AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 55/89 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.
Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes
AD/BEECH 55/89
Amdt 1
Right Hand Fuselage Rivets 3/2003
Applicability: | Model
Group 1 aircraft: | Serial Number |
| 58 | TH-1 through TH-1811 and TH-1813 through TH-1897 |
| Group 2 aircraft: |
|
| 58A | TH-1 through TH-1811 and TH-1813 through TH-1897 |
Requirement: Group 1 and Group 2 aircraft:
Inspect for missing rivets between fuselage station (F.S.) 83.00 and F.S. 91.00 at water line (W.L.) 90.3.
Inspect in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of Raytheon Mandatory Service Bulletin SB 53-3341 Revision 1, Revised May 2000, or SB 3341 Revision 2, Revised October 2002, and the Baron Model 58 Series Maintenance Manual.
If rivets are found to be missing, before further flight, install these rivets.
Note: FAA AD 2003-01-01 Amdt 39-13012 refers.
Compliance: For Group 1 aircraft: Within 100 hours’ time-in-service after 22 March 2001. For Group 2 aircraft: Within 100 hours’ time in service after 20 March 2003.
The compliance time remains unchanged for aircraft affected by the original issue of this Directive.
This Amendment becomes effective on 20 March 2003.
Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes
AD/BEECH 55/89 Amdt 1 (Continued)
Background: The manufacturer has identified several instances of missing rivets on affected aircraft. These rivets must be present for the fuselage to carry the ultimate load and prevent critical structural failure, with loss of aircraft control.
Amendment 1 is issued in response to a new FAA AD which corrects applicability.
The original issue of this Airworthiness Directive became effective on 22 March 2001.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 7 February 2003
The above AD is notified in the Commonwealth of Australia Gazette on 26 February 2003.