Crash of a Rockwell Grand Commander 680FL in Harrison

Date & Time: Oct 8, 2003 at 1825 LT
Registration:
N680WS
Flight Type:
Survivors:
Yes
Schedule:
Springdale – Harrison
MSN:
680-1413-63
YOM:
1964
Crew on board:
1
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
725
Captain / Total hours on type:
86.00
Aircraft flight hours:
9362
Circumstances:
The twin-engine airplane was on the base leg to final turn, about 1-1 1/2 miles from the approach end of the runway when the left engine lost power. Instantly after, the right engine lost power and the pilot feathered both engines. The airplane then impacted a 70-foot high tree and collided with the ground about 1,000 feet short of the runway. The 700-hour pilot reported that he activated the electric fuel boost pumps and switched the fuel selectors from the auxiliary fuel tank positions to the main fuel tank positions, about 17 miles from the airport. He recalled that the fuel gauges indicated approximately 70 gallons of fuel in the main tank and about 10-15 gallons of fuel in the auxiliary tanks. The original installed fuel system was configured with a center tank and two outboard tanks. The center tank was composed of five, interconnected rubber cells, having a total capacity of 150 to 159 US gallons. Each outboard fuel tank was composed of two fuel cells with a combined capacity of 33.5 gallons. The total of the two outboard fuel tanks (four cells) was 67 gallons, providing a total usable capacity of 233 gallons. Each engine had its own fuel shutoff switch. Rotating a switch to the RIGHT OUTBOARD or LEFT OUTBOARD position allows fuel from the outboard tanks to flow to the respective engine and shuts off fuel from the center tank. Rotating a fuel shutoff switch to the CENTER position allows fuel to flow from the center tank to the respective engine, and shuts off flow from the respective outboard tank. Rotating the switch to the OFF position shuts off all fuel flow to the respective engine. There was no cross-feed configuration of the switches. Documentation was found in the historical records that indicated extended range fuel system modifications, however, the information was incomplete. After review of all available records and examination of the wreckage, it was determined that the fuel system configuration/capacity of the airplane at the time of the accident was: 156 gallons for the center tank system; 67 gallons for the outboard wing tanks; and a set of auxiliary tanks capable of holding 21 gallons (records of installation unknown). The total usable fuel capacity was estimated at 244 gallons. Cockpit fuel selector positions were: LEFT Fuel Shut Off Valve Selector-LEFT HAND OUTBOARD; LEFT Fuel Boost Pump-OFF; LEFT Engine Primer-OFF; LEFT Ignition Switch-RIGHT; RIGHT Fuel Shut Off Valve Selector-RIGHT HAND OUTBOARD; RIGHT Fuel Boost Pump-ON; RIGHT Engine Primer-OFF; RIGHT Ignition Switch-BOTH. Airframe fuel shutoff valves were found in the following positions (Each valve position corresponded to the cockpit selectors): Right Wing Auxiliary-OPEN; Right Wing Main-CLOSED; Left Wing Auxiliary-OPEN; Left Wing Main-CLOSED. A total of 37.5 gallons of usable fuel was drained from the uncompromised tanks (unknown amount had leaked at the accident site). Excerpts from the " Normal Procedures" section of the flight manual regarding fuel selector positions for take off and landing: "CAUTION; Burn center tank fuel first, when 100 gallons is shown on center tank gauge, switch to outboard tanks. Do not allow engine to be starved of fuel when outboard tanks run dry. Select center tanks at first indication of fuel pressure loss. Fuel boost pumps must be on when switching tanks." The "BEFORE LANDING CHECK" procedures in the aircraft flight manual state that the Fuel Selector Valves must be in the "CENTER TANK" position before the approach. The manufacturer stated that the simultaneous loss of power of both engines was likely a result of the outboard fuel tanks unporting. No mechanical anomalies were found during examination of the engines or airframe, and usable fuel was available in the center tank at the time of the accident.
Probable cause:
The loss of power to both engines due to fuel starvation as a result of the pilot's failure to complete the landing checklist while on final approach. A factor contributing to the accident was the lack of suitable terrain for the forced landing.
Final Report:

Crash of a Beechcraft 1900C in Eagleton: 3 killed

Date & Time: Dec 9, 2002 at 1140 LT
Type of aircraft:
Operator:
Registration:
N127YV
Flight Phase:
Flight Type:
Survivors:
No
Site:
Schedule:
Wichita - Mena
MSN:
UC-127
YOM:
1990
Crew on board:
2
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
3
Captain / Total flying hours:
10200
Aircraft flight hours:
12473
Circumstances:
The aircraft collided with mountainous terrain in a level descent during a visual approach to the destination airport. According to recorded radar data, 10 minutes after descending from 15,000 feet, the flight impacted about 200 feet below the top of the partially obscured ridgeline (elevation of 2550 feet), and 8 miles from the destination. The data indicates the flight path was similar to the global positioning satellite (GPS) approach to the airport. Six minutes before the accident, and the pilot's last transmission to air traffic control, he was informed and acknowledged that radar service was terminated. The flight was 12.4 miles from the accident site when radar contact was lost. Reduced visibility due to fog hampered search & rescue efforts, and the aircraft wreckage was located the next day. The aircraft was equipped with a GPS navigation system; however the installation was incomplete, restricting its use to visual flight rules (VFR) only. The investigation did not determine if the GPS was being used at the time. A non-enhanced Ground Proximity Warning System was also installed. The maximum elevation figure listed on the sectional aeronautical chart covering the area of the accident site and destination airport was 3000 feet mean sea level. The chart also shows an advisory for the area to use caution due to rapidly rising.
Probable cause:
In-flight collision with terrain due to the pilot's failure to maintain clearance and altitude above rapidly rising terrain while on a VFR approach. Contributing factors were the obscuration of the terrain due to clouds.
Final Report:

Crash of a McDonnell Douglas MD-82 in Little Rock: 11 killed

Date & Time: Jun 1, 1999 at 2350 LT
Type of aircraft:
Operator:
Registration:
N215AA
Survivors:
Yes
Schedule:
Dallas – Little Rock
MSN:
49163
YOM:
1983
Flight number:
AA1420
Crew on board:
6
Crew fatalities:
Pax on board:
139
Pax fatalities:
Other fatalities:
Total fatalities:
11
Captain / Total flying hours:
10234
Captain / Total hours on type:
5518.00
Copilot / Total flying hours:
4292
Copilot / Total hours on type:
182
Aircraft flight hours:
49136
Aircraft flight cycles:
27103
Circumstances:
On June 1, 1999, at 2350:44 central daylight time, American Airlines flight 1420, a McDonnell Douglas DC-9-82 (MD-82), N215AA, crashed after it overran the end of runway 4R during landing at Little Rock National Airport in Little Rock, Arkansas. Flight 1420 departed from Dallas/Fort Worth International Airport, Texas, about 2240 with 2 flight crewmembers, 4 flight attendants, and 139 passengers aboard and touched down in Little Rock at 2350:20. After departing the end of the runway, the airplane struck several tubes extending outward from the left edge of the instrument landing system localizer array, located 411 feet beyond the end of the runway; passed through a chain link security fence and over a rock embankment to a flood plain, located approximately 15 feet below the runway elevation; and collided with the structure supporting the runway 22L approach lighting system. The captain and 10 passengers were killed; the first officer, the flight attendants, and 105 passengers received serious or minor injuries; and 24 passengers were not injured. The airplane was destroyed by impact forces and a post crash fire. Flight 1420 was operating under the provisions of 14 Code of Federal Regulations Part 121 on an instrument flight rules flight plan.
Probable cause:
The flight crew's failure to discontinue the approach when severe thunderstorms and their associated hazards to flight operations had moved into the airport area and the flight crew's failure to ensure that the spoilers had extended after touchdown. Contributing to the accident were the flight crew's:
(1) impaired performance resulting from fatigue and the situational stress associated with the intent to land under the circumstances,
(2) continuation of the approach to a landing when the company's maximum crosswind component was exceeded, and
(3) use of reverse thrust greater than 1.3 engine pressure ratio after landing.
Final Report:

Crash of a Beechcraft C18S Expeditor in Waldron: 1 killed

Date & Time: May 23, 1999 at 1915 LT
Type of aircraft:
Registration:
N9729H
Survivors:
No
Schedule:
Beaumont – Springdale
MSN:
8205
YOM:
1945
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
6860
Captain / Total hours on type:
860.00
Aircraft flight hours:
4400
Circumstances:
During a cross-country flight, the pilot of the twin-engine airplane reported to air traffic control that he has 'lost an engine.' A witness observed the right engine hanging from its lower mounts as the airplane turned right and headed towards the nearest airport. The airplane impacted trees approximately 1 mile short of the runway threshold. Examination of the right engine propeller revealed that one of its blades was separated about mid-span. The separated tip section of the blade was not recovered. Metallurgical examination of the fracture surface revealed that the blade failed as a result of a fatigue crack that originated from corrosion pits on the camber surface (face) of the blade. The failed blade was examined approximately 6 hours prior to the accident in accordance with an airworthiness directive (AD 81-13-06 R2) that called for inspections of the blade for corrosion and fatigue. However, the inspections called out in the AD were only applicable to the blade fillet and shank regions, well inboard of the fracture location on the failed blade. Overhaul of the propeller in accordance with the propeller manufacturer's manual includes grinding of each blade to 'remove all visual evidence of corrosion.' According to the airplane's owner, the propellers had not been overhauled in the eight years that he had owned the aircraft. The maintenance records were destroyed in the accident, which precluded determination of the date and time of the last propeller overhaul. The accident airplane was being operated under Title 14 CFR Part 91, and therefore, the propellers were not required to be overhauled at specified intervals.
Probable cause:
The separation of a propeller blade in cruise flight as a result of fatigue cracking emanating from surface corrosion pitting.
Final Report:

Crash of a Piper PA-46-350P Malibu Mirage in Waldron: 1 killed

Date & Time: Apr 4, 1999 at 1831 LT
Registration:
N497CA
Flight Phase:
Survivors:
No
Schedule:
Nashville – Addison
MSN:
46-36197
YOM:
1999
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
732
Captain / Total hours on type:
23.00
Aircraft flight hours:
30
Circumstances:
While in cruise flight at 24,000 feet msl, the pilot of the Piper Malibu Mirage advised Memphis Center that he had encountered icing conditions and was experiencing a fuel imbalance. The pilot requested and was cleared to deviate to the north. Subsequently, radio and radar contact were lost. A witness reported hearing the sound of the airplane's engine stop running and observed the airplane descending from the dark clouds in a nose down attitude and rotating clockwise. Residents of the area reported that the weather at the time of the accident was high ceilings with heavy rain just before and after the accident. There were thunderstorms with lightning in the area at the time of the accident. The wreckage of the airplane was scattered along an area of about four miles. The airplane was equipped with an autopilot, weather radar, and an ice protection system. The pilot had recently purchased the 1999 model airplane and had completed a Mirage initial training course. At the time of the accident the pilot had accumulated a total of 21.4 hours in the make and model of the accident aircraft. No anomalies were found with the airframe or engine that would have prevented normal operation.
Probable cause:
The pilot's encounter with adverse weather and loss of aircraft control, which resulted in exceeding the aircraft's design stress limits. Factors were the pilot's lack of total experience in the make and model of airplane, and the icing and thunderstorm weather conditions.
Final Report:

Crash of a Cessna 501 Citation I in Umpire: 1 killed

Date & Time: Dec 2, 1998 at 1216 LT
Type of aircraft:
Operator:
Registration:
N501EZ
Flight Phase:
Flight Type:
Survivors:
No
Site:
Schedule:
Mena - Texarkana
MSN:
501-0058
YOM:
1978
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
3700
Aircraft flight hours:
5874
Aircraft flight cycles:
5436
Circumstances:
The certificated commercial pilot picked up his newly painted airplane for a visual flight to the home base. About 17 miles south of the departure airport, witnesses initially observed the airplane in a 90 degree right bank. It continued to roll to an inverted position while simultaneously nosing down to a near vertical descent. The pilot's second class medical certificate application (July 7, 1997) indicated 3,700 hours flight time. A flight log indicted the pilot flew this aircraft 6.4 hours during the 60 days preceding the accident. No evidence was found that the pilot had not obtained sufficient rest before the flight. There was no evidence found to either suggest a medical cause for incapacitation or to rule out incapacitation for medical reasons. Aircraft maintenance records did not reveal any open discrepancies. All of the airplane was accounted for in the wreckage debris. No evidence of an in-flight fire and/or explosion, or in-flight mechanical and/or flight control malfunction was found.
Probable cause:
The pilot's in flight loss of control for undetermined reasons.
Final Report:

Crash of a Rockwell Grand Commander 680FL in Helena: 1 killed

Date & Time: Jun 16, 1998 at 1800 LT
Operator:
Registration:
N446JR
Flight Type:
Survivors:
No
Schedule:
Kalispell - Helena
MSN:
680-1325-10
YOM:
1963
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
1506
Captain / Total hours on type:
344.00
Aircraft flight hours:
17972
Circumstances:
The pilot of the Part 135 cargo flight was executing the 'full' ILS runway 27 approach at Helena Regional Airport in a non-radar environment. Although the approach calls for the pilot to maintain 7,000 feet until intercepting the glideslope, the aircraft impacted the terrain at 5,300 about 1.5 miles prior to reaching the point where the pilot should have crossed the Hauser NDB at an altitude of 6,741 feet. According to the approach plate, the aircraft should not have descended to an altitude below 5,400 feet until reaching the outer marker, which is located about five and one-half miles west of the impact site.
Probable cause:
The pilot's failure to maintain the correct altitude while turning inbound during a procedure turn to the ILS final approach course. Factors include hilly/mountainous terrain and clouds in the area where the course reversal was performed.
Final Report:

Crash of a Piper PA-31T Cheyenne II in Malvern: 5 killed

Date & Time: May 29, 1996 at 1835 LT
Type of aircraft:
Operator:
Registration:
N333LM
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Malvern - Malvern
MSN:
31-792005
YOM:
1979
Crew on board:
1
Crew fatalities:
Pax on board:
4
Pax fatalities:
Other fatalities:
Total fatalities:
5
Captain / Total flying hours:
7500
Captain / Total hours on type:
700.00
Aircraft flight hours:
4483
Circumstances:
After the completion of scheduled maintenance and a normal ground run up, the airplane departed the airport for a local test flight. Witnesses observed the airplane in a nose high attitude, turn to the left, and then saw the nose drop toward the ground approximately 1 1/2 miles from the departure end of the runway. The airplane impacted hilly terrain and was consumed by a post impact fire. Detailed examination of the airframe, engines, and propellers revealed no defects or anomalies that would have contributed to the accident.
Probable cause:
The pilot's failure to maintain control of the airplane after takeoff.
Final Report:

Crash of a Beechcraft C90 King Air in Royal: 2 killed

Date & Time: Jan 3, 1995 at 1817 LT
Type of aircraft:
Registration:
N101GA
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Hot Springs - Pueblo
MSN:
LJ-11
YOM:
1965
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
4000
Captain / Total hours on type:
185.00
Aircraft flight hours:
7507
Circumstances:
The pilot obtained a weather briefing, filed an IFR flight plan, and took off at night on a flight from Hot Springs, Arkansas, to Pueblo, Colorado. About one minute later, he advised air traffic control that he needed to return to Hot Springs. He then contacted the airplane operator and said the heater was not working. The operator suggested that he return for repairs. The pilot was then heard to say, 'oh, shoot!' No further radio transmissions were received from the flight. The airplane cut a 400 foot swath through trees, and the wreckage path measured 940 feet. With exception of a heater problem, no pre impact mechanical failure was evident. Both occupants were killed.
Probable cause:
The pilot inadvertently allowed the airplane to descend and collide with trees, after he became diverted by an inoperative cabin heater. Darkness was a related factor.
Final Report:

Crash of a Cessna T303 Crusader in Rogers: 2 killed

Date & Time: Nov 25, 1993 at 1804 LT
Type of aircraft:
Registration:
N2297C
Flight Type:
Survivors:
No
Schedule:
Arlington - Rogers
MSN:
303-00093
YOM:
1982
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
1786
Captain / Total hours on type:
907.00
Aircraft flight hours:
1450
Circumstances:
The instrument rated private pilot departed on a night ifr cross country flight into forecasted icing conditions. During the approach at his destination airport, the pilot requested lower altitude to attempt to breakout from the weather. After being assigned 3,100 feet and obtaining a clearance for the ILS approach, the pilot cancelled ifr during descent and proceeded visually for the airport. The aircraft operated in an area of reported freezing rain and ice pellets, with fog and drizzle. Control was lost during the turn from base to final approach. Both occupants were killed.
Probable cause:
The pilot's continued flight into known adverse weather conditions, and the ensuing inadvertent stall. Factors were the icing conditions, the fog, the drizzle, the dark night light conditions, and the pilot's disregard for the forecasted weather conditions.
Final Report: