# Boeing Service Bulletin 3477: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2013-0215, the docket of AD 2016-19-16. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Service Bulletin 3477](https://openairdocs.org/service-documents/boeing/sb-3477.md) - Title as filed: FAA-2013-0215_SB 3477_R2--BOEING - Pages: 42 - PDF: https://openairdocs.org/files/sha256/92/0f/920fc3d5b904d60c4af19d9a9de127971164446de0e1c152ca56394f2d61d4ec - Page: https://openairdocs.org/service-documents/boeing/sb-3477/file/920fc3d5b904 ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) BEHINO Commercial 707/720 Airplane Group Service Bulletin Number: 3477 Revision Transmittal Sheet Date: July 26, 1990 Revision 2: April 15, 1993 ATA System: 5211 SUBJECT: DOORS - MAIN CARGO DOOR - LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTING REPLACEMENT This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive 91-22-04, Amendment 39-8064, is related to this service bulletin. No more work is necessary on airplanes changed by the initial release or Revision 1 of this service bulletin. SUMMARY This revision 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 fitting. This revision also defines the maximum allowable wear limits for the latch cams. Paragraph I.A., Effectivity, shows changes of airplane operators. Each operator should 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 lines have no important changes. REVISION HISTORY Initial Release: July 26, 1990/ Revision 1: June 4, 1992 Revision 2: April 15, 1993 BOEING COMMERCIAL AIRPLANE GROUP P.O. BOX 3707 SEATTLE. WASHINGTON 98124-2207 ### Page 2 (OCR) BOEINO Commercial 707/720 Airplane Group Service Bulletin Number: Date: 3477 July 26, 1990 Summary Revision 2: April 15, 1993 ATA System: 5211 SUBJECT: DOORS - MAIN CARGO DOOR - LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTING REPLACEMENT BACKGROUND The main cargo 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 designed, better latch cams, and better hinge fittings for the pressure relief 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 Freighter Boeing has also received reports of wear of the latch cams on the main cargo doors on 707 and 727 Cargo and Freighter airplanes. Wear of the lock stop part of the hinge fittings and of the latch cams is thought to be caused by incorrect operation sequence of the hydraulic system of the 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 extend the service life of the door latch system. Continued operation with installed latch cams and hinge fittings that are worn beyond the limits given in 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 fittings or the latch cams are worn beyond the limits given in this service bulletin. ACTION At the next "C" check after receipt of this service bulletin, or 3000 flight-cycles, whichever occurs sooner, do a visual inspection of the mating surfaces on the hinge fittings and the latch cams. If the hinge fittings are not worn, or are worn within the limits given in this service bulletin, either install new hinge fittings and latch cams, or do the visual inspection again at each "5C" check, or 8000 flight-hours, whichever occurs sooner. If the hinge fittings are worn beyond the limits given in this service bulletin, install new hinge fittings and latch If the latch cams are worn or damaged, install new hinge fittings and latch cams. After the new hinge fittings and latch cams are installed as shown in this service bulletin, return to the normal inspection interval. Federal Aviation Administration (FAA) Airworthiness Directive 91-22-04, Amendment 39-8064 is related to this service bulletin EFFECTIVITY All 707 airplanes with main cargo doors MANPOWER Total Man hours - 34 for each airplane Elapsed Time - 17 Hours MATERIAL INFORMATION Boeing Supplied Kit See Paragraph IF for applicable terms and conditions. BOEING COMMERCIAL AIRPLANE GROUP P.O. BOX 3707 SEATTLE. WASHINGTON 98124-2207 Summary Page 1 of 2 ### Page 3 (OCR) BOEING SERVICE BULLETIN 3477 INBD PRESSURE RELIEF DOOR LATCH CAM- LATCH CAM BELLCRANK REPLACE THE HINGE FITTINGS REPLACE THE LATCH ON EACH PRESSURE RELIEF DOOR CAMS AND THE BELLCRANK 764748 (2 PLACES) INBD (4 PLACES) Jul 26/90 REV. 2: Apr 15/93 Summary Page 2 of 2 ### Page 4 (OCR) BOEINO Airplane Commercial 707/720 Group Service Bulletin Number: 3477 Date: July 26, 1990 Revision 2: April 15, 1993 ATA System: 5211 SUBJECT: DOORS - MAIN CARGO DOOR - LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTING REPLACEMENT 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Affected Refer to the Service Bulletin Index Document D6-1647, Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This change is applicable only to airplanes given below. IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER AERO URUGUAY (AUG) 07454 AERONAVES DEL PERU (REC) 07606 07618 AFRICAN AIRLINES (AFX) 07049 AHK AIR HONG KONG LTD. (AHK) 07008 08077 AIR CHINA (BEJ) 09003-09004 09006 AIR RWANDA (RWD) 08002 AIR TCHAD AIRLINES (TCH) 08402 ALENIA (AET) 08329-08330 ALYEMDA DEM. YEMEN AIRLINES (ALY) 08075 08475 ANGOLA AIRLINES (ANG) 07079 07081 20120 07608 07684 08401 Jul 26/90 3477 REV. 2: Apr 15/93 Page 1 of 37 ### Page 5 (OCR) BOEING SERVICE BULLETIN 3477 AVIATION CONSULTANTS (ACT) 07603 08073 AVIATION RESEARCH CENTRE (AVR) 07701-07702 AVISTAR CYPRUS LTD. (APU) 08003 BMAC E-3A FLT. CREW TRAINING (B02) 07403 07455 BUFFALO AIRWAYS, INC. (BUF) 07010 07042 07054 07207 07259-07260 07620 07807 07816 08152 08191 CANADIAN DEPT OF DEFENSE (DND) 08406-08410 CHALLENGE AIR CARGO (CHA) 08055 CHILIAN AIR FORCE (CHF) 07619 CHINA SOUTHWEST AIRLINES (XIN) 09001-09002 09005 COLOMBIAN AIRFORCE (CLB) 07109 COMTRAN INTERNATIONAL INC. (CII) 07078 CORDOBA AIR CARGO (CAG) 07625 CORSAIR (CRA) 07614 DIARO AIR SERVICES (DAR) 07052 07607 07802/ 08309 08474 DOMINICANA AIRLINES (DOM) 08192 DUBAI AIR WING (DAW) 09251 E-SYSTEMS (ESM) 08172 ECUATORIANA AIRLINES (ECU) 07045 REV. 2: Apr 15/93 Jul 26/90 347] ### Page 6 (OCR) BOEING SERVICE BULLETIN 3477 EGYPTAIR (EGP) 08201 08203 08205-08207 08210 EL AL ISRAEL AIRLINES, LTD. (ELA) 08581-08582 ETHIOPIAN AIRLINES, CORP. (ETH) 08129 EXECUTIVE AVIATION SERVICES (EXS) 07611 F.F.T. FRESH FOOD TRADING (FFT) 07262 FASTAIR CARRIER (FAC) 07458 FLORIDA WEST AIRLINES (PAI) 07615-07616 FUERZA AEREA ARGENTINA (AGF) 06461 08310 08312 08452 GENERAL ELECTRIC CORP. (GEC) 02017 GERMAN REPUBLIC (GRF) 08221-08224 GLOBAL AIR (GLH) 08051 GOVERNMENT OF BRAZIL (BRZ) 07080 08304 08308 08314 GOVERNMENT OF EGYPT (EGG) 08209 GRUMMAN MELBOURNE SYSTEM (GMS) 07057 07107 07265 07808-07809 07812-07813 07817 08102 08327 HEAVYLIFT AIRCRAFT ENGINEERING (HVL) 07075 INDONESIAN AIR FORCE (IDO) 09227 INTERNATIONAL AIR LEASES (IAL) 07043 IRAN AIR (IRN) 07016 08551-08553 09438 Jul 26/90 REV. 2: Apr 15/93 347] ### Page 7 (OCR) BOEING SERVICE BULLETIN 3477 IRAN ISLAMIC AIR FORCE (IAF) 09101-09107 09161-09167 IRAQI AIRWAYS (IRQ) 09221-09223 ISRAELI AIR FORCE (ISR) 07406-07407 08021 08243 08251 JAMAHIRIYA AIR TRANSPORT (UAA) 07502-07503 07605 JET CARGO LIBERIA LTD. (JTC) 08501 JET LEASE, INC. (JLI) 07058 07401 07451 JUGOSLOVENSKI AEROTRANSPORT (JAT) 07073 LADECO (LDE) 08128 LAN-CHILE S.A. (LAN) 07253 07602 07661 LIBYAN ARAB (LAA) 07819 09411 LLOYD AERO BOLIVIANO (LAB) 07261 MIDDLE EAST AIRLINES S.A. (MEA) 07251-07252 07264 08317-08318 08404-08405 MILLON AIR, INC. (MLA) 07257 NAGANAGANI (NNG) 08072 NIGERIA AIRWAYS, LTD. (NIA) 08319 08333 NMB SINGAPORE LTD. (NMB) 08313 NORTH ATLANTIC TREATY ORGANIZATION(NATO) (NAT) 07904-07906 OKADA AIR (OKD) 08301 OMEGA AIR (OMG) 07255 07810 08173 Jul 26/90 REV. 2: Apr 15/93 3477 ### Page 8 (OCR) BOEING SERVICE BULLETIN 3477 PAKISTAN INTERNATIONAL AIRLINES CORP. (PIA) 07104 07267 08143-08144 08325 PAN AVIATION (PAV) 07053 PERUVIAN AIR FORCE (PRF) 07266 QATAR (QAT) 08076 09421 RACE AVIATION CORPORATION (RAC) 07006 REPUBLIC OF LIBERIA (LBG) 05603 ROYAL AIR MAROC (RAM) 07622-07623 ROYAL AUSTRALIAN AIR FORCE (RAA) 07814-07815 07818 07820 09288 ROYAL JORDANIAN AIRLINE (RJA) 08101 ROYAL MOROCCAN AIR FORCE (MRC) 09441 S. R. ACQUISITION CORP. (SRC) 08127 SAETA S.A. (SAE) 07191 SAFAIR FREIGHTERS (PTY) LTD. (SFA) 07268 08242 08244 SAUDI ROYAL FLEET (SRF) 09281 09290 SCIBE-AIRLIFT KINSHASA (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 Jul 26/90 REV. 2: Apr 15/93 3477 ### Page 9 (OCR) 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 07077 07801 TAROM ROMANIA (TRM) 07044 07056 09201-09203 TRANS ARABIAN AIR TRANSPORT (TRB) 07047 08054 TRANS MEDITERRANEAN AIRWAYS (TMA) 07041 07046 07206 07453 08121-08122 08125 TRANSBRASIL AIRLINES INC. (TBL) 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 VENEZUELAN AIR FORCE (VEN) 08103-08104 ZAS AIRLINES (ZAA) 08007 08074 IDENTIFICATION BY VARIABLE NUMBER 02017 05603 06461 07001-07017 07041-07059 07071-07081 07101-07109 07181 07191 07201-07215 07251-07271 07401-07407 07451-07458 07501-07504 07601-07626 07661-07662 07681-07684 07701-07702 07801-07821 07901-07907 08001-08008 08021 08051-08056 08071-08077 08101-08104 08121-08129 08141-08144 08151-08153 08171-08173 08191-08192 08201-08210 08221-08224 08241-08244 08251 08261 08271 08301-08320 08324-08330 08333 08401-08410 08451-08452 08471-08475 08501-08502 08551-08553 08581-08582 09001-09006 09101-09107 09161-09167 09201-09204 09221-09223 09227 09231-09232 09251 09271 09281 09286-09290 09411 09421 09438 09441 Jul 26/90 3477 REV. 2: Apr 15/93 ### Page 10 (OCR) BOEING SERVICE BULLETIN 3477 2. Spares Exy pants are ourd, ster lo ferg apns D, Efed in Parts Accoun abiy, ing Pa resonendab use f Jul 26/90 REV. 2: Apr 15/93 3477 ### Page 11 (OCR) BOEING SERVICE BULLETIN 3477 B. Reason The main cargo doors on the 707 airplanes that have main cargo doors are almost the same as those on the 757 Package Freighter airplane. 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 hinge fittings for the 757 Package Freighter were designed to provide better resistance to wear. This service bulletin shows how to install the better latch cams and hinge fittings on the main cargo doors on 707 airplanes that have a main cargo door. Installation of the better parts on the main cargo doors will extend the service life of the door latch system. 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 Freighter airplanes. Boeing has also received reports of wear of the latch cams on the main cargo doors on 707 and 727 Cargo and Freighter airplanes. Wear of the lock stop part of the hinge fittings and of the latch cams is thought to be caused by incorrect operation sequence of the hydraulic system of the main cargo door. Incorrect operation sequence of the hydraulic system of the main cargo door can occur in service due to wear of components of the door's hydraulic system, or due to a hydraulic system that is not adjusted correctly. Continued operation with installed latch cams and hinge fittings that are worn beyond the limits given in this service bulletin is not satisfactory. Persons cannot make sure that the main cargo door is correctly locked and latched under all possible operational conditions if the hinge fittings 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 fitting. This revision also defines the maximum allowable wear limits for the latch cams. Jul 26/90 3477 REV. 2: Apr 15/93 8 ### Page 12 (OCR) BOEING SERVICE BULLETIN 3477 C. Description At the next "C" check after receipt of this service bulletin, or 3000 flight-cycles, whichever occurs sooner, do a visual inspection of the mating surfaces of the hinge fittings (on the pressure relief doors) and the latch cams. If the hinge fittings are not worn, or are worn within the limits given in this service bulletin, either install the new hinge fittings and latch cams as shown in this service bulletin, or do the visual inspection again at each "5C" check, or 8000 flight-hours, whichever occurs sooner, until the hinge fittings and latch cams are replaced as shown in this service bulletin. If the hinge fittings are worn 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 If it is necessary to install the new hinge fittings and latch cams, remove the lining and the insulation from the lower part of the main cargo door. Remove and discard the four pairs of 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 install new hinge fittings on the pressure relief doors. Do a test of the main cargo door to make sure that the door operates, latches, 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 for the main cargo door to make sure it operates correctly. Install the lining and the insulation on the inside of the cargo door and Federal 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 cargo 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 Installation" then the changes shown in this service bulletin 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 examined by the Federal Aviation Administration (FAA). The changes shown in this service bulletin agree with the applicable Federal Aviation Regulations (FAR's) and are FAA approved. The FAA has examined the inspection and replacement procedures specified in Revision 2 to Service Bulletin 3477, "DOORS - MAIN CARGO DOOR - LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTING REPLACEMENT". The FAA has approved the inspection and replacement procedures in Revision 2 of Service Bulletin 3477 as an alternative to those specified in Airworthiness Directive (AD) 91-22-04, Amendment 39-8064. Jul 26/90 3477 REV. 2: Apr 15/93 9 ### Page 13 (OCR) BOEING SERVICE BULLETIN 3477 E. Manpower Approximately 34 man-hours are necessary to do this change on one airplane. The data below shows an estimate of the man-hours necessary to do this change for each airplane. This estimate is for direct labor only, done only by an experienced crew. It does not include lost time such as: time to adjust to the workplace; schedule the work; examine the work; cure materials; make parts; find tools or other lost time. Adjust these estimates with operator man-hour data if necessary. Number of Elapsed Task Persons Man-Hours Time (Hours) Open Access 2 2 1 Change 2 26 13 Close Access 2 2 1 Test 2 4 2 TOTAL FOR EACH AIRPLANE 34 17 F. Material - Price and Availability Boeing can supply the kits shown in Paragraph II.A., Parts Necessary For Each Airplane, as shown below. Kit availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. ROLT Unit Price thru Kit Number Name (weeks) Oct 3, 1993 65-93534-1 (a) Top Kit 65-93534-9 Top Kit 51 $ 15,324.00 (a) Top Kit 65-93534-1 is held from more sales. Top Kit 65-93534-9 supersedes old Top Kit. The kits are subject to the terms and conditions of Boeing's standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States Dollars. Terms: Net 30 days. Send purchase orders and letters about the supply data to the Director of Spares and refer to this service bulletin number. G. Tooling - Price and Availability None Jul 26/90 3477 REV. 2: Apr 15/93 10 ### Page 14 (OCR) BOEING SERVICE BULLETIN 3477 H. Weight and Balance None 1. References 1. Existing 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 Bulletins: o 3311 "Main Cargo Door Deactivation/Reactivation System Installation" o 3387 "Main Cargo Door Cam Support Fitting Inspection and Replacement" e. Boeing Service Letters: o 707-SL-52-2 "Main Cargo Door Pressure Door Locking Stops" o 707-SL-52-12 "Main Cargo Door Partial Opening in Flight" f. FAA Airworthiness Directive 91-22-04, Amendment 39-8064 2. Data supplied in support of this service bulletin: None J. Publications Affected Publication Chapter-Section Overhaul Manual 52-36 707 Illustrated Parts Catalog 52-30 Jul 26/90 REV. 2: Apr 15/93 3477 ### Page 15 (OCR) 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 installation of the parts easier. One 65-93534-9 top kit and operator supplied materials specified in Paragraph II.A.2., Parts and Materials Supplied by the Operator, are necessary to change each airplane. 65-93534 - KIT - MAIN CARGO DOOR LATCH CAMS AND LOCK FITTINGS -6 -5 -4 -3 -2 -1 Quantity Part Number Nomenclature - 65-93534-1 Top Kit (a) 1 65-93534-2 Kit, Latch Cams and Bellcrank Installation, Body Station 495 65-93534-3 Kit, Latch Cams and Bellcrank Installation, Body Station 530 1 65-93534-4 Kit, Latch Cams and Bellcrank Installation, Body Station 570 1 65-93534-5 Kit, Latch Cams and Bellcrank Installation, Body Station 610 2 65-93534-6 Kit, Pressure Relief Valve Hinge Installation, Body Stations 510 and 143N8027-1 Cam 143N8027-2 Cam 143N8060-1 Cam 143N8060-2 Cam 65-93534-7 Hinge Fitting 65-93534-8 69-21969-11 69-21969-12 69-23438-1 Cam 69-23438-2 Cam 69-23439-3 Cam 69-23439-4 Cam 69-34974-3 Bracket, Lock Indicator 1 1 69-34974-4 Bracket, Lock Indicator AN960C616L Washer 2 2 2 AN960PD8L Washer Jul 26/90 3477 REV. 2: Apr 15/93 12 ### Page 16 (OCR) BOEING SERVICE BULLETIN 3477 65-93534 - KIT - MAIN CARGO DOOR LATCH CAMS AND LOCK FITTINGS Part Number Nomenclature 1 BACB30EL5CN19 Bolt, Countersink 3 6 3 BACW10P208S Washer 10 MS20470B8-14 Rivet 6 3 NAS1104-20W Bolt NAS1105-20W Bolt 1 NAS602-7 Screw NAS679A08W Nut 6 3 NAS679A4W Nut 2 2 NAS679A5 Nut (a) Top Kit 65-93534-1 is held from more sales. Top Kit 65-93534-9 replaces old top kit 65-93534 - KIT - MAIN CARGO DOOR LATCH CAMS AND LOCK FITTING -6 -13 -12 -11 -10 -9 Quantity Part Number Nomenclature - 65-93534-9 Top Kit 1 65-93534-10 Kit, Latch Cams and Bellcrank Installation, Body Station 495 1 65-93534-11 Kit, Latch Cams and Bellcrank Installation, Body Station 530 1 65-93534-12 Kit, Latch Cams and Bellcrank Installation, 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 • 65-93534-20 Cam • 65-93534-17 Cam 65-93534-14 Cam 65-93534-22 Cam 65-93534-7 Hinge Fitting 65-93534-8 Hinge Fitting 65-93534-18 Bellcrank 65-93534-15 Bellcrank 65-93534-23 Cam * 65-93534-16 Cam Jul 26/90 3477 REV. 2: Apr 15/93 13 ### Page 17 (OCR) BOEING SERVICE BULLETIN 3477 65-93534 - KIT - MAIN CARGO DOOR LATCH CAMS AND LOCK FITTING 6 -13 - 12 -11 -10 -9 Quantity Part Number Nomenclature 65-93534-9 Top Kit 65-93534-19 Cam 65-93534-21 Cam 69-34974-3 Bracket, Lock Indicator 69-34974-4 Bracket, Lock Indicator AN960C616L Washer 2 2 2 AN960PD8L Washer 1 BACB30EL5CN19 Bolt, Countersink 6 6 BACW10P208S Washer 10 MS20470B8-14 Rivet 6 6 NAS1104-20W Bolt NAS1105-20W Bolt NAS602-7 Screw NAS679A08W Nut 6 6 NAS679A4W Nut 2 2 NAS679A5 Nut\ 2. Parts and Materials Supplied by the Operator: Part Number or Quantity Specification Name 50 MS20470D6-7 Rivet, Universal Head BACB30FP6-3 Hi-Lok BACB30FP6-4 Hi-Lok BACB30FP6-5 Hi-Lok BACB30FP8A( ) Hi-Lok 20 BACB30GY8A( )X Lockbolt 20 BACC30K8 Collar 14 BACC30M6 Collar 16 BACC30M8 Collar As Necessary BMS 10-11, Type I Primer As Necessary BMS 5-95, Class A and Class B Sealant As Necessary MIL-G-23827 Grease 1 inch long by 1.75 inch diameter rod, 2024-T4 or 6061-T4 aluminum. See Figure 2. Jul 26/90 3477 REV. 2: Apr 15/93 14 ### Page 18 (OCR) BOEING SERVICE BULLETIN 3477 B. Parts Required to Modify Spares None C. Special Tools and Equipment Required The special tool shown in Figure 2 of this bulletin can be made by the operator. Maintenance and overhaul tools can be necessary as given in any manuals that are listed in Paragraph I.l., References, of this bulletin. Operators should review their tool inventory to make sure that tools are available. Jul 26/90 3477 REV. 2: Apr 15/93 15 ### Page 19 (OCR) 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 indented part is the number of parts used on the next higher assembly. The quantity of the non-indented part is the number of parts changed on the airplane. Installed Part Number Nomenclature Qty DC New Part Number PNC RC 65-25339-5 Latch Cam Assembly 1 DIS 65-93534-13 S A Of: Sta. 600 + 4.65 (Spares only) 69-21971-4 Latch Cam 1 DIS 65-93534-22 S A 69-23438-1 Latch Cam 1 DIS 65-93534-23 S A 69-21969-3, -8, Bellcrank Assembly 1 DIS 65-93534-15 S A or -502 65-25339-6 Latch Cam Assembly 1 DIS 