Crash of a Learjet 24 in Pachuca de Soto: 2 killed

Date & Time: Feb 18, 2011 at 1104 LT
Type of aircraft:
Registration:
XB-GHO
Flight Type:
Survivors:
No
Schedule:
Pachuca de Soto - Pachuca de Soto
MSN:
24-141
YOM:
1967
Country:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
2
Circumstances:
The crew was completing a local training flight at Pachuca de Soto Airport. After landing, the aircraft went out of control, veered off runway and eventually collided with a building housing a military canine unit, bursting into flames. The aircraft was destroyed and both pilots were killed.

Crash of a Beechcraft C90 King Air in Saint-Antonin-sur-Bayon: 2 killed

Date & Time: Nov 4, 2010 at 1620 LT
Type of aircraft:
Operator:
Registration:
F-BVTB
Flight Phase:
Flight Type:
Survivors:
No
Site:
Schedule:
Aix-les-Milles - Aix-les-Milles
MSN:
LJ-579
YOM:
1973
Country:
Region:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
9925
Captain / Total hours on type:
2100.00
Copilot / Total flying hours:
499
Copilot / Total hours on type:
1
Aircraft flight hours:
9716
Circumstances:
The twin engine aircraft departed Aix-les-Milles Airport at 1520LT on a local training flight. The crew was cleared to fly between 5,000 and 6,000 feet. The aircraft overflew successively Marseille and Toulon then passed over Le Castellet. While cruising at an altitude of 6,000 feet and at a speed of 110 knots, the airplane entered an uncontrolled descent, dove into the ground with a rate of descent of 6,000 feet per minute and crashed in a near vertical position in a rocky zone located in the Sainte-Victoire Mountain Range, near Saint-Antonin-sur-Bayon. The aircraft was destroyed by impact forces and a post crash fire and both occupants were killed, one instructor and one pilot under supervision.
Probable cause:
Loss of control during an exercise at low speed and certainly in a single engine configuration.
Contributory factors:
- No reference methods to conduct the exercise, for instructors on this type of aircraft,
- Exercise conducted in a height which insufficient margin and lower than the one recommended by the manufacturer,
- Insufficient vigilance on part of the instructor (however with unanimous recognized skills) but whose instruction on Beechcraft King Air 90 could not be established.
Final Report:

Crash of a McDonnell Douglas C-17A Globemaster III at Elmendorf AFB: 4 killed

Date & Time: Jul 28, 2010 at 1822 LT
Operator:
Registration:
00-0173
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Elmendorf AFB - Elmendorf AFB
MSN:
P-73
YOM:
2000
Crew on board:
4
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
4
Circumstances:
The crew was engaged in a training exercise in preparation to the 'Thunder Air Show' taking part at Elmendorf-Richardson AFB on 31JUL2010. Shortly after take off from runway 06, the pilot-in-command initiated a first turn to the left then a steep turn to the right when the aircraft entered an uncontrolled descent and crashed in a huge explosion in a wooded area located some 3 km northwest of the airbase. The aircraft was totally destroyed by impact forces and a post crash fire and all four crew members were killed.
Probable cause:
The board president found clear and convincing evidence that the cause of the mishap was pilot error. The pilot violated regulatory provisions and multiple flight manual procedures, placing the aircraft outside established flight parameters at an attitude and altitude where recovery was not possible. Furthermore, the copilot and safety observer did not realize the developing dangerous situation and failed to make appropriate inputs. In addition to multiple procedural errors, the board president found sufficient evidence that the crew on the flight deck ignored cautions and warnings and failed to respond to various challenge and reply items. The board also found channelized attention, overconfidence, expectancy, misplaced motivation, procedural guidance, and program oversight substantially contributed to the mishap.

Crash of a Beechcraft RC-12K Guardrail in Wiesbaden

Date & Time: Jun 30, 2010 at 1540 LT
Type of aircraft:
Operator:
Registration:
85-0155
Flight Type:
Survivors:
Yes
Schedule:
Wiesbaden - Wiesbaden
MSN:
FE-9
YOM:
1987
Country:
Region:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Circumstances:
The crew departed Wiesbaden-Erbenheim AFB on a local training flight. On approach, technical problem forced the crew to attempt an emergency landing in a cornfield 200 metres short of runway. Both pilots were slightly injured while the aircraft was damaged beyond repair.
Probable cause:

Crash of a Piper PA-31-350 Navajo Chieftain in Puerto Barrios: 2 killed

Date & Time: Jun 23, 2010 at 1050 LT
Registration:
N430LA
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Guatemala City – Rio Dulce
MSN:
31-7405446
YOM:
1974
Country:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
2
Circumstances:
The twin engine departed Guatemala City-La Aurora Airport at 0930LT on a flight to Rio Dulce with two pilots on board. En roue, the crew contacted ATC, modified his flight plan and was cleared to continue direct to Puerto Barrios. Following few touch-and-go manoeuvres at Puerto Barrios Airport, the crew completed a new approach and landing on runway 12. The pilot-in-command increased engine power and took off when he lost control of the airplane that crashed on a road, coming to rest upside down. The aircraft was destroyed and both occupants were killed.
Probable cause:
Loss of control following an unstabilized approach. The failure of the crew to initiate a go-around procedure was considered as a contributing factor.
Final Report:

Crash of a Piper PA-46-310P Malibu in Ontario

Date & Time: Jun 10, 2010 at 1627 LT
Registration:
N121HJ
Flight Type:
Survivors:
Yes
Schedule:
Santa Monica – Lake Havasu
MSN:
46-8508105
YOM:
1985
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
850
Captain / Total hours on type:
1.00
Copilot / Total flying hours:
5735
Copilot / Total hours on type:
192
Aircraft flight hours:
4803
Circumstances:
The pilot was conducting a cross-country flight with a certified flight instructor (CFI). During the climb-to-cruise phase of the flight, as the airplane was ascending through 16,000 feet mean sea level (msl), the pilot noticed a reduction in manifold pressure. He advanced the throttle and observed an increase of one or two inches of manifold pressure. Shortly thereafter, the pilot heard a loud bang originate from the engine followed by an immediate loss of engine power. The pilot and CFI attempted to troubleshoot the engine anomalies and noted that it seemed to respond with the low boost "on", however it began to run rough whenever the throttle was advanced more than half way. They diverted to a nearby airport and conducted an emergency descent. As the airplane approached the airport, the pilot descended through an overcast cloud layer and attempted to enter the airport traffic pattern. While on final approach to the airport, the pilot thought the airplane was high and extended the landing gear and applied flaps. Shortly thereafter, the airspeed and altitude decreased drastically and the pilot realized he was too low. The pilot applied throttle and noticed no change in engine performance. The airplane subsequently struck a fence and landed hard in an open field just short of the airport, which resulted in structural damage to the fuselage and wings. A postaccident examination of the engine revealed that the induction elbow for cylinders 1-3-5 (right side) was displaced from the throttle and metering assembly where the elbow couples with the throttle and metering assembly by an induction hose and clamp. The clamp was secure to the induction hose, however, the portion of the clamp that should have been installed
beyond the retention bead on the throttle and control assembly was observed on the inboard side of the bead on the induction elbow. Review of the aircraft maintenance logbooks revealed that cylinders 4 and 5 were recently replaced prior to the accident flight due to low compression. The replacement of these cylinders required removal of the induction system to allow for cylinder removal and installation. In addition, a manufacturer service bulletin stated that during the reinstallation of the induction system, one must slide the induction hose and clamp(s) onto one of the tubes to be joined and that the connection joint and both tube beads are to be positioned in the center of the induction hose. The clamps should be installed in a position centered between the tubing bead and end of the induction hose.
Probable cause:
A loss of engine power due to the in-flight separation of the 1-3-5 cylinder induction tube elbow, which was caused by the improper installation of the induction tube elbow by maintenance personnel.
Final Report:

Crash of a Beechcraft 60 Duke in Edenton: 1 killed

Date & Time: Jun 7, 2010 at 1932 LT
Type of aircraft:
Registration:
N7022D
Flight Phase:
Flight Type:
Survivors:
Yes
Schedule:
Edenton - Edenton
MSN:
P-13
YOM:
1968
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
1558
Captain / Total hours on type:
343.00
Copilot / Total flying hours:
30000
Aircraft flight hours:
3562
Circumstances:
The pilot was receiving instruction and an instrument proficiency check (IPC) from a flight instructor. Following an hour of uneventful instruction, the IPC was initiated. During the first takeoff of the IPC, the pilot was at the flight controls, and the flight instructor controlled the throttles. Although the pilot normally set about 40 inches of manifold pressure for takeoff, the flight instructor set about 37 inches, which resulted in a longer than expected takeoff roll. Shortly after takeoff, at an altitude of less than 100 feet, with the landing gear extended, the flight instructor retarded the left throttle at 83 to 85 knots indicated airspeed; 85 knots was the minimum single engine control speed for the airplane. The pilot attempted to advance the throttles, but was unable since the flight instructor’s hand was already on the throttles. The airplane veered sharply to the left and rolled. The pilot was able to level the wings just prior to the airplane colliding with trees and terrain. The pilot reported that procedures for simulating or demonstrating an engine failure were never discussed. Although the flight instructor’s experience in the accident airplane make and model was not determined, he reported prior to the flight that he had not flown that type of airplane recently. The flight instructor was taking medication for type II diabetes. According to his wife, the flight instructor had not experienced seizures or a loss of consciousness as a result of his medical condition.
Probable cause:
The flight instructor’s initiation of a simulated single engine scenario at or below the airplane’s minimum single engine control speed, resulting in a loss of airplane control. Contributing to the accident was the flight instructor’s failure to set full engine power during the takeoff roll and the flight instructor’s lack of recent experience in the airplane make and model.
Final Report:

Crash of a Rockwell T-39N Sabreliner near Morganton: 4 killed

Date & Time: Apr 12, 2010 at 1525 LT
Type of aircraft:
Operator:
Registration:
165513
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Pensacola - Pensacola
MSN:
282-66
YOM:
1966
Crew on board:
4
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
4
Circumstances:
The crew departed Pensacola NAS, Florida, for a training flight. En route, the aircraft entered an uncontrolled descent and crashed in unknown circumstances in a wooded area located 8 km northeast of Morganton. All four occupants were killed.

Crash of an Embraer EMB-120ER Brasília in Darwin: 2 killed

Date & Time: Mar 22, 2010 at 1009 LT
Type of aircraft:
Operator:
Registration:
VH-ANB
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Darwin - Darwin
MSN:
120-116
YOM:
1988
Country:
Region:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
8217
Captain / Total hours on type:
3749.00
Copilot / Total flying hours:
5664
Copilot / Total hours on type:
3085
Aircraft flight hours:
32799
Aircraft flight cycles:
33700
Circumstances:
Aircraft crashed moments after takeoff from runway 29 at Darwin Airport, Northern Territory, fatally injuring both pilots. The flight was for the purpose of revalidating the command instrument rating of the pilot under check and was under the command of a training and checking captain, who occupied the copilot’s seat. The takeoff included a simulated engine failure. Data from the aircraft’s flight recorders was used to establish the circumstances leading to the accident and showed that the pilot in command (PIC) retarded the left power lever to flight idle to simulate an engine failure. That introduced a simulated failure of the left engine and propeller autofeathering system. The increased drag from the ‘windmilling’ propeller increased the control forces required to maintain the aircraft’s flightpath. The pilot under check allowed the speed to decrease and the aircraft to bank toward the inoperative engine. Additionally, he increased power on the right engine, and engaged the yaw damper in an attempt to stabilize the aircraft’s flight. Those actions increased his workload and made control of the aircraft more difficult. The PIC did not restore power to the left engine to discontinue the manoeuvre. The few seconds available before the aircraft became uncontrollable were insufficient to allow ‘trouble shooting’ and deliberation before resolving the situation.
Probable cause:
• The pilot in command initiated a simulated left engine failure just after becoming airborne and at a speed that did not allow adequate margin for error.
• The pilot in command simulated a failure of the left engine by selecting flight idle instead of zero thrust, thereby simulating a simultaneous failure of the left engine and its propeller autofeather system, instead of a failure of the engine alone.
• The pilot under check operated the aircraft at a speed and attitude (bank angle) that when uncorrected, resulted in a loss of control.
• The pilot under check increased his workload by increasing torque on the right engine and selecting the yaw damper.
• The pilot in command probably became preoccupied and did not abandon the simulated engine failure after the heading and speed tolerance for the manoeuvre were exceeded and before control of the aircraft was lost.
Final Report:

Crash of a Beechcraft C90GTi King Air in Les Éplatures

Date & Time: Jan 15, 2010 at 1407 LT
Type of aircraft:
Operator:
Registration:
HB-GPL
Flight Phase:
Flight Type:
Survivors:
Yes
Schedule:
Les Éplatures - Dole
MSN:
LJ-1936
YOM:
2009
Country:
Region:
Crew on board:
2
Crew fatalities:
Pax on board:
2
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
920
Captain / Total hours on type:
62.00
Aircraft flight hours:
89
Aircraft flight cycles:
68
Circumstances:
The crew was departing Les Eplatures Airport on a training flight to Dole-Tavaux, Jura. During the takeoff roll on runway 24, the pilot-in-command realized that the aircraft' speed did not increase after 88 knots then dropped to 85 knots. He decided to reject the takeoff procedure and initiated an emergency braking procedure. Unable to stop within the remaining distance, the aircraft overran and collided with concrete blocks and the ILS equipment. All four occupants were injured, two seriously. The aircraft was damaged beyond repair.
Probable cause:
The accident was caused by a collision with obstacles after the runway end due to a late take off run interruption decision, most probably due to an involuntary braking action on behalf of the pilot.
The following contributing factors were identified:
- Poor pilot experience on this aircraft model.
- Inadequate take off configuration (flaps).
- Initial multi engine training performed on a different aircraft model.
- Pilot not familiarized with short runway.
Final Report: