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Last updated: 5 December 2019
Status:Final
Date:Thursday 4 November 2004
Time:16:00
Type:Silhouette image of generic C208 model; specific model in this crash may look slightly different
Cessna 208B Grand Caravan
Operator:Army Parachute Association
Registration: G-BZAH
C/n / msn: 208B0811
First flight: 2000
Engines: 1 Pratt & Whitney Canada PT6A-114A
Crew:Fatalities: 0 / Occupants: 1
Passengers:Fatalities: 0 / Occupants: 1
Total:Fatalities: 0 / Occupants: 2
Aircraft damage: Minor
Aircraft fate: Repaired
Location:Netheravon Airport (   United Kingdom)
Phase: Taxi (TXI)
Nature:Parachuting
Departure airport:Netheravon Airport (EGDN), United Kingdom
Destination airport:Netheravon Airport (EGDN), United Kingdom
Narrative:
The aircraft was being taxied from the dispersal to the holding point in preparation for departure for a local flight when the pilot heard two loud bangs from the area of the nose wheel. The pilot contacted ATC on the radio and requested them to look for damage or anything abnormal. ATC reported that a ‘panel’ appeared to be loose so the pilot returned the aircraft to dispersal and
shut down the engine.
Examination by the operator’s aircraft engineer found that the rear support of the nose landing gear (NLG) spring had come away from its rear fuselage mounting point and had dislodged the composite fairing that was fitted immediately below the spring and its supports.
Examination of the four bolts that attach the NLG rear spring support to the fuselage has shown that one bolt failed due to fatigue and the remaining three were pulled from their anchor nuts causing the bolt threads to strip. The fatigue crack initiated at multiple origins in the end thread at one side of the bolt indicating that it was due to bending fatigue.

From the geometry of the NLG it can be seen that towing the aircraft by the nose wheel increases the forward load on the NLG rear spring support. A sudden start, jerk or attempt to start towing with the parking brake on or wheel chocks in place could substantially increase the forward loads on the rear support attachment bolts. Therefore, any of these reasons could be the cause of the forward hole elongation seen in the fuselage structure.

Accident investigation:
cover
Investigating agency: AAIB
Status: Investigation completed
Accident number: EW/C2004/11/09
Download report: Final report

Classification:
Damaged on the ground

Sources:
» AAIB


Follow-up / safety actions

issued 4 Safety Recommendations

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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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