81 FR 37166 - Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 111 (June 9, 2016)

We propose to adopt a new airworthiness directive (AD) for PILATUS Aircraft Ltd. Model PC-7 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 stress corrosion cracking on the main frame on frame 11 left and right fittings. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

[Federal Register Volume 81, Number 111 (Thursday, June 9, 2016)]
[Proposed Rules]
[Pages 37166-37168]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-13544]


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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 81, No. 111 / Thursday, June 9, 2016 / 
Proposed Rules

[[Page 37166]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7026; Directorate Identifier 2016-CE-016-AD]
RIN 2120-AA64


Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
PILATUS Aircraft Ltd. Model PC-7 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 stress corrosion cracking on the main frame on frame 11 
left and right fittings. 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 July 25, 2016.

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: (202) 493-2251.
     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: +41 (0)41 619 67 74; fax: +41 (0)41 
619 67 73; email: aircraft.com">[email protected]aircraft.com; internet: http://
www.pilatus-aircraft.com. You may review this referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148.

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-2016-
7026; or in person at the Docket Management Facility 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 the Docket 
Office (telephone (800) 647-5527) 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 Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: 
[email protected].

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-2016-7026; 
Directorate Identifier 2016-CE-016-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 Federal Office of Civil Aviation (FOCA), which is the aviation 
authority for Switzerland, has issued AD HB-2016-001, dated May 17, 
2016 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for PILATUS Aircraft Ltd. Model PC-7 airplanes and was based 
on mandatory continuing airworthiness information originated by an 
aviation authority of another country. The MCAI states:

    This Airworthiness Directive (AD) is prompted due to a report of 
Stress Corrosion Cracking (SCC) on the Main Frame on Frame (FR) 11 
left fitting Part Number (P/N) 112.35.07.489 and right fitting P/N 
112.35.07.490.
    Such a condition, if left uncorrected, could lead to potential 
loss of the horizontal stabilizer.
    In order to correct and control the situation, this AD requires 
a one-time check to identify the material specification and inspect 
the affected areas of the airframe that are made of aluminum alloy 
AA2024-T351. Any structural parts of the aircraft structure found to 
be cracked must be reported to Pilatus prior to further flight

    You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7026.

Related Service Information Under 1 CFR Part 51

    PILATUS Aircraft Ltd. has issued PILATUS Aircraft Ltd. PC-7 Service 
Bulletin No: 53-013; and PILATUS Aircraft Ltd. PC-7 Service Bulletin 
No: 53-014, both dated February 25, 2016. PILATUS Aircraft Ltd. PC-7 
Service Bulletin No: 53-013, dated February 25, 2016, describes 
procedures for initial and repetitive inspection of the main frame FR11 
left and right fittings for stress corrosion cracking; and PILATUS 
Aircraft Ltd. PC-7 Service Bulletin No: 53-014, dated February 25, 
2016, describes procedures for replacement of the main frame FR11 left 
and right fittings when necessary. 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 of this NPRM.

[[Page 37167]]

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.

Differences Between This Proposed AD and the Service Information

    The service bulletin requires repetitive inspections by reference 
in a note, which the FAA cannot mandate, so the intent of the note has 
been incorporated into a required action for this proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 19 products of U.S. 
registry. We also estimate that it would take about 3 work-hours per 
product to check the material specification of the fittings and 11 
work-hours per product to inspect the 2014-T351 fittings as required in 
order to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $17,765, or $935 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 19 work-hours and require parts costing $5,000 for a cost of 
$1,615 per product. We have no way of determining the number of 
products that may need these actions.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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.

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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

Pilatus Aircraft Limited: Docket No. FAA-2016-7026; Directorate 
Identifier 2016-CE-016-AD.

(a) Comments Due Date

    We must receive comments by July 25, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Pilatus Aircraft Limited Model PC-7 
airplanes, manufacturer serial numbers (MSN) 101 through 618, 
certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 53: Fuselage.

(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 stress corrosion 
cracking on the main frame on frame 11 left and right fittings, 
which can cause potential loss of the horizontal stabilizer. We are 
issuing this proposed AD to detect and correct stress corrosion 
cracking on the frame 11 left and right fittings and replace if 
necessary.

(f) Actions and Compliance

    Unless already done, do the actions in paragraphs (f)(1) through 
(f)(4) of this AD:
    (1) Within the next 120 days after the effective date of this 
AD, check the material specification of the Frame (FR) 11 left 
fitting part number (P/N) 112.35.07.489 and the FR 11 right fitting 
P/N 112.35.07.490 following the Accomplishment Instructions in 
paragraph 3.B. of PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 
53-013, dated February 25, 2016.
    (2) If fittings made of aluminum alloy AA2124-T851 are found 
during the inspection required by paragraph (f)(1) of this AD, 
within 30 days after the inspection or within the next 30 days after 
the effective date of this AD, whichever occurs later, report the 
inspection results following the reporting requirements in paragraph 
3.D. of PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 53-013, 
dated February 25, 2016.
    (3) If fittings made of aluminum alloy AA2024-T351 are found 
during the inspection required by paragraph (f)(1) of this AD, 
before further flight, and repetitively thereafter at intervals not 
to exceed 12 months, inspect FR 11 left fitting, P/N 112.35.07.489 
and the FR 11 right fitting, P/N 112.35.07.490, for cracks following 
the Accomplishment Instructions in paragraph 3.C. of PILATUS 
Aircraft Ltd. PC-7 Service Bulletin No: 53-013, dated February 25, 
2016.
    (4) If cracks are found during any inspection required in 
paragraph (f)(3) of this AD, before further flight, replace the 
fittings following the Accomplishment Instructions in paragraph 3 of 
PILATUS Aircraft Ltd. PC-7 Service Bulletin No: 53-014, dated 
February 25, 2016.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs

[[Page 37168]]

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 Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; 
email: [email protected]. 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, a federal agency may not conduct or sponsor, and a person 
is not required to respond to, nor shall a person be subject to a 
penalty for failure to comply with a collection of information 
subject to the requirements of the Paperwork Reduction Act unless 
that collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(h) Related Information

    Refer to Federal Office of Civil Aviation (FOCA) AD HB-2016-001, 
dated May 17, 2016, for related information. You may examine the 
MCAI on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2016-7026. For service information 
related to this AD, contact PILATUS Aircraft Ltd., Customer 
Technical Support (MCC), P.O. Box 992, CH-6371 Stans, Switzerland; 
phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67 73; email: 
aircraft.com">[email protected]aircraft.com; internet: http://www.pilatus-
aircraft.com. You may review this referenced service information at 
the FAA, Small Airplane Directorate, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material 
at the FAA, call (816) 329-4148.


    Issued in Kansas City, Missouri, on June 2, 2016.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-13544 Filed 6-8-16; 8:45 am]
 BILLING CODE 4910-13-P