N14880

Part: FRAME — CRACKED (BS 1463)

INSPECTION FOUND THREE CRACKS IN WEB THROUGH LOWER FASTENERS IN A RADIAL STIFFENER OF LT CANTED BELTFRAME AT STA 1463. THE LENGTH OF THE THREE CRACKS TOTALED FIVE INCHES. THE CRACKS WERE STOP DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 53-14-04.

Part: ANGLE — CRACKED (VERTICAL STAB)

INSPECTION FOUND RT DORSAL FIN TO FUSELAGE ATTACH ANGLE CRACKED. THE ATTACH ANGLE WAS REPLACED IAW EA 5340-01012.

Part: FRAME — CRACKED (BS 101)

INSPECTION FOUND A 1 CRACK IN LT BELTFRAME AT STA101 BELOW PULLEY BRACKET. THE BELTFRAME WAS REPAIRED IAW SRM 51-30-2 AND 53-03.

Part: FITTING — CRACKED (RT MLG WW)

INSPECTION FOUND A 3 CRACK IN SUPPORT FITTING ABOVE AND FORWARD OF RT MLG DOOR ACTUATOR UPPER ATTACH POINT IN WHEEL WELL. A NEW FITTING WAS INSTALLED IAW SRM 51-30.

Part: RETAINER — CRACKED (COCKPIT WINDOW)

INSPECTION FOUND A 1.5 CRACK IN LT COCKPIT WINDOW RETAINER. THE RETAINER WAS REMOVED AND A NEW RETAINER WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5.

Part: FITTING — CRACKED (PAX DOOR)

INSPECTION FOUND A 2 CRACK IN AFT ENTRANCE DOOR CENTER HORIZONTAL BEAM RT END FITTING FLANGE. ANGLES WERE INSTALLED IAW SRM 51-30-5 AND 51-30-2.

Part: JAMB — CRACKED (MLG DOOR)

INSPECTION FOUND A 10 INCH CRACK IN RT WHEEL WELL FORWARD O/B DOOR JAMB. THE RT WHEEL WELL FORWARD O/B DOOR JAMB WAS REMOVED AND A NEW JAMB WAS INSTALLED IAW SRM 53-03, FIGURE 26.

Part: FLOORBEAM — DENTED (BS 1174)

INSPECTION FOUND ABB LOWER SIDE OF MAIN CABIN FLOORBEAM DENTED AND CREASED FROM CARGO DOOR LOWER FLANGE AT STA 1174. REPAIRED IAW SRM 53-05, FIGURE 86.

Part: PAN — CRACKED (CARGO DOOR)

INSPECTION FOUND A .25 INCH CRACK IN FORWARD BAGGAGE BIN DOOR PAN AT FORWARD MIDDLE STOP PAD. THE AREA WAS REPAIRED IAW SRM 52-05, FIGURE 50, SHEET 1.

Part: STRINGER — CRACKED (BS 1088 - 1117)

INSPECTION FOUND A .25 INCH CRACK IN STRINGER 1L BETWEEN STA 1088 AND 1117. THE STRINGER SPLICE WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: SKIN — CRACKED (BS 1338)

INSPECTION FOUND A 0.15 CRACK IN FUSELAGE SKIN AT STA 1338, BELOW L5L. THE CRACK WAS CUT OUT. DOUBLERS AND FILLER PLUG WERE INSTALLED IAW DAC DRAWING J060138.

Part: LONGERON — CORRODED (BS 155 - 160)

INSPECTION FOUND LONGERON 22R CORRODED IN E/E COMPARTMENT AT STA 155-160. THE LONGERON WAS REMOVED AND REPLACED IAW SRM 51-30-2.

Part: CUSP — CRACKED (BS 1309)

INSPECTION FOUND A 2.5 CRACK INCH LT CUSP MEMBRANE AT STA 1309. THE CRACK WAS STOP DRILLED AND A REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 96.

Part: SEAT TRACK — CORRODED (BS 1098 - 1140)

INSPECTION FOUND LT I/B SEAT TRACK CORRODED AT STA1098-1140. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-0.

Part: CUSP — CRACKED (BS 1309)

INSPECTION FOUND A 3 CRACK IN RT CUSP MEMBRAME ATSTA 1309. A DOUBLER REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 96.

Part: STRUT — DISCHARGED (NLG)

THE NOSE GEAR DID NOT RETRACT AFTER TAKEOFF. THE GEAR RED UNSAFE LIGHT REMAINED ILLUMINATED. THE GEAR WAS CYCLED AND RETRACTION WAS SUCCESSFUL WITH ALL GEAR INDICATION LIGHTS GREEN. THE FLIGHT WAS CONTINUED WITHOUT FURTHER PROBLEM. A NOSE STRUT FULL SERVICE WAS PERFORMED IAW MM 32-21-02, PAGE 301-304A. A NOSE GEAR EXTENSION AND RETRACTION CHECK WAS PERFORMED IAW MM 32-30-00, PAGE 201-206 AND NOSE GEAR OPERATION CHECKED GOOD.

