Glenn County Airport, Willows, CA

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Airport Area Accident History:
Accident occurred Friday, April 28, 2006 in Willows, CA
Probable Cause Approval Date: 10/31/2006
Aircraft: Cirrus SR-20, registration: N1488C
Injuries: 1 Uninjured.
The airplane incurred structural damage during landing when the airplane entered a porpoise pilot induced oscillation and the propeller struck the runway. The student pilot was on the second leg of his solo cross-country flight. The approach to runway 34 was normal, but during touchdown the airplane porpoised. The pilot initiated an aborted landing, and flew the airplane to Red Bluff Municipal Airport where he landed uneventfully. He parked the airplane at the ramp and shut down the engine. The pilot inspected the airplane and found damage to the propeller resulting from ground impact during the porpoise. An inspection by maintenance personnel revealed structural damage. The pilot stated that the airplane and engine had no mechanical failures or malfunctions during the flight. The National Transportation Safety Board determines the probable cause(s) of this accident as follows: the pilot's misjudged landing flare and improper recovery from a bounced landing. ===
Accident occurred Sunday, May 08, 2005 in Willows, CA
Probable Cause Approval Date: 5/30/2006
Aircraft: Grumman G-164C, registration: N6535K
Injuries: 1 Uninjured.
The pilot force landed the airplane in a rice field following a loss of engine power and the main landing gear was sheared off after contacting a berm. While the pilot was seeding rice over a field, the engine lost partial power. The pilot force landed the airplane in a field. During the landing roll, the landing gear impacted a berm and were sheared from their structural attachment points on the airplane. Until the ground impact, the engine was producing partial power, but not enough to sustain flight. Post accident inspection of the engine by the Federal Aviation Administration accident coordinator revealed that the number 5 cylinder piston had fractured at the piston pin boss. The piston pin, which is mounted in the piston pin boss and holds the piston to the connecting rod, fell from the boss and the connecting rod was free to rotate. The engine was overhauled about 1,154 hours prior to the accident. The maintenance history on the piston could not be determined based on available records.
The National Transportation Safety Board determines the probable cause(s) of this accident as follows: the loss of engine power due to the fractured piston pin boss on the number 5 cylinder. ===
Accident occurred Wednesday, May 21, 2003 in Willows, CA
Probable Cause Approval Date: 12/28/2004
Aircraft: Ayres S2R-T34, registration: N5653X
Injuries: 1 Uninjured.
The commercial pilot was making a steep turn during an agricultural aerial applicationwhen the airplane's engine lost power. He made a forced landing in a field, and in the process, the airframe received structural damage. The pilot said he had ground crew fuel the left tank of the airplane with the engine still running. He completed three loads, with each load cycle taking about 12 minutes. He then performed a steep turn of about 70-degrees to complete one last pass. About 400 above ground level, the engine lost power and he was unable to restart it. He landed the airplane in the field below, and the airplane skidded about 100 feet and nosed over. The person who recovered the airplane did not observe any fuel in the airplane fuel tanks, or at the accident site. The National Transportation Safety Board determines the probable cause(s) of this accident as follows: A loss of engine power for an undetermined reason during an aerial application. ===
Accident occurred Wednesday, August 21, 2002 in Willows, CA
Probable Cause Approval Date: 9/29/2004
Aircraft: Cessna 195, registration: N4344V
Injuries: 2 Uninjured.
The pilot failed to maintain runway alignment during the landing flare, which resulted in the airplane touching down off the runway in soft dirt and nosing over. The pilot had just purchased the tail wheel equipped airplane and was practicing touch-and-go takeoffs and landings to gain confidence in the airplane prior to flying it home. The pilot said that during the first landing, about 2 feet above the ground, the airplane was "blown" to the right of the runway where it touched down in the soft dirt. The main tires dug into the dirt, and the airplane nosed over. The pilot reported that having more flight time in the airplane may have helped prevent the accident. He had 5 hours in this make and model of airplane. The National Transportation Safety Board determines the probable cause(s) of this accident as follows: the pilot's inadequate compensation for crosswind conditions resulting in his failure to maintain runway alignment. Contributing factors to the accident were the pilot's lack of familiarity with the airplane. ===
Accident occurred Thursday, April 11, 2002 in Willows, CA
Probable Cause Approval Date: 6/30/2004
Aircraft: Beech G35, registration: N4487D
Injuries: 2 Fatal.
