Crash of a Canadair CL-600-1A11 Challenger in Teterboro

Date & Time: Feb 2, 2005 at 0718 LT
Type of aircraft:
Operator:
Registration:
N370V
Flight Phase:
Survivors:
Yes
Schedule:
Teterboro - Chicago
MSN:
1014
YOM:
1980
Crew on board:
3
Crew fatalities:
Pax on board:
8
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
16374
Captain / Total hours on type:
3378.00
Copilot / Total flying hours:
5962
Copilot / Total hours on type:
82
Aircraft flight hours:
6901
Aircraft flight cycles:
4314
Circumstances:
On February 2, 2005, about 0718 eastern standard time, a Bombardier Challenger CL-600-1A11, N370V, ran off the departure end of runway 6 at Teterboro Airport (TEB), Teterboro, New Jersey, at a ground speed of about 110 knots; through an airport perimeter fence; across a six-lane highway (where it struck a vehicle); and into a parking lot before impacting a building. The two pilots were seriously injured, as were two occupants in the vehicle. The cabin aide, eight passengers, and one person in the building received minor injuries. The airplane was destroyed by impact forces and postimpact fire. The accident flight was an on-demand passenger charter flight from TEB to Chicago Midway Airport, Chicago, Illinois. The flight was subject to the provisions of 14 Code of Federal Regulations (CFR) Part 135 and operated by Platinum Jet Management, LLC (PJM), Fort Lauderdale, Florida, under the auspices of a charter management agreement with Darby Aviation (Darby), Muscle Shoals, Alabama. Visual meteorological conditions prevailed for the flight, which operated on an instrument flight rules flight plan.
Probable cause:
The pilots' failure to ensure the airplane was loaded within weight and balance limits and their attempt to takeoff with the center of gravity well forward of the forward takeoff limit, which prevented the airplane from rotating at the intended rotation speed.
Contributing to the accident were:
1) PJM's conduct of charter flights (using PJM pilots and airplanes) without proper Federal Aviation Administration (FAA) certification and its failure to ensure that all for-hire flights were conducted in accordance with 14 CFR Part 135 requirements;
2) Darby Aviation's failure to maintain operational control over 14 CFR Part 135 flights being conducted under its certificate by PJM, which resulted in an environment conducive to the development of systemic patterns of flight crew performance deficiencies like those observed in this accident;
3) the failure of the Birmingham, Alabama, FAA Flight Standards District Office to provide adequate surveillance and oversight of operations conducted under Darby's Part 135 certificate; and
4) the FAA's tacit approval of arrangements such as that between Darby and PJM.
Final Report:

Crash of a Gulfstream GIV in Teterboro

Date & Time: Dec 1, 2004 at 1623 LT
Type of aircraft:
Operator:
Registration:
G-GMAC
Survivors:
Yes
Schedule:
Farnborough – Luton – Teterboro
MSN:
1058
YOM:
1988
Flight number:
GMA946
Crew on board:
3
Crew fatalities:
Pax on board:
6
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
10000
Captain / Total hours on type:
1000.00
Copilot / Total flying hours:
8000
Copilot / Total hours on type:
2000
Aircraft flight hours:
7452
Circumstances:
The flight was cleared for the ILS Runway 19 approach, circle-to-land on Runway 24; a 6,013-foot-long, 150-foot wide, asphalt runway. The auto throttle and autopilot were disengaged during the approach, about 800 feet agl. However, the auto throttle reengaged just prior to touchdown, about 35 feet agl. The flightcrew did not recall reengaging the auto throttle, and were not aware of the autothrottle reengagement. According to the auto throttle computers, the reengagement was commanded through one of the Engage/Disengage paddle switches located on each power lever. The target airspeed set for the auto throttle system was 138 knots. After touchdown, as the airplane decelerated below 138 knots, the auto throttle system gradually increased the power levers in an attempt to maintain the target airspeed. Without the power levers in the idle position, the ground spoilers and thrust reversers would not deploy. While the flightcrew was pulling up on the thrust reverser levers, they may not have initially provided enough aft force on the power levers (15 to 32 lbs.) to override and disconnect the auto throttle system. The flight data recorder indicated that the autothrottle system disengaged 16 seconds after the weight-on-wheels switches were activated in ground mode. As the airplane neared the end of the runway, the pilot engaged the emergency brake, and the airplane departed the right side of the runway. The autothrottle Engage/Disengage paddle switches were not equipped with switch guards. Although the autothrottle system provided an audible tone when disengaged, it did not provide a tone when engaged. The reported wind about the time of the accident was from 290 degrees at 16 knots, gusting to 25 knots, with a peak wind from 300 degrees at 32 knots.
Probable cause:
The flightcrew's inadvertent engagement of the autothrottle system, and their failure to recognize the engagement during landing, which resulted in a runway excursion. Factors were the lack of autothrottle switch guards, lack of an autothrottle engagement audible tone, and gusty winds.
Final Report: