1AD/BAe 146/14 - Electric Flap Control Unit

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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British Aerospace BAe 146 Series Aeroplanes

AD/BAe 146/14 Electric Flap Control Unit 8/89

Applicability: All series 100 and 100A aircraft constructors number E1002 and subsequent. All series 200 and 200A aircraft constructors number E2012 and subsequent. All series 300 and 300A aircraft constructors number E3118 and subsequent.

Requirement: 1. Action in accordance with BAe Mandatory Service Bulletin 11-36-01104A and B.

2. Action in accordance with BAe Mandatory Service Bulletin 27-95-70420A. Compliance: Requirement 1 prior to 10 October 1989. Requirement 2 prior to 10 May 1990. Background: These modifications are intended to:

deter flight crew from removing or re-racking the flap system E.C.U. or pulling associated circuit breakers in light and thus endangering the aircraft during a legitimate flap system fault condition.

overcome spurious warnings caused by slow start-ups after prolonged cold soak conditions.

overcome the need to provide additional warning against re-racking in flight.

overcome the need to reduce the computer lightning susceptibility to an approved level.