[Federal Register: May 3, 2004 (Volume 69, Number 85)]
[Proposed Rules]
[Page 24097-24099]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03my04-21]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-16-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to all Airbus Model A300 B2
and B4 series airplanes, that currently requires determining the part
and amendment number of the variable lever arm (VLA) of the rudder
control system to verify the parts were installed using the correct
standard, and corrective actions if necessary. For certain VLAs, this
action would require repetitive inspections for damage, and replacement
with a new VLA if necessary. This action would also provide an optional
action to replace the VLA with a new VLA, which would constitute
terminating action for the repetitive inspections. The actions
specified by the proposed AD are intended to prevent failure of both
spring boxes of certain VLAs due to corrosion damage, which could
result in loss of rudder control and consequent reduced controllability
of the airplane. This action is intended to address the identified
unsafe condition.
DATES: Comments must be received by June 2, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-16-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-16-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: 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:
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-16-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. 2003-NM-16-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On October 18, 2001, the FAA issued AD 2001-22-02, amendment 39-
12481 (66 FR 54416, October 29, 2001), applicable to all Airbus Model
A300 B2 and B4 series airplanes. That AD requires determining the part
and amendment numbers of the variable lever arm (VLA) of the rudder
control system to verify the parts were installed using the correct
standard, and corrective actions if necessary. That action was prompted
by reports that, during regularly scheduled maintenance, damage to the
VLA of the rudder control system was found. Further investigation
revealed that the VLA spring box mountings, the mounting trunnion, and
a tie rod also were damaged due to corrosion of the spring boxes. The
requirements of that AD are intended to prevent failure of both spring
boxes of the VLA due to corrosion damage, which could result in loss of
rudder control and consequent reduced controllability of the airplane.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, a new inspection program has been
developed by the manufacturer that introduces a repetitive inspection
of VLAs that are equipped with spring boxes having certain part
numbers.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-27-0196, Revision 01, dated
November 13, 2002, which describes procedures for inspecting the VLA to
determine the part number (P/N) of the spring box, and for performing
repetitive detailed inspections of any VLA that does not have a
particular P/N. For any airplane on which any damage is found during
any inspection, the service bulletin describes procedures for replacing
the VLA with a new VLA. The Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC) classified this
[[Page 24098]]
service bulletin as mandatory and issued French airworthiness directive
2003-006(B), dated January 8, 2003, to ensure the continued
airworthiness of these airplanes in France.
FAA's Conclusions
This airplane model is manufactured in France and is 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 supersede AD 2001-22-02 to
continue to require inspection of the VLA of the rudder control system
to verify the parts were installed using the correct standard;
inspection for damage of the VLA tie rod if the standard is not
correct; and replacement with a new VLA, if necessary. This proposed
action would require repetitive inspections of VLAs equipped with
spring boxes having certain P/Ns. This proposed action would also
provide an optional action to replace the VLA with a new VLA, which
would constitute terminating action for the repetitive inspections. The
actions would be required to be accomplished in accordance with the
service bulletin described previously, except as discussed below.
Difference Between the Proposed AD and the Service Bulletin
Operators should note that, although the service bulletin describes
procedures for submitting certain information to the manufacturer, and
for returning certain VLAs to the manufacturer, this proposed AD would
not require those actions.
Explanation of Change to Inspection Definition
We have changed all references to a ``detailed visual inspection''
in the existing AD to ``detailed inspection'' in this proposed AD.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Cost Impact
There are approximately 24 airplanes of U.S. registry that would be
affected by this proposed AD.
The actions that are currently required by AD 2001-22-02, and
retained in this proposed AD, take approximately 1 work hour per
airplane to accomplish, at an average labor rate of $65 per work hour.
Based on these figures, the cost impact of the currently required
actions on U.S. operators is estimated to be $1,560, or $65 per
airplane.
The new actions that would be required by the proposed AD, would
take approximately 1 work hour per airplane to accomplish, at an
average labor rate of $65 per work hour. Based on these figures, the
cost impact of the new in the proposed AD on U.S. operators is
estimated to be $1,560, or $65 per airplane, per inspection cycle.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or 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 removing amendment 39-12481 (66 FR
55416, October 29, 2001), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus: Docket 2003-NM-16-AD. Supersedes AD 2001-22-02, Amendment 39-
12481.
Applicability: All Model A300 B2 and B4 series airplanes,
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of both spring boxes of the variable lever
arm (VLA) due to corrosion damage, which could result in loss of
rudder control and consequent reduced controllability of the
airplane, accomplish the following:
Restatement of the Requirements of AD 2001-22-02:
(a) Within 10 days after November 13, 2001 (the effective date
of AD 2001-22-02, amendment 39-12481): Determine the part and
amendment numbers of the VLA of the rudder control system to verify
the parts were installed using the correct standard, per Airbus All
Operators Telex (AOT) A300-27A0196, dated September 20, 2001; or per
the Accomplishment Instructions of Airbus Service Bulletin A300-27-
0196, Revision 01, dated November 13, 2002.
(1) If the part and amendment numbers shown are not correct, as
specified in the AOT or the service bulletin, before further flight,
do a detailed inspection of the VLA tie rod for damage (bent or
ruptured rod) per the AOT or the service bulletin.
(i) If the tie rod is damaged, replace the VLA with a new VLA
per the AOT or the service bulletin. Such replacement ends the
requirements of this paragraph.
(ii) If the tie rod is not damaged, no further action is
required by this paragraph.
[[Page 24099]]
(2) If the part and amendment numbers shown are correct, no
further action is required by this paragraph.
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.''
New Requirements of this AD:
(b) For airplanes having a VLA with any part number (P/N) other
than 418473-20 or 418473-200: Within 500 flight hours after the
effective date of this AD, do a detailed inspection of the tie rod
for damage (bent or ruptured rod), per the Accomplishment
Instructions of Airbus Service Bulletin A300-27-0196, Revision 01,
dated November 13, 2002. Repeat the inspection thereafter at
intervals not to exceed 1,000 flight hours.
Replacement or Repair
(c) If any damage is found to the VLA or the rudder control
system during any inspection required by paragraph (a)(1) or (b) of
this AD, prior to further flight, replace the VLA with a new VLA
(including a follow-up test) per the Accomplishment Instructions of
Airbus Service Bulletin A300-27-0196, Revision 01, dated November
13, 2002.
Optional Terminating Action
(d) Replacement of the VLA with a new VLA having P/N 418473-20
or P/N 418473-200 constitutes terminating action for the repetitive
inspections in paragraph (b) of this AD.
No Reporting/Parts Return Requirements
(e) Although the referenced service bulletin describes
procedures for submitting certain information to the manufacturer,
and for returning certain parts to the manufacturer, this AD does
not require those actions.
Actions Accomplished per Previous Issue of the Service Bulletin
(f) Actions accomplished before the effective date of this AD
per Airbus Service Bulletin A300-27-0196, dated September 20, 2002,
are considered acceptable for compliance with the corresponding
actions specified in this AD.
Alternative Methods of Compliance
(g) In accordance with 14 CFR 39.19, the Manager, International
Branch, FAA, ANM-116, 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 2003-006(B), dated January 8, 2003.
Issued in Renton, Washington, on April 21, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-9904 Filed 4-30-04; 8:45 am]
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