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Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1358 Original Issue: April 27, 2017 ATA System: 5331 SUBJECT: FUSELAGE - Skin - 0.036 Inch Crown Skin Panels Between S-10L and S-10R, STA 360 to STA 540 and STA 727 to STA 908 - Inspection, Repair and Replacement 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 © 2017 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Unpublished Work.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: April 27, 2017 737-53A1358 1 of 270
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Table of Contents
S u m m a r y7
1. PLANNING INFORMATION ........................................ 1 1 A . E f f e c t i v i t y ............................................... 1 1
1. Airplanes ............................................ 1 1 2 . S p a r e s A f f e c t e d ........................................ 2 5 B. Concurrent Requirements ...................................... 2 5 C. Reason ................................................ 2 5 D. Description .............................................. 2 6 E. Compliance .............................................. 2 7 F . A p p r o v a l ............................................... 3 3 G. Manpower .............................................. 3 3 H. Weight and Balance Changes .................................... 4 4 I. Electrical Load Data ......................................... 4 4 J . R e f e r e n c e s .............................................. 4 5
1. Existing Data: ......................................... 4 5
2. Data Supplied with this Service Bulletin: ........................... 4 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 5 K. Publications Affected ........................................ 4 6 L. Interchangeability and Intermixability of Parts ........................... 4 6 M. Software Accomplishment Summary ................................ 4 6
2. MATERIAL INFORMATION ........................................ 4 7 A. Material - Price and Availability ................................... 4 7 B. Industry Support Information .................................... 7 2 C. Parts Necessary for Each Airplane ................................. 7 2 1 . K i t s / P a r t s ............................................ 7 2
2. Parts and Materials Supplied by the Operator ........................ 9 5
3. Parts Modified and Reidentified ................................ 9 7
4. Parts Removed and Not Replaced .............................. 9 7 D. Parts Necessary to Change Spares ................................. 9 7 E. Special Tooling - Price and Availability ............................... 9 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 9 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 9 9 A. GENERAL INFORMATION ..................................... 9 9 B. WORK INSTRUCTIONS ...................................... 1 0 1 FIGURE 1: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 1-2] . . . 122 FIGURE 2: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 3-4] . . . 124 FIGURE 3: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 5] .... 1 2 6 FIGURE 4: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 6-7] . . . 128 FIGURE 5: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 8-9] . . . 130 FIGURE 6: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 10-11] . . 132 FIGURE 7: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 12] .... 1 3 4 FIGURE 8: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 13] .... 1 3 6 FIGURE 9: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 14-16] . . 138 FIGURE 10: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 17] .... 1 4 0 FIGURE 11: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 18] .... 1 4 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 12: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 19] .... 1 4 4 FIGURE 13: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 20] .... 1 4 6 FIGURE 14: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 21] .... 1 4 8 FIGURE 15: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 22] . . . 150 FIGURE 16: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 23] . . . 152 FIGURE 17: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 24] . . . 154 FIGURE 18: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 25] . . . 156 FIGURE 19: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 26] . . . 158 FIGURE 20: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 27] . . . 160 FIGURE 21: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 28] . . . 162 FIGURE 22: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 29-31] . . 164 FIGURE 23: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 32] .... 1 6 6 FIGURE 24: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 33-35, 37] . 168 FIGURE 25: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 36, 39] . . 170 FIGURE 26: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 38, 40] . . 172 FIGURE 27: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 41] .... 1 7 4 FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI .............. 1 7 6 FIGURE 29: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 1-4] . 182 FIGURE 30: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 5] . 184 FIGURE 31: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 6-7] . 186 FIGURE 32: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 8, 10, 12-14, 1 7 - 2 1 ] ............................................. 1 8 8 FIGURE 33: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 9, 11, 16] ................................................. 1 9 0 FIGURE 34: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 15] . 192 FIGURE 35: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727G AND 908 [Group 22-28] ................................................. 1 9 4 FIGURE 36: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 29-30, 33, 3 5 - 3 6 , 3 8 , 4 0 - 4 1 ] ....................................... 1 9 6 FIGURE 37: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 31, 37] ................................................. 1 9 8 FIGURE 38: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 32, 34, 39] ................................................. 2 0 0 FIGURE 39: INSPECTION OF CHEM-MILL POCKETS ADJACENT TO CRACK LOCATION ..... 2 0 2 FIGURE 40: DAMAGED SKIN REMOVAL ................................. 2 0 4 FIGURE 41: CUT SURFACE AND FASTENER HOLES INSPECTION ................. 2 0 5 F I G U R E 4 2 : I N S U R A N C E C U T A N D S U R F A C E T R E A T M E N T ..................... 2 0 7 FIGURE 43: CATEGORY C REPAIR INSTALLATION .......................... 2 0 9 FIGURE 44: CATEGORY C REPAIR INSPECTION ........................... 2 1 3 FIGURE 45: PRE-REPAIR CONVERSION INSPECTION ........................ 2 1 4 FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND T E A R S T R A P D O U B L E R S .................................. 2 1 5 FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER, S O L I D F A S T E N E R S A N D T E A R S T R A P D O U B L E R S ................... 2 2 0 FIGURE 48: POST REPAIR LFEC INSPECTION OF SB REPAIR, OPTION 1 ............. 2 2 6 FIGURE 49: POST REPAIR LFEC INSPECTION OF SB REPAIR, OPTION 2 ............. 2 2 8 FIGURE 50: SKIN BUTT JOINT INSPECTION AT STA 360 ....................... 2 3 0 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 51: SKIN BUTT JOINT INSPECTION AT STA 540 ....................... 2 3 2 FIGURE 52: SKIN BUTT JOINT INSPECTION AT STA 727 ....................... 2 3 4 FIGURE 53: SKIN BUTT JOINT INSPECTION AT STA 908 ....................... 2 3 6 FIGURE 54: SKIN BUTT JOINT INSPECTION AT STA 500C ...................... 2 3 8 FIGURE 55: SKIN BUTT JOINT INSPECTION AT STA 727G ...................... 2 4 0 APPENDIX A: L OGIC DIAGRAM FOR TABLE 1 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN BONDED DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-10L TO S-10R - STA 360 TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO STA 908 (GROUP 22-28) .......................... 2 4 2 APPENDIX B: LOGIC DIAGRAM FOR TABLE 2 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR INSPECTION OF CATEGORY C REPAIR ......................... 2 4 5 APPENDIX C: LOGIC DIAGRAM FOR TABLE 3 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR INSPECTION OF SB REPAIRS INSTALLED IN ACCORDANCE WITH PART 6: CHANGE CATEGORY C REPAIR TO SB REPAIR OF THIS SERVICE BULLETIN ......... 2 4 7 APPENDIX D: LOGIC DIAGRAM FOR TABLE 4 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN PANEL REPLACEMENT FROM S-10L TO S-10R - STA 360 TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO STA 908 (GROUP 22-28) ................................................. 2 4 9 APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS ......................... 2 5 0 APPENDIX F: PART DEMAND INTENT ................................... 2 7 0 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1358Original Issue: April 27, 2017 ATA System: 5331 SUBJECT: FUSELAGE - Skin - 0.036 Inch Crown Skin Panels Between S-10L and S-10R, STA 360 to STA 540 and STA 727 to STA 908 - Inspection, Repair and Replacement
THIS DOCUMENT 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 DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.
CONCURRENT REQUIREMENTS None.
BACKGROUND This service bulletin gives instructions for inspection, repair, and replacement of 0.036 inch fuselage crown skin panels where cracking at the chem-mill steps can occur between stringer (S)-10L and S-10R from station (STA) 360 to STA 540 and from STA 727 to STA 908 for 737-200/200C/300/500 airplanes and from STA 360 to STA 500C and from STA 727G to STA 908 for 737-400 airplanes. On these skin panels, the bonded doubler is chemically milled to create pockets. At these locations, the loads could cause a condition where cracks could form along the longitudinal edges of the doubler at the step of the chem-mill pockets. The inspection, in accordance with this service bulletin, will allow early detection of cracks in the crown skin panels and prevent Widespread Fatigue Damage (WFD) by reducing the chance of multiple adjacent chem-mill step cracks from linking with each other. The repair of cracks in accordance with this service bulletin will restore the structural integrity of the skin panel. If the skin cracks propagate without detection, they could adversely affect the structural integrity of the airplane.
An operator of a 737-300 airplane reported multiple chem-mill step cracks in adjacent bays of the fuselage crown skin. These cracks were discovered by visual inspection only 855 flight cycles after the last detailed inspection in accordance with Boeing Alert Service Bulletin (SB) 737-53A1210. The initial visual inspection revealed three cracks varying in length from 1.8 inches to 8.5 inches. Further inspection using Ultrasonic Phased Array revealed nine additional sub-surface cracks. The airplane had 55,232 flight cycles.
Boeing Service Related Problem (SRP) 737-SRP-53-0517 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-15007 is related to this service bulletin.
The fuselage crown skin has been determined to be structure that is susceptible to WFD.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph
1.F., Approval YesAD 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/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Classification of repairs in this service bulletin
DESCRIPTIONREPAIR TYPE A Category B repair for which supplemental inspections are necessary at the specified threshold and repeat intervals in accordance with the Structural Repair Manual (SRM).
SRM Repair A Category C repair that has been changed to a Category B repair for which supplemental inspections are necessary at the specified threshold and repeat intervals in accordance with this Service Bulletin (SB).
SB Repair A time-limited repair which must be replaced or reworked within a specified time limit. Also supplemental inspections are necessary at a specified threshold and repeat interval in accordance with this SB.
Category C Group 1-21, 29-41:
Do a Non-Destructive Inspection (NDI) for any crack of the crown skin adjacent to the chem-mill steps in the area from S-10L to S-10R, from STA 360 to STA 540 and from STA 727 to STA 908. If any crack is found, install a SRM Repair or install a Category C Repair and repeat the external NDI of the crown skin for any crack. If no crack is found, repeat the NDI inspections for any crack.
Group 22-28:
Do a Non-Destructive Inspection (NDI) for any crack of the crown skin adjacent to the chem-mill steps in the area from S-10L to S-10R, from STA 360 to STA 500C and from STA 727G to STA 908. If any crack is found, install a SRM Repair or install a Category C Repair and repeat the external NDI of the crown skin for any crack.
If no crack is found, repeat the NDI inspections for any crack.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Group 1- 41: If any Category C Repair is installed, do an external detailed inspection for any loose or missing fasteners. Replace any loose or missing fasteners and change the Category C repair to a SB Repair. If no loose or missing fasteners are found, repeat the external detailed inspection for any loose or missing fasteners and change the Category C repair to a SB Repair.
Group 1- 41: If any SB Repair is installed, do a post-repair external Low Frequency Eddy Current (LFEC) inspection for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair. If no crack is found, repeat the post-repair external LFEC inspection of the SB Repair for any crack.
Group 1- 41: If any SRM repair is installed, do post repair inspections in accordance with the SRM.
Group 1-21, 29-41:
Replace all six crown skin panel assemblies in the area from S-10L to S-10R, from STA 360 to STA 540 and from STA 727 to STA 908.
Group 22-28:
Replace all six crown skin panel assemblies in the area from S-10L to S-10R, from STA 360 to STA 500C and from STA 727G to STA 908.
EFFECTIVITY 737-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.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 inspection and repair procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX F of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 737-53A1358
ALERT ALERT STA 908 STA 540 STA STA 360 INSPECTION AND SKIN
REPLACEMENT AREAS FOR GROUPS 1-21 AND 29-41
DO A NON-DESTRUCTIVE INSPECTION (NDI) OF THE
CROWN SKIN ADJACENT TO CHEM-MILL STEPS FOR
ANY CRACK, IF NO CRACK IS FOUND, REPEAT THE FRAME NDI FOR ANY CRACK. IF ANY CRACK IS FOUND,
INSTALL AN SRM REPAIR OR A CATEGORY C REPAIR AND REPEAT THE NDI AT ALL UNREPAIRED AREAS.
INSPECT ALI _ CATEGORY C REPAIRS FOR ANY LOOSE OR TENERS. REPLACE ANY _OOSE OR TENERS. CHANGE ALL & STRINGER CATEGOR TO SB REPAIRS AND DO A
POST-REPAIR UENCY EDDY CURRENT (LFEC) INSPEC FOR ANY CRACK. IF ANY CRACK IS FOUND. COI THE BOEING COMPANY FOR REPAIR INSTRUC ONS AND DO THE REPAIR.
REPEAT THE LFEC INSPE TION AT ALL OTHER SB REPAIR LOCATIONS. NO CRACK IS FOUND € STRINGER REPEAT THE POST-REPAIR LFEC INSPECTION FOR ANY CRACK.
REPLACE ALL SIX CROWN SKIN PANEL ASSEMBLIES.
OUTBOARD VIEW OF SKIN (TYPICAL)
STA STA 500C 908 STA 727G STA 360 INSPECTION AND SKIN
REPLACEMENT AREAS FOR GROUPS 22-28 2483009 Original Issue: April 27, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53A1358 Work - See page 1 for details. 10 of 270
Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1358 Original Issue: April 27, 2017 ATA System: 5331 SUBJECT: FUSELAGE - Skin - 0.036 Inch Crown Skin Panels Between S-10L and S-10R, STA 360 to STA 540 and STA 727 to STA 908 - Inspection, Repair and Replacement
THIS DOCUMENT 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 DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER.
1. PLANNING INFORMATION A. Effectivity
1. Airplanes This service bulletin is applicable to 737-200/-200C/-300/-400/-500 Airplanes, line numbers 292-2552 in 41 Groups. The airplanes are grouped by crown skin configurations. The Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP 737-200 Airplanes without UHF/VHF antenna provision.-1 737-200 Airplanes without UHF/VHF antenna provision and a different surface finish than Group 1 airplanes -2 737-200 Airplanes with UHF/VHF antenna provision.-3 737-200 Airplanes with UHF/VHF antenna provision and unique configuration from STA 847 to STA 857.
-4 737-200 Airplanes without chem-milled pockets from S-4L and S-4R.-5 737-200C Airplanes.-6 737-200C Airplanes and a different surface finish than Group 6 airplanes.
-7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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DESCRIPTIONCONFIGURATIONGROUP 737-300 Airplanes with no antenna provisions.-8 737-300 Airplanes with no antenna provisions and no chem-milled pockets from STA 540 to STA 727E at S-4L to S-10L and S-4R to S-10R.
-9 737-300 Airplanes with ATC antenna provision.-10 737-300 Airplanes with ATC antenna provision and no chem-milled pockets from STA 540 to STA 727E at S-4L to S-10L and S-4R to S-10R.
-11 737-300 Airplanes with ADF antenna provision.-12 737-300 Airplanes with ATC and MLS antenna provisions.-13 737-300 Airplanes with TCAS and ATC antenna provisions.-14 737-300 Airplanes with TCAS, ATC and ELT antenna provisions.-15 737-300 Airplanes with TCAS and ATC antenna provisions and no chem-milled pockets from STA 540 to STA 727E at S-4L to S-10L and S-4R to S-10R.
-16 737-300 Airplanes with TCAS, ATC and MLS antenna provisions.-17 737-300 Airplanes with ATC and Broadcast antenna provisions.-18 737-300 Airplanes with TCAS, ATC and GPS antenna provisions.-19 737-300 Airplanes with TCAS, ATC, MLS and GPS antenna provisions.
-20 737-300 Airplanes with unique configuration at STA 420 to STA 430.-21 737-400 Airplanes with no antenna provisions.-22 737-400 Airplanes with ATC antenna provision.-23 737-400 Airplanes with ATC and MLS antenna provisions.-24 737-400 Airplanes with ATC and Broadcast antenna provisions.-25 737-400 Airplanes with TCAS, ATC and MLS antenna provisions.-26 737-400 Airplanes with TCAS, ATC and Broadcast antenna provisions.
-27 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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