N625VA

Part: UNKNOWN — ODOR (CABIN) · airframe 39,076 hrs · 11,847 cycles

NOXIOUS SMELL DEVELOPED ON DESCENT THROUGHOUT ENTIRE CABIN. GROUNDED - YES. ACCOMPLISHED ENG 1, 2 CHECK. FLT CREW RAN PACK 1 &2 ONE AT A TIME & APU BLEED. NO SMELL NOTICED IAW TSM 05-50-00-810-831A.

Part: CONTROL UNIT — FAILED (THRUST REVERSER)

ABORTED TAKE OFF DUE TO A NR 2 THRUST REVERSER FAULT. THE ACFT RETURNED TO THE GATE. R & R HYDRAULIC CONTROL UNIT IAW AMM 78-31-51. NO FURTHER REPORTS ON SUBSEQUENT FLIGHTS.

Part: CONTROL UNIT — FAILED (HYD SYSTEM)

THE FLIGHT CREW REPORTED AN ABORTED TAKEOFF DUE TO A NR 2 THRUST REVERSER FAULT. THE ACFT RETURNED TO THE GATE. R & R HYDRAULIC CONTROL UNIT IAW AMM 78-31-51.

Part: COMPRESSOR — SEIZED (AIR CON SYS)

UNUSUAL AND UNKNOWN ODOR EMITTING THROUGHOUT ACFT. PERFORMED TSM 05-50-00-810-831-A AND DETERMINED ODOR EMITTING FROM AIR COMPRESSOR. THE AIR COMPRESSOR HAS BEEN ISOLATED. NO FURTHER ODOR, ODOR HAS DISSIPATED. WATER COMPRESSOR WAS DEACTIVATED. REPLACED THE COMPRESSOR.

Part: SEAL — DAMAGED (OXYGEN SYSTEM)

COCKPIT OXYGEN ADVISORY CAME ON IN FLIGHT AT APPROXIMATELY 580 PSI. AT 540 PSI, DIVERTED. RESET COCKPIT OXYGEN MASKS AND COCKPIT OXYGEN WAS STABLE AT 530 PSI. 20 MINUTES OUT, NOTICED THE COCKPIT OXYGEN AT 480 PSI. COCKPIT OXYGEN WAS APPROXIMATELY 760 PSI. CREW DECLARED AN EMERGENCY AND DIVERTED. PERFORMED TROUBLESHOOTING AND FOUND A SMALL LEAK FROM THE CONNECTION OF THE FLEX HOSE TO THE THIRD OCCUPANT BOX AND MUCH BIGGER AT THE CONNECTION OF CAPTAIN`S FLEX HOSE TO THE T FITTING DUE TO DAMAGED SEALS. REPLACED THE SEALS IAW AMM 35-12-41-04. OPS AND LEAK CHECKED GOOD. REMOVED, SERVICED AND REINSTALLED CREW OXYGEN BOTTLE IAW 1059 AND AMM 35-11-41-04. LEAK AND OPS CHECKED GOOD.

Part: NUT — MISSING (THRUST REVERSER)

NR 2 ENGINE EXPERIENCED A THRUST REVERSER UNLOCK ECAM MESSAGE, NO ACFT BUFFETING. FOLLOWED THE FCOM PROCEDURES AND SHUTDOWN THE ENGINE. RETURNED TO DEPARTURE. DURING TROUBLESHOOTING FOUND 2 OF THE 4 MOUNT BOLT NUTS MISSING ON THE THRUST REVERSER HOOK LATCH. REPLACED THE THRUST REVERSER ASSY. ACFT RETURNED TO SERVICE.

Part: SLIDE — UNWANTED DEPLOY (R2 DOOR)

ACFT WAS IN FOR SCHEDULED OVERNIGHT MX. PRIOR TO DEPARTURE, THE FOLLOWING MORNING, AND AFTER ARMING ALL DOORS, THE ITM NR3 WAS ADVISED THAT THE SAFETY STRAP WAS CLOSED IN THE R2 DOOR. SHE WENT TO OPEN THE DOOR TO GET THE SAFETY STRAP AND INADVERTENTLY DEPLOYED THE SLIDE. IAW THE MX CALLED TO THE ACFT, IT APPEARED TO BE A FULL SLIDE DEPLOYMENT. IT WAS NOTED THAT THE STAINLESS STEEL CABLE THAT IS NORMALLY SECURED BY A VELCRO STRAP TO THE SLIDE PACK CAME OUT OF THE VELCRO UPON THE INITIATION OF THE SLIDE DEPLOYMENT AND BECAME CAUGHT ON A METAL TAB ON THE BACK SIDE OF THE SLIDE BUSTLE. THIS SEEMED TO PREVENT THE DOOR FROM GOING TO THE FULL OPEN AND LOCKED POSITION EVEN THROUGH THE SLIDE WAS FULLY DEPLOYED. THE CABLE CAUSED A 6 INCH TEAR OF THE COMPOSITE BUSTLE DURING THE ACTION. THE DEPLOYED R2 DOOR SLIDE WAS REMOVED AND A SERVICEABLE SLIDE WAS INSTALLED. PN OFF D31516-417 AND SN ON L21274.

Part: SKIN — DENTED (FUSELAGE)

A DENT WAS DISCOVERED ON THE AFT CTR FUSELAGE LOWER SKIN BETWEEN FR63 AND FR64, RANGING FROM STR 43L TO STR 41R. THE DENT MEASURED APPROX 12" IN LENGTH, OVERLAPPING THE AFORE MENTIONED STRINGERS. THE UNDERLYING STRINGERS 43L, 43R, 42R AND 41R WERE UNDAMAGED. INTERNAL DETAILED VISUAL AND HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS FOUND NO CRACKING IN THE STRINGERS. THE DAMAGED FUSELAGE SKIN WAS CUT OUT AND REPAIRED IAW SRM 53-00-11, FIG 209 AND 53-00-11, FIG 217. FIG 217 WAS REFERENCED DUE TO THE CLOSE PROXIMITY OF THE REPAIR TO THE STR 40R LAP JOINT AND FR64 BUTT JOINT.