[Federal Register Volume 61, Number 216 (Wednesday, November 6, 1996)]
[Rules and Regulations]
[Pages 57315-57317]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-27676]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-CE-85-AD; Amendment 39-9801; AD 96-22-13]
RIN 2120-AA64


Airworthiness Directives: Pilatus Aircraft Ltd., Model PC-6 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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[[Page 57316]]

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Pilatus Aircraft Ltd. (Pilatus), Model PC-6 airplanes. This 
action requires inspecting for loose or sheared rivets in the hinge 
brackets on the horizontal stabilizer and inspecting for incorrect 
spacing tolerance of the hinge brackets. If the rivets are found loose 
or sheared, the AD requires replacing the rivets and also re-
positioning the hinge brackets, if found incorrectly spaced. Several 
reports of rivets shearing on the hinge brackets prompted this action. 
The actions specified by this AD are intended to prevent structural 
failure of the hinge bracket on the horizontal stabilizer, which could 
result in partial or complete loss of control of the horizontal 
stabilizer and loss of control of the airplane.

DATES: Effective December 27, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 27, 1996.

ADDRESSES: Service information that applies to this AD may be obtained 
from Pilatus Aircraft Ltd., CH-6370 Stans, Switzerland. This 
information may also be examined at the Federal Aviation Administration 
(FAA), Central Region, Office of the Assistant Chief Counsel, 
Attention: Rules Docket 95-CE-85-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: Mr. Roman T. Gabrys, Project Officer, 
Small Airplane Directorate, Aircraft Certification Service, FAA, 1201 
Walnut, suite 900, Kansas City, Missouri 64106; telephone (816) 426-
6934; facsimile (816) 426-2169.

SUPPLEMENTARY INFORMATION:

Events Leading to This Action

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Pilatus Model PC-6 
airplanes was published in the Federal Register on June 11, 1996 (61 FR 
29501). The action proposed to require the following:

-- Inspecting the hinge brackets attached to the fuselage for loose or 
sheared rivets,
--Inspecting the hinge brackets for correct spacing tolerance and 
positioning,
--Removing the brackets and adjusting any incorrect spacing or 
positioning, and
--Replacing any loose or sheared rivets with new rivets.

Related Service Information

    Accomplishment of this action would be in accordance with Pilatus 
Service Bulletin (SB) PC-6 165, dated February 7, 1994.

Comments

    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.

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 one airplane in the U.S. registry will be 
affected by this AD, that it will take less than 1 workhour per 
airplane to accomplish these actions, and that the average labor rate 
is approximately $60 an hour. Based on these figures, the total cost 
impact of this AD for the only U.S. operator is estimated to be $60. 
This is the cost of the inspection only and does not include the cost 
for replacing any loose rivets, if found. This figure is based on the 
assumption that the affected owner/operator of the affected airplane 
has not performed the inspection or modification.

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 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:

96-22-13  Pilatus Aircraft Ltd.: Amendment 39-9801; Docket No. 95-
CE-85-AD.

    Applicability: Model PC-6 airplanes (all serial numbers), 
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 (e) 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 within the next 75 hours time-in-service 
(TIS), after the effective date of this AD, unless already 
accomplished.

    Note 2: The compliance time required in this AD takes precedence 
over the compliance time in Pilatus Service Bulletin PC-6 165, dated 
February 7, 1994.

    To prevent structural failure of the hinge bracket on the 
horizontal stabilizer, which could result in partial or complete 
loss of control of the horizontal stabilizer and loss of control of 
the airplane, accomplish the following:
    (a) Inspect the hinge brackets on the horizontal stabilizer for 
sheared or loose rivets in accordance with paragraph 2.A. in the 
ACCOMPLISHMENT INSTRUCTIONS section of Pilatus Service Bulletin (SB) 
PC-6 165, dated February 7, 1994.

[[Page 57317]]

    (b) Inspect the spacing tolerance of the hinge bracket in 
accordance with paragraph 2.C. in the ACCOMPLISHMENT INSTRUCTIONS 
section of Pilatus SB PC-6 165, dated February 7, 1994.
    (c) If there are loose or sheared rivets or if the bracket 
spacing is out of the spacing tolerance, prior to further flight, 
modify the position and space tolerance of the hinge brackets, and 
replace any loose or sheared rivets in accordance with paragraph 
2.D. in the ACCOMPLISHMENT INSTRUCTIONS section of Pilatus SB PC-6 
165, dated February 7, 1994.
    (d) 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.
    (e) 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, Aircraft 
Certification Service, FAA, 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Small Airplane Directorate.

    (f) The inspection, modification, and replacement required by 
this AD shall be done in accordance of Pilatus Service Bulletin PC-6 
165, dated February 7, 1994. 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 of this document may be 
obtained from Pilatus Aircraft Ltd., CH-6370 Stans, Switzerland. 
Copies also may be inspected at the FAA, Central Region, Office of 
the Assistant Chief 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.
    (g) This amendment (39-9801) becomes effective on December 27, 
1996.

    Issued in Kansas City, Missouri, on October 22, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-27676 Filed 11-5-96; 8:45 am]
BILLING CODE 4910-13-U