Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-7 Airplanes

[Federal Register Volume 63, Number 68 (Thursday, April 9, 1998)]
[Rules and Regulations]
[Pages 17323-17324]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9153]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-149-AD; Amendment 39-10456; AD 98-08-07]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-7 
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) Model PC-7 
airplanes. This AD requires replacing the rudder and elevator pivot 
arms with parts of improved design. This AD results from reports of 
cracks in the elevator and rudder trim tab pivot arms on the above-
referenced airplanes. The actions specified by this AD are intended to 
prevent failure of the elevator and rudder caused by fatigue cracking 
of the pivot arms, which could result in reduced airplane 
controllability and possible loss of control of the airplane.

DATES: Effective April 28, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 28, 1998.

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 6509; facsimile: +41 41 610 3351. 
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-149-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: Roman T. Gabrys, Project Officer, 
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 Model 
PC-7 airplanes was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on February 2, 1998 (63 FR 5765). The NPRM 
proposed to require replacing the rudder and elevator pivot arms with 
parts of improved design. Accomplishment of the proposed action as 
specified in the NPRM would be in accordance with Pilatus Service 
Bulletin No. PC7-55-001, Revision No. 1, dated June 20, 1995.
    The NPRM was the result of reports of cracks in the elevator and 
rudder trim tab pivot arms on the above-referenced airplanes.
    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 8 airplanes in the U.S. registry will be 
affected by the replacement required by this AD, that it will take 
approximately 6 workhours per airplane to accomplish this replacement, 
and that the average labor rate is approximately $60 an hour. 
Modification kits cost approximately $300 per airplane. Based on these 
figures, the total cost impact of this AD on U.S. operators is 
estimated to be $5,280, or $660 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

[[Page 17324]]

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:

98-08-07  Pilatus Aircraft Ltd.: Amendment 39-10456; Docket No. 97-
CE-149-AD.

    Applicability: Model PC-7 airplanes, serial numbers MSN 001 
through MSN 564, 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 (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 upon accumulating 1,000 hours time-in-
service (TIS) or within the next 100 hours TIS after the effective 
date of this AD, whichever occurs later, unless already 
accomplished.
    To prevent fatigue failure of the elevator and rudder trim tab 
pivot arms because of cracks, which could result in the loss of 
airplane control, accomplish the following:
    (a) Replace the rudder and elevator pivot arms with parts of 
improved design as specified in and in accordance with Pilatus 
Service Bulletin No. PC7-55-001, Revision No. 1, dated June 20, 
1995.
    (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 
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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Small Airplane Directorate.

    (d) Questions or technical information related to Pilatus 
Service Bulletin No. PC7-55-001, Revision No. 1, dated June 20, 
1995, should be directed to Pilatus Aircraft Ltd., Customer Liaison 
Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6509; 
facsimile: +41 41 610 3351. 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.
    (e) The replacement required by this AD shall be done in 
accordance with Pilatus Service Bulletin No. PC7-55-001, Revision 
No. 1, dated June 20, 1995. 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.
    (f) This amendment becomes effective on April 28, 1998.

    Issued in Kansas City, Missouri, on March 31, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-9153 Filed 4-8-98; 8:45 am]
BILLING CODE 4910-13-U

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