Airworthiness Directive · Amendment 39-16140 · Landing gear
PILATUS Aircraft Ltd. Model PC-7 Airplanes
This AD applies to Model PC-7 airplanes, manufacturer serial numbers 101 through 618 that are:
(1) Equipped with main-gear support struts part number (P/N) 532.10.09.039 or P/N 114.48.07.127; and
(2) Certificated in any category.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions:
(1) Within the next 30 hours time-in-service (TIS) after February 1, 2010 (the effective date of this AD) or within the next 30 days after February 1, 2010 (the effective date of this AD), whichever occurs first, visually inspect the left and right main-gear support struts to determine if they have rounded or chamfered clevis lugs. Do the inspection following paragraph 3.A. of Pilatus PC-7 Service Bulletin No. 32-024, Rev. No. 1, dated November 17, 2008.
(2) Based on the results of the inspection required in paragraph (f)(1) of this AD, if the main-gear support strut has rounded clevis lugs, no further action is required except the requirement specified in paragraph (f)(4) of this AD still applies. Make an entry in the airplane logbook to show compliance with this AD. Based on the reports of the results of the inspection required by this AD, further rulemaking action may be taken to mandate repetitive inspections or terminating action.
(3) Based on the results of the inspection required in paragraph (f)(1) of this AD, if the main-gear support strut has chamfered clevis lugs, before further flight do a Non-Destructive Inspection (NDI). Do the NDI following paragraphs 3.B. through 3.E. of Pilatus PC-7 Service Bulletin No. 32-024, Rev. No. 1, dated November 17, 2008.
(i) If cracks are found during the inspection required in paragraph (f)(3) of this AD:
(A) Before further flight after the inspection, replace any cracked main-gear support struts with new main-gear support struts, P/N 532.10.09.128. Do the replacement following Pilatus PC-7 Service Bulletin No. 32-025, Rev. No. 1, dated November 17, 2008.
(B) Within the next 10 days after the inspection, report the cracks to Pilatus Aircraft LTD., Customer Liaison Manager, CH-6371 STANS, Switzerland, using the Crack Report Form (Figure 4) in Pilatus PC-7 Service Bulletin No. 32-024, Rev. No. 1, dated November 17, 2008.
(ii) If no cracks are found during the inspection required in paragraph (f)(3) of this AD, no further action is required. Make an entry in the airplane logbook to show compliance with this AD.
(4) As of 30 days after February 1, 2010 (the effective date of this AD), do not install any main-gear support struts, P/N 532.10.09.039 or P/N 114.48.07.127, with chamfered clevis lugs.
Note 1: If you have any main-gear support struts, P/N 532.10.09.039 or P/N 114.48.07.127, with chamfered clevis lugs held as spares, you may return them to Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 STANS, Switzerland, for replacement with a new main-gear support strut, P/N 532.10.09.128.
Note 2: This AD differs from the MCAI and/or service information as follows: No differences.
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.
Aircraft
