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September 26, 2002 Revision 2: January 15, 2010 767-53A0100 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 310
ALERT ALERT Commercial Airplane Group 767
ALERTALERT Service Bulletin Number: 767-53A0100 Date: September 26, 2002 Revision 2: January 15, 2010 ATA System: 5350 SUBJECT: FUSELAGE - Section 45 - STA 955 Rear Spar Bulkhead Side Fittings - Fail-safe Strap
- Inspection
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2002 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document or otherwise.
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ALERT ALERT
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Table of Contents Original Issue: September 26, 2002 Revision 2: January 15, 2010 767-53A0100 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 310 BOEING SERVICE BULLETIN 767-53A0100
ALERT ALERT
Table of Contents Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 33
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 34 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 34
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 55
3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 56
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 FIGURE 1: LOGIC DIAGRAM (DELETED) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64 FIGURE 2: STA 955 FAIL-SAFE STRAP INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . 65 FIGURE 3: FASTENER/PART REMOVE/REPLACE - GROUP 1 AIRPLANES - LEFT SIDE. . . . . . 67 FIGURE 4: FASTENER/PART REMOVE/REPLACE - GROUP 1 AIRPLANES - RIGHT SIDE . . . . . 76 FIGURE 5: FASTENER/PART REMOVE/REPLACE - GROUP 2, 3, 10 AIRPLANES - LEFT SIDE . . 85 FIGURE 6: FASTENER/PART REMOVE/REPLACE- GROUP 2, 3, 10 AIRPLANES - RIGHT SIDE . . 95 FIGURE 7: FASTENER/PART REMOVE/REPLACE- GROUP 4, 7 AIRPLANES - LEFT SIDE. . . . . 105 FIGURE 8: FASTENER/PART REMOVE/REPLACE- GROUP 4, 7 AIRPLANES - RIGHT SIDE . . . . 115 FIGURE 9: FASTENER/PART REMOVE/REPLACE- GROUP 5 AIRPLANES - LEFT SIDE . . . . . . 125 FIGURE 10: FASTENER/PART REMOVE/REPLACE - GROUP 5 AIRPLANES - RIGHT SIDE . . . . 136 FIGURE 11: FASTENER/PART REMOVE/REPLACE- GROUP 6, 11 AIRPLANES - LEFT SIDE . . . 147
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FIGURE 12: FASTENER/PART REMOVE/REPLACE - GROUP 6, 11 AIRPLANES - RIGHT SIDE . 158 FIGURE 13: TUBING - REMOVE/REPLACE - LEFT SIDE - GROUP 1-7, 10, 11 AIRPLANES . . . . 169 FIGURE 14: TUBING - REMOVE/REPLACE - RIGHT SIDE - GROUP 1-7, 10, 11 AIRPLANES . . . 172 FIGURE 15: FAIL-SAFE STRAP REPAIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 175 FIGURE 16: FASTENER/PART REMOVE/REPLACE- GROUP 8 - LEFT SIDE. . . . . . . . . . . . 180 FIGURE 17: FASTENER/PART REMOVE/REPLACE- GROUP 8 - RIGHT SIDE . . . . . . . . . . . 190 FIGURE 18: FASTENER/PART REMOVE/REPLACE- GROUP 9 - LEFT SIDE. . . . . . . . . . . . 200 FIGURE 19: FASTENER/PART REMOVE/REPLACE - GROUP 9 - RIGHT SIDE . . . . . . . . . . 211 FIGURE 20: TUBING - REMOVE/REPLACE - GROUP 8, 9 - LEFT SIDE. . . . . . . . . . . . . . . 222 FIGURE 21: TUBING - REMOVE/REPLACE - GROUP 8, 9 - RIGHT SIDE . . . . . . . . . . . . . . 226 FIGURE 22: JACK AND SUPPORT WORK - GROUP 1, 2, 5, 10 AIRPLANES . . . . . . . . . . . . 229 FIGURE 23: JACK AND SUPPORT WORK - GROUP 3, 4, 6 AIRPLANES . . . . . . . . . . . . . . 232 FIGURE 24: JACK AND SUPPORT WORK - GROUP 8,9 AIRPLANES. . . . . . . . . . . . . . . . 235 FIGURE 25: ACCESS AT WING/BODY INTERFACE - LEFT SIDE - GROUP 1-7, 10, 11 AIRPLANES .
238 FIGURE 26: ACCESS AT WING/BODY INTERFACE - RIGHT SIDE - GROUP 1-7, 10, 11 AIRPLANES 241 FIGURE 27: ACCESS AT WING/BODY INTERFACE - LEFT SIDE - GROUP 8, 9 AIRPLANES . . . 244 FIGURE 28: ACCESS AT WING/BODY INTERFACE - RIGHT SIDE - GROUP 8, 9 AIRPLANES . . 248 FIGURE 29: ACCESS AT WHEEL WELL/PRESSURE DECK - LEFT SIDE. . . . . . . . . . . . . . 252 FIGURE 30: ACCESS AT WHEEL WELL/PRESSURE DECK - RIGHT SIDE . . . . . . . . . . . . . 258 FIGURE 31: AILERON CONTROL CABLE PULL/STOW - LEFT SIDE . . . . . . . . . . . . . . . . 264 FIGURE 32: AILERON CONTROL CABLE PULL/STOW - RIGHT SIDE . . . . . . . . . . . . . . . 268 FIGURE 33: AILERON CONTROL CABLE RESTORE - LEFT SIDE . . . . . . . . . . . . . . . . . 273 FIGURE 34: AILERON CONTROL CABLE RESTORE - RIGHT SIDE . . . . . . . . . . . . . . . . 277 FIGURE 35: PRESSURE DECK RESTORE - LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . 282 FIGURE 36: PRESSURE DECK RESTORE - RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . 289 FIGURE 37: SKIN PANEL REPAIR - REMOVAL OF FRETTING AND/OR CORROSION . . . . . . 296 FIGURE 38: SKIN PANEL REPAIR - MAKE/ASSEMBLE PARTS . . . . . . . . . . . . . . . . . . 302 FIGURE 39: JACK AND SUPPORT WORK - GROUP 7, 11 AIRPLANES. . . . . . . . . . . . . . . 308
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ALERT ALERT Commercial Airplanes 767
ALERTALERT Service Bulletin Number: 767-53A0100 Revision Transmittal Sheet Original Issue: September 26, 2002 Revision 2: January 15, 2010 ATA System: 5350 SUBJECT: FUSELAGE - Section 45 - STA 955 Rear Spar Bulkhead Side Fittings - Fail-safe Strap
- Inspection This Revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on airplanes changed as shown in Revision 1 of this service bulletin.
Airplane VS729 was added to the effectivity of this service bulletin as a Group 6 airplane. Airplane VS729 was accidentally omitted from the effectivity of the previous release of this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directive 2004-19-06 R1 is related to this service bulletin.
REASON FOR REVISION This revision is sent to give more instruction about how to get access to the repair/modification area and also to give instruction about how to repair skin fretting and/or corrosion which has been found on some airplanes when the fail-safe strap was trimmed in accordance with this service bulletin. Also, this revision is sent to give instruction to inspect adjacent structure in cases where a crack is indicated in the fail-safe strap with the ultrasonic inspection. Also, this revision is sent to give changed fastener data and changed instruction about how to support the airplane.
These sections were changed:
1. Summary: Service history data has been added and manpower estimates have been adjusted.
2. 1.A., Effectivity: Airplane VS729 has been added as a Group 6 airplane. Created new groups 10 and 11 which contain airplanes moved from group 3 and group 6 respectively. These groups were created to separate airplanes that have different jacking/support instruction. In Group/Configuration table, created configurations for group 2 and group 4 airplanes with Special Freighter (SF) and Boeing Converted Freighter (BCF) modifications respectively.
3. 1.C., Reason: Service history data has been added.
4. 1.G., Manpower: Manpower estimates have been adjusted.
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5. 2.A., Material - Price and Delivery: Data about replacement kits, supplemental kits, and replacement T- fittings has been added.
6. 2.C., Material - Parts Necessary For Each Airplane: Data about replacement and supplemental kits has been added.
7. 3.B., Work Instructions: Steps associated with access work and fretting and/or corrosion repair work have been added. Also, instruction to do an open hole HFEC inspection for cracks in adjacent structure has been added. Also, a note has been added to clarify that removal and replacement of certain fasteners identified in the figures is necessary only as required to accomplish the trim of the fail-safe strap without causing damage to the skin or the fail-safe strap.
8. Figures 3 -12, 16 - 19: Changes have been made to fastener data and a note has been added to clarify that removal and replacement of fasteners identified in the figure is necessary only as required to accomplish the trim of the fail-safe strap without causing damage. Where specified, fastener torque values have been changed to agree with standard ranges.
9. Figures 22 - 24: Changes have been made to the position of two body supports and instruction has been added to change the configuration of one of the body supports so that removal of certain wing/body fairing structure can be avoided. The jacking/support instructions for the airplanes now in group 10 have been changed.
10. Figures 25 - 28: Steps associated with more access work have been added to these figures.
11. Figures 29 - 36: These figures have been added to give more open/close access work instruction.
12. Figure 37, 38: These figures have been added to give instruction for repair of corrosion found on the inner surface of the skin panel.
13. Figure 39: This figure has been added to give revised jacking/support instruction for freighter (group 7, 11) airplanes.
As a part of a service bulletin validation program, this change was completed on airplane VK089 by Service Bulletin 767-53A0100, Revision 1. Airplane VK089 has the configuration of a Group 3 airplane.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
Pages with no vertical lines have no important changes.
Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity paragraph for changes.
REVISION HISTORY Original Issue: September 26, 2002 Revision 1: August 11, 2006 Revision 2: January 15, 2010
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ALERT ALERT Commercial Airplanes 767
ALERTALERT Service Bulletin Number: 767-53A0100 Summary Original Issue: September 26, 2002 Revision 2: January 15, 2010 ATA System: 5350 SUBJECT: FUSELAGE - Section 45 - STA 955 Rear Spar Bulkhead Side Fittings - Fail-safe Strap
- Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.
CONCURRENT REQUIREMENTS None.
BACKGROUND The inspections specified in this service bulletin are necessary to make sure that cracks and/or corrosion in a fail-safe strap will be found and repaired before the damage can have an effect on flight safety. The fail-safe strap is held/attached between the rear spar bulkhead side fitting and the body skin at body station 955 on both sides of the airplane. If the airplane is operated with a crack and/or corrosion in the fail-safe strap, a difficult repair that requires removal of the fail-safe strap could become necessary. Also, the damage in the strap could cause cracks in the body skin and other adjacent structure which then could be unable to sustain regulatory loads, possibly resulting in a loss of structural integrity.
It is anticipated that cracks and/or corrosion in the fail-safe strap will be found with the inspections given in this service bulletin before there is damage in the body skin and other adjacent structure, and before it is necessary to replace the strap. The repair specified in this service bulletin requires only a fraction of the work and down time required to replace the fail-safe strap.
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ALERT ALERT
Before the release of revision 1 of this service bulletin there were ten reports of cracks and/or corrosion in the fail-safe strap on nine airplanes as shown in the table below. All but one of the damaged fail-safe straps were replaced. One fail-safe strap was repaired with the trim-out repair given in this service bulletin.
Crack growth in the fail-safe strap is not due to classical tensile fatigue. Boeing has found that the fatigue is due to residual tension in the fail-safe strap. This tension is from locally high compressive stress yielding the part.
The fatigue occurs when the yielded section of the fail-safe strap repeatedly goes through cyclic loading. The 767 fatigue test aircraft was tested for 100,000 flight cycles and cracks were found in the fail-safe strap on both the right and left sides of the test airplane.
At the release of revision 2 of this service bulletin, cracks have been found in 51 fail-safe straps on 41 airplanes.
Of these cases, 42 fail-safe straps were repaired in accordance with this service bulletin and nine fail-safe straps were not repairable and were replaced. Fail-safe straps were repaired on 33 airplanes with flight-cycles ranging from 9,250 to 38,490 and flight-hours ranging from 39,886 to 89,236. Fail-safe straps were replaced on nine airplanes with flight-cycles ranging from 12,565 to 31,809 and flight-hours ranging from 48,704 to 93,212. Also, four fail-safe straps have been replaced due to corrosion damage only (no cracks) on four airplanes with flightcycles ranging from 12,540 to 23,987 and flight-hours ranging from 37,634 to 74,823.
At the release of revision 2 of this service bulletin, there has also been one report of a crack found in the "T" fitting which connects the fail-safe strap and the pressure deck. The cracked "T" fitting was found at 13,449 flight-cycles / 74,008 flight-hours and the crack was located at the lower of the three fastener holes common to the fail-safe strap. As a result of this finding, instruction to do an open hole HFEC inspection of the "T" fitting has been added to this service bulletin.
See Boeing Fleet Team Digest Article Number 767-FTD-53-02004 for pictures and more information of cracks that have been found in-service on the fail-safe strap.
Boeing Service Related Problem (SRP) 767-SRP-53-0180 is related to this service bulletin.
Boeing Structural Item Interim Advisory (SIIA) 767-21 is related to this service bulletin.
The Federal Aviation Administration (FAA) has issued an Airworthiness Directive (AD) which requires incorporation of this service bulletin for group 1-7, 10, 11 airplanes.
Flight Cycles Flight Hours Damage Comments 13,472 37,634 Corrosion left and right side, cracks left and right side.
Straps had extreme corrosion.
16,403 55,609 Crack left side. Crack may have started from damage in strap surface.
18,061 72,706 Crack left side. Crack started at area of small gouging and fretting on strap surface.
15,694 71,643 Corrosion on left side Strap had extreme corrosion 18,545 62,360 Corrosion and cracks right side Fastener hole elongation 23,337 63,549 Corrosion on left side Strap had extreme corrosion 23,987 74,823 Corrosion on right side Strap had extreme corrosion 31,809 66,467 Crack right side Fretting, fastener hole elongation 36,635 51,129 Crack right side Strap repaired with trim-out repair given in this service bulletin.