65-93534-12 S A Of: Sta. 571.80 (Spares only) 69-23439-3 Latch Cam 1 DIS 65-93534-20 S 69-23439-4 Latch Cam DIS 65-93534-17 S 69-21969-1, -7, or Bellcrank Assembly 1 DIS 65-93534-18 A -501 65-25339-7 Latch Cam Assembly 1 DIS | 65-93534-11 S Of: Sta. 528.20 (Spares only) 69-23439-3 Latch Cam 1 DIS 65-93534-20 S 69-23439-4 Latch Cam DIS 65-93534-17 S A 69-21969-2, -7, or Bellcrank Assembly 1 DIS 65-93534-18 S -501 65-25339-8 Latch Cam Assembly 1 DIS 65-93534-10 S Of: Sta. 495.35 (Spares only) 69-21971-3 Latch Cam 1 DIS 65-93534-14 S A 69-23438-2 Latch Cam 1 DIS 65-93534-16 S A 69-21969-4, -8, or Bellcrank Assembly DIS 65-93534-15 -502 65-26120-1, -3, Hinge, Pressure Valve Sia 65-93534-7 or-5 65-26120-2,-4, or Hinge, Pressure Valve DIS 65-93534-8 A -6 69-21971-3 or -501 Latch Cam 1 DIS 65-93534-14 I S 69-21971-4 or -502 Latch Cam 1 DIS 65-93534-22 I S 69-23439-1 or -3 Latch Cam 1 Sia 65-93534-20 I S A 69-23439-2 or -4 Latch Cam 1 DIS 65-93534-17 I S Jul 26/90 LIVE REV. 2: Apr 15/93 91 ### Page 20 (OCR) 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 interchangeable. Do not replace one part with the other. Jul 26/90 3477 REV. 2: Apr 15/93 17 ### Page 21 (OCR) BOEING SERVICE BULLETIN 3477 BLANK PAGE Jul 26/90 3477 REV. 2: Apr 15/93 18 ### Page 22 (OCR) BOEING SERVICE BULLETIN 3477 III. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. The paragraphs identified with letters give the general work instructions and the necessary tests. The instructions identified with numbers on the figures give the recommended sequence of operations. 2. Unless specified differently, the dimensions and tolerances given below are used: - All linear dimensions are in inches - Tolerance on linear dimensions other than rivet and bolt edge margin is plus or minus 0.03 - Tolerance on rivet and bolt 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 bolts are found in the 707 Structural Repair Manual, Chapter 51 3. Refer to 707 Structural Repair Manual Chapter 51 for alternative fasteners. 4. Obey all warnings and cautions in the specified manual 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 worn 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, install new hinge fittings and latch cams in 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 interior lining and the insulation from the lower area of the main cargo door (Reference - 707 Maintenance 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, Subject 52-11-0, Inspection/Check. Cycle the latch cams into the locked position with the door in the open position as shown in the Maintenance Manual Subject 52-11-0. E. Remove pressure from the hydraulic system for the main cargo door (Reference - 707 Maintenance Manual, Subject 52-11-0, Maintenance Practices). F. Remove the most forward and aft main cargo door latch actuators as shown in the 707 Maintenance Manual, Subject 52-11-11. Jul 26/90 3477 REV. 2: Apr 15/93 19 ### Page 23 (OCR) BOEING SERVICE BULLETIN 3477 G. Remove the web and access cover from each pressure relief door location as shown in Figure 4. H. Remove the pressure relief doors and carefully drill out the rivets that attach the hinge fittings to the pressure relief doors as shown in Figure 5, circle notes 1 through 9. 1. Remove the latch 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 fittings on the pressure relief doors as shown in Figure 5, circle notes 10 through 26. K. Install the most forward and aft main cargo door latch actuators as shown in the 707 Maintenance Manual Subject 52-11-11. L. Operate the main cargo door as necessary to remove air from the hydraulic system for the main cargo door. Select door open control and open door sufficient to remove the wood blocks. Do not operate the main cargo door into the completely closed 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/Test). NOTE: Inspect to make sure that the tab on the marking bracket is inserted into the index hole in the cam. Also do a check to see if the marking bracket is visible through the viewport in the cargo door skin when the door is closed and the latch cams are in the latched position. N. Do a test of the warning system for the main cargo door to make sure that it operates correctly (Reference - 707 Maintenance Manual, Subject 52-70-00 or -01) O. 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 Figure 6. Q. Install the insulation and the interior lining on the lower area of the main cargo door (Reference - 707 Maintenance Manual, Subjects 52-11-171 and 52-11-192). R. Restore airplane to serviceable condition. Jul 26/90 3477 REV. 2: Apr 15/93 20 ### Page 24 (OCR) BOEING SERVICE BULLETIN 3477 Illustration Table of Contents Title Page Figure 1. Inspection . 22 Figure 2. Alignment Tool Fabrication . 24 Figure 3. Latch Cam Replacement ... 25 Figure 4. Web Removal .. 31 Figure 5. Hinge Fitting Replacement . 32 Figure 6. Web Installation 36 Jul 26/90 3477 REV. 2: Apr 15/93 21 ### Page 25 (OCR) BOEING SERVICE BULLETIN 3477 SEE DETAIL I ALMOST THE SAME AS DETAIL I ALMOST THE SAME AS DETAIL I → FWD INBD PRESSURE RELIEF DOOR PRESSURE DOOR PRESSURE SEAL 0.15 INCH MINIMUM OVERLAP REQUIRED VIEW A-A (2 PLACES) HINGE TIP OF FITTING HINGE 2 FITTING - 0.12 INCH MAXIMUM FLAT ALLOWED FIGURE 1. INSPECTION Jul 26/90 LIVE REV. 2: Apr 15/93 ### Page 26 (OCR) BOEING SERVICE BULLETIN 3477 LATCH CAM LATCH CAM DETAIL I The instructions given below agree with the numbers shown inside the circle symbols in the figure: 1 Do a visual inspection of the area on each latch cam that contacts a hinge fitting on a pressure relief door (4 places). If the cam is notched as shown, or if the cam shows any damage beyond 0.05 inches deep from contact with the hinge fitting, replace the latch cams and the hinge fittings as shown in this service bulletin. 2 Measure the tip of each hinge fitting as shown (4 places). If any of the hinge fittings are worn beyond the limit shown, replace the latch cams and the hinge fittings as shown in this service bulletin. Refer to the 707 Maintenance Manual, Subject 52-11-0. NOTE: Removal of the pressure relief door from the main cargo door can be necessary to do the inspection given in Step 2, above. Instructions for removal of the pressure relief door are given in the 707 Maintenance Manual, Subject 52-11-43. 3. If either the cam or the hinge fitting is worn, measure the overlap as shown in view AA. Make sure that there is minimum of 0.15 inch overlap. If there is less than a 0.15 inch overlap, replace the cam and the hinge fittings as shown in this service bulletin. FIGURE 1. INSPECTION Jul 26/90 3477 REV. 2: Apr 15/93 23 ### Page 27 (OCR) BOEING SERVICE BULLETIN 3477 90° 1-10 DIA. 0.84 0.54 0.86 R 0.55 R 0.50 0.50 VIEW A-A VIEW B-B The instructions given below agree with the numbers shown inside the circle symbols in the figure: 1 Make the two alignment tools to the dimensions shown from one of the materials given below: o 2024-T42 aluminum rod, 1.75 inch outside diameter o 6061-T42 aluminum rod, 1.75 inch outside diameter FIGURE 2. ALIGNMENT TOOL FABRICATION Jul 26/90 REV. 2: Apr 15/93 3477 ### Page 28 (OCR) BOEING SERVICE BULLETIN 3477 MAIN CARGO DOOR SEE DETAIL I SEE DETAIL II DETAIL III SEE DETAIL IV SEE DETAIL V SEE DETAIL VI SEE DETAIL I DETAIL II , FWD INBD AD5224 FIGURE 3. LATCH CAM REPLACEMENT Jul 26/90 3477 REV. 2: Apr 15/93 25 ### Page 29 (OCR) BOEING SERVICE BULLETIN 3477 LUG ASSEMBLY SEE DETAIL II FOR LATCH CAM FASTENER LOCATIONS LATCH CAM 1.00 1 TRIM AREA 0.75 SHEAR WEB > FWD DETAIL I AFT LATCH CAM AND BELLCRANK ASSEMBLY SHOWN, FORWARD LATCH AND BELLCRANK ASSEMBLY OPPOSITE FRAME SHEAR WEB 69-24209-() 2 11 9-66095-1 , LUG ASSEMBLY → INBD DETAIL II A05225 AFT LUG ASSEMBLY SHOWN, FORWARD LUG ASSEMBLY OPPOSITE VIEW LOOKING FORWARD FIGURE 3. LATCH CAM REPLACEMENT Jul 26/90 3477 REV. 2: Apr 15/93 • 26 ### Page 30 (OCR) BOEING SERVICE BULLETIN 3477 65-93535-14 LATCH ACTUATOR 10 ฿ (4)9 9) 65-93535-16 BELLCRANK 65-93535-159 69-34974-3 DETAIL III 965-93535-19 69-34974-46 LATCH ACTUATOR 3 10 65-93535-17 65-93535-189 BELLCRANK ( 4X "FWD A05227 DETAIL IV FIGURE 3. LATCH CAM REPLACEMENT Jul 26/90 LIVE REV. 2: Apr 15/93 1Z ### Page 31 (OCR) BOEING SERVICE BULLETIN 3477 69-34974-46 LATCH ACTUATOR 65-93535-219 9 65-93535-18 BELLCRANK DETAIL V 65-93535-20 65-93535-15 65-93535-239 49 • 9 65-93535-22 BELLCRANK 6 69-34974-3 A05228 DETAIL VI FIGURE 3. LATCH CAM REPLACEMENT Jul 26/90 3477 REV. 2: Apr 15/93 28 ### Page 32 (OCR) BOEING SERVICE BULLETIN 3477 6 MARKING BRACKET VIEWPORT LATCH CAM DOOR SKIN • INBD VIEW A-A A05230 The instructions given below apply to latch cams and bellcranks located at Body Stations 495, 530, 570, and 610. See Details I, II, Ill and VI for complete figures that show replacement of the forward and aft latch cam and bellcrank. See Details IV and V for complete figures that show replacement of the latch cam and bellcrank assembly located at Body Stations 530 and 570. The instructions given below agree with the numbers shown inside the circle symbols in the figure: 1 For the most forward and aft latch cam, trim the shear web 69-24209-(* ) and extend the cut out of the lower beam web and doubler 65-25338-(* ) inboard, up to the maximum amount as shown. Do not trim shear web or extend the cut out of the lower beam web beyond what is necessary for the removal of the lug assembly. Maintain 0.50 R or larger corner radius. On the aluminum shear web 69-24209-3, -4 and the lower beam web and doubler 65-25338-(* ), finish trimmed areas with brushed on chemical film treatment (Alodine or Iridite), and one coat of BMS 10-11 Type I primer. Touch up with one coat of decorative enamel. On steel shear web 69-24109-7 and -8, finish trimmed areas with brush cadmium plate and one coat of BMS 10-11 Type I primer. Touch up with one coat of decorative enamel. 2 Remove the fasteners that attach the forward and aft Lug Assembly to the frame. 3 Remove the fastener that attaches the latch actuator to the bellcrank. Keep the fastener for later use. NOTE: If the fastener is worn, corroded, or is missing finish, 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. FIGURE 3. LATCH CAM REPLACEMENT Jul 26/90 3477 REV. 2: Apr 15/93 29 ### Page 33 (OCR) BOEING SERVICE BULLETIN 3477 6 Use a screw NAS602-7, two washers AN960PD8L and a nut NAS679A08W to install the marking bracket on the new latch cam. Make sure that the tab on the marking bracket fits into the index hole on the cam. Make sure that the cams are in the latched position, and verify that the marking bracket is visible through the viewport in the cargo door skin. CAUTION: Make sure that the correct marking bracket is installed on each cam as shown in Figure 3. There are two different part numbered marking brackets. If the wrong bracket is installed on the cam, it will not be visible through the viewport in the door skin when the door is in the latched position. 7 Apply a thin coat of grease MIL-G-23827 (or equivalent) to the bearing surfaces of the new latch cams and the new bellcrank. 8 Apply primer (Reference - BMS 10-11, Type I) to the tapered end of bellcrank. Do not allow the primer to dry before the next step is done. 9 Use the fasteners indicated to install the new latch cams and the new bellcrank in position on the cargo door. NOTE: Make sure that the forward an aft lug assembly are in place prior to the installation of the most forward and aft latch cams and bellcrank. 10 Attach the latch actuator to the new bellcrank. Use the fasteners that were kept when the instructions 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 of the fastener symbols in the figure. A number in the lower-right corner of the fastener symbol is the length of the fastener. A Install a bolt NAS1104-20W with a washer BACW10P208S under the bolthead. Use a nut NAS679A4W to secure the bolt, and torque the nut with 50 to 80 inch-pounds. B Install a bolt NAS1105-20W with a washer AN960C616L under the bolthead. Use a nut NAS679A5 to secure the bolt, and torque the nut with 100 to 150 inch-pounds. C Install a countersink bolt BACB30EL5CN19 with a nut NAS679A5. Torque the nut with 60 to 65 inch-pounds. D Install BACB30GY8A( )X Lockbolt with a BACC30K8 Collar. FIGURE 3. LATCH CAM REPLACEMENT Jul 26/90 3477 REV. 2: Apr 15/93 30 ### Page 34 (OCR) BOEING SERVICE BULLETIN 3477 INBD The instructions given below agree with the numbers shown inside the circle symbols 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 panel for later 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 later use. FIGURE 4. WEB REMOVAL Jul 26/90 3477 REV. 2: Apr 15/93 31 ### Page 35 (OCR) BOEING SERVICE BULLETIN 3477 SEE DETAIL I FOR DOOR EXTERNAL VIEW INBD SEE DETAIL II STA STA 480 600D DETAIL I A05233 DOOR EXTERNAL VIEW FIGURE 5. HINGE FITTING REPLACEMENT Jul 26/90 3472 REV. 2: Apr 15/93 ### Page 36 (OCR) BOEING SERVICE BULLETIN 3477 8 10 11 19 23 PRESSURE RELIEF DOOR HINGE FITTING 9 13 14 BELLCRANK NUT 4125 9 13 14 HINGE FITTING 4) 25 BOLT DETAIL II (4) 25) SPACER 913 HINGE FITTING SECTION A-A SPACER 7 13 18 23 (20 22 7 13 18 23 3 26 HINGE BOLT 16 21 NUT 7 13 (18 23) SECTION B-B PRESSURE RELIEF 12 19 (2 PLACES) DOOR 17 ALIGNMENT TOOLS VIEW C-C (2 PLACES) FIGURE 5. HINGE FITTING REPLACEMENT Jul 26/90 3477 REV. 2: Apr 15/93 33 ### Page 37 (OCR) BOEING SERVICE BULLETIN 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 closed and seated against its cutout in the main cargo door. 2 Make marks on the outside of the pressure relief door and on the outside of the cargo door skin with a marker that will 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 will be used later to correctly position the pressure relief door on the cargo door when the new hinge fittings are 3 At the aft pressure relief door location only, remove the hydraulic tubes that are located inboard of the pressure relief door. Temporarily plug or cap the open hydraulic tubes to make sure that hydraulic fluid does not spill all over in the pressure relief door area in the cargo door. 4 Remove the nut, the bolt, the washers and the spacers from the bellcrank on the torque tube that is above the pressure relief door. Keep all of this hardware for later use. 5 Remove the nut, the washer, and the bolt from the bellcrank on the torque tube that is above the pressure relief door. Keep all of this hardware for later 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 relief door. Keep all of this hardware for later use. 8 Remove the pressure relief door from the cargo door. 9 Carefully drill out the rivets that attach the hinge fittings to the pressure relief door. 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 marks on the cargo door skin. 11 Wedge the pressure relief door so that it is firmly seated in its cutout on the cargo door. NOTE: Make sure that the outside surface of the pressure door is flush with the outside skin of the main cargo door. Refer to the 707 Maintenance Manual, Subject 52-11-43. 12 Put the alignment tools that were made in Figure 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 turn 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 Jul 26/90 3477 REV. 2: Apr 15/93 34 ### Page 38 (OCR) BOEING SERVICE BULLETIN 3477 15 Rotate the hinge fittings until the 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 interferes with the cam, then do the steps that follow: a. Trim up to a maximum of 0.05 inch from the outboard surface on the hinge fitting. Make sure that the removal of material is done so to maintain the radius of the part. Maintain a 63 AA surface finish 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 Tightly clamp the hinge fittings to the pressure relief door and remove the wedges that held the pressure relief door in position in the cargo door. 17 Make sure that the pressure relief door moves freely with the new hinge fittings. 18 Remove the nut, the special bolt, the washers, and the spacer from the hinge points of the pressure relief door. Keep all of this hardware for later use. 19 Remove the pressure relief door form the cargo door, and remove the alignment tools from the cup of the cam. Make sure that the new hinge fittings are not moved out of the clamped position when the pressure relief door is removed. 20 Carefully drill matching 0.257 inch diameter (drill Size "F") holes in the new hinge fittings at locations where fastener holes 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 holes to the final size. NOTE As an option, the operator may use Hi-Loks BACB30FP8A() and collars BACC30M8 in place of rivets to install the hinge fitting to the pressure door. To use Hi-Loks Carefully 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 MS20470B8-14 or optional fasteners coated with sealant (Reference - BMS 5-95, Class A) to install the new hinge fittings on the pressure 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 is above the pressure relief door into 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. Torque 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 FITTING REPLACEMENT Jul 26/90 3477 REV. 2: Apr 15/93 35 ### Page 39 (OCR) BOEING SERVICE BULLETIN 3477 INBD SEE DETAIL I SEE DETAIL II (14 PLACES) (24 PLACES) FIGURE 6. WEB INSTALLATION Jul 26/90 REV. 2: Apr 15/93 3477 ### Page 40 (OCR) BOEING SERVICE BULLETIN 3477 (14 PLACES) 3 (24 PLACES) DETAIL II The instructions given below agree with the numbers shown inside the circle symbols in the figure: 1 Clean all old sealant from mating surfaces of the web and the cargo door structure. 2 Apply sealant (Reference - BMS 5-95, Class B) to mating surfaces of web 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 install the webs that were kept when the instructions in Figure 3 were done. 4 Use the screws that were kept when Figure 3 was done to install the access cover on the web. The instructions given below agree with the letter shown in the upper-left corner of the fastener symbols in the figure. A number in the lower-right corner 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) inch diameter. Install a Hi-Lok BACB30FP6-() with a collar BACC30M6. B Install a rivet MS20470D6-7 (24 Places). FIGURE 6. WEB INSTALLATION Jul 26/90 3477 REV. 2: Apr 15/93 37 ### Page 41 (No text on this page.) ### Page 42 (OCR) BOEINO Commercial 707/720 Airplane Group Service Bulletin Number: Date: 3477 July 26, 1990 Evaluation Form Revision 2: April 15, 1993 ATA System: 5211 Prepared By: Mark Miller SUBJECT: DOORS - MAIN CARGO DOOR - LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTING REPLACEMENT Use this evaluation form to tell us what you think of the quality of this service bulletin. We will use the data that you give us to improve the quality of our service bulletins. Please include data about these or other items: - Did this service bulletin meet your estimate of quality? - How easy is this service bulletin to understand? - Are the Planning Information, Material Information and Accomplishment Instructions satisfactory? - Will you do this service bulletin fully? If not, please tell us why. - Is the Manpower estimate satisfactory? NOTE: Please do not use this evaluation form to tell us to make changes to your manuals. To make these changes, please use a Publication Change Request (PCR) form. Please give us this data: OPERATOR: TODAY'S DATE: PREPARED BY: TITLE: ORGANIZATION: TELEX CODE: TELEPHONE NUMBER: COMMENTS: If you have other comments please use the other side. Thank you for the time you used to complete this form. Give the completed evaluation form to your Boeing Field Service Representative or send the evaluation form directly to this address: R.G. Kelsey, Manager Service Bulletin Engineering Boeing Commercial Airplane Group P.O. Box 3707. Mail Stop 2L-02 Seattle, WA 98124-2207 BOEING COMMERCIAL AIRPLANE GROUP P.O. BOX 3707 SEATTLE, WASHINGTON 98124-2207 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.