N95AG
Registered owner: ALJ AVIATION LLC, DE (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
14 reports on file, 2008-12-02 – 2012-05-30.
Part: SWITCH — FAILED (THRUST REVERSER) · airframe 9,706 hrs · 6,715 cycles
AFTER LANDING, THE LEFT THRUST REVERSER DEPLOYED AND STOWED SEVERAL TIMES BEFORE FINALLY STAYING DEPLOYED.
Part: SENSOR — FAILED (ENGINES) · airframe 9,706 hrs · 6,715 cycles
APPROXIMATELY 45 MINUTES INTO FLIGHT, BOTH ENGINE STACKS (N1, ITT, N2 AND WF) ROLLED BACK AND FORTH FOR SEVERAL MINUTES THEN OCCASSIONALLY FLUCTUATED DURING REST OF FLIGHT.
Part: ENGINE — SURGES (LEFT) · airframe 9,616 hrs · 6,657 cycles
LEFT ENGINE SURGED ABOUT 5 PERCENT N1 SHORTLY AFTER TAKEOFF (TO APPROX 100%) WHILE THE THRUST LEVER WAS IN MCT THEN RETURNED TO NORMAL. POWER WAS BROUGHT BACK TO MCR AND THE LT ENGINE N1 BUG STARTED TO FLUCTUATE FROM 95% TO 92%. LT ENGINE N1 NEEDLE AND RT ENGINE N1 NEEDLE BUGS WERE STEADY AT 95%. LT BUG EVENTUALLY STOPPED FLUCTUATING AFTER A COUPLE MINUTES, FLIGHT CONTINUED NORMALLY.
Part: ENGINE — POWER LOSS (LEFT) · airframe 9,610 hrs · 6,653 cycles
DURING CLIMBOUT, APPROX 8 MIN INTO FLIGHT, THE LT ENGINE ROLLED BACK ABOUT 4 PERCENT WHILE IN MCR WITH THE SYNC ON. APPROX 1 MIN LATER THE LT AMBER ENGINE COMP LIGHT CAME ON. ENGINE INDICATION RETURNED TO NORMAL AFTER CHANGING POWER SETTING. LIGHT WENT OUT AFTER POWER WAS TAKEN OFF THE AIRCRAFT WHEN SHUTTING DOWN.
Earlier reports · 2008–2011 · 10 reports
2011
Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 9,389 hrs · 6,523 cycles
THE LEFT AMBER T/R "UNLOCK LIGHT" ILLUMINATED NUMEROUS TIMES DURING THE DESCENT AND CAME ON STEADY DURING THE APPROACH PHASE.
Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 9,379 hrs · 6,516 cycles
THE RIGHT AMBER T/R UNLOCK LIGHT ILLUMINATED NUMEROUS TIMES DURING THE ARRIVAL PHASE OF FLIGHT.
Part: UNKNOWN — MALFUNCTIONED (UNKNOWN) · airframe 9,362 hrs · 6,503 cycles
APPROXIMATELY 38 MINUTES INTO FLIGHT, AT FL410, HEARD A MODERATELY LOUD BOOM NOISE COMING FROM THE BACK LEFT SIDE OF THE AIRCRAFT, FELT A MINOR YAW MOMENT AND OBSERVED THE LEFT ENGINE STACK INCREASE SLIGHTLY THEN RETURN TO NORMAL. FLIGHT CONTINUED WITH NO FURTHER ANOMALIES.
Part: WARNING LIGHT — ILLUMINATED (THRUST REVERSER) · airframe 9,240 hrs · 6,421 cycles
THE RT THRUST REVERSER AMBER UNLOCK LIGHT ILLUMINATED AFTER TAKEOFF.
2010
Part: CAM FOLLOWER — DAMAGED (NLG)
NLG UPLOCK BRACKET CONTACTING SWITCH PLUG UPON RETRACTION INTO THE WHEEL WELL. NLG LOWER FORK NOTICED TO BE 5 DEGREES LT OF MECHANICAL CTR. SERVICED STRUT WITH NO CORRECTION TO 5 DEGREE DIFFERENCE. DISASSEMBLY OF STRUT REVEALED LOCK PIN GROOVE ON LOWER CAM TO BE ROTATED 5 DEGREES FROM POSITION NECESSARY TO NULL STRUT MECHANICALLY TO THE -0- DEGREE POSITION.
2009
Part: PUMP — FAILED (HYD SYSTEM)
LT HYD PUMP FAILED IN FLIGHT. (K)
Part: PUMP — FAILED (HYDRAULIC SYS) · airframe 8,022 hrs · 5,569 cycles
DURING PART 91 REPOSITIONING LEG FROM PDK TO FXE, CREW HEARD A LOUD NOISE FROM LEFT SIDE OF AIRCRAFT WHILE IN CRUISE. NOISE QUIT AFTER 10 MINUTES AND LOW HYD PRESS LIGHT ILLUMINATED. CREW DIVERTED TO PBI AS IT HAD A LONGER AVAILABLE RUNWAY THAN FXE. INSPECTION REVEALED THAT THE LEFT HYDRAULIC PUMP HAD FAILED. REPLACED LEFT HYDRAULIC PUMP WITH OVERHAULED UNIT AND RETURNED AIRCRAFT TO SERVICE. NOTE: REMOVED HYDRAULIC PUMP WAS LAST REPAIRED BY PARKER HANNIFIN ON 4/18/2008 THEN INSTALLED ON THIS AIRCRAFT ON 5/19/2008. REASON FOR LAST REPAIR GIVEN AS "LEAKING AT CASE DRAIN"
Part: SEAL — FROZEN (AILERONS) · airframe 7,863 hrs · 5,462 cycles
DURING CLIMB WITH AUTOPILOT ENGAGED PASSING FL340 THE PFD INDICATED AN AILERON MISTRIM ANNUNCIATION. AFTER DISCONNECTING THE A/P, THE CREW NOTED THAT THE AILERONS FELT STIFF. THE CREW STOPPED THE CLIMB AT FL350, RAN THE APPROPRIATE CHECKLISTS, AND DECLARED AN EMERGENCY. THE FLIGHT WAS DIVERTED FROM OKC TO BNA. WHILE PASSING FL230, THE CAPTAIN NOTICED THE FLIGHT CONTROLS "SNAPPED LOOSE" AND THEN APPEARED TO BE WORKING NORMALLY FROM THEN ON. MAINTENANCE FOUND THE AILERON BRUSH SEALS SATURATED WITH WATER. BLEW OUT WATER WITH DRY NITROGEN AND LUBRICATED SEALS. PERFORMED CHECK OF AILERON SYSTEM. NO INTERFERENCE NOTED. PERFORMED FLIGHT TEST. NO DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE.
2008
Part: EEC — FAILED (NR 1 ENGINE)
LT ENGINE FAILED ABOUT 10-15 MINUTES INTO FLIGHT AT FL190. THE CREW REPORTED HEARING A BOOM AND THE 1ST OFFICER NOTICED THE LT ENGINE ROLL BACK. AN AIR START WAS NOT ATTEMPTED AND THE ACFT DIVERTED. REPLACED EEC WITH REPAIRED UNIT. PERFORMED GROUND RUNS AND THE TEST FLIGHT. ACFT RETURNED TO SERVICE. MFG SUSPECTS ONE CHANNEL OF THE EEC DEVELOPED A FAULT AND ATTEMPTED TO CHANGE CHANNEL. THE EEC HAS A LANE-CHANGE RELAY, WHICH IS AN ELECTROMECHANICAL RELAY (AND NOT A SOLID STATE RELAY AS IN THE NEWER EEC`S) WHICH HAS A TENDENCY TO STICK OR TOO SLOW TO SWITCH CONTACTS. WHEN THIS TYPE OF FAILURE OCCURS NEITHER CHANNEL IS IN CONTROL OF THE FUEL FLOW AND FLAMEOUT WILL OCCUR. THIS TYPE OF FAILURE WILL GENERATE A 4C CODE WHICH WAS OBSERVED ON THIS ENGINE. (K)
Part: EEC — FAILED (LT ENGINE)
LT ENG FAILED ABOUT 10-15 MINUTES INTO FLIGHT AT FL190. CREW REPORTED HEARING A BOOM AND THE 1ST OFFICER NOTICED THE LT ENGINE ROLL BACK. AN AIR START WAS NOT ATTEMPTED AND THE ACFT DIVERTED. REPLACED EEC WITH REPAIRED UNIT. PERFORMED GROUND RUNS AND TEST FLIGHT. AC RETURNED TO SERVICE. THIS ENG IS PRE SB 24-434 (EEC). SUSPECTS ONE CHANNEL OF THE EEC DEVELOPED A FAULT AND ATTEMPTED TO CHANGE CHANNEL. THE EEC HAS A LANE-CHANGE CHANEL. THE EEC HAS A LANE-CHANGE RELAY, WHICH IS AN ELECTROMECHANICAL RELAY (AND NOT A SOLID STATE RELAY AS IN THE NEWER EEC`S) WHICH HAS A TENDENCY TO STICK OR TO TOO SLOW TO SWITCH CONTACTS. WHEN THIS TYPE OF FAILURE OCCURS NEITHER CHANNEL IS IN CONTROL OF THE FUEL FLOW AND FLAMEOUT WILL OCCUR. THIS TYPE OF FAILURE WILL GENERATE A 4C CODE WHICH WAS OBSERVED ON THIS ENGINE. (K)