N920DC
Registered owner: SPECIALIZED DRONE SOLUTIONS LLC, KY (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
No NTSB accidents or incidents on file for this aircraft.
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, 1999-09-21 – 2006-11-01.
Part: PITOT TUBE — BLOCKED · airframe 5,142 hrs · 1,968 cycles
NR 1MADC HAD AN ALTITUDE COMPARATOR AT 15000 FT AND A 400 FT SPLIT FROM MADC AND STDBY AT FL230. IT ALSO HAD A 5 CKAS SPLIT IN AIRSPEED. BLOCKAGE FOUND IN LT UPPER PITOT/STATIC PROBE, OF UNKNOWN ORIGIN. BLEW OUT STATIC LINES USING DRY NITOGEN. INSTALLED NEW LT UPPER PITOT PROBE IAW GAC CMP CODE 341102. PERFORMED PITOT/STATIC SYSTEM RECONNECT CHECKS IAW GAC CMP CODE 341030. AIRCRAFT RETURNED TO SERVICE.
Part: ACTUATOR — FROZEN (AILERON) · airframe 4,946 hrs · 1,903 cycles
AILERON TRIM WILL NOT TRIM/MOVE RIGHT WING DOWN. THE AILERON TRIM ACTUATOR MOUNTED ON THE FORWARD SIDE OF THE AILERON WAS REPLACED WITH A TNO 0 ACTUATOR. THE TRIM SYSTEM WAS RIG AND OPERATIONALLY CHECKED PER CHPT 27 OF THE G-V MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: EEC — MALFUNCTIONED (LT ENGINE) · airframe 4,715 hrs · 1,818 cycles
DURING CRUISE, THE LEFT ENGINE ROLLED BACK AND FLAMED OUT. EICAS MESSAGE -LEFT ENGINE FAILED- DISPLAYED. UNSCHEDULED LANDING MADE. THE LT ENGINE ELECTRONIC ENGINE CONTROLLER (EEC) WAS FOUND TO HAVE VARIOUS FADEC SYSTEM FAULTS WHEN INTERROGATING THE MDAU. THE EEC WAS REPLACED. ENGINE OPS CHECKED NORMAL, AIRCRAFT RETURNED TO SERVICE. THE FAILED EEC SOFTWARE VERSION WAS G7.02. GULFSTREAM ASC 157 WAS INCORPORATED AND AN EEC WITH SOFTWARE VERSION G9.1 WAS INSTALLED. THIS, I BELIEVE, MAY BE THE FIRST TIME A GV ENGINE ROLLED-BACK TO FLAME OUT DUE TO EEC FAILURE. THIS IS UNACCEPTABLE. THE FAA SHOULD PURSUE AIRWORTHINESS DIRECTIVE INVESTIGATION ON THESE EECS.
Earlier reports · 1999–2004 · 11 reports
2004
Part: FASTENER — CORRODED (MAIN ENTRY)
CORROSION FOUND ON FASTENERS UNDER MAIN ENTRANCE DOOR SEAL AT THE HINGE AREA. DISSIMILAR MATERIAL CORROSION BETWEEN THE HUCK FASTENERS AND THE SURROUNDING COMPOSITE STRUCTURE. REPLACED HUCK FASTENERS WITH RECOMMENDED FASTENERS FROM THE MANUFACTURE. AIRCRAFT WAS RETURNED TO SERVICE.
Part: EEC — FAULTY (RT ENGINE)
RT ENGINE ROLLED BACK AFTER TAKE OF ABOUT 20 PERCENT. SWITCHED DAU NR 1 TO CH B AND ENGINE, OK. TROUBLESHOOTING REVEALED A FAULTY NR 2 EEC (ELECTRONIC ENGINE CONTROLLER). INSTALLED A SERVICEABLE EEC IAW MDG MM AND PERFORMED ENGINE OPERATIONAL CHECKS. ALL PARAMETERS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE.
Part: EEC — FAULTY (RT ENGINE)
RT ENGINE ROLLED BACK AFTER TAKEOFF, ABOUT 20 PERCENT. SWITCHED DAU NR 1 TO CHANNEL B AND ENGINE OK. TROUBLESHOOTING REVEALED A FAULTY NR 2 EEC (ELECTRONIC ENGINE CONTROLLER). INSTALLED A SERVICE EEC IAW MFG MM AND PERFORMED ENGINE OPERATIONAL CHECKS. ALL PARAMETERS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE.
