AD 2001-14-17

[Federal Register Volume 66, Number 133 (Wednesday, July 11, 2001)]
[Rules and Regulations]
[Pages 36154-36156]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-17165]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-214-AD; Amendment 39-12328; AD 2001-14-17]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 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 A300 B2 and B4 series airplanes. This 
action requires a one-time inspection to detect and correct corrosion 
of the lower bulkhead attachment, and corrective action, if necessary. 
This action is necessary to detect and correct corrosion of the lower 
bulkhead attachment, which could result in reduced structural integrity 
of the rear pressure bulkhead and consequent damage to components of 
the flight control, hydraulic, and auxiliary power unit fuel systems. 
This action is intended to address the identified unsafe condition.

DATES: Effective July 26, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 26, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before August 10, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-214-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: 
<a href="/cdn-cgi/l/email-protection#221b0f434c4f0f4b4350414d4f4f474c56624443430c454d54"><span class="__cf_email__" data-cfemail="f8c1d5999695d591998a9b9795959d968cb89e9999d69f978e">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-214-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, notified the 
FAA that an unsafe condition may exist on all Airbus Model A300 B2 and 
B4 series airplanes. The DGAC advises of the reported failure of the 
rear pressure bulkhead on an Airbus Model A300 series airplane during 
flight, which led to rapid cabin decompression. The rupture occurred at 
the junction between the pressure bulkhead and the fuselage/frame 80. 
The main damage was circumferential on the inner and outer rim 
attachment angles from stringers 48LH to 34RH. The airplane had 
accumulated approximately 50,000 total flight hours and 25,000 total 
flight cycles. The initial investigation revealed heavy corrosion on 
the inner and outer rim attachment angles, which extended underneath 
the sealant bead covering the junction. The exact cause and sequence of 
this bulkhead failure is under investigation. Undetected corrosion in 
this area of the lower bulkhead attachment could significantly affect 
the structural integrity of the rear pressure bulkhead. This condition, 
if not corrected, could result in damage to components of the flight 
control, hydraulic, and auxiliary power unit fuel systems.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-53A0361, dated 
June 14, 2001. The AOT describes procedures for a one-time detailed 
visual inspection (including the removal of sealant from stringer 27LH 
to stringer 27RH) to detect corrosion in the area between the cleat 
profile and the inner rim attachment angle of the lower bulkhead 
attachment, and repair if necessary. The DGAC classified this AOT as 
mandatory and issued French telegraphic airworthiness directive 2001-
245(B), dated June 16, 2001, to ensure the continued airworthiness of 
these airplanes in France.
    The AOT refers to Airbus Service Bulletin A300-53-217, Revision 4, 
dated January 14, 1997, as an additional source of service information 
for accomplishment of the inspection. The AOT additionally specifies 
that the sealant be removed before the inspection, which is not 
specified in the service bulletin.

FAA's Conclusions

    These airplane 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 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 
corrosion of the lower bulkhead attachment, which could result in 
reduced structural integrity of the rear pressure bulkhead and 
consequent damage to components of the flight control, hydraulic, and 
auxiliary power unit fuel systems. This AD requires accomplishment of 
the actions specified in the AOT described previously, except as 
discussed below.

Differences Between AD and AOT

    Operators should note that, although the AOT implies that the 
manufacturer may be contacted for disposition of certain repair 
conditions, 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 agreements, the FAA has 
determined that, for this AD,

[[Page 36155]]

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 until final action is 
identified, at which time 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:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> 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-214-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 adding the following new 
airworthiness directive:

2001-14-17  Airbus Industrie: Amendment 39-12328. Docket 2001-NM-
214-AD.

    Applicability: All Model A300 B2 and B4 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 (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 corrosion of the lower bulkhead 
attachment, which could result in reduced structural integrity of 
the rear pressure bulkhead and consequent damage to components of 
the flight control, hydraulic, and auxiliary power unit fuel 
systems, accomplish the following:

Inspection

    (a) At the applicable time specified by paragraph (a)(1) or 
(a)(2) of this AD: Perform a detailed visual inspection (including 
the removal of sealant from stringer 27LH to stringer 27RH) to 
detect corrosion between the cleat profile and the inner rim 
attachment angle of the lower bulkhead attachment, in accordance 
with Airbus All Operators Telex (AOT) A300-53A0361, dated June 14, 
2001. Perform applicable repair at the applicable time specified by 
and in accordance with the AOT, except as required by paragraph (b) 
of this AD.
    (1) For airplanes inspected within a year before the effective 
date of this AD in accordance with Airbus Service Bulletin A300-53-
217, Revision 4, dated January 14, 1997, and for which no corrosion 
was detected: Inspect within 4 weeks after the effective date of 
this AD.
    (2) For airplanes not identified in paragraph (a)(1) of this AD: 
Inspect within 2 weeks after the effective date of this AD.

    Note 2: The AOT refers to Airbus Service Bulletin A300-53-217, 
Revision 4, dated January 14, 1997, as an additional source of 
service information for accomplishment of the inspection required by 
paragraph (a) of this AD.


    Note 3: 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, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (b) If corrosion is found during the inspection required by this 
AD, and the AOT indicates that operators are to contact Airbus for 
appropriate action: Repair in accordance with a method approved by 
either the Manager, International Branch, ANM-116,

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FAA, Transport Airplane Directorate; or the Direction Generale de 
l'Aviation Civile (DGAC) (or its delegated agent).

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 4: 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 (b) of this AD: The actions 
shall be done in accordance with Airbus All Operators Telex A300-
53A0361, dated June 14, 2001. 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 5: The subject of this AD is addressed in French 
telegraphic airworthiness directive 2001-245(B), dated June 16, 
2001.

Effective Date

    (f) This amendment becomes effective on July 26, 2001.

    Issued in Renton, Washington, on July 3, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-17165 Filed 7-10-01; 8:45 am]
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