FQIS in-tank wire harnessmust be approved by the Seattle FAA ACO.The following design feature must be maintained wheninstalling the FQIS in-tank wire harness (refer toBoeing AMM 28-41-44):1. Wire slack clearance between wires and structure must be a minimum of 0.125 inch.The following design features must be maintained when installing the FQIS spar penetration connector(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 - 40 N-m).3. The electrical fay surface bond between the sparconnector and the spar inside the tank is 0.001 ohm(1 milliohm) or less.4. Sealant is applied around the connector inside and outside the fuel tank.28-AWL-10 CDCCL N/AALL Lightning Protection– Hydraulic Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting and thespar during a lightning strike event.The following design features must be maintained ifthe bulkhead fitting is removed and replaced (refer toBoeing AMM 29-11-04):1. The electrical fay surface bond from the bulkhead fitting to the spar outside the tank is 0.001 ohm(1 milliohm) or less.2. A fillet seal is applied on the fitting tothe tank wall interface outside the tank.3. Sealant is applied, encapsulating the fitting to the tank wall interface inside the tank.4. An electrostatic bonding jumper exists between the structure and the HydraulicHeat Exchanger insidethe tank.5. The electrical bonding resistancebetween the structure and the Hydraulic Heat Exchanger inside thetank is 0.0025 ohm (2.5 milliohms) or less ifthe bonding jumper was removed and replaced.AWL Number Task Interval ApplicabilityDescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12728-AWL-11 CDCCL N/A AirplanesL/N 1498 and on,or airplanes thathave incorporatedService Bulletin737-28-1225Lightning Protection – Engine Fuel Feed Line Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting and thespar during a lightning strike event.The following design features must be maintained if the bulkhead fitting or attached tubing are removed andreplaced (refer to Boeing AMM 28-22-15):1. The electrical fay surface bond between the bulkhead fitting and the spar inside the tank is0.0005 ohm (0.5 milliohms) or less.2. Sealant is applied, encapsulating the fitting to the tank wall interface inside the tank.3. Sealant is applied, encapsulating the first fitting to the tube interface inside the tank.4. A fillet seal is applied between the jam nut and the spar outside the tank.5. An electrostatic bonding jumper exists between thespar and the first tube mating with the bulkheadfitting inside the tank.6. The electrical bonding resistance from the spar tothe first tube mating with the bulkhead fitting insidethe tank is 0.010 ohm (10 milliohms) or less ifthe tube bonding jumper was removed and replaced.28-AWL-12 CDCCL N/A ALL Lightning, Fault Current orHot Short Protection – Fuel Tank PenetrationsConcern: Potential for arcing or sparking inside the tank at a conductivemetal-to-ground structure interfaceas a result of electrical fault currents or lightning strike events due to insufficient bonding within the groundelectrical path.Any alteration, design change, or repair involving newpenetrations to the fuel tanks (such as a repair withfasteners, adding a bracket, bulkhead fitting or equipment) or change to the designfeatures of the existingequipment penetrations (such as fuelmeasuring sticks, sump drain valves,fueling manifold, fuel temperaturesensor, and motor operated fuel shutoff valve adaptor plate) requires approval by the Seattle FAA ACO.Electrical bonding of fittings and brackets and/or cap sealing of fasteners and/or fillet sealing of componentinterface to structure inside and/or outside the fuel tank will be required.AWL Number Task Interval ApplicabilityDescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-128737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-13 CDCCL N/AALL AC and DC Electrical Fuel Tank Pump MaintenanceConcern: Potential for maintenance error during pumpoverhaul. Fuel pump designs contain ignition sourceprevention means (i.e., flame arrestor, thermal fuses, materials, leadwire retention means, etc.) that must bemaintained if pump is overhauled.Repair and overhaul of AC Fuel Pumps must be per the Crane (V81982) CMM 28-22-05 Revision 4,CMM 28-22-06 Revision 6, CMM 28-22-08 Revision 4, CMM28-22-09 Revision 2, or later revisions that havebeen approved by the Seattle FAA ACO.Repair and overhaul of DC Fuel Pump must be per the Intertechnique (VF0553) CMM 28-20-02 Revision 9,or a later revision that has been approved by the Seattle FAA ACO.28-AWL-14 CDCCL N/AALL AC Fuel Pump Fault Current Bonding Jumper InstallationConcern: Potential for fault currentpath through the pump housing to structure inside the tank. Electricalfaults internal to the fuel pump motor impeller areby design routed through the motor impeller assembly tothe bonding jumpers on the front face of the motor impeller assembly to structure outside the tank. Thebonding jumpers ensure that fault currents are conductedto structure outside the tankuntil the circuit breakerand/or GFI has had time to remove power from the pump.The following design features must be maintained during pump replacement (refer to Boeing AMM 28-22-41):1. Two fay sealed bonding jumpers are installed between the pump motor impeller end-cap andthe spar.2. The electrical bonding resistance between the motor impeller end-cap and the spar is 0.0004 ohm(0.4 milliohm) or less.28-AWL-15 CDCCL N/A AirplanesL/N 928 and on,or airplanes thathave incorporatedService Bulletin737-28A1142.Fueling Float Switch System InstallationConcern: Potential for wire chafing and arcing to conduit inside the tank. The float switch assemblies in FuelTank 1 and 2 are not repairable to the initial manufactured standards. Thecenter tank float switch and linerare not repairable to the initial manufactured standards.The following design features must be met during float switch replacement as applicable (refer to BoeingAMM 28-21-71):1. A new float switch assembly must be used for Fuel Tank 1 or Fuel Tank 2.2. A new float switch and liner system must be used for the center fuel tank.AWL Number Task Interval ApplicabilityDescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12928-AWL-16 CDCCL N/AALL Fuel Tank Access Doors – Lightning ProtectionConcern: Potential for arcing or sparking inside thetank at the interface between the door and the tankstructure as a result of a direct strike or conducting currents through the wing skin.The following design features must be maintained duringfuel tank access door installation (refer to BoeingAMMs 28-11-11 and 28-11-31):1. For doors installed at door position numbersother than 531AB, 631AB, 531BB, 631BB, 532AB, and632AB, verify presence of a phenolic strip positioned around the outermost periphery of the door thatmates with the wing skin inside the tank.2. For 737-900ER airplanes with machined style impact-resistant doors, door position numbers 531AB,631AB, 531BB, 631BB, 532AB, and 632AB, verify presence of a phenolic strip positioned around theoutermost periphery of the door that mates with the wing skin inside the tank.3. A corrosion-free access door, clamp ring, and lower wing skin electrical faying surfaces.4. A new knitted aluminum mesh gasket is installed.If a new gasket is not available, a used gasketmeeting 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 be a minimum of0.015 inches thick.d. No more than 10% of strands in all three layers are broken through in any one area.NOTE: A