COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Pilatus PC-12 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/PC-12/27 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.
Applicability: PC-12 and PC-12/45 series aeroplanes with manufacturer serial numbers MSN 101 up to and including MSN 400.
Requirement: 1. Insert Temporary Revision No 32 in the Pilot’s Operating Handbook/Aircraft Flight manual (POH/AFM).
2. Install the flap system Primary Drive Unit field control panel and modify the flap control wiring in accordance with the Accomplishment Instructions of Pilatus PC- 12 service Bulletin 27-011 Revision 1 dated 26 January 2001.
Temporary Revision No 32 may be removed from the POH/AFM following accomplishment of Requirement 2.
Note: FOCA Switzerland AD HB 2001-070 refers.
Compliance: For Requirement 1 - Remains unchanged as ‘Before further flight after 14 February 2001’.
For Requirement 2 - Within 50 hours time in service or 30 days after the effective date of this Directive, whichever occurs first.
This amendment becomes effective on 21 February 2001.
Background: The Swiss Federal Office for Civil Aviation (FOCA) has advised that during system maintenance it was found that certain failures of the flap system Primary Drive Unit motor contactor could result in uncommanded cycling of the flaps between 40º and selected positions. Investigation revealed that that current surges were being generated due to the motor coil power being removed after the field coil power was removed or reversed. These surges can cause the contactor to fail in the closed position which could cause cycling of the flaps.
The original issue of this Directive required a Temporary Revision to be inserted in the POH/AFM which introduced limitations on operation of the flaps.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
This amendment introduces a modification which provides terminating action for the POH/AFM flap operating limitations introduced by Temporary Revision 32.
The original issue of this Directive became effective on 14 February 2001.
Eugene Paul Holzapfel
Delegate of the Civil Aviation Safety Authority 15 February 2001
The above AD is notified in the Commonwealth of Australia Gazette on 21 February 2001.
Overview
The Civil Aviation Regulations 1998 (CAR 1998) were enacted to provide a comprehensive regulatory framework for civil aviation safety in Australia. Part 39 of the Regulations, in particular, focuses on airworthiness directives (ADs), which are legally enforceable rules designed to address safety issues in aircraft operation. The Airworthiness Directive in question, AD/PC-12/27, was introduced to address an unsafe condition identified in Pilatus PC-12 series aeroplanes, specifically those with manufacturer serial numbers MSN 101 up to and including MSN 400. The problem identified was related to potential failures of the flap system's Primary Drive Unit motor contactor, which could cause uncommanded cycling of the flaps due to current surges. This issue was first flagged by the Swiss Federal Office for Civil Aviation (FOCA) and subsequently addressed by the Civil Aviation Safety Authority (CASA) through the issuance of the AD. The policy objective of the AD is to ensure the safe operation of the affected aircraft by requiring specific modifications and updates to the Pilot’s Operating Handbook/Aircraft Flight Manual (POH/AFM) and the flap control system.
Scope and Application
The Airworthiness Directive (AD) issued under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 applies specifically to Pilatus PC-12 and PC-12/45 series aeroplanes with manufacturer serial numbers ranging from MSN 101 up to and including MSN 400. The directive mandates corrective actions to address an identified unsafe condition concerning the flap system Primary Drive Unit motor contactor, which could result in uncommanded cycling of the flaps. The AD requires the insertion of Temporary Revision No 32 in the Pilot’s Operating Handbook/Aircraft Flight Manual (POH/AFM) and the installation of the flap system Primary Drive Unit field control panel along with modifications to the flap control wiring in accordance with specified instructions. Compliance with these requirements must be achieved before further flight after 14 February 2001 for the insertion of the temporary revision, and within 50 hours time in service or 30 days after the effective date of the directive for the installation and wiring modifications, whichever occurs first. The AD is issued by a delegate of the Civil Aviation Safety Authority and becomes effective on 21 February 2001.
Key Provisions
The Civil Aviation Safety Authority (CASA) has issued an Airworthiness Directive (AD) under the Civil Aviation Regulations 1998 (CAR 1998), specifically targeting Pilatus PC-12 series aeroplanes with manufacturer serial numbers (MSN) ranging from 101 to 400. This directive mandates specific actions to address safety concerns related to the flap system Primary Drive Unit (section 39.1 (1)). The directive's applicability section identifies the affected aircraft models and serial numbers, ensuring that all relevant parties are aware of the requirements and compliance deadlines.
The directive outlines two primary requirements for affected aircraft operators. The first requirement is to insert Temporary Revision No 32 into the Pilot’s Operating Handbook/Aircraft Flight Manual (POH/AFM). This temporary revision introduces operational limitations on the flap system to mitigate potential risks. The second requirement is to install the flap system Primary Drive Unit field control panel and modify the flap control wiring in accordance with the instructions provided in Pilatus PC-12 service bulletin 27-011 Revision 1 dated 26 January 2001. Once Requirement 2 is fulfilled, Temporary Revision No 32 can be removed from the POH/AFM. The directive also references FOCA Switzerland AD HB 2001-070, providing additional context and alignment with international safety standards.
Aircraft operators must adhere to strict compliance timelines to ensure safety. For Requirement 1, the temporary revision must be inserted before further flight after 14 February 2001. For Requirement 2, the installation and modification must be completed within 50 hours of time in service or 30 days after the effective date of the directive, whichever comes first. Failure to comply with these deadlines could result in serious safety risks, as the directive was issued in response to findings of potential uncommanded flap cycling due to surges in the motor coil power.
Breaches of the AD requirements could result in civil or criminal penalties. The Civil Aviation Regulations 1998 impose stringent obligations on aircraft operators to ensure compliance with airworthiness directives. Non-compliance could lead to enforcement actions, including fines and potential criminal charges. The specific penalties are not detailed in the AD itself but can be substantial under the broader regulatory framework, reflecting the serious nature of aviation safety regulations.