[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