N16884

Part: LATCH — OUT OF RIG (TAIL CONE)

TAIL CONE PULL FROM INSIDE HANDLE WAS EXCESSIVE. THE TAIL CONE WOULD NOT DEPLOY FROM THE AFT SERVICE DOOR. THE TAIL CONE LATCHES WERE ADJUSTED AND OPERATIONAL CHECKS WERE GOOD IAW MM 53-53-00.

Part: BEAM — CORRODED (CARGO BAY)

INSPECTION FOUND Z-BEAM CORRODED BENEATH CENTER THRESHOLD PLATE IN MID CARGO BIN. THE Z-BEAM WAS REPLACED IAW SRM 53-05, FIGURE 63.

Part: FRAME — CRACKED (BS 1463)

INSPECTION FOUND A 2 AND .125 INCH CRACK IN CANTED BELTFRAME WEB AT LEFT SIDE, STA 1463. THE WEB WAS REMOVED AND REPLACED IAW SRM 51-30-1.

Part: ANGLE — CORRODED (BS 1338)

INSPECTION FOUND ANGLE CORRODED AT STA 1338, LONGERON 18L. A NEW SECTION OF ANGLE WAS SPLICED IN IAW SRM 53-03, FIGURE 14.

Part: SEAT TRACK — CORRODED (BS 218 - 256)

INSPECTION FOUND RT O/B SEAT TRACK CORRODED AT STA 218-256. THE CORRODED SECTION OF SEAT TRACK WAS REPLACED IAW SRM 53-05, FIGURE 4F.

Part: SKIN — CRACKED (BS 222)

INSPECTION FOUND A 4 INCH CRACK IN FUSELAGE SKIN NEAR FORWARD LAV ON LT SIDE AT STA 222. REPAIRED IAW ECRA 5330-02445.

Part: SEAT TRACK — CORRODED (BS 1079 - 1309)

INSPECTION FOUND LT I/B SEAT TRACK CORRODED AT STA 1079-1309. A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-30-1.

Part: LONGERON — CRACKED (BS 237)

INSPECTION FOUND A .5 INCH CRACK AT LOWER FASTENER HOLE OF LONGERON 17L AT STA 237. A NEW SECTION OF LONGERON WAS INSTALLED IAW SRM 53-02, FIGURE 18.

Part: VALVE — LEAKING (RT PACK)

SMOKE APPEARED IN COCKPIT AND CABIN ON DEPARTURE FROM DCA. THE RT PACK WAS SHUT OFF AND THE SMOKE CLEARED. THE FLIGHT WAS CONTINUED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND RT OIL FILLED WATER SEPARATOR VALVE LEAKING OIL. THE VALVE WAS REMOVED AND REPLACED. IN ADDITION, THE WATER SEPARATOR BAG WAS REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: WIRE — BURNED (HORIZ STAB)

THE AIRCRAFT WAS RETURNED TO IAH WHEN THE PRIMARY TRIM BECAME INOPERATIVE. THE AIRCRAFT LANDED AT IAH WITHOUT INCIDENT. MAINTENANCE OPENED DOGHOUSE ON VERTICAL STABILIZER AND FOUND WIRE BUNDLES BURNED. NEW WIRES WERE SPLICED IN TO PLUG P10-399 FOR PRIMARY TRIM MOTOR IAW MM 27-41-01 AND STANDARD PRACTICES 20-50-01. THE WIRING IN THE AREA WAS INSPECTED AND WRAPPED IAW STANDARD PRACTICES. THE PRIMARY TRIM MOTOR WAS REMOVED AND REPLACED IAW MM 27-40-01. WIRING CLEARANCE AND OPERATION CHECKED GOOD.

Part: SKIN — CRACKED (WS 286)

INSPECTION FOUND A 2.5 INCH CRACK IN RT WING LEADING EDGE SKIN WHERE NR 2 AND NR 3 SLAT PANELS MEET, WS XOS 286. A REPAIR WAS INSTALLED IAW ECRA 5720-01619.

Part: CABLE — FRAYED (TAILCONE)

INSPECTION FOUND TAIL CONE RELEASE CABLE FRAYED. THE CABLE WAS REMOVED AND REPLACED AND PULL CHECKED IAW MM 53-53-00.

Part: DOUBLER — CRACKED (COCKPIT WINDOW)

INSPECTION FOUND A 1 INCH CRACK IN COCKPIT RT WINDOW RETAINER DOUBLER. THE COCKPIT RT WINDOW RETAINER DOUBLER WAS REMOVED AND REPLACED IAW EA SA 006-5600-01004.

Part: DOUBLER — CRACKED (COCKPIT WINDOW)

INSPECTION FOUND THREE CRACKS IN COCKPIT LT WINDOW RETAINER DOUBLER. THE CRACKS WERE LOCATED AT FASTENERS AND MEASURED .0625 TO .125 INCH LENGTH. THE COCKPIT LT WINDOW RETAINER DOUBLER WAS REMOVED AND REPLACED IAW EA SA 005-5600-01004.

Part: WIRE — BROKEN (CABIN)

EMERGENCY TRACK LIGHTING INOP FROM ROW 5 THROUGH ROW 12. REPAIRED BROKEN WIRE FOUND AT MID BATTERY PACK.

Part: BATTERIES — DISCHARGED (CABIN)

THE EMERGENCY EXIT LIGHT ARM AND CHARGE CIRCUIT BREAKER POPPED WITH EMERGENCY EXIT LIGHT SWITCH IN ARM POSITION. THE BATTERIES AT ROW 20 AND 21 OVERHEAD BINS WERE REMOVED AND REPLACED. THE CIRCUIT BREAKER WAS RESET AND THE SWITCH WAS ARMED WITH NO FAULTS NOTED.

Part: STRUT — LEAKING (NLG)

THE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. THE GEAR HANDLE WOULD ONLY GO HALF WAY UP. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. THIS WAS A REPEAT PROBLEM. MAINTENANCE FOUND THE NOSE STRUT FLAT WITH THE STRUT METERING PIN LEAKING. THE INNER CYLINDER AND GLAND NUT WERE REMOVED AND REPLACED IAW MM 32-21-2. THE STRUT WAS SERVICED AND THE GEAR WAS CYCLED SEVERAL TIMES WITH NO DEFECTS NOTED. IN ADDITION, A DIP WAS ISSUED TO PERFORM FULL NLG STRUT SERVICE WITHIN 50 HOURS.

Part: HYD PUMP — SHAFT WORN (LT ENGINE)

THE LEFT ENGINE HYDRAULIC PRESSURE DROPPED TO ZERO SHORTLY AFTER TAKEOFF. THE HYDRAULIC QUANTITY WAS NORMAL. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LT ENGINE DRIVEN HYDRAULIC PUMP HAD FAILED DUE TO A WORN SHAFT. THE HYDRAULIC PUMP WAS REMOVED AND REPLACED. THE ENGINE WAS RUN AND LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: BRAKE — LOCKED UP (NR 2 MLG)

THE WHEEL NOT TURNING LIGHT ILLUMINATED UPON LANDING, NR 2 MAIN TIRE BLEW. MAINTENANCE FOUND THE NR 2 BRAKE LOCKED UP AND THE QUICK DISCONNECT ON NR 2 BRAKE WAS LOOSE AND LEAKING. THE NR 2 BRAKE, NR 2 WHEEL ASSY, AND QUICK DISCONNECT WERE REPLACED. IN ADDITION, THE NR 1 WHEEL ASSEMBLY WAS REPLACED AS A PRECAUTIONARY MEASURE, LEAK AND OPERATIONAL CHECKS WERE GOOD. THE AIRCRAFT AND ENGINE INLET WERE INSPECTED AND NO DAMAGE WAS FOUND. *S/D* EXAMINATION OF THE BRAKE DURING TEARDOWN REVEALED NORMAL WEAR. ENGINEERING CONCLUDED THAT BRAKE LOCK UP WAS DUE TO FAILURE AND SUBSEQUENT LEAKAGE OF THE NR 2 BRAKE QUICK DISCONNECT.

Part: PROX SWITCH — DIRTY (NLG)

THE RED NOSE GEAR UNSAFE LIGHT ILLUMINATED INTERMITTENTLY AFTER GEAR WAS RETRACTED. THE GEAR WAS CYCLED, BUT THE LIGHT CONTINUED TO ILLUMINATE INTERMITTENTLY. THE LIGHT EXTINGUISHED AT A SPEED OF 240 KNOTS AND REMAINED OUT. THE FLIGHT WAS CONTINUED TO EWR WHERE IT LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND MOISTURE AND DEBRIS ON THE NLG PROXIMITY SWITCH AND THE SWITCH WAS CLEANED. THE GEAR WAS CYCLED SEVERAL TIMES WITH OPERATION AND INDICATIONS CHECKING GOOD. THE AIRCRAFT HAS FLOWN FOUR FLIGHTS WITHOUT A REPEAT OF NLG INDICATION PROBLEMS SINCE THIS CORRECTIVE ACTION WAS IMPLEMENTED.

