# rtJ--BDE'NG

DEC 2009 

## 747-400 MAINTENANCE PLA NNING DATA 

# 747-400 MAINTENANCE PLANNING DATA (MPD) DOCUMENT SECTION 9 AIRWORTHINESS LIMITATIONS (AWLs) AND CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs) D621U400-9 DECEMBER 2009 CO MPILED AND PUB LI SHED BY : MA I NTENANCE PROGRAMS ENG I NEERING COMMERCIAL AVIATI ON SERVICES BOEING COMMERCIAL A IR PLANE GROUP SEA TTLE , WASHINGTON

D621U 4 0Q·9 

### BOEING PROPR I ETARY - Copyrigh t (c) - Un pu blished Work - See title page for detai ls Page 9.0-1

## !j}.-BOE'NG 

## 747-400 MAINTENANCE PLANNING DATA

THIS PAGE I NTENTIONALLY LEF T BLANK

D621 U400-9 BLANK BOEING PROP R IE TARY - Copy right 

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## fJ-- . BDE'NG 

## 747-400 MAINTENANCE PLANNING DATA T

A BL E OF CO NTENT S

REVISIONS ........................... . ..... . ... .............. . . . . . .. .. . .. .. .. . ..... 9.0-5 LIST OF EFFECT IVE PAGES ......... . ... . ..... _ .. .. . ....... . .. . .. ....... ... 9.0-17 A . SCOPE ......................... . . ...... . ...................... . 

# ... .......... .. ................ ........................... .... ............. ... . ........ . .. ...................... . .......... . .................... 9.0 - 19 B . AIRWORT H INESS LI M I TATIO N S (AWl S)- SyS T EMS . ...... ......................... ..... .. .. .. . ... .. . ........... .................................... ...... . . .. .................................. . . .. .... ... 

### 9.0-20 C. PAGE FORMAT: F U EL SYST EMS AIRWORTHIN E SS LIM ITAT I O N S ....... . ......... . ...... . .. .................... . . . ...... .. . . . .................. ... . ......... .... ....... . ................. .. ..... . . 9.0 - 22 D . AIRWORTHINESS LI MITAT I ONS - FUEL SYSTEMS .. . ... ..... .. ... . . . . ..... . . . . ....................................................... . . . ..... 9 .0- 23 E . AIRWORT H INESS LIM ITATIONS - N I TROGEN GE N ERAT ION SYSTE M TASKS . . ......... . ..................... .. ....... . . .. ...... ................ 9.0-4 1 F. AIRWORTHINESS LIMITATIO N S (AW L S) - STRUC T URAL INSP E CT I O N S . .. . . . ....... . . ..... .. . 9.0-45 G . CERTIF I CAT I O N MAINTENA N C E REQUIR E ME N TS (C M Rs) . . ................ . ............ . .. .. ................................ .. . .... . . . ......... .. . 9 .0-47 H . CERTI F I CA T IO N MAI NT E NANC E R E QU I REMEN TS TA S K S . . . . . ............... . ....... . ...... . ... 9 .0 -50 

### I. REPORTING UN CO NTRO LLA B L E HIGH THRUST FAIL U R E COND IT I O N S ................ . 

### .9.0 -55



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## fJ.-H0EINC 

## 747-400 MA INTE NANC E PLA NNIN G DA T

A

T H IS PAGE I NTENTIO N ALLY LEFT B LANK

D621 U400-9 

### BLANK BOE I NG PROPRIETARY**~** Copyright (e) . Unpubl ished Work**~** See title page for details Page 9.0-4

# BDE'NG 747-400 MA I NTENANCE PLANNING DAT A REVISIONS APPROVAL REV I SION AND REV I SION DESCRIPTION MANAGER SEATTLE FAA AIRCRAFT 

### CERTIFICATION OFFICE , ANM-100S Revision 0 - Jan uary 1989 D . 

### l. Ri ggin Original Issue

# 1Jt:~r Rev ision 1 - February 1989 

### O. l. 

### Rig gi n Removed require m ents to chec k for Ope rative bus between EEC and EIU one flight prio r to 150 h our check and

# t!713r~ cha nged FADEC C 2 check fro m 15 0 hours 1 0 50 0 flight hours . Revis io n 2 - J une 1989 

### D . L. 

### R iggin Added requirements to accomplish a 1000 hour operational test which checks that air conditioni ng pack 3 high 

# tJ.t Ltr' flow mode is disabled with lower lobe ca rgo compartment conditioned air on. 

# ¥y'!,J Added requirements to interrogate the CMC for e ngine p osition 2 turbine overspeed failure message every 

### 150 hours on RB211 · 524G or RB211·524G2. Revised requirements to check e ng ine control system for Ca tegory 2 fa u lts to 

### 250 nigh t hours on RB211·524G or RB211 ·524G2 . Revision 3 - Jun e 1989 D. L. Rigg i n Added require m en t to Drain PW4000 Gearbox whenever cumulative oi l addition tota ls 12 quarts . 

# jJ 

# ,b'Rt ,/.. .**~y--.- ~I**  Revis io n 4 • June 1989 D. L. Riggin De l eted CMR 22- l ssue covered in FAA approved PW4 000 Ma i n tenance Manual via P&W Alert Servi ce Bulleti n 

# iJf/2,r-r PW4 E NG A79-39.



### D621U400-9 DEC 2009 BOEING PR OPRIETARY - Copyright (c) - Unpublished Work · See title page for detai ls Page 9 . 0·5

## r{;- HDE'NG 

## 747-400 MAINTEN A N C E PLA NN I NG DA TA RE V ISIONS APPROVAL REVIS ION A N D REVISION DESCRIP T ION MANAGER SEATTLE FAA A I RCRAF T CERTIFICATI O N OFFICE , ANM·100S Revision 5 - August 1989 

### D. L Riggin Revised CMR 12 to i nclude in operalionallesllhe E&E Coo l ing System Bypass Valve. 

# -;:) r**~** Revised CMR 13 from an operationa l lesl o f the E&E Cool ing System Fan Check Valves to a detail visual 

# u_ ..

# e'rrin sp ect ion of the lIapper doors and hi n ges. Added req u ireme n t to adjusVles t th e ma in deck air distribution shutoff valves on the Combi main deck fire 

### protection system . Revision 6 - February 1991 D. L. Rigg i n Revise d C M R 3 RR effectiv ity to RR RB2 1 1- S2 4 Ser i es eng i nes .**<;;.~_._t** :1!""'h;1' .•. l**"'I ""**  Revised CMR 21 RR effectiv ity to RR R B211-52 4 series engines and excluded requirement to inte rro g ate CMC for engine 2 TOS on RB2 1 1 powered 747-400s equipped with EICAS Version RR004. Revision 7 - March 1992 D . 

### l. Riggin Revised CMR 1 task de script i on 1 0 Operationa l (Short) T est - 11 5-Vol t Standby Power Generation. 

# .Ae,,»;....u..,

# r Revised CMR 1 6 to l i mit appl i cab i l ity to 747-400 's equipped with sta b ilizer fuel capability. Dele l ed CMR 21 because all RB211 powered 747-400s are now equipped with EICAS Software Version RR004 or a later ve rsi on. Re vision 8 - N ovember 1 992 D. 

### l. R igg i n Revised CMR 3to change the 250 F H check for RR RB211 powered 747-400s to 500 FH in accordance with the

# /tKf"'ff'**~** 

# f updated Type Certificate Data Sheet (TeDS No. E30NE. Rev date: June 5, 1992) . Rev is i on 9 - January 199 3 D. 

### l. R i gg i n Revise d CMR 3to change the 500 FH check for GE CF6-80C2B 1 F powe red 747-4oos to 1000 FH in

# *~....e&faccordance with the FAA approved GE documen t GEK 98408. Rev. 6, dated September 1992.

0621U400 -9 DEC 2009 BOEING PROPR I E T ARY - Copyright (c) - Unpublished Work - See ti ll e page for details Page 9.0-6

## l?i-SDE'NG 

## 747-400 MAINTENANCE PLANNING DATA REVISIONS APPROVAL REVISION AND REV I S I ON DESCRIPTION MANAGER SEATTLE FAA A IR CRAFT CERT I FICATION OFF I CE, ANM-100S Revision 10 - October 1993 D. 

### L. Riggin Revised CMRs 9,10 ,12, 14 , a nd 

### 1 510 exclude the 747-400F due to addition of an E&E cooli n g system self-test

# 0-j~rg: design feature . Rev i sed CMR 1 8 and 20 to exclude 747 - 400F model appl i cabi l ity _ Revision 11 - January 1994 D. 

### L. Ri ggin Revised CMR 6 to change the 

### 1000 FH check for th e E&E cool i ng system override mode function to 20 ,00 0 FH

# CJL£~ for the 747 -400F. Revised CMR 13 to exclude the 747-400F model app li cability. Revised CMR 20 to change thel0 00 FH check 

### 01 the lower lobe cargo compartment conditioned air system to 7400 Fl-! . Added 747-400 CMR-MPDfTask Card co r re l atio n li st for reference. Revision 12 - May 1994 D . L Riggin Revised CMR 3 to change the 500 F H check for the PW4000 eng ine to 1 000 FH.**:i~l/J-** 

# J?"' ":rr Revision 13 - June 1995 D . L Ri ggin Revised CMR 18to revise the system descri ption to note door #5 is not applicable on 747-400 Combi airplanes**f;:t'£~ "4'**  in the cargo mode and to add a note to the task which specifies check is requ i red immediate ly after conversion "t' to passenger mode. Revi sion 14 - February 19 97 D. L Ri ggin Revised CMR 18 to change the i nterval of part of t he functional check procedu re relati n g to the escape slide/raft

# ;)/;r1tt~ packs from 30 months to 36 months. The remainder of the check retains the inte rval of 30 months.

0621 U400-9 DEC 

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## rtJ-aOEING 

## 74 7-400 MA INTEN A N CE PLANN I NG DATA REVISIONS APPROVAL 

### REVISION AND REVISION DESCRIPT I ON MANAGER SEATTLE FAA A I RCRAFT CERT I FICATIO N OFF ICE, ANM-100S Revision 15 - May 1998 D. 

### L. Riggin Revised CMR 3 to change the 1000 FH check for GE CF6-80C2B1F powered 747-400'5 to 2000 FH in

### , 

# "'/d accordance with t he FAA approved GE document GEK 98408, Rev 10 , da ted March 1996. 

# V f- ,**c<~** I Revised C MR 3 to change the 500 FH check for RR RB21 1 powered 747-400'5 to 560 FH in accordance with , , 

### the updated Type 

### Certificated Data Sheet (TeDS No. E30NE). Revision 16 - Ju l y 200 1 

### Liu-Ne l son Revised CMR 88 to ch ange the intelVal from 6000 F H to 10 ,000 FH based on rev i sed H igh lifl Sys tem fau lt ).,: "!. !'**~** "--- 

### tre e analys is.**~** 

# .,- Rev ised CMR 9 a n d 10 to excl ude 747-4 00F model applicabil i ty since the fre i ghte r airplane has the Ef E Cool i ng automatic system se lf test wh ic h occ urs every te n th landing. Revision 17 - September 2002 Liu - Nelson Added requ ire ments to replace door strike assembly at fou r-year intervals.

# f~**,;.~** \ 

# Q.,e,... - > 

## \ r., .- ,'"u.>

### 'S'/t.'I·**~** Revision 18 - Oc tober 2002 Liu-N elso n Added C M R 25 app l icable only to airplanes incorporating any of Ih ese Boeing Se rvice Bulletins 747-25-3306

# ' andlor 747 -25 - 3312. This ame nded type certificate comp l ies with the new 14 CFR 25.795 and the amended 

# " .1UL. 14 CFR 25.772 as issued under Fede ral Register Docket No . FAA-2001-11 032. 

# \**Io(~ /~**  Revision 19 - February 2003 Liu- Nelson Added CMR 26 applicable for line numbers 1320 and on except freighter models . This amended type certificale

# ~ complies with the new 14 CFR 25.795 and the amended 14 CFR 25.772 as i ss ued under Federa l Reg i ster I 

# :C'-- Docket No . FAA-2001 ·1 1032 .

### ~A- ,..

### ~JI<IIJ.

D621U400 - 9 DEC 2009 BOEING PRO PRIETARY - Copyright (c) - Unpublished Wo rk - See title page f or detai ls Page 9.0-8

## (I)..**J~OE'NG** 747-400 MA I NTEN ANC E PLANNING DATA REV I S I ONS APPROVAL 

### REVIS IO N AND REV ISIO N D ESCR I PTIO N MANAG ER SEATTL E FAA AIRCRAFT CERTIFICATION OF FI CE, ANM-100S ; 

### Revi sio n 20 • M a rch 2005 Jeffrey Duven , Rev ised th e for m at of MPD Section 910 include the 

### 747-400 Maintenance Planning Data (MPD) task references 

# fjII'"'f£ 

# Q**~.~** alongside each C MR task . Added sta nda lo n e list of Effective Pages (L EP) to docu ment. 

### Added MP D Ta sk Reference 52-051-08 to CM Rs #24, #25 and #26. 

# 0 4

# /0;- R evise d MPD Item N umbers to renect new i l em nu m be rs as a resu lt o f tran sit ion to a new m ainte na nce documen tat ion pu bl ishi ng sys te m . Revi sion 21 - August 2005 Revi sed M PD Sectio n 9 to add Ai rworthiness li m ita t i ons sec tio n .

# ~t

# ...

# l_Ll Added N itrogen Ge nerati on System AW L and COCe L. 

### Revised Scope and CMR descri ption sect ion to explain and clarify. 

# *1/'15 Revision 22 • September 2005 J eff rey Duven Revised MPD Section 9 to add Airworthiness Limi tations Structures I nspection note for

# g~E~ 747 · 400 Specia l Freigh ter. Revised Ce rtifi ca t io n M a i n te nan ce Requirements section to reflect 747 · 400 Special F reigh te r incorporation . Revised MPD item number fo r CMR 8 

### a nd 20 to correct reference . 

# U/9/or Revi se d CMR 18, 

### Note 2 to spec ify tha t th e task be accom p lished at 30 months rath e r than 36, whereas the remainder of the p rocedure can be performed at 36 months rather than 30. Revised p rocedure refere nce to remove E19 re fere nce no longer required.

