Airworthiness Directives; Airbus Airplanes, 25590-25595 [2018-11822]
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(3) During any detailed or rototest
inspection required by paragraph (h)(2) of
this AD, if any crack is found, before further
flight, replace the NLG door mechanism
actuator shaft with a serviceable part, in
accordance with the instructions of Airbus
Defence and Space AOT AOT–CN235–32–
0001, Revision 2, dated October 26, 2016; or
AOT AOT–C295–32–0001, Revision 2, dated
October 26, 2016; as applicable.
(j) Replacement not Terminating Action
Accomplishment of any corrective action
on an airplane, as required by paragraph
(i)(1), (i)(2), or (i)(3) of this AD, as applicable,
is not terminating action for the repetitive
detailed or rototest inspections required by
paragraphs (h)(1) and (h)(2) of this AD, for
that airplane.
(k) Optional Terminating Action
For Model CN–235, CN–235–100, CN–235–
200, and CN–235–300 airplanes:
Modification of the NLG door latching
mechanism, in accordance with the
Accomplishment Instructions of Airbus
Defence and Space Service Bulletin SB–235–
32–0031C, dated September 22, 2016, is
terminating action for the repetitive
inspections required by paragraphs (h)(1) and
(h)(2) of this AD, for that airplane.
(l) Parts Installation Limitation
As of the effective date of this AD,
installation of an NLG door mechanism
actuator shaft assembly having P/N 35–
42311–00 or P/N 95–42315–00, or any of its
components, is allowed, provided that the
part is new; or provided that the assembly or
the components, as applicable, has passed an
inspection; in accordance with the
instructions of Airbus Space and Defence
AOT AOT–CN235–32–0001, Revision 2,
dated October 26, 2016; or AOT AOT–C295–
32–0001, Revision 2, dated October 26, 2016;
as applicable.
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(m) Reporting Not Required
Although Airbus Space and Defence AOT
AOT–CN235–32–0001, Revision 2, dated
October 26, 2016; and AOT AOT–C295–32–
0001, Revision 2, dated October 26, 2016;
both specify to submit certain information to
the manufacturer, this AD does not include
that requirement.
(n) Credit for Previous Actions
This paragraph provides credit for the
initial inspection required by paragraph
(h)(1) and (h)(2) of this AD, and the
corrective actions required by paragraphs
(i)(1), (i)(2), and (i)(3) of this AD, if those
actions were performed before the effective
date of this AD using the applicable service
information identified in paragraphs (n)(1)
through (n)(4) of this AD.
(1) Airbus Space and Defence AOT AOT–
CN235–32–0001, dated September 29, 2015.
(2) Airbus Space and Defence AOT AOT–
CN235–32–0001, Revision 1, dated February
19, 2016.
(3) Airbus Space and Defence AOT AOT–
C295–32–0001, dated September 29, 2015.
(4) Airbus Space and Defence AOT AOT–
C295–32–0001, Revision 1, dated February
19, 2016.
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(o) Other FAA AD Provisions
DEPARTMENT OF TRANSPORTATION
The following provisions also apply to this
AD:
(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 (p)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus Space and Defense’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0181, dated September 18, 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–2018–0493.
(2) For more information about this AD,
contact Shahram Daneshmandi, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3220.
(3) For service information identified in
this AD, contact Airbus Defense and Space
Services/Engineering Support, Avenida de
´
Aragon 404, 28022 Madrid, Spain; telephone
+34 91 585 55 84; fax +34 91 585 31 27; email
MTA.TechnicalService@airbus.com. You
may view this service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
Issued in Des Moines, Washington, on May
23, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–11699 Filed 6–1–18; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0497; Product
Identifier 2017–NM–140–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A300 B4–603, B4–620,
and B4–622 airplanes; Model A300 F4–
605R airplanes; Model A300 C4–605R
Variant F airplanes; and Model A300
B4–600R series airplanes. This proposed
AD was prompted by reports of cracking
on the frame (FR) 47 angle fitting. This
proposed AD would require, depending
on airplane configuration, a
modification of certain angle fitting
attachment holes, repetitive inspections
for cracking of certain holes of the
internal lower angle fitting web, certain
holes of the internal lower angle fitting
horizontal splicing, the aft bottom
panel, and the FR47/Rib 1 junction area,
and related investigative and corrective
actions if necessary. We are proposing
this AD to address the unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by July 19, 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 SAS,
Airworthiness Office—EAW, 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, 2200
SUMMARY:
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South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
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–2018–
0497; 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 NPRM, 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: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3225.
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–
2018–0497; Product Identifier 2017–
NM–140–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM 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 NPRM.
sradovich on DSK3GMQ082PROD with PROPOSALS
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0210,
dated October 24, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A300 B4–603,
B4–620, and B4–622 airplanes; Model
A300 F4–605R airplanes; Model A300
C4–605R Variant F airplanes; and Model
A300 B4–600R series airplanes. The
MCAI states:
Prompted by cracks found on the Frame
(FR) 47 angle fitting, Airbus issued SB
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[Service Bulletin] A300–57–6049, SB A300–
57–6050, and SB A300–57–6086.
These cracks, if not detected and corrected,
could affect the structural integrity of the
centre wing box (CWB) of the aeroplane.
´ ´
Consequently, DGAC [Direction Generale
de l’Aviation Civile] France published AD
94–241–170, AD 1999–147–279, AD 2000–
533–328 and AD F–2004–159 (EASA
approval 2004–9779), each AD superseding
the previous one, to require repetitive high
frequency eddy current (HFEC) rotating
probe inspections of the FR47 internal lower
angle fitting.
After DGAC France AD F–2004–159 was
issued, cracks were reportedly found on the
horizontal flange of FR47 internal corner
angle fitting during accomplishment of
routine maintenance structural inspection
and modification in accordance with the
instructions of Airbus SB A300–57–6050.
Prompted by these findings, Airbus reviewed
and amended the inspection programme for
the internal lower angle fitting flange
(horizontal face).
Consequently, EASA issued AD 2012–0092
[which corresponds to FAA AD 2014–20–18,
Amendment 39–17991 (79 FR 65879,
November 6, 2014) (‘‘AD 2014–20–18’’)],
retaining the requirements of DGAC France
AD F–2004–159, which was superseded, and
requiring additional repetitive inspections of
the CWB lower panel through the ultrasonic
method and, depending on findings, reinstallation of removed fasteners in transition
fit instead of interface.
In addition, DGAC France had previously
issued AD F–2005–124 (EASA approval
2005–6071) to require the same inspections
for A300 F4–608ST aeroplanes, in
accordance with Airbus SB A300–57–9001
and SB A300–57–9002.
Following the discovery of numerous
cracks during the accomplishment of SB
A300–57–6049 and SB A300–57–6089
inspections, Airbus developed in a first step
a new (recommended) modification (Airbus
SB A300–57–6113) and defined, for post-mod
aeroplanes, new inspections, and published
SB A300–57–6119, which included new
inspection methods (ultrasonic/radiographic)
with new inspection thresholds and
intervals.
Consequently, EASA issued AD 2016–
0198, retaining the requirements of EASA AD
2012–0092, which was superseded, to require
repetitive inspections for post-SB A300–57–
6113 aeroplanes.
Since EASA AD 2016–0198 was issued,
Airbus revised in a second step the
inspection programme for A300–600 pre-SB
57–6113 and A300–600ST aeroplanes,
reducing inspection thresholds and intervals.
At this opportunity, the existing ultrasonic
inspection for A300–600 aeroplanes has been
added for A300–600ST aeroplanes.
For the reasons described above, this new
[EASA] AD retains the requirements of EASA
AD 2016–0198 for A300–600 aeroplanes and
of DGAC France AD F–2005–124 for A300–
600ST aeroplanes, which are both
superseded, and requires [modification
through cold expansion of certain angle
fitting attachment holes and] repetitive
inspections [for cracking of certain holes of
the internal lower angle fitting web, certain
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25591
holes of the internal lower angle fitting
horizontal splicing, the aft bottom panel, and
the FR47/Rib 1 junction area, and applicable
related investigative and corrective actions]
with new compliance times and intervals.
This [EASA] AD is applicable to both A300–
600 and A300–600ST aeroplanes * * *.
Related investigative actions include a
rotating probe inspection for cracking.
Corrective actions include replacing
damaged fasteners, reaming and drilling
holes, installing the next nominal
fastener for oversized bore holes, and
repairing cracks. 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–2018–0497.