gasket not meeting Items a through c criteria may be used for a maximum duration of 30 days.5. Grease or anti-corrosion compound is applied to both sides of the knitted aluminum mesh gasket. (notrequired for a new knitted aluminum mesh gasket that is less than five years old).NOTE: If the new knitted aluminum mesh gasket isgreater than five years old from manufacturingdate, de-grease and re-impregnate with 0.5-1 ounce of MIL-G-25537 (AeroShell 14)grease, or anti-corrosion compound BMS 3-38 (CorBan 27L Compound), or equivalentbefore installation.6. The knitted aluminum mesh gasket is installed between the outside face of the door and the wing skinto establish the electrical conductivity between the access door andthe wing skin using the Clamp Ringand fasteners torqued to 35 ±5 in-lb (4 ±1 N-m)for all doors except 737-900ER machined impactresistant doors. For machined impact-resistant doors installed on 737-900ER, torque to 65 ±5 in-lb (7±1 N-m).NOTE: Not applicable to Access Doors 533BB and 633BB (Surge Tank Access Doors with the NACAVent Scoop and Pressure Relief Valve).AWL Number Task Interval ApplicabilityDescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-130737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-17 CDCCL N/AALL Surge Tank Access Doors(533BB and 633BB) – Lightning ProtectionConcern: Potential for arcing or sparking inside thetank at the interface between the door and the tankstructure as a result of a direct strikeor conducting currents through the wing skin.During surge tank access door installation, perform the following actions (refer to Boeing AMMs 28-11-11,28-13-41, and 28-13-31):Clean the countersinks on the door.If the pressure relief valve is removed and replaced, verify the electrical fay surface bond between thepressure relief valve and the door is 0.010 ohm (10 milliohms) or less (refer to Boeing AMM 28-13-41).If the upper duct of the flame arrestor is removedand replaced, verify the following bonds (refer to BoeingAMM 28-13-31):1. The sealed electrical fay surface bond betweenthe flame arrestor and the flange on the lower airvent stack is 0.010 ohm (10 milliohms) or less, and2. The sealed electrical fay surface bond betweenthe flange on the lower air vent stack and the flangeon the upper duct is 0.010 ohm (10 milliohms) or less.Install door using the BACB30LH3-10 conductive fasteners torqued to 35 ±5 in-lb (4 ±1 N-m). No fastenersubstitution is allowed.28-AWL-18 CDCCL N/AALL Resetting of Tripped Fuel Pump Circuit Breakers or Ground Fault Interrupters (GFIs)Concern: Potential for arcing orsparking inside the tank between fuel pumps and fuel pump housings andoutside the tank between pump wiring and structure in flammable leakage zones.To reset the circuit breaker(s) or GFIs, the following must be performed:1. Accomplish the troubleshooting procedures (referto Boeing Fault Isolation Manual, Section 28-22).2. The fault(s) that resulted in circuit breaker or GFI tripping must be isolated and corrected prior to reset.AWL Number Task Interval ApplicabilityDescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13128-AWL-19 ALI 1 YR AirplanesL/N 1494 and on,or airplanes thathave incorporatedService Bulletin737-28A1206.Center Tank Fuel Boost Pump Automatic Shutoff SystemConcern: Dry running the center tank fuel pumpshas the potential for single failure ignition sourcesdeveloping at the pump inlet due to either frictional heating or sparking as a result of Foreign Object Debris(FOD) contacting the pump rotating elements, rotating elements contactingstationary parts, or hot journalbearings due to bearing contamination or failure.The automatic shutoff system is installed and designed tolimit continuous dryrunning condition to15 seconds.The following test is required in order to protect against latent faults:Functionally check the center tank fuelboost pump automatic shutoff system (refer to Boeing AMM28-22-00).28-AWL-20 ALI 1 YR Airplanes L/N 1981,2093, 2210 and on,or airplanes thathave incorporatedService Bulletin737-28A1201.Boost Pump Ground Fault Interrupter (GFI)Concern: Potential for pump housing burn-through, either internal or external to the fuel tank, as a result ofmajor arcing due to electrical failure (i.e., damagedelectrical connector, statorwindings or lead wire tohousing/end cap shorting).The GFI is designed to detect electrical faults and open the circuit prior to pump housing burn-through. Thefollowing maintenance check is required in order toensure continued functionality of the GFI circuit:Operationally check the GFI of all AC Fuel Tank Boost Pumps (refer to Boeing AMM 28-22-41).AWL Number Task Interval ApplicabilityDescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-132737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-21 CDCCL N/A See Description. Motor Operated Valve (MOV)Actuator – Lightning and Fault Current ProtectionConcern: Potential for arcing orsparking inside the fuel tank at a conductive metal-to-ground structureinterface as a result of lightningor electrical fault current event.Applicability: 737-600/700/700C/700IGW/800/900 airplanes starting with Line Numbers 1877 - 1980, 1982,or airplanes that have incorporated Service Bulletin 737-28A1207.The following design features must be maintained during actuator, index plate, oradapter plate replacement(refer to Boeing AMM 28-22-11 or 28-22-21):1. Maintain the following if the Spar Valve adapter plate is removed and replaced:a. The electrical bonding resistance between theadapter plate and the spar is 0.0005 ohm(0.5 milliohm) or less.b. A fillet seal is applied around the periphery ofthe adapter plate and the spar outside the tank.c. The four bolts that attach theadapter plate to the spar insidethe tank are wet installed and capsealed, and fillet seal is applied around the edgeof the hole and on the stationary part of theadapter plate inside the tank.d. The sealed electrical fay surface bond between the serrated mating surfaces of the index plateand the adapter plate. The index plate screws are wet installed using same sealant.e. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.f. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.003 ohm (3.0 milliohms) or less.g. The electrical bonding resistance between the loose end of the bonding jumper and thestiffener, prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm(1.5 milliohms) or less.h The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.i. The electrical bonding resistance between the FQIS outermost shield ground terminal to thespar is 0.007 ohm (7.0 milliohms) or less.(Continued on next page)AWL Number Task Interval Applicability DescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13328-AWL-21,ContinuedMOV Actuator – Lightning and Fault Current Protection, Continued2. Maintain the following if the Spar Valve index plate is removed and replaced:a. The sealed electrical fay surface bond between the serrated mating surfaces of the index plateand the adapter plate. The index plate screws are wet installed using same sealant.b. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.c. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.004 ohm (4.0 milliohms) or less.d. The electrical bonding resistance between the loose end of the bonding jumper and thestiffener, prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm(1.5 milliohms) or less.e. The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.f. The electrical bonding resistance between the FQIS outermost shield ground terminal to thespar is 0.007 ohm (7.0 milliohms) or less.3. Maintain the following If the Spar Valve actuator is removed and replaced:a. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.b. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.004 ohm (4.0 milliohms) or less.c. The electrical bonding resistance between the loose end of the bonding jumper and thestiffener, prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm(1.5 milliohms) or less.d. The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.e. The electrical bonding resistance between the FQIS outermost shield ground terminal to thespar is 0.007 ohm (7.0 milliohms) or less.(Continued on next page)AWL Number Task Interval ApplicabilityDescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-134737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-21,ContinuedMOV Actuator – Lightning and Fault Current Protection, Continued4. Maintain the following if the Cross-feedValve Adapter Plate is removed and replaced:a. The electrical bonding resistance between the adapter plate and the spar is 0.0005 ohm(0.5 milliohm) or less.b. A fillet seal is applied around the periphery ofthe adapter plate and the spar outside the tank.c. The four bolts that attach the adapter plate tothe spar inside the tank are wet installed and capsealed, and fillet seal is applied around the edgeof the hole and on the stationary part of theadapter plate inside the tank.d. The sealed electrical fay surface bond between the serrated mating surfaces of the index plateand the adapter plate. The index plate screws are wet installed using same sealant.e. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.f. The electrical bonding resistance between theactuator upper housing and the spar, prior toattachment of the bonding jumper and electrical connector, is 0.003 ohm (3.0 milliohms) or less.g. The electrical bonding resistance between the loose end of the bonding jumper and the spar,prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm (1.5 milliohms) or less.h. The electrical bonding resistance betweenthe actuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.5. Maintain the following if the Cross-feed Index Plate is removed and replaced:a. The sealed electrical fay surface bond between the serrated mating surfaces of the index plateand the adapter plate. The index plate screws are wet installed using same sealant.b. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.c. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.004 ohm (4.0 milliohms) or less.d. The electrical bonding resistance between theloose end of the bonding jumper and the spar,prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm (1.5 milliohms) or less.e. The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.(Continued on next page)AWL Number Task Interval Applicability DescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13528-AWL-21,ContinuedMOV Actuator – Lightning and Fault Current Protection, Continued6. Maintain the following If the Cross-feedValve Actuator is removed and replaced:a. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.b. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.004 ohm (4.0 milliohms) or less.c. The electrical bonding resistance between the loose end of the bonding jumper and the spar,prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm (1.5 milliohms) or less.d. The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.Applicability: 737-600/700/700C/700IGW/800/900 airplanes; Line Number 1981 or airplanes starting withLine Number 1983 and on.The following design features must be maintainedduring actuator, indexplate and adapter platereplacement (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 theadapter plate and the spar is 0.0005 ohm(0.5 milliohm) or less.b. A fillet seal is applied around the periphery ofthe adapter plate and the spar outside the tank.c. The four bolts that attach theadapter plate to the spar insidethe tank are wet installed and capsealed, and fillet seal is applied around the edgeof the hole and on the stationary part of theadapter plate inside the tank.d. The sealed electrical fay surface bond between the serrated mating surfaces of the index plateand the adapter plate. The index plate screws are wet installed using same sealant.e. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.f. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.003 ohm (3.0 milliohms) or less.g The electrical bonding resistance between theloose end of the bonding jumper and the spar,prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm (1.5 milliohms) or less.h. The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.(Continued on next page)AWL Number Task Interval Applicability DescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-136737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA28-AWL-21,ContinuedMOV 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 mating surfaces of the index plateand the adapter plate. The index plate screws are wet installed using same sealant.b. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.c. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.004 ohm (4.0 milliohms) or less.d The electrical bonding resistance between theloose end of the bonding jumper and the spar,prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm (1.5 milliohms) or less.e. The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.3. Maintain the following if the actuator is removed and replaced:a. The sealed electrical fay surface bond betweenthe mating surfaces of the actuator and theindex plate. The actuator screws are wet installed using same sealant.b. The electrical bonding resistance between the actuator upper housing andthe spar, prior toattachment of the bonding jumperand electrical connector, is 0.004 ohm (4.0 milliohms) or less.c. The electrical bonding resistance between the loose end of the bonding jumper and the spar,prior to attachment of the bonding jumper to the actuator, is 0.0015 ohm (1.5 milliohms) or less.d. The electrical bonding resistance between theactuator upper housing and the attachedbonding jumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.28-AWL-22 CDCCL N/A AirplanesL/N 1877 and on,or airplanes thathave incorporatedService Bulletin737-28A1207.MOV Actuator – Removed or RepairedConcern: Potential for arcing orsparking inside the fuel tank at a conductive metal-to-ground structureinterface as a result of lightning or electrical fault current event. An electrical isolator onthe actuator outputshaft is intended to disconnect the output shaft electrically from the motor internal electrical circuitry andground path structure.To verify the integrity of the electrical isolation feature, conduct the following bench test if the actuator wasremoved or repaired (refer toITT (V73760) CMM 28-20-21):A Dielectric Strength test on the completed actuatorassembly shall be performed by applying 3000 VACRMS, 60 Hz for one (1) minute between any mounting footof the actuator and the output shaft spline. Thereshall be no evidence of disruptive discharge in the formof leakage current in excess of 1.0 milli-amps. The3000V test is a bench test only andmust not be performed on the aircraft.AWL Number Task Interval Applicability DescriptionFEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13728-AWL-23 ALI 1 YR AirplanesL/N 1973 and on,or airplanes thathave incorporatedService Bulletin737-28A1248.Center Tank Fuel Boost Pump Power Failed On Protection SystemConcern: Dry running the center tank fuel pumpshas the potential for single failure ignition sourcesdeveloping at the pump inlet due to either frictionalheating or sparking as a result of FOD contacting thepump rotating elements, rotating elements contacting stationary parts,or hot journal bearings due to bearingcontamination or failure.The power failed on protection system is installed anddesigned in order to protect against a single failure(i.e., wiring faults or a welded fuel pump control relay) keeping power on the pump when the associated fuelpump 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 Failed On Protection System (refer toBoeing AMM 28-22-00).28-AWL-24 ALI 6 YR AirplanesL/N 1877 - 1980,1982, or airplanesthat haveincorporatedService Bulletin737-28A1207.MOV Actuator – Lightning and Fault Current ProtectionConcern: Potential for arcing orsparking inside the fuel tank at a conductive metal-to-ground structureinterface as a result of lightningor electrical fault current event.Perform the following functional check to ensure the integrity of the Spar Valve Actuator electrical bondingpath (refer to Boeing AMM 28-22-11):1. The electrical bonding resistance between the actuator connector flange and the spar, with theelectrical connector and the bonding jumper disconnected, is 0.010 ohm (10 milliohms) or less.2. The electrical bonding resistance between the actuator upper housingand the attached bondingjumper terminal (using a sealed electrical bond) is 0.001 ohm (1 milliohm) or less.3. The electrical bonding resistancebetween the outermost FQIS shieldground terminal and the spar,with the actuator electrical connector disconnected, is0.014 ohm (14 milliohms) or less.Restore the bonds if the measured resistance is greater than the maximum allowed value (refer to BoeingSWPM 20-20-00).AWL Number Task Interval ApplicabilityDescriptionFEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-138737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAE.2 ENGINE FUEL SUCTION FEED SYSTEMThis section contains an FAA approved program of scheduled inspections for operators to incorporate into their maintenance program for this type designto meet Title 14 CFR § 25.951.The 737NG Engine Fuel Suction Feed System was type certificatedas being compliant to Title 14 CFR § 25.951(b) when performingsuction feedoperations. The Engine Fuel Suction Feed System AWL results fromservice experience of loss offuel system suction feed capability due to air leaks inthe engine fuel feed system. The AWL is required maintenance needed to detect and correct failure of the Engine Fuel Suction Feed System to reducethe possibility of engine flameout resulting from air ingestion into the Engine FuelSuction Feed System during low fuel leveloperation with boost pumpsinoperative.The Engine Fuel Suction Feed System AWL is mandatory maintenanceto ensure that thesystem retains the performance of the Engine Fuel SuctionFeed System required by Title 14 CFR § 25.951(b) that arise dueto air leaks in the Engine Fuel Suction Feed System do not result in flameout ofboth engines.AUG 2012737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-139AWL Number Task Interval ApplicabilityDescription28-AWL-101 ALI 7500 FH or3 YRS,whicheveroccurs firstALL Engine Fuel Suction Feed Operational TestAn Engine Fuel Suction Feed Operational Test must be accomplished successfully on each engineindividually. This test is required in order to protect against engine flameout during suction feed operations,(refer to Boeing AMM 28-22-00):1. Each engine (fuelsystem) to be tested must meet the following Fuel TankQuantity and TestProcedural Limitations listed below.A. Fuel Tank Quantity – Engine No. 1I. The Center Tank Fuel Quantity must not exceed 3000 lbs (1360 kg).II. The Main Tank No. 1 Fuel Quantity must be between 1870 lbs - 2080 lbs (850 kg - 940 kg).NOTE: Excess fuel can be transferred to Main Tank No. 2.B. Fuel Tank Quantity – Engine No. 2I. The Center Tank Fuel Quantity must not exceed 3000 lbs (1360 kg).II. The Main Tank No. 2 Fuel Quantity must be between 1870 lbs - 2080 lbs (850 kg - 940 kg).NOTE: 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 Boost Pump ON.IV. Idle Engine Suction Feed (Boost Pump OFF) operation of minimum five minutes.NOTE: The APU may be used to start the engines, provided the fuel tank quantity and testprocedural limitations are met.2. The test is considered a success if engine operation is maintained during the five-minute period andengine parameters (N1, N2, and Fuel Flow) do not decay relative to those observed with Boost PumpON.3. An Engine Fuel Suction Feed System that fails the operational test mustbe repaired and successfullypass the Engine Fuel Suction Feed Operational Test prior to further flight.AUG 2012D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-140737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAF. AWLs – NITROGEN GENERATION SYSTEM ALIs AND CDCCLsThe following list of AWLs contains FAA approved scheduled inspections for operators to incorporate into their maintenance program for this type designto meet the requirementsfor the introduction of the Nitrogen Generation System (NGS). The FAA Final Flammability Rule, E8-16084, requiresmaintenance instructions and control limitations for certain NGS critical design configurations. § 25.981 (d) also requires AWLs to preclude ignition sourcesinside the fuel tank that may beintroduced by the addition of NGS.E8-16084, Final Flammability Rule, Paragraph III(F), Section 7,Identification of AirworthinessLimitations: Paragraph M25.4(a)requires that if FlammabilityReduction Means (FRM) is used to comply with Paragraph M25.1,AWLs must be identified for all maintenance or inspection tasks required to identifyfailures of components within the FRM thatare needed to meet Paragraph M25.1. NGSAWLs are mandatory maintenance actions thatensure thatunsafe conditions that arise due to NGS failures do not occur orare not introduced into the airplane as a result of configuration changes, repairs,alterations, or deficiencies in the NGS maintenanceprogram throughout the operational life of the airplane.See Section E for the definition of an ALI or CDCCL.FEB 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-141AWL Number Task IntervalApplicabilityDescription47-AWL-01 CDCCL N/AAll airplanesL/N 1820, 1831, 1935 and on.All airplanes that haveincorporated Service Bulletin737-47-1002.Lightning Protection – Nitrogen Generation System (NGS) Nitrogen Enriched Air (NEA) DistributionLine Fuel Tank PenetrationConcern: Potential for arcing or sparking insidethe tank at the interface between the bulkhead fittingand the spar during a lightning strike event.The following must be maintained if the bulkhead fitting is removed and replaced or re-installed (referto Boeing AMM 47-21-07):1. Install the same part number bulkhead fitting,2. Verify electrical fay surface bond from the bulkhead fitting to the rearspar structure inside thetank is 0.0005 ohm (0.5 milliohm) or less,3. Install fillet seal on both the inside and outsidesurfaces of the rear spar around the perimeterof the bulkhead fitting and jam nut, and4. Verify electrical bond from structure to first tube mating with the bulkhead fitting is 0.10 ohm(100 milliohms) or less.NOTE: The bulkhead fitting is a special partwhich has an integral flame arrestor. Anychange to this part requires approval by the Seattle FAA ACO.JUL 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-142737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA47-AWL-02 CDCCL N/AAll airplanesL/Ns 1820, 1831, 2517, 2620and on.All airplanes that haveincorporatedService Bulletin737-47-1003.Nitrogen Generation System (NGS) – Flammability Exposure and PerformanceConcern: Airplane alterations may impact the performance of the NGS and hence the flammability ofthe Center Wing Fuel Tank.Background: The NGS is designed to provide the proper level of nitrogen to the center wing tank inorder to reduce the flammability exposure byreducing the oxygen content of the ullage. Theflammability exposure is also affected by the temperature of the fuel. The following are criticalfeatures of the airplane that, if altered, can negatively affect the performanceof the NGS which in turnmay increase the center fuel tank flammability exposure beyond the limits of 14 Code of FederalRegulations, Section 25.981 at Amendment 25-125, utilizing the equivalent level of safety findingdescribed in FAA Memorandum PS05-0177-P-2.1. Transferring air (20.9% oxygen) to the center fuel tank will dilute the nitrogen richatmosphere created by the NGS inthe fuel tank. Some Auxiliary Fuel Tank installationstransfer air to the center wing tank aspart of venting and fuel transfer.2. NGS performance depends on bleed air pressure in the bleed air cross-over manifold suppliedby the engines.3. Certification of the NGS depends on the inherentflammability of the center fuel tank withoutNGS installed. Center tank flammability is a direct function of fuel tanktemperature. Any heatsources around the tank, heat sources introducedinto the tank (such as warm fuel or newheat exchangers), or changes that would causeheat to be retained (such installation ofblankets adjacent to tank walls) could affectfuel tank flammability in a negative manner.CDCCL: Any design change that affects the vent systemby adding air to the center tank, reduces thebleed pressure in the cross-over manifold duringany phase of flight orground operations, or addsany heat to the center wing fuel tank or increasesheat retention of the center wing fuel tank is notallowed without an FAA approved analysis to showthat the change, or combination of changes, doesnot affect the NGS performance per the requirements of 14 CFR Section 25.981(b), Amendment 25-125 utilizing the equivalent level of safety finding described in FAA Memorandum PS05-0177-P-2See Boeing AMM Chapter 28 for a description of the Fuel System. See Boeing AMM Chapter 47 fora description of the NGS.AWL Number Task IntervalApplicabilityDescriptionJUL 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-14347-AWL-03DELETEDALI1200 FHAll airplanesL/N 1820 and 1831Nitrogen Generation System – Functional Check Performance InspectionConcern: Latent failure of theHollow Fiber Membranes that make up the Air Separation Modules(ASMs) will reduce the percentage of nitrogen inthe nitrogen enriched airentering the center wingfuel tank.Perform the ASM inspection listed in Boeing AMM 47-00-00:1. Measure the oxygen concentration of the NEAat the output of the ASM per Boeing AMM 47-00-00).2. Verify the NEA purity is in the satisfactoryzone (shaded area) of the ASM performance chartspublished in Boeing AMM 47-00-00.If the nitrogen content is not satisfactory, troubleshoot per Boeing Fault Isolation Manual 47-31-00and perform the recommended repairs per Boeing AMM 47-00-00.47-AWL-04 ALI 22500 FHAll airplanesL/N 1820, 1831, 2517, 2620and on.All airplanes that haveincorporated Service Bulletin737-47-1003.Nitrogen Generation System – Thermal Switch Functional and Operational TestConcern: Latent failure of the Thermal Switch removes a layer of protection against fuel tank ignitionby hot bleed air.The NGS uses enginebleed air from the bleed system cross-over manifold to generate nitrogen toreduce the flammability of the center fuel tank. The NGS has features to prevent directly feeding hotbleed air into the fuel tank. The Thermal Switch provides a redundant backup to the NGS controller toprotect the Air Separation Module (ASM) and prevent hot bleed air fromentering the fuel tank. TheThermal Switch backup feature is a latent (notdetected) failure and must be tested to maintaincertification of the NGS.Perform a functional and operational test of the thermal switch to ensure the integrity of the thermalswitch (refer to Boeing AMM 47-43-02).AWL Number Task IntervalApplicabilityDescriptionJUL 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-144737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA47-AWL-05 CDCCL N/AAll AirplanesL/N 1820, 1831, 1935and on.All airplanes that haveincorporated Service Bulletin737-47-1003.Lightning Protection – FRS NEA Distribution Line Fuel Tank Lightning ShieldsConcern: Potential for arcing, sparking or filament heating inside the tankat the interface betweenthe bulkhead fitting and the sparduring a lightning strike event.The following features must be maintained if the upper or lower lightning shields are removed andreplaced or reinstalled (refer to Boeing AMM 47-21-08):1. Install Upper Lightning Shield sealed electrical fay surface bond to rear spar stiffener andstiffener sealed electrical faysurface bond to Rear Spar Web.2. Verify Upper Lightning Shield bonding resistance to Rear Spar Web is 0.0010 ohm(1.0 milliohms) or less.3. Install Lower Lightning Shield sealed electrical fay surface bond to bracket, bracket drivenrivet bond to stiffener, and stiffener sealed electrical fay surface bond to Rear Spar Web.4. Verify Lower Lightning Shield bonding resistance to Rear Spar Web is 0.0015 ohm(1.5 milliohms) or less.47-AWL-06 ALI 13,000 FHAll AirplanesL/N 1820, 1831, 2517, 2620and on.All Airplanes that haveincorporated Service Bulletin737-47-1003.Nitrogen Generation System – Cross-Vent Check Valve – Operational CheckConcern: The Cross-Vent Check Valve may fail open,latently allowing air to flow through the centertank, diluting the nitrogen rich environmentcreated by the Nitrogen Generation System.Operationally check the Cross-Vent Check Valve byaccessing the right wing surge tank and verifyingthe valve opens and closes (refer to Boeing AMM 47-00-00).47-AWL-07 ALI 6,500 FHAll AirplanesL/N 1820, 1831, 2517, 2620and on.All Airplanes that haveincorporated Service Bulletin737-47-1003.Nitrogen Generation System – NEA Distribution Ducting InspectionConcern: The NEA Distribution System ducting outside the fuel tank may fail, latently allowing NEA toleak without reaching the fuel tank, resulting in the fuel tanknot reaching required inert levels.Inspect the NEA distribution lines from the ASM to the fuel tank rear spar for damage and leaks (referto Boeing AMM 47-00-00).AWL Number Task IntervalApplicabilityDescriptionJUL 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-145NOTE: SHADED AWLs HAVE BEEN DELETED.47-AWL-08 CDCCL N/AAll AirplanesL/N 1820, 1831, 2517, 2620and on.All Airplanes that haveincorporated Service Bulletin737-47-1003.Industry Fleet Average Flammability ExposureConcern: NGS performance is dependent on industrydescent times. Industry efforts to reducedescent time may result inNGS performance that does not meet FAA requirements.Fleet Average flammability exposure for the fuel tanks with flammability reduction of this airplane typemust be maintained in accordance with 14 CFR Part 25, Appendix M. Boeing will monitor U.S.descent statistics and, if necessary to maintain compliance, will publish service information. If Boeingpublishes such service information, this CDCCL requires either that operators implement these FAAapproved design changes or that operators implement other design changes or operationalprocedural changes approved by the Seattle Aircraft Certification Office to maintain compliance with14 CFR Part 25, Appendix M.NOTE: This CDCCL does not require individual operators to monitor descent rates of theirfleets. Boeing will monitor US descent statistics and provide any needed serviceinstructions to operators. To preventincreasing flammability exposure abovepermissible levels, this CDCCL requires operators to incorporate future Boeingpublished service instructions denoted to maintain compliance with this CDCCL, orother approved actions, within the compliancetimes stated in the service instructions.AWL Number Task IntervalApplicabilityDescriptionJUL 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-146737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAG. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)SELECTION OF CMRsIn order to grant operators of the 737-600/700/700C/800/900/900ER airplanean opportunity to participate in the evaluation andselection of CMRs in anintegrated process with MRBR tasksand intervals, a CertificationMaintenance Coordination Committee (CMCC) was convened to review all of the737-600/700/700C/800/900/900ER CMRs. The CMRs listed in this document are the result of applying the CMCC process as describedin AC 25-19.CMR DEFINITIONAs defined by AC 25-19, a CMR is a required periodic task, established during the design certification of the airplane as an operating limitation of the typecertificate. CMRs usually result froma formal, numerical analysis conducted to show compliance with catastrophic and hazardous failure conditions.Additional 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 specificfailures or events, result in ahazardous or catastrophic failure condition.2. It is important to note that CMRs are derived from a fundamentally different analysis process than the maintenance tasks andintervals thatresult fromthe Maintenance Steering Group (MSG-3) analysis associated with Maintenance Review Board (MRB) activities. MSG-3 Analysis activity producesmaintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance tasks, which areperformed before failure occurs (and are intended to prevent failures), as well as failure-findingtasks. CMRs, on the other hand, are failure-findingtasks only, and exist solely to limit the exposure to otherwisehidden failures. Although CMR tasks are failure-finding tasks,use of potential failurefinding 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, anddo notprovide any preventative maintenance function. CMRs “restartthe failure clock to zero” for latent failures by verifying that the item has not failed, or cause repair if it has failed. Because the exposure time to a latentfailure is a key element in the calculationsused in a safety analysis performed toshow compliance withCFR Title 14, limitingthe exposure time willhave a significant effect on the resultant overall failure probability ofthe system. The CMR taskinterval should be designated in terms of flight hours,cycles, or calendar time, as appropriate.JUN 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-1474. The type certification processassumes that the airplane will bemaintained in a condition ofairworthiness at least equal toits certified or properly alteredcondition. The process described in AC 25-19 is not intended to establish normal maintenance tasks that should be defined through the MSG-3analysis process. Also, this process is not intended to establish CMRs for the purpose of providing supplemental margins of safety for concerns arisinglate in the type design approval process.5. CMRs should not be confused with required structural inspection programs that are developedby the type certificate applicantto meet the inspectionrequirements for damage tolerance, as required by CFR Title 14,Appendix H25.4 (Airworthiness Limitations section). CMRs are to be developed andadministered 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 without the concurrence of theSeattle FAA ACO.2. Two Star CMRs (**) – Task intervals maybe adjusted in accordance with each operator’s approved escalation program or an approved reliabilityprogram 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 asany MRB Report task; however, they can not be deleted from anoperator’s programwithout prior Seattle FAA ACO approval. For operators with approved escalation practices oran approved reliability program, data collection andanalytical techniques are used to make adjustments to an operator’s maintenance program. It has been demonstrated that the management of amaintenance program does not give rise to undue escalations; consequently, the escalation of Two Star CMR (**) intervals withinan operator’smaintenance program will be properly managed by the operator subject to local regulatory authority approval.MAY 2003D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-148737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAEXCEPTIONAL SHORT-TERM EXTENSIONSSince CMR intervals are based on statistical averages and reliability rates, an exceptional short-term extension of 10% for each CMR listed in thisdocument may be made without jeopardizing safety. The local regulatory authority (e.g. a Principle Maintenance Inspector) mustconcur with anyexceptional short-term extensions before they take place using procedures established with the local regulatory authority in the operators’ manuals. The“exceptional short-term extension” process is applicable to CMRintervals. It should not be confused with the operator’s “short-term escalation” programfor normal maintenance tasks described in the operators’manuals and in the FlightStandards Handbook 8300.10.The Seattle FAA ACO has accepted that these exceptional short-term extensions may be granted without consultation with that office:1. The term “exceptional short-term extension” is defined as an increase in a CMR interval that may be needed to cover an uncontrollable or unexpectedsituation. All CMRs listed in thisdocument 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 asa substitute for goodmanagement practices. Exceptionalshort-term extensions must not be used for fleet CMR escalation.After a CMR has experienced an exceptionalshort-term extension, the CMR interval will revert back toits interval listed in this document. The Seattle FAAACO 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 StatesFAA jurisdiction only.Operators who are not underthe U.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.FEB 2008737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-149POST-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 the Seattle FAA ACO:1. Since the purpose of a CMR is to limit the exposure time to agiven significant latent failure as part of an engineering analysis of overall systemreliability, instances of a CMR task repeatedly finding that nofailure has occurred may not besufficient justification for deleting the task or increasing thetime between repetitive performances of the CMR task. In general, * CMRs are not good candidates for escalation under an operator’s reliabilityprogram. A * CMR task change or interval escalation can only bemade if world fleet service experience indicates that certain assumptions regardingcomponent failure rates made early during the engineering analysiswere overly conservative, and a re-calculation of system reliability with revisedfailure 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 initial certification. It isimportant that operators be afforded the same opportunity to participate that they received during the original certification of the airplane, in order toallow 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), thechange may be documented by anFAA 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 by a change to this CMRdocument and enforced by an FAA Airworthiness Directive (AD).5. After initial aircraft certification, the only basis for adding a new CMR is inassociation with the certification of designchanges.6. A new CMR created as part of a design change should be partof the approved data for that change and added to this CMR document.