N360WA
Registered owner: NORTHERN AIR CARGO LLC, AK (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| NORTHERN AIR CARGO INC | Operator | 2011-03-30 – 2011-03-30 | Operator named in NTSB report |
| NORTHERN AIR CARGO LLC (NACA) | Operator | 2011-03-30 – 2011-03-30 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
L1 WINDOW CRACKED IMMEDIATELY AFTER TAKEOFF
FLT 55. CAPTAIN'S WINDOW L1 CRACKED.
CRACK FOUND 3 INCH FWD OF BS 727E ALONG STR 22R
WHILE ACCOMPLISHING SERVICE CHECK, CRACK WAS FOUND. CRACK IS APPROXIMATELY 1 5/8 INCHES LONG, 7 ¼ INCHES AFT OF STA 727D (727D +7 ¼), 12 INCHES FWD OF STA 727E (727E -12), 7 ½ BELOW S-20R, 3 ¾ INCHES AFT OF THE WING-TO-BODY FAIRING, 10 ¾ INCHES ABOVE THE EXISTING REPAIR AROUND THE EMERGENCY LIGHT & 12 ¾ FWD OF THE OTHER REPAIR.
POST FLIGHT CHECK FOUND CRACK IN FUSELAGE AFT OF THE AFT CARGO DOOR. CRACK MEASURES AT 2 1/8 WIDE AFT OF BS 868 ALONG STR 24
DEFECTED HOLES (4EA) FOUND ON STA 400 FRAME REPAIR.
A STRINGER TIE CLIP CRACK WAS FOUND AT STA 616, S-5R & S-5L. STRINGER TIE CLIP REPLACED. PER EO 737-53-0251-01 SB 737-53-1268 APPENDIX A PAGE 288-289 & TABLE 35 PAGE 318-319. B737-300 SRM 51-40-02 PARA 4.
A STRINGER TIE CLIP CRACK WAS FOUND AT STA 727B, S-3L, 727C, S-6R 727D, S-4R STA 727D, S-5R, STA 727E, S-5L. STRINGER TIE CLIPS REPLACED. PER EO 737-53-0251-01 SB 737-53-1268 APPENDIX A PAGE 288-289 & TABLE 35 PAGE 318-319. B737-300 SRM 51-40-02 PARA 4.
A STRINGER TIE CLIP CRACK WAS FOUND AT STA 747, S-4R. STRINGER TIE CLIP REPLACED. PER EO 737-53-0251-01 SB 737-53-1268 APPENDIX A PAGE 288-289 & TABLE 35 PAGE 318-319. B737-300 SRM 51-40-02 PARA 4.
UPPER FUSELAGE STRINGER CLIP CRACK, STA907, 4R & 8L. STRINGER TIE CLIP REPLACED. PER EO 737-53-0251-01 SB 737-53-1268 APPENDIX A PAGE 288-289 & TABLE 35 PAGE 318-319. B737-300 SRM 51-40-02 PARA 4.
A CRACK WAS FOUND AT FAIL-SAFE CHORD S-15R OF RIGHT SIDE(AT UPPER FASTENER LOCATION , LENGTH 5MM). PERFORMED REPAIR AT FAIL-STAFE CHORD STA 380, S-15R. 1. TRIM OFF DAMAGED AREA 2. MADE REPAIR PARTS AND INSTALLED I.A.W. EO 737-53-0379, REF FAA 8110-3 DTD 04/28/2025 AND FAA AMOC DTD 5/10/25.
UPPER FUSELAGE STRINGER CLIP CRACK, STA887, 4R. STRINGER TIE CLIP (STA 827-4L SYMBOL "D") REPLACED. PER EO 737-53-0251-01 SB 737-53-1268 APPENDIX A PAGE 288-289 & TABLE 35 PAGE 318-319. B737-300 SRM 51-40-02 PARA 4.
STRINGER TIE CLIP (STA 847-4L SYMBOL "D") REPLACED. PER EO 737-53-0251-01 SB 737-53-1268 APPENDIX A PAGE 288-289 & TABLE 35 PAGE 318-319. B737-300 SRM 51-40-02 PARA 4 .
UPPER FUSELAGE STRINGER CLIP CRACK, STA827, 4L. STRINGER TIE CLIP (STA 827-4L SYMBOL "D") REPLACED. PER EO 737-53-0251-01 SB 737-53-1268 APPENDIX A PAGE 288-289 & TABLE 35 PAGE 318-319. B737-300 SRM 51-40-02 PARA 4.
DURING NRC: CA1624-309 CORRECTION ,AFT ANGLE REMOVE FOUND CORROSION AT RH WING UPPER SKIN UPPER SURFACE WS.259 STR-13. REMOVED CORROSION LEVEL 2 AT RH WING UPPER SKIN ANGLE WWS.259 BETWEEN STR-11 -STR-12. FROM PN 65C27356-22, AFTER CORROSION REMOVED, ANGLE THROUGH REPLACED ANGLE PER B737-300 SRM 51-40-02 PARA 4 (R136) & DWG 65C27356.
DURING NRC: CA1624-309 CORRECTION ,AFT ANGLE REMOVE FOUND CORROSION AT RH WING UPPER SKIN UPPER SURFACE WS.258 STR-13. REMOVED CORROSION LEVEL 2 AT RH WING UPPER SKIN ANGLE WWS.258 BETWEEN STR-11 -STR-12. FROM PN 65C27356-22, AFTER CORROSION REMOVED, ANGLE THROUGH REPLACED ANGLE PER B737-300 SRM 51-40-02 PARA 4 (R136) & DWG 65C27356.
CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.372 AND WS.374 , BETWEEN S-11 AND S-12 AREA . CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.409.5 AND WS.412 , S-13 AREA . CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.497 AND WS.500 , S-11 AREA . CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.485.5 AND WS.488.5 , BETWEEN S-9 AND S-10 AREA. REMOVED CORROSION LEVEL 2 AT LH WING UPPER SKIN SURFACE AND REMAINING THICKNESS IS WITHIN LIMITS. AREA CLEAN AND PROTECIVE. PER: EO 737-57-0051 PME NO: 004693.
CORROSION WAS FOUND AT LT WING UPPER SKIN UPPER SURFACE BETWEEN WS.364 AND WS.367 , LEADING EDGE SKIN AREA. WS.371 AND WS.374 , LEADING EDGE SKIN AREA. WS.422 AND WS.424 , LEADING EDGE SKIN AREA. WS.428 AND WS.430 , LEADING EDGE SKIN AREA. WS 456 AND WS.463 , LEADING EDGE SKIN AREA . WS.472.5 AND WS.490.5 , LEADING EDGE SKIN AREA. REMOVED CORROSION LEVEL 2 AT LH WING UPPER SKIN SURFACE REMAINING THICKNESS IS WITHIN LIMITS. AREA CLEAN AND PROTECIVE. PER: EO 737-57-0051 PME NO: 004693.
LEFT WING UPPER SKIN UPPER SURFACE BETWEEN WS.260 AND WS.208.5, 363, AND WS.366 , WS.376 AND WS.380 , WS 417 AND WS.418.5 , WS.427 AND WS.428.5 , WS.433 AND WS.434.5 , FRONT SPAR AREA . REMOVED CORROSION LEVEL AT LH WING UPPER SKIN SURFACE SRM 51-10-02 PARA 14 (R136). REMAINING THICKNESS IS OVER LIMIT. AREA CLEAN AND PROTECIVE. PER: EO 737-57-0051 PME NO: 004693.
CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.399 AND WS.401 , REAR SPAR AREA. CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.390 AND WS.392 , REAR SPAR AREA. CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.380 AND WS.382, REAR SPAR AREA. CORROSION WAS FOUND AT LH WING UPPER SKIN UPPER SURFACE BETWEEN WS.369 AND WS.371 , REAR SPAR AREA. REMOVED CORROSION LEVEL 2 AT LH WING UPPER SKIN UPPER SURFACE AND REMAINING THICKNESS 0.191" IS OVER LIMIT. AREA CLEAN AND PROTECTIVE. PER EO 737-57-0051 PME NO: 004693 DATE DUE: DEC 01 2025 CAT B REPAIR.
RH WING OUTBOARD AFT FLAP LOWER SKIN DISBOND BETWEEN WBL.270~WBL.280. PERFORMED CATEGORY A METAL BOND REPAIR WITH 250 F CURE MATERIAL AT RH WING OUTBOARD AFT FLAP LOWER SKIN BETWEEN WBL 270-WBL 280 IAW B737-300 SRM 57-53-02 REPAIR 2 & SRM 51-70-10 REPAIR 4 (R136)
CORROSION FOUND AT RH WING UPPER SKIN UPPER SURFACE WS.135 , STR-7, WS.136 , STR-6, WS.137 , STR-4, WS.140 , STR-4, WS.147 , STR-7. CORROSION FOUND AT RH WING UPPER SKIN ANGLE WS.143 BETWEEN STR-9~ STR-10. PERFORMED REPAIR AS PER EO NO 737-57-0052 CAT B REPAIR,
LH OVERWING EMERGENCY EXIT HATCH CORROSION AROUND LOW PORTION. REPLACED NEW SEAL ANGLE - BOTTOM IAW B737-300 SRM 51-40-02 PARA 4 PAGE 2 AND DWG NO. 50-7978 SH 2.
CORROSION FOUND AT RH WING UPPER SKIN UPPER SURFACE WS.583 BETWEEN STR-11~ FRONT SPAR. PERFORMED REPAIR AS PER EO NO 737-57-0052 CAT B REPAIR, REF FAA 8100-9, EO 202504160065-0003.
FLOOR BEAM CRACK AROUND FASTENER ON STA294.5 RBL 51, APPROXIMATE SIZE: 0.375" NEAR FWD SERVICE DOOR CUTOUT FWD LOW CORNER.
MAIN WHEEL WELL PRESSURE WEB CRACK STA663.75+3" LBL24.5+8" APPROXIMATE SIZE L0.375. PERFORMED REPAIR AT STA 663.75+3, LBL 245.5+8 IAW SRM 53-60-51 REPAIR 4.
CORROSION FOUND AT RH WING UPPER SKIN ANGLE WS.259 BETWEEN STR 11-12. REMOVED CORROSION LEVEL 2 AT RH WING UPPER SKIN ANGLE WWS.259 BETWEEN STR-11 -STR-12. FROM PN 65C27356-22, AFTER CORROSION REMOVED, ANGLE THROUGH REPLACED ANGLE PER SRM 51-40-02 PARA 4 & DWG 65C27356.
CORROSION FOUND AT RT WING UPPER SKIN UPPER SURFACE WS.252, FRONT SPAR. WS.261 , FRONT SPAR . CORROSION FOUND AT RT WING UPPER SKIN UPPER SURFACE WS.266 , SKIN FWD EDGE. CORROSION FOUND AT RT WING UPPER SKIN UPPER SURFACE WS.268, SKIN FWD EDGE. CORROSION FOUND AT RT WING UPPER SKIN UPPER SURFACE WS.533 BETWEEN STR-10~ STR-11. CORROSION FOUND AT RT WING UPPER SKIN UPPER SURFACE WS.554 , SKIN TRAILING EDGE. PERFORMED REPAIR AS PER EO NO 737-57-0052 CAT B REPAIR.
PERFORMED REPAIR AT STA 294.5 RBL51. TRIMED OUT DAMAGED AREA. MADE REPAIR PARTS AND INSTALLED. PER B737-300 SRM 53-10-51 REPAIR 5 FIG 201.
RH OVERWING EMERGENCY EXIT HATCH CORROSION AROUND LOW PORTION. REPLACED NEW SEAL ANGLE - BOTTOM IAW B737-300 SRM 51-40-02 PARA 4 PAGE 2 AND DWG NO. 50-7978 SH 2.
CORROSION FOUND AT RH WING UPPER SKIN UPPER SURFACE WS.565 BETWEEN STR-11~ STR-12. PERFORMED REPAIR AS PER EO NO 737-57-0052 CAT B REPAIR, REF FAA 8100-9, EO 202504160065-0003.
GOUGE WAS FOUND AT LH WIN O/B FORE FLAP NOSE LOWER SKIN , WBL 412.11. MADE REPAIR PARTS. INSTALL REPAIR PARTS AT LH WIN O/B FORE FLAP NOSE LOWER SKIN PER: 737-300 SRM 57-53-01 REPAIR 1. (R136)"
SURFACE CORROSION ON FUSELAGE LH SIDE WATER SERVICE PANEL 1501L EXTERNAL SURFACE. REPLACED LH SIDE WATER SERVICE PANEL PER AMM 52-48-00 PAGE 1 REV 101.
RH WING INBOARD FORE FLAP SKIN WORN AT WBL.73. REMOVED THE DAMAGED DOUBLER AT RH WING INBOARD FORE FLAP SKIN AT WBL.73. PERFORMED CATEGORY A METAL BONDING WITH250 F CURE MATERIAL. IAW B737-300 SRM 57-53-02 REPAIR 1 & SRM 51-70-10 REPAIR 4 (REV136).
CHAFING WAS FOUND AT LH WING O/B MID FLAP LOWER SKIN , WBL 272.6 , L:2.1 INCH , W:0.4 INCH. PERFORMED PERMANENT METAL BOND REPAIR WITH 250 F CURE MATERIAL AT LH WING O/B MID FLAP LOWER SKIN, WBL 272.6 IAW B737-300 SRM 57-53-01 REPAIR 6 & SRM 51-70-10 REPAIR 4 (REV 136).
CHAFING WAS FOUND AT LH WING O/B MID FLAP LOWER SKIN , WBL 258.6 , L:2.1 INCH , W:0.5 INCH. PERFORMED PERMANENT METAL BOND REPAIR WITH 250 F CURE MATERIAL AT LH WING O/B MID FLAP LOWER SKIN, WBL 258.6 IAW B737-300 SRM 57-53-01 REPAIR 6 & SRM 51-70-10 REPAIR 4 (REV 136).
CORROSION AT RH HORIZONTAL STABILIZER TRAILING EDGE BEAM UPPER SURFACE AT STAB STA 223. CORROSION REMOVED & CONDITION CHECK. THE BLEND-OUT DEPTH IS 0.048 ' INCH. WERE OVER LIMIT. MADE REPAIR DOUBLER TO INSTALL WITH REPAIR WASHER & SEALANT PER B737-300 SRM 51-10-02 PARA 14, 55-10-13 FIG 101, 55-10-13 REPAR 3 FIG 201 SH 7/9 (R136).
RH WING INBOARD AFT FLAP LOWER NOSE SKIN SKIN BULGE AT WBL.115. CORROSION REMOVED SKIN THROUGH. REPLACED NOSESKIN ASSY AT RH WING I/B AFT FLAP WBL 115 PER B737-300 SRM 51-40-02 PAGE 2-3 (R136) & DWG 65-46434.
BULGE WAS FOUND AT LH WING I/B AFT FLAP NOSE LOWER SKIN , BETWEEN WBL 136 AND WBL 140. SHIM REPLACED, REMOVED AND INSTALLED LEADING EDGE SKIN AT LH WING I/B AFT FLAP, BETWEEN WBL 136 AND WBL 140. PER AIR ASIA NRC: CA1624-102 FOR SHIM FABRICATION.
SURFACE CORROSION ON LH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S9C BETWEEN LBL40.875+5" AND LBL40.875+8. PERFORMED PERMANENT REPAIR PER NAC EO 737-57-0053 CAT B REPAIR.
