Nu mber: Date: Revi sion 2 : ATA System : 

### 34n July 26 , 1990 Apri l 15, 1993 52 1 1 

### Commercial Airplane Group 

# 707/720 Service Bulleti n Revision Transmittal Sheet

SUBJECT : DOORS- MAIN CARGO DOOR - LATCH CA M R EP LAC E M E N T AND PRESSUR E RELIEF DOOR HI NG E FITTI N G REPLACEMENT T his revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive 9 1 -22-04 , Amendmen t 39-8064 , is related to this service bu ll etin . No more work is necessary on airplanes changed by the initial re l ease or Revision 1 or this service bulletin . SUMMARY This revision adds Instructions to trim the hinge filling if there is interference between the cam and the hinge fi tting when the door i s in the closed position . Optional fasteners are added for the installation of the hinge fitting . This revision also defines the maximum allowab l e wear limits for the latch cams . Paragraph I.A ., Effectivity, shows changes of airplane operators . Each operator shou l d examine the Effectivity paragraph for changes. Vertical lines are put on the left edge of each page , except in Paragraph I.A. , Effectivity, to show the location of Important changes. Pages with a revision number and date, but no vertical l ines have no important changes . REVISION HISTORY I ni tia l Release : Revision 1 : Revision 2 : Ju ly 26 , 1990 June 4 , 1992 April15 , 1993

BOEING COMM ERCIAl. AI RPLANE GROUP P 0 BOX 3707 SEA TILE . WASHI NGTON 96124-2207

## .BDIIND

Numbe r: Date Rev•sion 2 . ATA System : 

## 34n July 

### 26. 1990 Apnl 

### 15, 1993 5211 

### Commercial Airplane Group 

# 707/720 Service Bulletin Summary

SUBJECT: DOORS- MAI N CARGO DOOR- LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FI TTING REPLACEMENT BACKGROUND The main ca rg o doors on 707 airplanes with main cargo doors are almost the same as those on the 757 Package Freighter airplane . When the 757 Package Freighter was deslgned , better latch cams. and better hinge fillings for the pressure rehef doors were designed for the main cargo door. Boeing has received several reports of wear of the lock stop part of hinge fittings on the pressure relief doors on 707 and 727 Cargo and Frei ghter airplanes. Boeing has a lso received reports of wear of the latch cams on the main cargo doors on 707 and 727 Ca rg o and Freighter airp l anes. Wear of th e lock stop part of the hinge fi lling s and of the l atch cams Is thought t o be caused by Incorrec t operation sequence of the hydraulic system of lh e main cargo door. This service bulletin shows how to Install the better latch cams and hinge fittings on main cargo doors . Installation of the better parts will elCtend 

### the servi ce life of the 

### door latch system. Contmued operation with I nstalled latch cams and h1nge fillings that are 

### worn beyond the hm1ts given i n this service bulletin 

### is not satisfactory Persons cannot make sure that the main cargo 

### door Is correctly latched and locked under all possible operational conditions if the hinge fillings or the latch cams are worn beyond the limits given In this service bulletin . ACTION At the nelCt 

# ·c· check after receip t of this service bullefin. or 3000 fligh t-cycles, Whichever occurs sooner, do a visual inspection of the mating surfaces on the hinge fitbngs and the latch cams. If the hinge fittings are not 

### worn, or are wom wilhin the limits gJVen In this service bulletin , eilher install new hinge fittings and latch cams, or do the visual i nspection again at each 

# ·sc· check , or 8000 ftlght-hours, Whichever occurs sooner . If the hinge fitt1ngs are wom beyond the limits g1ven in thiS service bulletin , i nstall new hinge filt1ngs and latch cams. If th e latch cams are worn or damaged, install new hinge fittings and l atch cams. After the new hinge fitllng s and l atch cams a re Insta lled as s hown in th is servi ce bulletin, re lum to the normal Inspection In terval Federal Aviation Administration (FAA) Airworthiness Directive 

### 91 -22-04. Amendment 39-8064 is related to this service bulletin EFFECTIVITY All 707 airplanes wrth ma1n cargo doors MANPOWER Total Man hours - 34 for each airplane Elapsed Time - 17 Hours MATERIAL INFOR MA TIO N Boeing Supplied Kll See Paragraph I . F for applicable terms and conditions

BOO ING COMMERCIAl. AIRPLAN E GROVP P 0 SOX 3707 SEAT'Il£ W ASHOoiGTON 961 2<-2207 Summary Page 

### 1 or 2

### BOEING SERVICE BULLETIN 3477

/ .j



# -::~' ' tl/ 

# '/

**~**

**~--..._,_**



# ~ 

# r#

.) 

### / 

## REPLACE THE HINGE FITTINGS PRESSURE RELIEF DOOR

**FWD** 

## : ON E A

CH PRESSURE RELIEF DOOR :; (2 PLACES)



# ~INBD

**~**



### Jul26/90

REV 2 · Apr 15/93 

## L A

TC H CAM LATCH CA M BELLCRANK REPLACE THE LATCH CAMS AND THE BELLCRANK (4 PLACES)

Summary Page 2 of 2

## IIIII NII

Number: 

## 34n Date July 26, 1990 Revisoon 

### 2 April15, 1993 ATASystem : 5211 

### Commercial Airplane G roup 

# 707/720 Service Bulletin

SUBJECT: DOORS · MAIN CARGO DOOR· LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTIN G REPLACEMENT 

### I. PLA NNIN G INFORMATI O N

A . Effectivity 

### 1 . Airplanes Affected Refer to the Service Bulletm Index Document 06-164

### 7. Pan 

### 3 for Airplane Vanable Number. Une Number. and Serial Number data This change is applocable only to airplanes goven below. IDENTIFICATION BY CUSTOMER, CUSTOMER CODE , GROUP AND VARIABLE NUMBER AERO URUGUAY (AUG) 07454 AERONAVES DE L PERU ( RE C) 07606 07618 AFR ICAN AIRLINES (AFX) 07049 AHK AIR HONG KONG LTO. (A HK ) 07008 

# oaon AIR CHINA ( BEJ) 09003-09004 

### 09006 AIR RWANDA (RWO) 08002 A I R TCHAD A IR LINES (TCH) 08402 ALENIA (AET) 08329-08330 ALYEMOA OEM . YEMEN AIRLINES (AL Y) 08075 08475 ANGOLA AIRLINES (ANG) 07079 07081 07102

Jul26/90 REV 2 : Apr 15193 07608 07684 08401



### 3477 Page 1 of 37

### BOEING SERVICE BULLETIN 3477

AVIATION CONSULTANTS (ACT) 07603 08073 AVIATION RESEARCH CENTRE (AV R) 07701-07702 AVISTAR CYPRUS LTO. (APU) 08003 BMAC E-3A FL T . CREW TRAIN I NG ( B02) 07403 07455 BUFFALO AIRWAYS. IN C. (BUF) 07010 07042 07054 07807 07816 08152 CANADIAN DEPT OF DEFENSE (DND) 08406-08410 CHALLENGE A I R CARGO (C HA) 08055 CHILIAN AIR FORCE (CHF) 07619 CH IN A SOUTHWEST AIRLINES (XIN) 09001-09002 09005 COLOMBIAN AIRFORCE (CLB) 07109 COMTRAN INTE RNATIONA L I NC. (C II) 07078 CORDOBA AIR CARGO (CAG) 07625 CORSA I R (CRA) 07614 DIARO AIR SERVICES (DAR) 07052 07607 DOMINICANA AIRLINES (DOM) 08192 DUBAJ AIR WING (DAW) 09251 E-SYSTEMS (ES M) 08172 ECUATORJANA AIR LINES (ECU) 07045

