X-Mozilla-Keys:
I take it back. More than one crash. However there was only one engine
failure
if you can call it taht.
Paul Lamar
NTSB Report Brief
Accident Date: 04/24/94
Report adopted on: 11/18/1994
NTSB Accident ID: MIA94LA126
NTBS File No.: 333
Place of Accident: BUNNELL, FL
Aircraft Reg. No.: N54WP
Local Time of Accident: 10:30 EDT
------------------------------------------------------------------------------
Aircraft Make/Model: PARSONS BP GYRO
Aircraft Damage: Substantial
Engine Make/Model: MAZDA 12A
Number of Engines: 1
Operating Cerificates: None
Type of Flight Operation: Instructional
FAR Flight Conducted Under: 14 CFR 91
Crew Injuries, Fatal: 0
Crew Injuries, Serious: 0
Crew Injuries, Minor/None: 2
Pass. Injuries, Fatal: 0
Pass. Injuries, Serious: 0
Pass. Injuries, Minor/None: 0
------------------------------------------------------------------------------
Last Departure Point: Same as Accident
Destination: Local
Condition of Light: Daylight
Airport Proximity: On airport
Airport Name: BUNNELL FLAGLER COUNTY
Runway Identification: 06
Runway Surface: Asphalt
Runway Surface Condition: Dry
Weather Information Source: Weather observation facility
Basic Weather: Visual (VMC)
Lowest Ceiling: None
Visibility: 0015.000 SM
Wind Direction: Unk/Nr
Wind Speed: Unk/Nr
Temperature (F): 78
Obstruction to Vision: None
Precipitation: None
------------------------------------------------------------------------------
Age Pilot-in-Command (PIC): 49
PIC Certificates/Ratings: Commercial, Flight instructor#Single-engine
land, Multi-engine land#Gyroplane
PIC Instrument Ratings: Airplane
PIC Time, All Aircraft: 650
PIC Time, Last 90 Days: Unk/Nr
PIC Time, Total Make/Model: 220
PIC Time, Total Instrument: Unk/Nr
------------------------------------------------------------------------------
Accident Narrative:
The commercial pilot/certified flight instructor and student pilot
were on initial takeoff climb at about 150 to 200 feet agl on a
crosswind turn when the gryoplane experienced a total loss of
engine power. A forced landing was initiated and the gyroplane
touched down on the nose gear, nosed over and came to rest on its
right side. Examination of the gyroplane by the FAA and the
pilot-in-command revealed the alternator drive belt failed for
undetermined reasons, and severed the ignition wires.
------------------------------------------------------------------------------
Occurrence# 1 LOSS OF ENGINE POWER
Phase of Operation: TAKEOFF - INITIAL CLIMB
Findings:
1. - MISCELLANEOUS - FAILURE,TOTAL
2. - IGNITION SYSTEM,IGNITION LEAD - SEPARATION
------------------------------------------------------------------------------
Occurrence# 2 FORCED LANDING
Phase of Operation: DESCENT - EMERGENCY
Findings:
------------------------------------------------------------------------------
Occurrence# 3 NOSE OVER
Phase of Operation: LANDING - FLARE/TOUCHDOWN
Findings:
3. - FLIGHT CONTROLS - IMPROPER USE OF - PILOT IN COMMAND
------------------------------------------------------------------------------
Accident Cause:
THE PILOT-IN-COMMAND'S IMPROPER USE OF THE FLIGHT CONTROLS DURING
LANDING
FLARE TOUCHDOWN, RESULTING IN THE GYROPLANE TOUCHING DOWN ON THE NOSE
GEAR, AND SUBSEQUENT NOSE OVER. THE LOSS OF ENGINE POWER WAS ALSO A
CAUSE.
------------------------------------------------------------------------------
Accident Date: 06/18/94
Report adopted on: 05/10/1995
NTSB Accident ID: LAX94LA259
NTBS File No.: 1424
Place of Accident: SALINAS, CA
Aircraft Reg. No.: N999
Local Time of Accident: 16:04 PDT
------------------------------------------------------------------------------
Aircraft Make/Model: MASCARI DISCOVERY S-12
Aircraft Damage: Destroyed
Engine Make/Model: MAZDA RX7 ROTARY
Number of Engines: 1
Operating Cerificates: None
Type of Flight Operation: GROUND TEST
FAR Flight Conducted Under: 14 CFR 91
Crew Injuries, Fatal: 0
Crew Injuries, Serious: 1
Crew Injuries, Minor/None: 0
Pass. Injuries, Fatal: 0
Pass. Injuries, Serious: 0
Pass. Injuries, Minor/None: 0
------------------------------------------------------------------------------
Last Departure Point: Same as Accident
Destination: Local
Condition of Light: Daylight
Airport Proximity: Off airport/airstrip
Airport Name: SALINAS MUNICIPAL
Runway Identification: 31
Runway Surface: Asphalt
Runway Surface Condition: Dry
Weather Information Source: Weather observation facility
Basic Weather: Visual (VMC)
Lowest Ceiling: None
Visibility: 0025.000 SM
Wind Direction: 300
Wind Speed: 009 KTS
Temperature (F): 64
Obstruction to Vision: None
Precipitation: None
------------------------------------------------------------------------------
Age Pilot-in-Command (PIC): Unk
PIC Certificates/Ratings: None
PIC Instrument Ratings: None
PIC Time, All Aircraft: Unk/Nr
PIC Time, Last 90 Days: Unk/Nr
PIC Time, Total Make/Model: Unk/Nr
PIC Time, Total Instrument: Unk/Nr
------------------------------------------------------------------------------
Accident Narrative:
THE EXPERIMENTAL HOMEBUILT DISCOVERY S-12 AIRAILE INADVERTENTLY
BECAME AIRBORNE DURING HIGH-SPEED TAXI TESTS. THE MECHANIC CONDUCTING
THE TAXI TESTS WAS NOT A CERTIFICATED PILOT. HE CONTACTED THE TOWER
AND INFORMED THEM OF HIS SUPRISE FLIGHT. WITHIN MOMENTS THE ENGINE
FAILED, AND A FORCED LANDING WAS MADE IN A NEARBY FIELD. THE AIRPLANE
COLLIDED WITH A STANDPIPE. WITNESSES REPORTED THAT THE PROPELLER,
MUFFLER, AND REDUCTION GEARBOX HAD SEPARATED BEFORE THE AIRPLANE
STRUCK THE STANDPIPE. EXAMINATION REVEALED THAT THE MUFFLER FRACTURED
AT A FACTORY WELD; THE FRACTURE EXHIBITED EVIDENCE OF OXIDATION.
THE MUFFLER THEN SEPARATED AS A RESULT OF NORMAL VIBRATION DURING
OPERATION OF THE ENGINE. THE PROPELLER WAS DAMAGED AFTER THE MUFFLER
STRUCK IT. THE DAMAGED PROPELLER WAS THEN OUT OF BALANCE, RESULTING
IN THE REDUCTION GEARBOX SEPARATING FROM THE ENGINE.
------------------------------------------------------------------------------
Occurrence# 1 PROPELLER FAILURE/MALFUNCTION
Phase of Operation: TAKEOFF - INITIAL CLIMB
Findings:
1. - TAXISPEED - EXCESSIVE - UNQUALIFIED PERSON
2. - EXHAUST SYSTEM,MUFFLER - CORRODED
3. - EXHAUST SYSTEM,MUFFLER - SEPARATION
4. - PROPELLER SYSTEM/ACCESSORIES,BLADE - FOREIGN OBJECT DAMAGE
5. - PROPELLER SYSTEM/ACCESSORIES,BLADE - OUT OF BALANCE
6. - PROPELLER SYSTEM/ACCESSORIES,BLADE - SEPARATION
7. - REDUCTION GEAR ASSY,PROPELLER SHAFT - SEPARATION
------------------------------------------------------------------------------
Occurrence# 2 FORCED LANDING
Phase of Operation: EMERGENCY LANDING AFTER TAKEOFF
Findings:
------------------------------------------------------------------------------
Occurrence# 3 IN FLIGHT COLLISION WITH OBJECT
Phase of Operation: EMERGENCY LANDING AFTER TAKEOFF
Findings:
8. - OBJECT - POLE
------------------------------------------------------------------------------
Accident Cause:
THE FAILURE OF THE MUFFLER ASSEMBLY DUE TO PREEXISTING CRACKING IN THE
OXIDIZED AREA OF THE WELD, WITH SUBSEQUENT DAMAGE AND SEPARATION OF
THE PROPELLER AND REDUCTION GEAR BOX. A RELATED FACTOR WAS THE
EXCESSIVE TAXISPEED WHICH RESULTED IN THE AIRPLANE BECOMING
INADVERTENTLY AIRBORNE.
