COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
British Aerospace BAe 125 Series Aeroplanes
AD/HS 125/157 Rudder Flow Separator Triggers and Strut Spring
12/97
Applicability: Model BAe 125 Series 800A and Series 800B, and Model Hawker 800 and Hawker 800XP series aircraft; on which Raytheon Modification 25FO17A&B has not been installed.
Requirement: Modify the rudder in accordance with Raytheon Service Bulletin 55-36-25FO17A&B.
Note: FAA AD 97-18-07 Amdt 39-10117 refers.
Compliance: Unless already accomplished, within 100 hours time in service or within 6 months after 6 November 1997, whichever occurs first.
This airworthiness directive becomes effective on 6 November 1997.
Background: The FAA received a report indicating that, due to the existing design of the rudder, overbias or overbalance of the rudder occurs during single engine handling. The actions specified by this Directive are intended to prevent this occurrence, which could result in reduced controllability of the aircraft.
Overview
The Civil Aviation Regulations 1998, specifically Part 39, was enacted by the Commonwealth of Australia to ensure the safety and regulation of civil aviation within the country. Within this regulatory framework, Schedule 105 pertains to airworthiness directives that must be followed to maintain the safe operation of aircraft. One such directive, AD/HS 125/157, addresses the rudder flow separator triggers and strut spring for British Aerospace BAe 125 Series aeroplanes, models 800A and 800B, as well as Hawker 800 and Hawker 800XP series aircraft, excluding those that have already had the Raytheon Modification 25FO17A&B installed. This directive was introduced to address a safety issue where the existing design of the rudder could cause overbias or overbalance during single engine handling, potentially leading to reduced controllability. The objective of this directive is to ensure that modifications are made in accordance with Raytheon Service Bulletin 55-36-25FO17A&B, with compliance required within 100 hours of time in service or within six months after 6 November 1997, whichever is sooner. This airworthiness directive became effective on 6 November 1997, aligning with the Federal Aviation Administration's AD 97-18-07 Amendment 39-10117.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, which pertains to the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, applies to certain British Aerospace BAe 125 Series aeroplanes, namely the Model BAe 125 Series 800A and 800B, as well as the Model Hawker 800 and Hawker 800XP series aircraft, provided they have not been installed with the Raytheon Modification 25FO17A&B. This regulation mandates the modification of the rudder to comply with Raytheon Service Bulletin 55-36-25FO17A&B, to address the risk of rudder overbias or overbalance during single engine handling, which could lead to reduced controllability. Compliance with this directive is required within 100 hours of time in service or within six months from 6 November 1997, whichever comes first, and it became effective on that date. The directive references FAA AD 97-18-07 Amendment 39-10117, indicating a collaborative effort between Australian and US aviation authorities in addressing this safety issue.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, address airworthiness directives, with AD/HS 125/157 focusing on the British Aerospace BAe 125 Series aeroplanes (Section 12/97). This directive pertains to BAe 125 Series 800A and 800B, and Hawker 800 and 800XP series aircraft that have not had the Raytheon Modification 25FO17A&B installed. The requirement outlined is to modify the rudder in accordance with Raytheon Service Bulletin 55-36-25FO17A&B, referencing FAA AD 97-18-07 Amdt 39-10117 (Section 12/97). The directive stipulates compliance within 100 hours of time in service or within six months from 6 November 1997, whichever is sooner. The directive was made effective on 6 November 1997.
Entities and individuals governed by these regulations must ensure compliance with the specified modifications to the rudder to maintain airworthiness standards. This involves implementing the changes as per Raytheon Service Bulletin 55-36-25FO17A&B, which is essential for preventing overbias or overbalance of the rudder during single engine handling. This, in turn, is crucial for maintaining the aircraft's controllability and safety. Non-compliance with these requirements may result in the aircraft not meeting the necessary airworthiness standards, potentially leading to safety issues and regulatory penalties.
Failure to comply with the airworthiness directive AD/HS 125/157 can result in various civil and criminal consequences. Specifically, if the required modifications to the rudder are not performed within the stipulated timeframe, the aircraft may be deemed non-compliant with the regulations. This non-compliance could lead to grounding of the aircraft until the required modifications are completed. Additionally, operators and owners of the aircraft may face enforcement actions, including fines and other penalties as prescribed under the Civil Aviation Act 1988. The maximum penalties for non-compliance can be significant, reflecting the importance of adhering to airworthiness directives to ensure the safety of aviation operations.