[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]
BILLING CODE 4910-13-U
