Federal Express - FedEx

Cessna 208B Grand Caravan

The pilot reported that, upon reaching the decision altitude on a GPS instrument approach, he saw the runway end identifier lights and continued the approach. Shortly after, the lights disappeared and then reappeared. He continued the approach and landing thinking the airplane was lined up with the runway by using the runway edge lights for reference. Upon touching down about 225 ft left of the runway, the airplane dug into snow and flipped over, which resulted in substantial damage to the wings and tail. The pilot reported that there were no preaccident mechanical malfunctions or failures with the airplane that would have precluded normal operation.

Douglas DC-10

On October 28, 2016, about 1751 eastern daylight time, FedEx Express (FedEx) flight 910, a McDonnell Douglas MD-10-10F, N370FE, experienced a left main landing gear (MLG) collapse after landing on runway 10L at Fort Lauderdale–Hollywood International Airport (KFLL), Fort Lauderdale, Florida, and the left wing subsequently caught fire. The airplane came to rest off the left side of the runway. The two flight crew members evacuated the airplane. The captain reported a minor cut and abrasions from the evacuation, and the first officer was not injured. The airplane sustained substantial damage. The cargo flight was operating on an instrument flight plan under the provisions of Title 14 Code of Federal Regulation (CFR) Part 121 and originated at Memphis International Airport (KMEM), Memphis, Tennessee. The first officer was the pilot flying, and the captain was the pilot monitoring. Both flight crew members stated in post accident interviews that the departure from MEM and the en route portion of the flight were normal. About 1745, air traffic control (ATC) cleared the flight for final approach to the instrument landing system (ILS) approach to runway 10L at KFLL. Recorder data indicate that the first officer set the flaps at 35º about 1746 when the airplane was 3,000 ft above ground level (agl). The first officer disconnected the autopilot about 1749 when the airplane was 1,000 ft agl. Both flight crew members reported that the approach was stable at 500 ft agl. At 200 ft agl, the first officer began making airspeed corrections to compensate for the crosswind. About 1750, the first officer disconnected the autothrottles, as briefed, when the airplane was at 100 ft agl. At 50 ft agl, the first officer initiated the flare. The left MLG touched down about 1750:31 in the touchdown zone and left of the runway centerline. The first officer deployed the spoilers at 1750:34, and the nose gear touched down 3 seconds later. The thrust reversers were deployed at 1750:40. According to cockpit voice recorder (CVR) data, the captain instructed the first officer to begin braking about 1750:39 (the airplane was not equipped with autobrakes). FDR data indicate an increase in brake pedal position angle and increase in longitudinal deceleration (indicating braking) about 1750:41. In post accident interviews, the flight crew members reported hearing a "bang" as the first officer applied the brakes, and the airplane yawed to the left. About this time, the CVR recorded the sound of multiple thuds, consistent with the sound of a gear collapse. About 1750:48, the captain stated, "I have the airplane," and the first officer replied, "you got the airplane." The captain applied full right rudder without effect while the first officer continued braking. About 1750:53, the captain instructed the first officer to call and inform the tower about the emergency. An airport video of the landing showed that the No. 1 engine was initially supporting the airplane after the left MLG collapse when a fire began near the left-wing tip. The airplane eventually stopped off the left side of runway 10L, about 30º to 40º off the runway heading. About 1751, the flight crew began executing the evacuation checklist. The pilots reported that, as they were about to evacuate, they heard an explosion. The airport video showed a fireball erupted at the No. 1 engine. The captain attempted to discharge a fire bottle in the No. 1 engine, but it didn't discharge. They evacuated the airplane through the right cockpit window.

Cessna 208B Grand Caravan

The pilot departed San Juan-Luis Muñoz Marín Airport at 1049LT on a cargo flight to Basseterre-Robert L. Bradshaw International Airport, Saint Kitts & Nevis. The flight was performed by Mountain Air Cargo on behalf of FedEx. The pilot continued the flight at FL110 until 1139LT, reduced his altitude down to FL100 and maintained this level until 1153LT. At this moment, the aircraft was descending between 600 and 800 feet per minute and the pilot decided to divert to the Juancho E. Yrausquin Airport located on Saba Island, Dutch Antilles. While approaching to island from the south, the pilot realized he would not make it, so he attempted to ditch the aircraft some 900 metres off shore. The pilot evacuated the cabin and was quickly rescued while the aircraft sank by a depth of about 1,500 feet. According to the pilot, he decided to divert to the nearest airport due to a loss of engine power.

Cessna 208B Grand Caravan

On behalf of Morningstar Air Express, the pilot departed Sault Sainte Marie Airport, south Ontario, in the morning, for a local training flight. For unknown reasons, the pilot did not maintain any radio contact with his base or ATC and continued to the north for about 1,200 km when the aircraft crashed in unknown circumstances in the Hudson Bay, some 500 km east of Churchill, Manitoba. The aircraft was destroyed and the pilot was killed.

