[Federal Register Volume 69, Number 4 (Wednesday, January 7, 2004)]
[Rules and Regulations]
[Pages 867-869]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-46]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-248-AD; Amendment 39-13408; AD 2003-26-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; and A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R 
(Collectively Called A300-600) 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 the Airbus airplanes listed above. This action 
requires a one-time inspection for cracking of the lower outboard 
flange of gantry No. 4 in the main landing gear bay area, and repair if 
necessary. This action is necessary to find and fix such cracking, 
which could result in reduced structural integrity of the fuselage, and 
consequent rapid decompression of the airplane. This action is intended 
to address the identified unsafe condition.

DATES: Effective January 22, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 22, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before February 6, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-248-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 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 the Internet must contain 
``Docket No. 2003-NM-248-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via fax or the Internet as 
attached electronic files must be formatted in Microsoft Word 97 or 
2000 or ASCII text.
    The service information referenced in this AD may be obtained from 
Airbus, 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: Tony Jopling, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2190; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction G[ebreve]n[ebreve]rale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, notified the FAA that an unsafe condition may exist on certain 
Model A300 B2 and B4 series airplanes, and A300-600 series airplanes. 
The DGAC advises that cracks have been found on the lower outboard 
flange of gantry No. 4 in the main landing gear bay area on several 
Model A300-600 airplanes. During a maintenance inspection on one 
airplane, a 670-mm crack was found on the left side of gantry beam No. 
4 between frame (FR) 52 and FR 53. The crack extended along the 
outboard flange of the beam. A 710-mm crack between FR 52 and FR 54 was 
found during an inspection done on another airplane after detection of 
an air leak. Subsequent to detection of the cracks, an emergency 
inspection was done by the manufacturer in a part of the structure 
between FR 52 and FR 53 that was not previously inspected, which 
revealed a 227-mm crack. Such cracking, if not found and fixed, could 
result in reduced structural integrity of the fuselage, and consequent 
rapid decompression of the airplane. This action is intended to address 
the identified unsafe condition.
    The subject area on certain Model A300 B2 and B4 series airplanes 
is almost identical to that on affected Model A300-600 series 
airplanes. Therefore, those airplanes may be subject to the same unsafe 
condition revealed on the Model A300-600 series airplanes.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-53A0371, Revision 
01 (for Model A300 B2 and B4 series airplanes); and AOT A300-53A6145, 
Revision 01 (for Model A300-600 series airplanes); both dated September 
10, 2003. The AOTs describe procedures for a detailed visual inspection 
of the left and right sides of the lower outboard flange of gantry No. 
4 in the MLG bay area between FR 51 and FR 54. The AOTs recommend 
contacting Airbus if any cracks are found, in addition to specifying 
that flight with certain cracks is allowed and temporary repairs are 
available in case of large crack findings. The AOTs also recommend 
reporting inspection results to Airbus. The DGAC classified these AOTs 
as mandatory and issued French airworthiness directive 2003-356(B), 
dated September 17, 2003, 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 us informed of the 
situation described above. We have 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

[[Page 868]]

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 find and fix cracking 
of the lower outboard flange of gantry No. 4, which could result in 
reduced structural integrity of the fuselage, and consequent rapid 
decompression of the airplane. This AD requires a one-time inspection 
for cracking of the lower outboard flange of gantry No. 4 in the main 
landing gear bay area, and repair if necessary. The actions are 
required to be accomplished in accordance with the AOTs described 
previously, except as discussed below. This AD also includes a 
reporting requirement.

Differences Among This AD, AOTs, and French Airworthiness Directive

    Unlike the procedures described in the AOTs, this AD will not 
permit further flight if cracks are detected in the lower outboard 
flange of gantry No. 4. We have determined that, because of the safety 
implications and consequences associated with such cracking, any 
cracked flange must be repaired or modified before further flight.
    The French airworthiness directive and the AOTs recommend 
accomplishing the inspection before the accumulation of 8,000 flights 
``since new'' or within 14 days after the effective date of the French 
airworthiness directive. However, this AD requires accomplishment of 
the inspection before the accumulation of 8,000 total flight cycles 
since the date of issuance of the original Airworthiness Certificate or 
the date of issuance of the Export Certificate of Airworthiness, 
whichever is first; with a grace period of 30 days after the effective 
date of this AD. This decision is based on our determination that 
``since new'' may be interpreted differently by different operators. We 
find that our proposed terminology is generally understood within the 
industry and records will always exist that establish these dates with 
certainty. In addition, we have determined that a 30 day grace period 
will ensure an acceptable level of safety and is an appropriate 
interval of time wherein the inspection can be accomplished during 
scheduled maintenance intervals for the majority of affected operators.
    Although the AOTs specify that operators may contact the 
manufacturer for disposition of certain repair conditions, this AD 
requires operators to repair those conditions per a method approved by 
either us or the DGAC (or its delegated agent). In light of the type of 
repair that would be required to address the unsafe condition, and 
consistent with existing bilateral airworthiness agreements, we have 
determined that, for this AD, a repair approved by either us or the 
DGAC will be acceptable for compliance with this AD.

Interim Action

    This AD is considered to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer 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, we 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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] 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.
    Comments 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 2003-NM-248-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

0
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:

[[Page 869]]

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-26-10 Airbus: Amendment 39-13408. Docket 2003-NM-248-AD.

    Applicability: Model A300 B2 and B4 series airplanes; and A300 
B4-600, B4-600R, C4-605R Variant F, and F4-600R (collectively called 
A300-600) series airplanes; on which Airbus Modification 10147 has 
not been done; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To find and fix cracking of the lower outboard flange of gantry 
No. 4, which could result in reduced structural integrity of the 
fuselage, and consequent rapid decompression of the airplane, 
accomplish the following:

One-Time Inspection

    (a) At the later of the times specified in paragraphs (a)(1) and 
(a)(2) of this AD: Do a one-time detailed inspection for cracking of 
the lower outboard flange of gantry No. 4 in the main landing gear 
bay area per paragraph 4.2.1 of Airbus All Operators Telex (AOT) 
A300-53A0371, Revision 01 (for Model A300 B2 and B4 series 
airplanes); or AOT A300-53A6145, Revision 01 (for Model A300-600 
series airplanes); both dated September 10, 2003; as applicable.
    (1) Before the accumulation of 8,000 total flight cycles since 
the date of issuance of the original Airworthiness Certificate or 
the date of issuance of the Export Certificate of Airworthiness, 
whichever is first.
    (2) Within 30 days after the effective date of this AD.

    Note 1: For the purposes of this AD, a detailed 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.''

Repair

    (b) Repair any cracking found during the inspection required by 
paragraph (a) of this AD before further flight, per a method 
approved by either the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated 
agent).

Reporting

    (c) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (a) of this AD to Airbus 
Customer Services, SEA21, Attention: Mr. Davide Cavazzini, fax 
number +33+ (0) 5.61.93.36.14, at the applicable time specified in 
paragraph (c)(1) or (c)(2) of this AD. The report must include the 
inspection results, a description of any cracking found, the 
airplane serial number, and the number of flight cycles on the 
airplane. Under the provisions of the Paperwork Reduction Act of 
1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget 
(OMB) has approved the information collection requirements contained 
in this AD and has assigned OMB Control Number 2120-0056.
    (1) If the inspection was done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

Alternative Methods of Compliance

    (d) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, is authorized to approve alternative methods of 
compliance for this AD.

Incorporation by Reference

    (e) Unless otherwise provided in this AD, the actions shall be 
done in accordance with Airbus All Operators Telex A300-53A0371, 
Revision 01, dated September 10, 2003; or Airbus All Operators Telex 
A300-53A6145, Revision 01, dated September 10, 2003; 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, 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 2: The subject of this AD is addressed in French 
airworthiness directive 2003-356(B), dated September 17, 2003.

Effective Date

    (f) This amendment becomes effective on January 22, 2004.


    Issued in Renton, Washington, on December 23, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-46 Filed 1-6-04; 8:45 am]
BILLING CODE 4910-13-P