Airworthiness Directives; Airbus Airplanes, 58772-58777 [2017-26362]
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amount and percent of capital measure is
designed to limit the filing exemption to
institutions that create only low-dollar risks
to the Reserve Banks and that incur small
overdrafts relative to their capital measure.
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3. Capital Measure
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b. U.S. Branches and Agencies for Foreign
Banks
For U.S. branches and agencies of foreign
banks, net debit caps on daylight overdrafts
in Federal Reserve accounts are calculated by
applying the cap multiples for each cap
category to the FBO’s U.S. capital
equivalency measure.69 U.S. capital
equivalency is equal to 10 percent of
worldwide capital for FBOs.70
An FBO that is well capitalized (calculated
as if the FBO were subject to the Board’s
Regulation H 71) may be eligible for a
streamlined procedure (see section II.E.) for
obtaining additional collateralized intraday
credit under the maximum daylight overdraft
capacity provision.
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Revisions to Section II.E of the PSR
Policy
The Board proposes to revise Section
II.E of the ‘‘Federal Reserve Policy on
Payment System Risk’’ as follows:
E. Maximum Daylight Overdraft Capacity
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directors resolution indicating its board’s
approval of that level. * * *
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2. Streamlined Procedure for Certain FBOs
An FBO that is well capitalized (calculated
as if the FBO were subject to the Board’s
Regulation H 75) and has a self-assessed net
debit cap may request from its Reserve Bank
a streamlined procedure to obtain a
maximum daylight overdraft capacity. These
FBOs are not required to provide
documentation of the business need or obtain
the board of directors’ resolution for
collateralized capacity in an amount that
exceeds its current net debit cap (which is
based on 10 percent worldwide capital times
its cap multiple), as long as the requested
total capacity is 100 percent or less of
worldwide capital times a self-assessed cap
multiple.76 In order to ensure that intraday
liquidity risk is managed appropriately and
that the FBO will be able to repay daylight
overdrafts, eligible FBOs under the
streamlined procedure will be subject to
initial and periodic reviews of liquidity plans
that are analogous to the liquidity reviews
undergone by U.S. institutions.77 If an
eligible FBO requests capacity in excess of
100 percent of worldwide capital times the
self-assessed cap multiple, it would be
subject to the general procedure.
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By order of the Board of Governors of the
Federal Reserve System, December 8, 2017.
Ann E. Misback,
Secretary of the Board.
[FR Doc. 2017–26923 Filed 12–13–17; 8:45 am]
1. General Procedure
An institution with a self-assessed net
debit cap that wishes to expand its daylight
overdraft capacity by pledging collateral
should consult with its administrative
Reserve Bank. The Reserve Bank will work
with an institution that requests additional
daylight overdraft capacity to determine the
appropriate maximum daylight overdraft
capacity level. In considering the
institution’s request, the Reserve Bank will
evaluate the institution’s rationale for
requesting additional daylight overdraft
capacity as well as its financial and
supervisory information. The financial and
supervisory information considered may
include, but is not limited to, capital and
liquidity ratios, the composition of balance
sheet assets, and CAMELS or other
supervisory ratings and assessments. An
institution approved for a maximum daylight
overdraft capacity level must submit at least
once in each twelve-month period a board of
BILLING CODE 6210–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1100; Product
Identifier 2017–NM–077–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
75 See
sradovich on DSK3GMQ082PROD with PROPOSALS
69 The
term ‘‘U.S. capital equivalency’’ is used in
this context to refer the particular measure calculate
net debit caps and does not necessarily represent
an appropriate for supervisory or other purposes.
70 FBOs that wish to establish a non-zero net debit
cap must report their worldwide capital on the
Annual Daylight Overdraft Capital Report for U.S.
Branches and Agencies of Foreign Banks (FR 2225).
The instructions for FR explain how FBOs should
calculate their worldwide capital. See https://
www.federalreserve.gov/apps/reportforms/
reportdetail.aspx?sOoYJ+5BzDZ1kLYTc+ZpEQ==.
71 See 12 CFR 208.43(b).
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12 CFR 208.43(b).
example, an FBO that is well capitalized is
eligible for uncollateralized capacity of 10 percent
of worldwide capital times the cap multiple. The
streamlined max cap procedure would provide such
an institution with additional collateralized
capacity of 90 percent of worldwide capital times
the cap multiple. As noted above, FBOs report their
worldwide capital on the Annual Daylight
Overdraft Capital Report for U.S. Branches and
Agencies of Foreign Banks (FR 2225).
77 The liquidity reviews will be conducted by the
administrative Reserve Bank, in consultation with
each FBO’s home country supervisor.
76 For
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We propose to supersede
Airworthiness Directive (AD) 2015–15–
13, which applies to certain Airbus
Model A319 series airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes; and Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. AD 2015–15–13 requires
modification of the potable water
service panel and waste water service
panel, including doing applicable
related investigative and corrective
actions. Since we issued AD 2015–15–
13, further investigations linked to
widespread fatigue damage (WFD)
analysis highlighted that, to meet the
WFD requirements, it is necessary that
the affected modification not be
accomplished before reaching a certain
threshold. This proposed AD would
require modification of the waste water
and potable water service panels with
new compliance times. This proposed
AD would also remove certain airplanes
from the applicability and add Model
A320–216 airplanes to the applicability.
