[Federal Register Volume 76, Number 80 (Tuesday, April 26, 2011)]
[Proposed Rules]
[Pages 23218-23221]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-10007]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0385; Directorate Identifier 2010-NM-256-AD]
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), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed 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. The proposed
AD would require actions that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on this proposed AD by June 10, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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 [email protected]; Internet http://www.airbus.com. You may review copies of the referenced 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.
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 this proposed AD, 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.
[[Page 23219]]
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0385;
Directorate Identifier 2010-NM-256-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2010-0191, dated September 27, 2010 [Corrected
October 7, 2010] (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:
During a Back-up Control Module (BCM) retrofit campaign in
accordance with 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 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 A340-300 series aeroplanes fitted with
electrical rudder, and
--an improved PFTU on A330 and A340-300 series aeroplanes fitted
with an electrical rudder and A340-500/-600 series aeroplanes,
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.
Relevant Service Information
Airbus has issued the service bulletins in the following table.
Service Bulletins
------------------------------------------------------------------------
Document Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin May 3, 2010.
A330-27-3169.
Airbus Mandatory Service Bulletin May 3, 2010.
A340-27-4167.
Airbus Mandatory Service Bulletin May 3, 2010.
A340-27-5053.
Airbus Service Bulletin A330-27-3161. November 6, 2009.
Airbus Service Bulletin A340-27-4160. November 6, 2009.
------------------------------------------------------------------------
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
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 proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 46 products of U.S. registry. We also estimate that
it would take about 17 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Required parts would 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 costs.
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 the proposed AD on U.S. operators to
be $66,470, or $1,445 per product.
[[Page 23220]]
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2011-0385; Directorate Identifier 2010-NM-
256-AD.
Comments Due Date
(a) We must receive comments by June 10, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to airplanes 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 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 Revision
(h) Within 30 days after the effective date of this AD, revise
the Limitations section of the Airbus A330 or A340 airplane flight
manual (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 AFM.
Note 1: When a statement identical to that in paragraph (h) of
this AD has been included in the general revisions of the AFM, the
general revisions may be inserted into the AFM, and the copy of this
AD may be removed from the 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
Instructions of Airbus Service Bulletin A330-27-3161 (for Model
A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -
321, -322, -323, -341, -342, -343 airplanes) or A340-27-4160 (for
Model A340-311, -312, and -313 airplanes), both dated November 6,
2009, as applicable.
(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
[[Page 23221]]
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: [email protected].
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
------------------------------------------------------------------------
Document Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin May 3, 2010.
A330-27-3169.
Airbus Mandatory Service Bulletin May 3, 2010.
A340-27-4167.
Airbus Mandatory Service Bulletin May 3, 2010.
A340-27-5053.
Airbus Service Bulletin A330-27-3161. November 6, 2009.
Airbus Service Bulletin A340-27-4160. November 6, 2009.
------------------------------------------------------------------------
Issued in Renton, Washington, on April 18, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-10007 Filed 4-25-11; 8:45 am]
BILLING CODE 4910-13-P