CORROSION FOUND AT RH WING UPPER SKIN UPPER SURFACE WS.135 , STR-9. PERFORMED REPAIR AS PER EO NO 737-57-0052 CAT B REPAIR, REF FAA 8100-9, EO 202504160065-0003
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 727E+5" S-11L+10", AREA: L 0.680", W 2.420".
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 887+10" S-11R+15", AREA: L 1.310", W 0.921". REPLACED PASSENGER CABIN WINDOW PLUG PER AEI R-817-MM 56-21-11 PAGE 401. REPLACED PASSENGER CABIN WINDOW PLUG PER AEI R-817-MM 56-21-11 PAGE 401 AND CABIN WINDOW SCREW TORQUE COMPLETED 15 IN-LB PME: 005683.
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 559+4" S-11R+7", AREA: L 0.460", W 1.023". REPLACED PASSENGER CABIN WINDOW PLUG PER AEI R-817-MM 56-21-11 PAGE 401.
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 559+4" S-11R+7", AREA: L 0.460", W 1.023". REPLACED PASSENGER CABIN WINDOW PLUG PER AEI R-817-MM 56-21-11 PAGE 401.
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 559+10" S-11R+15", AREA: L 3.50", W 0.432".
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 559+16" S-11R+11", AREA: L 1.081", W 9.0". CORROSION LEVEL 2 AT PASSENGER CABIN WINDOW PLUG STA559+16", S-11R+11", AREA: L1.081", W9.0" CORROSION REMOVED AND FOUND DAMAGE AREA OVER LIMIT PER CMM 56-21-51 REPAIR 2-1 PARA2-D(2)( C)R.45 PME: #5465 DUE DATE: 2025/JUN/05 WINDOW REPLACED PER NRC CA1624-077.
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 360+8" S-11R+15", AREA: L1.130", W0.516". REPLACED PASSENGER CABIN WINDOW PLUG PER AEI R-817 MM 56-21-11 PAGE 401.
BULGE WAS FOUND AT LH WING I/B AFT FLAP NOSE LOWER SKIN , BETWEEN WBL 149 AND WBL 151. SHIM REPLACED, REMOVED AND INSTALLED LEADING EDGE SKIN AT LH WING I/B AFT FLAP, BETWEEN WBL 149 AND WBL 151. PER AIR ASIA W.P.S. CODE LM 65-46434-506, SRM 51-40-02 PARA 4 PARA 5 (R136).
REMOVE AND REINSTALL PASSENGER CABIN WINDOW PLUG PER AEIR-817-MM 56-21-11 PAGE 401 SERVICEABLE PARTS TAG ATTACHED ON NRC CA1624-082
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 847+5" S-11L+9", AREA: L0.383", W 1.825". REPLACED PASSENGER CABIN WONDOW PLUG PER AEI R-817-MM 56-21-11 PAGE 401.
PASSENGER CABIN WINDOW PLUG GOT CORROSION, STA 847+11" S-11L+1", AREA: L 2.239", W 0.339".
CORROSION FOUND ON RH HORIZONTAL STAB AT STA 98. REPAIRED PER EO 737-55-0017
WHILE PERFORMING N360WA SERVICE CHECK, CORROSION WAS FOUND ON THE KEEL BEAM LOWER CHORD AT BS 540, LBBL 6.50. FOLLOWING CORROSION REMOVAL, IT WAS DETERMINED THAT THE BLENDOUT EXCEEDED THE 737-300 BOEING SRM 53-60-12 ALLOWABLE LIMITS. AAC ENGINEERING CONTACTED ASAP INC. TO REQUEST A REPAIR PLAN. AN ALTERNATE REPAIR WAS PROVIDED FROM THAT OF BOEING SRM 53-60-12, REPAIR 3 - KEEL BEAM SPLICE. CORROSION REMOVED AND REPAIRED IAW NAC EO 737-53-0369.
FOUND CRACK INDICATION BELOW STRINGER 2R @ BS 400 + 1/38. FOUND INTERNAL NICK ON SKIN. REPAIRED NICK @ BS400 + 1 3/8 STR 2R PER NAC EO 737-53-0341-01 AEI EO 233-49
MECHANIC FOUND CRACK DURING SERVICE CHECK AT BS 727E, STR 22L APPROX 2 1/8" LONG. CRACK CONFIRMED BY EDDY CURRENT, COMPLETED REPAIR OF CRACK FOUND ON BS 727E STR 22L IAW SRM 52-31-00 REPAIR 31 & NAC PROJECT WORKSHEET ON 3/20/2024 & WITH REF TO EO 737-53-0339.
AUTOFAIL LIGHT WITH CABIN ALT WARNING ACCOMPANIED BY HISSING NOISE FROM CAPT SIDE WINDOW, COULD NOT PRESSURIZE. PERFORMED OPS TEST OF PRESSURIZATION CONTROLLER IAW AMM 21-31-00 OPS CHECK OK. CHECKED AND CLEANED CAPT'S SLIDING WINDOW SEAL. NO DEFECTS NOTED.
#2 ENGINE.- DURING ACCOMPLISHMENT OF AD 200-16-51 WAS FOUND RH 5TH STAGE ENGINE BLEED VALVE CORRODED AND STUCKED P/N 3202222-1 AND S/N 2243. "REMOVED AND REPLACED RH 5TH STAGE ENG BLEED AIR CHECK VALVE IAW B737 AMM 36-11-35 PAG 401-408. PERFORMED LEAK CHECK IAW B737 AMM 36-11-35 PAG 407. VERIFIED SATISFACTORY, NO LEAKS NOTED."
RH WING.- INBD T/E MID FLAP UPPER SKIN SHOW CORROSION. REMOVED AND REPLACED MID FLAP ASSY AT INBD T/E FLAP ON RH WING IAW B737 AMM 27-51-04, PAGE 401-415. PERFORMED OPS CHECK AND ADJUSTMENT TEST IAW B737 AMM 27-51-04, PAGE 415-423, VERIFIED SATISFACTORY.
AFT CARGO COMPT.- SECTION 46 S-27L SPLICE WITH CORROSION STA 907.0. PERFORMED MAJOR REPAIR CATEGORY "A" ON AFT CARGO CAOMPARTMENT SECTION 45 STA 907.0, S-27L. REMOVED CORRODED SPLICE IAW B737 SRM 51-40-02 PAG 4, FABRICATED SPLICE FROM AL 7075 "0" 0.063 IAW B737 SRM 51-30-01 PAG 1, PERFORMED HEAT TREATMENT FROM AL 7075 "0" TO 7075-T6 IAW BAC 5602, CLEANED, TREATED AND PRIMED AREA IAW B737 SRM 51-20-01 PAG 1. INSTALLED SPLICE ON AFT CARGO COMPARTMENT, SECTION 46 STA 907.0 S-27L IAW B737 SRM 51-40-02 PAG 4. ENTERED ON FAA FORM 337.
LH WING.- OUTBD AFT FLAP LWR PART WITH CORROSION POINT STA WBL 351.0. REMOVED DAMAGED AREA OUTBD AFT FLAP LWR PART STA WBL 351.0 ON LH WING IAW B737 SRM 51-70-10 REV 130. FABRICATED FILLER AND DOUBLER OF CLAD 2024 T3-0.016 IAW SRM 57-53-02, REV 130 APPLIED PRIMER BMS5-89 IAW B737 SRM 51-70-10 REV 130 BONDED FILLER AND DOUBLER WITH HYSOL EA 9394 IAW B737 SRM 51-70-10 APPLIED SEALANT AROUND THE DOUBLER IAW B737 SRM 51-70-10 REV 130
LH WING.- WING SKIN UPPER SURFACE CORRODED AT FORWARD SPAR WS 235.00. EFFECTED OEM FASTENER REMOVED AND NEW FASTENER INSTALLED IAW SRM 57-20-01 ALLOWABLE DAMAGE 4 TABLE II AND IAW BOEING REPAIR MESSAGE: NAC- NAC -23-0022-08B , DATED 13, APRIL 2023 RESTORED AERODYNAMIC SURFACE USING BMS 5-95 SEALANT PER SRM 51-20-05 . PAINTED THE UPPER SURFACE OF THE REWORKED AREA IAW AMM 51-21-99 REV 97, SEE ATTACHED NDT REPORTS ULTRASONIC INSPECTION 0585, LIQUID PENETRANT INSPECTION 0656, 0657 EDDY CURRENT INSPECTION 0654, 0659 ATTACHED CORROSION DAMAGE REMOVED FROM UPPER SURFACE WING STATION 249 AT FRONT SPAR LH IAW BOEING REPAIR MESSAGE : NAC- NAC-23-0022-08B, DATED 13, APRIL 2023, THE ORIGINAL MATERIAL THICKNESS WAS 0.278 MAXIMUN MATERIAL REMOVAL DEPTH IS 0.024 REMAINING MATERIAL THICKNESS IS 0.254. MAXIMUN CROSS SECTION REMOVAL IS 0.030 SQ IN AND FOUND TO BE WITHIN ALLOWABLE LIMITS OF BOEING REPAIR MESSAGE NAC-NAC-23-0022-08B, DATED 13, APRIL 2023. REPAIR AREA FLAP PEENED INS ACCORDANCE WITHIN SRM 51-20-06 AND SOPM 20-10-03 REWORK AREA PREPPED AND PRIMER IAW SRM 51-20-01 AND SOPM 20-44-04
RH WING.- WING SKIN UPPER SURFACE CORRODED AT FORWARD SPAR WS 495.00. CORROSION DAMAGE REMOVED AT WING STATION 494.00 AT REAR SPAR R/H IAW BOEING REPAIR MESSAGE NAC-NAC 23-0022-08B, DATED 13, APRIL 2023, NOMINAL MATERIAL THICKNESS WAS 0.145 MAXIMUM MATERIAL REMOVAL DEPTH IS 0.023 REMAINING MATERIAL THICKNESS IS 0.122 MAXIMUM CROSS SECTION REMOVAL IS 0.0161 SQ IN AND FOUNS TO BE WITHIN ALLOWABLE LIMITS OF BOEING REPAIR MESSAGE : NAC-23-0022-08B DATED 13, APRIL 2023. REPAIR AREA FLAP PEENED IN ACCORDANCE WITH SRM 51-20-06 AND SOPM 20-10-03, REWORK AREA PREPPED AND PRIMED IAW SRM 51-20-01 AND SOPM 20-44-04 EFFECTED OEM FASTENER REMOVED AND NEW FASTENER INSTALLED IAW BOEING 737-300 AMM 20-50-11 REV 96 , SEPT 25, 2022 RESTORE AERODYNAMIC SURFACE USING BMS 5-95 SEALANT PER SRM 51-21-05 PAINTED THE UPPER SURFACE OF THE REWORKED AREA IAW AMM 51-21-99 REV 97 SEE ATTACHED NDT REPORTS ULTRSONIC ISNPECTION 0591, LIQUID PENETRANT INSPECTION 0702, 0703 EDDY CURRENT INSPECTION 0701,0704
RH WING.- WING SKIN UPPER SURFACE CORRODED AT REAR SPAR WS 495.00. CORROSION DAMAGE REMOVED FROM UPPER SURFACE WING STATION 495.00 AT FRONT SPAR R/H IAW BOEING REPAIR MESSAGE : NAC- NAC 23-0022-08B, DATED 13, APRIL 2023, NOMINAL MATERIAL THICKNESS WAS 0.150 MAXIMUM MATERIAL REMOVAL DEPTH IS 0.023 REMAINING MATERIAL THICKNESS IS 0.127 MAXIMUM CROSS SECTION REMOVAL IS 0.0115 SQ IN AND FOUND TO BE WITHIN ALLOWABLE LIMITS OF BOEING REPAIR MESSAGE : NAC-NAC -23-0022-0813, DATED 13, APRIL 2023 REPAIR AREA FLAP PEENED IN ACCORDANCE WITH SRM 51-20-06 AND SOPM 20-10-03, REWORK AREA PREPPED AND PRIMEDIAW SRM 51-20-01 AND SOPM 20-44-04 EFFECTED OEM FASTENER REMOVED , AND NEW FASTENER ISNTALLED IAW SRM 57-20-01 ALLOWABLE DAMAGE 4 , TABLE I AND BOEING REPAIR MESSAGE: NAC-NAC -23-0022-08B , DATED 13, APRIL 2023 . RESTORE AERODYNAMIC SURFACE USING BMS 5-95 SEALANT PER SRM 51-20-05. PAINTED THE UPPER SURFACE OF THE REWORKED AREA IAW AMM 51-21-99 REV 97 SEE ATTCHED NDT REPORTS ULTRSASONIC ISNPECTION 0597, LIQUID PENETRANT INSPECTION 0688, 0689 EDDY CURRENT INSPECTIONS 0687, 0690
FOUND CRACK AT LOCATION LAP 142 BS 807 BETWEEN 807 +2 AND 807 +4. REF PROJECT WORKSHEET AND NR TASK CARD 0004, FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-00-01
FOUND 3/8 INCH HOLE IN BS 520L FRAME BETWEEN STR 16 AND 17 ON THE RADIUS. REPAIRED 520L FRAME PER EO# 19321, REFERENCE PROJECT WORKSHEET.
CRACK INDICATIONS AT BS 360+11 @ STRINGER 19R - 11/16 AND 1 3/4 INCHES. BS 727E +12 AND STR 23R - 2 5/16 INCHES. B727D+15 AND STR 23 R - 3 3/4 INCHES. REPAIR PERFORMED IAW SRM 53-00-01 REPAIR 31.
ON GEAR RETRACTION THE HYDRAULIC SYSTEM A, ENGINE LOW PRESSURE LIGHT CAME ON
HYDRAULIC SYSTEM - A, LOSS ALL FLUID ON CLIMB OUT THROUGH 14,000 FT. REF THE QRH, NORMAL LANDING.
DISCREPANCY: HYDRAULIC SYSTEM A, LOSS ALL FLUID ON CLIMB OUT THROUGH 14,000FT. RAN QRH, NORMAL LANDING. CORRECTIVE ACTION: REMOVED AND REPLACED SYSTEM A ELEVATOR ISOLATION VALVE IAW AMM 27-31-84, LEAK AND OPT CHECKED GOOD.
HYDRAULIC SYSTEM - A, LOSS ALL FLUID ON CLIMB OUT THROUGH 14,000 FT. REF THE QRH, NORMAL LANDING.
DISCREPANCY: 1 7/8 INCH CRACK AT BS927 + 6 3/4 INCHES, STR25R. CORRECTIVE ACTION: INSTALLED REPAIR PER SRM 53-00-01 REPAIR 31 DETAIL XIX.
DISCREPANCY: 1.25 INCH CRACK AT BS907+7.25 INCHES, STR25R. CORRECTIVE ACTION: INSTALLED REPAIR PER SRM 53-00-01, REPAIR 31 DETAIL XXVIII.
DISCREPANCY: ON WALK AROUND FOUND 2.5" CRACK LOCATED BS727D + 2.5 TO BS727D + 5, BELOW STR23R. CORRECTIVE ACTION: REPAIRED IAW SRM 53-00-01 DETAIL VII PAGE 234.
LEFT HORIZONTAL STAB HAS CORROSION ON UPPER TRAILING EDGE BEAM AT STAB STA 258.28 AND 239.9. STA 258.28 CLEAN, TREATED AND PRIMED AREA, WITHIN LIMITS PER SRM 51-10-2. STAB STA 239.9 INSTALLED REPAIR PER ENGINEERING REPAIR ORDER FOR INSTALL OF FASTENER DEVIATION AND SRM 55-10-1 REPAIR.
LT HORIZONTAL STAB REAR SPAR UPPER CHORD HAS CORROSION. COMPLIED WITH DRAWING 5510D2824.
RIGHT HORIZONTAL STAB REAR SPAR UPPER CHORD HAS CORROSION. COMPLIED WITH DRAWING NR 5510D2824.
BS500C S9L HAS A CRACK IN INNER FLANGE OF BELTFRAME, FOUND WHEN ACCESSING FOR W/O 1940290. REPAIR IAW B737-300 SRM REV 119 CH 53-00-07 REPAIR 1 DETAIL 1
BS180 RBL5.7 WL183 CRACKED VERTICAL BEAM. STA 180 RBL 5.7 WL 183 CRACKED VERTICAL BEAM REPAIRED IAW SERVICE BULLETIN 737-53A1225 REV 1 APRIL 15,2005.
BS180 LBL5.7 WL178 CRACKED VERTICAL BEAM. STA 180 LBL 5-7 WL 178 CRACKED VERTICAL BEAM REPLACED WITH NEW PART IAW DWG 65C38473 REV -.
BS500A S25R + 6.5" CRACK ON FRAME OUTER FLANGE. STA 500A STR 25 + 6.5R CRACK ON FRAME OUTER FLANGE REPAIRED IAW B737-300 SRM SECTION 53-00-07 FIG 201 PAG 201 REV 119
BS344 S11R STRINGER CLIP CRACK INDICATION. STA 344 STR 11R STRINGER CLIP REPLACED IAW B737-300 SRM REV 119 CH 51-40-02 PAR 07
BS303 S16L + 4 INTERCOSTAL GOUGED. BLEND AND ASSESS, REPLACED IAW SB737-53A1240 PART 4.
LEFT HAND BS344 - BS351 BETWEEN S27L - S26L CORROSION FOUND ON FRAME SHEAR TIE AND SKIN DOUBLER. LT STA 344 STR 27L CORRODED SHEAR TIE REPLACED WITH MADE REPAIR PART IAW DWG 65-45885 REV D VIEW BS AND SRM REV 119 CH 57-40-02.
BS360 - BS351 BETWEEN LBL1- RBL3 CORROSION FOUND ON FRAME WEB. STA 360-351 BTW LBL 1-RBL 3 CORROSION ON FRAME WEB REPAIRED IAW SRM 53-00-07 REV 119. REPAIR 3 FIGURE 201.
RIGHT HAND BS344 S27R AND S26R CORROSION FOUND ON FRAME SHEAR TIE. RT STA AT 344 STR 27R AND 26R CORRRODED SHEAR TIE. REPLACED WITH MADE REPAIR PART IAW SRM REV 119 CH 53-00-07 REPAIR 8.
RIGHT HAND BS294 - BS312 RBL53 AT S17R CRACKED SHEAR WEB. CREASE BEAM WEB AT R1 SILL. RT STA 294 - 312 RBL 53 AT STR 17 SHEAR WEB REPLACED WITH MADE REPAIR PART IAW SRM REV 119 CH 53-10-15 AND CH 51-30-01.
BS303.9 S16L DOOR STOP FITTING CUT OUT REINFORCEMENT DOUBLER CRACKED. STA 303.9 STR 16L DOOR STOP FITTING CUT OUT REINFORCEMENT DOUBLER REPAIRED IAW SB 737-53A1197 PART 3 FIG 3,4 DATED AUG 25, 2006.
BS967 TO BS987, S25L AFT PIT CORRODED STRINGER. FS 967 TO 987 STR 25L AFT PIT STRINGER REPLACED WITH MADE REPAIR PARTS IAW SRM REV 120 53-00-03 FIG 201 REPAIR 1.
BS351 S15L CLIP IS CRACKED. STA 351 STR 15L SLIP REPLACED WITH MADE PART IAW DWG #65- 45817 REV BE. PART INSTALLED IAW SRM 51-40-02 REV 120, DWG #65-45817 REV F.
BS360 S15L STRINGER SPLICE IS CRACKED. STA 360 STR 15L STRINGER SPLICE REPLACED WITH NEW STRINGER SPLICE IAW SRM REV 120 51-40-02 AND DWG 65-17685 REV E.
BS304 S7R R1 DOORWAY SKIN CORNER CUTOUT CRACKED. STA 304 STR 7R RI DOORWAY SKIN CORNER CUTOUT CRACK REPAIRED IAW SR# 4-4490828110.
CRACK FOUND WHILE CARRYING OUT AD 2017-13-13 @ STA 344 BELT FRAME WEB 1 INCH HOLE BETWEEN STR 23L & 24L. CRACKED FRAME AT STN 344 BETWEEN STR23L AND 24L: REPLACED COMPLETE FRAME AT STA 344 STR 22L TO 28L IAW DWG 65- 45815 REV H AND SRM REV120 51-40-02 AND SR # 3-4463126198. REFER TO NDT19-1322 FOR INTERNAL FRAME CRACK VERIFICATION. REFER TO FAN FORM 8100-9 TO 201905300074-0006.
BS1040 AFT PRESSURE BULKHEAD HAS 3 CRACKED WEBS. STA 1016 AFT PRESSURE BULKHEAD 3 CRACKED WEBS REPAIRED. IAW SR #3-4470-728395. 5 CRACKED STIFFENERS FOUND WHILE ACCOMPLISHING GORE WEB REPAIR REPLACED IAW SR# 4- 4501377456. SEE ATTACHED MTC 114S FOR DETAILS. REPAIRED S- 21R IAW KFC-NAC-19-004-17C.
BS288 - BS294 LBL3 CRACKED INTERCOSTAL (FORWARD OF ELECTRONIC ACCESS DOOR). STA 322-328 LBL 3 CRACKED INTERCOSTAL REPLACED WITH MADE REPAIR PART IAW BOEING DRAWING #69-48277 REV A
BS380 - BS400 BL0, INTERCOSTAL CRACKED AT FLOORBEAM. STA 390 - 400 BL 0 INTERCOSTAL AT FLOORBEAM IDENTIFIED IN B737-300 SRM REV 119 CH 53-30-51 REPAIRED IAW CH 51-30-01 WITH MADE REPAIR PART AND INSTALLED IAW B737-300 SRM REV 119 CH 51-40-02.
BS500B - BS500B + 10" AFT JAMB INNER SKIN OF MAIN CARGO DOOR HAS EXISTING SKIN REPAIR, IMPROPER FASTENER INSTALLATION, ELONGATED HOLES IN SKIN AND MANY GOUGES. REPLACED INNER SKIN WITH MADE REPAIR PART AT STA 500B-500B+ 10 IAW AEI DWG AE737-3-200-2 REV E, THIS REPLACEMENT OF SKIN REMOVED EXISTING REPAIR, FIXED IMPROPER FASTENERS AND ELONGATED HOLES AND GOUGES IN SKIN.
BS348 S13L CRACKED INTERCOSTAL ANGLE. STA 438 STR 13L CRACKED INTERCOSTAL ANGLE REPLACED WITH MADE PART IAW B737-300 SRM 51-30-01 AND MATERIAL ID IAW NDT19-4360. ANGLE INSTALLED IAW B737-300 SRM 51-40-02 REV 120
BS958.5 LOWER FORWARD CORNER OF L2 DOOR CUTOUT SKIN CRACKED. APPROX 3" LONG. CRACK AT STA 958.5 LOWER FWD CORNER OF L2 DOOR CUT OUT REPAIRED IAW BOEING SB 737-53A1350 ORIGINAL ISSUE DATE 6 MAY 2016 AND BOEING 737-300 SRM 53-00-01 REPAIR 32 REV 119.
