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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1323 Original Issue: December 06, 2013 ATA System: 5311 5331 2158 SUBJECT: FUSELAGE - Frames - Cracking of Frames at STA 328 Between Stringers S-20R to S-21R, STA 360 Between Stringers S-19R to S-21R, and STA 380 Between Stringers S-18R to S-20R, and Missing Strap on Frame at STA 312 - Inspection, Modification, and Repair Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2013 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
Original Issue: December 06, 2013 737-53A1323 1 of 321
6.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 2 of 321 BOEING SERVICE BULLETIN 737-53A1323
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BLANK PAGE
Table of Contents
Summary5
1. PLANNING INFORMATION ........................................ 1 3 A. Effectivity ............................................... 1 3
1. Airplanes ............................................ 1 3
2. Spares Affected ........................................ 2 8 B. Concurrent Requirements ...................................... 2 8 C. Reason ................................................ 2 8 D. Description .............................................. 2 9 E. Compliance .............................................. 3 2 F. Approval ............................................... 6 0 G. Manpower .............................................. 6 1 H. Weight and Balance Changes .................................... 7 1 I. Electrical Load Data ......................................... 7 1 J. References .............................................. 7 1
1. Existing Data: ......................................... 7 1
2. Data Supplied with this Service Bulletin: ........................... 7 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 7 2 K. Publications Affected ........................................ 7 2 L. Interchangeability and Intermixability of Parts ........................... 7 3 M. Software Accomplishment Summary ................................ 7 3
2. MATERIAL INFORMATION ........................................ 7 5 A. Material - Price and Availability ................................... 7 5 B. Industry Support Information .................................... 7 5 C. Parts Necessary for Each Airplane ................................. 7 5
1. Kits/Parts ............................................ 7 5
2. Parts and Materials Supplied by the Operator ........................ 7 5
3. Parts Modified and Reidentified ................................ 8 0
4. Parts Removed and Not Replaced .............................. 8 0 D. Parts Necessary to Change Spares ................................. 8 0 E. Special Tooling - Price and Availability ............................... 8 0 F. Special Tooling Necessary to do this Service Bulletin ....................... 8 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 8 1 A. GENERAL INFORMATION ..................................... 8 1 B. WORK INSTRUCTIONS ....................................... 8 2 FIGURE 1: OPEN ACCESS [Group 2-5] .................................. 9 8 FIGURE 2: OPEN ACCESS [Group 6-7] ................................. 1 0 2 FIGURE 3: GENERAL VISUAL INSPECTION OF THE FRAME AT STA 312 TO MAKE SURE STRAP IS INSTALLED [Group 2-7] ................................... 1 0 4 FIGURE 4: DETAILED INSPECTION OF THE FRAME AT STA 328 [Group 2-7] ........... 1 0 8 FIGURE 5: HFEC INSPECTION OF THE FRAME AT STA 328 [Group 2-7] .............. 1 1 4 FIGURE 6: DETAILED INSPECTION OF THE FRAME AT STA 312 [Group 2-7] ........... 1 2 1 FIGURE 7: DETAILED INSPECTION OF THE FRAME AT STA 344 [Group 2-7] ........... 1 2 5 FIGURE 8: DETAILED INSPECTION OF THE FRAME AT STA 360 [Group 2-5] ........... 1 2 9 FIGURE 9: HFEC INSPECTION OF THE FRAME AT STA 360 [Group 2-5] .............. 1 3 5 FIGURE 10: DETAILED INSPECTION OF THE FRAME AT STA 380 [Group 2, 4] ........... 1 4 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 3 of 321 BOEING SERVICE BULLETIN 737-53A1323
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FIGURE 11: HFEC INSPECTION OF THE FRAME AT STA 380 [Group 2, 4] .............. 1 4 8 FIGURE 12: DETAILED INSPECTION OF THE FRAME AT STA 380 [Group 3, 5] ........... 1 5 3 FIGURE 13: HFEC INSPECTION OF THE FRAME AT STA 380 [Group 3, 5] .............. 1 5 8 FIGURE 14: DETAILED AND EDDY CURRENT INSPECTIONS OF THE FUSELAGE SKIN [Group 2-3] . 163 FIGURE 15: DETAILED AND EDDY CURRENT INSPECTIONS OF THE FUSELAGE SKIN [Group 4-5] . 165 FIGURE 16: DETAILED AND EDDY CURRENT INSPECTIONS OF THE FUSELAGE SKIN [Group 6] . 167 FIGURE 17: PRE-MODIFICATION INSPECTION - TOOL HOLE - FRAME AT STA 360 [Group 2-5] . 169 FIGURE 18: MODIFICATION - TOOL HOLE - FRAME AT STA 360 [Group 2-5] ............ 1 7 3 FIGURE 19: PRE-MODIFICATION INSPECTION - INSULATION BLANKET STUD HOLE - FRAME AT STA 360 [Group 2-5] ........................................ 1 7 8 FIGURE 20: MODIFICATION - INSULATION BLANKET STUD HOLE - FRAME AT STA 360 [Group 2-5] ................................................. 1 8 2 FIGURE 21: PRE-MODIFICATION INSPECTION - END FASTENERS IN THE DOUBLER - FRAME AT STA 360 [Group 2-5] ........................................ 1 8 7 FIGURE 22: MODIFICATION - END FASTENERS IN THE DOUBLER - FRAME AT STA 360 [Group 2-5] ................................................. 1 9 4 FIGURE 23: PRE-REPAIR INSPECTION - REMOVAL OF PARTS AND INSPECTION OF FASTENER HOLES
- FRAME AT STA 328 [Group 2-7] .............................. 2 0 2 FIGURE 24: MAKE THE REPAIR PARTS - FRAME AT STA 328 [Group 2-6] .............. 2 1 6 FIGURE 25: REPAIR - FRAME AT STA 328 [Group 2-6] ......................... 2 3 6 FIGURE 26: MAKE THE REPAIR PARTS - FRAME AT STA 328 [Group 7] ............... 2 5 9 FIGURE 27: REPAIR - FRAME AT STA 328 [Group 7] .......................... 2 7 9 FIGURE 28: POST-MODIFICATION DAMAGE TOLERANCE INSPECTION - FRAME AT STA 360 [Group 2-5] ............................................... 3 0 2 FIGURE 29: POST-REPAIR DAMAGE TOLERANCE INSPECTION - FRAME AT STA 328 [Group 2-7] . 308 FIGURE 30: CLOSE ACCESS [Group 2-5] ................................ 3 1 3 FIGURE 31: CLOSE ACCESS [Group 6-7] ................................ 3 1 6 APPENDIX A: REMOVAL AND INSTALLATION OF THE EQUIPMENT COOLING PLENUM FOR ADDITIONAL ACCESS [Group 2-5] ..................................... 3 1 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 4 of 321 BOEING SERVICE BULLETIN 737-53A1323
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Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1323Original Issue: December 06, 2013 ATA System: 5311 5331 2158 SUBJECT: FUSELAGE - Frames - Cracking of Frames at STA 328 Between Stringers S-20R to S-21R, STA 360 Between Stringers S-19R to S-21R, and STA 380 Between Stringers S-18R to S-20R, and Missing Strap on Frame at STA 312 - Inspection, Modification, and Repair
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 This service bulletin is sent to inspect frames at STA 328 between stringers S-20R to S-21R, STA 360 between stringers S-19R to S-21R, and STA 380 between stringers S-18R to S-22R for cracking. Operators have sent in reports of cracking in these frames. Also, this service bulletin inspects adjacent frames at STA 312 between stringers S-19R to S-22R and STA 344 between stringers S-18R to S-22R. In addition, this service bulletin inspects the frame at STA 312 for a missing strap adjacent to stringer S-22R. A missing strap can make the frame crack. If cracks in the frames are not detected and repaired, they can grow until the frames sever. Continued operation of the airplane with multiple adjacent severed frames can result in uncontrolled decompression of the airplane, and also, the combination of a severed frame and fuselage skin chem mill cracks in this area can result in uncontrolled decompression of the airplane.
Refer to Boeing Service Bulletin 737-53A1210 for reports of fuselage skin chem mill cracks.
Accomplishment of the inspections in this service bulletin will make sure that cracks in the frames at STA 328 between stringers S-20R to S-21R, STA 360 between stringers S-19R to S-21R, and STA 380 between stringer S-18R to S-22R are found and repaired. Also, accomplishment of the inspections in this service bulletin will make sure that cracks in adjacent frames at STA 312 between stringers S-19R to S-22R and STA 344 between stringers S-19R to S-22R are found and repaired. If cracks in the frames are found and repaired, then the effect of a severed frame can not interact with the effect of fuselage skin cracks. In addition, accomplishment of the inspection in this service bulletin will ensure that the strap adjacent to stringer S-22R on the frame at STA 312 is installed.
One operator of a 737-300 airplane sent a report of a crack in the frame at STA 328 and a crack that severed the frame at STA 360 on the right side of the same airplane with 59,756 flight cycles. The crack in the frame at STA 328 was between stringers S-20R to S-21R. The crack length was not reported. The crack in the frame at STA 360 was between stringers S-19R to S-20R. The frame web and the failsafe chord were completely severed.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 5 of 321
Operators of 737-200, 737-300, and 737-500 airplanes sent ten reports of cracks in the frame at STA 328 between stringers S-20R and S-21R on ten airplanes with 43,581 to 73,655 flight cycles. Cracks were in the frame web at an open tool hole, in the frame web at the end fastener in the inner chord, and in the frame web notch. The cracks were from 0.3 inch to 3.0 inches long.
Operators of 737-200 and 737-300 airplanes sent fourteen reports of cracks in the frame at STA 360 between stringers S-19R and S-21R on fourteen airplanes with 42,183 to 66,588 flight cycles. Cracks were in the frame web at an open tool hole, in the frame web at an insulation blanket stud hole, in the frame web at an end fastener in the doubler, and in the inner flange at the end fastener in the doubler. The cracks were from 2.5 inches long to cracks that severed the frame web and fail-safe chord.
An operator of a 737-300 airplane sent one report of three cracks in the frame at STA 380 between stringers S-18R and S-20R on one airplane with 32,218 flight cycles. Cracks were in the frame inner flange at fasteners common to the bulkhead support angle. One of the three cracks was also in the doubler. Crack lengths were not reported.
An operator of a 737-400 airplane sent in one report of a strap that was not installed on the frame at STA 312 adjacent to stringer S-22R on one airplane with 24,037 flight cycles. Investigation of the drawings revealed that this was an incorrect frame configuration and that the strap should have been installed. The incorrect frame configuration was discovered during a repair of the STA 312 frame because of ground damage. There was no report of cracks caused by the incorrect frame configuration.
Boeing Fleet Team Digest (FTD) 737 FTD 53-10001 is related to this service bulletin.
Boeing Service Related Problem (SRP) 737-SRP-53-0359 is related to this service bulletin.
The table below is provided to operators for planning purposes only. Refer to the applicable sections for more information.
ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., ComplianceYesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedNoPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 6 of 321 BOEING SERVICE BULLETIN 737-53A1323
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ACTION Group 1:
On Group 1 airplanes, contact Boeing to get instructions for the inspection and/or repair for this service bulletin, and do the work instructed by Boeing.
Group 2-5:
On the frame at STA 312, do a general visual inspection of the frame to make sure that the strap adjacent to stringer S-22R is installed. If the strap is installed, then no more work is necessary to make sure that the strap is installed. If the strap is not installed, then before further flight, repair the frame at STA 312.
On the frame at STA 328, do a detailed inspection between stringers S-20R to S-21R for cracking or a severed frame web. Do an open hole High Frequency Eddy Current (HFEC) inspection of a tool hole in the frame web for cracking, a surface HFEC inspection of the frame web around the end fastener in the inner chord for cracking, and a surface HFEC inspection of the frame web notch for cracking. If no crack is found, then continue to do repeat inspections. If any crack is found, then before further flight, repair the frame. If a severed frame web is found, then before further flight, repair the frame, do a detailed inspection of the frame at STA 312 between stringers S-19R to S-22R for cracking, do a detailed inspection of the frame at STA 344 between stringers S-18R to S-22R for cracking, and do detailed and eddy current inspections of the fuselage skin for cracking. If no crack is found, then no more work is necessary on the frame at STA 312, but continue to do repeat inspections of the frame at STA 344. If any crack is found on the frame at STA 312, or on the frame at STA 344, then before further flight, repair the frame. If any crack is found in the fuselage skin, then before further flight, repair the skin. If you do the repair of the frame at STA 328 in accordance with this service bulletin, then you can stop repeat inspections of the frame at STA 328. Do post-repair damage tolerance inspections of the repair of the frame at STA 328.
On the frame at STA 344, do a detailed inspection between stringers S-18R to S-22R for cracking. If no crack is found, then continue to do repeat inspections. If any crack is found, then before further flight, repair the frame at STA 344. If you do the repair of the frame at STA 328 in accordance with this service bulletin, and you do the optional preventative modification to the frame at STA 360 in accordance with this service bulletin, then you can stop repeat inspections of the frame at STA 344.
On the frame at STA 360, do a detailed inspection between stringers S-19R to S-21R for cracking or a severed frame web. Do an open hole HFEC inspection of a tool hole in the frame web for cracking, an open hole HFEC inspection of an insulation blanket stud hole in the frame web for cracking, a surface HFEC inspection of the frame web around an end fastener in the doubler, and a surface HFEC inspection of the inner flange around the end fastener in the doubler for cracking. If no crack is found, then continue to do repeat inspections. If any crack is found, then before further flight, repair the frame at STA 360. If a severed frame web is found, then before further flight, repair the frame at STA 360, do a detailed inspection of the frame at STA 344 between stringers S-18R to S-22R for cracking, do a detailed inspection of the frame at STA 380 between stringers S-18R to S-22R for cracking, and do detailed and eddy current inspections of the fuselage skin for cracking. If no crack is found, then continue to do repeat inspections on the frame at STA 344, and the frame at STA 380. If any crack is found in the frame at STA 344, or on the frame at STA 380, then before further flight, repair the frame.
If any crack is found in the fuselage skin, then before further flight, repair the skin. If you do the optional preventative modification to the frame at STA 360 in accordance with this service bulletin, then you can stop repeat inspections of the frame at STA 360. Do post-modification damage tolerance inspections of the modified area of the frame at STA 360.
On the frame at STA 380, do a detailed inspection of the frame between stringers S-18R to S-22R for cracking or a severed frame web. Do a surface HFEC inspection of the inner flange adjacent to fasteners common to the bulkhead support angle in the frame at STA 380 for cracking. If no crack is found, then continue to do repeat inspections. If any crack is found, then before further flight, repair the frame at STA 380. If a severed frame web is found, then before further flight, repair the frame at STA 380 and inspect adjacent structure.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 7 of 321 BOEING SERVICE BULLETIN 737-53A1323
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On the fuselage skin adjacent to the frames at STA 328 and STA 360 inspected by this service bulletin, you can do optional external detailed and eddy current inspections for cracking. If you do the optional inspections of the fuselage skin, you can increase the repeat inspection intervals for the frames. If no crack is found in the fuselage skin, then you must continue to do repeat inspections of the fuselage skin for cracking. If any crack is found, then before further flight, repair the fuselage skin, do a detailed inspection of the frame at STA 328 between stringers S-20R to S-21R for cracking, and do a detailed inspection of the frame at STA 360 between stringers S-19R to S-21R for cracking. If any crack is found on the frame at STA 328, or on the frame at STA 360, then before further flight, repair the frame. You must continue to do repeat inspections of the unrepaired area of the fuselage skin for cracking. If you do a repair of the fuselage skin in accordance with this service bulletin, then you can stop repeat inspections of the skin common to the repair. Do post-repair damage tolerance inspections of the repair of the fuselage skin. If you do the repair of the frame at STA 328 in accordance with this service bulletin, and you do the optional preventative modification to the frame at STA 360 in accordance with this service bulletin, then you can stop repeat inspections of the fuselage skin in accordance with this service bulletin.
Refer to AMOC in Paragraph 1.F., Approval.
Group 6:
On the frame at STA 312, do a general visual inspection of the frame to make sure that the strap adjacent to stringer S-22R is installed. If the strap is installed, then no more work is necessary to make sure that the strap is installed. If the strap is not installed, then before further flight, repair the frame at STA 312.
On the frame at STA 328, do a detailed inspection between stringers S-20R to S-21R for cracking or a severed frame web. Do an open hole High Frequency Eddy Current (HFEC) inspection of a tool hole in the frame web for cracking, a surface HFEC inspection of the frame web around the end fastener in the inner chord for cracking, and a surface HFEC inspection of the frame web notch for cracking. If no crack is found, then continue to do repeat inspections. If any crack is found, then before further flight, repair the frame. If a severed frame web is found, then before further flight, repair the frame, do a detailed inspection of the frame at STA 312 between stringers S-19R to S-22R for cracking, do a detailed inspection of the frame at STA 344 between stringers S-18R to S-22R for cracking, and do detailed and eddy current inspections of the fuselage skin for cracking. If no crack is found, then no more work is necessary on the frame at STA 312, or on the frame at STA 344. If any crack is found on the frame at STA 312, or on the frame at STA 344, then before further flight, repair the frame. If any crack is found in the fuselage skin, then before further flight, repair the skin. If you do the repair of the frame at STA 328 in accordance with this service bulletin, then you can stop repeat inspections of the frame at STA 328.
Do post-repair damage tolerance inspections of the repair of the frame at STA 328.
On the fuselage skin adjacent to the frame at STA 328 inspected by this service bulletin, you can do optional external detailed and eddy current inspections for cracking. If you do the optional inspections of the fuselage skin, then you can increase the repeat inspection interval for the frame. If no crack is found in the fuselage skin, then you must continue to do repeat inspections of the fuselage skin. If any crack is found, then before further flight, repair the fuselage skin and do a detailed inspection of the frame at STA 328 between stringers S-20R to S-21R for cracking. If any crack is found on the frame at STA 328, then before further flight, repair the frame.
You must continue to do repeat inspections of the unrepaired area of the fuselage skin for cracking. If you do skin repairs in accordance with this service bulletin, then you can stop repeat inspections of the skin common to the repair. Do post-repair damage tolerance inspections of the repair of the fuselage skin. If you do the repair of the frame at STA 328 in accordance with this service bulletin, then you can stop repeat inspections of the fuselage skin in accordance with this service bulletin. Refer to AMOC in Paragraph 1.F., Approval.
Group 7:
On the frame at STA 312, do a general visual inspection of the frame to make sure that the strap adjacent to stringer S-22R is installed. If the strap is installed, then no more work is necessary to make sure that the strap is installed. If the strap is not installed, then before further flight, repair the frame at STA 312.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 8 of 321 BOEING SERVICE BULLETIN 737-53A1323
ALERTALERT
On the frame at STA 328, do a detailed inspection between stringers S-20R to S-21R for cracking or a severed frame web. Do an open hole High Frequency Eddy Current (HFEC) inspection of a tool hole in the frame web for cracking, a surface HFEC inspection of the frame web around the end fastener in the inner chord for cracking, and a surface HFEC inspection of the frame web notch for cracking. If no crack is found, then continue to do repeat inspections. If any crack is found, then before further flight, repair the frame. If a severed frame web is found, then before further flight, repair the frame, do a detailed inspection of the frame at STA 312 between stringers S-19R to S-22R for cracking, and do a detailed inspection of the frame at STA 344 between stringers S-18R to S-22R for cracking. If no crack is found, then no more work is necessary on the frame at STA 312, or on the frame at STA 344. If any crack is found on the frame at STA 312, or on the frame at STA 344, then before further flight, repair the frame. If you do the repair of the frame at STA 328 in accordance with this service bulletin, then you can stop repeat inspections of the frame at STA 328. Do post-repair damage tolerance inspections of the repair of the frame at STA 328.
