MU-2Solitaire · Marquise

Parts most often named Landing Gear (3) · Switch (2) · Motor (2) · Emergency Ext (1)

WHEN GEAR WAS SELECTED TO GEAR DOWN POSITION, GEAR DID NOT DEPLOY. PILOT HAD TO MANUALLY DEPLOY GEAR USING MANUAL EXTENSION. GEAR CAME DOWN AND LOCKED WITH ALL INDICATIONS NORMAL. PILOT THEN MADE A NORMAL LANDING AFTER DECLARING AN EMERGENCY.

(CAN) PILOT SELECTED GEAR DOWN THE DOOR MOTOR CIRCUIT BREAKER POPPED. MANUAL GEAR EXTENSION COMPLETED AND ACFT LANDED WITHOUT INCIDENT. MECHANIC DISPATCHED AND FOUND THE GEAR DOOR ACTUATOR/MOTOR UNSERVICEABLE. ACFT FERRIED TO MAINTENANCE BASE, DOOR ACTUATOR/MOTOR REPLACED AND GEAR SWING COMPLETED. ACFT RETURNED TO [S/N removed].

(CAN) THE LANDING GEAR FAILED TO EXTEND WHEN SELECTED DUE TO A FROZEN DOOR ACTUATOR CLUTCH. THE CREW THEN INITIATED AN EMERGENCY EXTENSION WHICH WAS UNSUCCESSFUL.

Parts most often named Adapter (2) · Housing (2) · Pump (2) · Gasket (1)

(CAN) PILOT RETURNED TO BASE DUE TO FLUCTUATING OIL PRESSURE. MAINTENANCE OBSERVED OIL LEAK AND DETERMINED IT WAS COMING FROM THE END OF THE OIL FILTER HOUSING.UPON FURTHER EXAMINATION A CRACK WAS FOUND IN THE CHAMFERED END OF THE HOUSING. (TC# 20141015002)

(CAN) LEFT ENGINE OIL PRESSURE WAS FLICKERING IN THE YELLOW DURING GROUND RUNS. FOUND THE OIL FILTER ADAPTER HOUSING HAD TWO BROKEN MOUNTING TABS. ADAPTER WAS REPLACED & AIRCRAFT RETURNED TO [S/N removed].

(CAN) DURING ROUTINE ENG INSPECTION THE OIL FILTER CAP WAS FOUND TO BE CONTACTING THE ENG MOUNT CAUSING WEAR ON THE CAP. THIS ENG HAD [S/N removed] BULLETIN 79-0012 OIL FILTER HOUSING ADAPTER INCORPORATED THAT ALLOWED THE CONTACT. THE FILTER CAP WAS REPLACED & THE ADAPTER WAS R & R WITH A PRE SB 79-0012 ADAPTER.

Parts most often named Tire (13)

AT ROTATION (110 KNOTS), PILOT FELT BAD VIBRATION. PILOT RETURNED TO AIRPORT, FOUND THAT RIGHT HAND RECAP CAME OFF. RECAP DONE BY HAWKINS AIRCRAFT TIRE COMPANY. LANDINGS: 98.

UPON ROTATION, TREAD SEPARATED FROM CARCASS ON THE NR 1 TIRE ASSEMBLY. AT SEPARATION TIRE TREAD DAMAGED AFT GEAR DOOR AND DOOR CONNECTING ROD. TREAD THEN FLEW FORWARD AND STRUCK PROP. TIRE WAS A RECAP.

RIGHT HAND MAIN GEAR TIRE TREAD SEPARATED FROM CASING ALONG INBOARD EDGE COMPLETELY AROUND CIRCUMFERENCE. OCCURRED ON LANDING. TIRE REMAINED INFLATED. TREAD STAYED ATTACHED AROUND OUTBOARD EDGE CIRCUMFERENCE. THIS WAS ONE OF THREE SIMILAR OCCURRENCES WITHIN 30 DAYS ON TWO DIFFERENT AIRCRAFT (BOTH MU-2'S). TIRE RETURNED TO MFG FOR EVALUATION.

Parts most often named Engine (9) · Duct (1) · Bearing (1) · Powerplant (1)

(CAN) DURING INITIAL DESENT THE RT ENGINE FAILED, THE ENGINE WAS SECURED AND ACFT LANDED ON 1 ENGINE WITHOUT INCIDENT. OIL FILTER WAS PULLED AND FOUND METAL IN THE OIL. ENGINE REPLACED. WE ARE AWAITING THE TEARDOWN REPORT FROM THE ENGINE O/H FACILITY.

DURING FLIGHT PILOT EXPERIENCED A FAILURE OF THE LEFT ENGINE. INITIATED INFLIGHT SHUT DOWN, DECLARED AN EMERGENCY AND LANDED AT RICHMOND INTERNATIONAL AIRPORT UNEVENTFUL. PILOT DID DECLARE AN EMERGENCY.

(CAN) DURING CLIMBOUT, RT ENGINE SHUTDOWN, ENGINE WAS SECURED AND ACFT LANDED WITH 1 ENGINE, WITHOUT INCIDENT. AWAITING ENGINE TEARDOWN REPORT FOR FURTHER INFORMATION.

Parts most often named Pilot Tube (3) · Bracket (2) · Bearing (2) · Blade (1)

FIVE B-3493 START LOCK BRACKETS WERE FOUND DURING PENETRANT INSPECTION TO BE CRACKED AT THE SAME LOCATION. CRACKS ARE LOCATED ON THE EXTERIOR START PIN BORE NEXT TO THE SPINNER MOUNTING BOLT RELIEF CUT-OUT. THIS BRACKET IS PART OF THE 830-34L START LOCK UNIT INSTALLED ON 4-BLADED MU-2S.

CUSTOMER WORK ORDER WAS OPENED TO DYNAMIC BALANCE PROPELLERS. UPON INSPECTION OF THE AIRCRAFT, THE BLADES WERE FOUND NOT TO BE SHOT PEENED IN ACCORDANCE WITH AD 95-01-02. THE PROPELLERS HAD BEEN PREVIOUSLY OVERHAULED BY YINGLING AIRCRAFT, INC., ON 7-31-2000. BOTH PROPELLERS WERE REMOVED FOR OVERHAUL AND AD COMPLIANCE. PROPELLER [S/N removed]: CDA3361, CDA3363. BLADE [S/N removed]: H57913, H57910, H57908, H57916, H57911, H57912, H57909, H57917. (X)

DURING A ROUTINE 100 HR INSPECTION, IT WAS DISCOVERED THAT 2 OF THE 4 BLADES ON EACH OF THE 2 HARTZELL PROPELLERS HAD A ROUGH MOVEMENT WHEN ROTATED FROM REVERSE PITCH TO FEATHER POSITION AND BACK AGAIN. SENT BOTH PROPS TO A PROPELLER O/H FACILITY AND FOUND THE BEARINGS ON THE ROUGH BLADES WERE WORN TO THE LIMITS. THIS IS THE SECOND TIME DISCOVERED THIS PROBLEM ON THE 4 BLADED HARTZELL PROPELLERS INSTALLED ON THE MU-2 AIRCRAFT.

Parts most often named Housing (2) · Gear (2) · Ring Gear (1) · Line (1)

PILOT REPORTED LOW AND FLUCTUATING OIL PRESSURE FROM LEFT ENGINE IN FLIGHT AND ELECTED TO SHUT THE ENGINE DOWN. AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. THE ENGINE OIL BYPASS VALVE WAS FOUND TO BE IN THE "POPPED" CONDITION, THE OIL FILTER WAS THEN REMOVED AND FOUND TO BE BLACK IN COLOR WITH THE FORWARD SEALING SURFACE BROKEN IN SEVERAL SMALL PIECES. THE REDUCTION GEAR BOX WAS DISASSEMBLED AND THE OIL PRESSURE PUMP REMOVED. THE FORWARD HOUSING WAS CRACKED APPROXIMATELY (3 INCH) RADIALLY AT FWD DETAIL. (K)

NR 8 SCAVENGE OIL LINE FROM ENGINE GEARBOX TO VERNATHERM CRACKED INSIDE THE B-NUT SLEEVE AT GEARBOX. THIS LED TO SIGNIFICANT LOSS OF OIL AND A PRECAUTIONARY SHUTDOWN IN FLIGHT. AC RETURNED DEPARTURE, UNEVENTFUL LANDING, REPLACED OIL LINE. (K)

IN FLIGHT, PILOT NOTICED FLUCTUATING OIL PRESSURE AND TORQUE. PRECAUTIONARY LANDING MADE, FOLLOWING TROUBLESHOOTING ENGINE WAS DISASSEMBLIED GEARBOX SCAVENGE OIL PUMP WAS CRACKED. APPROXIMATELY 7 HOURS PRIOR, THE NR 8 STAINLESS OIL SCAV. LINE CRACKED. APPROXIMATELY 7 HOURS PRIOR THE NR 8 STAINLESS OIL SCAV LINE CRACKED. IT IS BELIEVED OIL PRESSURE CYCLING FROM LINE FAILURE FRACTURED SCAV PUMP HSG REPLACED PUMP. (K)

Parts most often named Switch (7) · Limit Switch (1) · Drag Strut (1) · Downlock Switch (1)

AFTER THE PILOT SELECTED GEAR UP THE NOSE GEAR "DOWN" LIGHT REMAINED ILLUMINATED. CREW CONTINUED TO A MAINTENANCE BASE AND COMPLETED A MANUAL EXTENSION AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE LANDING GEAR DOWN LIMIT SWITCH CONTAMINATED WITH ICE. SWITCH REPLACED AND AIRCRAFT RETURNED TO [S/N removed]. NOTE ALL OTHER AIRCRAFT IN FLEET HAD THE LANDING GEAR SWITCHES CLEANED AND LUBRICATED AS A PRECAUTIONARY MEASURE.

