Timberland Helicopters, Inc.

Operated by TIMBERLAND HELICOPTERS INC (per NTSB report)

The premature failure of one of the No. 2 engine compressor bleed valve, which resulted in a partial loss of power to that engine.

Operated by Timberland Helicopters (per NTSB report)

The pilot's failure to see and avoid wires while maneuvering at a low-altitude, which resulted in the main rotor blades striking the wires.

Part: ENGINE — MAKING METAL (ZONE 200) · airframe 29,453 hrs · 30,578 cycles

#1 ENGINE CHIP LIGHT ILLUMINATED DURING FLIGHT. PILOT LANDED AT FIRST SAFEST SPOT AT SOUTHWEST WYOMING REGIONAL AIRPORT WITH NO INCIDENT. GROUNDED AC. SENT MECHANIC OUT AND FOUND CHIPS ON UPPER MAG. PLUG ON GEARBOX

Part: LONGERON — WORN (ZONE 200) · airframe 29,453 hrs · 22,649 cycles

FOUND WORKING FASTENERS ON L/H UPPER LONGERON FITTING. AFTER INSPECTION FOUND HOLE OUT OF TOLERANCE. REPLACE L/H UPPER LONGERON

Part: FRAME — CRACKED (ZONE 200) · airframe 29,437 hrs · 22,645 cycles

DURING 300 HOUR A/F INSPECTION FOUND A CRACK AT STATION 142 R/H SIDE ON THE UPPER FRAME NOT RELATED TO ANY INCIDENT OR ACCIDENT.

Part: LONGERON — WORN (ZONE 200) · airframe 29,453 hrs · 22,649 cycles

FOUND WORKING FASTENERS ON L/H UPPER LONGERON FITTING. AFTER INSPECTION FOUND HOLE OUT OF TOLERANCE. REPLACED L/H UPPER LONGERON

Part: FRAME — CRACKED (ZONE 100) · airframe 29,437 hrs · 22,645 cycles

DURING 300 HOUR AF INSPECTION FOUND A CRACK AT STATION 142 R/H SIDE ON THE UPPER FRAME. NOT RELATED TO ANY INCIDENT OR ACCIDENT

Part: RIVET — LOOSE (BS 142) · airframe 19,665 hrs · 36,871 cycles

DURING SCHEDULED INSPECTION WORKING RIVETS WERE FOUND IN CABIN ROOF STRUCTURE STATION 142. THIS IS A COMMON LOCATION FOR WORKING FASTENERS IN THE 206 SERIES AIRCRAFT, ESPECIALLY ON HIGH TIME FUSELAGES. DISCREPANT FASTENERS REPLACE IAW DER STRUCTURAL ENGINEERING REPORT FW-THI709-91 AND BHT-ALL-SRM SECTION 3.

Part: FASTENER — LOOSE (ZONE 200) · airframe 27,804 hrs · 46,865 cycles

DURING ROUTINE INSPECTION FOUND LOOSE AND WORKING RIVETS IN CABIN ROOF STRUCTURE STATION 142.71. THIS IS A COMMON AREA FOR WORKING FASTENERS IN THIS SERIES AIRCRAFT, ESPECIALLY ON HIGH TIME FUSELAGES. DISCREPANT FASTENERS REPLACED IAW DER STRUCTURAL SUBSTANTIATION DOCUMENT FW-TH1687-25 AND BHT-ALL-SRM SECTION 3.

Part: STIFFENER — CRACKED (CREW SEAT) · airframe 19,407 hrs · 36,162 cycles

CRACKS AT SEAT-PAN ATTACHMENT NUTPLATE LOCATION ON TOP FRONT STIFFENER OF CREW SEAT FORWARD BULKHEAD. REPLACED IAW STANDARD RIVETING PRACTICES.

Part: SUPPORT — CRACKED

DURING DAILY INSPECTION, FOUND CRACKS IN THE ARFT CROSSTUBE SUPPORT STRUCTURE LOWER CORNERS AND STIFFENERS. THE CRACKS ARE COMMON IN THIS MODEL ACFT AND THE REPAIR PROCEDURES ARE DETAILED IN THE SRM BHT 206, SRM-1, REPAIR 5-2-1. THIS ACFT MAY HAVE HAD A HISTORY OF FLIGHT TRAINING USE WITH PREVIOUS OPERATORS.

Part: STIFFENER — CRACKED

DURING DAILY INSPECTION, FOUND CRACKS IN THE AFT CROSSTUBE SUPPORT LOWER CORNERS AND STIFFENERS. THE CRACKS ARE COMMON IN THIS MODEL ACFT AND THE REPAIR PROCEDURES ARE DETAILED IN THE SRM BHT-206 SRM-1, REPAIR 5-2-1. ACFT MAY HAVE HAD A HISTORY OF FLIGHT TRAINING USE WITH PREVIOUS OPERATORS.

Part: WEB — CRACKED (ROOF BEAM)

DURING SCHEDULED ANNUAL INSPECTION, FOUND A CRACK EMANATING FROM ACCESS HOLE IN LOWER WEB OF ROOF BEAM AT BS 119.0. THIS AREA INSPECTION IS DETAILED IN MM1-5-29, 300 HR INSPECTION. THIS ACFT HAS A CARGO HOOK, BUT HAS NO HISTORY OF UNUSUAL FLIGHT PARAMETERS: THE CRACK APPEARS TO BE THE RESULT OF NORMAL STRUCTURAL STRESSES.

Part: FITTING — CRACKED (FUSELAGE)

CRACKS RUN FROM 1ST RIVET TO EDGE OF FITTING, ABOUT .5". THE INSPECTION OF THIS PART IS SPECIFICALLY DETAILED IN MFG INSPECTION CHECKLIST. LIKELY CAUSE IS AGE OF ACFT.

Part: FITTING — CRACKED (TAILBOOM)

DURING SCHEDULED 100 HR INSPECTION, FOUND UPPER LT FUSELAGE, SIDE TAILBOOM MOUNT FITTING, PN 206-031-329-103 CRACKED. INSPECTION OF THIS PART IS ROUTINE IN THE CHECKLIST FOR 100 HR INSPECTION, REF BHT-206L1-MM-1, 5/19, 5-20. THIS PART APPEARED TO BE ORIGINAL EQUIPMENT.

Part: GEARBOX — MAKING METAL (TAIL ROTOR)

MAIN ROTOR TRANSMISSION CHIP LIGHT CAME ON IN-FLIGHT WHILE LANDING AT ITS BASE OF OPERATION. MAINTENANCE REMOVED CHIP PLUG. SEVERAL CHIPS WERE FOUND ON PLUG. EXAMINED OIL FILTER METAL AND ALUMINUM WAS PRESENT IN FILTER. REMOVED BEVEL REDUCTION GEARBOX ON COMBINING GEARBOX FOR REPAIR. TSO: 2,359.4 HOURS. OVERHAUL IS 3,000 HOURS.

Part: RETAINER — BROKEN (GEARBOX)

THE NYLON RETAINER FOR THE PLANATARY GEAR BEARING WAS FOUND IN THE TRANSMISSION OIL SCREEN IN SMALL PIECES. SUBMITTER STATED THIS IS THE FOURTH TRANSMISSION IN THE LAST 6 MONTHS WITH THIS PROBLEM.

Part: RETAINER — CRACKED (TRANSMISSION)

UPON TEAR-DOWN OF TRANSMISSION FOR INSPECTION, SCREEN ASSY WAS FULL OF NYLON PIECES. INVESTIGATION REVEALED RETAINERS ON PLANETARY GEAR, 1 EACH, COMPLETELY MISSING AND, 2 EACH, CRACKED.

Part: DRIVE LINK — WORN (PYLON)

INSPECTION FOUND DRIVE LINK ASSY WITH EXCESSIVE PLAY AT TWO PLACES. SEE BELL MM L-3 FIG 62-21. ON TEAR DOWN, FOUND BEARINGS AND SPACERS WORN BEYOND LIMITS. TOTAL TIME OF PARTS, LESS THAN 1,000 HRS/1 YEAR SINCE REPLACEMENT.

Part: DRIVE LINK — WORN (M/R MAST)

PLAY IN EXCESS OF .025 INCH AT TWO PLACES. SEE BELL MM L3, FIGURE 62.21. AT TEAR DOWN FOUND BEARINGS AND SPACERS WORN. TOTAL TIMES LESS THAN 1,000 HOURS AND 1 YEAR SINCE REPLACED.