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NTSB Report
October 11, 1989 · Beech F33A · N67536
Goodyear, AZ
Overview
Report Status
Probable Cause
Event Type
Accident
Date
October 11, 1989
Injury Outcomes
3 injuries (3 fatalities)
Location
Goodyear, AZ
Aircraft
Beech F33A
Tail Number
N67536
Operator
Airline Training Center
Injuries
Fatal
Aircraft Damage
Destroyed
NTSB Number
LAX90FA008
DURING THE TAKEOFF INITIAL CLIMB, ONE PROPELLER BLADE SEPARATED AND THE RESULTING IMBALANCE CAUSED THE REMAINING PROPELLER BLADE AND HUB TO SEPARATE. WITNESSES SAW THE AIRCRAFT PITCH UP, THEN ENTER A RIGHT TURN, IN AN APPARENT MANEUVER TO RETURN TO THE RUNWAY. WITNESSES SAW THE AIRCRAFT BANK ANGLE CONTINUE TO STEEPEN UNTIL THE AIRCRAFT ROLLED OVER AND ENTERED A SPIN. METALLURGICAL EXAMINATION OF THE FAILED BLADE REVEALED THAT IT SEPARATED DUE TO A FATIGUE FRACTURE IN THE FIRST FULL THREAD OF THE THREADED SHANK PORTION, WHICH FITTED INSIDE A FERRULED FITTING. EXTENSIVE METALLURGICAL EXAMINATION OF THE FRACTURE FAILED TO IDENTIFY THE INITIATING DEFECT IN THE FATIGUE FRACTURE. ON SITE EXAMINATION REVEALED THAT THE WINDSHIELD WAS HEAVILY COATED WITH ENGINE OIL.
NTSB Probable Cause
THE INFLIGHT SEPARATION OF ONE PROPELLER BLADE DUE TO A FATIGUE FRACTURE OF UNDETERMINED ORIGIN, AND FAILURE OF THE PILOT TO MAINTAIN CONTROL OF THE AIRCRAFT DURING AN ATTEMPT TO RETURN TO THE RUNWAY. A FACTOR IN THE ACCIDENT WAS THE OIL COVERED WINDSHEILD, WHICH HINDERED THE PILOT IN MAINTAINING OUTSIDE VISUAL REFERENCES DURING A LOW ALTITUDE MANEUVER.
Full Narrative
DURING THE TAKEOFF INITIAL CLIMB, ONE PROPELLER BLADE SEPARATED AND THE RESULTING IMBALANCE CAUSED THE REMAINING PROPELLER BLADE AND HUB TO SEPARATE. WITNESSES SAW THE AIRCRAFT PITCH UP, THEN ENTER A RIGHT TURN, IN AN APPARENT MANEUVER TO RETURN TO THE RUNWAY. WITNESSES SAW THE AIRCRAFT BANK ANGLE CONTINUE TO STEEPEN UNTIL THE AIRCRAFT ROLLED OVER AND ENTERED A SPIN. METALLURGICAL EXAMINATION OF THE FAILED BLADE REVEALED THAT IT SEPARATED DUE TO A FATIGUE FRACTURE IN THE FIRST FULL THREAD OF THE THREADED SHANK PORTION, WHICH FITTED INSIDE A FERRULED FITTING. EXTENSIVE METALLURGICAL EXAMINATION OF THE FRACTURE FAILED TO IDENTIFY THE INITIATING DEFECT IN THE FATIGUE FRACTURE. ON SITE EXAMINATION REVEALED THAT THE WINDSHIELD WAS HEAVILY COATED WITH ENGINE OIL.
Flight
Event TypeAccident
Event Time09:33 MST
Nearest AirportLitchfield (0nm N)
Runway21
Runway Length8500 ft
Runway Width150 ft
Flight Plan FiledCvfr
Aircraft FireNo
Aircraft ExplosionNo
Aircraft
AircraftBeech F33A
Tail NumberN67536
Aircraft CategoryAir
DamageDestroyed
OperatorAirline Training Center
Operating RulePart 91
Engines1
Engine TypeReciprocating
Engine DetailsContinental · IO-520-BB · Reciprocating · 285
Seats4
People & Injuries
Injury Summary3 injuries (3 fatalities)
Fatal3
Serious0
Minor0
Uninjured0
Total3
Crew 1Age 28 · Third Class
Conditions
ConditionsVMC
LightDaylight
WindCalm
Visibility40 sm
CeilingNone
Temperature / Dew Point46
Altimeter30.00 inHg
Observation Time16:45
Weather SourceWFAC