N581P
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.
17 reports on file, 2002-11-01 – 2008-12-19.
Part: O-RING — LEAKING (AUTOFEATHER SYS) · airframe 62,897 hrs · 49,416 cycles
DURING THE TAKEOFF ROLL DEPARTING, ENROUTE, THE NR ONE ENG AUTO-FEATHERED. THE CREW ABORTED THE TAKEOFF AND RETURNED TO BASE. MX PERSONNEL OBSERVED A LARGE AMOUNT OF OIL AROUND THE FRONT OF THE PROPELLER. FURTHER INSP REVEALED A FAILED OâRING BENEATH THE FEATHER RESERVOIR CAUSING A MASSIVE OIL LEAK RESULTING IN THE AUTO-FEATHER. THE OâRING WAS REPLACED AND THE ENGINE OPERATED BY MX WITH NO LEAKS OBSERVED. THE ACFT WAS RETURNED TO SERVICE.
Part: CHANNEL — DAMAGED (FUSELAGE)
DURING A STORM A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE OF ACFT. THE RT PROPELLER WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STATIONS 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. ACFT WAS REPAIRED AND THE ACFT TEST FLOWN. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: CHANNEL — DAMAGED
DURING A STORM ON APRIL 6, 2008 A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE OF ACFT. THE RT PROPELLER WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STATIONS 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. ACFT WAS REPAIRED AND THE ACFT TEST FLOWN ON JULY 3, 2008. THE AIRCRAFT WAS RETURNED TO SERVICE JULY 8, 2008.
Part: ACTUATOR — DAMAGED (STEERING SYSTEM)
DURING A STORM IN MIA ON APRIL 6, 2008 A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE OF N581P. THE RT PROPELLER WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STATIONS 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. N581P WAS REPAIRED AND THE ACFT TEST FLOWN ON JULY 3, 2008. THE ACFT WAS RETURNED TO SERVICE JULY 8, 2008. (S)
Part: ANGLE — DAMAGED (FUSELAGE)
DURING A STORM (MIA) A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE OF N581P. THE RT PROPELLER WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STATIONS 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. N581P WAS REPAIRED AND THE ACFT TEST FLOWN ON JULY 3, 2008. THE ACFT WAS RETURNED TO SERVICE JULY 8, 2008. (S)
Part: ANGLE — DAMAGED
DURING A STORM (MIA) A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE OF N581P. THE RT PROPELLER WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STATIONS 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. N581P WAS REPAIRED AND THE ACFT TEST FLOWN ON JULY 3, 2008. THE ACFT WAS RETURNED TO SERVICE JULY 8, 2008. (S)
Part: ANGLE — DAMAGED
DURING A STORM (MIA) A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE OF N581P. THE RT PROPELLER WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STATIONS 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. N581P WAS REPAIRED AND THE ACFT TEST FLOWN ON JULY 3, 2008. THE ACFT WAS RETURNED TO SERVICE JULY 8, 2008. (S)