We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by January 29, 2018.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue
SW, Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
SUMMARY:
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–2017–
1100; or in person at the Docket
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Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–
1149.
SUPPLEMENTARY INFORMATION:
sradovich on DSK3GMQ082PROD with PROPOSALS
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2017–1100; Product Identifier 2017–
NM–077–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
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as WFD. It is
associated with general degradation of
large areas of structure with similar
structural details and stress levels. As
an airplane ages, WFD will likely occur,
and will certainly occur if the airplane
is operated long enough without any
intervention.
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The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
We issued AD 2015–15–13,
Amendment 39–18223 (80 FR 45857,
August 3, 2015) (‘‘AD 2015–15–13’’), for
certain Airbus Model A319 series
airplanes; Model A320–211, –212, –214,
–231,–232, and –233 airplanes; and
Model A321 series airplanes. AD 2015–
15–13 was prompted by reports of
cracks that could be initiated at the
waste water service panel area and the
potable water service panel area. AD
2015–15–13 requires modification of the
potable water service panel and waste
water service panel, including doing
applicable related investigative and
corrective actions. We issued AD 2015–
15–13 to prevent any cracking at the
waste water service panel area and the
potable water service panel area, which
could affect the structural integrity of
the airplane.
Since we issued AD 2015–15–13,
further investigations linked to WFD
analysis highlighted that, to meet the
WFD requirements, it is necessary that
the affected modification is not
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accomplished before reaching a certain
threshold by imposing a ‘‘window of
embodiment.’’
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0098, dated June 7, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Airbus Model
A319 series airplanes; Airbus Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes; and Airbus
Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
The MCAI states:
During the full scale fatigue test on A320–
200, it was noticed that, due to fatigue, cracks
could initiate at the potable water and waste
water service panel areas.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
Prompted by these findings, Airworthiness
Limitation Section (ALS) Part 2 tasks were
introduced for the affected aeroplanes. Since
those actions were taken, Airbus developed
production mod 160055 and mod 160056 to
embody reinforcements (cold working on
certain rivet rows) of the potable water and
waste water service panels, and published
associated Airbus Service Bulletin (SB)
A320–53–1272 and Airbus SB A320–53–1267
for in-service embodiment. Complementary
design office studies highlighted that the
‘‘Sharklets’’ installation on certain aeroplanes
has a significant impact on the aeroplane
structure (particularly, A319 and A320 postmod 160001, A320 post-SB A320–57–1193
(mod 160080), and A321 post-mod 160021),
leading to different compliance times,
depending on aeroplane configuration.
Consequently, EASA issued AD 2014–0081
[which corresponds to FAA AD 2015–15–13]
to require reinforcement of the potable water
and waste water service panels.
Accomplishment of these modifications
cancelled the need for the related ALS Part
2 Tasks.
Since that AD was issued, further
investigations linked to the Widespread
Fatigue Damage (WFD) analysis highlighted
that, to meet the WFD requirements, it is
necessary that the affected modification is
not accomplished before reaching a certain
threshold, by imposing a so-called ‘‘window
of embodiment’’. Consequently, Airbus
revised SB A320–53–1272 (now at revision
(Rev.) 04) and SB A320–53–1267 (now at
Rev. 05).
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0081, which is superseded, and
introduces additional compliance times for
those actions.
This proposed AD would also remove
Model A319 series airplanes on which
modification 28162, 28238, and 28342
have been embodied (‘‘Corporate Jet’’
modifications) from the applicability
because production modifications
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mitigated the risk associated with the
unsafe condition. This proposed AD
would also add Model A320–216
airplanes to the applicability because
those airplanes are affected by the
identified unsafe condition.
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–2017–
1100.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–53–1267, Revision 05, dated
November 29, 2016, which describes
procedures for modifying the waste
water service panel. Airbus has also
issued Service Bulletin A320–53–1272,
Revision 04, dated November 29, 2016,
which describes procedures for
modifying the potable water service
panel. Both modifications include a
check of the diameter of the holes of
removed fasteners, a related
investigative action (rotating probe
inspection for cracking on the holes of
the removed fasteners) and a corrective
action (repair). This service information
is reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
sradovich on DSK3GMQ082PROD with PROPOSALS
Explanation of Compliance Time
The compliance time for the
replacement specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
replaced before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
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Costs of Compliance
We estimate that this proposed AD
affects 851 airplanes of U.S. registry.
We also estimate that it would take
about 27 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $700 per
product. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $2,548,745, or
$2,995 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
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:
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2015–15–13, Amendment 39–18223 (80
FR 45857, August 3, 2015), and adding
the following new AD:
■
Airbus: Docket No. FAA–2017–1100; Product
Identifier 2017–NM–077–AD.
(a) Comments Due Date
We must receive comments by January 29,
2018.
(b) Affected ADs
This AD replaces AD 2015–15–13,
Amendment 39–18223 (80 FR 45857, August
3, 2015) (‘‘AD 2015–15–13’’).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, certificated in any category, except for
those airplanes on which Airbus
modification 160055 or modification 160056
has been embodied in production, and except
for Model A319 series airplanes on which
modification 28162, 28238, and 28342 have
been embodied (‘‘Corporate Jet’’).
(1) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(2) Airbus Model A320–211, –212, –214,
–216, –231, –232, and –233 airplanes.
(3) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
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that the potable water and waste water
service panel areas are subject to widespread
fatigue damage (WFD). We are issuing this
AD to prevent cracking of the potable water
and waste water service panel areas, which
could result in reduced structural integrity of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Modification of the Potable Water Service
Panel
(1) Within the compliance times specified
in Table 1 to paragraphs (g)(1) and (i) of this
AD, as applicable, modify the potable water
service panel, including doing a check of the
diameter of the holes of removed fasteners,
and do all applicable related investigative
and corrective actions, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–53–1272, Revision 04,
dated November 29, 2016, except as required
by paragraph (g)(2) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
TABLE 1 TO PARAGRAPHS (g)(1) AND (i) OF THIS AD—COMPLIANCE TIMES FOR THE PORTABLE WATER SERVICE PANEL
REINFORCEMENT
Compliance time maximum
(before the accumulation of the
specified total flight cycles since
the airplane’s first flight)
Affected airplanes *
Compliance time minimum **
A319, pre-modification 160001 and pre-service bulletin A320–57–1193
A319, post-modification 160001 or post-service bulletin A320–57–1193
A320, pre-modification 160001 and pre-service bulletin A320–57–1193
A320, post-modification 160001 or post-service bulletin A320–57–1193
A321–100 .................................................................................................
A321–200 pre-modification 160021 .........................................................
A321–200 post-modification 160021 .......................................................
33,100 total flight cycles ...............
None ..............................................
25,100 total flight cycles ...............
None ..............................................
25,100 total flight cycles ...............
22,100 total flight cycles ...............
None ..............................................
48,500
46,000
54,200
48,300
60,000
60,000
60,000
total
total
total
total
total
total
total
flight
flight
flight
flight
flight
flight
flight
cycles.
cycles.
cycles.
cycles.
cycles.
cycles.
cycles.
* A321–111, A321–112 and A321-131 airplanes are collectively referred to as ‘‘A321–100.’’ Similarly, A321–211, A321–212, A321–213, A321–
231 and A321–232 airplanes are collectively referred to as ‘‘A321-200’’.
** Not before accumulating the specified total flight cycles since the airplane’s first flight.
(2) Where Airbus Service Bulletin A320–
53–1272, Revision 04, dated November 29,
2016, specifies to contact Airbus for
appropriate action, and specifies that action
as ‘‘RC’’ (Required for Compliance): Before
further flight, accomplish corrective actions
in accordance with the procedures specified
in paragraph (m)(2) of this AD.
(h) Modification of the Waste Water Service
Panel
(1) Within the compliance times specified
in Table 2 to paragraphs (h)(1) and (i) of this
AD, as applicable, modify the waste water
service panel, including doing a check of the
diameter of the holes of removed fasteners,
and do all applicable related investigative
and corrective actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1267, Revision 05,
dated November 29, 2016, except as required
by paragraph (h)(2) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
TABLE 2 TO PARAGRAPHS (h)(1) AND (i) OF THIS AD—COMPLIANCE TIMES FOR THE WASTE WATER SERVICE PANEL
REINFORCEMENT
Compliance time minimum **
Compliance time maximum
A319, pre-modification
160001 and pre-service
bulletin A320–57–1193.
A319, post-modification
160001 or post-service
bulletin A320–57–1193.
A320, pre-modification
160001 and pre-service
bulletin A320–57–1193.
28,600 total flight cycles ....................
Before the accumulation of 44,400 total flight cycles since the airplane’s first
flight.
None ...................................................
Before the accumulation of 43,600 total flight cycles since the airplane’s first
flight.
35,800 total flight cycles ....................
A320, post-modification
160001 or post-service
bulletin A320–57–1193.
A321–100 ........................
5,400 total flight cycles ......................
Before the accumulation of 46,000 total flight cycles since the airplane’s first
flight; or within 2,300 flight cycles since the last accomplishment of Airworthiness Limitation Section (ALS) Part 2 Task 534126–01–3 without exceeding 48,000 total flight cycles since the airplane’s first flight; whichever
occurs later.
Before the accumulation of 39,200 total flight cycles since the airplane’s first
flight.
A321–200 pre-modification 160021.
A321–200 post-modification 160021.
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Affected airplanes *
35,700 total flight cycles ....................
36,900 total flight cycles ....................
None ...................................................
Before the accumulation of 52,500 total flight cycles since the airplane’s first
flight.
Before the accumulation of 53,500 total flight cycles since the airplane’s first
flight.
Before the accumulation of 51,200 total flight cycles since the airplane’s first
flight.
* A321–111, A321–112 and A321–131 airplanes are collectively referred to as ‘‘A321–100.’’ Similarly, A321–211, A321–212, A321–213, A321–
231 and A321–232 airplanes are collectively referred to as ‘‘A321–200’’.
** Not before accumulating the specified total flight cycles since the airplane’s first flight.
(2) Where Airbus Service Bulletin A320–
53–1267, Revision 05, dated November 29,
2016, specifies to contact Airbus for
appropriate action, and specifies that action
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as ‘‘RC’’ (Required for Compliance): Before
further flight, accomplish corrective actions
in accordance with the procedures specified
in paragraph (m)(2) of this AD.
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Sfmt 4702
(i) Corrective Action for Airplanes With
Certain Modifications
For airplanes on which the modification,
as required by paragraph (g) or (h) of this AD,
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Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules
as applicable, was accomplished before
reaching the applicable minimum
compliance time as defined in Table 1 to
paragraphs (g)(1) and (i) of this AD or Table
2 to paragraphs (h)(1) and (i) of this AD:
Before exceeding 60,000 flight cycles since
the airplane’s first flight, contact the
Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA)
for approved corrective action instructions
and accomplish those instructions
accordingly.
(j) Terminating Action for Airplanes on
Which the Potable Water Service Panel
Modification Is Done
Modification of an airplane as required by
paragraph (g) of this AD terminates the
requirement for accomplishing the ALS Part
2 task for that airplane as specified in Table
3 to paragraph (j) of this AD, as applicable.
TABLE 3 TO PARAGRAPH (j) OF THIS AD—ALS PART 2 TASK TERMINATED AFTER POTABLE WATER SERVICE PANEL
MODIFICATION
ALS Part 2
task No.
Affected airplanes
A319, pre-modification 160001 and pre-service bulletin A320–57–1193 ...........................................................................................
A319, post-modification 160001 or post-service bulletin A320–57–1193 ...........................................................................................
A320, pre-modification 160001 and pre-service bulletin A320–57–1193 ...........................................................................................
A320, post-modification 160001 or post-service bulletin A320–57–1193 ...........................................................................................
A321 pre-modification 160021 .............................................................................................................................................................
A321 post-modification 160021 ...........................................................................................................................................................
(k) Terminating Action for Airplanes on
Which the Waste Water Service Panel
Modification Is Done
Modification of an airplane as required by
paragraph (h) of this AD terminates the
534125–01–2
534125–01–5
534125–01–3
534125–01–6
534125–01–4
534125–01–7
requirement for accomplishing the ALS Part
2 task for that airplane as specified in Table
4 to paragraph (k) of this AD, as applicable.
TABLE 4 TO PARAGRAPH (k) OF THIS AD—ALS PART 2 TASK TERMINATED AFTER WASTE WATER SERVICE PANEL
MODIFICATION
ALS Part 2
task No.
Affected airplanes
A319, pre-modification 160001 and pre-service bulletin A320-57–1193 ............................................................................................
A319, post-modification 160001 or post-service bulletin A320-57–1193 ............................................................................................
A320, pre-modification 160001 and pre-service bulletin A320-57–1193 ............................................................................................
A320, post-modification 160001 or post-service bulletin A320-57–1193 ............................................................................................
A321 pre-modification 160021 .............................................................................................................................................................
A321 post-modification 160021 ...........................................................................................................................................................
sradovich on DSK3GMQ082PROD with PROPOSALS
(l) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g) of this AD
if those actions were performed before the
effective date of this AD using the service
information in paragraphs (l)(1)(i) through
(l)(1)(iv) of this AD.
(i) Airbus Service Bulletin A320–53–1272,
Revision 00, dated January 10, 2013, which
is not incorporated by reference in this AD.
(ii) Airbus Service Bulletin A320–53–1272,
Revision 01, dated August 6, 2013, which is
not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A320–53–
1272, Revision 02, dated May 19, 2014,
which was incorporated by reference in AD
2015–15–13.
(iv) Airbus Service Bulletin A320–53–
1272, Revision 03, dated November 26, 2015,
which is not incorporated by reference in this
AD.
(2) This paragraph provides credit for
actions required by paragraph (h) of this AD
if those actions were performed before the
effective date of this AD using the service
information in paragraphs (l)(2)(i) through
(l)(2)(v) of this AD.
(i) Airbus Service Bulletin A320–53–1267,
Revision 00, dated June 24, 2013, which is
not incorporated by reference in this AD.
VerDate Sep<11>2014
17:01 Dec 13, 2017
Jkt 244001
(ii) Airbus Service Bulletin A320–53–1267,
Revision 01, dated October 2, 2013, which is
not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A320–53–
1267, Revision 02, dated May 19, 2014,
which was incorporated by reference in AD
2015–15–13.
(iv) Airbus Service Bulletin A320–53–
1267, Revision 03, dated November 26, 2015,
which is not incorporated by reference in this
AD.
(v) Airbus Service Bulletin A320–53–1267,
Revision 04, dated February 1, 2016, which
is not incorporated by reference in this AD.
(m) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, 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 Section, send it
to the attention of the person identified in
paragraph (n)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
PO 00000
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Fmt 4702
Sfmt 4702
534126–01–2
534126–01–5
534126–01–3
534126–01–6
534126–01–4
534126–01–7
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (g)(2) and (h)(2) of
this AD: If any service information contains
procedures or tests that are identified as RC,
those procedures and tests must be done to
comply with this AD; any procedures or tests
that are not identified as RC are
recommended. Those procedures and tests
that are not identified as RC may be deviated
from using accepted methods in accordance
with the operator’s maintenance or
inspection program without obtaining
approval of an AMOC, provided the
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
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Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules
changes to procedures or tests identified as
RC require approval of an AMOC.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2017–0098, dated
June 7, 2017, 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–
2017–1100.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW,
Renton, WA 98057–3356; telephone 425–
227–1405; fax 425–227–1149.
(3) 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 Standards Branch, 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
November 29, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–26362 Filed 12–13–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Office of the Secretary
14 CFR Part 241
Amendatory instructions 3
through 6 of the proposed rule
published July 15, 2011 (76 FR 41726),
are withdrawn as of December 14, 2017.
ADDRESSES: Electronic Access: You can
view and download related documents
and public comments by going to the
website https://www.regulations.gov.
Enter the docket number DOT–RITA–
2011–0001 in the search field.
FOR FURTHER INFORMATION CONTACT:
Zeenat Iqbal and Blane A. Workie,
Office of Aviation Enforcement and
Proceedings, 1200 New Jersey SE, Room
W96–414, Washington, DC 20590, (202)
366–9893, zeenat.iqbal@dot.gov (email).
SUPPLEMENTARY INFORMATION:
DATES:
Background
On July 7, 2011, the Office of the
Secretary issued a notice of proposed
rulemaking (NPRM) proposing to collect
detailed information about ancillary fees
paid by airline consumers to determine
the total amount of fees carriers collect
through the a la carte pricing approach
for optional services related to air
transportation. The Department also
proposed to alter its matrix for
collecting and publishing data on
mishandled baggage and to collect
information regarding damage, delay or
loss of wheelchairs and scooters
transported in the aircraft cargo
compartment. The final rule relating to
reporting of data for mishandled
baggage and wheelchairs (2104–AE41)
was issued on November 2, 2016 (81 FR
76300). We are withdrawing the other
topic covered in the proposed rule, the
reporting of airline fee revenue.
[Docket No. RITA–2011–0001]
The NPRM
RIN 2105–AE31
In the NPRM, the Department
proposed to create two stand-alone
reporting forms, designated P–9 and P–
9.1, to capture ancillary revenues.
Specifically, air carriers with annual
reporting revenue of $20 million or
more would be required to submit the
P–9 form quarterly and air carriers with
annual reporting revenue below $20
million would be required to submit the
form P–9.1 on a semiannual basis. The
information required by the two
proposed schedules was identical; they
differed only in the required reporting
frequency. The NPRM also proposed to
define ancillary revenues as those
charges paid by airline passengers that
are not included in the standard ticket
fare. The Department solicited
comments on which items should be
specifically identified as ancillary
revenues, and proposed to collect data
on 19 separate charges for optional
services. The categories included: (1)
Booking fees, (2) priority check-in and
Ancillary Airline Passenger Revenues
Office of the Secretary,
Department of Transportation.
ACTION: Proposed rule; withdrawal.
AGENCY:
The Department of
Transportation (the Department) is
withdrawing a notice of proposed
rulemaking (NPRM) published on July
15, 2011 that proposed to collect
detailed revenue information regarding
airline imposed fees from those air
carriers meeting the definition of a large
certificated air carrier. We are
withdrawing this rulemaking in light of
the comments we received. The
withdrawal of this rulemaking
corresponds with the Department’s and
Administration’s priorities and is
consistent with the Executive Order
13771, Reducing Regulation and
Controlling Regulatory Costs, January
30, 2017.
sradovich on DSK3GMQ082PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
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58777
security screening, (3) baggage, (4) inflight medical equipment, (5) in-flight
entertainment/internet access, (6) sleep
sets, (7) in-flight food/non-alcoholic
drinks, (8) alcoholic drinks, (9) pets,
(10) seating assignments, (11)
reservation cancellation and change
fees; (12) charges for lost ticket; (13)
unaccompanied minor/passenger
assistance fee; (14) frequent flyer points/
points acceleration; (15) commissions
on travel packages; (16) travel
insurance; (17) duty-free and retail
sales; (18) one-time access to lounges
and (19) other.
Comments Received
In response to the 2011 NPRM, the
Department received approximately 280
comments from airlines, airports, trade
associations, unions, consumer groups
and private citizens who use this data.
There was wide support among
consumers and consumer rights groups
for the proposed rule’s reporting
requirements. Consumers and consumer
rights groups, as well as ACI–NA and
Southwest Airlines, commented that the
reporting requirement would bring the
benefits of both increased transparency
and improved data corroboration
regarding the impact of ancillary fees on
the Airport and Airway Trust Fund.
On the other hand, most airlines and
industry organizations commented that
the proposed rule will not benefit the
public because the Department has not
demonstrated a need for this
information. They asserted that the rule
will not increase the transparency of
pricing for airline revenues. Airlines
also commented that if the justification
for this rule is to tax ancillary revenues,
the Department must state that
justification. In addition, several airlines
and industry groups suggested that the
Department underestimated the
proposed rule’s economic burden on
industry.
With regard to the proposed 19
categories, industry groups, consumer
groups and airlines commented that the
Department failed to justify the
proposed categories and suggested
various changes to the list of 19 charges
for which air carriers would have to
report revenues under the proposed
rule. Carriers also expressed concern
that the proposed reporting
requirements would require carriers to
reveal proprietary information to their
competitors. Some carriers suggested
that there is no correlation between a
carrier’s disclosure of itemized aggregate
revenue data and consumer concerns
regarding fare transparency. Southwest
Airlines, which supported the
Department’s stated goal of making
ticket pricing more transparent for
E:\FR\FM\14DEP1.SGM
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]]>Agencies
[Federal Register Volume 82, Number 239 (Thursday, December 14, 2017)]
[Proposed Rules]
[Pages 58772-58777]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26362]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1100; Product Identifier 2017-NM-077-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-15-
13, which applies to certain Airbus Model A319 series airplanes; Model
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015-
15-13 requires modification of the potable water service panel and
waste water service panel, including doing applicable related
investigative and corrective actions. Since we issued AD 2015-15-13,
further investigations linked to widespread fatigue damage (WFD)
analysis highlighted that, to meet the WFD requirements, it is
necessary that the affected modification not be accomplished before
reaching a certain threshold. This proposed AD would require
modification of the waste water and potable water service panels with
new compliance times. This proposed AD would also remove certain
airplanes from the applicability and add Model A320-216 airplanes to
the applicability. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by January 29,
2018.
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus,
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email [email protected]; internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Standards Branch, 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-2017-
1100; or in person at the Docket
[[Page 58773]]
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this proposed AD, the
regulatory evaluation, any comments received, and other information.
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, 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 proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-1100;
Product Identifier 2017-NM-077-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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as WFD. It is associated with general
degradation of large areas of structure with similar structural details
and stress levels. As an airplane ages, WFD will likely occur, and will
certainly occur if the airplane is operated long enough without any
intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
We issued AD 2015-15-13, Amendment 39-18223 (80 FR 45857, August 3,
2015) (``AD 2015-15-13''), for certain Airbus Model A319 series
airplanes; Model A320-211, -212, -214, -231,-232, and -233 airplanes;
and Model A321 series airplanes. AD 2015-15-13 was prompted by reports
of cracks that could be initiated at the waste water service panel area
and the potable water service panel area. AD 2015-15-13 requires
modification of the potable water service panel and waste water service
panel, including doing applicable related investigative and corrective
actions. We issued AD 2015-15-13 to prevent any cracking at the waste
water service panel area and the potable water service panel area,
which could affect the structural integrity of the airplane.
Since we issued AD 2015-15-13, further investigations linked to WFD
analysis highlighted that, to meet the WFD requirements, it is
necessary that the affected modification is not accomplished before
reaching a certain threshold by imposing a ``window of embodiment.''
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0098, dated June 7, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A319 series airplanes; Airbus Model A320-211, -212, -214, -216, -231, -
232, and -233 airplanes; and Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. The MCAI states:
During the full scale fatigue test on A320-200, it was noticed
that, due to fatigue, cracks could initiate at the potable water and
waste water service panel areas.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
Prompted by these findings, Airworthiness Limitation Section
(ALS) Part 2 tasks were introduced for the affected aeroplanes.
Since those actions were taken, Airbus developed production mod
160055 and mod 160056 to embody reinforcements (cold working on
certain rivet rows) of the potable water and waste water service
panels, and published associated Airbus Service Bulletin (SB) A320-
53-1272 and Airbus SB A320-53-1267 for in-service embodiment.
Complementary design office studies highlighted that the
``Sharklets'' installation on certain aeroplanes has a significant
impact on the aeroplane structure (particularly, A319 and A320 post-
mod 160001, A320 post-SB A320-57-1193 (mod 160080), and A321 post-
mod 160021), leading to different compliance times, depending on
aeroplane configuration.
Consequently, EASA issued AD 2014-0081 [which corresponds to FAA
AD 2015-15-13] to require reinforcement of the potable water and
waste water service panels. Accomplishment of these modifications
cancelled the need for the related ALS Part 2 Tasks.
Since that AD was issued, further investigations linked to the
Widespread Fatigue Damage (WFD) analysis highlighted that, to meet
the WFD requirements, it is necessary that the affected modification
is not accomplished before reaching a certain threshold, by imposing
a so-called ``window of embodiment''. Consequently, Airbus revised
SB A320-53-1272 (now at revision (Rev.) 04) and SB A320-53-1267 (now
at Rev. 05).
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0081, which is superseded, and
introduces additional compliance times for those actions.
This proposed AD would also remove Model A319 series airplanes on
which modification 28162, 28238, and 28342 have been embodied
(``Corporate Jet'' modifications) from the applicability because
production modifications
[[Page 58774]]
mitigated the risk associated with the unsafe condition. This proposed
AD would also add Model A320-216 airplanes to the applicability because
those airplanes are affected by the identified unsafe condition.
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-2017-
1100.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-53-1267, Revision 05, dated
November 29, 2016, which describes procedures for modifying the waste
water service panel. Airbus has also issued Service Bulletin A320-53-
1272, Revision 04, dated November 29, 2016, which describes procedures
for modifying the potable water service panel. Both modifications
include a check of the diameter of the holes of removed fasteners, a
related investigative action (rotating probe inspection for cracking on
the holes of the removed fasteners) and a corrective action (repair).
This service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Explanation of Compliance Time
The compliance time for the replacement specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
We also estimate that it would take about 27 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $700
per product. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $2,548,745, or $2,995 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
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 removing Airworthiness Directive (AD)
2015-15-13, Amendment 39-18223 (80 FR 45857, August 3, 2015), and
adding the following new AD:
Airbus: Docket No. FAA-2017-1100; Product Identifier 2017-NM-077-AD.
(a) Comments Due Date
We must receive comments by January 29, 2018.
(b) Affected ADs
This AD replaces AD 2015-15-13, Amendment 39-18223 (80 FR 45857,
August 3, 2015) (``AD 2015-15-13'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
except for those airplanes on which Airbus modification 160055 or
modification 160056 has been embodied in production, and except for
Model A319 series airplanes on which modification 28162, 28238, and
28342 have been embodied (``Corporate Jet'').
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes.
(3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating
[[Page 58775]]
that the potable water and waste water service panel areas are
subject to widespread fatigue damage (WFD). We are issuing this AD
to prevent cracking of the potable water and waste water service
panel areas, which could result in reduced structural integrity of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Modification of the Potable Water Service Panel
(1) Within the compliance times specified in Table 1 to
paragraphs (g)(1) and (i) of this AD, as applicable, modify the
potable water service panel, including doing a check of the diameter
of the holes of removed fasteners, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1272,
Revision 04, dated November 29, 2016, except as required by
paragraph (g)(2) of this AD. Do all applicable related investigative
and corrective actions before further flight.
Table 1 to Paragraphs (g)(1) and (i) of This AD--Compliance Times for the Portable Water Service Panel
Reinforcement
----------------------------------------------------------------------------------------------------------------
Compliance time maximum
(before the accumulation of
Affected airplanes * Compliance time minimum ** the specified total flight
cycles since the airplane's
first flight)
----------------------------------------------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service 33,100 total flight cycles... 48,500 total flight cycles.
bulletin A320-57-1193.
A319, post-modification 160001 or post-service None......................... 46,000 total flight cycles.
bulletin A320-57-1193.
A320, pre-modification 160001 and pre-service 25,100 total flight cycles... 54,200 total flight cycles.
bulletin A320-57-1193.
A320, post-modification 160001 or post-service None......................... 48,300 total flight cycles.
bulletin A320-57-1193.
A321-100.......................................... 25,100 total flight cycles... 60,000 total flight cycles.
A321-200 pre[dash]modification 160021............. 22,100 total flight cycles... 60,000 total flight cycles.
A321-200 post[dash]modification 160021............ None......................... 60,000 total flight cycles.
----------------------------------------------------------------------------------------------------------------
* A321-111, A321-112 and A321[dash]131 airplanes are collectively referred to as ``A321-100.'' Similarly, A321-
211, A321-212, A321-213, A321-231 and A321-232 airplanes are collectively referred to as ``A321[dash]200''.
** Not before accumulating the specified total flight cycles since the airplane's first flight.
(2) Where Airbus Service Bulletin A320-53-1272, Revision 04,
dated November 29, 2016, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (m)(2) of this
AD.
(h) Modification of the Waste Water Service Panel
(1) Within the compliance times specified in Table 2 to
paragraphs (h)(1) and (i) of this AD, as applicable, modify the
waste water service panel, including doing a check of the diameter
of the holes of removed fasteners, and do all applicable related
investigative and corrective actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1267,
Revision 05, dated November 29, 2016, except as required by
paragraph (h)(2) of this AD. Do all applicable related investigative
and corrective actions before further flight.
Table 2 to Paragraphs (h)(1) and (i) of This AD--Compliance Times for the Waste Water Service Panel
Reinforcement
----------------------------------------------------------------------------------------------------------------
Affected airplanes * Compliance time minimum ** Compliance time maximum
----------------------------------------------------------------------------------------------------------------
A319, pre-modification 160001 28,600 total flight cycles..................... Before the accumulation of
and pre-service bulletin A320- 44,400 total flight cycles
57-1193. since the airplane's first
flight.
A319, post-modification 160001 None........................................... Before the accumulation of
or post-service bulletin A320- 43,600 total flight cycles
57-1193. since the airplane's first
flight.
A320, pre-modification 160001 35,800 total flight cycles..................... Before the accumulation of
and pre-service bulletin A320- 46,000 total flight cycles
57-1193. since the airplane's first
flight; or within 2,300 flight
cycles since the last
accomplishment of
Airworthiness Limitation
Section (ALS) Part 2 Task
534126-01-3 without exceeding
48,000 total flight cycles
since the airplane's first
flight; whichever occurs
later.
A320, post-modification 160001 5,400 total flight cycles...................... Before the accumulation of
or post-service bulletin A320- 39,200 total flight cycles
57-1193. since the airplane's first
flight.
A321-100...................... 36,900 total flight cycles..................... Before the accumulation of
52,500 total flight cycles
since the airplane's first
flight.
A321-200 pre-modification 35,700 total flight cycles..................... Before the accumulation of
160021. 53,500 total flight cycles
since the airplane's first
flight.
A321-200 post-modification None........................................... Before the accumulation of
160021. 51,200 total flight cycles
since the airplane's first
flight.
----------------------------------------------------------------------------------------------------------------
* A321-111, A321-112 and A321-131 airplanes are collectively referred to as ``A321-100.'' Similarly, A321-211,
A321-212, A321-213, A321-231 and A321-232 airplanes are collectively referred to as ``A321-200''.
** Not before accumulating the specified total flight cycles since the airplane's first flight.
(2) Where Airbus Service Bulletin A320-53-1267, Revision 05,
dated November 29, 2016, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (m)(2) of this
AD.
(i) Corrective Action for Airplanes With Certain Modifications
For airplanes on which the modification, as required by
paragraph (g) or (h) of this AD,
[[Page 58776]]
as applicable, was accomplished before reaching the applicable
minimum compliance time as defined in Table 1 to paragraphs (g)(1)
and (i) of this AD or Table 2 to paragraphs (h)(1) and (i) of this
AD: Before exceeding 60,000 flight cycles since the airplane's first
flight, contact the Manager, International Section, Transport
Standards Branch, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA) for
approved corrective action instructions and accomplish those
instructions accordingly.
(j) Terminating Action for Airplanes on Which the Potable Water Service
Panel Modification Is Done
Modification of an airplane as required by paragraph (g) of this
AD terminates the requirement for accomplishing the ALS Part 2 task
for that airplane as specified in Table 3 to paragraph (j) of this
AD, as applicable.
Table 3 to Paragraph (j) of This AD--ALS Part 2 Task Terminated After
Potable Water Service Panel Modification
------------------------------------------------------------------------
ALS Part 2
Affected airplanes task No.
------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service bulletin 534125-01-2
A320-57-1193...........................................
A319, post-modification 160001 or post-service bulletin 534125-01-5
A320-57-1193...........................................
A320, pre-modification 160001 and pre-service bulletin 534125-01-3
A320-57-1193...........................................
A320, post-modification 160001 or post-service bulletin 534125-01-6
A320-57-1193...........................................
A321 pre-modification 160021............................ 534125-01-4
A321 post-modification 160021........................... 534125-01-7
------------------------------------------------------------------------
(k) Terminating Action for Airplanes on Which the Waste Water Service
Panel Modification Is Done
Modification of an airplane as required by paragraph (h) of this
AD terminates the requirement for accomplishing the ALS Part 2 task
for that airplane as specified in Table 4 to paragraph (k) of this
AD, as applicable.
Table 4 to Paragraph (k) of This AD--ALS Part 2 Task Terminated After
Waste Water Service Panel Modification
------------------------------------------------------------------------
ALS Part 2
Affected airplanes task No.
------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service bulletin 534126-01-2
A320[dash]57-1193......................................
A319, post-modification 160001 or post-service bulletin 534126-01-5
A320[dash]57-1193......................................
A320, pre-modification 160001 and pre-service bulletin 534126-01-3
A320[dash]57-1193......................................
A320, post-modification 160001 or post-service bulletin 534126-01-6
A320[dash]57-1193......................................
A321 pre-modification 160021............................ 534126-01-4
A321 post-modification 160021........................... 534126-01-7
------------------------------------------------------------------------
(l) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g) of this AD if those actions were performed before the
effective date of this AD using the service information in
paragraphs (l)(1)(i) through (l)(1)(iv) of this AD.
(i) Airbus Service Bulletin A320-53-1272, Revision 00, dated
January 10, 2013, which is not incorporated by reference in this AD.
(ii) Airbus Service Bulletin A320-53-1272, Revision 01, dated
August 6, 2013, which is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A320-53-1272, Revision 02, dated
May 19, 2014, which was incorporated by reference in AD 2015-15-13.
(iv) Airbus Service Bulletin A320-53-1272, Revision 03, dated
November 26, 2015, which is not incorporated by reference in this
AD.
(2) This paragraph provides credit for actions required by
paragraph (h) of this AD if those actions were performed before the
effective date of this AD using the service information in
paragraphs (l)(2)(i) through (l)(2)(v) of this AD.
(i) Airbus Service Bulletin A320-53-1267, Revision 00, dated
June 24, 2013, which is not incorporated by reference in this AD.
(ii) Airbus Service Bulletin A320-53-1267, Revision 01, dated
October 2, 2013, which is not incorporated by reference in this AD.
(iii) Airbus Service Bulletin A320-53-1267, Revision 02, dated
May 19, 2014, which was incorporated by reference in AD 2015-15-13.
(iv) Airbus Service Bulletin A320-53-1267, Revision 03, dated
November 26, 2015, which is not incorporated by reference in this
AD.
(v) Airbus Service Bulletin A320-53-1267, Revision 04, dated
February 1, 2016, which is not incorporated by reference in this AD.
(m) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (n)(2) of this AD. Information
may be emailed to: [email protected]. 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: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (g)(2) and (h)(2) of this AD: If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or
[[Page 58777]]
changes to procedures or tests identified as RC require approval of
an AMOC.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0098, dated June 7, 2017,
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-2017-1100.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone
425-227-1405; fax 425-227-1149.
(3) 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 [email protected]; Internet https://www.airbus.com. You may view this service information at the FAA,
Transport Standards Branch, 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 November 29, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26362 Filed 12-13-17; 8:45 am]
BILLING CODE 4910-13-P
