N243WA

Part: FLOORBEAM — CRACKED (LBL 0.07 BS 660) · airframe 52,377 hrs · 37,863 cycles

CRACKS WERE FOUND IN THE LBL 0.07 FLOORBEAM UPPER CHORD AT THE FLOOR PANEL ATTACH HOLES BETWEEN BS 660-663. CHORD WAS REPAIRED AND MODIFIED PER ER/A 451389-14. REF S/B 737-57-1210 AND 3-062982-03AD.

Part: TRANSMITTER — LEAKING (THRUST REVERSER) · airframe 51,857 hrs · 37,502 cycles

ODOR IN CABIN, DIVERSION TO CLT. FOUND HYDRAULIC LEAK AT RT THRUST REVERSER PRESSURE TRANSMITTER LEAKING INTO RT PACK INLET. SECURED LEAK. CLEANED PACK INLET. REPLACED COALESCER.

Part: SKIN — CRACKED (FUSELAGE) · airframe 50,594 hrs · 36,564 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 1.2 INCH CRACK NEAR FS 767, RUNNING ALONG THE BONDED DOUBLER MILL LINE JUST ABOVE STRINGER 19R. THE CRACK IS TYPICAL OF AD 2004-18-06. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B737 SRM AND ER/A 097069-14AD.

Part: SKIN PANEL — CRACKED (FUSELAGE) · airframe 50,594 hrs · 36,564 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 1.5 INCH LONG CRACK AT APPROX FS 727B RUNNING ALONG THE BONDED DOUBLER MILL LINE JUST BELOW STRINGER 18R. THE CRACK IS TYPICAL OF AD 2004-18-06. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B737 SRM AND PER ER/A 097068-14AD.

Part: SKIN — CORRODED (FUSELAGE) · airframe 50,119 hrs · 36,195 cycles

FOUND ON S2 LETTER CK, CORROSION ON LOWER FUSELAGE SKIN STA 727A BETWEEN STRINGERS 27 LEFT AND 27 RIGHT. REPAIRED PER SRM 53-30-3 FIG 1.

Part: SMOKE DETECTOR — FALSE ACTIVATION (LAVATORY) · airframe 49,854 hrs · 36,000 cycles

LAV SMOKE LIGHT CAME ON IN FLIGHT. SILENCED ALARM AND F/A INVESTIGATED. NO SIGN OF SMOKE. TESTED LAV SMOKE DETECTORS PER M/M. CHECKS GOOD.

Part: CONNECTOR — WORN (FLAP TRANSMITTER) · airframe 49,055 hrs · 35,396 cycles

DURING TAKEOFF FLAPS LOCKED UP BETWEEN 1 AND 2 DEG, THE LEFT FLAP STAYED AT 1.5 AND RIGHT AT 2.0. CHECK OF SYSTEM SHOWED LEFT FLAP SYSTEM FLUCUATING. REPLACED LEFT FLAP TRANSMITTER CONNECTOR D275, OP CHECKS NORMAL.

Part: SMOKE DETECTOR — DEFECTIVE (AFT LAVATORY) · airframe 48,854 hrs · 35,251 cycles

AFT LAV SMOKE DETECTOR CHIMES ONLY ONCE DURING TEST. REPLACED SMOKE DETECTOR.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,549 hrs · 35,013 cycles

SCRIBE MARKS WERE NOTED AT S14L BETWEEN BS 259.5 AND 303.9. DAMAGE WAS REMOVED AND REPAIRED PER ERA 089014-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,549 hrs · 35,013 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S14R LAP JOINT BETWEEN BS 908 AND BS 960. DAMAGE WAS REMOVED AND REPAIRED PER ERA 088728-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,549 hrs · 35,013 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S14L LAP JOINT BETWEEN BS 908 AND BS 960. DAMAGE WAS REMOVED AND REPAIRED PER ERA 088591-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,549 hrs · 35,013 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S10L LAP JOINT BETWEEN BS 259.5 AND BS 303.9. DAMAGE WAS REMOVED AND REPAIRED PER ERA 088638-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,549 hrs · 35,013 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S4R LAP JOINT BETWEEN BS 259.9 AND BS 360. DAMAGE WAS REMOVED AND REPAIRED PER ERA 089005-14.

