N113DA

Part: SUPPORT FITTING — CORRODED (LT WING) · airframe 62,481 hrs · 29,470 cycles

THE HOLE BORES FOR THE FLAP ATTACMENTS ON THE INBD SUPPORT FITTING ON THE LT INBD FLAP ON THE LT WING WERE FOUND CORRODED. THE CORROSION WAS REMOVED BY OVERSIZING THE BORES, HFEC INSPECTION, INSURANCE REAM, AND INSTALLATION OF ALUMINUM BUSHINGS PER ER/A 384975-14, REV B.

Part: SUPPORT FITTING — CORRODED (LT WING TE FLAP) · airframe 62,473 hrs · 29,466 cycles

THE ATTACH HOLE BORES FOR THE INBD FLAP, OUTBD SUPPORT FITTING ON THE LT WING WERE FOUND CORRODED WITH ADDITIONAL CORROSION ON THE FACES OF THE LUGS. THE HOLE BORES WERE OVERSIZED TO CLEAN UP THE CORROSION, HFEC INSPECTED, INSURANCE REAMED, AND ALUMINUM BUSHINGS INSTALLED. THE FACES WERE LIGHTLY SPOT FACED TO REMOVE THE CORROSION. THE REPAIR WAS ACCOMPLISHED PER ER/A 384974-14.

Part: MODULE — LEAKING (RT MLG WW) · airframe 61,774 hrs · 29,108 cycles

A/C 113 LOST C-SYS HYDRAULIC QUANTITY INFLIGHT. A/C WAS INBOARD TO ATL. FOUND RAT TEST MODULE IN RT W/W LEAKING. REPLACED SAME.

Part: FAN — FAILED (CABIN) · airframe 59,816 hrs · 28,164 cycles

EICAS MSG INFLT - RT RECIR FAN, ALONG WITH INOP LIGHT IN RT RECIR FAN SWITCH. REPLACED RT RECIRC FAN, OP CKS GOOD.

Part: MONITOR — FAULTY (HYD SYSTEM) · airframe 59,669 hrs · 28,088 cycles

AFTER T/O, RIGHT HYD QTY WENT TO ZERO, ATB. FOUND RIGHT HYD QTY IND INOP. NO ASSOCIATED LOW PRESS LIGHTS REPLACED MONITOR AND TRANSMITTER PER M/M, OP CHECKED NORMAL. REMOVED MCO/PLA.

Part: PANEL — FAULTY (COCKPIT) · airframe 58,075 hrs · 27,263 cycles

DURING TROUBLESHOOTING OF OVERWING SLIDE DOOR SQUIB TEST, SQUIBS WERE INADVERTANTLY FIRED. REPLACED SQUIB PANEL

Part: MEC — DEFECTIVE (NR 2 ENGINE) · airframe 58,068 hrs · 27,258 cycles

NR 2 ENGINE SHUT DOWN BY CREW ON APPROACH TO PBI. DURING CRUISE NOTICED RT THROTTLE/ENGINE WAS NOT RESPONDING TO MOVEMENT, COMMAND BAR WAS PRESENT. DURING DESCENT GOT EICAS R ENG SPEED CARD. REPLACED ENGINE MEC.

Part: CONTROLLER — INOPERATIVE (NR 2) · airframe 55,882 hrs · 26,280 cycles

CABIN WILL NOT PRESSURIZE IN AUTO 1 OR AUTO 2. REPLACED NR 2 CABIN PRESS CONTROLLER AND CONTROL PANEL. RAN SELF TEST ALL NORMAL. FWD NBR 1 SYS TO MCO AND PLAC PER MEL 21-31-01A

Part: SKIN — DENTED (FUSELAGE) · airframe 55,815 hrs · 26,253 cycles

FUSELAGE SKIN AT STA 1480-1502, STR 24R TO 29R, PERMANENT REPAIR WAS ACCOMPLISHED FOR EXISTING SKIN REPAIR. REFERENCEERA 396597-14.

Part: SKIN — DENTED (FUSELAGE) · airframe 55,815 hrs · 26,253 cycles

FUSELAGE SKIN REPAIR AT STA 566-573 AND STR 35L-36L, ERA 396471-14 ISSUED TO REPAIR DENT DAMAGE (DUE TO GROUND DAMAGE)

Part: BULKHEAD CHORD — CRACKED (BS 1809.5)

FUSELAGE BULKHEAD FS 1809.5, LBL 45 OUTER CHORD, CRACK REPAIR. THE FS 1809.5 BULKHEAD OUTER CAP WAS FOUND WITH A TYPICAL CRACK AT LBL 45. THE CRACK IS TYPICAL OF BAC S/B 767-53-0078. THE CRACKED SECTION OF CHORD WAS REMOVED AND A NEW SECTION SPLICED IN PER THE S/B AND ER/A 368414-14.

