N14245

Boeing 737-200 Serious injury Part 121 — operator not named in the NTSB record

ATA 3260

Part: ACCESSORY UNIT — MALFUNCTIONED (E & E COMPT)

THE NOSE GEAR GREEN LIGHT DID NOT ILLUMINATE WHEN GEAR WAS EXTENDED ON FINAL APPROACH TO EWR. THE RED LIGHT WAS ON, A MANUAL GEAR EXTENSION WAS PERFORMED DURING GO-AROUND AND THE GEAR WAS VISUALLY CHECKED THROUGH VIEW PORT. THE GREEN LIGHT ILLUMINATED ON SECOND APPROACH WHEN FLAPS WERE SET TO 30 DEGREES FOR A NORMAL LANDING. MAINTENANCE INSPECTED THE NOSE GEAR ASSEMBLY AND PROXIMITY SWITCH WIRING WITH NO DEFECTS NOTED. THE NOSE GEAR WAS SWUNG FOUR TIMES AND THE FAILURE COULD NOT BE DUPLICATED. THE LANDING GEAR ACCESSORY UNIT WAS REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE IAW MM 32-09-100.

ATA 3350

Part: BATTERY PACK — DISCHARGED (ROW 12 & 20)

INSPECTION FOUND THE AISLE PATH EMERGENCY LIGHTING STRIP IS INOPERATIVE FORWARD OF ROW 12 AND AFT OF ROW 20. THE BATTERY PACK WAS REMOVED AND REPLACED AND OPERATIONAL CHECKS WERE GOOD.

ATA 5330

Part: SKIN — CORRODED (BS 294.5)

INSPECTION FOUND FUSELAGE SKIN CORRODED AT STA 294.5 BETWEEN S26L AND S27L. THE SKIN WAS REMOVED AND REPLACED IAW ECRA 5330-02708 AND ECRA 5330-02707.

ATA 5320

Part: STRAP — PUNCTURED (E & E COMPT)

INSPECTION FOUND A HOLE IN STRAP JUST FORWARD OF E & E COMPARTMENT ENTRANCE. A DOUBLER WAS INSTALLED IAW SRM 51-10-2 AND ECRA 5330-02712.

ATA 5320

Part: DOUBLER — CORRODED (BS 294.5)

INSPECTION FOUND INTERNAL DOUBLER CORRODED AT STA 294.5 LEFT. THE CORRODED SECTION OF DOUBLER WAS CUT OUT, FILLER AND DOUBLER WERE INSTALLED IAW ECRA 5330-02709.

ATA 5230

Part: SKIN — CRACKED (CARGO DOOR)

INSPECTION FOUND A .5 INCH CRACK IN AFT CARGO DOOR SKIN CUTOUT AT LOWER AFT CORNER. THE EXISTING DOUBLERS WERE REMOVED, FILLERS, DOUBLERS, AND TRIPLERS WERE INSTALLED IAW SRM 51-30-2 AND ECRA 5330-02710.

ATA 5330

Part: SKIN — CRACKED (BS 312)

INSPECTION FOUND FORWARD GALLEY DOOR CUTOUT UPPER FORWARD CORNER CRACKED AT STA 312. THE CRACKED AREA WAS ROUTED OUT. REPAIR FILLERS, DOUBLERS, AND TRIPLERS WERE INSTALLED IAW SRM 51-30, ECRA 5330-02703 AND BOEING DRAWING 65C33800.

ATA 5321

Part: FLOOR — CRACKED (CARGO COMPT)

INSPECTION FOUND A 1 INCH CRACK AT SCREW IN FLOOR PANEL AT AFT CARGO COMPARTMENT DOOR ENTRANCE. THE FLOOR PANEL WAS REMOVED IAW SRM 51-30-2. A REPAIR WAS INSTALLED IAW SRM 51-30-2, 51-10-2, AND MM 51-20-11. THE FLOOR PANEL WAS REINSTALLED IAW SRM 51-30-2.

ATA 7110

Part: COWL — CRACKED (NR 2 ENGINE)

INSPECTION FOUND A 1 INCH CRACK AT FASTENER HOLE IN NR 2 ENGINE INBOARD ENGINE COWL. THE CRACKED AREA WAS CUT OUT IAW SRM 51-40-2. TWO REPAIR DOUBLERS WERE INSTALLED IAW SRM 51-40-2 AND 51-30-0.

ATA 5753

Part: SKIN — GOUGED (LT TE FOREFLAP)

INSPECTION FOUND LT INBOARD FOREFLAP GOUGED IN TWO PLACES AT INBOARD SIDE. THE GOUGED AREAS WERE TRIMMED OUT. AN ADHESIVE PRIMER AND BONDED FIBERGLASS REPAIR WAS INSTALLED IAW SRM 51-40-6, 51-40-9, AND MM 51-20-11.

