MIA00FA117

According to the PIC, substantiated by the widow of the passenger/pilot, the airplane fuel tanks were topped off at Orangeburg Municipal Airport, Orangeburg, South Carolina, on March 19, 2000. The PIC further stated that he flew directly home to Columbia Downtown Airport, parked, and tied down for a total fuel burn time of about 30 minutes. On March 22, 2000, the airplane took off from Columbia Downtown Airport, the PIC having radioed his intention to stay in the traffic pattern, and sustained an engine stoppage as the airplane approached the abeam position for its first landing. The airplane collided with the terrain and revealed no evidence of onboard fuel at the crash site. The engine underwent a factory test cell run, and it was unsatisfactory until factory fuel injector nozzles were substituted, at which time the engine met factory specifications. Subsequent disassembly examination of the fuel system components revealed contamination in the fuel injector servo. The fuel quantity indication system underwent factory testing and revealed the right tank system was operating erratically, which appeared to be a precrash condition.

History of flight

On March 22, 2000, about 1820 eastern standard time, a Cessna 177RG, N1556H, registered to Aircraft Holding Co., LLC, operating as a Title 14 CFR Part 91 personal flight, crashed during an emergency landing at Columbia, South Carolina. Visual meteorological conditions prevailed and no flight plan was filed. The airplane was destroyed, the private-rated pilot was seriously injured, and a private pilot-rated passenger was fatally injured. The flight originated from the same airport about 10 minutes before the accident.

According to another pilot who was in the landing pattern at Columbia Owens Downtown Airport when N1556H announced on unicom frequency that he was taxiing onto runway 31 for takeoff, intending to stay in the pattern, the departure and crosswind turn appeared normal. The other pilot completed a touch-and-go landing and lost sight of N1556H somewhere during his, (N1556's) downwind leg. The other pilot heard N1556H begin his "on base" call, pause for a few seconds, and then transmit that he was declaring an emergency because of an engine failure, and that he didn't think he could make the field. At about 1850, the other pilot could see that rescue workers were on the scene.

Personnel information

The PIC/owner possessed a private pilot's license with single engine-land and instrument/airplane ratings. The PIC's logbook indicates he had logged 24.7 hours of PIC time in the airplane, and had accumulated a total of 449 flying hours. According to the PIC, although the pilot/passenger held a current private pilot's license, he had not flown, nor was he flying N1556H, at the time of the accident.

Two FAA inspectors interviewed the PIC/owner at the Richland Hospital, Columbia, South Carolina, on April 28, 2000. Any details pertinent to the day of the accident could not be recalled by the PIC. The PIC's submission of NTSB form 6120.1/2 on August 7, 2000, omitted any narrative of the accident. The FAA report of the hospital interview is an attachment to this report.

Aircraft information

The airplane had been purchased by the PIC/owner from a private owner and delivered from Caldwell, New Jersey, on December 30, 1999. At the time of the airplane's annual inspection on September 1, 1994, the accumulated tachometer time was 1576.5 hours, and at the time of it's annual on September 9, 1999, tachometer time was 1598.7 hours. The repair station work order associated with the 1999 annual inspection contained the following entries, (1) "Check fuel screen on servo found debris, flushed out with boost pump. Pull and check injectors, flow fuel thru fuel lines to injectors. OK. 2650 (rpm) reached at static run up awaiting pilot report." (2) "Remove gascolator and disassemble. Replace bad plunger valve and shaft o-ring. Reassemble and check for leaks, OK."

According to maintenance records, the left fuel quantity/oil pressure combination gage was replaced in September, 1995, in accordance with Cessna service kit, SK177-55, 58, and 52.

Meteorological information

Visual meteorological conditions prevailed at the time of the accident. For additional information, see Weather Information on page 4 of this report.

Wreckage and impact information

Ground collision occurred about 1/2 mile from the threshold of runway 31, very near runway extended centerline in an area of trees and dense scrub underbrush running along the northern edge of railroad tracks. The airplane's left wingtip first impacted a 70-foot-tall pine tree located about 30 feet north of the northern edge of that railroad bed. Fragments of the fiberglass wingtip remained in the tree. The power supply for the left wingtip strobe light was found on the railroad bed abeam of the tree strike. A distance of about 160 feet further, on a heading of about 310 degrees, the main wreckage was located in the underbrush. The airplane came to rest inverted, intact but heavily battered, about 30 degrees nose down, heading about 320 degrees. The right cabin door had been removed by emergency personnel. About 18 inches aft of the wing trailing edge, the fuselage was bent downward until the vertical stabilizer contacted the ground. The wing fuel tanks had ruptured and both wing leading edges had been crushed flat corresponding to the angle of terrain impact. Fire rescue workers arrived within 7 minutes of the crash prepared to foam the wreckage; however, they reported that the wreckage site or surrounding area lacked any evidence of fuel spill. There was no odor of spilled fuel when they arrived, nor did they observe any leakage from the wings or engine.

The fuel caps and filler ports revealed a proper fit and there were no fuel stains present. There was no evidence of fuel spewage in the foliage and no residual fuel was found in either tank. The wing skin revealed no evidence of hydraulic bulging in the vicinity of the fuel tanks. The right tank's inner walls were dry and the left tank's inner walls revealed only beads of water. The landing gear were in the extended position and the flaps were retracted. The spinner revealed heavy non-rotational crushing. Both propeller blades were contained in the hub and revealed aft bending with little leading edge or rotational damage.

Aileron control continuity was confirmed from the flight controls to the cockpit yoke. Rudder, stabilator, and trim tab control continuity was confirmed from the flight surface to the firewall bulkhead. The stabilator trim was at about 5 degrees tab down. Both pilot's yokes had broken off their push/pull tubes. The lap belts and left side harness had been cut by emergency personnel. The right side harness was intact and found disconnected at the site. The lower attachment stud plastic bushing was missing. The fuel tank selector was positioned to the right tank. The fuel quantity gages indicated 1/8 tank on the right and empty on the left. The lower fuselage mounted twin fuel reservoir tanks were found intact and undamaged. They were drained and contained 1.5 oz. in the right, and 0.5 oz. in the left, of uncontaminated 100LL aviation fuel. The mixture control was 1 5/16 inch out, the throttle was full in, and the prop control was at full increase. Found in the wreckage was a computer generated technical article titled, "Sacramento Sky Ranch RSA Fuel Injection Troubleshooting".

Fuel feed line continuity was confirmed from each fuel tank to the engine- driven fuel pump using compressed air. The electric auxiliary fuel pump was powered and operated normally. The fuel flow divider was missing the inspection seal on the cover screws safety wiring, and the washers under the cover screws appeared new and shiny. The spark plugs exhibited a light gray to whitish coloring, electrode gaps were proper, and wear was minimal. Six quarts of uncontaminated oil were contained in the crankcase. Engine rotation produced compression at all four cylinders, and valve, accessory drive, and gear train continuity was confirmed. Pumping action was observed for fuel and oil. Spark was observed from all magneto towers upon rotation. The magneto timing to valve/piston relationship appeared proper. The induction, exhaust, and alternate air systems revealed no obstructions, and the exhaust pipe interiors were white in color.

Medical and pathological information

Toxicological testing of specimens of the PIC was conducted by Richland Hospital, Columbia, South Carolina. The medical records are an attachment to this report.

Postmortem examination of the passenger was conducted by Dr. Frank E. Barron, III, Richland County Coroner. Cause of death was attributed to multiple trauma due to airplane crash. Toxicological tests of specimens from the passenger were conducted at the Federal Aviation Administration Research Laboratory, Oklahoma City, Oklahoma. No ethanol was detected. Pseudoephedrine was present in the blood and urine. Ephedrine was present in the blood and urine. Phenylpropanolamine was present i