Ultralight aircraft accidents, experimental aircraft accidents, light sport aircraft accident reports 6

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Ultralight Aircraft Accident Data

Accident occurred OCT-13-91 at HARTFORD, VT
Aircraft: DENNEY AIRCRAFT BEHN KIT FOX III, registration: N898KG
Injuries: 2 Uninjured.

THE PILOT MISREAD THE TERRAIN AND INITIATED AN APPROACH TO RISING TERRAIN. HE MADE A GO AROUND AND WAS UNABLE TO LOWER THE NOSE ENOUGH TO ACCELERATE. DURING THE GO AROUND, THE AIRPLANE ENTERED A STALL/SPIN. IN ADDITION, THE WINDS WERE GUSTY AND THE AIRPLANE WAS FLYING THROUGH TURBULENT AIR.
Probable Cause
AN INADVERTENT STALL/SPIN. FACTORS RELATED TO THE ACCIDENT WERE AN IMPROPERLY PLANNED APPROACH BY THE PILOT, THE FAILURE OF THE PILOT TO ATTAIN AND MAINTAIN FLYING SPEED, RISING TERRAIN, AND TURBULENT AIR CONDITIONS.

Accident occurred NOV-17-91 at PALMER, MA
Aircraft: ADVANCED AVIATION BUCCANEER SX B1B-503, registration: NONE
Injuries: 1 Serious.

AFTER TAKEOFF, THE PILOT STARTED A TURN. HE HEARD SOMETHING LET GO AND THE RUDDER AND ELEVATOR JAMMED. HE WAS UNABLE TO CONTROL THE AIRPLANE AND MADE AN UNCONTROLLED DESCENT INTO TREES. POST ACCIDENT INVESTIGATION DISCLOSED THE LOWER RUDDER ATTACH PIVOT BOLT HAD FAILED DUE TO CORROSION. THE AIRPLANE WAS AN ULTRALIGHT OPERATING AS AN UNREGISTERED AIRPLANE.
Probable Cause
A FAILED LOWER RUDDER ATTACH PIVOT BOLT WHICH RESULTED IN JAMMED FLIGHT CONTROLS AND AN UNCONTROLLED DESCENT INTO TREES.

Accident occurred OCT-24-92 at LONGMONT, CO
Aircraft: MARCY KITFOX IV, registration: N130T
Injuries: 1 Fatal.

THE PILOT WAS PLANNING TO PURCHASE THE HOMEBUILT AIRPLANE. THE OWNER SAID HE GAVE THE PILOT PERMISSION TO TAXI THE AIRPLANE AROUND THE RAMP, BUT DID NOT GIVE HIM PERMISSION TO FLY. THE AIRPLANE WAS SEEN TO TAKE OFF AND ATTAIN A NOSE HIGH ATTITUDE. ONE WITNESS SAID THE AIRPLANE WAS FLYING "SLOWLY" AND IT APPEARED THE PILOT WAS NOT "IN FULL LATERAL CONTROL." ANOTHER WITNESS SAID IT APPEARED THE PILOT WAS MAKING "A LOT OF SMALL CONTROL ADJUSTMENTS, LIKE HE WAS BUSY KEEPING IT WHERE HE WANTED IT, BUT IT WAS UNDER CONTROL." THE FIRST WITNESS SAID THE AIRPLANE DID "A CLASSIC DEPARTURE STALL," WENT INVERTED, AND ENTERED A FLAT SPIN. ANOTHER WITNESS SAW THE AIRPLANE SPIN TO THE GROUND. TWO OTHER WITNESSES REPORTED THAT THE AIRPLANE NOSED DOWN TO IMPACT. NO AIRFRAME, ENGINE, PROPELLER, OR FLIGHT CONTROL DISCREPANCIES WERE NOTED.
Probable Cause
AN INADVERTENT STALL. A FACTOR WAS: THE PILOT'S LACK OF FAMILIARITY WITH THE AIRPLANE.

Accident occurred DEC-16-92 at ROCKLEDGE, FL
Aircraft: HIGHCRAFT KEUTHAN BUCCANEER II, registration: NONE
Injuries: 2 Minor.

THE PILOT AND A PILOT RATED PASSENGER WERE FLYING AN UNREGISTERED AMPHIBIAN AIRPLANE. ON TAKEOFF THE ENGINE FAILED DUE TO THE FAILURE OF THE FUEL PUMP. DURING THE FORCED LANDING THE AIRPLANE RECEIVED SUBSTANTIAL DAMAGE AND THE PILOT AND PILOT RATED PASSENGER RECEIVED MINOR INJURIES.
Probable Cause
THE TOTAL FAILURE OF THE ENGINE-DRIVEN FUEL PUMP ON TAKEOFF INITIAL CLIMB. A FACTOR WAS UNSUITABLE TERRAIN.

Accident occurred NOV-15-92 at PALM SPRINGS, CA
Aircraft: LITCHFORD FALCON XP, registration: NONE
Injuries: 1 Fatal.

THE PILOT OF THE UNREGISTERED AND UNLICENSED EXPERIMENTAL HOMEBUILT REQUESTED A HIGH SPEED TAXI TEST FROM THE ATCT CONTROLLERS WITH AN OPTION TO TAKEOFF FOR CLOSED TRAFFIC. WITNESSES SAID THE AIRCRAFT BECAME AIRBORNE AFTER ABOUT A 150 FOOT GROUND ROLL AND ENTERED A STEEP CLIMB. THE PILOT THEN REPORTED TO ATCT THAT "I'VE JUST LOST A RUDDER PEDAL." THE AIRCRAFT THEN FELL OFF ON A WING AND ENTERED A STEEP NOSE DOWN SPIN OR SPIRAL TO GROUND IMPACT. EARLIER IN THE DAY A AIRLINE PILOT WHO ALSO HOLDS AN A & P MECHANIC'S CERTIFICATE TALKED TO THE PILOT AND LOOKED OVER THE AIRCRAFT. THE PILOT TOLD THE WITNESS THAT THE AIRCRAFT HAD NOT FLOWN IN TWO OR THREE YEARS. THE WITNESS SAID HE SAW MANY DISCREPANCIES ON THE AIRCRAFT AS HE WATCHED THE PILOT WORK ON THE RUDDER CABLES IN THE REAR SEAT AREA. SOME ITEMS NOTED BY THE WITNESS WERE: 1) RUDDER CABLES NOT ROUTED CORRECTLY ON THE PULLEYS IN THE COCKPIT AREA, 2) REAR COCKPIT RIGHT RUDDER PEDAL WAS COLLAPSED ON THE FLOOR, AND 3) RUDDER CABLES CONNECTED TO THE WINGLET RUDDERS WITH BUNGEE CORDS WHICH WERE TIED TOGETHER. THE WITNESS SAID HE RECOMMENDED TO THE PILOT THAT IT NOT BE FLOWN. FAA INSPECTORS EXAMINED THE AIRCRAFT AND REPORTED THAT CONTROL SYSTEM CONTINUITY COULD NOT BE ESTABLISHED DUE TO COCKPIT IMPACT DAMAGE.
Probable Cause
THE PILOT'S INFLIGHT LOSS OF CONTROL FOR REASONS RELATED TO THE IMPROPER INSTALLATION AND FUNCTIONING OF THE RUDDER CONTROL SYSTEM, AND, THE PILOT'S INADVERTENT ENTRY INTO A STALL SPIN.

Accident occurred NOV-21-92 at SAN JOSE, CA
Aircraft: RANS S-10 SAKOTA, registration: N821DR
Injuries: 1 Fatal.

ABOUT ONE MINUTE AFTER TAKEOFF, AT AN ALTITUDE OF ABOUT 150 TO 200 FEET, THE PILOT CONTACTED THE CONTROL TOWER LOCAL CONTROLLER TO REPORT HE WAS HAVING ENGINE PROBLEMS AND WAS RETURNING TO LAND. THE LOCAL CONTROLLER CLEARED THE PILOT TO LAND ON ANY RUNWAY. WITNESSES REPORTED THE PILOT ENTERED A "TIGHT" RIGHT TURN AND THEN ENTERED A STALL/SPIN. THE AIRPLANE IMPACTED THE GROUND AND EXPLODED. AN FAA AIRWORTHINESS INSPECTOR, WHO EXAMINED THE AIRPLANE AFTER THE ACCIDENT, DETERMINED ALL FLIGHT CONTROLS WERE INTACT, OPERABLE, AND WORKING CORRECTLY. DUE TO THE DAMAGE TO THE ENGINE, THE CAUSE OF THE LOSS OF POWER COULD NOT BE DETERMINED.
Probable Cause
1) THE LOSS OF ENGINE POWER DUE TO UNDETERMINED REASON(S), AND, 2) THE PILOT NOT MAINTAINING AIRSPEED ABOVE THE POWER OFF STALL SPEED WHILE MANEUVERING TO THE RUNWAY RESULTING IN AN INADVERTENT STALL/SPIN. A FACTOR IN THIS ACCIDENT WAS THE PILOT NOT HAVING SUFFICIENT ALTITUDE TO RECOVER FROM THE STALL/SPIN.

Accident occurred MAR-15-93 at SHERIDAN, WY
Aircraft: BARR KITFOX II, registration: N569F
Injuries: 2 Uninjured.

DURING THE INITIAL CLIMB, THE AIRCRAFT EXPERIENCED A PARTIAL POWER LOSS. BECAUSE THEY FELT THAT THEY COULD NOT SAFELY RETURN TO THE AIRPORT, THE PILOTS MADE A DECISION TO ATTEMPT A FORCED LANDING ON A NEARBY DIRT ROAD. DURING THE LANDING ROLL IN A STRONG CROSSWIND, THE AIRCRAFT'S RUDDER BECAME INEFFECTIVE AS THE AIRCRAFT SLOWED. THE INSTRUCTOR PILOT WAS UNABLE TO KEEP THE AIRCRAFT FROM WEATHER VANING INTO THE WIND AND DEPARTING THE SIDE OF THE ROAD. AS THE AIRPLANE DEPARTED THE ROAD IT IMPACTED A NEARBY FENCE.
Probable Cause
A PARTIAL POWER LOSS FOR UNDETERMINED REASONS. FACTORS INCLUDE A STRONG CROSSWIND ON LANDING.

Accident occurred JUL-11-93 at PORT ARTHUR, TX
Aircraft: WEEDHOPPER B, registration: NONE
Injuries: 2 Fatal.

THE UNREGISTERED AIRPLANE WAS SEEN TO MAKE A HARD LEFT TURN AND ENTER A VERTICAL DIVE FROM AN ALTITUDE OF BETWEEN 100 AND 150 FEET. AT AN ALTITUDE OF ABOUT 75 FEET, THE FABRIC SEPARATED FROM THE RIGHT WING AND THE WING FAILED. POST ACCIDENT INVESTIGATION DISCLOSED THE RUDDER CONTROL CABLE WAS FRAYED, HAD BROKEN, AND WAS OF THE WRONG SIZE. THE WING FABRIC WAS DETERIORATED, HAD BEEN PREVIOUSLY PATCHED, WAS OF THE WRONG TYPE AND WEIGHT, AND BORE SPANWISE TEARS. THE WING SPAR HAD FAILED AT A POINT WHERE PREVIOUS REPAIRS HAD BEEN MADE. ADDITIONALLY, THE WING RIBS WERE OF THE WRONG TYPE. THE PILOT HAD CONVERTED WHAT HAD BEEN A SINGLE PLACE ULTRALIGHT VEHICLE INTO A TWO PLACE AIRPLANE BY USING PARTS FROM WRECKED ULTRALIGHTS, CAUSING THE EMPTY WEIGHT TO EXCEED THE MAXIMUM ALLOWABLE.
Probable Cause
THE FAILURE OF THE WING FABRIC AND WING SPAR. FACTORS WERE: THE IMPROPER DESIGN CHANGE, MAJOR REPAIR, AND REBUILDING OF THE AIRCRAFT BY THE PILOT IN COMMAND.

Accident occurred MAY-01-93 at WAMPUM, PA
Aircraft: MCMILLIN FISHER 404, registration: NONE
Injuries: 1 Uninjured.

ABOUT 45 SECONDS AFTER TAKEOFF, THE AIRPLANE'S ENGINE LOST TOTAL POWER. THE PILOT MADE A FORCED LANDING, AND DURING THE APPROACH, THE AIRPLANE IMPACTED A TREE. POST ACCIDENT EXAMINATION OF THE AIRPLANE REVEALED THAT A PLASTIC FUEL LINE HAD BEEN SAFETY WIRED AND THE WIRE WAS OVER TORQUED, CAUSING THE FUEL LINE TO SPLIT. THERE WAS EVIDENCE THAT DURING INITIAL CLIMB FROM TAKE OFF, AIR ENTERED THE FUEL LINE, STARVING THE ENGINE OF FUEL. THE PILOT WAS OPERATING THE AIRPLANE UNDER 14 CFR PART 103 AS AN ULTRALIGHT AND DID NOT HOLD ANY FAA CERTIFICATES. THE POST ACCIDENT INVESTIGATION REVEALED THE AIRCRAFT WEIGHED OVER THE WEIGHT LIMITATION OF 254 POUNDS AS IMPOSED BY 14 CFR PART 103; THEREFORE, IT WAS DESIGNATED AN AIRPLANE.
Probable Cause
THE OVERTORQUE OF A SAFETY WIRE ON A PLASTIC FUEL LINE, CAUSING THE LINE TO SPLIT.

Accident occurred APR-28-93 at E STROUDSBURG, PA
Aircraft: STEVEN KURTIS RAND S 12, registration: N6784J
Injuries: 2 Minor.

SHORTLY AFTER TAKEOFF AT AN APPROXIMATE ALTITUDE OF 100 TO 150 FEET ABOVE THE GROUND THE ENGINE LOST POWER. THE PILOT TURNED THE AIRPLANE 180 DEGREES IN AN ATTEMPT TO MAKE IT BACK TO THE AIRPORT BUT COLLIDED WITH TREES DURING THE FORCED LANDING. EXAMINATION OF THE ENGINE BY A MECHANIC AFTER THE ACCIDENT REVEALED NO DISCREPANCIES. THE BUILDER OF THE AIRPLANE SAID THAT THERE HAD BEEN MECHANICAL DIFFICULTIES WITH THE ENGINE PRIOR TO THE FLIGHT, AND THE MECHANIC THAT HAD WORKED ON THE ENGINE SAID THAT THEY WERE CORRECTED AND THAT THE AIRPLANE WAS "OKAY" TO FLY.
Probable Cause
A FORCED LANDING IN TREES AS A RESULT OF A COMPLETE LOSS OF ENGINE POWER FOR UNKNOWN REASONS.

Accident occurred MAR-11-93 at ALBUQUERQUE, NM
Aircraft: MISTRETTA CHALLENGER II, registration: N3207C
Injuries: 1 Uninjured.

THE PILOT OF THE AMATEUR BUILT AIRPLANE STATED THAT AS HE TURNED FROM DOWNWIND TO BASE, HE WAS UNABLE TO ROLL OUT OF THE LEFT TURN. HE FURTHER STATED THAT THE RUDDER DID NOT SEEM TO RESPOND. THE AIRPLANE CONTINUED IN THE LEFT BANK UNTIL IT IMPACTED THE GROUND. THERE WERE MOUNTAINS IN THE VICINITY OF THE AIRPORT AND TOWERING CUMULUS WAS REPORTED IN THE WESTERN, NORTHERN, AND EASTERN QUADRANTS OVER THE MOUNTAINS. NO EVIDENCE OF PRE IMPACT FLIGHT CONTROL MALFUNCTION OR FAILURE WAS FOUND DURING THE INVESTIGATION.
Probable Cause
THE PILOT'S FAILURE TO MAINTAIN CONTROL OF THE AIRPLANE. A FACTOR WAS HIS POSSIBLE ENCOUNTER WITH TURBULENCE.

Accident occurred MAR-28-93 at LINCOLN, MO
Aircraft: MANVILLE AVID FLYER, registration: N714J
Injuries: 1 Uninjured.

The pilot started on a cross-country flight with 18 gallons of fuel in the right tank, and 13 gallons of fuel in the left tank. This was the first time the airplane had been flown with fuel in the left tank. While en route, the pilot noticed that the right tank was almost empty, and the left tank had more fuel than he started with. The pilot attempted to make a precautionary landing at the Lincoln, Missouri, Airport, to troubleshoot the problem. When he made a left base-to-final turn he could not level the wings using full right aileron and rudder. The airplane made a 360 degree left turn. The pilot got the wings level at about 50 feet agl, and landed in a field next to the airport. He made an adjustment to the fuel vent system, and took off again. On takeoff the airplane started a hard left turn and crashed.
Probable Cause
The pilot's failure to maintain control of the airplane, and his operation of an airplane with known defects.

Accident occurred JUL-15-93 at NUMIDIA, PA
Aircraft: ROLANDO RANS S-10, registration: N217ER
Injuries: 1 Fatal.

WITNESSES STATED THAT SHORTLY AFTER TAKEOFF, AT ABOUT 200 TO 300 FEET ABOVE THE GROUND, THE AIRPLANE BANKED LEFT ABOUT 60 DEGREES. THEY STATED THAT DURING THE LEFT TURN, THE AIRPLANE'S NOSE WENT DOWN AND THE AIRPLANE SPUN INTO THE GROUND. THE WITNESSES STATED THAT THE AIRPLANE'S ENGINE WAS RUNNING THROUGHOUT THE MANEUVER. POST ACCIDENT EXAMINATION OF THE AIRPLANE WRECKAGE DID NOT DISCLOSE ANY AIRFRAME OR ENGINE ANOMALIES. THE PILOT PURCHASED THE AIRPLANE FOUR DAYS PRIOR TO THE ACCIDENT. THE PILOT'S LOGBOOK INDICATED HE HAD ABOUT 20 HOURS OF TOTAL FLIGHT TIME IN THE ACCIDENT AIRPLANE.
Probable Cause
THE EXCESSIVE MANEUVER ATTEMPTED BY THE PILOT WHICH RESULTED IN A LOSS OF CONTROL IN FLIGHT AND AN INADVERTENT SPIN AT AN ALTITUDE INSUFFICIENT FOR RECOVERY.

Accident occurred JUN-12-93 at NEW SMYRNA BCH, FL
Aircraft: SAYER, TREVOR A. RANS S-12, registration: N162JT
Injuries: 1 Uninjured.

THE PILOT STATED THAT SHORTLY AFTER TAKEOFF, THE EGT GAGE FOR ONE OF THE TWO CYLINDERS WAS INDICATING HIGHER THAN NORMAL. HE INITIATED A TURN TO RETURN FOR LANDING BUT THE ENGINE FAILED DUE TO FUEL STARVATION. HE THEN INADVERTENTLY STALLED AND SPUN THE AIRPLANE WHICH CRASHED INTO A POND ON THE AIRPORT. THE AIRPLANE WAS RECOVERED AND EXAMINATION REVEALED THAT THE CAUSE OF THE FUEL STARVATION WAS DUE TO THE IMPROPER PLACEMENT OF A "Y" FITTING WHICH CONNECTS THE FORE AND AFT FUEL LINES FROM EACH FUEL TANK. THE PILOT HAD PLACED THE "Y" FITTING IN THE CENTER OF THE FUEL TANK BETWEEN THE FORE AND AFT FUEL WITHDRAWALS AT THE BOTTOM EDGE OF THE TANK. THE CORRECT PLACEMENT OF THE FITTING IS ABOUT 12 INCHES BELOW THE FUEL TANK.
Probable Cause
FAILURE OF THE PILOT TO MAINTAIN ADEQUATE AIRSPEED AND INADVERTENT STALL/SPIN. CONTRIBUTING TO THE ACCIDENT WAS TOTAL LOSS OF ENGINE POWER DUE TO FUEL STARVATION. THIS WAS DUE TO IMPROPER PLACEMENT OF A COMPONENT OF THE FUEL SYSTEM BY THE BUILDER/PILOT.

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