BS308 - BS348 BL0 FLOORBEAM STRAP CRACKED. STA 308-348 BL 0 FAILURE COMPRESSION STRAP REPLACED WITH MADE REPAIR PART IAW B737-300 SRM REV 119 CH 53-10-51 AND 51-30-01 WITH ORIGINAL PART USED AS TEMPLATE
500C S2L DAMAGED STRINGER CLIP JUST AFT OF MAIN CARGO DOOR. 500C STR 2L STRINGER CLIP JUST AFT OF MAIN CARGO DOOR REPLACED WITH NEW PART IAW B737-300 SRM REV 119 CH 51-40-02 PARA 4
BS308 - BS348. LBL11 FLOOR BEAM STRAP CRACKED. STA 308-348 LBL 11 FAILURE COMPRESSION STRAP REPLACED WITH MADE REPAIR PART IAW B737-300 SRM REV 119 CH 53-10-51 AND 51-30-01 WITH ORIGINAL PART USED AS TEMPLATE
BS807 AND BS767 ABOVE S20L SHEAR TIES CORRODED. STA 807 AND 767 ABOVE STR 20L SHEAR TIES REPLACED WITH MADE REPAIR PART IAW DWG 65-46549 REV H AND INSTALLED IAW SRM REV 120 51-40-02; AND DWG 65-46551 REV D.
BS360 S11L CRACKED INTERCOSTAL CLIP. STA 360 STR 11L NEW INTERCOSTAL CLIP INSTALLED IAW B737-300 FRM 51-40-02 REV 120
BS 294.5 TO 303, S16L INTERCOSTAL CRACKED. REPLACE IAW SB737-53-1240 PART 4.
BS294.5-303 S15L INTERCOSTAL CRACKED. REPLACED IAW SB737-53-1240 PART 4.
RIGHT HAND BS312 - BS344 RBL25 AND AT RBL40 FLOORSTRAP CRACKED. RH STA 312-344 RBL 25 AND RBL 40 FAILURE COMPRESSION STRAP REPLACED WITH MADE REPAIR PART IAW B737-300 SRM CH 53-10-51 AND 51-30-01 USING ORIGINAL PART AS TEMPLATE, REV 119
BS847 BELTFRAME CORRODED AT S25-27L [RT]. STA 847 CARGO DOOR OPENING FRAME AT STR 17R-27R REPLACED WITH NEW FRAME IAW DRAWING 65-47960 REV K AND SRM REV 120 51-40-02.
BS294.5-303 S7L INTERCOSTAL CRACKED @ TWO LOCATIONS. STA 294.5-303 STR 7L INTERCOSTAL REPLACED WITH NEW PARTS IAW SR# 4-4491026014. SEE FAA FORM 8100-9 ID 201906040114-0003 FOR APPROVAL.
BS817, BS867, BS897 [STRINGER] S20L IN AFT PIT CORRODED. FS 817, 867 & 897 STR 20L IN AFT PIT REPLACED WITH NEW PART AND INSTALLED IAW SRM REV 120 53-00-03.
REMOVE THE AEI DOUBLER & STIFFENERS AT BS706 RBL24.82 TO ACCOMPLISH AD2016-13-11 PARAGRAPH (G)(2). REMOVED THE AEI DOUBLER AND STIFFENERS AT BS 706 RBL 24.82 TO ACCOMPLISH AD 2016-13-11 PARAGRAPH (G)(2). BS 706 RBL 24.82 REPAIRED IAW AEI EO 8058 REV A AND REF DWG AE 6201 REV C. REFER TO FAA FORM 8110-3. REFER TO AMOC 790-19-8966
BS520 S28R CORROSION FOUND ON KEEL BEAM ON VERTICAL FLANGE. REPAIRED IAW SRM SECTION 53-60-12 REPAIR 3 DETAIL II REV 119. CORRODED KEEL BEAM SECTION REPLACED WITH MADE REPAIR PARTS IAW SRM SECTION 53-60-12 REPAIR 3 REV 119.
BS500C S2L HAS SUSPECTED CRACK AND TOOLING MARKS ON STRINGER. STA 500C STR 2L REPAIRED IAW R23553.1-053-014-001 REV IR.
BS1016 AT S6L AFT PRESSURE BULKHEAD WEB CRACKED. STA 1016 @ STR 6L AFT PRESSURE BULKHEAD REPAIRED IAW SRM 53-80-08 REPAIR 7, FIG 201 REV 120.
STA 312 STR 6R HAS EXTRA HOLES AND HOLE DAMAGE AT EXISTING FASTENERS. INSTALLED NEW STR AT STA 312 STR 6R IAW SRM REV 120 CH 51-40-02 PARA 4 AND PARA 7 AND DOCUMENT #65-45800 REV F.
CRACK AND DAMAGED HOLE ON INTERCOSTAL "L" ANGLE STA 291-270 STR 11-12R. CRACK AND DAMAGED HOLE ON INTERCOSTAL "L" ANGLE STA 291-270 STR 11-12R REPLACED "L" ANGLE WITH MADE REPAIR PART IAW SRM REV 120 SEC 51-30-01 AND REFER TO SRM REV 120, 53-10-15 PAGE 4 AND 5 AND MATERIAL TEST REPORT #1038.
FUSELAGE SKIN CRACKED AT STRINGER 21R, BS 767 +31.5 INCHES, FWD OF AFT CARGO DOOR CUTOUT. REPAIR DOUBLER AND TRIPLER INSTALLED IAW SRM 53-00-01, REPAIR 31, DETAIL XI.
DAMAGE TO STRINGER 22L, BS 500C. THE STRINGER WAS REPAIRED IAW EO4707 REVISION B.
CRACK FOUND ON FRAME BS 360, STRINGER 19R - 20R. REPAIRED THE FRAME IAW 17-0005-05B, 27. SR 3-3B93507665.
CRACK FOUND ON FRAME BS 380, STRINGER 18R - 19R. REPAIRED IAW AEI EO 4669, REV. IR.
CRACK IN TOOLING HOLE ON FORWARD FRAME OF C2 CARGO DOOR AT STRINGER 20R. THE FRAME WAS REPLACED IAW SRM 51-10-02, REV 113, PAGE 8, PARA 8, 51-40-02, PARA 4, PAGE 2, PAGE 4, PARA 7, AND DWG. 65-47959, REV D, SHEET 5.
CRACK ON FRAME BS 727, STRINGER 26L, CONFIRMED BY NDT. REPLACED THE FRAME IAW SB 737-53-1088, REV 1 AND DWG 65C33722.
DAMAGED STRINGER CLIP BS 500B, STRINGER 18L. REPLACED THE STRINGER CLIP IAW SRM 51-40-02 REV 113, PAGE 2, PARA 4, PAGE 4, PARA 7, PAGE 8, PARA 8.
CORROSION FOUND ON THE KEEL BEAM LEFT LOWER CAP BS 556 TO 572, STRINGER 28L. REPAIRED IAW DRAWING R23553.1-053-004-001, REV A, AND REPAIR DESIGN APPROVAL P-RA17-039/D.
TWO CRACKS FOUND IN THE FLOOR SUPPORT AT LBL 24, BS 656 - 685. THE FLOOR SUPPORT WAS REPAIRED IAW SERVICE BULLETIN 737-57A1296 REV 2.
DURING AN OPEN HOLE INSPECTION ON THE LEFT MAIN LANDING GEAR BEAM FITTING NR 5, A HOLE HAS INDICATIONS OF GOUGING & GALLING. REPAIRED IAW SR 3-3891900272.
LEFT OTBD FORE FLAP INBOARD END IS WORN. THE FORE FLAP WAS REPAIRED IAW DWG R23553.1-057-001-001 REV NC.
CRACK INDICATION USING NDT ON BS 727 GILLER STRAP AT LBL 10 TO RBL 10. REPLACED THE STRAP IAW DWG 69-46547 REV DK , & SRM 51-40-02, PG 2-4, REV 113.