Part: STRAP — DAMAGED (FUSELAGE) · airframe 48,549 hrs · 35,013 cycles

SCRIBE MARKS WERE NOTED IN THE BUTT JOINT AT BS 360 BETWEEN S13L AND S28R. DAMAGE WAS REMOVED AND REPAIRED PER ERA 088793-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,546 hrs · 35,011 cycles

THE FUSELAGE SKIN LAP JOINTS AND BUTT JOINTS WERE FOUND WITH NUMEROUS AREAS OF SCRIBE DAMAGE FROM FS 259.5 TO 1016 IN THE JOINTS FROM STRINGER 14 AND ABOVE. THE AFFECTED LAP JOINTS WERE CUT OUT AND ALUMINUM REPAIR DOUBLERS INSTALLED TO RESTORE THE JOINTS. THE BUTT JOINT STRAPS WERE REMOVED AND REPLACED. THE REPAIRS ARE SUMMARIZED ON ER/A 386200-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 48,546 hrs · 35,011 cycles

BS 663 FRAME WAS FOUND CRACKED NEAR S7R. CRACK WAS REMOVED AND REPAIRED PER ERA 089232-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,546 hrs · 35,011 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S4L LAP JOINT BETWEEN BS 259.5 AND BS 360. DAMAGE WAS REMOVED AND REPAIRED PER ERA 089308-14.

Part: INTERCOSTAL — MISINSTALLED (SERVICE DOOR) · airframe 48,546 hrs · 35,011 cycles

DURING ACCOMPLISHMENT OF EO03-055852-03AD, THREE INTERCOSTALS WERE NOTED AS BEING DISCREPANT AS NOTED IN THE INTRODUCTION OF ERA 089386-14. DISCREPANCIES WERE DISPOSTIONED PER ERA 089386-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,546 hrs · 35,011 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S4L LAP JOINT BETWEEN BS 727 AND BS 908. DAMAGE WAS REMOVED AND REPAIRED PER ERA 088665-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,546 hrs · 35,011 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S4R LAP JOINT FROM BS 727 - 908. DAMAGE WAS REMOVED AND REPAIRED IAW ERA 088676-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 48,546 hrs · 35,011 cycles

SCRIBE MARKS WERE NOTED IN THE LOWER SKIN OF THE S25L LAP JOINT BETWEEN BS 727 AND BS 908. DAMAGE WAS REMOVED AND REPAIRED PER ERA 088651-14.

Part: FITTING — CORRODED (MLG) · airframe 48,546 hrs · 35,011 cycles

THE BS 685 MLG SIDE STRUT SUPPORT FITTINGS ON BOTH THE LT & RT WERE FOUND WITH CORROSION IN THE LUG BORES. REMOVAL OF THE CORROSION RESULTED IN DECREASING THE LUG STRENGTH TO AN UNACCEPTABLE LEVEL. THE FITTING ON BOTH SIDES OF THE AIRCRAFT WERE REMOVED AND NEW FITTINGS INSTALLED PER ER/A 088086-14.

Part: WIRE HARNESS — SHORTED (NR 1 ENGINE) · airframe 48,511 hrs · 34,986 cycles

ON APPROACH, THE LEFT GEN TRIPPED. RT BUS ATTEMPTED TO PICK UP AND TRIPPED ALSO. DOWN TO STBY POWER. CREW DECLARED EMERGENCY. FOUND LT GENERATOR CABLE SHORTED. REPLACED GENERATOR FEEDER HARNESS.