Relationship Between Proposed AD and
AD 2014–20–18
This NPRM would not supersede AD
2014–20–18. Rather, we have
determined that a stand-alone AD
would be more appropriate to address
the changes in the MCAI. This NPRM
would require depending on airplane
configuration, a modification of certain
angle fitting attachment holes,
inspections for cracking of certain holes
of the internal lower angle fitting web,
certain holes of the internal lower angle
fitting horizontal splicing, the aft bottom
panel, and the FR47/Rib 1 junction area.
Accomplishment of the proposed
modification and initial inspections
would then terminate all of the
requirements of AD 2014–20–18.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Service Bulletin A300–57–6049,
Revision 8, dated July 4, 2017. This
service information describes
procedures for HFEC rotating probe
inspections for cracking of certain holes
of the internal lower angle fitting web.
• Service Bulletin A300–57–6086,
Revision 6, dated July 4, 2017. This
service information describes
procedures for HFEC rotating probe
inspections for cracking of certain holes
in the internal lower angle fitting
horizontal splicing (left-hand and righthand sides) and for ultrasonic
inspections for cracking of the aft
bottom panel.
• Service Bulletin A300–57–6119,
Revision 00, dated April 25, 2016. This
service information describes
procedures for ultrasonic and
radiographic inspections for cracking of
the FR47/Rib 1 junction area.
This service information is reasonably
available because the interested parties
have access to it through their normal
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Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules
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.
Costs of Compliance
We estimate that this proposed AD
affects 65 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Up to 727 work-hours × $85 per hour = Up to $61,795 .......
Up to $3,370 .........
Up to $65,165 .......
Up to $4,235,725 per inspection cycle.
We estimate that it would take about
1 work-hour per product to comply with
the proposed reporting requirement in
this proposed AD. The average labor
rate is $85 per hour. Based on these
figures, we estimate the cost of reporting
the inspection results on U.S. operators
to be $5,525, or $85 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this 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.
sradovich on DSK3GMQ082PROD with PROPOSALS
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:
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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 proposed 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.
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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 adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2018–0497; Product
Identifier 2017–NM–140–AD.
(a) Comments Due Date
We must receive comments by July 19,
2018.
(b) Affected ADs
This AD affects AD 2014–20–18,
Amendment 39–17991 (79 FR 65879,
November 6, 2014) (‘‘AD 2014–20–18’’).
(c) Applicability
This AD applies to Airbus Model A300 B4–
603, A300 B4–620, A300 B4–622, A300 B4–
605R, A300 B4–622R, A300 C4–605R Variant
F, and A300 F4–605R airplanes, certificated
in any category, all manufacturer serial
numbers, except airplanes on which Airbus
Modification 12171 or 12249 has been
embodied in production, or on which Airbus
Service Bulletin A300–57–6069 has been
embodied in service.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of
cracking on the frame (FR) 47 angle fitting.
We are issuing this AD to detect and correct
cracking of FR47 angle fitting, which could
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result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definitions
For the purposes of this AD, the definitions
in paragraphs (g)(1) through (g)(6) apply.
(1) Group 1 airplanes are those airplanes
on which Airbus Service Bulletin A300–57–
6113, Revision 00, dated April 25, 2016, has
not been incorporated as of the effective date
of this AD.
(2) Group 2 airplanes are those airplanes
on which Airbus Service Bulletin A300–57–
6113, Revision 00, dated April 25, 2016, has
been incorporated as of the effective date of
this AD.
(3) The average flight time (AFT) for the
inspection threshold is defined as the flight
hours (FH) divided by the flight cycles (FC),
counted from the first flight of the airplane.
(4) The AFT for the inspection interval is
defined as the FH divided by the FC, counted
from the date of the last inspection required
by paragraph (i), (j), (k), or (l) of this AD, as
applicable.
(5) For airplanes on which Airbus
modification 10155 has been embodied, the
(h) Modification
For all airplanes on which Airbus
modification 10155 has not been embodied:
Before exceeding 15,100 FC or 38,900 FH,
whichever occurs first after first flight of the
airplane; or within the ‘‘grace periods’’
defined in paragraph 1.B.(4),
‘‘Accomplishment Timescale,’’ of Airbus
Service Bulletin A300–57–6050, Revision 3,
dated May 31, 2001; whichever occurs later,
modify the angle fitting attachment holes of
the wing center box by cold expansion,
including doing a rotating probe inspection
for cracking, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6050, Revision 3,
dated May 31, 2001. Where paragraph 1.B.(4),
‘‘Accomplishment Timescale,’’ of Airbus
Service Bulletin A300–57–6050, Revision 3,
dated May 31, 2001, specifies ‘‘grace
(i) Internal Lower Angle Fitting (Vertical
Face) Web Inspections
For Group 1 airplanes: Before exceeding
the applicable threshold specified in figure 1
to paragraph (i) of this AD, or within 12
months after the effective date of this AD,
whichever occurs later, do a high frequency
eddy current (HFEC) rotating probe
inspection for cracking of holes H, I, K, L, M,
N, U, V, W, X, and Y of the internal lower
angle fitting web (left-hand and right-hand
sides), in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6049, Revision 8,
dated July 4, 2017. Repeat the inspection
thereafter at intervals not to exceed those
specified in figure 1 to paragraph (i) of this
AD.
