Ultralight aircraft accidents, experimental aircraft accidents, light sport aircraft accident reports 5

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Ultralight Aircraft Accident Data

Aircraft: CHALLENGER II, registration: N425DE
Injuries: 1 Fatal.

WHILE CONDUCTING A 6 MILE FLIGHT FROM A PRIVATE AIRSTRIP TO A COUNTY AIRPORT, THE PILOT ENCOUNTERED IN FLIGHT WINDS WHICH EXCEEDED THE PERFORMANCE CAPABILITY OF THE AIRCRAFT. AIRCRAFT ALTITUDE CONTROL WAS NOT POSSIBLE AND THE AIRCRAFT IMPACTED THE GROUND IN UNCONTROLLED FLIGHT.
Probable Cause
AN IN FLIGHT ENCOUNTER WITH WIND CONDITIONS WHICH EXCEEDED THE AIRCRAFT PERFORMANCE CAPABILITY. A FACTOR WAS: THE PILOT'S FAILURE TO OBTAIN AVAILABLE EN ROUTE WEATHER INFORMATION.

Accident occurred APR-08-91 at THOMASTON, GA
Aircraft: LEWIS CHALLENGER II, registration: N283EL
Injuries: 1 Fatal.

N283EL WAS THE THIRD AIRPLANE OF A FLIGHT OF THREE. THE OTHER AIRPLANES CLIMBED OUT WITHOUT INCIDENT, BUT AS N283EL STARTED ITS CLIMB, REPORTEDLY THE ENGINE LOST POWER. WITNESSES REPORTED THAT THE PILOT APPEARED TO HAVE STARTED A LEFT TURN AND CRASHED 180 DEGREES FROM THE TAKEOFF HEADING ON THE PARALLEL TAXIWAY. DURING THE WRECKAGE EXAMINATION WATER WAS FOUND IN THE CARBURETOR BOWL AND THE SPARK PLUGS WERE FOULED. THE PILOT HAD PREVIOUSLY REPORTED A ROUGH RUNNING ENGINE, BUT LATER REPORTED THAT THE PROBLEM HAD BEEN CORRECTED. ACCORDING TO THE OPERATIONAL LIMITATION FOR THE AIRPLANE, A CONDITIONAL INSPECTION IS REQUIRED ANNUALLY. THERE WAS NO RECORD OF A COMPLETED CONDITIONAL INSPECTION SINCE THE AIRPLANE WAS CERTIFICATED IN 1988. SUFFICIENT RUNWAY WAS AVAILABLE FOR A FORCED LANDING.
Probable Cause
THE PILOT'S FAILURE TO PROPERLY MAINTAIN THE AIRPLANE IN ACCORDANCE WITH PRESCRIBED PROCEDURES WHICH RESULTED IN FUEL CONTAMINATION, FOULED SPARK PLUGS, AND A LOSS OF ENGINE POWER. THE PILOT ALSO FAILED TO FOLLOW NORMAL EMERGENCY PROCEDURES FOR THE LOSS OF ENGINE POWER AFTER LIFTOFF AND STALLED THE AIRPLANE.

Accident occurred AUG-10-91 at COLORADO SPRING, CO
Aircraft: LARS AVID FLYER, registration: N49BP
Injuries: 1 Uninjured.

THE PILOT REPORTED HEARING TWO SUCCESSIVE LOUD EXPLOSIONS. ENGINE RPMS DROPPED FROM 6500 TO 2800-3000, AND THE ENGINE DID NOT RESPOND TO THROTTLE APPLICATION. THE PILOT MADE A NO-FLAP FORCED LANDING. WHEN HE ATTEMPTED TO FLARE WITH FULL AFT ELEVATOR, THERE WAS NO RESPONSE. CONTROL CONTINUITY WAS LATER ESTABLISHED. THE ENGINE WAS FUNCTIONALLY TESTED AND DEVELOPED FULL POWER. SUBSEQUENT ENGINE DISASSEMBLY DISCLOSED THE PISTON RINGS WERE STUCK IN THE RING GROOVES.
Probable Cause
THE PILOT'S DELAY IN FLARING THE AIRPLANE. FACTORS WERE: (1) STUCK PISTON RINGS AND (2) THE PILOT'S FAILURE TO USE FLAPS.

Accident occurred JUL-28-91 at KILLEN, AL
Aircraft: HINTON KITFOX, registration: N174PH
Injuries: 1 Uninjured.

DURING LANDING, A DOG WANDERED ONTO THE RUNWAY INTO THE PATH OF THE LANDING ROLL. A GO-AROUND WAS BEGUN, DURING WHICH THE ENGINE LOST POWER. WIRES AT THE END OF THE RWY FORCED THE PILOT TO DUCK UNDER THEM AND THE AIRPLANE HIT A POLE. A MECHANIC RAN THE ENGINE AFTERWARDS AND NOTHING WAS FOUND TO PRECLUDE NORMAL OPERATION. HE ALSO NOTED THAT THE CARBURETOR MOUNT INSULATED THE CARBURETOR FROM THE ENGINE HEAT AND NO CARBURETOR HEAT SYSTEM WAS INSTALLED. HUMIDITY CONDITIONS WERE CONDUCIVE TO CARBURETOR ICING.
Probable Cause
WEATHER CONDITIONS CONDUCIVE TO CARBURETOR ICING. A FACTOR WAS THE LACK OF A CARBURETOR HEAT SYSTEM ON THE ENGINE.

Accident occurred JUL-04-91 at MYRTLE CREEK, OR
Aircraft: DEREGO AVID FLYER/B, registration: N220B
Injuries: 2 Minor.

SHORTLY AFTER TAKEOFF, THE ENGINE LOST PARTIAL POWER. THE PILOT ATTEMPTED TO RETURN TO THE AIRPORT; HOWEVER, THE AIRPLANE WAS UNABLE TO MAINTAIN ALTITUDE. AN OFF AIRPORT LANDING WAS INITIATED TO AN OPEN FIELD. DURING THE DESCENT, THE AIRPLANE COLLIDED WITH POWER LINES. DURING THE LANDING ROLL, THE AIRPLANE NOSED OVER. POST CRASH INSPECTION OF THE ENGINE DID NOT REVEAL ANY MECHANICAL FAILURES OR MALFUNCTIONS. THE ELECTRICAL SYSTEM WAS DAMAGED AND TESTING WAS NOT POSSIBLE.
Probable Cause
LOSS OF ENGINE POWER FOR AN UNDETERMINED REASON.

Accident occurred APR-06-91 at BULLHEAD CITY, AZ
Aircraft: BURNETT, JERRY D. CHALLENGER II, registration: N4555J
Injuries: 1 Uninjured.

THE PILOT PURCHASED THE AIRPLANE AFTER RECEIVING A 3 HOUR CHECKOUT A DAY PRIOR TO THE ACCIDENT. HE DEPARTED BULLHEAD CITY AIRPORT IN THE MORNING OF THE ACCIDENT AND PROCEEDED TO THE PRACTICE AREA ABOUT 5 MILES NORTH OF THE AIRPORT. AFTER PRACTICING SOME MANEUVERS AND WHILE FLYING AT NORMAL CRUISE HE BEGAN A TURN. WHILE IN THE TURN THE DEBRIS BEGAN TO COME OFF THE AIRPLANE AND IT BEGAN TO VIOLENTLY VIBRATE. HE AIRPLANE BECAME IMPOSSIBLE TO CONTROL BUT THE PILOT WAS ABLE TO LAND IN A ROUGH/UNEVEN AREA, BUT NOT WITHOUT DAMAGING THE AIRPLANE. EXAMINATION OF THE PROPELLER DISCLOSED THAT IT DISINTEGRATED WHILE IN FLIGHT.
Probable Cause
THE DISINTEGRATION OF THE PROPELLER. CONTRIBUTING TO THIS ACCIDENT WAS THE DETERIORATION OF AIRCRAFT CONTROL AND THE NONAVILABILITY OF SUITABLE LANDING TERRAIN.

Accident occurred AUG-08-91 at O'BRIEN, FL
Aircraft: SCHULTZ AVID FLYER 502, registration: N15DW
Injuries: 1 Minor.

THE PRIVATE PILOT WAS LANDING AT AN ULTRALIGHT LANDING AREA WITH A KNOWN OBSTACLE (ELECTRICAL SERVICE LINE). THE HOMEBUILT AIRPLANE COLLIDED WITH THE ELECTRICAL SERVICE LINE AND THE TERRAIN. THE PILOT DID NOT HAVE A CURRENT BIENNIAL FLIGHT REVIEW OR A MEDICAL CERTIFICATE AT THE TIME OF THE ACCIDENT.
Probable Cause
THE PILOT IN COMMAND'S IMPROPER PLANNED FINAL APPROACH, WHICH RESULTED IN AN IN FLIGHT COLLISION WITH AN ELECTRICAL SERVICE LINE, AND IN FLIGHT COLLISION WITH TERRAIN.

Accident occurred AUG-26-91 at JACKSONVILLE, FL
Aircraft: MAXAIR ARV-582, registration: NONE
Injuries: 2 Serious.

THE AIRPLANE WAS OBSERVED BY WITNESSES IN THE TRAFFIC PATTERN AT 150 FEET AGL WITH A 20 TO 30 DEGREE NOSE UP ATTITUDE. THE AIRPLANE BEGAN A LEFT TURN TOWARDS THE RUNWAY WITH A 30 DEGREE ANGLE OF BANK. THE LEFT WING DROPPED DOWN 90 DEGREES, THE NOSE PITCHED DOWN 60 DEGREES, AND THE AIRPLANE DISAPPEARED BELOW THE TREE LINE COLLIDING WITH THE TERRAIN. THE AIRPLANE SUSTAINED SUBSTANTIAL DAMAGE. THE OWNER STATED IN AN INTERVIEW WITH THE FAA THAT THE PIC STALLED THE AIRPLANE. THE PILOT DID NOT HOLD A RATING TO FLY AIRPLANES AND IN ADDITION, DID NOT HAVE A CURRENT MEDICAL CERTIFICATE.
Probable Cause
THE UNQUALIFIED PILOT'S FAILURE TO MAINTAIN AIRSPEED (VSO) WHILE MANEUVERING TO LAND, WHICH RESULTED IN AN IN FLIGHT LOSS OF CONTROL, STALL SPIN, AND COLLISION WITH TERRAIN.

Accident occurred AUG-24-91 at SANTA MARGARITA, CA
Aircraft: BEIERLE THUNDER GULL J, registration: UNREG
Injuries: 1 Serious, 1 Minor.

THE CERTIFICATED PRIVATE PILOT AND A PASSENGER WERE CONDUCTING A FLIGHT TEST OF AN UNREGISTERED, HOMEBUILT AIRPLANE. THE AIRPLANE WAS BEING MARKETED AS AN ULTRALIGHT VEHICLE WITH AN EXCEPTION OF THE ULTRALIGHT REGULATIONS GRANTED TO THE EXPERIMENTAL AIRCRAFT ASSOCIATION. THE PILOT WAS PERFORMING AEROBATIC MANEUVERS WHILE THE PASSENGER WAS FILMING THE EVENT FROM THE REAR SEAT. DURING THE PULL-UP PORTION OF AN IMMELMAN MANEUVER, THE LEFT WING FAILED AND FOLDED UPWARDS. THE PILOT DEPLOYED A BALLISTIC PARACHUTE TO CONTROL THE AIRPLNE'S DESCENT. AS THE PARACHUTE DEPLOYED, IT BECAME ENTANGLED WITH THE ENGINE PROPELLER AND WAS DAMAGED AND ONLY PARTIALLY INFLATED. THE AIRPLANE DESCENDED AND STRUCK THE GROUND AT ABOUT 50 MPH. THE AIRPLANE AND PILOT DID NOT QUALIFY FOR THE CONDITIONS OF THE ULTRALIGHT REGULATION EXEMPTION, AND THE VEHICLE IS CONSIDERED TO BE AN AIRPLANE.
Probable Cause
THE FAILURE OF THE WING SPAR WHEN THE DESIGN LIMITS OF THE AIRPLANE WAS EXCEEDED BY THE PILOT. CONTRIBUTING TO THE ACCIDENT WAS AN INADEQUATE AIRFRAME DESIGN AND AN ABRUPT MOVEMENT OF THE FLIGHT CONTROLS BY THE PILOT.

Accident occurred AUG-13-91 at MEXICO, MO
Aircraft: MANVILLE AVID FLYER, registration: N714J
Injuries: 1 Minor.

THE ACCIDENT AIRPLANE WAS SUBSTANTIALLY DAMAGED WHEN IT WENT OFF THE SIDE OF THE RUNWAY DURING A LANDING ROLL AND GROUND LOOPED IN SOFT TERRAIN. THE ACCIDENT OCCURRED DURING THE AIRPLANE'S INITIAL TEST FLIGHT.
Probable Cause
FAILURE OF THE PILOT TO MAINTAIN DIRECTIONAL CONTROL DURING A LANDING ROLL. A FACTOR ASSOCIATED WITH THE ACCIDENT IS THE PILOT'S LACK OF FAMILIARITY WITH THE ACCIDENT AIRPLANE.

Accident occurred AUG-31-91 at OTTUMWA, IA
Aircraft: TULLIS TIERRA II, registration: N2162S
Injuries: 2 Fatal.

THE ACCIDENT AIRPLANE WAS OBSERVED TO DESCEND STEEPLY INTO TERRAIN WHILE CIRCLING A FAMILY FARM. NO MECHANICAL DEFECTS WERE DISCOVERED IN THE AIRPLANE DURING A POST-ACCIDENT INSPECTION.
Probable Cause
FAILURE OF THE PILOT TO MAINTAIN CONTROL OF THE AIRPLANE DURING MANEUVERING FLIGHT.

Accident occurred SEP-07-91 at MARION, OH
Aircraft: TIMOTHY WINGATE S-7 COURIER, registration: N42784
Injuries: 1 Serious, 1 Minor.

THE PILOT DEPARTED RUNWAY 22, IMMEDIATELY FOLLOWING A LARGER AIRPLANE. THE AIRCRAFT ROLLED INVERTED AND IMPACTED THE RUNWAY IN A STEEP NOSE DOWN ATTIUTDE. WITNESSES STATED THAT THEY SAW ITS "WINGS ROCKING" JUST BEFORE THE ACCIDENT. THE FAA FOUND NO FLIGHT CONTROL MALFUNCTIONS.
Probable Cause
THE PILOT'S FAILURE TO MAINTAIN ADEQUATE SEPARATION BEHIND A DEPARTING LARGER AIRCRAFT RESULTED IN TURBULENCE ENCOUNTER & SUBSEQUENT LOSS OF CONTROL.

Accident occurred JUL-04-91 at LEBANON, IN
Aircraft: WILBUR D. BATMAN CHALLENGER II, registration: N503DB
Injuries: 1 Minor.

PILOT EXPERIENCED A TOTAL LOSS OF ENGINE POWER AFTER PERFORMING A FLY OVER OF A PRIVATE AIRSTRIP. PILOT ATTEMPTED TO EXECUTE A FORCED LANDING WITHIN THE FIELD BOUNDARIES AND STALLED THE AIRCRAFT AT APPROXIMATELY 30 FEET ABOVE GROUND, AND IMPACTED IN A NOSE DOWN ATTITUDE. INVESTIGATION REVEALED A FAILED ENGINE STARTER CLUTCH CAUSED THE POWER LOSS.
Probable Cause
FAILURE TO MAINTAIN STALL AIRSPEED WHILE EXECUTING A FORCED LANDING. A FACTOR RELATED TO THE ACCIDENT IS FAILURE OF THE ENGINE STARTER CLUTCH.

Accident occurred JAN-27-91 at ROUND LAKE, NY
Aircraft: HAYES KOLB/TWINSTAR, registration: N71817
Injuries: 1 Fatal.

THE AMATEUR BUILT ACFT WAS ON ITS 1ST FLT AFTER BEING CONSTRUCTED. IT FLEW ABOUT 5 MIN BEFORE THE OWNER/BUILDER/PLT RETURNED THE PLANE FOR LANDING. AT ABOUT 75 FT AGL ON FINAL APCH, BOTH WINGS FAILED & THE ACFT CRASHED. INVESTIGATION REVEALED THAT STEEL BOLTS WERE MISSING FROM THE OUTBOARD WING STRUT ATTACHMENT FITTINGS, RIVETS THAT HELD THE OUTBOARD ATTACHMENT FITTINGS TO THE WING HAD SHEARED OFF. THE REASON FOR THE MISSING BOLTS AND SHEARED REVITS WAS NOT VERIFIED. THE ACFT HAD BEEN REGISTERED WITH THE FAA, BUT THERE WAS NO AIRWORTHINESS CERTIFICATE. ALSO, NO WEIGHT & BALANCE DATA WAS FOUND IN THE ACFT, THE PLT WAS NOT AN FAA CERTIFIED AIRMAN, NOR DID HE POSSESS A VALID FAA MEDICAL CERTIFICATE.
Probable Cause
IN-FLIGHT STRUCTURAL FAILURE OF THE OUTBOARD WING ATTACHMENT FITTINGS ON BOTH WINGS DUE TO AN UNDETERMINED REASON.

Accident occurred OCT-01-91 at SONORA, CA
Aircraft: CANO AVID FLYER, registration: N860CD
Injuries: 1 Uninjured.

THE PILOT STATED IN HIS WRITTEN REPORT THAT HE REFUELED THE AIRCRAFT PRIOR TO DEPARTURE WITH ABOUT 19 GALLONS OF AVIATION FUEL. ACCORDING TO THE PILOT, HE DEPARTED COLUMBIA AND CLIMBED TO ABOUT 10,000 FEET WHILE HE FLEW AROUND THE SIERRA NEVADA MOUNTAINS. AT ABOUT 1200 HOURS, HE TURNED AND HEADED BACK TO COLUMBIA. HE REPORTED THAT THE ENGINE BEGAN TO SURGE AND THE REAR CYLINDER EGT INDICATED A POTENTIAL FUEL STARVATION PROBLEM. THE ENGINE WAS NOT PRODUCING SUFFICIENT POWER TO MAINTAIN FLIGHT AND THE PILOT SET UP FOR A FORCED LANDING IN A MOUNTAIN MEADOW. HE STATED THAT THE ENGINE CONTINUED TO SURGE, EVEN AFTER THE THROTTLE WAS REDUCED TO IDLE, WHICH CAUSED THE AIRCRAFT TO OVER SHOOT HIS INTENDED LANDING SPOT. THE AIRCRAFT COLLIDED WITH TREES AT THE FAR END OF THE MEADOW. THE PILOT SAID THE AIRCRAFT IS NOT EQUIPPED WITH AN ELECTRIC BOOST PUMP. HE SPECULATED THAT THE ENGINE POWER PROBLEM WAS DUE TO EITHER VAPOR LOCK OR A MALFUNCTION OF THE ENGINE DRIVEN PUMP.
Probable Cause
FUEL STARVATION DUE TO VAPOR LOCK.

Accident occurred NOV-23-91 at WEST JORDAN, UT
Aircraft: KITFOX TEN, INC MODEL 2, registration: N66257
Injuries: 1 Uninjured.

THE ENG QUIT IN CRUISE FLT WHEN IT OVERHEATED AND THE PILOT MADE AN EMERGENCY FORCED LDG IN AN OPEN FIELD. THE ACFT IMPACTED A LOG DURING LDG GND ROLL AND NOSED OVER. EXAM OF THE ACFT REVEALED THE LIQUID COOLANT FOR THE ENG WAS LOW.
Probable Cause
THE LOSS OF ENGINE POWER WHEN IT OVERHEATED DUE TO LOW COOLANT LEVEL, WHICH RESULTED FROM THE INADEQUATE PREFLIGHT INSPECTION BY THE PILOT. A FACTOR RELATING TO THE ACCIDENT WAS THE OBSTRUCTION IN THE LANDING AREA.

Accident occurred NOV-22-91 at SAN YSIDRO, CA
Aircraft: SPEYER AVID AMPHIBIAN, registration: N118A
Injuries: 1 Fatal.

THE CERTIFICATED COMMERCIAL PILOT, THE SOLE OCCUPANT, WAS CONDUCTING FLIGHT TESTS ON A NEWLY MANUFACTURED EXPERIMENTAL, AMATEUR BUILT AIRPLANE. WHILE ORBITING OVER AN AIRPORT, THE PILOT DECLARED AN EMERGENCY AND WAS OBSERVED DESCENDING IN A LEFT SPIRALLING DIVE. THE LEFT FLAPERON AND LEFT WING SEPARATED FROM THE FUSELAGE. THE PILOT, WHO WAS WEARING A PARACHUTE, ATTEMPTED TO BAIL OUT OF THE AIRPLANE AT LOW ALTITUDE. THE PARACHUTE FAILED TO SUFFICIENTLY OPEN DUE TO THE LOW ALTITUDE. AN EXAMINATION OF THE SEPARATED FLAPERON DISCLOSED CYCLIC OVERLOAD AND OVERTRAVEL ATTRIBUTED TO FLUTTER. FLAPERON COUNTER WEIGHTS WERE STRONGLY RECOMMENDED BY THE MANUFACTURER TO PREVENT FLUTTER. THE PILOT ELECTED NOT TO INSTALL THE COUNTER WEIGHTS BECAUSE IT WOULD IMPOSE AN ADDITION OF WEIGHT, AND THE PILOT FELT THAT THEY WERE NOT NEEDED.
Probable Cause
FAILURE OF THE PILOT/BUILDER TO FOLLOW THE MANUFACTURER'S RECOMMENDED AIRFRAME MODIFICATION PROCEDURE TO PREVENT THE INFLIGHT LOSS OF A FLAPERON DUE TO FLUTTER. CONTRIBUTING TO THE ACCIDENT WAS IN INFLIGHT SEPARATION OF THE WING WHEN THE DESIGN LIMITS OF THE AIRFRAME WERE EXCEEDED.

Accident occurred OCT-13-91 at MORICHES, NY
Aircraft: CHALLENGER II BOMBADIER, registration: N8182K
Injuries: 1 Fatal, 1 Serious.

THE PILOT WAS ON FINAL APPROACH IN A HOMEBUILT AIRPLANE WHEN HE EXPERIENCED A FLIGHT CONTROL PROBLEM. ACCORDING TO A PASSENGER, THE RIGHT FLAPERON DID NOT RESPOND TO CONTROL INPUTS. THE AIRPLANE BANKED LEFT AND CRASHED.
Probable Cause
A LOSS OF CONTROL IN FLIGHT DUE TO A FLIGHT CONTROL MALFUNCTION FOR UNDETERMINED REASONS.

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