Airworthiness Directives; Airbus Airplanes, 21722-21726 [2016-08267]
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21722
Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
actions were performed before the effective
date of this AD using Boeing Alert Service
Bulletin B787–81205–SB290015–00, Issue
001, dated September 4, 2014, which is not
incorporated by reference in this AD.
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 airworthiness
directive (AD):
■
2016–07–25 The Boeing Company:
Amendment 39–18470; Docket No.
FAA–2015–2959; Directorate Identifier
2015–NM–008–AD.
(a) Effective Date
This AD is effective May 18, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 787–8 airplanes, certificated in any
category, as identified in Boeing Alert
Service Bulletin B787–81205–SB290015–00,
Issue 002, dated November 25, 2014.
(d) Subject
Air Transport Association (ATA) of
America Code 29, Hydraulic Power.
(e) Unsafe Condition
This AD was prompted by reports
indicating that the ram air turbine (RAT)
assembly may fail to operate if deployed at
low airspeeds. We are issuing this AD to
prevent failure of the RAT assembly to
operate at low air speeds. The volume fuse
on the RAT assembly may be activated inflight before the RAT is deployed. This may
lead to improper pump hydraulic pressure
offloading when the RAT is needed. Failure
of the RAT to operate in an all engine out
event would result in loss of control of the
airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement
Within 36 months after the effective date
of this AD, replace the RAT pump and
control module assembly or the RAT
assembly, including an installation test and
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin B787–81205–
SB290015–00, Issue 002, dated November 25,
2014. Do all applicable corrective actions
before further flight.
(h) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
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(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (j)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (i)(4)(i) and (i)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(j) Related Information
(1) For more information about this AD,
contact Sean J. Schauer, Aerospace Engineer,
Systems and Equipment Branch, ANM 130S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6479; fax: 425–917–6590; email:
sean.schauer@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) 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.
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(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin B787–
81205–SB290015–00, Issue 002, dated
November 25, 2014.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at FAA, 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
26, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–07839 Filed 4–12–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–4810; Directorate
Identifier 2015–NM–090–AD; Amendment
39–18475; AD 2016–07–30]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–200, –200
Freighter, and –300 series airplanes, and
all Airbus Model A340–200, –300, –500,
and –600 series airplanes. This AD was
prompted by a report of blockage of
Angle of Attack (AOA) probes during
climb, leading to activation of the Alpha
Protection (Alpha Prot) while the Mach
number increased. This activation could
cause a continuous nose-down pitch
rate that cannot be stopped with
backward sidestick input, even in the
full backward position. For certain
airplanes, this AD requires replacing
certain AOA sensors (probes) with
SUMMARY:
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certain new AOA sensors. For certain
other airplanes, this AD also requires
inspections and functional heat testing
of certain AOA sensors for
discrepancies, and replacement if
necessary. We are issuing this AD to
prevent erroneous AOA information and
Alpha Prot activation due to blocked
AOA probes, which could result in a
continuous nose-down command and
loss of control of the airplane.
DATES: This AD becomes effective May
18, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 18, 2016.
ADDRESSES: For service information
identified in this final rule, 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. 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–2015–4810.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-4810; 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 street address for the
Docket Operations office (telephone
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.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
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apply to all Airbus Model A330–200,
–200 Freighter, and –300 series
airplanes; and all Airbus Model A340–
200, –300, –500, and –600 series
airplanes. The NPRM published in the
Federal Register on November 12, 2015
(80 FR 69899) (‘‘the NPRM’’).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0134, dated July 8, 2015
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A330–
200, –200 Freighter, and –300 series
airplanes; and all Model A340–200,
–300, –500, and –600 series airplanes.
The MCAI states:
An occurrence was reported where an
Airbus A321 aeroplane encountered a
blockage of two Angle of Attack (AOA)
probes during climb, leading to activation of
the Alpha Protection (Alpha Prot) while the
Mach number increased. The flight crew
managed to regain full control and the flight
landed uneventfully. It was determined that
the affected AOA probes are also fitted on
A330 and A340 aeroplanes.
When Alpha Prot is activated due to
blocked AOA probes, the flight control laws
order a continuous nose down pitch rate that,
in a worst case scenario, cannot be stopped
with backward sidestick inputs, even in the
full backward position. If the Mach number
increases during a nose down order, the AOA
value of the Alpha Prot will continue to
decrease. As a result, the flight control laws
will continue to order a nose down pitch
rate, even if the speed is above minimum
selectable speed, known as VLS.
This condition, if not corrected, could
result in loss of control of the aeroplane.
