Embraer EMB-120 Brasília

The flight was being vectored for the approach to runway 3R at Detroit Metropolitan Wayne County Airport (DTW) when the aircraft descended and impacted the ground. The aircraft struck the ground in a steep nose-down attitude in a level field in a rural area about 19 nm southwest of DTW. The flight carried 26 passengers and 3 crew members. There were no survivors and the airplane was destroyed by impact forces and a post crash fire. Instrument meteorological conditions prevailed at the time of the accident. The investigation revealed that it was likely that the airplane gradually accumulated a thin, rough glaze/mixed ice coverage on the leading edge deicing boot surfaces, possibly with ice ridge formation on the leading edge upper surface, as the airplane descended from 7,000 feet mean sea level (msl) to 4,000 feet msl in icing conditions, which may have been imperceptible to the pilots. The pilots had been instructed by air traffic control to slow to 150 knots and according to flight data recorder information, the airplane began to show signs of departure from controlled flight as it decelerated from 155 to 156 knots while in a flaps-up configuration. The investigation disclosed that the FAA failed to adopt a systematic and proactive approach to the certification, and operational issues of turbopropeller-driven transport airplane icing. The icing certification process has been inadequate because it has not required manufacturers to demonstrate the airplane's flight handling and stall characteristics under a sufficiently realistic range of adverse ice accretion/flight handling conditions. The aircraft manufacturer had issued a revision in April, 1996 to the approved flight manual which included activation of the leading edge deicing boots at the first sign of ice formation. The airplane operator did not incorporate the procedure, because it was contrary to the company's trained procedures and practices and of the belief that enacting the changes would result in potentially unsafe operation. Investigators' discussion with management personnel at each of the seven U.S.-based operators of the aircraft indicated that at the time of the accident only two of these operators had changed their procedures to reflect the information in the revision. The FAA, at the time of the accident, did not require manufacturers of all turbine-engine driven airplanes to publish minimum airspeed information for various flap configurations and phases and conditions of flight. During Safety Board investigators postaccident interviews with company pilots, there were inconsistent answers on the complex and varied minimum airspeed requirements established by the company for both icing and nonicing conditions. It was also noted that the pilots uncertainty of the appropriate airspeeds might have been associated with the language used, the different airspeeds and criteria contained in the guidance, the company's methods of distribution, and the company's failure t o incorporate the guidance as a formal, permanent revision to the flight standards manual.

Atlantic Southeast Airline Flight 529 was climbing through 18,000 feet, when a blade from the left propeller separated. This resulted in distortion of the left engine nacelle, excessive drag, loss of wing lift, and reduced directional control. The degraded performance resulted in a forced landing. While landing, the airplane passed through trees, impacted the ground, and was further damaged by post impact fire. An exam of the left propeller revealed the blade had failed due to a fatigue crack that originated from multiple corrosion pits in the taper bore surface of the blade spar. The crack had propagated toward the outside of the blade and around both sides of the taper bore. Due to 2 previous blade failures (separations), a borescope inspection procedure had been developed by Hamilton Standard to inspect returned blades (that had rejectable ultrasonic indications) for evidence of cracks, pits and corrosion. The accident blade was one of 490 rejected blades that had been sent to Hamilton Standard for further evaluation and possible repair. Maintenance technicians, who inspected the blade, lacked proper NDI familiarization training and specific equipment to identify the corrosion that resulted in fatigue. The captain and seven passengers were killed.

In climb, captain (pic) increased pitch, when flight attendant (f/a) entered cockpit and suggested faster climb, so she could begin cabin service. Autoflight was set in pitch and heading modes, contrary to company policy. Pic and f/a had non- pertinent conversation for 4.5 min, while 1st officer (f/o) was making log entries. Airplane stalled in IMC at 17,400 feet. Initial recovery was at 6,700 feet after f/o lower gear, then due to improper recovery, 2nd stall occurred and recovery was at 5,500 feet. Left propeller shed 3 blades, left engine cowling separated, left engine was shut down in descent. Level flight could not be maintained and forced landing was made at closed airport. Pic overshot final turn due to controllability problems and landed fast with 1,880 feet of wet runway remaining. Airplane hydroplaned off runway and was further damaged. Crew got limited sleep during 3 day trip, though rest periods available. Freezing level near 11,500 feet, clouds tops to 21,000 feet with potential for icing to 19,000 feet. No pre-accident malfunction was found.

The airplane broke up in flight while descending from FL240. The horizontal stabilizer, or top of the T-type tail, had separated from the fuselage before ground impact. Examination revealed that the 47 screw fasteners that would have attached the upper surface of the leading edge assembly for the left side of the horizontal stabilizer were missing. They had been removed the night before during scheduled maintenance. Investigation revealed that there was a lack of compliance with the FAA-approved general maintenance manual procedures by the mechanics, inspectors, and supervisors responsible for assuring the airworthiness of the airplane the night before the accident. In addition, routine surveillance of the continental express maintenance department by the FAA was inadequate and did not detect deficiencies, such as those that led to this accident. All 14 occupants were killed.

Witnesses reported that the airplane suddenly turned or rolled left until the wings were perpendicular to the ground. The airplane then fell in a nose-down attitude. Examination of the left propeller components indicated a blade angle of about 3°, while the left propeller control unit (pcu) ballscrew position was consistent with a commanded blade angle of 79.2°. Extreme wear on the pcu quill spline teeth, which normally engaged the titanium-nitrided splines of the propeller transfer tube, was found. The titanium-nitrided surface was much harder and rougher than the nitrided surface of the quill. Therefore, the transfer tube splines acted like a file and caused abnormal wear of the gear teeth on the quill. Wear of the quill was not considered during the certification of the propeller system. The aircraft was totally destroyed upon impact and all 23 occupants were killed, among them John Goodwin Tower, Senator of Texas and the astronaut Manley Sonny Carter.

The crew was completing a local training flight at São José dos Campos Airport. While circling with one engine out, the pilot-in-command lost control of the airplane that crashed near the runway. Five occupants were killed and four others were injured.

Following an uneventful flight from Brussels, the crew contacted Bordeaux Approach at 15:01 and was vectored for an ILS approach to runway 23. Visibility was poor with low clouds at 100 feet and a runway visual range (RVR) of between 650 and 350 metres. Flight 1919 crossed the KERAG beacon, the initial approach fix (IAF) at an altitude of FL144, at 15:04:40. Cloud base was still around 100 feet so the crew requested to enter a holding pattern to the south of the airport. The weather conditions slightly improved during the next few minutes and Bordeaux Approach reported a cloud base at 160 feet. Flight 1919 had not reached the holding pattern yet and the pilot decided to attempt to rejoin the ILS. At 15:06:38 the flight was cleared direct to the BD beacon and to descend down to 2000 feet. At the BD beacon, the flight was cleared for final approach and instructed to contact Bordeaux Tower. The airplane had overshot the centreline and was slightly right on the glidepath. Bordeaux Tower then instructed the flight to report over the Outer Marker, which was acknowledged by the captain. After crossing the Outer Marker, the airplane was still not properly established on the ILS. The airplane descended below the glideslope with the crew hurriedly deploying flaps and landing gear. The captain did not contact Bordeaux Tower as requested. Instead he took over control of the airplane, attempting to continue the approach. Both crew members had very little time to adapt to their new roles as the airplane was descending below the glide slope. The descent continued until the aircraft struck tree tops and crashed in the Eysines forrest, about 5 km short of runway. The aircraft was totally destroyed and all 16 occupants were killed.

Brand new, the aircraft was took over by ASA crew to be delivered to Atlanta, Georgia. He was cleared by the São José Tower controller to follow the 010° radial to the SJC VOR, and cross the VOR at 5,000 feet. Some time after takeoff São José Tower instructed the flight to climb to FL280 out of 5,000 feet and intercept the 352 radial of the SJC VOR. The flight crew failed to follow the instructions and continued at an altitude of 5,000 feet. In limited visibility due to low clouds, the airplane struck the slope of a mountain located in the Mantiqueira Mountain Range. The wreckage was found 700 feet below the summit. All five occupants were killed.