Airworthiness Directives; Airbus Airplanes, 16948-16952 [2017-06705]
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16948
Proposed Rules
Federal Register
Vol. 82, No. 66
Friday, April 7, 2017
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–0461; Directorate
Identifier 2014–NM–159–AD]
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for all Airbus Model A319, A320, and
A321 series airplanes. This action
revises the notice of proposed
rulemaking (NPRM) by reducing the
compliance time for replacing the main
landing gear (MLG) actuator fitting and
removing an inspection requirement for
certain airplanes. We are proposing this
AD to address the unsafe condition on
these products. 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 May 22, 2017.
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.,
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SUMMARY:
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Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this SNPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
0461; 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–2016–0461; Directorate Identifier
2014–NM–159–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
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personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We issued an NPRM to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A319, A320,
and A321 series airplanes. The NPRM
published in the Federal Register on
January 28, 2016 (81 FR 4901) (‘‘the
NPRM’’). The NPRM was prompted by
a report that an MLG door could not be
closed due to rupture of the actuator
fitting. The NPRM proposed to require
repetitive inspections for cracking of the
MLG door actuator fitting and its
components, and corrective actions if
necessary. The NPRM also proposed to
require eventual replacement of all
affected MLG door actuator fittings with
new monoblock fittings, which would
terminate the repetitive inspections.
Actions Since the NPRM Was Issued
Since the NPRM was issued, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2016–0182, dated September
13, 2016 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A319, A320, and A321 series
airplanes. The MCAI states:
On one A320 aeroplane, it was reported
that one of the main landing gear (MLG)
doors could not be closed. Investigations
revealed the rupture of the actuator fitting at
the actuator attachment area on the door side.
The MLG door is attached to the aeroplane
by 2 (two) hinge fittings.
This condition, if not corrected, could,
under certain circumstances, lead to
detachment of a MLG door from the
aeroplane, possibly resulting in damage to
the aeroplane, and/or injury to persons on
the ground.
Prompted by these findings, [Direction
´ ´
Generale de l’Aviation Civile] France issued
* * * [an AD] * * *, to require a MLG door
actuator fitting inspection for cracks and to
check the grain direction on a batch of
aeroplanes. Subsequently, DGAC France
issued * * * [an AD], retaining the
requirements of DGAC France AD * * *,
which was superseded, to require an
inspection of the lower part of the MLG door
actuator fitting.
After that [DGAC] AD was issued,
additional investigations revealed that
damage could also appear on the nerve area
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[of the forward monoblock fitting], in the
upper part of the MLG door actuator fitting
in the area of the hinge.
Consequently, DGAC France issued F–
2003–434, dated December 10, 2003 [https://
ad.easa.europa.eu/ad/F-2003-454] (EASA
approval 2003–1436), retaining the
requirements of [a] DGAC France AD * * *,
which was superseded, to require additional
repetitive inspections. That [DGAC] AD also
included an optional terminating action, by
replacing the MLG door actuator fittings in
accordance with the instructions of Airbus
Service Bulletin (SB) A320–52–1073.
After DGAC France AD F–2003–434 was
issued, in the framework of the extended
service goal campaign, it was decided to
make replacement of the MLG door actuator
fittings a required modification.
Consequently, EASA issued AD 2014–0166
* * *, retaining the requirements of DGAC
France AD F–2003–434, which was
superseded, and requiring replacement of the
MLG door actuator fittings with new
monoblock fittings, which constitutes
terminating action for the repetitive
inspections.
After EASA AD 2014–0166 [corresponding
to the NPRM] was issued, errors were
identified in the compliance time definitions.
Replacement of the MLG door actuator
fittings was required ‘‘before exceeding
48,000 flight cycles (FC) or 96,000 flight
hours (FH), whichever occurs later since
aeroplane first flight’’, which should have
been ‘‘whichever occurs first’’. Furthermore,
since the MLG door is an interchangeable
part, the compliance time must be defined as
FC/FH accumulated by the MLG door.
Furthermore, it was discovered that one of
the required inspection[s] is applicable only
to a batch of MLG door fittings.
For the reason described above, this AD
retains the requirements of EASA AD 2014–
0166, which is superseded, but requires
accomplishment of the terminating action
within more stringent compliance times, and
reduce[s] the applicability of one of the
required inspection[s].
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
0461.
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Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
• Airbus Service Bulletin A320–52–
1073, Revision 04, dated August 10,
1999.
• Airbus Service Bulletin A320–52–
1073, Revision 05, dated September 28,
2006.
• Airbus Service Bulletin A320–
52A1086, Revision 01, dated September
10, 1999.
• Airbus Service Bulletin A320–52–
1096, Revision 02, dated July 12, 2006.
This service information describes
procedures for inspections for cracking
of the MLG door actuator fitting and its
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components, and corrective actions if
necessary. This service information also
describes procedures for replacement of
all affected MLG door actuator fittings
with new monoblock fittings. These
documents are distinct since they apply
to different airplane models. 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.