Part: EEC — INOPERATIVE (RT ENGINE)
RT ENGINE ROLLED BACK AFTER TAKE OFF ABOUT 20 PERCENT. SWITCHED DAU NR 1 TO CH. B AND ENGINE OK.
Part: EEC — FAULTY (RT ENGINE)
DURING CLIMB, RT ENGINE ROLLED BACK AFTER TAKE OFF ABOUT 20 DEGREES. SWITCHED DAU NR 1 TO CHANNEL B AND ENGINE OK. TROUBLESHOOTING REVEALED A FAULTY NR 2 EEC (ELECTRONIC ENGINE CONTROLLER). INSTALLED A SERVICEABLE EEC IAW MFG MM AND PERFORMED ENGINE OPERATIONAL CHECKS. ALL PARAMETERS NORMAL.
2003
Part: PITOT HEAD — DAMAGED (PITOT/STATIC SYS)
DURING THE SCHEDULED FLIGHT BETWEEN STUTTGART AND BASEL, THE FLT CREW NOTED THE ALTIMETERS HAVE AN OUT OF TOLERANCE 'SPLIT' BETWEEN THE NR 1 AND NR 2 SYSTEMS. THE NR 1 PITOT/STATIC PROBES WERE DAMAGED, CAUSING INACCURATE READINGS IN THE NR 1 SYSTEM. THE UPPER LT AND LOWER RT PITOT/STATIC PROBES WERE CHANGED PER CHAPTER 34 OF THE GV MM. THE SYSTEM WAS CHECKED FOR ACCURACY PER THE GV MM AND FOUND TO BE WITHIN TOLERANCE. ALL RVSM MAINTENANCE WAS PERFORMED PER THE AAR RVSM MX PROGRAM. THE AIRCRAFT WAS RETURNED TO SERVICE. (M)
Part: ACTUATOR — MALFUNCTIONED (RUDDER)
UNUSUAL NOISE COMING FROM RUDDER ACTUATOR DURING MANUAL OPERATION. RUDDER QUADRANT BELLCRANK RUBBING ON CABLE GUIDE. SUPPORT MOUNT HOLE TOO BIG FOR PIVOT BUSHING. GULFSTREAM RESEARCHING REASON FOR DEFECT. (M)
Part: CONTROLLER — FAILED (AUTOTHROTTLE SYS)
AUTOTHROTTLE 2 NUMEROUS INTERMITTENT FAILURES. FOUND NO FAILURES REPORTED IN MDUA FAULT HISTORY. OPERATIONALLY CHECKED AUTOTHROTTLE SYSTEM CHANNELS 1 AND 2 IAW CMP CODE 223005 SEVERAL TIMES WITH NO FAILURES NOTED. AIRCRAFT WAS RETURNED TO SERVICE.
Part: LINE — CRACKED (PNEUMATIC SYS)
WHILE PERFORMING THE ELEVATOR HARD OVER PROTECTION TEST, FOUND THE ELEVATOR DISCONNECT HANDLE GUIDE FOR THE PNEUMATIC ASSIST TO BE CRACKED. THE ELEVATOR DISCONNECT HANDLE ASSY WAS REPLACED, APPROPRIATE OPERATIONAL CHECKS PERFORMED PER THE G-V MM AND THE AIRCRAFT RETURNED TO SERVICE. (M)
2001
Part: CLIP — SHEARED (BRAKE ROTOR)
NR 1 BRAKE, OUTBOARD ROTOR, DRIVE CLIPS FAILED AND SHEARED OFF THE ROTOR. EIGHT(8) SHEARED OFF OUT OF SIXTEEN (16) TOTAL PER ROTOR. CAUSE: THE CARBON FIBER ROTOR MATERIAL, FAILED. BRAKE WAS REPLACED WITH OVERHAULED UNIT. NO OTHER DAMAGE WAS NOTED. AIRCRAFT RETURNED TO SERVICE.
1999
Part: MONITOR — FAILED (CABIN)
CABIN COMPARTMENT AFT TV SCREEN CAUGHT FIRE DURING TAXI FOR TAKEOFF. FORWARD GALLEY HALON FIRE EXTINGUISHER USED TO PUT OUT FLAME. SUBMITTER STATED AT THIS TIME, THE CAUSE OF THE MONITOR FAILURE IS UNDETERMINED.