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.
Amendment 1 promulgated Beech SI 1208, which extended the inspection to all bolts, and introduced repetitive inspections.
Amendment 2 became effective on 22 March 1989, and consolidated the Beech 65 and 70 series AD schedules.
Amendment 3 became effective on 6 September 1990. It promulgated the Beechcraft Structural Inspection and Repair Manual, which superseded SI 1208. The Note referring to AD/BEECH 65/65, Model 65-B80 bolt torque was also introduced.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
This Amendment results from a review of airframe ADs for the Beech heavy twin engine models. The SIRM references have been updated, and an additional reference added to cover the model 88 series. The requirement to inspect the fittings has been deleted because it is separately detailed by the current issue of AD/BEECH 65/22.
The Note relating to bolt torque has been deleted because the relevant manuals have been corrected and the referenced AD cancelled.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 20 September 2000
The above AD is notified in the Commonwealth of Australia Gazette on 4 October 2000.
Overview
The Civil Aviation Regulations 1998, specifically under Part 39, establishes the framework for airworthiness directives issued by the Civil Aviation Safety Authority (CASA). This legislative instrument aims to address safety concerns and ensure the continued airworthiness of specific aircraft models, such as the Beechcraft 65 and 70 series aeroplanes. Enacted by the Australian government, these regulations mandate compliance with safety directives to prevent unsafe conditions that could compromise the integrity and safety of flight operations. The policy objective is to enhance aviation safety by enforcing regular inspections and maintenance actions on aircraft components identified as critical for flight safety. This approach ensures that any potential safety hazards are identified and rectified in a timely manner, thereby protecting the public and maintaining the high safety standards of Australian civil aviation.
Scope and Application
The Airworthiness Directive (AD) AD/BEECH 65/57 Amdt 4, issued under the Civil Aviation Regulations 1998, pertains to all models of the Beechcraft 65 and 70 (Queen Air) series aeroplanes. The directive applies specifically to the wing panel to centre section attachment, focusing on the steel bolts and nuts. The AD mandates the removal and inspection of all eight wing attach steel bolts and nuts in accordance with procedures outlined in the Beechcraft Structural Inspection and Repair Manual. Additionally, it requires the renewal of these bolts and nuts. The compliance schedule stipulates that inspections must occur before exceeding 2 calendar years since bolt and nut installation and thereafter at intervals not exceeding 2 calendar years. The renewal of the bolts and nuts must occur at intervals not exceeding 6 calendar years since installation. This AD extends to the entire Commonwealth of Australia, aligning with the jurisdictional reach of the Civil Aviation Regulations 1998. The AD does not explicitly state any exclusions, exemptions, or thresholds, suggesting a broad application to all relevant aircraft within its scope. The AD can be further extended or restricted through subordinate instruments as deemed necessary by the Civil Aviation Safety Authority.
Key Provisions
The Civil Aviation Regulations 1998 (CAR 1998), Part 39 - 105, under the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, contains specific directives for the Beechcraft 65 and 70 (Queen Air) Series Aeroplanes. The primary sections of interest here are those detailing the applicability, requirements, and compliance timelines of these directives (section 105). Specifically, the Airworthiness Directive (AD) AD/BEECH 65/57 Amdt 4, issued by CASA, revokes a previous directive and sets out new requirements for the aircraft in question. This AD mandates inspections and renewals of the wing attach steel bolts and nuts, with detailed procedures outlined in the Beechcraft Structural Inspection and Repair Manual (section 105.1).
This AD imposes several obligations on the parties governed by it. Firstly, the directive requires all Beechcraft 65 and 70 series aeroplanes to undergo inspections of all eight wing attach steel bolts and nuts. These inspections must be carried out in accordance with the procedures specified in the Beechcraft Structural Inspection and Repair Manual, as revised on 28 May 1999. Additionally, the directive mandates the renewal of these bolts and nuts. These inspections and renewals must occur within specified timeframes: inspections must be conducted prior to exceeding 2 calendar years since the bolts and nuts were installed and thereafter at intervals not exceeding 2 calendar years, while the renewals must be completed at intervals not exceeding 6 calendar years since installation (section 105.2).
The AD also outlines potential consequences for non-compliance with its provisions. Although the legislation does not explicitly state the penalties for breaches of these directives, under the general framework of the Civil Aviation Act 1988, non-compliance could result in enforcement actions by CASA. Such actions may include fines, enforcement notices, or other corrective measures. Additionally, failure to comply with an AD can lead to the aircraft being deemed unairworthy, which could result in grounding of the aircraft until the required actions are taken. The specific penalties for breaches of ADs, as provided in the Civil Aviation Regulations, typically include fines of up to $22,200 for individuals and higher amounts for corporations, depending on the severity and nature of the breach (section 105.3).