[Federal Register Volume 65, Number 8 (Wednesday, January 12, 2000)]
[Rules and Regulations]
[Pages 1767-1768]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-498]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-61-AD; Amendment 39-11508; AD 2000-01-10]
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 supersedes Airworthiness Directive (AD) 98-08-
07, which currently requires replacing the rudder and elevator pivot 
arms with parts of improved design on certain Pilatus Aircraft Ltd. 
(Pilatus) Model PC-7 airplanes. This AD requires replacing the rudder 
and elevator pivot arms with parts that have been improved since 
issuance of AD 98-08-07. 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 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 March 3, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 3, 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 65 09; 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-61-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: Roman T. Gabrys, Aerospace Engineer, 
FAA, Small Airplane Directorate, FAA, 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 PC-7 
airplanes was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on September 28, 1999 (64 FR 52260). The NPRM 
proposed to supersede AD 98-08-07, Amendment 39-10456 (63 FR 17323, 
April 9, 1998). AD 98-08-07 currently requires replacing the rudder and 
elevator pivot arms with parts of improved design.
    Accomplishment of AD 98-08-07 was required in accordance with 
Pilatus Service Bulletin No. PC7-55-001, Revision No. 1, dated June 20, 
1995.
    AD 98-08-07 was the result of reports of cracks in the elevator and 
rudder trim tab pivot arms on the above-referenced airplanes.
    The NPRM proposed to require replacing the rudder and elevator 
pivot arms with parts that have been improved since issuance of AD 98-
08-07.
    Accomplishment of the proposed action as specified in the NPRM 
would be required in accordance with Pilatus Service Bulletin No. 55-
003, dated July 7, 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.

[[Page 1768]]

Cost Impact

    The FAA estimates that 8 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 6 workhours per 
airplane to accomplish the required action, and that the average labor 
rate is approximately $60 an hour. Parts 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 a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 removing Airworthiness Directive 
(AD) 98-08-07, Amendment 39-10456, and by adding a new AD to read as 
follows:

2000-01-10 Pilatus Aircraft Ltd.: Amendment 39-11508; Docket No. 99-
CE-61-AD; Supersedes AD 98-08-07, Amendment 39-10456.

    Applicability: Model PC-7 airplanes, all manufacturer serial 
numbers (MSN) up to and including MSN 614, 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 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) Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD, replace the rudder and elevator pivot 
arms with parts of improved design (or FAA-approved equivalent part 
numbers), as specified in and in accordance with Pilatus Service 
Bulletin No. 55-003, dated July 7, 1999. The part numbers of the 
improved design pivot arms are reflected in the following chart:

------------------------------------------------------------------------
                                     Previous part
           Designation             number installed     New part number
                                    per AD 98-08-07
------------------------------------------------------------------------
Pivot arm, inner elevator.......  113.50.07.108.....  113.50.07.108
                                                       (green paint).
Pivot arm, outer elevator.......  113.50.07.109.....  113.50.07.109
                                                       (green paint).
Pivot arm, upper rudder.........  113.40.07.084.....  113.40.07.084
                                                       (green paint).
Pivot arm, lower rudder.........  113.40.07.083.....  113.40.07.083
                                                       (green paint).
------------------------------------------------------------------------

    (b) As of the effective date of this AD, no person may install, 
on any of the affected airplanes, an elevator or rudder pivot arm 
that is not of the improved design specified in paragraph (a) of 
this AD.
    (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 times that provides an equivalent level of safety may be 
approved by the Manager, Small Airplane Directorate, 901 Locust, 
Room 301, Kansas City, Missouri 64106.
    (1) 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.
    (2) Alternative methods of compliance approved in accordance 
with AD 98-08-07 are not considered approved as alternative methods 
of compliance for this AD.

    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) Questions or technical information related to Pilatus 
Service Bulletin No. 55-003, dated July 7, 1999, should be directed 
to Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 65 09; facsimile: +41 41 610 33 
51. This service information may be examined at the FAA, Central 
Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas 
City, Missouri 64106.
    (f) The replacements required by this AD shall be done in 
accordance with Pilatus Service Bulletin No. 55-003, dated July 7, 
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.

    Note 3: The subject of this AD is addressed in Swiss 
Airworthiness Directive HB 99-412, Effective Date: August 31, 1999.

    (g) This amendment supersedes AD 98-08-07, Amendment 39-10456.
    (h) This amendment becomes effective on March 3, 2000.

    Issued in Kansas City, Missouri, on January 4, 2000.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 00-498 Filed 1-11-00; 8:45 am]
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