Crash of a Beechcraft C90A King Air in Caratinga: 5 killed

Date & Time: Nov 5, 2021 at 1515 LT
Type of aircraft:
Operator:
Registration:
PT-ONJ
Survivors:
No
Schedule:
Goiânia – Caratinga
MSN:
LJ-1078
YOM:
1984
Country:
Crew on board:
2
Crew fatalities:
Pax on board:
3
Pax fatalities:
Other fatalities:
Total fatalities:
5
Captain / Total flying hours:
16352
Copilot / Total flying hours:
2768
Circumstances:
The twin engine airplane departed Goiânia-Santa Genoveva Airport on a taxi flight to Caratinga, carrying three passengers and two pilots. On final approach to Caratinga-Ubaporanga Airport in VFR conditions, the airplane collided with a lightning rod located on the top of a high-voltage pylon. Upon impact, the left engine was torn off and the airplane stalled before crashing in a river bed located about 4,1 km short of runway 02. The airplane was destroyed by impact forces and all five occupants were killed, among them the Brazilian singer Marília Mendonça aged 26.
Probable cause:
The following factors were identified:
- Attention – undetermined.
It was found the possibility that the PT-ONJ aircraft crew had their attention (focused vision) on the runway at the expense of maintaining proper separation with the terrain on a visual approach.
- Piloting judgment – a contributor.
Regarding the approach to landing profile, there was an inadequate assessment of the aircraft's operating parameters, since the downwind leg was elongated by a significantly greater distance than that expected for a "Category B" aircraft in landing procedures under VFR.
- Memory – undetermined.
It is likely that, based on the experience of ten years of operation in a company governed by the RBAC 121, the PIC procedural memory has influenced the decisions made concerning the conduct of the aircraft. The habit of performing long final approaches in another type of operation may have activated his procedural memory, involving cognitive activities and motor skills, making the actions automated in relation to the profile performed in the accident.
- Flight planning – undetermined.
A possible non-use of the available aeronautical charts (CAP 9453 and WAC 3189), which were intended to meet the needs of visual flight, may have contributed to low situational awareness about the characteristics of the relief around the SNCT Aerodrome and the presence of the power grid that interfered with the aircraft's landing approach.
Final Report:

Crash of a Gulfstream GIV in Fort Lauderdale

Date & Time: Aug 21, 2021 at 1340 LT
Type of aircraft:
Operator:
Registration:
N277GM
Flight Phase:
Survivors:
Yes
Schedule:
Fort Lauderdale – Las Vegas
MSN:
1124
YOM:
1989
Crew on board:
4
Crew fatalities:
Pax on board:
10
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
20053
Captain / Total hours on type:
3120.00
Copilot / Total flying hours:
1617
Copilot / Total hours on type:
204
Aircraft flight hours:
12990
Circumstances:
The flight crew, which consisted of the pilot- and second-in-command (PIC and SIC), and a non-type-rated observer pilot, reported that during takeoff near 100 knots a violent shimmy developed at the nose landing gear (NLG). The PIC aborted the takeoff and during the abort procedure, the NLG separated. The airplane veered off the runway, and the right wing and right main landing gear struck approach lights, which resulted in substantial damage to the fuselage and right wing. The passengers and flight crew evacuated the airplane without incident through the main cabin door. Postaccident interviews revealed that following towing operations prior to the flight crew’s arrival, ground personnel were unable to get the plunger button and locking balls of the NLG’s removable pip pin to release normally. Following a brief troubleshooting effort by the ground crew, the pip pin’s plunger button remained stuck fully inward, and the locking balls remained retracted. The ground crew re-installed the pip pin through the steering collar with the upper torque link arm connected. However, with the locking balls in the retracted position, the pin was not secured in position as it should have been. Further, the ground personnel could not install the safety pin through the pip pin because the pin’s design prevented the safety pin from being inserted if the locking balls and plunger were not released. The ground personnel left the safety pin hanging from its lanyard on the right side of the NLG. The ground personnel subsequently informed their ramp supervisor of the anomaly. The supervisor reported that he informed the first arriving crewmember at the airplane (the observer pilot) that the nose pin needed to be checked. However, all three pilots reported that no ground crewmember told them about any issues with the NLG or pins. Examination of the runway environment revealed that the first item of debris located on the runway was the pip pin. Shortly after this location, tire swivel marks were located near the runway centerline, which were followed by large scrape and tire marks, leading to the separated NLG. The safety pin remained attached to the NLG via its lanyard and was undamaged. Postaccident examination and testing of the NLG and its pins revealed no evidence of preimpact mechanical malfunctions or failures. The sticking of the pip pin plunger button that the ground crew reported experiencing could not be duplicated during postaccident testing. When installed on the NLG, the locking ball mechanism worked as intended, and the pip pin could not be removed by hand. Although the airplane’s preflight checklist called for a visual check of the NLG’s torque link to ensure that it was connected to the steering collar by the pip pin and that the safety pin was installed, it is likely that none of the pilots noticed that the pip pin did not have its safety pin installed during preflight. Subsequently, during the takeoff roll, without the locking balls extended, the pip pin likely moved outward and fell from its position holding the upper torque link arm. This allowed the upper torque link arm to move freely, which resulted in the violent shimmy and NLG separation. The location of the debris on the runway, tire marks, and postaccident examination and testing support this likely chain of events. Contributing to the PIC and SIC’s omission during preflight was the ground crew’s failure to directly inform the PIC or SIC that there was a problem with the NLG pip pin. The ground crew also failed to discard the malfunctioning pip pin per the airplane’s ground handling procedures and instead re-installed the pip pin. Although the observer pilot was reportedly informed of an issue with a nose gear pin, he was not qualified to act as a required flight crewmember for the airplane and was on his cell phone when he was reportedly informed of the issue by the ramp supervisor. These factors likely contributed to the miscommunication and the PIC’s and SIC’s subsequent lack of awareness of the NLG issue.
Probable cause:
The pilot-in-command’s (PIC) and second-in-command’s (SIC) failure during preflight inspection to ensure that the nose landing gear’s pip pin was properly installed, which resulted in separation of the pip pin during takeoff. Contributing to the accident was the ground crew supervisor’s failure to inform the PIC or SIC of the anomaly concerning the pip pin following a towing operation.
Final Report:

Crash of a De Havilland DHC-2 Beaver near Ketchikan: 6 killed

Date & Time: Aug 5, 2021 at 1050 LT
Type of aircraft:
Operator:
Registration:
N1249K
Flight Phase:
Survivors:
No
Site:
Schedule:
Ketchikan - Ketchikan
MSN:
1594
YOM:
1965
Crew on board:
1
Crew fatalities:
Pax on board:
5
Pax fatalities:
Other fatalities:
Total fatalities:
6
Captain / Total flying hours:
15552
Captain / Total hours on type:
8000.00
Aircraft flight hours:
15028
Circumstances:
The accident flight was the pilot’s second passenger sightseeing flight of the day that overflew remote inland fjords, coastal waterways, and mountainous, tree-covered terrain in the Misty Fjords National Monument. Limited information was available about the airplane’s flight track due to radar limitations, and the flight tracking information from the airplane only provided data in 1-minute intervals. The data indicated that the airplane was on the return leg of the flight and in the final minutes of flight, the pilot was flying on the right side of a valley. The airplane impacted mountainous terrain at 1,750 ft mean sea level (msl), about 250 ft below the summit. Examination of the wreckage revealed no evidence of pre accident failures or malfunctions that would have precluded normal operation. Damage to the propeller indicated that it was rotating and under power at the time of the accident. The orientation and distribution of the wreckage indicated that the airplane impacted a tree in a left-wing-low attitude, likely as the pilot was attempting to maneuver away from terrain. Review of weather information for the day of the accident revealed a conditionally unstable environment below 6,000 ft msl, which led to rain organizing in bands of shower activity. Satellite imagery depicted that one of these bands was moving northeastward across the accident site at the accident time. Federal Aviation Administration (FAA) weather cameras and local weather observations also indicated that lower visibility and mountain obscuration conditions were progressing northward across the accident area with time. Based on photographs recovered from passenger cell phones along with FAA weather camera imagery, the accident flight encountered mountain obscuration conditions, rain shower activity, and reduced visibilities and cloud ceilings, resulting in instrument meteorological conditions (IMC) before the impact with terrain. The pilot reviewed weather conditions before the first flight of the day; however, there was no indication that he obtained updated weather conditions or additional weather information before departing on the accident flight. Based on interviews, the accident pilot landed following the first flight of the day in lowering visibility, ceiling, and precipitation, and departed on the accident flight in precipitation, based on passenger photos. Therefore, the pilot had knowledge of the weather conditions that he could have encountered along the route of flight before departure. The operator had adequate policies and procedures in place for pilots regarding inadvertent encounters with IMC; however, the pilot’s training records indicated that he was signed off for cue-based training that did not occur. Cue-based training is intended to help calibrate pilots’ weather assessment and foster an ability to accurately assess and respond appropriately to cues associated with deteriorating weather. Had the pilot completed the training, it might have helped improve his decision-making skills to either cancel the flight before departure or turn around earlier in the flight. The operator’s lack of safety management protocols resulted in the pilot not receiving the required cue-based training, allowed him to continue operating air tours with minimal remedial training following a previous accident, and allowed the accident airplane to operate without a valid FAA registration. The operator was signatory to a voluntary local air tour operator’s group letter of agreement that was developed to improve the overall safety of flight operations in the area of the Misty Fjords National Monument. Participation was voluntary and not regulated by the FAA, and the investigation noted multiple instances in which the LOA policies were ignored, including on the accident flight. For example, the accident flight did not follow the standard Misty Fjords route outlined in the LOA nor did it comply with the recommended altitudes for flights into and out of the Misty Fjords. FAA inspectors providing oversight for the area reported that, when they addressed operators about disregarding the LOA, the operators would respond that the LOA was voluntary and that they did not need to follow the guidance. The FAA’s reliance on voluntary compliance initiatives in the local air tour industry failed to produce compliance with safety initiatives or to reduce accidents in the Ketchikan region.
Probable cause:
The pilot’s decision to continue visual flight rules (VFR) flight into instrument meteorological conditions (IMC), which resulted in controlled flight into terrain. Contributing to the accident was the FAA’s reliance on voluntary compliance with the Ketchikan Operator’s Letter of Agreement.
Final Report:

Crash of a De Havilland DHC-8-106 in Bur Ache

Date & Time: Jul 21, 2021
Operator:
Registration:
5Y-GRS
Survivors:
Yes
Schedule:
Nairobi – El Wak
MSN:
355
YOM:
1993
Country:
Region:
Crew on board:
4
Crew fatalities:
Pax on board:
37
Pax fatalities:
Other fatalities:
Total fatalities:
0
Circumstances:
The airplane departed Nairobi-Wilson Airport on a charter flight to El Wak, carrying 37 passengers and 4 crew members. While descending to El Wak Airport, the pilot continued to the east and elected to land on an airfield located 18 km east of El Wak, near Bur Ache, in Somalia. After landing, the airplane veered to the left and impacted a pile of earth and rocks, causing the left main gear to collapse. All 41 occupants evaacuated safely and the aircraft was damaged beyond repair.

Crash of a Beechcraft C90A King Air in Durango: 3 killed

Date & Time: Jul 18, 2021 at 0935 LT
Type of aircraft:
Operator:
Registration:
N333WW
Survivors:
Yes
Schedule:
San Luis Potosí – Durango
MSN:
LJ-1741
YOM:
2005
Location:
Country:
Crew on board:
2
Crew fatalities:
Pax on board:
5
Pax fatalities:
Other fatalities:
Total fatalities:
3
Circumstances:
Upon landing at Durango-Guadalupe Victoria Airport following an uneventful flight from San Luis Potosí, the twin engine aircraft went out of control and crashed in a grassy area, coming to rest upside down and bursting into flames. A pilot and two passengers were killed while four other occupants were injured.

Crash of a Piper PA-31-350 Navajo Chieftain in Sergio Butrón Casas

Date & Time: Mar 3, 2021 at 1447 LT
Operator:
Registration:
N640WA
Flight Phase:
Survivors:
Yes
Schedule:
Morelia - Chetumal
MSN:
31-8252065
YOM:
1982
Country:
Crew on board:
1
Crew fatalities:
Pax on board:
1
Pax fatalities:
Other fatalities:
Total fatalities:
0
Circumstances:
The pilot was approaching Chetumal Airport when he reported engine problems. He elected to make an amergency landing when the aircraft crash landed in an open field located in Sergio Butrón Casas, about 25 km west of Chetumal Airport. Both occupants were slightly injured and the aircraft was damaged beyond repair.

Crash of a Cessna 208B Grand Caravan in Mundri

Date & Time: Oct 10, 2020
Type of aircraft:
Operator:
Registration:
5H-NWA
Flight Phase:
Survivors:
Yes
Schedule:
Mundri - Juba
MSN:
208B-0891
YOM:
2001
Country:
Region:
Crew on board:
0
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Circumstances:
The single engine airplane suffered an accident while taking off from Mundri Airfield, causing the right main gear and the nose gear to be torn off. Also, both wings were severely damaged. There were no fire and no injuries. The aircraft was damaged beyond repair. It seems it was owned by Newton Air and leased to Zantas Air Services.

Crash of a Boeing 737-8HG in Kozhikode: 21 killed

Date & Time: Aug 7, 2020 at 1941 LT
Type of aircraft:
Operator:
Registration:
VT-AXH
Survivors:
Yes
Schedule:
Dubai - Kozhikode
MSN:
36323/2109
YOM:
2006
Flight number:
IX1344
Country:
Region:
Crew on board:
6
Crew fatalities:
Pax on board:
184
Pax fatalities:
Other fatalities:
Total fatalities:
21
Captain / Total flying hours:
10848
Captain / Total hours on type:
4612.00
Copilot / Total flying hours:
1989
Copilot / Total hours on type:
1723
Aircraft flight hours:
43691
Aircraft flight cycles:
15309
Circumstances:
Air-India Express Limited B737-800 aircraft VT-AXH was operating a quick return flight on sector Kozhikode-Dubai-Kozhikode under ‘Vande Bharat Mission’ to repatriate passengers who were stranded overseas due to closure of airspace and flight operations owing to the Covid-19 pandemic. The aircraft departed from Kozhikode for Dubai at 10:19 IST (04:49 UTC) on 07 August 2020 and landed at Dubai at 08:11 UTC. The flight was uneventful. There was no change of crew and no defect was reported on the first sector. The aircraft departed from Dubai for Kozhikode at 10:00 UTC as flight AXB 1344 carrying 184 passengers and six crew members. AXB 1344 made two approaches for landing at Kozhikode. The aircraft carried out a missed approach on the first attempt while coming into land on runway 28. The second approach was on runway 10 and the aircraft landed at 14:10:25 UTC. The aircraft touched down approximately at 4,438 ft on 8,858 ft long runway, in light rain with tailwind component of 15 knots and a ground speed of 165 knots. The aircraft could not be stopped on the runway and this ended in runway overrun. The aircraft exited the runway 10 end at a ground speed of 84 knots and then overshot the RESA, breaking the ILS antennae and a fence before plummeting down the tabletop runway. The aircraft fell to a depth of approximately 110 ft below the runway elevation and impacted the perimeter road that runs just below the tabletop runway, at a ground speed of 41 knots and then came to an abrupt halt on the airport perimeter road just short of the perimeter wall. There was fuel leak from both the wing tanks; however, there was no postcrash fire. The aircraft was destroyed and its fuselage broke into three sections. Both engines were completely separated from the wings. The rescue operations were carried out by the ARFF crew on duty with help of Central Industrial Security Force (CISF) personnel stationed at the airport and several civilians who rushed to the crash site when the accident occurred. Upon receipt of the information about the aircraft crash the district administration immediately despatched fire tenders and ambulances to the crash site. Nineteen passengers were fatally injured and Seventy Five passengers suffered serious injuries in the accident while Ninety passengers suffered minor or no injuries. Both Pilots suffered fatal injuries while one cabin crew was seriously injured and three cabin crew received minor injuries. The rescue operation was completed at 16:45 UTC (22:15 IST).
Probable cause:
The probable cause of the accident was the non adherence to SOP by the PF, wherein, he continued an unstabilized approach and landed beyond the touchdown zone, half way down the runway, in spite of ‘Go Around’ call by PM which warranted a mandatory ‘Go Around’ and the failure of the PM to take over controls and execute a ‘Go Around’.

The following contributing factors were identitified:

The investigation team is of the opinion that the role of systemic failures as a contributory factor cannot be overlooked in this accident. A large number of similar accidents/incidents that have continued to take place, more so in AIXL, reinforce existing systemic failures within the aviation sector. These usually occur due to prevailing safety culture that give rise to errors, mistakes and violation of routine tasks performed by people operating within the system. Hence, the contributory factors enumerated below include both the immediate causes and the deeper or systemic causes.

(i) The actions and decisions of the PIC were steered by a misplaced motivation to land back at Kozhikode to operate next day morning flight AXB 1373. The unavailability of sufficient number of Captains at Kozhikode was the result of faulty AIXL HR policy which does not take into account operational requirement while assigning permanent base to its Captains. There was only 01 Captain against 26 First Officers on the posted strength at Kozhikode.

(ii) The PIC had vast experience of landing at Kozhikode under similar weather conditions. This experience might have led to over confidence leading to complacency and a state of reduced conscious attention that would have seriously affected his actions, decision making as well as CRM.

(iii) The PIC was taking multiple un-prescribed anti-diabetic drugs that could have probably caused subtle cognitive deficits due to mild hypoglycaemia which probably contributed to errors in complex decision making as well as susceptibility to perceptual errors.

(iv) The possibility of visual illusions causing errors in distance and depth perception (like black hole approach and up-sloping runway) cannot be ruled out due to degraded visual cues of orientation due to low visibility and suboptimal performance of the PIC’s windshield wiper in rain.

(v) Poor CRM was a major contributory factor in this crash. As a consequence of lack of assertiveness and the steep authority gradient in the cockpit, the First Officer did not take over the controls in spite of being well aware of the grave situation. The lack of effective CRM training of AIXL resulted in poor CRM and steep cockpit gradient.

(vi) AIXL policies of upper level management have led to a lack of supervision in training, operations and safety practices, resulting in deficiencies at various levels causing repeated human error accidents in AIXL

(vii) The AIXL pilot training program lacked effectiveness and did not impart the requisite skills for performance enhancement. One of the drawbacks in training was inadequate maintenance and lack of periodic system upgrades of the simulator. Frequently recurring major snags resulted in negative training. Further, pilots were often not checked for all the mandatory flying exercises during simulator check sessions by the Examiners.

(viii) The non availability of OPT made it very difficult for the pilots to quickly calculate accurate landing data in the adverse weather conditions. The quick and accurate calculations would have helped the pilots to foresee the extremely low margin for error, enabling them to opt for other safer alternative.

(ix) The scrutiny of Tech Logs and Maintenance Record showed evidence of nonstandard practice of reporting of certain snags through verbal briefing rather than in writing. There was no entry of windshield wiper snag in the Tech log of VT-AXH. Though it could not be verified, but a verbal briefing regarding this issue is highly probable.

(x) The DATCO changed the runway in use in a hurry to accommodate the departure of AIC 425 without understanding the repercussions on recovery of AXB 1344 in tail winds on a wet runway in rain. He did not caution AXB 1344 of prevailing strong tail winds and also did not convey the updated QNH settings.

(xi) Accuracy of reported surface winds for runway 10 was affected by installation of wind sensor in contravention to the laid down criteria in CAR. This was aggravated by frequent breakdown due to poor maintenance.

(xii) The Tower Met Officer (TMO) was not available in the ATC tower at the time of the accident. The airfield was under two concurrent weather warnings and it is mandatory for the TMO to be present to update and inform the fast changing weather variations to enhance air safety. During adverse weather conditions the presence of the TMO in the ATC tower was even more critical.

(xiii) The AAI has managed to fulfil ICAO and DGCA certification requirements at Kozhikode aerodrome for certain critical areas like RESA, runway lights and approach lights. Each of these, in isolation fulfils the safety criteria however, when considered in totality, this left the aircrew of AXB 1344 with little or no margin for error. Although not directly contributory to the accident causation, availability of runway centreline lights would have certainly enhanced the spatial orientation of the PIC.

(xiv) The absence of a detailed proactive policy and clear cut guidelines by the Regulator on monitoring of Long Landings at the time of the accident was another contributory factor in such runway overrun accidents. Long Landing has been major factor in various accidents and incidents involving runway excursion since 2010 and has not been addressed in CAR Section 5, Series F, Part II.

(xv) DGCA did not comprehensively revise CAR Section 5, Series F, Part II Issue I, dated 30 Sep 99 (Rev. on 26 Jul 2017) on ‘Monitoring of DFDR/QAR/PMR Data for Accident/Incident Prevention’ to address the recommendations of the COI of 2010 AIXL Managlore Crash regarding the exceedance limits, resulting in the persisting ambiguities in this matter.

(xvi) DFDR data monitoring for prevention of accidents/incidents is done by AIXL. However 100% DFDR monitoring is not being done, in spite of the provisions laid down in the relevant CAR and repeated audit observations by DGCA. DFDR data monitoring is the most effective tool to identify exceedance and provide suitable corrective training in order to prevent runway accidents like the crash of AXB 1344. However, ATR submitted by AIXL on the said findings were accepted by DGCA year after year without ascertaining its implementation or giving due importance to its adverse implications.
Final Report:

Crash of a De Havilland DHC-2 Beaver in Soldotna: 6 killed

Date & Time: Jul 31, 2020 at 0827 LT
Type of aircraft:
Operator:
Registration:
N4982U
Flight Phase:
Survivors:
No
MSN:
904
YOM:
1956
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
5
Pax fatalities:
Other fatalities:
Total fatalities:
6
Captain / Total flying hours:
19530
Captain / Total hours on type:
13480.00
Aircraft flight hours:
23595
Circumstances:
On July 31, 2020, about 0827 Alaska daylight time, a de Havilland DHC-2 (Beaver) airplane, N4982U, and a Piper PA-12 airplane, N2587M, sustained substantial damage when they were involved in an accident near Soldotna, Alaska. The pilot of the PA-12 and the pilot and the five passengers on the DHC-2 were fatally injured. The DHC-2 was operated as a Title 14 Code of Federal Regulations (CFR) Part 135 on-demand charter flight. The PA-12 was operated as a Title 14 CFR Part 91 personal flight. The float-equipped DHC-2, operated by High Adventure Charter, departed Longmere Lake, near Soldotna, about 0824 bound for a remote lake on the west side of Cook Inlet. The purpose of the flight was to transport the passengers to a remote fishing location. The PA-12, operated by a private individual, departed Soldotna Airport, Soldotna, Alaska, (PASX) about 0824 bound for Fairbanks, Alaska. Flight track data revealed that the DHC-2 was traveling northwest about 78 knots (kts) groundspeed and gradually climbing through about 1,175 ft mean sea level (msl) when it crossed the Sterling Highway. The PA-12 was traveling northeast about 1,175 ft msl and about 71 kts north of, and parallel to, the Sterling Highway. The airplanes collided about 2.5 miles northeast of the Soldotna airport at an altitude of about 1,175 ft msl. A witness located near the accident site observed the DHC-2 traveling in a westerly direction and the PA-12 traveling in a northerly direction. He stated that the PA-12 impacted the DHC-2 on the left side of the fuselage toward the back of the airplane. After the collision, he observed what he believed to be the DHC-2's left wing separate, and the airplane entered an uncontrolled, descending counterclockwise spiral before it disappeared from view. He did not observe the PA-12 following the collision.
Probable cause:
The failure of both pilots to see and avoid the other airplane.
Contributing to the accident were:
1) the PA-12 pilot’s decision to fly with a known severe vision deficiency that had resulted in denial of his most recent application for medical certification and
2) the Federal Aviation Administration’s absence of a requirement for airborne traffic advisory systems with aural alerting among operators who carry passengers for hire.
Final Report:

Crash of a De Havilland DHC-2 Beaver in Lake Coeur d'Alene: 6 killed

Date & Time: Jul 5, 2020 at 1422 LT
Type of aircraft:
Operator:
Registration:
N2106K
Flight Phase:
Survivors:
No
Schedule:
Coeur d'Alene - Coeur d'Alene
MSN:
1131
YOM:
1957
Crew on board:
1
Crew fatalities:
Pax on board:
5
Pax fatalities:
Other fatalities:
Total fatalities:
6
Captain / Total flying hours:
21173
Captain / Total hours on type:
217.00
Aircraft flight hours:
6171
Circumstances:
The float-equipped De Havilland DHC-2 was on a tour flight, and the Cessna 206 was on a personal flight. The airplanes collided in midair over a lake during day visual meteorological conditions. No radar or automatic dependent surveillance-broadcast data were available for either airplane. Witnesses reported that the airplanes were flying directly toward each other before they collided about 700 to 800 ft above the water. Other witnesses reported that the Cessna was at a lower altitude and had initiated a climb before the collision. Review of 2 seconds of video captured as part of a witness’ “live” photo showed that both airplanes appeared to be in level flight before the collision. No evidence of any preexisting mechanical malfunction was observed with either airplane. Recovered wreckage and impact signatures were consistent with the upper fuselage of the Cessna colliding with the floats and the lower fuselage of the De Havilland. The impact angle could not be determined due to the lack of available evidence, including unrecovered wreckage. The available evidence was consistent with both pilots’ failure to see and avoid the other airplane.
Probable cause:
The failure of the pilots of both airplanes to see and avoid the other airplane.
Final Report: