NTSB Final Report: Joby Aero Inc JAS4-2 | Aero-News Network
Aero-News Network
RSS icon RSS feed
podcast icon MP3 podcast
Subscribe Aero-News e-mail Newsletter Subscribe

Airborne Unlimited -- Most Recent Daily Episodes

Episode Date



Airborne-Wednesday Airborne-Thursday


Airborne On YouTube






Sat, Feb 10, 2024

NTSB Final Report: Joby Aero Inc JAS4-2

First Of Their Two Second Generation, Pre-Production Prototype Flight Test Aircraft

Location: Jolon, California Accident Number: DCA22FA082
Date & Time: February 16, 2022, 09:58 Local Registration: N542AJ
Aircraft: Joby Aero Inc JAS4-2 Aircraft Damage: Substantial
Defining Event: Part(s) separation from AC Injuries: N/A
Flight Conducted Under: Part 91: General aviation - Flight test

Analysis: On February 16, 2022, Joby Aero Inc. was conducting planned, remotely piloted, airspeed and altitude envelope expansion flight tests on aircraft JAS4-2, the first of their two second generation, pre-production prototype flight test aircraft. The envelope expansion flight test conditions were beyond the expected operating conditions of the aircraft. During the second test flight, and after reaching a maximum dive speed of 181 knots indicated airspeed (KIAS) at an altitude of approximately 8,900 feet, a propeller blade on propulsion station 3 (located on the right wing inboard) experienced a bending failure near the root of the blade which culminated in the release of the propeller blade. The released blade impacted the propeller on propulsion station 4 (located on the right wing outboard), which subsequently resulted in a release of the impacted blade. Cascading effects resulted from the initial inflight blade failures including the separation of multiple propulsion motor/propeller assemblies and loss of remote pilot control of the aircraft. The aircraft departed controlled flight after the initial inflight blade failure and impacted the ground about 0.5 nautical miles (nm) south-southeast away.

Examination of the High-Resolution Recorder data for the accident time period revealed that the variable pitch actuator for station 3 was commanding a typical cruise pitch when the blade release occurred, whereas video evidence indicated a steeper pitch on some blades immediately before the initial blade release. Accelerometer data for station 3 showed a rapid growth in vibration after reaching the accident flights test condition before the initial blade release. Tilt actuator position values for station 3 also showed an oscillation at this time. 

Examination of prior flight test data by Joby revealed consistent asymmetric behavior between station 2 and station 3, despite identical mirrored designs. In cruise mode, the tilt actuators on station 3 showed increased activity in all flight conditions compared to station 2. Tilt actuator linkage loads were also higher in station 3, which can be an indication of anomalous  behavior in the tilt mechanism. The resonant response to this propeller mode crossing in station 3 was also consistently stronger than in station 2, indicative of a coupled interaction with the anomalous tilt mechanism. While prior flights excited the propeller mode in transition flight, the strong excitation in cruise was not predicted; post-accident analysis revealed this strong excitation was due to aerodynamic interactions that only became significant when the airspeeds were beyond the expected operating conditions of the aircraft. 

The dive speed of 181 KIAS reached during the speed and altitude envelope expansion flight test in conjunction with an anomalous propeller tilt system condition at propulsion station 3, likely resulted in unanticipated aerodynamic interactions that excited a propeller mode, leading to a non-uniform blade pitch increase beyond its design limitations. This likely caused a load exceedance which resulted in the initial blade failure. Aircraft control was lost as a result of cascading effects following the initial propeller blade separation.

Probable Cause and Findings: The National Transportation Safety Board determines the probable cause(s) of this accident to be -- The separation of a propeller blade during expansion flight testing that resulted in cascading effects to include the separation of multiple propulsion motor/propeller assemblies and the loss of remote pilot control of the aircraft. Contributing to the accident was the tilt rotor actuator linkage for propulsion station 3 that allowed some propeller blades to be at a steeper angle than commanded. 

FMI: www.ntsb.gov


More News

ANN's Daily Aero-Linx (07.21.24)

Aero Linx: WACO Historical Society The WACO Aircraft Company was the largest manufacturer of civil aircraft in the country in the late 1920's and early 30's and this museum is dedi>[...]

ANN's Daily Aero-Term (07.21.24): Radar Flight Following

Radar Flight Following The observation of the progress of radar-identified aircraft, whose primary navigation is being provided by the pilot, wherein the controller retains and cor>[...]

Airborne 07.17.24: Illegal Parts, Fantasy of Flight, Apollo 11's 55th

Also: Aerox, WI ANG, HI Helo Accident, Gulfstream Expansion Another criminal case involving non-airworthy parts swappage has seen the sentencing of those involved, costing the perp>[...]

Airborne-NextGen 07.16.24: Joby Record, Pelican Spray, Beta’s ALIA

Also: UAS4STEM, uAvionix Waiver, 1st J-1 Pulsejets, ZeroAvia Hydrogen Joby Aviation managed to pull off a 523-mile flight using their hybrid electric/hydrogen VTOL aircraft, once a>[...]

ANN's Daily Aero-Linx (07.22.24)

Aero Linx: Michigan Department of Transportation Aeronautics is an integral part of our transportation system, moving people and goods throughout the world. The airports that suppo>[...]

blog comments powered by Disqus





© 2007 - 2024 Web Development & Design by Pauli Systems, LC