Cessna 208B Grand Caravan

The aircraft was substantially damaged when it collided with a hedgerow during a forced landing following a loss of engine power near Wichita, Kansas. The loss of engine power occurred about 4-1/2 minutes after departing Wichita Mid-Continent Airport (ICT), Wichita, Kansas. The commercial pilot, who was the sole occupant, was fatally injured. The airplane was registered to the Federal Express Corporation and operated by Baron Aviation Services Incorporated, under the provisions of 14 Code of Federal Regulations Part 135 while on an instrument flight plan. Day visual meteorological conditions prevailed for the cargo flight that had the intended destination of Garden City Regional Airport (GCK), Garden City, Kansas. According to air traffic control transmissions, at 0734:35 (hhmm:ss), the pilot requested an instrument flight rules clearance from ICT to GCK. Radar track data indicated that the airplane departed runway 19R approximately 0737:45. At 0738:18, the tower controller told the pilot to change to the departure control frequency. The departure controller then cleared the flight to proceed direct to GCK and to climb to 8,000 ft mean sea level (msl). The airplane continued to climb on a westerly heading until 0742:02, at which time the airplane began a left 180-degree turn back toward the departure airport. According to radar data, the airplane had reached 4,700 ft msl when it began the left turn. At 0742:13, the pilot transmitted that his airplane had experienced a loss of engine power and that he was attempting to return to the departure airport. At 0742:31, the pilot asked if there were any nearby airports because he was unable to reach ICT. The departure controller provided vectors toward an airstrip that was approximately 2.5 miles southeast of the airplane's position. At 0743:46, the pilot advised that he could not see the airstrip because the airplane's windshield was contaminated with oil. At 0744:57, the pilot's final transmission was that he was landing in a grass field. The airplane was located about 2.2 miles south of ICT at 1,600 feet msl, about 300 feet above ground level (agl) at the time of the last transmission. The radar data continued northeast another 1/2 mile before radar contact was lost at 0745:15. A witness to the accident reported that he was outside his residence when he observed the accident airplane overfly his position. He recalled that the airplane's propeller was not rotating and that he did not hear the sound of the engine operating. He stated that the airplane landed in a nearby agricultural field on a northeast heading. He reported that during the landing rollout the airplane impacted a hedgerow located at the northern edge of the field. The witness indicated that the pilot was unresponsive when he arrived at the accident site and that there was a small grass fire located 8 to 10 feet in front of the main wreckage.

McDonnell Douglas MD-11

Aircraft bounced repeatedly during landing on Runway 34L at Narita International Airport. During the course of bouncing, its left wing was broken and separated from the fuselage attaching point and the airplane caught fire. The airplane rolled over to the left being engulfed in flames, swerved off the runway to the left and came to rest inverted in a grass area. The Pilot in Command (PIC) and the First Officer (FO) were on board the airplane, and both of them suffered fatal injuries. The airplane was destroyed and the post-crash fire consumed most parts.

ATR42-300

Aircraft was on an instrument approach when it crashed short of the runway at Lubbock Preston Smith International Airport, Lubbock, Texas. The captain sustained serious injuries, and the first officer sustained minor injuries. The airplane was substantially damaged. The airplane was registered to FedEx Corporation and operated by Empire Airlines, Inc., as a 14 Code of Federal Regulations Part 121 supplemental cargo flight. The flight departed from Fort Worth Alliance Airport, Fort Worth, Texas, about 0313. Instrument meteorological conditions prevailed, and an instrument flight rules flight plan was filed.

Cessna 208B Grand Caravan

The airplane was on a visual approach to an airport when the engine stopped producing power. The pilot subsequently landed the airplane in a field, but struck trees at the edge of the field during the forced landing. Examination of the engine, engine fuel controls, and Power Analyzer and Recorder (PAR), provided evidence that the engine shut down during the flight. Further examination of engine and fuel system components from the accident airplane failed to reveal a definitive reason for the uncommanded engine shut-down.

Douglas DC-10

The approach and landing were stabilized and within specified limits. Recorded data indicates that the loads experienced by the landing gear at touchdown were within the certification limits for an intact landing gear without any pre-existing cracks or flaws. The weather and runway conditions did not affect the landing. The application of braking by the accident crew, and the overall effect of the carbon brake modification did not initiate or contribute to the landing gear fracture. Post-accident modifications to the MD-10 carbon brake system were implemented due to investigative findings for the purposes of braking effectiveness and reliability. Post accident emergency response by the flight crew and ARFF was timely and correct. The left main landing gear (LMLG) outer cylinder on the accident airplane had been operated about 8 ½ years since its last overhaul where stray nickel plating likely was introduced in the air filler valve hole. Nickel plating is a permissible procedure for maintaining the tolerances of the inner diameter of the outer gear cylinder, however the plating is not allowed in the air filler valve bore hole. Literature and test research revealed that a nickel plating thickness of 0.008" results in a stress factor increase of 35%. At some point in the life of the LMLG, there was a load event that compressively yielded the material in the vicinity of the air filler valve hole causing a residual tension stress. During normal operations the stress levels in the air filler valve hole were likely within the design envelope, but the addition of the residual stress and the stress intensity factor due to the nickel increased these to a level high enough to initiate and grow a fatigue crack on each side of the air filler valve hole. The stresses at the air filler valve hole were examined via development of a Finite Element Model (FEM) which was validated with data gathered from an instrumented in-service FedEx MD-10 airplane. The in-service data and FEM showed that for all of the conditions, the stress in the air filler valve hole was much higher than anticipated in the design of the outer cylinder. Fatigue analysis of the in service findings and using the nickel plating factor resulted in a significantly reduced fatigue life of the gear cylinder compared with the certification limits. During the accident landing the spring back loads on the LMLG were sufficient to produce a stress level in the air filler valve hole that exceeded the residual strength of the material with the fatigue cracks present.

Cessna 208B Grand Caravan

The pilot stated that during takeoff, "after becoming airborne, the airplane quit accelerating and a positive climb rate was not established." He pushed the power lever all the way forward, but did not feel a response from the airplane. Witnesses reported that the airplane became airborne, but failed to gain altitude and struck an antenna array and a fence off the departure end of the runway. The airplane continued across a slough, struck an embankment and came to rest about 900 feet from the departure end of the runway on a golf course located adjacent to the airport. Examination of the airplane revealed no pre-mishap airframe anomalies. Examination of the engine revealed that the compressor and power turbines displayed moderate circular rubbing damage to the blades suggesting engine operation at impact, likely in the low to mid power range. Examination of the airframe and engine revealed no anomalies that would have prevented the engine from producing power prior to impact. The reason for the partial loss of engine power was not determined.

