Jump to Content
Download Final Report
[ Download PDF: 15KB]
The pneumatic system on this aircraft type operates the landing gear, flaps and brakes. The aircraft is equipped with a castering nosewheel and steering is achieved by differential braking. The pneumatic system normal operating pressure is 450 to 600 psi. The minimum pressure for engine start is 90 psi. Prior to engine start, the pilot noted that the pneumatic pressure was about 250 psi. He anticipated the pressure would increase to normal operating pressure after engine start. The engines were started and the aircraft commenced taxiing. Shortly afterwards the pilot noted that pneumatic pressure had not increased to normal operating pressure as anticipated. At about this time he recalled that he had activated the pneumatic system drain valves during a ground inspection of the aircraft. He suspected that he may not have tightened the valves and that this could be the reason for lack of pneumatic pressure. He therefore decided to return to the parking area and investigate. As there was still over 100 psi pressure he considered it safe to taxy back to the hangar (bearing in mind that 90 psi is the minimum for start which infers that the brakes should work at that pressure). Approaching the hangar which involved taxiing on a downhill slope, he applied differential braking but there was no response. Realising that he would be unable to turn the aircraft he quickly shut the engines down. The aircraft rolled slowly towards a hangar where it collided with a scaffolding fence, incurring minor damage to the nosegear doors and skin areas of the nose and one wing. During a post incident inspection, the pilot noted that the pneumatic system drain valves had not been properly tightened. This explained the reason for the lack of normal system pressure build up after engine start. However, the pilot said he believed there should still have been enough pressure for differential braking/steering. Accordingly, he would have a complete check made of the pneumatic system after the damage sustained in the incident had been repaired.
Download Final Report
[ Download PDF: 15KB]
General details
Date: 13 March 1995 Investigation status: Completed 
Time: 12:15 ESuT  
 Investigation type: Occurrence Investigation 
Release date: 03 April 1995 Occurrence class: Operational 
Report status: Final Occurrence category: Incident 
Aircraft details
Aircraft manufacturer: de Havilland Aircraft Pty Ltd 
Aircraft model: DH-104 SERIES 8 
Aircraft registration: VH-DHQ 
Sector: Piston 
Damage to aircraft: Minor 
Destination:King Island TAS
Share this page Provide feedback on this investigation
Last update 21 October 2014