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 Seattle FAA ACO. Thisrevision will then be forwarded to all 737-600/700/700C/800/900/900ER operators and theSeattle FAA ACO offices.JUN 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-150737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATATYPE KASTEXAMPLE ILLUSTRATING FORMAT12000 HRSSYSTEM.Operationally check CENTER HYDRAULIC ISOLATION29-13029-CMR-02* OPALL ALL737-600/700/700C/800/900/900ERITEMCMRNUMBERITEMMRBRELATEDNUMBERENGAPLTASK DESCRIPTIONAPPLICABILITYINTERVALCMRCERTIFICATION MAINTENANCE REQUIREMENTS

G95488MAR 2007737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-151PAGE FORMAT: CERTIFICATION MAINTENANCE REQUIREMENTSCOLUMNEXPLANATIONCMR ITEM NUMBER Each task is given a unique CMR Item Number.The first and second digits are the ATA Chapter Number.TYPECMR TYPECMRs are categorized into one or two starCMRs based on whether or not they can beescalated by the operator without prior FAA-ACO approval.* 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 continuous analysis andsurveillance; however, these tasks cannotbe deleted withoutprior Seattle FAA ACO approval.RELATED MRBRITEM NUMBERThis column is for the related MRBR itemnumber, if there is an applicable MRBR itemnumber. Not all CMRs have a one to one relationship to aMRBR item number.TASKMSG-3 TASK CATEGORIESOP = OPERATIONAL CHECKFC = FUNCTIONAL CHECKA failure finding task to determine if an itemis fulfilling its intended purposes. Does notrequire quantitative tolerances.A quantitative check to determine if one ormore functions of anitem performs withinlimits.CMR INTERVALTask frequencies are specified in terms of a usage parameter such as flight hours, cycles and calendar time.APPLICABILITYAPL ENGApplicable Airplane Model and Engine.AIRPLANEALL = All AirplanesENGINEALL = All EnginesTASK DESCRIPTION Description ofthe task to be performed.FEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-152737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATACERTIFICATION MAINTENANCE REQUIREMENT TASKSCMRITEMNUMBERTYPERELATEDMRBRITEMNUMBERTASKCMRINTERVALAPPLICABILITY737-600/700/700C/800/900/900ERCERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTION26-CMR-01DELETED*DI560 CYC90 DaysNoteL/N 2093,2216through2318(Exclude2285)NoteAllPerform a detailed inspection of the Center Wing Rear Spar Vapor Web for crackingnear the stiffening beads on the fiberglass panels from inside the main gear wheel well.Interval Note: Whichever comes first.Perform the task per AMM 05-41-01-211-801.For applicable airplanes that have replaced the fiberglass panels per Service Bulletin737-57-1298, perform 26-CMR-02 instead of this CMR.26-CMR-02 * DI 5500 CYC24 MONoteL/N 2093,2216and onAll Perform a detailed inspection of the Center Wing Rear Spar Vapor Web for cracking inthe fiberglass panel between the vertical structural members. Do the inspection frominside the main gear wheel well.Interval Note: Whichever comes first.Perform the task per AMM 05-41-01-211-802.27-CMR-01DELETED*FCNoteNoteAllPerform a Functional Check of the Horizontal Stabilizer TrimJackscrew ActuatorBacklash.Interval Note: First inspection at 2000 FH and every 1000 FH thereafter.Airplane Note: Applicable to airplanes equipped with 251A4510-4 Actuators.27-CMR-02 * 27-108 RS 4,500 FH Note All Remove the Horizontal Stabilizer Trim Actuator for restoration of the Primary and/or theSecondary Brake.Applicability Note: For 251A4510-4 Actuator, Restore both Primary and SecondaryStabilizer Trim Actuator Brakes. For 251A4510-5 ActuatorRestore only theSecondary Brake.AUG 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-15327-CMR-03 * 27-044 FC 8,000 FH Note All Perform a Functional Check of the Main Rudder Power Control Unit Internal Leakage ina loaded condition.NOTE: Applicable to Airplane Line Numbers 1 - 595 and 597 - 1267 that have notincorporated Service Bulletin SB 737-27-1253.27-CMR-04 27-194 OP 20,000 FH Note All Perform an Operational Check of the Spoiler Mixer Centering Mechanism.NOTE: This CMR is ONLY applicable toaircraft on EASA/JAA Member StateRegistries.27-CMR-05 * 27-095 IN 2,000 CYC4,000 FHNote All Detail Visual Inspection ofthe Elevator Tab Rods, Tab Mechanism.NOTE: Applicable to 737-900 airplanes, L/N 683 to 1174, that have notincorporated SB 737-55-1081.27-CMR-06 * 27-097 FC 2,000 CYC4,000 FHNote All Perform a Functional Check of the Elevator Tab Freeplay.NOTE: Applicable to 737-900 airplanes, L/N 683 to 1174, that have notincorporated SB 737-55-1081.27-CMR-07 * 27-093 IN 2,000 CYC4,000 FHNote All Detail Visual Inspection ofthe Elevator Tab Rods, Tab Mechanism.NOTE: Applicable to L/N 596 and 1175 and on, and L/Ns 1 thru 595 and 597 thru1174 that have incorporated SB 737-55A1080 or SB 737-55-1081.27-CMR-08 * 27-099 FC 2,000 CYC4,000 FHNote All Perform a Functional Check of the Elevator Tab Freeplay.NOTE: Applicable to L/N 596 and 1175 and on, and L/Ns 1 thru 595 and 597 thru1174 that have incorporated SB 737-55A1080 or SB 737-55-1081.27-CMR-09DELETED*DS2 YearsL/N 1175And OnAllDiscard the Elevator Tab Hinge Bearings (6 per side).Interval Note: This CMR is temporary based on Fatigue Tests completed to date andwill be deleted or permanent based on results.CMRITEMNUMBERTYPERELATEDMRBRITEMNUMBERTASKCMRINTERVALAPPLICABILITY737-600/700/700C/800/900/900ERCERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONAUG 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-154737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA27-CMR-10 * 27-047 FC 10,000 FH Note*All Perform a Functional Check of the Main Rudder Power Control Unit Internal Leakage ina loaded condition.NOTE: Applicable to Airplane Line Numbers 596 and 1268 and on and L/Ns 1thru 595 and 597 thru 1267 that have incorporated SB 737-27-1253.27-CMR-11 * 27-026 LU Note 900ER All Lubricate the aileron tab hinge bearing and rod end bearings.Interval Note: Airplanes using BMS 3-33 Grease, interval is 4,000 FH or 12 Months(whichever comes first).Airplanes not using BMS 3-33 Grease, interval is 3,000 FH or 9 Months (whichevercomes first).Perform the task per AMM 12-22-11.27-CMR-12 * 27-033 FC 8,000 FH24 MonthsNote900ER All Perform a functional check of the aileron tab freeplay.Interval Note: Whichever comes first.Perform the task per Boeing Service Bulletin 737-27-1273 R2 or later FAA approvedrevision.28-CMR-01 * N/A IN Note Note All Perform a Detail Visual Inspection of the following items on all the Fuel Boost Pumpsfor signs of Fuel Leaks, Heat Discoloration, or Damage: Wire Terminal Assembly,Electrical Connector, and Wire Insulation.If any discrepancy is detected, prior to further flight, replace the Fuel Pump with a newor serviceable Fuel Pump and perform an Insulation Resistance