N656AF
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.
8 reports on file, 2010-01-09 – 2013-11-13.
Part: STRUCTURE — DAMAGED (LT WING TE FLAP) · airframe 6,337 hrs · 6,047 cycles
LEFT FLAP HAD DAMAGE THAT REQUIRED MAJOR REPAIR. THE FLAP WAS REPAIRED AND SKIN REPLACED USING THE SRM 12-A-57-50-00-00A-664B-A,12-A-51-40-03-00A-041A-A,12-A-57-50-00-00A-664C-A,AND 12-A-51-20-00-00A-663A-A.
Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 6,279 hrs · 5,988 cycles
LEFT FLAP SKIN DAMAGED. THE INNER SKIN PANEL WAS REPLACED WITH A FACTORY NEW PANEL IAW SRM 12-A-51-40-03-00A-041A-A.
Part: MOTOR — FAULTY (COMPRESSOR) · airframe 4,638 hrs · 4,440 cycles
VCCS SYS REPORTED AS INOPERATIVE, FANS BLOWING BUT AIR IS NOT COLD. THE VCCS COMPRESSOR MOTOR WAS FOUND FAULTY AND WAS R & R WITH SERVICEABLE UNIT OF THE SAME PN 959-90-22-126, IAW CMM 21-00-23 AND AMM 12-A-21-50-01-00A-920B-A.
Part: ATTACH FITTING — OUT OF ALIGNMENT (HORIZONTAL STAB) · airframe 4,630 hrs · 4,430 cycles
THE HORIZ STABILIZER ATTACHMENT FITTING, WHERE THE PITCH TRIM ACTUATOR IS SECURED TO THE STABILIZER. EACH SIDE OF THE ATTACHMENT FITTING HAS 2 LUGS. ON THE LT SIDE, THESE 2 LUGS ARE SEPARATING. THE GAP WAS MEASURED WITH A FEELER GUAGE, AND FOUND TO BE .406MM. THERE IS NO EVIDENCE OF DAMAGE TO THE STABILIZER. THE BRACKET PN IS 555.10.12.150, ANGLE FITTING LEFT. THE ACFT MFG ISSUED A REPAIR MEMO WITH STATEMENT OF APPROVED DESIGN DATA (ECC-12-RM-11-182) WITH THE FOLLOWING INSTRUCTIONS: CHECK THE LUGGED FACE OF THE LT BRACKET PN 555.10.12.150 (ANGLE FITTING LT) FOR STRAIGHTNESS. IF WITHIN LIMITS, COMPLETE A VISUAL AND NDT INSP (DYE PENETRANT OR EDDY CURRENT) OF THE ANGLE FITTING AND THE BOLTS. IF NO CRACKS OR DEFECTS NOTED, REINSTAL1 THE FITTING AND HARDWARE USING SEALANT.
Part: FUEL CONTROL — FAILED (ENGINE) · airframe 3,830 hrs · 3,567 cycles
DURING DESCENT, ENGINE POWER ROLLED BACK & NO RESPONSE WITH POWER CONTROL LEVER. CREW DECLARED AN EMERGENCY, PERFORMED EMERGENCY CHECKLISTS & ATTEMPTED TO UTILIZE MANUAL OVERRIDE LEVER (MOR) TO PROVIDE FUEL TO ENGINE. ITT INDICATION BEGAN TO RISE QUICKLY DUE TO LIMITED NG SPEED, CREW ELECTED TO STOW MANUAL OVERRIDE LEVER (MOR) & SECURE ENGINE. DIVERTED & MADE AN UNEVENTFUL LANDING WITH ENGINE SHUTDOWN. INITIAL TROUBLESHOOTING POINTS TOWARD AN INTERNAL FCU OR INTERNAL PROPELLER GOVERNOR ISSUE AS NO EXTERNAL P3 LEAKS WERE DETECTED. AFTER INSPECTING THE ENGINE MX ATTEMPTED TO START ENGINE & DETERMINED IT WOULD START BUT NOT ACCELERATE PAST MINIMUM FUEL FLOW. TROUBLE SHOOTING CONTINUED AND THE FUEL CONTROL UNIT WAS ULTIMATELY REPLACED. ENGINE STARTED & ACCELERATED NORMALLY.
Part: BRAKE DISC — BROKEN (MLG BRAKE) · airframe 3,544 hrs · 3,318 cycles
DURING A LINE CHECK THE LT MAIN BRAKE OTBD BRAKE DISC WAS DISCOVERED BROKEN. R & R BRAKE ASSEMBLY IAW MM.
Part: BRAKE DISC — BROKEN (MLG) · airframe 3,450 hrs · 3,233 cycles
DURING A 100 HR INSP, DISCOVERED THE RT BRAKE OTBD DISC WAS BROKEN INTO 2 PIECES. REMOVED AND REPLACED BRAKE ASSY IAW MM INSTRUCTIONS.
Part: DRAG LINK — CRACKED (NLG DOOR) · airframe 3,450 hrs · 3,233 cycles
DURING NDT INSP OF NLG RT DRAG LINK PN 532.20.12.289 IAW AMM 12-A-32-20-06-00A-313A-A AND AD 09-14-13 A CRACK INDICATION WAS DETECTED IN THE PRESCRIBED NDT INSPECTION AREA. REMOVED RT DRAG LINK AND INSTALLED AN UPGRADED DRAG LINK PN 532.20.12.296 IAW SRM AND AD 09-14-13.