Comments
We gave the public the opportunity to
participate in developing this proposed
AD. We considered the comments
received.
Support for the NPRM
A commenter, Kevin Grandberry,
stated that he supports the inspections
of the MLG door actuator fittings
specified in the NPRM.
Request To Reduce the Compliance
Time for Replacing the MLG Actuator
Fitting
Airbus asked that we reduce the
compliance time for the replacement
specified in paragraph (j)(1) of the
proposed AD (in the NPRM) from
‘‘whichever occurs later since the first
flight of the airplane’’ to ‘‘whichever
occurs first since the first flight of the
airplane.’’ Airbus stated that EASA
updated EASA AD 2014–0166, dated
July 16, 2014 (referenced in the NPRM),
to correct the error noted in the
compliance time (among other changes).
We agree with the commenter’s
request in light of the superseded EASA
AD, which corrects the compliance
time. We have changed the compliance
time specified in paragraph (j)(1) of this
proposed AD accordingly.
Request To Change Applicability
United Airlines (UA) asked that we
limit the applicability of the NPRM to
the manufacturer serial numbers (MSNs)
included in Airbus Service Bulletin
A320–52–1073, Revision 05, dated
September 28, 2006. UA did not provide
a reason for the request.
We do not agree with the commenter’s
request. The effectivity of Airbus
Service Bulletin A320–52–1073,
Revision 05, dated September 28, 2006,
is based on airplanes delivered with the
affected parts. However, the parts are
rotable and could be installed on MSNs
other than those identified in Airbus
Service Bulletin A320–52–1073,
Revision 05, dated September 28, 2006.
Therefore, this AD applies to all
airplanes identified in paragraph (c) of
this AD. We have not changed this
proposed AD in this regard.
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Request for Credit for Previous
Accomplishment of the Optional
Terminating Action
UA asked that we give credit for
modifying the airplane (as specified in
the optional terminating action in
paragraph (k) of the proposed AD (in the
NPRM)) using Airbus Service Bulletin
A320–52–1073, Revision 04, dated
August 10, 1999; or any prior revision.
UA stated that accomplishing any
revisions (including future revisions)
would terminate the repetitive
inspections required by paragraphs (g)
and (h) of the proposed AD.
We partially agree with the request.
We agree to include Airbus Service
Bulletin A320–52–1073, Revision 04,
dated August 10, 1999, in this proposed
AD; however, we do not agree to allow
the use of any prior version because
changes to the installation procedures
were added to Airbus Service Bulletin
A320–52–1073, Revision 04, dated
August 10, 1999, to prevent damage to
the carbon fiber of the MLG door. We
have added Airbus Service Bulletin
A320–52–1073, Revision 04, dated
August 10, 1999, as a method of
compliance for the optional terminating
action in paragraph (k) of this proposed
AD.
Request To Extend the Compliance
Time for the Inspections
Delta Air Lines (DAL) asked that we
extend the compliance time specified in
paragraphs (g) and (j)(2) of the proposed
AD (in the NPRM). DAL stated that the
FAA waited years to take any action on
the subject unsafe condition and, in
light of that fact, the ‘‘calendar date’’ for
the compliance time in paragraph (g) of
the proposed AD (in the NPRM) should
be extended from 30 to 180 days. DAL
also stated that using a calendar date for
a crack growth concern is not based on
industry-accepted analysis. DAL noted
that mandating the inspections with this
short interval has a significant impact
on operators with multiple aircraft that
are affected by the proposed AD. DAL
added that an immediate safety concern
is not evident in the speed with which
the FAA moved to enact the regulatory
action, or in the details provided in the
NPRM. In addition, DAL asked that the
compliance time in paragraph (j)(2) of
the proposed AD (in the NPRM) be
extended from 30 days to 24 months.
DAL stated that operators would have
difficulty complying with the 30-day
compliance time for replacing the MLG
door actuator fitting due to the extensive
time necessary to modify each door.
DAL added that the replacement should
be done in a hangar environment where
skilled composite facilities and
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technicians are available, which occurs
every 24 months.
We do not agree with the commenter’s
requests. The compliance times in
paragraphs (g) and (j)(2) of this proposed
AD are based on EASA’s assessment of
the overall risk to the fleet, including
the severity of the failure and the
likelihood of the failure to occur. We are
unaware of any information or data that
substantiates the compliance time
change the commenter has requested,
and nothing was provided by the
commenter to support the request. We
also do not agree that FAA requirements
related to crack growth are based on
calendar time. The calendar time of 30
days, as retained in this proposed AD,
is a grace period to provide additional
time for airplanes that have exceeded
their limit of validity of engineering
data. All other compliance time
requirements are based on flight cycles
and flight hours.
We also note that since this is a
SNPRM, operators will have additional
time to plan for AD compliance.
However, under the provisions of
paragraph (n)(1) of this proposed AD,
we will consider requests for approval
of an extension of the compliance time
if sufficient data are submitted to
substantiate that the new compliance
time would provide an acceptable level
of safety. We have not changed this
proposed AD in this regard.
Request To Include MLG Serial
Numbers
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DAL asked that we change paragraph
(h) of the proposed AD (in the NPRM)
to include the affected serial numbers of
the left- and right-hand doors of the
MLG. DAL stated that paragraph (g) of
the proposed AD (in the NPRM)
provides the door serial numbers to
assist with identifying the affected
doors, and similar information should
be provided in paragraph (h) of the
proposed AD (in the NPRM).
We agree with the commenter’s
request. Paragraph (4) of EASA AD
2016–0182, dated September 13, 2016,
which corresponds to paragraph (h) of
this proposed AD, identifies the affected
serial numbers. It was not our intent to
deviate from the MCAI. We have added
the serial numbers to paragraph (h) of
this proposed AD.
Request To Clarify Modification Titles
UA asked that we clarify the language
in paragraph (l) of the proposed AD (in
the NPRM) to add ‘‘or Airbus
Modification’’ before each modification
number specified.
We agree and have clarified paragraph
(l) of this proposed AD accordingly.
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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.
Costs of Compliance
We estimate that this proposed AD
affects 71 airplanes of U.S. registry.
We also estimate that it would take
about 38 work-hours per product to
comply with the inspection
requirements of this proposed AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost for the inspection specified in this
proposed AD on U.S. operators to be
$229,330, or $3,230 per product.
We estimate that it would take about
98 work-hours per product to comply
with the MLG actuator replacement
requirements of this proposed AD.
Required parts would cost about $6,258
per product. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost for the
actuator replacement specified in this
proposed AD on U.S. operators to be
$1,035,748, or $14,588 per product.
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
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
■
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2016–0461;
Directorate Identifier 2014–NM–159–AD.
(a) Comments Due Date
We must receive comments by May 22,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD,
all manufacturer serial numbers.
(1) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(2) Model A320–211, –212, –214, –231,
–232, and –233 airplanes.
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cycles, except as provided by paragraphs
(i)(1), (j), and (k) of this AD.
(1) Left-hand MLG doors with S/Ns 1206
through 1510 inclusive, 1548, 1564, and 2000
through 2065 inclusive.
(2) Right-hand MLG doors with S/Ns 1208
through 1519 inclusive, 1551, and 2000
through 2065 inclusive.
(3) Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(e) Reason
This AD was prompted by a report that a
main landing gear (MLG) door could not be
closed due to rupture of the actuator fitting.
Later reports indicated that the forward
monoblock fitting of the MLG door actuator
(referred to as the nerve area) could be
damaged after rupture of the actuator fitting.
We are issuing this AD to prevent rupture of
the door actuator fittings, which could result
in detachment of an MLG door and
subsequent exterior damage and consequent
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections of MLG Door
Actuator Fittings
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For airplanes equipped with MLG door
actuator fittings having part number (P/N)
D52880224000 or P/N D52880224001 that
were installed before the first flight of the
airplane on MLG doors identified in
paragraphs (g)(1) and (g)(2) of this AD:
Within 500 flight hours since the most recent
high frequency eddy current (HFEC)
inspection done as specified in Airbus
Service Bulletin A320–52A1086, Revision 01,
dated September 10, 1999, or within 30 days
after the effective date of this AD, whichever
occurs later, perform an HFEC inspection for
cracking of the MLG door fittings, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52A1086, Revision 01, dated September 10,
1999. Repeat the inspection thereafter at
intervals not to exceed 500 flight hours,
except as provided by paragraphs (i), (j), and
(k) of this AD.
(1) Left-hand MLG doors with serial
numbers (S/Ns) 1206 through 1237 inclusive,
1239 through 1247 inclusive, and 1249
through 1251 inclusive.
(2) Right-hand MLG doors with S/Ns 1208
through 1239 inclusive, 1241 through 1249
inclusive, and 1251.
(h) Repetitive Inspections of MLG Hinge and
Nerve Areas
For airplanes equipped with MLG door
actuator fittings having P/N D52880224000,
P/N D52880224001, P/N D52880235000, or
P/N D52880235001 that were installed before
the first flight of the airplane on MLG doors
identified in paragraphs (h)(1) and (h)(2) of
this AD: Within 400 flight cycles after the
effective date of this AD, or before the
accumulation of 9,000 total flight cycles
since first flight of the airplane, whichever
occurs later, perform an HFEC inspection of
both hinge and nerve areas of the MLG doors
for cracking, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1096, Revision 02,
dated July 12, 2006. Repeat the inspection
thereafter at intervals not to exceed 800 flight
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(i) Inspections/Corrective Actions
(1) If any crack is found during any
inspection required by paragraph (g) or (h) of
this AD: Before further flight, replace the
affected MLG door actuator fittings with new
monoblock fittings, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1073, Revision 05,
dated September 28, 2006. Accomplishing
this replacement terminates the repetitive
inspections required by paragraphs (g) and
(h) of this AD.
(2) If, during any HFEC inspection required
by paragraph (g) of this AD, no crack is
found: Before further flight, perform a low
frequency eddy current (LFEC) inspection to
determine the grain direction of the raw
material of each MLG actuator fitting, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52A1086, Revision 01, dated September 10,
1999.
(i) If the grain direction of the raw material
is correct, the repetitive inspections required
by paragraph (g) of this AD may be
terminated.
(ii) If the grain direction of the raw material
is incorrect, repeat the HFEC inspection
required by paragraph (g) of this AD at the
time specified in paragraph (g) of this AD.
Replacement of the MLG door actuator
fittings with new monoblock fittings as
specified in paragraph (i)(1) of this AD
terminates the repetitive inspections required
by paragraphs (g) and (i) of this AD.
(j) MLG Door Actuator Fitting Replacement
For airplanes equipped with any MLG door
actuator fitting having P/N D52880102000, P/
N D52880102001, P/N D52880220000, P/N
D52880220001, P/N D52880224000, P/N
D52880224001, P/N D52880235000, or P/N
D52880235001: At the later of the times
specified in paragraphs (j)(1) and (j)(2) of this
AD, replace the MLG door actuator fittings
with new monoblock fittings, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–52–1073,
Revision 05, dated September 28, 2006.
Accomplishing this replacement terminates
the repetitive inspections required by
paragraphs (g) and (h) of this AD.
(1) Before the accumulation of 48,000 total
flight cycles or 96,000 total flight hours on
the MLG door, whichever occurs first.
(2) Within 30 days after the effective date
of this AD.
(k) Optional Terminating Action
Replacement of the MLG door actuator
fittings with new monoblock fittings, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1073, Revision 04, dated August 10, 1999;
or Airbus Service Bulletin A320–52–1073,
Revision 05, dated September 28, 2006;
terminates the repetitive inspections required
by paragraphs (g) and (h) of this AD.
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16951
(l) Airplanes Excluded From Certain AD
Requirements
(1) For airplanes on which Airbus
Modification 24903, or Airbus Modification
25372, or Airbus Modification 36979 has
been embodied in production, no action is
required by this AD, provided that no MLG
door actuator fitting having any part number
identified in paragraph (j) of this AD has
been reinstalled on the airplane since first
flight.
(2) Modification of an airplane by
installing a version (P/N) of the MLG door
actuator fitting approved after the effective
date of this AD is acceptable for compliance
with the requirements in paragraph (j) of this
AD, provided the conditions specified in
paragraphs (l)(2)(i) and (l)(2)(ii) are met.
(i) The MLG door actuator fitting (P/N)
must be approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
(ii) The modification must be
accomplished in accordance with
instructions approved by the Manager,
International Branch, EASA, or Airbus’s
EASA DOA.
(m) Parts Installation Limitation
As of the effective date of this AD, no
person may install an MLG door actuator
fitting having any part number identified in
paragraph (j) of this AD on any airplane.
(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
E:\FR\FM\07APP1.SGM
07APP1
16952
Federal Register / Vol. 82, No. 66 / Friday, April 7, 2017 / Proposed Rules
Airworthiness Directive 2016–0182, dated
September 13, 2016, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–0461.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on March
29, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–06705 Filed 4–6–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2017–0032; Airspace
Docket No. 17–AEA–1]
Proposed Amendment of Class D
Airspace and Revocation of Class E
Airspace; Fort Eustis, VA
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
remove Class E airspace designated as
an extension at Fort Eustis, VA, as the
Felker Non-Directional Beacon (NDB)
has been decommissioned, and the
approaches cancelled at Felker Army
Airfield, (AAF). This action also would
update the geographic coordinates of the
airport under Class D airspace.
DATES: Comments must be received on
or before May 22, 2017.
ADDRESSES: Send comments on this
proposal to: U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE., West Bldg.
Ground Floor, Rm. W12–140,
Washington, DC 20590; Telephone: 1–
800–647–5527, or 202–366–9826. You
must identify the Docket No. FAA–
2017–0032; Airspace Docket No. 17–
AEA–1, at the beginning of your
comments. You may also submit and
review received comments through the
Internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
nlaroche on DSK30NT082PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
14:51 Apr 06, 2017
Jkt 241001
received, and any final disposition in
person in the Dockets Office between
9:00 a.m. and 5:00 p.m., Monday
through Friday, except Federal holidays.
FAA Order 7400.11A, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
on line at https://www.faa.gov/air_
traffic/publications/. For further
information, you can contact the
Airspace Policy Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: 202–267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11A at NARA, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT: John
Fornito, Operations Support Group,
Eastern Service Center, Federal Aviation
Administration, P.O. Box 20636,
Atlanta, Georgia 30320; telephone 404
305–6364.
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it would
remove Class E airspace, and amend
Class D at Felker AAF, Fort Eustis, VA.
Comments Invited
Interested persons are invited to
comment on this rule by submitting
such written data, views, or arguments,
as they may desire. Comments that
provide the factual basis supporting the
views and suggestions presented are
particularly helpful in developing
reasoned regulatory decisions on the
proposal. Comments are specifically
invited on the overall regulatory,
aeronautical, economic, environmental,
and energy-related aspects of the
proposal.
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Communications should identify both
docket numbers and be submitted in
triplicate to the address listed above.
You may also submit comments through
the Internet at https://
www.regulations.gov.
Persons wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2017–0032; Airspace
Docket No. 17–AEA–1.’’ The postcard
will be date/time stamped and returned
to the commenter.
All communications received before
the specified closing date for comments
will be considered before taking action
on the proposed rule. The proposal
contained in this notice may be changed
in light of the comments received. A
report summarizing each substantive
public contact with FAA personnel
concerned with this rulemaking will be
filed in the docket.
Availability of NPRMs
An electronic copy of this document
may be downloaded from and
comments submitted through https://
www.regulations.gov. Recently
published rulemaking documents can
also be accessed through the FAA’s Web
page at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received, and any final disposition in
person in the Dockets Office (see the
ADDRESSES section for address and
phone number) between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except Federal holidays. An informal
docket may also be examined between
8:00 a.m. and 4:30 p.m., Monday
through Friday, except Federal Holidays
at the office of the Eastern Service
Center, Federal Aviation
Administration, Room 350, 1701
Columbia Avenue, College Park, Georgia
30337.
Availability and Summary of
Documents for Incorporation by
Reference
This document proposes to amend
FAA Order 7400.11A, Airspace
Designations and Reporting Points,
dated August 3, 2016, and effective
September 15, 2016. FAA Order
7400.11A is publicly available as listed
in the ADDRESSES section of this
document. FAA Order 7400.11A lists
Class A, B, C, D, and E airspace areas,
air traffic service routes, and reporting
points.
E:\FR\FM\07APP1.SGM
07APP1
Agencies
[Federal Register Volume 82, Number 66 (Friday, April 7, 2017)]
[Proposed Rules]
[Pages 16948-16952]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06705]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 82, No. 66 / Friday, April 7, 2017 / Proposed
Rules
[[Page 16948]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-0461; Directorate Identifier 2014-NM-159-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for all Airbus Model A319, A320, and A321 series airplanes. This
action revises the notice of proposed rulemaking (NPRM) by reducing the
compliance time for replacing the main landing gear (MLG) actuator
fitting and removing an inspection requirement for certain airplanes.
We are proposing this AD to address the unsafe condition on these
products. 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 May 22, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this SNPRM, contact Airbus,
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0461; 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-2016-0461;
Directorate Identifier 2014-NM-159-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 an NPRM to amend 14 CFR part 39 by adding an AD that
would apply to all Airbus Model A319, A320, and A321 series airplanes.
The NPRM published in the Federal Register on January 28, 2016 (81 FR
4901) (``the NPRM''). The NPRM was prompted by a report that an MLG
door could not be closed due to rupture of the actuator fitting. The
NPRM proposed to require repetitive inspections for cracking of the MLG
door actuator fitting and its components, and corrective actions if
necessary. The NPRM also proposed to require eventual replacement of
all affected MLG door actuator fittings with new monoblock fittings,
which would terminate the repetitive inspections.
Actions Since the NPRM Was Issued
Since the NPRM was issued, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Union, has issued EASA Airworthiness Directive 2016-0182,
dated September 13, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus Model A319, A320, and A321 series
airplanes. The MCAI states:
On one A320 aeroplane, it was reported that one of the main
landing gear (MLG) doors could not be closed. Investigations
revealed the rupture of the actuator fitting at the actuator
attachment area on the door side. The MLG door is attached to the
aeroplane by 2 (two) hinge fittings.
This condition, if not corrected, could, under certain
circumstances, lead to detachment of a MLG door from the aeroplane,
possibly resulting in damage to the aeroplane, and/or injury to
persons on the ground.
Prompted by these findings, [Direction G[eacute]n[eacute]rale de
l'Aviation Civile] France issued * * * [an AD] * * *, to require a
MLG door actuator fitting inspection for cracks and to check the
grain direction on a batch of aeroplanes. Subsequently, DGAC France
issued * * * [an AD], retaining the requirements of DGAC France AD *
* *, which was superseded, to require an inspection of the lower
part of the MLG door actuator fitting.
After that [DGAC] AD was issued, additional investigations
revealed that damage could also appear on the nerve area
[[Page 16949]]
[of the forward monoblock fitting], in the upper part of the MLG
door actuator fitting in the area of the hinge.
