AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Beechcraft 56TC(Turbo Baron) Series Aeroplanes

AD/BEECH 56/33 Electroluminescent Panel Retaining S crew 8/2002

DM

Applicability: Beech Model A56TC aeroplanes with serial numbers TG-84 through TG-94. Requirement:              1.              Inspect the Instrument Subpanel electroluminescent panel in accordance with the

Accomplishment Instructions of Raytheon Aircraft Mandatory Service Bulletin SB 33-3452, issued May 2001, for the installation of a rotating beacon circuit breaker switch or any other switch directly above the lower electroluminescent panel retaining screw as follows:

1. If a blanking plug is installed above the lower electroluminescent panel retaining screw, ensure that the correct length screw is installed. (The correct length is 5.3 to 7.8mm or 0.28 to 0.31 inches.)
2. If a rotating beacon circuit breaker switch or any other switch is installed, inspect the switch for damage.

2.        Replace any damaged switch found during the Requirement 1 inspection and replace the electroluminescent panel retaining screw if it is not 0.28 to 0.31 inches (5.3 to 7.8mm) in length with a P/N MS35214-24 screw or approved equivalent part number.

3.        Electroluminescent panel retaining screw, that is not P/N MS35214-24 or an approved equivalent part number, may not be installed in the lower part of the Instrument Subpanel (underneath the circuit breaker switches).

Note: FAA AD 2002-11-07 Amdt 12768 refers.

Compliance: For Requirement 1 - Within 100 hours’ time in service after the effective date of this Directive.

For Requirement 2 - Before further flight after the Requirement 1 inspection. For Requirement 3 - As of the effective date of this Directive.

This Airworthiness Directive becomes effective on 15 July 2002.

Beechcraft 56TC(Turbo Baron) Series Aeroplanes

AD/BEECH 56/33 (continued)

Background: The United States Federal Aviation Administration has advised that an improper length electroluminescent panel retaining screw damaged the rotating beacon circuit breaker switch, which resulted in damaged wiring. This condition could result in failure of the circuit breaker and lead to smoke and/or fire in the cockpit.

This Directive requires an inspection of the Instrument Subpanel electroluminescent panel retaining screw for proper length and the rotating beacon circuit breaker switch (or any other switch in the same location) for damage together with replacement of any screw or circuit breaker switch as necessary. These actions are intended to prevent damage to the rotating beacon circuit breaker switch or any other switch in the same location which could cause smoke and/or fire in the cockpit.

Eugene Paul Holzapfel

Delegate of the Civil Aviation Safety Authority 26 June 2002

The above AD is notified in the Commonwealth of Australia Gazette on 3 July 2002.