AEKO KULA, LLC

Sanction: $37,000 · case closed 2014-08-25

Sanction: $48,000 · case closed 2013-07-13

Sanction: 22525 · case closed 2012-02-13

Part: CABIN PRESS SYS — FAULTED · airframe 54,829 hrs · 65,163 cycles

AT 1000 FT ON CLIMB OUT AUTO FAIL LIGHT ILLUMINATE AND STANDBY LIGHT ILLUMINATE CLIMB RATE PASS 3000FT/MIN DRIVE CABIN PRESS BELOW SEA LEVEL

Part: SYMBOL GENERATOR — FAILED (NR 1) · airframe 63,118 hrs · 48,619 cycles

CAPTAINS SIDE EFIS DISPLAYS WENT BLANK. NR 1 SG FAILED.

Part: SKIN — DAMAGED (ZONE 100) · airframe 6,626 hrs · 39,690 cycles

FELT TAIL STRIKE ON ROTATION

Part: WINDOW — CRACKED (ZONE 200) · airframe 66,010 hrs · 56,991 cycles

L1 WINDOW CRACKED IMMEDIATELY AFTER TAKEOFF

Part: WINDOW — CRACKED (ZONE 200) · airframe 66,009 hrs · 56,987 cycles

FLT 55. CAPTAIN'S WINDOW L1 CRACKED.

Part: SYMBOL GENERATOR — FAILED (NR 1) · airframe 62,940 hrs · 48,257 cycles

NR 1 SYMBOL GENERATOR FAILED.

Part: NOT REPORTED — CRACKED · airframe 65,980 hrs · 56,925 cycles

CRACK FOUND 3 INCH FWD OF BS 727E ALONG STR 22R

Part: SKIN — CRACKED (ZONE 100) · airframe 65,980 hrs · 56,925 cycles

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.

Part: INDICATOR — FAILED (AIRSPEED) · airframe 66,124 hrs · 39,385 cycles

FIRST OFFICER'S AIRSPEED INDICATOR FAILED WITH A RED FLAG. NEEDLE FROZEN AT 296 KTS.

Part: SKIN — CRACKED (ZONE 100) · airframe 62,470 hrs · 47,295 cycles

CRACK FOUND AT BS 7270+13 BELOW ; STR 23L APPRX 1.75"LONG. CORRECTIVE: 8110 RECEIVED FOR IAW EO 737-53-0407

Part: SKIN — CRACKED (ZONE 100) · airframe 65,486 hrs · 55,825 cycles

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

Part: COVER — ERODED (ZONE 300) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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)

Part: ATTACH FITTING — CORRODED (ZONE 100) · airframe 52,862 hrs · 61,126 cycles

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

Part: FUEL TANK — CORRODED (ZONE 100) · airframe 52,862 hrs · 61,126 cycles

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.

Part: FUEL TANK — CORRODED (ZONE 100) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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.

Part: PRESSURE BLKHD — CRACKED (ZONE 100) · airframe 52,862 hrs · 61,126 cycles

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)

Part: FRAME ANGLE — CRACKED (ZONE 200) · airframe 52,862 hrs · 61,126 cycles

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)

Part: SKIN — CRACKED (ZONE 500 SLAT) · airframe 52,862 hrs · 61,126 cycles

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)

Part: SKIN — CRACKED (ZONE 500 SLAT) · airframe 52,862 hrs · 61,126 cycles

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)

Part: SKIN — CORRODED (ZONE 100) · airframe 52,862 hrs · 61,126 cycles

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

Part: SKIN — CORRODED (ZONE 100) · airframe 52,862 hrs · 61,126 cycles

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

Part: SKIN — CORRODED (ZONE 600 SLAT) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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

Part: FUEL TANK — CORRODED (ZONE 100) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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.

Part: FUEL TANK — CORRODED (ZONE 100) · airframe 52,862 hrs · 61,126 cycles

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.

Part: FUEL TANK — CORRODED (ZONE 100) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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

Part: SPAR — CORRODED (ZONE 300) · airframe 52,862 hrs · 61,126 cycles

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)

Part: SPAR — CORRODED (ZONE 300) · airframe 52,862 hrs · 61,126 cycles

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)

Part: FRAME — CORRODED (ZONE 300) · airframe 52,862 hrs · 61,126 cycles

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

Part: SPAR — CORRODED (ZONE 300) · airframe 52,862 hrs · 61,126 cycles

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)

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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

Part: FUEL TANK — CORRODED (ZONE 100) · corrosion level 2 · airframe 52,862 hrs · 61,126 cycles

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

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 52,862 hrs · 61,126 cycles

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.

Part: SKIN — CORRODED (ZONE 200) · airframe 52,862 hrs · 61,126 cycles

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.

Part: SKIN — CORRODED (ZONE 200) · airframe 52,862 hrs · 61,126 cycles

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

Part: SKIN — CORRODED (ZONE 200) · airframe 52,862 hrs · 61,126 cycles

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

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,704 hrs · 58,723 cycles

DURING ECO 3925, DISCOVERED DENT AT BS 440R APPROX 5" FROM FLOOR, 1 1/4" WIDE, AND 0.07" DEEP.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,704 hrs · 58,723 cycles

DURING ECO 3925, DISCOVERED 2 RIVETS MISSING AT BS 360R JUST ABOVE FLOOR BOARD.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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).

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 51,243 hrs · 57,789 cycles

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.