N686TA

ATA 7200

Part: UNKNOWN — VIBRATION · airframe 42,408 hrs · 17,012 cycles

NR 1 ENG HIGH VIBRATION DURING TAKE OFF ROLL OUT 95 KTS APROXIMATE, IAW AMM 72-21-00-210-804-A DETAILED INSPECTION AND RELUBRICATION OF THE FAN BLADES, DOVETAILS, MIDSPAN SHROUDS, SPACERS, PLATFORMS AND FAN DISK DOVETAILS SLOTS WERE PERFORMED SATISFACTORY. TSM TASK 77-00-00-810-864-A, PERFORMED STEPS 4 A (2) (B) 1, THROUGH 6. DO A CHECK AND INSPECTION OF ACCESORIES, QEC COMPONENTS , AGB MOUNTS LINKS, BRAKCETS AND SUPPORTS. WAS PERFORMED MASTER CHIP DETECTOR AND SCAVENGE SCREENS PLUGS , FOR DEBRIS , NO DISCREPANCIES FOUND, WAS PERFORMED BOOSTER ASSEMBLY AND LPT BORESCOPE INSPECTION, NO DAMAGES FOUND. PENDING TO PERFORMED MIN IDLE CHECK FOR LEAKS AND FOR VIBRATION IN ORDER TO CONTINUE TSM. IN ACCORDANCE WITH AMM 71-00-00-710-003B IDLE CHECK WAS PERFORMED, NO LEAKS FOUND. IAW AMM 77-32-34-750-001-A FAN TRIM BALANCE WAS PERFORMED. VIBRATION CHECK WAS PERFORMED. MAX VIBRATION PEAK 1.9 AT 99% N1 ALL OK.

ATA 5300

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 35,431 hrs · 13,527 cycles

DURING WALK AROUND AS PART OF THE PRELIMINARY INSPECTION OF THE AIRCRAFT FOR MAINTENANCE SERVICE, WERE FOUND 2 BROKEN FASTENERS ON RH WASTE SERVICE PANEL AND CORROSION AT LOWER AFT CORNER OF WASTE SERVICE PANEL CUT OUT. ADDITIONAL, CLAMP-SHELLS HOLDING THE WASTE DRAIN VALVE ASSEMBLY WERE BROKEN DUE TO CORROSION. AS CORRECTIVE ACTIONS, THE CORROSION WAS REMOVED, AND SERVICE PANEL REINSTALLED PER AIRCRAFT MANUFACTURER INSTRUCTIONS.

ATA 2100

Part: VALVE — INOPERATIVE (ZONE 100) · airframe 34,793 hrs · 13,262 cycles

VENT AVNCS SYS FAULT AFTER TAKEOFF PHASE AND NO OVERWEIGHT LANDING. DEFERRED SKINK AIR OUTLET VLV IAW MEL 21-26-04 CAT C REV 35 25 APR 22 MAIN FLAP´PLACED IN FULL CLOSED POS AND INTERNAL FLAP IN OPEN POS AT LWR ECAM DU THE VLV STAYS AT 45° SKIN HEAT XCHANGER ISOL VLV WAS PLACED IN OPEN POSITION AND ITS ELEC CONTROL WAS DISCONEDTED. DUE TO VENT SKIN OUTLET VALVE FAULT FOLLOWING TSM 21-26-00-810-804-A REV 65 WAS REMOVED AND REPLACED SKIN AIR OUTLET VALVE (22HQ) IAW AMM TASK 21-26-53-000-002-A REV 65 AND AMM TASK 21-26-53-400-001-A REV 65 AND PERFORMED OPERATIONAL CHECK OF SYSTEM VIA MCDU IAW AMM TASK 21-26-00-710-001-A REV 65 TEST OK CLEARED DMI/MEL.