(CAN) DURING APPROACH, THE CREW SELECTED GEAR DOWN AND FAILED TO GET A GREEN LIGHT FOR THE NOSE GEAR, THE UNSAFE LIGHT WAS NOT ILLUMINATED. AFTER A TOWER FLYBY THE GREENLIGHT CAME ON AND THE AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND A LOOSE / BROKEN WIRE AT THE BACK OF THE SWITCH.

(CAN) AFTER TAKEOFF, RT MAIN LANDING GEAR DOWN LIGHT (GREEN) REMAINED ON WITH NO UNSAFE LIGHTS ON. LIGHT EXTINGUISHED AFTER 2O MINUTES. MAINTENANCE ACTION FOUND FROZEN LANDING GEAR DOWN SWITCH. AIRCRAFT WASHED PREVIOUS DAY AND LEFT OUTSIDE IN EXTREME COLD TEMPERATURE. SWITCH DRIED AND CLEANED.

Parts most often named Clamp (4) · Bearing (2) · Blade (2) · Bolt (1)

AIRCRAFT AT CRUISE, ALT 11,000 FEET, NR 1 PROPELLER BLADE BROKE APPROXIMATELY 10 INCHES FROM HUB ON NR 2 ENGINE. BLADE DID NOT CONTACT AIRCRAFT. DAMAGE TO COWLING, NACELLE, REAR ENGINE MOUNT, OUTBOARD FLAP, WING TRAILING EDGE. ENGINE REMAINED ON WING. CREW MADE NORMAL LANDING. REMAINING PORTION OF BLADE REMOVED FROM PROP HUB AND SENT TO NTSB LAB FOR INSPECTION. (X)

DURING 150-HOUR INSPECTION ON BOTH PROPELLERS, THE PROPELLER STOP LOCK BOLTS ON ALL PROP BLADES WERE FOUND CHAFING ON THE BLADE STOP PLATES. REMOVED ALL 6 BOLTS, PN AN4-417A, ON THE STOP LOCKS. INSTALLED ALL NEW BOLTS, PN AN4-16A, AND NEW NUTS, P/N B3808. RT PROP [S/N removed].

DURING A 150 HOUR INSPECTION, A CLAMP WAS FOUND CRACKED ON THE LEFT PROP. THE PILOT THAT DELIVERED THE AIRCRAFT FOR THE INSPECTION REPORTED VIBRATION FROM THE RIGHT ENGINE. RECOMMENDED TO INSPECT PROPS IAW HC-SL-61-165 ANY TIME THERE IS GREASE LEAKAGE OR VIBRATION.

Parts most often named Solenoid Valve (4) · Valve (3) · Line (1) · Heater (1)

VALVE LEAKING FUEL BETWEEN THE SOLENOID AND VALVE BODY DUE TO BLOWN O-RING. THE FUEL WAS LEAKING INTO THE COWLING AND DRIPPING OUT.

PILOT REPORTED FUEL LEAKING FROM COWLING. INVESTIGATION FOUND FUEL LEAK FROM MATING SURFACES OF PRIMARIES ONLY SOLENOID VALVE. REPLACED VALVE WITH [S/N removed].

(AUS) RH ENGINE OIL/FUEL HEATER OIL OUTLET FITTING PNO AN815-8J LOOSE AND LEAKING DUE TO STRIPPED THREADS IN THE HEATER HOUSING -PERSONNEL/MAINTENANCE ERROR

Parts most often named Control Cable (6) · Nut (1)

DURING ROUTINE MAINTENANCE FOUND A FRAYED ENGINE CONTROL CABLE. THE FRAYED PORTION WAS LOCATED IN THE AFT FUSELAGE WHERE THE CABE GOES OVER A 90DEGREE TURN PULLEY. THIS IS THE FIRST OF THREE CABLE PROBLEMS THIS OPERATOR HAS FOUND IN THE LAST 90 DAYS

DURING INSPECTION IN THE AFT FUSELAGE FOUND ONE OF THE ENGINE CONTROL CABLES FRAYED WHERE THE CABLE GOES OVER A PULLEY AND TURNS 90 DEGREES. THIS IS THE 2ND OF THREE REPORTED BY THE SAME OPERATOR IN 90 DAYS. ALL HAVE BEEN THE LEFT ENGINE CONTROL

ON ENGINE SHUTDOWN, PILOT COULD NOT BRING LEFT PROP BACK ON LOCKS. INSPECTION FOUND LEFT ENGINE POWER LEVER CONTROL CABLE BROKEN BELOW CENTER PEDISTAL IN COCKPIT AT LOWER PULLEY. (SW15200209701)