Hyannis Air Service Inc.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

The tug crew’s inadequate visual lookout while towing an airplane at night and their failure to identify a stationary airplane within sufficient time/distance to stop.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

The failure of a solid hydraulic fluid line, which resulted in a loss of hydraulic fluid that prevented the landing gear extension process from completing normally. Contributing to the outcome was the pilot’s failure to fully activate the emergency landing gear extension system.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

An in-flight collision with a bird while entering the traffic pattern.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

The airplane’s impact with a bird while enroute.

Operated by Hyannis Air Service, Inc (per NTSB report)

The accident airplane encountered jet blast from a departing Boeing 737.

Operated by Hyannis Air Service (per NTSB report)

The flight instructor’s failure to confirm the position of the left engine’s auxiliary fuel boost pump switch during a simulated engine out procedure, which resulted in an excess amount of fuel in the engine and subsequent partial loss of power during a go-around/rejected landing. Contributing to the accident was the flight instructor’s failure to maintain control of the airplane, which resulted in a hard landing.

Operated by Hyannis Air Service, Inc. (per NTSB report)

An inadvertent collision with a bird during descent, resulting in substantial damage to the vertical stabilizer.

Operated by Hyannis Air Service Inc Dba (per NTSB report)

The pilot's failure to properly secure the crew hatch door before takeoff, which resulted in the door’s forward hinge assembly tearing from its fuselage mount point.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

The airplane’s collision with a bird during short final.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

The pilot's failure to maintain directional control during the landing roll with a strong crosswind, which resulted in a runway excursion.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

Company maintenance personnel’s failure to comply with the airplane manufacturer’s service instructions by not removing the cracked drag brace from service nor inspecting the repaired drag brace at the appropriate interval, which resulted in the failure of the nose landing gear drag brace due to fatigue cracking and collapse of the nose landing gear during the landing roll. Contributing to the failure of the nose landing gear drag brace was the failure of the repair station to detect a remaining portion of a crack following repair.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

The airplane manufacturer’s inadequate inspection procedures, resulting in the undetected fatigue cracking of the right upper barrel and trunnion assembly.

Operated by HYANNIS AIR LEASING INC (per NTSB report)

The pilot's decision to continue the approach with a known anomaly with the left airspeed indicator. Contributing to the accident was an undetermined malfunction of the left airspeed indicator and the condition of the runway, resulting in decreased braking capability.

Operated by Hyannis Air Services Inc (per NTSB report)

Installation of an improper bearing in the landing gear actuator.

Operated by HYANNIS AIR SERVICE INC (per NTSB report)

The pilot's failure to recognize that both engines were being supplied fuel only from the right main fuel tank, resulting in fuel starvation and a subsequent loss of engine power from both engines. Contributing to the incident were the pilot's inability to properly position the left fuel selector valve and the airplane operator's misinterpretation of the manufacturer's service recommendations to lubricate the fuel selector detents.

Operated by Hyannis Air Service (per NTSB report)

A loss of aircraft control due to spatial disorientation.

The failure of the pilot to use on-board weather radar equipment for weather avoidance and the pilot's continued operation into known adverse weather conditions, resulting in injury to passengers.

an inflight collision with a bird during descent that resulted in substantial damage to the airplane's vertical stabilizer spar.

Operated by HYANNIS AIR SERVICE (per NTSB report)

the pilot's inadequate inflight planning/decision, and his misjudgment of speed and distance. Related factors were: fog, tailwind, and soft terrain on the overrun area at the end of the runway.

Sanction: $4,400 · case closed 2019-06-17

Sanction: $30,000 · case closed 2014-05-30

Sanction: $10,000 · case closed 2013-04-29

Sanction: $12,390 · case closed 2013-07-17

Sanction: $10,000 · case closed 2013-04-29

Sanction: $5,000 · case closed 2008-04-02

Sanction: $5,500 · case closed 2005-03-28

Part: BEAM — CRACKED (ZONE 400) · airframe 25,840 hrs · 19,536 cycles

DURING SCHEDULED INSPECTION A CRACK WAS VISUALLY IDENTIFIED ON THE LEFT HAND CROSSOVER BEAM (OEM: 5654104-11) FORWARD FACE. THIS CRACK MEASURES APPROXIMATELY 1.375 INCHES LONG AND IS CONSISTENT WITH OTHER CRACKS VISUALLY IDENTIFIED ON THESE BEAMS IN THE PAST. THIS BEAM HAS BEEN CHANGED USING NEW PARTS.

Part: FITTING — CRACKED (ZONE 600) · airframe 35,490 hrs · 45,538 cycles

DURING SCHEDULED WING FITTING INSPECTION 2 CRACKS WERE VISUALLY IDENTIFIED IN THE LOWER RADIUS OF THE RIGHT SIDE LOWER AFT WING ATTACH FITTING (OEM: 0822550-44). THE INBOARD CRACK MEASURES APPROXIMATELY 2.750 INCHES LONG AND THE OUTBOARD CRACK MEASURES APPROXIMATELY 3.250 INCHES LONG. BOTH CRACKS APPEAR TO BE CONSISTENT WITH RADIUS CRACKS WE HAVE DISCOVERED VISUALLY IN THE PAST ON OTHER AIRCRAFT. THIS FITTING HAS BEEN REPLACED USING FACTORY NEW PARTS.

Part: PUMP — OBSTRUCTED (ZONE 500 FUEL) · airframe 30,492 hrs · 26,447 cycles

CREW REPORTED LEFT HAND ENGINE VIBRATION AND SLIGHT SURGING, ALL ENGINE INDICATIONS REPORTED NORMAL. CREW PERFORMED MAG CHECK (NORMAL) AND TURNED THE LEFT AUXILIARY PUMP OFF, THEN TO HIGH AND STILL HAD THE VIBRATION, SLIGHT SURGING AND DROPPING RPM. CREW DECIDED TO FEATHER THE ENGINE AND SHUT IT DOWN. COMPANY MAINTENANCE INSPECTED AND FOUND THE INTERNAL CHECK VALVE ON THE LEFT SIDE AUXILIARY PUMP WAS STUCK. THIS PUMP WAS REMOVED AND REPLACED WITH AN OVERHAULED UNIT. ALL FUNCTIONAL CHECKS NORMAL AFTER REPLACEMENT.

Part: BRAKE CALIPER — FAULTY (ZONE 700) · airframe 3,670 hrs · 3,970 cycles

PILOT REPORTED A LOSS OF ALL BRAKING ACTION ON LEFT HAND SIDE DURING LANDING. MAINTENANCE INSPECTED AND REPLACED FAULTY LEFT BRAKE CALIPER ASSY, PRESSURE PLATE, BACKING PLATES AND LININGS WITH NO FURTHER DEFECTS NOTED.

Part: GOVERNOR — FAULTED (RIGHT) · airframe 4,011 hrs · 3,731 cycles

PILOT REPORTED AN UN-COMMANDED FEATHER ON THE RIGHT ENGINE. MAINTENANCE INSPECTED RH PROP AND FOUND NO DEFECTS NOTED AT THIS TIME. REMOVED RH PROP GOVERNOR AND INSPECTED INSIDE CRANK CASE AND FOUND NO DEFECTS. NOTED THAT RH PROP GOVERNOR NOT HITTING BOTH STOPS COMPLETELY. REMOVED AND REPLACED RH PROP GOVERNOR WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST PIPE — CRACKED (ENGINE) · airframe 3,477 hrs · 3,627 cycles

DURING SCHEDULED INSPECTION IT WAS NOTED THE LEFT ENGINE EXHAUST TRANSITION PIPE WAS CRACKED IN THE CENTER. THE TRANSITION PIPE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CYLINDER — OIL CONSUMPTION (#1) · airframe 3,477 hrs · 3,627 cycles

DURING SCHEDULED INSPECTION IT WAS NOTED THE LEFT ENGINE #1 CYLINDER HAD AN OIL FOULED PLUG AND EXCESSIVE OIL IN THE CYLINDER. THE #1 CYLINDER WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST PIPE — BROKEN (ENGINE) · airframe 13,713 hrs · 15,596 cycles

DURING PREFLIGHT THE PILOT NOTED THAT AN EXHAUST PIPE ON THE RIGHT ENGINE WAS CRACKED, WHICH CAUSED DAMAGE TO THE ENGINE COWLING. MAINTENANCE REPLACED THE RIGHT ENGINE CROSSOVER EXHAUST PIPE AND REPAIRED THE ENGINE COWLING WITH NO FURTHER DEFECTS NOTED.

Part: CYLINDER — FAILED INSP (ENGINE) · airframe 3,352 hrs · 3,698 cycles

CREW REPORTED THE RIGHT ENGINE HAD AN OIL LEAK. MAINTENANCE INSPECTED THE ENGINE, BORESCOPED THE CYLINDERS AND FOUND THE #5 CYLINDER TO HAVE EXCESSIVE OIL POOLING AND PITTING ON THE EXHAUST VALVE. THE CYLINDER WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: COOLING FAN — FAILED (ZONE 200) · airframe 3,399 hrs · 5,046 cycles

FLIGHT CREW REPORTED SMOKE IN THE CABIN. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE COPILOT AVIONICS COOLING FAN HAVE FAILED. THE FAN WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: COOLING FAN — FAILED (ZONE 200) · airframe 3,399 hrs · 5,046 cycles

FLIGHT CREW REPORTED SMOKE IN THE CABIN. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE COPILOT AVIONICS COOLING FAN HAVE FAILED. THE FAN WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST PIPE — BROKEN (LEFT) · airframe 3,334 hrs · 3,673 cycles

DURING AN ENGINE CHANGE, THE LEFT EXHAUST PIPE WAS FOUND TO BE CRACKED. THE PIPE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: BEAM — CRACKED (ZONE 400) · airframe 32,911 hrs · 22,534 cycles

DURING MAINTENANCE A CRACK WAS VISUALLY DISCOVERED ON THE INBOARD FACE OF THE RIGHT HAND INBOARD ENGINE BEAM IN THE AREA OF THE VERTICAL ATTACH CHANNELS FOR THE CROSSOVER BEAM. THIS CRACK WAS DISCOVERED AFTER CHANGING THE CROSSOVER BEAM VERTICAL ATTACH BRACKET P/N: 5654107-15 AND THEREFORE NOT VISIBLE UNTIL THE BRACKET WAS REMOVED. THE CRACK MEASURES APPROXIMATELY 1.210 INCHES LONG, AND IS CONSISTENT WITH OTHERS FOUND IN THIS AREA USING A DETAILED VISUAL INSPECTION. THIS BEAM HAS BEEN REPLACED USING NEW PARTS.

Part: EXHAUST PIPE — CRACKED · airframe 3,960 hrs · 3,997 cycles

DURING SCHEDULED INSPECTION MAINTENANCE FOUND THE LEFT ENGINE TURBO TRANSITION PIPE CRACKED. THE TRANSITION PIPE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: STUD — BROKEN (NR 6 CYLINDER) · airframe 3,334 hrs · 3,673 cycles

PILOT REPORTED DURING CRUISE, THE LEFT ENGINE ONLY PRODUCING 59% POWER AT 2100 RPM. MAINTENANCE INSPECTED AND FOUND THE LEFT ENGINE #6 CYLINDER TO HAVE TWO BROKEN CYLINDER STUDS. THE ENGINE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: BELT — FAILED (ALTERNATOR) · airframe 3,920 hrs · 3,743 cycles

PILOT REPORTED LEFT AND RIGHT ALTERNATOR FAILURES IN FLIGHT. MAINTENANCE INSPECTED AND FOUND FOUND BOTH ALTERNATOR BELTS TO HAVE FAILED. LEFT AND RIGHT ALTERNATOR BELTS WERE REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: FAN — FAILED (ZONE 200) · airframe 3,380 hrs · 5,016 cycles

PILOT REPORTED STRONG BURNING ODOR AND SMOKE COMING FROM THE COPILOT'S SIDE DURING CLIMB. MAINTENANCE INSPECTED AND FOUND THE ELECTRIC HEATER FAN IN THE NOSE WERE MAKING A GRINDING NOISE WHEN TURNED ON AND OFF. THE FAN WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST PIPE — BROKEN (ENGINE) · airframe 3,332 hrs · 3,668 cycles

PILOT REPORTED LEFT ENGINE NOT PRODUCING FULL POWER AT 2500 FT, 28" MP AND 2515 RPM. MAINTENANCE INSPECTED AND FOUND THE LEFT REAR EXHAUST PIPE FLANGE BROKEN LEADING TO TRANSITION BLOCK. THE PART WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CYLINDER — LOW PRESSURE (NR 6) · airframe 3,925 hrs · 3,968 cycles

PILOT REPORTED EXCESSIVE ENGINE VIBRATION DURING TAKE OFF AND CRUISE. MAINTENANCE INSPECTED AND FOUND THE #6 CYLINDER DEAD, THE CYLINDER WAS REPLACED ALONG WITH CYLINDER #5'S SPARK PLUGS WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST PIPE — CRACKED (ENGINE) · airframe 3,361 hrs · 3,606 cycles

