[Federal Register Volume 69, Number 85 (Monday, May 3, 2004)]
[Proposed Rules]
[Pages 24097-24099]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-9904]


-----------------------------------------------------------------------

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).

-----------------------------------------------------------------------

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: 
[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 
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]
BILLING CODE 4910-13-P