[Federal Register Volume 64, Number 55 (Tuesday, March 23, 1999)]
[Rules and Regulations]
[Pages 13882-13883]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-6715]
[[Page 13882]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-03-AD; Amendment 39-11081; AD 99-06-17]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and
PC-12/45 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Direct final rule; request for comments.
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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 installing a support bracket and a
cut-out relay for the second generator control unit. This AD also
requires making all the wiring additions and adjustments necessary for
the above-referenced installations. 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 prevent damage to electrical components because incorrectly
connected cables or broken or damaged wires cause excessive voltages to
the second generator, which could result in loss of electrical power
during any phase of flight.
DATES: Effective June 16, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 16, 1999.
Comments for inclusion in the Rules Docket must be received on or
before April 23, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 99-CE-03-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 62 33; facsimile: +41 41 610 33 51.
This information may also be examined at the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 99-CE-03-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, FAA, Small Airplane Directorate, 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
The Federal Office for Civil Aviation (FOCA), which is the
airworthiness authority for Switzerland, recently notified the FAA that
an unsafe condition may exist on certain Pilatus Models PC-12 and PC-
12/45 airplanes. The FOCA of Switzerland reports three occurrences
where the cables behind the second generator were incorrectly
connected. In the above-referenced incidents, the over-voltage
protection did not automatically disconnect the second generator from
the electrical system when excessive voltage was experienced.
This condition, if not corrected in a timely manner, could result
in electrical component damage and loss of electrical power during any
phase of flight.
Relevant Service Information
Pilatus has issued Service Bulletin No. 24-009, dated September 23,
1998, which specifies procedures for installing a support bracket and a
cut-out relay for the second generator control unit, and making all the
wiring additions and adjustments necessary for the above-referenced
installations. Modification Kit No. 500.50.12.171 includes the parts
necessary to accomplish this installation and modification.
The FOCA of Switzerland classified this service bulletin as
mandatory and issued Swiss AD HB 98-537, dated December 29, 1998, in
order to assure the continued airworthiness of these airplanes in
Switzerland.
The FAA's Determination
This airplane model is manufactured in Switzerland and is 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. Pursuant to this
bilateral airworthiness agreement, the FOCA of Switzerland has kept the
FAA informed of the situation described above.
The FAA has examined the findings of the FOCA of Switzerland;
reviewed all available information, including the service information
referenced above; and determined that AD action is necessary for
products of this type design that are certificated for operation in the
United States.
Explanation of the Provisions of This AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Pilatus PC-12 and PC-12/45 airplanes of the
same type design registered in the United States, the FAA is issuing an
AD. This AD requires installing a support bracket and a cut-out relay
for the second generator control unit. This AD also requires making all
the wiring additions and adjustments necessary for the above-referenced
installations. Accomplishment of the actions of this AD would be
required in accordance with the previously referenced service bulletin.
Cost Impact
The FAA estimates that 50 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 8 workhours per
airplane to accomplish the required action, and that the average labor
rate is approximately $60 per work hour. The manufacture will provide
parts to owners/operators of the affected airplanes at no cost. Based
on these figures, the cost impact of this AD on U.S. operators is
estimated to be $24,000, or $480 per airplane.
The Direct Final Rule Procedure
The FAA anticipates that this regulation will not result in adverse
or negative comment and therefore is issuing it as a direct final rule.
The requirements of this direct final rule address an unsafe condition
identified by a foreign civil airworthiness authority and do not impose
a significant burden on affected operators. In accordance with Section
11.17 of the Federal Aviation Regulations (14 CFR 11.17) unless a
written adverse or negative comment, or a written notice of intent to
submit an adverse or negative comment, is received within the comment
period, the regulation will become effective on the date specified
above. After the close of the comment period, the FAA will publish a
document in the Federal Register indicating that no adverse or negative
comments were received and confirming the date on which the final rule
will become effective. If the FAA does receive, within the comment
period, a written adverse or negative comment, or written notice of
intent to submit such a comment, a document withdrawing the direct
final rule will be published in the Federal Register, and
[[Page 13883]]
a notice of proposed rulemaking may be published with a new comment
period.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and an opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
rule by submitting such written data, views, or arguments as they may
desire. Communications shall identify the Rules Docket number and be
submitted in triplicate to the address specified under the caption
ADDRESSES. All communications received on or before the closing date
for comments will be considered, and this rule may be amended in light
of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 99-CE-03-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is noncontroversial and
unlikely to result in adverse or negative comments. For reasons
discussed in the preamble, I certify that this regulation (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 final
evaluation has been prepared for this action and is contained in the
Rules Docket. A copy of it may be obtained from 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:
99-06-17 Pilatus Aircraft LTD.: Amendment 39-11081; 99-06-18 Docket
No. 99-CE-03-AD.
Applicability: Models PC-12 and PC-12/45 airplanes, manufacturer
serial numbers (MSN) 101 through MSN 180, certificated in any
category.
Note 1: The installations and modifications required by this AD
will be incorporated at the factory on Models PC-12 and PC-12/45
airplanes beginning with MSN 181.
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 (c) 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.
Compliance: Required within the next 50 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
Note 3: The compliance time of this AD differs from that
specified in Pilatus Service Bulletin No. 24-009, dated September
23, 1998, and in Swiss AD HB 98-537, dated December 29, 1998. This
AD takes precedence over any other information on airplanes
registered for operation in the United States.
To prevent damage to electrical components because incorrectly
connected cables or broken or damaged wires cause excessive voltages
to the second generator, which could result in loss of electrical
power during any phase of flight, accomplish the following:
(a) Install a support bracket and a cut-out relay for the second
generator control unit, and make all the wiring additions and
adjustments necessary for the above-referenced installations.
Modification Kit No. 500.50.12.171 includes the parts necessary to
accomplish this installation and modification. Perform these actions
in accordance with the Accomplishment Instructions section of
Pilatus Service Bulletin No. 24-009, dated September 23, 1998.
(b) 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.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
used if 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(d) The installation and modification required by this AD shall
be done in accordance with Pilatus Service Bulletin No. 24-009,
dated September 23, 1998. 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., Customer Liaison Manager, CH-6371 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 5: The subject of this AD is addressed in Swiss AD HB 98-
537, dated December 29, 1998.
(e) This amendment becomes effective on June 16, 1999.
Issued in Kansas City, Missouri, on March 11, 1999.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-6715 Filed 3-22-99; 8:45 am]
BILLING CODE 4910-13-U
