[Federal Register Volume 63, Number 69 (Friday, April 10, 1998)]
[Rules and Regulations]
[Pages 17670-17672]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9343]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-107-AD; Amendment 39-10457; AD 98-08-08]
RIN 2120-AA64
Airworthiness Directives; Aerospatiale Model ATR42-500 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Aerospatiale Model ATR42-500 series airplanes.
This action requires a one-time inspection to verify the installation
of certain stringer clips at the junction of frame 34 and stringer 6,
and installation of stringer clips, if necessary. This amendment is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified in
this AD are intended to prevent fatigue cracking in the skin of the
fuselage, which could result in loss of pressure inside the airplane.
DATES: Effective April 27, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 27, 1998.
Comments for inclusion in the Rules Docket must be received on or
before 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-107-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
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 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.
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: 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
ATR42-500 series airplanes. The DGAC advises that the manufacturer has
reported that certain stringer clips were not installed during
production on several in-service airplanes. The stringer clips are
missing at the junction of frame 34 and stringer 6 of the fuselage.
Without the installation of these clips, fatigue cracking may occur in
the skin of the fuselage. This condition, if not corrected, could
result in a loss of pressure inside the airplane.
Explanation of Relevant Service Information
The manufacturer has issued Aerospatiale Service Bulletin ATR42-
[[Page 17671]]
53-0103, dated September 23, 1996, which describes procedures for
installing stringer clips at the junction of frame 34 and stringer 6,
on the left and right side of the airplane. Accomplishment of the
actions specified in the service bulletin is intended to adequately
address the identified unsafe condition. The DGAC classified this
service bulletin as mandatory and issued French airworthiness directive
96-132-065(B), dated July 3, 1996, 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 the 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, this AD is being issued to prevent fatigue
cracking in the skin of the fuselage, which could result in loss of
pressure inside the airplane. This AD requires accomplishment of the
actions specified in the service bulletin described previously, except
as described below.
Differences Between This AD, Foreign Airworthiness Directive, and
Service Bulletin
Operators should note that this AD differs from procedures
described in the foreign airworthiness directive and the service
bulletin in that it requires a one-time inspection to verify whether
installation of the stringer clips at the junction of frame 34 and
stringer 6 has been accomplished, and installation of the stringer
clips on the condition that the clips are not already installed. The
foreign airworthiness directive and the service bulletin specify only
that the stringer clips be installed at the junction of frame 34 and
stringer 6. The FAA has determined that because the possibility exists
that installation of stringer clips at the junction of frame 34 and
stringer 6 has already been accomplished, before installing stringer
clips, operators should first conduct an inspection of the junction of
frame 34 and stringer 6 to ensure that installation of such clips has
not already been accomplished.
Cost Impact
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this rule
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 6 work hours to
accomplish the installation, if necessary, at an average labor rate of
$60 per work hour. Required parts would be provided by the manufacturer
at no cost to the operator. Based on these figures, the cost impact of
this AD would be $360 per airplane.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, prior notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
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 under the caption
ADDRESSES. All communications received on or before the closing date
for comments will be considered, and this rule may be amended in light
of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-107-AD.'' The postcard will be date stamped and
returned to the commenter.
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:
[[Page 17672]]
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:
98-08-08 Aerospatiale: Amendment 39-10457. Docket 98-NM-107-AD.
Applicability: Model ATR42-500 series airplanes, as listed in
Aerospatiale Service Bulletin ATR42-53-0103, dated September 23,
1996; 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 prevent fatigue cracking in the skin of the fuselage, which
could result in loss of pressure inside the airplane, accomplish the
following:
(a) Within 3,000 flight cycles after the effective date of this
AD, perform a one-time visual inspection to verify the installation
of stringer clips at the junction of frame 34 and stringer 6, on the
left and right side of the airplane.
(1) If the stringer clips have been installed, no further action
is required by this AD.
(2) If any stringer clip has not been installed, prior to
further flight, install the stringer clip, in accordance with
Aerospatiale Service Bulletin ATR42-53-0103, dated September 23,
1996.
(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, FAA,
Transport Airplane Directorate. 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.
(d) The installation shall be done in accordance with
Aerospatiale Service Bulletin ATR42-53-0103, dated September 23,
1996. 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 3: The subject of this AD is addressed in French
airworthiness directive 96-132-065(B), dated July 3, 1996.
(e) This amendment becomes effective on April 27, 1998.
Issued in Renton, Washington, on April 3, 1998.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-9343 Filed 4-9-98; 8:45 am]
BILLING CODE 4910-13-U
