Document ID: FAA-2011-0385-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A330-200, A330-300, A340-300, A340-500, and A340-600 Series Airplanes
Posted Date: 2011-08-22T04:00Z

[Federal Register Volume 76, Number 162 (Monday, August 22, 2011)]
[Rules and Regulations]
[Pages 52217-52220]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-21152]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0385; Directorate Identifier 2010-NM-256-AD; 
Amendment 39-16780; AD 2011-17-16]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
300, A340-500, and A340-600 Series Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    During a Back-up Control Module (BCM) retrofit campaign * * *, 
some BCMs have been found with loose gyrometer screws.
    * * * When the aeroplane is in control back up configuration 
(considered to be an extremely remote case), an oscillation of the 
BCM output order may cause degradation of the BCM piloting laws, 
potentially leading to erratic motion of the rudder and possible 
subsequent impact on the Dutch Roll, which constitutes an unsafe 
condition.
* * * * *
    * * * [S]everal Pedal Feel Trim Units (PFTU) have been found 
with loose or broken screws during the accomplishment of maintenance 
tasks on A330 fitted with electrical rudder and A340-600. The loose 
or failed screws could lead to the loss of the coupling between the 
Rotary Variable Differential Transducer (RVDT) shaft and the PFTU 
shaft, and consequently to a potential rudder runaway when the BCM 
is activated.
* * * * *
    The unsafe condition is loss of control of the airplane. We are 
issuing this AD to require actions to correct the unsafe condition on 
these products.

DATES: This AD becomes effective September 26, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 26, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on April 26, 2011 (76 
FR 23218). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During a Back-up Control Module (BCM) retrofit campaign in 
accordance with [European Aviation Safety Agency] (EASA) AD 2006-
0313 requirements, some BCMs have been found with loose gyrometer 
screws.
    The gyrometer is installed on the DELRIN plate by internal 
screws and the DELRIN plate is installed on BCM casing by external 
screws.
    Investigations done by the BCM manufacturer SAGEM have shown 
that the root cause of these events is a lack of design robustness 
of the BCM[.] When the aeroplane is in control back up configuration 
(considered to be an extremely remote case), an oscillation of the 
BCM output order may cause degradation of the BCM piloting laws, 
potentially leading to erratic motion of the rudder and possible 
subsequent impact on the Dutch Roll, which constitutes an unsafe 
condition.
    EASA AD 2008-0131 was issued to prohibit aeroplane dispatch with 
FCPC3 [flight control primary computer] inoperative (from GO IF to 
NO GO) as an interim solution, limited to A330 and A340-300 fitted 
with electrical rudder.
    After EASA AD 2008-0131 issuance, several Pedal Feel Trim Units 
(PFTU) have been found with loose or broken screws during the 
accomplishment of maintenance tasks on A330 fitted with electrical 
rudder and A340-600. The loose or failed screws could lead to the 
loss of the coupling between the Rotary Variable Differential 
Transducer (RVDT) shaft and the PFTU shaft, and consequently to a 
potential rudder runaway when the BCM is activated.
    EASA AD 2009-0153 retained the requirements of EASA AD 2008-0131 
and extended the applicability to A340-500/600 aeroplanes.
    This [EASA] AD, which supersedes EASA AD 2009-0153 retaining its 
requirements, requires the installation of:

--a new BCM on A330 and A340-200/-300 series aeroplanes fitted with 
electrical rudder, and
--an improved PFTU on A330 and A340-200/-300 series aeroplanes 
fitted with an electrical rudder and A340-500/&600 series 
aeroplanes,

[[Page 52218]]

which, once installed, eliminate the root cause of the unsafe 
condition and cancel the operational limitation.
* * * * *
The unsafe condition is loss of control of the airplane. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a Note within the AD.

Costs of Compliance

    We estimate that this AD will affect 46 products of U.S. registry. 
We also estimate that it will take about 17 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $0 per product. 
Where the service information lists required parts costs that are 
covered under warranty, we have assumed that there will be no charge 
for these parts. As we do not control warranty coverage for affected 
parties, some parties may incur costs higher than estimated here. Based 
on these figures, we estimate the cost of this AD to the U.S. operators 
to be $66,470, or $1,445 per product.

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 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 this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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 FAA amends Sec.  39.13 by adding the following new AD:
2011-17-16 Airbus: Amendment 39-16780. Docket No. FAA-2011-0385; 
Directorate Identifier 2010-NM-256-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 26, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to airplanes specified in paragraphs (c)(1), 
(c)(2), and (c)(3) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, 
all manufacturer serial numbers on which Airbus modification 49144 
(install electrical rudder) has been embodied in production, except 
those on which Airbus modification 58118 and Airbus modification 
200667 have been embodied in production.
    (2) Airbus Model A340-311, -312, and -313 airplanes, all 
manufacturer serial numbers on which Airbus modification 49144 has 
been embodied in production, except those on which Airbus 
modification 58118 and Airbus modification 200667 have been embodied 
in production.
    (3) Airbus Model A340-541 and -642 airplanes, all manufacturer 
serial numbers, except those on which Airbus modification 200667 has 
been embodied in production.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    During a Back-up Control Module (BCM) retrofit campaign * * *, 
some BCMs have been found with loose gyrometer screws.
    * * * When the aeroplane is in control back up configuration 
(considered to be an extremely remote case), an oscillation of the 
BCM output order may cause degradation of the BCM piloting laws, 
potentially leading to erratic motion of the rudder and possible 
subsequent impact on the Dutch Roll, which constitutes an unsafe 
condition.
* * * * *
    * * * [S]everal Pedal Feel Trim Units (PFTU) have been found 
with loose or broken screws during the accomplishment of maintenance 
tasks on A330 fitted with electrical rudder and A340-600. The loose 
or failed screws could lead to the loss of the coupling between the 
Rotary Variable Differential Transducer (RVDT) shaft and the

[[Page 52219]]

PFTU shaft, and consequently to a potential rudder runaway when the 
BCM is activated.
* * * * *
    The unsafe condition is loss of control of the airplane.

Compliance

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

Dispatch Prohibition

    (g) As of the effective date of this AD, dispatch with the 
flight control primary computer (FCPC) 3 ``PRIM 3'' inoperative is 
prohibited unless the applicable modifications required by this AD 
have been done within the compliance time in this AD.

Airplane Flight Manual (AFM) Revision

    (h) Within 30 days after the effective date of this AD, revise 
the Limitations section of the Airbus A330 or A340 AFM, as 
applicable, to include the following statement:''Dispatch with the 
flight control primary computer (FCPC) 3 ``PRIM 3'' inoperative is 
prohibited.'' This may be done by inserting a copy of this AD into 
the applicable AFM.

    Note 1:  When a statement identical to that in paragraph (h) of 
this AD has been included in the general revisions of the applicable 
AFM, the general revisions may be inserted into the applicable AFM, 
and the copy of this AD may be removed from the applicable AFM.

Modification

    (i) For Airbus Model A330-201, -202, -203, -223, -223F, -243, -
243F, -301, -302, -303, -321, -322, -323, -341, -342, -343, and 
A340-311, -312, and -313 series airplanes: Within 48 months after 
the effective date of this AD, do the actions specified in 
paragraphs (i)(1) and (i)(2) of this AD:
    (1) Modify the BCM, in accordance with the Accomplishment 
Instruction of Airbus Service Bulletin A330-27-3161 (for Model A330-
201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -
322, -341, -343 airplanes) or A340-27-4160 (for Model A340-311, -
312, and -313 airplanes), both dated November 6, 2009.
    (2) Modify the PFTU, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-27-3169 or 
A340-27-4167, both dated May 3, 2010, as applicable.
    (j) For Airbus Model 340-541 and -642 airplanes: Within 48 
months after the effective date of this AD, modify the PFTU, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A340-27-5053, dated May 3, 2010.

Terminating Action

    (k) Modifying both the BCM and PFTU as required by paragraphs 
(i)(1) and (i)(2) of this AD terminates the requirements of 
paragraphs (g) and (h) of this AD.
    (l) Modifying the PFTU as required by paragraph (j) of this AD 
terminates the requirements in paragraphs (g) and (h) of this AD.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (m) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

Related Information

    (n) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0191, dated September 27, 2010 [Corrected October 7, 
2010], and the service bulletins listed in table 1 of this AD, for 
related information.

                    Table 1--Airbus Service Bulletins
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               Document                               Date
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Airbus Mandatory Service Bulletin A330- May 3, 2010.
 27-3169.
Airbus Mandatory Service Bulletin A340- May 3, 2010.
 27-4167.
Airbus Mandatory Service Bulletin A340- May 3, 2010.
 27-5053.
Airbus Service Bulletin A330-27-3161..  November 6, 2009.
Airbus Service Bulletin A340-27-4160..  November 6, 2009.
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Material Incorporated by Reference

    (o) You must use the service information contained in table 2 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; e-mail airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference 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/code_of_federal_regulations/ibr_locations.html.

               Table 2--Material Incorporated by Reference
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               Document                               Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A330- May 3, 2010.
 27-3169.
Airbus Mandatory Service Bulletin A340- May 3, 2010.
 27-4167.
Airbus Mandatory Service Bulletin A340- May 3, 2010.
 27-5053.
Airbus Service Bulletin A330-27-3161..  November 6, 2009.

[[Page 52220]]

 
Airbus Service Bulletin A340-27-4160..  November 6, 2009.
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    Issued in Renton, Washington on August 10, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2011-21152 Filed 8-19-11; 8:45 am]
BILLING CODE 4910-13-P