Document ID: chunk:federal_register_of_legislation:F2006B06076:body:0:p1
Version: federal_register_of_legislation:F2006B06076
Segment Type: other
Provision Reference: 
Character Range: 4–3226

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-12/13 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/PC-12/13
    Amdt 1

    Flap System 1/2001 DM

    Applicability: All PC-12 and PC-12/45 aircraft.

                 Requirement:  1. Inspect flap actuators to check axial end-play and backlash of each flap actuator in accordance with the Pilatus PC12 Maintenance Manual, Temporary Revision (TR) 27-13, dated 30 April 2000.

                 If the acceptance criteria specified in TR 27-13 cannot be met, replace defective actuators before further flight.

                 Compliance with a later revision of the Pilatus PC12 Maintenance Manual approved by FOCA satisfies this Directive.

                 Note 1: Switzerland FOCA AD's HB 98-460 and HB 2000-443 refer.

                 2.    Modify the flap system in accordance with Pilatus PC-12 Service Bulletin (SB) 27- 008, Revision 2, dated 13 September 2000.

                 Note 2: Switzerland FOCA AD HB 2000-443 refers.

                 3.    Amend the PC-12 Pilot's Operating Handbook (POH) with POH/AFM Temporary Revision No. 15 - MODIFIED FLAP SYSTEM - dated 3 April 2000.

                 4.    For aircraft incorporating SB 27-008 as of the effective date of this Directive, inspect the Flap Control and Warning Unit (FCWU) to determine its serial number and remove from service any FCWU, Part No. FCWU99-3 with serial number 100,000 or less in accordance with Pilatus PC-12 Service Bulletin (SB) 27-012, dated 13 September 2000. From the effective date of this Amendment, no such FCWU may be installed on any model Pilatus PC-12 aircraft.

                 Note 3: Switzerland FOCA AD HB 2000-444 refers
 COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Compliance: 1. (a) Pre - SB 27-008 Configuration Flap System:

             Within 65 landings following the last backlash inspection per the original issue of this Directive and, thereafter, at periods specified in Pilatus PC12 Maintenance Manual, Temporary Revision 04-05, dated 30 April 2000.

             (b) Post - SB 27-008 Configuration Flap System:

             Concurrent with the incorporation of SB 27-008 and thereafter at the intervals specified in the Pilatus PC12 Maintenance Manual, Chapter 05-10-20, Time Limited Inspection Requirements.

2.    Unless previously accomplished