N301KH
Registered owner: AEKO KULA LLC DBA, HI (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| ALOHA AIRLINES INC | Operator | 2014-10-16 – 2014-10-16 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
CA1579/202 REF ECO 3845 PART X PAGE 37 OF 98 REPAIR 2: TWO FANTENERS HOLE CRACK WERE FOUND AT BL 45.5 LONGITUDINAL FLOOR BEAM WEB AT BS 639 STUB RH BEAM. CORRECTIVE ACTION:WEB WITH HOLE CRACKS FOUND AT BL 45.5 LONGITUDINAL FLOOR BEAMWEB AT BS 639 REPLACED PER ECO 3845 PART X PAGE 37 AND B737-300 SRM 53-60-61 REPAIR 7 (R134) AND ATTACHED S.W.S.
SURFACE CORROSION ON LH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S9C AND S10C LBL40.875+13". CORROSION REMOVED AND CONDITION CHECK OK WITHIN LIMIT ON LH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S9C AND SPC LBL 40.875+13" PER AIRASIA WPS CODE:EI-737-241001. CENTER WING TANK LEAK CHECK NO LEAKING.
CORROSION AT ATTACH FITTING AT AFT PRESSURE BULKHEAD AFT SIDE AT STA 1016, S-21L. REPLACED FITTING AT AFT PRESSURE BULKHEAD AFT SIDE STA1016, S-21L REMOVED AND REINSTALLED S-21L/ I.A.W. B737-300 SRM 51-40-02 PARA 4 (R134) & DWG 65-46568 & 65-46881
EROSION (1.0" X 1.0") AT HF ANTENNA COVER OF VERTICAL STABILIZER LEADING EDGE AT LE STA 90. PERFORMED THE EROSION AREA AT HF ANTENNA COVER OF VERTICAL STABILIZER LEADING EDGE AT LE STA 90. APPLIED THE REPAIR PLIES WITH RESIN AND CURED. MADE THE REPAIR SURFACE SMOOTH. I.A.W. B737-300 SRM 55-30-01 REPAIR 11 (R134)
CORROSION AT RH SIDE FUSELAGE EXTERNAL SKIN AT STA 1028~1042, S-9R. CORROSION REMOVED LEVEL 1 AT STA 1028-1042, S-9R FROM PN 65-46882-1 ORIGINAL THICKNESS 0.0064" REMOVED 0.002" AND REMAINING THICKNESS IS 0.062 AND IS WITHIN LIMITS PER SRM 53-00-01 ALLOWABLE DAMAGE 1 R134, AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-20-01 P3-7 51-10-02 P12-15 REV 134. PME: 006646 DUE DATE: 07.28.2025. NO CORROSION REMAINING.
CA1579/20 SURFACE CORROSION ON RH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S11C AND S12C ,AT RBL 40.875+5.7" AND RBL 45.72+9.5" CORRECTIVE ACTION:1.THE R/H CENTER TANK LOWER SKIN BETWEEN S-11C AND S-12C ,AT RBL 40.875+5.7" AND RBL 45.72+9.5" CORROSION REMOVED & NDT CHECK 2. FLAP PEEN REMVED AREA & PRIMER APPLY REFER TO NRC:CA1579/108 ATTACH WPS CODE EI-737-241102 FOR DETAIL
CORROSION (2.0" X 0.5") AT RH SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD AT STA 116. CORROSION REMOVED LEVEL 1 AT HOR1 STAB REAR SPAR UPPER CHORD STAB STA116 FROM PN 65-50581-526 ORIGINAL THICKNESS 2.320" REMOVED 0.050" AND REMAINING THICKNESS IS 2.270" AND IS WITHIN LIMITS PER SRM DAMAGE 1 55-10-10 ALLOWABLE R134, AREA CLEAN & PROTECTIVE I.A.W B737-300 SRM 51-10-02 P12-15, 51-20-01 P3-7 (REV 134)
SURFACE CORROSION ON FUSELAGE EXTERIOR SKIN AT BS947+6" S25L+3". SURFACE CORROSION ON FUSELAGE EXTERIOR SKIN AT BS947+6" S25L+3" WAS REMOVED LEVEL 1, P/N 65-45776-11 ORIGINAL THICKNESS WAS 0.063" AND AFTER REMOVING 0.003" REMAINED 0.06" AND IS WITHIN LIMIT PER I.A.W B737-300 SRM 53-60-01 IDENTIFICATION P1-8(R134) & 53-00-01 ALLOWABLE DAMAGE1 P101-108(R134) AR
SEAT TRACK CORRODED ABOUT 1.0 INCH, STA: BS887 BL0. CORROSION REMOVED LEVEL 2 THE BLEND OUT DEPTH IS 0.059" AND IS OVER LIMITS PER SRM 53-00-52 ALLOWABLE DAMAGE 1, PERFORMED REPAIR AS PER AIR ASIA WPS CODE: EI-B737-241101
CORROSION (19.0" X 1.0") RH SIDE CONDUCTIVE FRAME TRAILING EDGE AT RUD STA 233~252. CORROSION REMOVED LEVEL 1 AT RH SIDE CONDUCTIVE FRAME TRAILING EDGE AT RUD STA 233~252 FROM PN 65C31496-4 AFTER REMOVED SKIN THROUGH REPLACED CONDUCTIVE FRAME I.A.W B737-300 SRM 51-400 ALLOWABLE DAMAGE 1 (R134) & DWG 65
CORROSION (3.0" X 0.8") AT RH SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD AT STA 143. CORROSION REMOVED LEVEL 1 AT HOR1 STAB REAR SPAR UPPER CHORD STAB STA116 FROM PN 65-50581-526 ORIGINAL THICKNESS 1.790" REMOVED 0.095" AND REMAINING THICKNESS IS 1.695" AND IS WITHIN LIMITS PER SRM DAMAGE 1 55-10-10 ALLOWABLE R134, AREA CLEAN & PROTECTIVE I.A.W B737-300 SRM 51-10-02 P12-15, 51-20-01 P3-7 (REV 134)
SURFACE CORROSION ON RH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S5C RBL40.875+13"&2.5" AND 4.5". THE R/H CENTER TANK LOWER SKIN BETWEEN S-5C -RBL40.875+13"&2.5" AND 4.5" CORROSION REMOVED & NDT CHECK 2. FLAP PEEN REMVED AREA & PRIMER APPLY REFER TO ATTACH WPS CODE EI-737-241102 FOR DETAIL
SURFACE CORROSION ON LH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S5C AND S6C AT LBL40.875+5.5" & S5C AT LBL 40.875+1.0";LBL40.875+3.5",LBL40.875+5.5" & BETWEEN STRINGERS S4C AND S5C AT LBL40.875+2.0". CORROSION REMOVED AND CONDITION CHECK OK WITHIN LIMIT ON LH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S5C AND S6C AT LBL 40.875+5.5" & S5C AND LBL 40.875+10"; LBL 40.875+3.5", LBL 40.875+5.5" & BETWEEN STRINGERS S4C AND S5C AT LBL 40.875+2.0" PER REF CA1579/28 WPS CODE:EI-737-241001. LH SIDE CENTER WING TANK LEAK CHECK NO LEAKING.
CORROSION FOUND AT RH WING NO.4 SLAT SLAT STA.13 , BETWEEN OUTER SKIN AND TEE CHORD. CUT & REMOVED THE DAMAGED AREA FROM RH WING NO.4 SLAT STA13 2.MADE REPAIR DOUBLER & FILL TO INSTALL WITH SEALANT I.A.W B737-300 SRM 57-43-01 REPAIR 6 FIG201(REV134) REF BOEING DWG 65C26603 SHEET 6 FOR MATERIAL ID & PART INFO
SURFACE CORROSION ON FUSELAGE EXTERIOR SKIN AT BS907 S23R. CORROSION REMOVE LEVEL 1 AT BS907 S23R, FROM PN 65C35778-21, ORIGINAL THICRNESS 0.071" REMOVED 0.007" AND REMAINING THICRNESS IS 0.064" AND IS WITHIN LIMITS PER IAW B737-300 SRM 52-30-01 IDENTIFICATION P1-P9(R134) 52-30-01 ALLOWABLE DAMAGE 1 P101-108(R134), AREA CLEAN & PROTECTIVE I.A.W. B737-300 SRM 51-20-01 P3-7, 51-10-02 P12-15(R134) PME:004692 DUE DATE:NOV.05.2024
SURFACE CORROSION ON FUSELAGE EXTERIOR SKIN AT BS907 S17R+4". CORROSION REMOVE LEVEL 1 AT BS907 S17R+4", FROM PN 65C35768-21, ORIGINAL THICRNESS 0.071" REMOVED 0.007" AND REMAINING THICRNESS IS 0.064" AND IS WITHIN LIMITS PER IAW B737-300 SRM 52-30-01 IDENTIFICATION P1-P9(R134) 52-30-01 ALLOWABLE DAMAGE 1 P101-108(R134), AREA CLEAN & PROTECTIVE I.A.W. B737-300 SRM 51-20-01 P3-7, 51-10-02 P12-15(R134) PME:004692 DUE DATE:NOV.05.2024
LH WING NO.2 SLAT OUTER SKIN BULGE AROUND FASTENER HOLE BETWEEN SLAT STA 183 AND SLAT STA 196. LH WING NO.2 SLAT OUTER SKIN REPAIRED BETWEEN SLAT STA 183 AND SLAT STA 196 I.A.W SRM 57-43-01 REPAIR 6 (R134)
LH WING NO.1 SLAT OUTER SKIN CRACKED AROUND FASTENER HOLE BETWEEN SLAT STA 294.03 AND SLAT STA 302.03. LH WING NO.1 SLAT OUTER SKIN REPAIRED BETWEEN SLAT STA 294.03 AND SLAT STA 302.03 I.A.W SRM 57-43-01 REPAIR 6 (R134)
FUSELAGE FRAME CLIP CRACK, STA 360, S-11L. CLIP REPLACED AT FUSELAGE FRAME STA360, S-11L PER:B737-300 DRAWING:65-58280 SHEET2, SRM 51-40-02 PARA.4&7 (REV.134)
MAIN GEAR WHEEL WELL PRESSURE BLUCKHEAD CRACKS ABOUT 1", STA 663.75 LBL24.75+6". PERFORMED REPAIR AT STA663.75, LBL24.75+6" AS PER B737-300 SRM 53-60-51 REPAIR 4 (R134)
CORROSION (2.0" X 0.4") AT LH SIDE HORI.STAB. REAR SPAR UPPER CHORD. CORROSION REMOVED LEVEL 1 AT HOR1 STAB REAR SPAR UPPER CHORD STAB STA116 FROM PN 65-50581-525 ORIGINAL THICKNESS 1.790" REMOVED 0.036" AND REMAINING THICKNESS IS 1.754" AND IS WITHIN LIMITS PER SRM DAMAGE 1 55-10-10 ALLOWABLE R134, AREA CLEAN & PROTECTIVE I.A.W B737-300 SRM 51-10-02 P12-15, 51-20-01 P3-7 (REV 134)
SURFACE CORROSION ON LH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S6C LBL40.875+4". CORROSION REMOVED AND CONDITION CHECK OK WITHIN LIMIT ON LH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S6C AND LBL 40.874+4" PER REF CA1579/28 WPS CODE:EI-737-241001. LH SIDE CENTER WING TANK LEAK CHECK NO LEAKING.
SURFACE CORROSION ON RH SIDE CENTER WING TANK LOWER SKIN BETWEEN STRINGERS S9C & RBL 40.875+13"-15". THE R/H CENTER TANK LOWER SKIN BETWEEN S-9C & RBL 40.875+13"-15" CORROSION REMOVED & NDT CHECK NORMAL 2. FLAP PEEN REMVED AREA & PRIMER APPLY REFER TO NRC:CA1579/108 ATTACH WPS CODE EI-737-241102 FOR DETAIL.
CORROSION AT LH SIDE FUSELAGE EXTERNAL SKIN AT STA 1088, S-5L~S-6L. CORROSION REMOVED LEVEL 1 AT 1088, S-5L~S-6L FROM PN 65-46882-1 ORIGINAL THICKNESS 0.064" REMOVED 0.002" AND REMAINING THICKNESS IS 0.062 AND IS WITHIN LIMITS PER SRM 53-00-01 ALLOWABLE DAMAGE 1 R134, AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-20-01 P3-7 51-10-02 P12-15 REV 134. PME: 006646 DUE DATE: 07.28.2025
CORROSION AT LH SIDE FUSELAGE EXTERNAL SKIN AT STA 1088, S-2L~S-4L. CORROSION REMOVED LEVEL 1 AT STA 1088, S-2L~S-4L FROM PN 65-46882-1 ORIGINAL THICKNESS 0.071" REMOVED 0.001" AND REMAINING THICKNESS IS 0.070 AND IS WITHIN LIMITS PER SRM 53-00-01 ALLOWABLE DAMAGE 1 R134, AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-20-01 P3-7 51-10-02 P12-15 REV 134. PME: 006646 DUE DATE: 07.28.2025
DURING ECO 3925, DISCOVERED 2 RIVETS MISSING AT BS 360R JUST ABOVE FLOOR BOARD.
DURING ECO 3925, DISCOVERED DENT AT BS 440R APPROX 5" FROM FLOOR, 1 1/4" WIDE, AND 0.07" DEEP.
CA 1464/192 CORROSION AT R/H SIDE HORIZONTAL STABILIZER REAR SAPR UPPER SURFACE AT STAB STA 116 (0.5" X 0.2" IN AREA). ALL CORROSION REMOVED AT RH HORIZONTAL STABILIZER REAR SPAR UPPER SURFACE AT STAB STA 116 (0.5" X 0.2" IN AREA). REMOVED 0.015" AND REMAINING 1.130" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 55-10-10 ALLOWABLE DAMAGE 1 FIG 101 (R130).
CA 1464/95 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 540 AND STA 559, 2 AREA (L:0.7",W:0.5")(L:0.6",W:0.2"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 540 AND STA 559 (L:0.7", W:0.5") (L:0.6", W:0.2"). REMOVED 0.006", 0.005" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/296 THE CORROSION WAS FOUND AT LH WING I/B FLAP LOWER PNL 8404, AROUND FASTENER (9EA). ALL CORROSION REMOVED AT LH WING I/B FLAP LOWER PANEL 8404 AROUND FASTENER. REMOVED 0.005" MATERIAL & REMAINING 0.120" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-53-01 ALLOWABLE DAMAGE 1.
CA 1464/297 THE CORROSION WAS FOUND AT LH WING I/B FLAP LOWER PNL 8406, AROUND FASTENER (10EA). ALL CORROSION REMOVED AT LH WING I/B FLAP LOWER PANEL 8406 AROUND FASTENER. REMOVED 0.004" MATERIAL & REMAINING 0.121" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-53-01 ALLOWABLE DAMAGE 1.
CA 1464/298 THE CORROSION WAS FOUND AT LH WING I/B FLAP LOWER PNL 8407, AROUND FASTENER (6EA). ALL CORROSION REMOVED AT LH WING I/B FLAP LOWER PANEL 8407 AROUND FASTENER. REMOVED 0.004" MATERIAL & REMAINING 0.121" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-53-01 ALLOWABLE DAMAGE 1.
CA 1464/302 LIGHT CORROSION AT LH SIDE EXTERNAL SKIN AT STA 1073 S-20L. ALL CORROSION REMOVED AT LH SIDE EXTERNAL SKIN AT STA 1073 S-20L. REMOVED 0.004" MATERIAL & REMAINING 0.049" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN & PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 53-00-01 ALLOWABLE DAMAGE 1.
CA 1464/22 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN AFT CARGO CUTOUT FWD EDGE AS MARK. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AFT CARGO CUTOUT FWD EDGE. REMOVED 0.001" MATERIAL AND REMAINING 0.035" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-20-01, 51-10-2 AND 53-00-01.
CA 1464/31 FILIFORM CORROSION WERE FOUND ON THE AFT CARGO DOOR EXTERNAL SKIN EDGE AND HANDLE CUTOUT COVER AS MARK. ALL CORROSION REMOVED AT AFT CARGO DOOR EXTERNAL SKIN EDGE AND HANDLE CUTOUT COVER. REMOVED 0.001" MATERIAL AND REMAINING 0.035" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-20-01, 51-10-2 AND 52-30-01 ALLOWABLE DAMAGE.
CA 1464/37 MAIN DECK CARGO DOOR SEAL RETAINER CRACK ON FWD LOW CORNER. DAMAGE SEAL RETAINER REMOVED AT FWD LOWER CORNER MAIN DECK CARGO DOOR. INSTALL NEW PARTS IAW B737-300 SRM 51-40-2 PARA 4 P2 (R130).
CA 1464/49 CORROSION AT FUSELAGE SKIN STA 947.5, BETWEEN S-13L AND S-16L, 2 AREA (L:11", W:0.7")(L:5", W:1"). REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE.
CA 1464/50 CORROSION AT FUSELAGE SKIN STA 907, BETWEEN S-15L AND S-16L (L:10", W:0.5"). ALL CORROSION REMOVED AT FUSELAGE SKIN STA 907, BETWEEN S-15L & S-16L (L:10", W:0.5"). REMOVED 0.004" MATERIAL AND REMAINING 0.061" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE.
CA 1464/52 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 727E AND STA 747 (L:0.7", W:0.5"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE BETWEEN STA 727E AND STA 747 (L:0.7", W:0.5"). REMOVED 0.0078" MATERIAL IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1.
CA 1464/53 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 747 AND STA 767 (L:4.6", W:0.5"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE BETWEEN STA 747 & STA 767 (L:4.6", W:0.5"). REMOVED 0.006" MATERIAL IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1.
CA 1464/54 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 767 AND STA 787, 2 AREA (L:0.9",W:0.3")(L:1.2", W:0.3"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 767 & STA 787, 2 AREA (L:0.9",W:0.3")(L:1.2", W:0.3"). REMOVED 0.003" MATERIAL IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1.
CA 1464/12 LIGHT CORROSION ON R/H OVERWING EMERGENCY EXIT HATCH AT LOW PORTION. ALL CORROSION REMOVED AT R/H OVERWING EMERGENCY EXIT HATCH AT LOW PORTION. REMOVED 0.002" MATERIAL AND REMAINING 0.061" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 52-20-02 ALLOWABLE DAMAGE 1 (R130).
CA 1464/14 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN LH SIDE STRINGER 20 STATION 727D TO 727D+3, 747 TO 787, 825 TO 827, 868 TO 897 AND 986 TO 990. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT S-20L STA 727D TO STA 727+3, STA 747 TO STA 787, STA 825 TO 827, STA 868 TO 897, STA 986 TO 990. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AN 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/16 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN LH SIDE STRINGER 25 STATION 827 TO 847, 881 TO 901. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT S-25L STA 827 TO STA 847, STA 881 TO STA 901. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/96 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 559 AND STA 578 (L:0.4",W:0.4"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 559 AND STA 578 (L:0.4", W:0.4"). REMOVED 0.009" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/94 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 520 AND STA 540, 3 AREA (L:2",W:0.5")(L:0.5",W:0.5)(L:0.5",W:0.5"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 520 AND STA E540 (L:2",W:0.5") (L:0.5",W:0.5") (L:0.5",W:0.5"). REMOVED 0.005", 0.007", 0.007" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/93 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 500B AND STA 500C (L:0.6",W:0.5"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 500B AND STA 500C. REMOVED 0.006" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/115 LIGHT CORROSION AT ACCESS AND BLOWOUT DOOR CUTOUT AREA AT STA 1064, S-23L. ALL CORROSION REMOVED AT ACCESS AND BLOWOUT DOOR CUTOUT AREA AT STA 1064,S-23L. REMOVED 0.002" MATERIAL AND REMAINING 0.054" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/116 LIGHT CORROSION AT ACCESS AND BLOWOUT DOOR CUTOUT AREA AT STA 1058, S-20L. ALL CORROSION REMOVED AT ACCESS AND BLOWOUT DOOR CUTOUT AREA AT STA 1058, S-20L. REMOVED 0.002" MATERIAL AND REMAINING 0.054" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/117 LIGHT CORROSION AT RIVET AREA OF STRINGER AT STA 1040~1060, S-24L. ALL CORROSION REMOVED AT RIVET AREA OF STRINGER AT STA 1040~1060 S-24L. REMOVED 0.005" AND REMAINING 0.040" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-03 ALLOWABLE DAMAGE 1 (R130).
