AD 2021-10-28 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

Makes named: pilatus. Models named: PC-24. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Pilatus Aircraft Ltd. Model PC-24 airplanes, all serial numbers, certificated in any category.

(1) Before further flight, unless already done, revise the ALS of the existing AMM or instructions for continued airworthiness (ICA) for your airplane by incorporating the following documents. (i) Airworthiness Limitations, AMM data module PC24-A-A04-00-0000-00A-040A-A, Issue 008, Revision 00, dated May 26, 2020, from Chapter 04, Airworthiness Limitations, Pilatus PC-24 Aircraft Maintenance Manual (PC-24 AMM) Report 02378, Issue 005, Revision 19, dated May 26, 2020. (ii) Mandatory structural inspection items, AMM data module PC24-A-A04-20-0000-00A-000A-A, Issue 005, Revision 00, dated May 26, 2020, from Chapter 04, Airworthiness Limitations, Pilatus PC-24 Aircraft Maintenance Manual (PC-24 AMM) Report 02378, Issue 005, Revision 19, dated May 26, 2020. (iii) Certification maintenance requirements, AMM data module PC24-A-A04-30-0000-00A-000A-A, Issue 007, Revision 00, dated October 14, 2019, from Chapter 04, Airworthiness Limitations, Pilatus PC-24 Aircraft Maintenance Manual (PC-24 AMM) Report 02378, Issue 005, Revision 19, dated May 26, 2020. (iv) Horizontal stabilizer primary trim system secondary power source—Operation test, AMM data module PC24-A-E27-40-0000-01A-320A-A, dated September 25, 2019, from PC-24 AMM Report 02378, Issue 005, Revision 19, dated May 26, 2020. Your ALS must require this procedure for task number AL-27-40-022 in the certification maintenance requirements. Note 1 to paragraph (f)(1) of this AD: Pilatus PC-24 Aircraft Maintenance Manual, Airworthiness Limitations, AMM data module PC24-A-A04-00-0000-00A-040A-A, Issue 008, Revision 00, dated May 26, 2020, is the parent data module for Chapter 04 of the PC-24 AMM and consists of four subsections (sub-data modules). The parent data module and four sub-data modules comprise the complete ALS of Chapter 04, Airworthiness Limitations, Pilatus PC-24 Aircraft Maintenance Manual (PC-24 AMM) Report 02378, Issue 005, Revision 19, dated May 26, 2020. Incorporating Pilatus PC-24 Aircraft Maintenance Manual, Airworthiness Limitations, AMM data module PC24-A-A04-00-0000-00A-040A-A, Issue 008 Revision 00, dated May 26, 2020, and all four subsections listed in Section 1 General, is acceptable, but not required, for compliance with this AD. (2) As of the effective date of this AD, except as provided in paragraph (g) of this AD, no alternative replacement times, inspection intervals, or tasks may be approved for the affected parts. (3) The actions required by paragraph (f)(1) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4), and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.

The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Doug Rudolph, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, MO 64106; phone: (816) 329-4059; fax: (816) 329-4090; email: doug.rudolph@faa.gov . Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.

This AD was prompted by the need to revise the Airworthiness Limitations section (ALS) of the existing aircraft maintenance manual (AMM) to add new and more restrictive tasks for the control column sprocket gear assembly and control wheel column assembly, to address the new limit of validity and update the usage assumptions and conditions for operations on unpaved and grass runways, and to correct an error in the horizontal stabilizer primary trim system secondary power source operational test. The FAA is issuing this AD to prevent reduction in the structural integrity of the airframe and components, as well as an unrecognized failure of the manual pitch trim. These conditions, if not addressed, could result in loss of airplane control.

None.