NTSB Identification: WPR13FA073
14 CFR Part 91: General Aviation
Accident occurred Tuesday, December 18, 2012 in Libby, MT
Aircraft: BEECH B100, registration: N499SW
Injuries: 2 Fatal.
This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when the final report has been completed. NTSB investigators either traveled in support of this investigation or conducted a significant amount of investigative work without any travel, and used data obtained from various sources to prepare this aircraft accident report.
On December 18, 2012, about 0002 mountain standard time (MST), a Beech B100, N499SW, collided with trees at Libby, Montana. Stinger Welding was operating the airplane under the provisions of 14 Code of Federal Regulations (CFR) Part 91. The noncertificated pilot and one passenger sustained fatal injuries; the airplane sustained substantial damage from impact forces. The cross-country personal flight departed Coolidge, Arizona, about 2025 MST on December 17th, with Libby as the planned destination. Visual meteorological conditions prevailed at the nearest official reporting station of Sandpoint, Idaho, 264 degrees at 46 miles, and an instrument flight rules (IFR) flight plan had been filed.
The Federal Aviation Administration (FAA) reported that the pilot had been cleared for the GPS-A instrument approach procedure for the Libby Airport. The clearance had a crossing restriction of 10,700 feet at the PACCE intersection, which was the initial approach fix for the GPS-A approach. The pilot acknowledged that clearance at 2353. At 2359, the airplane target was about 7 miles south of the airport; the pilot reported the field in sight, and cancelled the IFR flight plan.
A police officer reported that he observed an airplane fly over the city of Libby, which was north of the airport; the airplane then turned toward the airport. The officer went to the airport to investigate, but observed no airplane. He noted that it was foggy in town, but the airport was clear. He also observed that the rotating beacon was illuminated, but not the pilot controlled runway lighting.
When the pilot did not appear at a company function at midday on December 18, they reported him overdue. The Prescott, Arizona, Automated Flight Service Station (AFSS) issued an alert notice (ALNOT) at 1102 MST; the wreckage was located at 1835.
The National Transportation Safety Board investigator-in-charge (IIC) and investigators from the FAA and Honeywell examined the wreckage on site. A description of the debris field references debris from left and right of the centerline of the debris path. The debris was through trees on a slope that went downhill from left to right.
The first identified point of contact (FIPC) was a topped tree with branches on the ground below it and in the direction of the debris field. About 50 feet from the tree were composite shards, and a piece of the composite engine nacelle, which had a hole punched in it.
The next point of contact was a 4-foot tree stump with shiny splinters on the stump. The lower portion of the tree had been displaced about 30 feet in the direction of the debris field with the top folded back toward the stump. Underneath the tree trunk were the nose gear and a couple of control surfaces followed by wing pieces.
One engine with the propeller attached was about 50 feet from the stump, and on the right side of the debris path. Next on the left side of the debris path was the outboard half of one propeller blade; another propeller blade was about 10 feet further into the debris field.
Midway into the debris field were several trees with sheet metal wrapped around them. Near the midpoint of the debris field, a portion of the instrument panel had imbedded into a tree about 15 feet above the ground. The wiring bundle hung down the tree trunk to ground level. To the left of the instrument panel was one of the largest pieces of wreckage. This piece contained the left and right horizontal stabilizers, vertical stabilizer, and part of one wing with the landing gear strut attached. The rudder separated, but was a few feet left of this piece.
Next in the debris field was a 6- by 8-foot piece of twisted metal, which contained the throttle quadrant.
About 100 feet right of the debris path centerline and downhill from the throttle quadrant was a 10-foot section of the aft cabin. This section was connected by steel cables and wires to a 4- by 7-foot piece of twisted metal.
The furthest large piece of wreckage was the second engine; the propeller hub with two blades attached had separated.
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