CA 1464/118 CORROSION AT RH SIDE FUSELAGE AT STA 1156, S-20R. CORROSION ON FUSELAGE SECTION 48 STRAP 65-45688-172 AT STA 1156, REPAIR IAW AIR ASIA EL-737-230507. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01859-001 R01)
CA 1464/119 CORROSION AT RH SIDE FUSELAGE AT STA 1115-1128, S-20R. ALL CORROSION REMOVED AT RH FUSELAGE AT STA 1115-1128, S-20R. REMOVED 0.004" MATERIAL AND REMAINING 0.067" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/121 CORROSION AT REPAIRED DOUBLER SKIN AT STA 1076, S-17AR. ALL CORROSION REMOVED AT REPAIRED DOUBLER SKIN AT STA 1076.5, S-17AR. REMOVED 0.003" MATERIAL AND REMAINING 0.053" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW 8737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/140 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 887 AND STA 907, (L:0.7",W:0.3"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 887 AND STA 907 (L: 0.7", W:0.3"). REMOVED 0.003" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/160 LH WING I/B FORE FLAP LOWER SKIN DELAMINATION BETWEEN WBL REPAIR IAW AIR ASIA EL-737-230504. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01844-001)
CA 1464/161 CORROSION AT LH WING I/B EXHAUST GATE LOWER SKIN WBL 169. ALL CORROSION REMOVED AT LH WING I/B EXHAUST GATE LOWER SKIN BETWEEN WBL 169. REMOVED MATERIAL 0.002" AND REMAINING 0.078" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-01-1A-1 ALLOWABLE DAMAGE 1 DETAIL VL (R130).
CA 1464/162 CORROSION AT LH WING I/B EXHAUST GATE LOWER SKIN WBL 183. ALL CORROSION REMOVED AT LH WING I/B EXHAUST GATE LOWER SKIN BETWEEN WBL 183. REMOVED MATERIAL 0.002" AND REMAINING 0.078" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-01-1A-1 ALLOWABLE DAMAGE 1 DETAIL VL (R130).
CA 1464/163 CORROSION AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 86.25 AND WBL 87.25. ALL CORROSION REMOVED AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 86.25 AND 87.25. REMOVED MATERIAL 0.001" AND REMAINING 0.015" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/193 CORROSION AT R/H SIDE HORIZONTAL STABILIZER REAR SPAR UPPER SURFACE AT STAB STA 143 (1.0" X 0.4" IN AREA). ALL CORROSION REMOVED AT RH HORIZONTAL STABILIZER REAR SPAR UPPER SURFACE AT STAB STA 143 (1.0" X 0.4" IN AREA). REMOVED 0.020" AND REMAINING 0.730" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 55-10-10 ALLOWABLE DAMAGE 1 FIG 101 (R130).
CA 1464/196 SURFACE CORROSION ON CENTER WING LOWER EXTERIOR SKIN BS600 LBL 50. CORROSION ON CENTER WING LOWER EXTERIOR SKIN BS600, BS640 AND BS645. REPAIRED IAW AIR ASIA EL-737-230502. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01839-001)
CA 1464/197 SURFACE CORROSION ON CENTER WING EXTERIOR LOWER SKIN BS640 LBL44. CORROSION ON CENTER WING LOWER EXTERIOR SKIN BS600, BS640 AND BS645, REPAIRED IAW AIR ASIA EL-737-230502. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01839-002)
CA 1464/198 SURFACE CORROSION ON CENTER WING EXTERIOR LOWER SKIN BS645 LBL 47. CORROSION ON CENTER WING LOWER EXTERIOR SKIN BS600, BS640 AND BS645, REPAIRED IAW AIR ASIA EL-737-230502. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01839-003)
CA1464/199 SURFACE CORROSION ON CENTER WING EXTERIOR LOWER SKIN BS570 FORM RBL 44 TO RBL 50. CORROSION ON CENTER WING LOWER EXTERIOR SKIN BS570 FORM RBL 44 TO RBL 50, REPAIRED IAW AIR ASIA EL-737-230501. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01840-001)
CA 1464/288 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN W STA 627.5 AND W STA 629.7. CORROSION AT LH WING LOWER SURFACE, BETWEEN W STA 627.5 AND W STA 629.7, REPAIR IAW AIR ASIA EL-737-230503. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01849-001R01)
CA 1464/229 CORROSION AT RH REAR FUSELAGE SKIN AT STA 1088, S-3R~S-5R. ALL CORROSION REMOVED AT RH REAR FUSELAGE SKIN AT STA 1088, S-3R ~ S-5R. REMOVED 0.003" MATERIAL & REMAINING 0.060" WITHIN ALLOWABLE LIMIT. AREA CLEAN & PROTECTIVE I.AW. B737-300 SRM 51-20-4 & 51-10-2 & 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/230 CORROSION AT RH REAR FUSELAGE SKIN AT STA 1016, S-4R~S-9R. ALL CORROSION REMOVED AT RH REAR FUSELAGE SKIN AT STA 1016, S-4R ~ S-9R. REMOVED 0.003" MATERIAL & REMAINING 0.059" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN & PROTECTIVE I.A.W. B737-300 SRM 51-20-1 & 51-10-2 & 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/231 LIGHT CORROSION AT RH SIDE VERTICAL STABILIZER EXTERNAL SKIN AT REAR SPAR AREA AT FIN STA 79~93. ALL CORROSION REMOVED AT RH SIDE VERTICAL STABILIZER EXTERNAL SKIN AT REAR SPAR AREA AT FIN STA 79 ~ 93. REMOVED 0.002" MATERIAL & REMAINING 0.097" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN & PROTECTIVE I.A.W. B737-300 SRM 51-20-1 & 51-10-2 & 55-30-01 ALLOWABLE DAMAGE 1 (R130),
CA 1464/232 LIGHT CORROSION AT LH SIDE VERTICAL STABILIZER EXTERNAL SKIN AT REAR SPAR AREA AT FIN STA 247. ALL CORROSION REMOVED AT LH SIDE VERTICAL STABILIZER EXTERNAL SKIN AT REAR SPAR AREA AT FIN STA 247. REMOVED 0.002" MATERIAL & REMAINING 0.097" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN & PROTECTIVE I.A.W. B737-300 SRM 51-20-1 & 51-10-2 & 55-30-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/97 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 597 AND STA 616 (L:0.4",W:0.4"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 597 AND STA 616 (L:0.4", W:0.4"). REMOVED 0.009" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/233 LIGHT CORROSION AT RUDDER LEADING EDGE RIB AT RUDDER STA 90 NEARBY RUDDER HINGE 4. ALL CORROSION REMOVED AT RUDDER LEADING EDGE RIB AT RUDDER STA 90 NEARBY RUDDER HINGE 4. REMOVED 0.002" MATERIAL & REMAINING 0.038" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-20-1 & 51-10-2 & 55-40-02 ALLOWABLE DAMAGE 1.
CA 1464/241 THE DENTS WERE FOUND AT LH WING O/B AFT FLAP LOWER SKIN, BETWEEN WBL 276.55 AND WBL 281.05. (WBL 277.55, L:0.9", W:0.8", D:0.018"),(WBL 279.05, L:0.7", W:0.6", D:0.005"),(WBL 280.5, L:1.1", W:0.9", D:0.014"),(WBL 280.8, L:0.7", W:0.4" , D:0.003"). REMOVED THE DAMAGE AREA AT LH WING O/B AFT FLAP LOWER SKIN BETWEEN WBL 276.55 AND WBL 281.05. MADE THE REPAIR SKIN AND DOUBLER. INSTALLED THE REPAIR PARTS AND PERFORMED 250°F CURE METAL BOND. CLEANED AND SEALED I.A.W. B737-300 SRM 57-53-02 REPAIR 2 AND SRM 51-70-10 REPAIR 4 (R130).
CA 1464/242 THE DENT WAS FOUND AT LH WING O/B AFT FLAP LOWER SKIN, WBL 287.05, L:2.8 INCH, W:2.7 INCH, D:0.070 INCH. REMOVED THE DAMAGE AREA AT LH WING O/B AFT FLAP LOWER SKIN WBL 287.05. MADE THE REPAIR SKIN AND DOUBLER. INSTALLED THE REPAIR PARTS AND PERFORMED 250°F CURE METAL BOND. CLEANED AND SEALED I.A.W. B737-300 SRM 57-53-02 REPAIR 2 AND SRM 51-70-10 REPAIR 4 (R130).
CA 1464/243 THE DENT WAS FOUND AT LH WING O/B AFT FLAP LOWER SKIN, WBL 335.4, L:1.2 INCH, W:0.9 INCH, D:0.007 INCH. DENT AT LH WING O/B AFT FLAP LOWER SKIN WBL 335.4, L:1.2", W:0.9", D:0.007" CHECK WITHIN ALLOWABLE LIMIT. I.A.W. B737-300 SRM 57-53-01 ALLOWABLE DAMAGE 2 (REV:130).
CA 1464/244 THE DENTS WERE FOUND AT LH WING O/B AFT FLAP LOWER SKIN, BETWEEN WBL 342.64 AND WBL 344.9 (WBL 342.9, L:0.8", W:0.6", D:0.008"),(WBL 343.9, L:0.8", W:0.4", D:0.002"). REMOVED SURFACE FINISH OF DENTS AND DID SURFACE PREPARATION AT LH WING O/B AFT FLAP LOWER SKIN BETWEEN WBL 342.64 AND WBL 344.9. MADE THE REPAIR DOUBLER AND FILLED THE DENTS WITH FILM ADHESIVE. PERFORMED 250°F METAL BOND REPAIR I.A.W. B737-300 SRM 57-53-02 REPAIR 2 AND SRM 51-70-10 REPAIR 2 (R130).
CA 1464/255 SKIN GOUGE AT RH WING I/B FORE FLAP LOWER SURFACE WBL 99. REMOVED SURFACE FINISH OF GOUGE AREA AT RH WING I/B FORE FLAP LOWER SURFACE WBL 99. FILLED THE DAMAGE WITH FILM ADHESIVE. MADE REPAIR DOUBLER. INSTALLED REPAIR PARTS AND CURED THE BOND. CLEANED AND SEAL I.A.W. B737-300 SRM 57-53-02 REPAIR 2 & SRM 51-70-10 REPAIR 2 (R130).
CA 1464/256 CORROSION AT RH WING I/B MID FLAP UPPER SKIN BETWEEN WBL 83, WBL 111 AND WBL 138. ALL CORROSION REMOVED AT RH WING I/B FLAP UPPER SKIN BETWEEN WBL83, WBL111 AND WBL138. REMOVED 0.001" MATERIAL & REMAIN 0.019" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-53-01 ALLOWABLE DAMAGE 1.
CA 1464/264 DRILL OFF HI-LOCK FASTENER ON FWD ENTRY DOOR LOWER HINGE EXTERNAL DOUBLER, STA 303.9 S-13L AND S-14L. FASTENER REMOVED AT FWD ENTRY DOOR LOWER HINGE EXTERNAL DOUBLER STA 303.9, S-13L & S14L. REINSTALL FASTENER I.A.W. B737-300 SRM 51-40-2 PARA 7, PAGE 4 ~ PAGE 6.
CA 1464/269 THE CORROSION WAS FOUND AT #1 SPOILER LOWER SURFACE, RSS 412. ALL CORROSION REMOVED AT #1 SPOILER LOWER SURFACE, RSS412. REMOVED 0.001" MATERIAL & REMAIN 0.019" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-70-01 ALLOWABLE DAMAGE 2.
CA 1464/284 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN WBL 559 AND WBL 560.9. ALL CORROSION REMOVED AT LH WING LOWER SURFACE BETWEEN WBL 559 AND WBL 560.9. REMOVED 0.002" MATERIAL & REMAIN 0.048" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-30-01 ALLOWABLE DAMAGE 1.
CA 1464/287 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN W STA 614.0 AND W STA 617.7. CORROSION AT LH WING LOWER SURFACE, BETWEEN W STA 614.0 AND W STA 617.7, REPAIR IAW AIR ASIA EL-737-230503. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01849-001R01)
CA 1464/164 CORROSION AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 87.25 AND WBL 91.25. ALL CORROSION REMOVED AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 87.25 AND 91.25. REMOVED MATERIAL 0.001" AND REMAINING 0.015" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/165 CORROSION AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 92.75 AND WBL 94.05. ALL CORROSION REMOVED AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 92.75 AND 94.05. REMOVED MATERIAL 0.003" AND REMAINING 0.013" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-51 ALLOWABLE DAMAGE 1 (R130).
CA 1464/167 CORROSION AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 116.0 AND WBL 118.0. ALL CORROSION REMOVED AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 116.0 AND WBL 118.0. REMOVED MATERIAL 0.003" AND REMAINING 0.013" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-51 ALLOWABLE DAMAGE 1 (R130).
CA1464/172 CORROSION AT LH WING I/B AFT FLAP UPPER SKIN BETWEEN WBL 84.0 AND WBL 85.5. ALL CORROSION REMOVED AT LH WING I/B AFT FLAP UPPER SKIN BETWEEN WBL 84.0 AND 85.5. REMOVED MATERIAL 0.001" AND REMAINING 0.015" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-51 ALLOWABLE DAMAGE 1 (R130).
CA 1464/173 CORROSION AT LH WING I/B AFT FLAP UPPER SKIN BETWEEN WBL 88.5 AND WBL 90.5. ALL CORROSION REMOVED AT LH WING I/B AFT FLAP UPPER SKIN BETWEEN WBL 88.5 AND WBL 90.5. REMOVED MATERIAL 0.001" AND REMAINING 0.015" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-51 ALLOWABLE DAMAGE 1 (R130).
CA 1464/184 CORROSION AT FUSELAGE SKIN STA 947.5, BETWEEN S-2R AND S-3R (L:5.6",W:1.4"). ALL CORROSION REMOVED AT FUSELAGE SKIN AT STA 947.5, BETWEEN S-2R AND S-3R (L:5.6", W:1.4"). REMOVED MATERIAL 0.003" AND REMAINING 0.037" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/185 CORROSION AT FUSELAGE CROWN SKIN STA727, BETWEEN S-3L AND S-3R, 5 AREA (L:0.7",W:0.5")(L:1.5",W:0.6")(L:5.7"W:0.8)(L:1",W:0.5")(L:0.8",W:0.7"). ALL CORROSION REMOVED AT FUSELAGE CROWN SKIN AT STA 727, BETWEEN S-3L AND S-3R (L:0.7", W:0.5") (L:1.5", W:0.6")(L:5.7", W:0.8") (L:1", W:0.5")(L:0.8", W:0.7"). REMOVED AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/98 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 663.75 AND STA 685 (L:4",W:0.3"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 663.75 AND STA 685 (L:4", W:0.3"). REMOVED 0.003" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/99 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 685 AND STA 706, 2 AREA (L:3.2",W:0.2")(L:0.5",W:0.3"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 685 AND STA 706 (L:3.2", W:0.2") (L:0.5", W:0.3"). REMOVED 0.003", 0.004" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/114 DENT (1.0" X 0.5" IN AREA, MAX DEPTH=0.015") AT LH SIDE FUSELAGE EXTERNAL SKIN AT STA 1072, IN ABOVE S-22L 0.5" DENT (1.0" X 0.5" IN AREA, MAX DEPTH=0.015") AT LH FUSELAGE EXTERNAL SKIN AT STA 1072. ABOVE TO S-22L 0.5". CHECK WITHIN ALLOWABLE LIMIT IAW B737-300 SRM 53-00-01 ALLOWABLE DAMAGE 1 DETAIL ILL (R130), A/T RATIO 0.5"/0.015"=33.33730.
CA 1464/186 CORROSION AT FUSELAGE CROWN DOUBLER BETWEEN STA 500 AND STA 540, S-1R AND S-2R, 14 AREA (L:3.1",W:2.2")(L:1.4",W:1.4")(L:0.9",W:0.5")(L:0.5",W:0.4") (L:1.9",W:0.7")(L:2.3",W:1.4")(L:1.7",W:1")(L:1.3",W:0.6")(L:1.1",W:0.6")(L:0.4",W:0.3)(L:0.8",W:0.6") (L:0.7",W:0.6")(L:1",W:0.7)(L:1.1",W:0.7"). ALL CORROSION REMOVED AT STA 500E & STA 540, S-1R & S-2R (L:3.1", W:2.2") (L:1.4", W:1.4") (L:0.9", W:0.5") (L:0.5", W:0.4") (L:1.9", W:0.7") (L:2.3", W:1.4") (L:1.7", W:1") (L:1.3", W:0.6") (L:1.1", W:0.6") (L:0.4", W:0.3") (L: 0.8", W: 0.6") (L:0.7", W: 0.6") (L:1", W:0.7") (L:1.1", W:0.7"). REMOVED AND REMAINING (0.004", 0.046") (0.002", 0.048") (0.002", 0.048") (0.003", 0.047") (0.002", 0.048") (0.002", 0.048") (0.001", 0.049") IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/190 CORROSION AT L/H SIDE HORIZONTAL STABILIZER REAR SPAR UPPER SURFACE AT STAB STA 116. (1.0" X 0.3" IN AREA). ALL CORROSION REMOVED AT LH HORIZONTAL STABILIZER REAR SPAR UPPER SURFACE AT STAB STA 116 (1.0" X 0.3" IN AREA). REMOVED 0.002" AND REMAINING 1.130" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 55-10-10 ALLOWABLE DAMAGE 1 FIG 101 (R130).
CA 1464/191 CORROSION AT L/H SIDE HORIZONTAL STABILIZER REAR SPAR UPPER SURFACE AT STAB STA 153 (1.2" X 0.3" IN AREA). ALL CORROSION REMOVED AT LH HORIZONTAL STABILIZER REAR SPAR UPPER SURFACE AT STAB STA 153 (1.2" X 0.3" IN AREA). REMOVED 0.040" AND REMAINING 0.620" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 55-10-10 ALLOWABLE DAMAGE 1 FIG 101 (R130).
CA 1464/122 CORROSION AT RH SIDE FUSELAGE AT STA 1071, S-20R. ALL CORROSION REMOVED AT RH FUSELAGE AT STA 1071, S-20R.. REMOVED 0.002" MATERIAL AND REMAINING 0.073" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/123 CORROSION AT APU INLET DOOR AT STA 1064, S-15R. CORROSION AT APU INLET DOOR AT STA 1064, S-15R, REPAIRED IAW AIR ASIA EL-737-230506. (ASAP INC. EO 5323-075)
CA 1464/129 SURFACE CORROSION ON FUSELAGE EXTERIOR SKIN BS500B/S24R+2". ALL CORROSION REMOVED AT FUSELAGE EXTERIOR SKIN BS5008, S-24R+2". REMOVED 0.001" AND REMAINING 0.070" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 PAGE 101~111(R130).
CA 1464/135 T-BRACKET LOWER SKIN CORROSION AT BS 508 /S26R. DAMAGE T-BRACKET REMOVED AT BS 508, S-26R. INSTALL NEW PARTS I.A.W. B737-300 SRM 51-40-2 PARA 4. P2 (R130).
CA 1464/139 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 867 AND STA 887, (L:0.7",W:0.3"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 867 AND STA 887. REMOVED 0.006" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/289 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN W STA 477.75 AND W STA 478.25. ALL CORROSION REMOVED AT LH WING LOWER SURFACE BETWEEN WSTA 477.75 AND WSTA 478.25. REMOVED 0.011" MATERIAL & REMAIN 0.139" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-20-01 ALLOWABLE DAMAGE 1 TABLE 11.
CA 1464/290 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN W STA 581.3 AND W STA 582.1. CORROSION AT LH WING LOWER SURFACE, BETWEEN W STA 581.3 AND W STA 582.1, REPAIR IAW AIR ASIA EL-737-230503. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01849-001R01)
CA 1464/291 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN W STA 475.0 AND W STA 477.0. CORROSION AT LH WING LOWER SURFACE, BETWEEN W STA 475.0 AND W STA 477.0, REPAIR IAW AIR ASIA EL-737-230503. (V1 AEROSPACE, LLC REPAIR INSTRUCTION R23-01849-001 R01)
CA 1464/292 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN W STA 468.2 AND W STA 469.0. ALL CORROSION REMOVED AT LH WING LOWER SURFACE BETWEEN WSTA 468.2 AND WSTA 469.0. REMOVED 0.023" MATERIAL & REMAIN 0.149" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-20-01 ALLOWABLE DAMAGE 1 TABLE II.
CA 1464/293 THE CORROSION WAS FOUND AT LH WING LOWER SURFACE, BETWEEN WBL 266.25 AND WBL 266.75. ALL CORROSION REMOVED AT LH WING LOWER SURFACE BETWEEN WBL 266.25 AND WBL 266.75. REMOVED 0.028" MATERIAL AND REMAINING 0.283" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTION I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 57-20-01 ALLOWABLE DAMAGE 4.
CA 1464/303 LIGHT CORROSION AT RH SIDE EXTERNAL SKIN AT STA 1088, S-16R. ALL CORROSION REMOVED AT RH SIDE EXTERNAL SKIN AT STA 1088, S-16R. REMOVED 0.004" MATERIAL & REMAINING 0.049" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN & PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 53-00-01 ALLOWABLE DAMAGE 1.
CA 1464/9 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN RH SIDE STRINGER 20 STATION 767 TO 787, 867 TO 897, 927 TO 929. ALL CORROSION REMOVED AT STA500 & STA500E, S-1R & S-2R (L:3.1", W:2.2") (L:14", W:1.4") (L:0.9", W:0.5") L:0.5", W:0.4") (L:1.9", W:0.7") (L:2.3", W:14") (L:1.7", W:1"). REMOVED AND REMAINING (0.002", 0.048") (0.002", 0.048") (0.002", 0.048") (0.001", 0.049") (0.002", 0.048") (0.004", 0.046") (0.002", 0.048"). AREA CLEAN AND PROTECTIVE I.A.W. B737- SRM 51-10-2 / 51-20-01 / 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/82 RH WING O/B AFT FLAP LOWER SKIN DELAMINATION BETWEEN WBL 245-WBL 249.5. TRIMMED AND REMOVED THE DAMAGE AREA ON RH WING O/B AFT FLAP LOWER SKIN BETWEEN WBL 245 ~ WBL 247.5. MADE THE REPAIR SKIN AND DOUBLER AND CORE. INSTALLED THE REPAIR PARTS AND CURED THE BOND. CLEANED AND SEALED I.A.W. B737-300 SRM 57-53-02-2R-2 & SRM 51-70-10-2R-4 (R130).
CA 1464/166 CORROSION AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 100.0 AND WBL 102.5. ALL CORROSION REMOVED AT LH WING I/B AFT FLAP LOWER SKIN BETWEEN WBL 100.0 & WBL 102.5. REMOVED 0.001" MATERIAL AND REMAINING 0.015" IS WITHIN ALLOWABLE LIMITS. AREA CLEAN AND PROTECTIVE I.A.W. B737-300 SRM 51-10-2 / 51-20-01 / 57-53-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/100 CORROSION AT FUSELAGE SKIN BETWEEN STA579 AND STA616, S-14R AND S-15R ( L:4.5" W:1"). ALL CORROSION REMOVED AT FUSELAGE SKIN BETWEEN STA 579 AND STA 616, S-14R AND S-15R (L:4.5", W:1"). REMOVED 0.004" AND REMAINING 0.114" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/361 WHILE PERFORM CUSTOMER PROVIDE TASK CARD ECO 3531-R10 WHICH INDICATED IN SB 737-53A1240, FOUND FASTENER HAD BEEN UPSIDE. PERFORM TASK CARD ECO 3531-R10 INSP FOUND FASTENER WRONG. PERFORM PER AIRASIA EL-737-230508.
CA 1464/60 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 887 AND STA 907, 3 AREA (L:0.8", W:0.4")(L:0.3", W:0.3")(L:7.5", W:0.6"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE BETWEEN STA 887 AND STA 907 (L:0.8, W:0.4")(L:0.3", W:0.3")(L:7.5", W:0.6"). REMOVED 0.003", 0.005", 0.003" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1 (R130).
CA 1464/61 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 907 AND STA 927, 6 AREA (L:1.3",W:0.5")(L:0.7",W:0.5")(L:0.8",W:0.5")(L:1",W:0.5")(L:0.3",W:0.3")(L:0.6",W:0.2"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE BETWEEN STA 907 AND STA 927 (L:1.3",W:0.5")(L:0.7",W:0.5")(L:0.8",W:0.5")(L:1",W:0.5")(L:0.3",W:0.3")(L:0.6",W:0.2"). REMOVED 0.003", 0.004", 0.004", 0.005", 0.005", 0.003" MATERIAL IS WITHIN ALLOWABLE LIMIT. AREA CLEAN & PROTECTION I.A.W. B737-300 SRM 51-10-2 / 51-20-1 & 56-20-2 ALLOWABLE DAMAGE 1.
CA 1464/75 CORROSION AT RH WING I/B AFT FLAP LOWER NOSE SKIN BETWEEN WBL 120 AND WBL 146. ALL CORROSION REMOVED AT RH WING I/B AFT FLAP LOWER NOSE SKIN BETWEEN WBL 120 & WBL 146. REMOVED 0.007" MATERIAL AND REMAINING 0.009" OVER LIMIT. PERFORM REPAIR I.A.W. B737-300 SRM 57-53-01 REPAIR 4 (R130).
CA 1464/76 CORROSION AT RH WING I/B EXHAUST GATE LOWER SKIN BETWEEN WBL 169 AND WBL 183. ALL CORROSION REMOVED AT RH WING I/B EXHAUST GATE LOWER SKIN BETWEEN WBL 169 AND WBL 183. REMOVED MATERIAL 0.002" AND REMAINING 0.018" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/77 CORROSION AT RH WING I/B MIDDLE FLAP LOWER SKIN BETWEEN WBL 74 AND WBL 114.5. ALL CORROSION REMOVED AT RH WING I/B MIDDLE FLAP LOWER SKIN BETWEEN WBL 74 AND WBL 114.5. REMOVED MATERIAL 0.009" AND REMAINING 0.116" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW 8737-300 SRM 51-10-2, 51-20-01 AND 57-53-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/83 CORROSION AT RH WING O/B T/E EXHAUST GATE TRAILING EDGE WEDGE BETWEEN WBL 202.5 AND WBL 224. ALL CORROSION REMOVED AT RH WING I/B EXHAUST GATE LOWER SKIN BETWEEN WBL 202.5 AND WBL 224. REMOVED MATERIAL 0.002" AND REMAINING 0.018" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 57-53-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/101 CORROSION AT FUSELAGE SKIN BETWEEN STA 685 AND STA 706, S-11R AND S-12R (L:3.5", W:1"). ALL CORROSION REMOVED AT FUSELAGE SKIN BETWEEN STA 685 AND STA 706, S-11R AND S-12R (L:3.5", W:1"). REMOVED 0.004" AND REMAINING 0.114" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/91 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 400 AND STA 420 (L:0.5",W:0.3"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 400 AND STA 420 (L:0.5",W:0.3"). REMOVED 0.005" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/92 CORROSION AT RH WINDOWS CUTOUT EDGE, BETWEEN STA 500A AND STA 500B (L:0.5",W:0.4"). ALL CORROSION REMOVED AT RH WINDOWS CUTOUT EDGE BETWEEN STA 500A AND STA 500B (L:0.5",W:0.4"). REMOVED 0.004" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-2 ALLOWABLE DAMAGE 1 (R130).
CA 1464/55 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 787 AND STA 807, 2 AREA (L:0.4", W:0.2")(L:1.1", W:0.5"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 787 AND STA 807 (L:0.4", W:0.2")(L:1.1", W:0.5"). REMOVED 0.002", 0.004" MATERIAL IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1.
CA 1464/56 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 807 AND STA 827, 5 AREA (L:1", W:0.5")(L:0.4", W:0.3")(L:0.5", W:0.5")(L:0.6", W:0.4")(L:0.5", W:0.4"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE BETWEEN STA 807 AND STA 827 (L:1", W:0.5")(L:0.4", W:0.3")(L:0.5", W:0.5")(L:0.6", W:0.4")(L:0.5", W:0.4"). REMOVED 0.002", 0.004", 0,004", 0.002", 0.003" MATERIAL IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1.
CA 1464/57 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 827 AND STA 847, 3 AREA (L:1", W:0,3")(L:2,7", W:0.5")(L:1.4", W:0.5"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 827 AND STA 847 (L:1", W:0.3")(L:2.7", W:0.5")(L:1.4", W:0.5"). REMOVED 0.002", 0.004", 0.004" MATERIAL IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1.
CA 1464/58 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 847 AND STA 867, 8 AREA (L:5.5", W:0.5")(L:1.7", W:0.5")(L:0.6", W:0.3")(L:0.5", W:0.3")(L:1.1", W:0.6")(L:0.5", W:0.4")(L:0.9", W:0.5")(L:1.6", W:0.5"). ALL CORROSION REMOVED LH WINDOWS CUTOUT EDGE, BETWEEN STA 847 AND STA 867 (L:5.5", W:0.5")(L:1.7", W:0.5")(L:0.6", W:0.3")(L:0.5", W:0.3")(L:1.1", W:0.6")(L:0.5", W:0.4")(L:0.9", W:0.5")(L:1.6", W:0.5"). REMOVED 0.003", 0.005", 0.003", 0.006", 0.004", 0.004", 0.003", 0.002" MATERIAL WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1.
CA 1464/59 CORROSION AT LH WINDOWS CUTOUT EDGE, BETWEEN STA 867 AND STA 887, 8 AREA (L:1.9", W:0.4")(L:1.6", W:0.5")(L:1.7", W:0.5")(L:1.9", W:0.5")(L:2.9", W:0.5")(L:0.4", W:0.3")(L:0.5, W:0.3")(L:0.5", W:0.4"). ALL CORROSION REMOVED AT LH WINDOWS CUTOUT EDGE BETWEEN STA 867 AND STA STA 887 (L:1.9", W:0.4")(L:1.6", W:0.5")(L:1.7", W:0.5")(L:1.9", W:0.5")(L:2.9", W:0.5")(L:0.4", W:0.3")(L:0.5", W:0.3")(L:0.5", W:0.4"). REMOVED 0.003", 0.005", 0.005", 0.007", 0.004", 0.004", 0.003", 0.003" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 56-20-02 ALLOWABLE DAMAGE 1 (R130).
CA 1464/17 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN LH SIDE STA 986 BETWEEN STRINGER 18 AND 19. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT STA 986 BETWEEN S-18L AND S-19L. REMOVED MATERIAL 0.002" AND REMAINING 0.069" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/18 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN RH SIDE STRINGER 26 STATION 922, 926 TO 928, 938 TO 942, 954 TO 957, 982 TO 990. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT S-26R STA 922, STA 926 TO STA 928, STA 938 TO STA 942, STA 954 TO 957, STA 982 TO STA 990. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/19 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN RH SIDE STRINGER 27 STATION 938 TO 951, 903 TO 907. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT S-27R STA 938 TO STA 951, STA 903 TO STA 907. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/20 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN LH SIDE STRINGER 26 STATION 900 TO 905. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN S-26L, STA 900 TO 905. REMOVED 0.002" MATERIAL AND REMAINING 0.061" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-20-01, 51-10-2 AND 53-00-01 ALLOWABLE DAMAGE.
CA 1464/21 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN LH SIDE STRINGER 27 STATION 987, 900 TO 903. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN S-27L STA 987, STA 900 TO STA 903. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-20-01, 51-10-2 AND 53-00-01 ALLOWABLE DAMAGE.
CA 1464/5 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN STATION 907 BETWEEN LH SIDE STRINGER 17 AND RH SIDE STRINGER 17. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT STA 907 BETWEEN LH SIDE S-17 AND RH SIDE S-17. REMOVED 0.001" MATERIAL AND REMAINING 0.035" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/6 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN STATION 1016 BETWEEN LH SIDE STRINGER 17 TO 20 AND RH SIDE STRINGER 17-25. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT STA 1016 BETWEEN S-17L TO S-20L AND S-17R TO S-25R. REMOVED 0.002" MATERIAL AND REMAINING 0.069" IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/7 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN RH SIDE STRINGER 20 STATION 767 TO 787, 867 TO 897, 927 TO 929. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT S-20R STA 767 TO STA 787, STA 867 TO STA 897, STA 927 TO STA 929. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/8 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN RH SIDE STRINGER 25 STATION 868 TO 907, 947 TO 957, 990 TO 1006. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT S-25R STA 868 TO STA 907, STA 947 TO STA 957, STA 990 TO 1006. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B37-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
CA 1464/10 FILIFORM CORROSION WERE FOUND ON FUSELAGE EXTERNAL SKIN RH SIDE STRINGER 17 STATION 747 TO 767, STRINGER 24 STATION 847 TO 854. ALL CORROSION REMOVED AT FUSELAGE EXTERNAL SKIN AT S-17R STA 747 TO STA 767, S-24R STA 847 TO STA 854. REMOVED MATERIAL AND REMAINING IS WITHIN ALLOWABLE LIMIT. AREA CLEAN AND PROTECTIVE IAW B737-300 SRM 51-10-2, 51-20-01 AND 53-00-01 ALLOWABLE DAMAGE 1 (R130).
FLIGHT CREW REPORTED INSOLATION COMING THROUGH RH NOSE WHEEL WELL. SUSPECT CRACK APPROXIMATELY 4 INCHES LONG.
REPLACED BELTFRAME @ FS 440 R/H SIDE BETWEEN ST 17R-16R WITH MADE REPAIR PART IAW B737-300 SRM REV 125 51-10-02 PARA 8. INSTALLED BELTFRAME IAW BOEING DWG 65-20722 REV: AH AND B737-300 SRM REV 125 51-40-02.
REPLACED STRINGER CLIP STA 685 STR10L IAW ALOHA AIR CARGO ECO 3759 REV 2 3/20/17 PARA 8.0 PART III FIGURE 16.
CORROSION ON VHF ANTENNA DOUBLER HAT SECTION STA 727D-727E,LBL 2 TO RBL 2 INSPECTION CARRIED OUT, NO CORROSION PERMITTED IAW BOEING SB 737-53-1287 REV 1. DATED NOV 15 2010 REPLACED VHF ANTENNA HAT SECTION STA 727D-727E, LBL 2 TO RBL 2 IAW BOEING SB 737-53-1287 REV 1. DATED NOV 15 2010.
REPLACED AUXILIARY CHORD AT STA 727 LH BETWEEN STR 17L & STR 22L. I.A.W. B737-300 SRM REV 126 CH 51-40-02 REF BOEING DOC #65-46547 REV:DK.
REPLACED CONDUCTIVE FRAME FROM UPPER CORNER L/H SIDE OF RUDDER STA 237.64 - FWL 230.25 WITH MADE REPAIR PART I.A.W. B737-300 SRM REV 126 CHP. 55-40-01 AND CHP 51-40-02-0G-O PARA 9,10,11 AND BOEING DWG 65C25841 REV C.
CRACKED PANEL ON UPPER SURFACE OF L/H PYLON @ WBL 180, 60" AFT OF LIE SPAR REPLACED WITH NEW PART IAW B737-300 SRM REV 125 51-40-02 PAR 9.
REMOVED & REINSTALLED FASTENER IN L/H WING UPPER SKIN @ WBL 522-560 30" FWD OFT/E I.A.W. B737-300 SRM REV 126 CH 51-40-02 PAR 7, RE-PROTECTED I.A.W. B737-300 AMM REV 94 CH 51-21-99. INSPECTED WITH 1OX MAG GLASS, CONFIRMED THERE WAS NO CORROSION LIMITED TO PAINT ONLY.
1000605593 - REPLACED STRINGER CLIP@ STA 685, STR 7L IAW ALOHA AIR CARGO ECO 3759 REV 2, DATE 3/20/17, PARA 8.0 PART ILL FIG16. + IAW B737-300 SRM CH 51-40-02 REV 125.
COMPLIED WITH AD 2014-01-05, PERFORMED INSPECTION OF STRINGER SPLICES AND BUTT STRAPS AND REPLACEMENT IAW ALOHA AIR CARGO ECO 3866, PT. II, REVISION 1, DATE: 8/17/17, CRACKS FOUND. SEE NDT REPORT NDT21-1540 ON STRINGER SPLICE AT STA 908 AT STR 4R & 4L CRACKS FOUND. (NOTE ALSO COMPLETED PART III STRINGER REPLACEMENT.)
1000578901 - DENTS (X2) ON BELT FRAME STA 727C STR 23L-25L ASSESSED IAW B737-300 SRM REV 125 CH 53-00-07 FIG 101 SHEET 2 NOTE E AND FOUND TO BE BEYOND ALLOWABLE LIMITS. DENTS ARE ON THE FREE FLANGE. NOTE ESTATES "DENTS ARE ALLOWED, IN FRAME WEB ONLY". DENTED BELT FRAME@ STA 727C STR 23R-23L REPLACED WITH MADE REPAIR PART. 65-46596-165RF INSTALLED IAW B737-300 SRM REV 125 CH51-40-02 REF BOEING DWG 65C25228 REV BK.
COMPLIED WITH AD 2019-09-01, INSTALL NEW J18 JUNCTION BOX TO CHANGE ANTI-ICING SYSTEM MOD, AND WIRING PROVISIONS TO ANTI-ICING SYSTEM IAW ALOHA AIR CARGO ECO 4233 PART 3, REV 1.
1000573101- REPLACED FAIL SAFE ANGLE AT STA 420 STR 26L IAW REFERENCE BOEING DRAWING #65-46527 ID:0011 REV A & B737-300 SRM REV 125 CHAPTER 51-40-02 WITH MADE REPAIR PART.
1000570352 - CORROSION UNDER A/NON FLOOR SUPPORT CHANNEL, AFT CARGO PIT STA 773 LBL 3 REMOVED IAW B737-300 SRM REV 125 51-10-02 PARA 14A. NOMINAL THICKNESS .063", REMAINING THICKNESS .020". MATERIAL REMOVAL OF .043" IS BEYOND THE ALLOWABLE LIMIT OF .0063" IAW B737-300 SRM REV 125 53-60-53 FIGURE 101 DETAIL VII. MATERIAL ID IAW 8737-300 SRM REV 125 53-60-53 FIGURE 1 DETAIL I ITEM 3. CORRODED FLOOR SUPPORT CHANNEL AFT CARGO PIT STA 773 LBL 3 REPAIRED IAW 8737-300 SRM REV 125 53-60-53 FIGURE 201 REPAIR 1. RE-PROTECTED IAW B737-300 SOPM REV 21 20-41-02.
1000570259 - REPAIRED R/H KEEL BEAM LWR SURFACE@ STA 663.75-727, RBL 7, WL 148.5 IAW KF AEROSPACE DWG #R27904.1-053-023-001 REV:NC.
REPLACED STRINGER CLIP @ STA. 727D STR. 5R IAW ECO NO.3759R2 DATED 3/20/17. FASTENERS INSTALLED IAW B737-300 SRM 51-40-02 REV.125.
1000578902 - DENT ON BELT FRAME STA 727B STR24R ASSESSED IAW B737-300 SRM REV 125 CH 53-00-07 FIG 101 SHEET 2 NOTE E AND FOUND TO BE BEYOND ALLOWABLE LIMITS. DENT IS ON THE FREE FLANGE AND NOTE E STATES, "DENTS ALLOWED IN FRAME WEBS ONLY" REPLACED DENTED BELT FRAME @ STA 727B STR 23R-23L WITH KF MADE PART. 65-45696-165KF INSTALLED IAW B737-300 SRM REV 125 CH, 51-40-02 WITH REF TO BOEING DWG 65-46596 REV B.
