Document ID: chunk:federal_register_of_legislation:F2006B04034:body:0:p1
Version: federal_register_of_legislation:F2006B04034
Segment Type: other
Provision Reference: 
Character Range: 4–3187

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

    Beechcraft 55, 58 and 95-55 (Baron) Series Aeroplanes

                       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.

AD/BEECH 55/88 Rudder Bellcrank Interconnect Tube 3/2001
    Applicability: Model 58 aircraft; serial numbers TH-1389, and TH-1396 through TH-1885 Requirement:               1. Inspect the rudder bellcrank interconnect tube for damage in accordance with the
                 Accomplishment Instructions paragraph of Raytheon Mandatory Service Bulletin
                 SB 27-3013, Issued: June 2000, and the Baron Model 58 Shop Manual; and ensure the floorboard panel screws are ¾ inch or less in length. Screws that are longer than ¾ inch in length can damage parts installed immediately below the floorboards.

2.    If no damage to the rudder bellcrank interconnect tube is evident, discard any self- tapping coarse thread screw installed in the flanges that is longer than ¾ inch.

3.    If damage to the rudder bellcrank interconnect tube is evident, and the damage has not worn into the aluminium interconnect tube, refinish the interconnect tube and discard any self-tapping coarse thread screw installed in the flanges that is longer than ¾ inch.

4.    If damage to the rudder bellcrank interconnect tube is evident, and the damage has worn into the aluminium interconnect tube, replace the interconnect tube and discard any self-tapping coarse thread screw installed in the flanges that is longer than ¾ inch.

                 5.    Plug the floorboard screw hole.

               Note: FAA AD 2000-22-18 Amendment 39-11965 refers.

    Compliance: Within 6 calendar months after 22 March 2001, unless already accomplished.

               Accomplish all follow-on actions, such as replacement or repair, before further flight after the inspection.

               This Airworthiness Directive becomes effective on 22 March 2001.
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Background: The FAA received four reports of damage to the rudder bellcrank interconnect tube.
            The actions specified by this Directive are intended to correct the wrong use of screws, and consequent wear in the pilot/co-pilot pedal interconnect tube which could result in loss of rudder control.

 David Alan Villiers
 Delegate of the Civil Aviation Safety Authority 24