Part: BATTERIES — DISCHARGED (CABIN)

INSPECTION FOUND BOTH THE LEFT AND RIGHT FORWARD OVERWING EMERGENCY EXIT LIGHTS INOPERATIVE DURING PRE-DEPARTURE CHECK. TROUBLESHOOTING FOUND THE BATTERIES AT FAULT. THE BATTERIES WERE REPLACED AND OPERATION OF THE OVERWING EMERGENCY EXIT LIGHTS WAS RESTORED.

Part: BEAM — CRACKED (PAX DOOR)

HOU - INSPECTION FOUND A 1 INCH CRACK IN HORIZONTAL BEAM AT MAIN CABIN DOOR UPPER AFT CORNER. THE CRACK WAS STOP DRILLED IAW SRM 52-05, PAGE 189, FIGURE 31. A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 52-05, PAGE 189, FIGURE 31, SRM 51-30-2, AND SRM 51-30-5. (M)

Part: FUEL CONTROL — INOPERATIVE (APU)

EWR - FLT 0210 - THE APU AUTO SHUT-DOWN WHILE THE APU GENERATOR WAS POWERING THE LEFT BUS DURING CLIMB THROUGH FL 290. THE APU WAS RESTARTED AFTER DESCENDING TO FL 230. WHILE CLIMBING BACK THROUGH FL 270, THE APU RPM APPROACHED 108 PERCENT WITH FREQUENCY IN EXCESS OF 420 CPS. THE AIRCRAFT WAS DESCENDED BACK TO FL 230 WHERE THE FLIGHT WAS COMPELTED WITHOUT FURTHER PROBLEM. MAINTENANCE REMOVED AND REPLACED THE APU FUEL CONTROL UNIT. LEAK AND OPERATIONAL CHECKS WERE GOOD. (X)

Part: EEL BATTERIES — DISCHARGED (CABIN)

FLT NR 0344 - EWR - INSPECTION FOUND THE OVERHEAD EMERGENCY LIGHTS IN AFT CABIN AT ROWS 9-14 AND 23-27 INOPERATIVE. THE BATTERIES FOR THREE BATTERY PACKS WERE REPLACED AND OPERATION OF THE OVERHEAD EMERGENCY LIGHTS WAS RESTORED. (W)

Part: EEL WIRE — BROKEN (CABIN)

FLT NR 0344 - EWR - INSPECTION FOUND THE EMERGENCY EXIT LIGHT ON THE OUTSIDE WALL OF AFT LEFT LAV INOPERATIVE. MAINTENANCE FOUND A BROKEN WIRE AT THE EXIT LIGHT. THE WIRE WAS REMOVED AND REPLACED AND OPERATION OF THE EXIT LIGHT WAS RESTORED. (W)

Part: EEL BATTERIES — DISCHARGED (CABIN)

EWR - FLT 301 - THE OVERHEAD EMERGENCY LIGHTS AT ROW 9 TO 14 WERE FOUND INOPERATIVE DURING A PREFLIGHT CHECK. MAINTENANCE REMOVED AND REPLACED THE BATTERIES AND OPERATION OF THE OVERHEAD EMERGENCY LIGHTS WAS RESTORED. (W)

Part: O-RING — RUPTURED (LT MLG BRAKE)

FLT NR 0318 - EWR - THE LEFT HYDRAULIC SYSTEM FLUID QUANTITY BEGAN TO DECREASE WHILE IN FLIGHT. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND A RUPTURED O-RING ON THE CAPPED END OF VALVE ASSEMBLY LEADING TO LEFT BRAKE PRESSURE TRANSMITTER. THE O-RING WAS REPLACED AND THE LEFT HYDRAULIC SYSTEM WAS SERVICED. THE LEFT ENGINE WAS RUN AND ALL HYDRAULIC FLIGHT CONTROLS WERE CYCLED WITH NO LEAKAGE NOTED. (Z)