N245WA

Part: GENERATOR — INOPERATIVE (NR 2 ENGINE) · airframe 46,195 hrs · 36,450 cycles

ON TAKEOFF ROLL APPROX 100 KIAS EXPERIENCED RT GENERATOR BUSS OFF LIGHT. ABORTED TAKEOFF. REPLACED NR 2 CSD & GEN.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 45,331 hrs · 35,797 cycles

WHILE ACCOMPLISHING S/B 737-53A1075 A CRACKED Z-STIFFENER ON THE BS 1016 AFT P-DOME AT S23R WAS NOTED. THE STIFFENER IS LOCATED IN THE INSPECTION AREA, HOWEVER, IS NOT ONE OF THE STIFFENERS DETAILED IN THE BAC DWG. DAMAGE REMOVED AND REPAIRED VIA ERA 089941-14AD.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 45,299 hrs · 35,777 cycles

FUSELAGE KEEL LT LOWER CHORD FS 727A SPLICE. THE LT LOWER KEEL CHORD WAS FOUND WITH CORROSION AT THE FACTORY SPLICE LOCATION AT FS 727A. THE CORROSION WAS REMOVED WITH CUTOUTS IN THE CHORD FLANGES AND LOCAL BLENDS. THE REMOVED MATERIAL WAS REPAIRED WITH ALUMINUM STRAPS AND NEW SPLICE ANGLES IAW ER/A 090184-14.

Part: FITTING — CORRODED (FUSELAGE) · airframe 45,299 hrs · 35,777 cycles

DURING ACCOMPLISHMENT OF EO 3-085220-03, CORROSION DAMAGE WAS NOTED WHICH EXCEEDED THE ALLOWABLE LIMITS OF THE SUBJECT EO ON THE NR 6 AND NR 12 LUGS LOCATED AT BS 1088. CORROSION REMOVED AND DAMAGE REWORKED IAW ERA 089944-14.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 45,299 hrs · 35,777 cycles

CRACKS WERE NOTED IN THE BS520 FLOORBEAM UPPER RADII WHERE THE SEAT TRACKS CROSS OVER THE BEAM. DAMAGE WAS REMOVED AND THE FLOORBEAM REPAIRED IAW ERA 089860-14.

Part: FRAME — DENTED (FUSELAGE) · airframe 45,299 hrs · 35,777 cycles

MULTIPLE FRAMES WERE FOUND TO BE DENTED IN THE FWD CARGO BIN AREA. THE DENTED FRAMES ARE LOCATED BETWEEN BS 400 AND 440. THE DAMAGE WAS DISPOSITIONED AS PER INSTRUCTIONS IN ERA 090192-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,299 hrs · 35,777 cycles

A CRACK APPROXIMATELY 2.3 INCHES LONG WAS NOTED IN THE FUSELAGE SKIN APPROX. 1 INCH AFT OF BS 727B JUST BELOW S18R. DAMAGE WAS REMOVED AND REPAIRED PER ERA 089987-14.

Part: FRAME — CORRODED (FUSELAGE) · airframe 45,299 hrs · 35,777 cycles

CORROSION WAS NOTED ON THE BS 847 FRAME JUST ABOVE S25R. DAMAGE WAS REMOVED AND REPAIRED AS PER ERA 089931-14.

Part: FRAME — DENTED (FUSELAGE) · airframe 45,299 hrs · 35,777 cycles

MULTIPLE DENTS WERE NOTED IN ADJACENT FUSELAGE FRAMES IN THE AFT BAG BIN AREA. DAMAGES WERE REPAIRED IAW ERA 090120-14.

