[Federal Register Volume 64, Number 227 (Friday, November 26, 1999)]
[Rules and Regulations]
[Pages 66365-66366]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30520]
[[Page 66365]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-54-AD; Amendment 39-11433; AD 99-24-09]
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 modifying the flap inboard attachment
fittings through the installation of a reinforcement angle bracket on
the inside of the center web of both flap inner attachment fittings.
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 the potential of
the inboard flap attachment fittings buckling while operating at full
flaps with full power into a head-on wind gust, which could result in
loss of control of the airplane.
DATES: Effective January 14, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 14, 2000.
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-54-AD, 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.
FOR FURTHER INFORMATION CONTACT: Mr. Roman T. Gabrys, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas
City, Missouri 64106; telephone: (816) 329-4141; facsimile: (816) 329-
4090.
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 August 13, 1999
(64 FR 44137). The NPRM proposed to require modifying the flap inboard
attachment fittings through the installation of a reinforcement angle
bracket on the inside of the center web of both flap inner attachment
fittings. Accomplishment of the proposed action as specified in the
NPRM would be required in accordance with Pilatus Service Bulletin No.
57-004, dated June 11, 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 77 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 by the manufacturer
at no cost to the owners/operators of the affected airplanes. Based on
these figures, the total cost impact of this AD on U.S. operators is
estimated to be $23,100, or $300 per airplane.
Regulatory Impact
This rule does not have Federalism implications as defined in
Executive Order No. 13132. This means it does 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. The FAA has
not consulted with state authorities prior to publication of this rule.
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:
99-24-09 Pilatus Aircraft Ltd.: Amendment 39-11433; Docket No. 99-
CE-54-AD.
Applicability: Models PC-12 and PC-12/45 airplanes, manufacturer
serial number (MSN) 101 through MSN 300, 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.
[[Page 66366]]
To prevent the potential for the inboard flap attachment
fittings buckling while operating at full flaps with full power into
a head-on wind gust, which could result in 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, modify the flap inboard attachment
fittings by installing a reinforcement angle bracket on the inside
of the center web of both flap inner attachment fittings
(Modification Kit Number 500.50.12.199). Accomplish this
modification in accordance with the Accomplishment Instructions
section of Pilatus Service Bulletin No. 57-004, dated June 11, 1999.
(b) As of the effective date of this AD, no person may install
on any of the affected airplanes, flap inboard attachment fittings
that do not have Modification Kit Number 500.50.12.199 incorporated.
(c) Special flight permits may be issued in accordance with
Secs. 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, 901 Locust,
Room 301, 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 2: 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 modification required by this AD shall be done in
accordance with Pilatus Service Bulletin No. 57-004, dated June 11,
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, 901
Locust, Room 506, Kansas City, Missouri, or at the Office of the
Federal Register, 800 North Capitol Street, NW, suite 700,
Washington, DC.
(f) This amendment becomes effective on January 14, 2000.
Issued in Kansas City, Missouri, on November 15, 1999.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-30520 Filed 11-24-99; 8:45 am]
BILLING CODE 4910-13-P