Part: STRUT — DISCHARGED (NLG)

THE NOSE GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM EWR. THE GEAR WAS EXTENDED AND ALL THREE GEAR GREEN LIGHTS WERE INDICATED. THE AIRCRAFT WAS RETURNED TO EWR. CREW NOTICED GEAR HANDLE RELEASE BUTTON WAS IN. THE BUTTON POPPED OUT WITH NOSE GEAR TOUCHDOWN. A FULL NOSE GEAR STRUT SERVICING WAS PERFORMED IAW MM 32-21-02. IN ADDITION, THE NOSE GEAR UPPER TORQUE LINK WAS REPLACED DUE TO WEAR AND THE GROUND SENSING CABLES WERE ADJUSTED IAW MM 32-23-01. THE GEAR WAS SWUNG AND OPERATION CHECKED GOOD.

Part: SKIN — CRACKED (BS 1337.5)

INSPECTION FOUND A .25 AND .125 INCH CRACK IN FUSELAGE SKIN AT LONGERON 1R STA 1337.5. A REPAIR WAS INSTALLED IAW ECRA 5331-01009 AND SRM 53-04, FIGURE 38, VIEW H.

Part: SKIN — BENT (BS 484)

INSPECTION FOUND FUSELAGE SKIN BENT AND FASTENERS FOR INTERCOSTAL SHEARED AT LOWER VHF ANTENNA, STA 484. A REPAIR WAS INSTALLED IAW EA 5330-01823, OPERATION 3.

Part: BRACKET — CRACKED (RT SPOILER)

INSPECTION FOUND A 1.75 INCH CRACK ON THE RT WING INBOARD FLIGHT SPOILER ACTUATOR BRACKET. THE BRACKET WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: ANGLE — CRACKED (BS 1474)

INSPECTION FOUND A .75 INCH CRACK EXTENDING FROM FASTENER IN RT AFT VERTICAL STABILIZER TO FUSELAGE ATTACH ANGLE AT STA 1474. A REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 23.

Part: SPAR TANG — CRACKED (WS 164)

AFT SPAR LEFT SIDE AFT TANG CRACKED (.250) FROM BUTE DOOR ATTACH HOLE APPROXIMATELY 5 OUTBOARD OF STATION 164. CUT OUT 2 CRACK AREA. FABRICATED AND INSTALLED REPAIR IN ACCORDANCE WITH EC/RA 5710-01844 AND DRAWING J060271-503.

Part: HYD LINE — LEAKING (RUDDER CONTL)

THE RT HYDRAULIC SYSTEM QUANTITY DROPPED TO AS LOW AS THREE QUARTS WHILE EN ROUTE. THE AIRCRAFT LANDED AT BOS WITHOUT INCIDENT. MAINTENANCE FOUND THE HYDRAULIC LINE FOR RUDDER CONTROL SYSTEM LEAKING. THE HYDRAULIC LINE WAS REPLACED USING FLEX LINE. A DIP WAS ISSUED TO REPLACE THE FLEX LINE WITH A PERMANENT LINE WITHIN 1200 HOURS OR 500 FLIGHTS, WHICHEVER COMES FIRST. LEAK CHECK WAS GOOD.

Part: COMPRESSOR BLADE — FAILED (NR 1 ENGINE)

THE TOWER REPORTED SPARKS COMING FROM THE NR 1 ENGINE AT START OF TAKEOFF ROLL. THE TAKEOFF WAS REJECTED AT LESS THAN 60 KNOTS. EQUIPMENT WAS DISPATCHED AND THERE NO VISIBLE SIGNS OF FIRE OR SMOKE. THE NR 1 ENGINE WAS REMOVED AND REPLACED. ENGINE OPERATION AND LEAK CHECK WAS GOOD. SHOP FINDINGS REVEALED THE PRIMARY CAUSE OF ENGINE FAILURE WAS DUE TO THE FAILURE OF A C-7 BLADE.

Part: STARTER — FAILED (NR 2 ENGINE)

ENGINE START WAS ABORTED AFTER PUSHBACK WHEN THE NR 2 ENGINE REACHED 500 DEGREES. THE NR 2 ENGINE COWLING WAS OPENED WHICH REVEALED AN UNCONTAINED STARTER FAILURE. THE STARTER HAD DAMAGED THE SECONDARY FUEL SUPPLY MANIFOLD. THE STARTER AND FUEL MANIFOLD WERE REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: SKIN — CRACKED (FUSELAGE)

INSPECTION FOUND A 1 CRACK IN FUSELAGE SKIN ABOVE FORWARD SERVICE PANEL. THE CRACKED AREA OF SKIN WAS REMOVED. A CLASS III REPAIR WAS INSTALLED IAW SRM 53-04, FIGURE 12B. A DIP WAS ISSUED TO REPLACE THE CLASS III REPAIR WITH A CLASS I OR II REPAIR WITHIN 8,000 LANDINGS AND TO REINSPECT THE AREA WITHIN EVERY 3,000 LANDINGS.

