N826AA

ATA 5310

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 19,641 hrs · 17,641 cycles

DURING "A" CHECK INSPECTION FOUND 2 CRACKS ON CARGO DOOR FRAME AT THE AFT SCISSOR ASSY AREA.

ATA 7200

Part: ENGINE — FLAMED OUT (NR 1)

NR 1 ENG FAILED (FLAMED OUT) AT 36,300 FT IN CLIMB TO 36,500 FT. CREW ATTEMPTED RE-LIGHTS AT 29,000, 24,000, AND 19,000 TO NO AVAIL. CREW DECLARED EMER, RETURNED TO DEPART, LANDED WITHOUT INCIDENT. AC WAS IN EXPERIMENTAL CONFIGURATION FOR RVSM TESTING. MAINT INSPECTED THE NR 1 ENG FOR FOD, WITH NO DEFECTS NOTED. FLAMEOUT INSP WAS PERFORMED IAW MM. OVERSPEED GOVERNOR WAS REPLACED DUE TO LEAKING. T2 SENSE LINE WAS REPLACED DUE TO BEING CRUSHED. LEAK AT THE FUEL FLOW TRANSMITTER WAS REPAIRED BY RESEALING. ENGINE WAS RUN, LEAK AND OPERATIONAL CHECKS SHOWED NO DEFECTS. NR 1 ENG FLAMED OUT DURING TEST. RETURNED, LANDED WITHOUT INCIDENT. ENGINE WAS REPLACED, RUN UP WITH NO DEFECTS, AC RETURNED TO SERVICE.

ATA 7314

Part: FUEL PUMP — INOP (NR 2 ENGINE)

YIP - NR 2 ENGINE FLAMED OUT WHILE CLIMBING THROUGH FL325. ENGINE RELIT AT FL290, FLIGHT CONTINUED AT FL270. NO EMERGENCY PROCEDURES WERE NECESSARY. MAINTENANCE PERFORMED ENGINE RUN AND FOUND ENGINE NOT RESPONDING CORRECTLY TO THROTTLE MOVEMENT. MAINTENANCE REMOVED AND REPLACED FCU AND FUEL PUMP WITH O/H UNITS IAW SEI 187. MAINTENANCE PERFORMED ENGINE RUN, OPS CHECK AND LEAK CHECK IAW SEI 189. NO DEFECTS NOTED. THE AIRCRAFT WAS TEST FLOWN TO PERFORM ACCELERATION CHECK AT FL350. THE AIRCRAFT PASSED CHECK AND WAS RETURN TO SERVICE. (M)

ATA 7321

Part: FUEL CONTROL — INOP (NR 2 ENGINE)

YIP - NR 2 ENGINE FLAMED OUT WHILE CLIMBING THROUGH FL325. ENGINE RELIT AT FL290, FLIGHT CONTINUED AT FL270. NO EMERGENCY PROCEDURES WERE NECESSARY. MAINTENANCE PERFORMED ENGINE RUN AND FOUND ENGINE NOT RESPONDING CORRECTLY TO THROTTLE MOVEMENT. MAINTENANCE REMOVED AND REPLACED FCU AND FUEL PUMP WITH O/H UNITS IAW SEI 187. MAINTENANCE PERFORMED ENGINE RUN, OPS CHECK AND LEAK CHECK IAW SEI 189. NO DEFECTS NOTED. THE AIRCRAFT WAS TEST FLOWN TO PERFORM ACCELERATION CHECK AT FL350. THE AIRCRAFT PASSED CHECK AND WAS RETURN TO SERVICE. (M)

ATA 7260

Part: CARBON SEAL — FAILED (LEFT ENGINE)

