What happened
The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.
During a personal flight conducted under 14 CFR §91, N701MG impacted terrain resulting in substantial damage to the aircraft, fatal injuries to the airman and serious injuries to the only passenger on board.
The accident scene revealed the following information:
The aircraft impacted in a high angle, low energy state with all wreckage with exception of the propeller contained in one primary area.
Ground scaring under the nose cowling shows very little, if any, forward momentum after initial impact.
The left wing made ground contact first and is angled toward the rear of the fuselage, followed by the right wing which is angled forward.
Both wings roots separated from the fuselage at the rear spar attach point which is mounted with rivets.
The propeller blades separated from the propeller hub and were located after a brief search.
Cord span witness marks are present on the propeller. Engine rotation at time of impact will be investigated further and this report will be amended if necessary.
Aircraft control cable continuity was established to all primary flight controls.
When the fuel caps were removed from both the inboard and outboard fuel tanks, it was observed that both outboard tanks were full and both inboard tanks were empty.
Fuel selector was found in the ?off? Position but it could not be verified if it was in that position pre or post impact.
As the FAA filed it
DURING A PERSONAL FLIGHT CONDUCTED UNDER 14 CFR §91, N701MG IMPACTED TERRAIN RESULTING IN SUBSTANTIAL DAMAGE TO THE AIRCRAFT, FATAL INJURIES TO THE AIRMAN AND SERIOUS INJURIES TO THE ONLY PASSENGER ON BOARD.
THE ACCIDENT SCENE REVEALED THE FOLLOWING INFORMATION:
THE AIRCRAFT IMPACTED IN A HIGH ANGLE, LOW ENERGY STATE WITH ALL WRECKAGE WITH EXCEPTION OF THE PROPELLER CONTAINED IN ONE PRIMARY AREA.
GROUND SCARING UNDER THE NOSE COWLING SHOWS VERY LITTLE, IF ANY, FORWARD MOMENTUM AFTER INITIAL IMPACT.
THE LEFT WING MADE GROUND CONTACT FIRST AND IS ANGLED TOWARD THE REAR OF THE FUSELAGE, FOLLOWED BY THE RIGHT WING WHICH IS ANGLED FORWARD.
BOTH WINGS ROOTS SEPARATED FROM THE FUSELAGE AT THE REAR SPAR ATTACH POINT WHICH IS MOUNTED WITH RIVETS.
THE PROPELLER BLADES SEPARATED FROM THE PROPELLER HUB AND WERE LOCATED AFTER A BRIEF SEARCH.
CORD SPAN WITNESS MARKS ARE PRESENT ON THE PROPELLER. ENGINE ROTATION AT TIME OF IMPACT WILL BE INVESTIGATED FURTHER AND THIS REPORT WILL BE AMENDED IF NECESSARY.
AIRCRAFT CONTROL CABLE CONTINUITY WAS ESTABLISHED TO ALL PRIMARY FLIGHT CONTROLS.
WHEN THE FUEL CAPS WERE REMOVED FROM BOTH THE INBOARD AND OUTBOARD FUEL TANKS, IT WAS OBSERVED THAT BOTH OUTBOARD TANKS WERE FULL AND BOTH INBOARD TANKS WERE EMPTY.
FUEL SELECTOR WAS FOUND IN THE ?OFF? POSITION BUT IT COULD NOT BE VERIFIED IF IT WAS IN THAT POSITION PRE OR POST IMPACT.
NTSB investigation
The NTSB’s investigation of this event, with its probable cause and findings. Matched to this report by N-number and date.