[Federal Register Volume 63, Number 53 (Thursday, March 19, 1998)]
[Proposed Rules]
[Pages 13374-13376]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7089]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-14-AD]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company 180, 182, and
185 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to all Cessna Aircraft Company (Cessna) 180, 182,
and 185 series airplanes equipped with wing extension supplemental type
certificate (STC) SA00276NY. The proposed action would require
inspecting between wing station (W.S.) 90 and W.S. 110 for an angle
stiffener at the lower wing spar splice. If the angle stiffener is not
installed, the proposed action would require installing a reinforcing
strap. The proposed action is the result of failed test results
revealing that the wings of these Cessna airplanes, without the
stiffener, do not meet the applicable design requirements after being
modified by the above STC. The actions specified by the proposed AD are
intended to prevent wing failure during flight, which, if not
corrected, could cause loss of control of the airplane.
DATES: Comments must be received on or before May 15, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 97-CE-14-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106. Comments may be inspected at this location
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from Air Research Technology, Inc., 3440 McCarthy, Montreal, Quebec,
Canada H4K 2P5; telephone (514) 337-7588; facsimile (514) 337-3293.
This information also may be examined at the Rules Docket at the
address above.
FOR FURTHER INFORMATION CONTACT: Sol Maroof, Aerospace Engineer, New
York Aircraft Certification Office, 10 Fifth Street, 3rd Floor, Valley
Stream, New York, 11581-1200; telephone (516) 256-7522; facsimile (516)
568-2716.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
[[Page 13375]]
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 97-CE-14-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 97-CE-14-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The FAA has been notified by the Canadian civil airworthiness
authority, Transport Canada, that certain Cessna 180, 182, and 185
series airplanes, equipped with wing extensions by way of supplemental
type certificate (STC) SA00276NY, may not have had a wing stiffener
installed at factory. This condition has been discovered on several of
these airplanes during routine inspections. Since this discovery,
further investigation has shown that without the wing stiffener, the
wing is susceptible to structural failure. Both the FAA and Transport
Canada have been in contact with the manufacturer of this particular
STC and have approved an alternative to the wing stiffener. Tests have
shown that the wing would be stabilized by installing a wing
reinforcement strap to add strength to this area of the wing, if it is
without the wing stiffener.
Relevant Service Information
Air Research Technology, Inc. has issued Service Bulletin No. SB-1-
96, Issue 1, dated April 11, 1996, which specifies procedures for
visually inspecting the underside of the wing, aft of the spar, closest
to where the strut connects to the wing, for the installation of an
angle stiffener along the lower spar cap between Wing Station (W.S.) 90
and W.S. 110. If an angle stiffener is not installed, then the service
information provides procedures for installing a stainless steel
reinforcement strap on the underside of the wing, along the spar, at
W.S. 100.50.
The FAA's Determination
After examining the circumstances and reviewing all available
information, including the relevant service information, related to the
incidents described above, the FAA has determined that AD action should
be taken to prevent wing failure during flight, which, if not corrected
could cause loss of control of the airplane.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other (Cessna) 180, 182, and 185 series airplanes
equipped with wing extension STC SA00276NY, the proposed AD would
require inspecting the inside of the underside of the wing, near Wing
Station (W.S.) 100, for an angle stiffener. If an angle stiffener is
not installed, the proposed AD would require installing a reinforcement
strap along the lower wing spar.
Cost Impact
The FAA estimates that there are 55 airplanes in the U.S. registry
that would be affected by the proposed AD, that it would take
approximately 1 workhour for the initial inspection and 7 workhours for
the installation of the reinforcement strap per airplane, and that the
average labor rate is approximately $60 an hour. Parts are supplied by
the wing extension kit manufacturer at no cost to the owner/operator.
Based on these figures, the total cost impact of the proposed AD on
U.S. operators is estimated to be $26,400 or $480 per airplane. The FAA
has no way to determine the number of owners/operators who may have
already accomplished the proposed action, and would presume that none
of the owners/operators of the affected airplanes have accomplished the
proposed action.
Regulatory Impact
The regulations proposed herein would 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
proposal would 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) if promulgated,
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 draft regulatory evaluation
prepared for this action has been placed 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Cessna Aircraft Company: Docket No. 97-CE-14-AD.
Applicability: The following airplane models (all serial
numbers), certificated in any category, that are equipped with wing
extension supplemental type certificate (STC) SA00276NY.
Models
180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K,
182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K,
182L, 182M, 182N, 182P, 182Q, 182R, 182S, R182, T182, TR182, 185,
185A, 185B, 185C, 185D, 185E, A185E, A185F
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.
[[Page 13376]]
Compliance: Required within the next 50 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
To prevent wing failure during flight, which, if not corrected,
could cause loss of control of the airplane, accomplish the
following:
(a) Inspect inside both left and right wings, aft of the spar,
closest to where the strut connects to the wing, for an angle
stiffener along the lower spar cap between Wing Station (W.S.) 90
and W.S. 110 in accordance with Part A of the Accomplishment
Instructions of Air Research Technology, Inc. (ART) Service Bulletin
(SB) No. SB-1-96, Issue 1, dated April 11, 1996.
(b) If an angle stiffener is not installed, prior to further
flight, install a stainless steel reinforcement strap on the
underside of each wing, along the spar at W.S. 100.50 in accordance
with Part B of the Accomplishment Instructions of ART SB No. SB-1-
96, Issue 1, dated April 11, 1996.
(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 time that provides an equivalent level of safety may be
approved by the Manager, New York Aircraft Certification Office, 10
Fifth Street, 3rd Floor, Valley Stream, New York, 11581-1200. The
request shall be forwarded through an appropriate FAA Maintenance
Inspector, who may add comments and then send it to the Manager, New
York Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York Aircraft Certification Office.
(e) All persons affected by this directive may obtain copies of
the document referred to herein upon request to Air Research
Technology, Inc., 3440 McCarthy, Montreal, Quebec, Canada H4K 2P5;
or may examine this document at the FAA, Central Region, Office of
the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
Issued in Kansas City, Missouri, on March 11, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-7089 Filed 3-18-98; 8:45 am]
BILLING CODE 4910-13-U