Airworthiness Directives; Airbus Airplanes, 58566-58572 [2017-26622]
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58566
Proposed Rules
Federal Register
Vol. 82, No. 238
Wednesday, December 13, 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–2017–1102; Product
Identifier 2017–NM–078–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–01–
11, which applies to certain Airbus
Model A320–211, –212, and –231
airplanes. AD 2016–01–11 requires
repetitive inspections for cracking of the
radius of the front spar vertical stringers
and the horizontal floor beam on frame
36, repetitive inspections for cracking of
the fastener holes of the front spar
vertical stringers on frame 36, and repair
if necessary. Since we issued AD 2016–
01–11, we received a report that, during
a center fuselage certification full scale
fatigue test, cracks were found on the
front vertical stringer at a certain frame.
This proposed AD would add new
thresholds and intervals for the
repetitive inspections; would require,
for certain airplanes, a modification of
the center wing box area; and would
expand 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
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SUMMARY:
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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.
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–
1102; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International 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–
2017–1102; Product Identifier 2017–
NM–078–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.
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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 widespread
fatigue damage (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
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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 2016–01–11,
Amendment 39–18370 (81 FR 3316,
January 21, 2016) (‘‘AD 2016–01–11’’),
for certain Airbus Model A320–211,
–212, and –231 airplanes. AD 2016–01–
11 was prompted by reports that
indicate new repetitive inspections
having new thresholds and intervals
were needed and that additional work
was needed to accomplish the
inspections on airplanes on which a
previous modification has been
accomplished. AD 2016–01–11 requires
repetitive high frequency eddy current
(HFEC) inspections for cracking of the
radius of the front spar vertical stringers
and the horizontal floor beam on frame
36, repetitive rototest inspections for
cracking of the fastener holes of the
front spar vertical stringers on frame 36,
and repair if necessary. We issued AD
2016–01–11 to detect and correct fatigue
cracking of the front spar vertical
stringers on the wings, which could
result in the reduced structural integrity
of the airplane.
Since we issued AD 2016–01–11, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0099, dated June 8, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Airbus Model
A318 series airplanes; Model A319
series airplanes; Model A320–211, –212,
–214, –231, –232, and –233 airplanes;
and Model A321 series airplanes. The
MCAI states:
During centre fuselage certification full
scale fatigue test, cracks were found on the
front vertical stringer at frame (FR) 36.
Analysis of these findings indicated that a
number of in-service aeroplanes could be
similarly affected.
This condition, if not detected and
corrected, could lead to crack propagation
and consequent deterioration of the
structural integrity of the aeroplane.
To address this potential unsafe condition,
Airbus issued Airbus Service Bulletin (SB)
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A320–57–1016 to provide inspection
instructions, and, consequently, [Directorate
General for Civil Aviation] DGAC France
issued AD 97–311–105 [which corresponds
to FAA AD 98–18–26, Amendment 39–10742
(63 FR 47423, September 8, 1998)] to require
those repetitive [high frequency eddy current
(HFEC)] inspections [for cracking]. At the
same time, modification in accordance with
Airbus SB A320–57–1017 was introduced as
(optional) terminating action for the
repetitive inspections * * *.
After that [DGAC] AD was issued, and
following new analysis, modification per
Airbus SB A320–57–1017 was no longer
considered to be terminating action for the
repetitive inspections as required by DGAC
France AD 97–311–105. Aeroplanes with
[manufacturer serial number] MSN 0080 up
to MSN 0155 inclusive were delivered with
the addition of a 5 [millimeter] mm thick
light alloy shim under the heads of 2
fasteners at the top end of the front spar
vertical stringers (Airbus mod 21290P1546,
which is the production line equivalent to inservice modification through Airbus SB
A320–57–1017). Aeroplanes with MSN 0156
or higher are delivered with vertical
stiffeners of the forward wing spar upper end
with stiffener cap thickness increased from 4
to 6 mm (Airbus mod 21290P1547).
Prompted by these findings, Airbus issued
SB A320–57–1178 Revision 01 to introduce
new repetitive inspections and,
consequently, EASA issued AD 2014–0069
[which corresponds to FAA AD 2016–01–11],
superseding DGAC France AD 97–311–105 to
require the new repetitive inspections, and,
depending on findings, accomplishment of
applicable corrective action(s).
Since AD 2014–0069 was issued, further
investigations in the frame of the Widespread
Fatigue Damage (WFD) campaign identified
that some repetitive inspection thresholds
and intervals have to be revised or
introduced, and a new terminating action
modification has been designed.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0069, which is superseded, revises
and introduces thresholds and intervals for
the repetitive inspections, and expands the
Applicability.
Required actions also include
reporting. Although this proposed AD
does not explicitly restate the
requirements of AD 2016–01–11, this
proposed AD would retain certain
requirements of AD 2016–01–11. Those
requirements are referenced in the
service information identified below in
‘‘Related Service Information under 1
CFR part 51,’’ which is referenced in
paragraph (i)(1) of this proposed AD.
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–
1102.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information:
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• Service Bulletin A320–57–1178,
Revision 03, dated November 29, 2016;
excluding Appendixes 01 and 04, and
including Appendix 03, all dated
November 29, 2016. Appendix 02 does
not exist. The service information
describes procedures for a rototest
inspection for cracking of the radius of
the front spar vertical stringers on frame
36, a HFEC for cracking of the
horizontal floor beam, and an HFEC
inspection for cracking of the fastener
holes of the front spar vertical stringers.
• Service Bulletin A320–57–1200,
dated November 20, 2015. The service
information describes procedures for
modifying the center wing box area,
which includes related investigative and
corrective actions. Related investigative
actions include an HFEC inspection on
the radius of the rib flanges, a rototest
inspection of the fastener holes, detailed
and high frequency eddy current
inspections for cracking on the cut
edges, detailed and rototest inspections
on all open fastener holes and an
inspection to determine if secondary
structure brackets are installed.
Corrective action includes reworking
the secondary structure bracket and
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.
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Costs of Compliance
We estimate that this proposed AD
affects 815 airplanes of U.S. registry.
The actions required by AD 2016–01–
11, take about 24 work-hours per
product, at an average labor rate of $85
per work-hour. Based on these figures,
the estimated cost of the actions that are
required by AD 2016–01–11 is $2,040
per product.
We also estimate that it would take
about 25 work-hours per product to
comply with the basic requirements of
this proposed AD and 1 work-hour for
reporting. The average labor rate is $85
per work-hour. Required parts would
cost about $180 per product. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $1,947,850, or $2,390 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the repair of cracking
specified in this proposed AD.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this NPRM is 2120–0056.
The paperwork cost associated with this
NPRM has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this NPRM is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW, Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
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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
1. The authority citation for part 39
continues to read as follows:
■
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2016–01–11, Amendment 39–18370 (81
FR 3316, January 21, 2016), and adding
the following new AD:
■
Airbus: Docket No. FAA–2017–1102; Product
Identifier 2017–NM–078–AD.
(a) Comments Due Date
We must receive comments by January 29,
2018.
(b) Affected ADs
This AD replaces AD 2016–01–11,
Amendment 39–18370 (81 FR 3316, January
21, 2016) (‘‘AD 2016–01–11’’).
(c) Applicability
This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–211,
–212, –214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers, except airplanes specified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A319 and A320 series airplanes
on which Airbus Modification (Mod) 160000
(structural reinforcement for sharklet
installation) has been embodied in
production.
(2) Model A321 series airplanes on which
Airbus Modification (Mod) 160021
(structural reinforcement for sharklet
installation) has been embodied in
production.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by a report that,
during a center fuselage certification full
scale fatigue test, cracks were found on the
front vertical stringer at frame (FR) 36. We
are issuing this AD to detect and correct
fatigue cracking of the front spar vertical
stringers on the wings, which could result in
the reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definition of Airplane Configurations
For the purposes of this AD, airplane
configurations are defined in table 1 to
paragraphs (g), (h), (i)(1), and (j) of this AD
and table 2 to paragraphs (g) and (i)(1) of this
AD.
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Table 1 to Paragraphs (g), (h), (i)(l ), and (j) of this AD- Airplane Configuration
(Con:fig.) Definitionfor Con:figs. 1, 2, 3, 5, 6, and 7
Airbus Modification (Mod) embodied in production I
Service Bulletin (SB) embodied
Config.
Affected Airplanes
21290P1546
21290P1547
36993P9963
SB A320-57-1017
A320
Series
1
No
No
No
No
X
2
No
No
No
Yes
X
3
Yes
No
No
No
X
No
Yes
No
No
X
No
Yes
No
No
No
Yes
No
No
No
Yes
Yes
No
No
Yes
Yes
No
No
Yes
Yes
No
No
No
No
No
5
6
7
A321
Series
A319
Series
A318
Series
X
X
X
X
X
X
Table 2 to Paragraphs (g) and (i)(l) of this AD- Airplane Configuration
(Config.) Definition for Configs. 4, 8, 9, and 10
Config.
Airbus Modification (Mod) embodied I not embodied in
production I Service Bulletin (SB) embodied
Affected Airplanes
A319
Series
A318
and
A321
Series
NIA
(NI A)
A320
Series
NIA
NIA
Not applicable
8
Airplanes on which Mod 28162, 28238 and 28342 have been
embodied ("Corporate Jet"), and Mod 36993P9963 is not
embodied
X
9
Airplanes on which Mod 28162, 28238 and 28342 have been
embodied ("Corporate Jet"), and Mod 36993P9963 is embodied
X
10
Airplanes post-SB A320-57-1200
(h) Actions Required for Previously
Inspected Airplanes
For Configuration 1, 2, or 3 airplanes, as
identified in table 1 to paragraphs (g), (h),
(i)(1), and (j) of this AD, on which the
inspections specified in Airbus Service
Bulletin A320–57–1178, dated October 29,
2013, have been accomplished before the
effective date of this AD; but the additional
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X
work specified in Airbus Service Bulletin
A320–57–1178, Revision 01, dated May 28,
2014, including Appendix 01, dated May 28,
2014, has not been accomplished before the
effective date of this AD: Before
accomplishing the initial inspection required
by paragraph (i)(1) of this AD, contact the
Manager, International Section, Transport
Standards Branch, FAA; or the European
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Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA)
for further instructions and accomplish those
instructions accordingly.
(i) Repetitive Inspections
(1) Within the compliance time defined in
table 3 to paragraph (i)(1) of this AD, as
applicable to airplane configuration as
identified in table 1 to paragraphs (g), (h),
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57–1178, Revision 03, dated November 29,
2016.
paragraph (i)(1) of this AD thereafter at
intervals not to exceed the inspection
interval values defined in table 4 to
paragraphs (i)(2) and (l) of this AD, except as
provided by paragraph (l) of this AD.
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spar vertical stringers and the horizontal
floor beam and the fastener holes on frame
36, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
(2) If no cracking is found during any
inspection required by paragraph (i)(1) of this
AD, repeat the inspection required by
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(i)(1), and (j) of this AD and table 2 to
paragraphs (g) and (i)(1) of this AD,
accomplish a special detailed inspection
(SDI) for cracking of the radius of the front
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58571
Service Bulletin A320–57–1200, dated
November 20, 2015, except as required by
paragraph (k) of this AD. Do all applicable
related investigative and corrective actions
before further flight.
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DOA, the approval must include the DOAauthorized signature. Where Airbus Service
Bulletin A320–57–1178, Revision 03, dated
November 29, 2016; and Airbus Service
Bulletin A320–57–1200, dated November 20,
2015; specify to contact Airbus for
appropriate action, and specifies that action
as ‘‘RC’’ (Required for Compliance),
accomplish corrective actions in accordance
with this paragraph.
(k) Corrective Action
If any crack is found during any inspection
required by this AD: Before further flight,
repair 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
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(l) Previous Repairs
For airplanes that have been repaired in
the inspection area specified in paragraph
(i)(1) of this AD before the effective date of
this AD, using a method approved by the
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paragraph (j) of this AD, as applicable,
modify the center wing box area, including
doing all applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
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(j) Modification
For A320 series airplanes, Configuration 1,
2, or 3 as identified in table 1 to paragraphs
(g), (h), (i)(1), and (j) of this AD: Within the
compliance time defined in table 5 to
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Manager, International Section, Transport
Standards Branch, FAA; or the EASA; or
Airbus’s EASA DOA: Accomplish repetitive
SDIs within the compliance time defined in
those repair instructions for repetitive SDIs.
If no compliance time is identified in the
repair instructions for repetitive SDIs,
accomplish the repetitive SDIs required by
paragraph (i)(2) of this AD at the compliance
times defined in table 4 to paragraphs (i)(2)
and (l) of this AD.
(m) No Terminating Action
Modification or repair of an airplane, as
specified in paragraph (j) or (k) of this AD,
does not constitute terminating action for the
repetitive inspections required by this AD,
unless it is specified otherwise in a repair
method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or the EASA; or Airbus’s EASA
DOA.
sradovich on DSK3GMQ082PROD with PROPOSALS
(n) Reporting Requirement
Submit a report of the findings (both
positive and negative) of the inspections
required by paragraphs (i) and (j) of this AD
to ‘‘Airbus Service Bulletin Reporting Online
Application’’ on Airbus World (https://
w3.airbus.com/), at the applicable time
specified in paragraph (n)(1) or (n)(2) of this
AD.
(1) If the inspection was done on or after
the effective date of this AD: Report within
30 days after that inspection.
(2) If the inspection was done before the
effective date of this AD: Report within 30
days after the effective date of this AD.
(o) 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 manager of the International
Section, send it to the attention of the person
identified in paragraph (p)(2) of this AD.
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: 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 specified in paragraph (k) 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
VerDate Sep<11>2014
16:09 Dec 12, 2017
Jkt 244001
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(4) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately [XX] per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at 800 Independence
Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2017–0099, dated
June 8, 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–
2017–1102.
(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 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–26622 Filed 12–12–17; 8:45 am]
Frm 00007
Fmt 4702
Food and Drug Administration
21 CFR Part 15
[Docket No. FDA–2017–N–6502]
Opioid Policy Steering Committee:
Prescribing Intervention—Exploring a
Strategy for Implementation; Public
Hearing; Request for Comments
AGENCY:
Food and Drug Administration,
HHS.
Notification of public hearing;
request for comments.
ACTION:
The Food and Drug
Administration (FDA, the Agency, or
we) is announcing a public hearing
entitled, ‘‘Opioid Policy Steering
Committee: Prescribing Intervention—
Exploring a Strategy for
Implementation.’’ The purpose of the
public hearing is to receive stakeholder
input on how FDA might, under its Risk
Evaluation and Mitigation Strategy
(REMS) authority, improve the safe use
of opioid analgesics by curbing
overprescribing to decrease the
occurrence of new addictions and limit
misuse and abuse of opioid analgesics.
DATES: The public hearing will be held
on January 30, 2018, from 8:30 a.m. to
4:30 p.m. The public hearing may be
extended or may end early depending
on the level of public participation.
Persons seeking to attend, or to present
at, the public hearing must register by
January 16, 2018. Electronic or written
comments will be accepted after the
public hearing until March 16, 2018.
See the SUPPLEMENTARY INFORMATION
section for registration date and
information.
SUMMARY:
The public hearing will be
held at FDA White Oak Campus, 10903
New Hampshire Ave., Bldg. 31
Conference Center, the Great Room (Rm.
1503 B and C), Silver Spring, MD
20993–0002. Entrance for public hearing
participants (non-FDA employees) is
through Building 1 where routine
security check procedures will be
performed. For parking and security
information, please refer to https://
www.fda.gov/AboutFDA/Working
atFDA/BuildingsandFacilities/WhiteOak
CampusInformation/ucm241740.htm.
You may submit comments as
follows. Please note that late, untimely
filed comments will not be considered.
ADDRESSES:
Electronic Submissions
Electronic comments must be
submitted on or before March 16, 2018.
The https://www.regulations.gov
BILLING CODE 4910–13–P
PO 00000
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Sfmt 4702
E:\FR\FM\13DEP1.SGM
13DEP1
]]>Agencies
[Federal Register Volume 82, Number 238 (Wednesday, December 13, 2017)]
[Proposed Rules]
[Pages 58566-58572]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26622]
========================================================================
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. 238 / Wednesday, December 13, 2017 /
Proposed Rules
[[Page 58566]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1102; Product Identifier 2017-NM-078-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) 2016-01-
11, which applies to certain Airbus Model A320-211, -212, and -231
airplanes. AD 2016-01-11 requires repetitive inspections for cracking
of the radius of the front spar vertical stringers and the horizontal
floor beam on frame 36, repetitive inspections for cracking of the
fastener holes of the front spar vertical stringers on frame 36, and
repair if necessary. Since we issued AD 2016-01-11, we received a
report that, during a center fuselage certification full scale fatigue
test, cracks were found on the front vertical stringer at a certain
frame. This proposed AD would add new thresholds and intervals for the
repetitive inspections; would require, for certain airplanes, a
modification of the center wing box area; and would expand 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-
1102; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International 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-2017-1102;
Product Identifier 2017-NM-078-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 widespread fatigue damage (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
[[Page 58567]]
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 2016-01-11, Amendment 39-18370 (81 FR 3316, January
21, 2016) (``AD 2016-01-11''), for certain Airbus Model A320-211, -212,
and -231 airplanes. AD 2016-01-11 was prompted by reports that indicate
new repetitive inspections having new thresholds and intervals were
needed and that additional work was needed to accomplish the
inspections on airplanes on which a previous modification has been
accomplished. AD 2016-01-11 requires repetitive high frequency eddy
current (HFEC) inspections for cracking of the radius of the front spar
vertical stringers and the horizontal floor beam on frame 36,
repetitive rototest inspections for cracking of the fastener holes of
the front spar vertical stringers on frame 36, and repair if necessary.
We issued AD 2016-01-11 to detect and correct fatigue cracking of the
front spar vertical stringers on the wings, which could result in the
reduced structural integrity of the airplane.
Since we issued AD 2016-01-11, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Union, has issued EASA Airworthiness Directive 2017-0099,
dated June 8, 2017 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Airbus Model A318 series airplanes; Model A319
series airplanes; Model A320-211, -212, -214, -231, -232, and -233
airplanes; and Model A321 series airplanes. The MCAI states:
During centre fuselage certification full scale fatigue test,
cracks were found on the front vertical stringer at frame (FR) 36.
Analysis of these findings indicated that a number of in-service
aeroplanes could be similarly affected.
This condition, if not detected and corrected, could lead to
crack propagation and consequent deterioration of the structural
integrity of the aeroplane.
To address this potential unsafe condition, Airbus issued Airbus
Service Bulletin (SB) A320-57-1016 to provide inspection
instructions, and, consequently, [Directorate General for Civil
Aviation] DGAC France issued AD 97-311-105 [which corresponds to FAA
AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998)] to
require those repetitive [high frequency eddy current (HFEC)]
inspections [for cracking]. At the same time, modification in
accordance with Airbus SB A320-57-1017 was introduced as (optional)
terminating action for the repetitive inspections * * *.
After that [DGAC] AD was issued, and following new analysis,
modification per Airbus SB A320-57-1017 was no longer considered to
be terminating action for the repetitive inspections as required by
DGAC France AD 97-311-105. Aeroplanes with [manufacturer serial
number] MSN 0080 up to MSN 0155 inclusive were delivered with the
addition of a 5 [millimeter] mm thick light alloy shim under the
heads of 2 fasteners at the top end of the front spar vertical
stringers (Airbus mod 21290P1546, which is the production line
equivalent to in-service modification through Airbus SB A320-57-
1017). Aeroplanes with MSN 0156 or higher are delivered with
vertical stiffeners of the forward wing spar upper end with
stiffener cap thickness increased from 4 to 6 mm (Airbus mod
21290P1547).
Prompted by these findings, Airbus issued SB A320-57-1178
Revision 01 to introduce new repetitive inspections and,
consequently, EASA issued AD 2014-0069 [which corresponds to FAA AD
2016-01-11], superseding DGAC France AD 97-311-105 to require the
new repetitive inspections, and, depending on findings,
accomplishment of applicable corrective action(s).
Since AD 2014-0069 was issued, further investigations in the
frame of the Widespread Fatigue Damage (WFD) campaign identified
that some repetitive inspection thresholds and intervals have to be
revised or introduced, and a new terminating action modification has
been designed.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0069, which is superseded, revises and
introduces thresholds and intervals for the repetitive inspections,
and expands the Applicability.
Required actions also include reporting. Although this proposed AD
does not explicitly restate the requirements of AD 2016-01-11, this
proposed AD would retain certain requirements of AD 2016-01-11. Those
requirements are referenced in the service information identified below
in ``Related Service Information under 1 CFR part 51,'' which is
referenced in paragraph (i)(1) of this proposed AD. 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-2017-1102.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Service Bulletin A320-57-1178, Revision 03, dated November
29, 2016; excluding Appendixes 01 and 04, and including Appendix 03,
all dated November 29, 2016. Appendix 02 does not exist. The service
information describes procedures for a rototest inspection for cracking
of the radius of the front spar vertical stringers on frame 36, a HFEC
for cracking of the horizontal floor beam, and an HFEC inspection for
cracking of the fastener holes of the front spar vertical stringers.
Service Bulletin A320-57-1200, dated November 20, 2015.
The service information describes procedures for modifying the center
wing box area, which includes related investigative and corrective
actions. Related investigative actions include an HFEC inspection on
the radius of the rib flanges, a rototest inspection of the fastener
holes, detailed and high frequency eddy current inspections for
cracking on the cut edges, detailed and rototest inspections on all
open fastener holes and an inspection to determine if secondary
structure brackets are installed. Corrective action includes reworking
the secondary structure bracket and 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.
[[Page 58568]]
Costs of Compliance
We estimate that this proposed AD affects 815 airplanes of U.S.
registry.
The actions required by AD 2016-01-11, take about 24 work-hours per
product, at an average labor rate of $85 per work-hour. Based on these
figures, the estimated cost of the actions that are required by AD
2016-01-11 is $2,040 per product.
We also estimate that it would take about 25 work-hours per product
to comply with the basic requirements of this proposed AD and 1 work-
hour for reporting. The average labor rate is $85 per work-hour.
Required parts would cost about $180 per product. Based on these
figures, we estimate the cost of this proposed AD on U.S. operators to
be $1,947,850, or $2,390 per product.
We have received no definitive data that would enable us to provide
cost estimates for the repair of cracking specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this NPRM is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
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)
2016-01-11, Amendment 39-18370 (81 FR 3316, January 21, 2016), and
adding the following new AD:
Airbus: Docket No. FAA-2017-1102; Product Identifier 2017-NM-078-AD.
(a) Comments Due Date
We must receive comments by January 29, 2018.
(b) Affected ADs
This AD replaces AD 2016-01-11, Amendment 39-18370 (81 FR 3316,
January 21, 2016) (``AD 2016-01-11'').
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all
manufacturer serial numbers, except airplanes specified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A319 and A320 series airplanes on which Airbus
Modification (Mod) 160000 (structural reinforcement for sharklet
installation) has been embodied in production.
(2) Model A321 series airplanes on which Airbus Modification
(Mod) 160021 (structural reinforcement for sharklet installation)
has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a report that, during a center fuselage
certification full scale fatigue test, cracks were found on the
front vertical stringer at frame (FR) 36. We are issuing this AD to
detect and correct fatigue cracking of the front spar vertical
stringers on the wings, which could result in the reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definition of Airplane Configurations
For the purposes of this AD, airplane configurations are defined
in table 1 to paragraphs (g), (h), (i)(1), and (j) of this AD and
table 2 to paragraphs (g) and (i)(1) of this AD.
BILLING CODE 4910-13-P
[[Page 58569]]
[GRAPHIC] [TIFF OMITTED] TP13DE17.000
(h) Actions Required for Previously Inspected Airplanes
For Configuration 1, 2, or 3 airplanes, as identified in table 1
to paragraphs (g), (h), (i)(1), and (j) of this AD, on which the
inspections specified in Airbus Service Bulletin A320-57-1178, dated
October 29, 2013, have been accomplished before the effective date
of this AD; but the additional work specified in Airbus Service
Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including
Appendix 01, dated May 28, 2014, has not been accomplished before
the effective date of this AD: Before accomplishing the initial
inspection required by paragraph (i)(1) of this AD, 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 further instructions and accomplish
those instructions accordingly.