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6086, Revision 6,
dated July 4, 2017. Repeat the inspection
thereafter at intervals not to exceed those
specified in figure 2 to paragraph (j) of this
AD.
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whichever occurs later, do an HFEC rotating
probe inspection for cracking of holes A, B,
C, D, E, F, G, P, Q, S, and T (adjacent to hole
G) of the internal lower angle fitting
horizontal splicing (left-hand and right-hand
sides), in accordance with the
periods’’ relative to the receipt of the service
bulletin, count the ‘‘grace periods’’ from
December 19, 2005 (the effective date of AD
2005–23–08). If any crack is found during
any inspection: Before further flight, repair
using a method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
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(j) Internal Lower Angle Fitting (Horizontal
Face) Inspections
For Group 1 airplanes: Before exceeding
the applicable threshold specified in figure 2
to paragraph (j) of this AD, or within 12
months after the effective date of this AD,
thresholds for the inspections required by
paragraphs (i), (j), and (k) of this AD are
counted from the first flight of the airplane.
(6) For airplanes on which Airbus
modification 10155 has not been embodied,
the thresholds for the inspections required by
paragraphs (i), (j), and (k) of this AD are
counted since the date on which Airbus
Service Bulletin A300–57–6050 was
embodied on the airplane.
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months after the effective date of this AD,
whichever occurs later, do an ultrasonic
inspection for cracking of the aft bottom
panel, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–6086, Revision 6,
dated July 4, 2017. Repeat the inspection
thereafter at intervals not to exceed those
specified in figure 3 to paragraph (k) of this
AD.
For Group 2 airplanes: Before exceeding
the applicable thresholds specified in figure
4 to paragraph (l) of this AD, do ultrasonic
and radiographic inspections for cracking of
the FR47/Rib 1 junction area, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A300–57–6119,
Revision 00, dated April 25, 2016. Repeat the
inspections thereafter at intervals not to
exceed those specified in figure 4 to
paragraph (l) of this AD. Count the threshold
compliance times from the date on which
Airbus Service Bulletin A300–57–6113,
Revision 00, dated April 25, 2016, was
embodied on the airplane.
(m) Related Investigative and Corrective
Actions
If, during any inspection required by
paragraph (i), (j), (k), or (l) of this AD, any
crack is found: Before further flight,
accomplish all applicable related
investigative and corrective actions in
accordance with the Accomplishment
Instructions of the service information
specified in paragraphs (m)(1) through (m)(3)
of this AD, as applicable. Where the service
information specified in paragraphs (m)(1)
through (m)(3) of this AD specifies to contact
Airbus for instructions, before further flight,
obtain instructions approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus’s EASA
DOA and accomplish those instructions
accordingly. If approved by the DOA, the
approval must include the DOA-authorized
signature.
(1) If the inspection was done as specified
in paragraph (i) of this AD: Airbus Service
Bulletin A300–57–6049, Revision 8, dated
July 4, 2017.
(2) If the inspection was done as specified
in paragraph (j) or (k) of this AD: Airbus
Service Bulletin A300–57–6086, Revision 6,
dated July 4, 2017.
(3) If the inspection was done as specified
in paragraph (l) of this AD: Airbus Service
Bulletin A300–57–6119, Revision 00, dated
April 25, 2016.
sradovich on DSK3GMQ082PROD with PROPOSALS
(l) FR47/Rib 1 Junction Area Inspections
VerDate Sep<11>2014
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(n) Reporting
At the applicable time specified in
paragraph (n)(1) or (n)(2) of this AD: Report
the results of the inspections required by
paragraphs (i), (j), (k), and (l) of this AD to
Airbus Service Bulletin Reporting Online
Application on Airbus World (https://
w3.airbus.com/), or submit the results to
Airbus in accordance with the instructions of
the applicable service information specified
in paragraphs (i), (j), (k), or (l) of this AD. The
report must include the inspection results, a
description of any discrepancies found, the
E:\FR\FM\04JNP1.SGM
04JNP1
EP04JN18.005</GPH>
For Group 1 airplanes: Before exceeding
the applicable thresholds specified in figure
3 to paragraph (k) of this AD, or within 12
EP04JN18.004</GPH>
(k) Aft Bottom Panel Inspections
Federal Register / Vol. 83, No. 107 / Monday, June 4, 2018 / Proposed Rules
airplane serial number, and the number of
flight cycles and flight hours on the airplane.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
(o) Terminating Action for AD 2014–20–18
Accomplishment of the action required by
paragraph (h) of this AD and the initial
inspections required by paragraphs (i) and (j),
and (k) of this AD terminates all
requirements of AD 2014–20–18.
sradovich on DSK3GMQ082PROD with PROPOSALS
(p) Credit for Previous Actions
This paragraph provides credit for actions
specified in paragraph (h) of this AD, if those
actions were performed before December 19,
2005 (the effective date of AD 2005–23–08),
using Airbus Service Bulletin A300–57–6050,
Revision 02, dated February 10, 2000.
(q) Other FAA AD Provisions
The following provisions also apply to this
AD:
(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 (r)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Paperwork Reduction Act Burden
Statement: 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 1 work-hour
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,
VerDate Sep<11>2014
16:57 Jun 01, 2018
Jkt 244001
Washington, DC 20591, Attn: Information
Collection Clearance Officer, AES–200.
(4) Required for Compliance (RC): Except
as required by paragraph (m) 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.
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0210, dated October 24, 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–2018–0497.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3225.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 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, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
Issued in Des Moines, Washington, on May
23, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–11822 Filed 6–1–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0498; Product
Identifier 2018–NM–013–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
SUMMARY:
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
25595
Airbus Model A330–200 Freighter series
airplanes; Airbus Model A330–200
series airplanes; and Airbus Model
A330–300 series airplanes. This
proposed AD was prompted by reports
of Angle of Attack (AOA) blockages not
detected by upgraded flight control
primary computer (FCPC) software
standards. This proposed AD would
require upgrading certain FCPCs, which
would terminate a certain airplane flight
manual revision for certain airplanes.
We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by July 19, 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 SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
internet https://www.airbus.com. You
may view this service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
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–2018–
0498; 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 NPRM, 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:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229.
E:\FR\FM\04JNP1.SGM
04JNP1
]]>Agencies
[Federal Register Volume 83, Number 107 (Monday, June 4, 2018)]
[Proposed Rules]
[Pages 25590-25595]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11822]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0497; Product Identifier 2017-NM-140-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A300 B4-603, B4-620, and B4-622 airplanes; Model
A300 F4-605R airplanes; Model A300 C4-605R Variant F airplanes; and
Model A300 B4-600R series airplanes. This proposed AD was prompted by
reports of cracking on the frame (FR) 47 angle fitting. This proposed
AD would require, depending on airplane configuration, a modification
of certain angle fitting attachment holes, repetitive inspections for
cracking of certain holes of the internal lower angle fitting web,
certain holes of the internal lower angle fitting horizontal splicing,
the aft bottom panel, and the FR47/Rib 1 junction area, and related
investigative and corrective actions if necessary. We are proposing
this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by July 19, 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
SAS, Airworthiness Office--EAW, 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, 2200
[[Page 25591]]
South 216th St., Des Moines, WA. For information on the availability of
this material at the FAA, call 206-231-3195.
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-2018-
0497; 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 NPRM, 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: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.
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-2018-0497;
Product Identifier 2017-NM-140-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM 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 NPRM.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0210, dated October 24, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A300 B4-603, B4-
620, and B4-622 airplanes; Model A300 F4-605R airplanes; Model A300 C4-
605R Variant F airplanes; and Model A300 B4-600R series airplanes. The
MCAI states:
Prompted by cracks found on the Frame (FR) 47 angle fitting,
Airbus issued SB [Service Bulletin] A300-57-6049, SB A300-57-6050,
and SB A300-57-6086.
These cracks, if not detected and corrected, could affect the
structural integrity of the centre wing box (CWB) of the aeroplane.
Consequently, DGAC [Direction G[eacute]n[eacute]rale de
l'Aviation Civile] France published AD 94-241-170, AD 1999-147-279,
AD 2000-533-328 and AD F-2004-159 (EASA approval 2004-9779), each AD
superseding the previous one, to require repetitive high frequency
eddy current (HFEC) rotating probe inspections of the FR47 internal
lower angle fitting.
After DGAC France AD F-2004-159 was issued, cracks were
reportedly found on the horizontal flange of FR47 internal corner
angle fitting during accomplishment of routine maintenance
structural inspection and modification in accordance with the
instructions of Airbus SB A300-57-6050. Prompted by these findings,
Airbus reviewed and amended the inspection programme for the
internal lower angle fitting flange (horizontal face).
Consequently, EASA issued AD 2012-0092 [which corresponds to FAA
AD 2014-20-18, Amendment 39-17991 (79 FR 65879, November 6, 2014)
(``AD 2014-20-18'')], retaining the requirements of DGAC France AD
F-2004-159, which was superseded, and requiring additional
repetitive inspections of the CWB lower panel through the ultrasonic
method and, depending on findings, re-installation of removed
fasteners in transition fit instead of interface.
In addition, DGAC France had previously issued AD F-2005-124
(EASA approval 2005-6071) to require the same inspections for A300
F4-608ST aeroplanes, in accordance with Airbus SB A300-57-9001 and
SB A300-57-9002.
Following the discovery of numerous cracks during the
accomplishment of SB A300-57-6049 and SB A300-57-6089 inspections,
Airbus developed in a first step a new (recommended) modification
(Airbus SB A300-57-6113) and defined, for post-mod aeroplanes, new
inspections, and published SB A300-57-6119, which included new
inspection methods (ultrasonic/radiographic) with new inspection
thresholds and intervals.
Consequently, EASA issued AD 2016-0198, retaining the
requirements of EASA AD 2012-0092, which was superseded, to require
repetitive inspections for post-SB A300-57-6113 aeroplanes.
Since EASA AD 2016-0198 was issued, Airbus revised in a second
step the inspection programme for A300-600 pre-SB 57-6113 and A300-
600ST aeroplanes, reducing inspection thresholds and intervals. At
this opportunity, the existing ultrasonic inspection for A300-600
aeroplanes has been added for A300-600ST aeroplanes.
For the reasons described above, this new [EASA] AD retains the
requirements of EASA AD 2016-0198 for A300-600 aeroplanes and of
DGAC France AD F-2005-124 for A300-600ST aeroplanes, which are both
superseded, and requires [modification through cold expansion of
certain angle fitting attachment holes and] repetitive inspections
[for cracking of certain holes of the internal lower angle fitting
web, certain holes of the internal lower angle fitting horizontal
splicing, the aft bottom panel, and the FR47/Rib 1 junction area,
and applicable related investigative and corrective actions] with
new compliance times and intervals. This [EASA] AD is applicable to
both A300-600 and A300-600ST aeroplanes * * *.
Related investigative actions include a rotating probe inspection
for cracking. Corrective actions include replacing damaged fasteners,
reaming and drilling holes, installing the next nominal fastener for
oversized bore holes, and repairing cracks. 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-2018-0497.
Relationship Between Proposed AD and AD 2014-20-18
This NPRM would not supersede AD 2014-20-18. Rather, we have
determined that a stand-alone AD would be more appropriate to address
the changes in the MCAI. This NPRM would require depending on airplane
configuration, a modification of certain angle fitting attachment
holes, inspections for cracking of certain holes of the internal lower
angle fitting web, certain holes of the internal lower angle fitting
horizontal splicing, the aft bottom panel, and the FR47/Rib 1 junction
area. Accomplishment of the proposed modification and initial
inspections would then terminate all of the requirements of AD 2014-20-
18.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Service Bulletin A300-57-6049, Revision 8, dated July 4,
2017. This service information describes procedures for HFEC rotating
probe inspections for cracking of certain holes of the internal lower
angle fitting web.
Service Bulletin A300-57-6086, Revision 6, dated July 4,
2017. This service information describes procedures for HFEC rotating
probe inspections for cracking of certain holes in the internal lower
angle fitting horizontal splicing (left-hand and right-hand sides) and
for ultrasonic inspections for cracking of the aft bottom panel.
