ASN Wikibase Occurrence # 275604
This information is added by users of ASN. Neither ASN nor the Flight Safety Foundation are responsible for the completeness or correctness of this information.
If you feel this information is incomplete or incorrect, you can submit corrected information.
| Date: | Wednesday 16 February 2022 |
| Time: | 09:58 |
| Type: | Joby Aero JAS4-2 |
| Owner/operator: | Joby Aero |
| Registration: | N542AJ |
| MSN: | JAS4-201 |
| Year of manufacture: | 2019 |
| Fatalities: | Fatalities: 0 / Occupants: 0 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Jolon, CA -
 United States of America
|
| Phase: | Manoeuvring (airshow, firefighting, ag.ops.) |
| Nature: | Test |
| Departure airport: | Jolon, CA |
| Jolon, CA | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
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: 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.
Accident investigation:
 |
|
Sources:
NTSB
https://data.ntsb.gov/Docket?ProjectID=104654
Location
Images:
09:58:11.440 PST, failure blade departs station 3 (NTSB)
09:58:11.473 PST, failure blade contacts station 4 (NTSB)
09:58:12.793 PST, vehicle pitches forward, glaireshield begins to detach (NTSB)
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 17-Feb-2022 16:36 | harro | Added |
| 08-Mar-2022 20:48 | Captain Adam | Updated [Time, Phase, Departure airport, Destination airport, Source, Damage, Narrative, Category] |
| 07-Feb-2024 21:03 | Captain Adam | Updated [Time, Phase, Source, Narrative, Category, Accident report, Photo] |
| 07-Feb-2024 21:04 | Captain Adam | Updated [Time] |
| 07-Feb-2024 21:06 | Captain Adam | Updated [Photo] |
| 07-Feb-2024 21:06 | Captain Adam | Updated [Photo] |
| 11-Feb-2024 11:14 | ASN | Updated [Date] |
Corrections or additions? ... Edit this accident description
The Aviation Safety Network is an exclusive service provided by:
Quick Links:
| ASN Home | Send Correction / Feedback |
| FSF Home | Disclaimer | Copyright |
| Contact Us | Privacy Policy |
| Press / Media |
CONNECT WITH US:
©2024 Flight Safety Foundation