N553V

ATA 5743

Part: ATTACH FITTING — CRACKED (RT MLG) · airframe 11,529 hrs · 8,397 cycles

DURING COMPLIANCE OF A 6000 MAJOR LANDING GEAR INSPECTION THE RIGHT MAIN GEAR ACTUATOR ATTACH PILLAR WAS FOUND TO HAVE A .25 INCH CRACK IN IT. THE CRACK WAS APPROXIMATELY 3.7 INCHES FROM THE MAIN GEAR ACTUATOR END OF THE PILLAR. THE CRACK WAS IN A CIRCUMFERENTIAL DIRECTION. THE CRACK WAS FOUND DURING THE NDT PART OF THE INSPECTION USING MAGNETIC PARTICLE INSPECTION. THE CRACK ONCE FOUND WAS VISIBLE USING A 10 X MAGNIFYING GLASS. THIS UNIT WAS INSPECTED 5764 LANDING PRIOR TO THIS AS PART OF A 6000 LANDING INSPECTION. THIS UNIT IS A LIFE LIMITED COMPONENT AT 18,000 LANDINGS.

ATA 1420

Part: WIRE — BROKEN (ELECTRIAL CONNEC) · airframe 11,340 hrs · 8,270 cycles

DURING COMPLIANCE OF AD 82-01-05 R2, THE TEST OF THE STALL WARNING ACCELEROMETER FAILED TO FUNCTION PROPERLY. WHEN THE ACCELEROMETER WAS ROTATED PAST THE 45 DEGREE POSITION THE PULLER WOULD NOT WORK AT ALL. IN THE PROCESS OF TROUBLESHOOTING THE SYSTEM, TWO WIRES ATTACHED TO THE CONNECTOR OF THE ACCELEROMETER WERE FOUND BROKEN LOOSE. THE WIRES WERE RESOLDERED ONTO THE CANNON PLUG AND THE SYSTEM WORKED NORMAL. PROBABLE CAUSE. THE WIRES ARE VERY SMALL, AND DUE TO THE CONTINUED TESTING OF THE SYSTEM, HAD BEEN FLEXED SO MANY TIMES THAT THE FINALLY BROKE. ADDITIONAL NOTE: IN THE PROCESS OF TROUBLE SHOOTING THIS AIRCRAFT, THE ACCELEROMETER WAS REMOVED FROM ANOTHER AIRCRAFT. DURING THAT PROCESS, A WIRE WAS BROKE

ATA 7532

Part: BLEED VALVE — STUCK (LT ENGINE) · airframe 10,830 hrs · 7,928 cycles

AFTER T/O IFR CONDITIONS, PILOT NOTICED LT ENG UNABLE TO MAINTAIN N1 POWER & ITT WAS CLOSE TO MAX. RETURNED TO BASE. MX PERFORMED GROUND RUN & WAS ABLE TO VERIFY CONDITION ON GROUND. ENG SURGE VALVE SOLENOID PACK FOUND TO HAVE WATER CONTAMINATION. ENG REMOVED ENOUGH TO GAIN ACCESS TO SURGE VALVE, VALVE FOUND STUCK IN OPEN POSITION. REASON FOR MOISTURE NOT DETERMINED. SURGE VALVE & SURGE VALVE SOLENOID PACK REPLACED WITH SERVICEABLE OVERHAULED UNITS. ALL INNER CONNECT TUBING INSPECTED FOR CONDITION, SECURITY & CONTAMINATION, AND CLEANED. ENG REINSTALLED, RUN & CHECKED ON GROUND, FOUND NORMAL. THIS SDR WILL CONTAIN INFO FOR SURGE VALVE & AN ADDITIONAL UNIT WILL BE SUBMITTED FOR SURGE VALVE SOLENOID PACK.

ATA 7532

Part: BLEED VALVE — CONTAMINATED (LT ENGINE) · airframe 10,830 hrs · 7,928 cycles

AFTER T/O IFR CONDITIONS PILOT NOTICED LT ENG UNABLE TO MAINTAIN N1 POWER & ITT CLOSE TO MAX. RETURNED TO BASE. MX PERFORMED GROUND RUN, WAS ABLE TO VERIFY CONDITION ON GROUND. ENG SURGE VALVE SOLENOID PACK FOUND TO HAVE WATER CONTAMINATION. ENG REMOVED ENOUGH TO GAIN ACCESS TO SURGE VALVE, VALVE FOUND STUCK IN OPEN POSITION. REASON FOR MOISTURE IN SURGE VALVE SOLENOID PACK NOT DETERMINED. SURGE VALVE & SURGE VALVE SOLENOID PACK REPLACED WITH SERVICEABLE OVERHAULED UNITS. INNER CONNECT TUBING INSPECTED FOR CONDITION, SECURITY & CONTAMINATION AND WERE CLEANED. ENG REINSTALLED, RUN AND CHECKED ON THE GROUND AND FOUND TO PERFORM NORMAL.

ATA 7532

Part: BLEED VALVE — DEFECTIVE (LT ENGINE) · airframe 10,763 hrs · 7,891 cycles

DURING TAKEOFF ROLL, PILOT UNABLE TO GET PROPER N1 INDICATION REQUIRED FOR TAKEOFF & ENGINE THEN STARTED ROLLING BACK ON POWER. TAKEOFF ABORTED & AIRCRAFT STOPPED WITHOUT INCIDENT. MX INSPECTED ENGINE & PERFORMED A GROUND RUN, UNABLE TO DUPLICATE PROBLEM. DEEC (DIGITAL ELECTRONIC ENGINE COMPUTER) DOWNLOADED & CHECKED. DOWNLOAD INDICATED A MOMENTARY OVERTEMP ON ITT. NO OTHER FAULTS NOTED. MODIFICATION OF SDR A COMPLETE FUNCTIONAL CHECK OF SURGE BLEED VALVE PERFORMED & UNIT FOUND TO NOT PERFORM WITHIN SPECIFICATIONS. UNIT REPLACED PER SB TFE731-76-3072. ENGINE RUN & CHECKED ON GROUND.

ATA 3232

Part: ACTUATOR — OUT OF ADJUST (RT MLG DOOR) · airframe 9,751 hrs · 7,185 cycles

AFTER TAKEOFF, THE GEAR RETRACTED NORMAL BUT RT MAIN GEAR SHOWED AN UNSAFE INDICATION. THE INBOARD GEAR DOOR DID NOT CLOSE ENOUGH TO COMPRESS THE INBOARD GEAR DOOR SWITCH. INBOARD GEAR DOOR ACTUATOR HAD BEEN RESEALED DURING A 600 HR INSPECTION PRIOR TO TAKEOFF. THE DOOR ACTUATOR REMOVED, RESEALED, REINSTALLED & OPERATIONAL CHECKED PER LEAR JET MM PRIOR TO TAKEOFF. AFTER TAKEOFF HAD UNSAFE GEAR INDICATION, RETURNED TO AIRPORT, EXTENDED THE GEAR AND GEAR EXTENDED NORMAL. AFTER RETURN ACFT WAS PLACED ON JACKS. DURING RETRACTION, MX WAS ABLE TO DUPLICATE THE INDICATION. INBOARD GEAR DOOR ACTUATOR WAS READJUSTED AND GEAR WAS AGAIN CHECKED FOR OPERATION & CHECKED NORMAL.

ATA 7120

Part: MOUNT — CRACKED (LT ENGINE) · airframe 9,140 hrs · 6,770 cycles

DURING COMPLIANCE OF RECURRING AD 87-02-06 EFFECTIVE 2-6-87, WHILE PERFORMING VISUAL INSPECTION AS REQUIRED BY PAR A (1) OF THE AD, A SUSPECTED CRACK WAS NOTED IN THE UPPER FORWARD RADIUS OF THE MOUNT. THE CRACK WAS CONFIRMED BY MAGNETIC PARTICLE INSPECTION AS REQUIRED BY PAR A (2)(B)(2) OF THE AD AND FOUND TO BE .3750 INCH LONG. THE UNIT WAS REPLACED WITH A NEW UNIT P/N 2651034-3 AS REQUIRED BY PAR A (2)(B)(1) OF THE AD. (X)

ATA 3244

Part: WEIGHT — LOOSE (NOSE WHEEL)

DURING TAKEOFF ROLL THERE WAS AN ABNORMAL VIBRATION FROM THE NOSE GEAR AT LIFT-OFF. THE AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT. THE NOSE WHEEL WAS DISASSEMBLED AND THE BALANCE WEIGHT HAD BROKEN LOOSE FROM INSIDE THE TIRE.