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ALERT ALERT
ACTION (PRR B12901-63S) A detailed and HFEC inspection for corrosion and crack damage are to be done over the visible surface of the fail-safe strap on each side of the airplane. Also, an ultrasonic inspection is to be done to find if there is a crack in the area of the fail-safe strap under (covered by) the "T" fitting which is connected to the fail-safe strap and to the outboard edge of the sloping pressure deck.
If no corrosion or cracks are found with the inspections, repeat inspections are to be made at regular intervals.
If cracks and/or corrosion are found, a repair must be made before more flights. If crack damage has not extended outside the tab part of the strap where the "T" fitting is attached, the fail-safe strap repair given in this service bulletin is to be made. If crack damage extends outside the specified area, it will be necessary to replace the strap. Boeing plans to release service bulletin 767-53-0116 at a later date with instructions to install a replacement strap.
NOTE: The change made to the airplane with the fail-safe strap repair given in this service bulletin can be made at any time to end the need for more inspections per this service bulletin at the side of the airplane that has the repair.
EFFECTIVITY 767-200/-300/-300F/-400ER airplanes. Refer to paragraph 1.A.1 for effectivity.
COMPLIANCE Refer to paragraph 1.E for compliance information.
Federal Aviation Administration (FAA) Airworthiness Directive 2004-19-06 R1 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection given in this service bulletin.
MANPOWER
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Airplanes Total Task Hours Elapsed Hours Group 1-10 4.0 2.0 Airplanes Total Task Hours Elapsed Hours Group 1-7, 10 295 85 Group 8, 9 297 86
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ALERT ALERT
TYPICAL
CORROSION FWD FWD
T-FITTING
DO ULTRASONIC INSPECTION OF
THE AREA OF THE FAILSAFE
STRAP UNDER THE T-FITTING
DO A DETAILED INSPECTION AND
A SURFACE HFEC INSPECTION OF
ACCESSABLE AREAS OF FAILSAFE STRAP
T- FITTING STA 955 A SEE A
RIGHT SIDE OPPOSITE
LEFT SIDE SHOWN,
INSPECTION
FITTING
BULKHEAD
REAR SPAR STA 955 AREA
FAILSAFE STRAP
TYPICAL CRACK
IN FAILSAFE STRAP V88417
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ALERT ALERT Commercial Airplanes 767
ALERTALERT Service Bulletin Number: 767-53A0100 Original Issue: September 26, 2002 Revision 2: January 15, 2010 ATA System: 5350 SUBJECT: FUSELAGE - Section 45 - STA 955 Rear Spar Bulkhead Side Fittings - Fail-safe Strap
- Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.
1. PLANNING INFORMATION A. Effectivity
1. Airplanes Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B12901-63S for data about this change.
GROUP CONFIGURATION DESCRIPTION 1 - 767-200 with longeron splice installation 145T0083-7/-8, -9/-10, -11/-12 1 Not modified to Boeing Approved Special Freighter configuration 2 767-200 with longeron splice installation 145T0083-11/-12 and Special Freighter modification which is given in Boeing service bulletin 767-53-0125 and is applicable to VA511 only 2 - 767-200 with longeron splice installation 145T0083-19/-20 3 - 767-300 with longeron splice installation 145T0083-13/-14
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Airplane models:
767-200 767-300 767-300F 767-400ER
IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER AA 767 LLC (SVX) 1 VE067 4 - 767-300 with longeron splice installation 145T0083-21/-22, -25/-26, -33/-34 1 Not modified to Boeing Converted Freighter (BCF) configuration 2 Longeron splice installation 145T0083-21/-22 and BCF modification which is given in Boeing service bulletin 767-53-0140 and is applicable to VN191 only 3 Longeron splice installation 145T0083-21/-22 and BCF modification which is given in Boeing service bulletin 767-53-0148 and is applicable to VN192 only 4 Longeron splice installation 145T0083-21/-22 and BCF modification which is given in Boeing service bulletin 767-53-0150 and is applicable to VN 193 only 5 Longeron splice installation 145T0083-21/-22 and BCF modification which is given in Boeing service bulletin 767-53-0154 and is applicable to VN194 only 6 Longeron splice installation 145T0083-21/-22 and BCF modification which is given in Boeing service bulletin 767-53-0157 and is applicable to VN195 - VN197 only 5 - 767-200 with longeron splice installation 145T0083-41/-42 6 - 767-300 with longeron splice installation 145T0083-45/-46, -47/-48 7 - 767-300F with longeron splice installation 145T0083-25/-26, -27/-28, -37/-38 8 - 767-400ER with longeron splice installation 145T0083-31/-32 9 - 767-400ER with longeron splice installation 145T0083-43/-44 10 - 767-200 with longeron splice installation 145T0083-13/-14 11 - 767-300F with longeron splice installation 145T0083-49/-50