[Federal Register Volume 63, Number 82 (Wednesday, April 29, 1998)]
[Rules and Regulations]
[Pages 23381-23382]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11068]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-303-AD; Amendment 39-10503; AD 98-09-22]
RIN 2120-AA64
Airworthiness Directives; Aerospatiale Model ATR42-200, -300, and
-320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Aerospatiale Model ATR42-200, -300, and -320
series airplanes, that requires an inspection to detect fatigue
cracking of the windshield frame structure, and modification of the
windshield frame structure. This amendment is prompted by the issuance
of mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by this AD are intended
to prevent reduced structural integrity of the airplane resulting from
fatigue cracking of the windshield frame structure.
DATES: Effective June 3, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 3, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex
03, France. This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Aerospatiale Model ATR42-
200, -300, and -320 series airplanes was published in the Federal
Register on February 19, 1998 (63 FR 8373). That action proposed to
require an inspection to detect fatigue cracking of the windshield
frame structure, and modification of the windshield frame structure.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
The FAA estimates that 106 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 19 work hours per airplane to accomplish
the required inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection required by
this AD on U.S. operators is estimated to be $120,840, or $1,140 per
airplane.
It will take approximately 191 work hours per airplane to
accomplish the required modification specified in Aerospatiale Service
Bulletin ATR42-53-0093, Revision 1, dated February 19, 1996, at an
average labor rate of $60 per work hour. Required parts will be
provided by the manufacturer at no cost to the operators. Based on
these figures, the cost impact of this modification on U.S. operators
is estimated to be $11,460 per airplane.
It will take approximately 281 work hours per airplane to
accomplish the required 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 will be
provided by the manufacturer at no cost to the operators. Based on
these figures, the cost impact of this 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 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 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from 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 the following new
airworthiness directive:
98-09-22 Aerospatiale: Amendment 39-10503. Docket 97-NM-303-AD.
Applicability: Model ATR42-200, -300, and -320 series airplanes,
on which
[[Page 23382]]
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.
(d) The actions shall be done in accordance with the following
Aerospatiale Service Bulletins, which contain the specified
effective pages:
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Service bulletin referenced and Revision level
date Page number shown on page shown on page Date shown on page
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ATR42-53-0093, Revision 1, 1-4, 13.................. 1................. February 19, 1996.
February 19, 1996.
5-12, 14-41............. Original.......... April 26, 1995.
ATR42-53-0094, Revision 2, 1, 2, 8, 9, 16, 18, 39, 2................. February 19, 1996.
February 19, 1996. 40, 48, 53, 54.
3, 4, 7, 10-15, 17, 19- 1................. May 29, 1995.
24, 26, 27, 29-32, 34-
38, 47, 55, 56.
5, 6, 25, 28, 33, 41-46, Original.......... April 24, 1995
49-52.
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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 may be obtained from Aerospatiale, 316 Route de
Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
Note 4: The subject of this AD is addressed in French
airworthiness directive 95-126-061(B), dated June 21, 1995.
(e) This amendment becomes effective on June 3, 1998.
Issued in Renton, Washington, on April 21, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-11068 Filed 4-28-98; 8:45 am]
BILLING CODE 4910-13-U
