[Federal Register Volume 70, Number 56 (Thursday, March 24, 2005)]
[Proposed Rules]
[Pages 15019-15022]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-5801]



[[Page 15019]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Pilatus Aircraft Ltd. (Pilatus) Model PC-6 airplanes. This 
proposed AD would require you to repetitively inspect the stabilizer-
trim attachment and structural components for cracks, corrosion, and 
discrepancies and replace any defective part with a new part. This 
proposed AD would also require you to replace all Fairchild connecting 
pieces, part number 6232.0026.XX, with a Pilatus connecting piece. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) issued by the airworthiness authority for Switzerland. We are 
issuing this proposed AD to detect and correct defective stabilizer-
trim attachments and surrounding structural components, which could 
result in failure of the stabilizer-trim attachment. This failure could 
lead to loss of control of the airplane.

DATES: We must receive any comments on this proposed AD by April 25, 
2005.

ADDRESSES: Use one of the following to submit comments on this proposed 
AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: 1-202-493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    To get the service information identified in this proposed AD, 
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576; or 
from Pilatus Business Aircraft Ltd., Product Support Department, 11755 
Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-9099; 
facsimile: (303) 465-6040.
    To view the comments to this proposed AD, go to http://dms.dot.gov. 
This is docket number FAA-2005-20515; Directorate Identifier 2005-CE-
09-AD.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

    How do I comment on this proposed AD? We invite you to submit any 
written relevant data, views, or arguments regarding this proposal. 
Send your comments to an address listed under ADDRESSES. Include the 
docket number, ``FAA-2005-20515; Directorate Identifier 2005-CE-09-AD'' 
at the beginning of your comments. We will post all comments we 
receive, without change, to http://dms.dot.gov, including any personal 
information you provide. We will also post a report summarizing each 
substantive verbal contact with FAA personnel concerning this proposed 
rulemaking. Using the search function of our docket Web site, anyone 
can find and read the comments received into any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
This is docket number FAA-2005-20515; Directorate Identifier 2005-CE-
09-AD. You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78) or you 
may visit http://dms.dot.gov.
    Are there any specific portions of this proposed AD I should pay 
attention to? We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of this 
proposed AD. If you contact us through a nonwritten communication and 
that contact relates to a substantive part of this proposed AD, we will 
summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend this 
proposed AD in light of those comments and contacts.

Docket Information

    Where can I go to view the docket information? You may view the AD 
docket that contains the proposal, any comments received, and any final 
disposition in person at the DMS Docket Offices between 9 a.m. and 5 
p.m. (eastern standard time), Monday through Friday, except Federal 
holidays. The Docket Office (telephone 1-800-647-5227) is located on 
the plaza level of the Department of Transportation NASSIF Building at 
the street address stated in ADDRESSES. You may also view the AD docket 
on the Internet at http://dms.dot.gov. The comments will be available 
in the AD docket shortly after the DMS receives them.

Discussion

    What events have caused this proposed AD? The Federal Office for 
Civil Aviation (FOCA), which is the airworthiness authority for 
Switzerland, recently notified FAA that an unsafe condition may exist 
on all Pilatus Model PC-6 airplanes. The FOCA reports that the lower 
attachment bracket of the horizontal stabilizer actuator broke on a PC-
6 airplane. This resulted in an emergency landing outside the airport.
    The FOCA reports two other instances of total failure of the 
stabilizer trim attachment on airplanes in-service.
    What is the potential impact if FAA took no action? If not detected 
and corrected, defects in the stabilizer-trim attachment and 
surrounding structural components could cause the stabilizer-trim 
attachment to fail. This failure could lead to loss of control of the 
airplane.
    Is there service information that applies to this subject? Pilatus 
has issued PC-6 Service Bulletin No. 53-001, dated February 16, 2005.
    What are the provisions of this service information? The service 
bulletin includes procedures for:

--Inspecting the stabilizer-trim attachment and structural components 
(the fitting, the connecting piece, the bearing fork, the bearing 
support assembly, and the auxiliary frame, as applicable) for cracks 
and corrosion;
--Inspecting the diameters of the bolt holes on the actuator 
attachment, fittings, and connecting piece (as applicable);
--Replacing any cracked, corroded, or defective part with a new part; 
and
--Replacing all Fairchild connecting pieces with a Pilatus connecting 
piece.

    What action did the FOCA take? The FOCA classified this service 
bulletin as mandatory and issued Swiss AD

[[Page 15020]]

Number HB-2005-080, effective date March 2, 2005, in order to ensure 
the continued airworthiness of these airplanes in Switzerland.
    Did the FOCA inform the United States under the bilateral 
airworthiness agreement? These Pilatus PC-6 airplanes are manufactured 
in Switzerland and are type-certificated for operation in the United 
States under the provisions of section 21.29 of the Federal Aviation 
Regulations (14 CFR 21.29) and the applicable bilateral airworthiness 
agreement. Fairchild also manufactured these airplanes under a United 
States licensing agreement with Pilatus under the same type 
certificate.
    Under this bilateral airworthiness agreement, the FOCA has kept us 
informed of the situation described above.

FAA's Determination and Requirements of This Proposed AD

    What has FAA decided? We have examined the FOCA's findings, 
reviewed all available information, and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.
    Since the unsafe condition described previously is likely to exist 
or develop on other Pilatus PC-6 airplanes of the same type design that 
are registered in the United States, we are proposing AD action to 
detect and correct defects in the stabilizer-trim attachment and 
surrounding structural components, which could result in failure of the 
stabilizer-trim attachment. This failure could lead to loss of control 
of the airplane.
    What would this proposed AD require? This proposed AD would require 
you to incorporate the actions in the previously-referenced service 
bulletin.
    How does the revision to 14 CFR part 39 affect this proposed AD? On 
July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs FAA's AD system. This regulation 
now includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many airplanes would this proposed AD impact? We estimate that 
this proposed AD affects 41 airplanes in the U.S. registry.
    What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
do the proposed inspections:

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                                                          Total cost per
            Labor cost                  Parts cost           airplane          Total cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
11 work hours x $65 per hour =     Not applicable.....               $715  $715 x 41 = $29,315.
 $715.
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    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed 
inspections. We have no way of determining the number of airplanes that 
may need these replacements:

----------------------------------------------------------------------------------------------------------------
                                                                        Total cost per airplane to replace all
               Labor cost                        Parts cost                             parts
----------------------------------------------------------------------------------------------------------------
10 work hours x $65 = $650.............  $2,000 to replace all       $650 + $2,000 = $2,650.
                                          parts.
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Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
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 AD.

Regulatory Findings

    Would this proposed AD impact various entities? We have 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.
    Would this proposed AD involve a significant rule or regulatory 
action? For the reasons discussed above, I certify that this proposed 
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); 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 summary of the costs to comply with this proposed AD 
and placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket FAA-2005-20515; Directorate Identifier 2005-CE-09-AD'' in 
your request.

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 Federal Aviation Administration 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.

[[Page 15021]]

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Pilatus Aircraft Ltd.: Docket No. FAA-2005-20515; Directorate 
Identifier 2005-CE-09-AD.

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by April 25, 2005.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects Model PC-6 airplanes, all manufacturer 
serial numbers (MSN), that are certificated in any category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Switzerland. We are issuing this proposed AD to detect and correct 
cracks in the stabilizer-trim attachment and surrounding structural 
components, which could result in failure of the stabilizer-trim 
attachment. This failure could lead to loss of control of the 
airplane.

What Must I Do to Address This Problem?

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
Inspect the following:
    (i) the stabilizer-trim
     attachment and
     structural components
     (fitting, connecting
     piece, bearing fork,
     bearing support
     assembly, and auxiliary
     frame, as applicable)
     for cracks and
     corrosion; and
    (ii) the diameters of     Within the next 100   Follow Pilatus PC-6
     the actuator attachment   hours time-in-        Service Bulletin
     bolt holes on the         service (TIS) after   No. 53-001, dated
     fittings, auxiliary       the effective date    February 16, 2005.
     frame, and connecting     of this AD.
     piece (as applicable)     Repetitively
     for discrepancies.        inspect thereafter
                               at intervals not-to-
                               exceed 100 hours
                               TIS even if the
                               part is replaced.
(2) If cracks are found       Replace the           Follow Pilatus PC-6
 during any inspection         defective part        Service Bulletin
 required in paragraph         before further        No. 53-001, dated
 (e)(1)(i) of this AD,         flight after the      February 16, 2005.
 replace the defective part    inspection in which
 with a new part.              cracks are found.
                               After each
                               replacement,
                               continue with the
                               repetitive
                               inspection
                               requirement in
                               paragraph (e)(1) of
                               this AD.
-----------------------------
(3) If corrosion or
 discrepancies are found
 during any inspection
 required in paragraphs
 (e)(1)(i) and (e)(1)(ii) of
 this AD, do the following:
    (i) replace the
     defective part with a
     new part if the
     corrosion or
     discrepancy is beyond
     the repairable limits
     stated in the service
     information; or
    (ii) repair the           Replace or repair     Follow Pilatus PC-6
     defective part if the     the defective part    Service Bulletin
     corrosion or              before further        No. 53-001, dated
     discrepancy is within     flight after the      February 16, 2005.
     the repairable limits     inspection in which
     stated in the service     corrosion or
     information.              discrepancies are
                               found. After each
                               replacement or
                               repair, continue
                               with the repetitive
                               inspection
                               requirement in
                               paragraph (e)(1) of
                               this AD.
-----------------------------
(4) Replace all Fairchild     Within the next 100   Follow Pilatus PC-6
 connecting pieces, part       hours time-in-        Service Bulletin
 number (P/N) 6232.0026.XX,    service (TIS) after   No. 53-001. dated
 with a Pilatus connecting     the effective date    February 16, 2005.
 piece, P/N 6232.0026.XX.      of this AD.
 The Fairchild part has a      Repetitively
 rivet in the middle that is   inspect thereafter
 not on the Pilatus part.      at intervals not-to-
                               exceed 100 hours
                               TIS.
-----------------------------
(5) Do not install any        As of the effective   Follow Pilatus PC-6
 Fairchild connecting piece,   date of this AD.      Service Bulletin
 P/N 6232.0026.XX. The                               No. 53-001, dated
 Fairchild part has a rivet                          February 16, 2005.
 in the middle that is not
 on the Pilatus part.
------------------------------------------------------------------------


    Note: Even though not required in this AD, the FAA recommends 
that you send all defective parts to Pilatus at the address 
specified in paragraph (h) of this AD. With the part, include the 
aircraft serial number, flying hours, and cycles.

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Standards Office, Small 
Airplane Directorate, FAA. For information on any already approved 
alternative methods of compliance, contact Doug Rudolph, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090.

Is There Other Information That Relates to This Subject?

    (g) Swiss AD HB-2005-080, effective date March 2, 2005, also 
addresses the subject of this AD.

May I Get Copies of the Documents Referenced in This AD?

    (h) To get copies of the documents referenced in this AD, 
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576; 
or from Pilatus Business Aircraft Ltd., Product Support

[[Page 15022]]

Department, 11755 Airport Way, Broomfield, Colorado 80021; 
telephone: (303) 465-9099; facsimile: (303) 465-6040. To view the AD 
docket, go to the Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC, or on the Internet at http://dms.dot.gov. This 
is docket number FAA-2005-20515; Directorate Identifier 2005-CE-09-
AD.

    Issued in Kansas City, Missouri, on March 17, 2005.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-5801 Filed 3-23-05; 8:45 am]
BILLING CODE 4910-13-P