REPLACED STRINGER CLIP @ STA 727C STR 7L IAW ALOHA AIR CARGO ECO 3759, REV 2, 3/20/17 PARA 8.0 PART III FIG 16 + IAW B737-300 SRM CH 51-40-02 REV 125.
REPLACED STRINGER CLIP STA 727D STR 1 IAW ALOHA AIR CARGO ECO 3759 REV 2 DATE 3/20/17. FASTENERS INSTALLED IAW B737-300 SRM 51-40-02 PG 2 REV 125.
REPLACED CRACKED STRINGER CLIP @ STA 727E, STR 1 IAW ALOHA AIR CARGO ECO 3759 REV 2, DATE 3/20/17, PARA 8.0, PART III, FIG 16. FASTENERS INSTALLED IAW 8737-300 SRM CH 51-40-02, REV 125.
INSPECTED FIRE DETECTION WIRES, FOUND TO BE WITHIN REPAIRABLE LIMITS, REQUIRED WIRES AND APPLIED CHAF PROTECTION NEAR CONNECTOR D3304 O/B #2 ENGINE UPPER CORE SECTION. IAW B737-300 WDM 26-11-21 REV 56 AND BSWPM 20-10-13 REV 78 SERVICEABLE.
CORROSION ON FUSELAGE BELLY SKIN AT STA 727B, STR 26R FOUND TO BE BEYOND LIMITS IAW B737-300 REV 125 SMR 53-00-01, NOM THICKNESS OF 0.063", ALOWABLE REMOVEL 0.0063", REAMING THICKNESS 0.053", REPAIRED FUSELAGE BELLY SKIN AT STA 727B STR 26R IAW B737-300 REV 125 SRM 53-00-01 REPAIR 35.
REPLACED CRACKED STRINGER CLIP STA 727A STR 4R IAW ALOHA AIR CARGO ECO 3759 REV 2 DATE 3/20/17. IAW B737-300 SRM REV 125 51-40-02.
BLENDED AND ASSESSED CORROSION ON BROWNLINE STA907-STA 1006 BL0 AND FOUND BEYOND ALLOWABLE LIMITS. NOMINAL THICK 0.280" REMOVED 0.034" REMAIN 0.246" IAW B737-300 SRM 53-00-52 FIG 101 DETAIL IX SECTION C-C REV 125. REPLACED BROWNLINE WITH MADE REPAIR PART IAW B737-300 AEI SEAT TRACK INSTALLATION DRAWING AE5714 REV G AND B737-300 SRM 51-40-02 PAR 7 REV 125 RE-PROTECTED AREA IAW B737-300 SRM 51-20-01 REV 125
REPLACED STRINGER CLIP@ STA 727C STR 9L IAW B737-300 SRM REV 125 51-10-02 PARA 8 AND INSTALLED IAW 8737-300 SRM REV 125 51-40-02. AND BOEING DOCUMENTS #65C25228 REV:BK, AND #65-73746 REV:CK.
COMPLIED WITH AD 2013-04-05, PERFORMED EXTERNAL HFEC & INTERNAL HFEC INSPECTION FOR ANY CRACKS & CORROSION IAW ALOHA AIR CARGO ECO 3849 PART III REV 2 PARAGRAPH D&H. 3 CRACKS FOUND. REF NOT REPORT #'S NDT21-1508 & NDT21-1529. SEE W/O# 1000580928 FOR RECTIFICATION. HFEC DONE ON VHF #3 ANTENNA & ATTACHED AMOC.
1000570256- REPAIRED L/H KEEL BEAM @STA 663.75-707, LBL 7, WL 148.5 IAW KF AEROSPACE DWG R27904.1- 053-022-001 REV:NC.
1000565725 - REPLACED STRINGER CLIP@ STA 616 AT STR 9L IAW 8737-300 SRM REV 125 51-10-02 PARA 8 AND INSTALLED IAW 8737-300 SRM REV 125 51-40-02 AND BOEING DOCUMENT #65-46539 REV:AV.
1000567496- REMOVED GOUGES ON INTERCOSTAL ATTACH CLIPS X3@ STA 847 STR 20L, 21L, 19L IAW 8737-300 SRM REV 125 CH 53-00-04 FIG 101, MAXIMUM ALLOWABLE EDGE MATERIAL LOSS 0.100" EDGE MATERIAL REMOVED 0.089" IS WITHIN ALLOWABLE LIMITS IAW 8737-300 SRM REV 125 CH 53-00-04 FIG 101 DETAIL 1. VERIFIED NO DAMAGE REMAINING WITH 10X MAGNIFYING GLASS IAW 8737-300 SRM REV 125 CH 51-10-02. REÂ PROTECTED AREA IAW B737-300 SOPM REV 21 CH 20-41-02.
1000570357 - CORROSION ON LOWER SURFACE ON CREASE BEAM WEB, STA 798 RBL 65 REMOVED AND INSPECTED USING A 10X MAGNIFYING GLASS IAW B737-300 SRM REV 125 51-10-02 PAR.14 NOMINAL THICKNESS .032" REMAINING THICKNESS .024" MATERIAL REMOVED .008" IS BEYOND ALLOWABLE LIMITS OF .003" IAW B737- 300 SRM REV 125 53-60-13 MATERIAL ID IAW B737-300 SRM REV 125 53-60-13. REPLACED WITH NEW PART IAW B737-300 SRM REV 125 53-60-13 PAGE 4 DETAIL ILL/ BOEING DWG #65-55885 REV B/B737-300 SRM REV 125 51-40-02. NO CORROSION REMAINING IAW B737-300 SRM REV 125 53-00-13.
1000570361 - CORROSION ON FWD CARGO PIT DUSTSILL WEB@ STA 420-STA 440 STR 26R REMOVED AND INSPECTED WITH A 10X MAGNIFYING GLASS I.AW B737-300 SRM REV. 125 51-10-02 PAR.14 NOMINAL THICKNESS:0.040", REMAINING THICKNESS: 0.033". MATERIAL REMOVAL OF 0.007" IS BEYOND ALLOWABLE LIMITS OF 0.004" (10% OF NOMINAL) I.AW B737-300 SRM REV.125 53-30-53 FIG. 101 DETAIL IV. REMADE DUSTSILL@ STA 420-STA 440 STR 26R I.AW B737-300 SRM REV. 125 51-30-01 PAR. 8 REINSTALLED I.AW B737-300 SRM REV. 125 51-40-02 PAR. 2.
1000570383 - CORROSION UNDER ANCHOR NUT ON SUPPORT STRUCTURE FOR R/H AIR CON ACCESS PANEL @STA 566 RBL 42 WL 149, BEYOND LIMITS IAW B737-300 SRM REV 125 CH.57-10-13 FIG 101. SUPPORT BEAM LWR CHORD REPLACED WITH MADE REPAIR PART FABRICATED AND INSTALLED IAW B737-300 SRM REV 125 CH 51-30- 01 AND 51-40-02. REFERENCE B737-300 SRM REV 125 CH 57-10-13 FIG 1 FOR MATERIAL ID AND PART INFO.
1000573058 - CORROSION ON FLOORBEAM TOP CAP@ STA 887 RBL 47 BLENDED I.AW B.737-300 SRM REV 125 CH 51-10-02 PARA 14 AND WAS FOUND TO BE BEYOND ALLOWABLE LIMITS. ORIGINAL THICKNESS .153, MAX REMOVAL ALLOWED.015 (.138), REMAINING THICKNESS .079 I.AW B.737-300 SRM REV 125 CH 53-60-51 FIG 101. REPAIRED I.AW AEROSPACE DWG NO. R27904.1-053-019-001 REV:NC, & E015509 REV IR.
1000573059 - CORROSION ON FLOORBEAM TOP CAP@ STA1006, RBL20 REPAIRED IAW AEI EO15495 REV IR
1000573102 - BLENDED CORROSION ON R1 DOOR ATTACH ANGLE FOR LOWER SCUFF PLATE RBL 57 STA 294.5+4 TO STA 328. IAW B737-300 SRM 53-10-15 PG 113 DETAIL IX REV 125. FOUND TO BE BEYOND LIMITS NOM THICKNESS .090", .040" REMOVED, .050 REMAINING IAW B737-300 SRM 53-60-15 FIG 101 REV 125. REPLACED R1 DOOR ATTACH ANGLE FOR LOWER SCUFF PLATE RBL 57 STA 294.5+4 TO STA 328 IAW B737 ENGINEERING DWG 65-45875 REV K. FASTENERS INSTALLED IAW B737-300 SRM 51-40-02 REV 125.
1000582023 - CRACKED INDICATION@ MAIN CARGO DOOR AFT MOST OUTER HINGE PLATE {HINGE ON DOOR)@ STA 500A-500B REPAIRED IAW AEI EO15562 REV IR.
1000575570 - X2 CRACKED L-ANGLES FROM FRAMES TO WEB IN E&E BAY STA'S 320 AND 328 BETWEEN STR 20L AND 21L WERE REPLACED WITH MADE REPAIR PARTS FABRICATED AND INSTALLED I.AW B.737-300 SRM REV 125 CH 51-30-01 AND 51-40-02. REFERENCE BOEING DWG 65-54892 ID:0002 REV:A AND PL REV:CW FOR MATERIAL ID AND PART INFORMATION
1000575571 - CRACKED L-ANGLE ON FLOOR STRUCTURE AT FWD WET AREA STA 328, RBL 32, WL 200 REPLACED WITH MADE REPAIR PART FABRICATED AND INSTALLED I.AW B.737-300 SRM REV 125 CH 51-30-01 AND 51-40-02. REFERENCE BOEING DWG 65-45812 ID:0003 REV: LAND PL REV: CR FOR MATERIAL ID AND PART INFORMATION.
