Pathfinder Aviation, LLC.

Operated by Pathfinder Aviation (per NTSB report)

Failure of the door lock due to interference between the door and a cargo box.

Operated by Pathfinder Aviation (per NTSB report)

The pilot's failure to maintain lateral control while hovering over an area of snow-covered terrain, in flat light conditions, which resulted in a dynamic rollover.

Operated by PATHFINDER AVIATION (per NTSB report)

The pilot's failure to maintain clearance from snow-covered terrain during hover in deteriorating weather and flat light conditions, which resulted in a tail rotor strike.

Part: CYLINDER — CRACKED (ENGINE)

DURING FLIGHT, PILOT REPORTED ENGINE RUNNING ROUGH. VISUAL INSPECTION FOUND LT AFT CYLINDER CRACKED.

Part: HOUSING — CRACKED (CHIP DETECTOR) · airframe 14,084 hrs · 37,098 cycles

ON INSPECTION, AN OIL LEAK WAS DISCOVERED IN THE COMBINED GEARBOX AREA. ON FURTHER INSPECTION THE NR 1 ENGINE CHIP DETECTOR HSG ATTACHED TO THE GEARBOX WAS FOUND CRACKED.

Part: STATOR VANE — FAILED (ENGINE) · airframe 11,166 hrs

WHILE IN FLIGHT, ENGINE LOST POWER WHICH RESULTED IN AUTO ROTATION ENDING IN HARD LANDING. FOUND THIRD STAGE EITHER STATOR OR 3RD STAGE WHEEL VANE FAILED CAUSING STAGES 4, 5, 6, 7 TO FAIL. THESE FAILURES FURTHER EXTENDED INTO COMBUSTION CAN AND TURBINE. ALL 3 MODULES OF ENGINE ARE TO BE SENT TO A MFG SERVICE FACILITY FOR FURTHER DISASSEMBLY. COMPRESSOR PARTS WILL BE SENT TO FACTORY FOR FURTHER ANALYSIS FOR ROOT CAUSE OF FAILURE.

Part: FRAME — CRACKED (TAILBOOM) · airframe 13,421 hrs · 36,448 cycles

FRAME WAS FOUND CRACKED AT APPROX STA 78 IN TAILBOOM ABOVE BAGGAGE COMPARTMENT.

Part: BLADE — DELAMINATED (MAIN ROTOR) · airframe 13,421 hrs · 34,448 cycles

M/R BLADE T/E "WEDGE" CAME DEBONDED. REMOVED REMAINING PORTION OF WEDGE AND TOUCHED UP PAINT IAW MFG PRODUCT SUPPORT ENGINEERING.

Part: BULKHEAD — CRACKED (TAILBOOM) · airframe 13,421 hrs · 36,448 cycles

FOUND .5 IN CRACK IN BULKHEAD ASSY LOCATED AT APPROX STA 185 IN TAILBOOM. CRACK WAS IN THE CTR RT PORTION OF THE FRAME.

Part: SEAL — UNSERVICEABLE (T/R GEARBOX) · airframe 4,483 hrs · 30,705 cycles

SEAL WAS LEAKING - HAVE NOTICED AN INCREASE IN T/R GEARBOX SEAL FAILURES.

Part: SPINDLE — CORRODED (TRANSMISSION)

TRANSMISSION SPINDLE MOUNT, WAS FOUND TO HAVE EXCESSIVE PITTING CORROSION DURING A 1200 HR TRANSMISSION TOP CASE INSPECTION. R & R WITH -0-TT, NEW SPINDLE. SENT OLD CORE TO VENDOR BUT UPON NDT INSP, VENDOR REJECTED CORE DUE TO POSSIBLE STRESS CRACKS AND WAS THEREFORE SCRAPPED. PROBABLE CAUSE: DUE TO METAL FATIGUE BECAUSE OF AGE OF COMPONENT. COMPONENT IS NOT TRACKED AS A TIME LIFE COMPONENT AND IS ONLY NDT`D AT 2400 HR TRANSMISSION O/H. REQUIRE COMPONENT TO BE NDT`D AT 1200 HR INSPECTION IN ADDITION TO 2400 TRANSMISSION O/H AND/OR INTRODUCE TIME LIFE LIMIT ON SPINDLE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 65,328 hrs · 28,619 cycles

DURING C-CHECK, FOUND CORROSION ON UPPER CAP OF FLOORBEAM 277 AT LBL 47. REPAIRED PER SRM 53-10-51 REPAIR 6.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,328 hrs · 28,619 cycles

DURING C-CHECK, FOUND CORROSION ON FLOORBEAM AT BS 294.5 AT RBL 48. REPLACED FLOORBEAM T-CAP FROM RBL 59 TO LBL 59 PER SRM 53-10-51 REPAIR 5 AND SRM 51-40-02.

Part: STRINGER SPLICE — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C-CHECK, FOUND STRINGER SPLICE CRACKED AT BS 359.2 FOR STR 14LT. REPLACED STRINGER SPLICE PER SRM 51-40-02.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,328 hrs · 28,619 cycles

DURING C-CHECK, FOUND RIVETS SHEARED ON SHEAR TIE AT STR 15LT AT BS 309. FOUND SHEAR TIE CORRODED. REPLACED SHEAR TIE PER BAC DWG 50-07946 AND SRM 51-40-02.

Part: FITTING — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C-CHECK, FOUND CLIP CRACKED AT BS 294.5 AND STR 13LT. REPLACED CLIP PER BAC DWG 65-17684 AND SRM 51-40-02.

Part: FITTING — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C-CHECK, FOUND CLIP CRACKED AT BS 294.5 AT STR 13LT. REPLACED CLIP PER BAC DWG 65-17684 AND SRM 51-40-02.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,328 hrs · 28,619 cycles

TIE STRAP AT BS 1016 IS CORRODED FROM RBL 2 TO LBL 2. REPLACED STRAP PER BAC DWG 65-46812 AND SRM 51-40-02.

Part: STRINGER SPLICE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,328 hrs · 28,619 cycles

CORROSION ON STRINGER SPLICE BETWEEN BS 360 AND BS 380, STR 28RT. REPLACED STRINGER SPLICE PER SRM 51-40-02.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

BELT LOADER DAMAGED FORWARD LOWER CARGO DOOR CUT-OUT FUSELAGE SKIN. REMAIRED DAMAGED AREA PER SRM 53-00-01, REPAIR 32.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND SUPPORT ANGLE FOR INTERCOSTAL WEB AT BS 290 BETWEEN STR 10RT AND 11RT, JUST FORWARD OF THE R-1 DOOR CUTOUT CRACKED. REPLACED ANGLE PER BAC DRAWING 65-45807 AND SRM 51-40-02.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND SUPPORT ANGLE FOR INTERCOSTAL WEB AT BS 290 BETWEEN STR 11RT AND 12RT CRACKED. REPLACED SUPPORT ANGLE PER BOEING DWG 65-45807 AND SRM 51-40-02.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND SUPPORT ANGLE FOR INTERCOSTAL WEB AT BS 290 JUST FORWARD OF THE R-1 DOOR CUTOUT BETWEEN STR 12RT AND 13RT CRACKED. REPLACED SUPPORT ANGLE PER BOEING DWG 65-45807 AND SRM 51-40-02.

Part: TIE CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 663.75 AND STR 11RT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND CORROSION ON BS 727D FLOORBEAM AT LBL 3. REPAIRED FLOORBEAM IAW SRM 53-00-53.

Part: DOUBLER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND CORROSION ON INNER SKIN DOUBLER AT BS 370 AT BL 0. REPLACED DOUBLER PER BAC DRAWING 65-45769 AND SRM 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 1006 AND STR 8LT. REPLACED TIE CLIP IAW 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 1006 AND STR 9LT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 1006 AND STR 10LT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 1006 AND STR 11LT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 1006 AND STR 12LT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 1006 AND STR 13LT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 1006 AND STR 14LT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,238 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 727C AND STR 4LT. REPLACED TIE CLIP IAW SRM 51-40-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND BS 787 LEFT FRAME CRACKED AT PSU RAIL. REPAIRED FRAME IAW SRM 53-00-07.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

FRAME CRACKED AT PSU RAIL ATTACH BRACKET BS 480 LEFT. REPAIRED FRAME PER SRM 53-00-07 FIGURE 201.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, NOTED FRAME CRACKED AT PSU RAIL ATTACH BRACKET AT BS 440 RIGHT. REPAIRED CRACKED FRAME PER SRM 53-00-07 FIGURE 201.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND FRAME CRACKED AT PSU RAIL ATTACH BRACKET AT BS 420 LEFT. REPAIRED FRAME PER SRM 53-00-07 FIGURE 201.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND FRAME CRACKED AT PSU RAIL ATTACH BRACKET AT BS 380 RIGHT. REPAIRED CRACKED FRAME PER SRM 53-00-07 FIGURE 201.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND STRINGER TIE CLIP CRACKED AT BS 663.75 AT STR 11 LEFT. REPLACED STRINGER TIE CLIP.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,328 hrs · 28,619 cycles

DURING C CHECK, FOUND BS 500A LEFT, FRAME CRACKED AT PSU RAIL. REPAIRED FRAME IAW SRM 53-00-07.

Part: B-NUT — LOOSE (HYD LINE) · airframe 53,858 hrs · 27,283 cycles

DURING LANDING ROLL-OUT, CONTROLLER OBSERVED SMOKE FROM LEFT WHEEL AREA. FOUND BRAKE HYDRAULIC LINE "B" NUT LOOSE AND LEAKING HYDRAULIC FLUID ONTO BRAKE. TIGHTENED NUT AND LEAK AND OPS CHECKED BRAKE. NO FURTHER INCIDENTS.

Part: COUPLER — INOPERATIVE (YAW DAMPER) · airframe 53,130 hrs · 26,896 cycles

YAW DAMPER IS INOP. PLACED ON MEL 22-3-1. REPLACED YAW DAMPER COUPLER PER MM 22-12-32. OPS CHECKS NORMAL.

Part: FITTING — CORRODED (NLG TRUNNION) · corrosion level 2 · airframe 52,588 hrs · 26,599 cycles

CORROSION FOUND IN THE BEARING CUP OF THE NLG TRUNNION FITTING ASSEMBLY BORES AT THE LEFT AND RIGHT SIDES. REPAIRED FITTING ASSEMBLIES PER EA 53-259A.

Part: SKIN — DELAMINATED (MLG DOOR) · airframe 52,588 hrs · 26,599 cycles

DELAMINATION IN INNER AND OUTER SKIN OF RIGHT CENTER MLG DOOR. REPAIRED DOOR PER EA 52-250.

Part: ACTUATOR — LEAKING (ZONE 500)

AFTER TAKEOFF, NR 1 SLAT WOULD NOT RETRACT. SYSTEM "A" HYDRAULIC QUANTITY DECREASED TO 0.3 GALLONS. MAINTENANCE REMOVED AND REPLACED NR 1 L/E SLAT ACTUATOR, LEAK AND OPS CHECK GOOD.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 18,702 hrs · 12,835 cycles

IMPACT DAMAGE TO THE FUSELAGE SKIN, FORWARD ENTRANCE DOORWAY BEARSTRAP AND BS 294.5 BULKHEAD SHEAR TIE AND WEB BETWEEN STR 19LT AND STR 20LT. REPAIRED PER EA 53-074.

Part: SKIN PANEL — DAMAGED (FUSELAGE) · airframe 18,702 hrs · 12,835 cycles

IMPACT DAMAGE (DENT) AT BS 483 SKIN PANEL BETWEEN STR 21 LT AND STR 22 LT. REPAIRED PER SRM 53-00-01 FIG 229.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 18,702 hrs · 12,835 cycles

CORROSION AT CLIP NUT HOLE AT LBL 27 ON FLOORBEAM AT BS 312. REPAIRED PER SRM 53-10-51.

Part: FRAME — CRACKED (FUSELAGE) · airframe 18,702 hrs · 12,835 cycles

TWO CRACKS IN BS 787 FRAME AT RIVET HOLE AT STR 9RT. REPAIRED PER SRM 53-00-07.

Part: FRAME — CRACKED (FUSELAGE) · airframe 18,702 hrs · 12,835 cycles

TWO CRACKS IN BS 827 FRAME AT STR 9RT. REPAIRED PER SRM 53-00-07.

Part: FRAME — CRACKED (FUSELAGE) · airframe 18,702 hrs · 12,835 cycles

TWO CRACKS AT RIVET HOLE IN BS 867 FRAME AT STR 9 RT. REPAIRED PER SRM 53-00-07.

Part: FRAME — CRACKED (FUSELAGE) · airframe 18,702 hrs · 12,835 cycles

TWO CRACKS IN BS 787 FRAME AT STR 9 LT. REPAIRED PER SRM 53-00-07.