Consequently, DGAC France issued F-2003-434, dated December 10,
2003 [https://ad.easa.europa.eu/ad/F-2003-454] (EASA approval 2003-
1436), retaining the requirements of [a] DGAC France AD * * *, which
was superseded, to require additional repetitive inspections. That
[DGAC] AD also included an optional terminating action, by replacing
the MLG door actuator fittings in accordance with the instructions
of Airbus Service Bulletin (SB) A320-52-1073.
After DGAC France AD F-2003-434 was issued, in the framework of
the extended service goal campaign, it was decided to make
replacement of the MLG door actuator fittings a required
modification. Consequently, EASA issued AD 2014-0166 * * *,
retaining the requirements of DGAC France AD F-2003-434, which was
superseded, and requiring replacement of the MLG door actuator
fittings with new monoblock fittings, which constitutes terminating
action for the repetitive inspections.
After EASA AD 2014-0166 [corresponding to the NPRM] was issued,
errors were identified in the compliance time definitions.
Replacement of the MLG door actuator fittings was required ``before
exceeding 48,000 flight cycles (FC) or 96,000 flight hours (FH),
whichever occurs later since aeroplane first flight'', which should
have been ``whichever occurs first''. Furthermore, since the MLG
door is an interchangeable part, the compliance time must be defined
as FC/FH accumulated by the MLG door. Furthermore, it was discovered
that one of the required inspection[s] is applicable only to a batch
of MLG door fittings.
For the reason described above, this AD retains the requirements
of EASA AD 2014-0166, which is superseded, but requires
accomplishment of the terminating action within more stringent
compliance times, and reduce[s] the applicability of one of the
required inspection[s].
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0461.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Airbus Service Bulletin A320-52-1073, Revision 04, dated
August 10, 1999.
Airbus Service Bulletin A320-52-1073, Revision 05, dated
September 28, 2006.
Airbus Service Bulletin A320-52A1086, Revision 01, dated
September 10, 1999.
Airbus Service Bulletin A320-52-1096, Revision 02, dated
July 12, 2006.
This service information describes procedures for inspections for
cracking of the MLG door actuator fitting and its components, and
corrective actions if necessary. This service information also
describes procedures for replacement of all affected MLG door actuator
fittings with new monoblock fittings. These documents are distinct
since they apply to different airplane models. 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.
Comments
We gave the public the opportunity to participate in developing
this proposed AD. We considered the comments received.
Support for the NPRM
A commenter, Kevin Grandberry, stated that he supports the
inspections of the MLG door actuator fittings specified in the NPRM.
Request To Reduce the Compliance Time for Replacing the MLG Actuator
Fitting
Airbus asked that we reduce the compliance time for the replacement
specified in paragraph (j)(1) of the proposed AD (in the NPRM) from
``whichever occurs later since the first flight of the airplane'' to
``whichever occurs first since the first flight of the airplane.''
Airbus stated that EASA updated EASA AD 2014-0166, dated July 16, 2014
(referenced in the NPRM), to correct the error noted in the compliance
time (among other changes).
We agree with the commenter's request in light of the superseded
EASA AD, which corrects the compliance time. We have changed the
compliance time specified in paragraph (j)(1) of this proposed AD
accordingly.
Request To Change Applicability
United Airlines (UA) asked that we limit the applicability of the
NPRM to the manufacturer serial numbers (MSNs) included in Airbus
Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006.
UA did not provide a reason for the request.
We do not agree with the commenter's request. The effectivity of
Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28,
2006, is based on airplanes delivered with the affected parts. However,
the parts are rotable and could be installed on MSNs other than those
identified in Airbus Service Bulletin A320-52-1073, Revision 05, dated
September 28, 2006. Therefore, this AD applies to all airplanes
identified in paragraph (c) of this AD. We have not changed this
proposed AD in this regard.
Request for Credit for Previous Accomplishment of the Optional
Terminating Action
UA asked that we give credit for modifying the airplane (as
specified in the optional terminating action in paragraph (k) of the
proposed AD (in the NPRM)) using Airbus Service Bulletin A320-52-1073,
Revision 04, dated August 10, 1999; or any prior revision. UA stated
that accomplishing any revisions (including future revisions) would
terminate the repetitive inspections required by paragraphs (g) and (h)
of the proposed AD.
We partially agree with the request. We agree to include Airbus
Service Bulletin A320-52-1073, Revision 04, dated August 10, 1999, in
this proposed AD; however, we do not agree to allow the use of any
prior version because changes to the installation procedures were added
to Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10,
1999, to prevent damage to the carbon fiber of the MLG door. We have
added Airbus Service Bulletin A320-52-1073, Revision 04, dated August
10, 1999, as a method of compliance for the optional terminating action
in paragraph (k) of this proposed AD.
Request To Extend the Compliance Time for the Inspections
Delta Air Lines (DAL) asked that we extend the compliance time
specified in paragraphs (g) and (j)(2) of the proposed AD (in the
NPRM). DAL stated that the FAA waited years to take any action on the
subject unsafe condition and, in light of that fact, the ``calendar
date'' for the compliance time in paragraph (g) of the proposed AD (in
the NPRM) should be extended from 30 to 180 days. DAL also stated that
using a calendar date for a crack growth concern is not based on
industry-accepted analysis. DAL noted that mandating the inspections
with this short interval has a significant impact on operators with
multiple aircraft that are affected by the proposed AD. DAL added that
an immediate safety concern is not evident in the speed with which the
FAA moved to enact the regulatory action, or in the details provided in
the NPRM. In addition, DAL asked that the compliance time in paragraph
(j)(2) of the proposed AD (in the NPRM) be extended from 30 days to 24
months. DAL stated that operators would have difficulty complying with
the 30-day compliance time for replacing the MLG door actuator fitting
due to the extensive time necessary to modify each door. DAL added that
the replacement should be done in a hangar environment where skilled
composite facilities and
[[Page 16950]]
technicians are available, which occurs every 24 months.
We do not agree with the commenter's requests. The compliance times
in paragraphs (g) and (j)(2) of this proposed AD are based on EASA's
assessment of the overall risk to the fleet, including the severity of
the failure and the likelihood of the failure to occur. We are unaware
of any information or data that substantiates the compliance time
change the commenter has requested, and nothing was provided by the
commenter to support the request. We also do not agree that FAA
requirements related to crack growth are based on calendar time. The
calendar time of 30 days, as retained in this proposed AD, is a grace
period to provide additional time for airplanes that have exceeded
their limit of validity of engineering data. All other compliance time
requirements are based on flight cycles and flight hours.
We also note that since this is a SNPRM, operators will have
additional time to plan for AD compliance. However, under the
provisions of paragraph (n)(1) of this proposed AD, we will consider
requests for approval of an extension of the compliance time if
sufficient data are submitted to substantiate that the new compliance
time would provide an acceptable level of safety. We have not changed
this proposed AD in this regard.
Request To Include MLG Serial Numbers
DAL asked that we change paragraph (h) of the proposed AD (in the
NPRM) to include the affected serial numbers of the left- and right-
hand doors of the MLG. DAL stated that paragraph (g) of the proposed AD
(in the NPRM) provides the door serial numbers to assist with
identifying the affected doors, and similar information should be
provided in paragraph (h) of the proposed AD (in the NPRM).
We agree with the commenter's request. Paragraph (4) of EASA AD
2016-0182, dated September 13, 2016, which corresponds to paragraph (h)
of this proposed AD, identifies the affected serial numbers. It was not
our intent to deviate from the MCAI. We have added the serial numbers
to paragraph (h) of this proposed AD.
Request To Clarify Modification Titles
UA asked that we clarify the language in paragraph (l) of the
proposed AD (in the NPRM) to add ``or Airbus Modification'' before each
modification number specified.
We agree and have clarified paragraph (l) of this proposed AD
accordingly.
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.
Costs of Compliance
We estimate that this proposed AD affects 71 airplanes of U.S.
registry.
We also estimate that it would take about 38 work-hours per product
to comply with the inspection requirements of this proposed AD. The
average labor rate is $85 per work-hour. Based on these figures, we
estimate the cost for the inspection specified in this proposed AD on
U.S. operators to be $229,330, or $3,230 per product.
We estimate that it would take about 98 work-hours per product to
comply with the MLG actuator replacement requirements of this proposed
AD. Required parts would cost about $6,258 per product. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost for the actuator replacement specified in this proposed AD on
U.S. operators to be $1,035,748, or $14,588 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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 adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2016-0461; Directorate Identifier 2014-NM-
159-AD.
(a) Comments Due Date
We must receive comments by May 22, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD, all manufacturer serial numbers.
(1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(2) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
[[Page 16951]]
(3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
(e) Reason
This AD was prompted by a report that a main landing gear (MLG)
door could not be closed due to rupture of the actuator fitting.
Later reports indicated that the forward monoblock fitting of the
MLG door actuator (referred to as the nerve area) could be damaged
after rupture of the actuator fitting. We are issuing this AD to
prevent rupture of the door actuator fittings, which could result in
detachment of an MLG door and subsequent exterior damage and
consequent reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections of MLG Door Actuator Fittings
For airplanes equipped with MLG door actuator fittings having
part number (P/N) D52880224000 or P/N D52880224001 that were
installed before the first flight of the airplane on MLG doors
identified in paragraphs (g)(1) and (g)(2) of this AD: Within 500
flight hours since the most recent high frequency eddy current
(HFEC) inspection done as specified in Airbus Service Bulletin A320-
52A1086, Revision 01, dated September 10, 1999, or within 30 days
after the effective date of this AD, whichever occurs later, perform
an HFEC inspection for cracking of the MLG door fittings, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52A1086, Revision 01, dated September 10, 1999. Repeat
the inspection thereafter at intervals not to exceed 500 flight
hours, except as provided by paragraphs (i), (j), and (k) of this
AD.
(1) Left-hand MLG doors with serial numbers (S/Ns) 1206 through
1237 inclusive, 1239 through 1247 inclusive, and 1249 through 1251
inclusive.
(2) Right-hand MLG doors with S/Ns 1208 through 1239 inclusive,
1241 through 1249 inclusive, and 1251.
(h) Repetitive Inspections of MLG Hinge and Nerve Areas
For airplanes equipped with MLG door actuator fittings having P/
N D52880224000, P/N D52880224001, P/N D52880235000, or P/N
D52880235001 that were installed before the first flight of the
airplane on MLG doors identified in paragraphs (h)(1) and (h)(2) of
this AD: Within 400 flight cycles after the effective date of this
AD, or before the accumulation of 9,000 total flight cycles since
first flight of the airplane, whichever occurs later, perform an
HFEC inspection of both hinge and nerve areas of the MLG doors for
cracking, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-52-1096, Revision 02, dated July 12,
2006. Repeat the inspection thereafter at intervals not to exceed
800 flight cycles, except as provided by paragraphs (i)(1), (j), and
(k) of this AD.
(1) Left-hand MLG doors with S/Ns 1206 through 1510 inclusive,
1548, 1564, and 2000 through 2065 inclusive.
(2) Right-hand MLG doors with S/Ns 1208 through 1519 inclusive,
1551, and 2000 through 2065 inclusive.
(i) Inspections/Corrective Actions
(1) If any crack is found during any inspection required by
paragraph (g) or (h) of this AD: Before further flight, replace the
affected MLG door actuator fittings with new monoblock fittings, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1073, Revision 05, dated September 28, 2006.
Accomplishing this replacement terminates the repetitive inspections
required by paragraphs (g) and (h) of this AD.
(2) If, during any HFEC inspection required by paragraph (g) of
this AD, no crack is found: Before further flight, perform a low
frequency eddy current (LFEC) inspection to determine the grain
direction of the raw material of each MLG actuator fitting, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52A1086, Revision 01, dated September 10, 1999.
(i) If the grain direction of the raw material is correct, the
repetitive inspections required by paragraph (g) of this AD may be
terminated.
(ii) If the grain direction of the raw material is incorrect,
repeat the HFEC inspection required by paragraph (g) of this AD at
the time specified in paragraph (g) of this AD. Replacement of the
MLG door actuator fittings with new monoblock fittings as specified
in paragraph (i)(1) of this AD terminates the repetitive inspections
required by paragraphs (g) and (i) of this AD.
(j) MLG Door Actuator Fitting Replacement
For airplanes equipped with any MLG door actuator fitting having
P/N D52880102000, P/N D52880102001, P/N D52880220000, P/N
D52880220001, P/N D52880224000, P/N D52880224001, P/N D52880235000,
or P/N D52880235001: At the later of the times specified in
paragraphs (j)(1) and (j)(2) of this AD, replace the MLG door
actuator fittings with new monoblock fittings, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-52-
1073, Revision 05, dated September 28, 2006. Accomplishing this
replacement terminates the repetitive inspections required by
paragraphs (g) and (h) of this AD.
(1) Before the accumulation of 48,000 total flight cycles or
96,000 total flight hours on the MLG door, whichever occurs first.
(2) Within 30 days after the effective date of this AD.
(k) Optional Terminating Action
Replacement of the MLG door actuator fittings with new monoblock
fittings, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10,
1999; or Airbus Service Bulletin A320-52-1073, Revision 05, dated
September 28, 2006; terminates the repetitive inspections required
by paragraphs (g) and (h) of this AD.
(l) Airplanes Excluded From Certain AD Requirements
(1) For airplanes on which Airbus Modification 24903, or Airbus
Modification 25372, or Airbus Modification 36979 has been embodied
in production, no action is required by this AD, provided that no
MLG door actuator fitting having any part number identified in
paragraph (j) of this AD has been reinstalled on the airplane since
first flight.
(2) Modification of an airplane by installing a version (P/N) of
the MLG door actuator fitting approved after the effective date of
this AD is acceptable for compliance with the requirements in
paragraph (j) of this AD, provided the conditions specified in
paragraphs (l)(2)(i) and (l)(2)(ii) are met.
(i) The MLG door actuator fitting (P/N) must be approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA).
(ii) The modification must be accomplished in accordance with
instructions approved by the Manager, International Branch, EASA, or
Airbus's EASA DOA.
(m) Parts Installation Limitation
As of the effective date of this AD, no person may install an
MLG door actuator fitting having any part number identified in
paragraph (j) of this AD on any airplane.
(n) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA Design Organization Approval (DOA). If approved by
the DOA, the approval must include the DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA
[[Page 16952]]
Airworthiness Directive 2016-0182, dated September 13, 2016, for
related information. This MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-0461.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on March 29, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-06705 Filed 4-6-17; 8:45 am]
BILLING CODE 4910-13-P