AD/BEECH 65/57 Amdt 4 - Wing Panel to Centre Section Attachment - Steel Bolts and Nuts (Cth)

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

Beechcraft 65 and 70 (Queen Air) Series Aeroplanes

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 65/57 Amdt 3 and issues the following 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.

AD/BEECH 65/57 Amdt 4

Applicability: All models.

Wing Panel to Centre Section Attachment - Steel Bolts and Nuts

11/2000

Requirement: 1. Remove and carry out inspections of all eight wing attach steel bolts and nuts in accordance with the procedures outlined in the Beechcraft Structural Inspection and Repair Manual 98-39006B3 as revised 28 May 1999, Chapter 57-11-00 for models 65, 70 & 80, and Chapter 57-12-00 for the model 88, Chart 201 Index No. 10, "Wing bolt, nut, and spar fitting inspection".

2. Renew all eight wing attach bolts and nuts.

Note: Inspection of the wing attach fittings is detailed in the current issue of AD/BEECH 65/22.

Compliance: For Requirement 1. Prior to exceeding 2 calendar years since bolt and nut installation, and thereafter at intervals not exceeding 2 calendar years.

For Requirement 2. At intervals not exceeding 6 calendar years since installation. This Amendment becomes effective on 2 November 2000. Background: The original issue of this AD became effective on 6 November 1981. It was distributed by Telex and was based on FAA AD 81-23-01. It followed an in-flight failure of a steel bolt in the USA and required inspection of the forward upper and lower bolts, nuts and fittings.