DURING SCHEDULED INSPECTION MAINTENANCE FOUND THE LEFT ENGINE EXHAUST TRANSITION PIPE IS CRACKED. THE TRANSITION PIPE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CROSSBEAM — CRACKED (ZONE 400) · airframe 34,711 hrs · 24,311 cycles

DURING MAINTENANCE A CRACK WAS VISUALLY IDENTIFIED ON THE RIGHT HAND CROSSOVER BEAM. THIS CRACK IS LOCATED ON THE AFT FACE OF THE BEAM, COMMON TO THE TOP OUTBOARD BOLT HOLE FOR THE TURBOCHARGER SUPPORT BRACKET. THIS CRACK MEASURES APPROXIMATELY .875 INCHES LONG TRAVELING LONGITUDINALLY ACROSS THE FASTENER LOCATION. IT IS CONSISTENT WITH OTHER CRACKS VISUALLY IDENTIFIED IN THIS AREA. THIS BEAM WILL BE REMOVED AND REPLACED.

Part: WYE PIPE — CRACKED · airframe 3,292 hrs · 3,605 cycles

DURING SCHEDULED INSPECTION MAINTENANCE FOUND THE LEFT ENGINE EXHAUST TRANSITION PIPE CRACKED. THE TRANSITION WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: SENSOR — DEFECTIVE (ENG FUEL) · airframe 3,810 hrs · 3,436 cycles

PILOT REPORTED ON CLIMB RIGHT ENGINE SURGING FOLLOWED BY RED LOW FUEL PRESSURE CAS MESSAGE WITH UNCONTROLLABLE YAW, THE PILOT FEATHERED THE PROP AND RETURNED TO LAND. MAINTENANCE INSPECTED AND FOUND THE FUEL PRESSURE SENSOR CAUSING THE ISSUE. THE SENSOR WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CROSSBEAM — CRACKED (ZONE 400) · airframe 29,104 hrs · 41,233 cycles

DURING MAINTENANCE A CRACK WAS VISUALLY IDENTIFIED ON THE AFT SIDE OF THE LEFT NACELLE CROSSOVER BEAM (P/N: 5654104-11). THIS CRACK MEASURES APPROXIMATELY 1.25 INCHES IN LENGTH, AND BEGINS AT THE TOP INBOARD TURBO BRACKET MOUNTING HOLE ON THE AFT FACE OF THE BEAM. THIS CRACK IS CONSISTENT WITH OTHERS FOUND IN THIS AREA AND IS NOT VISIBLE WITH THE TURBO MOUNTING BRACKET INSTALLED. THIS BEAM WILL BE REMOVED AND REPLACED USING NEW PARTS.

Part: CRANKCASE — CRACKED (ENGINE) · airframe 3,806 hrs · 3,430 cycles

DURING INSPECTION, WHILE TROUBLESHOOTING AN OIL LEAK, A CRACK FOUND IN THE ENGINE CRANK CASE. THE ENGINE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST VALVE — FAILED · airframe 3,796 hrs · 3,648 cycles

PILOT REPORTED RIGHT ENGINE HIGH EGT DURING CRUISE FLIGHT. MAINTENANCE INSPECTED AND FOUND THE NR 4 EXHAUST VALVE CHIPPED NEAR VALVE SEAT. THE CYLINDER WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: CYLINDER — SCORED (NR 3) · airframe 3,047 hrs · 3,460 cycles

DURING INSPECTION IT WAS FOUND THE NR 3 CYLINDER ON THE LEFT ENGINE HAD SCORING ON THE CYLINDER WALLS CAUSED BY A BROKEN OIL CONTROL RING. THE CYLINDER WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: INTAKE VALVE — FAILED (RT ENGINE) · airframe 4,307 hrs · 4,364 cycles

PILOT REPORTED THE RIGHT ENGINE CHT & EGT DROPPED RAPIDLY, ALONG WITH FUEL PRESSURE, AS WELL AS AIRCRAFT YAW AND ENGINE ROUGHNESS. MAINTENANCE INSPECTED AND FOUND THE RIGHT ENGINE #3 CYLINDER INTAKE VALVE FAILED, AND THE VALVE STEM BECAME LODGED IN THE CYLINDER HEAD. THE ENGINE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: EXHAUST PIPE — BROKEN (RT ENGINE) · airframe 3,254 hrs · 4,831 cycles