Part: HYD PUMP — LEAKING (LT HYD SYST)

THE LEFT HYDRAULIC SYSTEM QUANTITY DECREASED SHORTLY AFTER TAKEOFF FROM EWR. WHILE COMPLYING WITH ABNORMAL PROCEDURES THE LT HYDRAULIC PRESSURE LOW LIGHT ILLUMINATED. THE LEFT HYDRAULIC PUMP AND TRANSFER PUMP WERE SECURED. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE HYDRAULIC REVERSIBLE PUMP LEAKING. THE PUMP WAS REMOVED AND REPLACED PER MM 29-10-07, LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: SKIN — DAMAGED (BS 427)

EWR - FLT 0611 - THE FUSELAGE SKIN WAS DAMAGED BY A BELT LOADER AT STA 427, FORWARD CARGO DOOR JAMB. THE AREA WAS REPAIRED BY INSTALLING AN EXTERNAL DOUBLER IAW ECRA 5330-02381. (X)

Part: DFG COMPUTER — INOPERATIVE (EQUIP INSTAL)

EWR - FLT 0554 - THE LANDING GEAR AURAL WARNING SOUNDED ON FINAL APPROACH TO DWR WITH 3 GREEN LANDING GEAR LIGHTS INDICATED. CHECK LIST PROCEDURES WERE C/W DURING A 'GO-AROUND' AND THE GEAR WAS VISUALLY CONFIRMED DOWN AND LOCKED. ACFT LANDED WITHOUT INCIDENT. THE PROXIMITY UNIT, GEAR/FLAP SWITCHES, AND CAWS FUNCTION ALL TESTED GOOD. INSP OF CAWS/GPWS AT COCKPIT WAS GOOD. R2-295 LG LEVER RELAY FOUND BAD. RELAY REMOVED AND REPLACED. MAINTENANCE FOUND 'NO AUTOLAND' ON NR 2 DFGC DURING SENSORS/SWITCHES TROUBLESHOOTING. UNIT FAILED RETURN TO SERVICE TEST. NR 2 DFGC REMOVED AND REPLACED. UNIT PASSED RTS TEST PER MM 22-01-01. (X)

Part: ACTUATOR — ICED UP (NLG DOOR)

EWR - FLT 0491 - A SEVERE AIRFRAME VIBRATION WAS FELT IN THE VICINITY OF THE NOSE GEAR AREA AFTER GEAR WAS RAISED. THE NOSE GEAR UNSAFE LIGHT WAS ALSO ILLUMINATED. THE AIRCRAFT WAS RETURNED TO EWR WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE RT NOSE GEAR DOOR OPEN. THE FORWARD DOOR ACTUATOR WAS FOUND CAKED WITH ICE AND ICE WAS FOUND ON THE GEAR AS WELL. THE ACTUATOR AND GEAR WERE HEATED TO MELT THE ICE. TH RT FORWARD DOOR ACTUATOR WAS LUBRICATED. THE GEAR WAS SWUNG AND OPERATION CHECKED GOOD. (X)

Part: BRACKET — CRACKED (RT WING)

HOU - INSPECTION FOUND A.75 INCH CRACK IN RIGHT WING LEADING EDGE RIB AFT BRACKET, LOCATED AT FORWARD SPAR UPPER CAP OUTBOARD OF NR 8 SLAT TRACK. A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-60-0 AND 51-30-2. (M)

Part: BRACKET — BROKEN (RT WING)

HOU - INSPECTION FOUND RIGHT WING LEADING EDGE RIB LOWER ATTACH BRACKET BROKEN OUTBOARD OF NR 2 SLAT TRACK. A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-60-0 AND 51-30-2. (M)

Part: RIB — CRACKED (LT WING LE)

HOU - INSPECTION FOUND A .625 INCH CRACK IN LOWER RADIUS OF LEFT WING LEADING EDGE RIB, LOCATED OUTBOARD OF NR 8 SLAT TRACK. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-04. (M)

Part: RIB — CRACKED (CABIN DOOR)

HOU - INSPECTION FOUND A 1.5 INCH CRACK IN RIB OF MAIN CABIN DOOR. A DOUBLER WAS INSTALLED IAW SRM 52-05. (M)

Part: STEERING — UNSECURED (NLG)

KUL - DURING TAXI OUT STEERING HAD TO MUCH PLAY. REPLACED NLG TIRES AND SECURED STEERING PER MM 32-21-04. NO FURTHER INCIDENT. (W)