Summit Helicopters, Inc.

Operated by Summit Helicopters, Inc. (per NTSB report)

The pilot’s improper fuel planning and fuel management, which resulted in a total loss of engine power due to fuel exhaustion and subsequent impact with terrain during an autorotation.

Operated by SUMMIT HELICOPTERS INC (per NTSB report)

A partial loss of engine power due to the failure of the No. 2 engine accessory gearbox bearing for reasons that could not be determined based on the available information.

Operated by SUMMIT HELICOPTERS INC (per NTSB report)

The pilot's encounter with a settling with power condition while he was performing slow, low-level, out-of- ground-effect flight maneuvers.

Operated by Summit Helicopters Inc. (per NTSB report)

The fatigue failure of a main rotor blade drag strut.

Operated by SUMMIT HELICOPTERS INC (per NTSB report)

A loss of engine power due to fuel exhaustion as a result of the pilot's failure to refuel. A factor was unsuitable terrain to complete a successful autorotation.

Operated by SUMMIT HELICOPTERS, INC (per NTSB report)

THE PILOT'S IMPROPER PREFLIGHT AND IMPROPER IN-FLIGHT PLANNING/DECISION. PILOT FATIGUE WAS A RELATED FACTOR.

Part: ADAPTER — CONTAMINATED (ZONE 400) · airframe 2,062 hrs · 6,672 cycles

FADEC DEGRADED AND FADEC FAULT LIGHT ILLUMINATED IN-FLIGHT. DISCONNECTED FOST ADAPTER LOCATED IN ENGINE HARNESS AT (P3) AND VISUALLY INSPECTED FOR CORROSION. NO OBVIOUS DEFECTS WERE NOTED. WE CLEANED ALL THE CONTACTS OF HARNESS AT (P3). WE APPLIED ACF-50 TO PINS AND SOCKETS OF MAIN ENGINE, FOST ADAPTER, AND FIREWALL BULKHEAD CONNECTOR. REINSTALLED FOST ADAPTER, THEN CLEARED FADEC FAULT CODES. RESET FADEC AS PER FLIGHT MANUAL. NORMAL START WAS PERFORMED AND FAULTS WERE CLEARED. THE FOST ADAPTER WAS ORIGINALLY INSTALLED IN ACCORDANCE WITH ENGINE BULLETIN M250 CEB A-73-6059. DETERMINED ORIGINAL FAULT WAS A FALSE INDICATION.

Part: COUPLING — FAILED (HYD PUMP)

HYDRAULIC PUMP TACH DRIVE COUPLING BRAZED WELDING FAILED CAUSING COUPLING TO BECOME LOOSE. MFG SHOULD CHECK THE STRENGTH OF BRAZE AFTER WELDING. WHEN THIS COUPLING FAILS, LOST OF ROTOR TACH OCCURS. (K)

Part: BEARING — MALFUNCTIONED (FUEL CONTROL)

WHILE IN FLIGHT PILOT EXPERIENCED ENGINE HIGH SIDE GOVERNOR FAILURE. THE PILOT WAS UNABLE TO CONTROL RISING ENGINE SPEED WITH THE THROTTLE. RPM ROSE TO 115 PERCENT AND WAS SHUT DOWN BY THE PILOT. UPON REMOVAL OF THE FUEL CONTROL, IT WAS NOTICED THAT THE DRIVESHAFT HAD AN EXCESSIVE AMOUNT OF RADIAL MOVEMENT, ALSO THE SHAFT SUPPORT BEARING WAS COMING APART, WITH THE BEARING BALLS FALLING OUT. THIS PART HAS AN ESTABLISHED OVERHAUL PERIOD OF 2500 HOURS. THE PART HAD 2219.4 HOURS SINCE LAST OVERHAUL, AND HAD BEEN REPAIRED AND FUNCTIONALLY TESTED 498.3 HRS. NOT AWARE OF THE NATURE OF THE REPAIR.

Part: DOUBLER — CRACKED (LT WING)

DURING CHECK-C MAINT, FOUND ONE INCH CRACK IN LT WING IN UPPER WING FUEL TANK ACCESS PLATE DOUBLER NR 1307. STOP DRILLED CRACK AND INSTALLED REPAIR PER SRM 57-03 AND SRM 51-60-0.

