[Federal Register Volume 69, Number 28 (Wednesday, February 11, 2004)]
[Rules and Regulations]
[Pages 6549-6552]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2683]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-223-AD; Amendment 39-13468; AD 2004-03-24]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 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) that 
is applicable to all Airbus Model A330-200, A330-300, A340-200, and 
A340-300 series airplanes. This action requires a revision of the 
airplane flight manual to include procedures for a pre-flight elevator 
check before each flight, repetitive inspections for cracks of the 
attachment lugs of the mode selector valve position transducers on the 
elevator servocontrols, and corrective actions if necessary. This 
action is intended to advise the flightcrew of the potential for an 
undetected inoperative elevator, and of the action they must take to 
avoid this hazard. This action is necessary to ensure proper 
functioning of the elevator surfaces, and to detect and correct 
cracking of the attachment lugs, which could result in partial loss of 
elevator function and consequent reduced controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective February 26, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 26, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before March 11, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-223-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 the Internet must contain 
``Docket No. 2003-NM-223-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via fax or 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, 
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: The Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, notified the FAA that an unsafe condition may exist on all 
Airbus Model A330-200, A330-300, A340-200, and A340-300 series 
airplanes. Each elevator on these airplanes is equipped with two 
servocontrols having three operating modes. A selector valve installed 
in each servocontrol enables the servocontrol to change between 
operating modes; the selector valve's position is transmitted to the 
flight control computers by a transducer. The DGAC advises that several 
cracks of the transducer body at its attachment lugs have been 
detected. The affected transducers were installed at the damping 
positions 3CS1 and 3CS2. The cracks resulted in displacement of the 
transducer and consequent leakage of the hydraulic fluid into the 
affected servocontrol. In two cases the displacement of the transducer 
resulted in the elevator becoming inoperative (it dropped into a full 
down position), with no electronic centralized aircraft monitor (ECAM) 
warning provided to the flightcrew. Without an ECAM warning, this 
inoperative condition can be identified only if no elevator surface 
movement is detected during a pre-flight elevator check. Loss of 
elevator function, if not corrected, could result

[[Page 6550]]

in reduced controllability of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A330-27A3115 and A340-27A4119, 
both Revision 02, dated December 30, 2003. The service bulletins 
describe procedures for repetitive dye penetrant inspections for cracks 
of the attachment lugs of the mode selector valve position transducer 
on each elevator servocontrol installed at damping positions 3CS1 and 
3CS2. The service bulletins also provide procedures for replacing a 
cracked transducer with a new part and torqueing the bolts when the 
transducer is reinstalled. The DGAC classified the service bulletins as 
mandatory and issued French airworthiness directive F-2003-460, dated 
December 24, 2003, to ensure the continued airworthiness of these 
airplanes in France.
    The Airbus service bulletins refer to Goodrich Actuation Systems 
Inspection Service Bulletin SC4800-27-13 as an additional source of 
service information for the inspection.

FAA's Conclusions

    These airplane models are manufactured in France and are 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. 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 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, this AD is being issued to ensure proper 
functioning of the elevator surfaces, and to detect and correct 
cracking of the attachment lugs of the mode selector valve position 
transducers on the elevator servocontrols, which could result in 
partial loss of elevator function and consequent reduced 
controllability of the airplane. This AD requires a revision of the 
airplane flight manual (AFM) to include procedures for a pre-flight 
elevator check, repetitive inspections for cracks of the attachment 
lugs, and corrective action if necessary. The actions are required to 
be accomplished in accordance with the Airbus service bulletins 
described previously, except as discussed under ``Differences Between 
This AD and French Airworthiness Directive.''
    This AD also requires that operators report crack findings to 
Airbus. Because the cause of the cracking is not known, these required 
inspection reports will help determine the extent of the cracking in 
the affected fleet. Based on the results of these reports, we may 
determine that additional rulemaking is warranted.

Differences Between This AD and the French Airworthiness Directive

    The FAA and DGAC airworthiness directives differ in their 
compliance times for the first repetitive inspection interval for 
airplanes already inspected in accordance with Revision 01 of the 
service bulletin. The DGAC allows up to 700 flight cycles or 1,350 
total flight cycles (whichever occurs later) for this interval, but 
this AD requires that all inspections be done within intervals of 350 
flight cycles. French airworthiness directive 2003-371--which was 
replaced by the existing French airworthiness directive 2003-460--
required that the inspection be done only one time. Therefore, for 
operators that had complied with 2003-371, the additional time 
following the initial inspection could provide the necessary time to 
schedule the subsequent repetitive inspections. Since we have not 
previously required the subject inspection, this AD does not provide 
for any extension of the first-repeated inspection interval. However, 
we may approve requests to adjust that interval, according to the 
provisions of paragraph (g) of this AD, if the request includes data 
that prove that the first repetitive interval would provide an 
acceptable level of safety.
    Also, the DGAC airworthiness directive mandates a change to the 
flight crew operating manual (FCOM) to include an additional elevator 
pre-flight check. We agree with the need to check for proper 
functioning of the elevators before takeoff, but we have determined 
that the appropriate location for the procedure is in the AFM, in the 
Limitations section. We base this determination on the following 
considerations:
    1. The FCOM does not require FAA approval; therefore, FCOM changes 
cannot be mandated by an AD.
    2. It is possible that later changes to the FCOM made by an 
operator could result in removal of the necessary pre-flight check.
    3. An ECAM warning to the flightcrew would not be provided 
following an elevator failure.
    4. An elevator failure could result in reduced controllability of 
the airplane.
    The DGAC airworthiness directive specifies that the FCOM be amended 
``for one or both damping servo controls above 1000 FC since new.'' 
However, this AD requires that the parallel change to the AFM--which 
applies across airplane model/series--be incorporated within 30 days.

Interim Action

    We consider this AD interim action. The manufacturer is considering 
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.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an 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:
     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 AD is being requested.
     Include justification (e.g., reasons or data) 
for each request.

[[Page 6551]]

    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-223-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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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:

2004-03-24 Airbus: Amendment 39-13468. Docket 2003-NM-223-AD.

    Applicability: All Model A330-200, A330-300, A340-200, and A340-
300 series airplanes; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To ensure proper functioning of the elevator surfaces, and to 
detect and correct cracking of the attachment lugs of the mode 
selector valve position transducers on the elevator servocontrols, 
which could result in partial loss of elevator function and 
consequent reduced controllability of the airplane, accomplish the 
following:

AFM Revision

    (a) Within 30 days after the effective date of this AD, revise 
the Limitations section of the airplane flight manual (AFM) to 
include a pre-flight elevator check, by including the following 
language. This may be done by inserting a copy of this AD into the 
applicable AFM. Thereafter perform the pre-flight check before every 
flight in accordance with the procedure.

Prior or During Taxi:

 ``FLIGHT CONTROLS CHECK

 1. AT A CONVENIENT STAGE, PRIOR TO OR DURING TAXI, AND BEFORE 
ARMING THE AUTOBRAKE, THE PF SILENTLY APPLIES FULL LONGITUDINAL AND 
LATERAL SIDESTICK DEFLECTION. ON THE F/CTL PAGE, THE PNF CHECKS FULL 
TRAVEL OF ALL ELEVATORS AND ALL AILERONS, AND THE CORRECT DEFLECTION 
AND RETRACTION OF ALL SPOILERS. THE PNF CALLS OUT ``FULL UP,'' 
``FULL DOWN,'' ``NEUTRAL,'' ``FULL LEFT,'' ``FULL RIGHT,'' 
``NEUTRAL,'' AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED. THE PF 
SILENTLY CHECKS THAT THE PNF CALLS ARE IN ACCORDANCE WITH THE 
SIDESTICK ORDER.

 NOTE: IN ORDER TO REACH FULL TRAVEL, FULL SIDESTICK MUST BE HELD 
FOR A SUFFICIENT PERIOD OF TIME.

 2. THE PF PRESSES THE PEDAL DISC PUSHBUTTON ON THE NOSEWHEEL 
TILLER, AND SILENTLY APPLIES FULL LEFT RUDDER, FULL RIGHT RUDDER, 
AND NEUTRAL. THE PNF CALLS OUT ``FULL LEFT,'' ``FULL RIGHT,'' 
``NEUTRAL,'' AS EACH FULL TRAVEL/NEUTRAL POSITION IS REACHED.

 3. THE PNF APPLIES FULL LONGITUDINAL AND LATERAL SIDESTICK 
DEFLECTION, AND SILENTLY CHECKS FULL TRAVEL AND CORRECT SENSE OF ALL 
ELEVATORS AND ALL AILERONS, AND CORRECT DEFLECTION AND RETRACTION OF 
ALL SPOILERS, ON THE ECAM F/CTL PAGE.''

    Note 1: Full and complete elevator travel (position commanded) 
can be verified on the ECAM Flight Control Page. A determination of 
``correct sense'' should include verification that there is complete 
and full motion of the sidesticks without binding.

    (b) If any pre-flight check required by paragraph (a) of this AD 
reveals improper function of the elevator: Before further flight, 
perform the inspections required by paragraph (c) of this AD.

Inspections

    (c) At the applicable time specified in paragraph (c)(1) or 
(c)(2) of this AD, except as required by paragraph (b) of this AD: 
Perform a dye penetrant inspection of the attachment lugs of the 
mode selector valve position transducers on each elevator 
servocontrol installed at damping positions 3CS1 and 3CS2. Do the 
inspection in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-27A3115 or A340-27A4119, both Revision 
02, both dated December 30, 2003, as applicable (hereafter ``the 
service bulletin''). An inspection that is done before the effective 
date of this AD is acceptable for compliance with the initial 
inspection requirement of this paragraph, if the inspection is done 
in accordance with any of the following Airbus All Operators Telexes 
(AOTs): AOT A330-27A3115 or A340-27A4119, dated September 11, 2003, 
or Revision 01 of each AOT dated September 25, 2003; as applicable. 
Repeat the inspection thereafter at intervals not to exceed 350 
flight cycles.
    (1) If the age of the servocontrol from the date of its first 
installation on the airplane can be positively determined: Do the 
inspection before the accumulation of 1,000 total flight cycles on 
the elevator servocontrol, or within 350 flight cycles on the 
servocontrol after the effective date of this AD, whichever occurs 
later.
    (2) If the age of the servocontrol from the date of its first 
installation on the airplane cannot be positively determined, do the 
inspection within 350 flight cycles on the servocontrol after the 
effective date of this AD.

    Note 2: The service bulletin refers to Goodrich Actuation 
Systems Inspection Service Bulletin SC4800-27-13 as an additional 
source of service information for the inspection.

Corrective Actions

    (d) If any crack is found during any inspection required by 
paragraph (c) of this AD: Before further flight, replace either the 
transducer or servocontrol with a new part, in accordance with the 
service bulletin.

Reporting Requirement

    (e) If any crack is found during any inspection required by 
paragraph (c) of this AD: Submit a report in accordance with the 
service bulletin at the applicable time(s) specified in paragraphs 
(e)(1) and (e)(2) of this AD: Submit reports to Airbus Customer

[[Page 6552]]

Services, Engineering and Technical Support, Attention: J. Laurent, 
SEE53, fax +33/(0)5.61.93.44.25, Sita Code TLSBQ7X. 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) For an initial inspection done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.
    (2) For an inspection done after the effective date of this AD: 
Submit the report within 30 days after the inspection.

Parts Installation

    (f) As of the effective date of this AD, no person may install 
the following part on any airplane: a transducer, or a transducer 
fitted on an elevator servocontrol, in the operator's inventory 
before September 25, 2003, unless that transducer has been inspected 
in accordance with the service bulletin and is crack-free.

Alternative Methods of Compliance

    (g) 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

    (h) Unless otherwise specified in this AD, the actions must be 
done in accordance with Airbus Service Bulletin A330-27A3115, 
Revision 02, including Appendix 01, dated December 30, 2003; or 
Airbus Service Bulletin A340-27A4119, Revision 02, including 
Appendix 01, dated December 30, 2003; 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 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 F-2003-460, dated December 24, 2003.

Effective Date

    (i) This amendment becomes effective on February 26, 2004.

    Issued in Renton, Washington, on February 2, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-2683 Filed 2-10-04; 8:45 am]
BILLING CODE 4910-13-P