Part: CHECK VALVE — LEAKING (LAV SERVIE) · airframe 42,068 hrs · 33,598 cycles

ON ARRIVAL FOUND RIGHT HORIZONTAL STABILIZER LEADING EDGE DENTED. SUSPECT DAMAGE FROM BLUE ICE CAUSED BY LEAKING FWD LAV SERVICE PANEL. REPLACED STAB L/E ASSY AND REPLACED LAV SERVICE LINE CHECK VALVE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 40,367 hrs · 32,879 cycles

THE LOWER HINGE CUTOUT OF THE AFT GALLEY DOOR (R2) CUTOUT WAS FOUND WITH A .5 INCH TYPICAL CRACK IN THE BONDED SKIN ASSY. THE CRACK WAS REMOVED. THE SKIN WAS REPAIRED WITH AN EXTERNAL DOUBLER INSTALLED PER ER/A 382883-14 REV A.

Part: FUSE — BLOWN (CABIN) · airframe 40,184 hrs · 32,802 cycles

FOUND FORWARD EMERGENCY LIGHTS FROM ROWS 1 THRU 4 INOPERATIVE. REMOVED AND REPLACED FUSE IN EMERGENCY BATTERY PACK LOCATED AT STA 400 (IN EMERGENCY RAFT BAY). EMERGENCY LAMPS, NOW OPS NORMAL.

Part: SKIN — PUNCTURED (FS 460, S-26R) · airframe 39,198 hrs · 32,385 cycles

FUSELAGE / SKIN / FS 460 / STRG. 26R : GROUND DAMAGE CUTOUT REPAIR THE FUSELAGE SKIN WAS DAMAGED BY GROUND EQUIPMENT AT FS 460 BELOW STRINGER 26R. THE DAMAGE WAS REMOVED WITH A CUTOUT. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER INSTALLED PER ER/A 382029-14, REV A.

Part: PUMP — DEFECTIVE (ENGINE) · airframe 37,804 hrs · 31,782 cycles

IN CRUISE FLT 28,000 FEET, SYS-A HYD LOW PRESS LIGHT ON NR 1 ENGINE CAME ON. A-SYS HYD PRESS DROPPED. TURNED OFF THAT SWITCH. 3-5 MINUTES LATER THE OTHER LOW PRESS LIGHT CAME ON. THIS DROPPED SYS-A PRESS FROM 2500 PSI TO ZERO. FOLLOWED LOSS OF SYSTEM-A PROCEDURE AND LANDED UNEVENTFULLY. MAINT TOWED A/C TO GATE. HYD QTY CKD FULL. NO LEAKS FOUND. CASE DRAIN FILTERS CLEAN. ON ENGINE RUN OPN NORMAL. REPLACED BOTH ENGINE HYD PUMPS. RAN ENGINES AND CYCLED FLT CONTROLS.

Part: ENGINE — FOD (NR 1) · airframe 36,917 hrs · 31,353 cycles

ON T/O ROLL, LOUD BANG W/ FULL PWR FELT VIBRATIONS. ABORTED T/O AT 10 KTS. PASSENGER REPORTED FLASH FROM AFT OF NR 1 ENG. PASSENGERS REPORTED BURNING SMELL IN CABIN AFTER BANG. FOUND NR 1 ENGINE INGESTED PLASTIC BAG. PERFORMED BORESCOPE OF NR 1 ENGINE PER PFHB, CHECKS GOOD.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 35,972 hrs · 30,580 cycles

ON T/O NR 1 ENG EPR ERRATIC EGT RAPIDILY ROSE PAST YELLOW ARC TO 635. RAN BOTH ENGINES TO T/O EPR, ALL PARAMETERS WITHIN NORMAL OPERATING RANGES PER PFHB INSPECTED INLET AND EXHAUST ALL NORMAL.

Part: ENGINE — SURGES (NR 1) · airframe 35,376 hrs · 30,098 cycles

AFTER ENGAGING AUTO THROTTLES ON TAKEOFF ROLL THE NR 1 ENGINE SURGED ABOUT 3 TIMES TO AS HIGH AS 2.17 EPR. DISCONTINUED THE T/O AT APPROX 70 KTS. PAX REPORTED A SLIGHT ACRID SMELL IN CABIN. OPERATED ENG PER PFHB, ALL ENGINE PARAMETERS NORMAL WITH A/T OFF. FWD A/T TO MCO PER MEL 22-00-04. NO UNUSUAL SMELLS OR ODOR IN CABIN.

Part: DOOR FRAME — TOOL DAMAGE (FUSELAGE) · airframe 35,315 hrs · 30,047 cycles

TOOLING DAMAGE FOUND ON THE R1 DOOR AFT OPENING FRAME AT WL 214. DAMAGE FOUND IN THE FRAME RADIUS AS WELL AS EDGE OF FLANGE. NEW SECTION OF FRAME SPLICED AS PERMANENT REPAIR. ER/A 334431-14 REV A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 35,315 hrs · 30,047 cycles

STATION 178 BULKHEAD LT SIDE CHORD FOUND CRACKED AT WL 207. A NEW SECTION OF CHORD WAS SPLICED IN PER S/B 737-53A1173. ER/A 334445-14AD.

Part: FRAME — CRACKED (FUSELAGE) · airframe 35,315 hrs · 30,047 cycles

STATION 178 BULKHEAD SIDE CHORD FOUND CRACKED AT WL 196. NEW SECTION SPLICED IN PER BOEING S/B 737-53A1173. ER/A 334425-14AD.

Part: FRAME — TOOL DAMAGE (FUSELAGE) · airframe 35,315 hrs · 30,047 cycles

RT SIDE FRAME AT STA 480 FOUND WITH TOOLING DAMAGE AT THE UPPER FASTENER LOCATION. ER/A 334482-14 REV A.

Part: SKIN — WORN (RT WING) · airframe 35,315 hrs · 30,047 cycles

RT WING, O/B BOOST PUMP ACCESS PLATE CUTOUT FLANGE FOUND WORN ON THE UPPER SURFACE WHERE THE PLATE LATCHES MAKE CONTACT WITH THE CUTOUT FLANGE. ER/A 334473-14 REV B.

Part: SKIN — DENTED (FUSELAGE) · airframe 35,315 hrs · 30,047 cycles

TWO SKIN DENTS FOUND WHICH EXCEEDED SRM ALLOWABLE LIMITS. DENTS AT APPROX STA 787 BETWEEN S-19R AND S-20R. DENTS WERE CUT OUT AND REPAIRED WITH AN EXTERNAL DOUBLER. ER/A 334438-14 REV A.

Part: FRAME — CRACKED (BULKHEAD) · airframe 35,315 hrs · 30,047 cycles

STA 178 BULKHEAD LBL 5.7 VERTICAL CHORD WAS FOUND CRACKED ON BOTH FWD FLANGES, APPROX 9 ABOVE THE LOWER END OF THE CHORD. ER/A 334422-14AD.

Part: SKIN — CRACKED (SERVICE DOOR) · airframe 35,315 hrs · 30,047 cycles

CRACKS DISCOVERED IN THE FWD GALLEY DOOR UPPER CORNERS. CRACKS CONSISTENT WITH B S/B 737-53-1116 REV C AND WERE LIMITED TO THE BEAR STRAP AT BOTH THE FWD AND AFT UPPER CORNERS. ACOMPLISHED PER GUIDELINES OF S/B. ER/A 334479-14AD.

Part: SKIN — CRACKED (R1 DOORWAY)

FUSELAGE, SKIN ASSY, R1 DOOR CUTOUT, LOWER AFT CORNER, CRACK REPAIR. THE FUSELAGE SKIN, DOUBLER, AND BEAR STRAP WERE FOUND WITH A 1.5 CRACK AT THE LOWER AFT CORNER OF THE R1 DOOR CUTOUT. THE CRACK WAS REPAIRED WITH THREE EXTERNAL ALUMINUM DOUBLERSPER B737 SRM 53-30-3, FIG 26 AND ER/A 368409-14.

Part: FITTING — BROKEN (RT MLG ACT)

ON TRANS CHECK, FOUND RT MAIN GEAR RETRACT ACTUATOR O/B ATTACH FITTING BROKEN FREE FROM SPAR. REPLACED SHEARED BOLTS, CRACKED FITTING AND INSPECTED SPAR.

