Pilot Debrief

AVIA STROITEL AC-5M near North Plains, OR — 2023-07-05

Final reportWPR23LA255
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Date
2023-07-05
Location
North Plains, OR, USA
Airport
1OR4
Aircraft
AVIA STROITEL AC-5M
Registration
N40233
Category
Glider
Highest injury
Serious
Fatalities
0
Phase of flight
Maneuvering

Probable cause

The pilot’s failure to maintain control of the motor glider, which resulted in an inflight overstress separation of the right wing during a high-speed, high-wing-load spiral dive recovery. Contributing to the accident was the inadequately manufactured wing structure.

Contributing factors

Contributing to the accident was the inadequately manufactured wing structure.

NTSB narrative

The pilot stated the airspeed may have been too slow when he initiated a 30° - 45° right turn during his first flight in the foreign-manufactured experimental motor glider. The glider immediately entered a clockwise, tight spiraling dive. After several revolutions, he was able to arrest the rotation, but the motor glider’s high airspeed produced significant vibrations. He applied gentle aft pressure on the control stick to regain control, but an inflight separation of the right wing ensued. The pilot released the canopy, egressed about 500 ft above ground level (agl), and deployed his parachute. The motor glider impacted the ground, and the pilot’s parachute landing resulted in serious injury. Postaccident examination of the motor glider’s wing structure revealed that the right wing’s main spar fractured due to overstress from upward bending loads. No evidence of fatigue was observed with the fracture. However, the wing spar was likely weaker than expected due to wrinkles in the composite fiber reinforcement layers in the upper and lower caps at the critical location where the spar intersected the reinforced closeout rib at the inboard section of the wing. Since the overstress fractures showed no evidence of damage before separation from a progressive failure mechanism or impact, the loads on the right wing during the accident flight were likely higher than any previously applied loads. However, the extent and angle of the wrinkles in the reinforcement layers at the fracture location indicated that the load that produced the right wing failure in this accident was considerably less than the expected failure load for the design and was possibly lower than the expected maximum design operating load. However, without knowing the actual ratio between the design ultimate failure load and the maximum design operating load of the wing for this experimental foreign-made aircraft, it is uncertain whether the design maximum operating load was exceeded based solely on analysis of the lab findings.

Analysis

Primary failure mode
Loss of control
First missed decision gate
Pilot could have avoided the tight turn with insufficient airspeed.

NTSB coding

Evidence available

  • Photos
  • 9 docket documents
View NTSB final reportView NTSB docket

Docket documents9

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