AD/PC-12/27 Amdt 1 - Flap System Limitation (Cth)

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.