Part: HANDLE — OUT OF POSITION (SPEEDBRAKES)

TAKEOFF WARNING HORN SOUNDED ON TAKEOFF ROLL. DISCONTINUED TAKEOFF BELOW 60 KTS SPEEDBRAKE/FLAPS/STAB TRIM APPEAR NORMAL. FOUND SPEEDBRAKE HANDLE NOT IN DETENT REPOSITIONED HANDLE. PERFORMED TAKEOFF WARN TEST, CKS OK.

Part: COMPRESSOR — BIRD STRIKE (NR 1 ENGINE)

AFTER TAKEOFF, BIRDSTRIKES FOLLOWED BY COMPRESSOR STALLS ON THE NUMBER 1 ENGINE. CHANGED FAN.

Part: CIRCUIT BREAKER — TRIPPED (COCKPIT)

AFTER T/O, LND GEAR HANDLE WOULD NOT COME UP. C/W POM, PULLED RED LOCK OVERRIDE TRIGGER, RAISED GEAR, CONTINUED NML. AT GATE, MECH FOUND LVR LATCH C/B POPPED. TESTED LEV LATCH LOCK SOLENOID PER MM 32-31-31 PG 402 SEVERAL TIMES OPN TEST NML. C/B CKS NML. LAND GEAR HANDLE OPN CKS NML PER TEST. A/C OK FOR SVC. AIR/GD TELEFLEX CONNECTED AND SAFETIED.

Part: LIGHT — INOPERATIVE (RT PAX DOOR)

EMERGENCY LIGHT OUTSIDE AFT RIGHT DOOR INOP. RELAMPED.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING ACCOMPLISHMENT OF S.I. 3-69482-12 AT HMV, 2 CRACKS WERE DISCOVERED ON THE FORWARD FACE OF THE B.S. 178 BULKHEAD WEB. FIRST CRACK IS LOCATED AT RBL 5.7, WL 200. THE SECOND CRACK IS LOCATED AT LBL 5.7, WL 198. A .050 INCH DOUBLER WILL BE INSTALLED.

Part: INTERCOSTAL — CRACKED (BS 332)

THE R1 DOOR FRAME INTERCOSTAL AT STR 8A WAS FOUND CRACKED IN THE TYPICAL MANNER SHOWN IN S/B 737-53A1108, REV 5. THIS ER/A ACCOMPLISHES A REPAIR AT THIS LOCATIONS IN ACCORDANCE WITH BACO S/B 737-53A1108 AND AIRWORTHINESS DIRECTIVE 88-03-03.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING ACOMPLISHMENT OF SI 3-69482-12, TWO CRACKS WERE DISCOVERED ON THE FWD FACE OF THE STA 178 BULKHEAD WEB. THE FIRST CRACK IS LOCATED UNDER THE RBL 5.7 VERTICAL STRAP AT APPROX WL 200 AND THE SECOND IS LOCATED UNDER THE LBL 5.7 VERTICAL STRAP AT APPROX WL 198. THE WEB IS MANUFACTURED FROM 0.040 2024-T3 CLAD.

Part: SKIN — TORN (FS 937)

A/C 372 WAS STRUCK BY A SERVICE VEHICLE RESULTING IN A 6 INCH TEAR AND GOUGE IN THE SKIN AT STA 937, BETWEEN S-21R AND S-22R. IN ACCORDANCE WITH B737-200 SRM 53-30-3 FIG 3, THE SKIN WAS REPAIRED.

Part: EEL POWER SUPPLY — INOPERATIVE (L1 DOOR)

L1 DOOR EMERGENCY SLIDE LIGHT IS DIM. REPLACED EMERGENCY LIGHT POWER SUPPLY AND BATTERY PACK, CHECKS OK.

Part: EEL POWER SUPPLY — INOPERATIVE (R1 DOOR)

R1 DOOR EMERGENCY SLIDE LIGHT IS OUT. REPLACED EMERGENCY LIGHT POWER SUPPLY.