Airworthiness Directives; Airbus Airplanes, 68429-68432 [2015-27688]
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Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
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(b) Additional Information. You may
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Credit Drive, McLean, Virginia 22102–
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NONDISCRIMINATION ON THE BASIS
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FARM CREDIT ADMINISTRATION
4. The authority citation for part 606
continues to read as follows:
■
Authority: 29 U.S.C. 794.
§ 606.670
[Amended]
5. Amend § 606.670 by removing the
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■
Dated: October 30, 2015.
Dale L. Aultman,
Secretary, Farm Credit Administration Board.
[FR Doc. 2015–28244 Filed 11–4–15; 8:45 am]
BILLING CODE 6705–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–4211; Directorate
Identifier 2015–NM–150–AD; Amendment
39–18311; AD 2015–22–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
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 spoiler and
elevator computer (SEC) latent failures;
an undetected loss of a SEC in flight
will result in loss in redundancy for
elevator control. This AD requires
revising the After Start Normal
Procedures section of the airplane flight
manual (AFM) to provide procedures
that will address this loss of
SUMMARY:
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68429
redundancy. We are issuing this AD to
ensure that the flightcrew has
procedures to address loss of
redundancy of SEC 1 and SEC 2. A SEC
failure, in conjunction with a loss of
trimmable horizontal stabilizer (THS)
electrical control due to jamming or
rupture, could result in failure of an
elevator and aileron computer, and
consequent loss of elevator control and
reduced control of the airplane.
DATES: This AD becomes effective
November 20, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 20, 2015.
We must receive comments on this
AD by December 21, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 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. You may view this
referenced 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. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2015–4211.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
4211; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
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Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
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.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0191, dated September
22, 2015 (correction September 25,
2015) (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A318, A319, A320, and A321
series airplanes. The MCAI states:
jstallworth on DSK7TPTVN1PROD with RULES
With the introduction of new Spoiler and
Elevator Computer (SEC) hardware C Part
Number (P/N) B372CAM0100 with software
standards 122, 124 and 125 (identified by P/
N B372CAM0101, P/N B372CAM0102 and P/
N B372CAM0103, respectively), some
airlines have reported receiving maintenance
messages, e.g. ‘‘SEC OR WIRING FROM L or
R ELEV POS MON XDCR’’ and/or ‘‘SEC OR
WIRING FROM G or Y ELEV POS XDCR’’,
which are associated with servo control or
elevator transducer monitoring. Such
messages are triggered by a short data
inconsistency due to power transients, when
the engines are started.
This condition, if not corrected, could lead
to an undetected loss of redundancy during
flight if an affected SEC cannot control the
related elevator servo control(s), possibly
resulting in reduced control of the aeroplane.
It was determined that, to recover full
redundancy, a reset of SEC 1 and SEC 2 must
be done after engines start and Airbus have
developed an Airplane Flight Manual (AFM)
Temporary Revision (TR), published as TR
572 Issue 1.1, to provide the necessary flight
crew procedure.
describes the reset of SEC 1 and SEC 2
that must be done after engines start.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this AD.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because a SEC failure in
conjunction with a loss of THS
electrical control due to jamming or
rupture, could result in failure of an
elevator and aileron computer, and
consequent loss of elevator control and
reduced control of the airplane.
Therefore, we determined that notice
and opportunity for public comment
before issuing this AD are impracticable
and that good cause exists for making
this amendment effective in fewer than
30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Required actions include revising the
After Start Normal Procedures section of Send your comments to an address
the AFM to provide procedures that will listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2015–4211;
address this loss of redundancy. You
Directorate Identifier 2015–NM–150–
may examine the MCAI on the Internet
AD’’ at the beginning of your comments.
at https://www.regulations.gov by
We specifically invite comments on the
searching for and locating Docket No.
overall regulatory, economic,
FAA–2015–4211.
environmental, and energy aspects of
Related Service Information Under 1
this AD. We will consider all comments
CFR Part 51
received by the closing date and may
Airbus has issued A318/A319/A320/
amend this AD based on those
A321 Temporary Revision TR572, Issue comments.
We will post all comments we
1.0, dated August 13, 2015, to the
Airbus A318/A319/A320/A321 Airplane receive, without change, to https://
www.regulations.gov, including any
Flight Manual. The service information
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personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 959
airplanes of U.S. registry.
We also estimate that it will take
about 1 work-hour 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 on U.S.
operators to be $81,515, or $85 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 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.
