Airworthiness Directives; Airbus Model A330-200 and A330-300 Series Airplanes; and Model A340-200 and A340-300 Series Airplanes

[Federal Register Volume 70, Number 218 (Monday, November 14, 2005)]
[Rules and Regulations]
[Pages 69065-69067]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-22213]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22881; Directorate Identifier 2005-NM-202-AD; 
Amendment 39-14368; AD 2005-23-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200 and A330-300 
Series Airplanes; and Model A340-200 and A340-300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Model A330-200 and A330-300 series airplanes; and Model A340-200 
and A340-300 series airplanes. This AD requires an accelerated schedule 
of repetitive testing of the elevator servo control loops, and 
corrective actions if necessary. This AD results from reports of failed 
elevator servo controls due to broken guides. We are issuing this AD to 
ensure proper functioning of the elevator servo controls. Failure of 
the elevator servo controls during certain phases of takeoff could 
result in an unannounced loss of elevator control and consequent 
reduced controllability of the airplane.

DATES: This AD becomes effective November 29, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of November 29, 
2005.
    We must receive comments on this AD by January 13, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

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

SUPPLEMENTARY INFORMATION:

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified us that an unsafe 
condition may exist on all Airbus Model A330-200 and A330-300 series 
airplanes; and Model A340-200 and A340-300 series airplanes. The DGAC 
advises that it has received reports of elevator servo control removals 
resulting from the ``F/CTL ELEV SERVO FAULT'' warning. During repair, 
some of these servo controls installed at the active position (2CS1) 
(Left Green) or (2CS2) (Right Green) were found with a broken guide. 
The broken guides resulted in the inability for the affected servo 
controls to change their operating mode, leading to ``F/CTL ELEV SERVO 
FAULT'' warnings. Results of the investigation revealed a fatigue 
rupture inside the servo control induced by successive pressure cycles 
and resulting in a progressive decrease of the tightening torque of the 
plug to be the root cause of the broken guides.
    Each elevator is equipped with two servo controls having three 
operating modes: active mode, damping mode, and centering mode. In 
normal operating conditions, each elevator is actuated by one servo 
control in active mode, while the other is in damping mode. The mode 
change from active to damping is achieved by a mode-selector spool 
valve installed inside each servo control. The position of this spool 
valve is commanded by a rod that slides through a guide. A broken guide 
could result in the inability for the affected servo control to change 
its operating mode.
    Failure of the elevator servo controls during certain phases of 
takeoff, if not corrected, could result in an unannounced loss of 
elevator control and consequent reduced controllability of the 
airplane.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A330-27A3138, Revision 
01, dated October 3, 2005, for Model A330-200 and -300 series 
airplanes; and AOT A340-27A4137, Revision 01, dated October 3, 2005, 
for Model A340-200 and -300 series airplanes. The AOTs describe 
procedures for repetitive tests of the elevator servo-loops and 
corrective actions if the test fails. If the test fails, the AOTs 
specify performing the associated troubleshooting manual tasks and 
applicable corrective actions. The corrective actions include repairing 
wiring, replacing certain solenoid valves, replacing certain mode 
selector valve transducers, and replacing the elevator servo control, 
among other actions, depending on the fault message displayed. The AOTs 
also specify reporting failed tests and sending replaced servo controls 
to Airbus.
    The DGAC mandated the AOTs and issued French airworthiness 
directive UF-2005-171, dated October 3, 2005, to ensure the continued 
airworthiness of these airplanes in France.

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section

[[Page 69066]]

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. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are issuing this AD to ensure proper functioning of 
the elevator servo controls. Failure of the elevator servo controls 
during certain phases of takeoff could result in an unannounced loss of 
elevator control and consequent reduced controllability of the 
airplane. This AD requires accomplishing the actions specified in the 
service information described previously.
    This AD also requires that operators report results of failed 
servo-loop tests to Airbus. These required failed-test reports will be 
instrumental in ensuring that as much information as possible is 
gathered regarding the nature of the fatigue rupture causing the broken 
guides and that the new design of servo control to be used in a 
terminating modification, which the manufacturer is currently 
developing, will adequately address the subject unsafe condition.

