LAX05LA025

An inconsistency between the engines' two N2 sensor signals caused the fuel control to enter a fixed mode, which limited the power available. Contributing to the accident was the lack of altitude and airspeed available to give the pilot time to select a landing zone, disengage the flight notch, and exercise manual control of the engine after the illumination of the red 'GOV' light.

The helicopter experienced a partial loss of power during the transition from an out of ground effect hover to forward flight, and collided with the ground in a parking lot. About 10 seconds after the transition to forward flight, at 35 knots and between 150 to 200 feet above ground level, the pilot sensed the engine turbine start to spool down towards idle. He saw a red 'GOV' light illuminated on the instrument panel. The pilot did not disengage the flight notch on the collective twist grip to manually control the fuel flow to the engine and proceeded to fly the helicopter about 1/8 mile towards the parking lot, working the collective to try to keep the helicopter above the trees and the roofs of the houses. He used all the available rotor rpm in an attempt to arrest the landing. The helicopter landed hard, collapsing the landing skids, and the ship slid about 100 feet. After the helicopter came to rest, the main rotor was still rotating at a slower rpm, and the engine was operating at what seemed like a low idle speed. The partial loss of engine power was initiated by an inconsistency of greater than 3 percent between the two N2 (free turbine speed) sensors on the engine. This inconsistency resulted in the fuel control entering a fixed mode that freezes the fuel flow at the level it was at when the inconsistency was detected, and the illumination of a red 'GOV' light in the cockpit. The power required for forward flight is less than the power required to hover. The fixed fuel flow to the engine provided insufficient power to fly and land the helicopter at speeds below 35 knots, which resulted in low rotor rpm and a high rate of decent prior to the hard landing. In the event of a red 'GOV' light the pilot is to disengage the flight notch and control the fuel manually with the collective twist grip, which would allow the pilot to regain the full power range of the engine. At an altitude of 150 to 200 feet and airspeed of 35 knots, the pilot was operating in the avoidance zone of the documented height-velocity diagram, and therefore, may not have had enough time to fully respond to the partial loss of power by selecting an emergency landing site, disengaging the twist grip flight notch, and exercising manual control of the engine.

