Airworthiness Directives; Airbus Airplanes, 19085-19088 [2013-06172]
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Federal Register / Vol. 78, No. 61 / Friday, March 29, 2013 / Rules and Regulations
was listed in accordance with
§ 94.6(a)(2)(i) as one in which HPAI is
considered to exist, except for the
APHIS-defined EU Poultry Trade
Region;
(ii) A restricted zone in the APHISdefined EU Poultry Trade Region
established because of detection of
Newcastle disease or HPAI in
commercial poultry, from the time of
detection until the designation of the
zone as a restricted zone is removed by
the competent veterinary authority of
the Member State or until 3 months (90
days) following depopulation of the
poultry on affected premises in the
restricted zone and the cleaning and
disinfection of the last affected premises
in the zone, whichever is later; or
(iii) A restricted zone in the APHISdefined EU Poultry Trade Region
established because of detection of
Newcastle disease or HPAI in racing
pigeons, backyard flocks, and wild
birds, from the time of detection until
the designation of the zone as a
restricted zone is removed by the
competent veterinary authority of the
Member State.
(2) The birds and poultry must not
have been commingled with other birds
or poultry that have at any time been in
any of the regions or zones described in
paragraphs (b)(1)(i) through (b)(1)(iii) of
this section.
(3) The birds and poultry must only
originate from within the APHISdefined EU Poultry Trade Region and
the farms of origin must not have
received birds or poultry imported from
outside the APHIS-defined EU Poultry
Trade Region.
(4) No equipment or materials used in
transporting the birds and poultry may
have been used previously for
transporting birds or poultry that do not
meet the requirements of this paragraph,
unless the equipment and materials
have first been cleaned and disinfected.
(5) The birds and poultry must be
accompanied by a certificate issued by
an official of the competent veterinary
authority of the Member State who is
authorized to issue the inspection
certificate required by § 93.205 of this
subchapter, stating that the applicable
provisions of paragraphs (b)(1) through
(b)(4) of this section have been met. The
certification may be placed on the
foreign meat inspection certificate
required by § 381.196 of this title or may
be contained in a separate document.
(c) Hatching eggs. Hatching eggs
intended for import from the APHISdefined EU Poultry Trade Region are
subject to all applicable provisions of
paragraph (b) of this section, except that
such hatching eggs may be moved
through zones established because of
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detection of HPAI within the APHISdefined EU Poultry Trade Region
provided that the hatching eggs are
transported under official seal and
accompanied by a certificate as
indicated in § 94.28(b)(5) stating that the
applicable provisions of paragraph (b)
have been met. The import permit will
require the seal number to be listed on
the health certificate that accompanies
the shipment and the veterinarian who
places the seal will be required to sign
his or her name under the seal number.
Seals must not be broken until the
shipment reaches its U.S. port of entry.
Hatching egg shipment with seals that
are not intact will be rejected upon
inspection at the U.S. port of entry.
(d) Presentation of certificates. The
certificates required by paragraphs
(a)(5), (b)(5), and (c) of this section must
be presented by the importer to an
authorized inspector at the port of
arrival, upon arrival of the birds,
poultry, hatching eggs, or poultry meat
and products at the port.
PART 95—SANITARY CONTROL OF
ANIMAL BYPRODUCTS (EXCEPT
CASINGS), AND HAY AND STRAW,
OFFERED FOR ENTRY INTO THE
UNITED STATES
23. The authority citation for part 95
continues to read as follows:
■
Authority: 7 U.S.C. 8301–8317; 21 U.S.C.
136 and 136a; 31 U.S.C. 9701; 7 CFR 2.22,
2.80, and 371.4.
§ 95.5
[Amended]
24. In § 95.5, paragraph (c) is amended
by removing the words ‘‘exotic’’ and
‘‘subtype H5N1’’.
■
§ 95.6
[Amended]
25. In § 95.6, paragraph (c) is amended
by removing the word ‘‘exotic’’.
■
PART 104—PERMITS FOR
BIOLOGICAL PRODUCTS
26. The authority citation for part 104
continues to read as follows:
■
Authority: 21 U.S.C. 151–159; 7 CFR 2.22,
2.80, and 371.4.
§ 104.2
[Amended]
27. In § 104.2, paragraph (b) is
amended by removing the words ‘‘fowl
pest (fowl plague)’’ and adding the
words ‘‘highly pathogenic avian
influenza’’ in their place.
■
Done in Washington, DC, this 26th day of
March 2013.
Peter Fernandez,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. 2013–07345 Filed 3–28–13; 8:45 am]
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19085
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0150; Directorate
Identifier 2011–NM–234–AD; Amendment
39–17399; AD 2013–06–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 series airplanes. This AD was
prompted by reports of oil residue
between the stator and the rotor parts of
the position resolvers of the angle of
attack (AOA) vane, which was a result
of incorrect removal of the machining
oil during the manufacturing process of
the AOA resolvers. This AD requires an
inspection to determine if certain AOA
probes are installed, and replacement of
any affected AOA probe. We are issuing
this AD to prevent erroneous AOA
information and consequent delayed or
non-activation of the AOA protection
systems, which during flight at a high
AOA, could result in reduced control of
the airplane.
DATES: This AD becomes effective May
3, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 3, 2013.
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–1405; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a second supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 to include an
AD that would apply to the specified
products. That second SNPRM was
published in the Federal Register on
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December 10, 2012 (77 FR 73340). That
second SNPRM proposed to correct an
unsafe condition for the specified
products. The Mandatory Continuing
Airworthiness Information (MCAI)
states:
During Airbus Final Assembly Line flight
tests, AoA [angle of attack] data from two
different aeroplanes were found inaccurate,
which was confirmed by flight data analysis.
Investigation conducted by Airbus and
Thales on the removed probes revealed oil
residue between the stator and the rotor parts
of the AoA vane position resolvers. This oil
residue was the result of incorrect removal of
machining oil during the manufacturing
process of the AoA resolvers. At low
temperatures, this oil residue becomes
viscous (typically in cruise), causing delayed
and/or reduced AoA vane movement.
Multiple AOA probes could be
simultaneously affected, providing incorrect
indications of the AoA of the aeroplane.
This condition, if not corrected, could lead
to erroneous AoA information and
consequent delayed or non-activation of the
AoA protection systems which, during flight
at a high angle of attack, could result in
reduced control of the aeroplane.
For the reasons described above, this
[European Aviation Safety Agency (EASA)]
AD requires the identification of the serial
number (s/n) of each installed Thales
Avionics Part Number (P/N) C16291AA AoA
probe and the replacement of all suspect
units with serviceable ones. This AD also
prohibits the (re)installation of these same
s/n probes on any aeroplane, unless
corrective measures have been accomplished.
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
considered the comment received.
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Request to Update Service Information
Airbus requested that the service
information referenced in the second
SNPRM (77 FR 73340, December 10,
2012) be updated to include recently
added service information. Airbus
stated that EASA has issued AD 2012–
0236R1, dated December 17, 2012. In
addition, Airbus stated that Thales
Avionics has issued Service Bulletin
C16291A–34–007, Revision 04, dated
October 11, 2012.
We partially agree with Airbus’
request regarding using the most recent
service information. Since the second
SNPRM (77 FR 73340, December 10,
2012) was issued, we have reviewed
Thales Avionics Service Bulletin
C16291A–34–007, Revision 04, dated
October 11, 2012. The actions in that
service information remain unchanged
from the previous service information.
We have revised paragraphs (g), (i), and
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(k) of this AD accordingly to reflect the
most current Thales Avionics service
information.
In addition, we have reviewed EASA
AD 2012–0236, dated November 9, 2012
(corrected November 12, 2012), and
EASA AD 2012–0236R1, dated
December 17, 2012. We have
determined that no subsequent changes
are required in this final rule as done to
the EASA AD. We have not changed this
final rule in this regard.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously–
and minor editorial changes. We have
determined that these changes:
• Are consistent with the intent that
was proposed in the second SNPRM (77
FR 73340, December 10, 2012) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (77 FR 73340,
December 10, 2012).
Costs of Compliance
We estimate that this AD will affect
755 products of U.S. registry. We also
estimate that it will take about 2 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $128,350, or $170 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 3 work-hours and require parts
costing $0, for a cost of $255 per
product. We have no way of
determining the number of products
that may need these actions.
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
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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 that 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);
3. Will not affect intrastate aviation in
Alaska; and
4. 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 second SNPRM (77 FR
73340, December 10, 2012), 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
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:
■
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Federal Register / Vol. 78, No. 61 / Friday, March 29, 2013 / Rules and Regulations
2013–06–03 Airbus: Amendment 39–17399.
Docket No. FAA–2012–0150; Directorate
Identifier 2011–NM–234–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective May 3, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 34: Navigation.
(e) Reason
This AD was prompted by reports of oil
residue between the stator and the rotor parts
of the position resolvers of the angle of attack
(AOA) vane, which was a result of incorrect
removal of the machining oil during the
manufacturing process of the AOA resolvers.
We are issuing this AD to prevent erroneous
AOA information and consequent delayed or
non-activation of the AOA protection
systems, which during flight at a high angle
of attack, could result in reduced control of
the airplane.
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(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Inspection
Within 12 months after the effective date
of this AD, except as provided by paragraph
(h) of this AD: Do the inspections specified
in paragraphs (g)(1) and (g)(2) of this AD.
(1) Inspect to determine the part number
(P/N) and serial number of each Thales
Avionics AOA probe, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1452, dated
January 29, 2010. If any probe is found
having P/N C16291AA and having a serial
number listed in Thales Avionics Service
Bulletin C16291A–34–007, Revision 04,
dated October 11, 2012: Within 12 months
after the effective date of this AD, replace the
AOA probe, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1452, provided
that Thales Avionics Service Bulletin
C16291A–34–009, dated September 10, 2009;
or Airbus Service Bulletin A320–34–1444,
dated October 7, 2009; have not been
accomplished. Thales Avionics Service
Bulletin C16291A–34–009, dated September
10, 2009; and Airbus Service Bulletin A320–
34–1444, dated October 7, 2009; (which are
not incorporated by reference in this AD)
cannot be used for the installation of AOA
probes having P/N C16291AB. A review of
airplane maintenance records is acceptable in
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lieu of this inspection if the part number and
serial number of the installed AOA probes
can be conclusively determined from that
review.
(2) Inspect to determine the part number
and serial number of each Thales Avionics
AOA probe, in accordance with paragraph
3.C.(1)(a) of the Accomplishment Instructions
of Airbus Service Bulletin A320–34–1452,
dated January 29, 2010. If any probe is found
having P/N C16291AB, on which Thales
Avionics Service Bulletin C16291A–34–009,
dated September 10, 2009; or Airbus Service
Bulletin A320–34–1444, dated October 7,
2009; (which are not incorporated by
reference in this AD) has been accomplished:
Within 12 months after the effective date of
this AD, replace the AOA probe, in
accordance with a method approved by the
Manager, International Branch, ANM–116,
FAA, or European Aviation Safety Agency
(EASA) (or its delegated agent). A review of
airplane maintenance records is acceptable in
lieu of the inspection specified in this
paragraph if the part number of the installed
AOA probes can be conclusively determined
from that review.
Note 1 to paragraph (g)(2) of this AD:
Additional guidance for replacing the AOA
probes may be found in Task 34–11–19–000–
001–A, Removal of the Angle of Attack
Sensor, of the Airbus A318/A319/A320/A321
Aircraft Maintenance Manual, which is not
incorporated by reference in this AD.
(h) Exception to the Requirements of
Paragraph (g) of This AD
For any airplane on which Airbus
modification 150006 (installation of Thales
Avionics AOA probes P/N C16291AB) or
modification 26934 (installation of Goodrich
AOA probes P/N 0861ED) has been embodied
in production, and on which no AOA probe
replacement has been made since first flight:
The actions specified in paragraph (g) of this
AD are not required.
(i) Parts Installation Limitation and
Prohibition
(1) As of the effective date of this AD, no
person may install a Thales Avionics AOA
probe, P/N C16291AA, having a serial
number listed in Thales Avionics Service
Bulletin C16291A–34–007, Revision 04,
dated October 11, 2012, on any airplane,
unless that Thales Avionics probe has been
inspected, re-identified, and tested, in
accordance with the Accomplishment
Instructions of the service information
specified in paragraphs (i)(1)(i) through
(i)(1)(iv) of this AD.
(i) Thales Avionics Service Bulletin
C16291A–34–007, Revision 04, dated
October 11, 2012.
(ii) Thales Avionics Service Bulletin
C16291A–34–007, Revision 03, dated April
10, 2012.
(iii) Thales Avionics Service Bulletin
C16291A–34–007, Revision 02, dated
December 16, 2011.
(iv) Thales Avionics Service Bulletin
C16291A–34–007, Revision 01, dated
December 3, 2009.
(2) As of the effective date of this AD, no
person may install a Thales Avionics AOA
probe, P/N C16291AB, on which Thales
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19087
Avionics Service Bulletin C16291A–34–009,
dated September 10, 2009; or Airbus Service
Bulletin A320–34–1444, dated October 7,
2009; (which are not incorporated by
reference in this AD) has been incorporated.
(j) Other FAA AD Provisions
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1405; fax (425)
227–1149. Information may be emailed to: 9ANM-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.
(k) Related Information
Refer to MCAI EASA AD 2011–0203, dated
October 13, 2011, and the service information
specified in paragraphs (k)(1) through (k)(5)
of this AD, for related information.
(1) Airbus Service Bulletin A320–34–1452,
dated January 29, 2010.
(2) Thales Avionics Service Bulletin
C16291A–34–007, Revision 04, dated
October 11, 2012.
(3) Thales Avionics Service Bulletin
C16291A–34–007, Revision 03, dated April
10, 2012.
(4) Thales Avionics Service Bulletin
C16291A–34–007, Revision 02, dated
December 16, 2011.
(5) Thales Avionics Service Bulletin
C16291A–34–007, Revision 01, dated
December 3, 2009.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Service Bulletin A320–34–1452,
dated January 29, 2010.
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(ii) Thales Avionics Service Bulletin
C16291A–34–007, Revision 04, dated
October 11, 2012.
(iii) Thales Avionics Service Bulletin
C16291A–34–007, Revision 03, dated April
10, 2012. Pages 1, 8, 10, 11, and 13 of this
document are identified as Revision 03,
dated April 10, 2012. Pages 2, 7, and 12 are
identified as Revision 01, dated December 3,
2009. Page 9 is identified as Revision 02,
dated December 16, 2011.
(iv) Thales Avionics Service Bulletin
C16291A–34–007, Revision 02, dated
December 16, 2011. Pages 1, and pages 8
through 10 of this document are identified as
Revision 02, dated December 16, 2011; pages
2 through 7, and pages 11 through 13 are
identified as Revision 01, dated December 3,
2009.
(v) Thales Avionics Service Bulletin
C16291A–34–007, Revision 01, dated
December 3, 2009.
(3) For Airbus service information
identified in this AD, contact Airbus,
Airworthiness Office—EAS, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com. For Thales Avionics service
information identified in this AD, contact
Thales Avionics, Retrofit Manager, 105,
´ ´
Avenue du General Eisenhower, BP 63647,
31036 Toulouse Cedex 1, France; telephone
+33 5 61 19 76 95; fax +33 5 61 19 68 20;
email retrofit.ata@fr.thalesgroup.com;
Internet https://www.thalesgroup.com/
aerospace.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(5) You may view this 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 8,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–06172 Filed 3–28–13; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1346; Directorate
Identifier 2012–CE–047–AD; Amendment
39–17401; AD 2013–06–04]
RIN 2120–AA64
Airworthiness Directives; REIMS
AVIATION S.A. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for REIMS
AVIATION S.A. Model F406 airplanes.
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 fretting (wear
and/or chafing) found between the
elevator pushrod assembly and the
horizontal tail structure, which could
cause the elevator pushrod to jam and
could result in loss of control. We are
issuing this AD to require actions to
address the unsafe condition on these
products.
DATES: This AD is effective May 3, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 3, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
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 REIMS AVIATION
´
INDUSTRIES, Aerodrome de Reims
Prunay, 51360 Prunay, France;
telephone: 03.26.48.46.65; fax:
03.26.49.18.57; Internet: https://
www.geciaviation.com/en/. 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:
Albert Mercado, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
4119; fax: (816) 329–4090; email:
albert.mercado@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 January 3, 2013 (78 FR 275).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
During maintenance, fretting has been
found between the elevator pushrod
assembly and horizontal tail structure on
Reims F406 aeroplanes. In addition, bending
was found on a pushrod assembly Part
Number (P/N) 6015034–1. The investigation
has not yet established the exact cause(s) of
these occurrences.
This condition, if not detected and
corrected, could lead to failure of a pushrod
and consequent jamming of the elevator
controls, possibly resulting in loss of control
of the aeroplane.
For the reasons described above, this AD
requires inspection of the pushrods and
horizontal tail structure to detect fretting,
bending or eccentricity and, depending on
findings, replacement with a serviceable
pushrod, or repair. This AD also requires the
return on replaced pushrods to RAI for
investigation.
This AD is considered to be an interim
action and further AD action may follow.
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 (78
FR 275, January 3, 2013) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR 275,
January 3, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 275,
January 3, 2013).
Costs of Compliance
We estimate that this AD will affect 7
products of U.S. registry. We also
estimate that it will take about 4 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
E:\FR\FM\29MRR1.SGM
29MRR1
]]>Agencies
[Federal Register Volume 78, Number 61 (Friday, March 29, 2013)]
[Rules and Regulations]
[Pages 19085-19088]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-06172]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0150; Directorate Identifier 2011-NM-234-AD;
Amendment 39-17399; AD 2013-06-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and A321 series airplanes. This AD was
prompted by reports of oil residue between the stator and the rotor
parts of the position resolvers of the angle of attack (AOA) vane,
which was a result of incorrect removal of the machining oil during the
manufacturing process of the AOA resolvers. This AD requires an
inspection to determine if certain AOA probes are installed, and
replacement of any affected AOA probe. We are issuing this AD to
prevent erroneous AOA information and consequent delayed or non-
activation of the AOA protection systems, which during flight at a high
AOA, could result in reduced control of the airplane.
DATES: This AD becomes effective May 3, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 3, 2013.
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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1405; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a second supplemental notice of proposed rulemaking
(SNPRM) to amend 14 CFR part 39 to include an AD that would apply to
the specified products. That second SNPRM was published in the Federal
Register on
[[Page 19086]]
December 10, 2012 (77 FR 73340). That second SNPRM proposed to correct
an unsafe condition for the specified products. The Mandatory
Continuing Airworthiness Information (MCAI) states:
During Airbus Final Assembly Line flight tests, AoA [angle of
attack] data from two different aeroplanes were found inaccurate,
which was confirmed by flight data analysis.
Investigation conducted by Airbus and Thales on the removed
probes revealed oil residue between the stator and the rotor parts
of the AoA vane position resolvers. This oil residue was the result
of incorrect removal of machining oil during the manufacturing
process of the AoA resolvers. At low temperatures, this oil residue
becomes viscous (typically in cruise), causing delayed and/or
reduced AoA vane movement. Multiple AOA probes could be
simultaneously affected, providing incorrect indications of the AoA
of the aeroplane.
This condition, if not corrected, could lead to erroneous AoA
information and consequent delayed or non-activation of the AoA
protection systems which, during flight at a high angle of attack,
could result in reduced control of the aeroplane.
For the reasons described above, this [European Aviation Safety
Agency (EASA)] AD requires the identification of the serial number
(s/n) of each installed Thales Avionics Part Number (P/N) C16291AA
AoA probe and the replacement of all suspect units with serviceable
ones. This AD also prohibits the (re)installation of these same s/n
probes on any aeroplane, unless corrective measures have been
accomplished.
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 considered the comment received.
Request to Update Service Information
Airbus requested that the service information referenced in the
second SNPRM (77 FR 73340, December 10, 2012) be updated to include
recently added service information. Airbus stated that EASA has issued
AD 2012-0236R1, dated December 17, 2012. In addition, Airbus stated
that Thales Avionics has issued Service Bulletin C16291A-34-007,
Revision 04, dated October 11, 2012.
We partially agree with Airbus' request regarding using the most
recent service information. Since the second SNPRM (77 FR 73340,
December 10, 2012) was issued, we have reviewed Thales Avionics Service
Bulletin C16291A-34-007, Revision 04, dated October 11, 2012. The
actions in that service information remain unchanged from the previous
service information. We have revised paragraphs (g), (i), and (k) of
this AD accordingly to reflect the most current Thales Avionics service
information.
In addition, we have reviewed EASA AD 2012-0236, dated November 9,
2012 (corrected November 12, 2012), and EASA AD 2012-0236R1, dated
December 17, 2012. We have determined that no subsequent changes are
required in this final rule as done to the EASA AD. We have not changed
this final rule in this regard.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously-and minor editorial changes.
We have determined that these changes:
Are consistent with the intent that was proposed in the
second SNPRM (77 FR 73340, December 10, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (77 FR 73340, December 10, 2012).
Costs of Compliance
We estimate that this AD will affect 755 products of U.S. registry.
We also estimate that it will take about 2 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $128,350, or $170 per product.
In addition, we estimate that any necessary follow-on actions would
take about 3 work-hours and require parts costing $0, for a cost of
$255 per product. We have no way of determining the number of products
that may need these actions.
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 that 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);
3. Will not affect intrastate aviation in Alaska; and
4. 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 second SNPRM (77 FR 73340,
December 10, 2012), 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:
[[Page 19087]]
2013-06-03 Airbus: Amendment 39-17399. Docket No. FAA-2012-0150;
Directorate Identifier 2011-NM-234-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective May 3, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category; all
manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 34: Navigation.
(e) Reason
This AD was prompted by reports of oil residue between the
stator and the rotor parts of the position resolvers of the angle of
attack (AOA) vane, which was a result of incorrect removal of the
machining oil during the manufacturing process of the AOA resolvers.
We are issuing this AD to prevent erroneous AOA information and
consequent delayed or non-activation of the AOA protection systems,
which during flight at a high angle of attack, could result in
reduced control of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Inspection
Within 12 months after the effective date of this AD, except as
provided by paragraph (h) of this AD: Do the inspections specified
in paragraphs (g)(1) and (g)(2) of this AD.
(1) Inspect to determine the part number (P/N) and serial number
of each Thales Avionics AOA probe, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-34-1452,
dated January 29, 2010. If any probe is found having P/N C16291AA
and having a serial number listed in Thales Avionics Service
Bulletin C16291A-34-007, Revision 04, dated October 11, 2012: Within
12 months after the effective date of this AD, replace the AOA
probe, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-34-1452, provided that Thales Avionics Service
Bulletin C16291A-34-009, dated September 10, 2009; or Airbus Service
Bulletin A320-34-1444, dated October 7, 2009; have not been
accomplished. Thales Avionics Service Bulletin C16291A-34-009, dated
September 10, 2009; and Airbus Service Bulletin A320-34-1444, dated
October 7, 2009; (which are not incorporated by reference in this
AD) cannot be used for the installation of AOA probes having P/N
C16291AB. A review of airplane maintenance records is acceptable in
lieu of this inspection if the part number and serial number of the
installed AOA probes can be conclusively determined from that
review.
(2) Inspect to determine the part number and serial number of
each Thales Avionics AOA probe, in accordance with paragraph
3.C.(1)(a) of the Accomplishment Instructions of Airbus Service
Bulletin A320-34-1452, dated January 29, 2010. If any probe is found
having P/N C16291AB, on which Thales Avionics Service Bulletin
C16291A-34-009, dated September 10, 2009; or Airbus Service Bulletin
A320-34-1444, dated October 7, 2009; (which are not incorporated by
reference in this AD) has been accomplished: Within 12 months after
the effective date of this AD, replace the AOA probe, in accordance
with a method approved by the Manager, International Branch, ANM-
116, FAA, or European Aviation Safety Agency (EASA) (or its
delegated agent). A review of airplane maintenance records is
acceptable in lieu of the inspection specified in this paragraph if
the part number of the installed AOA probes can be conclusively
determined from that review.
Note 1 to paragraph (g)(2) of this AD: Additional guidance for
replacing the AOA probes may be found in Task 34-11-19-000-001-A,
Removal of the Angle of Attack Sensor, of the Airbus A318/A319/A320/
A321 Aircraft Maintenance Manual, which is not incorporated by
reference in this AD.
(h) Exception to the Requirements of Paragraph (g) of This AD
For any airplane on which Airbus modification 150006
(installation of Thales Avionics AOA probes P/N C16291AB) or
modification 26934 (installation of Goodrich AOA probes P/N 0861ED)
has been embodied in production, and on which no AOA probe
replacement has been made since first flight: The actions specified
in paragraph (g) of this AD are not required.
(i) Parts Installation Limitation and Prohibition
(1) As of the effective date of this AD, no person may install a
Thales Avionics AOA probe, P/N C16291AA, having a serial number
listed in Thales Avionics Service Bulletin C16291A-34-007, Revision
04, dated October 11, 2012, on any airplane, unless that Thales
Avionics probe has been inspected, re-identified, and tested, in
accordance with the Accomplishment Instructions of the service
information specified in paragraphs (i)(1)(i) through (i)(1)(iv) of
this AD.
(i) Thales Avionics Service Bulletin C16291A-34-007, Revision
04, dated October 11, 2012.
(ii) Thales Avionics Service Bulletin C16291A-34-007, Revision
03, dated April 10, 2012.
(iii) Thales Avionics Service Bulletin C16291A-34-007, Revision
02, dated December 16, 2011.
(iv) Thales Avionics Service Bulletin C16291A-34-007, Revision
01, dated December 3, 2009.
(2) As of the effective date of this AD, no person may install a
Thales Avionics AOA probe, P/N C16291AB, on which Thales Avionics
Service Bulletin C16291A-34-009, dated September 10, 2009; or Airbus
Service Bulletin A320-34-1444, dated October 7, 2009; (which are not
incorporated by reference in this AD) has been incorporated.
(j) Other FAA AD Provisions
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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington
98057-3356; telephone (425) 227-1405; fax (425) 227-1149.
Information may be emailed 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.
(k) Related Information
Refer to MCAI EASA AD 2011-0203, dated October 13, 2011, and the
service information specified in paragraphs (k)(1) through (k)(5) of
this AD, for related information.
(1) Airbus Service Bulletin A320-34-1452, dated January 29,
2010.
(2) Thales Avionics Service Bulletin C16291A-34-007, Revision
04, dated October 11, 2012.
(3) Thales Avionics Service Bulletin C16291A-34-007, Revision
03, dated April 10, 2012.
(4) Thales Avionics Service Bulletin C16291A-34-007, Revision
02, dated December 16, 2011.
(5) Thales Avionics Service Bulletin C16291A-34-007, Revision
01, dated December 3, 2009.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Service Bulletin A320-34-1452, dated January 29,
2010.
[[Page 19088]]
(ii) Thales Avionics Service Bulletin C16291A-34-007, Revision
04, dated October 11, 2012.
(iii) Thales Avionics Service Bulletin C16291A-34-007, Revision
03, dated April 10, 2012. Pages 1, 8, 10, 11, and 13 of this
document are identified as Revision 03, dated April 10, 2012. Pages
2, 7, and 12 are identified as Revision 01, dated December 3, 2009.
Page 9 is identified as Revision 02, dated December 16, 2011.
(iv) Thales Avionics Service Bulletin C16291A-34-007, Revision
02, dated December 16, 2011. Pages 1, and pages 8 through 10 of this
document are identified as Revision 02, dated December 16, 2011;
pages 2 through 7, and pages 11 through 13 are identified as
Revision 01, dated December 3, 2009.
(v) Thales Avionics Service Bulletin C16291A-34-007, Revision
01, dated December 3, 2009.
(3) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com. For Thales Avionics service
information identified in this AD, contact Thales Avionics, Retrofit
Manager, 105, Avenue du G[eacute]n[eacute]ral Eisenhower, BP 63647,
31036 Toulouse Cedex 1, France; telephone +33 5 61 19 76 95; fax +33
5 61 19 68 20; email retrofit.ata@fr.thalesgroup.com; Internet
https://www.thalesgroup.com/aerospace.
(4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
(5) You may view this 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 8, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-06172 Filed 3-28-13; 8:45 am]
BILLING CODE 4910-13-P
