Temsco Helicopters, Inc

Operated by TEMSCO HELICOPTERS INC (per NTSB report)

The pilot’s failure to maintain adequate obstacle clearance during takeoff from uneven, snow-covered terrain in flat light conditions.

Operated by TEMSCO HELICOPTERS, INC. (per NTSB report)

The pilot's decision to continue visual flight into an area of instrument meteorological conditions, which resulted in the pilot experiencing a loss of visual reference and subsequent controlled flight into terrain. Contributing to the accident were the pilot's self-induced pressure to complete the flight and the operator's failure to maintain operational control over the flight.

Operated by TEMSCO HELICOPTERS INC (per NTSB report)

The inadequate clearance from a tranquilized moose while hovering in ground effect, and the operator's inadequate procedures for such operations, which resulted in an in-flight collision with the moose. Factors associated with the accident were the moose, a sheared tail rotor drive shaft, and the resultant lack of tail rotor anti-torque control.

The improper installation of a bolt in the gas generator governor linkage by company maintenance personnel, which resulted in a loss of the bolt, a loss of engine power while maneuvering, and subsequent forced landing and collision with trees. Factors contributing to the accident were an inadequate preflight inspection by the pilot, and an uncommanded surge in engine power.

The pilot's inadvertent activation of the collective flight stop/emergency fuel augmentation switch, which resulted in engine and main rotor overspeeds, thereby precipitating failures of the tail rotor drive shaft coupling and power turbine blades. A factor associated with the accident was the manufacturer's inadequate design of the flight stop switch, which has insufficient safeguards to preclude inadvertent activation.

Operated by TEMSCO HELICOPTERS INC. (per NTSB report)

The pilot's failure to maintain control of the helicopter as a result of his continued flight into known adverse weather conditions. Factors were the dark night light condition, fog, low ceiling, and the pilot's lack of total instrument flight time.

Operated by TEMSCO HELICOPTERS, INC. (per NTSB report)

THE PILOT'S SELECTION OF UNSUITABLE LANDING TERRAIN. A FACTOR WAS THE CREVASSE IN THE ICE.

Operated by TEMSCO HELICOPTERS, INC. (per NTSB report)

THE PILOT'S IMPROPER IN FLIGHT PLANNING AND DECISION AND HIS FAILURE TO MAINTAIN ALTITUDE DURING THE TURN TO REVERSE DIRECTION. CONTRIBUTING TO THE ACCIDENT WAS THE CALM WATER.

Operated by TEMSCO HELICOPTERS, INC. (per NTSB report)

THE PILOT'S ATTEMPTING TO OPERATE VFR IN INSTRUMENT METEOROLOGICAL CONDITIONS. FACTORS CONTRIBUTING TO THE ACCIDENT WERE UPSLOPING TERRAIN IN THE AIRCRAFT'S FLIGHT PATH AS WELL AS WEATHER CONDITIONS RESULTING IN AN OBSCURATION OF THE TERRAIN.

Operated by TEMSCO HELICOPTERS INC. (per NTSB report)

THE PILOT FAILED TO OBTAIN CLEARANCE OVER TREES. CONTRIBUTING TO THE ACCIDENT WAS: THE AIRCRAFT BEING ABOVE ITS MAXIMUM CERTIFICATED GROSS WEIGHT LIMITATION AND THE TREES.

Operated by TEMSCO HELICOPTERS (per NTSB report)

Operated by TEMSCO HELICOPTERS, INC. (per NTSB report)

Sanction: $27,000 · case closed 2016-10-19

Sanction: $4,500 · case closed 2000-06-23

Sanction: $50,000 · case closed 1999-03-12

Part: BRACKET — CRACKED (RUDDER PEDALS)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON BOTH THE RT AND LT SIDES, THERE IS A BRACKET THAT IS PART OF THE FOOT PEDAL BELLCRANK ASSY, THE LT BRACKET PN 350A21136324, HAS A CRACK IN IT. THE RT BRACKET, SAME PN, CRACKED ALL THE WAY THROUGH WHICH ALLOWED THE FOOT PEDAL BELLCRANK PN 350A27-1170-00, TO GO OUT OF ALIGNMENT AND CONTACT THE SURROUNDING SUPPORT STRUCTURE THUS CAUSING A .25 INCH GROOVE INTO THE BELLCRANK. REMOVED BRACKETS AND REPLACED WITH SERVICEABLE BACKETS AND ALSO REMOVED AND REPLACED THE BAD BELLCRANK WITH A SERVICEABLE BELLCRANK AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT IN CHARGE IAW MFG MODIFICATION. THIS BRACKET IS WHAT HOLDS THE CENTERING ROD FOR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: BELLCRANK — CRACKED (RUDDER PEDALS)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON BOTH THE RT AND LT SIDES, THERE IS A BRACKET THAT IS PART OF THE FOOT PEDAL BELLCRANK PN 350A27-1170-00, TO GO OUT OF ALIGNMENT AND CONTACT THE SURROUNDING SUPPORT STRUCTURE THUS CAUSING A .2500 INCH GROOVE INTO THE BELLCRANK. REMOVED BRACKETS AND REPLACED WITH SERVICEABLE BRACKETS AND ALSO REMOVED AND REPLACED THE BAD BELLCRANK WITH A SERVICEABLE BELLCRANK AND RETURNED AC TO SERVICE. (K)

Part: BRACKET — CRACKED (RUDDER PEDALS)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-1313-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT IN CHARGE SEAT IAW MFG MODIFICATIONS. THIS BRACKET IS WHAT HOLDS THE CENTERING ROD FOR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: BRACKET — CRACKED (RUDDER PEDALS)

ON BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A211183-24, HAS A CRACK IN IT. REMOVED THE BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT CHARGE IAW MFG MODIFICATIONS. THIS BRACKET IS WHAT HOLDS THE CENTERING ROD FOR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: BRACKET — CRACKED (RUDDER PEDALS)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-1363-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT IN CHARGE IAW MFG MODIFICATION. THIS BRACKET HOLDS THE CENTERING ROD FOR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: BRACKET — CRACKED (RUDDER PEDALS)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-1363-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT IN CHARGE IAW MFG MODIFICATION. THIS BRACKET IS WHAT HOLDS THE CENTERING ROD FOR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: BRACKET — CRACKED (RUDDER PEDALS)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-13636-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT IN CHARGE IAW MFG MODIFICATION. THIS BRACKET IS WHAT HOLDS THE CENTERING ROD OR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: BRACKET — CRACKED (RUDDER PEDALS)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-13636-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT IN CHARGE IAW MFG MODIFICATION. THIS BRACKET IS WHAT HOLDS THE CENTERING ROD OR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: BRACKET — CRACKED (UNDER FWD FLOOR)

ON THE BOTTOM SIDE OF THE FOOT PEDAL CONTROLS, ON THE RT PILOT SIDE, THE BRACKET THAT IS PART OF THE BELLCRANK ASSY, BRACKET PN 350A21-13636-24, HAS A CRACK IN IT. REMOVED BRACKET AND REPLACED WITH A SERVICEABLE BRACKET AND RETURNED AC TO SERVICE. THIS AC HAS BEEN PREVIOUSLY CONVERTED TO LT PILOT IN CHARGE IAW MFG MODIFICATION. THIS BRACKET IS WHAT HOLDS THE CENTERING ROD OR THE FOOT PEDAL BELLCRANK IN THE FOOT PEDAL FLIGHT CONTROLS. (K)

Part: TURBINE — CRACKED (ENGINE)

MECHANIC WAS INSTALLING TU-22 WHICH IS AN UPGRADED CONTAINMENT RING ON THE MO4, AND FOUND A CRACKED OUT BOLT HOLE ON THE MOUNTING FLANGE OF THE MO4. PULLED MODULE AND SENT TO MFG FOR REPAIR. (K)

Part: RING — CRACKED (ENGINE)

IN COMPLIANCE WITH AD AND SB, OUR MECHANIC WAS INSPECTING THE ABOVE DESCRIBED ENGINE AND FOUND THE COMPONENT LISTED BELOW TO BE OUT OF SERVICEABLE LIMITS AS INDICATED IN THE 2 DOCUMENTS. REMOVED THE CONTAINMENT RING FROM SERVICE AND INSTALLED A NEW POST MOD TU-22 RING AS ADVISED. (K)

Part: BEARING — FAILED (ENGINE)

ENGINE CHIP LIGHTS FOLLOWED BY ENGINE NOISE. (K)

Part: PROBE — FAULTY (FIRE DETECTION)

PILOT REPORTED THAT HIS FIRE INDICATION LIGHT HAD FLICKERED A COUPLE OF TIMES BUT THEN WENT AWAY. LIGHT WOULD NOT FLICKER ON THE GROUND WHILE NOT RUNNING. MECHANIC COULD NOT FIND THE FAULT. CLEANED THE CONNECTIONS AND FIRE DETECTION PROBES AND TRIED A RUN UP. FIRE LIGHT AGAIN FLICKERED A COUPLE OF TIMES THEN WENT OUT. TROUBLESHOOTING AGAIN FOUND A FIRE DETECTION PROBE TO BE PROBABLE. CHANGED THE PROBE AND AGAIN RAN UP THE AC. THIS TIME THE FIRE SYSTEM WORKED IAW THE MM. TOOK THE AC FOR A FLIGHT TO DETERMINE PROPER FUNCTION UNDER FLIGHT LOADS AND AGAIN THE SYSTEM WORKS IAW MM. RETURNED THE AC TO SERVICE. (K)

Part: TURBINE WHEEL — FAILED (ENGINE) · airframe 9,280 hrs · 36,333 cycles

AS-350 CRASHED IN BOGGY TERRAIN WHILE DEPARTING JUNEAU AIRPORT. AIRCRAFT HAD SUBSTANTIAL DAMAGE. IT APPEARS THAT AFTER TAKEOFF THE TURBINE BLADE OR BLADES CAME APART IN THE ENGINE AND SMOKE/FIRE WAS OBSERVED FROM PERSONS ON THE GROUND RESULTING IN AUTOROTATION, EMERGENCY HARD LANDING. THIS HAPPENED JUST AFTER THE INITIAL LIFTOFF FROM THE HELIPORT AND ATTAINING ABOUT 100 FEET ALTITUDE. ENGINE SENT TO TMECA FOR REPORT OF DAMAGE/REASON. SOME UNKNOWNS AT THIS TIME.

Part: PUMP — FAILED (HYDRAULIC SYS)

PILOT WAS ON HIS INTENDED ROUTE AND NOTIFIED OPERATIONS BASE THAT HE WAS TURNING AROUND AND THAT HAD LOST HYDRAULIC ASSIST TO FLIGHT CONTROLS. RETURNED TO BASE AND LANDED WITH NO INCIDENT. MAINT FOUND THAT THE HYDRAULIC PUMP SPLINES HAD FAILED AND REMOVED AND REPLACED WITH A SERVICEABLE PUMP. AC HAS BEEN RETURNED TO SERVICE. (K)

Part: MODULE — MAKING METAL (ENGINE)

PILOT REPORTED ENGINE CHIP LIGHT ON HIS WAY TO HANGAR. MECHANIC DID THE INSPECTIONS IAW MFG MM AND FOUND A SMALL SINGLE FLAKE ON THE ELECTRIC MAG PLUG WHICH MONITORS THE REAR BEARING OIL RETURN LINE. MECHANIC ALSO THEN FOUND MULTIPLE FLAKES OF PLATEING ON THIS CHIP PLUG. REMOVED THE (ENGINE SN9695) AND INSTALLED (ENGINE SN 9120). SENT ENGINE FOR EVALUATION AND REPAIR.

Part: TRANSMITTER — FAILED (OIL PRESSURE)

AIRCRAFT WAS LIFTING OFF FOR A STANDARD TOUR AND THEN REPORTED A LOSS OF OIL PRESSURE. THE PILOT THEN RETURNED TO BASE WITH NO TROUBLE AND REPORTED TO MAINTENANCE. MECHANIC FOUND THAT THE OIL PRESSURE SENSOR HAD FAILED AND REPLACED PART. AIRCRAFT HAS BEEN RETURNED TO SERVICE. (K)

Part: BEARING — MAKING METAL (MGB)

PILOT REPORTED MGB CHIP LIGHT. INVESTIGATION REVEALED METALIC CHIPS ON THE BEVEL REDUCTION GEAR BOX THAT EXCEEDED SERVICABILITY STANDARDS. REMOVED GEARBOX AND FOUND EPICYCLIC HAS A BAD BEARING WHICH IS THE SOURCE OF THE METAL. SENT EPICYCLIC AND BEVEL GEAR BOX FOR REPAIR OF CYCYLIC AND INSPECTION OF BEVEL GEAR BOX FOR CROSS METAL CONTAMINATION.

Part: GEARBOX — MAKING METAL (TAIL ROTOR)

PILOT REPORTED A CHIP LIGHT FOR THE TAIL ROTOR GEAR BOX. MECHANIC INVESTIGATED AND FOUND FOUR HAIR LINE SLIVERS ON THE CHIP PLUG ALL WHICH EXCEEDED LIMITS AS DESCRIBED BY THE MM. REMOVED THE GEAR BOX (PN 369D25400 SN 0295) AND INSTALLED SERVICEABLE GEAR BOX WITH SAME PN AND SN 0022220081. (AL05200402907)

Part: ENGINE — MAKING METAL

PILOT REPORTED ENGINE CHIP LIGHT. MECHANIC FOUND ENGINE MAGNETIC CHIP DETECTOR HAD METAL PARTICLES WHICH EXCEDED ALLOWABLE LIMIT IN SIZE. MECHANIC REMOVED ENGINE AND INSTALLED LIKE PN ENGINE, SN CAE834274. (AL05200402908)

Part: COMPRESSOR — FOD (ENGINE)

ENGINE WAS FOUND TO HAVE INGESTED A ROCK THROUGH THE INTAKE AND DAMAGED TO INLET COMPRESSOR. FOD DAMAGE. THIS ENGINE IS TO BE SENT FOR EVALUATION AND REPAIR.

Part: COMPRESSOR — FOD (ENGINE)

ENGINE WAS BEING INSPECTED AT THE 100 HOUR INSPECTION INTERVAL AND THE MECHANICS FOUND THAT THE ENGINE HAD BEEN DAMAGED AT THE INLET COMPRESSOR BY FOD. ENGINE WAS REMOVED FROM SERVICE AND SENT FOR EVALUATION AND REPAIR.

Part: BLADE — CRACKED (TAIL ROTOR)

INSPECTOR FOUND CRACK IN TAIL ROTOR PROTRUDING OUT OF RIVET LOCATION ON TRIM TAB. CRACK WAS FOUND DURING INSPECTION IAW AD 2001-26-55. (AL05200402466)

Part: BLADE — CRACKED (MAIN ROTOR) · airframe 3,539 hrs · 3,893 cycles

ON 3/25/04, MAIN ROTOR BLADE, SN 7530 REMOVED FROM AC DURING ANNUAL INSPECTION. 130MM SPANWISE CRACK FOUND AT 68.375.

Part: FILTER — DAMAGED (M/R GEARBOX)

PILOT REPORTED THAT THE INDICATOR LIGHT FOR THE MAIN GEAR BOX PRESSURE. PILOT REPORTED THAT HE FOUND A LANDING SPOT AND LANDED, BUT BEFORE HE LANDED THE LIGHT WENT BACK OUT. LOOKED THROUGH THE AMERICAN EUROCOPTER MM FOR THIS SITUATION AND FOUND NOTHING. CALLED AEC TECH REP AND WAS TOLD THERE IS NO COVERAGE FOR THIS. CHANGED OIL AND FILTER ON THE SIDE OF SAFETY. DID 10 MIN HOVER AND FOUND NO MORE PROBLEMS. AIRCRAFT WAS RELEASED TO SERVICE. (M)

Part: ROLL PIN — FAILED (TORQUE TUBE)

AIRCRAFT FAILED POWER CHECKS DUE TO TORQUE FAILURE. INVESTIGATED SITUATION AND DETERMINED THAT A ROLL PIN FAILURE HAD OCCURED.

Part: ENGINE — MAKING METAL

PILOT IN FLIGHT NOTICED AN ENGINE CHIP LIGHT. HE THEN LANDED AND THEN FOUND SMALL FLAKE OF WHAT APPEARED TO BE CARBON WHICH IS CLASSIFIED IN MFG MM AS CATEGORY ONE WHICH ALLOWS ONLY CLEANING OF THE PLUG AND CONTINUED SERVICE. PILOT TOOK OFF AND HEADED FOR HIS BASE. ON THE WAY THERE HE GOT ANOTER ENGINE CHIP LIGHT AND HE LANDED AT HIS BASE. THE DECISION WAS MADE TO GROUND THE AIRCRAFT AND CHANGE ENGINES. REMOVED ENGINE SN 4815 AND INSTALLED SN 477. ENGINE WILL BE SENT FOR EVALUATION AND REPAIR.

Part: BLADE — CRACKED (MAIN ROTOR)

MAIN ROTOR BLADE CRACKED ON TOP ROOT FITTING IN THE AREA OF BOLTS IN A CORDWISE DIRECTION FOLLOWING AD 96-10-09(B).

Part: DOOR — OPEN (PAX DOOR)

DEPARTING JUNEAU ABOUT 5 MINUTES OUT, AND THE LEFT MAIN CABIN DOOR WAS NOTICED AJAR. AIRCRAFT RETURNED TO BASE AND PILOT REPORTED THAT THE BOTTOM AND MIDDLE PINS WERE GOOD BUT THAT THE UPPER LATCH WAS NOT ENGATED. INSTRUCTED ATTENDANTS ON PROPER DOOR LATCHING AND ALSO HAD THE MECHANICS REWORK THE LATCH PLATE TO ALLOW BETTER LOCKING. (M)

Part: CHIP DETECTOR — CONTAMINATED (ENGINE)

PILOT CALLED IN AN AMBER CHIP LIGHT JUST AFTER LIFT OFF AND RETURNED TO BASE. INSPECTED ENGINE CHIP PLUGS AND FOUND A SMALL PIECE OF MATERIAL IDENTIFIED AS A SMALL BLACK PARTICLE OF CARBON WHICH IN THE MAINTENANCE MANUAL PLACES IT AS CATEGORY ONE. CLEANED CHIP PLUG AND PLACED AIRCRAFT BACK INTO SERVICE IAW MM.

Part: BUCKLE — BROKEN (SEAT BELT)

LT OB SEATBELT BUCKLE BROKEN.

Part: COUPLER — SEIZED (HEATER HOSE)

P2 HEATER HOSE SEIZED ONTO THE FITTING AT THE ENGINE.

Part: MODULE — INOPERATIVE (ENGINE)

THE PILOT CALLED IN LOW OIL PRESSURE AND DECLARED AN EMERGENCY. LANDED THE HELICOPTER SAFELY. PRELIMINARY INVESTIGATION SHOWED THAT THE OIL EVACUATED OUT THE EXHAUST PIPE INDICATING LOSS OF LABYRINTH SEAL PRESSURIZATION. THE RETURN OIL STRUT TUBE HAD ALSO COKED SHUT, WHICH CAN ALSO CAUSE THE OIL PRESSURE TO OVERCOME THE LABYRINTH SEAL PRESSURE. THIS OIL STRUT RETURNS OIL FROM THE REAR MAIN BEARING. THIS MODULE IS POST TU MOD NR 274, 281, 283, AND 284. THIS IS A MODIFICATION BY FACTORY OF THE REAR BEARING HOUSING TO CHANGE OIL PRESSURES AT THE REAR BEARING TO PREVENT COKING. THIS MODIFICATION SET DISCONTINUES THE REQUIREMENT OF THE MANUAL CLEANING OF THE REAR BEARING.

Part: SHIM — MISSING (HYD FILTER)

HYDRAULIC FILTER BYPASS BUTTON POPPED (NO SHIMS INSTALLED).

Part: HMU — LEAKING (ENGINE)

REMOVED HMU / SN 504B DUE TO UNIT LEAKING OUT OF LIMITS. UNIT IS LEAKING BETWEEN HIGH VOLUME PUMP AND HMU BODY. WILL INSTALL SAME UNIT WHEN COMPLETE. RETURNING UNIT TO MFG. FOR REPAIR.

Part: TRANSMISSION — MAKING METAL (MAIN ROTOR)

MAIN ROTOR TRANSMISSION, MAKING METAL.

Part: STRUCTURE — BUCKLED (FUSELAGE)

FUSELAGE BOX STRUCTURE CROSS BRACES BUCKLED. SENT FOR JIG SET AND REPAIR.

Part: MODULE — FAILED (TORQUE)

TORQUE INDICATION STARTED TO FLUCTUATE, AIRCRAFT GROUNDED.

Part: MODULE — FAILED (TORQUE INDICATOR)

TORQUE INDICATION STARTED TO FLUCTUATE. REMOVED MO1 MODULE WHICH HOURS THE TORQUE TUBE AND INSTALLED RENTAL MODUAL, SENT MO1 TO MFG. THIS WAS THEIR RENTAL. THEY DID NOTIFICATION THAT THIS WAS THE SAME TYPE OF FAILURE BEFORE IN THE FACT THAT THE ROLL PINS ON THE TORQUE TUBE HAD SHEARED.

Part: BLADE — DELAMINATED (MAIN ROTOR)

REMOVED MAIN ROTOR BLADE, DUE TO DELAMINATION OF BLADE TIP. SENT TO AEC FOR INSPECTION. REPLACED.

Part: BLADE — DELAMINATED (MAIN ROTOR)

REMOVED MAIN ROTOR BLADE, DUE TO DELAMINATION OF BLADE TIP. SENT TO AEC FOR INSPECTION. REPLACED.

Part: BLADE — DELAMINATED (MAIN ROTOR)

REMOVED MAIN ROTOR BLADE, DUE TO DELAMINATION OF BLADE TIP. SENT FOR INSPECTION. REPLACED.

Part: MODULE — FAILED (TORQUE INDICATOR)

REMOVED ENGINE MODULE 1 DUE TO TORQUE SYSTEM REFERENCE SHAFT PHONIC WHEEL ROLL PINS SHEARING CAUSING LOSS OF TORQUE INDICATION VEMD. REMOVED LOANER MODULE 1 FOR REPAIR. INSTALLED LOANER MODULE. SENDING UNIT TO MFG FOR REPAIR.

Part: MODULE — FAILED (TORQUE INDICATOR)

TORQUE INDICATION STARTED TO FLUCTUATE. REMOVED NR 1 MODULE WHICH HOUSES THE TORQUE TUBE AND INSTALLED A RENTAL. SENT NR 1 OUT FOR REPAIR. IT WAS DETERMINED THAT THE ROLL PINS IN TORQUE TUBE HAD SHEARED OFF.

Part: BULB — FAILED (ROW 4)

DFW - FLT 3868 - OVERHEAD EMERGENCY LIGHT OUT AT SEAT 4A. REMOVED AND REPLACED BULB AT 4A. OPS CHECK GOOD. (M)

Part: BULB — INOPERATIVE (CABIN)

DFW - FLT 3318 - OVERHEAD EMERGENCY LIGHT AT SEAT 3C INOPERATIVE. REMOVED AND REPLACED BULB. OPS CHECK GOOD. (M)

Part: BULB — FAILED (CABIN)

DFW - FLT 3668 - EMERGENCY LIGHT BULB AT SEAT 11A DOES NOT ILLUMINATED. REMOVED AND REPLACED BULB. OPERATIONAL CHECK GOOD. (M)

Part: FCU — CONTAMINATED (ENGINE)

ENGINE FAILURE RESULTING IN EMERGENCY LANDING. INVESTIGATION REVEALED A PIECE OF BLACK RUBBER APPROXIMATELY 18 BY 8 MILLIMETERS IN SIZE LODGED IN THE EJECTOR PUMP ORIFICE OF THE FUEL SYSTEM LOW PRESSURE UNIT. THIS CAUSED THE HIGH PRESSURE FUEL PUMP, INSIDE THE FUEL CONTROL UNIT TO SHUT DOWN, RESULTING IN COMPLETE POWER LOSS. TEMSCO HELICOPTERS BELIEVES THE RUBBER PARTICLE WAS A RESULT OF MANUFACTURE ASSEMBLY. TEMSCO RECOMMENDS THE MANUFACTURER INSTALL AN AIRFRAME MOUNTED FUEL FILTER UPSTREAM OF THE LOW PRESSURE UNIT. CURRENTLY, THE LOW PRESSURE UNIT/EJECTOR PUMP IS NOT PROTECTED BY THE EXISTING FUEL FILTER. (X)

Part: BULB — FAILED (CABIN)

DFW - FLT 5086 - EMERGENCY FLOOR PROXIMITY LIGHT AT SEAT 11BC DOES NOT ILLUMINATE. REMOVED AND REPLACED BULB. OPERATIONAL CHECK GOOD. (M)

Part: FAIRING — CHAFED (STAB/FUSELAGE)

ABI - DURING AN MBV INSPECTION, A CHAFE WAS DISCOVERED AT LT STABLIZER TO FUSELAGE FILLET FAIRING CONTACT AREA. BLENDED CHAFE AND PERFORMED AN EDDY CURRENT INSPECTION WITH NO INDICATIONS OF CRACKS. APPLIED PROTECTIVE TREATMENT INCLUDING TOP COAT TO BLENDED AREA. FABRICATED AN EXTERNAL DOUBLER .025 INCH THICK. APPLIED PROTECTIVE TREATMENT INCLUDING POLYURETHANE TOP COAT. INSTALLED DOUBLER TO AIRCRAFT. WORK DONE IAW SAAB REPAIR STATEMENT 72SDS1375, SB 340-53-042 AND SAAB SRM 51-20-52. AIRCRAFT OK FOR SERVICE. (X)