[Federal Register Volume 64, Number 160 (Thursday, August 19, 1999)]
[Rules and Regulations]
[Pages 45149-45150]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-21016]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 64, No. 160 / Thursday, August 19, 1999 /
Rules and Regulations
[[Page 45149]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-10-AD; Amendment 39-11256; AD 99-17-08]
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 certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-
12/45 airplanes. This AD requires modifying the generator 2 excitation
by removing certain diodes and installing a new 5-amp circuit breaker
and suppression filter. 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
prevent damage to electrical components if the generator 2 is not
switched off prior to engine shutdown and it overheats, which could
result in loss of electrical power to certain critical airplane
components.
DATES: Effective October 4, 1999. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of October 4, 1999.
ADDRESSES: 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 63 19; 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-10-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
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 June 14, 1999 (64
FR 31758). The NPRM proposed to require modifying the generator 2
excitation by removing certain diodes and installing a new 5-amp
circuit breaker and suppression filter. Accomplishment of the proposed
action as specified in the NPRM would be required in accordance with
Pilatus Service Bulletin No. 24-012, dated February 19, 1999.
The NPRM was the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland.
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 69 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 5 workhours per
airplane to accomplish this action, and that the average labor rate is
approximately $60 an hour. Parts will be provided at no cost to the
owners/operators of the affected aircraft. Based on these figures, the
total cost impact of this AD on U.S. operators is estimated to be
$20,700, 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.
[[Page 45150]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
99-17-08 Pilatus Aircraft Ltd.: Amendment 39-11256; Docket No. 99-
CE-10-AD.
Applicability: Models PC-12 and PC-12/45 airplanes, manufacturer
serial numbers (MSN) 101 through 260, certificated in any category.
Note 1: 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.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent damage to electrical components if the generator 2 is
not switched off prior to engine shutdown and it overheats, which
could result in loss of electrical power to certain critical
airplane components, accomplish the following:
(a) Within the next 100 hours time-in-service (TIS) after the
effective date of this AD, modify the generator 2 excitation by
removing certain diodes and installing a new 5-amp circuit breaker
and suppression filter. Perform these actions in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Pilatus Service Bulletin No.
24-012, dated February 19, 1999.
Note 2: The affected airplanes incorporate one of the following
generators:
--a BOSCH Generator 2, part number (P/N) 524.32.12.158. This
generator is installed at the factory on Pilatus Models PC-12 and
PC-12/45 airplanes beginning with MSN 231 and could be installed on
airplanes with a MSN in the range of 101 through 230 by
incorporating Pilatus Service Bulletin No. 24-010, dated September
28, 1998; or
--an ELECTRO SYSTEMS Generator 2, P/N 978.87.24.121, with
Pilatus Service Bulletin No. 24-009 (installation of support bracket
and cut-out relay) incorporated. This generator is installed at the
factory on Pilatus Models PC-12 and PC-12/45 airplanes with a MSN in
the range of 101 through 230. AD 99-06-17, Amendment 39-11081 (64 FR
13882, March 23, 1999), requires installing the support bracket and
cut-out relay specified in Pilatus Service Bulletin No. 24-009,
dated September 23, 1998, on Pilatus Models PC-12 and PC-12/45
airplanes with a MSN in the range of 101 through 180. This service
bulletin is incorporated at the factory on airplanes with a MSN in
the range of 181 through 230.
(b) As of the effective date of this AD, no person may install,
on any affected airplane, a generator 2 that does not have the
modification referenced in paragraph (a) of this AD incorporated.
(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) Questions or technical information related to Pilatus
Service Bulletin No. 24-012, dated February 19, 1999, should be
directed to Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371
Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41
610 33 51. This service information may be examined at the FAA,
Central Region, Office of the Regional Counsel, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106.
(f) The modification required by this AD shall be done in
accordance with Pilatus Service Bulletin No. 24-012, dated February
19, 1999. 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 4: The subject of this AD is addressed in Swiss AD HB 99-
143, dated February 19, 1999.
(g) This amendment becomes effective on October 4, 1999.
Issued in Kansas City, Missouri, on August 5, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-21016 Filed 8-18-99; 8:45 am]
BILLING CODE 4910-13-P