According to witnesses, the airplane was seen approaching the motor sports park from the southwest at approximately 1,200 feet agl and at a "faster than usual" rate of speed. The airplane was in a "sharp, 90-degree bank," as it began to circle the park in a level turn. After circling around to the east, the airplane returned to a wings-level attitude and began to climb. Shortly thereafter, the tail of the airplane began to "shake violently" and separate from the airplane. One witness said he heard a loud noise as "the tail came off, and all of it started falling apart." He said the tail section separated first, then the airplane pitched over, and the left wing broke off. Witnesses saw the airplane enter a downward spiral. As the airplane descended, the engine separated and the passenger was ejected. The airplane then entered an inverted flat spin and impacted the ground 1,000 feet north of park. An examination of the airplane's left wing, and stabilizers revealed structural failures consistent with overload. According to the manufacturer's Flight Strength Diagram or Vn diagram for the G35, abrupt control column deflection at a speed of 113 knots (Va, or maneuvering speed) could produce a 4.4 G structural load (Limit Load factor), while abrupt control column deflection at or above 152 knots (Vno/Vc, or maximum structural cruise speed) could produce a 6.6 G structural load (Ultimate Load limit ). Examination of the recorded radar data disclosed that the airplane was traveling at 142 knots at the time of the breakup. Engineering analysis concluded that in a level turn, the bank angle required to achieve Limit Load is 76.8 degrees, and the bank angle required to achieve the Ultimate Load is 81.2 degrees. FAA toxicology testing of the pilot revealed the presence of Diphenhydramine in urine, and Norverapamil, and Verapamil in urine and liver. The National Transportation Safety Board determines the probable cause(s) of this accident as follows: the pilot's entry into an abrupt maneuver at an excessive airspeed beyond Va, which resulted in exceeding the aircraft's design stress limits. ===
Accident occurred Friday, June 16, 2000 in WILLOWS, CA
Probable Cause Approval Date: 10/17/2001
Aircraft: Maule M4-210C, registration: N377BC
Injuries: 2 Fatal.
A witness saw the airplane complete the second and last set of two 360-degree turns just above treetop level over a herd of antelope and then descend to ground impact in a steep nose down attitude. This airplane was the last in a group of six other aircraft going to the same destination. Initial responders to the accident site said that a herd of antelope was in the immediate vicinity of the wreckage. Interviews with the other pilot's in the group revealed that both the pilot and passenger were avid animal lovers. They heard the pilot announce in a normal voice that he was turning downwind to base on the Common Traffic Advisory Frequency (CTAF). No other transmissions were heard from the airplane. The ground witness saw the airplane flying northbound at low level, and then enter the first set of steep 360-degree turns. The airplane ended this maneuver descending towards the ground in wings level flight and then rising up again, with a turn southbound. The airplane climbed above the tree line, leveled off, and then entered the second set of steep 360-degree turns, which culminated in the accident. Winds in the area were recorded from the north-northwest at 32 mph gusting to 42 mph. As the pilot turned from crosswind to downwind while in a steep turn about the antelope herd on the ground, it is likely that the airplane encountered strong wind shear like tailwind condition, which resulted in an inadvertent stall/spin. There were no discrepancies noted with the aircraft and engine. The National Transportation Safety Board determines the probable cause(s) of this accident as follows: Failure of the pilot to maintain an adequate airspeed margin while maneuvering in steep turns at low altitude in gusty and strong tailwind conditions, which lead to a wind shear encounter and a stall/spin. A contributing factor in the accident was the pilot's diverted attention due to looking at antelope on the ground, and, his decision to attempt the steep turns at low altitude. ===
Accident occurred Saturday, April 15, 2000 in WILLOWS, CA
Probable Cause Approval Date: 6/25/2003
Aircraft: Smith RV-4, registration: N63SM
Injuries: 2 Minor.
The pilot reported that he lost elevator control while in cruise flight. He was attempting to land at an airport on a runway he was nearly aligned with. Using the manipulation of aircraft trim and throttle as a means of controlling the aircraft's pitch attitude, he tried to gain altitude by trimming the airplane in the full aft position, but found the elevator to be jammed. The pilot reduced the throttle and mixture and landed in a field. The airplane came to rest in an upright position. An FAA inspector examined the airplane following recovery and reported that control rod was improperly installed, allowing the rear jam nut on the elevator push rod to work loose. The push rod then rotated off the forward connection. The National Transportation Safety Board determines the probable cause(s) of this accident as follows: Disconnection of the elevator push rod due to the owner/builder's improper installation of the rear jam nut on the elevator pushrod.


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