[Federal Register Volume 70, Number 70 (Wednesday, April 13, 2005)]
[Proposed Rules]
[Pages 19342-19345]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-7382]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20720; Directorate Identifier 2005-CE-17-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and 
PC-12/45 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 certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 
airplanes. This proposed AD would require you to insert a temporary 
revision into the Limitations Section of the Pilot Operating Handbook 
(POH). This proposed AD would also require you to replace the pitch 
actuator with an improved design pitch actuator and make the necessary 
wiring and circuit breaker changes, as applicable. Installing the 
improved design pitch actuator terminates the need for the temporary 
revision in the POH. This proposed AD results from mandatory continuing 
airworthiness information (MCAI) issued by the airworthiness authority 
for Switzerland. We are issuing this proposed AD to prevent an out-of-
trim condition from occurring when the flaps are at a 40-degree flight 
phase and the pilot disconnects the autopilot. This condition could 
lead to reduced ability to control the airplane.

DATES: We must receive any comments on this proposed AD by May 13, 
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 6208; facsimile: +41 41 619 7311; e-
mail:

[[Page 19343]]

aircraft.com">SupportPC12@pilatus-aircraft.com 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-2005-20720; Directorate Identifier 2005-CE-
17-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-2005-20720; Directorate Identifier 2005-CE-17-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-2005-20720; Directorate Identifier 2005-CE-
17-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 certain Pilatus Models PC-12 and PC-12/45 airplanes. The FOCA 
reports that an abrupt nose down pitch condition occurred on a PC-12 
airplane.
    Investigation revealed that the pilot disconnected the autopilot 
when the flaps were at a 40-degree selection.
    Pilatus has determined that the pitch actuator sense circuitry 
becomes over-active during a 40-degree flight phase. Therefore, Pilatus 
designed a new pitch actuator that modifies sense output signals and 
removes the flap in motion signal to the autopilot.
    What is the potential impact if FAA took no action? This condition, 
if not corrected, could result in an out-of-trim condition when the 
flaps are at a 40-degree flight phase and the pilot disconnects the 
autopilot. This condition could lead to reduced ability to control the 
airplane.
    Is there service information that applies to this subject? Pilatus 
has issued PC12 Service Bulletin No. 22-004, dated December 21, 2004; 
and Temporary Revision No. 11 (Report No. 02211) or No. 40 (Report No. 
01973-001).
    What are the provisions of this service information? The service 
bulletin includes procedures for:

--Replacing the pitch actuator, part number (P/N) 985.92.03.161, with 
an improved design pitch actuator, P/N 985.92.03.164; and
--Making the associated wiring and circuit breaker changes, as 
applicable.

    What action did the FOCA take? The FOCA classified this service 
bulletin as mandatory and issued Swiss AD Number HB-2005-128, effective 
date March 29, 2005, 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-12 and PC-12/45 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.
    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 Pilatus Models PC-12 and PC-12/45 airplanes of the same 
type design that are registered in the United States, we are proposing 
AD action to prevent an out-of-trim condition from occurring when the 
flaps are at a 40-degree flight phase and the pilot disconnects the 
autopilot. This condition could lead to reduced ability to control the 
airplane.
    What would this proposed AD require? This proposed AD would require 
you to insert the applicable temporary revision into the Pilot 
Operating Handbook (POH) and incorporate the actions in the previously-
referenced service bulletin. The POH revision is no longer necessary 
when the improved design pitch actuator referenced in the service 
information is installed.
    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 330 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 
incorporate the

[[Page 19344]]

proposed Pilot Operating Handbook (POH) Temporary Revision:

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                                                                                Total cost  per   Total cost  on
                  Labor cost                              Parts cost                airplane     U.S.  operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour = $65.............  Not applicable.................             $65          $21,450
----------------------------------------------------------------------------------------------------------------

    Pilatus will provide warranty credit for replacing the pitch 
actuator to the extent stated in the service information.

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 other information as included in the Regulatory Evaluation) 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-2005-20720; Directorate Identifier 005-CE-17-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.


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-2005-20720; Directorate 
Identifier 2005-CE-17-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 May 13, 2005.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects Models PC-12 and PC-12/45 airplanes, 
Manufacturers Serial Numbers (MSN) 101 through 620, 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. The actions specified in this AD are intended to 
prevent an out-of-trim condition from occurring when the flaps are 
at a 40-degree flight phase and the pilot disconnects the autopilot. 
This condition could lead to reduced ability to control the 
airplane.

What Must I Do To Address This Problem?

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

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Insert Temporary Revision     Within the next 90  The owner/operator
 No. 11 (Report No. 02211) or      days after the      holding at least
 No. 40 (Report No. 01973-001)     effective date of   a private pilot
 into the Limitations Section of   this AD, unless     certificate as
 the PC-12 Pilot's Operating       already done.       authorized by
 Handbook (POH).                                       section 43.7 of
                                                       the Federal
                                                       Aviation
                                                       Regulations (14
                                                       CFR 43.7) may
                                                       modify the POH as
                                                       specified in
                                                       paragraph (e)(1)
                                                       of this AD. Make
                                                       an entry into the
                                                       aircraft records
                                                       showing
                                                       compliance with
                                                       this the portion
                                                       of the AD
                                                       following section
                                                       43.9 of Federal
                                                       Aviation
                                                       Regulations (14
                                                       CFR 43.9).
(2) Replace the pitch actuator,   Within the next 6   Follow Pilatus
 part number (P/N)                 months after the    PC12 Service
 985.92.03.161, with an improved   effective date of   Bulletin No. 22-
 design pitch actuator, P/N        this AD, unless     004, dated
 985.92.03.164; and make the       already done.       December 21,
 associated wiring and circuit                         2004.
 breaker changes (as applicable).

[[Page 19345]]

 
(3) Remove the Temporary          Before further      The owner/operator
 Revision to the POH specified     flight after the    holding at least
 in paragraph (e)(1) of this AD    pitch actuator is   a private pilot
 after the pitch actuator is       replaced with an    certificate as
 replaced as required in           improved design     authorized by
 paragraph (e)(2) of this AD.      pitch actuator.     section 43.7 of
                                                       the Federal
                                                       Aviation
                                                       Regulations (14
                                                       CFR 43.7) may
                                                       modify the POH as
                                                       specified in
                                                       paragraph (e)(3)
                                                       of of this AD.
                                                       Make an entry
                                                       into the aircraft
                                                       records showing
                                                       compliance with
                                                       this portion of
                                                       the AD following
                                                       section 43.9 of
                                                       the Federal
                                                       Aviation
                                                       Regulations (14
                                                       CFR 43.9).
(4) Do not install a P/N          As of the           Not applicable.
 985.92.03.161 pitch actuator.     effective date of
                                   this AD.
------------------------------------------------------------------------

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 Number HB-2005-128, effective date March 29, 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, 
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 
Stans, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 
619 7311; e-mail: aircraft.com">SupportPC12@pilatus-aircraft.com 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 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-
20720; Directorate Identifier 2005-CE-17-AD.

    Issued in Kansas City, Missouri, on April 6, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7382 Filed 4-12-05; 8:45 am]
BILLING CODE 4910-13-P