Airworthiness Directives; Airbus Airplanes, 14404-14408 [2016-05830]
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Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules
(c) Applicability
This AD applies to The Boeing Company
Model 777–200 and -300 series airplanes
equipped with Rolls-Royce Model Trent 800
engines.
(d) Subject
Air Transport Association (ATA) of
America Code 78, Engine Exhaust.
(e) Unsafe Condition
This AD was prompted by reports of
damage to the upper bifurcation forward fire
seal and seal deflector, and localized damage
to the insulation blanket installed just aft of
the fire seal. We are issuing this AD to
prevent a breach in the engine firewall due
to a failed upper bifurcation forward fire seal.
A breach could delay or prevent the fire
detection and suppression system from
functioning properly, and could result in an
increased risk of a fire, prolonged burning,
and breach of the fire zone; and could allow
fire to reach unprotected areas of the engine,
the strut, and wing after engine shutdown.
Also, fan air bypassing the seal could cause
localized damage to the thrust reverser (T/R)
insulation blanket installed just aft of the fire
seal, which could allow limited thermal
degradation of the thrust reverser inner wall.
This could aggravate existing damage and
cause the thrust reverser’s inner wall to fail.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Installation of Serviceable T/R Halves on
Each Engine
Within 60 months after the effective date
of this AD: Install serviceable left and right
T/R halves on the left and right engines, in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–78–0101, Revision 1,
dated October 30, 2015. A serviceable T/R
half is defined in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–78–0101, Revision 1,
dated October 30, 2015.
(h) 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 (i) 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
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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 (h)(4)(i) and (h)(4)(ii) 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.
(i) Related Information
(1) For more information about this AD,
contact Kevin Nguyen, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6501; fax: 425–917–6590;
email: kevin.nguyen@faa.gov.
(2) For 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. 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.
Issued in Renton, Washington, on March 9,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–05831 Filed 3–16–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–4226; Directorate
Identifier 2015–NM–095–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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We propose to supersede
Airworthiness Directive (AD) 2003–25–
07 for certain Airbus Model A319 and
A320 series airplanes; and AD 2005–13–
39 for certain Airbus Model A321 series
airplanes. AD 2003–25–07 currently
requires a revision to the airplane flight
manual (AFM) and replacement of both
elevator aileron computers (ELACs)
having L80 standards with new ELACs
having L81 standards. AD 2005–13–39
currently requires a revision to the
AFM, replacement of existing ELACs
with ELACs having either L83 or L91
standards, as applicable; and a
concurrent action. Since we issued AD
2003–25–07 and AD 2005–13–39, we
have determined that new ELAC
standards must be incorporated. The
ELAC standards have been upgraded to
version L97+, which implements
enhanced angle-of-attack (AOA)
monitoring to better detect AOA
blockage, including multiple AOA
blockages. This proposed AD would
require replacing existing ELACs with
new ELACs having L97+ standards or
revising the software in an existing
ELAC to the L97+ standards, as
applicable, which would terminate the
requirements of AD 2003–25–07 and AD
2005–13–39. This proposed AD would
also add Airbus Model A318 series
airplanes to the applicability. We are
proposing this AD to prevent
inadvertent activation of the AOA
protections. Inadvertent activation of
the AOA protections could result in a
continuous nose down pitch rate that
could result in reduced controllability
of the airplane.
DATES: We must receive comments on
this proposed AD by May 2, 2016.
ADDRESSES: You may send comments 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 NPRM, 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;
SUMMARY:
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Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules
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.
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–2016–
4226; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
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:
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–4226; Directorate Identifier
2015–NM–095–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to 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 proposed AD.
Discussion
On December 5, 2003, we issued AD
2003–25–07, Amendment 39–13390 (68
FR 70431, December 18, 2003). AD
2003–25–07 requires a revision of the
AFM and replacement of both ELACs
having L80 standards with new ELACs
having L81 standards on Airbus Model
A319 and A320 series airplanes
equipped with L80 standards. The
replacement of both ELACs terminates
the requirement for the AFM revision.
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On June 17, 2005, we issued AD
2005–13–39, Amendment 39–14176 (70
FR 38580, July 5, 2005). AD 2005–13–
39 requires a revision of the AFM, a
concurrent action, and replacement of
existing ELACs with ELACs having L83
or L91 standards on certain Airbus
Model A321 series airplanes.
Since we issued AD 2003–25–07,
Amendment 39–13390 (68 FR 70431,
December 18, 2003); and AD 2005–13–
39, Amendment 39–14176 (70 FR
38580, July 5, 2005); we have
determined that new ELAC standards
must be incorporated. The ELAC
standard software has been updated to
version L97+ and the hardware is
available in a data loadable version and
a non-data-loadable version.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0088R1, dated June 2,
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:
existing ELACs to L97+ standards. This
proposed AD also adds Airbus Model
A318 series airplanes to the
applicability. 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–2016–4226.
The latest elevator aileron computer
(ELAC) standard, L97+, implements
enhanced Angle of Attack (AOA) monitoring
in order to better detect cases of AOA
blockage, including multiple AOA blockage.
Two ELAC L97+ versions are currently
available, Part Number (P/N) 3945129109
with data loading capability, and P/N
3945128215 without the data loading
capability. Three existing [EASA] ADs
requiring installation of earlier ELAC
(software) have been identified and taken
into account for cancellation by this new
[EASA] AD.
For the reasons described above, EASA
issued AD 2015–0088, cancelling DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France AD 95–203–072 (no requirements
retained) [which corresponds to FAA AD 98–
09–18, Amendment 39–10499 (63 FR 23374,
April 29, 1998)], and partially retaining the
requirements of DGAC France AD 2001–508
[which corresponds to FAA AD 2003–25–07,
Amendment 39–13390 (68 FR 70431,
December 18, 2003), and [DGAC] AD F–
2004–147 (EASA approval ref. 2004–8601)
[which corresponds to FAA AD 2005–13–39,
Amendment 39–14176 (70 FR 38580, July 5,
2005)], which were superseded, and to
require replacement of all ELAC with ELAC
L97+ standard.
Since that [EASA] AD was issued, some
errors were detected in Appendix 1 of the
[EASA] AD, and one P/N ELAC was
inadvertently omitted. This [EASA] AD
revises EASA AD 2015–0088 to correct these
errors and to add clarification to paragraph
(7) [of the EASA AD].
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
The required actions include either
replacing existing ELACs with new
ELACs having L97+ standards
uploaded, or revising the software in the
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Related Service Information Under
1 CFR Part 51
Airbus has issued Service Bulletin
A320–27–1243, dated March 17, 2015.
The service information describes
procedures for replacing the existing
ELACs with new ELACs having L97+
standards, and modifying existing
ELACs into units with L97+ standards.
Airbus has also issued Service
Bulletin A320–27–1244, dated March 5,
2015. The service information describes
procedures for modification of an
airplane by replacing any existing ELAC
unit with an ELAC 97+ unit having
P/N 3945128215.
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 proposed AD
affects 940 airplanes of U.S. registry.
The actions required by AD 2003–25–
07, Amendment 39–13390 (68 FR
70431, December 18, 2003), and
retained in this proposed AD take about
1 work-hour per product, at an average
labor rate of $85 per work-hour. Based
on these figures, the estimated cost of
the actions that are required by AD
2003–25–07 is $85 per product.
The actions required by AD 2005–13–
39, Amendment 39–14176 (70 FR
38580, July 5, 2005), and retained in this
proposed AD take about 1 work-hour
per product, at an average labor rate of
$85 per work-hour. Based on these
figures, the estimated cost of the actions
that are required by AD 2005–13–39 is
$85 per product.
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Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules
We also estimate that it would take
about 3 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $7,230 per
product. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $7,035,900, or
$7,485 per product.
According to the parts manufacturer,
some of the costs of this proposed AD
may be covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
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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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2003–25–07, Amendment 39–
13390 (68 FR 70431, December 18,
2003); and AD 2005–13–39,
Amendment 39–14176 (70 FR 38580,
July 5, 2005); and
■ b. Adding the following new AD:
■
■
Airbus: Docket No. FAA–2016–4226;
Directorate Identifier 2015–NM–095–AD.
(a) Comments Due Date
We must receive comments by May 2,
2016.
(b) Affected ADs
This AD replaces AD 2003–25–07,
Amendment 39–13390 (68 FR 70431,
December 18, 2003); and AD 2005–13–39,
Amendment 39–14176 (70 FR 38580, July 5,
2005).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) through (c)(4) of this AD,
certificated in any category, 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 a determination
that new elevator aileron computers (ELAC)
standards must be incorporated. The ELAC
standards have been upgraded to version
L97+, which implements enhanced angle-of-
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attack (AOA) monitoring to better detect
AOA blockage, including multiple AOA
blockages. We are issuing this AD to prevent
inadvertent activation of the AOA
protections. Inadvertent activation of the
AOA protections could result in a continuous
nose down pitch rate that could result in
reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Replacement of ELAC L80 Units
With L81 Units, With No Changes
For Model A319 and A320 series airplanes,
equipped with ELAC L80 standards having
part numbers listed in Airbus Service
Bulletin A320–27–1135, dated June 29, 2001:
This paragraph restates the requirements of
paragraph (b) of AD 2003–25–07,
Amendment 39–13390 (68 FR 70431,
December 18, 2003), with no changes. Within
1 year after January 22, 2004 (the effective
date of AD 2003–25–07): Replace both ELACs
having L80 standards with new ELACs
having L81 standards, by doing all the
actions per paragraphs A., B., C., and D. of
the Accomplishment Instructions of Airbus
Service Bulletin A320–27–1135, dated June
29, 2001.
(h) Retained Installation of ELAC L83 or L91
Software, With No Changes
For Model A321–111, –112, –131, –211,
and –231 airplanes, except those with Airbus
Modification 34043 installed in production:
This paragraph restates the requirements of
paragraph (g) of AD 2005–13–39,
Amendment 39–14176 (70 FR 38580, July 5,
2005), with no changes. Within 16 months
after August 9, 2005 (the effective date of AD
2005–13–39): Replace existing ELACs with
ELACs having L83 standards, by
accomplishing all of the actions specified in
the Accomplishment Instructions of Airbus
Service Bulletin A320–27–1151, dated March
9, 2004, including Appendix 01, dated March
9, 2004; or with ELACs having L91 standards,
by accomplishing all of the actions specified
in the Accomplishment Instructions of
Airbus Service Bulletin A320–27–1152,
dated June 4, 2004, including Appendix 01,
dated June 4, 2004; as applicable.
(i) New Requirement of This AD: ELAC
Replacement or Modification
At the applicable times specified in table
1 to paragraph (i) of this AD: Replace each
ELAC unit with an ELAC L97+ unit having
part number (P/N) 3945129100 and software
having P/N 3945129109, or modify existing
ELAC units into ELAC L97+ units having P/
N 3945129100 with L97+ operational
software P/N 3945129109 loaded, as
applicable, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1243, dated March
17, 2015. Accomplishing this replacement
terminates the actions required by paragraphs
(g) and (h) of this AD.
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TABLE 1 TO PARAGRAPH (I) OF THIS AD—COMPLIANCE TIMES
Compliance time
(after the effective
date of this AD)
Airbus airplane models
Model A318 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N
tions (captain, first officer, and standby).
Model A319 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N
tions (captain, first officer, and standby).
Model A320 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N
tions (captain, first officer, and standby).
Model A321 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N
tions (captain, first officer, and standby).
Model A318, A319, A320, and A321 series airplanes that do not have UTAS (formerly
P/N 0861ED2 installed in all 3 positions (captain, first officer, and standby).
(j) Optional Method of Compliance
Modification of an airplane by replacing
any existing ELAC unit with an ELAC 97+
unit having P/N 3945128215, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–27–1244,
dated March 5, 2015, is an acceptable method
of compliance for the requirements of
paragraph (i) of this AD, for only that
modified airplane. Accomplishing this
modification terminates the actions required
by paragraphs (g) and (h) of this AD for that
modified airplane.
0861ED2 installed in all 3 posi-
Within 5 months.
0861ED2 installed in all 3 posi-
Within 10 months.
0861ED2 installed in all 3 posi-
Within 10 months.
0861ED2 installed in all 3 posi-
Within 5 months.
Goodrich) AOA P/N 0861ED or
Within 25 months.
Note 1 to paragraph (j) of this AD: ELAC
unit P/N 3945128215 is not data-loadable,
but it is fully interchangeable and mixable
with data-loadable ELAC 97+ unit P/N
3945129100 with software P/N 3945129109
loaded.
(k) Exclusion From Requirements of
Paragraphs (g), (h), and (i), and the Actions
in Paragraph (j), of This AD
Airplanes on which Airbus Modification
156546 (installation of ELAC L97+ with
software P/N 3945129109) was installed in
production are excluded from the
requirements of paragraphs (g), (h), and (i) of
this AD and the actions specified in
paragraph (j) of this AD, provided it can be
determined that no ELAC having a part
number identified in table 2 to paragraph (k)
of this AD has been installed on that airplane
since the date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness.
TABLE 2 TO PARAGRAPH (k) OF THIS AD—PROHIBITED ELAC PART NUMBERS
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Part number
Designation
3945122202 ............................................
3945122203 ............................................
3945122303 ............................................
3945122304 ............................................
3945122305 ............................................
3945122306 ............................................
3945122307 ............................................
C12370AA01 ...........................................
3945122501 ............................................
3945122502 ............................................
3945122503 ............................................
3945122504 ............................................
3945122505 ............................................
3945123505 ............................................
3945128101 ............................................
3945122506 ............................................
3945123506 ............................................
3945128102 ............................................
3945122507 ............................................
3945123507 ............................................
3945128103 ............................................
3945122608 ............................................
3945123608 ............................................
3945122609 ............................................
3945123609 ............................................
3945128204 ............................................
3945128205 ............................................
3945128206 ............................................
3945129101 ............................................
3945128207 ............................................
3945128208 ............................................
3945128209 ............................................
3945129103 ............................................
3945128210 ............................................
3945129104 ............................................
3945128212 ............................................
3945129106 ............................................
3945129107 ............................................
3945128214 ............................................
3945129108 ............................................
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ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
ELAC
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ELAC
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Jkt 238001
FIN
A320–111 Type Def .....................................................................................
L50C .............................................................................................................
L50C .............................................................................................................
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A L80 ............................................................................................................
A’ L80 ...........................................................................................................
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A L81 ............................................................................................................
A’ L81 ...........................................................................................................
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A L82 ............................................................................................................
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A L83 ............................................................................................................
A’ L83 ...........................................................................................................
A L84 ............................................................................................................
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B L90N .........................................................................................................
B L91 ............................................................................................................
B L91 data loadable .....................................................................................
B L92 ............................................................................................................
B L92L ..........................................................................................................
B L93 ............................................................................................................
B L93 data loadable .....................................................................................
B L94 ............................................................................................................
B L94 data loadable .....................................................................................
B L96 ............................................................................................................
B L96 data loadable .....................................................................................
B L96 H–A data loadable .............................................................................
B L97 ............................................................................................................
B L97 data loadable .....................................................................................
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14408
Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules
(l) Later-Approved Parts
Installation of an ELAC version (part
number) approved after the effective date of
this AD is an approved method of
compliance with the requirements of
paragraphs (i) and (j) of this AD, provided the
requirements specified in paragraphs (l)(1)
and (l)(2) of this AD are met.
(1) The version (part number) must be
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).
(2) The installation must be done using a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the EASA; or
Airbus’s EASA DOA.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(m) Parts Installation Limitation
As of the applicable time specified in
paragraph (m)(1) or (m)(2) of this AD, do not
install on any airplane an ELAC unit having
a part number identified in table 2 to
paragraph (k) of this AD, except as specified
in paragraph (m)(3) of this AD.
(1) For an airplane that, as of the effective
date of this AD, has any ELAC unit installed
having a part number identified in table 2 to
paragraph (k) of this AD: After modification
of that airplane as required by paragraph (i)
of this AD, or as specified in paragraph (j) of
this AD.
(2) For an airplane that, as of the effective
date of this AD, does not have any ELAC unit
installed having a part number identified in
table 2 to paragraph (k) of this AD: As of the
effective date of this AD.
(3) As of the effective date of this AD, a
data-loadable ELAC B unit having a part
number identified in table 2 to paragraph (k)
of this AD can be installed on an airplane
provided that L97+ software P/N 3945129109
is uploaded at the applicable time specified
in paragraph (m)(3)(i) or (m)(3)(ii) of this AD.
(i) For all airplanes except those identified
in paragraph (m)(3)(ii) of this AD: Before
further flight after the ELAC B unit
installation.
(ii) For airplanes that have not been
modified as required by paragraph (i) of this
AD: Within the applicable compliance time
specified in table 1 to paragraph (i) of this
AD.
(n) 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-116AMOC-REQUESTS@faa.gov.
VerDate Sep<11>2014
16:06 Mar 16, 2016
Jkt 238001
(i) 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.
(ii) AMOCs approved previously for AD
2003–25–07, Amendment 39–13390 (68 FR
70431, December 18, 2003), are approved as
AMOCs for the corresponding provisions of
paragraph (g) of this AD.
(iii) AMOCs approved previously for AD
2005–13–39, Amendment 39–14176 (70 FR
38580, July 5, 2005), are approved as AMOCs
for the corresponding provisions of
paragraph (h) of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0088R1, dated
June 2, 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–
2016–4226.
(2) 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 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.
Issued in Renton, Washington, on March 9,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–05830 Filed 3–16–16; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF THE TREASURY
Financial Crimes Enforcement Network
31 CFR Part 1010
RIN 1506–AB19
Financial Crimes Enforcement
Network; Withdrawal of Notice of
Proposed Rulemaking Regarding JSC
CredexBank
Financial Crimes Enforcement
Network (‘‘FinCEN’’), Treasury.
ACTION: Proposed rule; withdrawal.
AGENCY:
This document withdraws
FinCEN’s proposed rulemaking to
impose the first and fifth special
measure regarding JSC CredexBank
(‘‘Credex’’), renamed JSC InterPayBank
(‘‘InterPay’’), as a financial institution of
primary money laundering concern,
pursuant to Section 311 of the USA
PATRIOT Act (‘‘Section 311’’).
Because of material subsequent
developments that have mitigated the
money laundering risks associated with
Credex, FinCEN has determined that
Credex is no longer a primary money
laundering concern that warrants the
implementation of a special measure
under Section 311. Elsewhere in this
issue of the Federal Register, FinCEN is
publishing a withdrawal of the related
finding regarding Credex.
DATES: As of March 17, 2016 the
proposed rule published May 30, 2012,
at 77 FR 31794, is withdrawn.
FOR FURTHER INFORMATION CONTACT: The
FinCEN Resource Center at (800) 767–
2825.
SUPPLEMENTARY INFORMATION:
SUMMARY:
I. Background
On October 26, 2001, the President
signed into law the Uniting and
Strengthening America by Providing
Appropriate Tools Required to Intercept
and Obstruct Terrorism Act of 2001,
Public Law 107–56 (the ‘‘USA PATRIOT
Act’’). Title III of the USA PATRIOT Act
amends the anti-money laundering
provisions of the Bank Secrecy Act
(‘‘BSA’’), codified at 12 U.S.C. 1829b, 12
U.S.C. 1951–1959, and 31 U.S.C. 5311–
5314, 5316–5332, to promote the
prevention, detection, and prosecution
of money laundering, tax evasion, the
financing of terrorism, and other
financial crimes. Regulations
implementing the BSA appear at 31 CFR
Chapter X. The authority of the
Secretary of the Treasury to administer
the BSA and its implementing
regulations has been delegated to the
Director of FinCEN.
Section 311 of the USA PATRIOT Act
(‘‘Section 311’’), codified at 31 U.S.C.
E:\FR\FM\17MRP1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 52 (Thursday, March 17, 2016)]
[Proposed Rules]
[Pages 14404-14408]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-05830]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-4226; Directorate Identifier 2015-NM-095-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003-25-
07 for certain Airbus Model A319 and A320 series airplanes; and AD
2005-13-39 for certain Airbus Model A321 series airplanes. AD 2003-25-
07 currently requires a revision to the airplane flight manual (AFM)
and replacement of both elevator aileron computers (ELACs) having L80
standards with new ELACs having L81 standards. AD 2005-13-39 currently
requires a revision to the AFM, replacement of existing ELACs with
ELACs having either L83 or L91 standards, as applicable; and a
concurrent action. Since we issued AD 2003-25-07 and AD 2005-13-39, we
have determined that new ELAC standards must be incorporated. The ELAC
standards have been upgraded to version L97+, which implements enhanced
angle-of-attack (AOA) monitoring to better detect AOA blockage,
including multiple AOA blockages. This proposed AD would require
replacing existing ELACs with new ELACs having L97+ standards or
revising the software in an existing ELAC to the L97+ standards, as
applicable, which would terminate the requirements of AD 2003-25-07 and
AD 2005-13-39. This proposed AD would also add Airbus Model A318 series
airplanes to the applicability. We are proposing this AD to prevent
inadvertent activation of the AOA protections. Inadvertent activation
of the AOA protections could result in a continuous nose down pitch
rate that could result in reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by May 2, 2016.
ADDRESSES: You may send comments 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 NPRM, 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;
[[Page 14405]]
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.
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-2016-
4226; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-4226;
Directorate Identifier 2015-NM-095-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to 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 proposed AD.
Discussion
On December 5, 2003, we issued AD 2003-25-07, Amendment 39-13390
(68 FR 70431, December 18, 2003). AD 2003-25-07 requires a revision of
the AFM and replacement of both ELACs having L80 standards with new
ELACs having L81 standards on Airbus Model A319 and A320 series
airplanes equipped with L80 standards. The replacement of both ELACs
terminates the requirement for the AFM revision.
On June 17, 2005, we issued AD 2005-13-39, Amendment 39-14176 (70
FR 38580, July 5, 2005). AD 2005-13-39 requires a revision of the AFM,
a concurrent action, and replacement of existing ELACs with ELACs
having L83 or L91 standards on certain Airbus Model A321 series
airplanes.
Since we issued AD 2003-25-07, Amendment 39-13390 (68 FR 70431,
December 18, 2003); and AD 2005-13-39, Amendment 39-14176 (70 FR 38580,
July 5, 2005); we have determined that new ELAC standards must be
incorporated. The ELAC standard software has been updated to version
L97+ and the hardware is available in a data loadable version and a
non-data-loadable version.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0088R1, dated June 2, 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:
The latest elevator aileron computer (ELAC) standard, L97+,
implements enhanced Angle of Attack (AOA) monitoring in order to
better detect cases of AOA blockage, including multiple AOA
blockage.
Two ELAC L97+ versions are currently available, Part Number (P/
N) 3945129109 with data loading capability, and P/N 3945128215
without the data loading capability. Three existing [EASA] ADs
requiring installation of earlier ELAC (software) have been
identified and taken into account for cancellation by this new
[EASA] AD.
For the reasons described above, EASA issued AD 2015-0088,
cancelling DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 95-203-072 (no requirements retained) [which
corresponds to FAA AD 98-09-18, Amendment 39-10499 (63 FR 23374,
April 29, 1998)], and partially retaining the requirements of DGAC
France AD 2001-508 [which corresponds to FAA AD 2003-25-07,
Amendment 39-13390 (68 FR 70431, December 18, 2003), and [DGAC] AD
F-2004-147 (EASA approval ref. 2004-8601) [which corresponds to FAA
AD 2005-13-39, Amendment 39-14176 (70 FR 38580, July 5, 2005)],
which were superseded, and to require replacement of all ELAC with
ELAC L97+ standard.
Since that [EASA] AD was issued, some errors were detected in
Appendix 1 of the [EASA] AD, and one P/N ELAC was inadvertently
omitted. This [EASA] AD revises EASA AD 2015-0088 to correct these
errors and to add clarification to paragraph (7) [of the EASA AD].
The required actions include either replacing existing ELACs with
new ELACs having L97+ standards uploaded, or revising the software in
the existing ELACs to L97+ standards. This proposed AD also adds Airbus
Model A318 series airplanes to the applicability. 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-2016-4226.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-27-1243, dated March 17,
2015. The service information describes procedures for replacing the
existing ELACs with new ELACs having L97+ standards, and modifying
existing ELACs into units with L97+ standards.
Airbus has also issued Service Bulletin A320-27-1244, dated March
5, 2015. The service information describes procedures for modification
of an airplane by replacing any existing ELAC unit with an ELAC 97+
unit having P/N 3945128215.
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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 940 airplanes of U.S.
registry.
The actions required by AD 2003-25-07, Amendment 39-13390 (68 FR
70431, December 18, 2003), and retained in this proposed AD take about
1 work-hour per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the actions that are
required by AD 2003-25-07 is $85 per product.
The actions required by AD 2005-13-39, Amendment 39-14176 (70 FR
38580, July 5, 2005), and retained in this proposed AD take about 1
work-hour per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the actions that are
required by AD 2005-13-39 is $85 per product.
[[Page 14406]]
We also estimate that it would take about 3 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $7,230
per product. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $7,035,900, or $7,485 per product.
According to the parts manufacturer, some of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected individuals. We do not control warranty coverage for
affected individuals. As a result, we have included all costs in our
cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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:
0
a. Removing Airworthiness Directive (AD) 2003-25-07, Amendment 39-13390
(68 FR 70431, December 18, 2003); and AD 2005-13-39, Amendment 39-14176
(70 FR 38580, July 5, 2005); and
0
b. Adding the following new AD:
Airbus: Docket No. FAA-2016-4226; Directorate Identifier 2015-NM-
095-AD.
(a) Comments Due Date
We must receive comments by May 2, 2016.
(b) Affected ADs
This AD replaces AD 2003-25-07, Amendment 39-13390 (68 FR 70431,
December 18, 2003); and AD 2005-13-39, Amendment 39-14176 (70 FR
38580, July 5, 2005).
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (c)(4) of this AD, certificated in any category, 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 a determination that new elevator
aileron computers (ELAC) standards must be incorporated. The ELAC
standards have been upgraded to version L97+, which implements
enhanced angle-of-attack (AOA) monitoring to better detect AOA
blockage, including multiple AOA blockages. We are issuing this AD
to prevent inadvertent activation of the AOA protections.
Inadvertent activation of the AOA protections could result in a
continuous nose down pitch rate that could result in reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Replacement of ELAC L80 Units With L81 Units, With No
Changes
For Model A319 and A320 series airplanes, equipped with ELAC L80
standards having part numbers listed in Airbus Service Bulletin
A320-27-1135, dated June 29, 2001: This paragraph restates the
requirements of paragraph (b) of AD 2003-25-07, Amendment 39-13390
(68 FR 70431, December 18, 2003), with no changes. Within 1 year
after January 22, 2004 (the effective date of AD 2003-25-07):
Replace both ELACs having L80 standards with new ELACs having L81
standards, by doing all the actions per paragraphs A., B., C., and
D. of the Accomplishment Instructions of Airbus Service Bulletin
A320-27-1135, dated June 29, 2001.
(h) Retained Installation of ELAC L83 or L91 Software, With No Changes
For Model A321-111, -112, -131, -211, and -231 airplanes, except
those with Airbus Modification 34043 installed in production: This
paragraph restates the requirements of paragraph (g) of AD 2005-13-
39, Amendment 39-14176 (70 FR 38580, July 5, 2005), with no changes.
Within 16 months after August 9, 2005 (the effective date of AD
2005-13-39): Replace existing ELACs with ELACs having L83 standards,
by accomplishing all of the actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1151, dated March 9,
2004, including Appendix 01, dated March 9, 2004; or with ELACs
having L91 standards, by accomplishing all of the actions specified
in the Accomplishment Instructions of Airbus Service Bulletin A320-
27-1152, dated June 4, 2004, including Appendix 01, dated June 4,
2004; as applicable.
(i) New Requirement of This AD: ELAC Replacement or Modification
At the applicable times specified in table 1 to paragraph (i) of
this AD: Replace each ELAC unit with an ELAC L97+ unit having part
number (P/N) 3945129100 and software having P/N 3945129109, or
modify existing ELAC units into ELAC L97+ units having P/N
3945129100 with L97+ operational software P/N 3945129109 loaded, as
applicable, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-27-1243, dated March 17, 2015.
Accomplishing this replacement terminates the actions required by
paragraphs (g) and (h) of this AD.
[[Page 14407]]
Table 1 to Paragraph (i) of This AD--Compliance Times
------------------------------------------------------------------------
Compliance time (after the
Airbus airplane models effective date of this AD)
------------------------------------------------------------------------
Model A318 series airplanes with UTAS Within 5 months.
(formerly Goodrich) AOA P/N 0861ED
or P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A319 series airplanes with UTAS Within 10 months.
(formerly Goodrich) AOA P/N 0861ED
or P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A320 series airplanes with UTAS Within 10 months.
(formerly Goodrich) AOA P/N 0861ED
or P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A321 series airplanes with UTAS Within 5 months.
(formerly Goodrich) AOA P/N 0861ED
or P/N 0861ED2 installed in all 3
positions (captain, first officer,
and standby).
Model A318, A319, A320, and A321 Within 25 months.
series airplanes that do not have
UTAS (formerly Goodrich) AOA P/N
0861ED or P/N 0861ED2 installed in
all 3 positions (captain, first
officer, and standby).
------------------------------------------------------------------------
(j) Optional Method of Compliance
Modification of an airplane by replacing any existing ELAC unit
with an ELAC 97+ unit having P/N 3945128215, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1244,
dated March 5, 2015, is an acceptable method of compliance for the
requirements of paragraph (i) of this AD, for only that modified
airplane. Accomplishing this modification terminates the actions
required by paragraphs (g) and (h) of this AD for that modified
airplane.
Note 1 to paragraph (j) of this AD: ELAC unit P/N 3945128215 is
not data-loadable, but it is fully interchangeable and mixable with
data-loadable ELAC 97+ unit P/N 3945129100 with software P/N
3945129109 loaded.
(k) Exclusion From Requirements of Paragraphs (g), (h), and (i), and
the Actions in Paragraph (j), of This AD
Airplanes on which Airbus Modification 156546 (installation of
ELAC L97+ with software P/N 3945129109) was installed in production
are excluded from the requirements of paragraphs (g), (h), and (i)
of this AD and the actions specified in paragraph (j) of this AD,
provided it can be determined that no ELAC having a part number
identified in table 2 to paragraph (k) of this AD has been installed
on that airplane since the date of issuance of the original
airworthiness certificate or the date of issuance of the original
export certificate of airworthiness.
Table 2 to Paragraph (k) of This AD--Prohibited ELAC Part Numbers
------------------------------------------------------------------------
Part number Designation FIN
------------------------------------------------------------------------
3945122202.................... ELAC A320-111 Type Def 2 CE 1/2.
3945122203.................... ELAC L50C............. 2 CE 1/2.
3945122303.................... ELAC L50C............. 2 CE 1/2.
3945122304.................... ELAC L60.............. 2 CE 1/2.
3945122305.................... ELAC L61B............. 2 CE 1/2.
3945122306.................... ELAC L61F............. 2 CE 1/2.
3945122307.................... ELAC L62C............. 2 CE 1/2.
C12370AA01.................... ELAC L68C............. 2 CE 1/2.
3945122501.................... ELAC L69.............. 2 CE 1/2.
3945122502.................... ELAC L69J............. 2 CE 1/2.
3945122503.................... ELAC L77.............. 2 CE 1/2.
3945122504.................... ELAC L78.............. 2 CE 1/2.
3945122505.................... ELAC A L80............ 2 CE 1/2.
3945123505.................... ELAC A' L80........... 2 CE 1/2.
3945128101.................... ELAC B L80............ 2 CE 1/2.
3945122506.................... ELAC A L81............ 2 CE 1/2.
3945123506.................... ELAC A' L81........... 2 CE 1/2.
3945128102.................... ELAC B L81............ 2 CE 1/2.
3945122507.................... ELAC A L82............ 2 CE 1/2.
3945123507.................... ELAC A' L82........... 2 CE 1/2.
3945128103.................... ELAC B L82............ 2 CE 1/2.
3945122608.................... ELAC A L83............ 2 CE 1/2.
3945123608.................... ELAC A' L83........... 2 CE 1/2.
3945122609.................... ELAC A L84............ 2 CE 1/2.
3945123609.................... ELAC A' L84........... 2 CE 1/2.
3945128204.................... ELAC B L90L........... 2 CE 1/2.
3945128205.................... ELAC B L90N........... 2 CE 1/2.
3945128206.................... ELAC B L91............ 2 CE 1/2.
3945129101.................... ELAC B L91 data 2 CE 1/2 SW1.
loadable.
3945128207.................... ELAC B L92............ 2 CE 1/2.
3945128208.................... ELAC B L92L........... 2 CE 1/2.
3945128209.................... ELAC B L93............ 2 CE 1/2.
3945129103.................... ELAC B L93 data 2 CE 1/2 SW1.
loadable.
3945128210.................... ELAC B L94............ 2 CE 1/2.
3945129104.................... ELAC B L94 data 2 CE 1/2 SW1.
loadable.
3945128212.................... ELAC B L96............ 2 CE 1/2.
3945129106.................... ELAC B L96 data 2 CE 1/2 SW1.
loadable.
3945129107.................... ELAC B L96 H-A data 2 CE 1/2 SW1.
loadable.
3945128214.................... ELAC B L97............ 2 CE 1/2.
3945129108.................... ELAC B L97 data 2 CE 1/2 SW1.
loadable.
------------------------------------------------------------------------
[[Page 14408]]
(l) Later-Approved Parts
Installation of an ELAC version (part number) approved after the
effective date of this AD is an approved method of compliance with
the requirements of paragraphs (i) and (j) of this AD, provided the
requirements specified in paragraphs (l)(1) and (l)(2) of this AD
are met.
(1) The version (part number) must be 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).
(2) The installation must be done using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(m) Parts Installation Limitation
As of the applicable time specified in paragraph (m)(1) or
(m)(2) of this AD, do not install on any airplane an ELAC unit
having a part number identified in table 2 to paragraph (k) of this
AD, except as specified in paragraph (m)(3) of this AD.
(1) For an airplane that, as of the effective date of this AD,
has any ELAC unit installed having a part number identified in table
2 to paragraph (k) of this AD: After modification of that airplane
as required by paragraph (i) of this AD, or as specified in
paragraph (j) of this AD.
(2) For an airplane that, as of the effective date of this AD,
does not have any ELAC unit installed having a part number
identified in table 2 to paragraph (k) of this AD: As of the
effective date of this AD.
(3) As of the effective date of this AD, a data-loadable ELAC B
unit having a part number identified in table 2 to paragraph (k) of
this AD can be installed on an airplane provided that L97+ software
P/N 3945129109 is uploaded at the applicable time specified in
paragraph (m)(3)(i) or (m)(3)(ii) of this AD.
(i) For all airplanes except those identified in paragraph
(m)(3)(ii) of this AD: Before further flight after the ELAC B unit
installation.
(ii) For airplanes that have not been modified as required by
paragraph (i) of this AD: Within the applicable compliance time
specified in table 1 to paragraph (i) of this AD.
(n) 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.
(i) 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.
(ii) AMOCs approved previously for AD 2003-25-07, Amendment 39-
13390 (68 FR 70431, December 18, 2003), are approved as AMOCs for
the corresponding provisions of paragraph (g) of this AD.
(iii) AMOCs approved previously for AD 2005-13-39, Amendment 39-
14176 (70 FR 38580, July 5, 2005), are approved as AMOCs for the
corresponding provisions of paragraph (h) of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0088R1, dated June 2, 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-2016-4226.
(2) 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 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.
Issued in Renton, Washington, on March 9, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-05830 Filed 3-16-16; 8:45 am]
BILLING CODE 4910-13-P
