- Registered owner
- Fly2mellc
- Location
- Ooltewah, TN
- Owner type
- LLC
- Serial number
- 668
- Year built
- 1974
- Type
- Fixed wing multi engine
- Engine
- Turbo-prop
- Airworthiness
- Experimental, research and development
- Airworthiness date
- September 13, 2012
- Certificate issued
- May 9, 2026
- Expires
- May 31, 2033
- Mode S code
- A63B3E
From the FAA registry file of October 24, 2026.
On this page
Airworthiness directives that may apply · 59
Matched by this aircraft’s airframe and engine models. Each AD’s applicability may narrow it by serial number, part number or equipment.
| 1974 | 2 |
|---|---|
| 1975 | 3 |
| 1976 | 1 |
| 1978 | 1 |
| 1979 | 2 |
| 1980 | 3 |
| 1982 | 2 |
| 1983 | 1 |
| 1984 | 4 |
| 1986 | 3 |
| 1987 | 1 |
| 1988 | 2 |
| 1989 | 2 |
| 1991 | 1 |
| 1993 | 4 |
| 1994 | 3 |
| 1995 | 2 |
| 1996 | 1 |
| 1997 | 2 |
| 1998 | 4 |
| 2000 | 3 |
| 2002 | 1 |
| 2003 | 3 |
| 2004 | 1 |
| 2005 | 2 |
| 2006 | 6 |
| 2007 | 1 |
| 2010 | 1 |
| 2011 | 1 |
| 2015 | 2 |
| 2016 | 3 |
| 2018 | 3 |
| 2021 | 1 |
See all 75 ADs
Information bulletins that may apply · 3
Advisory, not mandatory.
Airframe · Mitsubishi MU-2B-36
SAIB CE-19-09Wing Miscellaneous StructureSAIB CE-12-33Landing Gear Retraction/Extension System, Nose Landing GearEngine · Alliedsign TPE331-6
SAIB NE-16-18Power Lever Loss of Power ControlNTSB investigations
No NTSB investigations matched to N500PJMatched by N-number and event date, checked against the reported serial number, make and model. Investigations from before this aircraft carried the mark are under Earlier aircraft. Investigations on Mitsubishi MU-2B-36 aircraft
FAA incident reports
No FAA accident or incident reports matched to N500PJMatched by N-number and event date, checked against the reported make and model. Reports from before this aircraft carried the mark are under Earlier aircraft. Reports on Mitsubishi MU-2B-36 aircraft
Service difficulty reports · 9
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
SDR 2003FA0000840Tire · failedUPON LANDING, THE TIRE DISINTEGRATED. ASSURE THE TIRE WAS FLAT ON LANDING, DUE TO RUNWAY FOD ON TAKEOFF.SDR 99ZZZX2364Valve · damagedHIGH PRESSURE RELIEF VALVE BODY, P/N 867927-1, WAS STILL IN FUEL PUMP HOUSING, BUT THE WRENCHING FLATS AND CAP OF RELIEF VALVE WERE FOUND HANGING FROM SAFETY WIRE CAUSING FUEL TO BE SPRAYED ON ENGINE. FUEL COULD ONLY BE STOPPED BY SHUTTING OFF AIRFRAME SUPPLYSDR 98ZZZX2640Wheel · failedINNER WHEEL HALF EXPERIENCED A BEARING FAILURE. FAILURE RESULTED IN BRAKE DISC RUBBING INTO BRAKE ASSEMBLY REQUIRING BRAKE ASSEMBLY REPLACEMENT. INNER WHEEL HALF ALSO REQUIRED REPLACEMENT DUE TO CRACKING AROUND BEARING AREA.SDR 97ZZZX4686Tire · separatedLEFT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE FOR APPROXIMATELY 10 INCHES. OCCURRED ON LANDING. TIRE REMAINED INFLATED. THIS WAS ONE OF THREE SIMILAR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT MU-2'S. TIRE WAS RETURNED TO MFG FORSDR 97ZZZX2637Tire · separationLEFT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE FOR APPROXIMATELY 10 INCHES. OCCURRED ON LANDING. TIRE REMAINED INFLATED. THIS WAS ONE OF 3 SIMILAR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT MU-2'S. TIRE WAS RETURNED TO MFG FOR EVASDR 97ZZZX4687Tire · separatedRIGHT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE COMPLETELY AROUND CIRCUMFERENCE. OCCURRED ON LANDING. TIRE REMAINED INFLATED. TREAD STAYED ATTACHED AROUND OUTBOARD EDGE CIRCUMFERENCE. THIS WAS ONE OF THREE SIMILAR OCCURRENCES WITHISDR 97ZZZX2636Tire · separationRIGHT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE COMPLETELY AROUND CIRCUMFERENCE. OCCURRED ON LANDING. TIRE REMAINED INFLATED. TREAD STAYED ATTACHED AROUND OUTBOARD EDGE CIRCUMFERENCE. THIS WAS ONE OF THREE SIMILAR OCCURRENCES WITHISDR 95ZZZX6838Frame · crackedFRAME 4610, LEFT, CRACKED THROUGH SCREW HOLES APPROXMATELY 31MM BELOW LOWER HOLE. ALL 6 STATIONS HAD TO BE SHIMMED PER SB 209A.SDR 95ZZZX2304Window · crackedDURING A POST-INSPECTION WALK-AROUND, A CRACK WAS NOTED EXTENDING APPROXIMATELY 1 INCH INTO THE VISIBLE AREA OF THE OUTER WINDOW IN THE CREW EMERGENCY ESCAPE DOOR. WHEN WINDOW RETAINERS WERE REMOVED, A CRACK 16 INCHES LONG CONNECTING 11 BOLT HOLES ACROSS THE
STCs that may be installed · 190
Approved for this aircraft’s airframe or engine model. The registry doesn’t record which STCs an aircraft has; its records do.