[Federal Register: January 7, 2004 (Volume 69, Number 4)]
[Rules and Regulations]
[Page 867-869]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ja04-5]
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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:
9-anm-iarcomment@faa.gov. 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
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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
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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]
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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