[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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