Airworthiness Directives; Airbus Airplanes, 57122-57129 [2015-21730]
Download as PDF
<![CDATA[
57122
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0529; Directorate
Identifier 2013–NM–260–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for all Airbus Model A318, A319, A320,
and A321 series airplanes. The NPRM
proposed to supersede Airworthiness
Directives (AD) 2011–13–11 and AD
2013–16–09. AD 2011–13–11 currently
requires an amendment of the airplane
flight manual (AFM), repetitive checks
of specific centralized fault display
system (CFDS) messages, an inspection
of the opening sequence of the main
landing gear (MLG) door actuator for
discrepancies if certain messages are
found, and corrective actions if
necessary. AD 2013–16–09 currently
requires an inspection to determine
airplane configuration and part numbers
of the landing gear control interface unit
and MLG door actuators; and, for
affected airplanes, repetitive inspections
of the opening sequence of the MLG
door actuator, and replacement of the
MLG door actuator if necessary; and
provides optional terminating action for
the repetitive inspections. The NPRM
was prompted by a determination that
the interval of the MLG door opening
sequence inspection must be reduced.
The NPRM proposed to reduce the
interval of the MLG door opening
sequence inspection, and also to replace
or modify certain MLG door actuators.
This action revises the NPRM by adding
a flushing procedure to be performed
when installing a new MLG door
actuator. We are proposing this
supplemental NPRM (SNPRM) to detect
and correct deterioration of the damping
ring and associated retaining ring of the
MLG door actuator, which can
sufficiently increase the friction inside
the actuator to restrict opening of the
MLG door by gravity, during operation
of the landing gear alternate (free-fall)
extension system. This condition could
prevent the full extension and/or downlocking of the MLG, possibly resulting
in MLG collapse during landing and
consequent damage to the airplane and
Lhorne on DSK5TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
injury to occupants. Since these actions
impose an additional burden over those
proposed in the NPRM, we are
reopening the comment period to allow
the public the chance to comment on
these proposed changes.
DATES: We must receive comments on
this SNPRM by November 6, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Airbus service information
identified in this proposed 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. For
General Electric service information
identified in this AD contact GE
Aviation, Customer Support Center, 1
Neumann Way, Cincinnati, OH 45215;
phone: 513–552–3272; email:
cs.techpubs@ge.com; Internet: https://
www.geaviation.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–2014–
0529; 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 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,
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
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–2014–0529; Directorate Identifier
2013–NM–260–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
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 A318, A319,
A320, and A321 series airplanes. The
NPRM published in the Federal
Register on August 13, 2014 (79 FR
47395; corrected August 27, 2014 (79 FR
51117)) (‘‘the NPRM’’). The NPRM
proposed to supersede AD 2011–13–11,
Amendment 39–16734 (76 FR 37241,
June 27, 2011) (‘‘AD 2011–13–11’’); and
AD 2013–16–09, Amendment 39–17547
(78 FR 48286, August 8, 2013) (‘‘AD
2013–16–09’’). AD 2011–13–11
currently requires an amendment of the
AFM, repetitive checks of specific CFDS
messages, an inspection of the opening
sequence of the MLG door actuator for
discrepancies if certain messages are
found, and corrective actions if
necessary. AD 2013–16–09 currently
requires an inspection to determine
airplane configuration and part numbers
of the landing gear control interface unit
and MLG door actuators; and, for
affected airplanes, repetitive inspections
of the opening sequence of the MLG
door actuator, and replacement of the
MLG door actuator if necessary; and
provides optional terminating action for
the repetitive inspections. The NPRM
was prompted by a determination that
the interval of the MLG door opening
sequence inspection must be reduced.
The NPRM proposed to reduce the
interval of the MLG door opening
E:\FR\FM\22SEP1.SGM
22SEP1
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
sequence inspection, and also to replace
or modify certain MLG door actuators.
Lhorne on DSK5TPTVN1PROD with PROPOSALS
Actions Since Previous NPRM Was
Issued
Since we issued the NPRM, we have
determined that a flushing procedure
must be performed when installing a
new MLG door actuator. The European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Union, has
issued EASA Airworthiness Directive
2014–0221, dated September 30, 2014
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition on all Airbus Model A318,
A319, A320, and A321 series airplanes.
The MCAI states:
Some operators reported slow operation of
the main landing gear (MLG) door opening/
closing sequence, leading to the generation of
[electronic centralized aircraft monitor]
ECAM warnings during the landing gear
retraction or extension sequence.
Investigations showed that the damping
ring and associated retaining ring of the MLG
door actuator may deteriorate. The resultant
debris increases the friction inside the
actuator which can be sufficiently high to
restrict opening of the MLG door by gravity,
during operation of the landing gear alternate
(freefall) extension system.
This condition, if not corrected, could
prevent the full extension and/or down
locking of the MLG, possibly resulting in
MLG collapse during landing or rollout and
consequent damage to the aeroplane and
injury to occupants.
[An EASA AD] was issued [and later
revised] to require repetitive inspections of
the opening sequence of the MLG door in
order to identify the affected actuators, and
to introduce as an optional terminating
action Airbus production Modification (mod)
38274 and associated [Airbus] Service
Bulletin (SB) A320–32–1338, which
incorporate an improved retaining ring,
located on the piston rod’s extension end,
and a new piston rod with machined
shoulder to accommodate the thicker section
of the modified retaining ring.
After in-service introduction of the new
MLG door actuator, Part Number (P/N)
114122012 (Post-mod 38274—SB A320–32–
1338), several operators reported failures of
internal parts of the MLG door actuator.
Investigations confirmed that these failures
could result in slow extension of the actuator
rod, delaying the MLG door operation, or
possibly stopping just before the end of the
stroke, preventing the door to reach the fully
open position.
[An EASA AD], which superseded EASA
AD 2006–0112R1 [https://ad.easa.europa.eu/
blob/easa_ad_2006_0112_R1_
superseded.pdf/AD_2006-0112R1_1], was
issued [and later revised] to require
amendment of the applicable Airplane Flight
Manual (AFM), repetitive checks of specific
Centralized Fault Display System (CFDS)
messages, repetitive inspections of the
opening sequence of the MLG door actuator
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
and, depending on findings, corrective
action(s).
Since EASA AD 2011–0069R1 [https://
ad.easa.europa.eu/blob/easa_ad_2011_0069_
R1_superseded.pdf/AD_2011-0069R1_1] was
issued, Airbus introduced a reinforced MLG
door actuator P/N 114122014 (mod 153655).
Airbus issued SB A320–32–1407 containing
instructions for in-service replacement of the
affected MLG door actuators, or modification
of the actuators to the new standard.
In addition, following a recent occurrence
with a gear extension problem, the result of
additional analyses by Airbus revealed that
the CFDS expected specific messages may
not be generated and as a result, repetitive
checks of messages are not effective for
aeroplanes fitted with landing gear control
interface unit (LGCIU) interlink
communication ARINC 429 (applied in
production through Airbus mod 39303, or in
service through Airbus SB A320–32–1409),
in combination with LGCIUs 80–178–02–
88012 or 80–178–03–88013 in both positions
and at least one MLG door actuator pre-mod
153655 (pre-Airbus SB A320–32–1407—preGE SB 114122–32–105) installed.
Prompted by these findings, EASA issued
Emergency AD 2013–0132–E [https://
ad.easa.europa.eu/blob/easa_ad_2013_0132_
E_superseded.pdf/EAD_2013-0132-E_1
(which corresponds to FAA AD 2013–16–09)]
to require identification of the affected
aeroplanes to establish the configuration and,
for those aeroplanes, repetitive inspections of
the opening sequence of the MLG door
actuator and, depending on findings,
replacement of the MLG door actuator. That
[EASA] AD also provided an optional
terminating action by disconnection of the
interlink for certain LGCIUs, or in-service
modification of the aeroplane through Airbus
SB A320–32–1407 (equivalent to Airbus
production mod 153655).
Since those ADs (EASA AD 2011–0069R1
and EASA AD 2013–0132–E) were issued,
analyses performed by Airbus have revealed
that the MLG door opening sequence
inspection interval needed to be reduced,
and that the (previously optional)
terminating action needed to be made
mandatory.
Prompted by these findings, EASA issued
AD 2013–0288 [https://ad.easa.europa.eu/
blob/easa_ad_2013_0288_superseded.pdf/
AD_2013-0288_1], retaining the requirements
of EASA AD 2011–0069R1 and EASA AD
2013–0132–E, which were superseded, but
with reduced inspection intervals, and to
require replacement or modification, as
applicable, of the affected MLG door
actuators as terminating action to the
monitoring and repetitive checks and
inspections.
Following introduction of post-mod
153655 MLG door actuators on in-service
aeroplanes, it has been observed that, in case
the removed pre-mod MLG door actuator has
internal damage, contamination of the
hydraulic system could have occurred.
This condition, if not detected and
corrected, could result in performance
degradation (damping degradation) of the
post-mod MLG door actuator. Testing
performed with a new actuator tested in
heavily contaminated hydraulic system did
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
57123
not show abnormal hydraulic Restriction/
blockage. It is thus not requested to perform
this ‘‘flushing procedure’’ on aircraft already
retrofitted with std-14 actuators.
In addition, since EASA AD 2013–0288
was issued, the applicable AFM was revised
and repetitive checks of specific CFDS
messages are no longer considered to be
required, due to the reduced intervals
required by EASA AD 2013–0288.
For the reasons described above, this
[EASA] AD partially retains the requirements
of EASA AD 2013–0288, which is
superseded, introduces improved wording
for clarification and requires, in addition to
the revised operational (AFM) procedure,
hydraulic flushing prior to any installation of
a post-mod MLG door actuator.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-5290003.
Related Service Information Under 1
CFR part 51
Airbus has issued Service Bulletins
A320–32–1390, Revision 03, dated July
3, 2014; and A320–32–1407, Revision
01, dated July 3, 2014. Airbus has also
issued A318/A319/A320/A321
Temporary Revision (TR) TR437, L/G
GEAR NOT DOWNLOCKED, Issue 1.0,
dated May 23, 2014, to the Airplane
Flight Manual (AFM).
Airbus Service Bulletin A320–32–
1390, Revision 03, dated July 3, 2014,
describes procedures for inspecting the
operation of the MLG door opening
sequence to determine if an actuator is
defective, flushing contamination from
the landing gear extension and
retraction system (LGERS), and
replacing the door actuator if necessary.
Airbus Service Bulletin A320–32–
1407, Revision 01, dated July 3, 2014,
describes procedures for flushing
contamination from the LGERS, and
installing new MLG door actuators.
Airbus A318/A319/A320/A321 TR
TR437, L/G GEAR NOT
DOWNLOCKED, Issue 1.0, dated May
23, 2014, to the AFM updates the
procedure used for incomplete landing
gear extension during approach.
General Electric Service Bulletin
114122–32–105, Revision 2, dated June
24, 2014, describes procedures for
conversion of a MLG door actuator and
to remove unwanted material from the
hydraulic fluid route.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this SNPRM.
E:\FR\FM\22SEP1.SGM
22SEP1
57124
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
Comments
We gave the public the opportunity to
participate in developing this SNPRM.
We considered the comments received.
Requests To Adopt the Actions of EASA
Airworthiness Directive 2014–0221,
Dated September 30, 2014, and Certain
Service Bulletins
Airbus requested that we revise the
NPRM to adopt the requirements of
EASA Airworthiness Directive 2014–
0221, dated September 30, 2014; Airbus
Service Bulletin A320–32–1390,
Revision 03, dated July 3, 2014; and
Airbus Service Bulletin A320–32–1407
Revision 01, dated July 3, 2014. Airbus
stated that EASA issued a global
airplane flight manual (AFM) TR to
mandate updated operational
procedures. US Airways requested that
we reference Airbus Service Bulletin
A320–32–1407, Revision 01, dated July
3, 2014, and a new AFM procedure
referenced in ‘‘FOT 999–0032/14.’’
We agree with the commenters’
requests. EASA Airworthiness Directive
2014–0221, dated September 30, 2014,
requires, among other things, a revised
operational AFM procedure, and
hydraulic flushing prior to any
installation of a post-modification MLG
door actuator. We have revised
paragraphs (j), (k), (l), (m), and (w) as
designated in the NPRM (paragraphs (j),
(k), (l), (m), and (x) in this SNPRM)) to
reference Airbus Service Bulletin A320–
32–1390, Revision 03, dated July 3,
2014; and paragraphs (r), (t), (u), (w),
and (x) as designated in the NPRM
(paragraphs (r), (u), (v), (x), and (y) in
this SNPRM)) to reference Airbus
Service Bulletin A320–32–1407,
Revision 01, dated July 3, 2014; as the
appropriate sources of service
information for accomplishing the
proposed actions.
Lhorne on DSK5TPTVN1PROD with PROPOSALS
Request To Not Mandate the Actions in
Airbus Service Bulletin A320–32–1407,
Revision 01, Dated July 3, 2014
United Airlines requested that we not
require the actions in Airbus Service
Bulletin A320–32–1407, Revision 01,
dated July 3, 2014. United Airlines
stated that Airbus Service Bulletin
A320–32–1407, Revision 01, dated July
3, 2014, recommends that operators
flush the affected hydraulic system.
United Airlines stated that it disagrees
with this proposed action and explained
that Airbus instituted this requirement
to flush the hydraulic system as it failed
to recommend the removal, inspection,
and cleaning of the restrictors during
the modification of the MLG door
actuator to the part number (P/N)
114122014 configuration. United
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
Airlines also stated that it has opted to
overhaul the MLG door actuators as well
as perform the modification described
in Airbus Service Bulletin A320–32–
1407, dated May 14, 2013. United
Airlines explained that this overhaul
requires that the restrictors (P/N
114122233 and P/N 114122232) and
transfer pipe be removed, inspected,
and cleaned. United Airlines stated that
it is of the opinion that flushing the
hydraulic system is not required as
there is no contamination present in the
restrictors or the transfer pipe.
We disagree with the commenter’s
request. Airbus informed the FAA that
debris can leave the damaged actuator
and remain in the hydraulic lines
connected to the door actuator. Flushing
of the hydraulic system is required to
prevent debris from entering the new
actuator. If debris enters the new
actuator, its performance can be
affected. The flow rate during normal
operation is insufficient to ensure
complete flushing of the debris to the
hydraulic low pressure filter within a
few door cycles. Therefore, a specific
maintenance procedure has been
defined and introduced in Airbus
Service Bulletin A320–32–1407,
Revision 01, dated July 3, 2014; and
General Electric Service Bulletin
114122–32–105, Revision 2, dated June
24, 2014. EASA has issued AD 2014–
0221, dated September 30, 2014,
requiring flushing of the affected
hydraulic system in accordance with
Airbus Service Bulletin A320–32–1407,
Revision 01, dated July 3, 2014.
Request To Provide Credit for Previous
Actions
US Airways requested that we
provide credit for the actions required
by paragraphs (t) and (u) of the
proposed AD (paragraphs (u) and (v) of
this SNPRM)), if those actions were
done before the effective date of the AD
using Airbus Service Bulletins A320–
32–1407, dated May 14, 2013, or
Revision 01, dated July 3, 2014; or
General Electric Service Bulletin
114122–32–105, dated January 17, 2013.
We partially agree with the
commenter’s request. In this SNPRM,
paragraph (aa) already provides credit
for General Electric Service Bulletin
114122–32–105, dated January 17, 2013,
for the actions in paragraphs (u) and (v)
done prior to the effective date of the
final rule. We do not agree with giving
credit for Airbus Service Bulletin A320–
32–1407, dated May 14, 2013; or
Revision 01, dated July 3, 2014; because
those service bulletins do not require
flushing the hydraulic system prior to
the installation of P/N 114122014. We
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
have not changed the proposed AD in
this regard.
FAA’s Determination and Requirements
of This SNPRM
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.
Certain changes described above
expand the scope of the NPRM. As a
result, we have determined that it is
necessary to reopen the comment period
to provide additional opportunity for
the public to comment on this SNPRM.
Explanation of ‘‘RC’’ Procedures and
Tests in Service Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directives Implementation Aviation
Rulemaking Committee (ARC), to
enhance the AD system. One
enhancement was a new process for
annotating which procedures and tests
in the service information are required
for compliance with an AD.
Differentiating these procedures and
tests from other tasks in the service
information is expected to improve an
owner’s/operator’s understanding of
crucial AD requirements and help
provide consistent judgment in AD
compliance. The procedures and tests
identified as Required for Compliance
(RC) in any service information have a
direct effect on detecting, preventing,
resolving, or eliminating an identified
unsafe condition.
As specified in a NOTE under the
Accomplishment Instructions of the
specified Airbus service information,
procedures and tests identified as RC
must be done to comply with the
proposed AD. However, procedures and
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 alternative method of compliance
(AMOC), provided the procedures and
tests identified as RC can be done and
the airplane can be put back in a
serviceable condition. Any substitutions
or changes to procedures or tests
E:\FR\FM\22SEP1.SGM
22SEP1
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
identified as RC will require approval of
an AMOC.
Changes to the Proposed AD
This SNPRM makes the following
changes to the NPRM.
We have moved the credit for Airbus
Service Bulletin A320–32–1309, dated
March 7, 2006, specified in paragraph
(g) of AD 2011–13–11, into paragraph
(aa)(1) of the proposed AD.
We have reformatted and redesignated
three tables as figures to comply with
requirements of the Office of the Federal
Register, as follows:
• ‘‘Table 1 to Paragraph (p) of this
AD—Affected Part Numbers’’ is ‘‘Figure
2 to Paragraph (p) of this AD—Affected
Part Numbers;’’
• ‘‘Table 2 to Paragraph (v) of this
AD—Affected Part Numbers’’ is ‘‘Figure
3 to Paragraph (v) of this AD—Affected
Part Numbers;’’ and
• ‘‘Table 3 to Paragraph (z) of this
AD—Affected Part Numbers’’ is ‘‘Figure
4 to Paragraph (z) of this AD.’’
Lhorne on DSK5TPTVN1PROD with PROPOSALS
Costs of Compliance
We estimate that this SNPRM affects
953 airplanes of U.S. registry.
The actions that are required by AD
2011–13–11, and retained in this
SNPRM, take about 7 work-hours per
product, per inspection cycle, 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 2011–13–11 is $595 per product.
The actions that are required by AD
2013–16–09, and retained in this
SNPRM, take about 3 work-hours per
product, per inspection cycle, at an
average labor rate of $85 per work-hour.
Based on these figures, the estimated
cost of the actions that were required by
AD 2013–16–09 is $255 per product.
We also estimate that it would take
about 19 work-hours per product to
comply with the basic requirements of
this SNPRM. The average labor rate is
$85 per work-hour. Required parts
would cost about $17,140 per product.
Based on these figures, we estimate the
cost of this SNPRM on U.S. operators to
be $17,873,515, or $18,755 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 3 work-hours, for a cost of $255
per product. We have no way of
determining the number of aircraft that
might need these actions.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
Authority for This Rulemaking
§ 39.13
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
■
■
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directives
(AD) 2011–13–11, Amendment 39–
16734 (76 FR 37241, June 27, 2011)
(‘‘AD 2011–13–11’’); and AD 2013–16–
09, Amendment 39–17547 (78 FR
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
57125
48286, August 8, 2013) (‘‘AD 2013–16–
09’’); and
■ b. Adding the following new AD:
Airbus: Docket No. FAA–2014–0529;
Directorate Identifier 2013–NM–260–AD.
(a) Comments Due Date
We must receive comments by November
6, 2015.
(b) Affected ADs
This AD replaces AD 2011–13–11,
Amendment 39–16734 (76 FR 37241, June
27, 2011) (‘‘AD 2011–13–11’’); and AD 2013–
16–09, Amendment 39–17547 (78 FR 48286,
August 8, 2013) (‘‘AD 2013–16–09’’).
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of
this AD, all manufacturer serial numbers.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –231,
–232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by a determination
that the inspection interval of the main
landing gear (MLG) door opening sequence
must be reduced. We are issuing this AD to
detect and correct deterioration of the
damping ring and associated retaining ring of
the MLG door actuator, which can
sufficiently increase the friction inside the
actuator to restrict opening of the MLG door
by gravity, during operation of the landing
gear alternate (free-fall) extension system.
This condition could prevent the full
extension and/or down-locking of the MLG,
possibly resulting in MLG collapse during
landing and consequent damage to the
aeroplane and injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Repetitive Inspections/
Replacement, With a Formatting Change
This paragraph restates the requirements of
paragraph (g) of AD 2011–13–11, with a
formatting change. At the time specified in
paragraph (g)(1) or (g)(2) of this AD, as
applicable: Do a general visual inspection of
the operation of the MLG door opening
sequence to determine if a defective actuator
is installed by doing all the applicable
actions, including replacing the door
actuator, as applicable, specified in the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1309, Revision 01,
dated June 19, 2006. Do all applicable
replacements before further flight. Repeat the
inspection thereafter at intervals not to
exceed 900 flight cycles. Doing the
E:\FR\FM\22SEP1.SGM
22SEP1
57126
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
inspection required by paragraph (l) of this
AD terminates the requirements of this
paragraph.
(1) For airplanes on which a record of the
total number of flight cycles on the MLG door
actuator is available: Before the accumulation
of 3,000 total flight cycles on the MLG door
actuator, or within 800 flight cycles after
April 27, 2007 (the effective date of AD
2007–06–18, Amendment 39–14999 (72 FR
13681, March 23, 2007)), whichever is later.
(2) For airplanes on which a record of the
total number of flight cycles on the MLG door
actuator is not available: Within 800 flight
cycles after April 27, 2007 (the effective date
of AD 2007–06–18).
(3) For the purposes of this AD, a general
visual inspection is: ‘‘A visual examination
of an interior or exterior area, installation, or
assembly to detect obvious damage, failure,
or irregularity. This level of inspection is
made from within touching distance unless
otherwise specified. A mirror may be
necessary to enhance visual access to all
exposed surfaces in the inspection area. This
level of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
(h) Retained Provision Regarding Reporting/
Parts Return, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2011–13–11, with no
changes. Although the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1309, Revision 01, dated June 19, 2006,
specify submitting certain information to the
manufacturer and sending defective actuators
back to the component manufacturer for
investigation, this AD does not include those
requirements.
(i) Retained Revision of the Airplane Flight
Manual (AFM), With Formatting Changes
This paragraph restates the requirements of
paragraph (i) of AD 2011–13–11, with
formatting changes. Within 14 days after July
12, 2011 (the effective date of AD 2011–13–
11), revise the Emergency Procedure Section
of the AFM to incorporate the information in
figure 1 to paragraph (i) of this AD. This may
be done by inserting a copy of this AD into
the AFM. When a statement identical to that
in figure 1 to paragraph (i) of this AD has
been included in the Emergency Procedure
Section of the general revisions of the AFM,
the general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM. Doing the actions
required by paragraph (t) of this AD
terminates the requirements of this
paragraph.
FIGURE 1 TO PARAGRAPH (I) OF THIS AD—AFM REVISION
Lhorne on DSK5TPTVN1PROD with PROPOSALS
• If ECAM triggers the ‘‘L/G GEAR NOT DOWNLOCKED’’ warning, apply the following procedure:
Recycle landing gear.
• If unsuccessful after 2 min:
Extend landing gear by gravity. Refer to ABN–32 L/G GRAVITY EXTENSION.
(j) Retained Repetitive Checks, With New
Optional Actions and New Service
Information
This paragraph restates the requirements of
paragraph (j) of AD 2011–13–11, with new
optional actions and new service
information. Within 14 days after July 12,
2011 (the effective date of AD 2011–13–11),
or before the accumulation of 800 total flight
cycles, whichever occurs later, check the post
flight report (PFR) for centralized fault
display system (CFDS) messages triggered
within the last 8 days, in accordance with
paragraph 4.2.1 of Airbus All Operators Telex
(AOT) A320–32A1390, dated February 10,
2011. Repeat the check thereafter at intervals
not to exceed 8 days or 5 flight cycles,
whichever occurs later. If done in accordance
with a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, the use of an
alternative method to check the PFR for
CFDS messages (e.g., AIRMAN) is acceptable
in lieu of this check if the messages can be
conclusively determined from that method.
Repetitive inspections of the door opening
sequence of the left-hand (LH) and right-hand
(RH) doors of the MLG, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–32–1390, Revision 03,
dated July 13, 2014, are an acceptable
method of compliance for the actions
required by this paragraph. Repetitive
inspections of the door opening sequence of
the LH and RH doors of the MLG of an
airplane, as required by paragraph (p) of this
AD, is an acceptable method to comply with
the requirements of this paragraph.
(k) Retained On-Condition Inspection, With
New Service Information
This paragraph restates the requirements of
paragraph (k) of AD 2011–13–11, with new
service information. If, during any check
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
required by paragraph (j) of this AD, a pair
of specific CFDS messages specified in
paragraph 4.2.1 of Airbus AOT A320–
32A1390, dated February 10, 2011, has been
triggered by both landing gear control and
indication units (LGCIU) for the same flight,
before further flight, inspect the door opening
sequence of the affected doors of the MLG for
discrepancies (i.e., if any condition specified
in steps (a) through (d) of paragraph 4.2.2 of
Airbus AOT A320–32A1390, dated February
10, 2011, is not met; or if any door actuator
fails any inspection check specified in Airbus
Service Bulletin A320–32–1390, Revision 03,
dated July 13, 2014). Do the inspection in
accordance with paragraph 4.2.2 of Airbus
AOT A320–32A1390, dated February 10,
2011; or the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1390,
Revision 03, dated July 13, 2014. As of the
effective date of this AD, use only Airbus
Service Bulletin A320–32–1390, Revision 03,
dated July 13, 2014, for the actions required
by this paragraph.
(l) Retained Repetitive Inspections, With
New Service Information, New Optional
Actions, and Reduced Compliance Times
This paragraph restates the requirements of
paragraph (l) of AD 2011–13–11, with new
service information, new optional actions,
and reduced compliance times. At the
applicable time specified in paragraph (l)(1)
or (l)(2) of this AD: Inspect the door opening
sequence of the LH and RH doors of the MLG
for discrepancies (i.e., if any condition
specified in steps (a) through (d) of paragraph
4.2.2 of Airbus AOT A320–32A1390, dated
February 10, 2011, is not met; or if any door
actuator fails any inspection check specified
in the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1390,
Revision 03, dated July 13, 2014). Do the
inspection in accordance with the
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
instructions of paragraph 4.2.2 of Airbus
AOT A320–32A1390, dated February 10,
2011; or the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1390,
Revision 03, dated July 13, 2014. As of the
effective date of this AD, use only Airbus
Service Bulletin A320–32–1390, Revision 03,
dated July 13, 2014, for the actions required
by this paragraph. Repeat the inspection
within 8 days or 5 flight cycles after the
effective date of this AD, whichever occurs
later, without exceeding 425 flight cycles
since the most recent inspection; and
thereafter repeat the inspection at intervals
not to exceed 8 days or 5 flight cycles,
whichever occurs later. In addition,
whenever any airplane is not operated for a
period longer than 8 days, do the inspection
before further flight. Doing this inspection
terminates the requirements of paragraph (g)
of this AD. Repetitive inspections of the door
opening sequence of the LH and RH doors of
the MLG of an airplane, as required by
paragraph (p) of this AD, is an acceptable
method to comply with the requirements of
this paragraph.
(1) For airplanes on which an inspection
required by paragraph (g) of this AD has been
done as of July 12, 2011 (the effective date
of AD 2011–13–11): Within 800 flight cycles
after doing the most recent inspection
required by paragraph (g) of this AD, or
within 100 flight cycles after July 12, 2011,
whichever occurs later.
(2) For airplanes on which an inspection
required by paragraph (g) of this AD has not
been done as of July 12, 2011 (the effective
date of AD 2011–13–11): Within 800 flight
cycles after July 12, 2011.
(m) Retained Replacement, With New
Service Information
This paragraph restates the requirements of
paragraph (m) of AD 2011–13–11, with new
E:\FR\FM\22SEP1.SGM
22SEP1
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
service information. If any discrepancy (i.e.,
if any condition specified in steps (a) through
(d) of paragraph 4.2.2 of Airbus AOT A320–
32A1390, dated February 10, 2011, is not
met; or if any door actuator fails any
inspection check specified in the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1390, Revision 03,
dated July 13, 2014) is found during any
inspection required by paragraph (k) or (l) of
this AD, before further flight, replace the
affected MLG door actuator with a new MLG
door actuator, in accordance with the
instructions of Airbus AOT A320–32A1390,
dated February 10, 2011; or Airbus Service
Bulletin A320–32–1390, Revision 03, dated
July 13, 2014. As of the effective date of this
AD, use only Airbus Service Bulletin A320–
32–1390, Revision 03, dated July 13, 2014, to
do the actions required by this paragraph.
(n) Retained Statement of No Terminating
Action for Certain Requirements, With No
Changes
This paragraph restates the statement of
paragraph (n) of AD 2011–13–11, with no
changes. Replacement of the MLG door
actuator as required by paragraph (m) of this
AD is not a terminating action for the
repetitive actions required by paragraphs (j)
and (l) of this AD.
Lhorne on DSK5TPTVN1PROD with PROPOSALS
(o) Retained Configuration and Part Number
Determination, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2013–16–09, with no
changes. At the later of the compliance times
specified in paragraphs (o)(1) and (o)(2) of
this AD: Do an inspection to determine the
configuration (modification status) of the
airplane and identify the part number of the
LH and RH LGCIU and MLG door actuators.
A review of the airplane delivery or
maintenance records is acceptable for
compliance with the requirements of this
paragraph provided the airplane
configuration and installed components can
be conclusively determined from that review.
(1) Prior to the accumulation of 800 total
flight cycles since first flight of the airplane.
(2) Within 14 days after August 23, 2013
(the effective date of AD 2013–16–09).
(p) Retained MLG Door Opening Sequence
Repetitive Inspections, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2013–16–09, with no
changes. If, during the determination and
identification required by paragraph (o) of
this AD, the configuration of the airplane is
determined to be post-Airbus Modification
39303 or post-Airbus Service Bulletin A320–
32–1409 (Interlink Communication ARINC
429 installed), and both an LGCIU and a MLG
door actuator are installed with a part
number listed in figure 2 to paragraph (p) of
this AD: Except as provided by paragraph (s)
of this AD, at the later of the compliance
times specified in paragraphs (o)(1) and (o)(2)
of this AD, and thereafter at intervals not to
exceed 8 days or 5 flight cycles, whichever
occurs later, do an inspection of the door
opening sequence of the LH and RH MLG
doors, in accordance with the instructions of
Airbus AOT A32N001–13, dated June 24,
2013.
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
FIGURE 2 TO PARAGRAPH (P) OF THIS
AD—AFFECTED PART NUMBERS
Component name
LGCIU (LH and RH)
MLG door actuator ...
Part number
80–178–02–88012
80–178–03–88013
114122006
114122007
114122009
114122010
114122011
114122012
(q) Retained MLG Door Opening Sequence
Corrective Action, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2013–16–09, with no
changes. If a slow door operation or restricted
extension is found during any inspection
required by paragraph (p) of this AD: Before
further flight, replace the affected MLG door
actuator with a new or serviceable actuator,
in accordance with the instructions of Airbus
AOT A32N001–13, dated June 24, 2013.
(r) Retained Terminating Action Limitation
for Certain Actions, With New Service
Information
This paragraph restates the requirements of
paragraph (j) of AD 2013–16–09, with new
service information. Replacement of a MLG
door actuator, as required by paragraph (q) of
this AD, does not constitute terminating
action for the repetitive inspections required
by paragraph (p) of this AD, unless MLG door
actuators having P/N 114122014 are installed
on both LH and RH sides, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–32–1407, dated May
14, 2013; or Airbus Service Bulletin A320–
32–1407, Revision 01, dated July 3, 2014. As
of the effective date of this AD, use only
Airbus Service Bulletin A320–32–1407,
Revision 01, dated July 3, 2014, for the
actions required by this paragraph.
(s) Retained Repetitive Inspection Exception,
With No Changes
This paragraph restates the requirements of
paragraph (k) of AD 2013–16–09, with no
changes. Airplanes on which the LGCIU
interlink is disconnected (Airbus
Modification 155522 applied in production,
or modified in-service in accordance with the
instructions of Airbus AOT A32N001–13,
dated June 24, 2013), or on which MLG door
actuators having P/N 114122014 are installed
on both LH and RH sides (Airbus
Modification 153655 applied in production,
or modified in-service as described in Airbus
Service Bulletin A320–32–1407), are not
required to do the actions required by
paragraph (p) of this AD, provided that the
airplane is not modified to a configuration as
defined in paragraph (p) of this AD.
(t) New Revision of the AFM
Within 14 days after the effective date of
this AD, revise the Emergency Procedure
Section of the AFM to incorporate Airbus
A318/A319/A320/A321 Temporary Revision
(TR) TR437, L/G GEAR NOT
DOWNLOCKED, Issue 1.0, dated May 23,
2014. When this TR has been included in
general revisions of the AFM, the general
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
57127
revisions may be inserted in the AFM,
provided the relevant information in the
general revision is identical to that in this
TR, and the copy of this TR may be removed
from the AFM. Doing the action required by
this paragraph terminates the actions
required by paragraph (i) of this AD.
(u) New Replacement of MLG Door Actuator
Having P/N 114122012
Within 12 months after the effective date
of this AD: Replace each MLG door actuator
having P/N 114122012 with a MLG door
actuator having P/N 14122014, and flush the
affected hydraulic system, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–32–1407,
Revision 01, dated July 3, 2014; or modify
each actuator, including doing all applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of General Electric Service
Bulletin 114122–32–105, Revision 2, dated
June 24, 2014; except where General Electric
Service Bulletin 114122–32–105, Revision 2,
dated June 24, 2014, specifies to contact the
manufacturer, before further flight, repair
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(v) New Replacement of Certain Other MLG
Door Actuators
Within 24 months after the effective date
of this AD: Replace each MLG door actuator
having a part number listed in figure 3 to
paragraph (v) of this AD, except P/N
114122012, with a MLG door actuator having
P/N 14122014, and flush the affected
hydraulic system, in accordance with
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1407, Revision 01,
dated July 3, 2014; or modify each actuator,
including doing all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of General Electric Service
Bulletin 114122–32–105, Revision 2, dated
June 24, 2014; except where General Electric
Service Bulletin 114122–32–105, Revision 2,
dated June 24, 2014, specifies to contact the
manufacturer, before further flight, repair
using a method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the EASA; or
Airbus’s EASA DOA.
FIGURE 3 TO PARAGRAPH (V) OF THIS
AD—AFFECTED PART NUMBERS
Component name
MLG door actuator .................
Part number
114122006
114122007
114122009
114122010
114122011
114122012
(w) New Terminating Action
Modification of an airplane as required by
paragraphs (u) and (v) of this AD, as
applicable, constitutes terminating action for
E:\FR\FM\22SEP1.SGM
22SEP1
57128
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
all repetitive actions (PFR monitoring checks
and inspections) required by this AD for that
airplane.
(x) New Conditional Terminating Action
Replacement of a MLG door actuator as
required by paragraphs (m) and (q) of this
AD; or corrective actions as specified in
Airbus AOT A320–32A1390, dated February
10, 2011; or replacement of a MLG door
actuator as specified in Airbus Service
Bulletin A320–32–1390, Revision 03, dated
July 13, 2014; does not constitute terminating
action for the repetitive inspections required
by paragraphs (j), (l), and (p) of this AD,
unless MLG door actuators having P/N
114122014 are installed on both LH and RH
sides, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1407, Revision 01,
dated July 3, 2014.
(y) New Exception to AD Requirements
(1) An airplane on which MLG door
actuators having P/N 114122014 are installed
on both LH and RH sides (Airbus
Modification 153655 applied in production,
or modified in service as specified in Airbus
Service Bulletin A320–32–1407, dated May
14, 2013; Airbus Service Bulletin A320–32–
1407, Revision 01, dated July 3, 2014;
General Electric Service Bulletin 114122–32–
105, dated January 17, 2013; or General
Electric Service Bulletin 114122–32–105,
Revision 1, dated March 26, 2013; or General
Electric Service Bulletin 114122–32–105,
Revision 2, dated June 24, 2014); is not
affected by the requirements of paragraphs (j)
through (v) of this AD, provided that no MLG
door actuator with a part number in figure 3
to paragraph (v) of this AD has been installed
on that airplane since first flight, or since
modification, as applicable.
(2) An airplane in the configuration
specified in paragraph (y)(1) of this AD, and
with flight warning computers having P/N
350E053021212 (H2F7) installed (Airbus
Modification 153741 applied in production,
or modified in service as specified in Airbus
Service Bulletin A320–31–1414), is not
affected by the requirement of paragraph (t)
of this AD and, following modification,
Airbus A318/A319/A320/A321 TR TR437, L/
G GEAR NOT DOWNLOCKED, Issue 1.0,
dated May 23, 2014 (if inserted), may be
removed from the AFM of that airplane.
(z) New Parts Installation Prohibitions
(1) Except as specified in paragraph (z)(2)
of this AD, as of the effective date of this AD,
do not install on any airplane a MLG door
actuator having a part number listed in figure
3 to paragraph (v) of this AD.
(2) For an airplane subject to the
requirements of paragraphs (u) and (v) of this
AD, as applicable, do not install a MLG door
actuator having a part number listed in figure
3 to paragraph (v) of this AD after
modification of the airplane.
(3) Except as specified in paragraph (z)(4)
of this AD, as of the effective date of this AD,
do not install on any airplane a flight
warning computer (FWC) having a part
number listed in figure 4 to paragraph (z) of
this AD.
(4) For an airplane subject to the
requirements of paragraphs (u) and (v) of this
AD, as applicable, do not install a FWC
having a part number listed in figure 4 to
paragraph (z) of this AD after modification of
the airplane.
FIGURE 4 TO PARAGRAPH (Z) OF THIS AD—AFFECTED PART NUMBERS
Component name
Part number
Lhorne on DSK5TPTVN1PROD with PROPOSALS
Flight warning computer ..............................................................................................................................................
(aa) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g) of this AD,
if those actions were performed before April
27, 2007 (the effective date of AD 2007–06–
18), using Airbus Service Bulletin A320–32–
1309, dated March 7, 2006. This service
information is not incorporated by reference
in this AD.
(2) This paragraph provides credit for
actions required by paragraphs (k), (l), and
(m) of this AD, if those actions were
performed before the effective date of this AD
using Airbus Service Bulletin A320–32–1390,
Revision 01, dated September 21, 2011; or
Revision 02, dated October 23, 2013. Airbus
Service Bulletin A320–32–1390, Revision 01,
dated September 21, 2011, was incorporated
by reference in AD 2011–13–11. Airbus
Service Bulletin A320–32–1390, Revision 02,
dated October 23, 2013, is not incorporated
by reference in this AD.
(3) This paragraph provides credit for
actions required by paragraphs (u) and (v) of
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
this AD, if those actions were performed
before the effective date of this AD using
General Electric Service Bulletin 114122–32–
105, dated January 17, 2013; or General
Electric Service Bulletin 114122–32–105,
Revision 1, dated March 26, 2013. This
service information is not incorporated by
reference in this AD.
(bb) 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,
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
350E016187171 (C5)
350E017238484 (H1D1)
350E017248685 (H1D2)
350E017251414 (H1E1)
350E017271616 (H1E2)
350E018291818 (H1E3CJ)
350E018301919 (H1E3P)
350E018312020 (H1E3Q)
350E053020202 (H2E2)
350E053020303 (H2E3)
350E053020404 (H2E4)
350E053020606 (H2F2)
350E053020707 (H2F3)
350E053021010 (H2F3P)
350E053020808 (H2F4)
350E053020909 (H2F5)
350E053021111 (H2F6)
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Required for Compliance (RC): If any
Airbus 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
E:\FR\FM\22SEP1.SGM
22SEP1
Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules
procedures and tests identified as RC can be
done and the airplane can be put back in a
serviceable condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(3) Contacting the Manufacturer: As of the
effective date of this AD, except as specified
in paragraph (j) of this AD for the use of an
alternative method to check the PFR for
CFDS messages, 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
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(4) Previously Approved AMOCs: AMOCs
approved previously for the AD 2011–13–11
and AD 2013–16–09 are approved as AMOCs
for the corresponding provisions of this AD.
(cc) Special Flight Permits
Special flight permits may be issued in
accordance with sections 21.197 and 21.199
of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the airplane can be
modified (if the operator elects to do so),
provided the MLG remains extended and
locked, and that no MLG recycle is done.
(dd) Related Information
Lhorne on DSK5TPTVN1PROD with PROPOSALS
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0221, dated
September 30, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0529-0003.
(2) For Airbus 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.
(3) For General Electric service information
identified in this AD, contact GE Aviation,
Customer Support Center, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513–552–3272;
email: cs.techpubs@ge.com; Internet: https://
www.geaviation.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.
Issued in Renton, Washington, on August
21, 2015.
Kevin Hull,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–21730 Filed 9–21–15; 8:45 am]
COMMODITY FUTURES TRADING
COMMISSION
17 CFR Part 23
RIN 3038–AE17
Proposal To Amend the Definition of
‘‘Material Terms’’ for Purposes of
Swap Portfolio Reconciliation
Commodity Futures Trading
Commission.
ACTION: Notice of proposed rulemaking.
AGENCY:
The Commodity Futures
Trading Commission (‘‘Commission’’ or
‘‘CFTC’’) proposes to amend a provision
of the Commission’s regulations in
connection with the material terms for
which counterparties must resolve
discrepancies when engaging in
portfolio reconciliation.
DATES: Comments must be received on
or before November 23, 2015.
ADDRESSES: You may submit comments,
identified by RIN 3038–AE17, and
Proposal to Amend the Definition of
‘‘Material Terms’’ for Purposes of Swap
Portfolio Reconciliation by any of the
following methods:
• The agency’s Web site, at https://
comments.cftc.gov. Follow the
instructions for submitting comments
through the Web site.
• Mail: Christopher Kirkpatrick,
Secretary of the Commission,
Commodity Futures Trading
Commission, Three Lafayette Centre,
1155 21st Street NW., Washington, DC
20581.
• Hand Delivery/Courier: Same as
Mail above.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Please submit your comments using
only one method.
All comments must be submitted in
English, or if not, accompanied by an
English translation. Comments will be
posted as received to https://
www.cftc.gov. You should submit only
information that you wish to make
available publicly. If you wish the
Commission to consider information
that you believe is exempt from
disclosure under the Freedom of
Information Act, a petition for
confidential treatment of the exempt
information may be submitted according
to the procedures established in § 145.9
of the Commission’s regulations.1
The Commission reserves the right,
but shall have no obligation, to review,
pre-screen, filter, redact, refuse or
remove any or all of your submission
SUMMARY:
BILLING CODE 4910–13–P
1 17 CFR 145.9. Commission regulations referred
to herein are found at 17 CFR Chapter I.
VerDate Sep<11>2014
14:51 Sep 21, 2015
Jkt 235001
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
57129
from https://www.cftc.gov that it may
deem to be inappropriate for
publication, such as obscene language.
All submissions that have been redacted
or removed that contain comments on
the merits of the rulemaking will be
retained in the public comment file and
will be considered as required under the
Administrative Procedure Act and other
applicable laws, and may be accessible
under the Freedom of Information Act.
FOR FURTHER INFORMATION CONTACT:
Frank N. Fisanich, Chief Counsel, 202–
418–5949, ffisanich@cftc.gov; Katherine
S. Driscoll, Associate Chief Counsel,
202–418–5544, kdriscoll@cftc.gov;
Gregory Scopino, Special Counsel, 202–
418–5175, gscopino@cftc.gov, Division
of Swap Dealer and Intermediary
Oversight, Commodity Futures Trading
Commission, Three Lafayette Centre,
1155 21st Street NW., Washington, DC
20581.
SUPPLEMENTARY INFORMATION:
I. Background
On September 11, 2012, the
Commission published in the Federal
Register final rules § 23.500 through
§ 23.505 2 establishing requirements for
the timely and accurate confirmation of
swaps, the reconciliation and
compression of swap portfolios, and
documentation of swap trading
relationships between swap dealers
(‘‘SDs’’),3 major swap participants
(‘‘MSPs’’),4 and their counterparties.
These regulations were promulgated by
the Commission pursuant to the
authority granted under Sections
4s(h)(1)(D), 4s(h)(3)(D), and 4s(i) of the
Commodity Exchange Act (the ‘‘CEA’’),5
2 Confirmation, Portfolio Reconciliation, Portfolio
Compression, and Swap Trading Relationship
Documentation Requirements for Swap Dealers and
Major Swap Participants, 77 FR 55904 (Sept. 11,
2012) (hereinafter, ‘‘Portfolio Reconciliation Final
Rule’’).
3 Generally, an SD is any person who, in addition
to transacting in a notional amount of swaps in
excess of specified de minimis thresholds, holds
itself out as a dealer in swaps, makes a market in
swaps, regularly enters into swaps with
counterparties as an ordinary course of business for
its own account, or engages in any activity causing
it to be commonly known in the trade as a dealer
or market maker in swaps. See 7 U.S.C. 1a(49); 17
CFR 1.3(ggg).
4 Generally, an MSP is any non-dealer that
maintains a substantial position in swaps for any
of the specified major swap categories, whose
outstanding swaps create substantial counterparty
exposure that could have serious adverse effects on
the financial stability of the United States banking
system or financial markets, or any financial entity
that is highly leveraged relative to the amount of
capital such entity holds and that is not subject to
capital requirements established by an appropriate
Federal banking agency and maintains a substantial
position in outstanding swaps in any major swap
category. See 7 U.S.C. 1a(33); 17 CFR 1.3(hhh).
5 7 U.S.C. 6s(h)(1)(D), 6s(h)(3)(D) and 6s(i).
E:\FR\FM\22SEP1.SGM
22SEP1
]]>Agencies
[Federal Register Volume 80, Number 183 (Tuesday, September 22, 2015)]
[Proposed Rules]
[Pages 57122-57129]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21730]
[[Page 57122]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-260-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for all Airbus Model A318, A319, A320, and A321 series airplanes.
The NPRM proposed to supersede Airworthiness Directives (AD) 2011-13-11
and AD 2013-16-09. AD 2011-13-11 currently requires an amendment of the
airplane flight manual (AFM), repetitive checks of specific centralized
fault display system (CFDS) messages, an inspection of the opening
sequence of the main landing gear (MLG) door actuator for discrepancies
if certain messages are found, and corrective actions if necessary. AD
2013-16-09 currently requires an inspection to determine airplane
configuration and part numbers of the landing gear control interface
unit and MLG door actuators; and, for affected airplanes, repetitive
inspections of the opening sequence of the MLG door actuator, and
replacement of the MLG door actuator if necessary; and provides
optional terminating action for the repetitive inspections. The NPRM
was prompted by a determination that the interval of the MLG door
opening sequence inspection must be reduced. The NPRM proposed to
reduce the interval of the MLG door opening sequence inspection, and
also to replace or modify certain MLG door actuators. This action
revises the NPRM by adding a flushing procedure to be performed when
installing a new MLG door actuator. We are proposing this supplemental
NPRM (SNPRM) to detect and correct deterioration of the damping ring
and associated retaining ring of the MLG door actuator, which can
sufficiently increase the friction inside the actuator to restrict
opening of the MLG door by gravity, during operation of the landing
gear alternate (free-fall) extension system. This condition could
prevent the full extension and/or down-locking of the MLG, possibly
resulting in MLG collapse during landing and consequent damage to the
airplane and injury to occupants. Since these actions impose an
additional burden over those proposed in the NPRM, we are reopening the
comment period to allow the public the chance to comment on these
proposed changes.
DATES: We must receive comments on this SNPRM by November 6, 2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For Airbus service information identified in this proposed 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. For General Electric service information
identified in this AD contact GE Aviation, Customer Support Center, 1
Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; email:
cs.techpubs@ge.com; Internet: https://www.geaviation.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-2014-
0529; 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
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-2014-0529;
Directorate Identifier 2013-NM-260-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
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 A318,
A319, A320, and A321 series airplanes. The NPRM published in the
Federal Register on August 13, 2014 (79 FR 47395; corrected August 27,
2014 (79 FR 51117)) (``the NPRM''). The NPRM proposed to supersede AD
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011) (``AD 2011-
13-11''); and AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8,
2013) (``AD 2013-16-09''). AD 2011-13-11 currently requires an
amendment of the AFM, repetitive checks of specific CFDS messages, an
inspection of the opening sequence of the MLG door actuator for
discrepancies if certain messages are found, and corrective actions if
necessary. AD 2013-16-09 currently requires an inspection to determine
airplane configuration and part numbers of the landing gear control
interface unit and MLG door actuators; and, for affected airplanes,
repetitive inspections of the opening sequence of the MLG door
actuator, and replacement of the MLG door actuator if necessary; and
provides optional terminating action for the repetitive inspections.
The NPRM was prompted by a determination that the interval of the MLG
door opening sequence inspection must be reduced. The NPRM proposed to
reduce the interval of the MLG door opening
[[Page 57123]]
sequence inspection, and also to replace or modify certain MLG door
actuators.
Actions Since Previous NPRM Was Issued
Since we issued the NPRM, we have determined that a flushing
procedure must be performed when installing a new MLG door actuator.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0221, dated September 30, 2014 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on all Airbus Model A318,
A319, A320, and A321 series airplanes. The MCAI states:
Some operators reported slow operation of the main landing gear
(MLG) door opening/closing sequence, leading to the generation of
[electronic centralized aircraft monitor] ECAM warnings during the
landing gear retraction or extension sequence.
Investigations showed that the damping ring and associated
retaining ring of the MLG door actuator may deteriorate. The
resultant debris increases the friction inside the actuator which
can be sufficiently high to restrict opening of the MLG door by
gravity, during operation of the landing gear alternate (freefall)
extension system.
This condition, if not corrected, could prevent the full
extension and/or down locking of the MLG, possibly resulting in MLG
collapse during landing or rollout and consequent damage to the
aeroplane and injury to occupants.
[An EASA AD] was issued [and later revised] to require
repetitive inspections of the opening sequence of the MLG door in
order to identify the affected actuators, and to introduce as an
optional terminating action Airbus production Modification (mod)
38274 and associated [Airbus] Service Bulletin (SB) A320-32-1338,
which incorporate an improved retaining ring, located on the piston
rod's extension end, and a new piston rod with machined shoulder to
accommodate the thicker section of the modified retaining ring.
After in-service introduction of the new MLG door actuator, Part
Number (P/N) 114122012 (Post-mod 38274--SB A320-32-1338), several
operators reported failures of internal parts of the MLG door
actuator. Investigations confirmed that these failures could result
in slow extension of the actuator rod, delaying the MLG door
operation, or possibly stopping just before the end of the stroke,
preventing the door to reach the fully open position.
[An EASA AD], which superseded EASA AD 2006-0112R1 [https://ad.easa.europa.eu/blob/easa_ad_2006_0112_R1_superseded.pdf/AD_2006-0112R1_1], was issued [and later revised] to require amendment of
the applicable Airplane Flight Manual (AFM), repetitive checks of
specific Centralized Fault Display System (CFDS) messages,
repetitive inspections of the opening sequence of the MLG door
actuator and, depending on findings, corrective action(s).
Since EASA AD 2011-0069R1 [https://ad.easa.europa.eu/blob/easa_ad_2011_0069_R1_superseded.pdf/AD_2011-0069R1_1] was issued,
Airbus introduced a reinforced MLG door actuator P/N 114122014 (mod
153655). Airbus issued SB A320-32-1407 containing instructions for
in-service replacement of the affected MLG door actuators, or
modification of the actuators to the new standard.
In addition, following a recent occurrence with a gear extension
problem, the result of additional analyses by Airbus revealed that
the CFDS expected specific messages may not be generated and as a
result, repetitive checks of messages are not effective for
aeroplanes fitted with landing gear control interface unit (LGCIU)
interlink communication ARINC 429 (applied in production through
Airbus mod 39303, or in service through Airbus SB A320-32-1409), in
combination with LGCIUs 80-178-02-88012 or 80-178-03-88013 in both
positions and at least one MLG door actuator pre-mod 153655 (pre-
Airbus SB A320-32-1407--pre-GE SB 114122-32-105) installed.
Prompted by these findings, EASA issued Emergency AD 2013-0132-E
[https://ad.easa.europa.eu/blob/easa_ad_2013_0132_E_superseded.pdf/EAD_2013-0132-E_1 (which corresponds to FAA AD 2013-16-09)] to
require identification of the affected aeroplanes to establish the
configuration and, for those aeroplanes, repetitive inspections of
the opening sequence of the MLG door actuator and, depending on
findings, replacement of the MLG door actuator. That [EASA] AD also
provided an optional terminating action by disconnection of the
interlink for certain LGCIUs, or in-service modification of the
aeroplane through Airbus SB A320-32-1407 (equivalent to Airbus
production mod 153655).
Since those ADs (EASA AD 2011-0069R1 and EASA AD 2013-0132-E)
were issued, analyses performed by Airbus have revealed that the MLG
door opening sequence inspection interval needed to be reduced, and
that the (previously optional) terminating action needed to be made
mandatory.
Prompted by these findings, EASA issued AD 2013-0288 [https://ad.easa.europa.eu/blob/easa_ad_2013_0288_superseded.pdf/AD_2013-0288_1], retaining the requirements of EASA AD 2011-0069R1 and EASA
AD 2013-0132-E, which were superseded, but with reduced inspection
intervals, and to require replacement or modification, as
applicable, of the affected MLG door actuators as terminating action
to the monitoring and repetitive checks and inspections.
Following introduction of post-mod 153655 MLG door actuators on
in-service aeroplanes, it has been observed that, in case the
removed pre-mod MLG door actuator has internal damage, contamination
of the hydraulic system could have occurred.
This condition, if not detected and corrected, could result in
performance degradation (damping degradation) of the post-mod MLG
door actuator. Testing performed with a new actuator tested in
heavily contaminated hydraulic system did not show abnormal
hydraulic Restriction/blockage. It is thus not requested to perform
this ``flushing procedure'' on aircraft already retrofitted with
std-14 actuators.
In addition, since EASA AD 2013-0288 was issued, the applicable
AFM was revised and repetitive checks of specific CFDS messages are
no longer considered to be required, due to the reduced intervals
required by EASA AD 2013-0288.
For the reasons described above, this [EASA] AD partially
retains the requirements of EASA AD 2013-0288, which is superseded,
introduces improved wording for clarification and requires, in
addition to the revised operational (AFM) procedure, hydraulic
flushing prior to any installation of a post-mod MLG door actuator.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-529-0003.
Related Service Information Under 1 CFR part 51
Airbus has issued Service Bulletins A320-32-1390, Revision 03,
dated July 3, 2014; and A320-32-1407, Revision 01, dated July 3, 2014.
Airbus has also issued A318/A319/A320/A321 Temporary Revision (TR)
TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014, to the
Airplane Flight Manual (AFM).
Airbus Service Bulletin A320-32-1390, Revision 03, dated July 3,
2014, describes procedures for inspecting the operation of the MLG door
opening sequence to determine if an actuator is defective, flushing
contamination from the landing gear extension and retraction system
(LGERS), and replacing the door actuator if necessary.
Airbus Service Bulletin A320-32-1407, Revision 01, dated July 3,
2014, describes procedures for flushing contamination from the LGERS,
and installing new MLG door actuators.
Airbus A318/A319/A320/A321 TR TR437, L/G GEAR NOT DOWNLOCKED, Issue
1.0, dated May 23, 2014, to the AFM updates the procedure used for
incomplete landing gear extension during approach.
General Electric Service Bulletin 114122-32-105, Revision 2, dated
June 24, 2014, describes procedures for conversion of a MLG door
actuator and to remove unwanted material from the hydraulic fluid
route.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section of this
SNPRM.
[[Page 57124]]
Comments
We gave the public the opportunity to participate in developing
this SNPRM. We considered the comments received.
Requests To Adopt the Actions of EASA Airworthiness Directive 2014-
0221, Dated September 30, 2014, and Certain Service Bulletins
Airbus requested that we revise the NPRM to adopt the requirements
of EASA Airworthiness Directive 2014-0221, dated September 30, 2014;
Airbus Service Bulletin A320-32-1390, Revision 03, dated July 3, 2014;
and Airbus Service Bulletin A320-32-1407 Revision 01, dated July 3,
2014. Airbus stated that EASA issued a global airplane flight manual
(AFM) TR to mandate updated operational procedures. US Airways
requested that we reference Airbus Service Bulletin A320-32-1407,
Revision 01, dated July 3, 2014, and a new AFM procedure referenced in
``FOT 999-0032/14.''
We agree with the commenters' requests. EASA Airworthiness
Directive 2014-0221, dated September 30, 2014, requires, among other
things, a revised operational AFM procedure, and hydraulic flushing
prior to any installation of a post-modification MLG door actuator. We
have revised paragraphs (j), (k), (l), (m), and (w) as designated in
the NPRM (paragraphs (j), (k), (l), (m), and (x) in this SNPRM)) to
reference Airbus Service Bulletin A320-32-1390, Revision 03, dated July
3, 2014; and paragraphs (r), (t), (u), (w), and (x) as designated in
the NPRM (paragraphs (r), (u), (v), (x), and (y) in this SNPRM)) to
reference Airbus Service Bulletin A320-32-1407, Revision 01, dated July
3, 2014; as the appropriate sources of service information for
accomplishing the proposed actions.
Request To Not Mandate the Actions in Airbus Service Bulletin A320-32-
1407, Revision 01, Dated July 3, 2014
United Airlines requested that we not require the actions in Airbus
Service Bulletin A320-32-1407, Revision 01, dated July 3, 2014. United
Airlines stated that Airbus Service Bulletin A320-32-1407, Revision 01,
dated July 3, 2014, recommends that operators flush the affected
hydraulic system. United Airlines stated that it disagrees with this
proposed action and explained that Airbus instituted this requirement
to flush the hydraulic system as it failed to recommend the removal,
inspection, and cleaning of the restrictors during the modification of
the MLG door actuator to the part number (P/N) 114122014 configuration.
United Airlines also stated that it has opted to overhaul the MLG door
actuators as well as perform the modification described in Airbus
Service Bulletin A320-32-1407, dated May 14, 2013. United Airlines
explained that this overhaul requires that the restrictors (P/N
114122233 and P/N 114122232) and transfer pipe be removed, inspected,
and cleaned. United Airlines stated that it is of the opinion that
flushing the hydraulic system is not required as there is no
contamination present in the restrictors or the transfer pipe.
We disagree with the commenter's request. Airbus informed the FAA
that debris can leave the damaged actuator and remain in the hydraulic
lines connected to the door actuator. Flushing of the hydraulic system
is required to prevent debris from entering the new actuator. If debris
enters the new actuator, its performance can be affected. The flow rate
during normal operation is insufficient to ensure complete flushing of
the debris to the hydraulic low pressure filter within a few door
cycles. Therefore, a specific maintenance procedure has been defined
and introduced in Airbus Service Bulletin A320-32-1407, Revision 01,
dated July 3, 2014; and General Electric Service Bulletin 114122-32-
105, Revision 2, dated June 24, 2014. EASA has issued AD 2014-0221,
dated September 30, 2014, requiring flushing of the affected hydraulic
system in accordance with Airbus Service Bulletin A320-32-1407,
Revision 01, dated July 3, 2014.
Request To Provide Credit for Previous Actions
US Airways requested that we provide credit for the actions
required by paragraphs (t) and (u) of the proposed AD (paragraphs (u)
and (v) of this SNPRM)), if those actions were done before the
effective date of the AD using Airbus Service Bulletins A320-32-1407,
dated May 14, 2013, or Revision 01, dated July 3, 2014; or General
Electric Service Bulletin 114122-32-105, dated January 17, 2013.
We partially agree with the commenter's request. In this SNPRM,
paragraph (aa) already provides credit for General Electric Service
Bulletin 114122-32-105, dated January 17, 2013, for the actions in
paragraphs (u) and (v) done prior to the effective date of the final
rule. We do not agree with giving credit for Airbus Service Bulletin
A320-32-1407, dated May 14, 2013; or Revision 01, dated July 3, 2014;
because those service bulletins do not require flushing the hydraulic
system prior to the installation of P/N 114122014. We have not changed
the proposed AD in this regard.
FAA's Determination and Requirements of This SNPRM
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.
Certain changes described above expand the scope of the NPRM. As a
result, we have determined that it is necessary to reopen the comment
period to provide additional opportunity for the public to comment on
this SNPRM.
Explanation of ``RC'' Procedures and Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directives Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which procedures and tests in the service information are
required for compliance with an AD. Differentiating these procedures
and tests from other tasks in the service information is expected to
improve an owner's/operator's understanding of crucial AD requirements
and help provide consistent judgment in AD compliance. The procedures
and tests identified as Required for Compliance (RC) in any service
information have a direct effect on detecting, preventing, resolving,
or eliminating an identified unsafe condition.
As specified in a NOTE under the Accomplishment Instructions of the
specified Airbus service information, procedures and tests identified
as RC must be done to comply with the proposed AD. However, procedures
and 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 alternative method
of compliance (AMOC), provided the procedures and tests identified as
RC can be done and the airplane can be put back in a serviceable
condition. Any substitutions or changes to procedures or tests
[[Page 57125]]
identified as RC will require approval of an AMOC.
Changes to the Proposed AD
This SNPRM makes the following changes to the NPRM.
We have moved the credit for Airbus Service Bulletin A320-32-1309,
dated March 7, 2006, specified in paragraph (g) of AD 2011-13-11, into
paragraph (aa)(1) of the proposed AD.
We have reformatted and redesignated three tables as figures to
comply with requirements of the Office of the Federal Register, as
follows:
``Table 1 to Paragraph (p) of this AD--Affected Part
Numbers'' is ``Figure 2 to Paragraph (p) of this AD--Affected Part
Numbers;''
``Table 2 to Paragraph (v) of this AD--Affected Part
Numbers'' is ``Figure 3 to Paragraph (v) of this AD--Affected Part
Numbers;'' and
``Table 3 to Paragraph (z) of this AD--Affected Part
Numbers'' is ``Figure 4 to Paragraph (z) of this AD.''
Costs of Compliance
We estimate that this SNPRM affects 953 airplanes of U.S. registry.
The actions that are required by AD 2011-13-11, and retained in
this SNPRM, take about 7 work-hours per product, per inspection cycle,
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 2011-13-11 is
$595 per product.
The actions that are required by AD 2013-16-09, and retained in
this SNPRM, take about 3 work-hours per product, per inspection cycle,
at an average labor rate of $85 per work-hour. Based on these figures,
the estimated cost of the actions that were required by AD 2013-16-09
is $255 per product.
We also estimate that it would take about 19 work-hours per product
to comply with the basic requirements of this SNPRM. The average labor
rate is $85 per work-hour. Required parts would cost about $17,140 per
product. Based on these figures, we estimate the cost of this SNPRM on
U.S. operators to be $17,873,515, or $18,755 per product.
In addition, we estimate that any necessary follow-on actions would
take about 3 work-hours, for a cost of $255 per product. We have no way
of determining the number of aircraft that might need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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 Directives (AD) 2011-13-11, Amendment 39-
16734 (76 FR 37241, June 27, 2011) (``AD 2011-13-11''); and AD 2013-16-
09, Amendment 39-17547 (78 FR 48286, August 8, 2013) (``AD 2013-16-
09''); and
0
b. Adding the following new AD:
Airbus: Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-
260-AD.
(a) Comments Due Date
We must receive comments by November 6, 2015.
(b) Affected ADs
This AD replaces AD 2011-13-11, Amendment 39-16734 (76 FR 37241,
June 27, 2011) (``AD 2011-13-11''); and AD 2013-16-09, Amendment 39-
17547 (78 FR 48286, August 8, 2013) (``AD 2013-16-09'').
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), (c)(3), and
(c)(4) of this AD, all manufacturer serial numbers.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by a determination that the inspection
interval of the main landing gear (MLG) door opening sequence must
be reduced. We are issuing this AD to detect and correct
deterioration of the damping ring and associated retaining ring of
the MLG door actuator, which can sufficiently increase the friction
inside the actuator to restrict opening of the MLG door by gravity,
during operation of the landing gear alternate (free-fall) extension
system. This condition could prevent the full extension and/or down-
locking of the MLG, possibly resulting in MLG collapse during
landing and consequent damage to the aeroplane and injury to
occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Repetitive Inspections/Replacement, With a Formatting
Change
This paragraph restates the requirements of paragraph (g) of AD
2011-13-11, with a formatting change. At the time specified in
paragraph (g)(1) or (g)(2) of this AD, as applicable: Do a general
visual inspection of the operation of the MLG door opening sequence
to determine if a defective actuator is installed by doing all the
applicable actions, including replacing the door actuator, as
applicable, specified in the Accomplishment Instructions of Airbus
Service Bulletin A320-32-1309, Revision 01, dated June 19, 2006. Do
all applicable replacements before further flight. Repeat the
inspection thereafter at intervals not to exceed 900 flight cycles.
Doing the
[[Page 57126]]
inspection required by paragraph (l) of this AD terminates the
requirements of this paragraph.
(1) For airplanes on which a record of the total number of
flight cycles on the MLG door actuator is available: Before the
accumulation of 3,000 total flight cycles on the MLG door actuator,
or within 800 flight cycles after April 27, 2007 (the effective date
of AD 2007-06-18, Amendment 39-14999 (72 FR 13681, March 23, 2007)),
whichever is later.
(2) For airplanes on which a record of the total number of
flight cycles on the MLG door actuator is not available: Within 800
flight cycles after April 27, 2007 (the effective date of AD 2007-
06-18).
(3) For the purposes of this AD, a general visual inspection is:
``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
enhance visual access to all exposed surfaces in the inspection
area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight,
or droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
(h) Retained Provision Regarding Reporting/Parts Return, With No
Changes
This paragraph restates the requirements of paragraph (h) of AD
2011-13-11, with no changes. Although the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1309, Revision 01,
dated June 19, 2006, specify submitting certain information to the
manufacturer and sending defective actuators back to the component
manufacturer for investigation, this AD does not include those
requirements.
(i) Retained Revision of the Airplane Flight Manual (AFM), With
Formatting Changes
This paragraph restates the requirements of paragraph (i) of AD
2011-13-11, with formatting changes. Within 14 days after July 12,
2011 (the effective date of AD 2011-13-11), revise the Emergency
Procedure Section of the AFM to incorporate the information in
figure 1 to paragraph (i) of this AD. This may be done by inserting
a copy of this AD into the AFM. When a statement identical to that
in figure 1 to paragraph (i) of this AD has been included in the
Emergency Procedure Section of the general revisions of the AFM, the
general revisions may be inserted into the AFM, and the copy of this
AD may be removed from the AFM. Doing the actions required by
paragraph (t) of this AD terminates the requirements of this
paragraph.
Figure 1 to Paragraph (i) of This AD--AFM Revision
------------------------------------------------------------------------
-------------------------------------------------------------------------
If ECAM triggers the ``L/G GEAR NOT DOWNLOCKED'' warning, apply
the following procedure:
Recycle landing gear.
If unsuccessful after 2 min:
Extend landing gear by gravity. Refer to ABN-32 L/G GRAVITY EXTENSION.
------------------------------------------------------------------------
(j) Retained Repetitive Checks, With New Optional Actions and New
Service Information
This paragraph restates the requirements of paragraph (j) of AD
2011-13-11, with new optional actions and new service information.
Within 14 days after July 12, 2011 (the effective date of AD 2011-
13-11), or before the accumulation of 800 total flight cycles,
whichever occurs later, check the post flight report (PFR) for
centralized fault display system (CFDS) messages triggered within
the last 8 days, in accordance with paragraph 4.2.1 of Airbus All
Operators Telex (AOT) A320-32A1390, dated February 10, 2011. Repeat
the check thereafter at intervals not to exceed 8 days or 5 flight
cycles, whichever occurs later. If done in accordance with a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, the use of an alternative method to check
the PFR for CFDS messages (e.g., AIRMAN) is acceptable in lieu of
this check if the messages can be conclusively determined from that
method. Repetitive inspections of the door opening sequence of the
left-hand (LH) and right-hand (RH) doors of the MLG, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-32-1390, Revision 03, dated July 13, 2014, are an acceptable
method of compliance for the actions required by this paragraph.
Repetitive inspections of the door opening sequence of the LH and RH
doors of the MLG of an airplane, as required by paragraph (p) of
this AD, is an acceptable method to comply with the requirements of
this paragraph.
(k) Retained On-Condition Inspection, With New Service Information
This paragraph restates the requirements of paragraph (k) of AD
2011-13-11, with new service information. If, during any check
required by paragraph (j) of this AD, a pair of specific CFDS
messages specified in paragraph 4.2.1 of Airbus AOT A320-32A1390,
dated February 10, 2011, has been triggered by both landing gear
control and indication units (LGCIU) for the same flight, before
further flight, inspect the door opening sequence of the affected
doors of the MLG for discrepancies (i.e., if any condition specified
in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT A320-
32A1390, dated February 10, 2011, is not met; or if any door
actuator fails any inspection check specified in Airbus Service
Bulletin A320-32-1390, Revision 03, dated July 13, 2014). Do the
inspection in accordance with paragraph 4.2.2 of Airbus AOT A320-
32A1390, dated February 10, 2011; or the Accomplishment Instructions
of Airbus Service Bulletin A320-32-1390, Revision 03, dated July 13,
2014. As of the effective date of this AD, use only Airbus Service
Bulletin A320-32-1390, Revision 03, dated July 13, 2014, for the
actions required by this paragraph.
(l) Retained Repetitive Inspections, With New Service Information, New
Optional Actions, and Reduced Compliance Times
This paragraph restates the requirements of paragraph (l) of AD
2011-13-11, with new service information, new optional actions, and
reduced compliance times. At the applicable time specified in
paragraph (l)(1) or (l)(2) of this AD: Inspect the door opening
sequence of the LH and RH doors of the MLG for discrepancies (i.e.,
if any condition specified in steps (a) through (d) of paragraph
4.2.2 of Airbus AOT A320-32A1390, dated February 10, 2011, is not
met; or if any door actuator fails any inspection check specified in
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1390, Revision 03, dated July 13, 2014). Do the inspection in
accordance with the instructions of paragraph 4.2.2 of Airbus AOT
A320-32A1390, dated February 10, 2011; or the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1390, Revision 03,
dated July 13, 2014. As of the effective date of this AD, use only
Airbus Service Bulletin A320-32-1390, Revision 03, dated July 13,
2014, for the actions required by this paragraph. Repeat the
inspection within 8 days or 5 flight cycles after the effective date
of this AD, whichever occurs later, without exceeding 425 flight
cycles since the most recent inspection; and thereafter repeat the
inspection at intervals not to exceed 8 days or 5 flight cycles,
whichever occurs later. In addition, whenever any airplane is not
operated for a period longer than 8 days, do the inspection before
further flight. Doing this inspection terminates the requirements of
paragraph (g) of this AD. Repetitive inspections of the door opening
sequence of the LH and RH doors of the MLG of an airplane, as
required by paragraph (p) of this AD, is an acceptable method to
comply with the requirements of this paragraph.
(1) For airplanes on which an inspection required by paragraph
(g) of this AD has been done as of July 12, 2011 (the effective date
of AD 2011-13-11): Within 800 flight cycles after doing the most
recent inspection required by paragraph (g) of this AD, or within
100 flight cycles after July 12, 2011, whichever occurs later.
(2) For airplanes on which an inspection required by paragraph
(g) of this AD has not been done as of July 12, 2011 (the effective
date of AD 2011-13-11): Within 800 flight cycles after July 12,
2011.
(m) Retained Replacement, With New Service Information
This paragraph restates the requirements of paragraph (m) of AD
2011-13-11, with new
[[Page 57127]]
service information. If any discrepancy (i.e., if any condition
specified in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT
A320-32A1390, dated February 10, 2011, is not met; or if any door
actuator fails any inspection check specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1390, Revision 03,
dated July 13, 2014) is found during any inspection required by
paragraph (k) or (l) of this AD, before further flight, replace the
affected MLG door actuator with a new MLG door actuator, in
accordance with the instructions of Airbus AOT A320-32A1390, dated
February 10, 2011; or Airbus Service Bulletin A320-32-1390, Revision
03, dated July 13, 2014. As of the effective date of this AD, use
only Airbus Service Bulletin A320-32-1390, Revision 03, dated July
13, 2014, to do the actions required by this paragraph.
(n) Retained Statement of No Terminating Action for Certain
Requirements, With No Changes
This paragraph restates the statement of paragraph (n) of AD
2011-13-11, with no changes. Replacement of the MLG door actuator as
required by paragraph (m) of this AD is not a terminating action for
the repetitive actions required by paragraphs (j) and (l) of this
AD.
(o) Retained Configuration and Part Number Determination, With No
Changes
This paragraph restates the requirements of paragraph (g) of AD
2013-16-09, with no changes. At the later of the compliance times
specified in paragraphs (o)(1) and (o)(2) of this AD: Do an
inspection to determine the configuration (modification status) of
the airplane and identify the part number of the LH and RH LGCIU and
MLG door actuators. A review of the airplane delivery or maintenance
records is acceptable for compliance with the requirements of this
paragraph provided the airplane configuration and installed
components can be conclusively determined from that review.
(1) Prior to the accumulation of 800 total flight cycles since
first flight of the airplane.
(2) Within 14 days after August 23, 2013 (the effective date of
AD 2013-16-09).
(p) Retained MLG Door Opening Sequence Repetitive Inspections, With No
Changes
This paragraph restates the requirements of paragraph (h) of AD
2013-16-09, with no changes. If, during the determination and
identification required by paragraph (o) of this AD, the
configuration of the airplane is determined to be post-Airbus
Modification 39303 or post-Airbus Service Bulletin A320-32-1409
(Interlink Communication ARINC 429 installed), and both an LGCIU and
a MLG door actuator are installed with a part number listed in
figure 2 to paragraph (p) of this AD: Except as provided by
paragraph (s) of this AD, at the later of the compliance times
specified in paragraphs (o)(1) and (o)(2) of this AD, and thereafter
at intervals not to exceed 8 days or 5 flight cycles, whichever
occurs later, do an inspection of the door opening sequence of the
LH and RH MLG doors, in accordance with the instructions of Airbus
AOT A32N001-13, dated June 24, 2013.
Figure 2 to Paragraph (p) of This AD--Affected Part Numbers
------------------------------------------------------------------------
Component name Part number
------------------------------------------------------------------------
LGCIU (LH and RH)................................. 80-178-02-88012
80-178-03-88013
MLG door actuator................................. 114122006
114122007
114122009
114122010
114122011
114122012
------------------------------------------------------------------------
(q) Retained MLG Door Opening Sequence Corrective Action, With No
Changes
This paragraph restates the requirements of paragraph (i) of AD
2013-16-09, with no changes. If a slow door operation or restricted
extension is found during any inspection required by paragraph (p)
of this AD: Before further flight, replace the affected MLG door
actuator with a new or serviceable actuator, in accordance with the
instructions of Airbus AOT A32N001-13, dated June 24, 2013.
(r) Retained Terminating Action Limitation for Certain Actions, With
New Service Information
This paragraph restates the requirements of paragraph (j) of AD
2013-16-09, with new service information. Replacement of a MLG door
actuator, as required by paragraph (q) of this AD, does not
constitute terminating action for the repetitive inspections
required by paragraph (p) of this AD, unless MLG door actuators
having P/N 114122014 are installed on both LH and RH sides, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1407, dated May 14, 2013; or Airbus Service
Bulletin A320-32-1407, Revision 01, dated July 3, 2014. As of the
effective date of this AD, use only Airbus Service Bulletin A320-32-
1407, Revision 01, dated July 3, 2014, for the actions required by
this paragraph.
(s) Retained Repetitive Inspection Exception, With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2013-16-09, with no changes. Airplanes on which the LGCIU interlink
is disconnected (Airbus Modification 155522 applied in production,
or modified in-service in accordance with the instructions of Airbus
AOT A32N001-13, dated June 24, 2013), or on which MLG door actuators
having P/N 114122014 are installed on both LH and RH sides (Airbus
Modification 153655 applied in production, or modified in-service as
described in Airbus Service Bulletin A320-32-1407), are not required
to do the actions required by paragraph (p) of this AD, provided
that the airplane is not modified to a configuration as defined in
paragraph (p) of this AD.
(t) New Revision of the AFM
Within 14 days after the effective date of this AD, revise the
Emergency Procedure Section of the AFM to incorporate Airbus A318/
A319/A320/A321 Temporary Revision (TR) TR437, L/G GEAR NOT
DOWNLOCKED, Issue 1.0, dated May 23, 2014. When this TR has been
included in general revisions of the AFM, the general revisions may
be inserted in the AFM, provided the relevant information in the
general revision is identical to that in this TR, and the copy of
this TR may be removed from the AFM. Doing the action required by
this paragraph terminates the actions required by paragraph (i) of
this AD.
(u) New Replacement of MLG Door Actuator Having P/N 114122012
Within 12 months after the effective date of this AD: Replace
each MLG door actuator having P/N 114122012 with a MLG door actuator
having P/N 14122014, and flush the affected hydraulic system, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1407, Revision 01, dated July 3, 2014; or modify
each actuator, including doing all applicable related investigative
and corrective actions, in accordance with the Accomplishment
Instructions of General Electric Service Bulletin 114122-32-105,
Revision 2, dated June 24, 2014; except where General Electric
Service Bulletin 114122-32-105, Revision 2, dated June 24, 2014,
specifies to contact the manufacturer, before further flight, repair
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation
Safety Agency (EASA); or Airbus's EASA Design Organization Approval
(DOA).
(v) New Replacement of Certain Other MLG Door Actuators
Within 24 months after the effective date of this AD: Replace
each MLG door actuator having a part number listed in figure 3 to
paragraph (v) of this AD, except P/N 114122012, with a MLG door
actuator having P/N 14122014, and flush the affected hydraulic
system, in accordance with Accomplishment Instructions of Airbus
Service Bulletin A320-32-1407, Revision 01, dated July 3, 2014; or
modify each actuator, including doing all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of General Electric Service Bulletin
114122-32-105, Revision 2, dated June 24, 2014; except where General
Electric Service Bulletin 114122-32-105, Revision 2, dated June 24,
2014, specifies to contact the manufacturer, before further flight,
repair using a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the EASA; or
Airbus's EASA DOA.
Figure 3 to Paragraph (v) of This AD--Affected Part Numbers
------------------------------------------------------------------------
Component name Part number
------------------------------------------------------------------------
MLG door actuator......................................... 114122006
114122007
114122009
114122010
114122011
114122012
------------------------------------------------------------------------
(w) New Terminating Action
Modification of an airplane as required by paragraphs (u) and
(v) of this AD, as applicable, constitutes terminating action for
[[Page 57128]]
all repetitive actions (PFR monitoring checks and inspections)
required by this AD for that airplane.
(x) New Conditional Terminating Action
Replacement of a MLG door actuator as required by paragraphs (m)
and (q) of this AD; or corrective actions as specified in Airbus AOT
A320-32A1390, dated February 10, 2011; or replacement of a MLG door
actuator as specified in Airbus Service Bulletin A320-32-1390,
Revision 03, dated July 13, 2014; does not constitute terminating
action for the repetitive inspections required by paragraphs (j),
(l), and (p) of this AD, unless MLG door actuators having P/N
114122014 are installed on both LH and RH sides, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1407, Revision 01, dated July 3, 2014.
(y) New Exception to AD Requirements
(1) An airplane on which MLG door actuators having P/N 114122014
are installed on both LH and RH sides (Airbus Modification 153655
applied in production, or modified in service as specified in Airbus
Service Bulletin A320-32-1407, dated May 14, 2013; Airbus Service
Bulletin A320-32-1407, Revision 01, dated July 3, 2014; General
Electric Service Bulletin 114122-32-105, dated January 17, 2013; or
General Electric Service Bulletin 114122-32-105, Revision 1, dated
March 26, 2013; or General Electric Service Bulletin 114122-32-105,
Revision 2, dated June 24, 2014); is not affected by the
requirements of paragraphs (j) through (v) of this AD, provided that
no MLG door actuator with a part number in figure 3 to paragraph (v)
of this AD has been installed on that airplane since first flight,
or since modification, as applicable.
(2) An airplane in the configuration specified in paragraph
(y)(1) of this AD, and with flight warning computers having P/N
350E053021212 (H2F7) installed (Airbus Modification 153741 applied
in production, or modified in service as specified in Airbus Service
Bulletin A320-31-1414), is not affected by the requirement of
paragraph (t) of this AD and, following modification, Airbus A318/
A319/A320/A321 TR TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated
May 23, 2014 (if inserted), may be removed from the AFM of that
airplane.
(z) New Parts Installation Prohibitions
(1) Except as specified in paragraph (z)(2) of this AD, as of
the effective date of this AD, do not install on any airplane a MLG
door actuator having a part number listed in figure 3 to paragraph
(v) of this AD.
(2) For an airplane subject to the requirements of paragraphs
(u) and (v) of this AD, as applicable, do not install a MLG door
actuator having a part number listed in figure 3 to paragraph (v) of
this AD after modification of the airplane.
(3) Except as specified in paragraph (z)(4) of this AD, as of
the effective date of this AD, do not install on any airplane a
flight warning computer (FWC) having a part number listed in figure
4 to paragraph (z) of this AD.
(4) For an airplane subject to the requirements of paragraphs
(u) and (v) of this AD, as applicable, do not install a FWC having a
part number listed in figure 4 to paragraph (z) of this AD after
modification of the airplane.
Figure 4 to Paragraph (z) of This AD--Affected Part Numbers
------------------------------------------------------------------------
Component name Part number
------------------------------------------------------------------------
Flight warning computer.................... 350E016187171 (C5)
350E017238484 (H1D1)
350E017248685 (H1D2)
350E017251414 (H1E1)
350E017271616 (H1E2)
350E018291818 (H1E3CJ)
350E018301919 (H1E3P)
350E018312020 (H1E3Q)
350E053020202 (H2E2)
350E053020303 (H2E3)
350E053020404 (H2E4)
350E053020606 (H2F2)
350E053020707 (H2F3)
350E053021010 (H2F3P)
350E053020808 (H2F4)
350E053020909 (H2F5)
350E053021111 (H2F6)
------------------------------------------------------------------------
(aa) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g) of this AD, if those actions were performed before
April 27, 2007 (the effective date of AD 2007-06-18), using Airbus
Service Bulletin A320-32-1309, dated March 7, 2006. This service
information is not incorporated by reference in this AD.
(2) This paragraph provides credit for actions required by
paragraphs (k), (l), and (m) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A320-32-1390, Revision 01, dated September 21, 2011; or
Revision 02, dated October 23, 2013. Airbus Service Bulletin A320-
32-1390, Revision 01, dated September 21, 2011, was incorporated by
reference in AD 2011-13-11. Airbus Service Bulletin A320-32-1390,
Revision 02, dated October 23, 2013, is not incorporated by
reference in this AD.
(3) This paragraph provides credit for actions required by
paragraphs (u) and (v) of this AD, if those actions were performed
before the effective date of this AD using General Electric Service
Bulletin 114122-32-105, dated January 17, 2013; or General Electric
Service Bulletin 114122-32-105, Revision 1, dated March 26, 2013.
This service information is not incorporated by reference in this
AD.
(bb) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Required for Compliance (RC): If any Airbus 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
[[Page 57129]]
procedures and tests identified as RC can be done and the airplane
can be put back in a serviceable condition. Any substitutions or
changes to procedures or tests identified as RC require approval of
an AMOC.
(3) Contacting the Manufacturer: As of the effective date of
this AD, except as specified in paragraph (j) of this AD for the use
of an alternative method to check the PFR for CFDS messages, 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 EASA; or Airbus's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.
(4) Previously Approved AMOCs: AMOCs approved previously for the
AD 2011-13-11 and AD 2013-16-09 are approved as AMOCs for the
corresponding provisions of this AD.
(cc) Special Flight Permits
Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be modified (if the operator elects to do so), provided the MLG
remains extended and locked, and that no MLG recycle is done.
(dd) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0221, dated September 30,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0529-0003.
(2) For Airbus 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.
(3) For General Electric service information identified in this
AD, contact GE Aviation, Customer Support Center, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513-552-3272; email:
cs.techpubs@ge.com; Internet: https://www.geaviation.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.
Issued in Renton, Washington, on August 21, 2015.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-21730 Filed 9-21-15; 8:45 am]
BILLING CODE 4910-13-P