DOUBLER ON C2 DOOR FRAME (FWD) IS CORRODED. DOUBLER ON C2 DOOR FRAME (FWD) REPLACED IAW SRM 51-40-02, REV 113, PAGE 2, PARA 4, 51-10-02, PAGE 8, PARA 8, AND 51-40-02, PAGES 2-3.
BRACKET SUPPORT INSIDE SHEAR BEAM WEB AT BS 727, STRINGERS18A CORRODED BEYOND LIMITS. REPLACED THE BRACKET SUPPORT IAW DWG REV - 69-72495. AND SRM 51-40-02 PG 2-4 REV 113
THE FUSELAGE SKIN, FOUND A 3 INCH CRACK, 2 INCHES AFT OF BS 727E DIRECTLY ABOVE STRINGER 23R. THE SKIN WAS REPAIRED IAW SRM 53-00-01, REPAIR 31.
SKIN HAD A 2 1/2 INCH CRACK 6 INCHES AFT OF BS 727E DIRECTLY ABOVE STRINGER 21R. FUSELAGE SKIN REPAIRED IAW SRM 53-00-01, REPAIR 31.
RIGHT OTBD T/E FOREFLAP OTBD MOUNT SHEARED. RIGHT HAND OUTBOARD TRAINING EDGE FOREFLAP REPLACED.
CRACKED FRAME AT BS 907, STR 9L. CRACKED FRAME AT STA 907, STR 9L REPAIRED IAW SRM REV 105, CHAPTER 53 -00-07, REPAIR 2. REFERENCE KFC MCO3044 W/O 1349844.
CRACKED STRINGER SPLICE, BS360 S5R. REPLACED CRACKED STRINGER SPLICE AT BS360, STR 5R WITH FABRICATED PART IAW DWG 65-45765 ID: 0004, REV C INSTALLED IAW 51-40-02, REV 105. REF KFC MCO3044, W/O 1349767.
CRACKED FRAME AT STA 887, STR 9L. CRACKED FRAME AT STA 887, STR 9L REPAIRED IAW SRM 53-00-07, REV 105, REPAIR 2. REF KFC MCO3044, W/O 1349849
DOUBLE DRILLED HOLE ON STIFFENER FOR FLOOR STRUCTURE WEB AT BS 706, LBL 25. FABRICATED STIFFENER AND INSTALLED ON FLOOR STRUCTURE WEB IAW DWG 65-45410, REV P 51-30-01 AND 51-40-02, REV 105, SRM.
DAMAGED STRINGER CLIPS IAW ATTACHED MAINTENANCE. REPLACED DAMAGED STRINGER CLIP AT STA 727B THRU STA 727E, STA 747, 767, 787, 867, 807, STR 9R. ALSO, STA 967, STR6L, STA 380 STR1, STA 380 STR 2L, STA 887 STR 5L. IAW SRM, REV 105 51-10-02, PARA 8 AND 51-40-02.
CORRODED INTERCOSTALS AT BS 344-360, STR4L THRU STR12L. FABRICATED NEW PARTS IAW DWG 65-17685, REV H. AND SRM 53-10-15, FIG 1, REV 105. INSTALLED IAW SRM 51-30-01 AND 51-40-02, REV 105.
CRACKED BELT FRAME AT STRINGER CLIP BS 767, S9R. REPAIRED CRACKED BELT FRAME AT STRINGER CLIP BS 767, STR9R IAW SB 53-1216, FIG 8, REV 1.
CRACKED STRINGER WITH SPLICE AT BS 348, STR 4L. REPAIRED CRACKED STR WITH SPLICE AT BS 348, STR 4L IAW 53-00-03, REPAIR 1, REV 105. SRM KFC MCO3044, W/O 1358378.
DOUBLE DRILLED HOLE IN STRINGER 4R AT BS520. SPLICED IN REPAIR AT STR 4R, BS 510-540 WITH FABRICATED REPAIR SPLICE IAW SRM 53-00-03, FIG 201, REPAIR 3, REV 105. MATERIAL ID IDENTIFIED IAW SRM 53-00-03, FIG 1, REV 105. REF KFC MCO3044, W/O 1354245.
AFT FRAME, BS 348, OF THE L1 ORIFICE GOUGED. ASSESSED AND FOUND TO BE BEYOND LIMITS. ORIGINAL THICKNESS 0.080", REMAINING THICKNESS 0.043". MIN ALLOWABLE THICKNESS 0.072". DURING INSPECTION FOUND THE AFT FRAME, BS348, OF THE L1 ORIFICE GOUGED. ASSESSED AND FOUND TO BE BEYOND LIMITS. ORIGINAL THICKNESS 0.080", REMAINING THICKNESS 0.043". MIN ALLOWABLE THICKNESS 0.072". REPLACED FRAME WITH NEW. SRM 53-00-07. REF DWG 65-17685, REV G. SRM 51-40-02, REV 105. REF MCO 3044, WO 1350549 FOR ASSESSMENT. REF KFC MCO 3044, WO 1352835 FOR REPLACEMENT.
FWD CARGO DOOR AFT FRAME IS CRACKED AT LOWER DOOR STOP, BS492. REPLACED FORWARD CARGO DOOR FRAME AT BS492 IAW BAC DWG 65-20723 ID: 0003 AND 51-40-02, REV 105, SRM. REF KFC MCO3044, W/O 1350950.
CORRODED LOWER CHORD ANGLE BELOW L1 DOOR BS 294-BS 351, STR 17L. REPLACED CORRODED LOWER CHORD ANGLE BELOW L1 DOOR BS 294-BS 351, STR 17L WITH FABRICATED NEW PART IAW BAC DWG 65-17688, REV B. INSTALLED IAW 51-40-02, REV 105, SRM. REF KFC MCO3044, W/O 1350387.
CRACKED WEB, SHEAR TIE, ON STOPPER SUPPORT AT STA 348.2, STR 16L. REPLACED WITH FABRICATED PART IAW DWG 65-17685, REV D, PARTS LIST REV CG.
INTERCOSTAL BETWEEN BS 3448.2 TO 360 STR14L FOUND WITH COROSSION. REPLACED CORRODED INTERCOSTAL AT BS 348.2 AND BS 360, STR 14L WITH FABRICATED REPAIR PART IAW BAC DWG 65-17685, REV E. INSTALLED IAW 51-40-02 REV 105, SRM. REF KFC MCO3044, W/O 1350370.
INTERCOSTAL FOUND CRACKED AT BS 616-639, STR 17R, RBL 60. FABRICATED AND INSTALLED REPLACEMENT PART REF SRM 53-60-13, FIG 1, SHEET 1&2. KFC MCO 3044, WO 1350360.
CRACKED INTERCOSTAL AT BS 328-344, LBL 40. REPLACED WITH MADE REPAIR PART FABRICATED AND INSTALLED IAW SRM 51-30-01 AND 51-40-02, REV 105. MATERIAL VERIFICATION IDENTIFICATION IAW SRM 53-10-51, FIGURE 1, DETAIL IV, REV 105.
DURING INSPECTION, DRILL DAMAGE IN RADIUS OF BELTFRAME WAS NOTED AT BS360 FRAME, S9R. IT WAS DETERMINED THAT NO AC BRACKET WAS INSTALLED HERE SO AD2006-26-09 DOES NOT IMPACT THIS FRAME. FRAME WAS REPAIRED IAW SRM 53-00-07, REPAIR 2. REF KFC MCO 3044, WO 1350311.
GOUGED FLOOR STRUCTURE WEB AT BS720. LBL25 AND BS710, LBL25. REPAIRED FLOOR STRUCTURE WEB AT BS720-710 LBL25 IAW AEI EO 1825 DTD 2 MAR 2015 & SB 737-57-1296, REV. PERFORMED REPAIR AS SHOWN IN FIG 19 OF SB WITH THE FOLLOWING EXCEPTIONS: A. DOUBLER "D" MADE FROM AL 7075-T6 CLAD/BARE, O.100" THICK. B. INSTALLED ALL REINFORCING ANGLES WITH SAME TYPE AND DIAMETER FASTENER.
DURING INSPECTION, FRAME AT BS 887, STRINGER 5L WAS FOUND GOUGED. REPAIRED IAW SRM R105, 53-00-07, REPAIR 2.
STRINGER 4L FOUND CRACKED UPON INSPECTION. FABRICATED AND INSTALLED REPLACEMENT SPLICE IAW DWG 65C35777 REV M, INSTALLED IAW SRM 51-40-02, REV 105. REF KFC MCO 3044, WO 1355079.
AFT FUSELGE SKIN CRACKED AT BS 727E, S24R TWO INCHES LONG VERIFIED WITH HFEC. CUTOUT DAMAGE, VERIFIED WITH HFEC, FABRICATED DOUBLER, & TRIPLER IAW SRM 53-00-01, FIG 201, REPAIR 31.
FUSELAGE SKIN CRACKED 4.5 INCHES AT BS 884, S25R. CUT OUT DAMAGE. INSTALLED REPAIR IAW SRM REV. 101, 53-00-01, REPAIR 31, FIG. 201, DETAIL XIX. CAT A.
LEFT WING OUTBOARD FOREFLAP HAS GOUGE AND BARE METAL EXPOSED. REMOVED EXISTING DAMAGED REPAIR DOUBLER IAW B737-300 SRM 51-40-02. FABRICATE, LOCATED, DEBURRED REPAIR DOUBLER IAW 51-30-01. INSTALLED REPAIR DOUBLER IAW B737-300 SRM 51-40-02.
SMALL DIAMETER PUNCTURE TO UPPER SHEAR WEB/FLOOR FORWARD OF STATIN 1016 JUST RIGHT OF BL-0. CUT OUT DAMAGE TO THE UPPER SHEAR WEB/FLOOR IAW B737-300 SRM 51-70-13. FABRICATED REPAIR PARTS IAW B737-300 SRM 51-70-13. LOCATED DRILLED AND DEBURRED REPAIR PARTS IAW B737-300 SRM 51-70-13. INSTALLED REPAIR PART TO UPPER SHEAR WEB/FLOOR IAW B737-300 SRM 51-70-13 AND 51-40-02.
AT STATION 1016 AFT PRESSURE BULKHEAD ON FORWARD SIDE THE MOP SEAL RETAINER IS CRACKED IN 3 LOCATIONS, COMMON TO THE BULKHEAD, TWO CHANNELS FROM LBL 10 TO RBL 10. FABRICATED NEW MOP SEAL RETAINER SECTION IAW B737 SRM 51-40-05. INSTALLED NEW SEAL RETAINER AT STATION 1016 FORWARD SIDE OF BULKHEAD IAW SRM 51-40-02.
AFT CARGO BAY FLOOR SUPPORT LOWER SURFACE HAS CORROSION UNDER THE NUT PLATES AT BS 767 - 773 FROM RBL 3 TO LBL 17. CUT OUT DAMAGED PROTION OF FLOOR SUPPORT IAW SRM 53-00-53. FABRICATED REPAIR ANGLES FOR FLOOR SUPPORTS IAW SRM 53-00-53. LOCATED AND DRILLED REPAIR ANGLES IAW SRM 53-00-53. INSTALLED REPAIR ANGLES IAW SRM 53-00-53 AND 51-40-02.
AT AFT CARGO BAY BELOW FLOORBEAM HAS CORROSION UNDER THE NUT PLATES AT BS 727D+6 FROM RBL 8 TO LBL 12. REMOVED DAMAGED AND CORRODED FLOOR SUPPORT ANGLES. FABRICATED REPAIR ANGLES IAW SRM 53-00-53. LOCATED DRILLED AND DEBURRED REPAIR ANGLES IAW SRM 53-00-53. INSTALLED REPAIR ANGLES IAW SRM 51-40-02.
DICOVERED DAMAGE TO THE FUSELAGE SKIN BETWEEN STATION 8610 AND 887. DAMAGE TO THE SKIN WAS ACCOMPLISHED IAW BOEING 737-300 SRM 53-60-01 REPAIR NUMBER 9 AS STATED PER SB 737-53A 1266. MODIFICATION TO THE DORSAL FIN CAP WAS ALSO ACCOMPLISHED IAW SB 737-53A- 1266 PART 4
RIGHT WING LEADING EDGE CAVITY INBOARD OF NR 2 ENGINE HAS A CRACKED ANGLE OUTBOARD OF WING STATION 196. REMOVED CRACKED ANGLE FROM LEADING EDGE CAVITY OUTBOARD OF WING STATION 196 IAW SRM 51-40-02. FABRICATED NEW ANGLE, LOCATED AND DRILLED IAW SRM 51-30-01 AND 51-20-01. INSTALLED ANGLE IAW SRM 51-40-02.
MASTER CAUTION LIGHT, FLIGHT CONTROL CAP LIGHT, AND SPEED TRIM FAIL LIGHT ON TAKEOFF. TAKEOFF WAS REJECTED AT 100KTS. REMOVED AND REPLACED N1 RPM INDICATOR, OP CHECKED GOOD. REF: B737-300MM 77-12-00 PG 501.
DURING TAKEOFF ABORTED DUE TO MASTER CAUTION, FUEL ANNUNCIATOR LIGHT, SUSPECT FUEL FILTER BYPASS. REMOVED & REPLACED NR 1 ENGINE FUEL FILTER, NO CONTAMINANTS (MINOR FUZZ). REF: B737-300MM 73-11-401. OP & LEAK CHECKED GOOD.
CRACK FOUND IN FWD CARGO BAY STRINGERS 19 TO 21, FRAME 500D AT WIDE PENETRATION HOLE AT RIGHT. REPAIRED FRAME 500D RIGHT IAW SB737-53A1279R1 PER SRM 53-00-07 REPAIR 13.
CRACK FOUND IN FWD CARGO BAY BETWEEN STRINGERS 19 TO 21, FRAME 500D AT WIRE PENETRATION HOLE AT LEFT SIDE. REPAIRED FRAME 500D LEFT IAW SB737-53A1279R1 PER SRM 53-00-07 REPAIR 13. SEE ASCENT MWO 319-08-218 FOR REPAIR DETAILS.
CRACK FOUND IN FWD CARGO BAY STRINGER 19 TO 21, FRAME 500B AT WIRE PENETRATION HOLE, RIGHT. REPAIRED FRAME 500B RIGHT SIDE IAW SB 737-53A1279R1 PER SRM 53-00-07 REPAIR 13 AND AERONAUTICAL ENGINEERING EO 1563 DATED 3 DEC 2011.
CRACK FOUND IN FWD CARGO BAY STRINGER 19 TO 21, FRAME 500C AT WIRE PENETRATION HOLE, RIGHT. REPAIRED FRAME 500C RIGHT IAW SB737-53A1279R1 PER SRM 53-00-07 REPAIR 13 AND AERONAUTICAL ENGINEERING EO 1563 DATED 3 DEC 2011.
FRAME DAMAGE AT 927 BETWEEN 16R & 17R STRINGERS. INSTALLED TEMPORARY REPAIR PER ASI SOLUTION DRAWING 53101081-1 REVA TO FACILITATE FERRY FLIGHT TO APPROVED REPAIR STATION PER FAA FORM 8110-3 NR 092-1406-11-1081. UPON ARRIVAL AT REPAIR STATION REPLACED RT FRAME AT STA 927. AWAITING FINAL DOCUMENTATION OF REPAIR.
L1 DOOR EMERGENCY LIGHT OUT. REPLACED BATTERY PACK, REF B737-300 AMM 33-51-02. OP CHECK GOOD.