AD 2004-08-19

[Federal Register Volume 69, Number 80 (Monday, April 26, 2004)]
[Rules and Regulations]
[Pages 22389-22392]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 04-9109]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-128-AD; Amendment 39-13589; AD 2004-08-19]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A330-200 series airplanes. This 
action requires certain modifications of the rudder servo controls. 
This action is necessary to prevent failure of the driving finger of 
the rudder servo control and consequent loss of the rudder servo 
control function in driving the rudder to its commanded position, 
which, if combined with an engine failure during takeoff or go around, 
could result in loss of control of the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Effective May 11, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 11, 2004.

[[Page 22390]]

    Comments for inclusion in the Rules Docket must be received on or 
before May 26, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-128-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: 
<a href="/cdn-cgi/l/email-protection#7841551916155511190a1b1715151d160c381e1919561f170e"><span class="__cf_email__" data-cfemail="a69f8bc7c8cb8bcfc7d4c5c9cbcbc3c8d2e6c0c7c788c1c9d0">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-128-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 this AD 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; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, ANM-
116, International Branch, FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified the 
FAA that an unsafe condition may exist on certain Model A330-200 series 
airplanes. The DGAC advises that, during a pre-flight check, an 
Electronic Aircraft Centralized Monitoring (ECAM) warning message for 
rudder servo control jamming was displayed, ``F/CTL RUD Y SERVO JAM.'' 
Following this incident, two similar incidents occurred on other 
airplanes. In each case, investigation revealed that the driving finger 
of the affected rudder servo control was found broken due to fatigue 
failure. Such fatigue failure was caused by additional loads resulting 
from jamming of a hard particle between the servo control valve spool 
and the sleeve. In addition, a sealing defect of the jamming detection 
switches of the rudder servo control was found on other airplanes on 
which the message was displayed. Such conditions, if not corrected, 
could result in inability of the rudder servo control to drive the 
rudder to its commanded position, which, if combined with an engine 
failure during takeoff or go around, could result in loss of control of 
the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A330-27-3101, Revision 01, 
dated March 13, 2003; and Revision 02, dated February 4, 2004, which 
describe procedures for modification of the rudder servo controls. The 
modification includes replacing the existing driving finger and control 
valve assembly of the rudder servo controls with new, improved parts, 
and re-identifying the rudder servo controls. The service bulletins 
cite Goodrich Actuation Systems Retrofit Information Letter, 31110-27-
05, dated October 30, 2002, as an additional source of service 
information for accomplishment of the modification.
    Service Bulletins A330-27-3101, Revision 01 and Revision 02, 
recommend prior or concurrent accomplishment of Airbus Service Bulletin 
A330-27-3078, dated May 18, 2000. This service bulletin describes 
procedures for modification of the jamming detection switches of the 
rudder servo controls. The modification includes adding packing, 
replacing filling product in the switches, and re-identifying the 
rudder servo controls. Service Bulletin A330-27-3078 cites Lucas 
Aerospace Service Bulletin No. 31110-27-02, dated April 20, 2000, as an 
additional source of service information for accomplishment of the 
modification.
    Accomplishment of the actions specified in the Airbus service 
information is intended to adequately address the identified unsafe 
condition. The DGAC classified this service information as mandatory 
and issued French airworthiness directive 2003-102(B), dated March 5, 
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 us informed of the 
situation described above. We have 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 the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
being issued to prevent failure of the driving finger of the rudder 
servo control and consequent loss of the rudder servo control function 
in driving the rudder to its commanded position, which could result in 
loss of control of the airplane, if combined with an engine failure 
during takeoff or go around. This AD requires certain modifications of 
the rudder servo control. The actions are required to be accomplished 
in accordance with the Airbus service information described previously, 
except as discussed below.

Difference Between Proposed AD and Service Bulletin

    The applicability of French airworthiness directive 2003-102(B) 
excludes airplanes that accomplished Airbus Service Bulletins A330-27-
3101, Revision 01, dated March 13, 2003; and Revision 02, dated 
February 4, 2004, in service. However, we have not excluded those 
airplanes in the applicability of this proposed AD; rather, this 
proposed AD includes a requirement to accomplish the actions specified 
in those service bulletins. Such a requirement would ensure that the 
actions specified in those service bulletins and required by this 
proposed AD are accomplished on all affected airplanes. Operators must 
continue to operate the airplane in the configuration required by this 
proposed AD unless an alternative method of compliance is approved.

Cost Impact

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this rule 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
we consider that this rule is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future:
    For Service Bulletin A330-27-3101, Revision 01 or Revision 02: It 
would require about 12 work hours to do the

[[Page 22391]]

modification of the rudder servo controls, at an average labor rate of 
$65 per work hour. Parts cost would be negligible. Based on these 
figures, the cost impact of this modification would be $780 per 
airplane.
    For Service Bulletin A330-27-3078: Modification of the jamming 
detection switches, if required, would take about 12 work hours to do, 
at an average labor rate of $65 per work hour. Parts cost would be 
negligible. Based on these figures, the cost impact of this 
modification would be $780 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
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 under the caption 
ADDRESSES. All communications received on or before the closing date 
for comments will be considered, and this rule may be amended in light 
of the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Submit comments using the following format:
    <bullet<ls-thn-eq> 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.
    <bullet<ls-thn-eq> For each issue, state what specific change to 
the AD is being requested.
    <bullet<ls-thn-eq> 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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-128-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-08-19 Airbus: Amendment 39-13589. Docket 2003-NM-128-AD.

    Applicability: Model A330-200 series airplanes; certificated in 
any category; on which Airbus Modifications 48510 and 47628 have not 
been done during production.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the driving finger of the rudder servo 
control and consequent loss of the rudder servo control function in 
driving the rudder to its commanded position, which, if combined 
with an engine failure during takeoff or go around, could result in 
loss of control of the airplane, accomplish the following:

Modification

    (a) Within 24 months after the effective date of this AD: Modify 
the rudder servo controls by doing all the actions per the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3101, 
Revision 01, dated March 13, 2003; or Revision 02, dated February 4, 
2004.

    Note 1: Goodrich Actuation Systems Retrofit Information Letter, 
31110-27-05, dated October 30, 2002, is cited in Airbus Service 
Bulletins A330-27-3101, Revision 01, dated March 13, 2003; and 
Revision 02, dated February 4, 2004; as an additional source of 
service information for accomplishment of the modification.

Credit for Previous Issue of Service Bulletin

    (b) Accomplishment of the modification of the rudder servo 
controls before the effective date of this AD per Airbus Service 
Bulletin A330-27-3101, dated October 24, 2002, is considered 
acceptable for compliance with the modification specified in 
paragraph (a) of this AD.

Prior or Concurrent Requirements

    (c) Prior to or concurrent with accomplishment of paragraph (a) 
of this AD: Modify the jamming detection switches of the rudder 
servo controls by doing all the actions per the Accomplishment 
Instructions of Airbus Service Bulletin A330-27-3078, dated May 18, 
2000.

    Note 2: Lucas Aerospace Service Bulletin No. 31110-27-02, dated 
April 20, 2000, is cited in Airbus Service Bulletin A330-27-3078, 
dated May 18, 2000, as an additional source of service information 
for accomplishment of the modification of the jamming detection 
switches.

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.

Incorporation by Reference

    (e) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Airbus Service Bulletin A330-27-3101, 
Revision 01, dated March 13, 2003; Airbus Service Bulletin A330-27-
3101, Revision 02, dated February 4, 2004; and Airbus Service 
Bulletin A330-27-3078, dated May 18, 2000; as applicable. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be

[[Page 22392]]

obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2003-102(B), dated March 5, 2003.

Effective Date

    (f) This amendment becomes effective on May 11, 2004.

    Issued in Renton, Washington, on April 15, 2004.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-9109 Filed 4-23-04; 8:45 am]
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