1000575816 - DENT/ GOUGE ON BELT FRAME REPAIR MEMBER INNER FLANGE@ F.S. 500 RH SIDE BETWEEN STR 17R-16R BEYOND LIMITS AND REPLACED WITH NEW FABRICATED REPAIR MEMBER IAWAEI ENGINEERING ORDER # EO9520 REV IR
REPAIRED CRACKED FIXED LEADING EDGE SKIN ON RIGHT WING STA 196, JUST I/B OF PYLON I.A.W. B737-300 SRM 57-41-01 REPAIR 9 REV. 125.
COMPLIED WITH AD 2019-09-01. PERFORMED PITOT-STATIC MOD, TEMPERATURE PROBE AND ALPHA VANE ANTI-ICING SYSTEM TEST SERVICEABLE I.A.W. ALOHA AIR CARGO ECO 4233 PT.II, REV.1 DATE: 9/17/2021.
1000580928 - CRACKS FOUND (X4) COMMON TO THE FOOTPRINT OF THE #3 VHF ANTENNA REPAIR REMOVED IAW SB737-53-1287 REV 1 NOVE 15, 2010 AND REPAIRED IAW DWG NO.R27904.1-053-021-001 REV NC.
1000581539 - REPAIRED CRACK EMANATING FROM FASTENER ON STA 1016 BULKHEAD AT CABIN FLOOR LEVEL AT LBL9 AFT FACE OF BULKHEAD IAW KF AEROSPACE DRAWING #R27904.1-53-018-001 REV NC.
REPLACED AUXILIARY CHORD AT STA 727 LH BETWEEN STR 17L & STR 22L. I.A.W. B737-300 SRM REV 126 CH 51-40-02 REF BOEING DOC #65-46547 REV:DK.
1000582022 - REPLACED INTERCOSTAL AT STA 328, LBL 47 FWD GALLEY FLOOR STRUCTURE IAW BOEING DRAWING NUMBER 65-45834 REV HD, FASTENERS INSTALLED IAW B737-300 SRM 51-40-02 PG 2 REV 125.
REPLACED STRINGER CLIP STA 685 STR 10L IAW ALOHA AIR CARGO ECO 3759 REV 2 3/20/17 PARA 8.0 PART III FIGURE 16.
1000582164 - REPAIRED CRACKS ON SKIN AT O/B CHORD@ B.S 727 LH STR 18L I.AW KF AEROSPACE DWG NO R27904.1-053-020-001 REV:NC AND BOEING PREVENTATIVE MOD SB 737-531166 REV 2 DATED JUNE 30,1994. AMOC ATTACHED.
CORROSION ON FILL PORT L/H WING PORT OPENING CORRODED BEYOND LIMITS. REPLACED FILL PORT WITH MADE REPAIR PART I.A.W. B737-300 SRM REV 125 CH 51-40-02, REF BOEING DOC #65-45461 REV:M.
PERFORMED HFEC SURFACE INSPECTION ON BLENDED AREAS ON BELTFRAME STA 727B STR 20R-23R. NO CRACKS FOUND. SEE EXECAIRE WO #498478. REMOVED GOUGES ON I/B FLANGE OF BELTFRAME, STA 727B STR 20R-23R IAW B737-300 SRM REV 125 51-10-02 PARA 5. NOM THICK .063", REMOVED .002", REMAINING .061". FOUND TO BE WITHIN LIMITS (10%) IAW B737-300 SRM REV 125 53-00-07 AND 53-60-07. RE-PROTECTED AREA IAW B737-300 SRM REV 125 51-20-01.
CORROSION ON INTERCOSTAL UNDER ANCHOR NUT @ STA 5008+2" BETWEEN STR 25L-26L REMOVED I.A.W. B.737-300 SRM REV 125 CH 51-10-02. NOMINAL THICKNESS:0.020", REMAINING THICKNESS:0.008". MATERIAL REMOVAL OF 0.012" IS NOT WITHIN ALLOWABLE LIMIT OF 0.002" I.A.W. B.737-300 SRM REV 125 CH 53-00-04 FIG 101 DETAIL II. REPLACED WITH MADE REPAIR PART FABRICATED AND INSTALLED I.A.W. B.737-300 SRM REV 125 CH 51-30-01 AND 51-40-02 MATERIAL ID I.A.W. B.737-300 SRM REV 125 CH 53-330-04 FIG 1.
1000582166 - REPAIRED FWD FLANGE ON O/B CHORD@ B.S 727 R/H STR 18R I.AW KF AEROSPACE DWG #R27904.1-053-017-001 REV NC AND BOEING PREVENTATIVE MOD SB 737-53A1166 REV 2 DATED JUNE 30, 1994
CORROSION ON INTERCOSTAL UNDER ANCHOR NUT @ STA 500A+18" BETWEEN STR 25L-26L REMOVED I.A.W. SRM REV 125 CH 51-10-02. NOMINAL THICKNESS: 0.020", REMAINING THICKNESS: 0.011". MATERIAL REMOVAL OF 0.009" IS NOT WITHIN ALLOWABLE LIMITS OF 0.002" I.A.W. B.737-300 SRM REV 125 CH 53-00-04 FIG 101 DETAIL II. REPLACED WITH MADE REPAIR PART FABRICATED AND INSTALLED I.A.W. B.737-300 SRM REV 125 CH 51-30-01 AND 51-40-02. MATERIAL ID I.A.W. B.737-300 SRM REV 125 CH 53-30-04 FIG 1.
1000605591 - REPLACED STRINGER CLIP@ STA 597 STR 7L IAW ECO. NO. 3759R2 DATED 3/20/17. FASTENERS INSTALLED IAW B737-300 SRM 51-40-02 REV.125
1000605592 - REPLACED STRINGER CLIP@ STA639 STR. 2R IAW ECO NO.3759R2 DATED 3/20/17. FASTENERS INSTALLED IAW B737-300 SRM 51-40-02 REV. 125.
REPLACED CRACKED STRINGER CLIP STA 727D STR 2R IAW ALOHA AIR CARGO ECO 3759 REV 2 DATE 3/20/17 IAW B737-300 SRM REV 125 51-40-02.
REPLACED STRINGER CLIP STA 727L STR 5R IAW ALOHA AIR CARGO ECO 3759 REV 2 DATE 3/20/17. FASTENERS INSTALLED IAW B737-300 SRM 51-40-02 PG 2 REV 125.
REPLACED CRACKED STRINGER CLIP STA 727E STR 5L IAW ALOHA AIR CARGO ECO 3759 REV 2 DATE 3/20/17, IAW 8737-300 SRM REV 125 51-40-02.
REPLACED STRINGER CLIP STA 887 STR 4R IAW ALOHA AIR CARGO ECO 3759 REV 2 DATE 3/20/17. FASTENERS INSTALLED IAW 8737-300 SRM 51-40-02 PG 2 REV 125.
REPAIRED DENT DAMAGE ON FUSELAGE BELLY SKIN AT STA 1016-1088 STR 25L-25R IAW KF DRAWING NO. R27904.1-053-011-001 REV NC, SEE FAA FORM 8110-3 FOR APPROVAL.
REPAIRED CRACKED FASTENER HOLE ON RH WING T/E WBL 136 IAW BOEING SR# 4-4546890303 DATED SEP 23, 2019.
REPAIRED FLOOR BEAM UPPER CHORD AT STA 986.5 RBL 40-45. REPLACED UPPER CAP FROM LBL 50 TO RBL 50 AS PER AEI EO 9563 REV IR AND FAA FORM 8110-3.
REPAIRED RH WING ROOT TO W STA 270, UPPER WING SKIN IN MULTIPLE LOCATIONS AS PER BOEING SR# 4-45466890303 DATED SEPT 23, 2019 AND FAA 8100-9.
REPAIRED DENT DAMAGE ON INNER FLANGE OF STA 500 FRAME AT STR 16R+4" IAW KF DWG# R27904.1-053-099-001 REV A AND AEI EO 09520 REV IR. SEE FORM 8110-3 FOR FAA APPROVAL.
REPAIRED CRACKED STRAPS AT STA 312 BL 0 AND LBL 14 IAW BOEING 737-300 SRM 53-10-51 REPAIR 4 REV 119.
STRINGER CLIP AT STA 639 STR 4L, STA 597 STR 3L AND STA 616 STR 4R REPLACED WITH OEM PART. FASTENERS INSTALLED IAW SRM 51-40-02 REV 117.
CRACK FOUND DURING NDT INSPECTION, AFT HOLE BS 900, ON STRINGER SPLICE 5L. REPLACED THE STRINGER SPLICE IAW SRM 51-40-02, PARA 4, DWG 65-52988, REV D, AND 65-46558 REV L.
CRACKED INTERCOSTAL AT BS 348.2, STRINGER 16L. REPLACED THE INTERCOSTAL IAW ECO 3531 R9.
DENTS BETWEEN BS 277 - 294, STRINGERS 17 AND 18R, REPAIRED IAW EO EO5438, REV A.
STRINGER CLIP, BS 908, STRINGER 8L. REPLACED IAW.DWG 69-35352-15 AND SRM 51-40-02, REV 114.
CRACKED FRAME, BS 420 STRINGER 26L. REPAIRED IAW EO 5363 REV IR.
CRACK IN THE FLOOR SUPPORT, BS 663, RBL 24.82. REPAIR IAW 3-3995809716.
AFT CARGO BAY BS 927, CENTER GOUGE REMOVED IAW SRM 51-10-02 AND REPAIRED IAW EO5425.
REPAIRED CRACK IN BELT FRAME, AT FLANGE TO SKIN ATTACH POINT, AT FS 520, STRINGER 22L IAW SRM 53-00-07 REPAIRED 7 REV 108.
CRACKED BEAR STRAP AT L1 LOWER HINGE CUT OUT. REPAIRED IAW SR 3-3474985717.
CRACKED HINGE FITTING AT L1 LOWER HINGE CUT OUT. REPLACED & INSTALLED IAW DWG 65-17684 REV T & SRM 51-40-02 REV 108.
DURING SCHEDULED MX DISCOVERED A DENT 3 INCHES LONG X 2.5 INCHES WIDE X .05 INCHES DEEP AT BS 390 BETWEEN STRINGER 2R & 3R.