Cessna 208B Grand Caravan

The airplane was fueled with 65-gallons of jet-A in preparation for the evening's flight. The 6,600-hour pilot stated that no abnormalities were noted during the engine start, and takeoff. However; shortly after departure, and after the pilot had leveled off at 7,000-feet, he reported to air traffic control that he had an engine failure and a total power loss. During the descent, the pilot attempted both an air and battery engine restart, but was not successful. The inspection on the engine was conducted on November 30, 2005. The accessory gearbox had a reddish-brown stain visible beneath the fuel pump/fuel control unit. The accessory gearbox was turned; rotation of the drive splines in the fuel pump (splines for the fuel control unit) was not observed. The fuel pump unit was then removed, the area between the fuel pump and accessory gearbox was stained with a reddish brown color. The fuel pump drive splines were worn. Additionally, the internal splines on the fuel pump drive coupling were worn. The wear on the spline drive and coupling prevented full engagement of the spline drives. Both pieces had evidence of fretting, with a reddish brown material present. The airplane had approximately 130 hours since a maintenance inspection (which included inspection of the fuel pump). The engine had accumulated approximately a total time of 9,852 hours, with 5,574 hours since overhaul.

Cessna 208B Grand Caravan

On the day before the occurrence, the accident aircraft arrived in Winnipeg, Manitoba, on a flight from Thunder Bay, Ontario. The aircraft was parked in a heated hangar overnight and was pulled outside at about 0410 central daylight time. The pilot reviewed the weather information and completed planning for the flight, which was estimated to take two hours and six minutes. The aircraft was refuelled and taxied to Apron V at the Winnipeg International Airport, where it was loaded with cargo. After loading was complete, the pilot obtained an instrument flight rules (IFR) clearance for the flight to Thunder Bay, taxied to Runway 36, received take-off clearance, and departed. The aircraft climbed on runway heading for about one minute to an altitude of 1300 feet above sea level (asl), 500 feet above ground level (agl). The flight was cleared to 9000 feet asl direct to Thunder Bay, and the pilot turned on course. The aircraft continued to climb, reaching a maximum altitude of 2400 feet asl about 2.5 minutes after take-off. The aircraft then started a gradual descent averaging about 400 feet per minute (fpm) until it descended below radar coverage. The accident occurred during hours of darkness at 0543. The Winnipeg Fire Paramedic Service were notified and responded from a nearby station.

Fokker F27 Friendship

The crew departed Buenos Aires-Ezeiza-Ministro Pistarini Airport on a night cargo service to Campinas-Viracopos with an intermediate stop in Porto Alegre. While cruising at an altitude of 17,000 feet, smoke was detected in the cargo compartment. The crew elected to extinguish the fire but without success. The crew contacted ATC, declared an emergency and attempted to divert to Montevideo Airport but ATC suggested the crew to divert to Melo which was the nearest airport. As this airfield was closed to traffic at this time, ATC contacted a night guard who switched on the runway lights and alerted the local emergency services. The aircraft landed 340 metres past the runway 07 threshold and stopped 640 metres further. The crew evacuated via the cockpit windows and was uninjured. The aircraft was damaged beyond repair.

Douglas DC-10

On December 18, 2003, about 1226 central standard time, Federal Express Corporation (FedEx) flight 647, a Boeing MD-10-10F (MD-10), N364FE, crashed while landing at Memphis International Airport (MEM), Memphis, Tennessee. The right main landing gear collapsed after touchdown on runway 36R, and the airplane veered off the right side of the runway. After the gear collapsed, a fire developed on the right side of the airplane. Of the two flight crewmembers and five non revenue FedEx pilots on board the airplane, the first officer and one non revenue pilot received minor injuries during the evacuation. The post crash fire destroyed the airplaneís right wing and portions of the right side of the fuselage. Flight 647 departed from Metropolitan Oakland International Airport (OAK), Oakland, California, about 0832 (0632 Pacific standard time) and was operating under the provisions of 14 Code of Federal Regulations (CFR) Part 121 on an instrument flight rules flight plan.

Cessna 208B Grand Caravan

ARTCC asked the pilot of Airspur 8773 if he would be able to execute the VOR instrument approach. The pilot said he could, but he wanted to "hold for a while to see if [the weather] gets a little better" [according to the METAR, visibility was 1.75 statute miles and there was a 200-foot overcast ceiling]. He was cleared to hold north of the VOR at 12,000 feet msl. While holding, the pilot filed the following PIREP indicating light rime icing. Shortly thereafter, he was cleared for the approach. Three witnesses saw the airplane on the downwind leg, just past midfield, at an estimated altitude of 500 feet. Shortly thereafter, one of them heard the engine "spool up to high power...[like reversing] the pitch of the propeller to slow down," and he thought the airplane had landed. Five witnesses said the airplane emerged from the overcast and banked "sharply to the left, then back to the right, then back to the left, then took a hard bank to the right," rolled inverted and struck the highway just south of the airport perimeter. The airplane slid down the embankment and out into a lake, becoming partially submerged. Witnesses said it was "snowing hard" and the highway was covered with 1 to 2 inches of slush. Wreckage examination revealed the flaps were down 30 degrees, the wing deice boots were "ribbed," and the inertial separator was open. According to the toxicological report, chlorpheniramine, desmethylsertraline, sertraline, and pseudoephedrine were detected in blood. In addition, chlorpheniramine, sertraline, phenylpropanolamine, and pseudoephedrine were detected in the urine. The urine also contained acetaminophen. Sertraline (trade name Zoloft) is a prescription antidepressant medication. According to the Guide for Aviation Medical Examiners, "The use of a psychotropic medication is considered disqualifying. This includes all... antidepressant drugs..." Chlorpheniramine is an over-the-counter sedating antihistamine used primarily for the treatment of allergies. Pseudophedrine (trade name Sudafed) is a decongestant. Acetaminophen (trade name Tylenol) is an over-the-counter pain reliever and fever-reducer. According to Dr. Stanley R. Mohler's "Medication and Flying: A Pilot's Guide," the adverse side effects of chlorpheniramine include drowsiness, dizziness, and lessened coordination. The side effects of pseudophedrine are usually mild and infrequent, but may include sleepiness, dizziness, restlessness, headache, and perhaps some loss of coordination and alertness or confusion.

Fokker F27 Friendship

According to the pilot, an unsafe right gear indication was received during the approach, and the control tower controller confirmed the right gear was not fully extended. On landing roll the right main landing gear collapsed and the airplane slid off of the runway. Examination of the right main landing gear revealed the drag brace was fractured. The fracture was located at the lower side of a transition from a smaller internal diameter on the upper piece to a larger internal diameter on the lower piece. The region of the fracture surface was flat and perpendicular to the tube longitudinal axis. The region had a smooth, curving boundary, also consistent with fatigue. The fatigue features emanated from multiple origins at the inner surface of the tube. The Federal Aviation Administration (FAA) issued an Airworthiness Directive (AD) requiring an inspections of main landing gear drag stay units. The AD was prompted by the fracture of a drag stay tube from fatigue cracking that initiated from an improperly machined transition radius at the inner surface of the tube. According to Fokker ,the Fokker F27 Mark 500 airplanes (such as the incident airplane) were not equipped with drag stay units having part number 200261001, 200485001, or 200684001. One tube, part number 200259300, had a change in internal diameter (stepped bore), and the other tube, part number 200485300, had a straight internal bore. AD 97-04-08 required an ultrasonic inspection to determine if the installed tube had a straight or stepped bore. A review of maintenance records revealed that the failed drag stay tube had accumulated 28, 285 total cycles.

Cessna 208B Grand Caravan

The airplane impacted a dirt field and a power line following a loss of control during a simulated engine failure while on a Part 135 proficiency check flight. Both pilots were seriously injured and could not recall any details of the flight after the simulated engine failure. Witnesses observed the airplane flying on a westerly heading at an altitude of 100 to 200 feet, and descending. They heard the sound of an engine “surging” and observed the airplane’s wings bank left and right. The airplane continued to descend and impacted the ground and power lines before becoming inverted. A pilot-rated witness reported that he observed about ¼ inch of clear and rime ice on the airplane’s protected surfaces (deice boots) and about ½ inch of ice on the airplane’s unprotected surfaces. An NTSB performance study of the accident flight based on radar data indicated that the airplane entered a descent rate of 1,300 feet per minute (fpm) about 1,100 feet above the ground. This rate of descent was associated with a decrease in airspeed from 130 knots to 92 knots over a span of 30 seconds. The airplane’s rate of descent leveled off at the 1,300 fpm rate for 45 seconds before increasing to a 2,000 fpm descent rate. The true airspeed fluctuated between a low of 88 knots to 102 knots during the last 45 seconds of flight. According to the aircraft manufacturer, the clean, wing flaps up stall speed was 78 knots. However, after a light rime encounter, the Pilot’s Operating Handbook (POH) instructed pilots to maintain additional airspeed (10 to 20 KIAS) on approach “to compensate for the increased pre-stall buffet associated with ice on the unprotected areas and the increased weight.” With flaps up, a minimum approach speed of 105 KIAS was recommended. The POH also stated that a significantly higher airspeed should be maintained if ½ inch of clear ice had accumulated on the wings.

Boeing 727-200

On July 26, 2002, about 0537 eastern daylight time, Federal Express flight 1478, a Boeing 727-232F, N497FE, struck trees on short final approach and crashed short of runway 9 at the Tallahassee Regional Airport (TLH), Tallahassee, Florida. The flight was operating under the provisions of 14 Code of Federal Regulations Part 121 as a scheduled cargo flight from Memphis International Airport, in Memphis, Tennessee, to TLH. The captain, first officer, and flight engineer were seriously injured, and the airplane was destroyed by impact and resulting fire. Night visual meteorological conditions prevailed for the flight, which operated on an instrument flight rules flight plan.