EFFECTIVITY 737-100/200/200C/300/400/500 Airplanes. Refer to Paragraph1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes or inspection and/or modification procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 9 of 321 BOEING SERVICE BULLETIN 737-53A1323
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BOEING SERVICE BULLETIN 737-53A1323
ALERT ALERT
IF SEVERED FRAME DO DETAILED AND DO DETAILED INSPECTION
WEB IS FOUND AT STA HFEC INSPECTIONS FOR CRACKS 328, THEN DO DETAILED FOR CRACKS GROUPS 2 THRU 5 INSPECTION OF STA 312 (GROUPS 2 THRU 7) F SEVERED FRAME WEB IS FRAME FOR CRACKS FOUND AT STA 328, THEN DO (GROUPS 2 THRU 7) DETAILED INSPECTION OF STA 344 FRAME FOR CRACKS STA 312 IF SEVERED FRAME WEB IS (GROUP 2 THRU 7) FOUND AT STA 360, THEN DO
STA DETAILED INSPECTION OF DO DETAILED AND 328 HFEC INSPECTIONS STA STA 344 FRAME FOR CRACKS (GROUP 2 THRU 5) FOR CRACKS 344 (GROUP 2 THRU 5) STA 360
STA DO DETAILED AND 380 HFEC INSPECTIONS
FOR CRACKS (GROUPS 2 THRU 5)
IF SEVERED FRAME
WEB IS FOUND AT STA 360, THEN DO
DETAILED
INSPECTION OF STA S-18R 380 FRAME FOR CRACKS S-19R (GROUP 2 THRU 5) S-20R INSPECT FRAME TO S-21R
MAKE SURE STRAP
IS INSTALLED (GROUPS 2-7) AREAS OF REPORTED - S-22R
CRACKING 2138257 Original Issue: December 06, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1323 Work - See page 1 for details. 10 of 321
BOEING SERVICE BULLETIN 737-53A1323
ALERT ALERT
SERVICE
DOOR IF SEVERED FRAME WEB IS FOUND,
DO DETAILED AND EDDY CURRENT INSPECTIONS OF THE SKIN.
(GROUPS 2-6)
YOU CAN DO OPTIONAL EXTERNAL
DETAILED AND EDDY CURRENT
INSPECTIONS OF THE FUSELAGE
SKIN TO INCREASE REPEAT
INSPECTION INTERVALS FOR THE FRAMES.
(GROUPS 2-6)
DETAILED INSPECTION DETAILED INSPECTION DETAILED INSPECTION
AREA AND EDDY AREA AND EDDY AREA AND EDDY
CURRENT INSPECTION CURRENT INSPECTION CURRENT INSPECTION ZONES FOR GROUPS 4 ZONES FOR GROUPS 2 / ZONES FOR GROUP 6 AND 5 AND 3
SERVICE DOOR S-17R S-18R S-19R S-20R J S-21R S-22R
STA STA STA STA STA STA STA 370 360 352 344 336 328 320
FWD (FRAME) (FRAME) (FRAME) EDDY CURRENT
INSPECTIONZONEL Original Issue: December 06, 2013 Export Controlled ECCN: 9E991 - BOEING 737-53A1323 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 321
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 06, 2013 737-53A1323 12 of 321 BOEING SERVICE BULLETIN 737-53A1323