Part: TAB — FLUTTER (LT & RT ELEVATOR) · airframe 48,510 hrs · 34,985 cycles

ON CLIMB FROM CVG AT 250 - 280 KTS. F/A REPORTED VIBRATION IN AFT OF AIRCRAFT. VERIFIED BY F/O. NO CHANGE WITH CHANGE IN AIRSPEED, ON DESCENT F/A NOTICED VIBES, SIGNIFICANTLY REDUCED AIRSPEED BELOW 250 KTS. REPLACED LEFT AND RIGHT ELEVATOR TABS.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 47,249 hrs · 34,246 cycles

EMERGENCY FLOOR LIGHTING INOP AT ROWS 1 THRU 4. REPLACED POWER SUPPLY

Part: LINE — DAMAGED (NR 1 ADC) · airframe 46,970 hrs · 34,127 cycles

CAPT'S A/S INDICATOR FAILED ABOVE 110K ON TAKEOFF. ON T/O IT WENT TO 45K, AFTER AIRBORNE TO 360K, LATER DECREASED TO 45K PRIOR TO LANDING. REPLACED PITOT FLEX LINE ON FRONT OF NR 1 ADC, PERFORMED LEAK CK PER MM AND FOUND NO LEAKS. ALL INST TEST OK PER MM.

Part: ACTUATOR — BROKEN (NLG) · airframe 46,966 hrs · 34,124 cycles

ON APPROACH INTO MCO NOSE LANDING GEAR FAILED TO EXTEND ON FIRST ATTEMPT. OK ON SECOND ATTEMP AND LANDED WITH OUT INCIDENT. AMT FOUND LOCK ACTUATOR FAILED CAUSING 1 INCH DIAMETER HOLE IN FWD PRESS BULKHEAD NOSE WHEEL WELL.

Part: DUCT — RUPTURED (NR 2 ENGINE) · airframe 46,699 hrs · 34,015 cycles

SHORTLY AFTER LIFT OFF, NR 2 ENGINE OVERHEAT LIGHT CAME ON ACCOMPANIED BY A BLEED TRIP LIGHT. OVERHEAT LIGHT EXTINGUISHED WHEN THRUST LEVERS RETARDED TO IDLE. FOUND SENSE LINE LEAKING AT PRBC AND COWL ANTI-ICE DUCT BLOWN. REPLACED SENSE LINE, COWL DUCT, AND 490 DEGREE OVERHEAT SWITCH. RAN ENGINES TO T/O POWER, OPN AND INDICATION NORMAL.

Part: HYDRAULIC LINE — LEAKING (NR 2 ENGINE) · airframe 45,035 hrs · 33,334 cycles

NR 2 ENGINE HYD PUMP RUPTURED THE PRESS LINE AND LOST ALL HYD QTY. FOUND RIGHT ENGINE HYD PUMP PRESS LINE LEAKING. REPLACED LINE. PULLED AND INSPECTED ALL SYSTEM AND CASE DRAIN FILTERS, NO TROUBLE FOUND. SERVICED HYD TO FULL. RAN ENGINE AND ELEC PUMPS. CYCLED ALL FLT CONT. LEAK CHECKS GOOD. ALL CHECKS NORMAL.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,618 hrs · 32,743 cycles

THE LT SIDE CHORD OF THE FS 178 BULKHEAD WAS FOUND CRACKED AT WL 195. THE FLOOR WEBS AT WL 207 WERE ALSO FOUND CRACKED. THE CHORD WAS REPAIRED WITH REPAIR ANGLES PER BAC S/B AND THE FLOOR WEBS WERE REPLACED PER THE S/B. THE WORK WAS DOCUMENTED PER ER/A 382559-14AD.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 43,253 hrs · 32,588 cycles

THE OVERWING LONGITUDINAL FLOORBEAM AT RBL 24 WAS FOUND WITH A CRACK IN THE WEB, WEB REINFORCING DOUBLER AND UPPER CAP AT FS 680. THE UPPER CAP AND REINFORCING DOUBLER WERE REMOVED AND REPLACED. THE WEB DAMAGE WAS TRIMMED OUT AND REPAIRED WITH AN ALUMINUM DOUBLER. A REINFORCING CHANNEL WAS INSTALLED ON THE CAP PER BAC S/B 737-57-1139. THE WORK WAS ACCOMPLISHED PER ER/A 382280-14, REV A.

Part: STOP FITTING — OUT OF ADJ (L1 DOOR) · airframe 41,821 hrs · 31,974 cycles

PASSING 10,000 FEET IN CLIMBOUT FWD F/A REPORTED THUMP NOISE AT LEFT FWD ENTRY DOOR. WHILE CONTINUING CLIMB CAPT WENT BACK TO ACCESS NOISE/SOURCE. LEVELED AT FL230 FOR 4 MINUTES, DECIDED OK FOR CONTINUE. PASSING FL280, IN COCKPIT BOTH PILOTS HEARD LOUD THUMP AND FELT ASSOC VIBRATION THROUGH FLOORING, HALTED CLIMB AT FL290. PRESS CONTROLLER AUTO 33000, 5 PSID INDICATED. REMOVED DOOR LINER AND SIDEWALL AFT OF L1 DOOR TO INSP, NO VISIBLE DAMAGE FOUND. ADJ DOOR STOPS ON DOOR FRAME. PRESSURIZED TO 6.5 PSID.

Part: SKIN — CRACKED (FUSELAGE) · airframe 38,166 hrs · 30,390 cycles

THE LOWER HINGE CUTOUT OF THE AFT GALLEY DOOR CUTOUT WAS FOUND WITH A SMALL TYPICAL CRACK IN THE SKIN AND BONDED SURROUND DOUBLER. THE CRACK WAS REMOVED WITH A .375 INCH LONG TRIM OUT AND REPAIRED WITH AND EXTERNAL DOUBLER PER B737 SRM 53-30-3, FIG 15 AND ER/A 377446-14, REV A.

Part: CONTROLLER — NOISY (ACM) · airframe 37,739 hrs · 30,197 cycles

AUDIBLE RUMBLE WHEN ADDING POWER AS A/C POSITIONED RUNWAY. CYCLED ENGINE BLEEDS AND RUMBLE STOPPED. ON CLIMBOUT RUMBLE RETURNED AT CLIMB POWER. RUMBLE DIDN''T RETURN DURING DESCENT APPROACH AND LANDING. NO FLIGHT CONTROL PROBLEMS. INSPECTED A/C VISUALLY, NO FAULTS NOTED. INSPECTED 01-02 ENG INTAKES AND EXHAUST. OPENED AND INSPECTED BOTH ACM COMPARTMENTS, INSPECTED WATER SEPARATORS. REMOVED AND REPLACED L/R 35 DEGREE VALVES AND RT CONTROLLER. PERFORMED ENG RUN AND BLEED SYS CK OUT PER PFHB. ALL CKS NORMAL.

Part: SKIN — CRACKED (FUSELAGE)

HFEC INSP OF FWD GALLEY DOOR CUT OUT LOWER AFT CORNER REVEALS .125 INCH LONG CRACK AT 2 FASTENER LOCATIONS. ROUTED OUT DAMAGED AREA PER SRM 53-30-3. HFEC INSP ROUTED AREA NO INDICATIONS. FABRICATED DOUBLER DRILLED UP DOUBLER AND INSTALLED DOUBLER PER SRM 53-30-3.

Part: BATTERY — DISCHARGED (FLASHLIGHT)

AFT TOP EMERGENCY FLASHLIGHT INDICATOR NOT FLASHING. REPLACED BATTERY, NOW CKS OK.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY LIGHT ABOVE 23 DEF INOP. REPLACED BATTERY PACK.

Part: BULKHEAD WEB — CRACKED (BS 178)

STA 178 BULKHEAD WEB WAS FOUND WITH CRACKS IN THE TYP LOCATIONS AT LBL 5.7 AND RBL 5.7. THE CRACKS WERE TRIMMED OUT WITH 1 X 4 CUTOUTS. THE DAMAGED AREAS WERE REPAIRED WITH SINGLE ALUMINUM REPAIR DOUBLER PER ER/A 363850-12, REV A.

