[Federal Register Volume 69, Number 6 (Friday, January 9, 2004)]
[Proposed Rules]
[Pages 1551-1554]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-476]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-55-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 1552]]


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) Models PC-12 and PC-12/45 
airplanes. This proposed AD would require you to determine whether 
certain main landing gear shock absorber attachment bolts have been 
replaced and, if not replaced would require you to replace shock 
absorber attachment bolts on main landing gear assemblies that had a 
serial number beginning with AM. This proposed 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 hydrogen embrittlement in the main landing 
gear shock absorber attachment bolts, which could result in failure of 
the main landing gear. This failure could lead to main landing gear 
collapse during operation with consequent loss of airplane control.

DATES: We must receive any comments on this proposed AD by February 19, 
2004.

ADDRESSES: Use one of the following to submit comments on this proposed 
AD:
    [sbull] By mail: FAA, Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2003-CE-55-AD, 901 Locust, Room 
506, Kansas City, Missouri 64106.
    [sbull] By fax: (816) 329-3771.
    [sbull] By e-mail: [email protected]. Comments sent 
electronically must contain ``Docket No. 2003-CE-55-AD'' in the subject 
line. If you send comments electronically as attached electronic files, 
the files must be formatted in Microsoft Word 97 for Windows or ASCII.
    You may get the service information identified in this proposed 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 the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2003-CE-55-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

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 ``AD 
Docket No. 2003-CE-55-AD'' in the subject line of your comments. If you 
want us to acknowledge receipt of your mailed comments, send us a self-
addressed, stamped postcard with the docket number written on it. We 
will date-stamp your postcard and mail it back to you.
    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.

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 Pilatus Models PC-12 and PC-12/45 airplanes. The FOCA reports that 
certain shock absorber attachment bolts (part number 532.10.12.110) in 
the main landing gear assemblies could fail during operation. 
Investigations revealed that an improper cadmium plating process 
applied to the high strength steel part causes the problem. This can 
cause hydrogen embrittlement.
    The only bolts affected are those installed on main landing gear 
assemblies with a serial number that starts with AM.
    What are the consequences if the condition is not corrected? 
Failure of the main landing gear could lead to main landing gear 
collapse during operation with consequent loss of airplane control.
    Is there service information that applies to this subject? Pilatus 
has issued PC12 Service Bulletin No. 32-015, dated September 12, 2003.
    What are the provisions of this service information? The service 
bulletin includes procedures for:

--Inspecting the left and right main landing gear assemblies if the 
assemblies have a serial number beginning with AM; and
--Replacing the shock absorber attachment bolts if any main landing 
gear assembly has a serial number beginning with AM.

    What action did the FOCA take? The FOCA classified this service 
bulletin as mandatory and issued Swiss AD Number HB 2003-522, dated 
November 14, 2003, to ensure the continued airworthiness of these 
airplanes in Switzerland.
    Did the FOCA inform the United States under the bilateral 
airworthiness agreement? These Pilatus Models 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 other 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 detect and correct hydrogen embrittlement in the 
main landing gear shock absorber attachment bolts, which could result 
in failure of the main landing gear.
    What would this proposed AD require? This proposed AD would require 
you to determine whether certain main landing gear shock absorber 
attachment bolts have been replaced and, if not replaced would require 
you to replace shock absorber attachment bolts on main landing gear 
assemblies that had a serial number beginning with AM.
    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

[[Page 1553]]

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 260 airplanes in the U.S. registry.
    What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? The manufacturer will provide 
parts free of charge and will pay for the estimated 3 workhours 
required to do the inspection and replacement of the shock absorber 
attachment bolts.

Compliance Time of This Proposed AD

    What would be the compliance time of this proposed AD? The 
compliance time of this proposed AD is within the next 30 calendar days 
after the effective date of this AD.
    Why is this proposed compliance time presented in calendar time 
instead of hours time-in-service (TIS)? The unsafe condition exists or 
could develop on airplanes equipped with the affected parts regardless 
of airplane operation. For example, the unsafe condition has the same 
chance of occurring on an airplane with 50 hours TIS as it does on one 
with 5,000 hours TIS. Therefore, we are presenting the compliance time 
of the proposed AD in calendar time instead of hours TIS.

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 No. 2003-CE-55-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. 2003-CE-55-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 February 19, 2004.

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, all 
serial numbers, 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 hydrogen embrittlement in the main landing gear shock 
absorber attachment bolts, which could result in failure of the main 
landing gear. This failure could lead to main landing gear collapse 
during operation with consequent loss of airplane control.

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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(1) Maintenance Records Check:        Within the next 30 calendar days      No special procedures necessary to
(i) Check the maintenance records to   after the effective date of this      check the maintenance records.
 determine whether the main landing    AD, unless already done.
 gear (MLG) shock absorber
 attachment bolts (part number (P/N)
 532.10.12.110) have been replaced.
 The bolts must have been replaced
 by following Pilatus PC12 Service
 Bulletin No: 32-015, dated
 September 12, 2003. The owner/
 operator holding at least a private
 pilot certificate as authorized by
 section 43.7 of the Federal
 Aviation Regulations (14 CFR 43.7)
 may perform this check.
(ii) If, by checking the maintenance
 records, the owner/operator can
 definitely show that the MLG gear
 shock absorber attachment bolts (P/
 N 532.10.12.110) have been replaced
 (by following Pilatus PC12 Service
 Bulletin No: 32-015, dated
 September 12, 2003), then report
 the removal of any bolts to FAA at
 the address in paragraph (f) of
 this AD. You must make an entry
 into the aircraft records that
 shows compliance with this portion
 of the AD in accordance with
 section 43.9 of the Federal
 Aviation Regulations (14 CFR 43.9).

[[Page 1554]]

 
(2) If you find as a result of the    Within the next 30 calendar days      Follow the Accomplishment
 check in paragraph (e)(1) that        after the effective date of this      Instructions of Pilatus PC12
 there is no record of bolt            AD, unless already done.              Service Bulletin No: 32-015, dated
 replacement, inspect the left and                                           September 12, 2003.
 right MLG assemblies (P/N
 532.10.12.049 and P/N
 532.10.12.050) for any serial
 number beginning with AM. You may
 choose to do the inspection without
 doing the logbook check.
(3) If during the inspection          Before further flight after the       Follow the Accomplishment
 required by paragraph (e)(2) of       inspection required by paragraph      Instructions of Pilatus PC12
 this AD, you find any MLG assembly    (e)(2) of this AD.                    Service Bulletin No: 32-015, dated
 with a serial number beginning with                                         September 12, 2003.
 AM, replace the shock absorber
 bolts (P/N 532.10.12.110) with new
 bolts.
(4) After removal of the shock        Within the next 30 calendar days      Not Applicable.
 absorber bolts (P/N 532.10.12.110),   after the effective date of this
 send the old removed bolts to         AD, unless already done.
 Pilatus. Report this to FAA at the
 address in paragraph (f) of this
 AD.
(5) Before installing any left or     As of the effective date of this AD.  Not Applicable.
 right MLG assembly (P/N
 532.10.12.049 or P/N 532.10.12.050)
 that has a serial number beginning
 with AM, ensure that the shock
 absorber bolts (P/N 532.10.12.110)
 have been replaced, and, if not,
 replace with new bolts.
----------------------------------------------------------------------------------------------------------------

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 39.13. 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.

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

    (g) You may get copies of the documents 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 
these documents at FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

Is There Other Information That Relates to This Subject?

    (h) Swiss AD Number HB 2003-522, dated November 14, 2003, also 
addresses the subject of this AD.

    Issued in Kansas City, Missouri, on January 2, 2004.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-476 Filed 1-8-04; 8:45 am]
BILLING CODE 4910-13-P