Cessna 208B Grand Caravan

The pilot obtained a weather briefing, filed an IFR flight plan, and departed on a nonscheduled domestic cargo flight, carrying 270 pounds of freight. The flight proceeded uneventfully until it was established on the VOR/DME-C approach. Radar data indicates that after turning inbound towards the VORTAC from the DME arc, the airplane began its descent from 10,600 feet to the VOR crossing altitude of 9,200 feet. Enlargement of the radar track showed the airplane correcting slightly to the left as it proceeded inbound to the VORTAC at 9,400 feet. Shortly thereafter, aircraft track and altitude deviated 0.75 miles northwest and 9,700 feet, 0.5 miles southeast and 9,600 feet, and 0.5 miles northwest and 9,400 feet before disappearing from radar. Witnesses said the weather at the time of the accident was 600 foot overcast, 1.5 miles visibility in "misting" rain that became "almost slushy on the ground," and a temperature of 36 degrees Fahrenheit. One weather study indicated "an icing potential greater than 50% and visible moisture" in the accident area. Another report said "icing conditions were likely present in the area of the accident." The airplane was equipped and certified for flight into known icing conditions. The wreckage was found in a closely area. There was no evidence of pre-impact airframe, engine, or propeller malfunction/failure. The pilot was properly certificated, but his flight time in aircraft make/model was only 38 hours. He had previously recorded 16 icing encounters, totaling 11.2 hours in actual meteorological conditions. He recorded no ice encounters and only 1.0 hour of simulated (hooded) instrument time in the Cessna 208. Microscopic examination of annunciator light bulbs revealed the GENERATOR OFF light was illuminated. This condition indicates a generator disconnection due to a line surge, tripped circuit breaker, or inadvertent switch operation. The operator's chief pilot agreed, noting that one of the items on the Before Landing Checklist requires the IGNITION SWITCH be placed in the ON position. The START SWITCH is located next to the IGNITION SWITCH. Inadvertently moving the START SWITCH to the ON position would cause the generator to disconnect and the GENERATOR OFF annunciator light to illuminate. He said this would be distracting to the pilot.

Cessna 208B Grand Caravan

The pilot said the preflight, engine start, run-up, taxi and takeoff were "normal". The pilot said that during the climb after takeoff, approximately 1,000 to 1,500 feet above the ground, the airplane's engine "spooled down, slowly and smoothly, like a loss of torque or the propeller going to feather." The pilot performed a forced landing to a field, where the airplane nosed over, and came to rest inverted. Examination of the engine and propeller revealed that the propeller-reversing lever was installed on the wrong side of the reversing lever guide pin, and that the reversing linkage carbon block was no longer installed, and had departed the airplane. Examination of the airplane's maintenance records revealed that the carbon block was replaced during a 100-hour maintenance inspection, 5 hours prior to the accident. Installation of the reversing lever on the incorrect side of the guide pin resulted in improper seating and premature wear of the carbon block. According to the engine manufacturer, any disconnection in operation of the propeller control linkage will cause the propeller governor beta control valve to extend, and drive the propeller into feather.

Cessna 208B Grand Caravan

With a reported ceiling of 500 feet and visibility of 2 miles, the pilot requested and received a Special Visual Flight Rules (VFR) clearance to depart the Bellingham airport. He then took off and called clear of Bellingham's Class D airspace. A witness reported seeing the aircraft flying very low over water near the accident site, appearing to go in and out of clouds, and subsequently seeing it turn toward rising wooded terrain and disappear into the clouds. The aircraft crashed shortly thereafter. Witnesses reported very low ceilings and fog in the accident area at the time. Pieces of the aircraft's left wing and left horizontal stabilizer, along with a felled treetop, were found between the location of the witness's sighting and the main crash site, on or near the crest of a hill about 1/4 mile from the main crash site. These pieces exhibited leading-edge and primary structure damage, and leading-edge-embedded plant material, consistent with the pieces separating from the aircraft upon contact with trees. Wreckage and impact signatures at the main crash site were indicative of an uncontrolled impact with the ground. Investigators found no evidence of any aircraft malfunctions or cargo anomalies occurring prior to the apparent tree strikes.

McDonnell Douglas MD-11

The aircraft departed Shanghai-Hongqiao Airport at 2116LT on a cargo flight to Subic Bay with a load of electronics and garments. Weather conditions at Subic Bay Airport was at follow: scattered at 1,800 feet and 7,000 feet, light rain, wind calm and visibility six km. At 2315LT, the aircraft landed on runway 07 (2,400 metres long). Unable to stop within the remaining distance (the runway was wet), the aircraft overran and plunged in the Subic Bay. Both pilots were injured and the aircraft was totally destroyed.

Cessna 208B Grand Caravan

The airplane was making an instrument landing system approach in instrument meteorological icing conditions when control was lost. The airplane impacted the terrain 1.6 miles from the approach end on the runway. The airplane contacted the terrain with the left wing first prior to cartwheeling and coming to rest approximately 120 feet from the point of first impact. The pilot had 19 hours total flight time in Cessna 208's of which 1.9 hours were in actual instrument meteorological conditions.

