[Federal Register: October 5, 2004 (Volume 69, Number 192)]
[Proposed Rules]
[Page 59557-59559]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05oc04-16]
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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: Supplemental notice of proposed rulemaking; reopening of
comment period.
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SUMMARY: This document revises an earlier proposed airworthiness
directive (AD), applicable to all Airbus Model A300 B2 and B4 series
airplanes, that would have superseded an existing AD that currently
requires determining the part and amendment numbers of the variable
lever arm (VLA) of the rudder control system to verify that the parts
were installed using the correct standard, and corrective actions if
necessary. For certain VLAs, the proposed AD would also have required
repetitive inspections for damage, and replacement with a new VLA if
necessary. This new action revises the proposed AD by mandating a
terminating modification of the VLA, which would end the repetitive
inspections. This new action also changes the applicability in the
proposed AD. The actions specified by this new 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 October 26, 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
[[Page 59558]]
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
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to add an airworthiness directive (AD), applicable to all
Airbus Model A300 B2 and B4 series airplanes, was published as a notice
of proposed rulemaking (NPRM) (hereafter referred to as the ``original
NPRM'') in the Federal Register on May 3, 2004 (69 FR 24097). The
original NPRM proposed to supersede AD 2001-22-02, amendment 39-12481
(66 FR 54416, October 29, 2001), which is applicable to certain Airbus
Model A300 B2 and B4 series airplanes. That original NPRM would have
continued to require 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, the original NPRM would have added
repetitive inspections for damage, and replacement with a new VLA if
necessary. The original NPRM would also have provided an optional
action to replace the VLA with a new VLA, which would constitute
terminating action for the repetitive inspections. The original NPRM
was prompted by a new inspection program developed by the manufacturer
that introduces a repetitive inspection of VLAs that are equipped with
spring boxes having certain part numbers. Failure of both spring boxes
of certain VLAs due to corrosion damage could result in loss of rudder
control and consequent reduced controllability of the airplane.
In the preamble to the original NPRM, the FAA indicated that the
actions required by that NPRM were considered ``interim action'' and
that further rulemaking action was being considered. We have now
determined that further rulemaking is indeed necessary, and this
supplemental NPRM follows from that determination.
Actions Since Issuance of Original NPRM
Since the issuance of the original NPRM, the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, issued French airworthiness
directive 2004-091(B), dated June 23, 2004. The French airworthiness
directive mandates modification of the VLA, which ends the repetitive
inspections required by French airworthiness directive 2003-006(B),
dated January 8, 2003 (referenced in the original NPRM). The revised
French airworthiness directive supersedes French airworthiness
directive F-2003-006(B).
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-27-0198, dated December 1,
2003, which describes procedures for modification of the VLA of the
rudder control system. The modification includes installation of new,
improved spring boxes, and re-identification of certain placards. The
service bulletin specifies that accomplishing the modification
eliminates the need for the repetitive inspections specified in Airbus
Service Bulletin A300-27-0196, Revision 01, dated November 13, 2002
(which was referenced in the NPRM as the appropriate source of service
information for accomplishment of the inspections and corrective
actions). The service bulletin also describes procedures for a
functional test of the VLA unit. The service bulletin references
Goodrich Actuation Systems Service Bulletin 27-21-1H, dated December 8,
2003, as an additional source of service information for accomplishing
the modification.
Conclusion
Since these changes expand the scope of the originally proposed
rule, we have determined that it is necessary to reopen the comment
period to provide additional opportunity for public comment.
Cost Impact
About 33 airplanes of U.S. registry 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 about 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 $65 per airplane.
The new inspection that would be required by the proposed AD would
take about 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 inspections on U.S. operators is estimated to be $2,145, or $65
per airplane, per inspection cycle.
The new modification that would be required by the proposed AD
would take about 4 hours per airplane to accomplish, at an average
labor rate of $65 per work hour. Required parts cost would be minimal.
Based on these figures, the cost impact of the new modification on U.S.
operators is $8,580, or $260 per airplane.
The cost impact figures discussed above are 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
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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
54416, October 29, 2001), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus: Docket 2003-NM-16-AD. Supersedes AD 2002-08-13, Amendment
39-12481.
Applicability: Model A300 B2 and B4 series airplanes,
certificated in any category; except those airplanes modified by
Airbus Modification 12656.
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, in accordance
with Airbus All Operators Telex (AOT) A300-27A0196, dated September
20, 2001; or in accordance with 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) in accordance with the AOT or the service bulletin.
(i) If the tie rod is damaged, replace the VLA with a new VLA in
accordance with 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.
(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:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate 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), in accordance with 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, until
paragraph (f) of this AD has been accomplished.
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, before further flight, replace the VLA with a new VLA
(including a follow-up test) in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-27-0196, Revision 01,
dated November 13, 2002.
Actions Accomplished in Accordance With Previous Issue of the Service
Bulletin
(d) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A300-27-0196, dated
September 20, 2002, are considered acceptable for compliance with
the corresponding actions specified in paragraphs (a), (b), and (c)
of this AD.
No Reporting/Parts Return Requirements
(e) Although Airbus Service Bulletin A300-27-0196, Revision 01,
dated November 13, 2002, describes procedures for submitting certain
information to the manufacturer, and for returning certain parts to
the manufacturer, this AD does not require those actions.
Terminating Modification
(f) Within 24 months after the effective date of this AD: Modify
the applicable VLA, as required by either paragraph (f)(1) or (f)(2)
of this AD, by doing all the applicable actions in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-27-
0198, dated December 1, 2003. Accomplishing this modification ends
the repetitive inspections required by paragraph (b) of this AD.
(1) For any VLA having a spring box with P/N 418473-20 or
418473-200: Install a new identification plate and re-identify the
VLA.
(2) For any VLA having a spring box with P/N 418473 or 418473-
100: Modify the spring box and re-identify the VLA.
Note 2: Airbus Service Bulletin A300-27-0198, dated December 1,
2003, references Goodrich Actuation Systems Service Bulletin 27-21-
1H, Revision 3, dated December 8, 2003, as an additional source of
service information for accomplishing the modification.
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 3: The subject of this AD is addressed in French
airworthiness directive F-2004-091(B), dated June 23, 2004.
Issued in Renton, Washington, on September 29, 2004.
Kalene C. Yanamura,
Acting Manager, , Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 04-22356 Filed 10-4-04; 8:45 am]
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