Investigation results indicated that
aeroplanes equipped with certain UTC
Aerospace (UTAS, formerly known as
Goodrich) AOA sensors, or equipped with
certain SEXTANT/THOMSON AOA sensors,
appear to have a greater susceptibility to
adverse environmental conditions than
aeroplanes equipped with the latest Thales
AOA sensor, Part Number (P/N) C16291AB,
which was designed to improve AOA
indication behaviour in heavy rain
conditions.
Having determined that replacement of
these AOA sensors is necessary to achieve
and maintain the required safety level of the
aeroplane, EASA issued [an AD ***], to
require modification of the aeroplanes by
replacement of the affected P/N sensors, and,
after modification, prohibits (re-) installation
of those P/N AOA sensors. That [EASA] AD
also required repetitive detailed visual
inspections (DET) and functional heating
tests of certain Thales AOA sensors and
provided an optional terminating action for
those inspections.
Since EASA AD 2015–0089 was issued,
based on further analysis results, Airbus
issued Operators Information Transmission
(OIT) Ref. 999.0017/15 Revision 1,
instructing operators to speed up the removal
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21723
from service of UTAS P/N 0861ED2 AOA
sensors.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
[AD ***], which is superseded, but reduces
the compliance times for aeroplanes with
UTAS P/N 0861ED2 AOA sensors installed.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
4810.
Actions Since the NPRM Was Issued
Since we issued the NPRM Airbus has
issued the following service
information:
• Service Bulletin A330–34–3215,
Revision 03, dated July 23, 2015.
• Service Bulletin A340–34–4215,
Revision 03, dated July 27, 2015.
• Service Bulletin A340–34–5062,
Revision 02, dated July 24, 2015.
Explanation of Certain Changes to the
NPRM
We have revised paragraph (j) of this
AD to refer to this revised service
information.
We have also added a new paragraph
(l) to this AD, and reidentified
subsequent paragraphs, to give credit for
doing the actions using the following
service information:
• Airbus Service Bulletin A330–34–
3215, Revision 02, dated March 29,
2010.
• Airbus Service Bulletin A340–34–
4215, Revision 02, dated March 29,
2010.
• Airbus Service Bulletin A340–34–
5062, Revision 01, dated March 29,
2010.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response.
Request To Reduce Certain Compliance
Times
Airbus asked that we reduce the
compliance time from 22 months to 12
months for P/N 0861ED removal, and
from 7 months to 3 months for P/N
0861ED2 removal.
We do not agree with the request, as
no supporting data was provided by the
commenter. We contacted Airbus to
determine if there was a justification for
reducing the compliance times specified
in the proposed AD. We noted that
reducing the compliance times would
necessitate (under the provisions of the
Administrative Procedure Act) reissuing
the notice, reopening the period for
public comment, considering additional
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comments subsequently received, and
eventually issuing a final rule. Airbus
stated it concurs with keeping the
compliance times specified in the
proposed AD. We have determined that
further delay of this final rule is not
appropriate. However, if additional data
are presented that would justify a
shorter compliance time, we may
consider further rulemaking on this
issue.
In developing an appropriate
compliance time, we considered the
safety implications, parts availability,
and normal maintenance schedules for
timely accomplishment of replacing the
AOA sensors, as well as the compliance
times required by the EASA AD. In
consideration of these factors, we have
determined that the compliance time, as
proposed, represents an appropriate
time in which the AOA sensors can be
replaced in a timely manner within the
fleet, while still maintaining an
adequate level of safety. Most ADs,
including this one, permit operators to
accomplish the requirements of an AD
at a time earlier than the specified
compliance time; therefore, an operator
may choose to replace the AOA sensors
earlier. We have not changed this final
rule in this regard.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Service Bulletin A330–34–3215,
Revision 03, dated July 23, 2015.
• Service Bulletin A330–34–3228,
dated October 7, 2009.
• Service Bulletin A330–34–3315,
dated March 26, 2015.
• Service Bulletin A340–34–4215,
Revision 03, dated July 27, 2015.
• Service Bulletin A340–34–4234,
dated October 7, 2009.
• Service Bulletin A340–34–4294,
dated March 26, 2015.
• Service Bulletin A340–34–5062,
Revision 02, dated July 24, 2015.
• Service Bulletin A340–34–5070,
dated October 9, 2009.
• Service Bulletin A340–34–5105,
dated March 26, 2015.
The service information describes
procedures for replacing certain pitot
probes with certain new pitot probes.
The service information also describes
procedures for inspections and
functional heat testing of certain pitot
probes, and replacement if necessary.
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.
Costs of Compliance
We estimate that this AD affects 55
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Replacement ...................................
5 work-hours × $85 per hour =
$425.
3 work-hours × $85 per hour =
$255.
Inspection/test .................................
We have received no definitive data
that will enable us to provide a cost
estimate for the on-condition actions
specified in this AD.
jstallworth on DSK7TPTVN1PROD with RULES
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
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Parts cost
Cost per product
$0
$425 ...............................................
$23,375
0
255 per inspection/test cycle .........
14,025
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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Cost on U.S.
operators
Sfmt 4700
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 airworthiness
directive (AD):
■
2016–07–30 Airbus: Amendment 39–18475.
Docket No. FAA–2015–4810; Directorate
Identifier 2015–NM–090–AD.
(a) Effective Date
This AD becomes effective May 18, 2016.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD, all
manufacturer serial numbers.
(1) Airbus Model A330–201, –202, –203,
–223, –223F, –243, –243F, –301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes.
(2) Airbus Model A340–211, –212, –213,
–311, –312, –313, –541, and –642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 34, Navigation.
(e) Reason
This AD was prompted by a report of
blockage of two Angle of Attack (AOA)
probes during climb, leading to activation of
the Alpha Protection (Alpha Prot) while the
Mach number increased. This activation
could cause a continuous nose-down pitch
rate that cannot be stopped with backward
sidestick input, even in the full backward
position. We are issuing this AD to prevent
erroneous AOA information and Alpha Prot
activation due to blocked AOA probes, which
could result in a continuous nose-down
command and consequent loss of control of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement of Certain UTC Aerospace
(UTAS) AOA Sensors
For airplanes on which any UTAS AOA
sensor having part number (P/N) 0861ED or
P/N 0861ED2 is installed: At the applicable
time specified in paragraph (h) of this AD,
replace all Captain and First Officer AOA
sensors (probes) having P/N 0861ED or
0861ED2 with AOA sensors having Thales P/
N C16291AB, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) Airbus Service Bulletin A330–34–3315,
dated March 26, 2015 (for Model A330
airplanes).
(2) Airbus Service Bulletin A340–34–4294,
dated March 26, 2015 (for Model A340–200
and –300 airplanes).
(3) Airbus Service Bulletin A340–34–5105,
dated March 26, 2015 (for Model A340–500
and –600 airplanes).
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(h) Compliance Times for the Requirements
of Paragraph (g) of This AD
Do the actions required by paragraph (g) of
this AD at the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD.
(1) For airplanes with AOA sensors having
P/N 0861ED: Within 22 months after the
effective date of this AD.
(2) For airplanes with AOA sensors having
P/N 0861ED2: Within 7 months after the
effective date of this AD.
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(i) Replacement of Certain SEXTANT/
THOMSON AOA Sensors
For airplanes on which any SEXTANT/
THOMSON AOA sensor having P/N
45150320 is installed: Within 22 months after
the effective date of this AD, replace all
SEXTANT/THOMSON AOA sensors (probes)
having P/N 45150320 with AOA sensors
having Thales P/N C16291AB, in accordance
with the Accomplishment Instructions of the
applicable service information identified in
paragraph (i)(1) or (i)(2) of this AD.
(1) Airbus Service Bulletin A330–34–3228,
dated October 7, 2009 (for Model A330
airplanes).
(2) Airbus Service Bulletin A340–34–4234,
dated October 7, 2009 (for Model A340–200
and –300 airplanes).
(j) Repetitive Inspections/Tests of Certain
Thales AOA Sensors
For airplanes on which one or more Thales
AOA sensor having P/N C16291AA is
installed: Before the accumulation of 17,000
total flight hours on the AOA sensor since
first installation on an airplane, or within 6
months after the effective date of this AD,
whichever occurs later; and thereafter at
intervals not to exceed 3,800 flight hours; do
a detailed inspection of the three AOA
sensors at FINs 3FP1, 3FP2, and 3FP3 for
discrepancies (e.g., the vane of the sensor
does not deice properly), and a functional
heating test of each AOA sensor having P/N
C16291AA, in accordance with the
Accomplishment Instructions of the
applicable service information identified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD.
(1) Airbus Service Bulletin A330–34–3215,
Revision 03, dated July 23, 2015 (for Model
A330 airplanes).
(2) Airbus Service Bulletin A340–34–4215,
Revision 03, dated July 27, 2015 (for Model
A340–200 and –300 airplanes).
(3) Airbus Service Bulletin A340–34–5062,
Revision 02, dated July 24, 2015 (for Model
A340–500 and –600 airplanes).
(k) Corrective Actions
If any discrepancy is found during any
inspection required by paragraph (j) of this
AD, or if any test is failed during the heating
test required by paragraph (j) of this AD:
Before further flight, replace all affected AOA
sensors with sensors identified in paragraph
(k)(1) or (k)(2) of this AD, in accordance with
the Accomplishment Instructions of the
applicable service information identified in
paragraph (j)(1), (j)(2), or (j)(3) of this AD.
(1) Replace with AOA sensors having
Thales P/N C16291AA, on which the
inspection and test required by paragraph (j)
of this AD were passed.
(2) Replace with AOA sensors having
Thales P/N C16291AB.
(l) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using the applicable
service information specified in paragraphs
(l)(1), (l)(2), and (l)(3) of this AD, which are
not incorporated by reference in this AD.
(1) Airbus Service Bulletin A330–34–3215,
Revision 02, dated March 29, 2010.
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(2) Airbus Service Bulletin A340–34–4215,
Revision 02, dated March 29, 2010.
(3) Airbus Service Bulletin A340–34–5062,
Revision 01, dated March 29, 2010.
(m) Airplanes Excluded From Certain
Requirements
(1) The actions specified in paragraphs (g),
(i), (j), and (k) of this AD are not required,
provided that the conditions specified in
paragraphs (m)(1)(i), (m)(1)(ii), and (m)(1)(iii)
of this AD are met.
(i) Airbus Modification 58555 (installation
of Thales P/N C16291AB AOA sensors) has
been embodied in production.
(ii) Airbus Modification 46921 (installation
of UTAS AOA sensors) has not been
embodied in production.
(iii) No AOA sensor having SEXTANT/
THOMSON P/N 45150320 or UTAS P/N
0861ED or P/N 0861ED2 has been installed
on the airplane since date of issuance of the
original airworthiness certificate or date of
issuance of the original export certificate of
airworthiness.
(2) The actions specified in paragraphs (g)
and (i) of this AD are not required, provided
that all conditions specified in paragraphs
(m)(2)(i), (m)(2)(ii), and (m)(2)(iii) of this AD
are met.
(i) Only AOA sensors with part numbers
approved after the effective date of this AD
have been installed.
(ii) The AOA sensor part number is
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA).
(iii) The installation is accomplished in
accordance with airplane modification
instructions approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; the EASA; or
Airbus’s EASA DOA.
(n) Optional Terminating Modification
Replacement of all Thales AOA sensors
having P/N C16291AA with Thales AOA
sensors having P/N C16291AB, in accordance
with the Accomplishment Instructions of the
applicable service information identified in
paragraph (n)(1), (n)(2), or (n)(3) of this AD,
terminates the repetitive inspections and
functional heating tests required by
paragraph (j) of this AD.
(1) Airbus Service Bulletin A330–34–3228,
dated October 7, 2009 (for Model A330
airplanes).
(2) Airbus Service Bulletin A340–34–4234,
dated October 7, 2009 (for Model A340–200
and –300 airplanes).
(3) Airbus Service Bulletin A340–34–5070,
dated October 9, 2009 (for Model A340–500
and –600 airplanes).
(o) Parts Installation Prohibitions
(1) For airplanes on which only Thales P/
N C16291AB AOA sensors are installed as of
the effective date of this AD: No person may
install, on any airplane, a Thales AOA sensor
having P/N C16291AA as of the effective date
of this AD.
(2) For airplanes on which the
modification specified in paragraph (n) of
this AD has been done: No person may
install, on any airplane, a Thales AOA sensor
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having P/N C16291AA after accomplishing
the specified modification.
(3) For airplanes on which Thales P/N
C16291AA or P/N C16291AB AOA sensors
are installed as of the effective date of this
AD: No person may install, on any airplane,
a UTAS AOA sensor having P/N 0861ED or
P/N 0861ED2, or a SEXTANT/THOMSON
AOA sensor having P/N 45150320, as of the
effective date of this AD.
(4) For airplanes on which the replacement
required by paragraph (i) of this AD has been
done: No person may install, on any airplane,
a UTAS AOA sensor having P/N 0861ED or
P/N 0861ED2, or a SEXTANT/THOMSON
AOA sensor having P/N 45150320, after
accomplishing the replacement.
(5) For airplanes on which the replacement
required by paragraph (g) of this AD has been
done: No person may install, on any airplane,
a UTAS AOA sensor having P/N 0861ED or
P/N 0861ED2, or a SEXTANT/THOMSON
AOA sensor having P/N 45150320, after
accomplishing the replacement, except that a
UTAS AOA sensor having P/N 0861ED may
be installed in the standby position of that
airplane.
(p) 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:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; 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 EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
VerDate Sep<11>2014
14:03 Apr 12, 2016
Jkt 238001
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
DEPARTMENT OF TRANSPORTATION
(q) Related Information
14 CFR Part 39
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0134, dated
July 8, 2015, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2015–4810.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
[Docket No. FAA–2015–2464; Directorate
Identifier 2014–NM–195–AD; Amendment
39–18476; AD 2016–07–31]
(r) Material Incorporated by Reference
SUMMARY:
(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 Service Bulletin A330–34–3215,
Revision 03, dated July 23, 2015.
(ii) Airbus Service Bulletin A330–34–3228,
dated October 7, 2009.
(iii) Airbus Service Bulletin A330–34–
3315, dated March 26, 2015.
(iv) Airbus Service Bulletin A340–34–
4215, Revision 03, dated July 27, 2015.
(v) Airbus Service Bulletin A340–34–4234,
dated October 7, 2009.
(vi) Airbus Service Bulletin A340–34–
4294, dated March 26, 2015.
(vii) Airbus Service Bulletin A340–34–
5062, Revision 02, dated July 24, 2015.
(viii) Airbus Service Bulletin A340–34–
5070, dated October 9, 2009.
(ix) Airbus Service Bulletin A340–34–
5105, dated March 26, 2015.
(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://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
26, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–08267 Filed 4–12–16; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00028
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Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–22–
11 for certain The Boeing Company
Model 747–400 and –400D series
airplanes. AD 2013–22–11 required
repetitive inspections to detect cracks in
the floor panel attachment fastener
holes of certain upper deck floor beam
upper chords, repetitive inspections,
corrective actions if necessary, and
replacement of the upper deck floor
beam upper chords. Since we issued AD
2013–22–11, we received a report that
certain fastener holes in the upper deck
floor beam upper chords may not have
been inspected in accordance with AD
2013–22–11. This AD adds additional
repetitive inspections for cracks for
certain airplanes, and corrective actions
if necessary. We are issuing this AD to
detect and correct fatigue cracking in
certain upper chords of the upper deck
floor beam. Such cracks could become
large and cause the floor beams to
become severed and result in rapid
decompression or reduced
controllability of the airplane.
DATES: This AD is effective May 18,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 18, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P.O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; Internet
https://www.myboeingfleet.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–
2464.
E:\FR\FM\13APR1.SGM
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Agencies
[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)]
[Rules and Regulations]
[Pages 21722-21726]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08267]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-4810; Directorate Identifier 2015-NM-090-AD;
Amendment 39-18475; AD 2016-07-30]
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 A330-200, -200 Freighter, and -300 series airplanes, and
all Airbus Model A340-200, -300, -500, and -600 series airplanes. This
AD was prompted by a report of blockage of Angle of Attack (AOA) probes
during climb, leading to activation of the Alpha Protection (Alpha
Prot) while the Mach number increased. This activation could cause a
continuous nose-down pitch rate that cannot be stopped with backward
sidestick input, even in the full backward position. For certain
airplanes, this AD requires replacing certain AOA sensors (probes) with
[[Page 21723]]
certain new AOA sensors. For certain other airplanes, this AD also
requires inspections and functional heat testing of certain AOA sensors
for discrepancies, and replacement if necessary. We are issuing this AD
to prevent erroneous AOA information and Alpha Prot activation due to
blocked AOA probes, which could result in a continuous nose-down
command and loss of control of the airplane.
DATES: This AD becomes effective May 18, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 18, 2016.
ADDRESSES: For service information identified in this final rule,
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. 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-
4810.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-4810; 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 street address for the Docket Operations office (telephone 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.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A330-200,
-200 Freighter, and -300 series airplanes; and all Airbus Model A340-
200, -300, -500, and -600 series airplanes. The NPRM published in the
Federal Register on November 12, 2015 (80 FR 69899) (``the NPRM'').
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0134, dated July 8, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200, -200 Freighter, and -300 series airplanes; and all Model
A340-200, -300, -500, and -600 series airplanes. The MCAI states:
An occurrence was reported where an Airbus A321 aeroplane
encountered a blockage of two Angle of Attack (AOA) probes during
climb, leading to activation of the Alpha Protection (Alpha Prot)
while the Mach number increased. The flight crew managed to regain
full control and the flight landed uneventfully. It was determined
that the affected AOA probes are also fitted on A330 and A340
aeroplanes.
When Alpha Prot is activated due to blocked AOA probes, the
flight control laws order a continuous nose down pitch rate that, in
a worst case scenario, cannot be stopped with backward sidestick
inputs, even in the full backward position. If the Mach number
increases during a nose down order, the AOA value of the Alpha Prot
will continue to decrease. As a result, the flight control laws will
continue to order a nose down pitch rate, even if the speed is above
minimum selectable speed, known as VLS.
This condition, if not corrected, could result in loss of
control of the aeroplane.
Investigation results indicated that aeroplanes equipped with
certain UTC Aerospace (UTAS, formerly known as Goodrich) AOA
sensors, or equipped with certain SEXTANT/THOMSON AOA sensors,
appear to have a greater susceptibility to adverse environmental
conditions than aeroplanes equipped with the latest Thales AOA
sensor, Part Number (P/N) C16291AB, which was designed to improve
AOA indication behaviour in heavy rain conditions.
Having determined that replacement of these AOA sensors is
necessary to achieve and maintain the required safety level of the
aeroplane, EASA issued [an AD ***], to require modification of the
aeroplanes by replacement of the affected P/N sensors, and, after
modification, prohibits (re-) installation of those P/N AOA sensors.
That [EASA] AD also required repetitive detailed visual inspections
(DET) and functional heating tests of certain Thales AOA sensors and
provided an optional terminating action for those inspections.
Since EASA AD 2015-0089 was issued, based on further analysis
results, Airbus issued Operators Information Transmission (OIT) Ref.
999.0017/15 Revision 1, instructing operators to speed up the
removal from service of UTAS P/N 0861ED2 AOA sensors.
For the reasons described above, this [EASA] AD retains the
requirements of EASA [AD ***], which is superseded, but reduces the
compliance times for aeroplanes with UTAS P/N 0861ED2 AOA sensors
installed.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4810.
Actions Since the NPRM Was Issued
Since we issued the NPRM Airbus has issued the following service
information:
Service Bulletin A330-34-3215, Revision 03, dated July 23,
2015.
Service Bulletin A340-34-4215, Revision 03, dated July 27,
2015.
Service Bulletin A340-34-5062, Revision 02, dated July 24,
2015.
Explanation of Certain Changes to the NPRM
We have revised paragraph (j) of this AD to refer to this revised
service information.
We have also added a new paragraph (l) to this AD, and reidentified
subsequent paragraphs, to give credit for doing the actions using the
following service information:
Airbus Service Bulletin A330-34-3215, Revision 02, dated
March 29, 2010.
Airbus Service Bulletin A340-34-4215, Revision 02, dated
March 29, 2010.
Airbus Service Bulletin A340-34-5062, Revision 01, dated
March 29, 2010.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM and
the FAA's response.
Request To Reduce Certain Compliance Times
Airbus asked that we reduce the compliance time from 22 months to
12 months for P/N 0861ED removal, and from 7 months to 3 months for P/N
0861ED2 removal.
We do not agree with the request, as no supporting data was
provided by the commenter. We contacted Airbus to determine if there
was a justification for reducing the compliance times specified in the
proposed AD. We noted that reducing the compliance times would
necessitate (under the provisions of the Administrative Procedure Act)
reissuing the notice, reopening the period for public comment,
considering additional
[[Page 21724]]
comments subsequently received, and eventually issuing a final rule.
Airbus stated it concurs with keeping the compliance times specified in
the proposed AD. We have determined that further delay of this final
rule is not appropriate. However, if additional data are presented that
would justify a shorter compliance time, we may consider further
rulemaking on this issue.
In developing an appropriate compliance time, we considered the
safety implications, parts availability, and normal maintenance
schedules for timely accomplishment of replacing the AOA sensors, as
well as the compliance times required by the EASA AD. In consideration
of these factors, we have determined that the compliance time, as
proposed, represents an appropriate time in which the AOA sensors can
be replaced in a timely manner within the fleet, while still
maintaining an adequate level of safety. Most ADs, including this one,
permit operators to accomplish the requirements of an AD at a time
earlier than the specified compliance time; therefore, an operator may
choose to replace the AOA sensors earlier. We have not changed this
final rule in this regard.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Service Bulletin A330-34-3215, Revision 03, dated July 23,
2015.
Service Bulletin A330-34-3228, dated October 7, 2009.
Service Bulletin A330-34-3315, dated March 26, 2015.
Service Bulletin A340-34-4215, Revision 03, dated July 27,
2015.
Service Bulletin A340-34-4234, dated October 7, 2009.
Service Bulletin A340-34-4294, dated March 26, 2015.
Service Bulletin A340-34-5062, Revision 02, dated July 24,
2015.
Service Bulletin A340-34-5070, dated October 9, 2009.
Service Bulletin A340-34-5105, dated March 26, 2015.
The service information describes procedures for replacing certain
pitot probes with certain new pitot probes. The service information
also describes procedures for inspections and functional heat testing
of certain pitot probes, and replacement if necessary. 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.
Costs of Compliance
We estimate that this AD affects 55 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Replacement....................... 5 work-hours x $85 $0 $425................. $23,375
per hour = $425.
Inspection/test................... 3 work-hours x $85 0 255 per inspection/ 14,025
per hour = $255. test cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will enable us to provide
a cost estimate for the on-condition actions specified in this AD.
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.
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):
2016-07-30 Airbus: Amendment 39-18475. Docket No. FAA-2015-4810;
Directorate Identifier 2015-NM-090-AD.
(a) Effective Date
This AD becomes effective May 18, 2016.
[[Page 21725]]
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of this AD, all
manufacturer serial numbers.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 34, Navigation.
(e) Reason
This AD was prompted by a report of blockage of two Angle of
Attack (AOA) probes during climb, leading to activation of the Alpha
Protection (Alpha Prot) while the Mach number increased. This
activation could cause a continuous nose-down pitch rate that cannot
be stopped with backward sidestick input, even in the full backward
position. We are issuing this AD to prevent erroneous AOA
information and Alpha Prot activation due to blocked AOA probes,
which could result in a continuous nose-down command and consequent
loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement of Certain UTC Aerospace (UTAS) AOA Sensors
For airplanes on which any UTAS AOA sensor having part number
(P/N) 0861ED or P/N 0861ED2 is installed: At the applicable time
specified in paragraph (h) of this AD, replace all Captain and First
Officer AOA sensors (probes) having P/N 0861ED or 0861ED2 with AOA
sensors having Thales P/N C16291AB, in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) Airbus Service Bulletin A330-34-3315, dated March 26, 2015
(for Model A330 airplanes).
(2) Airbus Service Bulletin A340-34-4294, dated March 26, 2015
(for Model A340-200 and -300 airplanes).
(3) Airbus Service Bulletin A340-34-5105, dated March 26, 2015
(for Model A340-500 and -600 airplanes).
(h) Compliance Times for the Requirements of Paragraph (g) of This AD
Do the actions required by paragraph (g) of this AD at the
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) For airplanes with AOA sensors having P/N 0861ED: Within 22
months after the effective date of this AD.
(2) For airplanes with AOA sensors having P/N 0861ED2: Within 7
months after the effective date of this AD.
(i) Replacement of Certain SEXTANT/THOMSON AOA Sensors
For airplanes on which any SEXTANT/THOMSON AOA sensor having P/N
45150320 is installed: Within 22 months after the effective date of
this AD, replace all SEXTANT/THOMSON AOA sensors (probes) having P/N
45150320 with AOA sensors having Thales P/N C16291AB, in accordance
with the Accomplishment Instructions of the applicable service
information identified in paragraph (i)(1) or (i)(2) of this AD.
(1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009
(for Model A330 airplanes).
(2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009
(for Model A340-200 and -300 airplanes).
(j) Repetitive Inspections/Tests of Certain Thales AOA Sensors
For airplanes on which one or more Thales AOA sensor having P/N
C16291AA is installed: Before the accumulation of 17,000 total
flight hours on the AOA sensor since first installation on an
airplane, or within 6 months after the effective date of this AD,
whichever occurs later; and thereafter at intervals not to exceed
3,800 flight hours; do a detailed inspection of the three AOA
sensors at FINs 3FP1, 3FP2, and 3FP3 for discrepancies (e.g., the
vane of the sensor does not deice properly), and a functional
heating test of each AOA sensor having P/N C16291AA, in accordance
with the Accomplishment Instructions of the applicable service
information identified in paragraph (j)(1), (j)(2), or (j)(3) of
this AD.
(1) Airbus Service Bulletin A330-34-3215, Revision 03, dated
July 23, 2015 (for Model A330 airplanes).
(2) Airbus Service Bulletin A340-34-4215, Revision 03, dated
July 27, 2015 (for Model A340-200 and -300 airplanes).
(3) Airbus Service Bulletin A340-34-5062, Revision 02, dated
July 24, 2015 (for Model A340-500 and -600 airplanes).
(k) Corrective Actions
If any discrepancy is found during any inspection required by
paragraph (j) of this AD, or if any test is failed during the
heating test required by paragraph (j) of this AD: Before further
flight, replace all affected AOA sensors with sensors identified in
paragraph (k)(1) or (k)(2) of this AD, in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD.
(1) Replace with AOA sensors having Thales P/N C16291AA, on
which the inspection and test required by paragraph (j) of this AD
were passed.
(2) Replace with AOA sensors having Thales P/N C16291AB.
(l) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the applicable service information
specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, which
are not incorporated by reference in this AD.
(1) Airbus Service Bulletin A330-34-3215, Revision 02, dated
March 29, 2010.
(2) Airbus Service Bulletin A340-34-4215, Revision 02, dated
March 29, 2010.
(3) Airbus Service Bulletin A340-34-5062, Revision 01, dated
March 29, 2010.
(m) Airplanes Excluded From Certain Requirements
(1) The actions specified in paragraphs (g), (i), (j), and (k)
of this AD are not required, provided that the conditions specified
in paragraphs (m)(1)(i), (m)(1)(ii), and (m)(1)(iii) of this AD are
met.
(i) Airbus Modification 58555 (installation of Thales P/N
C16291AB AOA sensors) has been embodied in production.
(ii) Airbus Modification 46921 (installation of UTAS AOA
sensors) has not been embodied in production.
(iii) No AOA sensor having SEXTANT/THOMSON P/N 45150320 or UTAS
P/N 0861ED or P/N 0861ED2 has been installed on the airplane since
date of issuance of the original airworthiness certificate or date
of issuance of the original export certificate of airworthiness.
(2) The actions specified in paragraphs (g) and (i) of this AD
are not required, provided that all conditions specified in
paragraphs (m)(2)(i), (m)(2)(ii), and (m)(2)(iii) of this AD are
met.
(i) Only AOA sensors with part numbers approved after the
effective date of this AD have been installed.
(ii) The AOA sensor part number is approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
the European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA).
(iii) The installation is accomplished in accordance with
airplane modification instructions approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
the EASA; or Airbus's EASA DOA.
(n) Optional Terminating Modification
Replacement of all Thales AOA sensors having P/N C16291AA with
Thales AOA sensors having P/N C16291AB, in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (n)(1), (n)(2), or (n)(3) of this AD,
terminates the repetitive inspections and functional heating tests
required by paragraph (j) of this AD.
(1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009
(for Model A330 airplanes).
(2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009
(for Model A340-200 and -300 airplanes).
(3) Airbus Service Bulletin A340-34-5070, dated October 9, 2009
(for Model A340-500 and -600 airplanes).
(o) Parts Installation Prohibitions
(1) For airplanes on which only Thales P/N C16291AB AOA sensors
are installed as of the effective date of this AD: No person may
install, on any airplane, a Thales AOA sensor having P/N C16291AA as
of the effective date of this AD.
(2) For airplanes on which the modification specified in
paragraph (n) of this AD has been done: No person may install, on
any airplane, a Thales AOA sensor
[[Page 21726]]
having P/N C16291AA after accomplishing the specified modification.
(3) For airplanes on which Thales P/N C16291AA or P/N C16291AB
AOA sensors are installed as of the effective date of this AD: No
person may install, on any airplane, a UTAS AOA sensor having P/N
0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N
45150320, as of the effective date of this AD.
(4) For airplanes on which the replacement required by paragraph
(i) of this AD has been done: No person may install, on any
airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a
SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing
the replacement.
(5) For airplanes on which the replacement required by paragraph
(g) of this AD has been done: No person may install, on any
airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a
SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing
the replacement, except that a UTAS AOA sensor having P/N 0861ED may
be installed in the standby position of that airplane.
(p) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; 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 EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0134, dated July 8, 2015,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2015-4810.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) 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 Service Bulletin A330-34-3215, Revision 03, dated
July 23, 2015.
(ii) Airbus Service Bulletin A330-34-3228, dated October 7,
2009.
(iii) Airbus Service Bulletin A330-34-3315, dated March 26,
2015.
(iv) Airbus Service Bulletin A340-34-4215, Revision 03, dated
July 27, 2015.
(v) Airbus Service Bulletin A340-34-4234, dated October 7, 2009.
(vi) Airbus Service Bulletin A340-34-4294, dated March 26, 2015.
(vii) Airbus Service Bulletin A340-34-5062, Revision 02, dated
July 24, 2015.
(viii) Airbus Service Bulletin A340-34-5070, dated October 9,
2009.
(ix) Airbus Service Bulletin A340-34-5105, dated March 26, 2015.
(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://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 26, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-08267 Filed 4-12-16; 8:45 am]
BILLING CODE 4910-13-P