Service Bulletin A300-57-6119, Revision 00, dated April
25, 2016. This service information describes procedures for ultrasonic
and radiographic inspections for cracking of the FR47/Rib 1 junction
area.
This service information is reasonably available because the
interested parties have access to it through their normal
[[Page 25592]]
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.
Costs of Compliance
We estimate that this proposed AD affects 65 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Up to 727 work-hours x $85 per Up to $3,370............... Up to $65,165.............. Up to $4,235,725
hour = Up to $61,795. per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We estimate that it would take about 1 work-hour per product to
comply with the proposed reporting requirement in this proposed AD. The
average labor rate is $85 per hour. Based on these figures, we estimate
the cost of reporting the inspection results on U.S. operators to be
$5,525, or $85 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this 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 proposed 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 adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2018-0497; Product Identifier 2017-NM-140-AD.
(a) Comments Due Date
We must receive comments by July 19, 2018.
(b) Affected ADs
This AD affects AD 2014-20-18, Amendment 39-17991 (79 FR 65879,
November 6, 2014) (``AD 2014-20-18'').
(c) Applicability
This AD applies to Airbus Model A300 B4-603, A300 B4-620, A300
B4-622, A300 B4-605R, A300 B4-622R, A300 C4-605R Variant F, and A300
F4-605R airplanes, certificated in any category, all manufacturer
serial numbers, except airplanes on which Airbus Modification 12171
or 12249 has been embodied in production, or on which Airbus Service
Bulletin A300-57-6069 has been embodied in service.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracking on the frame (FR) 47
angle fitting. We are issuing this AD to detect and correct cracking
of FR47 angle fitting, which could
[[Page 25593]]
result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
For the purposes of this AD, the definitions in paragraphs
(g)(1) through (g)(6) apply.
(1) Group 1 airplanes are those airplanes on which Airbus
Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016,
has not been incorporated as of the effective date of this AD.
(2) Group 2 airplanes are those airplanes on which Airbus
Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016,
has been incorporated as of the effective date of this AD.
(3) The average flight time (AFT) for the inspection threshold
is defined as the flight hours (FH) divided by the flight cycles
(FC), counted from the first flight of the airplane.
(4) The AFT for the inspection interval is defined as the FH
divided by the FC, counted from the date of the last inspection
required by paragraph (i), (j), (k), or (l) of this AD, as
applicable.
(5) For airplanes on which Airbus modification 10155 has been
embodied, the thresholds for the inspections required by paragraphs
(i), (j), and (k) of this AD are counted from the first flight of
the airplane.
(6) For airplanes on which Airbus modification 10155 has not
been embodied, the thresholds for the inspections required by
paragraphs (i), (j), and (k) of this AD are counted since the date
on which Airbus Service Bulletin A300-57-6050 was embodied on the
airplane.
(h) Modification
For all airplanes on which Airbus modification 10155 has not
been embodied: Before exceeding 15,100 FC or 38,900 FH, whichever
occurs first after first flight of the airplane; or within the
``grace periods'' defined in paragraph 1.B.(4), ``Accomplishment
Timescale,'' of Airbus Service Bulletin A300-57-6050, Revision 3,
dated May 31, 2001; whichever occurs later, modify the angle fitting
attachment holes of the wing center box by cold expansion, including
doing a rotating probe inspection for cracking, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A300-57-
6050, Revision 3, dated May 31, 2001. Where paragraph 1.B.(4),
``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-
6050, Revision 3, dated May 31, 2001, specifies ``grace periods''
relative to the receipt of the service bulletin, count the ``grace
periods'' from December 19, 2005 (the effective date of AD 2005-23-
08). If any crack is found during any inspection: Before further
flight, repair using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus's EASA Design Organization Approval
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
(i) Internal Lower Angle Fitting (Vertical Face) Web Inspections
For Group 1 airplanes: Before exceeding the applicable threshold
specified in figure 1 to paragraph (i) of this AD, or within 12
months after the effective date of this AD, whichever occurs later,
do a high frequency eddy current (HFEC) rotating probe inspection
for cracking of holes H, I, K, L, M, N, U, V, W, X, and Y of the
internal lower angle fitting web (left-hand and right-hand sides),
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6049, Revision 8, dated July 4, 2017. Repeat the
inspection thereafter at intervals not to exceed those specified in
figure 1 to paragraph (i) of this AD.