DURING INVESTIGATION OF PILOT REPORT FOR SMOKE IN THE COCKPIT IT WAS DISCOVERED THE LEFT ENGINE RIGHT EXHAUST PIPE HAD BROKEN, WHICH CAUSED DAMAGE TO A TKS LINE AND AN ALTERNATE AIR CONTROL CABLE IN THE VICINITY. THE EXHAUST PIPE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: ENGINE — MAKING METAL · airframe 3,546 hrs · 3,231 cycles

PILOT REPORTED LEFT ENGINE LOW OIL PRESSURE, WHICH DROPPED INTO THE RED DURING LANDING. MAINTENANCE INSPECTED AND FOUND METAL CONTAMINATION IN THE LEFT ENGINE AND OIL POOLING IN 5 OUR OF 6 CYLINDERS. THE ENGINE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: ELEC CONNECTOR — BURNED (ZONE 100) · airframe 3,119 hrs · 3,352 cycles

PILOT REPORTED PITOT HEAT INOP. UPON INSPECTION THE PITOT SWITCH & SWITCH CONNECTION WERE FOUND TO BE BURNT. BOTH WERE REPLACED WITH NO ADDITIONAL DEFECTS NOTED.

Part: BLOWER — FAILED (ZONE 100) · airframe 3,074 hrs · 2,778 cycles

PILOT REPORTED LOW AIRFLOW AND A BURNING SMELL FROM THE CABIN HEATER. MAINTENANCE INSPECTED AND FOUND THE COMBUSTION HEATER VENT BLOWER AT FAULT. THE BLOWER WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: ELEC CONNECTOR — BURNED (ZONE 100) · airframe 3,611 hrs · 3,614 cycles

PILOT REPORTED PITOT HEAT INOP. UPON INSPECTION THE PITOT SWITCH & SWITCH CONNECTION WERE FOUND TO BE BURNT. BOTH WERE REPLACED WITH NO ADDITIONAL DEFECTS NOTED.

Part: HINGE FITTING — DAMAGED (ZONE 300) · airframe 2,671 hrs · 2,886 cycles

DURING SCHEDULED EMPENNAGE INSPECTION. , THE LT OTBD ELEVATOR HINGE ASSY WAS VISUALLY IDENTIFIED AS LOOSE. UPON INSPECTION, FOUND THE FOUR MS204070AD4 SOLID RIVETS ATTACHING THE HINGE ASSY TO THE UPPER & LOWER SKINS OF THE HORIZONTAL STABILIZER WERE WORKING THROUGH THE SKINS, & THREE AN3-10A BOLTS SECURING THE HINGE ASSEMBLY TO REAR SPAR OF HORIZONTAL STAB WERE ALSO FOUND LOOSE. THE TORQUE SEAL ON THE AN365-1032 FIBER LOCK NUTS FOR THESE THREE BOLTS WAS STILL INTACT WITH ORIGINAL PAINT FROM MANUFACTURER. AFTER REMOVAL OF THE HINGE ASSY, FOUND THE CORRESPONDING HOLES FOR THESE BOLTS HAVE BEEN ELONGATED. THE LAST INSPECTION PERFORMED OF THE EMPENNAGE IAW AMM 5-20 WAS PERFORMED AT TAT 2252.6 AND 2430 CYCLES.

Part: BLADE — CRACKED (PROPELLER)

DURING DISASSEMBLY FOR SCHEDULED OVERHAUL A CRACK WAS IDENTIFIED AT A SINGLE BLADE ROOT. MULTIPLE BEARING RACES WERE FOUND TO BE CORRODED AND FAILED.

Part: FITTING — CRACKED (ZONE 400) · airframe 30,630 hrs · 26,388 cycles

DURING NDT INSPECTION AS NOTED IN SID 57-10-16, A CRACK WAS DISCOVERED ON THE LEFT HAND INBOARD NACELLE FITTING. (P/N: 5292029-21) THIS CRACK MEASURES APPROXIMATELY .100 INCHES LONG ON THE INBOARD LOWER LEG OF THE FITTING, AND IS CONSISTENT WITH OTHER CRACKS FOUND USING THE LIGHTED BORESCOPE INSPECTION TECHNIQUE (TEXTRON MEL54-02R2) TO SATISFY REQUIREMENT OF AD2017-10-09. THIS FITTING WILL BE REPLACED USING NEW PARTS.

Part: CROSSBEAM — CHAFED (ZONE 400) · airframe 30,630 hrs · 26,388 cycles

DURING MAINTENANCE CHAFING DAMAGE WAS VISUALLY IDENTIFIED ON THE FORWARD FACE OF THE LH CROSSOVER BEAM (OEM: 5654104-11). THIS CHAFE MEASURES APPROXIMATELY .700 LONG, .500 WIDE, WITH A DEPTH OF APPROXIMATELY .011. THIS BEAM HAS BEEN REPLACED.

Part: CASE — CRACKED (ENGINE) · airframe 2,993 hrs · 2,715 cycles

DURING TROUBLESHOOTING FOR AN OIL LEAK DURING SCHEDULED INSPECTION, A CRACK IN THE ENGINE CASE WAS FOUND IN THE AREA OF THE #1-CYLINDER BOTTOM MOUNT. THIS ENGINE WAS REPLACED WITH NO FURTHER ISSUES.

Part: ELEC CONNECTOR — BURNED (ZONE 200)

PILOT REPORTED PITOT HEAT NOT WORKING. MAINTENANCE INSPECTED AND FOUND THE LEFT PIOTO HEAT SWITCH CONNECTOR MELTED. REPLACED WITH NEW SWITCH WITH NO FURTHER DEFECTS NOTED.

Part: PUMP — LEAKING (HEATER) · airframe 20,416 hrs · 33,385 cycles

PILOT REPORTED A FUEL SMELL IN THE CABIN. MAINTENANCE INSPECTED AND FOUND THE HEATER FUEL PUMP LEAKING. THE FUEL PUMP WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: NUT — BROKEN (ENG CYLINGER) · airframe 3,540 hrs · 3,556 cycles

DURING TROUBLESHOOTING FOR A HIGH OIL CONSUMPTION CONCERN, IT WAS DISCOVERED THE RH ENG #2 CYLINDER BASE NUTS 1/2 IN. #3 AND 3/8 # 2,3,4 BROKEN AND MISSING FROM THROUGH STUDS. THE ENGINE WAS REPLACED WITH NO FURTHER ISSUES NOTED.

Part: FITTING — CORRODED (ZONE 500) · airframe 36,822 hrs · 46,298 cycles

DURING MAINTENANCE A SMALL AREA OF SURFACE CORROSION WAS VISUALLY IDENTIFIED ON THE TOP FACE OF THE VERTICAL LEG OF THE 0822550-43 WING ATTACH FITTING (LT LOWER AFT). THIS CORROSION MEASURES APPROXIMATELY 1.5 INCHES LONG, BY .125 INCHES WIDE WITH AN APPROXIMATE DEPTH OF .030.THIS FITTING WILL BE REPLACED USING FACTORY NEW PARTS.

Part: BEAM — CRACKED (ZONE 400) · airframe 36,821 hrs · 46,297 cycles

DURING MAINTENANCE A CRACK WAS DISCOVERED ON THE INBOARD FACE OF THE RIGHT INBD ENGINE BEAM IN THE AREA OF THE VERTICAL ATTACH CHANNELS FOR THE CROSSOVER BEAM. THIS CRACK WAS DISCOVERED AFTER CHANGING THE CROSSOVER BEAM VERTICAL ATTACH BRACKET P/N: 5654107-15 , THEREFORE NOT VISIBLE UNTIL THE BRACKET WAS REMOVED. THE CRACK MEASURES APPROXIMATELY .750 INCHES LONG, AND IS CONSISTENT WITH OTHERS FOUND IN THIS AREA USING A DETAILED VISUAL INSPECTION. THIS BEAM HAS BEEN REPLACED USING NEW PARTS.

Part: SWITCH — SHORTED (ZONE 200) · airframe 41,418 hrs · 41,289 cycles

PILOT REPORTED THE AUXILIARY CABIN FAN SWITCH FELT HOT WITH A BURNING SMELL AND NOTED SPARKS. COMPANY MAINTENANCE INSPECTED AND FOUND A BURNT WIRE TERMINAL. THE TERMINAL WAS REPLACED WITH NO FURTHER DEFECTS NOTED.

Part: HEATER — LEAKING (ZONE 200) · airframe 3,375 hrs · 3,087 cycles

PILOT REPORTED A FUEL SMELL IN THE COCKPIT WITH THE HEATER RUNNING. MAINTENANCE INSPECTED AND FOUND COMBUSTION HEATER FUEL SOLENOID LEAKING. REMOVED AND REPLACED COMBUSTION HEATER WITH NO FURTHER DEFECTS NOTED.

Part: FITTING — CRACKED (ZONE 400) · airframe 34,885 hrs · 20,590 cycles

DURING LIGHTED BORESCOPE INSPECTION (TEXTRON MEL54-02R3) TO SATISFY THE REQUIREMENT OF AD 2017-10-09, A CRACK WAS IDENTIFIED ON THE OUTBOARD SIDE OF THE LEFT HAND INBOARD NACELLE FITTING ( OEM: 5292029-21). THIS CRACK MEASURES APPROXIMATELY .287 INCHES LONG AND PROPAGATES VERTICALLY UP THE OUTBOARD FACE OF THE FITTING. THE CRACK IS CONSISTENT WITH SIMILAR CRACKING IDENTIFIED USING THE SAME INSPECTION METHOD. THIS FITTING WILL BE REPLACED USING NEW PARTS. THE LAST EDDY CURRENT INSPECTION TO SATISFY CESSNA SID 57-10-16 WAS PERFORMED AT 34824.8 TT.

Part: FITTING — CRACKED (ZONE 400) · airframe 38,029 hrs · 44,290 cycles

DURING SCHEDULED NONDESTRUCTIVE TESTING AS NOTED IN CESSNA SUPPLEMENTAL INSPECTION DOCUMENT (SID) 57-10-16, A CRACK WAS DISCOVERED ON THE RIGHT HAND INBOARD NACELLE FITTING (OEM P/N: 5292029-30) THIS CRACK MEASURES APPROXIMATELY .104 INCHES LONG ON THE LOWER OUTBOARD LEG OF THE FITTING. THIS CRACK IS NOT DETECTABLE VISUALLY BUT, IS CONSISTENT WITH OTHERS FOUND USING THE LIGHTED BORESCOPE INSPECTION TECHNIQUE (TEXTRON MEL54-02R2) TO SATISFY THE REQUIREMENT OF AD 2017-10-09. PREVIOUS COMPLIANCE WITH SID 57-10-16 WAS ACCOMPLISHED AT 37573.0 ACTT (456.4 FLIGHT HOURS AGO). THIS FITTING WILL BE REMOVED AND REPLACED USING NEW PARTS.

Part: RIB — CRACKED (ZONE 600) · airframe 24,158 hrs · 40,028 cycles

DURING MAINTENANCE A CRACK WAS VISUALLY DISCOVERED ON THE RIGHT HAND CLOSEOUT RIB (P/N: 5122115-56) AT R.W.S. 106.79. THIS CRACK ORIGINATES FROM A HOLE IN THE FORWARD ROW OF FASTENERS COMMON TO THE AFT MAIN LANDING GEAR TRUNNION SUPPORT PLATE AND TRAVELS FORWARD AN APPROXIMATE LENGTH OF 1.400 INCHES. THE CRACK IS CONSISTENT WITH OTHERS VISUALLY IDENTIFIED IN THIS SAME AREA. THIS RIB WILL BE REPLACED.

Part: PUMP — LEAKING (FUEL) · airframe 3,300 hrs · 3,358 cycles

PILOT REPORTED A SMELL OF GAS IN THE CABIN DURING FLIGHT. MAINTENANCE INSPECTED AND REPLACED THE RIGHT PRIMARY FUEL BOOT PUMP WITH NO ADDITIONAL FAULTS FOUND.

Part: RIB — CRACKED (ZONE 600) · airframe 23,940 hrs · 9,910 cycles

DURING SCHEDULED INSPECTION, A CRACK WAS VISUALLY IDENTIFIED ON THE RIGHT HAND CLOSEOUT RIB LOCATED AT RWS 106.79. THIS CRACK IS LOCATED IN THE FORWARD VERTICAL ROW OF FASTENERS COMMON TO THE AFT TRUNNION SUPPORT. IT TRAVELS IN AN UP AND DOWN DIRECTION BETWEEN TWO FASTENERS AND IS APPROXIMATELY 1 INCH LONG AND IS CONSISTENT WITH OTHER CRACKS VISUALLY IDENTIFIED IN THIS AREA IN THE PAST. THIS RIB WILL BE REPLACED USING NEW PARTS.