[Federal Register Volume 60, Number 114 (Wednesday, June 14, 1995)]
[Rules and Regulations]
[Pages 31232-31234]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-14317]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-61-AD; Amendment 39-9274; AD 95-12-22]
Airworthiness Directives; Airbus Model A340-211, -212, -311, and
-312 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 Airbus Model A340 series airplanes. This action
requires installation of a reinforcement modification on the structure
of the left- and right-hand cowls of the thrust reversers. This
amendment is prompted by the results of a full-scale fatigue test,
conducted by the manufacturer, which indicated that fatigue cracks can
occur between the 3 and 9 o'clock thrust reverser beams and the forward
frame/``J''-ring. The actions specified in this AD are intended to
prevent loss of the use of the thrust reversers as a result of the
problems associated with fatigue cracking in their cowling structure.
DATES: Effective June 29, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 29, 1995.
Comments for inclusion in the Rules Docket must be received on or
before August 14, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-61-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
The service information referenced in this AD may be obtained from
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France. This information may be examined at
[[Page 31233]]
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: Stephen Slotte, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1320.
SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile
(DGAC), which is the airworthiness authority for France, recently
notified the FAA that an unsafe condition may exist on certain Airbus
Model A340-211, -212, -311, and -312 series airplanes. The DGAC advises
that results of a full-scale fatigue test, which was conducted by
Airbus Industrie, indicate that fatigue cracking can occur between the
3 and 9 o'clock thrust reverser beams and the forward frame/``J''-ring
in the thrust reversers' cowling structure. This condition, if not
corrected, could result in loss of the use of the thrust reversers as a
result of the problems associated with fatigue cracking in their
cowling structure.
Airbus Industrie has issued Service Bulletin A340-78-4002, Revision
2, dated October 14, 1994, which describes procedures for installing a
reinforcement modification on the structure of the left- and right-hand
cowls of the thrust reversers. This modification consists of the
installation of modified fittings between the forward frame and the 3
and 9 o'clock thrust reverser beams, and between the 3 and 9 o'clock
beams and the internal fixed structure of the thrust reverser. This
modification is intended to improve the load transfer between the 3 and
9 o'clock thrust reverser beams and the forward frame/``J''-ring. The
DGAC classified this service bulletin as mandatory and issued French
Airworthiness Directive (CN) 94-055-006(B)(R1), dated April 13, 1994,
in order to assure the continued airworthiness of these airplanes in
France.
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 21.19) 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.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, this AD is
being issued to prevent loss of the use of the thrust reversers as a
result of the problems associated with fatigue cracking in their
cowling structure. This AD requires installation of a reinforcement
modification on the structure of the left- and right-hand cowls of the
thrust reversers. The actions are required to be accomplished in
accordance with the service bulletin described previously.
The modification of the right-hand cowl of the thrust reverser unit
having serial number 3062, which is installed on the affected airplane
having manufacturer's serial number (MSN) 011, is required at an
interval sooner than the modification of the other cowls. That
particular cowl section is required to be modified at 900 landings,
whereas, the other cowl sections are required to be modified at 4,000
landings. This difference in these compliance times is due to the fact
that the right-hand thrust reverser cowl section having serial number
3062 has an established life-limit of 900 cycles. In order to maintain
the structural integrity of that part, it is necessary that it be
modified before its currently-established life-limit is attained.
There currently are no Model A340-211, -212, -311, or -312 series
airplanes 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 92 work hours to
accomplish the required actions, at an average labor charge of $60 per
work hour. Required parts would be provided by the manufacturer at no
cost to operators. Based on these figures, the total cost impact of
this AD would be $5,520 per airplane.
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, 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 95-NM-61-AD.'' The postcard will be date stamped and
returned to the commenter.
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
[[Page 31234]]
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-12-22 Airbus: Amendment 39-9274. Docket 95-NM-61-AD.
Applicability: Model A340-211, -212, -311, and -312 series
airplanes; as listed in Airbus Service Bulletin A340-78-4002,
Revision 2, dated October 14, 1994; on which Modification No. 42445
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
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 use the authority
provided in paragraph (c) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of the use of the thrust reversers as a result
of the problems associated with fatigue cracking in their cowling
structure, accomplish the following:
(a) Except as required by paragraph (b) of this AD: Prior to the
accumulation of 4,000 total flight cycles or within 48 months after
the effective date of this AD, whichever occurs later, install the
reinforcement modification on the structure of the left- and right-
hand thrust reverser cowls in accordance with Airbus Service
Bulletin A340-78-4002, Revision 2, dated October 14, 1994.
(b) This paragraph applies to the right-hand cowl of the thrust
reverser installed on the affected airplane having manufacturer's
serial number (MSN) 011: Prior to the accumulation of 900 total
flight cycles or within 12 months after the effective date of this
AD, whichever occurs later, install the reinforcement modification
on the structure of the right-hand cowl of the thrust reverser unit,
serial number 3062, in accordance with Airbus Service Bulletin A340-
78-4002, Revision 2, dated October 14, 1994.
(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, Standardization Branch, ANM-113,
FAA, Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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.
(e) The installation of the modification shall be done in
accordance with Airbus Service Bulletin A340-78-4002, Revision 2,
dated October 14, 1994. 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 Airbus
Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
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.
(f) This amendment becomes effective on June 29, 1995.
Issued in Renton, Washington, on June 6, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-14317 Filed 6-13-95; 8:45 am]
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