Part: TRANSFORMER — INTERMITTENT (NR 1 ENGINE)

DURING CLIMB, NR 1 GEN BUSS TRIPPED AND WOULD NOT RESET/APU WOULD NOT PICK UP BUSS EITHER. REPLACED NUMBER 1 ENG CURRENT TRANSFORMER, CHECKS GOOD.

Part: GEN CONTL PNL — FAILED (NR 1 ENGINE)

DURING CLIMBOUT, LEFT GEN BUSS TRIPPED (NO VOLTS OR FREQS) AND APU WOULD NOT PWR THE BUSS. REPLACED LEFT GEN CONT PANEL, OPERATION OF GEN AND XFR SYS OP CKS GOOD.

Part: RELAY — STUCK (NR 1 ENGINE)

DURING CLIMBOUT, LT GEN BUSS TRIPPED OFF AND APU WOULD NOT PWR THE BUSS. REPLACED NR 1 GEN CONTROL RELAY. INSP ENG GEN LEADS AND DIFFERENTIAL LOOPS. ALL OK, RAN ENG AT T/O PWR.

Part: POWER SUPPLY — INOPERATIVE (LT SERVICE DOOR)

AFT LEFT SERVICE DOOR EMERGENCY SLIDE ILLUMINATION LIGHT INOP. REPLACED M1197 EMERGENCY LIGHT POWER SUPPLY.

Part: BATTERY PACK — DISCHARGED (CABIN)

RT FWD EXTERIOR EMERGENCY SPOT LIGHT ON EXTERIOR OF AIRCRAFT INOP. REPLACED RT FWD EXTERIOR EMERGENCY SPOT LIGHT BATTERY PACK.

Part: LIGHT — INOPERATIVE (R2 DOOR)

R2 DOOR EMERGENCY ESCAPE SLIDE LIGHT INOP.

Part: SKIN — CRACKED (FS 379)

DURING INSPECTION, A 1 INCH CRACK WAS FOUND JUST LEFT OF BL 0 AT STA 379 IN THE SKIN AFT OF THE E/E AIR DUCT CUTOUT. THE CRACK IS TYPICAL OF THOSE COVERED BY BOEING S/B 737-53-1117, REV 1. DURING REMOVAL OF THE EXHAUST DUCT, THE INTERNAL SURROUND DOUBLER WAS TORN RESULTING IN A 1 INCH BY 1.25 INCH CUTOUT. REPAIRED AS REQUIRED BY BOEING SERVICE BULLETIN 737-53-1117, WHICH INSTALLS A DOUBLER REF DL ERA 303053-14.

Part: FLOOR PANEL — CORRODED (FS 777)

DURING HMV, LT FIXED FLOOR PANEL AT FS 777 FOUND CORRODED BEYOND LIMITS. REPAIRED PER MM 53-21-04 PG 801.

Part: SKIN — CRACKED (FS 1027)

DURING OVERHAUL INSPECTION, MAINTENANCE FOUND A 2.5 CRACK UNDER AN EXISTING REPAIR DOUBLER AT APPROXIMATELY FS 1027, BETWEEN S-7L AND S-8L. THE CRACK PROPAGATED IN THE SKIN FROM THE LOWER FORWARD CORNER OF THE DOUBLER. IN ACCORDANCE WITH B737-200 SRM 53-30-3 FIG 6, THE PREVIOUS CUTOUT UNDER THE REPAIR DOUBLER AND THE NEW DAMAGE WERE INCORPORATED INTO A SINGLE REPAIR.

Part: DOOR — DAMAGED (LT MLG)

FOUND DURING LETTER CHECK, MLG FLY DOOR O/B FWD EDGE REPAIR DAMAGED, LT WING SIDE. REPAIRED PER SRM 52-80-2 INSTALLED DOOR PER MM 51-40-15.