N59764
Registered owner: WARBELOWS AIR VENTURES INC, AK (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| WRIGHT AIR SERVICE INC (HYTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
AFTER COMPLETING ROUTINE LANDING, PILOT NOTED THAT THE LT ENGINE WAS RUNNONG ROUGH ON GROUND WITH HIGH MANIFOLD PRESSURE AND THE LT FUEL FLOW INDICATED ZERO IN FLIGHT WHEN LEANED. ON INVESTIGATION, THE LEFT ENGINE CYLINDER NR 4 EXHAUST VALVE SEAT WAS DISLODGED AND WAS PREVENTING THE EXHAUST VALVE FROM CLOSING. THE PISTON WAS GOUGED BY THE PARTIALLY OPEN EXHAUST VALVE AND A PORTION OF CYLINDER MATERIAL WAS MISSING BETWEEN THE SPARK PLUG HOLE AND THE DISLODGED VALVE SEAT. THIS ENGINE HAS BEEN INSTALLED SINCE APRIL 21, 2015 AND HAD ACCRUED 166.4 HOURS SINCE OVERHAUL.
PILOT WAS ON APPROACH AND NOTICED GEAR UNSAFE LIGHT FAILED TO EXTINGUISH ON GEAR DOWN SELECTION. GREEN LIGHT ALSO FAILED TO ILLUMINATE FOR NOSE LANDING GEAR. PILOT DIVERTED & LANDED WITHOUT INCIDENT. MX ENSURED GEAR WAS LOCKED AND TOWED TO HANGAR FOR INSP AND FOUND THE LANDING GEAR DOWNLOCK SWITCH TO BE INOPERATIVE. REPLACED SWITCH, PN 487-862 IAW SRM 7-36; SWUNG GEAR MULTIPLE TIMES WITH GOOD RESULTS. SUBSEQUENT OPS CHECK-FLIGHT GOOD - ACFT RETURNED TO SERVICE.
EXCESSIVE CAM LOBE WEAR IS CAUSING POWER LOSS AND EARLY REMOVAL OF SEVERAL OF OUR ENGINES. THIS ENGINE WAS REMOVED AT 1650.2 TTSO WITH 549.8 REMAINING ON OUR 2200HR O/H INTERVAL. HAVE BEEN IN CONTACT WITH MFG TECH SUPPORT FOR AN EXTENDED PERIOD OF TIME NOW NAD HAVE YET TO FIND A SOLUTION. IT SEEMS THAT FOR SOME REASON USUALLY ONE CAM FOLLOWER WILL BECOME "PITTED" AND BEGIN TO ACCELERATE WEAR ON THE LOBE THAT IT RIDES ON. NO IDEA WHAT IS CAUSING THE PITTING OR HOW TO PREVENT IT. WE USE ONLY FACTORY REMANUFACTURED ENGINES IN OUR ENTIRE FLEET.
ON 24 MAR 04, AC DEPARTED, AT APPROX 50 MILES FROM DEPARTURE, PILOT NOTICED A LOSS OF MANIFOLD PRESSURE AND A LOSS OF OIL PRESSURE ON THE LT ENGINE, FEATHERED THE LT PROPELLER, SHUT DOWN THE LT ENGINE AND RETURNED TO DEPARTURE. A MAINTENANCE INSPECTION REVEALED THAT THE LT OIL COOLER HAD RUPTURED, LEAKING OIL FREELY. MAINT HAS ELECTED TO REPLACE THIS ENGINE.