ATA 5330

Part: SKIN — CORRODED (BS 219.8)

INSPECTION FOUND INSIDE OF SKIN CORRODED IN LT WHEEL WELL AT STA 219.8, STRINGER 27L. THE CORROSION WAS REMOVED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-10-6, 53-10-1, 53-30-3, 51-10-2, AND MM 51-11-20.

ATA 5313

Part: LONGERON — DELAMINATED (BS 287)

INSPECTION FOUND NLG WHEEL WELL LONGERON 28L DELAMINATED AT BS 287. THE LONGERON WAS REMOVED AND REPLACED IAW SRM 51-30-2, 51-10-2, 51-30-2, AND MM 51-20-11.

ATA 5320

Part: ANGLE — CORRODED (BS 277)

INSPECTION FOUND VERTICAL ANGLE CORRODED AT FS 277. THE VERTICAL ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-2.

ATA 5320

Part: CLIP — CORRODED (BS 277)

INSPECTION FOUND SHEAR CLIP CORRODED AT STA 277, LBL 17. THE SHEAR CLIP WAS REMOVED AND REPLACED IAW SRM 53-10-2 AND 51-30-2.

ATA 5313

Part: STIFFENER — CRACKED (BS 727)

INSPECTION FOUND A 2 INCH CRACK AT LOWER ATTACH POINT OF VERTICAL STIFFENER AT AFT CARGO FORWARD PRESSURE BULKHEAD STA 727, LBL 18. THE STIFFENER WAS REMOVED AND A NEW STIFFENER WAS INSTALLED IAW SRM 51-30-2.

ATA 5320

Part: ANGLE — CORRODED (BS 294-325)

INSPECTION FOUND ANGLE CORRODED AT STA 294.5 TO 325.38, LBL 8. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-30-5.

ATA 5320

Part: ANGLE — CRACKED (LT WING/FUS)

INSPECTION FOUND A 3 INCH CRACK IN LT FORWARD WING TO BODY FAIRING ATTACH ANGLE. THE ANGLE WAS REMOVED AND A REPAIR ANGLE WAS INSTALLED IAW ECRA 5350-01227 AND 51-30-2.

ATA 5330

Part: SKIN — CRACKED (BS 178)

INSPECTION FOUND A .0625 AND 1.5 INCH CRACK IN FUSELAGE SKIN DOUBLER FORWARD OF COCKPIT WINDOW AT STA 178, BL 0. THE SKIN DOUBLER WAS REMOVED IAW SRM 51-30-2. REPAIR PARTS WERE INSTALLED IAW SRM 51-30-2 AND ECRA 5310-03754.

ATA 5315

Part: FLOORBEAM — CRACKED (BS 675)

INSPECTION FOUND A 2 INCH CRACK IN FLOORBEAM LOWER CHORD AT STA 675, BBL 0.07. THE LOWER CHORD WAS REMOVED AND A NEW LOWER CHORD ANGLE AND TWO REINFORCING SPLICE ANGLES WERE INSTALLED IAW ECRA 5710-01929.

ATA 5315

Part: FLOORBEAM — CRACKED (BS 663)

INSPECTION FOUND A 1 INCH CRACK IN FLOORBEAM WEB AT STA 663, BL 0. A REPAIR WAS INSTALLED IAW ECRA 5710-01931.

ATA 5400

Part: CASTING — CRACKED (NR 1 PYLON)

INSPECTION FOUND NR 1 ENGINE PYLON PANEL LOWER SIDE NUT PLATE AREA CRACKED AND FOUND A 1 CRACK IN INBOARD FORWARD ATTACH CASTING. THE CASTING WAS REMOVED IAW SRM 51-30-2. A REPAIR ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-10-2, AND MM 51-20-11. A NEW CASTING WAS INSTALLED IAW SRM 51-30-2.

ATA 5712

Part: RIB — GOUGED (LT WING)

INSPECTION FOUND A GOUGE IN LT WING LEADING EDGE RIB INBOARD OF NR 3 SLAT. A REPAIR ANGLE DOUBLER AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 51-40-3, 51-10-2, 51-30-2, AND MM 51-21-31.

ATA 7830

Part: FAIRING — CHAFED (NR 1 ENGINE)

INSPECTION FOUND A HOLE CHAFED THROUGH NR 1 ENGINE THRUST REVERSER EXTENSION UPPER CLOSE OUT FAIRING. THE AREA WAS REPAIRED IAW SRM 51-20-1, FIGURE 7.

ATA 5413

Part: LONGERON — CRACKED (NR 2 NACELLE)

INSPECTION FOUND A 2.5 INCH CRACK ON END CAP (LONGERON) PANEL NR 2 ENGINE FAIRING. THE LONGERON WAS REMOVED AND A NEW LONGERON WAS INSTALLED IAW SRM 51-30-2.

ATA 5400

Part: FAIRING — CRACKED (WS 181)

INSPECTION FOUND A 1 INCH CRACK AT FASTENER HOLE ON NR 1 ENGINE WING TO ENGINE UPPER FAIRING AT LOWER INBOARD CORNER, WS 181.0. THE CRACK WAS STOP DRILLED, AN EXTERNAL REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 54-30-2, FIGURE 2 AND 51-40-2, FIGURE 1.

ATA 5400

Part: FAIRING — CRACKED (WS 183.4)

INSPECTION FOUND A 1 INCH CRACK ON NR 1 ENGINE WING TO ENGINE UPPER FAIRING AT LOWER INBOARD CORNER, WS 183.4. THE CRACK WAS STOP DRILLED, AN EXTERNAL REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 54-30-2, FIGURE 2, 51-40-2, FIGURE 1, AND 51-30-2.

ATA 5320

Part: ANGLE — CRACKED (BS 727)

INSPECTION FOUND A .5 INCH CRACK IN FORWARD ANGLE IN AFT CARGO COMPARTMENT AT STA 727, BL 0, STRINGER 29L. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-30-2.

ATA 3412

Part: TAT INDICATOR — SHORTED (RT COCKPIT)

THE TAT CIRCUIT BREAKER POPPED FOLLOWED BY SMOKE IN THE COCKPIT AFTER TAKEOFF. THE SMOKE APPEARED TO COME FROM THE TAT GUAGE. THE AIRCRAFT WAS RETURNED TO ATL WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE TAT INDICATOR AT FAULT. THE INDICATOR WAS REMOVED AND REPLACED. THE TAT CIRCUIT BREAKER WAS REPLACED AS A PRECAUTIONARY MEASURE. TAT INDICATION TESTED NORMAL. ALL WIRING FOR TAT INDICATOR AND BREAKER WAS INSPECTED AND NO DEFECTS WERE FOUND.

ATA 5320

Part: WEB — CRACKED (BS 727)

INSPECTION FOUND A 2 INCH CRACK IN SHEAR BEAM WEB IN LT WHEEL WELL AT STA 727. REPAIRED IAW DRAWING 65C29228.

ATA 3234

Part: CIRCUIT BREAKER — INOPERATIVE (COCKPIT)

THE LANDING GEAR HANDLE COULD NOT BE RAISED PAST THE OFF POSITION AFTER TAKEOFF FROM MSY. THE GEAR LIGHTS CIRCUIT BREAKER WAS FOUND POPPED. THE CIRCUIT BREAKER WAS RESET AND THE GEAR RAISED NORMALLY. A FEW MINUTES LATER THE LIGHTS CIRCUIT BREAKER POPPED AGAIN. THE CIRCUIT BREAKER WAS RESET TO EXTEND THE GEAR FOR LANDING AND THE CIRCUIT BREAKER POPPED AGAIN. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE CIRCUIT BREAKER EXTREMELY WEAK. THE LIGHTS CIRCUIT BREAKER WAS REPLACED AND OPERATION CHECKED GOOD.

ATA 2612

Part: FIRE LOOP — CHAFED (NR 2 ENGINE)

THE NR 2 ENG FIRE WARNING LIGHT AND BELL ACTIVATED BRIEFLY SEVERAL TIMES IN FLIGHT. THE DURATION OF EACH WARNING WAS LESS THAN ONE SECOND. THE NR 2 ENG FIRE LIGHT AND WARNING BELL CAME ON STEADY AFTER LANDING AT CLE. BOTH FIRE BOTTLES WERE DISCHARGED, AND SHORTLY AFTERWARDS THE FIRE WARNING CEASED. MAINTENANCE FOUND NO EVIDENCE OF FIRE. THE NR 2 ENGINE OVERHEAT/NORMAL POSITION FIRE DETECTION SYSTEM WAS PLACARDED INOPERATIVE. *S/D* MAINTENANCE FOUND FIRE LOOP WIRE CHAFED IN HALF AT DISCONNECT SOCKET PLUG FOR LOWER FORWARD LOOP ASSEMBLY. THE SOCKET PLUG AND INSULATION WERE REMOVED AND REPLACED, OPERATION CHECKED GOOD.