Cessna 208B Grand Caravan

The flight was in radio contact with air traffic controllers at the FAA Memphis Air Route Traffic Control Center (ARTCC), and was level at 9,000 feet, when the pilot checked in on frequency. The last radio contact with the flight was at 0447. At 0520, radar contact was lost. The airplane impacted in rough terrain, at a steep angle of impact. Two other company pilots flying in trail of the accident aircraft said, they had radio contact with the pilot of N840FE about 5 minutes before the accident. They said he sounded fine and did not say anything about any problems. Radar data showing the flight's ground speed indicated that at 0512, the ground speed was 158 knots (182 mph). The ground speed then decreased to 153 (176 mph), 143 (165 mph), 138 (159 mph), and 132 (152 mph), until at 0519:40, when the ground speed of the flight was 125 knots (144 mph). After the radar read out at 0519:40, the next radar hit was coast (no information), and then the flight disappeared from the radar scope. The airplane's heading and altitude did not change during the decrease in ground speed. According to the NTSB Radar Data Study, calculated flight parameters indicated the airplane "...experienced a slow reduction of airspeed in the final 8 minutes of flight at altitude, and then abruptly exhibited a sharp nose down pitch attitude with a rapid increase in airspeed." About the time of the reduction in airspeed, pitch angle began to slowly increase also. When radar contact was lost, the calculated airspeed had reduced to less then 102 knots [118 mph], and calculated body angle of attack [AOA] had increased to 8.8 degrees. A large reduction in pitch angle, angle of attack, and flight path angle as the airspeed increases after peak AOA was reached. Examination of the engine Power Analyzer and Recorder (PAR) revealed that no exceedences were in progress at the time power was removed from the PAR. It was determined that no caution timing events were in progress. The PAR computer appeared to be operating correctly until power was removed at impact. Examination of the airplane's autopilot were not conclusive due to impact damage. Determination of whether the autopilot was engaged or not engaged at the time of the accident could not be determined. The NTSB Meteorological Factual Report revealed that at 0515, about 7 minutes before the flight was lost on radar, the radiative temperature in an area centered at Clarksville (4 kilometer resolution data), showed that the Mean Radiative Temperature was -6.26 degrees C (21F). The Minimum Radiative Temperature was -6.66 degrees C (19F). The Maximum Radiative Temperature was -6.06 degrees C (21F). According to the Archive Level II Doppler weather radar tape for a beginning sweep time of 0508:10, showed that N840FE had tracked into a weather echo from 0510:34, to 0516:28. The Doppler Weather Radar data, revealed that N840FE, had entered a weak weather echo about the same time that the airspeed of the airplane started to decrease, at an altitude of about 9,000 feet, and the airplane was in the weak weather echo for a few minutes. Based on the weather data, it was determined that in-flight airplane icing conditions were encountered by N840FE. Cessna Aircraft Company Airworthiness Directive (AD) 96-09-15; Amendment 39-9591; Docket No. 96-CE-05-AD, applicable to this airplane and complied with by the company, on December 12, 1996, stated: "...to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions... operators must initiate action to notify and ensure that flight crewmembers are apprised of this change...revise the FAA-approved Airplane Flight Manual (AFM) by incorporating the following into the Limitation Section of the AFM. This may be accomplished by inserting a copy of this AD in the AFM...." The airplane was equipped with leading edge deicing boots on the wings, elevators, struts, and had a cargo pod deicing capability. Lights were installed to illuminate the leading edge of the wings, to aid the pilot in detecting ice on the leading edges of the wings during night operations. The airplane was not equipped with an ice detection device.

Cessna 208B Grand Caravan

The pilot was reported to be in a hurry as he positioned two aircraft and picked up the accident aircraft for his final positioning leg. He told company personnel he had a birthday party to go to and his family confirmed this. The pilot reported to company personnel that he was departing on runway 3 and that he would report in on his arrival at the destination. No further contacts with the flight were made and the wreckage of the aircraft was discovered off the end of the departure runway about 40 minutes after his reported takeoff. Examination showed the aircraft had run off the left side of the runway about 800 feet from the end and then crossed over the runway and entered into the woods at the departure end of the runway. Post crash examination showed no evidence of pre crash failure or malfunction of the aircraft structure, flight controls, or engine. The onboard engine computer showed the engine was producing normal engine power and the aircraft was traveling at 98 knots when electrical power was lost as it collided with trees. The aircraft's control lock was found tangled in the instrument panel near the left control yoke where it is normally installed and the lock had multiple abnormal bends, including a 90 degree bend in the last 1/2 inch of the lock where it engages the control column. Removal of the control lock and checking the flight controls for freedom is on the normal pilots checklist. The pilot was also found to not be wearing his shoulder harness.