Part: HOSE — FAILED (RT MLG)

RIGHT MAIN GEAR TRUCK TILT HYD HOSE BURST. A/C DECLARED EMERGENCY AND LANDED WITHOUT INCIDENT. FOUND HYDRAULIC HOSE TO TRUCK TILT ACTUATOR BURST. REPLACED HOSE. SERVICED SYSTEM, LEAK CHECKS NORMAL.

Part: AIR DIST — SMOKE (CABIN)

F/A REPORTED SMOKE IN AFT CABIN. UPON DISCONNECTING UTILITY BUSES ODOR/SMELL WENT AWAY. RESET UTILITY BUSES OPERATED ALL GALLEY EQUIPMENT, NO ODOR PRESENT. RAN PACK RECIRC FANS AND GASPER FANS, TURNED ON ALL LIGHTS AND VIDEO EQUIPMENT AND NO TROUBLE FOUND.

Part: SKIN — CORRODED (CENTER WING)

CORROSION DAMAGE WAS FOUND DURING ROUTINE INSPECTION OF THE CENTER WING UPPER SKIN OVERLYING THE REAR SPAR. CORROSION WAS LOCATED AT LBL 68 NEAR THE DRAIN AT LBL 75. REPAIRED PER ERA 332134-14.

Part: FLOORBEAM — CORRODED (BS 835-910)

CORROSION WAS FOUND ON THE UPPER CAP OF THE RBL 33 LONGITUDINAL OVERWING FLOORBEAM BETWEEN FS 835 AND 910. A SECTION OF UPPER CAP WILL BE REPLACED WITH A SPLICE REPAIR ON EACH END OF THE REPLACEMENT SECTION. REPAIRED PER ERA 332139-14.

Part: WEDGE — DELAMINATION (NR 5 LE SLAT)

THE UPPER SKIN OF THE LT WING NR 5 SLAT WAS FOUND WITH A 1 INCH DIAMETER AREA OF DELAMINATION. THE DAMAGE WAS REPAIRED PER B767 SRM 57-43-02 AND DOCUMENTED PER ER/A 364049-14AD.

Part: WEDGE — DELAMINATED (NR 8 LE SLAT)

THE UPPER SKIN OF THE RT WING NR 8 SLAT TRAILING EDGE WEDGE WAS FOUND WITH A 4 X 2.5 AREA OF DELAMINATION. THE DAMAGE WAS REPAIRED PER THE B767 SRM 57-43-02 AND DOCUMENTED PER ER/A 364048-14AD.

Part: BATTERY — DISCHARGED (CABIN)

JUMPSEAT TWO CENTER FLASHLIGHT RED LIGHT NOT FLASHING. REPLACED BATTERY AND BULB ASSY.

Part: SKIN — DELAMINATED (NR 11 LE SLAT)

TWO AREAS OF DELAMINATION WERE FOUND ON THE UPPER SKIN OF THE NR 11 SLAT T/E WEDGE. ONE AREA OF DELAMINATION WAS FOUND ON THE UPPER SKIN OF THE NR 12 SLAT T/E WEDGE. NO CORE DAMAGE OCCURRED ON ANY OF THE DAMAGE. THE DAMAGE WAS REPAIRED PER B767-200 SRM 57-43-02, FIGURE 201.

Part: IDG — MALFUNCTIONED (NR 1 ENGINE)

FORTY-FIVE MINUTES OUT OF SAN JUAN, GOT LEFT GENERATOR DRIVE LIGHT WITH 'L' IDG OIL TEMP STATUS MSG. DISCONNECTED CSD. STARTED APU, BUT APU GENERATOR BREAKER WOULD NOT PUT GENERATOR ON LINE. RETURNED TO SJU. REPLACED LEFT GCU AND IDG. LEAK AND OPS CHECK GOOD.

Part: BATTERY — DISCHARGED (RT SLIDE)

SQUIB TEST 1 THE LEFT LIGHT DOES NOT COME ON FOR SLIDE. SQUIB TEST 2 THE RIGHT LIGHT DOES NOT COME ON FOR SPOLILER. REPLACED RIGHT HAND OVER WING SLIDE BATTERY ASSEMBLY. SYSTEM SQUIB TEST CHECKS AS PER M/M. .

Part: EEL POWER SUPPLY — INOPERATIVE (CABIN)

POWER SUPPLY FOR ESCAPE PATH LIGHTING FAILED TEST DURING LAYOVER AT TOC. REPLACED POWER SUPPLY UNIT (P/N 333780100), CLEARED BY LOG BOOK ITEM.

Part: SKIN — DELAMINATED (NR 8 LE SLAT)

THE NR 8 L/E SLAT T/E WEDGE WAS FOUND TO HAVE UPPER SKIN DELAMINATED. REPAIRED PER DL ERA 272443-14AD.