[Federal Register: April 1, 2004 (Volume 69, Number 63)]
[Proposed Rules]
[Page 17115-17117]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01ap04-34]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-123-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and A300 B4; A300
B4-600, A300 B4-600R, A300 C4-605R Variant F, A300 F4-600R
(Collectively Called A300-600); and A310 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Airbus Model A300 B2 and A300
B4; A300 B4-600, A300 B4-600R, A300 C4-605R Variant F A300 F4-600R
(collectively called A300-600); and A310 series airplanes. This
proposal would require an inspection to detect breaks in the bottom
flange fitting of the ram air turbine (RAT); and corrective actions, if
necessary. This proposal would also require submission of an inspection
report to the airplane manufacturer. This action is necessary to
prevent failure of the RAT yoke fitting, which could result in the loss
of RAT function and possible loss of critical flight control in the
event of certain emergency situations. This action is intended to
address the identified unsafe condition.
DATES: Comments must be received by May 3, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-123-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-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-123-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 or 2000 or
ASCII text.
The service information referenced in the proposed rule 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.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
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 proposed 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 proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-123-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No.
[[Page 17116]]
2003-NM-123-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale 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 A300 B4;
A300 B4-600, A300 B4-600R, A300 C4-605R Variant F, A300 F4-600R
(collectively called A300-600); and A310 series airplanes. The DGAC
advises that, during scheduled maintenance on a Model A310 series
airplane, an operator reported that the swivel coupling of the ram air
turbine (RAT) yoke fitting was found broken. Investigation along the
corner radius of the bottom flange fitting of the part showed that the
failure was associated with abnormal static loads. The RAT drives a
pump that allows one hydraulic system to be pressurized in order to
maintain critical flight control in the event of certain emergency
situations. Failure of the RAT yoke fitting, if not corrected, could
result in the loss of RAT function and possible loss of critical flight
control.
Explanation of Relevant Service Information
Airbus has issued All Operators Telex (AOT) A300-57A0241, dated
March 6, 2003; AOT A300-57A6096, dated March 6, 2003; and AOT A310-
57A2085, dated March 6, 2003. These AOTs describe procedures for
inspecting the bottom flange fitting of the RAT for damage, and
replacing it with a new part, if necessary. The DGAC classified these
AOTs as mandatory and issued French airworthiness directive 2003-
149(B), dated April 16, 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
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 Proposed 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, the proposed AD would require accomplishment of
the actions specified in the AOTs described previously, except as
discussed below.
Differences Among the Proposed Rule, the AOTs, and the French
Airworthiness Directive
The French airworthiness directive mandates, and the AOTs describe,
a one-time inspection of the yoke fitting for the RAT swivel coupling.
However, because the root cause has not been identified, this proposed
AD would require repetitive inspections. We find it necessary to
require these repetitive inspections to ensure the safety of the fleet
until a terminating action can be developed.
Although the AOTs and the French AD do not give a compliance time
for submitting inspection reports to the manufacturer, this proposed AD
would require submission of such reports within 60 days following any
inspection.
Interim Action
This proposed AD is considered to be interim action. The inspection
reports that would be required by this proposed AD will enable the
manufacturer to obtain better insight into the nature, cause, and
extent of the damage, and eventually to develop final action to address
the unsafe condition. Once final action has been identified, we may
consider further rulemaking.
Cost Impact
The FAA estimates that 165 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 1 work
hour per airplane to accomplish the proposed inspection, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$10,725, or $65 per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted. The cost impact figures
discussed in AD rulemaking actions represent only the time necessary to
perform the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, will not have a significant economic impact,
positive or negative, on a substantial number of small entities under
the criteria of the Regulatory Flexibility Act. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Airbus: Docket 2003-NM-123-AD.
Applicability: Model A300 B2 and A300 B4; A300 B4-600, A300 B4-
600R, A300 C4-605R Variant F, A300 F4-600R (collectively called
A300-600); and A310 series airplanes; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the ram air turbine (RAT) yoke fitting,
which could result in the loss of RAT function and possible loss of
critical flight control in the event of certain emergency
situations, accomplish the following:
[[Page 17117]]
All Operators Telex (AOT) References
(a) The term ``All Operators Telex,'' or ``AOT'' as used in this
AD, means the following AOTs, as applicable:
(1) For Model A300 B2 and A300 B4 series airplanes: Airbus All
Operators Telex A300-57A0241, dated March 6, 2003;
(2) For Model A300 B4-600, A300 B4-600R, A300 C4-605R Variant F,
and A300 F4-600R (collectively called A300-600) series airplanes:
Airbus All Operators Telex A300-57A6096, dated March 6, 2003; and
(3) For Model A310 series airplanes: Airbus All Operators Telex
A310-57A2085, dated March 6, 2003.
Detailed Inspection and Replacement, If Necessary
(b) Within 600 flight hours or 3 months after the effective date
of this AD, whichever occurs first: Perform a detailed inspection of
the bottom flange fitting of the yoke fitting for the RAT swivel
coupling in accordance with the applicable AOT.
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.''
(1) If the flange fitting is not broken, repeat the inspection
required by paragraph (b) of this AD at intervals not to exceed 600
flight hours.
(2) If the flange fitting is broken, before further flight,
replace the flange fitting with a new flange fitting in accordance
with the applicable AOT. Repeat the inspection required by paragraph
(b) of this AD at intervals not to exceed 600 flight hours.
Inspection Report
(c) Submit a report of the findings, both positive (broken or
cracked fittings) and negative (no findings) of the initial
inspection required by paragraph (b) of this AD; thereafter report
only positive findings of the repetitive inspections required by
paragraphs (b)(1) and (b)(2) of this AD. Send the reports to Airbus,
Customer Service Engineering, Attention: Mr. Xavier Jolivet, SEA22,
1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax
number (33) 561933614, 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 discrepancies found, the airplane
serial number, and the number of landings and flight hours 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) For inspections done on or after the effective date of this
AD: Submit the report within 60 days after the inspection.
(2) For inspections done prior to the effective date of this AD:
Submit the report within 60 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, FAA, Transport Airplane Directorate, is authorized
to approve alternative methods of compliance for this AD.
Note 2: The subject of this AD is addressed in French
airworthiness directive 2003-149(B), dated April 16, 2003.
Issued in Renton, Washington, on March 24, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-7304 Filed 3-31-04; 8:45 am]
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