Part: CHANNEL — DAMAGED
DURING A STORM (MIA) A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE OF N581P. THE RT PROPELLER WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STATIONS 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. N581P WAS REPAIRED AND THE ACFT TEST FLOWN ON JULY 3, 2008. THE ACFT WAS RETURNED TO SERVICE JULY 8, 2008. (S)
Part: ACTUATOR — DAMAGED (NLG STEERING)
DURING A STORM, ON APR 6,2008, A CARGO CAN (ULB) WAS THROWN INTO THE RT SIDE. THE RT PROP WAS ALSO STRUCK A GLANCING BLOW. THERE WAS SIGNIFICANT DAMAGE TO THE SKIN AND SUPPORT STRUCTURE BENEATH THE SKIN. THERE WAS DAMAGE TO WIRING IN THE AREA. THE NOSE STEERING ACTUATOR WAS ALSO DAMAGED. DAMAGE AREA WAS BETWEEN FUSELAGE STA 72 TO 125 AT APPROXIMATELY BETWEEN STRINGERS 11 AND 3. THE PROPELLER AND REDUCTION GEARBOX WERE REMOVED AND INSPECTED. NO DAMAGE TO EITHER. AC WAS REPAIRED AND THE AC TEST FLOWN ON JULY 3, 2008. THE AC WAS RETURNED TO SERVICE JULY 8, 2008. SDR IS OPEN PENDING RECEIPT OF ADDITIONAL PN. (K)
Earlier reports · 2002–2007 · 8 reports
2007
Part: RELAY — FAILED (RT ENGINE)
ON TAKEOFF ROLL, RT ENGINE TURBINE INLET TEMPERATURE (TIT) REACHED 880 DEGREES AND BEGAN TO DETERIORATE. CREW NOTED A LOUD BANG (COMPRESSOR STALL) AND THE ENGINE SPOOLED DOWN. THE TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO BASE. SUBSEQUENT ATTEMPT TO RESTART THE ENGINE FAILED. THE ENGINE WOULD NOT ROTATE. INITIAL INSPECTION BY MAINT DID NOT INDICATE ANY OBVIOUS PROBLEM. A FURTHER DETAILED INSPECTION INCLUDING BOROSCOPE OF THE TURBINE AND VISUAL INSPECTION OF THE COMPRESSOR ALSO DID NOT INDICATE ANY PROBLEM OR DAMAGE. THE ENGINE WAS SUCCESSFULLY STARTED AND RUN AT HIGH POWER SETTINGS. WITH THE TEMPERATURE DATUM (TD) SYSTEM CIRCUIT BREAKER IN, THE ENGINE FUEL FLOW, RPM AND HORSE POWER WOULD DETERIOR
2006
Part: STRUCTURE — DAMAGED (RT NACELLE) · airframe 61,147 hrs · 48,391 cycles
ON NOVEMBER 8, 2006 WHILE EN-ROUTE, THE CREW OBSERVED A BIRD PASS CLOSE BY THE RT FUSELAGE. THE CREW NOTICED NO ABNORMAL FLIGHT CHARACTERISTICS OR ENGINE INDICATIONS AND ELECTED TO CONTINUE, WHERE THEY LANDED UNEVENTFULLY. MAINTENANCE PERSONNEL INSPECTED THE AIRCRAFT AND DISCOVERED A DAMAGED RT WING LEADING EDGE BETWEEN THE NACELLE AND FUSELAGE. THE AIRCRAFT WAS INSPECTED FOR FURTHER DAMAGE. NONE WAS FOUND. THE DAMAGED WING LEADING EDGE SECTION WAS REPLACED WITH A SERVICEABLE ONE AND THE AIRCRAFT RETURNED TO SERVICE.
Part: WING — GOUGED (WS45 LWR RT WING)
A BAGGAGE CART DISCONNECTED FROM ITS TOW VEHICLE AND IMPACTED THE AIRCRAFT IN THE AREA OF THE LOWER LT WING LEAVING GOUGES AT WING STATIONS 51.5 AND 52.5 RANGING FROM .078 TO .380 WIDE AND .016 TO .038 DEEP. THE DAMAGE WAS ACCESSED. THE DAMAGED AREA DOES NOT EXCEED THE CRITERIA DESCRIBED IN THE SRM BASED ON EDDY CURRENT INFORMATION WHICH DETERMINED THE EXACT DEPTH OF THE GOUGES. THE AREA WAS BLENDED AND A SRM REPAIR WAS PERFORMED. THE AC WAS RETURNED TO SERVICE. (K)
2005
Part: ACCESS PANEL — CRACKED (RT WING)
DURING A RECENT SCHEDULED INSPECTION, A FUEL LEAK WAS DISCOVERED ON THE LOWER RT WING NEAR THE IB FUEL TANK ACCESS PANEL. A CRACK LOCATED AT WS 8. A NEW ACCESS PANEL DOUBLER WAS INSTALLED IAW DWG. THE AIRCRAFT WAS RETURNED TO SERVICE. (K)
Part: ARM — BROKEN (MLG)
ENROUTE, CREW OBSERVED A (LANDING GEAR UNSAFE UP) INDICATION ON THE ANNUNCIATOR PANEL. THE LANDING GEAR WAS PLACED DOWN WITH ALL 3 LANDING GEAR INDICATING DOWN AND LOCKED. AC LANDED SAFELY. INSP OF RT LANDING GEAR BY THE OB MECHANIC REVEALED A BROKEN MLG ARM ASSY. ACTUATOR AND ARM ASSY WERE REMOVED AND THE HYDRAULIC LINES SECURED. AC FERRIED BACK WITH LANDING GEAR DOWN AND PINNED. MLG ACTUATOR AND MLG ARM WERE REPLACED WITH SERVICEABLE UNITS AND AC WAS RETURNED TO SERVICE. (K)
2004
Part: TIRE — DEPARTED (MLG)
MFD - DURING PILOT TRAINING, AIRPORT MX CREWS NOTICED ONE OF THE TIRES MISSING OFF THE AIRCRAFT AS IT TAXIED BY WHILE ON THE TAXI-WAY. THE MX CREW NOTIFIED THE TOWER WHO IN TURN NOTIFIED CRW. THE AIRCRAFT TAXIED TO THE TARMAC AREA AND SHUTDOWN. THE MX AND INSPECTION DEPARTMENT WERE NOTIFIED BY THE CRW THAT THE NR 2 MAIN LANDING GEAR TIRE AND WHEEL ASSY WAS GONE. A MX CREW WAS DISPATCHED FOM THE COLUMBUS, OH MX BASE. FURTHER EXAMINATION BY THE MAINTENANCE CREW DETERMINED THAT THE OUTER BEARING HAD SEIZED WHICH RESULTED IN THE TIRE AND WHEEL ASSY SPINNING OFF THE AXLE. THE NR 1 TIRE AND WHEEL ASSY WERE REMOVED AND THE AXLE WAS INSPECTED BOTH VISUALLY AND WITH DYE PENETRANT. THERE WAS NOT DAMAGE TO THE AXLE
2002
Part: ACTUATOR — SEPARATED (NLG)
AFTER TAKEOFF, ENROUTE, THE PILOT HEAR A POP OR SNAP AFTER RAISING THE LANDING GEAR. THERE WERE NO OTHER ABNORMAL INDICATIONS IN THE COCKPIT AND THE FLIGHT WAS CONTINUED AND TERMINATED. THE LANDING WAS LOWERED UNEVENTFULLY. DURING THE POSTFLIGHT INSPECTION, THE PILOT FOUND THAT THE NOSE LANDING GEAR ACTUATOR HAD BROKEN OFF THE NOSE LANDING GEAR WHERE IT ATTACHES TO THE GEAR. THE AIRCRAFT WAS FERRIED TO MAINTENANCE BASE WITH LANDING GEAR DOWN. WHERE THE NOSE LANDING GEAR WAS REMOVED AND REPLACED. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: WIRE — LOOSE (FLIGHT DIRECTOR)
WHILE EN ROUTE FROM CVG-PIT, THE CAPTAIN NOTICED A MOMENTARY PUFF OF SMOKE COMING FROM THE FLIGHT DIRECTOR. THE FLIGHT DIRECTOR FUSELAGE WAS REMOVED AND THE FLIGHT WAS CONTINUED UNEVENTFULLY AND TERMINATED IN PIT. A LOOSE POWER WIRE ON THE FLIGHT DIRECTOR CONNECTOR PLUG HAD ARCED MOMENTARILY AGAINST THE PLUG SHELL. THE WIRE WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE. NO FURTHER ACTION IS REQUIRED AT THIS TIME. REFER TO AIR TAHOMA LOG PAGE NR 64108. FLIGHT DIRECTOR P/N FD108. (M)