# Accident 20080923852979A: Nagel SAL2/3P51, Glenville, NY, September 23, 2008 - Type: FAA accident report (Accident/Incident Data System), as reported - Date: September 23, 2008, 14:58 local time - Place: Glenville, NY - Airport: Schenectady County - Damage: Destroyed - Phase of flight: Takeoff - Operating rules: General operating rules (Part 91) - Location: 42.8514° N, 73.9239° W: From the FAA - Nearby events: https://openairdocs.org/map.md?lat=42.8514&lon=-73.9239&mi=10 - Aircraft: N51WW, a cancelled registration (https://openairdocs.org/deregistered/N51WW-2017-03-06) (OpenAirDocs) - Registry model: Nagel SAL 2/3 P51 (registry code 1690414, https://openairdocs.org/model/nagel-sal-2-3-p51) (OpenAirDocs) - Registry engine: Amateur-built UNKNOWN ENG (registry code 99999, https://openairdocs.org/engine/amateur-built-unknown-eng) (OpenAirDocs) - Reported make and model: NAGEL SAL2/3P51 - Reported engine: CHEVY* - People aboard: 1 - Fatal injuries: 1 - Pilot flight hours: 440 total, 0 in this make and model, 0 in the last 90 days - NTSB investigation: [NTSB NYC08LA322](https://openairdocs.org/ntsb/NYC08LA322) (OpenAirDocs) - FAA source: FAA Aviation Safety Information Portal (https://asip.faa.gov/) - Page: https://openairdocs.org/incident/20080923852979A ## Narrative As the FAA filed it, in capitals; the FAA replaces private details with ^PRIVACY DATA OMITTED^. RESPONDED TO CRASH AT SCHENECTADY COUNTY AIRPORT AT APPROXIMATELY 1605 LOCAL SEPTEMBER 23, 2008. WITNESS STATEMENTS INDICATED AIRCRAFT DEPARTED RUNWAY FOUR ON TEST FLIGHT. AFTER TAKEOFF LEFT TURN OUT WAS MADE JUST PAST MIDFIELD AT HIGH RATE OF CLIMB. PILOT REPORTED TO TOWER A LOSS OF POWER AIRCRAFT MADE RIGHT TURN AND DESCENDED INTO TREES.AIRCRAFT CONTACTED TREES ON SOUTH SIDE OF DIRT ACCESS ROAD ON A HEADING OF APPROXIMATELY 360 MAGNETIC. BROKEN BRANCHES ON GROUND SHOWED MARKS CONSISTENT WITH ROTATING PROPELLER BLADE STRIKES; THE MAJORITY OF BROKEN PROPELLER BLADES WERE IN THIS AREA. AIRCRAFT CONTINUED INTO TREES ON NORTH SIDE OF ACCESS ROAD APPROXIMATELY FIFTY FEET UNTIL IMPACTING TREE. AIRCRAFT FUSELAGE WAS ON RIGHT SIDE TOWARDS BEING INVERTED WITH WING TOTALLY UPSIDE DOWN. AIRCRAFT WAS AGAINST TREE ON THE RIGHT SIDE WHICH IT APPEARS THE AIRCRAFT STRUCK APPROXIMATELY 20-25 FEET ABOVE GROUND AND SLIDE DOWN VERTICALLY. SITE WAS COVERED WITH FOAM USED TO EXTINGUISH POST CRASH FIRE IN ENGINE COMPARTMENT. TAIL SECTION AND AFT FLIGHT CONTROLS WERE REMOVED FROM FUSELAGE BY RESCUE PERSONAL, CABLES AND PUSH PULL RODS WERE ALL CUT. ALL CONTROL ATTACH POINTS HAD CORRESPONDING HARDWARE INTACT AND SECURED. ELEVATOR AND RUDDER TRIM TABS WERE IN NEUTRAL POSITION. WING WAS INTACT WITH NO NOTED FUEL LEAKAGE, WHEN FUEL SELECTOR WAS LOCATED IN WAS IN THE OFF POSITION FUEL LINES FROM SELECTOR FORWARD WERE BROKEN OFF, OR REMOVED BY RESCUE PERSONNEL, NO FUEL SPILLAGE WAS NOTED. ALL BLADES OF WOODEN FIXED PITCH PROPELLER WERE BROKEN AT HUB. WING SECTION WAS MOVED TO NEARBY HANGAR AND POSITIONED AS LEVEL AS POSSIBLE. AILERONS AND CONTROLS WERE INTACT FROM CONTROL STICK TO AILERONS AND OPERATED THROUGH FULL RANGE. FUEL SELECTOR FLOWED GAS FROM THE OUTPUT SIDE OF SELECTOR WHEN POSITIONED TO RIGHT TANK, LEFT TANK AND BOTH POSITIONS. WING CONTAINS TWO MAIN TANKS AT 13 GALLONS EACH AND TWO AUX TANKS AT 11 GALLONS EACH. THE RIGHT MAIN FUEL SENDING UNIT WAS REMOVED AND FUEL LEVEL MEASURED AT 5 INCHES FROM TANK BOTTOM WITH TOP OF TANK MEASURING EIGHT AND A HALF INCHES, FUEL FILLER CAP IS 20 INCHES OUTBOARD AND IN LINE WITH SENDING UNIT AND MEASURED TWO AND A HALF INCHES OF FUEL. LEFT MAIN TANK MEASURED TWO AND A HALF INCHES AT FILLER PORT.FUEL LEVEL IN AUX TANKS COULD NOT BE DETERMINED. REMOVED BOTH ELECTRIC FUEL PUMPS AND BOTH OPERATED WHEN TWELVE VOLTS OF BATTERY POWER WAS APPLIED. FUEL WAS PRESENT IN OUTPUT LINE TO CARBURETOR. LINE TO CARBURETOR WAS INTACT. FRONT FUEL BOWEL OF CARBURETOR WAS BURNED OPEN AND AIR FILTER WAS CRUSHED AND BURNED. THROTTLE LINKAGE WAS INTACT AND OPERABLE FULL RANGE FROM THROTTLE TO CARBURETOR, BOTH PRIMARY AND SECONDARY THROTTLE PLATES OPEN AND CLOSED FULLY. DISTRIBUTOR CAP, ROTOR, COIL AND IGNITION WIRING WAS CONSUMED BY POST CRASH FIRE. RIGHT SIDE SPARK PLUG REMOVED AND SHOWED NO ABNORMAL CONDITIONS, SAME SIDE ROCKER COVER WAS REMOVED, VALVES, SPRINGS AND ROCKERS ARMS APPEARED NORMAL, RESIDUAL OIL IN ROCKER AREA APPEARED NORMAL. WITNESS STATEMENTS, PHOTOS, CONTROL TOWER AUDIO TAPE AND WITNESS VIDEO FORWARDED TO NTSB. ## The NTSB's investigation of this event (1) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB NYC08LA322](https://openairdocs.org/ntsb/NYC08LA322), Sep 23, 2008: Nagel SAL 2/3 P51 (N51WW), Schenectady, NY, destroyed, 1 fatal. Probable cause: The pilot's failure to maintain adequate airspeed during the initial climb, which led to an aerodynamic stall. From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. For accidents, the NTSB's own investigation is the fuller record. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.