[GRAPHIC] [TIFF OMITTED] TP04JN18.002
(j) Internal Lower Angle Fitting (Horizontal Face) Inspections
For Group 1 airplanes: Before exceeding the applicable threshold
specified in figure 2 to paragraph (j) of this AD, or within 12
months after the effective date of this AD, whichever occurs later,
do an HFEC rotating probe inspection for cracking of holes A, B, C,
D, E, F, G, P, Q, S, and T (adjacent to hole G) of the internal
lower angle fitting horizontal splicing (left-hand and right-hand
sides), in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017.
Repeat the inspection thereafter at intervals not to exceed those
specified in figure 2 to paragraph (j) of this AD.
[GRAPHIC] [TIFF OMITTED] TP04JN18.003
[[Page 25594]]
(k) Aft Bottom Panel Inspections
For Group 1 airplanes: Before exceeding the applicable
thresholds specified in figure 3 to paragraph (k) of this AD, or
within 12 months after the effective date of this AD, whichever
occurs later, do an ultrasonic inspection for cracking of the aft
bottom panel, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4,
2017. Repeat the inspection thereafter at intervals not to exceed
those specified in figure 3 to paragraph (k) of this AD.
[GRAPHIC] [TIFF OMITTED] TP04JN18.004
(l) FR47/Rib 1 Junction Area Inspections
For Group 2 airplanes: Before exceeding the applicable
thresholds specified in figure 4 to paragraph (l) of this AD, do
ultrasonic and radiographic inspections for cracking of the FR47/Rib
1 junction area, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-57-6119, Revision 00, dated April
25, 2016. Repeat the inspections thereafter at intervals not to
exceed those specified in figure 4 to paragraph (l) of this AD.
Count the threshold compliance times from the date on which Airbus
Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016,
was embodied on the airplane.
[GRAPHIC] [TIFF OMITTED] TP04JN18.005
(m) Related Investigative and Corrective Actions
If, during any inspection required by paragraph (i), (j), (k),
or (l) of this AD, any crack is found: Before further flight,
accomplish all applicable related investigative and corrective
actions in accordance with the Accomplishment Instructions of the
service information specified in paragraphs (m)(1) through (m)(3) of
this AD, as applicable. Where the service information specified in
paragraphs (m)(1) through (m)(3) of this AD specifies to contact
Airbus for instructions, before further flight, obtain instructions
approved by the Manager, International Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA and accomplish those
instructions accordingly. If approved by the DOA, the approval must
include the DOA-authorized signature.
(1) If the inspection was done as specified in paragraph (i) of
this AD: Airbus Service Bulletin A300-57-6049, Revision 8, dated
July 4, 2017.
(2) If the inspection was done as specified in paragraph (j) or
(k) of this AD: Airbus Service Bulletin A300-57-6086, Revision 6,
dated July 4, 2017.
(3) If the inspection was done as specified in paragraph (l) of
this AD: Airbus Service Bulletin A300-57-6119, Revision 00, dated
April 25, 2016.
(n) Reporting
At the applicable time specified in paragraph (n)(1) or (n)(2)
of this AD: Report the results of the inspections required by
paragraphs (i), (j), (k), and (l) of this AD to Airbus Service
Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or submit the results to Airbus in accordance with
the instructions of the applicable service information specified in
paragraphs (i), (j), (k), or (l) of this AD. The report must include
the inspection results, a description of any discrepancies found,
the
[[Page 25595]]
airplane serial number, and the number of flight cycles and flight
hours on the airplane.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(o) Terminating Action for AD 2014-20-18
Accomplishment of the action required by paragraph (h) of this
AD and the initial inspections required by paragraphs (i) and (j),
and (k) of this AD terminates all requirements of AD 2014-20-18.
(p) Credit for Previous Actions
This paragraph provides credit for actions specified in
paragraph (h) of this AD, if those actions were performed before
December 19, 2005 (the effective date of AD 2005-23-08), using
Airbus Service Bulletin A300-57-6050, Revision 02, dated February
10, 2000.
(q) Other FAA AD Provisions
The following provisions also apply to this AD:
(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 (r)(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: 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 EASA; or Airbus's EASA
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Paperwork Reduction Act Burden Statement: 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 1
work-hour 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.
(4) Required for Compliance (RC): Except as required by
paragraph (m) 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.
(r) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0210, dated October 24, 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-2018-0497.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3225.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 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, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
Issued in Des Moines, Washington, on May 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-11822 Filed 6-1-18; 8:45 am]
BILLING CODE 4910-13-P
