[Federal Register Volume 63, Number 27 (Tuesday, February 10, 1998)]
[Proposed Rules]
[Pages 6683-6685]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3233]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-266-AD]
RIN 2120-AA64
Airworthiness Directives; Aerospatiale Model ATR42-200 and -300
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 certain Aerospatiale Model ATR42-
200 and -300 series airplanes. This proposal would require repetitive
inspections for cracking of the lower skin panels of the outer wings;
and repair, if necessary. This proposal also would require modification
of the panels and a follow-on inspection to detect cracking of the
modified areas, which would constitute terminating action for the
repetitive inspections. This proposal is prompted by the issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by the proposed AD are
intended to prevent fatigue cracking of the lower skin panels of the
outer wings, and consequent reduced structural integrity of the
airplane.
DATES: Comments must be received by March 12, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-266-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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex
03, France. This information may be examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.
[[Page 6684]]
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 97-NM-266-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. 97-NM-266-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on certain Aerospatiale Model ATR 42-200 and -300
series airplanes. The DGAC advises that full-scale fatigue testing by
the manufacturer has revealed damage of the lower skin panels of the
outer wings at several rib junction attachments. Such fatigue cracking,
if not detected and corrected in a timely manner, could result in
reduced structural integrity of the airplane.
Explanation of Relevant Service Information
Aerospatiale has issued Service Bulletin ATR42-57-0040, dated April
21, 1994, which describes procedures for repetitive ultrasonic
inspections for cracking of the lower skin panels of the outer wings at
rib 14. Aerospatiale also has issued Service Bulletin ATR42-57-0038,
Revision 2, dated December 18, 1997, which describes procedures for
modification of the lower skin panels of the outer wings at ribs 13 and
14, and a follow-on high frequency eddy current (HFEC) inspection to
detect cracking of the modified area. The modification involves
expansion of some holes located between ribs 13 and 18 (left and right
sides) to increase resistance of corresponding areas. Accomplishment of
the modification and the HFEC inspection would eliminate the need for
the repetitive ultrasonic inspections. The DGAC classified these
service bulletins as mandatory. Additionally, the DGAC previously
issued a French airworthiness directive [93-190-051(B), dated October
27, 1993] in order to assure the continued airworthiness of these
airplanes in France.
FAA's Conclusions
This airplane model is manufactured in France 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
the actions specified in the service bulletin described previously,
except as described below.
Differences Between the Proposed AD and the Related Service
Information
The proposed AD would differ from Aerospatiale Service Bulletins
ATR42-57-0038 and ATR42-57-0040, described previously, in that the
service bulletins recommend that any crack detected during an
inspection be repaired in accordance with instructions requested from
the manufacturer. However, the FAA has determined that the repair of
any crack would be required to be accomplished in accordance with a
method approved by the FAA.
Cost Impact
The FAA estimates that 101 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 4 work hours per airplane to accomplish
the proposed ultrasonic inspection, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of the ultrasonic
inspection proposed by this AD on U.S. operators is estimated to be
$24,240, or $240 per airplane, per inspection cycle.
It would take approximately 280 work hours per airplane to
accomplish the proposed modification, at an average labor rate of $60
per work hour. The cost of required parts could range from $1,576 to
$6,373 per airplane. Based on these figures, the cost impact of the
modification proposed by this AD on U.S. operators is estimated to be
between $1,855,976 ($18,376 per airplane) and $2,340,473 ($23,173 per
airplane).
The cost impact figures discussed above are 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
[[Page 6685]]
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:
Aerospatiale: Docket 97-NM-266-AD.
Applicability: Model ATR42-200 and -300 series airplanes on
which Aerospatiale Service Bulletins ATR42-57-0040, dated April 21,
1994, and ATR42-57-0038, Revision 2, dated December 18, 1997, have
not been accomplished; certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 (c) 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 prevent fatigue cracking of the lower skin panels of the
outer wings between ribs 13 and 18, and consequent reduced
structural integrity of the airplane, accomplish the following:
(a) Prior to the accumulation of 25,500 total landings, or
within 500 landings after the effective date of this AD, whichever
occurs later, perform an ultrasonic inspection for cracking of the
lower skin panels of the outer wings, in accordance with
Aerospatiale Service Bulletin ATR42-57-0040, dated April 21, 1994.
If any crack is detected, prior to further flight, repair it in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate. Thereafter,
repeat the inspection at intervals not to exceed 9,000 landings.
(b) Prior to the accumulation of 32,500 total landings, or
within 500 landings after the effective date of this AD, whichever
occurs later, modify the lower skin panels of the outer wings, and
perform a follow-on high frequency eddy current (HFEC) inspection
for cracking of the modified areas, in accordance with Aerospatiale
Service Bulletin ATR42-57-0038, Revision 2, dated December 18, 1997.
If any crack is detected, prior to further flight, repair it in
accordance with a method approved by the Manager, International
Branch, ANM-116. Accomplishment of the modification and follow-on
HFEC inspection constitutes terminating action for the repetitive
ultrasonic inspection requirements of paragraph (a) of this AD.
(c) 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 requests 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.
(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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 93-190-051(B), dated October 27, 1993.
Issued in Renton, Washington, on February 3, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-3233 Filed 2-9-98; 8:45 am]
BILLING CODE 4910-13-U