Part: SKIN — CRACKED (BS 514)

DURING CHECK-C MAINT CHECK, FOUND SIX INCH CRACK IN FUSELAGE SKIN AT STA 514, 12 IN BELOW OVERWING EXIT OPENING ON LEFT SIDE OF AIRCRAFT. REPAIRED CRACK PER ARA 15854 AND ARA 15856.

Part: ENGINE — BIRD STRIKE (LEFT)

SHORTLY AFTER TAKEOFF, SMELLED INITIAL ODOR IN COCKPIT AND CABIN. RESEMBLED BURNING IN OVENS BUT MORE ACRID. LATER DESCRIBED AS CHEMICAL ELECTRICAL SMELL. FLT RETURNED TO STL. FOUND BIRD HAD BEEN INJESTED IN LT ENGINE AFFECTING THE PNEUMATIC SYSTEM. ACCOMPLISHED BIRD STRIKE INSPECTION. NO DAMAGE TO ENGINE. CHECK-C 9-5-97 STL. (X)

Part: VALVE — FAILED (NR 2 ENGINE)

MCI - FLT 477 - DURING CLIMB, THE NR 2 ENGINE, FUEL HEAT VALVE STUCK IN THE OPEN POSITION CAUSING HIGH ENGINE OIL TEMPERATURE. SHUT DOWN ENGINE. REMOVED AND REPLACED THE FUEL HEAT VALVE, MFG P/N 3201115, MANUFACTURED BY WHITTAKER CONTROLS. OPERATIONAL CHECK AND ENGINE RUNS NORMAL. (M)

Part: BYPASS SWITCH — LEAKING (NR 2 ENGINE)

STL - DURING CRUISE, SHUT DOWN NR 2 ENGINE, S/N 3811, DUE TO LOSS OF OIL QTY. FOUND OIL FILTER BYPASS SWITCH, MFG P/N 42D109-1A, LEAKING. REPLACED OIL FILTER BYPASS SWITCH. ENGINE OPERATION AND LEAKS CHECKS NORMAL. (M)

Part: LAMP — FAILED (LANDING GEAR)

STL - FLT 483 - DURING APPROACH WHEN LANDING GEAR WAS EXTENDED, LANDING GEAR DID NOT SHOW DOWN AND LOCKED. FOUND LANDING GEAR INDICATOR LAMP, MFG PN MS25231-313, SHORTING OUT INDICATOR SOCKET, MFG PN 035-1881-007. RELAMPED INDICATOR AND RESET P26 CIRCUIT BREAKER. LANDING GEAR INDICATION THEN CHECKED NORMAL. CHECK C - 7-11-96 - STL. (X)

Part: BEAM FITTING — CRACKED (PAX DOOR)

STL - DURING OP-15, FOUND .25 INCH CRACK IN FORWARD LOWER DOOR BEAM FITTING RIVET HOLE. REPAIRED PER SRM 51-00 AND TWA STANDARD PRACTICES. AIRCRAFT TOTAL TIME 63,299, AIRCRAFT TOTAL CYCLES 77,392.

Part: LATCH ASSY — OUT OF ADJUST (RT MLG DOOR)

STL - FLT 692 - AFTER TAKEOFF FOLLOWING GEAR RETRACTION, THE RT MAIN GEAR UNSAFE LIGHT REMAINED ON. ADJUSTED RT MAIN GEAR DOOR LATCH ASSY. PERFORMED GEAR SWING, OPERATION NORMAL. CHECK C - 2-17-95 - MCI. (X)

Part: COFFEEMAKER — FAILED (GALLEY)

CID - FLT 64 - DURING CRUISE, FIRST CLASS COFFEEMAKER EMITTED SMOKE. TURNED OFF COFFEEMAKER AND OPENED CIRCUIT BREAKER. FOUND INTERNAL MALFUNCTION IN COFFEEMAKER. REPLACED COFFEEMAKER, MFG PN 50198A, AND OPERATION CHECKED NORMAL. CHECK C - 2-17-95 - MCI.