Airworthiness Directive · Amendment 39-14108 · Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This AD affects Models PC-12 and PC-12/45 airplanes, Manufacturers Serial Numbers (MSN) 101 through 620, that are certificated in any category.
The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to insert a temporary revision into the Limitations Section of the Pilot Operating Handbook (POH). This AD also requires you to replace the pitch actuator with an improved design pitch actuator and make the necessary wiring and circuit breaker changes, as applicable. Installing the improved design pitch actuator terminates the need for the temporary revision in the POH. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to prevent an out-of-trim condition from occurring when the flaps are at a 40-degree flight phase and the pilot disconnects the autopilot. This condition could lead to reduced ability to control the airplane.
To address this problem, you must do the following:
| Actions | Compliance | Procedures |
|---|---|---|
| (1) Insert Temporary Revision No. 11 (Report No. 02211) or No. 40 (Report No. 01973-001) into the Limitations Section of the PC-12 Pilot's Operating Handbook (POH) | Within the next 90 days after July 18, 2005 (the effective date of this AD), unless already done | The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may modify the POH as specified in paragraph (e)(1) of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). |
| (2) Replace the pitch actuator, part number (P/N) 985.92.03.161, with an improved design pitch actuator, P/N 985.92.03.164; and make the associated wiring and circuit breaker changes (as applicable) | Within the next 18 months after July 18, 2005 (the effective date of this AD), unless already done | Follow Pilatus PC12 Service Bulletin No. 22-004, dated December 21, 2004. |
| (3) Remove the Temporary Revision to the POH specified in paragraph (e)(1) of this AD after the pitch actuator is replaced as required in paragraph (e)(2) of this AD | Before further flight after the pitch actuator is replaced with an improved design pitch actuator | The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may modify the POH as specified in paragraph (e)(3) of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). |
| (4) Do not install a P/N 985.92.03.161 pitch actuator | As of July 18, 2005 (the effective date of this AD) | Not applicable. |
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
