code

AZ

Crash of a Piper PA-46-310P Malibu near Seligman: 2 killed

Date & Time: Sep 13, 2022 at 1148 LT
Registration:
N43605
Flight Phase:
Flight Type:
Survivors:
No
MSN:
46-8408052
YOM:
1984
Crew on board:
1
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
2
Circumstances:
The single engine airplane departed Albuquerque-Double Eagle II Airport on a private flight. It crashed in unknown circumstances north of Seligman shortly before noon. Both occupants were killed.

Crash of a Cessna 207A Turbo Stationair 8 into Lake Powell: 2 killed

Date & Time: Aug 13, 2022 at 1609 LT
Operator:
Registration:
N9582M
Flight Phase:
Survivors:
Yes
Schedule:
Page - Page
MSN:
207-0705
YOM:
1981
Crew on board:
1
Crew fatalities:
Pax on board:
6
Pax fatalities:
Other fatalities:
Total fatalities:
2
Circumstances:
The single engine airplane departed Page on a local sightseeing flight, carrying one pilot and six French tourists. In unknown circumstances, the aircraft crashed into Lake Powell. Two passengers were killed while five other occupants were injured, three seriously.

Crash of a Beechcraft C90 King Air near Wikieup: 2 killed

Date & Time: Jul 10, 2021 at 1254 LT
Type of aircraft:
Operator:
Registration:
N3688P
Flight Phase:
Flight Type:
Survivors:
No
Site:
Schedule:
Marana - Wikieup
MSN:
LJ-915
YOM:
1980
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
10400
Aircraft flight hours:
17126
Circumstances:
On July 10, 2021, about 1254 mountain standard time, a Beech C-90, turbo prop airplane, N3688P, was destroyed when it was involved in an accident near Wikieup, Arizona. The pilot and Air Tactical Group supervisor were fatally injured. The airplane was operated as a public use firefighting aircraft in support of the Bureau of Land Management conducting aerial reconnaissance and supervision. The airplane was on station for about 45 minutes over the area of the Cedar Basin fire. The ADS-B data showed the airplane had accomplished multiple orbits over the area of the fire about 2,500 ft above ground level (agl). The last ADS-B data point showed the airplane’s airspeed as 151 knots, its altitude about 2,300 ft agl, and in a descent, about 805 ft east southeast of the accident site. No distress call from the airplane was overheard on the radio. According to a witness, the airplane was observed in a steep dive towards the ground. The airplane impacted the side of a ridgeline in mountainous desert terrain. The main wreckage was mostly consumed by a post-crash fire. Debris was scattered over an area of several acres. Another witness observed the left wing falling to the ground after the aircraft had impacted the terrain. The left wing had separated outboard of the nacelle and was located about 0.79 miles northeast of the main wreckage and did not sustain thermal damage.
Probable cause:
The failure and separation of the left wing’s outboard section due to a fatigue crack in the lower spar cap. Contributing to the accident was the operator’s decision to repair the wing spar instead of replacing it as recommended by the aircraft manufacturer. Also contributing to the accident was the failure of the Non-Destructive Testing inspector to detect the fatigue crack during inspection.
Final Report:

Crash of a Swearingen SA226T Merlin IIIB in Winslow: 2 killed

Date & Time: Apr 23, 2021 at 1519 LT
Operator:
Registration:
N59EZ
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Scottsdale - Winslow
MSN:
T-394
YOM:
1981
Location:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
2
Aircraft flight hours:
5959
Circumstances:
The pilot was conducting a personal flight and was descending the airplane to the destination airport. Automatic dependent surveillance-broadcast (ADS-B) data showed that the airplane accomplished several turning maneuvers near the airport. These turns occurred from an elevation of 6,000 to 4,950 ft mean sea level, at which time the data ended. The airplane was 80 ft above ground level at the time. Witnesses reported seeing a low-flying airplane perform a turn and then veer toward the ground. The airplane came to rest about 4 miles east of the destination airport and 70 ft from the last data target. A postcrash fire ensued. Postaccident examination of the airframe and engines found no mechanical anomalies that would have precluded normal operation. Examination of the left engine revealed that the engine was likely producing power. The right engine examination revealed damage consistent with low or no rotation at the time of the accident, including distinct, localized contact marks on the rotating propeller shaft. In addition, no metal spray was found in the turbine section, and no dirt was found within the combustor section. The examination of the right propeller blades showed chordwise scoring with the blades bent aft and twisted toward a low-pitch setting. Examination of the fuel system noted no anomalies. The airplane was equipped with a single redline (SRL) autostart computer. Examination of the right (R) SRL-OFF annunciator panel light bulb showed signatures of hot filament stretch, which was consistent with illumination of the light at the time of the accident. The SRL light normally extinguishes above an engine speed of 80% rpm. Given the low rotational signatures on the right engine and the illuminated “R SRL-OFF” warning light, it is likely that the right engine lost engine power during the flight for reasons that could not be determined.
Probable cause:
The loss of engine power to the right engine for reasons that could not be determined. Contributing to the accident was the pilot’s failure to maintain control of the airplane.
Final Report:

Crash of a Hawker 800XP in Scottsdale

Date & Time: Mar 14, 2020 at 1600 LT
Type of aircraft:
Operator:
Registration:
N100AG
Flight Type:
Survivors:
Yes
Schedule:
Rogers – Scottsdale
MSN:
258747
YOM:
2005
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
9150
Captain / Total hours on type:
650.00
Copilot / Total flying hours:
10556
Copilot / Total hours on type:
52
Aircraft flight hours:
4823
Circumstances:
The pilot stated that, upon landing, the airplane touched down on the runway centerline with light and variable wind conditions. The pilot recalled that the touchdown felt normal but that, during the landing roll, the airplane began to veer to the right. The pilot added full left rudder, but the airplane continued to veer off the runway surface and encountered large rocks located between the runway and taxiway. A postaccident operational check of the nosewheel steering system revealed no mechanical malfunctions or anomalies that would have precluded normal operation. The left nosewheel tire was not adequately inflated and was worn to the point at which the cord was exposed; the right nosewheel tire was within tolerances. Also, one-third of the rim was absent on the left nosewheel tire outer wheel half. The available evidence precluded a determination of whether the imbalance between the nosewheel tires contributed to the control problem on the runway. It could also not be determined if the left nosewheel tire damage occurred before the touchdown or as a result of the accident sequence.
Probable cause:
The pilot’s inability to maintain directional control during landing for undetermined reasons, which resulted in a runway excursion.
Final Report:

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

Date & Time: May 29, 2018 at 2115 LT
Registration:
N148ME
Flight Type:
Survivors:
Yes
Site:
Schedule:
Santa Ana – Prescott
MSN:
46-8608009
YOM:
1986
Crew on board:
1
Crew fatalities:
Pax on board:
2
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
3100
Captain / Total hours on type:
3.00
Circumstances:
According to the pilot, about 15 minutes before reaching the destination airport during descent, the engine lost power. The pilot switched fuel tanks, and the engine power was momentarily restored, but the engine stopped producing power even though he thought it "was still running all the way to impact." The pilot conducted a forced landed on a highway at night, and the right wing struck an object and separated from the airplane. The airplane came to rest inverted. According to the Federal Aviation Administration (FAA) aviation safety inspector (ASI) that performed the postaccident airplane examination, the fuel lines to the fuel manifold were dry, and the fuel manifold valves were dry. He reported that the fuel strainer, the diaphragm, and the fuel filter in the duel manifold were unremarkable. Fuel was found in the gascolator. The FAA ASI reported that, during his interview with the pilot, "the pilot changed his story from fuel exhaustion, to fuel contamination." The inspector reported that there were no signs of fuel contamination during the examination of the fuel system. According to the fixed-base operator (FBO) at the departure airport, the pilot requested 20 gallons of fuel. He then canceled his fuel request and walked out of the FBO.
Probable cause:
The pilot's improper fuel planning, which resulted in fuel exhaustion and the subsequent total loss of engine power.
Final Report:

Crash of a Beechcraft 300 Super King Air in Tucson: 2 killed

Date & Time: Jan 23, 2017 at 1233 LT
Operator:
Registration:
N385KA
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Tucson - Hermosillo
MSN:
FA-42
YOM:
1985
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
15100
Aircraft flight hours:
9962
Circumstances:
The pilot and the passenger departed on a cross-country, personal flight in the airplane that the operator had purchased the day before the accident. Shortly after takeoff from runway 11L, after reaching an altitude of about 100 to 150 ft above the runway in a nose-high pitch attitude, the airplane rolled left to an inverted position as its nose dropped, and it descended to terrain impact on airport property, consistent with an aerodynamic stall. Post-accident examination of the accident site revealed propeller strike marks separated at distances consistent with both propellers rotating at the speed required for takeoff and in a normal blade angle range of operation at impact. Both engines exhibited rotational scoring signatures that indicated the engines were producing symmetrical power and were most likely operating in the mid-to upper-power range at impact. The engines did not display any pre-impact anomalies or distress that would have precluded normal engine operation before impact. No evidence was found of any preexisting mechanical anomalies that would have precluded normal operation of the airplane. Toxicology testing revealed the pilot's use of multiple psychoactive substances including marijuana, venlafaxine, amphetamine, pseudoephedrine, clonazepam, and pheniramine. The wide variety of psychoactive effects of these medications precludes predicting the specific effects of their use in combination. However, it is likely that the pilot was impaired by the effects of the combination of psychoactive substances he was using and that those effects contributed to his loss of control. The investigation was unable to obtain medical records regarding any underlying neuropsychiatric disease(s); therefore, whether these may have contributed to the accident circumstances could not be determined.
Probable cause:
The pilot's exceedance of the airplane's critical angle of attack during takeoff, which resulted in an aerodynamic stall. Contributing to the accident was the pilot's impairment by the effects of a combination of psychoactive substances.
Final Report:

Crash of a Rockwell Shrike Commander 500S in Fort Huachuca: 1 killed

Date & Time: May 17, 2014 at 1020 LT
Operator:
Registration:
N40TC
Flight Phase:
Flight Type:
Survivors:
Yes
Schedule:
Fort Huachuca - Fort Huachuca
MSN:
500-3091
YOM:
1976
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
13175
Captain / Total hours on type:
600.00
Copilot / Total flying hours:
16560
Copilot / Total hours on type:
4100
Aircraft flight hours:
21660
Circumstances:
The commercial pilot reported that the purpose of the flight was to perform a check/orientation flight with the airline transport pilot (ATP), who was new to the area; the ATP was the pilot flying. The airplane was started, and an engine run-up completed. The commercial pilot reported that, during the takeoff roll, all of the gauges were in the “green.” After reaching an airspeed of 80 knots, the airplane lifted off the ground. About 350 ft above ground level (agl), the pilots felt the airplane “jolt.” The commercial pilot stated that it felt like a loss of power had occurred and that the airplane was not responding. He immediately shut off the boost pumps, and the ATP initiated a slow left turn in an attempt to return to the airport to land. The airplane descended rapidly in a nose-low, right-wing-low attitude and impacted the ground. A witness reported that he watched the airplane take off and that it sounded normal until it reached the departure end of the runway, at which point he heard a distinct “pop pop,” followed by silence. The airplane then entered an approximate 45-degree left turn with no engine sound and descended at a high rate with the wings rolling level before the airplane went out of sight. Another witness made a similar statement. Based on the witnesses’ statements and photographs of the twisted airplane at the accident site, it is likely that a total loss of engine power occurred and that, during the subsequent turn back to the airport, the ATP did not maintain sufficient airspeed and exceeded the airplane’s critical angle-of-attack, which resulted in an aerodynamic stall and impact with terrain. Although a postaccident examination of the airframe and engines did reveal an inconsistency between the cockpit control positions and the positions of the fuel shutoff valves on the sump tank, this would not have precluded normal operation. No other anomalies were found that would have precluded normal operation.
Probable cause:
The pilot’s failure to maintain adequate airspeed and his exceedance of the airplane’s critical angle-of-attack after a total loss of engine power during the takeoff initial climb, which resulted in an aerodynamic stall and impact with terrain. The reason for the total loss of engine power could not be determined because an examination of the airframe and engines did not reveal any anomalies that would have precluded normal operation.
Final Report:

Crash of a Cessna T207A Turbo Stationair 7 in Page: 1 killed

Date & Time: May 10, 2014 at 1545 LT
Operator:
Registration:
N7311U
Survivors:
Yes
Schedule:
Page - Page
MSN:
207A-0395
YOM:
1977
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
6
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
6850
Captain / Total hours on type:
48.00
Aircraft flight hours:
14883
Circumstances:
During a local sightseeing flight, the pilot noticed that the engine had lost partial power, and he initiated a turn back toward the airport while troubleshooting the loss of power. Despite the pilot's attempts, the engine would not regain full power and was surging and sputtering randomly. The pilot entered the airport's traffic pattern on the downwind leg, and, while on final approach to the runway, the airplane encountered multiple downdrafts and wind gusts. It is likely that, due to the downdrafts and the partial loss of engine power, the pilot was not able to maintain airplane control. The airplane subsequently landed hard short of the runway surface and nosed over, coming to rest inverted. The reported wind conditions around the time of the accident varied between 20 and 70 degrees right of the runway heading and were 14 knots gusting to greater than 20 knots. In addition, a company pilot who landed about 8 minutes before the accident reported that he encountered strong downdrafts and windshear while on final approach to the runway and that he would not have been able to reach the runway if he had a partial or total loss of engine power. Postaccident examination of the airframe and engine revealed no evidence of any preexisting mechanical malfunctions or failures that would have precluded normal operation. The engine was subsequently installed on a test stand and was successfully run through various power settings for several minutes. The reason for the partial loss of engine power could not be determined.
Probable cause:
The pilot's inability to maintain aircraft control due to a partial loss of engine power and an encounter with downdrafts and gusting crosswinds while on final approach to the runway. The reason for the partial loss of engine power could not be determined because postaccident examination revealed no mechanical malfunction or failure that would have precluded normal operation.
Final Report:

Crash of a Cessna 340A in Paulden: 4 killed

Date & Time: Oct 4, 2013 at 1300 LT
Type of aircraft:
Registration:
N312GC
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Bullhead City – Prescott
MSN:
340A-0023
YOM:
1975
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
3
Pax fatalities:
Other fatalities:
Total fatalities:
4
Captain / Total flying hours:
4006
Circumstances:
Witnesses located at a gun club reported observing the airplane make a high-speed, low pass from north to south over the club's buildings and then maneuver around for another low pass from east to west. During the second low pass, the airplane collided with a radio tower that was about 50 ft tall, and the right wing sheared off about 10 ft of the tower's top. The tower's base was triangular shaped, and each of its sides was about 2 ft long. One witness reported that the airplane remained in a straight-and-level attitude until impact with the tower. The airplane then rolled right to an almost inverted position and subsequently impacted trees and terrain about 700 ft southwest of the initial impact point. One witness reported that, about 3 to 4 years before the accident, the pilot, who was a client of the gun club, had "buzzed" over the club and had been told to never do so again. A postaccident examination of the engines and the airframe revealed no evidence of a mechanical malfunction or failure that would have precluded normal operation.
Probable cause:
The pilot's failure to maintain sufficient altitude to clear a radio tower while maneuvering at low altitude and his decision to make a high-speed, low pass over the gun club.
Final Report: