[Federal Register Volume 66, Number 164 (Thursday, August 23, 2001)]
[Rules and Regulations]
[Pages 44291-44293]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21105]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-257-AD; Amendment 39-12385; AD 2001-16-16]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 and A340 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) that 
is applicable to all Airbus Model A330 and A340 series airplanes. This 
action requires a one-time inspection to detect cracking of the bogie 
beams of the main landing gear (MLG), and follow-on actions, if 
necessary. This action is necessary to detect and correct cracking of 
the MLG bogie beams, which could result in failure of the beams and 
consequent loss of the landing gear wheels and brakes, and structural 
damage to the MLG strut and airframe. This action is intended to 
address the identified unsafe condition.

DATES: Effective September 7, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 7, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before September 24, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-257-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. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-257-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    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 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

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 all Airbus Model 
A330 and A340 series airplanes. The DGAC advises that, during a C-check 
on a Model A330 series airplane, a crack was discovered in the upper 
part of the left-hand bogie beam of the main landing gear (MLG), in the 
area of the forward bogie stop pad. The crack was 120 mm (6 inches) 
long and 12 mm (0.4 inch) deep, and extended longitudinally along the 
bogie, underneath the stop pad. The airplane had accumulated a total of 
approximately 10,000 flight hours and 6,000 flight cycles.
    The retraction link on that MLG had previously failed, leading to 
an undamped extension of the MLG. The failure occurred approximately 
1,000 flight cycles and 11 months before the crack was discovered in 
the bogie beam. Analysis has shown that, due to the retraction link 
failure, loading in this area of the bogie is significantly greater 
than normally expected. Detailed analysis has not identified any other 
situation in which the load would cause such damage.
    There have been four in-service retraction link failures. In two 
cases, the

[[Page 44292]]

affected landing gears were replaced. There was a similar visible crack 
discovered on one of the bogies, which was installed on an airplane 
that had accumulated approximately 16,000 total flight hours and 7,000 
total flight cycles. Another was put in storage following the 
retraction failure and was subsequently inspected, revealing a crack. 
Inspection of a number of spare bogies that had been removed from 
service and had not been involved in retraction link failure incidents 
has revealed no similar cracks. It should be noted, however, that no 
proven connection has been made between failure of the retraction links 
and cracking in the bogie beams.
    Cracking of the MLG bogie beam could result in failure of the beam 
and consequent loss of the landing gear wheels and brakes, and 
structural damage to the MLG strut and airframe.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A330-32A3137, dated 
July 19, 2001; and AOT A340-32A4174, dated July 19, 2001. The AOTs 
describe procedures for a one-time visual inspection to detect cracking 
of the bogie beams of the MLG, in the area around the bogie stop pad. 
The AOTs also describe procedures for follow-on actions for certain 
conditions, if necessary. The DGAC classified these AOTs as mandatory 
and issued French telegraphic airworthiness directive T2001-320(B), 
dated July 20, 2001, to ensure the continued airworthiness of these 
airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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 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 detect and correct 
cracking of the MLG bogie beams, which could result in failure of the 
beams and consequent loss of the landing gear wheels and brakes, and 
structural damage to the MLG strut and airframe. This AD requires 
accomplishment of the actions specified in the AOTs described 
previously, except as discussed below.

Difference Between AD and AOTs

    Although the AOTs specify that the manufacturer may be contacted 
for disposition of certain inspection findings, this AD requires 
follow-on actions to be accomplished in accordance with a method 
approved by either the FAA or the DGAC (or its delegated agent).

Interim Action

    This is considered to be interim action. The manufacturer has 
indicated its intent to investigate the cracked MLG bogie beams and any 
additional findings to confirm the cause of the cracking. If final 
action is developed in the future to address the identified unsafe 
condition, the FAA may consider further rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an 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.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the AD is 
being requested.
     Include justification (e.g., reasons or data) for each 
request.
    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 2001-NM-257-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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

[[Page 44293]]

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:

2001-16-16  Airbus Industrie: Amendment 39-12385. Docket 2001-NM-
257-AD.

    Applicability: All Model A330 and A340 series airplanes, 
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 detect and correct cracking of the bogie beams of the main 
landing gear (MLG), which could result in failure of the beams and 
consequent loss of the landing gear wheels and brakes, and 
structural damage to the MLG strut and airframe, accomplish the 
following:

Inspection

    (a) Within 14 days or 50 flight cycles after the effective date 
of this AD, whichever occurs first: Perform a one-time general 
visual inspection to detect cracking of both MLG bogie beams, in 
accordance with Airbus All Operators Telex (AOT) A330-32A3137 (for 
Model A330 series airplanes) or A340-32A4174 (for Model A340 series 
airplanes), both dated July 19, 2001.
    (1) If any cracking of the base metal is detected, prior to 
further flight, replace the bogie beam assembly with a new assembly, 
in accordance with the AOT.
    (2) If any cracking is detected, but it is not possible to 
determine whether the crack is in the base metal, or only in the 
paint finish and/or sealant: Prior to further flight, perform 
follow-on actions in accordance with a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the Direction Generale de l'Aviation Civile 
(DGAC) (or its delegated agent).

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Alternative Methods of Compliance

    (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.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
Secs. 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.

Incorporation by Reference

    (d) Except as required by paragraph (a)(2) of this AD: The 
actions shall be done in accordance with Airbus All Operators Telex 
A330-32A3137, dated July 19, 2001; or Airbus All Operators Telex 
A340-32A4174, dated July 19, 2001; as applicable. 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.

    Note 4: The subject of this AD is addressed in French 
telegraphic airworthiness directive T2001-320(B), dated July 20, 
2001.

Effective Date

    (e) This amendment becomes effective on September 7, 2001.

    Issued in Renton, Washington, on August 15, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21105 Filed 8-22-01; 8:45 am]
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