Test, 28-CMR-02.Interval Note: 5,000 FH or 18 Months (whichever comes first) or 500 FH as determinedby CMR 28-CMR-02. (The interval for this task is always the same as the interval forCMR 28-CMR-02.)Airplane Note: This CMR is only applicable to the following fuel pumps if the fuel pumpsare installed without fuel pump ground fault interrupter (GFI): Boost Pumps 60B92404-6, 60B92404-7 and OverridePumps 60B89004-10, 60B89004-12.CMRITEMNUMBERTYPERELATEDMRBRITEMNUMBERTASKCMRINTERVALAPPLICABILITY737-600/700/700C/800/900/900ERCERTIFICATION MAINTENANCE REQUIREMENTSAPL ENGTASK DESCRIPTIONAUG 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-15528-CMR-02 * N/A FC Note Note All Perform an Insulation Resistance Test on all of the Fuel Boost Pumps.If any resistance measurement is less than orequal to 1 megohm, prior to further flight,replace the Fuel Pump with a new or serviceable Fuel Pump and repeat the InsulationResistance Test.Interval Note: If all resistance measurements are greater than or equal to 5 megohms,repeat this test at 5,000 FH or 18 Months(whichever comes first). If all resistancemeasurements are greater than 1 megohm,but one or more are less than 5 megohms:Repeat the Visual Inspection, 28-CMR-01, and the Insulation Resistance Test within500 FH for the affected Fuel Pumps, or replace the Fuel Pump with a new orserviceable Fuel Pump and repeat the Insulation Resistance Test.Airplane Note: This CMR is only applicable to the following fuel pumps if the fuel pumpsare installed without fuel pump ground fault interrupter (GFI): Boost Pumps 60B92404-6, 60B92404-7 and OverridePumps 60B89004-10, 60B89004-12.28-CMR-03Replaced by28-AWL-19.*N/AFC1 YearNoteAllPerform a Functional Check of the CenterTank Boost Pump Auto Shutoff SystemAirplane Note: Applicable to Airplane Line Numbers 1494 and On and operators thathave incorporated Boeing Service Bulletin 737-28A1206.CMRITEMNUMBERTYPERELATEDMRBRITEMNUMBERTASKCMRINTERVALAPPLICABILITY737-600/700/700C/800/900/900ERCERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONAUG 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-156737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA33-CMR-01DELETED*N/AIN2 Weeks-800 withwingletsPerform a General Visual Inspection of the Transparent Fairing Lens located on theForward Leading Edge of the Winglet, LH and RH.Visually inspect each lens for the following:Crazing - Lens should not exhibit a networkof the cracks on or beneath the surface.Clarity - Lens should be transparent and clear.Lens should not be translucent, cloudy,or opaque in appearance.Cracking - Lens should not have cracks.Blistering or Bubbling - Lens should not contain air pockets, lumps, or voids. Note:Small Bubbles in lens or coating that do not appear in large quantities or concentrationsis allowed. The appearance of a fewsmall bubbles can be introduced in themanufacturing process and is considered normal.Peeling or Flaking - Lens coating should not peel or flake.Discoloration - Lens should not exhibit signs or yellowing, darkening, stains, etc.Surface Deterioration - Lens should be smooth and have a glossy finish. Lens shouldnot exhibit signs of physical deteriorationsuch as abrasions, rough surface texture,matte finish, erosion, physical deformation orirregularities. Note: Minor scratching ofthe lens surface is allowed if there is not large quantities or concentration of thescratches.The General Visual Inspection should revealno optical defects described above. If anyof the above conditions exist removeand replace the lens per the maintenancemanual. Ensure the position and anti-collision lighting systems are deactivated per themaintenance manual.CMRITEMNUMBERTYPERELATEDMRBRITEMNUMBERTASKCMRINTERVALAPPLICABILITY737-600/700/700C/800/900/900ERCERTIFICATION MAINTENANCE REQUIREMENTSAPL ENGTASK DESCRIPTIONAUG 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-157DEFINITIONS:Appearance: The Aspect of visual experience by which things are recognized.Clarity: The characteristic of a transparent bodywhereby distinct high contrast images orhigh contrast objects are observable through the body.Crazing: Network of apparent fine cracks on or beneath the surface of materials such as intransparent plastics, glazed ceramics, glass, or clear coatings.Translucent: 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 straight pole viewedthrough a window having non-planar surfaces may appear to have bends in it.Matte: Lacking luster or gloss. Synonymous with “Flat” in paint terminology.CMRITEMNUMBERTYPERELATEDMRBRITEMNUMBERTASKCMRINTERVALAPPLICABILITY737-600/700/700C/800/900/900ERCERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONAUG 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-158737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATA52-CMR-01 * 52-360 FC 3,000 FH Note All Perform a Functional Check of the Locking and Unlocking Latch Bolt Mechanism on theFlight Deck Door Decompression Panel.Airplane Note: Applicable to airplane L/N 1221 and on and to those airplanes with thenew flight deck security door installed bythe customer specific Boeing ServiceBulletins.73-CMR-01 * N/A RS 300 FH -800 Note Remove the Left/Right Engine Hydro Mechanical Unit for Inspection per ServiceBulletin CFM 56-7B 73-016.Applicability Note: Applicable to Engine Hydro Mechanical UnitP/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 Sync Lock.CMRITEMNUMBERTYPERELATEDMRBRITEMNUMBERTASKCMRINTERVALAPPLICABILITY737-600/700/700C/800/900/900ERCERTIFICATION MAINTENANCE REQUIREMENTSAPL ENGTASK DESCRIPTIONAUG 2011737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAD626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-159H. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONSTitle 14 Code of Federal Regulations sections 121.703 and 135.415 state that “each certificate holder shall report any failure,malfunction or defect in anaircraft, system, component, or powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or defect has endangered ormay endanger the safe operation of an aircraft.” Section 125.409 also requires reporting offailures, malfunctions, or defects. In many cases a reportablefailure or malfunction will be obvious, but thereare some failure modes related to uncontrolled high thrust that are reportable but may not be obvious. Thefollowing information is provided, as required by FAA ExemptionNo. 7968 to assist the operators in identifying reportable malfunctions related touncontrolled high thrust.The FAA has concluded that the loss of capability to control thrust dueto a failure of the enginethrust control system may endanger the aircraft. Thisincludes any malfunctions having one ormore 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 presentlevel of safety ismaintained and/or to identify failureconditions that must be corrected.When filing a report of such an event with the FAA, the operatoris requested to include in the description of the event one ormore of the followingphrases:• “thrust control”• “no response to thrust lever’• “auto-acceleration’• “uncontrolled high thrust”FEB 2011D626A001-CMRBOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-160737-600/700/700C/800/900/900ER MAINTENANCE PLANNING DATAIn 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 theFAA Administrator that handles the appropriate reporting responsibility for 121.703, 125.409,and 135.415. In addition to filing reports with the FAA, it is recommended that a copybe sent to Boeing and to the engine manufacturer.FEB 2008