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 January 2001
The above AD is notified in the Commonwealth of Australia Gazette on 21 February 2001.
Overview
The Civil Aviation Regulations 1998 (CAR 1998) was enacted to regulate civil aviation safety in Australia and to ensure the safety of aircraft operations within the country. This legislation was introduced to address the need for comprehensive regulations governing the operation, maintenance, and certification of civil aircraft. The CAR 1998 was enacted by the Parliament of Australia and is administered by the Civil Aviation Safety Authority (CASA). The policy objective of this Act is to ensure the highest possible safety standards in civil aviation by regulating the airworthiness of aircraft and the qualifications and practices of aviation personnel. The specific Airworthiness Directive (AD) for Beechcraft 55, 58, and 95-55 (Baron) Series Aeroplanes, issued in 2001, was introduced to address the problem of damage to the rudder bellcrank interconnect tube. This AD requires inspections and corrective actions to prevent potential loss of rudder control due to improper use of screws and consequent wear.
Scope and Application
The Airworthiness Directive AD/BEECH 55/88 applies specifically to Beechcraft Model 58 aircraft with serial numbers TH-1389, and TH-1396 through TH-1885. The directive mandates actions to address potential safety issues related to the rudder bellcrank interconnect tube and floorboard panel screws. The AD is issued by a delegate of the Civil Aviation Safety Authority (CASA) under subregulation 39.1(1) of the Civil Aviation Regulations 1998 and applies within the Commonwealth of Australia. The directive requires inspections and corrective actions to be completed within six months of the directive's effective date, 22 March 2001, unless already accomplished. This directive becomes effective on the date it is published in the Commonwealth of Australia Gazette, which was 21 February 2001. The AD does not explicitly mention any exclusions or exemptions, implying that all applicable aircraft must comply with the specified actions. The directive can also be extended or modified through subordinate instruments, such as additional notices or updates published by CASA.
Key Provisions
The Civil Aviation Regulations 1998 (CAR 1998) Part 39, Subpart 105, includes an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) delegate for Beechcraft 55, 58, and 95-55 (Baron) series aeroplanes. Specifically, AD/BEECH 55/88 pertains to the rudder bellcrank interconnect tube. This directive applies to Model 58 aircraft with specific serial numbers (TH-1389, and TH-1396 through TH-1885). The AD requires operators to inspect the rudder bellcrank interconnect tube for damage and ensure that floorboard panel screws are no longer than ¾ inch. Depending on the condition of the interconnect tube, operators must either discard overlong screws, refinish the tube, replace it, or plug the screw hole.
Operators and owners of the affected aircraft must comply with the AD by conducting the specified inspections and repairs within six months of 22 March 2001, unless already completed. Any required follow-on actions, such as replacements or repairs, must be accomplished before further flight after the inspection. The AD aims to address the issue of screws damaging the interconnect tube, which could lead to loss of rudder control. It references FAA AD 2000-22-18 Amendment 39-11965, indicating alignment with international safety standards.
Failure to comply with the AD may result in serious safety hazards. The AD emphasises the necessity of adhering to the specified instructions and timelines to ensure the continued airworthiness of the affected aircraft. Non-compliance could lead to enforcement actions by CASA, potentially including fines or other regulatory penalties, as well as increased risk to flight safety. The maximum penalties for non-compliance with ADs are not explicitly stated in the provided text, but they generally include substantial fines and potential prosecution under civil aviation law.