[Federal Register Volume 63, Number 68 (Thursday, April 9, 1998)]
[Proposed Rules]
[Pages 17341-17342]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9342]
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Proposed Rules
Federal Register
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This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 63, No. 68 / Thursday, April 9, 1998 /
Proposed Rules
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-97-AD]
RIN 2120-AA64
Airworthiness Directives; CASA Model C-212 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all CASA Model C-212 series
airplanes. This proposal would require repetitive inspections for
cracking in the false spar of the wing, and repair, if necessary. This
proposal is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified by the proposed AD are intended to detect and correct
cracking in the false spar, which could result in reduced structural
integrity of the wing.
DATES: Comments must be received by May 11, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-97-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain.
This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
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 shall 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.
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 summarizing 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 Number 98-NM-97-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, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-97-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direccion General de Aviacion (DGAC), which is the
airworthiness authority for Spain, notified the FAA that an unsafe
condition may exist on all CASA Model C-212 series airplanes. The DGAC
advises that, on several airplanes, cracking has been detected in the
false spar of the wing, where the flaps of the airplane are housed
during flight. The cause of this cracking has not been determined, but
indications are that such cracking may result from stress corrosion
caused by interference between the flaps and the wing trailing edge
structure, which occurs when the flaps are stowed in flight. Such
cracking, if not detected and corrected in a timely manner, could
result in reduced structural integrity of the wing.
Explanation of Relevant Service Information
The manufacturer has issued CASA Product Support Document COM 212-
224, dated November 28, 1990, which describes procedures for performing
repetitive detailed visual inspections for cracking in the false spar
of the wing. The DGAC classified this service document as mandatory and
issued Spanish airworthiness directive 02/96, dated May 13, 1996, in
order to assure the continued airworthiness of these airplanes in
Spain.
FAA's Conclusions
This airplane model is manufactured in Spain and is type
certificated for operation in the United States under the provisions of
Section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
actions specified in the service document described previously, except
as discussed below.
Differences Between Proposed Rule and Service Document
Operators should note that, although the service document specifies
that affected parts are to be removed if cracking is detected, this
proposal would require the repair of any cracking to be accomplished in
accordance with either a method approved by the FAA, or the DGAC (or
its delegated agent). In
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light of the type of repair that would be required to address the
unsafe condition, and in consonance with existing bilateral
airworthiness agreements, the FAA has determined that, for this
proposed AD, a repair approved by either the FAA or the DGAC would be
acceptable for compliance with this proposed AD.
Cost Impact
The FAA estimates that 41 airplanes of U.S. registry would be
affected by this proposed AD, and that it would take approximately 30
work hours per airplane to accomplish the proposed inspection, at an
average labor rate of $60 per work hour. Based on these figures, the
cost impact of the inspection proposed by this AD on U.S. operators is
estimated to be $73,800, or $1,800 per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted.
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 proposed
regulation (1) is not a `significant regulatory action' under Executive
Order 12866; (2) is not a `significant rule' under the 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 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, 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 the following new
airworthiness directive:
Construcciones Aeronauticas, S.A. (CASA): Docket 98-NM-97-AD.
Applicability: All Model C-212 series airplanes, 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 (b) 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, unless accomplished
previously.
To detect and correct cracking in the false spar of the wing,
which could result in reduced structural integrity of the wing,
accomplish the following:
(a) Within 1,200 flight hours after the effective date of this
AD, perform a detailed visual inspection for cracking in the false
spar of the wing, on the left and right side of the airplane, in
accordance with CASA Product Support Document COM 212-224, dated
November 28, 1990.
(1) If no cracking is detected, repeat the detailed visual
inspection thereafter at intervals not to exceed 1,200 flight hours.
(2) If any cracking is detected, prior to further flight, repair
in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Direccion General de Aviacion (DGAC), which is the
airworthiness authority for Spain (or its delegated agent). Repeat
the detailed visual inspection thereafter at intervals not to exceed
1,200 flight hours.
(b) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, International Branch, ANM-116.
Operators shall submit their request through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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.
Note 3: The subject of this AD is addressed in Spanish
airworthiness directive 02/96, dated May 13, 1996.
Issued in Renton, Washington, on April 3, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-9342 Filed 4-8-98; 8:45 am]
BILLING CODE 4910-13-U
