Airworthiness Directives; Airbus Model A330-200, A330-300, A340-300, A340-500, and A340-600 Series Airplanes, 52217-52220 [2011-21152]
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Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
attachment lugs. We are issuing this AD to
prevent high-cycle fatigue cracking of the fan
rotor spinner support attachment lugs,
leading to separation of the fan rotor spinner
assembly, uncontained failure of the engine,
and damage to the airplane.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
52217
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.
Compliance
(e) Comply with this AD within 1,800
hours-in-service after the effective date of
this AD, unless already done.
[Docket No. FAA–2011–0385; Directorate
Identifier 2010–NM–256–AD; Amendment
39–16780; AD 2011–17–16]
RIN 2120–AA64
Discussion
Airworthiness Directives; Airbus Model
A330–200, A330–300, A340–300, A340–
500, and A340–600 Series Airplanes
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:
Removal of Fan Rotor Blade Retainers
(f) Remove from service the 24 fan rotor
blade retainers, P/N 2050M56P02.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
Removal of Fan Rotor Spinner Support
(g) Remove from service the fan rotor
spinner support that operated with the fan
rotor blade retainers removed in paragraph (f)
of this AD.
Installation Prohibition
(h) After the effective date of this AD, do
not install any fan rotor blade retainer, P/N
2050M56P02, into any engine. Do not
attempt to repair, make serviceable, or reinstall, this part.
(i) After the effective date of this AD, do
not install any fan rotor spinner support
removed in paragraph (g) of this AD, into any
engine. Do not attempt to repair, make
serviceable, or re-install, this part.
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
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:
SUMMARY:
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.
*
(k) For more information about this AD,
contact John Frost, Aerospace Engineer,
Engine Certification Office, FAA, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7756; fax: 781–238–
7199; e-mail: john.frost@faa.gov.
(l) Refer to GE Service Bulletin No. CF34–
10E S/B 72–0186, for related information.
Contact GE–Aviation, M/D Rm. 285, One
Neumann Way, Cincinnati, OH 45215,
phone: 513–552–3272; e-mail:
geae.aoc@ge.com, for a copy of this service
information. You may review copies of the
referenced service information at the FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
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Related Information
* * * [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.
Issued in Burlington, Massachusetts, on
August 15, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2011–21313 Filed 8–19–11; 8:45 am]
BILLING CODE 4910–13–P
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Jkt 223001
*
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*
*
*
*
*
*
*
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 https://
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.
PO 00000
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SUPPLEMENTARY INFORMATION:
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,
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52218
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
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.
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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 workhours 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.
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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
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:
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1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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
You may examine the AD docket on
the Internet at https://
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.
PO 00000
PART 39—AIRWORTHINESS
DIRECTIVES
(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
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22AUR1
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
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:
52219
(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
Document
Date
Airbus
Airbus
Airbus
Airbus
Airbus
May 3, 2010.
May 3, 2010.
May 3, 2010.
November 6, 2009.
November 6, 2009.
Mandatory Service Bulletin A330–27–3169 .....................................................................................................................
Mandatory Service Bulletin A340–27–4167 .....................................................................................................................
Mandatory Service Bulletin A340–27–5053 .....................................................................................................................
Service Bulletin A330–27–3161 .......................................................................................................................................
Service Bulletin A340–27–4160 .......................................................................................................................................
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 https://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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
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TABLE 2—MATERIAL INCORPORATED BY REFERENCE
Document
Date
Airbus
Airbus
Airbus
Airbus
May 3, 2010.
May 3, 2010.
May 3, 2010.
November 6, 2009.
Mandatory Service Bulletin A330–27–3169 .....................................................................................................................
Mandatory Service Bulletin A340–27–4167 .....................................................................................................................
Mandatory Service Bulletin A340–27–5053 .....................................................................................................................
Service Bulletin A330–27–3161 .......................................................................................................................................
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TABLE 2—MATERIAL INCORPORATED BY REFERENCE—Continued
Document
Date
Airbus Service Bulletin A340–27–4160 .......................................................................................................................................
November 6, 2009.
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0088 Directorate
Identifier 2010–CE–072–AD; Amendment
39–16779; AD 2011–17–15]
RIN 2120–AA64
Airworthiness Directives; Embraer—
Empresa Brasileira de Aeronautica
S.A. (EMBRAER) Model EMB–500
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final Rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued 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:
SUMMARY:
mstockstill on DSK4VPTVN1PROD with RULES
It has been found that moisture may
accumulate and freeze, under certain
conditions, in the gap between the AOA vane
base assembly and the stationary ring of the
sensor’s body. If freezing occurs both AOA
sensors may get stuck and the Stall Warning
Protection System (SWPS) will be no longer
effective without alerting. This may result in
inadvertent aerodynamic stall and loss of
controllability 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.
On September 26, 2011, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
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Jkt 223001
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 service information identified in
this AD, contact EMBRAER Empresa
´
Brasileira de Aeronautica S.A., Phenom
Maintenance Support, Av. Brig. Farina
Lima, 2170, Sao Jose dos Campos—SP,
CEP: 12227–901—PO Box: 36/2,
BRASIL; telephone: ++55 12 3927–5383;
fax: ++55 12 3927–2619; e-mail:
phenom.reliability@ embraer.com.br;
Internet: https://www.embraer.com.br.
You may review copies of the
referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
FOR FURTHER INFORMATION CONTACT: Jim
Rutherford, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4165; fax: (816)
329–4090; e-mail:
jim.rutherford@faa.gov.
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 May 10, 2011 (76 FR 26959).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
It has been found that moisture may
accumulate and freeze, under certain
conditions, in the gap between the AOA vane
base assembly and the stationary ring of the
sensor’s body. If freezing occurs both AOA
sensors may get stuck and the Stall Warning
Protection System (SWPS) will be no longer
effective without alerting. This may result in
inadvertent aerodynamic stall and loss of
controllability of the airplane.
Since this condition may occur in other
airplanes of the same type and affects flight
safety, a corrective action is required. Thus,
sufficient reason exists to request compliance
with this AD in the indicated time limit.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
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Sfmt 4700
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 FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
101 products of U.S. registry.
We estimate that 85 products of U.S.
registry will require the modification
and that it will take about 9.5 workhours per product to comply with the
modification requirements of this AD.
The average labor rate is $85 per workhour. Required parts will cost about
$1,550 per product.
Based on these figures, we estimate
the cost of the modification requirement
of this AD on U.S. operators to be
$200,387.50, or $2,357.50 per product.
We estimate that 101 products of U.S.
registry will require an inspection for
sealant application. We estimate it will
take .5 hour to comply with the
inspection requirements of this AD.
Based on these figures, we estimate
the cost of the inspection for the sealant
application requirement of this AD on
U.S. operators to be $4,292.50, or $42.50
per product.
In addition, we estimate that any
necessary follow-on actions will take
about 1.5 work-hours and require parts
costing $50, for a cost of $177.50 per
product. We have no way of
determining the number of products
that may need these actions.
E:\FR\FM\22AUR1.SGM
22AUR1
Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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 https://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
------------------------------------------------------------------------
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.
Airbus Service Bulletin A340-27-4160.. November 6, 2009.
------------------------------------------------------------------------
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 https://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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Table 2--Material Incorporated by Reference
------------------------------------------------------------------------
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.
------------------------------------------------------------------------
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