N629EK

This factual report was modified on September 7, 2007.

HISTORY OF FLIGHT

On February 8, 2006, at 1210 central standard time, a Swearingen SA-226-TC, N629EK, registered to and operated by Tri-Coastal Airlines, Incorporated, as a Title 14 CFR Part 135 cargo flight, from Dayton, Ohio to Harlingen, Texas, collided with the ground in a nose down, near vertical attitude, near Paris, Tennessee. Visual meteorological conditions prevailed and an instrument flight rules flight plan was filed. The airline transport-rated pilot received fatal injuries and the airplane was destroyed. The flight originated from Dayton, the same day at 1048.

Recorded communications between air traffic controllers at the FAA, Memphis Air Route Traffic Control Center, and the pilot of N629EK show that while in cruise flight at 16,000 feet, the pilot requested and was cleared to make a 360-degree turn to the left. Shortly after this, the pilot requested a 360-degree turn to the right. The pilot then requested radar vectors to the closest airport. Controllers gave the pilot a vector to the closest airport and asked if he had an emergency. The pilot reported he had an asymmetric fuel condition. The pilot then asked for a lower altitude. Controllers cleared the flight to 4,000 feet. About a minute later the pilot transmitted "Mayday" six times and shortly after this radar and radio contact with the flight was lost.

Recorded radar data from the FAA Memphis Air Route Traffic Control Center showed that at 1803:13 the accident airplane was proceeding on a southerly heading at 16,100 feet mean sea level (MSL). At 1803:53 the airplane turned left to a southeasterly heading. At 1804:13 the airplane turned right returning to its original southerly heading. At 1805:14 the accident airplane turned to the right on a southwesterly heading, and maintained that heading until 1809:04 at which time the airplane turned due west and was at an altitude of 15,400 feet. The last radar contact was at 1810:06 at an altitude of 13,800 feet. The airplane wreckage was located due north from this last recorded radar contact.

According to witnesses, the airplane was heard and then seen descending at a high rate of speed in a near vertical attitude and then collided with the ground and exploded. They stated that the impact shook the ground and their homes, and when they got to the impact sight, they observed a large fireball and a hole in the ground with small fires burning around it. Witnesses stated that the airplane sounded like a "top fuel dragster running wide open" that lasted about 20-seconds. Witnesses stated that after the crash they telephoned local authorities to report the accident.

PERSONNEL INFORMATION

A review of information on file with the Federal Aviation Administration Airman's Certification Division, Oklahoma City, Oklahoma, revealed that the pilot was issued a commercial pilot certificate (Foreign Based) for Airplane Multiengine Land, Airplane Single Engine Land, and Instrument Airplane. Limitations listed on the certificate had the following: Issued on basis of and valid only when accompanied by Libya Pilot License Number 648, all limitations and restrictions on the Libya pilot license apply. This included; not valid for the carriage of persons or property for compensation or hire or for agricultural aircraft operation. Additionally, the pilot was issued an Airline Transport Pilot Certificate on March 3, 2005 for airplane multiengine land, with a type rating in the SA-227.

A review of records on file with the FAA Aero Medical Records revealed the pilot held a first class medical certificate issued on July 22, 2005, with a restriction that it was not valid for any class after. The pilot reported on his application for the medical certificate that he had accumulated 5,237 total flight hours.

AIRCRAFT INFORMATION

The Swearingen SA226TC, Serial Number: TC-396, N629EK, was operated by TriCoastal Air Inc., Wilmington, Delaware, Certificate Number: E18A8091. A review of the airplane's maintenance records revealed that the airplane was maintained under an approved aircraft inspection program (AAIP). The last inspection was conducted on December 15, 2005. The airframe's total time was recorded as 15,883.0 hours. The left engine as of the date of the accident had accumulated 9,206.8 hours since new. The Right engine as of the date of the accident had accumulated 22,524.4 hours since new.

The left Engine P-54075C is on the Continuous Airworthiness Maintenance program. February 9, 2006: TSN 9206.8, TSCAM 3025.4, CSCAM 2537 Hot Section and Gearbox Inspection: March 1, 1999 CAM Inspection: May 1, 1995, TSN 22406.4, TSO 5600.3, CSO 6455, Worldwide Aircraft Services Engine Conversion and Overhaul: October 23, 1987, TSN 16,806.1, CSN Unknown, Garrett Turbine Engine Co. Engine Conversion and Overhaul: June 16, 1984, TSN 11,198.0, CSN Unknown, Garrett Turbine Engine Co.

The right Engine P-54275 is on the Continuous Airworthiness Maintenance program. February 9, 2006: TSN 22524.4, TSCAM 3069.5, CSCAM 3076 Hot Section and Gearbox Inspection: September 24, 2004, TSN 22,252.1, CSN 31,463, TSCAM 2797.2, CSCAM 2872, Turbine Standard Ltd. CAM Inspection: April 16, 1996 Engine Conversion and Overhaul: September 14, 1987, TSN 13,445.4, CSN 21,746, Turbine Standard Ltd. Engine Conversion and Overhaul: November 5, 1982, TSN 7098.2, CSN 12039, Garrett Turbine Engine Co.

WEIGHT AND BALANCE INFORMATION

The airplane's weight and balance data recorded for the accident flight showed the airplane's empty weight as 8,433.5 pounds, Captains weight as 190 pounds, Cargo Section two as 314 pounds, Zero fuel weight as 8,937 pounds, Fuel load as 3,200 pounds, Ramp weight as 12,137 pounds, and take off weight as 12,000 pounds. Take off Center of Gravity was 268. Fuel burn rate was 600 pounds per hour at 18,000 feet cruise.

METEOROLOGICAL INFORMATION

The nearest weather reporting facility at the time of the accident was Paducah, Kentucky. The 1249 surface weather observation was: Broken clouds at 1,700, visibility 8 statute miles, temperature 2-degrees Celsius, dew point temperature 0-degrees Celsius, wind 220 at 8 knots, and altimeter 30.11. Visual meteorological conditions prevailed at the time of the accident. Additional information indicated that there was a low-pressure system and cold front moving through the area at the time of the accident. Radar mosaic indicated a large band of echoes extending over western Kentucky and Tennessee, with the accident site on the leading edge. Soundings indicated saturated conditions with favorable conditions for rime icing between 3,000 and 11,000 feet (20-degree range), at 16,000 feet winds were from the West at 52 knots, temperature was minus 25.7 degrees Celsius.

WRECKAGE AND IMPACT INFORMATION

Examination of the accident site found the airplane next to a pasture in a heavily wooded area. The airplane was observed imbedded in a crater, which was approximately 25 feet deep, 40 feet long, and 23 feet wide at GPS Coordinates; N36.13.755, W088.16.285. The debris field extended about 375 feet forward of the crater, and about 100 feet in all other directions. Small pieces of airplane skin were observed in the debris field surrounding the crater.

The aircraft impacted the ground in an 80-degree nose-down attitude on a heading of approximately 243-degrees magnetic. There were propeller blade strikes observed on one tree.

The only visible wreckage on initial examination was a section of the aft fuselage and pieces of the empennage. The crater was excavated to a depth of about 25 feet using a large tracked backhoe. Small fragments of wreckage and several pieces of the propeller blades were found up to about 300 feet from the main wreckage.

The entire airplane was severely fragmented by impact forces, however, portions of all flight controls, the tail section, both wing tips; both engines and both propellers were located and identified. The fuel crossflow valve was not located.

Very small fragments of the instrument panel, several small gears from inside instruments, and one altimeter were found. The altimeter was retrieved from the crater and the instrument panel fragments and instrument gears were along a path heading about 270 from the crater and a distance ranging from 30 to 50 feet from the crater. No portion of the center console or either side panel was found.

Several small sections of wing spar caps and webs were located and all displayed overload fractures. A small section of the aft spar carry through with a short piece of fuselage belt frame attached was found with the wing to fuselage fitting attached and displayed bending overload type failures of both, the spar and the belt frame. The largest portion of wing main spar found was a section of the upper spar cap on the main spar carry through (Center Section) about 3 feet long. It was retrieved at a depth of about 10 feet at the west end of the crater.

Three sections of the aileron push pull tubes were found in or near the crater and each displayed bending overload type failures. Several sections of control cables were examined and each displayed tension overload failures. All recovered pieces of control cable were excavated from the crater.

Segments of both flaps were found in the crater and one flap actuator was located. The flap segments displayed severe compression and fragmentation. The actuator was in the retracted position and held in position by wing structure.

Several very small pieces of wing leading edge were located and all displayed severe compression fore to aft and fragmentation.

Both ailerons were severely fragmented. Most fragments were retrieved from the crater and two small segments were in the wreckage scatter around the crater.

Both wing tips were severely fragmented and found outside the crater on either end and within about 10 feet of the crater.

Both flaps were severely compressed and fragmented and most fragments were retrieved from w...