Document ID: FAA-2013-0025-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: PILATUS Aircraft Ltd. Airplanes
Posted Date: 2013-01-18T05:00Z

[Federal Register Volume 78, Number 13 (Friday, January 18, 2013)]
[Rules and Regulations]
[Pages 4053-4055]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-00894]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0025; Directorate Identifier 2012-CE-048-AD; 
Amendment 39-17320; AD 2013-01-06]
RIN 2120-AA64

Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for PILATUS 
Aircraft Ltd. Model PC-7 airplanes. This AD results from mandatory 
continuing airworthiness information (MCAI) issued by the aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as cracks in the engine mount fittings caused by stress 
corrosion. We are issuing this AD to require actions to address the 
unsafe condition on these products.

DATES: This AD is effective February 7, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 7, 
2013.
    We must receive comments on this AD by March 4, 2013.

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 AD, contact PILATUS 
AIRCRAFT LTD., Customer Technical Support (MCC), P.O. Box 992, CH-6371 
Stans, Switzerland; telephone: +41 (0)41 619 67 74; fax: 41 (0)41 619 
67 73; Internet: http://www.pilatus-aircraft.com or email: 
aircraft.com">Techsupport@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 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,

[[Page 4054]]

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:

Discussion

    The Federal Office of Civil Aviation (FOCA), which is the aviation 
authority for Switzerland, has issued FOCA AD HB-2012-009, dated 
December 20, 2012 (referred to after this as ``the MCAI''), to correct 
an unsafe condition for the specified products. The MCAI states:

    This Airworthiness Directive (AD) is prompted due to the 
discovery of cracks in the engine mount fittings. The cracks are 
caused by stress corrosion. It is possible for stress corrosion 
cracks to occur on engine mount fittings initially made of aluminium 
alloy AA2024-T351. Later in production, the material specification 
was changed to aluminium alloy AA2124-T851 to decrease the risk of 
stress corrosion. The Part Number (P/N) of the engine mount fittings 
remained the same.
    Such a condition, if left uncorrected, could lead to failure of 
the engine mount fittings and possible failure of the engine 
attachment.
    In order to correct and control the situation, this AD requires 
a one-time check to identify the material specification and inspect 
those affected engine mount fittings that are made of aluminium 
alloy AA2024-T351. Any engine mount fittings found to be cracked 
must be reported to Pilatus prior to further flight.

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

Relevant Service Information

    PILATUS Aircraft Ltd. has issued PILATUS PC-7 Service Bulletin No. 
53-008, dated November 30, 2012. 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 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 issuing this AD because we 
evaluated all information provided by the State of Design Authority and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

Interim Action

    We consider this AD interim action. The type certificate holder is 
looking at repetitive inspection intervals to be done through the 
maintenance program. When these intervals are established, we may take 
additional rulemaking action to mandate the repetitive inspections.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
stress corrosion cracking in the engine mount area presents a critical 
safety of flight condition that requires inspection to ensure that the 
unsafe condition is mitigated. Therefore, we determined that notice and 
opportunity for public comment before issuing this AD are impracticable 
and that good cause exists for making this amendment effective in fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2013-0025; Directorate 
Identifier 2012-CE-048-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD will affect 15 products of U.S. registry. 
We also estimate that it would take about 7 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts would cost about $0 per product.
    Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $8,925, or $595 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 10 work-hours and require parts costing $5,000, for a cost 
of $5,850 per product. We have no way of determining the number of 
products that may need these actions.

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 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 that this AD:
    (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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

[[Page 4055]]

     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:

2013-01-06 PILATUS Aircraft Ltd.: Amendment 39-17320; Docket No. 
FAA-2013-0025; Directorate Identifier 2012-CE-048-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective February 7, 
2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to PILATUS Aircraft Ltd. Models PC-7 airplanes, 
serial numbers 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) issued by the aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. We are issuing this AD to detect and correct cracks in the 
engine mount fittings.

(f) Actions and Compliance

    Unless already done, do the following actions.
    (1) Within the next 90 days after February 7, 2013 (the 
effective date of this AD), perform a conductivity test to identify 
the material specification of the engine mount fittings (part number 
(P/N) 112.35.07.152) following paragraph 3.B. of PILATUS Aircraft 
Ltd. PILATUS PC-7 Service Bulletin No. 53-008, dated November 30, 
2012.
    (2) If during the conductivity test required by paragraph (f)(1) 
of this AD, engine mount fittings made of aluminum alloy AA2024-T351 
are found, within the next 90 days after February 7, 2013 (the 
effective date of this AD), do the inspection following paragraph 
3.C. of PILATUS Aircraft Ltd. PILATUS PC-7 Service Bulletin No. 53-
008, dated November 30, 2012.
    (3) If during the inspection required by paragraph (f)(2) of 
this AD, any crack is found in the engine mount fittings, before 
further flight, contact Pilatus Customer Technical Support (MCC) for 
further instructions at P.O. Box 992, CH-6371 Stans, Switzerland; 
telephone: +41 (0)41 619 67 74; fax: 41 (0)41 619 67 73; Internet: 
http://www.pilatus aircraft.com or email: aircraft.com">Techsupport@pilatus-aircraft.com.

(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 Swiss MCAI Federal Office of Civil Aviation (FOCA) AD 
HB-2012-009, dated December 20, 2012; and PILATUS Aircraft Ltd. 
PILATUS PC-7 Service Bulletin No. 53-008, dated November 30, 2012, 
for related information.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) PILATUS Aircraft Ltd. PILATUS PC-7 Service Bulletin No. 53-
008, dated November 30, 2012.
    (ii) Reserved.
    (3) For PILATUS Aircraft Ltd. service information identified in 
this AD, contact PILATUS AIRCRAFT LTD., Customer Technical Support 
(MCC), P.O. Box 992, CH-6371 Stans, Switzerland; telephone: +41 
(0)41 619 67 74; fax: 41 (0)41 619 67 73; Internet: http://www.pilatus aircraft.com or email: aircraft.com">Techsupport@pilatus-aircraft.com.
    (4) You may view this service information at 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/index.html.

    Issued in Kansas City, Missouri, on January 11, 2013.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-00894 Filed 1-17-13; 8:45 am]
BILLING CODE 4910-13-P