Jul26/90 REV . 2: Apr 15 /93 07802 07207 08191

08309 07259-07260 07620

08474

3477 

### 2

### BOEING SERVI CE BU LLETIN 3477

EGYPT AIR (EGP) 08201 08203 08205-08207 08210 EL AL ISRAEL A I RLINES, LTD. (ELA) 08581-08582 ETHIOPIAN AIRLINES. CORP. (ETH) 08129 EXECUT IVE AVIATI ON SE RVICES (EXS) 07611 F.F.T. FRESH FOOD TRADING (FFT) 07262 FAST A I R CARR I ER (FAC) 07458 FLORI DA WE ST AIRLI NES (PA l) 076 1 5-07616 FUERZA AEREA ARGENTINA (AGF) 06461 06310 06312 06452 GEN E RAL ELECTRIC CORP. (GEC) 02017 GERMAN REPUBLIC (GRF) 08221..()6224 GLOBAL AIR (GLH) 06051 GOVERNMENT OF BRAZ I L (BRZ) 07060 08304 08308 06314 GOVERNM ENT OF EGYPT (EGG) 08209 GRUMMAN MELBOURNE SYSTEM (GMS) 07057 07107 07265 08102 08327 HEAVYL I FT AIRCRAFT ENGINEERING (HVL) 07075 INDONES IAN AIR FORCE (IDO) 09227 INTERNATIONAL AIR LEASES (IAL) 07043 IRAN AIR (IRN) 07016 08551-08553 09438 07806-07609 07612-07613 07817

Jul 26/90 3477 REV. 2 : Apr 15/93 3

### BOEING S ERVI C E B U LLETIN 3477

IRAN I SLAM IC AIR FORCE ( IAF) 

### 09101-09107 09161 -09167 I RAQI A I RWAYS (IRQ) 

### 09221-09223 ISRAELI AIR FORC E ( I SR) 

### 07406.()7407 0802 1 08243 JAMA H IR IYA A I R TRANSPORT ( UAA) 

### 07502-07503 07605 JET CARGO LIBERIA LTD . (JTC) 

### 08501 JET LEASE , I NC. (J LI ) 

### 07058 07401 07451 JUGOSLOVE NSKIAEROTRANSPORT(J An 

### 07073 LAOECO (LDE) 

### 08 128 LAN-CH I LE S.A. (LAN) 

### 07253 07602 07661 LIBYAN ARAB (LAA) 

### 07819 09411 L LOYD AERO BOLIV IANO (LAB) 

### 07261 MIDDLE EAST A I RLIN E S S.A. (MEA) 

### 08251

07251.07252 07264 08317 -08318 08404-08405 MILLON AIR, INC . ( M LA) 

### 07257 NAGANAGANI (NNG) 

### 08072 NIGER IA AIRWAYS, LTD . (NIA) 

### 08319 08333 NMB S I NGAPORE LTO . ( NMB) 

### 08313 NORTH ATLANTIC TREATY ORGAN IZATION(NATO) (NAT) 

### 07904-07906 OKADA AIR (OKO) 

### 08301 OMEGA AIR (OMG) 

### 07255 07810 08173

Jul26/90 REV. 

### 2 · Apr 

### 15/93 3477 4

### BO EING SERVI CE BULLETIN 34 77

PAKISTAN INTERNATIONAL AIRLINES CORP . (PIA) 07104 07267 08143-08144 08325 PAN AVIAT ION (PAV) 07053 PERUV IAN AIR FORCE (PRF) 07266 QATAR (OAT) 08076 09421 RACE AV IATION CORPORAT IO N (RAC) 07 006 REPUBLIC OF LIBERIA (LBG) 05603 ROYAL AIR MAROC (RAM) 07622..07623 ROYAL AUSTRALIAN AIR FORCE (RAA) 07814-078 1 5 07818 07820 09288 ROYAL JORDAN IAN A I RLINE (RJA) 08101 ROYAL MOROCCAN AIR FORCE ( MRC) 09441 S . 

### R. ACQUISITION CORP . (SRC) 08127 SAETA S.A. (SAE) 07191 SAFAIR FREIGHTERS (PTY) 

### LTO . (SFA) 07268 08242 08244 SAUDI ROYAL FLEET (SRF) 09281 09290 SCI BE-AIRLIFT KI NSHASA (SAK) 07907 SICOTRA AVIATION (SAZ) 07105 SKY AIR CARGO (SAC) 07201 SKYWAYS INTERNATIONAL, INC (SKL) 07617 07621 SOUTHERN AIR TRANSPORT, INC. (STT) 08306 08471-08472

Jul26/90 REV . 2 : Apr 15/93 

### 3477 5

### BOEING SERVICE BULLETIN 3477

SPANISH AIR FORCE DATA SUPPORT (SAF) 07405 09289 SUDAN (SUD) 08473 09231-09232 09287 TAMPA AIRLINES/COLOMBIA (TMP) 07004 07007 07071 TAROM ROMAN IA(TRM) 07044 07056 09201-09203 TRANS ARABIAN AIR TRANSPORT (TRB) 07047 08054 TRANS MED ITERRANEAN AIRWAYS (TMA) 07041 07046 07206 TRANSBRASIL A I RLINES INC . (TB L) 07270 08053 08171 TRATCO LEASING (TRT) 08004-08005 08008 USAF - 707 C- 137 PROGRAM (U02) 08271 USAF- 707 C-18A PROGRAM (U03) 07211-07213 07215 USAF- 707 EC·18B PROGRAM (U04) 07254 07256 07258 VE N EZUELAN AIR FORCE (VEN) 081 03-081 04 ZAS A I RLINES (ZAA) 08007 08074 I DENTI FICATION BY VAR IABLE NUMBER 02017 05603 06461 07101-07109 07181 07191 07451-07458 07501-07504 07601 - 07626 07801-07821 07901-07907 08001-08008 08101-08104 08121-08129 08141-08144 08201 - 08210 08221-08224 08241-08244 08301-08320 08324-08330 08333 08501-08502 08551-08553 08581-08582 09201-09204 09221-09223 09227 09281 09286-09290 09411

Jul26/90 REV . 2 : Apr 15193 07077 07801

07453 08 1 21-08122 08125

07001-07017 07041-07059 07071-07081 07201-07215 07251-07271 07401-07407 07661-07662 07681-07684 07701-07702 08021 08051-08056 08071-08077 08151-08153 08171-08173 08191-08192 08251 08261 08271 08401-08410 08451-08452 08471-08475 09001-09006 09101-09107 09161-09167 09231-09232 09251 09271 09421 09438 09441



### 3477 6

### BOEING SERVICE BULLETIN 3477

2. Spares Exam1ne your spares supply for 

### the pans Identified 

### in Paragraph 

### II.D., Ex1sllng Pans Accountability. 

### If any par1S are found, refer to Paragraph 

### II 0., Existing Par1S Acoountabtilty, for the recommended use.

Jul26/90 REV. 2: Apr 15/93 

### 3477 7

### BOEIN G SERVIC E BULLETIN 

## 3477
B. Reason 

### The ma1n cargo doors on 

### the 707 aorptanes that have main cargo doors are almost the same as those on the 757 Package Freighter a1rplane When 

### the 757 Package Freighter was designed, better latch cams, and better hinge fittings for the pressure relief doors were designed for the main cargo door. The new latch cams and h1nge fittings lor the 757 Package Freighter were designed to provide better resiStance to wear This service bulletin shows how to Insta ll the better l atch cams and hinge ftHings on the main cargo doors on 707 ai rp lanes that have a main cargo door. Installation or the bette r parts on Ihe main cargo doors will ext end the service life or the door l atch system . Boeing has received several reports or wear or the lock stop part or hinge fitllngs on the p ressure relief doors on 707 and 727 Cargo and Freighter airplanes. Boeing has also received reports or wear or the latch cams on the main cargo doors on 707 and 727 Cargo and Freighter airplanes . Wear of lhe lock stop part or the hinge fittings and of the latch cams Is thought to be caused by incorrect operation sequence or the hydraulic system of the main cargo 

### door Incorrect operation sequence or the hydraulic system or the main cargo door can occur In seMce due to wear or oomponents of the

**doo~s** hydraulic system. 

## or due to a hydraulic system that is not adJUSied correctly. Conl!nued operation With installed latch cams and h1nge fittings that are wom beyond the limits g1ven in this servtce bulletin Is not satisfactory. Persons cannot make sore that the main cargo door IS CO<Tectly locked and latched under all possible operational conditions if the hinge fitt1ngs 

## or the latch cams are worn beyond the limits given In this service bulletin Revision 

### 2 adds instructions to trim the hinge fitting if there is interference between the cam and the hinge fitting when the door is in the closed position . Optional fasteners are added for the Installation of the hinge fi tti ng . This revis i on also defines the maximum a ll owable wear limi ts for th e l atch cams .



### Jul26/90 REV 2 : Apr 

### 15/93 3477 

### 8

# I BOEING SERVICE BULLETIN 3477

C. Description At the next "C" check after receipt of this service bulletin , or 

### 3000 Oight-cyctes. whichever occurs sooner, do a visual inspection of the mating surfaces or the hinge fittings (on the pressure relief doors) and the latch cams. 

### If the hinge fittings are not wom , or are wom within the limits given In this service bu lletin, either install the new hinge fitting s and latch cams as shown In this service bulletin, or do the visual Inspection again at each 

# ·sc" check, or 

### 8000 night-hours, whichever occurs sooner, until the hinge fittings and latch cams are repl aced as shown In this service bulletin . If the hinge fittings are wom beyond the limits given in this service bulletin, Install the new hinge fittings and latch cams as shown in this service bulletin. If the latch cams are worn or damaged, install the new hinge fittings and latch cams as shown in this service bulletin. After the new hinge fittings and latch cams are installed, return to the normal in spection interval. If it is necessary to Install the new hinge fittings and latch cams, remove the lining and th e Insul ati on from the l ower part of the main cargo door. Remove and discard the four pairs or latch cams along with their matched bellcranks. Install new latch cams and their matched bellcranks on the main cargo door, along with new closed-and-latched indicators. Remove the hinge fittings from the pressure relief doors on the main cargo door and insta ll new hinge fittings on the pressure relief doors. Do a test of the main cargo door to make sure that the door operates, latch es, and locks correctly. Do a test of the control system for the door to make sure It operates correctly. 

### Do a test of the door warning system tor the main cargo door lo make sure It operates correct ly. Install the lining and the Insulation on the Inside of the cargo door and return the airplane to service. Federa l Aviation Administration (FAA) Airworthiness Directive 91-22-04. Amendment 39-8064 is related to this service bulletin , NOTES:1 . If the main cargo door was deactivated as shown in Service Bulletin 3311 "Main Cargo Door Deactivation/Reactivation System Installation•, and no attempt has been made to open the ca rgo door after it was deactivated, then the Inspection shown in this service bulletin can be ignored . 2 . If the main cargo door was deactivated as shown in Service Bulletin 3311 "Main Cargo Door Deactivation/Reactivation System I nstallation• then the changes shown in this service bulletin can be ignored . 

### 3. Time will be saved if the changes shown In this service bulletin are done at the same time as the changes shown in Service Bulletin 3387 "Main Cargo Door Cam Support Fitting Inspection and Replacement•. D . Approval This service bulletin was exami ned by the Federal Aviation Administration (FAA) . The changes shown in this service bulletin agree with the applicable Federal Aviatlon Regulatlons (FAR's) and are FAA approved . The FAA has examined the Inspection and replacement procedures specified I n Revi sion 

### 2 to Service Bulletin 3477 , 'DOORS - MAIN CARGO DOOR • LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTIN G REPLACEMENT" . The FAA has approved the i nspection and replacement procedures in Revision 2 of Servi ce Bulletin 3477 as an atternatlve to those specified In Airworthi ness Directive (AD ) 91 · 22·04 . Amendment 39-8064 .

Jul26/90 REV . 2 : Apr 15/ 93 3477 9

### BOEING SERVICE BULLETIN 3477

E . M anpo wer Approximately 34 man-hours are necessary to do this change on one a i rplane . The data below shows an eslimale of the man-hours necessary to do th i s change lor each a i rplane. This esti mate is lor direct laboronly, do ne only by an experienced crew. It does not Include l ost time such as: Ume to adjust to lhe workplace; schedule th e work; examine the work; cure material s ; make pa rts: find lools or o ther lost time . Adjust these estimates wi th operator man-hour data if necessary. N umber of Elapsed Task Persons M an-Hours Time (Hours) O pen Access 2 

### 2 1 Change 2 26 13 C l ose Access 2 2 1 Test 2 

### 4 2 TOTAL FOR EAC H AIRPLANE 34 

### 17 F . Material- Price and Availability Boeing can s u pply the kits shown In Pa ragraph II .A. , Parts Necessary For Each Airplane , as shown below. Kit ava ilab ility Is s hown In the Reo rder Lead Time (ROL T). RO LT i s calcul a ted 

### Irom the date Boeing gets the purchase o rde r .

Kit Number 65-93534-1 (a) 65-93534-9 Name Top Kit Top Klt RO LT (weeks) 51 Unit Price thru Oct3, 1993 

### $ 15.324.00 (a) Top Kit 65-93534- 1 i s held from more sales . Top Kit65-93534-9 supe rsedes old Top Kit. The kits are subject to the te rms and cond i Hons o r Boeing's standard purchase order acknowl edgmen t. After the Unit Price date, new pnce and ROL T data is applicable. Prices are in United States Doll ars. Terms: Net 30 days. Send purchase orders and l etters about the supply data lo the Director of Spares and refer to this service bulletin number. G. T ooling- P rice and A vailability None

Jul26/90 REV . 2: Apr 15/ 93 3477 10

### BOEING SERVICE BULLETIN 3477

H. Weight and Balance None I . References 1. Exisling Data a. 707 Maintenance Manual Subjects 52-7-0, 52-11-0, 52-11-43. 52- 11-171, 52-11-192 b. Overhaul Manual 52-36- 61. 52-36-62 c . Structural Repair Manual Chapter 51 d . Boeing Service Bu ll etins: o 3311 " Main Cargo Door Deactivation/Reactivati on System Installation· o 3387 "Main Cargo Door Cam Support Fitting Inspection and Replacement• e. Boeing Service Lette rs: o 707-SL-52-2 " Main Cargo Door Pressure Door Locking Stops• o 707-SL-52-12 "Ma in Cargo Door Partial Opening in Flight" 

### f. FAA Airworthiness Directive 91-22-04, Amendment 39-8064 2. Data supplied In support or this service bulletin : None J. Publications Aff ected Publication Overhaul Manual 707 Illustrated Parts Catalog

Jul26/90 REV. 

### 2 : Apr 15/93 Chapter-Section 52-36 52-30



### 3477 11

### BOEING SERVICE BULLETIN 3477 

## II. MATERIAL INFORMATION A. Parts Required Per Airplane 1 . To get the kit shown below , refer to Paragraph I .F., Material- Price and Availability. NOTE : Top kit is divided Into subkits to make Installati on of the parts easier. One 65- 93534-9 top kit and operator supplied materials specified In Paragraph II.A.2., Parts and Materia l s Supplied by the Operator, are necessary to change each airplane. -6 ·5

1 1 1 1

1 1 2

Jul26/90 REV 2 : Apr 15/93 65-93534 - KIT • MAIN CARGO DOOR LATCH CAMS AND LOCK F ITI INGS -4 -3 ·2 -1 Quantity 1 1 1 1 2



### 1 1

1 1 1 1 

### 1 1 1 2 2 2 Part Number 65-93534-1 65-93534-2 65-93534-3 65-93534-4 65-93534-5 65-93534-6 143N8027-1 143N8027-2 143N8060-1 143N8060-2 65-93534-7 65-93534-8 69-21969- 1 1 69-21969 -12 69-23438-1 69-23438-2 69-23439-3 69-23439-4 69-34974-3 69- 34974-4 AN960C616L AN960PD8L Nomenclature Top Kit (a) Kit , Latch Cams and Bellcrank Installation, Body Station 495 Kit , Latch Cams and Bellcrank Installation, Body Station 530 Kit, Latch Cams and Bellcrank Installation, Body Station 570 Kit. Latch Cams and Bellcrank Installation. Body Station 610 Kit, Pressure Relief Valve H inge i nstallation , Body Stations 510 and 590 Cam Cam Cam Cam Hinge FiUing Hinge Filling Bell crank Bellcrank Cam Cam Cam Cam Bracket, Lock Indicator Bracket, Lock Indicator Washer Washer

3477 12

### BOEING SERVICE BULLETIN 3477

65-93534- KIT- MAIN CARGO DOOR LATCH CAMS AND LOCK FITTINGS -6 -5 

### -4 

### -3 -2 -1 Quantity Part Number NomenClature 1 1 BACB30EL5CN19 Bo ll , Countersink 3 6 6 3 BACW10P208S Washer 10 MS20470B8-14 Rivet 3 6 6 3 NAS1104-20W Bolt 1 1 NAS1105-20W Bolt 1 1 1 1 NAS602-7 Screw 1 1 1 1 NAS679A08W Nut 3 6 6 3 NAS679A4W Nut 2 

### 2 NAS679A5 Nut (a) Top Kit 65-93534-1 Is held rrom more sales. Top Kit 65-93534-9 repl aces o ld lop kil 65-93534 • K IT • MAIN CARGO DOOR LATCH CAMS AND LOCK FITIING 

### -6 -13 -12 -11 -10 -9 Quantity Part Number NomenClature



# - 65-93534-9 Top Kit 65-93534-10 Kit. Latch Cams and Bellcrank Installation . Body Station 495 1 65-93534-11 Kll, Latch Cams and Bellcrank I nstallation, Body Station 530 1 65-93534-12 Kit, Latch Cams and Bellcrank I nstallation, Body Station 570 1 65-93534-13 Kit, Latch Cams and Bellcrank Installation, Body Station 610 2 65-93534-6 Kit, Pressure Relief Valve Hinge Installation, Body Stations 510 and 590 1 65-93534-20 Cam 1 65-93534-17 Cam 1 65-93534-14 Cam 1 65-93534-22 Cam 

### 1 65-93534-7 Hinge Filtmg 1 65-93534-8 Hinge Fitting 1 1 65-93534 - 18 Bellcrank 1 1 65-93534-15 Bellcrank 1 65-93534-23 Cam 1 65-93534-16 Cam

Jui26/90 REV. 2: Apr 15/93 

### 3477 13

### BOEING SERVICE BULLET I N 3477

65-93534 - KIT - MAIN CARGO DOOR LATCH CAMS AND LOCK FITTING 

### -6 - 13 - 12 - 11 -10 -9 Quanlity Part Number Nomenclature 65-93534-9 Top Kit 65- 93534-19 Cam 65-93534-21 Cam 

### 1 1 69-34974-3 B racket, Lock Indicator 1 69-34 974-4 Bracket , Lock Indicator 1 1 AN960C616l Washer 2 2 2 2 AN960PD8L Washer 1 1 BACB30ELSCN19 Boll. Cou ntersink 3 6 6 3 BACW10P208S Washer 10 MS20470B8-14 Rive ! 3 6 6 3 NAS1104-20W Bolt 1 1 NAS1105-20W Bolt 1 1 1 1 NAS602-7 Screw 

### 1 1 

### 1 1 NAS679A08W Nul 3 6 6 3 NAS679A4W Nul 2 2 NAS679A5 Nu ll 2 . Parts and M aterials Supplied by lhe Operator: Quantity 50 5 7 2 16 20 20 14 16 

### As Necessary 

### As Necessary 

### As Necessary 2

Jul26 / 90 REV. 2 : Apr 15/93 Part Number or Specification M S20470D6-7 BACB30FP6-3 BACB30FP6-4 BACB30 FP 6-5 BACB30FP8A( ) BACB30GY8A( )X BACC30K8 BACC30M6 BACC30M8 BMS 1Q-11 , Type I BMS 5-95. C l ass A and Class B MIL-G-23827 Name R ive t , Un iversa l Head H i-Lok Hi-Lok HI-Lok Hl-Lok Lockbolt Collar Collar Collar Pri mer Sealant Grease 

### 1 I nch l ong by 1 .751nch d i ameter rod , 2024-T4 or 6061 -T4 aluminum. See Flgure 2 .



### 3477 14

### BOEING SERVICE BULLETIN 3477

B. Parts Required to Mod ify Spares None C. Special Tools and Equipment Required The special 1001 

### shown in Figure 2 

### of lhis bulletin can be made by the operator. Main tenance and overhaul tools can be necessary as given in any manuals that are listed In Paragraph 

### 1.1 •• References. of this bulletin . Operators should review their tool inve ntory 

### to make sure that tools are available.

Jul26/90 REV. 

### 2 : Apr 

### 15/93 

### 3477 15

### BOEING SERVICE BULLETIN 3477

D. Existing Parts Accountability The parts shown below are changed by this service bulletin. Components or sub-assembly parts are Indented. The Quantity (Qty) of the Inden ted part Is the number of parts used on the next higher assembly. The quantity or the non-Indented part Is the number of parts changed on the airplane .

I nstalled Part Number Nomenclature 65-25339·5 Latch Cam Assembly Of: Sta. 600 + 4 .65 (Spares only) 69-2 1 971-4 Latch Cam 69-23438-1 Latch Cam 69-21969·3. -8, or -502 Bellcrank Assembly 65-25339-6 Latch Cam Assemb ly Of : Sta . 571 .80 (Spares only) 69-23439-3 Latch Cam 69·23439-4 Latch Cam 69-21969·1. -7, or ·501 Be ll crank Assembly 65-25339-7 Latch Cam Assembly Of: Sta . 528.20 (Spares only) 69-23439-3 Latch Cam 69-23439-4 Latch Cam 69-21969-2, -7, or ·501 Bellcrank Assembly 65-25339-8 Latch Cam Assembly 

## or: Sta . 495.35 (Spa re s only) 69-21971-3 Latch Cam 69-23438-2 Latch Cam 69-21969-4 , ·8,or -502 Bellcrank Assembly 65-26120- 1' ·3, or-5 Hinge , Pressure Valve 65-26120-2, -4 , or -6 Hinge. Pressure Valve 69-21971·3 or -501 Latch Cam 69-21971-4 or -502 Latch Cam 69·23439-1 or -3 Latch Cam 69-23439·2 or -4 Latch Cam

Jul26/90 REV. 2: Apr 15/93 Oly DC New Part Number 1 D IS 65-93534-13 1 D IS 65- 93534-22 1 D IS 65-93534-23 1 D IS 65-93534-15 1 D IS 65-93534-12 1 DIS 65·93534-20 1 DIS 65-93534-17 1 DIS 65-93534- 1 8 1 DIS 65-93534-11 1 DIS 65-93534-20 1 DIS 65-93534-17 1 DIS 65-93534-18 1 D I S 65-93534-10 1 D IS 65-93534-14 1 D IS 65-93534·16 1 DIS 65-93534-15 2 DIS 65·93534-7 

### 2 DIS 65-93534-8 1 DIS 65-93534-14 1 DIS 65-93534-22 1 DIS 65-93534-20 1 DIS 65-93534·17 PNC 

# s s s s s s s s s s s s s s s s s s s s s s RC A A A A A A A A A A A A A A A A A A A A A 

### A

3477 16

### BOEING SERVICE BULLETIN 3477

DC Disposition Code DIS • Discard Part PNC Part Number Code S - New equivalent or replacement part number. RC Replacement Code A - Not i nterchangeable . Do not replace one part with the other.

Jul26/90 REV. 2 : Apr 15 /93 

### 3477 17

### Jul26/90 REV 2 : Apr 15193 

### BOEING SERVICE BULLETIN 3477

BLANK PAGE

3477 

### 18

## I BOEING SERVICE BULLETIN 3477 

## Ill. ACCOMPLISHMENT INSTRUCTIONS NOTES : 1. The paragraphs Identified with letters give the general work Instructions and the necessary tests . The Instructions Identified wilh numbers on the figures give the recommended sequence of operations. 2 . Un le ss specified differently, the dimensions and tolerances given below a re used :

- All linear di mensions are in inches

- Tolerance on li near dimensions other than rivet and 

### boil edge margin is plus or minus

0.03

- Tolerance on rivet and boll edge margin Is plus or minus 0.05

- The hole dimensions for standard solid rivets are found In the 707 Structural Repair

Manual, Chapter 51

- The torque limits to tighten nuts and bolt s are found In the 707 Structural Repair Manual , Chapter 51 3 . Refer to 707 Structural Repair Manual Chapter 51 for alternative fasteners . 4 . Obey a ll warnings and cautions In the specified manua l sections. PART I · INSPECTION 

### A. Do an inspection of the hinge fittings and the latch cams on the main cargo door as shown in Figure 1. B. If any of the four hinge fittings are wo rn beyond the limit given in Figure 1, Install new hinge fittings and latch cams in the main cargo door as specified in PART II- REPLACEMENT , below. C . If any of the eight latch cams are worn or damaged as shown In Figure 1, Insta ll new hinge fittings and latch cams i n the main cargo door as specified In PART II- REPLACEMENT, below. PART II-REPLACEMENT 

### A. Make the hinge fitting tools for the pressure relief doors as shown in Figure 2 . B. Remove the In terior lining and the insu lation from the lower area of the main cargo door (Refe rence - 707 Main tenance Manual , Subjects 52-11-171 and 52-11-192) . C. Place a work platform next to the airplane at the main cargo door. D . Partially open the main cargo door. Use wood blocks to support the door in the opened position as shown In the 707 Maintenance Manual , Subject52-11-0 , Inspection/Check. Cycle the latch cams Into the l ocked position with the door In the open position as shown in the Maintenance Manual Sub j ect 52 · 11·0. E . Remove pressure from the hydraulic system for the mai n cargo door (Reference • 707 Mai ntenance Manual, Subject 52-11·0 , Maintenance Practices). F. Remove the most forward and aft main cargo door latch actuators as shown in th e 707 Mai ntenance Manual, Subject 52-11-11 .

Jul26/90 REV . 2 : Apr 15 /93 

### 3477 19

### BOEING SERVICE BULLETIN 3477

G Remove the web and access cover from each pressure rehel 

### door location as shown an Figure 4 . H . Remove the pressure relief doors and carefully drill out lhe rivets that attach the hinge fittings to the pressure relief doors as shown In Flgure 

### 5. circle notes 

### 1 lhrough 

### 9. 

### I. Remove the lalch cams and the bellcranks from the main cargo door, and Install new latch cams and

bellcranks as shown In Figure 

### 3 . J Install the pressure relief door and locate the new hinge filtangs on the pressure relief doors as shown in Fagure 

### 5, circle notes 

### 10 through 

### 26. 

### K. Install 

### the most forward and aft main cargo door latch actuators as shown tn the 

### 707 Maintenance Manual Subject52-11-11 

### L. Operate the main cargo door as necessary to remove air from the hydraulic system lor the main cargo door. Select door open control and open door sufficient to remove th e wood blocks. Do not o perate the main cargo door Into the comple te ly c l osed position while this step Is done . M Adjust the main cargo door as necessary and do a test of the main cargo door to make sure that 

### It operates correctly (Reference- 

### 707 Maintenance Manual . Subject 

### 52-34-0. Adjustment!Testl. NOTE · Inspect to make sure that the tab on the martong bracket is insened Into the Index hole in 

### the cam. 

### Also do a check to 

### see Lf the martong bracket as visible through the viewpon in the cargo door skin when the door is 

### closed and the latch cams are In the latched posation N . Do a test of the warning system lor the main cargo door to make sure that it operates correctly (Reference- 

### 707 Maintenance Manual , Subjec t 

### 52·70-00 or 

### -01) 

### 0 . Do a test of the control system of the main cargo door to make sure that 

### it operates correctly 

### P . Install the web and access cover at each pressure relief door location as shown In Fagure 

### 6 . 

### 0 Install the insulatJOn and the Interior Ianing 

## on the tower area or the maan cargo door (Reference • 

### 707 Maintenance Manual, Subjects 

### 52-11-171 and 

### 52-11·192) R Restore airplane to servaceable condation .

Jul26/90 REV 

### 2: Apr 15/93 

### 3477 20

### BOEING SERVICE BULLETIN 3477

Illustration Table of Contents

Tille Page Figure 1 . Inspection . . • • . • . . . . . . . . . . • . • . . . • • • . • . . • . • . . . • . • . • • . • . • . . . • . • • • • 22 Figure 

### 2 . Alignment Tool Fabrication • • . . . • . . • • • • . • . • . . . . . . • • . . • . . . . • • • • • • • . • . 

### 24 Flgu re 

### 3. Latch Cam Replacemen t . . . . . • . . . . . . . . . • . . • • . . . . . . . . . . . . . . . . . . . . . . . 

### 25 Figu re 4. Web Removal. . . . . . . . . . . . . . . . . • . . • . . • • . . • . . . . . . • . . • . . • . . • • . • • • • . . 31 Figure 

### 5. Hinge Fining Replacement . . . . . • • . . • . • . . • • . . • • . . • . . . . • • . . • • . . • . . . . . 

### 32 Figure 

### 6. Web tnsta ll allon . . • . • . . . • . . . . • . . . . . • . • . . . . • . • . • . . . . . . . . • . . . . . . . • . . 

### 36

Jut26f90 

## 3477 REV. 2 : Apr 15193 21

## ALMOST THE S

AM E AS DETAIL I

Jul26/90 REV . 2 : Apr 15193 

### BOEING SERVICE BULLETIN 3477



## SEE DETAIL I

INBD

PRESSURE RELIEF DOOR PRESSURE RELIEF DOOR PRESSURE DOOR SEAL



# - 0 . 1S INCH IIINIIIU M OVE RLAP REQUIRED

0.12 INCH MA X IliU M flAT ALLOWED

FIGURE 1 INS PECTION 3477 

### 22

## LATCH CAM BOEING SERVICE BULLETIN 3477**FWD** 

# DETAIL I LATC H CAM

The Instructions given below agree with the numbers shown i ns ide the ci rc le symbols i n the figu re : Do a visual i nspection of the area on each latch ca m that con tacts a hinge fitting on a press ure rellef door (4 places) . If the cam is notched as shown, o r if the cam shows any damage beyond 0.05 inches deep from co ntact with the hinge fitti ng , replace the latch cams and the h i nge fittings as shown I n this service bulletin . 

### 2 Measure the 

### tip or each hinge fitting as shown 

### (4 places) . If any or the hinge fillings a re wom beyond the limit shown, repla ce the latch cams and the hinge fittings as shown In this service bulletin . Refer to the 

### 707 M aintenance M anual, Subject 52-11-0 . NOTE Removal of th e pressure relief door from the main ca rgo door can be necessary to do the Inspection given In Step 

### 2 , above . I nstructions f or removal of the pressure relief door are given In the 

### 707 M ain tenance M anual, Subject 52- 11 -43 3 . If either the cam or the hinge fitti ng is wom , measure the overlap as shown In view AA . Make sure that there Is mini mum of 0.15 inch overl ap . If there is less than a 0.15 Inch overlap. replace the cam and the hinge fittings as shown in this service bulletin

Jul26/90 REV. 

### 2: Apr 15/93 F IGURE 1. INSP ECTION 

### 3477 23

# '\

A 

### BOEING SERVICE BULLETIN 3477



## 9

# o • 

# /-



# ___ _

- _ -----

_ 

# ......___'

0 . 54 R 

## 0.55 0 .8 4 R / 0 .8 6 A 8 

### l.OSOIA 1.1 0 •

B 

# L '<' 

# j 

# L j 

# I 

# - r 0.50 0.50 l____l ___ 

# .J_J _l L___ _ 

# _____J_l VIEW A-A VIE W B-B The i nstrucllons given bel ow agree with the numbers shown in side the circl e symbols in the figure: 1 Make the two alignment tools to the dimensions shown from one ol the materials given below:

o 2024· T42 a l uminum rod . 

### 1.75 Inch outside diameter o 6061·T42 aluminum rod , 1.751nch outside diameter

FIGURE 2 . AUGNMENT TOOL FABRICATION Ju l26/90 REV . 2 : Apr 15/93 

### 34n 

### 24

### Jul 26 /90 SEE DETAIL I DETAIL II

REV. 2 : Apr 15/93 

### BOEING SERVICE BULLETIN 3477



## SEE D

ETAIL VI SEE DETAIL V 

# e:> FWD

# ~I NBD SEE DETAIL IV

FIGURE 3. LATCH CAM REPLACEMENT 

## MA I N CAR GO DOOR



## -.. see DETAIL I SEE DETAIL II D

E

TA I L III



### 3477 

### 25

### Jul26/90 REV. 

## 2: Apr 

## 15/93 BOEING SERVICE BULLETIN 3477



# e::> FWD 

## DETAIL I A

FT LATCH CAMAND BELLCR ANK ASSEMBLY SHOWN, FOR WARD LATCH AND BELLCR ANK ASSEMBLY OP POSI TE

SHEAR WEB 69-24209-()



## DETAIL II VIEW LOOKING FOR WARD FRA ME I



## Z .\ 1 -1 LUG ASSEMBLY

-**~** 

### 9-66095-1 

## Q INBD AFT LUG ASSEMBLY SHOWN, FO RWARD LUG ASSEMBLY OPPOSITE FIGURE 3. LATCH CAM REPLACEMENT 3477 

### 26

### Ju l 26190 15193 REV . 2 : Apr 

### BOEING SERVICE BULLETIN 3477



## 8Ell CRANK

# II**D** DE T AIL I V

M REPLACEMENT FIGURE 3. LATC H CA 

### 3477 

### 27

### Jul26/90 

## LATCH AC T UATOR

REV. 2: Apr 15/93 

### BOEING SERVICE BULLETIN 3477



## D

ET A IL VI FIGURE3 LA ' TCHCA M REPLACEMENT 

### 3477 28

### BOEING SERVICE 

### BULLETIN 3477

VIEWPO R T-------_ \
D

OO R 

## SKIN 

# @ 11 ARKI N G**--='*=~** 

## / BR AC KET



### Q INBD 

## VIEW A-A L ATCH C A

l!

The Instructions given below apply to latch cams and bellcranks located at Body Stations 495, 530, 570, and 610. See Deta il s I , II, Il l and VI for comple te figu res that show repl acement of the forward and aft latch cam and beiiC<ank. See Detail s IV and V for compl ete figures that show repl acemen t of the latch cam and bellcrank assembly located at Body Stations 530 and 570 . The instructio ns given below agree with the numbers shown Inside the circl e symbol s in the figure: 1 Fo r the most f orward and aft l atch cam , trim the shear web 69-24209-( • ) and extend the cu t ou t of the lowe r beam web and doubl er 65-25338-( • ) inboard, up to the maximum amount as shown. Do not trim shear web or extend the cut out of the l owe r beam web beyond what is necessary for the removal of the lug assemb ly. M ain tain 0 .50 R or l arger comer radius. On the aluminum shear web 69-24209-3, 

### -4 a nd the lower beam web and d o ubler 65- 25338-( • ), finish trimmed areas with brushed on chemical film treatment (Aiodine or l ri dite), and one coat of B M S 10-11 Type I primer. Touch up with one coat of decorative ena m el. On sleet shear web 69-24109-7 and ·8 , fin i sh trimmed areas with brush cadmium plate and one coal of BMS 10-11 Type I primer. Touch up with one coa l of decorative ena m el. 2 Remove the fasteners that attach the forward and aft Lug Assemb ly to the frame. 3 Remove the fastener that attaches the latch actuator to the bellcrank . Keep the fastener for tater use. NOTE : If the fastener Is wom , corroded , or Is m i ssing fin i sh , use a new Bolt 66-17789-1 . 4 Remove and discard the fasteners that attach the bellcrank to the latch cams. 

### 5 Remove the bellcrank and the latch cams from the door, and discard the bellcrank and the latch cams .

Jul26/90 REV . 2 : Apr 15/93 FIGURE 3. LATCH CAM REPLACEMENT 3477 29

### BOE I NG S ERVI CE BULLETIN 3 4 77

6 Use a screw NAS602·7, two washers AN960P08L and a nut NAS679A08W to Install the marking bracket on the new latch cam. Make sure that the tab on the marl<ing bracket fi t s Into the index hole on the cam . Make sure that the cams are I n the l atched position , and verify that the marking bracket is vi sible through the viewport in the cargo door ski n . CAUTION : Make sure that the correct marl<lng bracket is Insta ll ed on each cam as shown in Fi gure 3 . There are lwo different part numbered marking brackets. If the wrong b racket Is Insta ll ed on the cam, It will not be visib l e through the viewport in the door skin when the door is in the latched position . 7 Apply a thin coat o r g rease MI L-G-23827 (or equivalent) to the bearing surfaces o r the new latch cams and the new bellcrank . 8 Apply primer (Reference· B M S 10-11, Type 

### I) to the tapered end of bellcrank. Do not a ll ow the prime r to dry befo re the next step I s done. 9 Use the fasteners indicated to install the new latch cams and the new bellcrank in position on the cargo door. NOTE : Make su re that the forward an aft lug assembly are in place prior to the Installati on of the most forward and aft latch cams and be ll crank . 10 Attach the latch actuator to the new bellcrank. Use the fas teners that were kept when the instructi ons given In Step 3 , above, were done . Torque the bolt with 50 to 80 inch-pounds. 11 Install the Lug Assembly to the web .

The Instructions given below agree with the letter shown in the upper-left comer or the fastener symbols in the figure. A number in the l ower-right corner of the fastener symbol i s the l ength of the fastener. A Insta ll a bolt NAS 1 104-20W with a washer BACW10P208S under the bolthead . Use a nut NAS679A4W to secure the boll, and torque the nut with 50 to 80 inch - pounds. B Inst all a bolt NAS1105-20W with a washer AN960C616L under the bollhead . Use a nut NAS679A5 to secure lhe bolt, and t o rque the nut wi th 100 t o 150 inch-pounds . C Install a countersink boll BACB30EL5CN19 wi th a nul NAS679A5. Torque the nul with 60 to 65 Inch-pounds . 0 Install BACB30GY8A( 

### )X lockbolt with a BACC30K8 Collar.

FIGURE 3 . LATCH CAM REPLACEMENT Ju l26/90 REV. 2 : Apr 15/93 

### 3477 30

### BOEING SERV I CE BU LL ETIN 3477



# e:> F W

D 

## INB D The instrucUons given below ag ree with the numbers shown Insi de the circle symbol s In the figure : 1 Remove and keep the screws that attach the access panel for the pressure relief door, and remove and keep the access pane l for l ater use . 

### 2 Drill out or otherwise remove all fasteners that attach the web to the structure around the pressure relief door. 

### 3 Remove and keep the web for l a ter use .

F IGURE 4 . WEB REMOVAL Jul26 /90 REV . 2 : Apr 15/93 

### 3477 3 1

### SEE DETAIL I 

## FOR DOOR EXTERNAL 

### BOEING SERVICE BULLETIN 3477

## VIEW~**~ar;;.--**

STA 

## 480



# I 

# I e:> FIID

# ~INBD SEE DETAIL II STA 

## 600D



# < 1Yi9

# ,~ 

# n u n n L; 

# /

Ju l26/90 REV. 2: Apr 15193 

## '

DETAIL I DOOR EXTERNAL VIEII
FIGURE 5 . HINGE FITTING REPLACEMENT 3477 

### 32

### SPACER 

### 7\ 13118 123

- -- """"f 

# rl

**~** 

### I NUT 

### 7113 N 

# - 

# - 18 1 23 BOEING SERVICE BULLETIN 3477



### 5 ! 24 _, 

### 8 110111 • 19 (23 PR ESSURE RELIEF DOOR

1 

# -- 

# ---

HINGE FITTING



### ~F **WD** 

## DETAI L II f 9I_J3 > HI N GE FITT ING 

# £:



# ~ 

# I /



# ... 7 

### 113 18 1 23 HINGE BOLT NUT

**~-** 

### 4 J

### 25 '-- 

### BELLCRANK 

# r 11 

# ' H 4 25



# ... 

# --- \ 

### BOLT



### • I 

### 4 

### 1 25 SPACER 

## SECTION A-A
20 1 22 

## I 3 26



## .... / 

# - 16 21



# ~ I 

# ,. SECTION B-B PRESSURE "' \ 1 

### <" RELIEF_ 

## 1 

# "" ..... J_2 1 

## !_9 (2 PLACES)

Jut26/90 REV. 2 : Apr 15/93 

### DOOR 1 

### 17 \_. _ 

# f .

**~.**



# \

**~** 

### 15 

# / ., ,...y 

# '-- VIEW C-C (2 PLACES) FIGURE 5 HINGE FITIING REPLACEMENT 

# I ALIGNMENT TOOLS



### 3477 33

### BOEIN G S E RVI CE B ULLETI N 3477

The instructions given below agree with the numbers shown Inside the circle symbols in the figure: 1 Make sure that the pressure relief door is cJosed and seated against its cutout in the main cargo door. 

### 2 Make marks on the outside of the pressure re l ief door and on Jhe outside of the cargo door skin with a marker that wlll not damage the pressure relief door or the cargo door skin . Make sure that the marks on the pressure relief door are aligned with the marks on the cargo door skin. These marks wlfl be used later to correctly position the pressure relief door on the cargo door when the new hinge fittings are lnsl a li ed as described in Step 

### 16. bel ow. 

### 3 At the aft pressure relief door location only, remove the hydraulic tubes that a re located inboa rd of the pressure relief door. Temporarily plug or cap the open hydrau l ic tubes to make sure that hydraulic fiuid does not spill all over In J he pressure relief door area In the cargo door. 

### 4 Remove the nut, the bolt, the washers and the spacers from the beilcrank on the torque tube that Is above the pressure relief door . Keep a il ofthis hardware for later use. 

### 5 Remove the 

### nut, the washer, and the bolt from the bellcrank on the torque tube !hat Is above the p ressure relief door . Keep all ofthis hardware for l ater use. 

### 6 Rotate the bellcrank on the torque tube so that it Is out of the way of the pressure relief door. 

### 7 Remove the nut, the special bolt, the washers, and the spacer from the hinge points of the pressure rel ief door . Keep all of this hardware for later use. 

### 8 Remove the pressure re l iefdoo r from the cargo door. 

### 9 Ca refully drfli out the rivets that attach the hinge fittings to the pressure reli efdoor. Discard the old hinge fittings. 10 Put the pressure relief door into the cargo door and align the marks on the pressure relief door with the ma rks on the cargo door skin . 11 Wedge the pressure reli efdoor so that ills firmly seated In Its cutout on the cargo door. NOTE : M ake sure that the outside surface of the pressure door is fiush with the outside skin of the main cargo door. Refer to the 

### 707 Maintenance Manual, Subject 52-11-43. 12 Put the alignment tools thai were made in Flgure 

### 2 In the cup of the cam as shown 

### 13 Attach the new hinge fittings 

### 65-93535-7 (aft) and 

### 65-93535-8 (forward) to the pivot points with the hardware that was kept when Step 

### 7, above, was done. Make sure that all of the hardware is installed exactly like It was before it was removed . 14 Make sure that the new hinge fittings tum freely on the special bolt, and that the mating surfaces of the hinge fittings and the pressure relief door are in contact with each other.

FIGURE 

### 5 . HINGE FITTING REPLACEMENT 

### Jui26/90 REV . 2 : Apr 15/93

### BOEING SERVICE BULLETIN 3477

15 Rotate the hinge fittings untillhe tip touches the alignment tool as shown. NOTE : Make sure that there Is no interference between the cam and the hinge fitting . If the hinge fitting Interfe res with the cam, then do the steps that follow: a . Trim up to a maximum ol 0.05 Inch from the outboard surface on the hinge fitting . Make sure that the removal of material is done so to maintain the rad ius of the part. Maintain a 63 AA surface fi nish or better. b . Finish filed area with two coats of BMS 10-11 Type I primer. c. Contact Boeing If a trim of 0.05 does not stop the Interference . 16 Tighlly clamp the hinge fittings to the pressure relief door and remove the wedges that held the pressure reli ef door In position in the ca rg o door. 17 Make sure that the pressure relief door moves freely with the new hinge fittings. 18 Remove the nut. the specia l bolt. the washers. and the spacer from the hinge poin ts of the pressure relief door. Keep all of this hardware for late r use. 19 Remove the pressure re lief door form the cargo door. and remove the ali gnment tools from the cup of th e cam. M ake sure that the new hinge fittings are not moved ou t of the clamped position when the pressure re li efdoor is removed . 20 Carefully drill matching 0 .257 inch diameter (drill Size "F") hol es in the new hinge fittings at locations where fas tener hol es exist in the pressure relief door. Use of a drill bushing to make 1/8 Inch diameter pilot holes In the new hinge fittings Is recommended. followed by gradual enlargement of the fastener hol es to the final size. NOTE : As an option, the operator may use HI-Lo ks BACB30FP8A( ) and collars BACC30M8 In place of rivets to install the hinge fitting to the pressure door. To use HI -Loks Carefu lly drill matching 0.266 to 0 .270 Inch diameter holes in the new hinge fittings at the locations where fasteners holes exist in the pressure relief door . 21 Remove the new hinge fittings from the pressure relief door and deburr all fastener holes In the hinge fittings . 22 Use rivets MS2047068-14 or optiona l fasteners coated with sea l ant (Reference - BMS 5-95. Class A) to insta ll the new hinge fittings on the pressu re relief door. 23 Put the pressure relief door in position in the cargo door and attach the hinge fittings to the pivot pOints with the hardware that was kept when Step 18, above . was done . Make sure that all of the hardware Is installed exactly like it was before It was removed. and make sure that the pressure relief door moves freely on its hinges . Torque the nut with 50 to 80 Inch-pounds . 24 Rotate the bellcrank on the torque tube that i s above the pressure relief door I nto correct position on the torque tube and attach the bellcrank to the torque tube with the hardware that was kept when Step 5, above, was done. Torque the nut with 25 to 35 inch-pOunds. 25 Use the hardware that was kept When Step 

### 4 . above. was done to attach the bellcrank to the slotted bracket on the pressure relief door. T orque the nut with 25 to 35 inch -pounds . 26 Install the two hydraulic tubes that were removed when Step 

### 3. above . was done. FIGURE 5 . HINGE FITIING REPLACEMENT Jul26 / 90 REV 2 : Apr 15/93 

### 34n 35

## 3 ,

::; N

**~**

**~**



### Jul26/90 

### BOEING S ERVICE BULLETIN 3477



# ~



# lf~l

**~~~~~---~~-** SEE DETAIL I 

### (

**~** 

### C l 4 PLA CES) SEE D ETA IL I I

**~** 

### ,A 

## B B B B B 4 I 

# r 

# "d ar

I 

## B

t 0 

## 0 0) 

## 0 

## B

j 

# "' f B f 

## 0 

# a

t B 

### I 

## / ' 

## 0 0 7



# B

t 8 t 

### 1 I 

### 2 

## DETAIL I 8



### FIGURE 6. WEB INSTALLATION 

### 1

REV. 2: Apr 15/93 

### e> F W

D



# ~INBD

3 B

._

**~** A 

# " s A 1 A 1 A J A J A 8 

# J

# l

3 

### C24 PLACES>



### 3477 

### 36

### BOEING SERVICE BULLETIN 3477



# Jt- a _ 

# / jl (24 PLACES) 

# DETAIL II

The instructions given bel ow agree with the numbers shown inside the clrcle symbols In the figure: 1 Clean all o l d sealant from mating surfaces of the web and the cargo door structure. 2 Apply sealant (Reference· BMS 

### 5-95, Class B) to mating surfaces ofweb and cargo door structure. Do not allow the sealant to dry before the next step Is done. 

### 3 Use the fasteners listed below at each pressure relief door location to insta ll the webs that were kept when the Instructions in Figure 

### 3 were done. 4 Use the screws that were kept when Rgure 3 was done to Insta ll the access cover on the web . The Instructions given below agree with the leHer shown In the upper-left corner of the fastener symbols in the figure. A number In the l ower-right comer of the fastener symbol is the length of the fastener. A Drill fastener holes In web and cargo door structure to 0 . 200 

### (+ 0 . 003 or • 0.000) i nch diameter. I nstall a HI-Lok BACB30FP6·( ) with a collar BACC30M6 . 

### B lnstaU a rivet MS20470D6-7 (24 Places) .

F IGURE 

### 6. WEB INSTALLATION Jul26/90 REV. 2: Apr 

### 15/93 3477 37

## BDIIND

N umbe r : Date: Revision 2: ATASystem: Prepa red By: 34 77 July 26. 1990 April 15. 1993 5211 Ma rk M iller 

### Commercial Ai rp l ane Group 

# 707/720 Serv ice Bulletin Eva lu atio n Fo rm

SUBJECT : DOORS- MAIN CARGO DOOR- LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR H INGE F ITI I NG REPLACE M E N T Use th i s evaluation form to tell us what you think or the quality or this servi ce bulletin. We will use the data that you give us to Im prove the qua lit y of o u r service bulleti ns. Pl ease Incl ude data about these or other Items: • Did thi s service bulletin meet your estimate or qua li ty?

- How easy Is this service bulletin to understand?

- Are th e P l anning Information. Materia l I nformation and Acco m plishment Instructions satisfactory?

- Will you do this service bulletin fully? II not , pl ease tell us why .

- Is the Manpower estimate satisfactory? NOTE : P l ease do not use this evaluation form to tell us to ma ke changes to your manua l s . To make these changes. p l ease use a Publication Change Request (PCR) form. Please give us th is data : OPERATOR : P R EPAREDBY: --------------------------- ORGAN IZATI ON : TODAY'S DATE : -------- TITLE: TELEX CODE : TE LEPHONE NUMBER: COMMENTS :

II you have other comments please use the other side. Thank you lor the time you used to complete this form . Give the completed evaluation form to your Boeing FJeld Service Representative or send the evaluation form directly to th is address: R .G. Kelsey. Manager Service Bulletin Engineering Boeing Commercial Airplane Group P .O. Box 3707, Mall Stop 2L·02 Sea!Ue, WA 98124·2207

BOEING COMMERQAJ... AJRPLANE CROUP P.O SOX 3107 SEAm£. WASHI NGTON 93124·22D7