
[Federal Register Volume 77, Number 138 (Wednesday, July 18, 2012)]
[Proposed Rules]
[Pages 42225-42228]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-17103]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0732; Directorate Identifier 2012-CE-022-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 all 
PILATUS AIRCRAFT LTD. Models PC 12, PC 12/45, PC 12/47, and PC 12/47E 
airplanes that would supersede an existing AD. 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 a need to incorporate new

[[Page 42226]]

revisions into the Limitations section, Chapter 4, of the FAA-approved 
maintenance program (e.g., maintenance manual). The limitations were 
revised to include an inspection of the wing main spar fastener holes 
at rib 6 for cracks. 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 September 4, 
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 Service Manager, CH 6371 STANS, 
Switzerland; telephone: +41 (0)41 619 62 08; fax: +41 (0)41 619 73 11; 
Internet: http://www.pilatus_aircraft.com or email: 
SupportPC12@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-2012-0732; 
Directorate Identifier 2012-CE-022-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://www.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

    On July 1, 2009, we issued AD 2009-14-13, Amendment 39-15963 (74 FR 
34213, July 15, 2009). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2009-14-13, Amendment 39-15963 (74 FR 34213, 
July 15, 2009), Pilatus Aircraft Ltd. has issued revisions to the 
Limitations section of the airplane maintenance manual to include an 
inspection of the wing main spar fastener holes at rib 6 for cracks.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2012-0099, dated June 8, 2012 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:
    The mandatory instructions and airworthiness limitations applicable 
to the Structure and Components of the PC-12 are specified in the 
Aircraft Maintenance Manual (AMM) under Chapter 4. Prompted by a crack 
found on one wing of the aeroplane fleet leader, a more restrictive 
airworthiness limitation was introduced, in that manual, for the 
inspection of the main spar rib 6 strap fastener.
    These documents include the maintenance instructions and/or 
airworthiness limitations developed by Pilatus Aircraft Ltd. and 
approved by EASA. Failure to comply with these instructions and 
limitations could potentially lead to unsafe condition.
    For the reasons described above, this AD requires the 
implementation of more restrictive maintenance instructions and/or 
airworthiness limitations. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Pilatus Aircraft Ltd. has issued Structural and Component 
Limitations--Airworthiness Limitations, document 12 B 04 00 00 00A 000A 
A, dated January 27, 2012; and Structural, Component and 
Miscellaneous--Airworthiness Limitations, document 12 A 04 00 00 00A 
000A A, dated January 27, 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 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.

Costs of Compliance

    We estimate that this proposed AD would affect 678 products of U.S. 
registry. We also estimate that it would take about 3.5 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 $300 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $405,105, or $597.50 per product.
    In addition, we estimate that any necessary follow on actions would 
take about 6 work hours and require parts costing $4,000, for a cost of 
$4,510 per product. We have no way of determining the number of 
products that may need these actions. We also estimate that it would 
take about 12 work hours per product to comply with the addition of the 
wing inspection 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 wing 
inspection on U.S. operators to be $691,560, or $1,020 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 7 work-hours and require parts costing approximately $5,000, 
for a cost of $5,595 per product. We have no way of determining the 
number of products that may need these actions.

[[Page 42227]]

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 removing Amendment 39-15963 (74 FR 
34213, July 15, 2009), and adding the following new AD:

PILATUS AIRCRAFT LTD.: Docket No. FAA-2012-0732; Directorate 
Identifier 2012-CE-022-AD.

(a) Comments Due Date

    We must receive comments by September 4, 2012.

(b) Affected ADs

    This AD supersedes AD 2009-14-13, Amendment 39-15963 (74 FR 
34213, July 15, 2009).

(c) Applicability

    This AD applies to Pilatus Aircraft LTD. Models PC 12, PC 12/45, 
PC 12/47, and PC-12/47E airplanes, all manufacturer serial numbers 
(MSNs), certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 05: Time Limits.

(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 a need to 
incorporate new revisions into the Limitations section, Chapter 4, 
of the FAA-approved maintenance program (e.g., maintenance manual). 
The limitations were revised to include an inspection of the wing 
main spar fastener holes at rib 6 for cracks. These actions are 
required to ensure the continued operational safety of the affected 
airplanes.

(f) Actions and Compliance

    Unless already done, do the following actions:
    (1) For Models PC 12 and PC 12/45 airplanes, MSNs 101 through 
299: Within the next 100 hours time in service (TIS) after August 
19, 2009 (the effective date retained from AD 2009-14-13, Amendment 
39-15963 (74 FR 34213, July 15, 2009)) or 1 year after August 19, 
2009 (the effective date retained from AD 2009-14-13), whichever 
occurs first, replace the torque tube P/N 532.50.12.047 with torque 
tube P/N 532.50.12.064 following PILATUS AIRCRAFT LTD. Service 
Bulletin No: 32 021, dated November 21, 2008.
    (2) For all airplanes: As of the effective date of this AD, do 
not install torque tube P/N 532.50.12.047.
    (3) For all airplanes: Before further flight after the effective 
date of this AD, insert Structural, Component and Miscellaneous--
Airworthiness Limitations, document 12 A 04 00 00 00A 000A A, dated 
January 27, 2012 (for Models PC 12, PC 12/45, PC 12/47), and 
Structural and Component Limitations--Airworthiness Limitations, 
document 12 B 04 00 00 00A 000A A, dated January 27, 2012 (for Model 
PC 12/47E), into the Limitations section of the FAA approved 
maintenance program (e.g., maintenance manual). The limitations 
section revision does the following:
    (i) Establishes an inspection of the wing main spar fastener 
holes at rib 6,
    (ii) Specifies replacement of components before or upon reaching 
the applicable life limit, and
    (iii) Specifies accomplishment of all applicable maintenance 
tasks within certain thresholds and intervals.
    (4) For all airplanes: If no compliance time is specified in the 
documents listed in paragraph (f)(3) of this AD when doing any 
corrective actions where discrepancies are found as required in 
paragraph (f)(3)(iii) of this AD, do these corrective actions before 
further flight after doing the applicable maintenance task.
    (5) For all airplanes: During the accomplishment of the actions 
required in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii) of 
this AD, if a discrepancy is found that is not identified in the 
documents listed in paragraph (f)(3) of this AD, before further 
flight after finding the discrepancy, contact Pilatus Aircraft Ltd. 
at the address specified in paragraph (h) of this AD for a repair 
scheme and incorporate that repair scheme.

    Note 1 to paragraph (f)(3) of this AD: Structural, Component and 
Miscellaneous--Airworthiness Limitations, document 12 A 04 00 00 00A 
000A A, dated January 27, 2012 (for Models PC 12, PC 12/45, PC 12/
47) is part of Chapter 4 of the Airplane Maintenance Manual (AMM) 
report 02049, issue 25, dated January 25, 2012.


    Note 2 to paragraph (f)(3) of this AD: Structural and Component 
Limitations--Airworthiness Limitations, document 12 B 04 00 00 00A 
000A A, dated January 27, 2012 (for Model PC 12/47E) is part of 
Chapter 4 of the AMM report 02300, issue 8, dated January 25, 2012.

(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.
    (i) 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.
    (ii) AMOCs approved for AD 2009-14-13, Amendment 39-15963 (74 FR 
34213, July 15, 2009) are not approved as AMOCs for this AD.
    (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.

[[Page 42228]]

    (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. 
2012-0099, dated June 8, 2012; Structural and Component 
Limitations--Airworthiness Limitations, document 12 B 04 00 00 00A 
000A A, dated January 27, 2012; Structural, Component and 
Miscellaneous--Airworthiness Limitations, document 12 A 04 00 00 00A 
000A A, dated January 27, 2012; and PILATUS AIRCRAFT LTD. Service 
Bulletin No: 32 021, dated November 21, 2008, for related 
information. For service information related to this AD, contact 
PILATUS AIRCRAFT LTD., Customer Service Manager, CH 6371 STANS, 
Switzerland; telephone: +41 (0)41 619 62 08; fax: +41 (0)41 619 73 
11; Internet: http://www.pilatus_aircraft.com or email: 
SupportPC12@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 July 5, 2012.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012-17103 Filed 7-17-12; 8:45 am]
BILLING CODE 4910-13-P


