N556UP
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| AMERIFLIGHT, LLC (JIKA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
Maintenance disclosures
MAINTENANCE DISCREPANCY: THE PILOT REPORTED WHILE IN CRUISE FLIGHT THAT THE L\H ENGINE CHIP DETECTOR LIGHT ILLUMINATED. THE PILOT FOLLOWING PROCEDURES PERFORMED AN IN-FLIGHT SHUT DOWN OF THE LEFT ENGINE. THEN THE PILOT DECLARED AND EMERGENCY AND REQUESTED TO RETURN TO THE DEPARTURE AIRPORT. THE PILOT AND CREW LANDED IN KLAN WITHOUT FURTHER INCIDENT AND TAXIED TO PARKING. MAINTENANCE INSPECTED THE LEFT ENGINE MAGNETIC CHIP DETECTOR AND FOUND METAL FUZZ AND ONE SMALL SLIVER. MAINTENANCE PERFORMED A CHIP DETECTOR DEBRIS INSPECTION AND NO FURTHER DEFECTS WERE NOTED. MAINTENANCE ACQUIRED A S.O.A.P. SAMPLE AND SENT FOR EVALUATION. THEN THE AIRCRAFT WAS RETURNED TO SERVICE WITH A 10 FLIGHT HOUR RE-INSPECT MAINTENANCE CONSTRAINT. A SUPPLEMENTAL REPORT WITH FINAL CORRECTIVE ACTION WILL HAVE TO BE SUBMITTED.
THE PILOT REPORTED DURING CRUISE, THAT BOTH HYDRAULIC PRESSURE WARNING LIGHTS ILLUMINATED, FOLLOWED BY HYDRAULIC PRESSURE BEGINNING TO FLUCTUATE. THE PILOT DECLARED AN EMERGENCY AND MANUALLY EXTENDED THE LANDING GEAR AND PERFORMED A ZERO FLAPS LANDING WITHOUT INCIDENT. MAINTENANCE INSPECTED THE HYDRAULIC SYSTEMS AND FOUND THAT THE NOSE WHEEL STEERING ACTUATOR HAD FAILED. THE PISTON CAP ON THE LEFT SIDE OF THE ACTUATOR HAD PULLED THE THREADS OUT OF THE CAP AND ALLOWED HYDRAULIC PRESSURE TO BE RELEASED. THERE WERE SIGNS OF CORROSION ON THE THREADED AREA. REMOVED AND REPLACED THE NOSE WHEEL STEERING ACTUATOR. MAINTENANCE REMOVED AND REPLACED BOTH HYDRAULIC PUMPS AND SERVICED THE HYDRAULIC SYSTEM WITH FLUID AND PERFORMED GEAR SWINGS AND OPERATIONAL CHECKS. THE AIRCRAFT WAS RELEASED FOR AN OPERATIONAL CHECK FLIGHT AND THE OPERATION OF THE HYDRAULIC SYSTEMS WERE NORMAL.
DURING DESCENT, BOTH LT & RT HYD PRESS ANNUNCIATORS ILLUMINATED. THE INDICATION WAS BACKED UP BY THE HYD PRESS GAUGE INDICATING 0 PSI. DUE TO THE LOSS OF HYD POWER & WEATHER CONDITIONS THE ACFT WAS DIVERTED. PERFORMED A MANUAL EXTENSION OF THE LG & LANDED WITHOUT INCIDENT. INSPECTION REVEALED A CRACK IN FLAP UP LINE IN LT NACELLE. REPLACED THE CRACKED HYD LINE IN LT NACELLE WITH NEW LINE & REPLACED BOTH ENG DRIVEN HYD PUMPS. SERVICED SYS & PERFORMED OPERATIONAL CHECKS OF THE HYD SYS, ALL CHECKS WERE NORMAL.
THE PILOT REPORTED THAT BOTH LT & RT HYD FAILURE LIGHTS ILLUMINATED, WHILE THE HYD PRESS GAUGE WAS FLUCTUATING. UNABLE TO EXTEND THE FLAPS PAST THE ¼ POSITION. WHEN THE PILOT PUT THE GEAR HANDLE TO THE DOWN POSITION THE LG DID NOT EXTEND & THE HYD SYS PRESS GAUGE INDICATED ZERO. THE PILOT PERFORMED A MANUAL GEAR EXTENSION IAW AMF PROCEDURES & RECEIVED A LG DOWN & LOCKED INDICATION. THE ACFT LANDED WITHOUT INCIDENT. TROUBLE SHOOTING REVEALED A LEAKING FLAP UP HYD LINE PN 27-81006-029 IN LT WW. REPLACED THE FLAP UP HYD LINE WITH A NEW FABRICATED LINE IAW AMM. PERFORMED FLAP SYS LEAK & OPERATIONAL CHECKS, ALL CHECKS WERE SATISFACTORY.
DURING APPROACH PILOT NOTICED A LOSS OF HYD PRESS. PILOT PERFORMED EMER CHECKLIST PROCEDURE ITEMS & MANUALLY EXTENDED LG. PILOT LANDED WITHOUT FURTHER INCIDENT. TROUBLESHOOTING REVEALED A PIN HOLE IN THE FLAP UP LINE AT HYD POWER PACK. REPLACED THE FLAP UP HYD LINE, PERFORMED LEAK & OPERATIONAL CHECKS OF HYD SYS ALL CHECKS WERE NORMAL.
DURING CLIMB OUT PILOT NOTICED A DROP IN HYD PRESS ON GAUGE NEAR ZERO, ALSO NOTICED BOTH HYD FAIL ANNUNCIATOR LIGHT ILLUMINATED. PILOT DECIDED TO RETURN, PILOT PERFORMED EMER CHECKLIST ITEM THAT INCLUDED MANUALLY EXTENDING LG. PILOT LANDED WITHOUT FURTHER INCIDENT. TROUBLESHOOTING REVEALED A PIN HOLE IN THE FLAP UP LINE IN LT WW. FABRICATED NEW LINE PN 27-81032-135. PERFORMED HYD SYS FUNCTIONAL CHECKS, ALL SYS CHECKS WERE NORMAL.
DURING CLIMBOUT CROSSING 7,000 MSL, PILOT NOTICE A LIGHT HAZE ACROSS AVIONICS. PILOT TURNED ON INTERIOR LIGHTS AND NOTICED A HAZE VAPOR FROM THE COCKPIT TO THE REAR CARGO BAYS. PILOT ISOLATED THE ISSUE BY TURNING OFF THE RADAR AND BLEED AIR SYSTEM. RETURNED TO DEPARTURE. MAINTENANCE PERFORMED ENGINE RUN WITH ACFT SYSTEM IN SAME CONFIGURATION AS IN FLIGHT AND DISCOVERED ACM WATER SEPARATOR DIRTY AND SOAKED. CLEANED WATER SEPARATOR PERFORMED GROUND OPS CHECK AND OPS CHECK FLIGHT ALL OPS CHECKS GOOD.
ENGINE CONTROL CABLE RUBBED THRU ON THE 90 DEGREES ANGLE FLANGE BY THE TOP OF THE LEFT NACELLE INBOARD SIDE. THIS CAP IS PART OF MAIN STRUCTURE OF THE NACELLE. FOUND AFTER UPPER NACELLE SKIN WAS REMOVED FOR REPAIR OF THE NACELLE.