FR Doc 05-5801

[Federal Register: March 24, 2005 (Volume 70, Number 56)]
[Proposed Rules]
[Page 15019-15022]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24mr05-15]

[[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
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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:

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Total cost per airplane to replace all
Labor cost Parts cost parts
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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?

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:

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Actions Compliance Procedures
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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.
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(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.
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(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.
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(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.
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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]

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