[Federal Register Volume 69, Number 192 (Tuesday, October 5, 2004)]
[Proposed Rules]
[Pages 59557-59559]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-22356]


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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airplanes, that would have superseded an existing AD that currently 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: 
[email protected]. 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

[[Page 59559]]

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]
BILLING CODE 4910-13-P