HISTORY OF FLIGHT On November 2, 2004, at 0731 mountain standard time, a Eurocopter AS350B3, N106LN, experienced a partial power loss after takeoff followed by a hard landing into a parking lot, in Sierra Vista, Arizona. LifeNet, Inc., was operating the helicopter under the provisions of 14 CFR Part 91 as a positioning flight. The commercial pilot and two medical flight crew were not injured, and the helicopter was substantially damaged. Visual meteorological conditions prevailed, and a company flight plan had been filed for the flight that was destined for Portal, Arizona. The pilot stated in the Pilot/Operator Accident Report and in a telephone interview with the National Transporation Safety Board investigator (IIC), that he and two medical attendants were on a flight to pickup a patient. Prior to takeoff he checked his instrument panel and then lifted the helicopter to a 50-foot hover over the elevated pad at Sierra Vista Hospital, which positioned the helicopter about 100 feet above ground level (agl). After receiving clearance from the Sierra Vista Municipal Airport tower he transitioned to forward flight. About 10 seconds later, at 35 knots and between 150 to 200 feet agl, he sensed the engine turbine start to spool down towards idle. He lowered the collective and saw a red 'GOV' light illuminated on the instrument panel. He identified a bank parking lot as a possible emergency landing area. He flew the helicopter about 1/8 mile towards the parking lot, working the collective to try to keep the helicopter above the trees and the roofs of houses. He lined up for the parking lot and used all the available rotor rpm to arrest the landing. The helicopter landed hard collapsing the landing skids, and the ship slid about 100 feet, rotating 90 degrees to the left as it did so. After the helicopter's motion had stopped, the main rotor was still rotating at a slower rpm, and the engine was operating at what seemed like a low idle speed. He rolled the twist grip to 'min,' pulled the fuel shutoff valve, and used the rotor brake to stop the rotor. Throughout the emergency landing he did not recall hearing a "low rotor rpm" aural warning. PERSONNEL INFORMATION A review of the Federal Aviation Administration (FAA) airman records revealed that the pilot held a commercial pilot certificate with ratings for rotorcraft-helicopter and instrument helicopter, issued on February 28, 2002, and a flight instructor certificate rated in helicopters issued November 16, 1998. Additionally, the pilot held a private pilot certificate with a single engine land rating. The pilot held a second-class medical issued on September 9, 2004, with the limitation that he must wear corrective lenses. The pilot reported that he had 9,992 flight hours of total time, 350 hours in the AS350B3, and had flown 25 hours in the last 30 days. AIRCRAFT INFORMATION The helicopter was a Eurocopter, AS350B3, serial number 3251, that was equipped to operate as an emergency medical evacuation helicopter. The engine was a Turbomeca Arriel 2B, serial number 22036, capable of producing 825 horsepower. Examination of the maintenance records revealed that the helicopter had 3,163.8 operating hours at the time of the accident, and had undergone a 30-hour inspection on October 28, 2004. On November 1, 2004, the engine had undergone a 600-hour inspection and had a total time of 3,382.7 hours. The operator, LifeNet, Inc., reported that the helicopter weight at the time of the accident was 4620.4 pounds; aircraft weight of 3,200.4 pounds plus; medical equipment 198 pounds; crew 565 pounds; and fuel 657 pounds. The engine is controlled by a Digital Engine Control Unit (DECU) that receives sensor signals from the gas generator turbine (NG), the free power turbine (NF), the outside air temperature (OAT), rotor speed (NR), and controls the fuel flow into the engine via the hydromechanical control unit. In the event that the hydromechanical fuel control or the DECU becomes inoperative the pilot is notified of the condition by the illumination of a red 'GOV' light on the annunciator panel and an aural 'gong.' By releasing the flight notch slide lock on the collective twist grip the pilot can manually meter fuel to the engine by manipulating the twist grip. Rotation of the twist grip mechanically controls the amount of fuel delivered to the engine. The AS350B3 flight manual states that aural warnings to the pilot are operative only if the 'horn' push button is in. The manual also states that the red 'GOV' light will illuminate when one of two conditions are present; 1- MANU mode (manual mode switch) is engaged. This switch allows the pilot to switch from 'auto' or automatic fuel governing of the engine to 'MANU,' or manual fuel governing of the engine for the purposes of pilot training; or 2- "Governing failure: the fuel flow is frozen at the value prior to the failure." The red 'GOV' light is accompanied by a 'gong' sound if the 'horn' button is in. The pilot should take the following steps when the red 'GOV' light is illuminated. 1-"Check flight parameters." 2- "Maintain NR in green arc." 3- "Unlock the 'FLIGHT' notch, the fuel flow can be increased or decreased by turning the twist grip." 4- "Only apply small amplitude adjustments synchronized with the collective in order to maintain NR in the green range." 5- "Fly the approach at 40 knots and adjust the fuel flow rate to maintain NR with in the upper section of the green range. Slowly reduce the speed if necessary adjust the fuel flow rate slightly on the twist grip to maintain NR within the green range. On final approach, when the collective pitch is increased on reaching the hover, let the NR drop for touchdown, reduce the fuel flow rate before lowering the collective pitch." TESTS & RESEARCH Vehicle and Engine Multifunctional Display (VEMD) The VEMD is an instrument that displays the engine and vehicle parameters in the cockpit. It replaces the conventional indicators and presents engine information, fuel quantity, electrical power, and torque readings. Additionally the VEMD, when in maintenance mode, can display recorded in-flight anomalies and discrete helicopter performance monitoring data. Investigators at the scene of the accident photographed the maintenance pages on the VEMD that displayed error messages from flight number 4600, which was the accident flight. At 2 minutes 08 seconds into flight 4600, an "INVAL NF-A," "FL AMB GOV NF B," and "FL AMB GOV NF A," errors were recorded. At 2 minutes 36 seconds into the flight a "OUT OF RNG OAT" and "FLI LOSS" error are recorded. The over limit page for flight 4600 displayed no limit exceedences for TRQ, T4, NG, NF, or NR parameters. The Turbomeca Arriel 2 Maintenance Manual defines these error messages and parameters as: INVAL NF-A (Invalid NF-A parameter) FL AMB GOV NF B (Flashing Amber GOV light, N2 failure (B on the harness)) FL AMB GOV NF A (Flashing Amber GOV light, N2 failure (C on the harness)) OUT OF RNG OAT (Out of Range OAT parameter) FLI LOSS (Amber GOV light, T0 failure) T0 (Outside Air Temperature (OAT)) T4 (Engine temperature measured by VEMD) TRQ (Torque, percent) NG (Engine power rating, percent) NF (Free turbine expressed in NR speed, rpm) NR (Rotor, rpm) Engine Exam On December 7, 2004, the Turbomeca Arriel 2B, serial number 22036, was examined and test run, under the supervision of the Safety Board IIC, at Turbomeca USA, Grand Prairie, Texas, and was observed by investigators from Turbomeca, LifeNet, Inc., and American Eurocopter. The engine was placed on a test stand in the test cell. The DECU was removed and the engine was connected to the test cell DECU. The engine was started and was run up to ground idle and then flight idle. The engine was then run through a series of 1-second jam accelerations from flight idle to max power. No performance discrepancies