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

[Federal Register Volume 73, Number 49 (Wednesday, March 12, 2008)]
[Rules and Regulations]
[Pages 13093-13096]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-4488]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0229; Directorate Identifier 2007-NM-042-AD; 
Amendment 39-15417; AD 2008-06-05]
RIN 2120-AA64


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

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Airbus Model A330-200, A330-300, A340-200, 
and A340-300 series airplanes. That AD currently 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 servo controls, and corrective actions if necessary. This 
new AD retains the existing requirements, reduces the applicability of 
the existing AD, and adds terminating actions. For certain airplanes, 
this AD requires upgrading the flight control primary computers. This 
AD results from a report of cracks of the transducer body at its 
attachment lugs. We are issuing this AD to ensure proper functioning of 
the elevator surfaces, and to prevent cracking of the attachment lugs, 
which could result in partial loss of elevator function and consequent 
reduced controllability of the airplane.

DATES: This AD becomes effective April 16, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of April 16, 
2008.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2004-03-24, amendment 
39-13468 (69 FR 6549, February 11, 2004). The existing AD applies to 
all Airbus Model A330-200, A330-300, A340-200, and A340-300 series 
airplanes. That NPRM was published in the Federal Register on November 
26, 2007 (72 FR 65897). That NPRM proposed to retain the existing 
requirements, reduce the applicability of the existing AD, and add 
terminating actions.

New Service Information

    Airbus has issued Revision 03 of Airbus Service Bulletins A330-27-
3115 and A340-27-4119, both dated April 22, 2005. In the NPRM, we 
referred to Revision 02 dated December 30, 2003, of those service 
bulletins as the appropriate sources of service information for 
accomplishing certain required actions. Revision 03 of the service 
bulletins updates the operator and aircraft effectivity to show the 
latest information. No additional work is required by this revision of 
the service bulletins. We have changed paragraph (h) of this AD to 
refer to Airbus Service Bulletins A330-27-3115 and A340-27-4119, both 
Revision 03, both dated April 22, 2005. We have also added paragraph 
(h)(3) to the AD to give credit to operators that have done the actions 
previously in accordance with Revision 02 of those service bulletins.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that has been 
received on the NPRM.

Request To Extend Compliance Time for the Modification

    Air Transport Association (ATA) and one of its members, Northwest 
Airlines (NWA), state that the terminating action specified in the 
proposed AD should be mandated at a maximum of 24 months after the 
effective date for coordination with the aircraft C-check intervals. 
NWA adds that the repetitive tests of the elevator servo-loops will 
ensure continued safe operation until terminating action is 
accomplished.
    We do not agree with the request from ATA and NWA to extend the 
compliance time. In developing an appropriate compliance time for this 
action, we considered the urgency associated with the subject unsafe 
condition, the availability of required parts, and the practical aspect 
of accomplishing the required modification within a period of time that 
corresponds to the normal scheduled maintenance for most affected 
operators. In light of these items, we have determined that a 17-month 
compliance time is appropriate. However, according to the provisions of 
paragraph (p) of the AD, we might approve requests to adjust the 
compliance time if the request includes data that justify that the new 
compliance time would provide an acceptable level of safety.

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been received, and determined that air safety and the 
public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
of the affected Model A330-200 and A330-300 series airplanes to comply 
with this AD.

[[Page 13094]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                              Number of
                                   Work       Average                           U.S.-
            Action                hours     labor rate   Cost per airplane   registered         Fleet cost
                                             per hour                         airplanes
----------------------------------------------------------------------------------------------------------------
AFM revision (required by AD            1           $80  $80..............            29  $2,320.
 2004-03-24).
Inspection (required by AD              4            80  $320, per                    29  $9,280, per inspection
 2004-03-24).                                             inspection cycle.                cycle.
Inspection (new action).......          1            80  $80..............            29  $2,320.
----------------------------------------------------------------------------------------------------------------

    Currently, there are no affected Model A340-200 and A340-300 series 
airplanes on the U.S. Register. However, if an affected airplane is 
imported and placed on the U.S. Register in the future, the upgrade of 
the flight control primary computers (FCPCs) would take about 2 work 
hours, at an average labor rate of $80 per work hour. The manufacturer 
states that it would supply required parts to the operators at no cost. 
Based on these figures, we estimate the cost of this AD for Model A340-
200 and A340-300 series airplanes to be $160 per airplane.

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 this AD:
    (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.
    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 
removing amendment 39-13468 (69 FR 6549, February 11, 2004) and by 
adding the following new airworthiness directive (AD):

2008-06-05 Airbus: Amendment 39-15417. Docket No. FAA-2007-0229; 
Directorate Identifier 2007-NM-042-AD.

Effective Date

    (a) This AD becomes effective April 16, 2008.

Affected ADs

    (b) This AD supersedes AD 2004-03-24.

Applicability

    (c) This AD applies to the airplanes identified in Table 1 of 
this AD, certificated in any category.

                                             Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
                                            Excluding those airplanes on
             Airbus model--                 which any of the following--            Has been installed--
----------------------------------------------------------------------------------------------------------------
A330-200, A330-300, A340-200, and A340-   Airbus Modification 50394,       In production.
 300 series airplanes.                     52195, 53969, or 54833.
                                          Airbus Service Bulletin A330-27- In service.
                                           3128, dated May 3, 2005.
                                          Airbus Service Bulletin A340-27- In service.
                                           4129, dated May 3, 2005.
                                          Airbus Service Bulletin A330-27- In service.
                                           3136, Revision 01, dated July
                                           19, 2006.
                                          Airbus Service Bulletin A340-27- In service.
                                           4135, dated January 12, 2006.
                                          Goodrich Actuation Systems       In service.
                                           Service Bulletin SC4800-27-16,
                                           Revision 3, dated May 19, 2006.
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report of cracks of the transducer 
body at its attachment lugs. We are issuing this AD to ensure proper 
functioning of the elevator surfaces, and to prevent cracking of the 
attachment lugs, which could result in partial loss of elevator 
function 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.

[[Page 13095]]

Requirements of AD 2004-03-24

Airplane Flight Manual (AFM) Revision

    (f) Within 30 days after February 26, 2004 (the effective date 
of AD 2004-03-24), revise the Limitations section of the 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.

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

Inspections

    (h) At the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD, except as required by paragraph (g) of this AD: 
Perform a dye penetrant inspection of the attachment lugs of the 
mode selector valve position transducers on each elevator servo 
control installed at damping positions 3CS1 and 3CS2. Do the 
inspection in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-27-3115 or A340-27-4119, both Revision 
03, both including Appendix 01, both dated April 22, 2005, as 
applicable (in paragraphs (h) through (k) of this AD, referred to as 
``the service bulletin''). An inspection that is done before 
February 26, 2004, 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, until the applicable actions required by paragraphs 
(m) and (n) of this AD have been done.
    (1) If the age of the servo control 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 servo control, or within 350 flight cycles on the servo 
control after February 26, 2004, whichever occurs later.
    (2) If the age of the servo control from the date of its first 
installation on the airplane cannot be positively determined, do the 
inspection within 350 flight cycles on the servo control after 
February 26, 2004.
    (3) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A330-27A3115 or A340-
27A4119, both Revision 02, both including Appendix 01, both dated 
December 30, 2003, are acceptable for compliance with the 
corresponding requirements 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

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

Reporting Requirement

    (j) If any crack is found during any inspection required by 
paragraph (h) of this AD: Submit a report in accordance with the 
service bulletin at the applicable time(s) specified in paragraphs 
(j)(1) and (j)(2) of this AD: Submit reports to Airbus Customer 
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 February 26, 2004: 
Submit the report within 30 days after February 26, 2004.
    (2) For an inspection done after February 26, 2004: Submit the 
report within 30 days after the inspection.

Parts Installation

    (k) As of February 26, 2004, no person may install the following 
part on any airplane: a transducer, or a transducer fitted on an 
elevator servo control, 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.

New Requirements of This AD

Upgrade Flight Control Primary Computers (FCPCs)

    (l) For Model A340-200 and -300 series airplanes: Within 2 
months after the effective date of this AD, upgrade the three FCPCs 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A340-27-4131, dated February 21, 2005.

    Note 3: Airbus Service Bulletin A340-27-4131 refers to Airbus 
Vendor Service Bulletins LA2K0-27-017 and LA2K1-27-009, both dated 
January 25, 2005, as additional sources of service information for 
upgrading the FCPCs.

Terminating Actions

    (m) Within 17 months after the effective date of this AD, do the 
actions specified in Table 2 of this AD.

                                          Table 2.--Terminating Actions
----------------------------------------------------------------------------------------------------------------
                                  In accordance with
                                  the Accomplishment
                                    Instructions of                                              In accordance
            Inspect--               Airbus Service         And if--             Then--              with--
                                      Bulletin--
 
----------------------------------------------------------------------------------------------------------------
(1) The elevator servo control    A330-27-3128,       P/N SC4800-7A or -  Modify the four     The Accomplishment
 to determine whether part         dated May 3, 2005   9 is found          elevator servo      Instructions of
 number (P/N) SC4800-7A or -9 is   (for Model A330-    installed.          controls.           the applicable
 installed.                        200 and -300                                                Airbus Service
                                   series                                                      Bulletin.
                                   airplanes); or
                                   A340-27-4129,
                                   dated May 3, 2005
                                   (for Model A340-
                                   200 and -300
                                   series
                                   airplanes); as
                                   applicable.

[[Page 13096]]

 
(2) The elevator servo controls,  None..............  S/N 2324 or below   Replace the mode    Paragraphs 3.A.(2)
 P/N SC4800-10 and SC4800-11 to                        is found            selector valve      and 3.B.(2) of
 determine the serial number (S/                       installed.          position            the
 N) installed.                                                             transducer (MVT)    Accomplishment
                                                                           of the elevator     Instructions of
                                                                           servo controls      Goodrich
                                                                           with a new MVT.     Actuation Systems
                                                                                               Service Bulletin
                                                                                               SC4800-27-16,
                                                                                               Revision 3, dated
                                                                                               May 19, 2006.
----------------------------------------------------------------------------------------------------------------


    Note 4: Airbus Service Bulletins A330-27-3128 and A340-27-4129 
refer to Goodrich Actuation Systems Service Bulletin SC4800-27-16, 
Revision 3, dated May 19, 2006, as an additional source of service 
information for accomplishing the modification of the four elevator 
servo controls.

    (n) Prior to or concurrently with the replacement, if required, 
specified in paragraph (m)(2) of this AD, replace the eye-end 
equipped with a self-lubricated bearing with a new eye-end equipped 
with a roller bearing, grease the new eye-end, and reidentify the 
servo control, in accordance with paragraph 2.A. of the 
Accomplishment Instructions of TRW Service Bulletin SC4800-27-34-09, 
Revision 1, dated November 9, 2001.
    (o) Accomplishing all of the applicable actions required by 
paragraphs (m) and (n) of this AD constitutes terminating action for 
paragraphs (f) through (k) of this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Related Information

    (q) European Aviation Safety Agency airworthiness directive 
2007-0011, dated January 9, 2007, also addresses the subject of this 
AD.

Material Incorporated by Reference

    (r) You must use the applicable service information contained in 
Table 3 of this AD to perform the actions that are required by this 
AD, unless the AD specifies otherwise.

                                  Table 3.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
           Service Bulletin                        Revision level                            Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A330-27-3115,   03.................................  April 22, 2005.
 including Appendix 01.
Airbus Service Bulletin A330-27-3128..  Original...........................  May 3, 2005.
Airbus Service Bulletin A340-27-4119,   03.................................  April 22, 2005.
 including Appendix 01.
Airbus Service Bulletin A340-27-4129..  Original...........................  May 3, 2005.
Airbus Service Bulletin A340-27-4131..  Original...........................  February 21, 2005.
Goodrich Actuation Systems Service      3..................................  May 19, 2006.
 Bulletin SC4800-27-16.
TRW Service Bulletin SC4800-27-34-09..  1..................................  November 9, 2001.
----------------------------------------------------------------------------------------------------------------

    Goodrich Actuation Systems Service Bulletin SC4800-27-16, 
Revision 3, contains the following effective pages:

------------------------------------------------------------------------
                                  Revision level
           Page No.               shown on page      Date shown on page
------------------------------------------------------------------------
1, 6, 8.......................  Original.........  May 9, 2005.
2-5, 7........................  3................  May 19, 2006.
------------------------------------------------------------------------

    (1) 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.
    (2) For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    (3) You may review copies at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-4488 Filed 3-11-08; 8:45 am]
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