N308WA

Part: SKIN — CRACKED (FS 727E S-24L) · airframe 53,220 hrs · 36,222 cycles

CRACK FOUND IN FUSELAGE SKIN AT CHEM-MIL WHILE ACCOMP OPN 57546. CRACK REPORTED TO BE 1.5 INCH LONG, LOCATED AT FS 727E, S-24L. REPAIRED PER SRM 53-00-01, FIGURE 201. RELATED TO AD 2004-18-06, S/B 737-53A1210, & S/B 737-53-1065.

Part: SKIN — CRACKED (FS 727E S-22R) · airframe 53,220 hrs · 36,222 cycles

CRACK WAS FOUND IN THE FUSELAGE SKIN WHILE DOING OPN 57546 INSPECTIONS. REPAIRED PER SRM 53-00-01, FIGURE 201. REF AD 2004-18-06 / S/B 737-53A1210 / 737-53-1065.

Part: OUTFLOW VALVE — UNSERVICEABLE (CABIN PRESSUR) · airframe 52,735 hrs · 35,926 cycles

AIRCRAFT WOULD NOT PRESSURIZE. FOUND AUTO FLOW CONTROL VALVE NOT CLOSING PER CABIN PRESS LEAK TEST 05-51-91-702. REPLACED VALVE PER MM 21-58-31. OP CK OK. AIRCRAFT PRESSURIZED ON GROUND PER MM.

Part: SKIN — CRACKED (FS S-L) · airframe 50,664 hrs · 34,776 cycles

A SKIN CRACK WAS FOUND ALONG THE THE MILL LINE OF THE UNDERLYING BONDED DOUBLER JUST AFT OF FS 727D AND BELOW STRINGER 23L. THE CRACK WAS REMOVED WITH A 1.5 X 2.5 INCH CUTOUT. THE CUTOUT WAS REPAIRED WITH 2 EXTERNAL ALUMINUM REPAIR DOUBLERS PER ER/A 092528-14, REV A.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 47,438 hrs · 32,960 cycles

AFT CABIN EMERGENCY LIGHT INOPERATIVE, RELAMPED NO HELP R & R POWER SUPPLY LIGHT OPS NORMAL.

Part: SMOKE DETECTOR — MALFUNCTIONED (LAVATORY) · airframe 47,151 hrs · 32,800 cycles

RT AFT LAV SMOKE DETECTOR LIGHT AND CHIME CAME ON AND OFF IN FLT. REPLACED SMOKE DETECTOR UNIT

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 47,128 hrs · 32,791 cycles

CORROSION WAS FOUND IN THE BORES OF BOTH THE LT AND RT PRIMARY FORWARD CLEVIS LUGS. THE LHS PRIMARY FORWARD CLEVIS LUG WAS OVERSIZED TO A DIAMETER OF 1.440 INCH TO REMOVE THE CORROSION. THE RHS PRIMARY FORWARD CLEVIS LUG WAS OVERSIZED TO A DIAMETER OF 1.408 INCH. NO OTHER MACHINING WAS DONE. THE DAMAGE WAS FOUND AT HMV.

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 47,128 hrs · 32,791 cycles

CORROSION WAS FOUND IN THE BORES OF BOTH THE REAR SPAR LT AND RT PRIMARY AND FAIL-SAFE FIN LUGS. THE BORES WERE ENLARGED TO REMOVE CORROSION. ALSO, THE FORWARD FACE OF THE LHS PRIMARY FIN LUG WAS SPOTFACED TO REMOVE CORROSION. REPAIR BUSHINGS WERE INSTALLED. THE DAMAGE WAS FOUND AT HMV.

Part: SENSOR — DIRTY (CARGO DOOR) · airframe 44,058 hrs · 30,925 cycles

CLIMBING THRU 4000 FT FWD CARGO LIGHT ILLUMINATED. RETURNED FOR LANDING. MAINTENANCE CONFIRMED DOOR CLOSED AND LOCKED. CLEANED FWD SENSOR OF FOREIGN SUBSTANCE, OP CHECKS GOOD.

Part: SKIN — GOUGED (FS 1000, S-25L/R) · airframe 43,656 hrs · 30,673 cycles

FUSELAGE / SKIN / FS 907-1156 / STRG. 25L-25R : TAIL STRIKE REPAIR THE FUSELAGE SKIN SUFFERED A TAIL STRIKE ON TAKEOFF WHICH RESULTED IN MULTIPLE GOUGES, SCRAPES, AND HOLES IN THE FUSELAGE SKIN FROM FS 907 TO 1156 AND BETWEEN STRINGERS 25L & 25R. AN UNDERLYING SECTION OF DOUBLER WAS ALSO DAMAGED. A NEW SECTION OF DOUBLER WAS INSTALLED WITH AN ALUMINUM DOUBLER SPLICE REPAIR AND THE TWO DAMAGED SKIN PANELS REPLACED PER ER/A 381560-14, REV A.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 42,184 hrs · 29,695 cycles

WHILE ACCOMPLISHING INSPECTIONS OF THE FS 178 BULKHEAD WEB A CRACK WAS FOUND AT RBL 5.7 AND WL 211. THE CRACK WAS LOCATED ABOVE AND EXISTING DOUBLER REPAIR FOR CRACKS BELOW WL 205. THE NEW CRACK WAS REMOVED WITH A 1 INCH CUTOUT AND THE EXISTING REPAIR DOUBLER REMOVED. A NEW ALUMINUM REPAIR DOUBLER WAS INSTALLED TO ENCOMPASS ALL CRACK CUTOUT REGIONS. THE REPAIR WAS ACCOMPLISHED PER ER/A 379797-14AD, REV A.

Part: FRAME — CRACKED (BULKHEAD) · airframe 42,184 hrs · 29,695 cycles

THE FS 178 BULKHEAD LT SIDE CHORD WAS FOUND WITH A .5 INCH VERTICAL CRACK IN THE RADIUS OF THE CHORD. A NEW SECTION OF SIDE CHORD WAS SPLICED IN PER THE REQUIREMENTS OF BAC S/B 737-53A1173 AND DOCUMENTED PER ER/A 379791-14AD.

Part: ACTUATOR — CRACKED (SPOILER)

AFTER LANDING, LOST HYD SYS A GROUND PERSONNEL REPORTED LEAK RT WING AREA. FOUND NR 8 GROUND SPOILER ACT LEAKING, REPLACED SAME. .

Part: ENGINE — FAILED (NR 1)

AT 1500 FT NR 1 ENGINE LOUD BANG AND OVERTEMP TO 930 CELSIUS. FOLLOWED BY VIBRATION WITH THROTTLE REDUCED IDLE INDICATIONS NORM FOR 4-5 MIN THEN VIBRATION IND WENT TO 3. A/C STARTED TO SHAKE. ENG SHUT DOWN. PAX REPORTED FLAMES AT TIME OF COMPRESSOR STALL THEN NONE UNTIL SLIGHTLY BEFORE ENG SHUT DOWN. INFLT SHUTDOWN AND AIR TURNBACK. MTC FOUND OIL IN TAILPIPE, CAUSE OF FLAMES AND COMPRESSOR AND TURBINE SEIZED. NO VISIBLE DAMAGE TO ENG OR BLADES.

Part: LINE — RUPTURED (RT MLG)

LOST A-SYS HYD PRESS AND QTY JUST AFTER RAISING GEAR ON T/O. FOUND RT GEAR UP LINE TO ACT RUPTURED. REPLACED LINE, BOTH A-SYS CASE DRAIN CHECK OK. LEAK CHECKED PUMPS, CHECK OK.

Part: BATTERY — DISCHARGED (CABIN)

FWD EMERGENCY FLASHLIGHT INOPERATIVE. REPLACED BATTERY AND BULB, OPS OK.

Part: SKIN — DENTED (NR 3 FORE FLAP)

DURING HMV SHOP INSPECTION, RIGHT WING NR 3 FORE FLAP WAS FOUND WITH DENTED SKIN, LOWER LEADING EDGE JUST OUTBOARD OF INBOARD ATTACH POINT. REPAIRED PER SRM 57-53-01 FIG 201.

Part: SKIN — PUNCTURED (LT ELEVATOR)

DURING HMV, FOUNG SMALL PUNCTURE AND FIBER DAMAGE IN LEFT ELEVATOR UPPER SURFACE. LOCATED 3 FEET FROM INBOARD AND 7 INCHES FROM SPAR AFT. REPAIRED ELEVATOR PUNCTURE PER SRM 55-20-01 IN REF TO 51-70-17.

