N9089N

HISTORY OF FLIGHT

On August 29, 2013, about 1945 eastern daylight time, a Piper PA-28-161, N9089N, was destroyed when it impacted an on airport instrument landing system (ILS) glide slope antenna, the ground, and then a postaccident fire ensued at Danville Regional Airport (DAN), Danville, Virginia. The student pilot, was fatally injured. Visual meteorological conditions prevailed and no flight plan was filed for the local solo flight which was conducted under the provisions of Title 14 Code of Federal Regulations Part 91.

According to several eyewitnesses, the airplane was observed performing repeated takeoffs and landings to runway 2. During one of the landing attempts the airplane "appeared too low;" the airplane's engine power could be heard increasing, and a go-around maneuver commenced. During the initial go-around the airplane rolled "sharply left…then sharply right" before it began to climb out. On the second attempt, the landing was "normal" and the airplane taxied back to the beginning of the runway for takeoff. During the accident approach, the airplane "flared high, then rolled left" and then began to climbout "very shallow" and "appeared level" prior to impacting the antenna. The witnesses reported hearing the engine power increase and just prior to impacting the antenna and then engine power decreased.

Based on certificated flight instructor (CFI) and eyewitness interviews the actual number of landing attempts could not be conclusively determined.

PERSONNEL INFORMATION

According to Federal Aviation Administration (FAA) and General Aviation Flight, Inc., the flight school, the pilot, age 42, held a student pilot certificate dated August 14, 2013, which was also a third-class medical certificate. At the time of certificate issuance, the student pilot reported 8.8 total flight hours. Although, at the time of this writing the student pilot's logbook had not been located, flight school records showed the student had accumulated about 13 total flight hours, of which, an estimated 1.6 of those hours were solo flight. The student's first flight was accomplished on June 24, 2013. The first solo flight recorded in the flight school's record was on August 25, 2013 and was 0.8 hours in duration. The flight school documentation further stated "SOP [Standard Operating Procedure] is to completely go through all requirements twice and then to review selected ones as per student needs and desires."

AIRCRAFT INFORMATION

According to FAA records, the airplane was issued an airworthiness certificate on December 11, 1986, and was registered to General Aviation, Inc on December 5, 1986. It was powered by a 160-hp Lycoming O-320-D3G engine, serial number RL-13625-39E, driving a Sensenich 2-bladed propeller. The airplane's most recent inspection, noted as an annual inspection in the logbook, was accomplished on August 6, 2013. At the time of that inspection the airplane had 13,976.8 total hours of time in service. The engine's most recent inspection, noted as a 100-hour inspection in the logbook, was accomplished on August 6, 2013, at 4,211.1 hours of total time in service and 1,876.2 total hours since major overhaul with a recorded tachometer time of 13,976.8 hours.

At the time of the inspections the tachometer was recorded as 3,976.8 hours. Prior to the accident flight the aircraft tachometer was recorded as 4020.6 hours.

The most recent recorded fueling was accomplished on August 27, 2013, at DAN. The airplane had been fueled with 20.1 gallons of fuel.

METEOROLOGICAL INFORMATION

The 1953 recorded weather observation at DAN included wind from 050 degrees at 5 knots, 10 miles visibility, clear skies, temperature 26 degrees C, dew point 21 degrees C; altimeter setting 29.99 inches of mercury.

On the day of the accident, official sunset was at 1950, end of civil twilight was at 2016.

AIRPORT INFORMATION

The airport was a publically owned airport and at the time of the accident did not have a control tower. There were two runways designated runway 2/20, and runway 13/31. However, at the time of the accident, the airport was under construction and runway 13/31 was closed. Runway 2/20 was normally 6,502 feet long; however, due to construction, it was 3,028 feet long and 150 feet wide. The airport elevation was 571 feet above mean sea level. The ILS glide slope antenna was located about 900 feet from the runway threshold to runway 2 and about 175 feet from the west side of the paved portion of runway 2/20.

The airport, at the time of the accident had numerous published Notices to Airman (NOTAM) and some of them that affected the landing runway were:

• DAN 06/009 DAN RWY 2/20 RWY LGTS PCL OTS EXC LOW INTST

• DAN 04/007 DAN RWY 2/20 NORTH 3474 CLSD WEF 1304251528

• DAN 03/040 DAN RWY 2/20 CLSD TO ACFT WITH APCH SPEED IN EXCESS OF 121 KTS

• DAN 03/035 DAN RWY 2/20 CLSD TGL

• DAN 03/027 DAN RWY 20 PAPI OTS

• DAN 03/026 DAN RWY 2 PAPI OTS

• DAN 03/021 DAN NAV ILS RWY 2 OM OTS WEF 1303251200-1401151200

• DAN 03/017 DAN NAV ILS RWY 2 GP/LLZ OTS WEF 1303251200

• DAN 03/016 DAN RWY 2 ALS OTS WEF 1303251200

• DAN 03/015 DAN RWY 2 REIL OTS WEF 1303251200

WRECKAGE AND IMPACT INFORMATION

The ILS glide slope antenna exhibited impact damage 39.5 feet above ground level (agl). Ground scars were present between the runway and taxiway "A." The left wing was collocated with the ILS glide slope antenna. The accident flight path was oriented on a 346 degree heading and the debris path began about 20 feet prior to ILS glide slope antenna and consisted of the left wing beginning at the wing root and included the entire wing. The debris path terminated 176 feet past the antenna. The debris path included a ground scar in a position consistent with the right wing impacting the ground in a right wing low attitude. The impact mark was located 105 feet from the antenna. Two propeller strike marks were also located along the debris path. The marks were 31 inches apart and the first strike mark was about 5 inches in depth. The second mark consisted of the propeller assembly including both blades and the propeller hub. The main wreckage came to rest on a heading of 129 degrees.

Nose and Cockpit Section

The engine and cockpit exhibited fore-to-aft crushing and thermal damage. The engine remained attached to the firewall via the tubular mounts. The propeller was found separated from the engine and was located along the debris field and one of the blades, which was imbedded in the ground, exhibited minimal S-bending and leading edge damage. The ignition switch was found with the key remaining in it; however, due to thermal damage it could not be determined on the actual position. The fuel selector valve remained attached to the side wall; however, due to thermal damage the position of the switch could not be determined. According to the CFI, the selector valve was likely in the "LEFT" position when he exited the airplane prior to the student departing on the solo flight just prior to the accident. Both front seats remained attached to their respective seat tracks. The rear seats remained attached to their attach points. The left shoulder harness buckle remained attached the left side of the belt buckle. One side of the seat belt in the rear seat remained attached to the fuselage structure; however, no other seatbelts or buckles were located. The flap lever, located between the two pilot seats, was in the bottom detent, which correlated to the flaps "UP" position, which also correlated to the flap position found on both wings. The main entry located on the right side of the airplane was thermally damaged; however, the door latch was in the locked position.

A cellular phone was located in the wreckage, in a carrying case, and the case had extensive thermal damage. Removing the phone from the case revealed it was not on; and after it was turned on for examination it revealed that a missed call was received at 1946 EDT. According to the cellular phone manufacturer's online technical support, the model of phone found in the wreckage may overheat and shutdown when exposed to temperatures that exceed 35 degrees C; and it will not register a missed call when powered off.

Engine

Engine continuity was confirmed from the propeller hub to the rear accessory pad via hand rotation of the propeller flange. Thumb compression was confirmed on all cylinders during hand rotation. The top and bottom spark plugs were removed, appeared to be light gray in color, and were "normal" in wear according to Champion Spark Plug Guide. The bottom spark plugs associated with the Nos. 2 and 4 cylinder were oily to the touch. Due to thermal damage, neither magneto was able to produce spark but the impulse coupling had positive contact that was heard when rotated by hand. The fuel pump was disassembled and no noted anomalies were found with the check valve, and all gaskets exhibited thermal damage. Examination of the fuel pump actuator rod revealed that it was able to be operated by hand. The oil filter, which was thermally damaged, was removed from the engine and disassembled. The filter media was removed for examination and no metal material was found. The oil suction screen was removed and was free of debris. The vacuum pump was removed and rotated by hand, it was disassembled, and the carbon vanes remained intact. The throttle and mixture control arm positions were unreliable due to impact and thermal damage.

Right Wing

The right wing remained attached to the fuselage and exhibited impact crush damage and thermal damage at the wing root. The wing tip also exhibited impact crush damage in the negative direction beginning at the wing tip and proceeding inboard 66 inches. The flap was in the retracted or flaps "UP" position. The aileron remained attached to the wing at its wing attach point. Cable continuity was confirmed from the control yoke to the right aileron as well as the cross aileron cable, which also remained attached to the left wing's aileron bell cran...