COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes
AD/SWSA226/61 Rudder Trim Tab Rod Assembly 2/91 TX
Applicability: All model SA 26, SA226, and SA227 series aircraft.
Requirement: Action in accordance with the technical requirements of FAA Emergency Airworthiness Directive 90-24-03, which requires the following:
Visually inspect the rudder trim tab link assemblies (Part Numbers 27-42025-001 through 27-42025-009 as installed) as follows:
(1) Remove the fairing strip between the vertical fin and rudder.
(2) Check each connecting rod end for freedom of movement and corrosion around the bearing as follows:
(i) Move the rudder trim system from full left to full right deflection and check for any indications of corrosion or binding in the rod and fittings.
(ii) If necessary, remove the bolt connecting the actuator and each rod end and check the bearings for freedom of movement.
(iii) Check the bolts connecting the rudder actuator to each rod end to insure each bolt is oriented vertically.
(3) If either rod end is corroded, prior to further flight replace the affected rod end with a serviceable part.
(4) If the rudder trim mechanism is incorrectly installed, or if either rod end bearing is binding, prior to further flight replace the affected connecting rod and rod end assembly with serviceable parts.
(5) If corrosion or binding is not found, reinstall the fairing strip and return the aeroplane to service.
Note 1: Fairchild Aircraft Service Notes 26-SN-061, 226-SN-162, and 227-SN-074 pertain to the subject of this AD.
Note 2: Although not required by this AD, the inspections specified in this AD should be included in the regular aircraft maintenance program.
Compliance: Within 15 hours time in service after 7 December 1990 or prior to 17 December 1990; whichever occurs first.
Background: This AD requires a one-time inspection of the rudder trim tab rod assemblies in all Fairchild SA26, SA226, and SA227 series aircraft. The FAA has been notified of three failures of these assemblies (Part Number 27-42025-001 through 27-42025-009) caused by improper installation in one instance, and corrosion in the other two instances. The actions specified in this AD will preclude failure of the rudder trim tab rod assemblies and the resultant aerodynamic vibration, structural deformation, and possible loss of control of the aircraft.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Overview
The Civil Aviation Regulations 1998, as amended, incorporate various airworthiness directives issued by the Civil Aviation Safety Authority (CASA) to ensure the safety of aircraft operating within Australian airspace. One such directive is the AD/SWSA226/61, which was enacted to address the specific issue of rudder trim tab rod assembly failures in Fairchild (Swearingen) SA226 and SA227 series aeroplanes. The directive was introduced in response to reports of three instances where these assemblies failed, resulting from either improper installation or corrosion. The policy objective of this directive is to prevent any future failures that could lead to aerodynamic vibration, structural deformation, and potential loss of control of the aircraft. CASA mandates that all affected aircraft must undergo a one-time inspection of their rudder trim tab rod assemblies within a specified timeframe to ensure compliance with safety standards and mitigate any potential risks.
Scope and Application
The Civil Aviation Regulations 1998, specifically PART 39 - 105, mandates Airworthiness Directives (AD) for the maintenance and safety of aircraft operating within Australian airspace. This particular AD, AD/SWSA226/61, applies to all Fairchild (Swearingen) SA226 and SA227 series aeroplanes, ensuring these aircraft meet specific technical requirements to maintain airworthiness. The directive mandates a one-time inspection of the rudder trim tab rod assemblies, which must be completed within 15 hours of time in service after 7 December 1990 or prior to 17 December 1990, whichever occurs first. This inspection is necessary to prevent potential failures caused by corrosion or improper installation, which could lead to aerodynamic vibration, structural deformation, and loss of control. While the AD is binding and must be adhered to by operators of the specified aircraft, it is recommended that these inspections be included in the regular aircraft maintenance program, even though not explicitly required by the directive. The AD extends its requirements nationally, affecting all operators within Australia who possess or operate the specified aircraft models.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39 - 105, mandate specific airworthiness directives for the Fairchild (Swearingen) SA226 and SA227 series aeroplanes, particularly concerning the rudder trim tab rod assembly (AD/SWSA226/61). This directive, applicable to all model SA 26, SA226, and SA227 series aircraft, requires a thorough visual inspection of the rudder trim tab link assemblies as per FAA Emergency Airworthiness Directive 90-24-03. Specifically, this involves removing the fairing strip between the vertical fin and rudder, checking each connecting rod end for freedom of movement and corrosion, and ensuring that the bolts connecting the rudder actuator to each rod end are oriented vertically (Section 1). If corrosion or improper installation is detected, the affected parts must be replaced with serviceable components before further flight.
These regulations impose clear obligations on aircraft owners and operators. They must ensure that the specified inspections are carried out within a stipulated timeframe: within 15 hours of the aircraft being in service after 7 December 1990, or prior to 17 December 1990, whichever comes first (Compliance). Failure to comply with this directive could lead to serious consequences, including the risk of aerodynamic vibration, structural deformation, and potential loss of control of the aircraft. It is also recommended that these inspections be included in the regular maintenance program, though this is not a mandatory requirement under the directive (Note 2).
Non-compliance with the airworthiness directives outlined in the Civil Aviation Regulations 1998 can lead to severe penalties and consequences. Although the specific penalties are not detailed in the text, non-compliance with airworthiness directives generally can result in both civil and criminal liabilities. Civil penalties may include fines, while criminal penalties could lead to imprisonment. The severity of the penalty often depends on the extent of the non-compliance and its impact on aviation safety. The importance of adhering to these directives cannot be overstated, as they are designed to prevent potentially catastrophic failures in aircraft systems.