YIP - PERFORMED PRECAUTION ENG SHUT DOWN NR 2 ENG DUE TO FLUCT OIL PRESS AND FLICKERING OIL PRESS LIGHT. A/C CONTINUED TO YIP. A/C WAS FLOWN UNDER SPECIAL FLT PERMIT, AFTER FAILURE OF NR 2 GEN WHERE GEN DRIVE SPLINES AND THE ACCY GEARBOX AXIS 'C' SPLINES FOUND WORN BEYOND LIMITS. THE START/GEN HAD BEEN REPLACED PRIOR TO FERRY FLT AND WAS OPS CHECKED OK FOR OPERATION AND NO LEAKS NOTED. MX FOUND THE AFT AXIS 'C' (GEN) DRIVE GEAR CARBON SEAL CRACKED IN 3 PLACES, ALLOWING OIL TO LEAK FROM GEARBOX. THE AFT AXIS 'C' DRIVE SPLINES WERE ALSO EXCESSIVELY WORN REQUIRING REPLACEMENT OF DRIVE GEAR. THE AFT AXIS 'C' DRIVE GEAR BEARING APPEARS WORN ALTHOUGH, THE FWD 'C' DRIVE GEAR BEARING APPEARS SERVICEABLE. THE GEA

ATA 2721

Part: RUDDER TRIM — MALFUNCTIONED (EMPENNAGE)

YIP - FLT 18779 - DURING DESCENT INTO YIP, THE RUDDER TRIM RAN AWAY FULL RIGHT AND CIRCUIT BREAKER TRIPPED. THE AIRCRAFT CONTINUED ON TO LANDING AT ITS INTENDED DESINATION AT YIP. CORRECTIVE ACTION: COULD NOT DUPLICATE. OPS CHECKED RUDDER TRIM SYSTEM BY OPERATION OF RUDDER TRIM SWITCH THROUGH ITS ENTIRE TRAVEL RANGE. OPS CHECKED NORMAL. NO DEFECTS NOTED. THE AIRCRAFT RETURNED TO SERVICE. (X)

ATA 2711

Part: TRIM CONTROL BOX — FAILED (E/E COMPT)

MCI - FLT 18713 - AILERON TRIM RAN AWAY FULL LEFT AND CIRCUIT BREAKER TRIPPED. RESET CIRCUIT BREAKER EMERGENCY/ABNORMAL CHECK LIST FOLLOWED BY CREW. APPROACH AND LANDING WERE NORMAL, AIRCRAFT WAS CONTROLLABLE. CORRECTIVE ACTION: THE TRIM SYSTEM WAS ACTUATED NUMEROUS TIMES WITHOUT REPEAT OF THE FAILURE IN THE TRIM SYSTEM. REMOVED AND REPLACED TRIM CONTROL BOX, AS A PRECAUTION, AND PERFORMED COMPLETE OPS CHECK IAW FALCON MM 27-10-00. OPS CHECK NORMAL. NO DEFECTS NOTED. AIRCRAFT WAS RETURNED TO SERVICE. (X)

ATA 7711

Part: EPR SENSE LINE — LEAKING (RT ENGINE)

ELP - FLT 18389 - TAKEOFF ABORTED WHEN RIGHT ENGINE DID NOT MAKE EPR DURING TAKEOFF ROLL. NO EMERGENCY PROCEDURES REQUIRED. FOUND EPR SENSE HOSE LEAKING IN RIGHT ENGINE NACELLE. A NEW HOSE WAS INSTALLED AND THE ENGINE WAS RUN-UP. A POWER ASSURANCE CHECK WAS PERFORMED IAW USA JET AIRLINES WORK CARD P001R. NO DEFECTS WERE NOTED. (X)

ATA 5320

Part: RIVETS — WORN (SKIN DOUBLER)

DURING INSPECTION, THE AIRCRAFT WAS FOUND TO HAVE SEVERAL RIVETS LOOSE IN THE AREA OF THE SKIN DOUBLER, INSTALLED AS PART OF THE CABIN DOOR, STC SA2490S0. FURTHER INSPECTION REVEALED DEFECTIVE 'UPSET' HEADS ON MANY OF THE RIVETS INSTALLED DURING THIS MODIFICATION. FOUND NO EVIDENCE OF STRUCTURAL FAILURE. SUBMITTER FEELS THIS IS A CASE OF IMPROPER INSTALLATION TECHNIQUE DURING THE MODIFICATION. TO CORRECT THIS, THE DEFECTIVE RIVETS WERE REMOVED AND REPLACED WITH NEW. SUBMITTER'S ESTIMATION IS THAT APPROXIMATELY 30 PERCENT OF THE TOTAL NUMBER OF RIVETS USED TO ATTACH THIS DOUBLER REQUIRED REPLACEMENT. (X)