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Last updated: 14 November 2019
Status:Schlussbericht
Datum:Dienstag 21 April 2015
Zeit:12:18
Flugzeugtyp:Silhouette image of generic C30J model; specific model in this crash may look slightly different
Lockheed AC-130J Ghostrider
Fluggesellschaft:United States Air Force - USAF
Kennzeichen: 09-5710
Werknummer: 5710
Baujahr: 2012
Besatzung:Todesopfer: 0 / Insassen: 8
Fluggäste:Todesopfer: 0 / Insassen: 0
Gesamt:Todesopfer: 0 / Insassen: 8
Sachschaden: schwer beschädigt
Konsequenzen: Written off (damaged beyond repair)
Unfallort:76 km (47.5 Meilen) S of Valparaiso-Eglin AFB, FL (VPS) (   USA)
Flugphase: Manövrieren (MNV)
Betriebsart:Militär
Flug von:Valparaiso-Eglin AFB, FL (VPS/KVPS), USA
Flug nach:Valparaiso-Eglin AFB, FL (VPS/KVPS), USA
Unfallbericht:
The Lockheed AC-130J Ghostrider, assigned to the USAF's 413th Flight Test Squadron, 96th Test Wing, departed controlled flight over water to the south of Eglin AFB and then was recovered and landed safely. There were no significant injuries to the crew. Post-flight engineering analysis revealed that the mishap aircraft exceeded the Design Limit Load (DLL), thus rendering it unsafe for further flight.
The mishap occurred on a medium risk flying qualities test sortie out to the edges of the flight envelope. The pilot was attempting to execute a Steady Heading Sideslip (SHSS) to the RUDDER Special Alert of the Advisory Caution and Warning System (ACAWS). This is normally a prohibited maneuver, but the Director of Operations at Air Force Materiel Command (AFMC/A3) signed a waiver approving the test team to fly to this limit. The MA exceeded 14.5° Angle of Sideslip (AoS), triggering the RUDDER Special Alert and continued increasing AoS until it departed controlled flight, eventually tumbling to an inverted position. Shortly thereafter, the aircraft recovered from the departure and the copilot took the controls to recover from the near vertical dive. In the process of the departure and recovery, the aircraft lost approximately 5,000 feet of altitude, experienced 3.19 times the normal force acceleration (Gs), and over sped the flaps by over 100 knots. The over G exceeded the aircraft's Design Limit Load.

Probable Cause:

The Accident Investigation Board (AIB) President found, by a preponderance of the evidence, the cause of this mishap was the MP's [Mishap Pilot's] excessive rudder input during the test point followed by inadequate rudder input to initiate a timely recovery from high AoS due to Overcontrolled/Undercontrolled Aircraft and Wrong Choice of Action During an Operation.

Additionally, the AIB President found, by a preponderance of the evidence, the following factors substantially contributed to the mishap: Instrumentation and Warning System Issues, Spatial Disorientation, Confusion, and the fact the test team was Provided Inadequate Procedural Guidance or Publications.

Accident investigation:
cover
Investigating agency: USAF AIB
Status: Investigation completed
Duration: 162 days (5 months)
Accident number: Final report
Download report: Final report


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This information is not presented as the Flight Safety Foundation or the Aviation Safety Network’s opinion as to the cause of the accident. It is preliminary and is based on the facts as they are known at this time.
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