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Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
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
(g) Airplane Flight Manual Revision
For airplanes equipped with SEC hardware
C part number (P/N) B372CAM0100 with
software standard 122 (P/N B372CAM0101),
124 (P/N B372CAM0102), or 125 (P/N
B372CAM0103), on SEC position 1 or 2, or
both: Within 30 days after the effective date
of this AD, revise the After Start Normal
Procedures section of the AFM to include the
statement specified in figure 1 to paragraph
(g) of this AD. This may be done by inserting
a copy of this AD, or Airbus A318/A319/
A320/A321 Temporary Revision TR572,
Issue 1.0, dated August 13, 2015, to the
Airbus A318/A319/A320/A321 Airplane
Flight Manual, into the applicable AFM.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2015–22–06 Airbus: Amendment 39–18311.
Docket No. FAA–2015–4211; Directorate
Identifier 2015–NM–150–AD.
(a) Effective Date
This AD becomes effective November 20,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) through (c)(4) of this AD, all
manufacturer serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
jstallworth on DSK7TPTVN1PROD with RULES
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
This AD was prompted by reports of
spoiler and elevator computer (SEC) latent
failures; an undetected loss of a SEC in flight
will result in loss in redundancy for elevator
control. This AD requires revising the After
Start Normal Procedures section of the
airplane fight manual (AFM) to provide
procedures that will address this loss of
redundancy. We are issuing this AD to
ensure that the flightcrew has procedures to
address loss of redundancy of SEC 1 and SEC
2. A SEC failure, in conjunction with a loss
of trimmable horizontal stabilizer (THS)
electrical control due to jamming or rupture,
could result in failure of an elevator and
aileron computer, and consequent loss of
elevator control and reduced control of the
airplane.
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FIGURE 1 TO PARAGRAPH (g) OF THIS
AD—AFM TEMPORARY REVISION
AFTER START NORMAL PROCEDURE
After both engines start:
Turn OFF then ON SEC 1 and SEC 2 one
after another.
Note 1 to paragraph (g) of this AD: When
a statement identical to that in figure 1 to
paragraph (g) of this AD has been included
in the After Start Normal Procedures section
of the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD or Airbus
A318/A319/A320/A321 Temporary Revision
TR572, Issue 1.0, dated August 13, 2015, may
be removed from the AFM.
Note 2 to paragraph (g) of this AD: Airbus
Operations Engineering Bulletin OEB–50
provides additional information on the
subject addressed by this AD.
(h) Optional Modification
Modification of an airplane by installation
of SEC hardware C with software standard
126 (P/N B372CAM0104) (Airbus
Modification 161208) allows removal of the
AFM revision required by paragraph (g) of
this AD for that airplane.
(i) Parts Installation Limitation
For all airplanes: As of the effective date
of this AD, do not install SEC hardware C P/
N B372CAM0100 with software standard 122
(P/N B372CAM0101), 124 (P/N
B372CAM0102), or 125 (P/N B372CAM0103),
on SEC position 1 or 2, or both, on any
airplane, unless the AFM of the airplane is
revised concurrently with that installation, as
required by paragraph (g) of this AD.
(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
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68431
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, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-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) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(k) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0191, dated
September 22, 2015 (corrected September 25,
2015), for related information. You may
examine the MCAI on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2015–4211.
(m) 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 this AD specifies otherwise.
(i) Airbus A318/A319/A320/A321
Temporary Revision TR572, Issue 1.0, dated
August 13, 2015, to the Airbus A318/A319/
A320/A321 Airplane Flight Manual.
(ii) Reserved.
(3) 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; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may view this 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://
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Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on October
22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–27688 Filed 11–4–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
[Docket No. FAA–2015–1425; Directorate
Identifier 2014–NM–185–AD; Amendment
39–18312; AD 2015–22–07]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model
188 series airplanes. This AD was
prompted by an evaluation by the
design approval holder (DAH)
indicating that the circumferential
fuselage splice at fuselage-station (FS)
695 is subject to widespread fatigue
damage (WFD). This AD requires an
inspection for corrosion and previous
repairs, severed stringers, cracking, and
loose or distressed fasteners of the
forward and aft ends of the stringer
splices of certain stringers, inspection
for cracking and modification of certain
fastener holes common to the stringer
and splice member at the forward and
aft ends of the splice, and related
investigative and corrective actions if
necessary. We are issuing this AD to
prevent loss of residual strength of the
circumferential fuselage splice at FS
695, which could lead to rapid
decompression of the cabin and
potential loss of the airplane.
DATES: This AD is effective December
10, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 10, 2015.
ADDRESSES: For service information
identified in this AD, contact Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company, Airworthiness
Office, Dept. 6A0M, Zone 0252, Column
P–58, 86 S. Cobb Drive, Marietta, GA
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SUMMARY:
VerDate Sep<11>2014
14:34 Nov 04, 2015
30063; phone: 770–494–5444; fax: 770–
494–5445; email: ams.portal@lmco.com;
Internet https://
www.lockheedmartin.com/ams/tools/
TechPubs.html. You may view this
referenced 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. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2015–1425.
Jkt 238001
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
1425; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Carl
Gray, Aerospace Engineer, Airframe
Branch, ACE–117A, FAA, Atlanta
Aircraft Certification Office (ACO), 1701
Columbia Avenue, College Park, GA
30337; phone: 404–474–5554; fax: 404–
474–5605; email: carl.w.gray@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Lockheed Martin
Corporation/Lockheed Martin
Aeronautics Company Model 188 series
airplanes. The NPRM published in the
Federal Register on May 28, 2015 (80
FR 30391). The NPRM was prompted by
an evaluation by the DAH indicating
that a certain circumferential fuselage
splice is subject to WFD. The NPRM
proposed to require an inspection for
corrosion and previous repairs, severed
stringers, cracking, and loose or
distressed fasteners of the forward and
aft ends of the stringer splices of certain
stringers, inspection for cracking and
modification of certain fastener holes
common to the stringer and splice
member at the forward and aft ends of
the splice, and related investigative and
corrective actions if necessary. We are
issuing this AD to prevent loss of
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residual strength of a certain
circumferential fuselage splice, which
could lead to rapid decompression of
the cabin and potential loss of the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (80
FR 30391, May 28, 2015) 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 this 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 (80 FR
30391, May 28, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 30391,
May 28, 2015).
Related Service Information Under 1
CFR Part 51
We reviewed Lockheed Martin Electra
Service Bulletin 88/SB–722, dated April
30, 2014. This service bulletin describes
procedures for doing the following
actions:
• A general visual inspection (GVI)
for corrosion and previous repairs,
severed stringers, cracking, and loose or
distressed fasteners of the forward and
aft ends of the stringer splices of
stringers 1–7 and 66–72, and corrective
actions if necessary.
• At stringers 1–7 and 66–72,
removing the four rivets common to the
stringer and splice member at the
forward and aft ends of the splice and
doing a bolt hole eddy current (BHEC)
inspection or an equivalent inspection
procedure for cracking in each of the
fastener holes, and corrective actions if
necessary.
• Corrective actions for cracked holes
include reaming to the maximum
permissible hole diameter of the next
larger size rivet. If a crack indication
remains after reaming, this service
information specifies repairing the
cracked stringer.
• If a severed stringer is found during
the GVI, doing related investigative
actions of an eddy current surface scan
inspection for cracking of the fuselage
skin at the skin-to-stringer attachments
immediately forward and aft of the
stringer break and confirming skin
cracks with a dye penetrant inspection.
Corrective actions include repairing the
severed stringer or skin cracks.
E:\FR\FM\05NOR1.SGM
05NOR1
]]>Agencies
[Federal Register Volume 80, Number 214 (Thursday, November 5, 2015)]
[Rules and Regulations]
[Pages 68429-68432]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27688]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-4211; Directorate Identifier 2015-NM-150-AD;
Amendment 39-18311; AD 2015-22-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
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 spoiler and elevator computer (SEC) latent
failures; an undetected loss of a SEC in flight will result in loss in
redundancy for elevator control. This AD requires revising the After
Start Normal Procedures section of the airplane flight manual (AFM) to
provide procedures that will address this loss of redundancy. We are
issuing this AD to ensure that the flightcrew has procedures to address
loss of redundancy of SEC 1 and SEC 2. A SEC failure, in conjunction
with a loss of trimmable horizontal stabilizer (THS) electrical control
due to jamming or rupture, could result in failure of an elevator and
aileron computer, and consequent loss of elevator control and reduced
control of the airplane.
DATES: This AD becomes effective November 20, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 20,
2015.
We must receive comments on this AD by December 21, 2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus,
Airworthiness Office--EIAS, 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. You may view this referenced 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4211.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4211; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
[[Page 68430]]
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.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0191, dated September 22, 2015 (correction
September 25, 2015) (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Airbus Model A318, A319, A320, and A321 series
airplanes. The MCAI states:
With the introduction of new Spoiler and Elevator Computer (SEC)
hardware C Part Number (P/N) B372CAM0100 with software standards
122, 124 and 125 (identified by P/N B372CAM0101, P/N B372CAM0102 and
P/N B372CAM0103, respectively), some airlines have reported
receiving maintenance messages, e.g. ``SEC OR WIRING FROM L or R
ELEV POS MON XDCR'' and/or ``SEC OR WIRING FROM G or Y ELEV POS
XDCR'', which are associated with servo control or elevator
transducer monitoring. Such messages are triggered by a short data
inconsistency due to power transients, when the engines are started.
This condition, if not corrected, could lead to an undetected
loss of redundancy during flight if an affected SEC cannot control
the related elevator servo control(s), possibly resulting in reduced
control of the aeroplane.
It was determined that, to recover full redundancy, a reset of
SEC 1 and SEC 2 must be done after engines start and Airbus have
developed an Airplane Flight Manual (AFM) Temporary Revision (TR),
published as TR 572 Issue 1.1, to provide the necessary flight crew
procedure.
Required actions include revising the After Start Normal Procedures
section of the AFM to provide procedures that will address this loss of
redundancy. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4211.
Related Service Information Under 1 CFR Part 51
Airbus has issued A318/A319/A320/A321 Temporary Revision TR572,
Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321
Airplane Flight Manual. The service information describes the reset of
SEC 1 and SEC 2 that must be done after engines start. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section of this AD.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because a SEC
failure in conjunction with a loss of THS electrical control due to
jamming or rupture, could result in failure of an elevator and aileron
computer, and consequent loss of elevator control and reduced control
of the airplane. Therefore, we determined that notice and opportunity
for public comment before issuing this AD are impracticable and that
good cause exists for making this amendment effective in fewer than 30
days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2015-4211; Directorate
Identifier 2015-NM-150-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD based on
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 959 airplanes of U.S. registry.
We also estimate that it will take about 1 work-hour 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 on U.S. operators to be $81,515, or $85 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 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.
[[Page 68431]]
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
airworthiness directive (AD):
2015-22-06 Airbus: Amendment 39-18311. Docket No. FAA-2015-4211;
Directorate Identifier 2015-NM-150-AD.
(a) Effective Date
This AD becomes effective November 20, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) through (c)(4) of this AD,
all manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by reports of spoiler and elevator computer
(SEC) latent failures; an undetected loss of a SEC in flight will
result in loss in redundancy for elevator control. This AD requires
revising the After Start Normal Procedures section of the airplane
fight manual (AFM) to provide procedures that will address this loss
of redundancy. We are issuing this AD to ensure that the flightcrew
has procedures to address loss of redundancy of SEC 1 and SEC 2. A
SEC failure, in conjunction with a loss of trimmable horizontal
stabilizer (THS) electrical control due to jamming or rupture, could
result in failure of an elevator and aileron computer, and
consequent loss of elevator control and reduced control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Airplane Flight Manual Revision
For airplanes equipped with SEC hardware C part number (P/N)
B372CAM0100 with software standard 122 (P/N B372CAM0101), 124 (P/N
B372CAM0102), or 125 (P/N B372CAM0103), on SEC position 1 or 2, or
both: Within 30 days after the effective date of this AD, revise the
After Start Normal Procedures section of the AFM to include the
statement specified in figure 1 to paragraph (g) of this AD. This
may be done by inserting a copy of this AD, or Airbus A318/A319/
A320/A321 Temporary Revision TR572, Issue 1.0, dated August 13,
2015, to the Airbus A318/A319/A320/A321 Airplane Flight Manual, into
the applicable AFM.
Figure 1 to Paragraph (g) of This AD--AFM Temporary Revision
------------------------------------------------------------------------
-------------------------------------------------------------------------
AFTER START NORMAL PROCEDURE
After both engines start:
Turn OFF then ON SEC 1 and SEC 2 one after another.
------------------------------------------------------------------------
Note 1 to paragraph (g) of this AD: When a statement identical
to that in figure 1 to paragraph (g) of this AD has been included in
the After Start Normal Procedures section of the general revisions
of the AFM, the general revisions may be inserted into the AFM, and
the copy of this AD or Airbus A318/A319/A320/A321 Temporary Revision
TR572, Issue 1.0, dated August 13, 2015, may be removed from the
AFM.
Note 2 to paragraph (g) of this AD: Airbus Operations
Engineering Bulletin OEB-50 provides additional information on the
subject addressed by this AD.
(h) Optional Modification
Modification of an airplane by installation of SEC hardware C
with software standard 126 (P/N B372CAM0104) (Airbus Modification
161208) allows removal of the AFM revision required by paragraph (g)
of this AD for that airplane.
(i) Parts Installation Limitation
For all airplanes: As of the effective date of this AD, do not
install SEC hardware C P/N B372CAM0100 with software standard 122
(P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103),
on SEC position 1 or 2, or both, on any airplane, unless the AFM of
the airplane is revised concurrently with that installation, as
required by paragraph (g) of this AD.
(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, WA 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) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(k) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(l) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2015-0191, dated September 22, 2015
(corrected September 25, 2015), for related information. You may
examine the MCAI on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2015-4211.
(m) 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 this AD specifies otherwise.
(i) Airbus A318/A319/A320/A321 Temporary Revision TR572, Issue
1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321
Airplane Flight Manual.
(ii) Reserved.
(3) 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; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may view this 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://
[[Page 68432]]
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on October 22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-27688 Filed 11-4-15; 8:45 am]
BILLING CODE 4910-13-P
