Document ID: FAA-2008-0070-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12, PC-12/45, and PC-12/47 Airplanes
Posted Date: 2008-01-25T05:00Z

[Federal Register: January 25, 2008 (Volume 73, Number 17)]
[Proposed Rules]               
[Page 4497-4499]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25ja08-18]                         

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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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[[Page 4497]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0070; Directorate Identifier 2007-CE-098-AD]
RIN 2120-AA64

 
Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-12, PC-
12/45, and PC-12/47 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 the 
products listed above. 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. This proposed AD would require 
inserting changes into the airworthiness limitations of the FAA-
approved maintenance program. The proposed AD would require actions 
that are intended to address the unsafe condition described in the 
MCAI.

DATES: We must receive comments on this proposed AD by February 25, 
2008.

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.

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.

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-2008-0070; 
Directorate Identifier 2007-CE-098-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

    Based on the results of a full-scale fatigue test of the pitch trim 
actuator on Pilatus Aircraft Ltd. (Pilatus) PC-12 series airplanes, the 
life-limit is being extended and the time between overhaul (TBO) is 
being reduced. In addition, based on the result of the fatigue test, a 
life-limit of the pitch trim actuator attachment has been established.
    These new limitations have been incorporated into the Airworthiness 
Limitations section of the Pilatus PC-12 Airplane Maintenance Manual 
(AMM) 12-A/AMP-04, chapter 4, revision 10, dated October 26, 2007. The 
life-limit of the pitch trim actuator has been increased based on the 
owner/operator complying with the new reduced TBO of 5,000 hours time-
in-service (TIS) or 5 years, whichever occurs first.
    The new limitations for the pitch trim actuator TBO have been moved 
from Chapter 5: Time Limits/Maintenance Checks, to Chapter 4: 
Structural, Component and Miscellaneous--Airworthiness Limitations. 
Since both chapter 4 and chapter 5 are mandatory within the European 
and Swiss airworthiness systems, it is not necessary for the European 
Aviation Safety Agency (EASA) and the Federal Office of Civil Aviation 
(FOCA) to issue an AD to mandate these new limitations.
    Proposing AD action is the only way the FAA can mandate change to 
the airworthiness limitations section of an FAA-approved maintenance 
program.
    If these new limitations are not mandated, the pitch trim actuator 
and the pitch trim actuator components could fail. This failure could 
lead to an unsafe flying configuration.
    Revisions to the Airworthiness Limitations section of AMM 12-A/AMP-
04 incorporate the following:
     TBO for the pitch trim actuator is reduced from 6,000 
hours TIS or 5 years, whichever occurs first, to 5,000 hours TIS or 5 
years, whichever occurs first;
     The life-limit for the pitch trim actuator is increased 
from 10,000 hours TIS or 13,500 flights, whichever occurs first, to 
20,000 hours TIS or 27,000 flights, whichever occurs first; and
     A life-limit of 10,000 hours TIS is introduced for the 
pitch trim actuator attachment parts.

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 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.

[[Page 4498]]

Differences Between This Proposed AD and the MCAI or Service 
Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect about 500 products 
of U.S. registry. We also estimate that it would take about .5 work-
hour per product to comply with the basic requirements of this proposed 
AD. The average labor rate is $80 per work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $20,000, or $40 per product.
    In addition, we estimate that any necessary follow-on actions (the 
replacements required by the limitations changes) would take about 3.5 
work-hours and require parts costing $11,960, for a cost of $12,240 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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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-2008-0070; Directorate 
Identifier 2007-CE-098-AD.

Comments Due Date

    (a) We must receive comments by February 25, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Models PC-12, PC-12/45, and PC-12/47 
airplanes, all serial numbers, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 27: Flight 
Controls.

Reason

    (e) This 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. We are issuing this AD to mandate new life-limits for the 
pitch trim actuator and pitch trim actuator attachment parts. If 
these new limitations are not mandated, the pitch trim actuator and 
the pitch trim actuator components could fail. This failure could 
lead to an unsafe flying configuration.

Actions and Compliance

    (f) Unless already done, do the following within the next 30 
days after the effective date of this AD.
    (1) Insert unclassified document 12-A/AMP-04, Structural, 
Component and Miscellaneous--Airworthiness Limitations, 12-A-04-00-
00-00A-000A-A, dated October 26, 2007 (Pilatus PC-12 Airplane 
Maintenance Manual, Chapter 4), into the airworthiness limitations 
section of the FAA-approved maintenance program (e.g., maintenance 
manual). You may use any future amendment to this airworthiness 
limitations section provided it does not change the inspection 
intervals, requirements, or the life-limits for the pitch trim 
actuator and pitch trim actuator attachment parts of the document 
referenced above. The owner/operator holding at least a private 
pilot certificate as authorized by section 43.7 of the Federal 
Aviation Regulations (14 CFR 43.7) may do this action. Make an entry 
in the aircraft records showing compliance with this portion of the 
AD following section 43.9 of the Federal Aviation Regulations (14 
CFR 43.9).
    (2) In order to avoid confusion with the new pitch trim actuator 
limitations now contained in chapter 4 (previously contained in 
chapter 5) make pen and ink changes in chapter 5 and line through 
references to limitations for the pitch trim actuator.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) 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. 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, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has

[[Page 4499]]

approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

    Issued in Kansas City, Missouri, on January 17, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-1245 Filed 1-24-08; 8:45 am]

BILLING CODE 4910-13-P