[Federal Register: March 24, 2004 (Volume 69, Number 57)]
[Rules and Regulations]
[Page 13712-13715]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24mr04-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-55-AD; Amendment 39-13531; AD 2004-06-05]
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 all
Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes.
This AD requires 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 have a serial number beginning
with AM001 through AM053. This AD is the result of mandatory continuing
airworthiness information (MCAI) issued by the airworthiness authority
for Switzerland. We are issuing this 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: This AD becomes effective on May 6, 2004.
As of May 6, 2004, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
ADDRESSES: You may get the service information identified 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 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:
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 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 is the potential impact if FAA took no action? Failure of the
main landing gear could lead to main landing gear collapse during
operation 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 all Pilatus Models PC-12 and PC-12/45
airplanes.
[[Page 13713]]
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on January 9, 2004 (69 FR 1551). The NPRM
proposed to 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 have a serial number beginning
with AM.
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 No. 1: Limit the Effectivity of the AD
What is the commenter's concern? Two commenters want the
effectivity of the AD limited to Pilatus Models PC-12 and PC-12/45
airplanes with serial numbers 101 through 482 (as listed in Pilatus SB
PC12 Service Bulletin No: 32-015, dated September 12, 2003). The
commenters state that the suspected bolts have been installed on a
limited number of landing gears. Further, it is very unlikely that
bolts have been swapped between airplanes. The proposed effectivity to
all serial numbers will place an undue burden on owners and operators.
The commenters conclude that limiting the effectivity to airplanes
with serial numbers 101 through 482 is enough to assure the
airworthiness of Pilatus Models PC-12 and PC-12/45 airplanes.
What is FAA's response to the concern? We believe that the practice
of swapping bolts is rare, however, it is still possible. To help
alleviate this possibility, we are including the action of a logbook
check in the AD.
We also believe that the swapping of the main landing gear
assemblies is possible so limiting the airplane serial numbers is not
enough to assure the airworthiness of Pilatus Models PC-12 and PC-12/45
airplanes.
We are not changing the final rule AD action as a result of theses
comments.
Comment Issue No. 2: Limit Effectivity on the Shock-Absorber Attachment
Bolts
What is the commenter's concern? Two commenters note that main
landing gear assemblies with new bolts (part number (P/N)
532.10.12.110) marked ``AT'' or ``VLG'' are good bolts and do not
require replacement.
The commenters request limiting the effectivity of the AD to those
P/N 532.10.12.110 bolts not marked ``AT'' or ``VLG.''
What is FAA's response to the concern? We agree that the main
landing gear assemblies with new bolts (part number (P/N)
532.10.12.110) marked ``AT'' or ``VLG'' are good bolts and do not
require replacement.
We are changing the final rule AD action accordingly to reflect the
commenters' request.
Comment Issue No. 3: AD Is Not Needed
What is the commenter's concern? One commenter suggests that the
aviation industry has influence over FAA. Further, FAA neglects the
public's concerns.
We infer that the commenters want us to withdraw the NPRM.
What is FAA's response to the concern? Through the NPRM process,
FAA provides the public opportunity to comment on and influence the AD
action.
Since the commenter gave no specific reasons to withdraw or change
the proposed rule, we are not changing the final rule AD action as a
result of these comments.
Comment Issue No. 4: Limit Effectivity on the Main Landing Gear
Assemblies
What is the commenter's concern? One commenter requests that FAA
limit the effectivity on the main landing gear assemblies to those
assemblies with the serial numbers that start ``AM001'' through
``AM053'' since Pilatus has identified these were assembled with the
defective bolts. The commenter notes that limiting the effectivity will
lessen the impact on owners/operators.
What is FAA's response to the concern? The FAA agrees that the AD
should limit the effectivity on the main landing gear assemblies.
We are changing the final rule AD action accordingly.
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.
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 260 airplanes in the U.S. registry.
What is the cost impact of this 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 AD
What will be the compliance time of this AD? The compliance time of
this AD is within the next 30 calendar days after the effective date of
this AD.
Why is this 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 this AD in calendar time instead of hours TIS.
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
[[Page 13714]]
under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this 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, 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
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:
2004-06-05 Pilatus Aircraft Ltd.: Amendment 39-13531; Docket No.
2003-CE-55-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on May 6, 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 No special
calendar days procedures
after May 6, 2004 necessary to
(the effective check the
date of this AD), maintenance
unless already records.
done.
(i) Check the maintenance
records to determine whether
the main landing 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).
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(2) If you find as a result of Within the next 30 Follow the
the check in paragraph (e)(1) calendar days Accomplishment
that there is no record of bolt after May 6, 2004 Instructions of
replacement, inspect the left (the effective Pilatus PC12
and right MLG assemblies (P/N date of this AD), Service Bulletin
532.10.12.049 and P/N unless already No: 32-015, dated
532.10.12.050) for any serial done. September 12,
number beginning with AM001 2003.
through AM053. You may choose
to do the inspection without
doing the logbook check.
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(3) If during the inspection Before further Follow the
required by paragraph (e)(2) of flight after the Accomplishment
this AD, you find any MLG inspection Instructions of
assembly with a serial number required by Pilatus PC12
beginning with AM001 through paragraph (e)(2) Service Bulletin
AM053, replace any shock of this AD. No: 32-015, dated
absorber bolts (P/N inspection September 12,
532.10.12.110) NOT MARKED with 2003.
``AT'' or ``VLG'' with new
bolts.
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[[Page 13715]]
(4) After removal of the shock Within the next 30 Not Applicable.
absorber bolts (P/N calendar days
532.10.12.110), send the old after May 6, 2004
removed bolts to Pilatus. (the effective
Report this to FAA at the date of this AD),
address in paragraph (f) of unless already
this AD. The Office of done..
Management and Budget (OMB)
approved the information
collection requirements
contained in this regulation
under the provisions of the
Paperwork Reduction Act of 1980
(44 U.S.C. 3501 et seq.) and
assigned OMB Control Number
2120-0056.
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(5) Before installing any left As of May 6, 2004 Follow Pilatus
or right MLG assembly (P/N (the effective PC12 Service
532.10.12.049 or P/N date of this AD). Bulletin No: 32-
532.10.12.050) that has a 015, dated
serial number beginning with September 12,
AM, ensure that the shock 2003
absorber bolts (P/N
532.10.12.110) NOT MARKED with
``AT'' or ``VLG'' have been
replaced, and, if not, replace
with new bolts.
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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.
Does This AD Incorporate Any Material by Reference?
(g) You must do the actions required by this AD following the
instructions in Pilatus PC12 Service Bulletin No: 32-015, dated
September 12, 2003. 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. You may get a
copy 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 review
copies at FAA, Central Region, Office of the Regional Counsel, 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.
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 March 15, 2004.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-6260 Filed 3-23-04; 8:45 am]
BILLING CODE 4910-13-P