[Federal Register Volume 66, Number 193 (Thursday, October 4, 2001)]
[Rules and Regulations]
[Pages 50529-50531]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-24779]



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  Federal Register / Vol. 66, No. 193 / Thursday, October 4, 2001 / 
Rules and Regulations  

[[Page 50529]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-282-AD; Amendment 39-12454; AD 2001-20-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplane, and Model A300 B4-600, B4-600R, and F4-600R (Collectively 
Called A300-600) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300 B2 and B4 series 
airplanes, and certain Model A300 B4-600, B4-60-R, and F4-600R 
(collectively called A300-600) series airplanes, that currently 
requires a one-time inspection to detect cracks in gear rib 5 (let and 
right) of the main landing gear (MLG) attachment fittings at the lower 
flange and vertical web, and repair if necessary. This amendment 
revises the applicability by including additional airplanes. The 
actions specified in this AD are intended to detect and correct fatigue 
cracking of the MLG attachment fittings, which could result in reduced 
structural integrity of the airplane.

DATES: October 19, 2001.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of September 13, 2001 (66 FR 45581, August 29, 2001).
    Comments for inclusion in the Rules Docket must be received on or 
before November 5, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-282-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-MN-282-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: On August 20, 2001, the FAA issued AD 2001-
17-29, amendment 39-12420 (66 FR 45581, August 29, 2001), applicable to 
certain Airbus Model A300 B2 and B4 series airplanes, and certain Model 
A300 B4-600, B4-6004, and F4-600R (collectively called A300-600) series 
airplanes, to require a one-time inspection to detect cracks in gear 
rib 5 (left and right) of the main landing gear (MLG) attachment 
fittings at the lower flange and vertical web, and repair if necessary. 
That action was prompted by issuance of mandatory continuing 
airworthiness information by a foreign civil airworthiness authority. 
The actions required by that AD are intended to detect and correct 
fatigue cracking of the MLG attachment fittings, which could result in 
reduced structural integrity of the airplane.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, the FAA has learned that three 
airplanes had been inadvertently omitted from the applicability. 
Airplanes having series number 789, 790, and 791 are also subject to 
the identified unsafe condition. This additional rulemaking is 
therefore necessary to correct this oversight and add those three 
airplane to the applicability of this AD.

FAA's Conclusions

    These airplanes models are manufactured in France and are 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 Direction Generale de 1 Aviation 
Civil (DGAC), which is the airworthiness authority for France, 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 supersedes AD-2001-17-29 to continue to 
require a on-time inspection to detect cracks in gear rib 5 (left and 
right) of the MLG attachment fittings at the lower flange and vertical 
web, and repair if necessary. This AD revises the applicability to 
include additional airplanes.

Difference Between AD and AOTs

    The AOTs refer to Airbus Service Bulletins A300-57A0234 and A300-
57A6087 for repair instructions. Those service bulletins specify that 
the manufacturer may be contacted for disposition of certain repair 
conditions. However, this AD requires the repair of those conditions to 
be accomplished in accordance with a method approved by either the FAA, 
or the DGAC (or its delegated agent). In light of the type of repair 
required to address the identified unsafe condition, and in consonance 
with existing bilateral airworthiness

[[Page 50530]]

agreements, the FAA has determined that, for this AD, a repair approved 
by either the FAA or the DGAC is acceptable for compliance with this 
AD.

Interim Action

    This is considered to be interim action. The manufacturer is 
gathering data that will enable it to obtain better insight into the 
nature, cause, and extent of the cracking, and eventually to develop 
final action to address the unsafe condition. Once final action has 
been identified, 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 fight 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 addressed 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 statements is made: ``Comments 
to Docket 2001-NM-282-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 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 removing amendment 39-12420 (66 FR 
45581, August 29, 2001), and by adding a new airworthiness directive 
(AD), amendment 39-12454, to read as follows:

2001-20-06  Airbus Industrie: Amendment 39-12454. Docket 2001-NM-
282-AD. Supersedes AD 2001-17-29, Amendment 39-12420.

    Applicability: The following airplanes, certificated in any 
category:

Applicability

------------------------------------------------------------------------
                 Model                                Except
------------------------------------------------------------------------
A300 B2 and A300 B4 series airplanes...  Those modified in accordance
                                          with Airbus Service Bulletin
                                          A300-57-0235 (Modification
                                          11932) or inspected in
                                          accordance with Airbus Service
                                          Bulletin A300-57A0234.
A300 B4-600, B4-600R, and F4-600R        Those modified in accordance
 (collectively called A300-600) series    with Airbus Modification 11912
 airplanes.                               or Service Bulletin A300-57-
                                          6088 (Modification 11932) or
                                          inspected in accordance with
                                          Airbus Service Bulletin A300-
                                          57A6087.
------------------------------------------------------------------------


    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 (c) 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 fatigue cracking of the attachment 
fittings of the main landing gear (MLG), which could result in 
reduced structural integrity of the airplane, accomplish the 
following:

    Note 2: The inspection required by paragraph (a) of this AD is 
also included in

[[Page 50531]]

the inspection requirement of paragraph (a) of AD 2000-05-07, 
amendment 39-11616. As indicated by the phrase, ``unless 
accomplished previously,'' for any airplane on which the initial 
inspection of AD-2000-05-07 has been accomplished before the 
effective date of this AD, the inspection specified by paragraph (a) 
of this AD is not required.

Restatement of Requirements of AD 2001-17-29

Inspection

    (a) For airplanes subject to the requirements of AD 2001-17-29, 
amendment 39-12420: Before the accumulation of 7,500 total flight 
cycles, or within 100 flight cycles after September 13, 2001 (the 
effective date of AD 2001-17-29), whichever occurs later, perform a 
one-time detailed visual inspection to detect cracks in gear rib 5 
(left and right) of the MLG attachment fittings at the lower flange 
and vertical web, in accordance with Airbus All Operators Telex 
(AOT) A300-57A0239 (for Model A300 B2 and B4 series airplanes) or 
A300-600-57A6094 (for Model A300-600 series airplanes), both dated 
August 2, 2001.
    (1) If any cracking is detected and it is found at one hole only 
and does not extend out of the spotface of the hole: Prior to 
further flight, repair in accordance with the applicable AOT.
    (2) If any cracking is detected and it is found at more than one 
hole or extends out of the spotface of any hole: Before further 
flight, repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l' Aviation Civile (or its delegated 
agent).

    Note 3: The AOTs refer to Airbus Service Bulletins A300-57A0234 
(for Model A300 B2 and B4 series airplanes) and A300-57A6087 (for 
Model A300-600 series airplanes) as additional sources of service 
information for the inspection and repair of any cracking found 
during the inspection.


    Note 4: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etec., may be used. Surface cleaning 
and elaborate access procedures may be required.''

New Requirements of This AD

Inspection

    (b) For airplanes not identified in paragraph (a) of this AD: 
Before the accumulation of 7,500 total flight cycles, or within 100 
flight cycles after the effective date of this AD, whichever occurs 
later, perform the inspection and applicable corrective actions 
specified by paragraph (a) of this AD.

Alternative Methods of Compliance

    (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, 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 5: 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

    (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.

Incorporation by Reference

    (e) Except as required by paragraph (a)(2) of this AD: The 
actions must be done in accordance with Airbus All Operators Telex 
A300-57A0239, dated August 2, 2001; or Airbus All Operators Telex 
A300-600-57A6094, dated August 2, 2001; as applicable. This 
incorporation by reference was approved previously by the Director 
of the Federal Register as of September 13, 2001 (66 FR 45581, 
August 29, 2001). 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 6: The subject of this AD is addressed in French 
telegraphic airworthiness directive T2001-364(B), dated August 2, 
2001.

Effective Date

    (f) This amendment becomes effective on October 19, 2001.

    Issued in Renton, Washington, on September 27, 2001.
Charles Huber,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-24779 Filed 10-3-01; 8:45 am]
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