ATA 5754

Part: SLAT — DAMAGED (LT WING) · airframe 27,665 hrs · 10,341 cycles

BIRD STRIKE ON LEFT WING DURING APPROACH. ACTION TAKEN: AS PER TSM TASK 05-50-00-810-803-A AND AMM TASK 05-51-14-200-803-A, PERFORMED INSPECTION OF THE AIRCRAFT AFTER BIRD STRIKE, AND ONLY L/H WING, SLAT #1 WAS FOUND DAMAGED, NO MORE DAMAGES FOUND. DENTS WERE EVALUATED IN A CCORDING WITH SRM TASK 57-40-283-001 LOCATED BETWEEN RIB3 AND RIB4. DENT 1 LOCATED AT SKIN AREA 2 WITH MEASURE DEPTH: 0.11 IN , LENGHT: 8.2 IN, AND WIDE: 6.25 , MINIMUM DISTANCE TO RIVET AREA IS: 0.60IN. DENT 2 IS LOCATED INN SKIN AREA 3. DEPTH:0.25 INCH WIDE: 3.2 INCH ; LENGHT: 7 INCH. MINIMUM DISTANCE TO THE RIVET LINE 0.59 INCH. NO RIVET FOUND LOOSE AND NO CRACKS WERE FOUND. DAMAGE IS ALLOWABLE. TEMPORARY REPAIR IS PERFORMED ASPER SRM 57-40-00-300-026 WICH IS VALID FOR 5000FC, 10000FH OR 24 MONTHS, THE REPAIR IS CONTROLLED UNDER HIL.

ATA 2780

Part: CONTROLLER — MALFUNCTIONED (SLAT/FLAP SYSTEM) · airframe 26,925 hrs · 10,062 cycles

AIRCRAFT HAD F/CTL SYS 2 FAULT DEFERRED ON DEC-04, THEN ON THE SAME DAY ON FLIGHT AV310 SAL-MIA SYSTEM 1 FAILS AND AIRCRAFT EMIT THE F/CTL FLAPS FAULT ECAM WARNING, WHICH LEADS THE CREW TO DECLARE EMERGENCY FOR LANDING. ONCE THE AIRCRAFT WAS ON GROUND TSM 27-81-00-810-804-A AND 27-51-00-810-836-A WERE FOLLOWED. SFCC 2 WAS REPLACED, TEST TO BOTH SFCC WERE OK AND RESTRICTED CONDITION F/CTLS FLAPS FAULT WAS CORRECTED. AIRCRAFT RETURNED TO SAL WERE SFCC 1 WAS REPLACED TO ELIMINATE THE POSSIBLITIES TO THE FAULT OCCURS AGAIN.

ATA 7200

Part: ENGINE — ABNORMAL (NR 1) · airframe 20,227 hrs · 7,336 cycles

PRIOR TO TAKE OFF, THE PILOT REPORTED THAT DURING APPLICATION OF TAKEOFF POWER, THE NR 1 ENGINE DID NOT SPOOL UP AS EXPECTED. LAGGED MORE THAN THE NR 2 ENGINE. THE AIRCRAFT RETURNED TO THE GATE, MAINTENANCE PERFORMED A FAULT ANALYSIS IAW TSM 71-00-00-810-807-A, PERFORMED ENGINE ACCELERATION TEST IAW MM 71-00-00-710-025. SATISFACTORY RESULTS, VERIFIED THE POST FLIGHT REPORT, THE FADEC LAST LEG REPORT AND THE SCHEDULED MAINTENANCE REPORT (SMR) IAW AMM 73-21-60-740-026, IN SEARCH OF ANY FAILURE MESSAGE OF PS3, ECU, HMU, FMV AND VSV. NO FAILURE MESSAGES FOUND. THE LAST TAKE OFF REPORT SHOWED ALL PARAMETERS WITHIN LIMITS. THE SENSING LINE PS3 OF THE NR 1 ENGINE WAS INSPECTED IAW AMM 72-00-00-200-026, FOUND SATISFACTORY. AFTER MAINTENANCE ACTIONS THE AIRCRAFT WAS RETURNED TO SERVICE

ATA 3610

Part: CHECK VALVE — FAULTY (BLEED AIR SYS) · airframe 15,801 hrs · 5,500 cycles

UPON ARRIVAL, THE PILOT REPORTED: "WHEN LANDING GEAR DOWN, ECAM MESSAGE BRAKES ALTN L RELEASED" MAINTENANCE PERSONNEL PERFORMED FAULT ANALYSIS AS PER TSM 32-43-00-810-824-A, PERFORMED THE OPERATIONAL CHECK TO START THE FUNCTIONAL TEST OF THE ALTERNATE BRAKING AUTOMATICALLY AS DETAILED IN AMM 32-43-00-710-002-A OBTAINING NORMAL RESULTS. THE PILOT ALSO REPORTED "DURING TAXI IN, ENG 1 FAIL MESSAGE APPEARS ON ECAM", MAINTENANCE PERSONNEL PERFORMED OPERATIONAL TEST TO FADEC 1A/1B AS PER TSM 72-00-00-810-806-A / AMM 73-29-00-710-040, ENGINE 1 MOTORING AND NON-MOTORING, NO ECAM MESSAGE WAS OBSERVED. WHILE PERFORMING BLEED TEST, THE FAIL REPORTED WAS TRIGGERED WHEN THE APU BLEED WAS SET TO "ON", SO THEN, THE ENGINE 1 IP VALVE WAS REMOVED AND REPLACED AS PER TSM 72-00-00-810-806-A / AMM 36-11-41 PB401. ADDITIONALLY WERE REPLACED THE BLEED 1 PRESSURE TRANSDUCER 8HA1 (P/N ZRA380-00, S/N ASA210163) AS PER AMM 36-11-16 PB401 / TSM 36-11-00-810-819-A AND THE PRV1 THERMOSTAT CONTROL SOLENOID 10HA1 (P/N 341F010000, S/N 10948) AS PER AMM 36-11-55 PB401 / TSM 36-11-00-810-813-A. PERFORMED OPERATIONAL TESTS AS PER AMM 71-00-00-710-006 AND 36-11-00-710-003-A WITH NORMAL RESULTS. THE AIRCRAFT WAS RETURNED TO SERVICE.

ATA 7400

Part: IGNITION SYS — FAULTED (NR 2 ENGINE) · airframe 4,252 hrs · 1,173 cycles

DURING THE DISPATCH OF FLIGHT TA311 FROM MIA TO SAL, THE PILOT REPORTED THAT THE ACFT HAD FAILURE OF ENG 2 IGNITION A FAULT, THE ACFT RETURNED TO THE GATE FOR MAINTENANCE. IT WAS VERIFIED THAT SUCH FAILURE IS DEFERRABLE IAW MEL 74-31-01 CAT C PROVIDED THAT THE IGNITIONS A & B ARE CONFIGURED IN ORDER TO MAINTAIN OPERATIVE THE IGNITION A. CONFIGURATION WAS MADE IAW AMM 74-31-00-040-005-A & TESTED THE IGNITION A IAW AMM 74-00-00-710-743 WITH NORMAL RESULTS. THE IGNITION B WAS ENTERED AS DEFERRED IAW THE MEL REFERENCE MENTIONED ABOVE. THE ACFT WAS RETURNED TO SERVICE.

ATA 2170

Part: COALESCER BAG — ODOR (CABIN AIR)

DURING DESCENT, AFTER INITIATING ENGINE ANTI-ICE, CREW NOTED A BURINING SMELL IN THE CABIN. AIRCRAFT LANDED SAFELY. MAINTENANCE COULD NOT DUPLICATE THE DISCREPANCY. THE COALESCER BAG WAS REPLACED AS A PRECAUTIONARY MEASURE.

ATA 7160

Part: INLET — CRACKED (RT ENGINE)

DURING A SCHEDULED MAINTENANCE EVENT MAINTENANCE FOUND A CRACK ON THE RT ENGINE INLET RING AT THE 12 O'CLOCK POSITION. THE CRACK IS ABOUT .25 INCH LONG. MAINTENANCE REPLACED THE INLET.

ATA 5514

Part: RIB — CRACKED (HORIZ STAB) · airframe 4,162 hrs · 3,458 cycles

CRACKED ROLLER RIB SUPPORT.

ATA 5511

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 4,162 hrs · 3,458 cycles

DURING A SCHEDULED MAINTENANCE VISIT WHILE PERFORMING A HORIZONTAL STABILIZER ROLLER BRACKET INSPECTION AS PART OF THE 'B' LEVEL INSPECTION THE LEFT INBOARD HORIZONTAL STABILIZER NOSE RIB STRUCTURE WAS FOUND CRACKED NEXT TO THE SIDE ROLLER ATTACH BRACKET. DETAILED INSPECTION INSTRUCTIONS OF THIS AREA ARE OUTLINED IN BEECHJET COMMUNIQUÉ' NUMBER 70. THE HORIZONTAL STABILIZER ASSEMBLY WAS REMOVED AND THE LEFT INBOARD LEADING EDGE ROLLER SUPPORT RIB WAS REPLACED IN ACCORDANCE WITH THE BEECHJET STRUCTURAL REPAIR MANUAL. THE HORIZONTAL STABILIZER WAS REINSTALLED TO THE AIRCRAFT. SATISFACTORY RIGGING AND OPERATIONAL CHECKS WERE COMPLETED FOLLOWING THE INSTALLATION. THE AIRCRAFT WAS RETURNED TO SERVICE.