AD 2020-22-17

This AD is effective December 14, 2020.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 14, 2020.

For service information identified in this final rule, contact Pilatus Aircraft Ltd., Customer Support General Aviation, CH-6371 Stans, Switzerland, telephone: +41 848 24 7 365, techsupport.ch@pilatus-aircraft.com, https://www.pilatus-aircraft.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call 816-329-4148. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-0719.

Doug Rudolph, Aerospace Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: doug.rudolph@faa.gov.

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to Pilatus Model PC-24 airplanes with a certain part-numbered flexible saddle clamp installed between frame 34 and 36. The NPRM published in the Federal Register on July 30, 2020 (85 FR 45810). The NPRM proposed to require actions to correct the unsafe condition on the specified products and was prompted by MCAI originated by the European Union Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. EASA issued AD No. 2019-0240, dated September 25, 2019 (referred to after this as “the MCAI”), which states:

An occurrence was reported where, during maintenance, when system pressure was applied to a motive-flow fuel pipe, the aft fuel pipe was found to move to the end stop within the coupling. When system pressure was released, the aft fuel pipe returned to its point of origin. This movement can cause damage to the O-rings.

This condition, if not corrected, could lead to a fuel leak and consequently a fuel contamination of the rear fuselage, which, in combination with an ignition source in this area, could possibly result in a fuel fire or fuel vapour explosion and consequent loss of the aeroplane.

To address this potential unsafe condition, Pilatus issued the [service bulletin] SB to provide modification instructions.

For the reason described above, this [EASA] AD requires replacement of affected parts with serviceable parts, as defined in this AD, and prohibits (re-) installation of affected parts.

You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-0719.

The FAA gave the public the opportunity to participate in developing this final rule. The FAA received no comments on the NPRM or on the determination of the cost to the public.

The FAA reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed.

The FAA reviewed Pilatus PC-24 Service Bulletin No. 28-002, dated May 3, 2019. The service information contains procedures for replacing the two flexible saddle clamps on the left-hand (LH) motive-flow fuel pipe and the two flexible saddle clamps on the right-hand (RH) motive-flow fuel pipe with fixed saddle clamps. This service information also contains procedures for replacing the four O-rings on the LH and RH motive-flow fuel pipes. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section.

The FAA estimates that this AD will affect 16 products of U.S. registry. The FAA also estimates that it will take about 7 work-hours per product to comply with the requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $5,000 per product.

Based on these figures, the FAA estimates the cost of the AD on U.S. operators will be $89,520 or $5,595 per product.

According to the manufacturer, all or some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. The FAA does not control warranty coverage for affected individuals. As a result, the FAA has included all costs in this cost estimate.

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority.

The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this AD:

(1) Is not a “significant regulatory action” under Executive Order 12866,

(2) Will not affect intrastate aviation in Alaska, and

(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

1. The authority citation for part 39 continues to read as follows:

2. The FAA amends § 39.13 by adding the following new airworthiness directive: