N3995R

HISTORY OF FLIGHT

On April 21, 1995, about 1703 eastern daylight time, a Piper PA-28-180, N3995R, crashed shortly after takeoff from the Quincy Municipal Airport, Quincy, Florida. Visual meteorological conditions prevailed at the time and no flight plan was filed for the 14 CFR Part 91 personal flight. The airplane was destroyed and the commercial-rated pilot and four passengers were fatally injured. The flight originated about 1700 from the Quincy Municipal Airport, Quincy, Florida.

According to a witness, the pilot, who was by himself, landed about 1200 and at the pilot's request, both fuel tanks were filled with 100 Low Lead fuel. A fuel receipt indicated that 23.1 gallons of fuel were added. The airplane was then parked. Review of recorded transcriptions from the Gainesville, Florida, Federal Aviation Administration Automated Flight Service Station (AFSS) revealed that the pilot called twice and obtained weather briefings for a proposed flight to the Arlington Municipal Airport, Arlington, Tennessee. The pilot and his family were then observed before departure around the airplane and before takeoff from runway 14, a witness heard run-up of the engine with no unusual sounds noted. The flight was observed to rotate about 1,584 feet down the 2,963-foot asphalt runway and during the initial climb on the upwind leg, the airplane was observed to roll left and right about the longitudinal axis. The airplane turned left crosswind and a witness who was about 1 mile east of the airport observed the airplane flying "slow" northbound about 100 feet above ground level (agl). The witness reported that the engine sounded normal and there was no smoke trailing the airplane.

Another witness who was about 1/4 mile south of the crash site observed the airplane flying northbound about 200-300 feet above ground level with "dark black smoke" trailing from the engine area. He stated that because of distance from the airplane he couldn't hear the engine operating and he did not observe the airplane crash. He did hear an explosion and stated he did not observe anything fall from the airplane during the 5- 10 seconds he observed the airplane flying.

According to a witness who lives about 1/4 mile north- northeast from the crash site she reported hearing the engine "backfiring & sputtering." She did not witness the accident and reported that the weather at the time of the accident included good visibility beneath the clouds with light drizzle. At the time of the accident the wind was from the south at about 8-10 miles per hour. She heard an explosion and then saw the postcrash fire.

A relative of the pilot's wife stated that the pilot had earlier in the week briefly stayed at a farm which is located about 1/4 mile east of the Quincy Airport.

PERSONNEL INFORMATION

Information pertaining to the pilot is contained in the NTSB Factual Report-Aviation. According to the owner of the airplane, the pilot had flown the accident airplane about 200 hours.

AIRCRAFT INFORMATION

Information pertaining to the airplane is contained in the NTSB Factual Report-Aviation. Review of airplane records revealed that Supplemental Type Certificates (STC Numbers SA2660CE & SE2563CE) were issued to the airplane. The STC's in part indicate removal of the single auxiliary fuel pump and installation of two auxiliary fuel pumps. This allows for the operation of the airplane on leaded and unleaded automotive gasoline or a mixture of automotive gasoline and 100 Low Lead fuel. The airplane owner stated that the fuel pumps are activated by a single, three position rocker-type switch in the cockpit. The STC instructions indicate that aluminum tubing connects the fuel pumps to the gascolator.

The airplane owner also stated that in 1990 or 1991 during an annual inspection of the airplane, the baffle tube weld at the end plate of the muffler for the right forward cylinder was found cracked circumferentially about 90 degrees. The owner stated that the muffler was removed and repaired then reinstalled. Review of the engine logbook revealed an entry dated June 15, 1989, which indicated in part "...removed exhaust and repaired...." Additionally, the airplane owner stated that he flew the airplane about 50-55 minutes on April 13, 1995, and about 50-55 minutes the following day. No discrepancies with the engine were noted. He also stated that there was no reported rough engine at low throttle settings, or inconsistent engine shutdown when he last flew the airplane. After landing on April 14, 1995, he changed the engine oil and then operated the engine checking for leaks; none were found. He also observed that there were no fuel leaks. An entry in the aircraft logbook associated with an annual inspection dated August 10, 1994, indicates in part that the gascolator was cleaned. There were no other fuel related entries in the aircraft logbook. An entry in the engine logbook associated with an annual inspection of the engine was dated August 10, 1994. There were no other entries in the engine logbook.

