ANC95FA008

According to the flight data recorder, when 50 degrees of flaps were selected at 985 feet AGL, the first officer, who was flying the airplane, did not stabilize the approach. The pitch attitude of the airplane varied approximately 2 degrees with corresponding elevator position changes. At 40 to 50 feet the pitch attitude of the airplane was decreasing. The captain stated he felt a higher than normal rate of descent at 20 feet so he grabbed the yoke and pulled back. The airplane landed hard, bounced, and oscillated at least three times, reaching a maximum pitch up attitude of 12.3 degrees. The tail struck the runway during the oscillations. The captain did not use verbal instructions as required by the flight manual and company procedures, when taking control of the airplane. Both pilots were manipulating the controls during the bounced landing recovery.

History of flight

On November 4, 1994 at 1125 Alaska standard time, a McDonnell Douglas, MD-11 airplane, N611FE, operating as Federal Express flight number 016, experienced a hard landing at Anchorage International Airport while landing on runway 6R, Anchorage, Alaska. The airplane landed hard and bounced. The tail struck the runway's surface. The airplane was substantially damaged. The all cargo flight, operating under 14 CFR Part 121, departed Kansai, Japan, on an instrument flight rules flight plan. The destination was Anchorage. Visual meteorological conditions prevailed. The Captain and the First Officer, the only occupants, were not injured.

According to the crew, they were following a Japan Air Lines Boeing 747, which preceded them by an estimated 3 miles. The Federal Express crew was cleared for a visual approach to runway 6R and they used the ILS course for guidance. The Captain stated that the airplane flew through a little bit of turbulence when crossing the shoreline but it was nothing unusual. At 50 feet above the ground everything looked normal, but at 20 feet the Captain stated he perceived an increase in the airplane's sink rate. He and the first officer (the flying pilot) both pulled the yoke back. The airplane hit the runway and bounced upward. The nose of the airplane began to pitch up and the crew pushed the yoke forward. The tail then struck the ground. The nose began to respond, and they landed normally.

Damage to aircraft

The airplane received substantial damage. Approximately 32 feet of lower fuselage skin on the underside of the tail section was scraped and dented. There were small puncture/scrape holes in the skin. The aft pressure bulkhead and supporting steel structures were crushed and bent. The VHF antenna, located on the underside of the tail section, was sheared off.

Personnel information

According to Federal Express flight crew records log, the Captain was hired and received his basic indoctrination into Federal Express on September 1, 1967. He has functioned as a Captain on the Boeing 727 and 747 airplanes. On August 25, 1992, he received transition/upgrade training to the MD-11 airplane. On October 28, 1992 he completed his Initial Operating Experience (IOE) as Captain on the MD-11. According to Federal Express records, the Captain had 1216 hours in the MD-11 airplane.

According to Federal Express flight crew records log, the First officer was hired and received his basic indoctrination to Federal Express on February 12, 1988. He was assigned to the Boeing 727 as a second officer on March 3, 1988. On February 8, 1989 he was assigned to the DC-10 as a second officer. On August 31, 1994, he received transition/upgrade training on the MD-11 airplane and completed his IOE on October 13, 1994. According to Federal Express records, the First Officer had 56 hours in the MD-11 airplane. The first Officer stated, this was his third landing after his IOE.

Flight recorders

The cockpit voice recorder and flight data recorder were retrieved and sent to NTSB Headquarters, Washington, D.C. for readout. The cockpit voice recorder did not contain any pertinent information.

The flight data recorder was deciphered and analyzed. The vertical rate of descent information (VSPD) was not valid on the main readout and was computed by the NTSB HQs flight data recorder analyst by using the altitude and time readouts. This information was portrayed on a chart (included) and at 100 feet above ground level (agl), the rate of descent increased to just over 1000 feet per minute with a nose pitch up attitude of 2.46 degrees. The rate of descent then decreased to 850 feet per minute and again increased to 900 feet per minute when the airplane was 50 feet above the ground. At this point the airplane's pitch attitude was 2.11 degrees up.

A review of the pitch attitude during the approach showed that the airplane's pitch attitude was approximately 3.87 degrees while flaps were selected and set at 35 degrees. The flight data recorder readout frame count number 115 shows that flaps were at 39.731 degrees which shows a transitory position. The pitch attitude of the airplane reached 4.57 degrees. At 785 feet agl, the flaps reached the selected 50 degree position and the airplanes's pitch attitude reduced to 2.11 degrees. From frame count 115 to frame count 127, the airplane's pitch attitude varied from a low of 1.41 degrees to a high of 4.57 degrees. There were two cycles of variation and at frame count number 127; the pitch attitude was decreasing through 2.46 degrees to reach a low of 2.11 degrees.

The flight data recorder elevator positions were examined and were found to fluctuate with the pitch attitude changes. The airplane's pitch attitude would reach its maximum deflection approximately 1 second after the maximum elevator input.

The flight data recorder readout shows that between 55 and 40 feet agl, the airplane's pitch attitude was increasing from 2.11 degrees to 2.81 degrees. The elevator position information shows a positive increase in elevator position. The pitch attitude of the airplane continued to increase to 8.44 degrees until ground contact. Upon ground contact, the elevator position began decreasing from its positive deflection. The flight data recorder readout shows elevator deflection varying to positive pitch up two more times before going to a negative position for the completion of landing.

According to McDonnell Douglas Aircraft, and Federal Express, Inc., the MD-11 has a tendency to pitch up when the spoilers deploy. The spoilers were designed to deploy only to the half position at main wheel spin up and if the throttles were retarded to less than 46 degrees of throttle travel. This was designed to reduce the pitch up effect. According to the flight data recorder readout information, the spoilers did not deploy upon initial ground contact. Throttle position travel was approximately 37 degrees. The spoilers did deploy to the half position upon the second touch down of the main wheels. The following information is excerpted from the flight data recorder readout and shows the relationship between the frame count, average elevator position between left and right and inboard and outboard elevators, spoiler position, and airplane pitch attitude.

frame count avg elev pitch spoiler grnd contact no. position attitude position

129 - 7.316 3.16 8.004 - 11.797 4.22 -- - 8.239 7.03 9.147 - 2.198 8.44 -- initial 130 - -0.6367 5.27 7.828 - 15.159 3.16 -- - 5.031 7.73 27.090 second - -7.66 12.30 -- 131 - -10.282 9.84 26.387 third + final

- 11.6875 4.22 -- - 15.15 -0.35 26.739 - -7.294 0.70 -- 132 - -14.613 0.00 58.667

This information shows that the airplane's pitch attitude responded to the control inputs selected by the flight crew.

Wreckage and impact information

There was no wreckage or debris on the runway after landing.

The damage to the airplane was discovered during the maintenance crews post flight examination of the airplane.

Tests and research

Flight simulator tests conducted at the Federal Express Training facility, Memphis, Tennessee, showed that the airplane had a pronounced tendency for the nose to pitch up upon main gear touchdown. The nose pitch up tendency was exaggerated by the deployment of the spoilers which occurred upon main landing wheel spin up. Upon main landing wheel spin up, the spoilers deployed to the half deployed position.

The simulator tests distinctly showed that