ANC93FA061

The helicopter was being used to move logs in a long-line lift operation. The pilot reported that as he increased collective to lift a log, he heard a loud noise, which was followed by a loss of power. An autorotation was made to a landing on rough, downhill terrain, downslope from where the log was being lifted. A teardown of the engine revealed evidence of foreign object damage at the 6th and 7th stages of the N1 (gas producer) compressor. Self-locking nuts (pn STD3064-4) were missing from 2 compressor case bolts (pn MS9566-36), which were located over a bleed port, leading to the 6th stage of the gas producer. Metallurgical exam revealed nut fragments of a chemical composition, consistent with the material specified in STD3064-4 nuts. The engine had been in operation about 283 hours, after being reassembled with a new compressor section.

History of flight

On May 8, 1993, at approximately 0930 Alaska daylight time, a Bell 214B1 helicopter, operated by Chet Rasberry, Inc., of Apple Valley, CA, d.b.a. CRI Helicopters, experienced a complete loss of engine power and collided with terrain while conducting aerologging operations near Thorne Bay, Prince of Wales Island, Alaska. The helicopter was on a local company VFR flight plan and was being operated under 14 CFR Part 133 in visual meteorological conditions. The commercial helicopter pilot and copilot received minor injuries and the aircraft was substantially damaged.

The helicopter had been operating for 30 minutes in its second on hour cycle, lifting logs with a 150 foot long line from a 4000 foot elevation and transporting them to a log landing about 1/2 mile down slope at the 1500 foot level. The helicopter had lifted a log when witnesses reported that the helicopter engine exhaust emitted a brief 5 foot flame with a "whoosh" sound before autorotating and impacting on a 30 degree slope studded with felled and bucked timer. The main and tail rotors struck stumps and the hillside, destroying the blades and substantially damaging the fuselage.

The T55-08D turboshaft engine was removed and an examination was conducted by an NTSB team including a powerplant investigator, and other team members from industry. The teardown of the engine revealed that the gas-producer compressor (N1) section and the power turbine (N2) had seized with metal debris and blade parts.

The 6th stage N1 stators were damaged and all 7th stage turbine blades had separated, with extensive foreign object damage aft of the point. Thermal damage was evident in the area of the first rotor of the power turbine as well.

The disassembly examination revealed that two self-locking nuts (PN STD3064-4) were missing from two compressor case bolts (PN MS9566-36) which were located beneath the 6th stage N1 bleed band the nut end(s) of the bolts in a cavity over an open bleed port leading to the 6th stage of the gas producer. Metallurgical examination revealed nut fragments of a chemical composition consistent with the material specified in PN STD 3064-4 nuts. (See attached Powerplant Group Chairman's report and the manufacturer's report of teardown).

Injuries to persons

The commercial pilot-in-command and commercial copilot received minor injuries.

Damage to aircraft

The helicopter was substantially damaged. Refer to wreckage information.

Personnel information

Captain Robin G. Kennedy and copilot Ford W. Chapman were interviewed by NTSB and FAA investigators on the day following the accident. (May 9, 1993 at Ketchikan, Alaska). Captain Kennedy told investigators that he had 7800 hours of pilot time in rotorcraft. He said that the aircraft had been operating normally before experiencing total engine failure.

The captain was asked about the weight of logs carried. He said that he never carried logs in excess of 7000 pounds, and that 7000 pounds was his "target weight". Records found in the wreckage indicated that 17 of the 60 lifts made on the day of the accident were recorded to be exactly 7000 pounds.

The captain told investigators that the company had told him not to exceed 7000 pound per turn. he indicated that he was not aware that the maximum allowable weight was approximately 5600 pounds with operating fuel at the beginning of his cycle, ranging to 6900 pounds with minimum fuel remaining.

Investigators were told by CFR management on May 9, 1993, that Captain Kennedy had been "promoted" to a position of head of pilot training following the accident on May 8, 1993.

On December 16, 1993, Mr. Kennedy contacted the NTSB from a location in Washington state. He said that he was no long working for CRI and wished to revise earlier statements made to investigators. (Refer to record of telephone call.)

Medical records indicated that Captain Kennedy weighed 188 pounds.

Mr. Chapman told investigators that he had worked for CRI Helicopters, Inc., for nine days before the accident. He said that he had no turbine experience before employment with CRI and his total helicopter experience consisted of approximately 100 hours of Robinson 22 flight time.

Mr. Chapman described his training as copilot on the Bell 214B1 to be "on-the-job-training." He said that he had not studied any lesson plans, manuals or taken any tests in conjunction with his assignment as copilot, nine days prior to the accident.

Mr. Chapman said that "7000 pound logs were the heaviest we carried." Investigators asked Mr. Chapman if he had discussed the maximum weight of logs carried, on any occasion after the accident. Mr. Chapman said, "yes, me and Robin had a meeting with Chet in his office."

Medical records indicated Mr. Chapman weighed 240 pounds. The standard weight and balance used by CRI computed their weight as 170 pounds for each pilot. (See weight and balance record for N314CR).

Aircraft information

Bell 214B1, SN 28055, was operated in normal category, with a maximum gross weight limitation of 16000 pounds with external load. The cargo belly hook had an operating limitation of 8000 pounds.

Wreckage and impact information

The helicopter completed an autorotation from approximately the 4000 foot elevation, beginning at an altitude of approximately 175 foot above ground level, abeam a 50 degree easterly slope, and impacting at approximately the 3000 foot level.

The aircraft's advancing main rotor blade contacted a stump and the ground in the helicopters four o'clock quadrant, prior to autorotative touchdown on a 30 degree up slope.

Both main rotor blades of composite material shattered with ground and log contact. Damage to the hull consisted of compartment crushing below the floor and a breaking of the tail cone at the hull and an upward realignment of the tail cone of approximately 15 degrees. Damage was seen to the tail rotor and the tail rotor drive shaft in the tunnel where rotational signatures and torsional stoppage fractures existed.

The helicopter rested on a heading of 200 degrees magnetic and 30 degrees nose up and 45 degrees right roll.

Tests and research

Refer to Powerplant Group Chairman's Factual Report of Investigation and the Corrective Action Evaluation Team (CAET) report of disassembly and examination of T55-08D engine, SN LE31938 at the Textron-Lycoming facility.

The weighing records of SN 28055, dated 10/4/90, showed that the helicopter had an empty weight of 8234.1 pounds (See weight record) and an operating weight of 10,389.6 pounds at the start of each cycle, without external load. The maximum external load that could be carried within the helicopter's certified load limit at the start of cycle was 5610.4 pounds, increasing to 6910.4 pounds at minimum fuel.

The Bell 214B1 helicopter was operated as an external load, aerologging helicopter under 14 CFR Part 133. The flight crew told investigators that at the beginning of each "cycle" lasting approximately one hour and ten minutes, the helicopter was fueled to approximately 1500 pounds of fuel. At the end of each cycle, the refueling amount was approximately 1200 to 1300 pounds. The crew members told investigators that according to company policy and their operating manual, they did not lift logs in excess of 7000 pounds.

The on-scene investigation revealed that the weight of a number of the logs being transported exceeded the aircraft gross weight limitations by approximately 1000 pounds, or approximately 20 percent. A review of available logging records of the helicopter at various southeast Alaska logging locations during the past 52 weeks indicated logs were carried in excess of 2000 pounds beyond the aircraft's gross weight limits.

The electronic load cell was removed from N314CR by investigators at the accident site and sent, by the FAA FSDO-05 Juneau office to Onboard Systems, Inc., in care of the FAA Northwest