[Federal Register Volume 70, Number 212 (Thursday, November 3, 2005)]
[Rules and Regulations]
[Pages 66749-66752]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-21803]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21835; Directorate Identifier 2005-CE-35-AD; 
Amendment 39-14357; AD 2005-22-13]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and 
PC-12/45 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. 
This AD requires you to inspect the left and right main landing gear 
(MLG) assemblies for any part number (P/N) 532.10.12.077 or FAA-
approved equivalent part number bolts that do not have white primed and 
painted heads; and replace any bolt found with new P/N 532.10.12.077F 
or FAA-approved equivalent part number bolts in all MLG assemblies. 
This AD results from mandatory continuing airworthiness information 
(MCAI) issued by the airworthiness authority for Switzerland. We are 
issuing this AD to detect and correct any P/N 532.10.12.077 or FAA-
approved equivalent part number bolts that do not have white primed and 
painted heads, which could result in corrosion of the bolt and 
consequent failure of the bolt. This failure could lead to MLG collapse 
during airplane landing and take-off operations with consequent loss of 
airplane control.

DATES: This AD becomes effective on December 19, 2005.
    As of December 19, 2005, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: To get the service information identified 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 20590-0001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-21835; Directorate 
Identifier 2005-CE-35-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:

Discussion

    What events have caused this 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 part 
number (P/N) 532.10.12.077 bolts that do not have white primed and 
painted heads are subject to corrosion. These bolts attach the 
hydraulic actuators to the left and right main landing gear (MLG) 
assemblies. The FOCA further reports the separation of a bolt head in 
an MLG assembly has occurred due to corrosion. The corrosion occurred 
because the bolt head was not primed and painted.

[[Page 66750]]

    Pilatus has designed and produced a new bolt (P/N 532.10.12.077F) 
as part of Modification Kit No. 500.50.12.299 to replace the subject 
bolt. Pilatus recommends the replacement of bolts in pairs.
    What is the potential impact if FAA took no action? Corrosion of 
the bolt could lead to MLG collapse during airplane landing and take-
off operations with consequent loss of airplane control.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to certain Pilatus Aircraft Ltd. 
(Pilatus) Models PC-12 and PC-12/45 airplanes. This proposal was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on August 2, 2005 (70 FR 44297). The NPRM proposed to require 
you to inspect the left and right main landing gear (MLG) assemblies 
for any part number (P/N) 532.10.12.077 bolts that do not have white 
primed and painted heads; and replace any bolt found with new P/N 
532.10.12.077F bolts in all MLG assemblies.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. The following 
presents the comments received on the proposal and FAA's response to 
each comment:

Comment Issue: Include Parts Manufacture Approval (PMA) Parts Approved 
by Identicality in Both the Parts Replaced and the Replacement Parts

    What is the commenters' concern? Two commenters specifically ask 
that the FAA address PMA parts approved by identicality in both the 
parts replaced (unsafe condition) and the replacement parts (correction 
of condition). Specifically, the commenters state:
    1. One commenter believes FAA should add the phrase ``or FAA-
approved equivalent part number'' to the replacement part as it did 
with the parts replaced; and
    2. Another commenter states that restricting parts to be replaced 
and parts installed to just those cited in the manufacturer service 
bulletin is not good form and might establish a dangerous precedent. 
The commenter believes that installed PMA parts could have the same 
unsafe condition and that the owner/operator should have the option of 
installing equivalent parts without applying for an alternative method 
of compliance (AMOC). The commenter also believes that the phrase ``or 
FAA-approved equivalent part number'' is inadequate for replacement 
parts and proposes language to clarify that phrase.
    What is FAA's response to the concern? The FAA concurs with all the 
comments above. The FAA will add information to further clarify the 
phrase ``or FAA-approved equivalent part number'', and add the phrase 
to cover the PMA replacement parts.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for the 
changes discussed above and minor editorial corrections. We have 
determined that these changes and minor corrections:

--Are consistent with the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Docket Information

    Where can I go to view the docket information? You may view the AD 
docket that contains information relating to this subject in person at 
the DMS Docket Offices between 9:00 a.m. and 5:00 p.m. (eastern 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.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the 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 does this AD impact? We estimate that this AD 
affects 350 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to do the 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                               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           $22,750
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary single bolt 
replacement (using Modification Kit No. 500.50.12.299) that would be 
required based on the results of this inspection. We have no way of 
determining the number of airplanes that may need this bolt 
replacement:

------------------------------------------------------------------------
                                                         Total cost per
          Labor cost                  Parts cost            airplane
------------------------------------------------------------------------
3 work hours x $65 per hour =   $1,000 estimate for              $1,195
 $195.                           each Modification Kit
                                 No. 500.50.12.299.
------------------------------------------------------------------------

    Pilatus will provide warranty credit for inspecting and replacing 
the specified bolts 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

[[Page 66751]]

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

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD will 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.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this 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 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 ``Docket 
No. FAA-2005-21835; Directorate Identifier 2005-CE-35-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2005-22-13 Pilatus Aircraft Ltd.: Amendment 39-14357; Docket No. 
FAA-2005-21835; Directorate Identifier 2005-CE-35-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on December 19, 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 detect 
and correct any part number (P/N) 532.10.12.077 or FAA-approved 
equivalent part number bolts that do not have white primed and 
painted heads, which could result in corrosion of the bolt and 
consequent failure of the bolt. This failure of the bolt could lead 
to main landing gear (MLG) collapse during airplane landing and 
take-off operations with consequent loss of airplane control.

What Must I Do To Address This Problem?

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the main landing  Within the next 100   Follow Pilatus PC12
 gear (MLG) assemblies, part   hours time-in-        Service Bulletin
 number (P/N) 532.10.12.049    service (TIS) or 90   No. 32-018, dated
 and P/N 532.10.12.050 or      days after December   May 2, 2005.
 FAA-approved equivalent       19, 2005 (the
 part number, for any P/N      effective date of
 532.10.12.077 or FAA-         this AD), whichever
 approved equivalent part      occurs first,
 number bolts that do not      unless already done.
 have white primed and
 painted heads.
(2) Replace any P/N           Before further        Follow Pilatus PC12
 532.10.12.077 bolts that do   flight after          Service Bulletin
 not have white primed and     inspection required   No. 32-018, dated
 painted heads found as a      by paragraph (e)(1)   May 2, 2005.
 result of the inspection      of this AD.
 required by paragraph
 (e)(1) of this AD. Replace
 with new bolts (new P/N
 532.10.12.077F or FAA-
 approved equivalent part
 number) in both MLG
 assemblies.
(3) 14 CFR 21.303 allows for  Not Applicable......  Not Applicable.
 replacement parts through
 parts manufacturer approval
 (PMA). The phrase ``or FAA-
 approved equivalent part
 number'' in this AD is
 intended to signify those
 parts that are PMA parts
 approved through
 identicality to the design
 of the part under the type
 certificate and replacement
 parts to correct the unsafe
 condition under PMA (other
 than identicality). If
 parts are installed that
 are identical to the unsafe
 parts, then the corrective
 actions of the AD affect
 these parts also. In
 addition, equivalent
 replacement parts to
 correct the unsafe
 condition under PMA (other
 than identicality) may also
 be installed provided they
 meet current airworthiness
 standards, which include
 those actions cited in this
 AD.

[[Page 66752]]

 
(4) Do not install:
    (i) Any P/N
     532.10.12.077 (or FAA-
     approved equivalent
     part number) bolt that
     does not have a white
     primed and painted head
     in any MLG assembly (P/
     N 532.10.12.049, P/N
     532.10.12.050, or FAA-
     approved equivalent
     part number); and
    (ii) Any MLG assembly (P/ As of December 19,    Not Applicable.
     N 532.10.12.049, P/N      2005 (the effective
     532.10.12.050 or FAA-     date of this AD).
     approved equivalent
     part number) that does
     not have P/N
     532.10.12.077F (or FAA-
     approved equivalent
     part number) bolts with
     white primed and
     painted heads.
------------------------------------------------------------------------


    Note: The FAA recommends that you return any removed bolts to 
Pilatus.

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-2005-288, dated June 29, 2005, also 
addresses the subject of this AD.

Does This AD Incorporate Any Material by Reference?

    (h) You must do the actions required by this AD following the 
instructions in Pilatus PC12 Service Bulletin No. 32-018, dated May 
2, 2005. The Director of the Federal Register approved the 
incorporation by reference of this service bulletin in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this 
service information, 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 review copies of this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. 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 20590-001 or on the Internet 
at http://dms.dot.gov. The docket number is FAA-2005-21835; 
Directorate Identifier 2005-CE-35-AD.

    Issued in Kansas City, Missouri, on October 25, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-21803 Filed 11-2-05; 8:45 am]
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