McDonnell Douglas MD-11

The aircraft crashed while landing on runway 22R at Newark International Airport (EWR), Newark, New Jersey. The regularly scheduled cargo flight originated in Singapore on July 30 with intermediate stops in Penang, Malaysia; Taipei, Taiwan; and Anchorage, Alaska. The flight from Anchorage International Airport (ANC), Anchorage, Alaska, to EWR was conducted on an instrument flight rules flight plan and operated under provisions of 14 Code of Federal Regulations (CFR) Part 121. On board were the captain and first officer, who had taken over the flight in Anchorage for the final leg to EWR, one jumpseat passenger, and two cabin passengers. All five occupants received minor injuries in the crash and during subsequent egress through a cockpit window. The airplane was destroyed by impact and a post crash fire. According to flight plan and release documents, the airplane was dispatched to ANC with the No. 1 (left engine) thrust reverser inoperative. The flight plan time from ANC to EWR was 5 hours and 51 minutes—47 minutes shorter than the scheduled time of 6 hours and 38 minutes because of 45-knot tailwinds en route. The flight crew stated that at flight level (FL) 330 (about 33,000 feet mean sea level [msl]), the flight from ANC to EWR was routine and uneventful. At 0102:11, a Federal Aviation Administration (FAA) Boston Air Route Traffic Control Center air traffic controller instructed flight 14 to descend and maintain FL180, according to the airplane’s cockpit voice recorder (CVR). About 0103, the captain and first officer discussed the approach and landing to runway 22R and the airplane’s landing performance. Using the airport performance laptop computer (APLC), the first officer determined that the airplane’s runway stopping distance would be approximately 6,080 feet using medium (MED) autobrakes. According to the CVR, at 0103:33, the flight crew then compared the APLC approximate landing distance for MED braking (6,080 feet) to the after-glideslope touchdown distance (6,860 feet) provided on the instrument approach plate. Based on the flight crew's calculation (6,860 – 6,080), MED braking provided a 780-foot margin after stopping. The flight crew then compared the APLC approximate landing distance for maximum (MAX) braking (5,030 feet) to the same 6,860-foot after-glideslope touchdown distance provided on the instrument approach plate. Based on the flight crew's calculation (6,860 – 5,030), MAX braking provided a 1,830-foot margin after stopping. On the basis of these calculations, the first officer suggested using MAX autobrakes. The captain agreed, stating “we got a lot of stuff going against us here so we’ll…start with max.” The first officer added, “I mean…I mean if we don’t have the reverser.” At 0114:22, the captain asked the first officer to advise the passengers that “we’re gonna have a pretty abrupt stop because of those brakes and the thrust reversers and all that stuff.” Twice during the approach, the captain asked the first officer to remind him to only use the No. 2 and No. 3 thrust reversers. At 0116:16, the captain noted that the left landing light was inoperative, adding “… just the right’s working.” The EWR tower controller cleared flight 14 to land at 0129:45 and advised the flight crew “winds two five zero at five.” At 0130:02, the first officer stated “max brakes” during the before-landing checklist. The captain replied “max brakes will be fine,” and the first officer responded “if they work.” At 0130:34, the captain stated “[landing gear] down in four green” and called for “flaps fifty.” At 0130:45, the captain disengaged the autopilot at an altitude of 1,200 feet during the approach and “hand flew” the airplane to touchdown. The autothrottles were engaged, as recommended by McDonnell Douglas and FedEx procedures. According to information from the airplane’s flight data recorder (FDR), the approach was flown on the glideslope and localizer until touchdown, and the airplane’s approach airspeed was about 158 knots until the flare. According to the CVR, the pilots had selected an approach reference speed of 157 knots, or Vref plus 5 knots. Altitude callouts were made by the on board central aural warning system (CAWS) at 1,000 feet and 500 feet, and the first officer called out minimums (211 feet) at 0132:03. At 0132:09, the first officer stated “brakes on max,” and CAWS callouts followed for 100, 50, 40, 30, 20, and 10 feet until the sound of initial touchdown at 0132:18.75. One-half second later, the CVR recorded an expletive by the captain. At 0132:20.26, the CVR recorded increasing high-frequency tones consistent with engine spool-up (accelerating engine rpms), and at 0132:21.06, the CVR recorded a decrease in high-frequency tones consistent with engine spool-down. The sound of a “loud thump” consistent with another touchdown was recorded at 0132:21.62. A series of expletives by the captain and first officer followed until sounds of “metallic breakup” were recorded at 0132:27. FDR data indicated that after the airplane’s initial touchdown, it became airborne and rolled to the right as it touched down again (see section 1.1.1 for a detailed description of the airplane’s performance during the landing sequence). The airplane continued to roll as it slid down the runway, coming to rest inverted about 5,126 feet beyond the runway threshold and about 580 feet to the right of the runway centerline. The accident occurred during the hours of darkness. Visual meteorological conditions prevailed at the time of the accident.

Douglas DC-10

The airplane was at FL 330 when the flightcrew determined that there was smoke in the cabin cargo compartment. An emergency was declared and the flight diverted to Newburgh/Stewart International Airport and landed. The airplane was destroyed by fire after landing. The fire had burned for about 4 hours after after smoke was first detected. Investigation revealed that the deepest and most severe heat and fire damage occurred in and around container 06R, which contained a DNA synthesizer containing flammable liquids. More of 06R's structure was consumed than of any other container, and it was the only container that exhibited severe floor damage. Further, 06R was the only container to exhibit heat damage on its bottom surface, and the area below container 06R showed the most extensive evidence of scorching of the composite flooring material. However, there was insufficient reliable evidence to reach a conclusion as to where the fire originated. The presence of flammable chemicals in the DNA synthesizer was wholly unintended and unknown to the preparer of the package and shipper. The captain did not adequately manage his crew resources when he failed to call for checklists or to monitor and facilitate the accomplishment of required checklist items. The Department of Transportation hazardous materials regulations do not adequately address the need for hazardous materials information on file at a carrier to be quickly retrievable in a format useful to emergency responders.

Cessna 208B Grand Caravan

A Cessna 208B struck a ridge line about 14 miles from the destination airport. The pilot reported to atc he had the airport in sight from 7,000 feet msl more than 30 miles away. A weather reporting station located 5 miles east of the accident site was reporting two cloud layers; a scattered layer at 1,500 feet agl, and a broken layer at 5,000 feet agl. The airplane was descending after the pilot was cleared for a visual approach. The airplane collided with a tree and the ground in a wings level attitude at an elevation of 1,500 feet msl. There was no evidence of mechanical failure or malfunction found with the airplane.

Cessna 208B Grand Caravan

A witness located near the departure end of the runway saw the airplane initially climb in a normal manner, then stay below the clouds and make a shallow bank 180-degree left turn and descend below a tree line. Tower tapes revealed that the pilot twice transmitted that he was "coming back" to the airport during which the background sound of the "fuel selector off" warning horn was heard. The pilot then informed the controller "I've got to get back", and no warning horn was heard. The airplane collided with trees and came to rest about 6,500 feet sse of the runway's end. Prior to departure, the airplane was refueled with 40 gals of jet a (20 gals per tank), which increased the total fuel load to 148 gals. The flight manual required that the fuel balance between the left and right tanks be kept within 200 pounds, and suggested turning off one fuel selector to correct unbalance situations. The condition of one fuel selector turned off will cause the "fuel selector off" warning horn to sound. Exam of the aircraft revealed no evidence of preimpact failures. Prop blade butt signatures indicated it was operating in the governing range, and engine power was being produced at impact.

Cessna 208B Grand Caravan

The pilot contacted approach control and was given the weather as sky partly obscured, ceiling 100 feet, visibility 1/16 mile with fog, wind calm. The pilot then requested a surveillance radar approach to runway 14, to be followed by a surveillance approach to runway 32, in the event of a missed approach from runway 14. The published approach minimums were 1-1/4 mile visibility, ceiling 460 feet msl (438 feet agl). The radar control observed an altitude readout that was below the published minimums and advised the pilot to execute a missed approach. No response was received from the pilot. The aircraft was found floating in the bay approximately 2 miles from the end of the runway. Another pilot (based at the same facility) stated that the two pilots had, on numerous occasions, attempted the approach at times when the weather was reported to be less than that required for the approach. The pilot, sole on board, was killed.

Cessna 208A Caravan

The engine lost oil pressure while climbing through 6,000 feet, and the pilot requested to return to his departure airport. ATC informed the pilot of a closer airport. The pilot secured the engine, feathered the prop, and made a power-off descent to the airport. The pilot elected to make a downwind approach to runway 12L due to his altitude. The airplane overflew the runway and touched down past the departure end. It penetrated the airport perimeter fence, struck several trees, a sign post, a light pole, and an auto before coming to rest in a residential area. Examination of the wreckage revealed the loss of pressure was due to oil leaking. The oil filler cap was found improperly adjusted after the original installation. The maintenance manual does not approve any field repairs on the oil filler cap engaging mechanisms. The airplane's flaps were found at a 7° intermediate setting.

Cessna 208A Caravan

The Cessna 208A was on an IFR flight to haul freight from Aspen to Denver, Colorado. Moderate to heavy icing conditions were forecast for the Denver area. While on an ILS runway 36 approach, the aircraft encountered icing conditions. Subsequently, it entered a steep descent and crashed about 3 miles from the approach end of the runway. No preimpact part failure of the aircraft was found during the investigation. The 1950 mst weather at the airport was in part: 800 feet scattered, 1,000 feet broken, visibility 4 miles with freezing drizzle and snow showers, temp 28°, dew point 25°.

Cessna 208B Grand Caravan

The Cessna 208B made a takeoff with light wet snow falling, at night. The airplane reached an altitude of 700 feet agl prior to making a steep descent, striking trees and impacting inverted. Radar data showed the aircraft lift off point and initial climb rate approached that shown in the flight manual for short field technique. Two other Cessna 208's preceded the accident aircraft from the same airport, one 13 minutes prior and the other 3 minutes prior. Radar data showed they climbed at a slower rate. The accident airplane had come from a hangar and was not deiced prior to departure. A pilot flying a identical airplane with a similar load commented that his climb rate was lower than normal. Another pilot commented that this was the first wet snow of the year and it was sticking to his engine cowling. The pilot, sole on board, was killed.

Cessna 208A Caravan

PM Air flight 824, a Federal Express scheduled domestic cargo flight, departed Denver, CO, at 0642, IFR to Montrose, CO. Flight was cleared to FL180, but pilot cancelled IFR at 0653. Radar showed aircraft leveled off at 14,500 feet on southwest heading. Aircraft maintained relative constant altitude and heading before crashing 50 feet below summit of 14,221-feet Mt Massive, second tallest peak in Colorado, at approximately 0719. Weather was cavu. Toxicological tests revealed marijuana metabolite level of 37 ng/ml in urine and 1 ng/ml in blood. Pilot was once convicted in 1974 for possession of controlled substance, but had no other alcohol/drug convictions. Evidence indicates pilot obtained adequate sleep prior to flight. During autopsy, two pages from airmen's information manual were found clutched in plt's hands. The pilot, sole on board, was killed.

Cessna 208B Grand Caravan

Pilot said he encountered severe to extreme turbulence upon reaching missed approach point and felt aircraft might stall if he began immediate right turn as called for in missed approach procedure. Pilot said he made left turn at 15 DME (missed approach point is at 11.5 DME) because there was higher terrain to right. Aircraft collided with trees on mountain 3 miles east of airport. Weather analysis indicated potential for light to moderate turbulence but not severe to extreme turbulence. Pilots landing and departing airport prior to and after accident reported light to moderate chop. Radar showed aircraft speed at 183.1 kts between iaf and faf. Between faf and missed approach point, aircraft speed was 95.7 kts. Pilot said he referred to current commercial instrument approach chart while executing approach. Only obsolete government instrument approach book was found in aircraft. Radios were not tuned to missed approach navaids. Pilot-rated passenger said pilot panicked after encountering turbulence.

Cessna 208A Caravan

While cruising on a scheduled cargo flight in IMC the pilot encountered moderate to severe turbulence near an area where weather cells could have been observed on the aircraft's radar. The pilot reversed course, declared an emergency and lost control of the aircraft. The aircraft entered an uncontrolled descent, collided with terrain and was destroyed. The recently hired pilot had completed the FAA approved ground and flight training program in the aircraft. During the pilot's recent training, neither the FAA nor the operator required the pilot to demonstrate proficiency in unusual attitude recoveries or have knowledge in the operation of the aircraft's weather radar. Company employees, which included the pilot's husband, stated that the pilot had no previous experience with weather radar and did not understand the weather radar installed in this aircraft. They further stated that the pilot appeared to be tired. The pilot, sole on board, was killed.

Dassault Falcon 20

The crew expected to make a straight-in approach but was cleared by ATC to make an ILS circling approach that was completed in rain showers with a tailwind of 8 knots. After touchdown on a wet runway, the crew encountered difficulties to decelerate properly as the airplane suffered hydroplaning. Unable to stop within the remaining distance, the airplane overran and came to rest few dozen yards further. Both pilots were seriously injured and the aircraft was damaged beyond repair.