[Federal Register Volume 63, Number 33 (Thursday, February 19, 1998)]
[Proposed Rules]
[Pages 8373-8374]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-4110]
[[Page 8373]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-303-AD]
RIN 2120-AA64
Airworthiness Directives; Aerospatiale Model ATR42-200, -300, and
-320 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, -300, and -320 series airplanes. This proposal would require an
inspection to detect fatigue cracking of the windshield frame
structure, and modification of the windshield frame structure. 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
reduced structural integrity of the airplane resulting from fatigue
cracking of the windshield frame structure.
DATES: Comments must be received by March 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-303-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.
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-303-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-303-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 ATR42-200, -300, and
-320 series airplanes. The DGAC advises that it has received reports of
fatigue cracking on in-service airplanes. The cracking began at the
lower end of the center post of the windshield frame structure. 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 Bulletins ATR42-53-0093, Revision
1, and ATR42-53-0094, Revision 2, both dated February 19, 1996. These
service bulletins describe procedures for an inspection to detect
fatigue cracking of the windshield frame structure, and modification of
the windshield frame structure. Accomplishment of the modification
involves installation of new supports and nut plates. Accomplishment of
these actions specified in the service bulletins is intended to
adequately address the identified unsafe condition. The DGAC classified
these service bulletins as mandatory and issued French airworthiness
directive 95-126-061(B), dated June 21, 1995, 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
Sec. 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 bulletins described previously,
except as discussed below.
Differences Between the Proposed Rule and the Service Information
Whereas Aerospatiale Service Bulletin ATR42-53-0094 requires that
operators contact the manufacturer for repair instructions for any
crack exceeding a specified length, this proposed AD would require that
repair of such cracking be accomplished in accordance with a method
approved by the FAA.
Cost Impact
The FAA estimates that 106 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 19 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 $120,840, or
$1,140 per airplane.
It would take approximately 191 work hours per airplane to
accomplish the proposed modification specified in
[[Page 8374]]
Aerospatiale Service Bulletin ATR42-53-0093, Revision 1, dated February
19, 1996, at an average labor rate of $60 per work hour. Required parts
would be provided by the manufacturer at no cost to the operators.
Based on these figures, the cost impact of this proposed modification
on U.S. operators is estimated to be $11,460 per airplane.
It would take approximately 281 work hours per airplane to
accomplish the proposed modification specified in Aerospatiale Service
Bulletin ATR42-53-0094, Revision 2, dated February 19, 1996, at an
average labor rate of $60 per work hour. Required parts would be
provided by the manufacturer at no cost to the operators. Based on
these figures, the cost impact of this proposed modification on U.S.
operators is estimated to be $16,860 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 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-303-AD.
Applicability: Model ATR42-200, -300, and -320 series airplanes,
on which Aerospatiale Modification 01392 has not been installed,
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 (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 prevent reduced structural integrity of the airplane
resulting from fatigue cracking of the windshield frame structure,
accomplish the following:
(a) Prior to the accumulation of 24,000 total flight cycles, or
within 60 days after the effective date of this AD, whichever occurs
later: Inspect to detect cracking of the windshield frame structure
in accordance with Operation Description (B--Inspection) of the
Accomplishment Instructions of Aerospatiale Service Bulletin ATR42-
53-0093, Revision 1, or ATR42-53-0094, Revision 2, both dated
February 19, 1996.
(1) If the inspection reveals no crack, or reveals cracking that
does not exceed the specifications listed in Figure 6, Sheet 1, of
Service Bulletin ATR42-53-0093, Revision 1, dated February 19, 1996:
Prior to further flight, modify the windshield frame structure in
accordance with either service bulletin.
(2) If the inspection reveals any crack that exceeds the
specifications in Figure 6, Sheet 1, of Service Bulletin ATR42-53-
0093, Revision 1, dated February 19, 1996, but does not exceed the
cut-out areas specified in Figure 7, Sheet 1, of Service Bulletin
ATR42-53-0094, Revision 2, dated February 19, 1996: Prior to further
flight, modify the windshield frame structure in accordance with
Service Bulletin 42-53-0094, Revision 2, dated February 19, 1996.
(3) If the inspection reveals any crack that exceeds the cut-out
areas specified in Figure 7, Sheet 1, of Service Bulletin ATR42-53-
0094, Revision 2, dated February 19, 1996: Prior to further flight,
modify the windshield frame structure in accordance with a method
approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate.
Note 2: Accomplishment of the modifications specified in ATR
Service Bulletin ATR42-53-0093, Revision 1, or ATR42-53-0094,
Revision 2, both dated February 19, 1996, is not equivalent to
accomplishment of Aerospatiale Modification 01392. Therefore the
ATR42 Time Limits Document inspection items with ``PRE MOD 1392''
effectivity are still applicable for airplanes modified by either of
the previously described service bulletins.
(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 requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 3: 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 4: The subject of this AD is addressed in French
airworthiness directive 95-126-061(B), dated June 21, 1995.
Issued in Renton, Washington, on February 11, 1998.
Gilbert L. Thompson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-4110 Filed 2-18-98; 8:45 am]
BILLING CODE 4910-13-U