D 621 U4 00·9 DEC 2009 BOE IN G PROPRIETARY· Copy rig ht (c) • Unpub l ished Work· See tille page for details Page 9.0-9

### rti- 0DEfN& 

## 747-4 00 MA INTEN A N C E PLANNING DATA REV IS I ONS APPROVAL R EVIS ION AN D REV I S I O N DESCRIPTION MAN AGER SEATT LE FAA AIRC RA FT CERT I FICATION OFF I CE, A N M- 1 00S Revis i on 23 • March 2006 A . 

### J . Pasion Added new Fuel System Airworth in ess limitations which i nclude inspect i ons and design l imita t ions to sat i sfy

# ~~ SFAR88 requ i rements. Revised AilWorthiness limitation 47-AWL-O l to add m issi ng Step 3, and AWL 47-AWL-03 to correct ATA reference.

# 3/~**I/Oh** Revi se d CMR 10 AMM reference from 21-058 -02 to 21-058-00 to correci reference. Revised CMR 20 MPD lI e m N u mbe r f rom 2 1 -028-01 to 21-028 -0 0 to correct reference. Revis io n 24 - June 2006 J eff re y Duven Revised l asks 

### 47-AWl -Ol, 47-AWL-02 , 47-AW L -03, 47-AWL-04 , 47-AWL-05 , 47-AWL-06 to correct a i rpla n e 

# '/I

# ~ applicabi l ity, Revised 28-AWL-9 and 28-AWl- 1 0 to clarify the i ntent of the inspection and to clari fy the locatio n of the 

# / 7 ,/ bond i n g meaSurements. 

# '7/ 2 '7/0 6 Deleted 28-AWl-21, because production i n corp oratio n and service bulletin release h ave been postpo n ed indefinite l y. Added 28-AW L ·24 which manda tes an i ns p ec tion for th e horizon tal stabilizer fue l boost pump a u to shu toff sys t em, Added new reserve tank fuel i ng va lve C OC C l AW L N u mber 28·AWl·25, Revised 47-AWl-05 and 47-AWl·06 to a dd Int erval N ot e . November 2006 Jeffrey Duven Added a new operational check of the M a i n 2 and Main 3 ove rride/jettison fuel pump uncommanded on system

# 'DfMn;~ AWL Number AWL 28-AWL-26. 

# f"

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## rti-BOE'NG 

## 747-400 MA I NTEN ANC E PLANN I NG DAT A REV ISI ONS APPROVAL R EV ISIO N AND REV IS ION D ESCR I PTIO N 

### MANAGER SEATTLE FAA AIRCRAFT CER T I F ICATIO N O FF I CE , ANM-100S December 2006 Jeffrey Duven Revi se d CMR-24. CMR-25 . and CMR-26 interva ls f rom 4 years to 6 years to 

### renect improved reliabil ity data for

# ~L6~ th e Flight Deck 

### Door Strike Assembly.**lG c.~"''1** **~ e.,~'**  

### Decembe r 2006 R1 Jeffrey Duven Revised to add Airworthiness li mitat ion Structu res Inspect io n N ote fo r 747-400 large Cargo Fre ig h te r (lC F).

# ~y~4O- Revise d CMRs 15, 16, 20 . 23 . 24. 25, 26 to exclude 747-400 LCF d erivative. Revised CMR 2 to exclude cargo and APU fire/overheat detectio n sys te m for 747-400 LCF. Rev ised CMR 1 8 to -o nly appl i cable to door 1 UH- for 

### 747
-400 lCF. In Parag raph 1 of Secti on F, changed reference to 747 Supplemen tal Slruclura l ln specl ion Document, 06- 35022, Rev ision H 10 Revision G due to unknown r e lea se date for Revision H . Revised Airworthines s Li mi tations-fuel system section int ro duct io n to include revisions recommended by the Seattle FAA Fli g ht Standards g roup. Revised a irworth iness limitatio n number 28-AWL-24 to correct AMM procedure number fro m 

### 28-22-00 to 28-17-00 and to rev ise line number in the applicabil ity column from 1342 to 1 343. Add ed Motor Opera ted Valve actuator Airworthiness Lim itat ion. This AWL is applicab l e to airplane Line Posit io n 1382 and on, a nd airplanes modifie d per Service Bulletins 747-28A2292 . and 747-28A2294. May 2007 Jeffrey Ouven Added new CMR 27 10 periorm a functional check of the Re seNe Tank 2 a nd 3 VTO Secondary Sh u t-off System

# fj¥h**~** 

# (0.- . for the 747·400 Large Cargo Fre i gh te r ( LCF ).

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### rzi-HDEfNC 

## 74 7-40 0 MAIN TEN A N C E PLA NNING DA T

A R EVI SIONS APPR OVAL REV I SION AND REVISION DESCRIPTION MANAGER SEATTLE FAA AIRCRAFT CE RT I FICATION OFFIC E, ANM - 100S October 2007 

### Dor r Anderson for Jeffrey Duven Revised Sectio n B. Airworth i ness Limi tat ions (AWLs)· Syste m s pa ra g raph on Exceptional Short-Term Extensio n s for AWLs to cl ar if y n otifica tion requiremenls. 

# '[j "" 

# Vtf**~** Revised the li tle of Secti on C to read " Page F o rmat: Fu el Systems Airworthiness**Limitations ~**  instead o f 

### ' Page Format: F ue l Tank System Airworlh iness limitatio n ". Revised AWL Number 28 ·AWL·1 9 to add Ground F aull Interrupter (G F I) rela ys to th e l imi tat io n thai rest ricts resetting of fuel pump c i rcui t brea ke rs. Add ed AWL Number 28·AWL·28, a yearly check of the M ai n Fuel Tan k Boost Pump GF I , appl i cable to airp l ane Li n e Numbers 1394 and on and airp l anes thai have i n co rp o rate d Service Bulletin 747 ·28A22 61. Added AWL Number 28- AW L-29, a yearly check o f th e Center Wing T ank El ectric Scavenge Pump GF I , app l i cab le to a irp lane s with Electric Center Wing Tank Scavenge Systems, airp lanes prior to Line N u mb ers 972 that have incorporated Service Bulleti n 747-2BA2261. Added Secti on G Ce rt ifi catio n Ma i ntenance Requirements ( CMRs) - Exception Short ·T e r m Extens i ons to clarify n oti ficati o n requ irements. Re v ised CMR-24 , CMR-25 and CM R-26 task in t erval from 6 years to 9 yea rs to re fle ct imp roved reliab ili ty data for the Flight Deck Security Door. Added Paragrap h "I" to in co rp o rate " Reporting Un cont roll ed High Thrust Failure C ond it ions" per FAR 121.703 a nd FAR 135.415. N ove mber 2007 Ph i lip Forde for Jeffrey Duven Rev ise d 28 -AWL-25 bonding resistan ce value from 0 . 015 ohms to 0.001 5 o h ms to correc t a typo.

# S~ (Th e cor r ect va l ue i s 1 . 5 millio h ms). Rev ised CMR-27 to i nclude M ain Fuel Ta nks 1 and 4 i n VTO seconda ry shut-off system ta sk for the 747-400 Large Cargo Freigh te r.

# ~~ZL

D621U400 -9 DEC 2009 BOE I N G PROPR I ETARY - Copyright (c) - Un pu b lis hed Work - See titl e page for detai l s Page 9.0 - 12

# fJ-aOE'NG 74 7-400 MAIN TE NANC E P L A NNIN G DA T

A REVISIONS APPROVAL REV I SION AND REV I SION DESCR I PTION MANAGER SEATTLE FAA AIRCRAFT CERTIF I CATION OFF I CE, ANM-l0DS FEBRUARY 2008 

### Robert Breneman for Jeffrey Duven Revised Paragraph F. AIRWORTHINESS LIMITATIONS (AWLs)· STRUCTURAL INSPECTIONS \0 add 

# L restriction for 

### 747-400 Special Frei ghters del ivered after Janu a ry 11, 2008, 

### v

# I'O~ MARCH 2008 D orr Anderson for Jeffrey Duven Revised Paragrap h 

### F. AIRWORTH I NESS LIMITATIONS (AW l s) - STRUCTURA L INSPEC T I ONS to add 

# i!P"",}I17

# ~ restriction for 

### 747-400 Large Cargo Fre ighte r ( LCF) delivered after Janu ary 11 , 2008 and to change end date of December 1 , 200710 May 30, 2 008 and add the text-appendix " per FAA lette r dated Ju ly 1 6, 2007. Revised 2a-AWL-01 by remov i ng t he 36000FH task inteNallimitation based upon eng in eering review and 

## 3//1/08 operator ma intenance pract ice. Revised 28-AWl-03 to reflect the new maximum loop res istance values associated with the lightning protection of the unpressurized FalS wire bundle installations so as to satisfy the Airworthiness limitation I nstructions required by SFAR 88 . Also removed the joint resistance values and 36000FH task interva l limitation based upon engineering revi ew and operator ma i ntenance practice. Revised 28-AWl-1D by removing the 36000FH task i n terval limitat ion ba sed upon engineering review and operator maintenance practice. Rev ised 28-AWl·16 to change the term "grease" to " Corrosion I nhibiting Compound (CIC)" in Step 2 to re fl ect correct consumable type. Added AWls 28·AWl-3D, 28·AWl·31 , and 28·AWl ·32 to add the Electronic Fu el levellndicalion System (EFLt) CoCel requiremen t for the 747-400 (910K).

0621U400·9 DEC 2009 BOEING PROPRIETARY - Copyright (c)" Unpublished Work· See title page for detaits Page 9.0·13

## !l1- DDE'NC 

## 747- 40 0 MAINTENANCE PLA NN I NG DA T

A REV I SIONS APPROVAL 

### REV I SION AND REVISION DESCR I PT IO N MANAGER SEATTLE FAA AIRCRAFT CER T I FI CATION OFF I CE, ANM-100S 

### APR IL 2008 Phi l ip Forde for Jeffrey Duven Revised th e Procedure R eference for CMR 27 to remo ve incorrect Task number a nd reflect the correct Page 

### Block num be r. 

# I
, 

# 9 / 

# 1.. 

# L. It /Ie 

# f\,,'JiV MARCH 2009 Jeffrey Du ve n Revised P a ragraph E , A I RWORT HI NESS LI M IT ATION S (AW L s) * STR U CT U RAL I N S PECTIONS to remove

# ~J~ opera t io nal l i m its on 747-4 00 airplanes converted to th e Special Freig hte r config urat i o n . as es tablis h ed f o r compliance to 14 CFR 

### § 26 .45 (c) , and co nfer standards for continued comp l ia n ce to the sp eci ficat io ns of 747 Supplemental S tru ct u ra l I ns p ec tio n Document, 06-35022. 

# ;e;;tL SH7

# ~}~o~

--- ..

# __ ..

## _----- DECEMBER 2009 Revised 28 -AWL - 03 by addi ng maximum l oop resistance values, associa te d with the light n ing protection of the FQ tS wi re bundle ins tallations. specific to the 747-4 00 L CF de riva tive. A l so specifi ed that the exis t ing va l ues are appl i cab l e to all 747-400 ai rp lanes except 

### 74 7-400 LCF. and clarified the wire bund l e references as supplier part numbers . Also added condi t iona l dependency o f ins tallat ion for resistance measuremen ts of Conn e ctors S IGNATURE ON FILE X0 1 014 an d X01015 , and listed additional w ire bundles associated with Connector X01 014. 1 / 1212010 Revi sed 28-AWl- 11 to clarify component of concern as FOtS pro cessor unit and ide ntify the componen t m anu facturer (Goodrich) . Revised 28-AWL-12 . 2B-AWl- 1 3, 2B -AWl-1B , and 2B -AWl-32 to identify the compo n en t manuracturers. (Con t inued o n n ex t page) 0621U400-9 DEC 2009 BO EING PRO PR IETARY - Copy r i gh t (c) - Unpublished Wo rk - See ti tle page for de tails Page 9.0 - 14

# Il'J.- HOEING 

## 747-400 MA I NTENANCE P LANNING DATA R EV IS IONS APPROVAL REVISION AND REVI SIO N DESCRIPTION MANAGER SEATT LE FAA A IR CRAFT CERTIFICATIO N OFF I CE, ANM·100S DECEMBER 2009, Cont i nued R evised 28-AWL- 1 4 to ident ify the component ma nufactu re r (Good ri ch) and correcl Revision ident ification for Component Maintenance Manua I 2S-40-59 from**~** to**·E .**  Rev ised 28-AWL-20 by add i ng note s i aling I hallhe maintenan ce req u iremen ts are only app l i cable to areas that have been dist urbed . Also clarified airplane a pplicability . Revised 28-AWL-22 by changing terminology in item references from "bonding strap" to "bondi ng jumper" to clarify the item of concern. Revised 2B-AWL- 2 3 by changing termino logy in item references from " bonding strap " to "bonding jumper" to clarify th e item of concern. Also co rre cted resistance limit from 0 . 25 milliohms to 2.5 milliohms and clarified airp la ne applicability. Revised 28-AWL-24 to nole cond itiona l dependency of H orizonta l Stabilizer Fuel B oost Pump Automatic Shu toff System installatio n for AWL app l i cab i l ity . Also cla r ified airplan e applicabil ity. Revised 28-AWL- 31 to correct spe ll ing of the acronym 

### f or E l ect ron i c Fuel L evel Indication Sys tem (EFLI) and identify the co mpon ent manu factu rer (Parker). Revised 28-AWL -05. 28-AWL-25, 28-AWL-26, 2B-AWL-27, and 26-AWL-28to clari fy the airplane applicability. Revised Section F., AIRWORTHINESS LIMITATIONS (AW Ls) - STRUCTURAL IN SPECTIO N S to include notice of the additional and revised in spec tion requirements fo r 747-400 Large Cargo F reighter (LCF) airplanes imposed by Service Bullelins 747-00-2120 and 747-53A2817, respectively; updated the document reference for the 747-400 LCF Supplemental St ru ctural Inspection Document, and removed operational limits on 747-400 L CF a i rplanes delive red after J anuary 11, 2008, originally established for compliance to 14 CFR 

### § 26.45 (c).

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## !lJ- BDE'NG 

## 74 7-400 MAINTENANCE PLANNING DATA

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# rti-HDE,NG 

## 747-400 MAINTENANCE PLANNING DATA

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D62 1U400-9 

### BLANK BOEING PROPR I ETARY - Copyright (c) - Unpub lis hed Work - See title page for details 

### Page 9.0-18

## fl-OOEING 

## 747-400 MAINT E NANCE PLANNING DATA A. SCOPE The scheduled maintenance requ i rements described in this section result from Mode l 747-400 airplane certif i cation activities with the U .S . Federal Aviation Administration (FAA). Accordingly, this FAA approved Airworthiness Limitations (AWLs) and Certification Ma i ntenance Requirements (CMRs) document is cross-referenced in the Model 747-400 Type Cert ificate Data Sheet. These maintenance actions are mandatory . This Airworthiness Limitations Section is FAA-approved and specifies maintenance required under 43 . 16 and 91.403 of the Federal Aviat i on Regu lations. 

### unless an alternative program has been FAA approved . AIRWORTHINESS LIMITATIONS (AWLs) The Airworthiness Limitations may only be revised with the approval of the Seattle FAA Aircraft Certifica t ion Office (ACO). 

### If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspeclion acceptab l e to the Seattle FAA ACO must be used. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs) These scheduled ma i ntenance tasks may only be revised by the Seattle FAA ACO. Principal Airworthiness Inspectors (loca l regu l atory authority) may not change these requirements 

### or the interva l s assoc i ated with these requirements.

D621U40Q-9 AUG 2005 BOEING PROPR I ETARY - Copyright (c) - Unpublished Work - See title page for deta i l s Page 9 . 0-19

## ~DEINC 747 -40 0 MA INTEN A NCE PLANN ING DA T

A B . AIRWORTHINE SS LI M ITATI ONS (AWLs) - SYSTEMS AIRWORTHINE SS LIMITATIONS - FUEL SYSTE M S This section contains an FAA. approved program of Airworthiness Limitations (AWLs) for opera tors to incorporate into their ma i ntenance p rogram for Ihis type des ig n. There are two sets of AWLs in this section; the first secHon is to meet the new standards and assumptions int rod uced by 

### § 25.981 and Special Federal Aviati on Regulation SFAR No. 88, and the seco n d section is to meellhe requirements for [he introduction of t he Nitrogen Generation Sys tem (NGS ). An AW L may be an Airworth i ness limitation Instruction (AU) or a Critical Oesign Configurat ion Conlrollimilation (GOCeL). CDCCLs are a means of identiry i ng certain design configuration features intended to prectude a fue l tank i gn i tion source for the operat io nal life o f the airplane, GDCCLs are mandatory and cannot be changed or deleted without the approval of the Seattle 

### FAA AGO or applicable regulatory agency. A c riti ca l fuel tank ignition source prevent ion feature may exist in the fuel system and its related installation or in systems that, if a fai l ure condition were to develop, cou ld interact with the fuel system in such 

### a way that an unsafe condition would deve lop without this l i mitation. Strict adherence to configuration, methods, techniques , and practices 

### as prescribed is required to ensure compliance with the GOGGL. Any use of parts, methods, techniques or practices not contai ned in the app l i cab l e COCCl must be approved by the Seattle FAA ACO o r applicable regulatory agency . AUs identify inspection tasks related to fue l tank ig nit io n source prevention which must be done to maintain the de si gn level of safety for the operational life of the ai rpl ane. These AUs are manda tory and cannot be changed or deleted without the approval of the S ea ttle FAA ACO or appl icab le reg ulatory age ncy. Strict adherence to methods, techniques and practices as prescribed is required to ensure the All is complied with. Any use of methods. tec hniques or practices not co nta ine d in these Alis must be approved by the Seattle FAA ACO or applicabl e regula tory agency. USE OF ALTERNATE T OOLS 

### For AWlslCDCG Ls wh i ch require use of certain tools, use o f alternate tools requires prior approval from the Seattle 

### FAA AGO.

0621U400 -9 DEC 2006 R 1 BOE ING PROPR I ET ARY - Copyright (c) - Unpub l ished Wo rk - See title page for details Page 9 .0 -20

## !li-DDE'NG 

## 747-400 MAINTENANCE PLANNING DATA DEVIATIONS FROM CMM OR AMM INSTRUCTIONS Any devia tion from the Boeing published AMM Instructions or supplier CMM referenced within this section require prior approva l from the Seattle 

### FMACO . EXCEPTIONAL SHORT-TERM EXTENSIONS FOR AWLs Since AWL intervals are based on estimations of the probability of an event, an except io nal short-term extension for each fue l sys tem AW L lis led i n Ihis document may be made without je o pardi zing safely. The lo cal regulatory authorily (e.g. a Princi pal Maintenance I nspector) must con c u r with any exceptiona l short-term extens ions before they take place us i ng procedures establishe d with the local regu latory authority in the operators' manua l s. The "exceptional shorl-term extension" process is applicable to AWL intervals. It should not be confused with the ope r ator's "shari-te rm escalation " program for normal maintenance tas ks described in the operators' manuals and in the Flight Standards Handbook 8300.10 . T he Seattle FAA AGO has accepted that these exceptiona l short-term extensions may be granted without consultation w ith that office: 1. The term "exceptional short-term extension" is defined as an increase in a fuel system AWL in terval that may be needed to cover an unc ontrollable or unexpected situation. All AWLs l isted in this section h ave been approve d with an exceptional short-te rm extension of 30 days. 

### 2. Repeated use of extensions, e ither on the sa me airp lane or on si m ilar airplanes in an operator's fleet, should not be used as a substitute for good management practices. Exceptional short-term extensions must not be us ed for fleet AWL extens ions . After a f ue l system AW L has experienced an exceptiona l shorl-term extension, the AWL interval w i l l revert back to it s interval liste d in t his document. The Seattle FAA ACO must approv e, prior to its use, any desi red extension not explicitly listed above . Thi s except ional short-term extension l isted above app l ies to ai r l i nes that fa ll under the Uni ted States FAA ju r isdiction only . Ope rators w ho are not under the U.S. FAA jurisd i ction shou ld obtain interval extension approvals from their local regulatory agency. AWL REVISION PROCESS In the eve nt tha t an AWL is revised, Boeing w ill document it by preparing a revision to this document that will be approved by the Seattle FAA ACO. This revision will then be forwarded to all 747-400 operators and the Seattle FAA ACO offices.
D621 U400 -9 OCT 2007 BOE I NG PROPRIETARY - Copyright (c) - U np ublished Work - See ti tle page for details Page 9.0-21

## fl-SDE'NG 

## 747-400 MAINTENANCE PLANNING DATA C. PAGE FORMAT: FUEL SYSTEMS AIRWORTHINESS LIMITATION S COLUMN AWL N U MBER TASK
INTERVAL APPLICABIL ITY DESCRIPT IO N



### OCT 2007 EXP LANATION Each task is given a unique AWL Item Number. The first and second digits are the AlA Chapter N umber. All 

# = Airwo rth iness limitati on I nstructio n . These tasks are inspecti ons th at shou ld be performed al the lis ted i n terva ls. 

### COCe l = 

### Critica l Design Configurat ion Controllimilalions Ta sk frequencies are specified in ter ms of a usage paramete r such as flight hours, cycles 

### or calendar time. Airplane model app li cab ility. Descript io n of the task to be performe d or cri t ical design configurations aspe cts that cannot 

### be c hang ed without violat i ng the i nten t of the design .

0621 U400-9 BOEING PROPRIETARY - Copyright (c) • Unpublished Work - See title page for deta i ls Page 9.0-22

## rp...a0E'NG 

## 747-400 MAINTENANCE PLANNING DATA D. AIRWORTHINESS LIMITATIONS - FUEL SYSTEMS The following lisl of AWLs contains FAA approved scheduled inspections for operators to incorporate i nto their maintenance program for this type design to meet the new standards and assumptions i ntroduced by 

### § 25.981 and Special Federal Aviation Regulation (SFAR) No . 88. SFAR 88 - Fue l Tank System Faull Tolerance Evaluation Requirements and Title 14 Code of Federal Regulations 

### § 25.981 - Fuel Tank Igni\ion Prevention requ ire maintenance instructions, and controllirnilations for certain f ue l tank c r itical design configurat i ons. 

### Paragraph 2(a) of SFAR 88 and Paragraph (b) of the new standard introduced by 

### § 25.981 require certain design approval holders of Type Certificates (TCs) and Supp lemental Type Certificates (STCs) of large transport airplanes to conduct a safety review of the fuel tank systems. The purpose of the safety review is to identify design features that may result in development of ignition sources in the f uel tank systems. Fuel System Airworthiness Limitation Items (AWls) are mandatory maintenance actions requ ired to ensure that unsafe conditions ident ified by the safety rev iew do not occur or are not introduced into the fue l tank system as 

### a result of configuration changes, repairs, alte ra tions, or deficiencies in the maintenance program throughout the operational l ife of the airplane.

0621 U400-9 

### NOV 2007 BOE ING PROPRIETARY - Copyrig ht (c) - Unpublished Work - See litle page for details Page 9.0-23

## rti- HDE'NG 

## 747 -4 00 MA INTEN A N C E P LA N N ING DAT A

AW L Num b er 

### Ta s k Int erv a l 

### App li c ability De sc r iption

28-AWL-Ol ALI 

### 12 YRS ALL External Wires Over Center Fuel Tank Concern: Potential for chafing and arcing through center Fue l T ank Upper Panel. Perform a detai l ed inspection of the bundles rouled on main deck over the center fuel tank and under the main deck floor boards per Boeing AMM 28-11-00 to detect damaged or loose clamps, wire chafing, and thai the wire bundle is not in contact with the surface of the cente r fuel lank . If discrepancies are found, ensure wires are installed per the applicable wire installation drawings and repair per the Boeing Standard Wiring Practices Manua l 06-54446 . 28-AWL-02 

### CDCel N/A ALL External Wires Over Center Fuel Tank Concern: Potentia l for wire chafing and arcing to center Fuel Tank Upper Panel. If any maintenance is performed in the area under the main deck noor boards and over the center fue l tank, verify the following: 

### 1. Ma i nta i n the existing w i re bundle routing and clamping . 

### 2. Installation of any new w i re bund l es must be per Boeing Standard W i ring Practices Manua l 06-54446 . 

### 3. A ll wire bundles over the center fuel tank are i nspected per 28-AWL-01 .

0621 U400-9 DEC 2009 BOEING PROPRIE T ARY - Copyright (c) - Unpublished Work - See title page for deta i ls Page 9.0-24

## YJ--DDEfNG 

## 747 -400 M A INTE NA N C E PLA NNIN G DATA A WL Num ber T ask Inte rva l 

### App li cab ili ty Descripti o n



### 28-AWl-03 ALI 12 YRS ALL Fuel Quantity Indicating System (FQ I S) - Out Of Tank Wiring Lightning Shield to Ground Terminat i on Concern: Potential for Lightning induced voltages on the FQrS wiring to enter th e fuel tank. Perform the follow i ng inspection to ensure the functiona l integrity of the FQIS wiring shield to ground termination per Boeing AMM 5-55-54: 1. Visually inspect all connectors at the location being tested to ensure they are tight. Th is i ncludes connector plugs and backshells. 

### 2. Us e a Loop Resistance Tesler, 

### PIN 906-10246-2 or 906-10246 -3, to measure and ver ify the res istance of the shield to ground termination for the following items: Th e follow in g app lie s t o a ll 74 7-400 except 747 -4 0 0 Large C arg o Freig ht er (LCF) Maj o r Desi gn Ch a n ge: The loop resistance shall not exceed 40 mi!l iohms for Connector X01021 and the wire bundle supplier part number CN1036-151(Wing LE UH Densitometer Main 1). The loop resistance shall not exceed 40 milliohms for Connector X01025 and the wire bund l e supplier part number CN1 036-152 (Wing LE l/H Dens itometer Main 2). The loop resistance sha l l not exceed 40 milliohms fo r Connector X01031 and the wire bund l e supplier part number CN1036-152 or -172 (Wing LE RlH Densitometer Main 3). The lo op resistance shall not exceed 40 milliohms for Connector X01037 and the wire bund l e supplier part number CN1 036-151 or -171 (Wing LE RlH Densitometer Main 4). The lo op resistance shall not exceed 40 milliohms for Connector X01019 and the wire bund l e supplier part number CN1 036-116 or -316 (Wing L E UH Main Tank 1). The loop resistance shall not exceed 40 mi lliohms for Connector X01023 and t he wire bund l e supplie r part number CN1 036-117 or -317 (Wing L E UH Main Tank 2). The loop resistance shall not exceed 40 milliohms for Connector X01030 and the wire bund l e supplier part number CN1036-117, -317 or -327 (Wing LE R/H Main Tank 3). The loop resistance shall not exceed 40 milliohms for Connector X01036 and the wi re bundle supplier part number CN1036-116 . -316 or -3 26 (Wing 

### lE R/H Main Tank4) . The loop resistance shall not exceed 40 mi lliohms for Connector X01028 and t he wire bund l e supplier part number CN1036-111 or -113 (Wing LE U H Main 2 Single Point Sensor) . The loop resistance shall not exceed 40 milliohms for Co n nector X01034 and t he wi re bundle supplier part number CN1 036-111 (Wing LE R/H Main 3 S i ngle Point Sensor). (Continued on next page) 0621 U400-9 DEC 2009 BOEING PROPRIETARY - Copyrigh t (c) - Unpublished Work - See title page for details Page 9.0-25

# ((;J .. J IDE'NG 

## 747-40 0 MA IN TE NA N CE PLA NNIN G DAT A AWL N um ber Tas k I nt erva l 

### Ap p licab il ity Desc ri p ti o n

28-AWL-03 ALI 12 YRS ALL Fuel Quantity I ndicating System (FOIS) - Out Of Tank W i r i ng Lightning Shield to (Continued) Ground Termination (Continued) The l oop resistance shall not exceed 40 milliohms for Connector X0100B and the wire bund l e suppl i er part number 

### eN 1 036-118, -318 or -518 (Center Wing Tank) . The l oop res istance shall not exceed 40 milliohms for Connector X010 1 2 and the wire bund l e suppl i er part number CN1036-112 or -312 (Center Tank Sing l e Point Sensor). The l oop res istance shall not exceed 40 milliohms for Connector X01009 and the wire bundle suppl i er part number CN1036-153 or -353 (Center Tank Densitometer). The l oop res istance shall no t exceed 40 milliohms for Connector X01040 and the wire bundle supplier part number CN1036-115, ·315 or -325 (Wing LE UH Reserve Tank 2). The loop resistance shall not exceed 40 milliohms for Connector X01042 and the wire bund!e supp!ier part number CN1036-115. ·315 or 325 (Wi ng LE RfH Reserve Tank 3) . The !oop res istance sha!! not exceed 61 milliohms for Connector X01015 and the wire bundle supplier part number CN1036-154, -354 or -554 (Horizontal Stab Densitometer, if installed). The loop res istance shall not exceed 59 milliohms for Connector X01014 and the wire bund l e supplie r part number CN1036 - 119 . - 319. -519 or -719 (Horizonta l Stab Fue l Tank, if installed). T he fo ll ow in g ap pl ie s o nl y t o 747-4 00 Large Ca rgo Freig ht er ( l C F) Maj o r D esign Ch ange: The loop resistance sha l l not exceed 24 mill i ohms for Connector X01021 and the wire bundle supp l ier part number CN1036-351{Wing LE Lf H Densitometer Main 1) . The loop resistance shall not exceed 22 mill i ohms for Connector X01025 and the wire bundle supplier part number CN1036 -352 (Wing LE LfH Densitometer Main 2) . The loop resistance shall not exceed 22 milliohms for Connector X01Q31 and the wire bundle supplier part number CN1036-355 (W i ng LE RfH Dens itometer Main 3). The loop res istance shall not exceed 24 milliohms for Connector X01037 and the wire bundle supplier part number CN1036-356 (Wing LE RfH Dens itometer Main 4) . The loop resistance shall not exceed 17 milliohms for Connector X01019 and t h e w i re bundle supp l ier part number CN1036-S16 (Wing LE LlH Main Tank 1). The loop resistance shall not exceed 15 milliohms for Connector X01023 and the wire bundle supplier part number CN1036-517 (Wing LE LlH Main Tank 2). (Continued on next page)
D621U400-9 DEC 2009 BOE I NG PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-26

# f)...J!i'DEfNG 

## 747-400 MAINTEN A NCE PLANNING DATA AWL Number Ta sk Interval 

### Applicability De sc ri ptio n



### 28-AWl-03 ALI 

### 1 2 YRS ALL Fue l Quan ti ty Indicati ng System (FOtS) - Out Of Tank W i ri ng lightn i ng Shield to (Continued) Ground Termination (Cont i nued) The l oop resistance shall not exceed 29 mi ll i ohms for Connector X0100B and the wire bundle suppl i er part number CN1036-718 (Center W i ng Tank ) . The loop resistance shall not exceed 15 mi ll iohms for Connector XQ1030 and the wire bundle supplier part number CN1036-522 (Wing LE RlH Main Tank 3) . 

### The loop resistance shall not exceed 1 7 mi ll iohms for Connector X01036 and the wire b u ndle suppl i er part number CN1036-S21 (Wing LE RlH Main Tank 4) . T h e loop resistance shan not exceed 34 miHiohms for Connector XQ 1 028 and the w i re bund l e suppl ier part number CN1036-31 1 (Wing l E 

### UH Main 2 Sing l e Point Sensor). The loop resistance shall not exceed 34 milliohms for Connector X01034 and the wire bund l e supplier part number CN1036 · 313 (Wing lE R/H Main 3 S i ngle Point Sensor) . The loop resistance shall not exceed 27 milliohms for Connector X0 1 009 and the wire bund l e supplier part number CN1036-557 (Center Tank Densitometer) . The loop resistance shall not exceed 28 milliohms for Connector X01040 and the wire bundle supplier part number CN1036-515 (W i ng lE 

### LlH Reserve Tank 2). T he l oop res i stance shal l not exceed 28 milliohms for Connector X01042 and the wire bund l e supplier part number CN1036 · 520 (Wing lE RlH Reserve Tank 3). 28-AWl-04 CDCC l NfA ALL FQIS - Out Of Tank Wiring Lightning Sh i eld to Ground Termina ti on Concern: Potential fo r l i ghtning i nduced voltages on the FQ I S w i ring to enter the fuel tank. If any mainte nance is performed on the FQ I S wire bundle i n the un- p ressur i zed zone at the spar pressure seal , verify the follow i ng : 1. Veri fy presence of shie lded wiring. 2. Verify the shield ground is term i nated per Boeing SWPM 20-10 - 15 . 

### 3. The insta ll ation is checked per 28-AWl -03 .

D621U400-9 DEC 2009 BOE I NG PROPRIETARY - Copyright (c) - Unpub l ished Work - See title page for details Page 9.0-27

## r;;J.-a DEING 

## 747-400 MA INTEN A N C E PLA NNING DATA AWL Number Task 

### I nterval App l icab i lity Desc r iptio n

28 -AWL-05 

### COCeL N/ A 

### 747 -400 ai rpla ne s Lightn i ng Protect io n - Hydraulic Line Fuel Tank P ene tration Line Numbers 1 272 Concern: Pot e nti a l for arcing or sparking in si d e th e tan k at the in terface b etwee n the bulkhead 

### and o n ; or airpla nes that fitling and th e spa r during a ligh tning strike event. 

### ha ve in co rp ora ted The follow ing des ig n feature s must be maintai n ed per Boeing AMM 29-11-22 . If the bul khead

Service Bulletin fittin g is re m oved and repla ced: 

### 747
-29A2 1 04. 1. Veri fy e l ectrica l fay surface bond between t he h ydra u lic fi tting fl a nge a nd th e s par must b e 0 .001 o hm s or l ess. 

### 2. Insl a ll fil let seal on th e fi tt i ng to the ta n k wall i n te rface ou tsi de the tank. 3. I nstall f ull bodied fille t s ea l encap su la ting the fi lt ing to the tank wall i n terface i n s ide the tank. 4. Verify an ele ctro stat ic bonding jumper exists b etween the structure and th e Hydraulic Heat Exch a nger in sid e the tank . 

### S . Verify electrical bond from structure to the Hydraul i c Heat Exchang er ins i de th e tank is 0 .005 ohms or l ess. 28-AWL-06 CDC C L N / A A LL AC Pump a n d D C Pump Ma i ntenan ce Concern : Potent i a l for main te nance erro r du ri ng pump ove rhau l. Fue l pu mp de si gns con ta i n ignition source prevention me ans (i .e. , flame a rresto r, thermal f uses , m ate r ials, l eadwire retention means, etc . ) that must be ma i nta i ne d if pu mp is ove rha ul ed. Repair and overhaul of Fuel Pumps must be pe r th e c urrent manufacturer Co m po nent Maintenance Manual (CMM) Numbe rs 28-22 - 07 Revi sio n Number 1, 28 - 31 - 03 Revi sio n Number 3, 28 -26- 12 Revision Number 0 , 28 -26 - 14 Revision Numbe r 0 , 28 - 20-02 Revi si on Number 

### 9 , or late r revis ion s of these CMM s th at have been approved by th e Sea tt le FAA ACO . 28-AWL-0 7 CDCCl N/A ALL lightning , Fa ult C urrent o r H ot Short Protection - Fue l Tank Pe netrat ions Concern: Potential for arci ng or sparking i ns i de the tank at 

### a conduct ive metal - to -g ro und st ru ctu re in terlace as a result of electrica l fau lt curren ts or ligh t ni ng strike eve nts du e to ins uffici ent b ond ing within th e g ro u nd elec tr i cal path . Addition of a n y new penetrations to the fuel tan ks (s uch as add ing a brac ke t or bulkhead fitti ng or equipm e nt) o r change to the design features of th e existing equ i pment penetrat i o n s (such as fue l measuring sticks. s ump d rain va lves, fue l ing man ifo l d, fuel temp e rature sensor , and motor operated fue l shutoff valve adaptor plate) re quire s a pproval by the Seattl e FAA ACO. D621U400-g D EC 2009 BO EING PROP R I ETARY - Co pyri ght (c) - Unpub l i sh ed Work - See title page fo r deta i ls Page 9 .0-28

## I{J- DDE'NG 

## 74 7-400 MA INTEN A N C E PLA NNING DA T

A AW L Numb e r Task Inte rva l 

### A p p li ca bility Des cri pt i on

28-AWL-08 

### COCCl N fA All Fuel Quantity Indicating System (FOIS) - Oul Of Tank Wiring I nsta l lation Separation Requirement Concern: Potential for hot shorts and EM I induced voltages on t he FQIS wiring outside of the lank to enter the fuel tank . Routing and installation of any new wiring must use wire types BMS 13 -48 , BMS 13-60 or 8MS 13 58, and not be wi th in a 2-inch rad ius of the FQIS wiring . When a single clamp fails, a separation greater than 

### Y. inch must be maintained from FQIS wiring. 28-AWL -09 

### COCe l NfA Al l Center Wing Tank Fuel i ng Valve-Fault Current Bond Concern: Pote ntial for arc i ng or filament heating i nside the center wing fuel tank . T he following design features must be ma i ntained per Boe i ng AMM 28-21 -1 3 when the center w i ng tank fue l ing valve is removed and replaced: 

### 1. Bonding jumper between the valve body and structure inside the tank. 2 . Meas u re the resistance from the valv e body to the adjacent structure. Res istance must be 0 .0 10 ohms ( 1 0 mi lliohms) 

### or l ess . T he following design features must be maintained per Boeing AMM 28-21 -02 when the center wing tank refuel va lve control un it is removed and replaced: 

### 1. The bonding resistance fro m the exposed threads on t he valve unit mounting stud (one location). to the refue l valve contro l unit AND the bonding resistance from the exposed threads on the valve unit mounting stud (one loca tion). to structure (spa r) must not be mo re than 0.010 ohms (10 milliohms). T h is installation is chec ked per 28 -AW L -10 . 28 -AWL-10 ALI 1 2 YRS 

### ALL Center W i ng Tank Fuel i ng Valve- Fault Current Bond Concern: Potential for arc i ng or filament heating ins i de t he center wing fue l tank . Th is installation includes the fol l owi ng checks per Boe ing AMM 28-21-13: 

### 1. The bonding resistance from the exposed threads on the valve unit mounti ng stud (one location). to the refuel valve control unit AND the bonding resistance from the exposed threads on the valve un it moun ting stud (one location ). to structure (spar) must not be more t han 0 .0 1 0 ohms (10 m i ll iohms) .

0621 U400-9 D E C 2009 BOE I NG PROPRIE TARY - Copyright (c) - Unpublished Work - See t itle page for deta i ls Page 9.0-29

## fi- BDE'N& 

## 747-400 MA I NTENANCE PLANN IN G DATA AWL Number 

### Ta s k 

### Interval Appl ica bili ty Desc r ip t ion

28-AW L-11 

### eOCe l NfA ALL 

### Fue l Quanti ty Indicating System (FQ I S) - Fu e l Quantity Processo r Unit (FQPU) Repair Concern : Potentia l for mainten ance e rror durin g FQ PU repair. The FQPU is de signe d to limit 

### the levels of e ne rg y, voltage, current , and power allowed w ithin the FQIS ci rcu it to i nt rins ically safe levels in order to p reclu de the potentia l of an ignition source with in any fuel tan k. 

# I Repair and overhaul of FQIS processo r units m u st be per Goodrich (V8930S) CMM 28 -41-62 

### Revision 4 , or later rev isio ns o f this CMM tha t have b ee n approved by the Seatt le FAA ACO. 28-AWL-12 

### eOCeL NfA ALL Si ng le Poin t Se n so r (S P S) Conlrol Card R epa ir Concern: Po tential fo r main tena nce error du ri ng SPS con trol card repa i r. The SPS con tro l card is designed to limit the levels of energy, vo lta ge , cu rre n t, and powe r allowed w ithin the SPS c i rcuit to int rin sically sa fe leve ls in order to preclude the potent i a l of a n ignition sou rce wit hin any f uel ta nk. Repair and overhau l of Single Point Sen so r Control Ca rd must be per Ragen Data Systems (V58880) CMM 28 -2 1-02 Revis io n 

### 2. or late r revisions of this CMM that have been approved by the Seattle FAA ACO. No te: Ragen Da ta Systems i s now Vi b ro-Meter In c. 28 -AWL-1 3 COCC l NfA All 747-400 with HST Re mote E l ect ron i c Unit ( R EU) Repa i r Concern: P ote nt ia l for maintenance erro r du r i ng REU repa i r. The REU is designed to l i mit the levels of energy , vo ltage. curren t , an d power allowed w it hin the REU circuit to i ntrinsically safe levels i n order to prec l ude t he potentia l of an ig ni ti on source within any fuel tank . 

# I Repair and ov e rh a ul of REU must be per Goodric h (V89305) 

### CMM 28-41 -63 Rev isio n 4, or later rev ision s of thi s C MM th at have been approved by the Seattle FAA ACO . 28 -AWL- 1 4 COCel NfA ALL Fue l Quantity Indi cating System (FaIS) - Repair of I n-Tan k H ardware (Tank Units, Densitometers , and Compensators) Concern : Poten ti al fo r m ainte nance e rror d uri n g repai r of i n-tank ha rdwa re (ta n k units , compe n satOfs and densilo m eters). Arc gaps may develop that cou ld resu lt i n an i g n i l ion sou rce i n side the fuel lank . 

# I Repair and ove rh aul of FQIS tank units, com p ensato rs , and dens itome ters must be per Goodr ic h (V8930S) 

### CMM 28-40 - 55 Rev ision 6. 28 - 40 - 56 Revis ion 4, 28-40-59 Rev is io n 

### E , or later revis io ns of th ese CM M s that have been approve d by the Seattle FAA A CO.
0621U400-9 O EC 2009 BOEING PR OPRIETARY - Copy ri g ht (c) - Un publ i shed Work - See Iitl e page for de ta i l s Page 9.0-30

## ([i.J IDE'NG 

## 747-400 MAINTENANCE PLANNING DAT A AWL Numb er 

### Task Interval 

### Applicabi li ty 

### Description**28~AWl 15**  

### COCel NfA ALL Fuel Quantity Indicating System (FOIS) - Repair of I n -Ta nk Wire Harness 

### Concern: Potential for error during repa i r or rep lacement of in-tank wire harness. Arc gaps may develop that could result in an ignition source inside the fuel lank . Repair and overhaul of FQIS in-tank w i re harness must be per SWPM 20-14- 1 2 . Installation of FQ I S in-tank w i re harness must be per Boe i ng AMM 28-41-09. Verify the fo l lowing when installing spar penetrations per Boeing AMM 28-41-09 : 1. 

### A new 

### O-ring is installed i n the groove of the FOIS wire bund le connectors. 2 . The spar connector and the mating surface a re clean 3. The connector jamnut is lightened to a torque of 200-250 inch-pounds. Verify the following when i nstalling the app l icable a ir plane wire bund l e connector to the in-tank w i re harness spar penetratio n : 1. The coupl i ng connector is tightened to a torque of 60-70 i nch-pounds . 

### 2 . The between the bonding j umper on the airplane wire bundle and the airplane spar structure is not more than 0.0005 ohm (0 .5 m illiohm s) for HST tank and 0.010 ohm (10 m i lliohms) for all other tanks. 28-AWL- 16 COCCl NfA ALL Fuel Tank Access Doors Configuration Concern : Potentia l for arcin g or sparking i nside the tank at t he i nterface between the door and the tank st ructure as a result of a di rect strike or conducting currents through the w in g skin. The following must be mainta i ned during fue l lank access door i nstallation (Boeing AMM 28-11-02,28-11 - 03): NOT E: Not app li cable to center w ing tank access door. 1. Verify presence of a molded r ub ber seal pos itioned around the outermost periphery of the door that mates with the wing sk i n inside the tank. 

### 2 . Apply Corrosion Inhibit in g Compound (CIC) 10 both sides of the kn itte d a lu minum mesh gasket, and 

### 3 . In sta ll the kni tted aluminum mesh gas ke t between the ou ts ide face of the doo r and the wi ng skin to estab l ish the electrica l conductiv ity betveen the access door and the wing skin .
0621 U400-9 

### DEC 2009 BOEING PROPR IETA RY - Copyright (c) - Unpub l is hed Wo r k - See title page for details Page 9.0-31

# ~DE'NG 747-400 MA INTEN ANC E PLANN I NG DATA AWL Numbe r Task 

### Int erva l 

### App licabi lity Desc riptio n

28 -AWL-17 

### ALI 18 mon ths 

### ALL Fault Current Detector for CWT and I nboa rd Main Tank Override/Jellison Pumps and HST Transfer Fuel Pumps Concern: Potentia l burn through of pump case in the even t of electrica l ground fau l t in f ue l pumps . Verify the following per Boeing AMM 28 -3 1-14 for CWT and inboard m ain tank pu m ps, 28 - 17 - 14 fo r H ST tra nsfer pumps. The ground fau lt detecto r for each pump is working properly. Use Fau lt Current Detector Test as specified in AMM . 28-AWL- 18 

### COCel NIA ALL F aul l Current Detectors Repa ir C M M Concern: Poten tial for ma i nten ance error duri ng Fault Current Detecto r repa ir. Faull c urrent may be i ntroduced to pumps creating an i gn iti on source. R epair and ove rh aul of Fau lt Current Detectors must be per Autronics (V03972) CMM 28-31-22 Revis ion 4, or later revisions of this GMM that have been approved by the Seattle FAA ACO. 28-AWL-19 GD GGL 

### NIA ALL Res etting T ripped Fuel Pump Circuit Breakers or Ground Faul t Inte rrupters (GFls) Concern : Potential fo r arcing or sparking ins ide the tank between fuel pumps and fue l pump hous i ngs and ou tside I he tank between pump wiring and stru ctu re in flam m ab i lity l eakage zones . Verify it is sa fe to reset the ci rcuit breaker( s) o r GFI{s) by fo ll owing the appl i cable OE M troubl esh ooting procedures. Fault(s) that resu lted in circu it breaker o r GFI{s) re lay trip must be isolated and corrected prior to reset.

0621 U4 00-9 DEC 2009 BOEING PROPRIETARY - Copyrigh t (c) - Unpublished Work - See title page for details Page 9 . 0-32

# f:5-HOE 'N& 

## 747-400 MAINTENANCE PLANNING DATA AWL Number Task 

### Interval Applicability Description

28 -AWL-20 

### COCCl N/A 747-400 airplane s Lightni n g Protect i o n - Engine Fuel Feed Line Fuel T an k Penetration 

### line Numbers 1 28 4 Concern: Potential for arcing. s parking or fi lament h ea ling inside th e lank at the interface and on; or a i rplanes modified between the bulkhead fitling an d the spar during a li ghtn i ng strike event. per Service Bulletin Th e following must be maintained per Boeing AMM 28-22-07 if the bulkhead fitting or attached

747-28A2239 

### or tubing are removed and replaced (Nole : Each of the following is only appl i cable if the subject

747- 28A2245. area has been distu rbed): Ve r ify e l ectri ca l fay surface bond between the bulkhead fitting and the fronl spar stru cture inside the tank m ust be 

### 0.0005 ohms 

### (0.5 milliohms) or l ess . Install full-bodied fillet seal encapsulating the bulkhead fitting to the tank wa ll i nterface ins i de t he tank . Install full-bodied fi llet seal encapsulat i ng the firs t co u p l i ng i nterface i ns id e the tank . Verify an electros t a tic bonding j umper presence between the st ructure and the fi rst t ube mating with the bu l khead fitting i ns ide the tank. Verify the electrical bond fro m structure to first tube mati ng with t he bulkhead fitting is 

### 0 .010 ohm 

### ( 1 0 milliohms) or l ess . 28-AWL-2 1 Reserved for fu ture S FA R 88 AWL. 

### I ,

D621U400-9 DEC 2009 

### BOEING PROPRIET ARY - Copyright (c) - Unpublished Work - See title page for de tails Page 9.0-33

# ~OE'N& 747-400 MAINTENANCE PLANN I NG DATA AWL Number Task Interval 

### App l icabi l ity 

### Description



### 28·AWl· 22 COCC l NfA All AC Fuel Pump Fau lt Current Bonding Path Concern: Pote ntial for fault current path through the pump hou s ing to structure inside the tank. El ectrical faults inlernal to the fuel pump motor i mpeller are by 

### design routed throu g h the motor impeller assembly to the bonding jumpers on the front face o f th e molor i mpeller assembly to stru ctu re outs ide the tank. The bonding j umpers ensure thai faul t c u r rents are co nducted to structure o utside the tank unti l the circu it breaker andfor GF I has had ti me 1 0 re move powe r 

### from the pump. 

### The fo llow in g features must be m a i nta i ned du ring pump rep l acement p er Boeing AMM 

### 28 · 22 · 03 : For H yd ro-Ake Pu m ps: 

## I 1. 

### The p rese nce of two bond in g j u mpers. 

### 2 . The m otor impeller bo ndi ng res istan ce across the jumpers to structu re for Center ta nk is not more th an 0. 0002 ohms (0.2 m ill ioh m s). Th e mo l o r i mpelle r bo nd ing resistan ce across the ju m p ers to structure for h o ri zo nta l stabi lizer tank pumps and m ain tank boost pumps is n ot more than 

### 0.0004 ohms (0 . 4 mi ltiohms). For FR - H ITEMP Pumps ; 

## I 1 . 

### Th e presence of one bond i ng jumper. 

### 2 . The motor impeller bonding resistance acro ss the jump e rs to struc tu re for Center tank is not more than 0.0002 ohms (0 .2 m i lliohms). 

### 3 . Th e mo to r i mpeller bonding resistance across the jumpers to stru cture for main tan k boost pumps is not more than 0.0005 ohms 

### (O.S milli ohms).

D621U400-9 

### DEC 2009 BOEING PROPRIETARY · Co py righ t (c) - Unpubli s hed Work - See title page for detai l s Page 9.0-34

# rtJ.- BOEING 

## 747-400 MAINTENANCE PLANNING DA T

A AWL Numb e r Task 

### I nterval 

### Applicability Description



### 28-AWL-23 CDCCL 

### N/A 747 - 400 airp lanes Fuel Quantity Indicating System (FO tS) - I nstallation of Cente r and HST Fuel Tan k Hot Short Line Numbers 1368 Protector (HSP) and on; Concern: Potential for wire to wire hot short voltages on the center lank fuel quan t ity or a i rp la nes that densitometer wiring to enter the fuel tank. This is applicable to airplanes with opt ional have incorporated densitometer insta ll ed.

Service Bulletin 747-28A2266 and Th e FQtS H SP is designed to prevent wire to w i re external hot short voltages from entering t he

(i f app l icable) fu el lank where 

### it may ca use an igni t ion . 747-28A2267. Th e following features mus t be main t a i ned d u ring rep lacement o f the HSP per Boeing AMM 28 · 41·2 4: 1. Ve rify the bonding ju m pe rs are insta lled per AMM task . 

### 2. Veri fy the bon ds fro m the HSP to stiffeners whe re the bondi n g j umpers are term i nate d are equal to o r less than 0.0025 ohms (2. 5 milliohms). 3. A new unit must be used. The Hot Short Protector unit is not repairable. 28·AWL·24 

### All 1 YR 747·400 airplanes Horizontal Stabilizer Fuel Boost Pump Automatic Shutoff System ( I f Installed) Line Numbers 1343 Conce rn : Dry running the hor izontal stabilizer tank fuel pumps has the potential fo r single

and on wi th HST installed; fai l ure ignition sou rces developing at the pump inlet due to ei th er frictional heat i ng or sparking or airplanes modified as a resu lt of FOD contacting the pump rota t ing e l ements, rotating ele m ents con tacting per Service Bulletin stationa ry parts, o r hot journa l bearings due to bearing contamination or failure. 747·28A2262. The automatic shutoff system is insta lled and designed to l imi t cont inu ous dry running cond ition to 15 seconds. Th e following te st is required in order to protect aga ins t late nt faults : Fun ctionally ch eck the horizontal stabilizer tank fuel boos t pu mp automatic shutoff system per Boeing AMM 28 · 17·00.

D621U400·9 DEC 2009 BOEING PROPRIETARY· Copyright (c) - Unpublished Work - See t itle page for details Page 9.0-35

# ~OE'NG 747 -400 MAINTENANCE PLANNING DATA AWL Numb e r Ta s k 

### Interval Applicability Description

28·AWL·25 COCC L NA 747-400 ai rplanes Reserve Tank Fueling Valve- Indu ced Lightning Protection Bond 

### line Numbers 1378 Concern: Potential fo r a rcing or filament hea tin g in side th e center 

### left/Righ i wing Reserve and on; 

### or airplanes that fu e l tank. 

### have incorporated The following design fea tures must be maintained per Boeing AMM 28-2 1-02 when the reserve

Service Bulleti n tank fueling valve cont roller is removed and replac ed: 

### 747-28A2291 . 1 . Two bonding jumpers between the valve controller and structure ou tside the tank. 

### 2. The bonding resistance from the mounting boll to structure (spar) must nol be more th an 0 .0015 ohms (1.5 milliohms). 28-AWL-2 6 A LI 1 Y R 747-400 a i rp lanes Main T ank 

### 2 and Ma in Tank 3 Override/J ettison Fue l Pump Uncommanded on System , 

### Line Numbers 1380 Concern : 

### Dry r unn ing the main 2 and ma in 3 tan k fuel overridefJettison pumps has the potential and on : 

### or airplanes tha t for s i ngle fa i l ure i gni tion so u rces developing at the pump i nlet d ue to ei th e r fri ction al healing o r have incorpo rated spa rk ing as a result o f FOD contacting the pump ro tating ele m en ts, rotating elements

Service Bulletin co ntacting stat ionary parts. or h ot jou rn al be a r i ngs due to bearing contam i nati on 

### or failu re . 747-28A2280 . Perform an operational lest of the ma i n 2 and main 3 ove rr ide/ jettison fuel p u mp uncommanded on system per Boeing AMM 28-31-00

D621U400-9 DEC 2009 BOEING PROPRIETARY - Copyright (c) - U npublished Work - See tiUe page for details Page 9.0-36

## !{ia0E'NC 747-400 MAINTENANCE PLANNING DATA AWL Number 

### Task Interval 

### Applicability Description

28-AWL-27 

### COCel 

## NA 747-400 airp lanes Fault Current Protect i on - Molor Operated Valve (MOV) Actuator Line Numbers 1382 Concern: Potential for arcing or spark i ng ins i de the fuel tank at a conductive metal-la-ground 

### and on; or airplanes modified structure interlace as a result of electri ca l fau lt currenl 

### event. per Service Bulletin The follow i ng design features must be maintained per Boeing AMMs: 747-28A2292 and 

### 28-14-21, 28
- 14-31, 28
- 14-41, 28-14-61 , 28-16-01, 28-16-04, 28-17
-01 , 28
-21-11, 28-22
-01,

747-28A2294. 28-22-02,28-25-02,28-31-04, and 28
- 31-05. I. If the MOV actuator is mounted to the spar w ith an adapter plate.

1. Maintain the following if the adapter plate is removed and replaced: a . Verify electrical fay surface bond resistance between the adapter plate and the spar is 0.0005 ohms 

### (O.S milliohms) or l ess. b. Install fay surface seal between the adapter plate and the spar outside the tank . c. Cap seal the four bolts that attach the adapter plate to the spar inside the tank and fillet sea l around the edge of the hole and on the stationary part of the adapter plate inside the lank. d . Install sealed e l ectrical fay surface bond and fay surface sea l between the serrated mating surfaces of the index pl ate and the adapter plate. e. Install sealed electri cal fay surface bond and fay surface sea l between the mating surfaces of the actuator and the index plate . 

### f. W ith the bonding jumper not installed. verify e l ectrical bonding resistance between the actuator mounti ng feet and the spar i s 

### 0.0025 ohms 

### (2 . 5 milliohms) or less . g. Pr i or to attachment of the bonding j umper to the actuator, verify electrical bonding resistance between the loose end of the bonding jumper and the spar is 0.0015 ohms (1.5 m i lliohms) or less. h. Attach the bonding j umper to the actuator bond i ng tab using a sealed e l ectrica l fay surface bond. (Continued on next page)

0621 U400-9 DEC 

### 2009 BOEING PROPRIETARY - Copyright (e) - Unpub l ished Work - See title page for details Page 9 . 0-37

## r{;-BOE'NG 

## 747-400 MAINTENANCE PLANNING DATA AW L Number Task I n terval 

### App l icability Descript i on

28-AWL-2 7 

### COCe l 

## NA 747 -400 airplan es 

### Fault Curre nt Protection - Motor Operated Valve (MOV) Actuator (co ntinu ed); Line Numbers 1382 2. M ain ta in the follo w i ng if the index plate is removed a nd replaced: 

### and on; or airplanes modified 

### a. In stall sealed electrical fay surface bond and fay su rface seal between the serra ted pe r Service Bullet i n mating s u rfaces of the index plate and the adapter plate . 747-2BA2292 and 

### b. In sta ll sealed e lect rical fay surface bond and fay surface sea l between the mat i ng

747-28A2294 . su rfaces of the actuator and the i ndex plate. c . With the bon d ing jumpe r not installed, verify elect r ical bond in g resistance between the actuator m o u nti ng fee l and the spar is 0.0025 oh m s (2.5 milliohms) or l ess. d . Prior to attach m ent of the bond i ng j umpe r to th e actuator, verify e l ectrica l b o ndin g res istance betwee n t he loose end of the bo nd ing j umper and the spar is 0 .001 5 ohms (1.5 mill io hms ) or less. e . Attach the bondi ng jumper to the actuato r bo nd i ng tab u sing a sealed e l eclrical fay surface bond. 3. M ai n tain the fo llowing If th e MOV actuator is removed and replaced : a. Ins tall seale d electrical fay su rface bond and fay surface seal b etween th e ma ti ng surfaces of the actuator and the i ndex pl ate. b. With the bonding jumper not installed , verify elec tri ca l bonding res istan ce between the actuator mounting feet and the spar is 0.0025 o h ms (2.5 m ill io hm s) or less. c. Prior to attac hm ent of the bonding j umper to th e actua to r, ve rify e l ectri cal bonding res istance between the loose end of the bond ing jumper a nd th e spa r is 0.0015 o hms (1.5 mi ll io hms) or less, d. Attach the bonding jumper to the actua to r bo nding tab usi ng a sealed e l ect rica l fay s urface bon d. (Cont inued on next page )

D 621 U4 00-9 

### DEC 20 09 BOE I N G PROPRIET A RY - Copy righ t (c) - Unpublished Wo rk - See title page for de tails Pag e 9. 0 -38

### rti-HOEfNG 

## 747-400 MAIN T ENANCE PLANNING DAT A AWL Numb e r Task 

### Interval Appli cabi l ity Descri pt i on

28-AWL· 27 

### COCe l NA 747- 4 00 ai rpl anes Fault Current Protection - Mo l or Operated Valve (MOV) Actuator (continued): Line Numbers 1382 I I. If th e MOV actuato r is mounted wit ho u t an adapter plate. and on; o r airp lanes modified 1. Maintain th e follow ing If t he MOV actuator is removed and rep l aced: 

### per Service Bulletin a . Install sealed electrical fay surface bond between the mating surfaces of the actuator 

### 747-28A2292 and

747-28A2294. 

### and structu re. b. With the b onding jumpe r not installed , verify electrical bonding resistance between the actuato r m ou n t ing feet a nd the spar is 0 .005 ohms (5 m i liiohms) or less. c . P r ior to attachment of the bon d ing jum per to the actuator, verify e l ectr i cal bonding resistance between the l oose end of the bonding ju mper and the spar is 

### 0 .00 1 5 ohms 

### (1.5 m illioh m s) or less , d. Attach th e bond ing j umper to the actu ator bond i ng tab u sing a sealed elect ri cal fay surface bond. 28·AWl - 28 ALI 

### 1 YR 747-400 airplanes Main Fuel T ank B oost Fuel Pump Ground Fault I nte rruption (G FI ) Con trol Relay System line Number 1394 Concern; GFt is installed to protect against burn·through of the pump housing, and to protect and on; or airp l anes that against overheating o f the pump cav ity andlor auto ignition temperature on the outside surface have incorporated of th e housin9, due to electrica l arcing.

SeNice Bulletin Perform an Operational Test of all Main F uel Tank Boost Pumps GF I Contro l relays per Boeing 747·28A2261. AMM 28-22 - 00. 28-AWL-29 ALI 

### 1 YR 747·400 ai rplanes Center Wing Tank E l ectri ca l Scavenge Pump Ground Fault I nte rrupt i on (GF t) Contro l Relay with E l ectric Center System Wing Tank Scavenge Concern; GF I is insta lled to protect aga i nst burn·through of th e pump housing, and to protect

Systems, airp l anes prior to line Number against overheating of th e pump cavity andlor au to ignition temperature on the outside surface 972 that have of the housing , due to electrical arC i ng . incorporated Perfo rm an Operational Test of all center wing tank scavenge system GFI Control relays pe r Service Bulletin Boeing AMM 28-22-00 . 747·28A2261 .

0621 U400 - 9 DEC 2009 BOEING PROPR IETAR Y· Copyright (c) - Unpublished Work· See title page for details Page 9.0·39

# !tJ.- BOE'NG 

## 747-400 MAIN TE NANCE PLANNING DATA AWL Number 

## Ta s k Interval 

### Applicability Description



### 28·AWL· 30 

### COCel 

## NA 747-400 (9 1 0K) Electron i c Fu el L evel Ind icatio n System (EFLI) - Ou t O f T ank Wiring In s tallatio n Separation with Auxil i ary Requirement

Fuel Tank Concern: Potential for hot shorts and EMI induced vo ltages on the E FLI wiri ng outs ide of the tank to e nter the fuel tank. Routing and i nstallation of any new wi ri n g must use wire types BMS 13-48, BMS 13-60 o r BMS 13 -58, and not be w ithin a 2-inch radius of th e E FLI wiring . When a sing l e cla mp fa ils, a separation g reater than 

### liz inc h must be ma in ta i ned from AUX Fue l lank EFl I wiring . 28-AW L-31 

### C DCel 

## NA 7 47 -400 (910K) El ectronic Fu e l 

### level Ind i cation System ( E FU ) Processor Display Un it ( PDU) o r AUX tank w ith A ux i l i ary EFU - Repai r

Fuel Tank Concern : Potential for mai n ten ance error during PDU repai r . The PDU AUX l an k EFU i s des ig ned 1 0 l i m i t the levels o f e nergy, vo ltag e, c u rrent, a nd power allowed wi th in the EF U circ uit to i ntrins i cally safe l eve l s i n order to preclude the potentia l of an i gnitio n source w ith i n 

### a fu el l ank. Repair and overhaul o f PDU must be per Parker (V260SS) CM M 28-41-81, Revi sion 0, or later revis i ons of this CM M t hat have been a pproved by th e Seattle FAA ACO. 28 -AWl - 32 COCCl 

## NA 747-400 (910K) Fuel Tank Elect ron i c F uel l ev el Indi cation System (EFLI) - Repair of In-Tank Hardware wi th Auxiliary Concern: Potentia l for ma in tenan ce error during re pair of in - tank hardware. Arc gaps may

Fuel T ank develop that could result in an ignition source in side the f ue l tank. EFU probe repa i r and overhaul must be per Parker (V260SS) C MM 28 -41 - 70, Revision 1, or late r revisions that have been approved by the Seattle FAA ACO.

D 621U400-9 D EC 2009 BOEI NG PROPRIETARY - Copy r ight (c) - Unpubl is hed Work - See title page for detai l s Page 9.0-40

## rp..a0E'NG 

## 74 7-400 MAIN T EN A N C E PLANN I NG DA TA E. A IRWORT HINESS LIMI TATIONS· NITROGEN GENERATION SYSTEM TASKS The follow i ng l ist of AW Ls contains FAA approved schedu l ed i nspections for ope rators to incorporate i nto the i r maintenance program for this type des i gn to meet the requ i rements for the introducti on of the Nitrogen Generation System (NGS) . The FAA Special Condition No . 2S - 285-SC requires m a i ntenance instruct ions and contro l l imitations for certa i n NGS c r itical design configurations. 

### § 25.981 (b) a lso requ i res AWLs to prec l ude ignition sources i n s ide the fue l tank that may be introduced by 

### the addit ion of N GS . Specia l Cond iti on, Paragraph III (a), Ma i ntenance , requires the applicant identify Airworthiness lim ita t ions for aU cr it ica l fea t ures identif i ed under Paragraph II (a)(3) and for a ll maintenance and/or i nspect ion tasks requ i red to identify fai lu res of components with i n the NGS t hat a re needed to meet Paragraphs 

### II (a) , (b), and (c)(2) of t he special condit ions . NGS A i rworthiness Li m itations (AWLs) are mandatory m a i ntenance act ions t h at ensure that unsafe conditions that arise due to NGS fa il u res do not occur or are not introduced into the airplane as a resu lt of configuration changes, re p airs, alte rat ion s , 

### or defic i enc i es i n the NGS m a i ntenance program throughou t the operat iona l life of the a i rplane .


### AWL TASK INTERVAL APPLICABILITY DESCRIPTION NUMBER 47-AWl-0 1 CDCCl 

### NIA 747-400 a i rp lane line Li ghtn i ng P rotection - N GS NEA Descri pt ion Line Fue l Tank Penet rat io n N um b ers 1 363 , 1 366 Concern : Potentia l for arcing, spark i ng of fi lament heating ins ide t he tank at t he interface between the bu l khead fi tting an d the spar du ri ng a l i ghtning st ri ke event. The follow i ng must be m aintained pe r Boeing AMM 47-21 -06 if the bulkhead fitt i ng 

### or attached tub i ng are re m oved and replac ed: 1. Verify e l ectrica l fay s urfa ce bond between t he bu l kh ead fitting and the front spar struct ure insid e the tank is 0 . 0005 o h ms or l ess , 2 . I n stall full-bodied fillet sea l en capsu lat i ng t he fi rst coup l ing conn e cting the tube to the bulkhead fitting ins ide the tank , 3 . I n stall f ull bodied fi ll et seal encapsulat i ng the first coupling i nte rface inside the tank, 

### a,d 4. Verify electrical bond from structure to fi rst tube mat i ng wi t h t he bu l khead fitting is 0 . 010 ohms or less .

062 1U400-9 JU N 2006 BOE I NG P ROPR I ET ARY - Copy righ t (c) - Unpubl ished Work - See titl e page fo r detai ls Page 9.0-41

# ~DE'NG 747-400 MA INTEN A N CE PLA NNING DA TA AWL 

### TAS K INTERVAL APPLICABILITY DESCRIPTION 

### NUMBER 

### 47·AWl·02 CDceL N fA 

### 747-400 airplane line Center Fuel Tank Vent System Auxiliary Tanks Numbers 1363, 1366 Concern: The addition of an Aux i liary Fuel Tank system via S uppl e mental Type Certi fi cate may reduce the effectiveness of the NGS resulting in an i ncrease in flammability exposure of th e center tank . The N GS in sta ll at ion is designed to provide the prope r l evel of n it roge n to the center wing lank in order to reduce the fleet wide average flammabi l ity exposu re to l eve ls equal to that of wing fu e l tanks. Auxi l iary fue l tank i n stallations typically tran sfer fuel and ull age gases to and from the ce nter wing l ank. Any n ew Su pplemen tal Type Cert ifica te (STC) d es ign auxiliary tank syste m tha t commun i cates ullage d i rect ly to o r from the cente r wing tank mu st n ot sig n ifi cantly affect the perform a n ce of t he FRS. 

### Al l new STC auxil iary ta nk installations m u st be reviewed a nd approved by t he Seattle FAA ACO . See Boeing AMM ATA 

### 28 fo r a d esc rip tion o f the Fuel System a nd Fu el Ve nt i ng Sys tem. 47-AWl -03 

### ALI 1200 Fl ig ht 747-400 airp l ane line Ni t ro g en Gene ration System Fun ctiona l Check P erform ance In s p ec lion Hours Numbers 1363, 1 366 Co nce rn : late nt failure of the Hollow Fi ber Memb ranes th at make up t he Air Separation Modul es (AS Ms) wi ll reduce the percentage of nitrog en in the n i trogen e nri c hed air entering the center win g fue l tank. P e rform th e inspection procedure listed in Boeing AMM 47 -00-01. 1 . Mea s ure the oxygen concentration of the NEA at the outpu t of the ASM per Boeing AMM 47 - 00-01. 

### 2. Verify the NEA purity is i n the satisfactory zon e (sha d ed a rea ) of th e ASM performance charts publi s hed in Boeing AMM 47-00-01. If the nitrogen co nlent is not satisfactory, trouble shoot per Boei ng Fau ll Iso lation Manual and pe rfo rm t he reco mmended repa i rs per Boe i ng AMM 47 · 00-01.



### D 621 U400-9 JUN 2006 BOEING PRO PRIETARY· Co pyri g ht (c)· Unpublished Work - See title page fo r de tai ls Page 9 .0-42

## r[iaDE'NG 

## 747-400 MA INTENANCE PLANNING DATA AWL TASK INTERVAL APPLICABILITY DESCRIPTION 

### NUMBER 47-AWl-04 ALI 9675 Flight 747-400 airplane Line Nitrogen Generation System - The r ma l Switch Functional and Operational Test Hours Nu mbers 1363, 1366 Concern: Latent fai lure of t he Thermal Switch removes a layer of protection against fuel tank ign ition by hot bleed air. The NGS uses engine bleed air from the bleed system cross-over manifold to generate nitrogen to reduce the flammability of the center fuel tank. The NGS has features to prevent direclly feeding hot bleed air into the fuel lank. The Thermal Switch provides a redundant backup to the NGS controller to protect the ASMs and prevent hot bleed air from entering the fuel tank. The Therma l Switch backup feature is a latent (not detected) failure and must be tested to mainta in certification of the NGS . Perform a functional and operational test of the thermal switch per Boe i ng , AMM 47-43-02 to ensure the integrity of the thermal switch. , 47-AWL-05 

### All 1500 Cycles 747-400 airplane Line Nitrogen Generation System - The rma l Contro l Unit (TCU) and Inte rcon nect Duct or 7500 Numbers 1363 , 1366 ReplacemenUUpgrade Flight Hours Note Concern : The TCU pallet fa il ed vibration testing during qualification. The interconnecl duct vibration analysis demonstrates l i m ited l ife capabil ity . The TCU and interconnect duct may fail in service if not replaced or upgraded . Replace the TCU Assembly PIN 5848740-1 or Duct Assembly 

### PIN 5849522-1 (component ofTCU) Replace the interconnect duct PIN 5849599-1 . I nterval Note: Whichever comes first.

D621U400-9 JUN 2006 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-43

# rp. ..J IOE 'NG 

## 74 7..400 MA I N TE NAN C E PLA NN I NG DAT A AW L T ASK 

### INTERVA L APP L I CA B ILI TY DE SC RIPTION 

### N

U

MB E R 47 -AWL - OB 

### ALI 3000 Cycle s 74 7-400 a i rp l an e U n e 

### N itrogen Gen e rat io n Syste m - A ir Sepa rati o n Unit (ASU) Re pl acemenUU p g ra de or 

### 15000 Numbe rs 1363 , 1 3 66 Fli ght Hours 

### Con cern : Th e A SU pa ll et fa i l ed v i b rat ion l estin g du ri ng Q ual ificat ion. T he A SU may fa i l in N ote 

### service if 

### not re pl ace d o r u pgra d ed . Re pl ace AS U Assembly PI N 584 8760-1 o r t h e fo ll owi n g co m bi natio n of AS U co m pon en ts: - Overt e mpe rat u re S h utoff Va lve B rac ket PI N 5849542-41

- N itrog en Enr ic hed Air Bracket PI N 5 84 9542- 2 5

- Two A S M I n l et D ucts PfN 584 954 8- 1 (one on the p ri m ary ASM and one on the adjacent



### s e conda ry A S M

- Supp ly Ai r Pri ma ry Du ct Asse m b ly 

### PIN 5849557 -1. I nt erva l Note : Whi c h eve r comes fi rst.



### D 621U400-9 J UN 2006 BO E I N G PR O P R I ET A RY - Co p yrig h t (c) - U np u bl i sh ed Wo r k - See ti tle page fo r details 

### Page 9.0 -44

# ~OE'NG 747-400 M A INTEN A N C E PLA NNING DAT A F. AIRWORTHINE SS LIMITATION S (AWLs)- STRUCTURAL IN S PECTIONS The 747-400 passenger ai rplane can be operated i n a 747-400 Special F reighter (SF) config uration if m od ifi ed in acco rdance w ith specific Boei ng service 

### bulle t ins . These se rv ice bulletins are ident ified (with associated effectivity) in Boeing Service Bulletin 747-00-2004 . Ai rplanes converted by inco rporat ion of Boeing service bulletin(s) to the 747-400 SF configuration require exis ting su pplemental structural inspections identifie d for the 747·40 0, and new supplemental st ructural ins pections specific to the 747 - 400SF configuration. For the 747 -400SF configuration, all of th ese supplemental inspections are 

### shown in the 747 Su pp leme nta l Structu ra l l nspeclion Do cume nt 06·35022, beginning with Revision G (and on) of that document. After reach in g the thresho ld specified in the 747 Su p p lemen ta l Structural I nspection Document , 06 -35 022 , 747-400SF aircraft mod ifi ed as noted above must l imit all repeat i n l e rva l s in MPO Section 2, Structural Ma in tenan ce Program , to the values shown there i n.

06 2 1U400-9 MAR 2009 BOEING PROPR I ETARY - Copyright (c) - Unpublished Work - See tille page fo r details Page 9.0-45

## Il1-- BDE'NG 

## 747-400 MAINTEN A N C E PLANN ING DA T

A Airplanes converted to a 747-400 La rge Cargo Fre ighte r (LCF) configura tion by in co rporation of Boe i ng Service Bulletins 747-00-0008, 747 - 00-0018, 747-00-0033, or 

### 747-00-2 1 20 requi re 

### additional supplemental st ructural inspections specific to the 747-400 

### lCF config u ration. These supplementa l inspections a re shown in the 747-400 LCF Supp l e m ental Structural I n spection Documen l - Appendix A, 

### 06
-35022 -1. dated January 2010, o r later FAA approve d revision . For these supple menta l fatigue related inspections, afte r the airplane reaches the thresho ld specified in 06 - 35022-1, is sued January 

### 20 1 0, or late r FAA app roved rev i sion, the repeal interva l s of the C-Checks and O-Checks specified by the MPD must 

### be l i mited by flight cycles in add i l io n to the requi red l i mi tat ion for fli gh t ho urs and calendar time. For MPD Section 2, Structures Maintenance Program , and MP D Sec tion 3, Zona l I nspection P rogram, th e chec k i nterva ls m ust not exceed the followi ng : C-Check**~** 

### 1 ,500 night cycles**2C~Check ~**  

### 3,000 flight cyc l es D·Check**~** 

### 6 , 000 flight cyc l es 2D-Check - 12 ,000 fl igh t cyc l es Ai rcraft co nverted to the 747-400 l CF configurat io n a lso requi re t he revi sed ins p ect ion a nd mod ifi cation requ irements l isted i n Boe i ng Service Bu lle ti n 747- 53A2817 Rev. 00, o r a later revision approved by the Manager of the Seattle Aircraft Certification Office, in order to adequately addres s differences in aircraft structure and int erna l loads/stresses. When Boeing Serv ice 747-53A2817 state s to contact the Bo ei ng Company for modification data, that modifica tion data mu st be approved by the manag er of the Sea ttl e Airc raft Certification Office .

D621U400 -g DEC 2009 BOE I NG PROPRIETARY - Copyright (cl - Unpu bl ished Work· See ti tl e page for detai l s Page 9.0-46

## fi--DDE'NG 

## 747-400 MAINTENANCE PLANNING DATA G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs) SELECTION OF CMRs In order to grant operators of the 747-400 airplane an opportunity to participate in the evaluation and selection of CMRs in an integrated process with MRB tasks and in tervals, a Certification Maintenance Coordination Committee (C MCC) was convened to review all of the 747-400 CMRs. Th e CMRs listed in this document are the result of applying the CMCC process as described in AC 25-19 . CMR DEFINITION As 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 type certificate. CMRs usually result f rom a formal. numerical analysis conducted to show compliance with catastrophic and hazardous failure conditions. Additional notes concerning the definition of CMRs: 1 . A CMR is i ntended to detect safety- significant latent (hidden) failures that would, in combination with one or more specific failures or events, result in a hazardous or catastrophic fai lure condition. 2. II is important to note that CMRs are derived from a fundamentally different analysis process than the maintenance tasks and interva ls tha t result from the Maintenance Steering Group (MSG-3) Analysis associated with Maintenance Review Board (MRB) activities . MSG · 3 Analysis activity produces maintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance tasks, which are perfonned before failure occurs (and are intended to prevent failures), as well as failure-finding tasks. CMRs, on the other hand, are failure-finding tasks only, and exist solely to l i m i! the exposure to otherwise hidden failures. Although CMR Tasks are fai lure -finding tasks , use of potential fai lure-finding tasks, such as functional checks and inspections, may also be appropriate. 3. CMRs are designed to verify that a certain failure has or has not occurred, and do not provide any preventative maintenance function. CMRs " restart the failure clock to zero n 

### for latent failures by verifying that the item has not failed, or cause repair if it has failed. Because the exposure time 10 

### a latent failure is a key element in Ihe calculations used in a safety analysis performed to show compliance with FAR 25.1309, l imit i ng the exposure time will have a significant effect on the resultant overall fai lu re probabil ity of the system. The CMR task interval should be designated in terms of flight hours, cycles, or calendar time , as appropriate .
0621U400-9 AUG 2005 BOEING PROPR IETARY - Copyright (c) - Unpublished Work - See title page for deta i ls Page 9.0-47

## HDE'NG 74 7-400 M A INTEN A N C E PLANNING DA T

A 4. The 

### t ype certification process assumes tha i the a i rplane will be maintained in a condition of airworth i ness at least equal to its certified or properly altered cond ition. The process described in AC 25-19 is not inte n ded to establish norma l maintenance tasks that shou l d be defined through the MSG-3 analysis process. Also, this process is not intended to establish CMRs for the purpose of providing supplemental margins of safely for concerns arising Jate i n the type design approva l process . 5. CMRs shou ld not be confused with requ ired structura l inspection prog rams thai are developed by the type certificate app l icant to meet the inspection requirements for damage tole rance, as requi red by FAR 25 .571 or 25 . 1529, Append ix H25.4 (Airworthiness limitations sect ion). CMRs are to be deve loped and adm i nistered separate ly from a n y structural inspec tion programs. 

### EXCEPTION A L SH O RT-TERM EX TENSIONS FOR CMR s S i nce CMR in terva l s are based on statist ical ave rages and re l iab i l ity rates, an exceptional sho rt · te rm extension of 90 days for CMRs 24, 25, and 26 l isted in this document may be made without jeopardizing safety . The local regu latory authority (e .g. a P r i nciple Maintenance Inspecto r) must concur with any exceptional short-term extensions before they take p lace us i ng p rocedu res established with the loca l regu latory authori ty i n the opera tors' manuals. The

" excep ti ona l short-te rm ex tension" process is app l i cable to CMR i nterva ls. II shou ld not be confuse d w ith the opera tor's "short-term escalation " program for normal ma i ntenance tasks d esc ribed i n the operators' manua ls and i n the Flight Standards Handbook 8300 . 10. The Sea tt l e FAA ACO has accepted that these except ional short-term extens ions may be granted without consu lta ti on w ith that office : 1. The term "exceptional short-term extens ion " is defined as an i ncrease in a CMR i nterval that m ay be needed to co ve r an uncontrollable or unexpected s i tuation. CMRs 24, 25, and 26 l i sted in th i s docu m ent have been approve d with an exceptiona l short-ter m extens ion of 90 days. 2. Repea ted u se of extensions , either on t he same ai rpl ane or on si m i la r a i rplanes i n an opera tor 's fleet, shou ld not be used as a substitu te for good management pract i ces. Exceptional short-term extens ions must not b e used for fleet CMR extensions . A ft er a CMR has experi enced an except ional sho rt - term extension , the CMR i nterval w i ll revert back to its i nterval listed i n th i s document. T he Seatlle FAA ACO must approve , prio r to its use, any des i red extens io n no t explicitly listed above . Th is exceptiona l sho rt-t e rm exte nsion l isted above applies to a i r l ines tha t fall u nder the Un ited States FAA j u r isd i ct ion on ly. Operators who are not under the U . S. FAA ju r isdiction should obta i n i nterva l extension approva ls from the i r local regu latory agency . D621U40Q · 9 OC T 2007 BOE I NG PROPR I ETARY - Copyright (c) - Unpublished Wo rk - See title page for deta i ls Page 9 .0 -4 8

## fi.-HDE'NG 

## 747-400 MAINTENANCE PLANNING DATA POST CERTIFICATION CHANGES TO CMRS Any post certification changes to CMRs should be reviewed by the 747-400 CMCC and approved by th e Seattle FAA ACO: 1. Since t he purpose of a CMR is to limit the exposure lime to a given significant la tent failure as part of an engineering analysis of overall system rel iab i lity, 

### instances of a CMR 

### task re peatedly finding that no failure has occurred may not be sufficient justification for de leting the task. 2. The introduction of a new CMR should be rev iewed 

### by t he same process used during initial certification. It is impo rtant that operators b e afforded the same opportunity to participate thai they received during the original certification of the airplane, in order to allow the operators to manage their own maintenance programs. 

### 3. In the event that late r data provide sufficient basis for relaxation of a CMR (less re strictive actions to be required), the change may be documented by an FAA-ACO approved change to this CMR document. 4. If the requirements of an existing CMR must be decreased (mo re restrictive actions to be performed) . it will be implemented by a change to this CMR document and enforced by an FAA Airworthiness Directive (AD) . 

### 5. After initial aircraft certification, the only basis for adding a new CMR is in association with the certificat ion of design changes. 6. A new CMR created as part of a design change should be part of the approved data for that change and added to this CMR 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 . This revision will then be forwarded to all 747-400 operators and the Seattle FAA ACO offices.

D621U400-9 OCT 2007 BOEING PROPRIETARY - Copyright (c) - Unpubl ished Wo r k - See title page for details Page 9.0-49

# (lJ ..**J~OE'NG** 747..400 MAINTENANCE PLANN ING DATA H . CERTIFICATION MAINTENANCE REQUIREMENTS TASKS NUMBER SYSTEM INTERVAL TASK 

## PROCEDURE MPDITEM 

## REFERENCE NUMBER 1 Standby Powe r System Daily Operat ional (Short) Test - 115-Volt AC Standby Mainte nance Manual 

### 24 -0 29
-01 Power Generation 

### D633 Ul 0 1 S ubject 24-29 -0 0 Page Bl ock 500 

### 2 Ca rgo, Engine a nd AP U Fi re/Overh eat Dai ly Ope rational Test for F i re/Ove rheat D e tect i on Ma i nte na nce Manua l 

### 26-010
-00 Detection System. Systems D6 33U101 ( Only applicable to Engine Fire/Overh ea t Subject 26- 1 0-00 Detection Sys tem for 747 -4 00 LC F) Pa ge Block 500 

### 3 FADEC C2 Failures 2000 FH Ch eck Eng i ne Contro l System for Category 2 Ma in t enance M a nu al 

### 73- 12 1
-00 ' (GE CF6 - Fau lts us i ng th e CMC D633U101 80C2 B1 F ) Subject 73-21-00 Page B lock 200 1000 FH 7 3 -22 1-00 (PW4000)

560 FH 73 - 32 1 -03 (RR RB211 -524 ) 4 Generator Con tro l Unit a nd Bus Co n trol Un i 500 FH Operational Test - Gene rator and Bus Contro l Uni t Mainten ance Man ual 2 4- 023- 01 D633U10 1 Subj ect 24-23 -01 Page Block 500 

### 5 lavatory Waste Compartment 1000 F H lavatory Waste Comp artmen t I n spection Check Maintenance Manu al 25-040 -01 D633U101 Subject 25-41 - 00 Page B lock 600

D621U 400-9 APR 2008 BOEI N G PROPR I ETARY - Copyright (c) - Un published Work - See title page for de tails Page 9 .0-50

## r{;-BDE'NG 

## 747 -400 MA INT ENANC E PLANNING DATA NUMBER SYSTEM INTERVAL 

## TASK PROCEDURE MPDITEM 

## REFEREN CE NUMBER 6 E&E Cooling System Override Mode 1 000 FH Ove rride Mode Operational Te st Ma i ntenance Manual 

### 21-058 -03 Function (Not App l icable D633U101 

### to 747-400 F or Subject 21-58-00

747-400SF) Page Blo ck 500 

### 20,000 F H (Applicable to 747-400F and

747-400SF) 

### 7 High 

### lift Co ntro l System 1200 F H Pri mary Electric Operational T est o f L E and TE Main tenance Manual 

### 27-081-0 1 A . T rail i ng Edge E l ectric Control 1200 F H Fl a p Systems. 

### D633 Ul 01 B . lead ing Edge E l ectric Con trol Subject 27-51-11 P age Bl ock 500 

### 8 H i gh 

### Lift Control System 1200 F H Alterna te E lect r ical Operational Test of 

### l E and Main tenance Manual 

### 27-051-01 

### A. Alternate Arm Swi tch 10,000 F H T E Flap Sys tem. D 633 U1 01 B . Altemate Control Subjec t 27 - 51 - 11 Page Blo ck 500 

### 9 E&E Coo li ng System Flow Detectors 2000 FH R emove Clean and I nstall Low Flow Detectors. Maintenance Manual 21-058-22 (Not Applicab l e to 747-400F or 747-400SF) 

### D633U101 Subject 21 - 58-00 Page Block 200 

### 10 E&E Coo l ing System Smo ke & Flow 2000 FH E quipment Cooling Detector Ground Test Maintenance M anua l 2 1 -058 -04 Detection D633U101 ( Not Applicable to 747-400F or 747 -400SF) Subject 21-058-00 Page Block 500 

### 11 E&E Cooling System E30 - 2 Shelf 2000 FH System Test-E30 Rack Pressure Maintenance Manual 2 1 -058-16 (Equipment Cool i ng System) 0633 U1 0 1 Subject 21-58-00 Page B lock 500 

### 12 E&E Cool i ng Sys te m Fan s & Bypass Va l ve 2000 FH Fan and Bypass Valve Opera tio na l T es t Maintenance Manua l 2 1 -058-01 ( N ot appl i cable to 747-400F or 747-400SF) (Normal Mode) D 633 U1 0 1 Subject 21-58-00 Pag e Block 500 D6 21U400-9 APR 2008 BOEING PROPRIETARY - Copyright (cl - Unpublished Work - Se e tit le page for deta i ls Page 9 . 0-51

### fl-- aOEfNG 

## 747-400 MA I NTENANCE PLANNING DATA NUMBER SYSTEM 

### INTERVAL TASK 

## PROCEDURE MPDITEM 

## REFERENCE NUMBER 13 E&E Coo l ing System Fan Check Valves 

### 6250 FH Check Va lve - Deta il Visual l nspeclio n Maintenance Manua l 

### 2 1- 058 -2 3 (Not Appli cab le to 747 -400F o r 747-4QO SF) D6 33 U101 

### Subjec t 21 - 58-03 Page B lock 600 14 

### E&E Cooling System Clean Mode 

### 6250 FH Clean Cycle - Operationa l Test {Equipment 

### Ma in ten ance Manua l 

### 2 1-058
-02 (Not Applicable to 7 47-400F or 747-400SF) 

### Coo li ng Card CMC init ia led B IT) D633U10 1 , 

### I SubjecI21-SB-DO Page Block 500 15 E 6J E9 E q u ip m ent Cooli n g Va lve 

### 6250 FH Cargo F ire Switch Test M ain tenance Manual 2 1-058 - 19 ( Not app l i cable to 747-400F, 

### 747400SF o r 

### 0 633 U101 

### 747400 l CF) S ubject 21-58 -00 

### Page Block SO D 

### 16 H orizon tal Stabi li zer Fu el T ank In stallat i on 6250 FH I nspect i o n of Ho r izo nta l Stabilize r Bond ing Main te n ance Manua l 55-010-04 (On ly app l icable to 747-400 ' s equipped with Jumpe rs (App l icab l e on ly to a i r pl anes with D 633U10 1 horizon tal s l abi l i zer fuel capability.) hori zontal stabi l izer fue l quan t ity gage and contro ls Subject 55-10-04 (Not applicable to 747-400 LCF ) on Fuel Co ntrol Panel) Page Block 600 17 Uppe r Rudde r System 6250 FH Test Uppe r Rudder Hinge Bearing and Rudder Maintenance Manua l 27-02 1 -02 Power Control Package Bearing Pla y D633U101 Subject 27- 21 -02 Page Block 600

D 621 U4 00-9 APR 2008 BOEING PROPRIETARY - Copyright (c) • Unpublished Work - See tille page for de ta i ls Page 9.0-52

# 1{') ..J i'DE'NG 

## 74 7-4 00 M A INTEN A N C E P LA NNING DA T

A SYSTEM I NTERV AL TAS K 

## PROC E D

U

R

E MPDITEM 

## REF E

R

EN CE NUMBER 

### 18 Main Entry Door Escape System (Not 30 months! Main Entry Door Escape System Functiona l Check 

# I Service Letter**52~O 1-18**  

### Applicable to 747-400F, 36 months -**SL-747~SL52-44** 747-400SF 

### or Door #5 on Combi Ai r planes See Note (2) i n Cargo Mode. See Note (1). Note ( 1 ) : On Combi airplanes. the check is also Maintenance Manual (Only applicable to Door #1 LlH for required on Door #5 immediately after conversion D633U101 747-400 LCF) to passenge r mode Subject 52 -11- 07 Page Block 600 - 

### Para 2 Emergency Linkage I nspection Note (2) : The reference functional check Maintenance Manua l procedure coveri ng examination of the escape D633U101 slide 

## or s l ide/raft packs, may be accompl ished at Subject 52-11-07 30 month intervals , (the rema inde r of the procedure Page Block 600 - at 36 month intervals) Eme rg ency Linkage Inspection - Para 2. Examine the escape slide or slide/raft pack . 

### 19 

## I Engine St rut Spring Bea m 12500 FH 

# I Spring Beam Bearing Movement Check Ma i ntenance Manual 154-051-03 0633U101 Subj ect 54-51-03 Page Bloc k 600 

### 20 Lower Lobe Cargo Compartment 7400 FH Check Cond itioned Ai r System ( Non-Standard, if Con t rol Valve High Flow Disable with Lower Lobe 0633U101 i nstalled) Cargo Compartment Conditioned A i r On Subject 2 1 -28-00 (Not Applicable to 747 -400F, 747-400SF o r Page Block 500 747-400 LCF)

0621U400-9 APR 2008 BOEING PROPRIETARY - Copyright (c) - Unpubl i shed Work - See title page for detai ls Page 9.0 -53

# rt1-SDE 'NG SYSTEM 

## 747 -400 MAINTENANCE PLANNING DATA INTERVAL 

### TASK 

### PROCEDURE 

## REFERENCE

flI1 r

## ~**p'-~ !~!** **:lf~-' t1~**  

# I**"~~,,~r** 

# I.J"**~" _~"~~~~b~~** **~;t~' :!** **pag~e ~loJ:k** **OO '}4Ai** **'** til"" 

### I

## ~ Combi Main Deck Fire Protection System 6250 FH Main Deck Air Distribution F la pper Va lve Maintenance Manua l 26-024-10



### 24
25


### 26 Zones 0 and E Air Dist r ibution Shutoff AdjustmentiTesl. D633U101 

### Va lves, V532 and V533. Subject 26-24-05 (Not app l i cable to 747-400 

### lCF) Page Bl ock 500 Flight Deck Security Doors Installed per Servi ce Bulleti n 747 -25-3302 (Not applicable to 747-400 

### lCF) Service Bulletin 747-25-3306 and/or 747-25-3312. (Not app l icab l e to 747-400 L CF) 

### pec Flight Deck Security Doors Installed beginn i ng al the line number 1320 and on (except freighter models) . (Not app l icab l e to 747--400 L CF) reserve 2 & 3 VTO secondary shut-off syste m (Applicab l e to 747 -400 LCF only) 9 Years

9 Years

15000 FH the

Discard the Adams Rile stri ke mechanism.

Discard t h e Adams Rite stri ke mechanism .
Fun ctional Check of the fuel main tanks 1 & 4 and fue l reserv e tanks 2 & 3 VTO secondary shut-off system. D633U101 Sub j ect 52 -51-02 Page B lock 400 Maintenance Manua l D633U 1 0 1 

### Sub j ecIS2-S1-02 

### Page Block 400 Maintenance Manual D633U10 1 Subject 52 -51-02 Page Block 400 Maintenance Manua l D633U101 Subject 28 - 21 -00 Page Block 500 NOTE: SHADED CMRs HAVE BEEN DELETED.

0621 U400- 9 APR 2008 BOE IN G PROPRIE T ARY - Copyright (c) - Unpublished Work - See tit le page for detai ls Page 9 . 0 -54" 

# rfJ-.-BOEING 

## 747-400 MAINTENANCE PLANNING DATA I . REPORTING UN CO NTR O LLABLE HIGH THRUST FAILURE CONDITIONS 

### Title 14 Code of Federal Regu la tions Sect io ns 12 1 .703 and 1 35.415 state that "each certifica te holde r shall report any failure, ma lfuncti on, or defect in an a i rcraft, system, componen t, or powerplant that occurs or is detected at any time 

### if, in its opinion. thai failure , malfunction, or defect has endangered or may endanger th e safe operatio n of an aircraft " , Section 1 25.409 also requires reporting of fai lu res, ma lfunctions or defe cts . In many cases a reportab le 

### failure or malfunction will be obvious, but there are some failure modes related to uncontrolled high thrus t that are reportable but may nol be obvious. The following information is provided, as required by FAA Exempti on No . 8518 , to assist the opera tors in iden tify ing reportable malfunctions re la ted to un contro ll ed h i gh thrust. Th e FAA has conc l uded that the loss of capabi lity to control thrust due to a fai l ure of the engine t hrust contro l system ma y endanger the a i rcraft . This includ es any ma lfunct ions having one or mo re of th e following characteristics : • Auto-accelerat ion or uncommanded th ru st change to high e r power • Stuck Ihrust lever above idle power • I nability to reduce thrust Although some of these in ciden ts may not appear to be safety related , documenting the events is i mporta nt to ensure th e present l evel of sa fety is maintained andlor 10 identify fa i lure con d itions that must be co rrected. When fi l ing a report of such an event w ith the FAA, the ope rato r is reques ted to i nclude in the descrip tion of the event one or more of the following phrases: • "thrust con tro r • "no response to thru st lever'" •**aulo-acce rat** **ion ~**  

### • · uncon tro ll ed high thru st"



### D621U4QO·9 OCT 

### 2007 BOEING PROPR IE T ARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0 - 55

### !l5-- BOEfNG 

## 747-400 MAINTENANCE PLANNING DATA In addition, the following in formation shou ld be included in the report: 

### • Event descrip tion • Flight C rew action • Maintenance act ion • lis t of affected o r removed components 

### Reports should be submi tted to t he local representative o f the FAA Adm i n i strator t hat hand l es the appropriate reporting respo n s ibil ity for 

### §§ 12 1 .703 , 

### 1 25.409 , and 1 35.4 1 5. I n addition to filing reports wHh the FAA. 

### it is recommended that a copy be sent to Boeing and to the engine manu fact urer.

0621U40Q-9 

### OCT 2007 BOE I NG PROPRIETARY - Copy r igh t (c) - Unpublished Work - See tille page for details 

### Page 9 .0-56