According to the airplane flight manual and equipment list, two individual rear seats and seatbelts were installed when the airplane was manufactured.

METEOROLOGICAL INFORMATION

Information pertaining to the weather is contained in the NTSB Factual Report-Aviation. Additionally, a pilot who departed on a flight about 10 minutes after the accident airplane departed reported the ceiling was about 5,000 feet with 15 miles visibility beneath the ceiling. He also stated that during the initial climb on the upwind leg, he did not experience the left and right rolls about the longitudinal axis in his airplane that he observed the accident airplane experience.

WRECKAGE AND IMPACT INFORMATION

Examination of the accident site area revealed that the left wing of the airplane forward of the fuel tank collided with an approximately 80-foot-tall tree. The magnetic heading of the airplane at the time of impact was determined to be about 340 degrees. Numerous tree branches, a tree trunk, and dead leaves were observed along the wreckage path. The airplane came to rest upright adjacent to a pond in a wooded area about 308 feet from the initial impact point on a magnetic heading of about 060 degrees. Located near the wreckage were several tree trunks severed by the propeller. The crash site was located about 009 degrees and 2.41 nautical miles from the departure airport.

Examination of the airplane at the accident site revealed all components necessary to sustain flight were in the immediate vicinity. The right horizontal stabilator was found separated and impact damage was noted near the outboard portion on the leading edge. Pieces of tree were found imbedded in creases of the left wing fuel tank skin and heat damage was noted adjacent to the fuel tank. Additionally, the left wing jack pad was located adjacent to the first impact point with the tree. No heat damage was noted to the jack pad. The right wing was examined and the top and bottom skin sections were displaced up and down respectively. Heat damage to the right wing was observed adjacent to the fuel tank. Both fuel tank caps were found secured and examination of the remaining sections of the fuel supply lines and outlet screens from each tank revealed no obstructions. The aileron, elevator, and rudder flight controls were also examined with no evidence of preimpact failure or malfunction. The cockpit, engine compartment and fuselage were damaged by the post crash fire. Soot was not observed on the horizontal stabilator or vertical stabilizer and the firewall was found to be upright, nearly vertical.

Examination of the engine compartment revealed that the gascolator was nearly destroyed by heat but the drain was closed and safety wire was found attached from the gascolator bowl set screw to the gascolator bowl drain fitting. Aluminum was observed adhering to the engine side of the firewall above the gascolator adjacent to the two auxiliary fuel pumps. Additionally, non-uniform shaped holes were observed in the firewall adjacent to the brake cylinder reservoir assembly and a section of firewall was extensively heat damaged adjacent to the gascolator attach bracket. The auxiliary fuel pumps were found secured to the firewall and threaded section of aluminum fittings were observed at the inlet and outlet of each auxiliary fuel pump which were heat damaged. Two sections of aluminum tubing were located in the engine compartment area both of which had one end connected to a steel fitting. The opposite ends of both were not connected to fittings and displayed heat damage.

Additionally, a copper fuel line which connects the fuel selector to the bulkhead tee fitting at the firewall was intact along its length. The line was connected to the bulkhead fitting aft of the firewall but was found separated at the fuel selector, which was heat damaged. Examination of the flexible fuel and oil hoses in the engine compartment revealed no evidence of preimpact failure or malfunction.

Examination of the carburetor which was found secured to the engine revealed that a nut with associated nipple and portion of a socket from a flexible hose was found to be tightly secured to the tee fitting at the inlet for the carburetor. The fuel pressure hose nut with associated nipple and portion of the flexible hose socket was also found to be secured to the tee fitting at the carburetor. Heat damage to the carburetor was observed.

Located adjacent to the gascolator attach area was a 90-degree steel fitting. The non-flared end of the fitting was not connected. The flared end of the fitting was observed to have a nut and associated sleeve with approximate 2-inch long aluminum tubing extending beyond the nut. According to the installation instructions of the STC, the steel 90-degree fitting was threaded into the in...