ON APPROACH, ON 10 NOVEMBER 2003, THE PILOT NOTICED FUEL FLOW FLUCTUATIONS AND AN ABRUPT LOSS OF OIL PRESSURE ON THE LT ENGINE AND IMMEDIATELY SHUT THE ENGINE DOWN. PILOT CONTINUED FLIGHT AND LANDED SAFELY WITHOUT FURTHER INCIDENT. PILOT IMMEDIATELY REPORTED THIS PROBLEM TO MAINTENANCE, WHO CAME IMMEDIATELY TO INVESTIGATE THE REPORTED DEFICIENCY. THE MECHANIC DISCOVERED THAT BOTH CASE HALVES WERE CRACKED IN THE VICINITY OF THE SHARED INTAKE CAME LOBE FOR NR 3 AND NR 4 CYLINDERS. FURTHER INVESTIGATION IS NECESSARY TO DETERMINE THE EXACT NATURE OF THE FAULT. WE ARE PROVIDING THIS AMENDMENT TO HELP EXPLAIN THE REASONS BEHIND THE SDR REPORT DATED 11/12/03 REGARDING THE ENGINE PROBLEMS. PURCHASED THIS ENGINE
PILOT RETURNED FROM FLIGHT AND NOTIFIED MAINTENANCE OF AN OIL LEAK ON THE LEFT ENGINE. IT WAS DISCOVERED THAT A LEAK WAS COMING FROM NR 2 CYLINDER EXHAUST PUSHROD TUBE. WHEN THE TUBE WAS REMOVED A CRACK WAS FOUND APPROXIMATELY 4 INCHES FROM THE CYLINDER END. THE CRACK STARTED AT A DENT IN THE TUBE WHICH SEEMS TO BE FROM SHIPPING DAMAGE. AS THIS ENGINE WAS NOT SHIPPED IN STANDARD CRATE SUCH AS THE MFG USES. THE PART WAS REMOVED AND REPLACED.
DURING INSPECTION A LARGE PIECE OF CAST ALUMINUM WAS FOUND IN THE SUCTION SCREEN. THE ODD BANK OF CYLINDERS WERE REMOVED TO LOOK FOR DAMAGE. NR 6 CONNECTING ROD CAP WAS OBSERVED TO BE SCUFFED. SEVERAL ACCESSORIES WERE REMOVED AND NO DAMAGE WAS NOTED IN THE ACCESSORIES SECTION. ENGINE WAS REMOVED AND REPLACED TEAR DOWN REPORT PENDING.
DURING INSPECTION METAL CONTAMINATION WAS DISCOVERED IN THE OIL FILTER. A CHECK OF VALVELIFT WAS DONE AND IT WAS DISCOVERED THAT NR5 AND NR6 INTAKE LOBES WERE EXCESSIVE. NR6 CYLINDER WAS REMOVED AND DAMAGE OBSERVED ON THE CAM LOBES AND TAPPET FOLLOWERS. NOTE: THIS IS THE 17TH ENGINE IN THREE YEARS.
PILOT REPORTED HEATER INOPERATIVE. UPON INSPECTION, FOUND FUEL PRESSURE REGULATOR LEAKING. UNIT WAS REPLACED, OPS GOOD.
DURING INSPECTION, BOTH CYLINDERS NR 1 AND NR 2 HAD LOW COMPRESSION. UPON REMOVING CYLINDERS INTAKE LOBES OF CAMSHAFT HAD EXTREME WEAR. THE TAPPET FACES WERE ALSO SPALLED. OVER PAST YEAR, THERE HAS BEEN FOUR SIMILAR PROBLEMS. SUBMITTER SUSPECTED PROBLEM IN MANUFACTURING PROCESS. (X)
DURING A DETAILED INSPECTION OF THE LANDING GEAR, THIS PART WAS FOUND TO HAVE A SMALL CRACK. THIS PART CONNECTS THE HYDRAULIC ACTUATOR TO THE FORWARD SIDE BRACE WHICH EXTENDS AND RETRACTS THE LANDING GEAR. THE WEIGHT OF THE GEAR AND THE SPEED OF MOVING THE GEAR UP AND DOWN EVENTUALLY FATIGUES PARTS. SUBMITTER STATED RECURRENCE CANNOT BE AVOIDED. (X)
PILOT RETURNED TO BASE CITING ENGINE FAILURE. ENGINE WOULD NOT START WHEN ATTEMPTED ON GROUND. FURTHER INVESTIGATION REVEALED THE DUAL MAGNETO EXPERIENCED TOTAL BEARING FAILURE. MAGNETO WAS REPLACED AND A FULL GROUND RUN AND LEAK CHECK ACCOMPLISHED. GROUND CHECK APPEARS NORMAL. NOTE: SEVERAL SINGLE ENGINE AIRCRAFT ALSO USE THIS DUEL MAGNETO.
OIL BLOWING OUT BREATHER. FOUND NR 1 CYLINDER AT 10/80. PULLED CYLINDER AND FOUND COMP. RINGS BROKEN IN MANY PIECES ABOUT .25 INCH TO 2.5 INCH. THESE RINGS ARE OF WRONG COMPOSITION. (BRITTLE).