Part: ATTACH FITTING — CRACKED (RT MLG)

DURING ROUTINE INSPECTION AT HMV, THE RT WING O/B AFT SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM WAS FOUND CRACKED. THE CRACKED FITTING WILL REMAIN IN SERVICE PER S/B 737-57-1216 AND WILL BE REPAIRED PER S/B REQUIREMENTS.

Part: SEAT TRACK — CORROSION (FS 344)

AT HMV, CORROSION WAS FOUND ON SEAT TRACK HORIZONTAL FLANGE AT STA 344 LBL 20. REMOVED OLD SECTION, FABRICATED NEW SEAT TRACK AND INSTALLED SEAT TRACK PER SRM53-00-52.

Part: FLOOR BEAM — CORRODED (FS 328)

DURING HMV, CORROSION WAS FOUND ON A FLOOR BEAM AT FS 328 AROUND FASTENER HOLES FROM LEFT TO RIGHT SIDE OF THE FUSELAGE. REPAIRS INVOLVED TREAT AND PAINT LBL49 PER PS 900-2 NR 5 AND REPAIR LBL 36 AND RT OUTBOARD END PER SRM 53-00-51 FIG 205.

Part: FLOOR BEAM — CORROSION (FS 960-975)

AT HMV, CORROSION WAS FOUND ON FLOOR BEAM CAPS SECTIONS AT STA 960 TO 975 RBL 30-40. REPAIRED PER SRM 53-00-51.

Part: LE SLAT — CRACKED (RT WING)

AT HMV, FOUND NR 5 LEADING EDGE SLAT CRACKED ON BOTTOM ALONG FASTENERS. REPAIRED PER SRM 57-43-01 FIG 205.

Part: FLOOR SUPPORT — CORRODED (FS 960)

AT HMV, FOUND FLOOR SUPPORT CORRODED AT STA 960 LBL 10-30. REMOVED OLD, FABRICATED AND INSTALLED NEW SUPPORT PER SRM 51-00-00.

Part: FLOOR BEAM — CORRODED (FS 986.5)

DURING HMV, CORROSION WAS FOUND ON FLOOR BEAM AT STA 986.5 AROUND FASTENER HOLES ON TOP FLANGE. REPAIRED PER SRM 53-00-51 PG 220.

Part: SEAT TRACK — CORROSION (FS 960)

AT HMV, CORROSION WAS FOUND ON SEAT TRACK UPPER SURFACES AT STA 960 ON THE OUTBOARD SIDE. REPAIRED PER SRM 53-00-52 FIG 204.

Part: FLOOR TRACK — CORROSION (FS 328)

AT HMV, CORROSION WAS FOUND ON GALLEY FLOOR TRACK AT FLOOR BEAM 328 ON RT SIDE AT CENTER FWD END. REPAIRED PER SRM 53-00-52 PG 202-205.

Part: FLOOR TRACK — CORROSION (FS 328)

AT HMV, CORROSION WAS FOUND ON GALLEY FLOOR TRACK AT FLOOR BEAM STA 328 ON OUTBOARD TRACK RIGHT HAND SIDE AT FWD END. REPLACED SEAT TRACK PER SRM 51-00-00.

Part: FLOOR BEAM — CORRODED (FS 312)

DURING HMV, CORROSION WAS FOUND AT FS 312 FLOOR BEAM FASTENER HOLES AT LBL 6, CENTERLINE AND RBL 8. REPAIRED PER SRM 53-10-51 FIG 205.

Part: FLOOR TRACK — CORROSION (FS 328)

AT HMV, CORROSION WAS FOUND ON GALLEY FLOOR TRACK AT FLOOR BEAM 328 RT SIDE ON THE FWD END OF INBOARD TRACK. REPAIRED PER SRM 53-00-52 PG 202-205.

Part: FLOOR BEAM — CORROSION (FS 294)

AT HMV, CORROSION WAS FOUND ON FLOOR BEAM 'T' CAP SURFACE AT STA 294 BL0 TO OUTBOARD RBL AROUND FASTENER HOLES. REPAIRED PER ERA 300920-14.

Part: SEAT TRACK — CORRODED (FS 344)

AT HMV, FOUND CORROSION ON LEFT OUTBOARD SEAT TRACK AT FS 344. REPAIRED PER SRM 53-00-52 PG 202-205.