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

[Federal Register Volume 67, Number 136 (Tuesday, July 16, 2002)]
[Rules and Regulations]
[Pages 46582-46584]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-17602]



[[Page 46582]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-44-AD; Amendment 39-12822; AD 2002-14-22]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all 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 bolts with a serial number (S/N) 
beginning with the letters ``AT'' and numbers 299 or lower and replace 
each bolt with a bolt that does not have a S/N with both the letters 
``AT'' and a number of 299 or lower. This AD is the result of mandatory 
continuing airworthiness information (MCAI) issued by the airworthiness 
authority for Switzerland. The actions specified by this AD are 
intended to detect and replace defective MLG assembly bolts that have 
an improper cadmium plating, which could cause hydrogen embrittlement 
and bolt failure. Such failure could lead to MLG collapse during 
landing.

DATES: This AD becomes effective on August 29, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
August 29, 2002.

ADDRESSES: You may get the service information referenced in this AD 
from Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224; 
or from Pilatus Business Aircraft Ltd., Product Support Department, 
11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-
9099; facsimile: (303) 465-6040. You may view this information at the 
Federal Aviation Administration (FAA), Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2001-CE-44-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the 
Federal Register, 800 North Capitol Street, NW, suite 700, Washington, 
DC.

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 that, because of a manufacturing defect, 
certain bolts on the main landing gear (MLG) assembly may be defective. 
The problem is caused by an improper cadmium process applied to the 
high strength steel part, which can cause hydrogen embrittlement and 
subsequent failure of the bolt.
    The defective bolts were initially installed on MLG assemblies that 
have a serial number beginning with the letters ``AM''. Each bolt in 
the defective lot incorporates the letters ``AT'' and a number of 299 
or lower.

What Is the Potential Impact if FAA Took No Action?

    If not corrected, such failure could lead to MLG collapse during 
landing.

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 all 
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 March 1, 2002 (67 FR 9420). The NPRM proposed to require you 
to inspect the left and right main landing gear (MLG) assemblies for 
bolts with a serial number (S/N) beginning with the letters ``AT'' and 
numbers 299 or lower and replace each bolt with a bolt that does not 
have a S/N with both the letters ``AT'' and a number of 299 or lower.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:

--Provide 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.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 16 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 accomplish the inspection and 
replacement:

----------------------------------------------------------------------------------------------------------------
                                                                      Total cost per        Total cost on U.S.
             Labor cost                       Parts cost                 airplane                operators
----------------------------------------------------------------------------------------------------------------
Manufacturer will pay for workhours  Parts will be provided at    None..................  None.
                                      no cost to the owners/
                                      operators of the affected
                                      aircraft.
----------------------------------------------------------------------------------------------------------------


[[Page 46583]]

Compliance Time of This AD

What Will Be the Compliance Time of This AD?

    The compliance time of this AD is ``within the next 30 days after 
the effective date of this AD''.

Why Is the Compliance Time Presented in Calendar Time Instead of Hours 
Time-in-service (TIS)?

    Although malfunction of the main landing gear is unsafe during 
flight, the condition is not a direct result of airplane operation. The 
chance of this situation occurring is the same for an airplane with 10 
hours TIS as it would be for an airplane with 500 hours TIS. A calendar 
time for compliance will ensure that the unsafe condition is addressed 
on all airplanes in a reasonable time period.

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A copy of the final evaluation prepared for this 
action is contained in the Rules Docket. A copy of it may be obtained 
by contacting the Rules Docket at the location provided under the 
caption ``ADDRESSES''.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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

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

2002-14-22--Pilatus Aircraft Ltd.: Amendment 39-12822; Docket No. 
2001-CE-44-AD.

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:
    (1) Group 1: Pilatus may have installed the affected bolts on 
the following airplanes at manufacture. All portions of this AD 
apply to these airplanes:

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
PC-12 and PC-12/45.....................  349, 352, 357, 359, 362 through
                                          365, 367, 369, 371, 375, 377,
                                          380, 384, 385, 388, 390, 391,
                                          393, 401, and 409.
------------------------------------------------------------------------

    (2) Group 2: The affected bolts could be installed through spare 
replacement on any of the following model airplanes. Paragraphs 
(d)(3) and (d)(4) of this AD apply to these airplanes:

------------------------------------------------------------------------
                   Model                             Serial Nos.
------------------------------------------------------------------------
PC-12 and PC-12/45........................  All serial numbers
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to detect and replace defective main landing 
gear (MLG) assembly bolts that have an improper cadmium plating, 
which could cause hydrogen embrittlement and bolt failure.
    (d) What actions must I accomplish to address this problem? To 
address this problem, accomplish all actions for Group 1 airplanes, 
and accomplish paragraphs (d)(3) and (d)(4) of this AD for Group 2 
airplanes:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the left and      Inspect within the    Pilatus PC-12
 right main landing gear       next 30 days after    Service bulletin
 (MLG) assembly for the        August 29, 2002       No. 32-012, dated
 existence of a bold, part     (the effective date   October 18, 2001,
 number (P/N) 532.10.12.077,   of this AD). Prior    provides
 that has a serial number (S/  to further flight,    information about
 N) with both the letters      replace bolts found   these actions.
 ``AT'' and a number of 299    during the
 or lower.                     inspection required
(i) If the above referenced    in paragraph (d)(1)
 bolts are not installed, no   of this AD.
 further action is required.
(ii) If the above referenced
 bolts are installed,
 replace each bolt with an
 FAA-approved bolt that does
 not have a S/N with both
 the letters ``AT'' and a
 number of 299 or lower.
------------------------------------------------------------------------
(2) Send the removed bolts    Within 10 days after  Send the removed
 to Pilatus Aircraft Ltd. so   removing the bolts    bolts to Pilatus
 the bolts cannot be reused    or within 10 days     Aircraft Ltd. at
 and report the results of     after August 29,      the address in
 the inspection (positive or   2002 (the effective   paragraph (h) of
 negative) to FAA. The         date of this AD),     this AD, and send
 Office of Management and      whichever occurs      the report to Doug
 Budget (OMB) approved the     later.                Rudolph, FAA, at
 information collection                              the address in
 requirements contained in                           paragraph (f) of
 this regulation under the                           this AD.
 provisions of the Paperwork
 Reduction Act of 1980 (44
 U.S.C. 3501 et seq.) and
 assigned OMB Control Number
 2120-0056.
------------------------------------------------------------------------
(3) Do not install any bolt,  As of August 29,      Not Applicable.
 P/N 532.10.12.077, on any     2002 (the effective
 MLG assembly that has a S/N   date of this AD).
 with bolt the letters
 ``AT'' and a number of 299
 or lower.
------------------------------------------------------------------------

[[Page 46584]]

 
(4) If you have already       Within the next 30    Not Applicable.
 accomplished the actions      days after August
 specified in Pilatus PC-12    29, 2002 (the
 Service Bulletin No. 32-      effective date of
 012, dated October 18,        this AD).
 2001, send a report to the
 FAA at the address in
 paragraph (f) of this AD,
 stating if one of the
 affected bolts was replaced
 and returned to Pilatus.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Small Airplane Directorate, approves your 
alternative. Submit your request through an FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Small Airplane Directorate.

    Note 1: This AD applies to each airplane identified in paragraph 
(a) of this AD, regardless of whether it has been modified, altered, 
or repaired in the area subject to the requirements of this AD. For 
airplanes that have been modified, altered, or repaired so that the 
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of 
compliance in accordance with paragraph (e) of this AD. The request 
should include an assessment of the effect of the modification, 
alteration, or repair on the unsafe condition addressed by this AD; 
and, if you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about 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.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Pilatus PC-12 Service Bulletin No. 32-012, dated October 18, 
2001. The Director of the Federal Register approved this 
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. 
You may get copies from Pilatus Aircraft Ltd., Customer Liaison 
Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19; 
facsimile: +41 41 619 6224; or from Pilatus Business Aircraft Ltd., 
Product Support Department, 11755 Airport Way, Broomfield, Colorado 
80021; telephone: (303) 465-9099; facsimile: (303) 465-6040. You may 
view copies at the FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the 
Office of the Federal Register, 800 North Capitol Street, NW, suite 
700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on August 29, 2002.

    Issued in Kansas City, Missouri, on July 8, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-17602 Filed 7-15-02; 8:45 am]
BILLING CODE 4910-13-P

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