Pilot Debrief

PIPER PA-28-180 near Millsap, TX — 2011-08-07

Final reportCEN11LA555
Sign in to save
Date
2011-08-07
Location
Millsap, TX, USA
Aircraft
PIPER PA-28-180
Registration
N7689W
Category
Airplane
Highest injury
None
Fatalities
0
Phase of flight
Climb

Probable cause

A sudden loss of engine thrust due to the separation of a propeller blade in cruise flight due to high cycle fatigue.

NTSB narrative

The pilot had just leveled off to cruise flight when the airplane jerked and began to vibrate violently. The pilot secured the engine and made a forced landing on a road. A postaccident examination revealed that an 18-inch section of one of the propeller blades had separated. Metallurgical examination of the remaining blade section revealed striations on the fracture surface consistent with high-cycle fatigue. At least three crack arrest marks were observed, which was consistent with the stopping and starting of the cyclic stresses. The propeller had accumulated 165.73 hours since being overhauled in 2004. The most recent 100-hour inspection was completed about 10 months before the accident. The Federal Aviation Administration issued Airworthiness Directive (AD) 69-09-03 R3 in 1996 to prevent propeller blade tip fatigue failure. The directive required that pilots avoid continuous operation between 2150 and 2350 rpm. The failure mode of the blade was consistent with it operating in the restricted rpm range. Due to the multiple arrest marks found in the examination, the fatigue crack had propagated over multiple flight cycles. It could not be determined when the fatigue crack was initiated.

Analysis

Primary failure mode
Mechanical failure
First missed decision gate
Performing a thorough inspection of the propeller before the flight.

NTSB coding

Evidence available

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

Docket documents4

Related mishaps