------------------------------------------------------------------------------
Accident Date: 07/03/94
Report adopted on: 12/07/1994
NTSB Accident ID: LAX94LA273
NTBS File No.: 562
Place of Accident: STOCKTON, CA
Aircraft Reg. No.: N51079
Local Time of Accident: 07:58 PDT
------------------------------------------------------------------------------
Aircraft Make/Model: ADAMS THORPE T-18
Aircraft Damage: Substantial
Engine Make/Model: MAZDA NSU WANKLE
Number of Engines: 1
Operating Cerificates: None
Type of Flight Operation: TEST FLIGHT
FAR Flight Conducted Under: 14 CFR 91
Crew Injuries, Fatal: 0
Crew Injuries, Serious: 0
Crew Injuries, Minor/None: 1
Pass. Injuries, Fatal: 0
Pass. Injuries, Serious: 0
Pass. Injuries, Minor/None: 0
------------------------------------------------------------------------------
Last Departure Point: Same as Accident
Destination: Local
Condition of Light: Daylight
Airport Proximity: Off airport/airstrip
Airport Name: STOCKTON METRO
Runway Identification: 29R
Runway Surface: Asphalt
Runway Surface Condition: Dry
Weather Information Source: Pilot
Basic Weather: Visual (VMC)
Lowest Ceiling: Unk/Nr
Visibility: 0015.000 SM
Wind Direction: variable
Wind Speed: Light
Temperature (F): 72
Obstruction to Vision: None
Precipitation: None
------------------------------------------------------------------------------
Age Pilot-in-Command (PIC): 42
PIC Certificates/Ratings: nk/Nr#Single-engine land
PIC Instrument Ratings: None
PIC Time, All Aircraft: 351
PIC Time, Last 90 Days: 3
PIC Time, Total Make/Model: 1
PIC Time, Total Instrument: Unk/Nr
------------------------------------------------------------------------------
Accident Narrative:
The accident flight was the second flight of the aircraft since
certification on April 6, 1994. The aircraft has a Mazda NSU wankle
rotary automobile engine installed and is operated on automotive
gasoline. The pilot was on initial climbout after takeoff when
the engine suddenly quit. The pilot was unable to make the runway
and executed a forced landing in a field near the airport. The
aircraft nosed over after encountering soft, rough terrain. The
pilot reported that the fuel lines and fuel pump do not have any
thermal shielding and he believes the engine failure was due to vapor
lock.
Occurrence# 1 LOSS OF ENGINE POWER
Phase of Operation: TAKEOFF - INITIAL CLIMB
Findings:
1. - FUEL SYSTEM,LINE - BLOCKED(TOTAL)
2. - FUEL SYSTEM,PUMP - BLOCKED(TOTAL)
3. - FLUID,FUEL - STARVATION
4. - ACFT/EQUIP, INADEQUATE DESIGN - MANUFACTURER
------------------------------------------------------------------------------
Occurrence# 2 FORCED LANDING
Phase of Operation: DESCENT - EMERGENCY
Findings:
------------------------------------------------------------------------------
Occurrence# 3 NOSE OVER
Phase of Operation: LANDING - ROLL
Findings:
5. - TERRAIN CONDITION - SOFT
------------------------------------------------------------------------------
Accident Cause:
A VAPOR LOCK INDUCED ENGINE FAILURE DUE TO INADEQUATE THERMAL
SHIELDING OF THE FUEL PUMP AND LINES. SOFT TERRAIN IN THE
LANDING AREA WAS A FACTOR.
------------------------------------------------------------------------------
Accident Date: 10/08/94
Report adopted on: 06/19/1995
NTSB Accident ID: SEA95LA007
NTBS File No.: 1862
Place of Accident: MADRAS, OR
Aircraft Reg. No.: N51MB
Local Time of Accident: 13:40 PDT
------------------------------------------------------------------------------
Aircraft Make/Model: BONY MB-1
Aircraft Damage: Destroyed
Engine Make/Model: MAZDA 12A
Number of Engines: 1
Operating Cerificates: None
Type of Flight Operation: Personal
FAR Flight Conducted Under: 14 CFR 91
Crew Injuries, Fatal: 0
Crew Injuries, Serious: 0
Crew Injuries, Minor/None: 1
Pass. Injuries, Fatal: 0
Pass. Injuries, Serious: 0
Pass. Injuries, Minor/None: 0
------------------------------------------------------------------------------
Last Departure Point: Same as Accident
Destination: PRINEVILLE,OR
Condition of Light: Daylight
Airport Proximity: Off airport/airstrip
Weather Information Source: Weather observation facility
Basic Weather: Visual (VMC)
Lowest Ceiling: None
Visibility: 0010.000 SM
Wind Direction: 060
Wind Speed: 003 KTS
Temperature (F): 73
Obstruction to Vision: None
Precipitation: None
------------------------------------------------------------------------------
Age Pilot-in-Command (PIC): 58
PIC Certificates/Ratings: Private#Single-engine land
PIC Instrument Ratings: None
PIC Time, All Aircraft: 197
PIC Time, Last 90 Days: 28
PIC Time, Total Make/Model: 71
PIC Time, Total Instrument: Unk/Nr
------------------------------------------------------------------------------
Accident Narrative:
WHILE CLIMBING OUT AFTER TAKEOFF, ABOUT 500 FEET ABOVE THE GROUND,
THE HOME BUILT AIRPLANE SUDDENLY ENTERED AN UNCOMMANDED RIGHT TURN.
THE PILOT ATTEMPTED TO APPLY LEFT RUDDER BUT COULD NOT.
THE RUDDER HAD JAMMED TO THE RIGHT. WHILE THE PILOT CONTINUED TO
MANEUVER THE AIRPLANE AND REMEDY THE SITUATION, HE SUDDENLY OBSERVED
POWERLINES AHEAD OF THE AIRPLANE AND BANKED AWAY FROM THEM.
THE AIRPLANE AERODYNAMICALLY STALLED AND SPUN INTO THE GROUND DURING
THE MANEUVER. AN EXAMINATION OF THE WRECKAGE TO DETERMINE FLIGHT
CONTROL FUNCTION WAS NOT POSSIBLE DUE TO FIRE AND IMPACT DAMAGE.
------------------------------------------------------------------------------
Occurrence# 1 AIRFRAME/COMPONENT/SYSTEM FAILURE/MALFUNCTION
Phase of Operation: CLIMB
Findings:
1. - FLT CONTROL SYST,RUDDER CONTROL - JAMMED
2. - REASON FOR OCCURRENCE UNDETERMINED
------------------------------------------------------------------------------
Occurrence# 2 LOSS OF CONTROL - IN FLIGHT
Phase of Operation: MANEUVERING
Findings:
3. - AIRCRAFT CONTROL - NOT POSSIBLE
4. - AIRSPEED(VS) - NOT MAINTAINED - PILOT IN COMMAND
------------------------------------------------------------------------------
Occurrence# 3 IN FLIGHT COLLISION WITH TERRAIN/WATER
Phase of Operation: DESCENT - UNCONTROLLED
Findings:
5. - TERRAIN CONDITION - OPEN FIELD
------------------------------------------------------------------------------
Accident Cause:
THE JAMMING OF THE RUDDER DURING DUE TO UNDETERMINED REASONS.
CONTRIBUTING TO THE ACCIDENT WAS THE PILOT-IN-COMMAND'S FAILURE TO
MAINTAIN ADEQUATE FLYING SPEED WHILE ATTEMPTING TO TAKE REMEDIAL ACTION.
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