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[Federal Register Volume 77, Number 10 (Tuesday, January 17, 2012)]
[Proposed Rules]
[Pages 2238-2240]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-746]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0018; Directorate Identifier 2011-CE-042-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. Models PC-6, PC-6-H1, PC-6-H2, 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, and PC-6/C1-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 loose elevator and rudder hinge 
bolts caused by incorrect torquing and locking of the bolts could lead 
to in-flight failure of the elevator or rudder attachment. If not 
corrected, this failure could result in loss of control of the 
airplane. 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 March 2, 2012.

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 Liaison Manager, CH-6371 STANS, 
Switzerland; telephone: +41 (0) 41 619 65 80; fax: +41 (0) 41 619 65 
76; Internet: http://www.pilatus-aircraft.com. You may review copies of 
the 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; 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: 
doug.rudolph@faa.gov.

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-2011-0018; 
Directorate Identifier 2011-CE-042-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 EASA 
AD No. 2011-0230, dated December 9, 2011 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    A case of loss of elevator and rudder hinge bolts on a PC-6 
aeroplane has been reported.
    The results of the investigations indicate that the elevator and 
rudder hinge bolt loss are suspected to have been caused by an 
incorrect torque and locking of the bolts.
    This condition, if not detected and corrected, could lead to in-
flight failure of the elevator or rudder attachment, possibly 
resulting in loss of control of the aeroplane.
    For the reasons described above, this AD requires the 
installation of a new locking screw and the modification of the 
installation of the hinge bolt.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Pilatus Aircraft Ltd. has issued PC-6 Service Bulletin No. 55-001, 
Rev. No. 1, dated November 25, 2011. The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI.

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

[[Page 2239]]

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.

Costs of Compliance

    We estimate that this proposed AD will affect 50 products of U.S. 
registry. We also estimate that it would take about 5 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $100 per product.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $26,250, or $525 per product.

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

    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]

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

Pilatus Aircraft Ltd.: Docket No. FAA-2011-0018; Directorate 
Identifier 2011-CE-042-AD.

(a) Comments Due Date

    We must receive comments by March 2, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Pilatus Aircraft Ltd. Models PC-6, PC-6-Hl, 
PC-6-H2, PC-6/350, PC-6/350-Hl, PC-6/350-H2, PC-6/A, PC-6/A-Hl, PC-
6/A-H2, PC-6/B-H2, PC-6/Bl-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, 
and PC-6/Cl-H2 airplanes, all manufacturer serial numbers (MSN), and 
MSN 2001 through 2092, certificated in any category. These airplanes 
are also identified as Fairchild Republic Company PC-6 airplanes, 
Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 
airplanes, or Fairchild-Hiller Corporation PC-6 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by loose elevator and rudder hinge bolts 
caused by incorrect torquing and locking of the bolts. We are 
issuing this AD to prevent in-flight failure of the elevator or 
rudder attachment, which could result in loss of control of the 
airplane.

 (f) Actions and Compliance

    Unless already done, do the following actions:
    (1) For airplanes that have not been modified before the 
effective date of this AD following Pilatus Aircraft Ltd. PC-6 
Service Bulletin No. 55-001 at initial issue, within 2 months after 
the effective date of this AD, install new elevator and rudder hinge 
bolt locking screws and modify the installation of the hinge bolt 
following the Accomplishment Instructions in Pilatus Aircraft Ltd. 
PC-6 Service Bulletin No. 55-001, Rev. No. 1, dated November 25, 
2011.
    (2) For airplanes that have been modified before the effective 
date of this AD following Pilatus Aircraft Ltd. PC-6 Service 
Bulletin No. 55-001 at initial issue, within 6 months after the 
effective date of this AD, install new elevator and rudder hinge 
bolt locking screws following the Accomplishment Instruction of 
Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 55-001, Rev. No. 1, 
dated November 25, 2011.

(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 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: 
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.
    (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 MCAI European Aviation Safety Agency (EASA) AD No. 
2011-0230, dated December 9, 2011, and Pilatus Aircraft Ltd.

[[Page 2240]]

PC-6 Service Bulletin No. 55-001, Rev. No. 1, dated November 25, 
2011, for related information. For service information related to 
this AD, contact PILATUS AIRCRAFT LTD., Customer Liaison Manager, 
CH-6371 STANS, Switzerland; telephone: +41 (0) 41 619 65 80; fax: 
+41 (0) 41 619 65 76; Internet: http://www.pilatus-aircraft.com. You 
may review copies of the 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 January 10, 2012.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-746 Filed 1-13-12; 8:45 am]
BILLING CODE 4910-13-P
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