2018-27899. Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Model PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, and PC-6-H2 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated 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 sheared or missing rivets on the horizontal stabilizer hinge bracket assemblies. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

DATES:

We must receive comments on this proposed AD by February 11, 2019.

ADDRESSES:

You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
• Fax: [phone].
• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
• Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact PILATUS Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH-6371 Stans, Switzerland; phone: [phone]; fax: [phone]; email: [e-mail]; internet: http://www.pilatus-aircraft.com. You may review this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call [phone].

Examining the AD Docket

You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-1058; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (telephone [phone]) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT:

Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: [phone]; fax: [phone]; email: [e-mail].

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2018-1058; Product Identifier 2018-CE-051-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments.

We will post all comments we receive, without change, to http://regulations.gov,, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2018-0217, dated October 10, 2018 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:

During a routine inspection, the rivets of the hinge bracket assemblies on a Pilatus PC-6 were found to be sheared or missing. Investigation results identified that this was most likely due to application of too much force to the ends of the horizontal stabilizer during ground handling.

This condition, if not detected and corrected, could lead to failure of the primary horizontal stabilizer load path and consequent separation of the horizontal stabilizer, possibly resulting in loss of control of the aeroplane.

To address this potential unsafe condition, Pilatus Aircraft Ltd issued the SB [service bulletin] to provide applicable inspection instructions.

For the reasons described above, this [EASA] AD requires a one-time inspection of the affected parts and the horizontal stabilizer front spar attachment area and, depending on findings, accomplishment of applicable corrective action(s). This [EASA] AD also requires, before installation, inspection of, and, depending on findings, corrective action(s) on, affected parts held as spare.

The amount of force to the ends of the horizontal stabilizer cannot be quantified; however, fleet experience shows that repetitive pushing or pulling on the horizontal stabilizer to move the airplane on the ground can overload the rivets. Although a root cause could not be determined, due to the severity of separation of a horizontal stabilizer, EASA determined that the corrective actions should be required for other airplanes of the same type design.

Pilatus Aircraft Ltd. had previously considered the small size of the original “DO NOT PUSH” markings and the significant chance of the markings being over-sprayed during a respray. As a result, Pilatus Aircraft Ltd. issued a service bulletin to specify replacing the smaller markings with new, larger placards. The FAA proposes to require these placards in the NPRM.

You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-1058.

Related Service Information Under 1 CFR Part 51

Pilatus Aircraft Ltd. has issued PC-6 Service Bulletin No. 55-004, dated July 2, 2018. The service information contains procedures for inspecting the left-hand and right-hand horizontal stabilizer hinge bracket assemblies and, if any discrepancies are found, repairing or replacing any damaged rivets and screws. Pilatus Aircraft Ltd. has also issued PC-6 Service Bulletin No. 55-002, Revision. No. 1, dated February 18, 2016. This service information contains procedures for inspecting and repairing the horizontal stabilizer attachment hardware and installing four “DO NOT PUSH” placards. 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.

FAA's Determination and Requirements of the Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

We have reviewed the MCAI and, in general, agree with the substance. The MCAI AD does not require installing “DO NOT PUSH” placards. We have added that requirement to this proposed AD.

Costs of Compliance

We estimate that this proposed AD would affect 30 products of U.S. registry. We also estimate that it would take about 9 work-hours per product to comply with the inspection and placard requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $200 per product.

Based on these figures, we estimate the cost of the proposed inspection and placard requirements on U.S. operators to be $28,950, or $965 per product.

In addition, we estimate the following to do any necessary follow-on actions: Each rivet replacement would take 2 work-hours, fastener replacement would take 3 work-hours, one hinge bracket assembly replacement would take 9 work-hours, and two hinge bracket assembly replacements would take 15 work-hours. The total estimated cost of parts would be $10,000. We have no way of determining the number of products that may need replacement.

Authority for This Rulemaking

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.

We are 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 is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to small airplanes, gliders, balloons, airships, domestic business jet transport airplanes, and associated appliances to the Director of the Policy and Innovation Division.

Regulatory Findings

We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation:

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

(2) Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),

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

(4) 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.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Incorporation by reference
• Safety

The Proposed Amendment

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

PART 39—AIRWORTHINESS DIRECTIVES

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

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13

[Amended]

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

Pilatus Aircraft Ltd.: Docket No. FAA-2018-1058; Product Identifier 2018-CE-051-AD.

(a) Comments Due Date

We must receive comments by February 11, 2019.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Pilatus Aircraft Ltd. Model PC-6, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, PC-6/C1-H2, PC-6-H1, PC-6-H2 airplanes, all serial numbers, certificated in any category.

Note 1 to paragraph (c):

These airplanes may also be identified as Fairchild Republic Company airplanes, Fairchild Industries airplanes, Fairchild Heli Porter airplanes, or Fairchild-Hiller Corporation airplanes.

(d) Subject

Air Transport Association of America (ATA) Code 55: Stabilizers.

(e) Reason

This AD was prompted by mandatory continuing airworthiness information (MCAI) originated 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 sheared or missing rivets on the horizontal stabilizer hinge bracket assemblies. We are issuing this AD to prevent failure of the primary horizontal stabilizer load path, which could lead to separation of the horizontal stabilizer and result in loss of control of the airplane.

(f) Actions and Compliance

Unless already done, do the following actions in paragraphs (f)(1) and (2).

(1) Within the next 100 hours time-in-service after the effective date of this AD or within the next 12 months after the effective date of this AD, whichever occurs first:

(i) Inspect the left-hand and the right-hand horizontal stabilizer hinge bracket assemblies for cracks, loose screws and rivets, sheared rivets, missing rivets, and looseness of the electrical bonding strap, and inspect the top and bottom screws at each hinge bracket. Repair or replace any parts with discrepancies before further flight. You must do the actions required by this paragraph by following sections C through G of the Accomplishment Instructions—Part 1—On Aircraft in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-004, dated July 2, 2018.

(ii) Install four “DO NOT PUSH” placards, part number 110.71.06.847 or 110.71.06.848, on the horizontal stabilizer by following section G of the Accomplishment Instructions—Aircraft in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-002, Revision. No. 1, dated February 18, 2016.

(2) After the effective date of this AD, do not install a horizontal stabilizer on any airplane unless it has been inspected as specified in paragraph (f)(1)(i) of this AD and found to be free of discrepancies or all discrepancies have been repaired or replaced.

(g) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Small Airplane Standards 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 ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: [phone]; fax: [phone]; email: [e-mail]. 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.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must instead be accomplished using a method approved by the Manager, Small Airplane Standards Branch, FAA, or the European Aviation Safety Agency (EASA).

(h) Related Information

Refer to MCAI European Aviation Safety Agency AD No. 2018-0217, dated October 10, 2018, for related information. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-1058. For service information related to this AD, contact PILATUS Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH-6371 Stans, Switzerland; phone: [phone]; fax: [phone]; email: [e-mail]; internet: http://www.pilatus-aircraft.com. You may review this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call [phone].

Issued in Kansas City, Missouri, on December 17, 2018.

Melvin J. Johnson,

Aircraft Certification Service, Deputy Director, Policy and Innovation Division, AIR-601.