(i) Repetitive Inspections
(1) Within the compliance time defined in table 3 to paragraph
(i)(1) of this AD, as applicable to airplane configuration as
identified in table 1 to paragraphs (g), (h),
[[Page 58570]]
(i)(1), and (j) of this AD and table 2 to paragraphs (g) and (i)(1)
of this AD, accomplish a special detailed inspection (SDI) for
cracking of the radius of the front spar vertical stringers and the
horizontal floor beam and the fastener holes on frame 36, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-57-1178, Revision 03, dated November 29, 2016.
[GRAPHIC] [TIFF OMITTED] TP13DE17.001
(2) If no cracking is found during any inspection required by
paragraph (i)(1) of this AD, repeat the inspection required by
paragraph (i)(1) of this AD thereafter at intervals not to exceed
the inspection interval values defined in table 4 to paragraphs
(i)(2) and (l) of this AD, except as provided by paragraph (l) of
this AD.
[[Page 58571]]
[GRAPHIC] [TIFF OMITTED] TP13DE17.002
(j) Modification
For A320 series airplanes, Configuration 1, 2, or 3 as
identified in table 1 to paragraphs (g), (h), (i)(1), and (j) of
this AD: Within the compliance time defined in table 5 to paragraph
(j) of this AD, as applicable, modify the center wing box area,
including doing all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-57-1200, dated November 20, 2015,
except as required by paragraph (k) of this AD. Do all applicable
related investigative and corrective actions before further flight.
[GRAPHIC] [TIFF OMITTED] TP13DE17.003
BILLING CODE 4910-13-C
(k) Corrective Action
If any crack is found during any inspection required by this AD:
Before further flight, repair 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. Where Airbus Service
Bulletin A320-57-1178, Revision 03, dated November 29, 2016; and
Airbus Service Bulletin A320-57-1200, dated November 20, 2015;
specify to contact Airbus for appropriate action, and specifies that
action as ``RC'' (Required for Compliance), accomplish corrective
actions in accordance with this paragraph.
(l) Previous Repairs
For airplanes that have been repaired in the inspection area
specified in paragraph (i)(1) of this AD before the effective date
of this AD, using a method approved by the
[[Page 58572]]
Manager, International Section, Transport Standards Branch, FAA; or
the EASA; or Airbus's EASA DOA: Accomplish repetitive SDIs within
the compliance time defined in those repair instructions for
repetitive SDIs. If no compliance time is identified in the repair
instructions for repetitive SDIs, accomplish the repetitive SDIs
required by paragraph (i)(2) of this AD at the compliance times
defined in table 4 to paragraphs (i)(2) and (l) of this AD.
(m) No Terminating Action
Modification or repair of an airplane, as specified in paragraph
(j) or (k) of this AD, does not constitute terminating action for
the repetitive inspections required by this AD, unless it is
specified otherwise in a repair method approved by the Manager,
International Section, Transport Standards Branch, FAA; or the EASA;
or Airbus's EASA DOA.
(n) Reporting Requirement
Submit a report of the findings (both positive and negative) of
the inspections required by paragraphs (i) and (j) of this AD to
``Airbus Service Bulletin Reporting Online Application'' on Airbus
World (https://w3.airbus.com/), at the applicable time specified in
paragraph (n)(1) or (n)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Report within 30 days after that inspection.
(2) If the inspection was done before the effective date of this
AD: Report within 30 days after the effective date of this AD.
(o) 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 manager of the International Section, send it to the
attention of the person identified in paragraph (p)(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 specified in
paragraph (k) 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 changes to procedures or tests identified as RC
require approval of an AMOC.
(4) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately [XX]
per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at 800 Independence Ave.
SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0099, dated June 8, 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-2017-1102.
(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 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26622 Filed 12-12-17; 8:45 am]
BILLING CODE 4910-13-P