Clarification of Corrective Actions Specified in the French 
Airworthiness Directive

    The French airworthiness directive does not define what 
``corrective actions'' should be taken when an elevator servo-loop test 
fails. We have verified that those corrective actions are the actions 
described previously under ``Relevant Service Information.''

Interim Action

    We consider this AD interim action. The manufacturer is currently 
developing a modification that will address the unsafe condition 
identified in this AD. Once this modification is developed, approved, 
and available, we may consider additional rulemaking.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
22881; Directorate Identifier 2005-NM-202-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of that Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you may visit 
http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-23-10 Airbus: Amendment 39-14368. Docket No. FAA-2005-22881; 
Directorate Identifier 2005-NM-202-AD.

Effective Date

    (a) This AD becomes effective November 29, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A330-201, -202, -203, -
223, -243, -301, -321, -322, -323, -341, -342, and -343

[[Page 69067]]

airplanes; and Model A340-211, -212, -213, -311, -312, and -313 
airplanes; certificated in any category.

Unsafe Condition

    (d) This AD results from reports of elevator servo control 
failures due to broken guides. We are issuing this AD to ensure 
proper functioning of the elevator servo controls. Failure of the 
elevator servo controls during certain phases of takeoff could 
result in an unannounced loss of elevator control and consequent 
reduced controllability of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Information

    (f) The term ``AOT,'' as used in this AD, means section 4.2. 
``Description'' of the following service information, as applicable:
    (1) For Model A330-200 and -300 series airplanes: Airbus All 
Operators Telex A330-27A3138, Revision 01, dated October 3, 2005; 
and
    (2) For Model A340-200 and -300 series airplanes: Airbus All 
Operators Telex A340-27A4137, Revision 01, dated October 3, 2005.

Initial and Repetitive Elevator Servo-Loop Tests

    (g) Within 200 flight hours after the effective date of this AD: 
Test the elevator servo-loops, in accordance with the AOT. If the 
test of the elevator servo-loops passes, repeat the test at 
intervals not to exceed 140 flight hours or 8 days, whichever occurs 
first.

Failed Tests

    (h) If any test of the elevator servo-loops required by 
paragraph (g) of this AD fails: Before further flight, troubleshoot 
the cause of the test failure, and do the applicable corrective 
actions; in accordance with the AOT. Thereafter, repeat the test at 
the times specified in paragraph (g) of this AD.

Reporting Requirement

    (i) Following each test required by paragraph (g) of this AD, 
submit a report of the findings of only failed elevator servo-loop 
tests to Airbus Customer Services, Engineering and Technical 
Support, Attention: Mr. J. Laurent, SEE53, fax +33/(0)5.61.93.44.25; 
at the applicable time specified in paragraph (i)(1) or (i)(2) of 
this AD. The report must include the description of the failure 
experienced during the test, the identified cause of the failure, 
and the number of flight hours and flight cycles on the airplane. 
Under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements contained in this 
AD and has assigned OMB Control Number 2120-0056.
    (1) If the test was done after the effective date of this AD: 
Submit the report within 10 days after the test.
    (2) If the test was done prior to the effective date of this AD: 
Submit the report within 10 days after the effective date of this 
AD.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (k) French airworthiness directive UF-2005-171, dated October 3, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Airbus All Operators Telex A330-27A3138, 
Revision 01, dated October 3, 2005; or Airbus All Operators Telex 
A340-27A4137, Revision 01, dated October 3, 2005; as applicable, to 
perform the actions that are required by this AD, unless the AD 
specifies otherwise. The Director of the Federal Register approved 
the incorporation by reference of these documents in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this 
service information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street SW., 
room PL-401, Nassif Building, Washington, DC; on the Internet at 
http://dms.dot.gov; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-22213 Filed 11-10-05; 8:45 am]
BILLING CODE 4910-13-P

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