[Federal Register Volume 63, Number 31 (Tuesday, February 17, 1998)]
[Rules and Regulations]
[Pages 7688-7689]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3637]
[[Page 7688]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-45-AD; Amendment 39-10328; AD 98-04-16]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-
12/45 airplanes. This AD requires inspecting the aileron tie-rod jam
nuts for looseness, tightening any loose jam nuts, and installing a
locking sleeve on both ends of the aileron tie-rod in the chain-drive
of the aileron system. The AD results from an incident where the
aileron tie-rod jam nuts on the chain-drive of the aileron system
became loose. This caused a differential of aileron control between the
pilot's control wheel and the co-pilot's control wheel. The actions
specified by this AD are intended to prevent such aileron control
differential caused by the aileron tie-rod jam nuts becoming loose,
which could result in loss of aileron control and consequent loss of
control of the airplane.
DATES: Effective April 2, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 2, 1998.
ADDRESSES: Service information that applies to this AD may be obtained
from Pilatus Aircraft Ltd., CH-6370 Stans, Switzerland. This
information may also be examined at the Federal Aviation Administration
(FAA), Central Region, Office of the Regional Counsel, Attention: Rules
Docket No. 97-CE-45-AD, Room 1558, 601 E. 12th Street, 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: Mr. Roman T. Gabrys, Aerospace
Engineer, Small Airplane Directorate, Airplane Certification Service,
FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone:
(816) 426-6932; facsimile: (816) 426-2169.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
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
Models PC-12 and PC-12/45 airplanes was published in the Federal
Register as a notice of proposed rulemaking (NPRM) on October 6, 1997
(62 FR 52055). The NPRM proposed to require inspecting the aileron tie-
rod jam nuts for looseness, tightening any loose jam nuts, and
installing a locking sleeve on both ends of the aileron tie-rod in the
chain-drive of the aileron system. Accomplishment of the proposed
actions as specified in the NPRM would be in accordance with Pilatus
Service Bulletin No. 27-001, dated March 25, 1997.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Cost Impact
The FAA estimates that 40 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 5 workhours per
airplane to accomplish the required action, and that the average labor
rate is approximately $60 an hour. Parts will be provided by the
manufacturer at no cost to the owner/operator of the affected
airplanes. Based on these figures, the total cost impact of this AD on
U.S. operators is estimated to be $12,000, or $300 per airplane.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
98-04-16 Pilatus Aircraft Ltd.: Amendment 39-10328; Docket No. 97-
CE-45-AD.
Applicability: Models PC-12 and PC-12/45 airplanes, serial
numbers 101 through 169, certificated in any category.
Note 1: The modification required by this AD is incorporated at
manufacture on Models PC-12 and PC-12/45 airplanes, beginning with
serial number 170. Airplanes with this modification are not affected
by this AD.
Note 2: This AD applies to each airplane identified in the
preceding applicability provision, 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 (d) 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 the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
[[Page 7689]]
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent a differential of aileron control between the pilot's
control wheel and the co-pilot's control wheel caused by the aileron
tie-rod jam nuts becoming loose, which could result in loss of
aileron control and consequent loss of control of the airplane,
accomplish the following:
(a) Within the next 100 hours time-in-service (TIS) after the
effective date of this AD, inspect the aileron tie-rod jam nuts for
looseness in accordance with the Accomplishment Instructions section
of Pilatus Service Bulletin No. 27-001, dated March 25, 1997. Prior
to further flight, tighten any loose jam nuts in accordance with the
above-referenced service bulletin.
(b) Within the next 100 hours TIS after the effective date of
this AD, install a locking sleeve on both ends of the aileron tie-
rod in the chain-drive of the aileron system in accordance with the
Accomplishment Instructions section of Pilatus Service Bulletin No.
27-001, dated March 25, 1997.
(c) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Small Airplane Directorate, 1201 Walnut,
suite 900, Kansas City, Missouri 64106. The request shall be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, Small Airplane
Directorate.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(e) The inspection, tightening, and installation required by
this AD shall be done in accordance with Pilatus Service Bulletin
No. 27-001, dated March 25, 1997. This incorporation by reference
was approved by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
Pilatus Aircraft Ltd., CH-6370 Stans, Switzerland. Copies may be
inspected at the FAA, Central Region, Office of the Regional
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at
the Office of the Federal Register, 800 North Capitol Street, NW,
suite 700, Washington, DC.
Note 4: The subject of this AD is addressed in Swiss AD HB 97-
174, dated April 30, 1997.
(f) This amendment (39-10328) becomes effective on April 2,
1998.
Issued in Kansas City, Missouri, on February 5, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-3637 Filed 2-13-98; 8:45 am]
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