Airworthiness Directives; Airbus Airplanes, 8201-8207 [2018-03599]
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Federal Register / Vol. 83, No. 38 / Monday, February 26, 2018 / Proposed Rules
of this service bulletin,’’ this AD requires
using ‘‘the effective date of this AD.’’
(i) Credit for Previous Actions
This paragraph provides credit for the
corresponding actions specified in paragraph
(g) of this AD, if those actions were
performed before the effective date of this AD
using Boeing Special Attention Service
Bulletin 777–25–0621, dated December 10,
2014.
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(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO 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
certification office, send it to the attention of
the person identified in paragraph (k)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) For service information that contains
steps that are labeled as RC, the provisions
of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled 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 RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
(1) For more information about this AD,
contact Scott Craig, Aerospace Engineer,
Cabin Safety and Environmental Systems
Section, FAA, Seattle ACO Branch, 2200
South 216th Street, Des Moines, WA 98198;
phone and fax: 206–231–3566; email:
Michael.S.Craig@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
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MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.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 Renton, Washington, on February
15, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–03712 Filed 2–23–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0113; Product
Identifier 2017–NM–060–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) 2016–12–
09, for certain Airbus Model A330–200,
–200 Freighter, and –300 series
airplanes; and Model A340–200 and
–300 series airplanes. AD 2016–12–09
requires removing fasteners, doing a
rototest inspection of fastener holes,
installing new fasteners, oversizing the
holes and doing rototest inspections for
cracks if necessary, and repairing any
cracking that was found. Since we
issued AD 2016–12–09, an evaluation
by the design approval holder (DAH)
indicates that certain fastener holes are
subject to widespread fatigue damage
(WFD). This proposed AD would add
airplanes to the effectivity, add
repetitive inspections of the fastener
holes at frame (FR) 40, and, for certain
airplanes, require a modification, which
terminates the inspections. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by April 12, 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.
SUMMARY:
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• 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 referenced 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–
0113; 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:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax: 206–231–3229.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2018–0113; Product Identifier
2017–NM–060–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
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will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as WFD. It is
associated with general degradation of
large areas of structure with similar
structural details and stress levels. As
an airplane ages, WFD will likely occur,
and will certainly occur if the airplane
is operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
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while providing operators with certainty
regarding the LOV applicable to their
airplanes.
We issued AD 2016–12–09,
Amendment 39–18558 (81 FR 38573,
June 14, 2016) (‘‘AD 2016–12–09’’), for
certain Airbus Model A330–200, –200
Freighter, and –300 series airplanes, and
Model A340–200 and –300 series
airplanes. AD 2016–12–09 was
prompted by reports that cracks were
found on an adjacent hole of certain
frames of the center wing box (CWB).
AD 2016–12–09 requires removing
fasteners, doing a rototest inspection of
fastener holes, installing new fasteners,
oversizing the holes and doing rototest
inspections for cracks if necessary, and
repairing any cracking that was found.
We issued AD 2016–12–09 to detect and
correct cracking on certain holes of the
CWB, which could affect the structural
integrity of the airplane.
Actions Since AD 2016–12–09 Was
Issued
Since we issued AD 2016–12–09, an
evaluation by the DAH indicates that
the fastener holes at FR40 of the inside
and outside CWB (above and below
bottom skin) are subject to WFD.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0069,
dated April 25, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A330–200,
–200 Freighter, and –300 series
airplanes, and Model A340–200 and
–300 series airplanes. The MCAI states:
During accomplishment of A330
Airworthiness Limitation Item (ALI) task 57–
11–04 on the rear fitting of the Frame (FR)
40 between stringers (STR) 38 and STR39 on
both LH [left-hand] and RH [right-hand] sides
of the fuselage, cracks were found on an
adjacent hole. After reaming at second
oversize of the subject hole, the crack was
still present. As a result of a sampling
inspection program, additional crack findings
were reported on this adjacent hole on other
A330 and A340 aeroplanes.
This condition, if not detected and
corrected, could affect the structural integrity
of the centre fuselage of the aeroplane.
Prompted by these findings, EASA issued
AD 2014–0149 [which corresponds to FAA
AD 2016–12–09] to require removal of the
fasteners and repetitive Special Detailed
Inspection (SDI) of fastener holes at FR40
vertical web above or below Centre Wing Box
(CWB) lower panel reference on both LH and
RH sides of the fuselage, and, depending on
findings, accomplishment of the applicable
corrective actions. That [EASA] AD excluded
certain aeroplanes from the Applicability, on
which Airbus modification (mod) 55792 or
mod 55306 had been embodied in
production.
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Since EASA AD 2014–0149 was issued,
prompted by complementary fatigue analyses
correlated with in-service findings, Airbus
published Service Bulletin (SB) A330–57–
3115 Revision 01 and SB A340–57–4124
Revision 02, which introduced revised
thresholds and intervals for the repetitive
inspections of the inside CWB (above bottom
skin), and an alleviation of the number of
holes to be inspected, for post-mod 44360
and pre-mod 55306 configuration aeroplanes.
In addition, for aeroplanes in post-mod
44360, post-mod 55306 and pre-mod 205225
configuration, Airbus developed mod
206051, introducing reinforcement of the
structural integrity of the inside CWB (above
bottom skin) area, and published associated
Airbus SB A330–57–3129 and SB A340–57–
4136, as applicable, which avoids the need
for required repetitive inspections for the
inside of the CWB.
Finally, Airbus published SB A330–57–
3116 Revision 01 and SB A330–57–4125
Revision 01, as applicable, to expand their
Effectivity to include aeroplanes in post-mod
44360 and post-mod 49202 configuration for
inspections of the outside CWB (below
bottom skin), and introduced revised
thresholds and intervals for the repetitive
inspections of the outside CWB, and to
provide an alleviation of the number of holes
to be inspected. The repetitive inspection
program for aeroplanes in pre-mod 44360
configuration remains unchanged.
For the reasons described above, this
[EASA] AD partially retains the requirements
of EASA AD 2014–0149, which is
superseded, and requires new repetitive
inspections of the fastener holes at FR40 of
the inside and the outside CWB (above and
below bottom skin), and the implementation
of the modification of the inside CWB, as
terminating action of the repetitive SDI.
Required actions also include
oversizing certain holes, installing new
fasteners, and repairing any cracking
that is found.
The compliance times for the
inspections range depending on
airplane operation and utilization. The
earliest initial flight-cycle compliance
time is 13,500 flight cycles. The earliest
initial flight-hour compliance time is
57,000 flight hours. The latest initial
flight-cycle compliance time is 30,900
flight cycles. The latest initial flighthour compliance time is 162,000 flight
hours. The earliest repetitive flight-cycle
compliance time is 5,950 flight cycles.
The earliest repetitive flight-hour
compliance time is 24,300 flight hours.
The latest repetitive flight-cycle
compliance time is 7,400 flight cycles.
The latest repetitive flight-hour
compliance time is 40,400 flight hours.
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–
0113.
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Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information. This service
information describes procedures for
removing the fasteners and doing a
repetitive rototest inspection of fastener
holes at FR40 vertical web on both
sides, checking for the existence of a
repair done as specified by a repair
design approval sheet (RDAS), installing
new fasteners in transition fit,
oversizing the holes, and repairing any
crack found. This service information is
distinct because it applies to different
airplane models and configurations.
• Airbus Service Bulletin A330–57–
3114, Revision 01, dated January 13,
2017.
• Airbus Service Bulletin A330–57–
3115, Revision 01, including
Appendices 01 and 02, dated November
23, 2016.
• Airbus Service Bulletin A330–57–
3116, Revision 01, including
Appendices 01 and 02, dated November
23, 2016.
• Airbus Service Bulletin A340–57–
4123, Revision 01, dated January 13,
2017.
• Airbus Service Bulletin A340–57–
4124, Revision 02, including
Appendices 01 and 02, dated November
23, 2016.
• Airbus Service Bulletin A340–57–
4125, Revision 01, including
Appendices 01 and 02, dated November
23, 2016.
Airbus has also issued the following
service information. This service
information describes procedures for
modification of certain fastener holes.
The modification includes a rotating
probe inspection for cracking, related
investigative actions (checks of the hole
diameter), and corrective actions
(repair). This service information is
distinct because it applies to different
airplane models and configurations.
• Airbus Service Bulletin A330–57–
3129, dated October 5, 2016.
• Airbus Service Bulletin A330–57–
3130, dated November 23, 2016.
• Airbus Service Bulletin A330–57–
3131, dated November 23, 2016.
• Airbus Service Bulletin A330–57–
3132, including Appendices 01 and 02,
dated November 23, 2016.
• Airbus Service Bulletin A340–57–
4136, dated October 5, 2016.
• Airbus Service Bulletin A340–57–
4137, dated November 23, 2016.
• Airbus Service Bulletin A340–57–
4138, dated November 23, 2016.
• Airbus Service Bulletin A340–57–
4139, including Appendices 01 and 02,
dated November 23, 2016.
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 these same
type designs.
Explanation of a Certain Compliance
Time
The compliance time for the
replacement specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
replaced before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
Costs of Compliance
We estimate that this proposed AD
affects 99 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection (retained actions from
AD 2016–12–09) (35 airplanes).
Inspection (new proposed action)
(99 airplanes).
78 work-hours × $85 per hour =
$6,630 per inspection cycle.
Up to 257 work-hours × $85 per
hour = $21,845 per inspection
cycle.
Up to 136 work-hours × $85 per
hour = $11,560.
$0 ...................
Modification (new proposed action)
(Up to 99 airplanes).
We estimate the following costs to do
any necessary on-condition actions that
$0 ...................
Up to $1,070 ..
Cost per product
Cost on U.S. operators
$6,630 per inspection
cycle.
Up to $21,845 per inspection cycle.
$232,050 per inspection
cycle.
Up to $2,162,655 per inspection cycle.
Up to $12,630 .................
Up to $1,250,370.
would be required based on the results
of the proposed inspection. We have no
way of determining the number of
aircraft that might need these actions:
ON-CONDITION COSTS
Labor cost
Parts cost
Oversize, installation, and inspection ......................
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Action
Up to 105 work-hours × $85 per hour = $8,925 .....
Up to $21,560 ..
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
specified in this proposed AD.
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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
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Cost per product
Up to $30,485.
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
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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.
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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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2016–12–09, Amendment 39–18558 (81
FR 38573, June 14, 2016), and adding
the following new AD:
■
Airbus: Docket No. FAA–2018–0113; Product
Identifier 2017–NM–060–AD.
(a) Comments Due Date
We must receive comments by April 12,
2018.
(b) Affected ADs
This AD replaces AD 2016–12–09,
Amendment 39–18558 (81 FR 38573, June
14, 2016) (‘‘AD 2016–12–09’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(5)
of this AD, certificated in any category, all
manufacturer serial numbers, except those on
which Airbus Repair Instructions R57115092
have been embodied in service on both righthand (RH) and left-hand (LH) sides.
(1) Model A330–201, –202, –203, –223, and
–243 airplanes.
(2) Model A330–223F and –243F airplanes.
(3) Model A330–301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes.
(4) Model A340–211, –212, and –213
airplanes.
(5) Model A340–311, –312, and –313
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports that
cracks were found on an adjacent hole of
certain frames of the center wing box (CWB).
We are issuing this AD to detect and correct
cracking of certain holes of certain frames of
the CWB, which could affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Service Information
(1) For the actions required by paragraphs
(h), (i), and (j) of this AD, use the applicable
service information specified in paragraphs
(g)(1)(i) through (g)(1)(vi) of this AD.
(i) Airbus Service Bulletin A330–57–3114,
Revision 01, dated January 13, 2017 (CWB
inspection area: Below) (for Model A330–300
series airplanes in pre-modification 44360
configuration).
(ii) Airbus Service Bulletin A330–57–3115,
Revision 01, including Appendices 01 and
02, dated November 23, 2016 (CWB
inspection area: Above) (for Model A330–200
and –300 series airplanes in pre-modification
55306 and pre-modification 55792
configuration).
(iii) Airbus Service Bulletin A330–57–
3116, Revision 01, including Appendices 01
and 02, dated November 23, 2016 (CWB
inspection area: Below) (for Model A330–200
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and –300 series airplanes in postmodification 44360 configuration).
(iv) Airbus Service Bulletin A340–57–
4123, Revision 01, dated January 13, 2017
(CWB inspection area: Below) (for Model
A340–200 and –300 series airplanes in premodification 44360 configuration).
(v) Airbus Service Bulletin A340–57–4124,
Revision 02, including Appendices 01 and
02, dated November 23, 2016 (CWB
inspection area: Above) (for Model A340–200
and –300 series airplanes in pre-modification
55306 and pre-modification 55792
configuration).
(vi) Airbus Service Bulletin A340–57–
4125, Revision 01, including Appendices 01
and 02, dated November 23, 2016 (CWB
inspection area: Below) (for Model A340–200
and –300 series airplanes in postmodification 44360 configuration).
(2) For the modification required by
paragraph (o)(1) of this AD, use the
applicable service information specified in
paragraphs (g)(2)(i) through (g)(2)(vi) of this
AD.
(i) Airbus Service Bulletin A330–57–3130,
dated November 23, 2016 (for Model A330–
200 and –300 series airplanes in postmodification 44360, post-Airbus Service
Bulletin A330–57–3131, and premodification 49202 configuration).
(ii) Airbus Service Bulletin A330–57–3131,
dated November 23, 2016 (for Model A330–
200 and –300 series airplanes in postmodification 44360 and pre-modification
55306 configuration).
(iii) Airbus Service Bulletin A330–57–
3132, including Appendices 01 and 02, dated
November 23, 2016 (for Model A330–200 and
–300 series airplanes in post-modification
44360 configuration).
(iv) Airbus Service Bulletin A340–57–
4137, dated November 23, 2016 (for Model
A340–200 and –300 series airplanes in postmodification 44360, post-Airbus Service
Bulletin A340–57–4138, and premodification 49202 configuration).
(v) Airbus Service Bulletin A340–57–4138,
dated November 23, 2016 (for Model A340–
200 and –300 series airplanes in postmodification 44360 and pre-modification
55306 configuration).
(vi) Airbus Service Bulletin A340–57–
4139, including Appendices 01 and 02, dated
November 23, 2016 (for Model A340–200 and
–300 series airplanes in post-modification
44360 configuration).
(h) Repetitive Inspections and Certain
Repairs
Except as specified in paragraphs (l)(2),
(l)(3), (p) of this AD: Before exceeding the
applicable threshold specified in paragraph
1.E., ‘‘Compliance’’ of the applicable service
information specified in paragraph (g)(1) of
this AD, or within the compliance time
specified in table 1 to paragraph (h) of this
AD, whichever occurs later; remove the
fasteners and accomplish a special detailed
inspection (SDI) of the fastener holes at frame
(FR) 40 vertical web, on both LH and RH
sides, of the affected CWB lower panel area,
and, as applicable, check for the existence of
a repair done as specified by a repair design
approval sheet (RDAS), in accordance with
the Accomplishment Instructions of the
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applicable service information specified in
paragraph (g)(1) of this AD, and if any RDAS
repair is found 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.
Repeat the SDI thereafter at the applicable
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of the applicable service
information identified in paragraph (g)(1) of
this AD.
(i) Follow-On Actions: No Cracking
If no crack is found during any inspection
required by paragraph (h) of this AD: Before
further flight, install new fasteners in the
transition fit, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraph (g)(1) of this AD.
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) When it is determined that no RDAS is
found to exist for the FR40 area it is
acceptable to accomplish the first SDI before
exceeding the applicable threshold, instead
of ‘‘before next flight’’, as specified in the
applicable service information specified in
paragraph (g)(1)(ii), (g)(1)(iii), (g)(1)(v) and
(g)(1)(vi) of this AD.
VerDate Sep<11>2014
17:05 Feb 23, 2018
Jkt 244001
(l) Exceptions to Service Information
(1) Where the applicable service
information identified in paragraphs (g) and
(m) of this AD specifies contacting Airbus for
appropriate action: Before further flight,
repair 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.
(2) Where paragraph 1.E., ‘‘Compliance,’’ of
the applicable service information specified
in paragraph (g)(1) of this AD specifies a
compliance time in terms of a ‘‘Threshold’’
and ‘‘Grace Period,’’ this AD requires
compliance at the later of the applicable
threshold and grace period.
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Fmt 4702
Sfmt 4702
(m) Modification for Airplanes in PostModification 55306 and Pre-Modification
205225 Configuration
For airplanes in post-modification 55306
and pre-modification 205225 configuration:
Before exceeding the applicable compliance
time specified in table 2 to paragraph (m) of
this AD, as applicable, or within 18 months
after the effective date of this AD, whichever
occurs later; modify the inside CWB (above
bottom skin), including doing a rotating
probe inspection for cracking and all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3129, dated
October 5, 2016; or Airbus Service Bulletin
A340–57–4136, dated October 5, 2016; as
applicable; except as required by paragraph
(l)(1) of this AD. Do all applicable related
investigative and corrective actions before
further flight.
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daltland on DSKBBV9HB2PROD with PROPOSALS
(j) Follow-On Actions: Cracking
If any crack is found during any inspection
required by paragraph (h) of this AD: Before
further flight, oversize the holes to the first
oversize in comparison with the current hole
diameter, and do an SDI for cracks, in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (g)(1) of
this AD.
(1) If no cracking is found during the SDI
required by the introductory text of
paragraph (j) of this AD: Before further flight,
install new fasteners in the transition fit, in
accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (g)(1) of
this AD.
(2) If any cracking is found during the SDI
required by the introductory text of
paragraph (j) of this AD: Before further flight,
repair using a method approved by the
Manager, International Section, Transport
(k) No Reporting Required
Although the applicable service
information specified in paragraph (g)(1) of
this AD specifies to submit certain
information to the manufacturer, and
specifies that action as ‘‘RC’’ (Required for
Compliance), this AD does not include that
requirement.
Federal Register / Vol. 83, No. 38 / Monday, February 26, 2018 / Proposed Rules
(n) Terminating Action for Certain
Airworthiness Limitation Item (ALI) Tasks
(1) Accomplishment on an airplane of the
initial and repetitive inspections required by
paragraph (h) of this AD terminates the
requirements of ALI task 57–11–02 and task
57–11–04 of the applicable Airbus
Airworthiness Limitation Section (ALS) Part
2, Damage Tolerant (DT) ALI, for that
airplane.
(2) Modification of an airplane as required
by paragraph (m) of this AD terminates the
requirements of ALI task 57–11–02 of the
applicable Airbus ALS Part 2, DT ALI, for
that airplane.
daltland on DSKBBV9HB2PROD with PROPOSALS
(o) Terminating Action for Repetitive SDI
Inspections
(1) Modification of a post-modification
44360 airplane by multiple cold working,
including doing a rotating probe inspection
for cracking and all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraph (g)(2) of
this AD, except as required by paragraph
(l)(1) of this AD, constitutes terminating
action for the repetitive SDI required by
paragraph (h) of this AD for that airplane,
provided the modification is accomplished
within the applicable compliance times
specified in the applicable Airbus service
information specified in paragraph (g)(1) of
this AD.
(2) If, during any inspection of a postmodification 44360 airplane, as required by
paragraph (h) of this AD, a crack previously
repaired by an Airbus RDAS is detected only
on the LH or RH side, it is permitted to do
the modification specified in paragraph (o)(1)
of this AD on the non-repaired side. Doing
the modification constitutes terminating
action for the repetitive SDI required by
paragraph (h) of this AD on the modified side
only.
VerDate Sep<11>2014
17:05 Feb 23, 2018
Jkt 244001
(p) Extension to Compliance Time for
Certain Airplanes
For post-modification 44360 airplanes and
pre-modification 55306 airplanes that have
been inspected before the effective date of
this AD as required by AD 2016–12–09: It is
permitted to defer the next due inspection to
18 months after the effective date of this AD,
provided the previous inspection interval, as
applicable, depending on airplane
configuration and utilization, as specified in
the service information used in the previous
inspection is not exceeded.
(q) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraphs (h) through (j)
of this AD, if those actions were performed
before the effective date of this AD using the
applicable service information specified in
paragraphs (q)(1)(i) through (q)(1)(vi) of this
AD. This service information was
incorporated by reference in AD 2016–09–11,
Amendment 39–18509 (81 FR 27986, May 9,
2016).
(i) Airbus Service Bulletin A330–57–3114,
dated March 12, 2013.
(ii) Airbus Service Bulletin A330–57–3115,
April 4, 2013.
(iii) Airbus Service Bulletin A330–57–
3116, dated March 12, 2013.
(iv) Airbus Service Bulletin A340–57–
4123, dated March 12, 2013.
(v) Airbus Service Bulletin A340–57–4124,
Revision 01, dated August 22, 2013.
(vi) Airbus Service Bulletin A340–57–
4125, dated March 12, 2013.
(2) This paragraph provides credit for the
actions required by paragraphs (h) through (j)
of this AD, if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A340–57–4124,
dated April 4, 2013. This service information
is not incorporated by reference in this AD.
(3) This paragraph provides credit for the
actions required by paragraphs (h) through (j)
of this AD, if those actions were performed
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
before the effective date of this AD using the
applicable service information specified in
paragraphs (q)(3)(i) through (q)(3)(viii) of this
AD. This service information is not
incorporated by reference in this AD.
(i) Airbus Technical Disposition
LR57D11023270, Issue B, dated July 12,
2011.
(ii) Airbus Technical Disposition
LR57D11029170, Issue C, dated September 6,
2011.
(iii) Airbus Technical Disposition
LR57D11029171, Issue B, dated September 6,
2011.
(iv) Airbus Technical Disposition
LR57D11029172, Issue B, dated September 6,
2011.
(v) Airbus Technical Disposition
LR57D11029173, Issue B, dated September 6,
2011.
(vi) Airbus Technical Disposition
LR57D11023714, Issue B, dated July 12,
2011.
(vii) Airbus Technical Disposition
LR57D11030740, Issue C, dated September
22, 2011.
(viii) Airbus Technical Disposition
LR57D11030741, Issue B, dated September
22, 2011.
(r) 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 manager of the International
Section, send it to the attention of the person
identified in paragraph (s)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
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Federal Register / Vol. 83, No. 38 / Monday, February 26, 2018 / Proposed Rules
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 EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (k) and (l)(1) 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.
(s) Related Information
daltland on DSKBBV9HB2PROD with PROPOSALS
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0069, dated April 25, 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–2018–0113.
(2) For more information about this AD,
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.
(3) For service information identified in
this AD, 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.
Issued in Renton, Washington, on February
14, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–03599 Filed 2–23–18; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
17:05 Feb 23, 2018
Jkt 244001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2017–1088; Airspace
Docket No. 17–AWP–25]
Proposed Revocation of Class E
Airspace; Crows Landing, CA
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
remove Class E airspace extending
upward from 1,200 feet above the
surface at Crows Landing Airport,
Crows Landing, CA. This airspace is
wholly contained within the
Sacramento en route airspace area and
duplication is not necessary.
DATES: Comments must be received on
or before April 12, 2018.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE, West Building,
Ground Floor, Room W12–140,
Washington, DC 20590; telephone: (800)
647–5527, or (202) 366–9826. You must
identify FAA Docket No. FAA–2017–
1088; Airspace Docket No. 17–AWP–25,
at the beginning of your comments. You
may also submit comments through the
internet at https://www.regulations.gov.
FAA Order 7400.11B, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
Avenue SW, Washington, DC 20591;
telephone: (202) 267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11B at NARA, call (202)
741–6030, or go to https://
www.archives.gov/federal-register/cfr/
ibr-locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT: Tom
Clark, Federal Aviation Administration,
Operations Support Group, Western
Service Center, 1601 Lind Avenue SW,
Renton, WA 98057; telephone (425)
203–4511.
SUPPLEMENTARY INFORMATION:
SUMMARY:
PO 00000
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8207
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
Subtitle I, Section 106 describes the
authority of the FAA Administrator.
Subtitle VII, Aviation Programs,
describes in more detail the scope of the
agency’s authority. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it clarifies
airspace designations by eliminating the
redundancy.
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (Docket No. FAA–
2017–1088; Airspace Docket No. 17–
AWP–25) and be submitted in triplicate
to DOT Docket Operations (see
ADDRESSES section for address and
phone number). You may also submit
comments through the internet at https://
www.regulations.gov.
Persons wishing the FAA to
acknowledge receipt of their comments
on this notice must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2017–1088, Airspace
Docket No. 17–AWP–25’’. The postcard
will be date/time stamped and returned
to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this notice may
be changed in light of the comments
received. A report summarizing each
substantive public contact with FAA
personnel concerned with this
rulemaking will be filed in the docket.
Availability of NPRMs
An electronic copy of this document
may be downloaded through the
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]]>Agencies
[Federal Register Volume 83, Number 38 (Monday, February 26, 2018)]
[Proposed Rules]
[Pages 8201-8207]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-03599]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0113; Product Identifier 2017-NM-060-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) 2016-12-
09, for certain Airbus Model A330-200, -200 Freighter, and -300 series
airplanes; and Model A340-200 and -300 series airplanes. AD 2016-12-09
requires removing fasteners, doing a rototest inspection of fastener
holes, installing new fasteners, oversizing the holes and doing
rototest inspections for cracks if necessary, and repairing any
cracking that was found. Since we issued AD 2016-12-09, an evaluation
by the design approval holder (DAH) indicates that certain fastener
holes are subject to widespread fatigue damage (WFD). This proposed AD
would add airplanes to the effectivity, add repetitive inspections of
the fastener holes at frame (FR) 40, and, for certain airplanes,
require a modification, which terminates the inspections. We are
proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 12, 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: [email protected]; internet: https://www.airbus.com. You may view this referenced 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-
0113; 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: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0113;
Product Identifier 2017-NM-060-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
[[Page 8202]]
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as WFD. It is associated with general
degradation of large areas of structure with similar structural details
and stress levels. As an airplane ages, WFD will likely occur, and will
certainly occur if the airplane is operated long enough without any
intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule does not require identifying and developing
maintenance actions if the DAHs can show that such actions are not
necessary to prevent WFD before the airplane reaches the LOV. Many
LOVs, however, do depend on accomplishment of future maintenance
actions. As stated in the WFD rule, any maintenance actions necessary
to reach the LOV will be mandated by airworthiness directives through
separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
We issued AD 2016-12-09, Amendment 39-18558 (81 FR 38573, June 14,
2016) (``AD 2016-12-09''), for certain Airbus Model A330-200, -200
Freighter, and -300 series airplanes, and Model A340-200 and -300
series airplanes. AD 2016-12-09 was prompted by reports that cracks
were found on an adjacent hole of certain frames of the center wing box
(CWB). AD 2016-12-09 requires removing fasteners, doing a rototest
inspection of fastener holes, installing new fasteners, oversizing the
holes and doing rototest inspections for cracks if necessary, and
repairing any cracking that was found. We issued AD 2016-12-09 to
detect and correct cracking on certain holes of the CWB, which could
affect the structural integrity of the airplane.
Actions Since AD 2016-12-09 Was Issued
Since we issued AD 2016-12-09, an evaluation by the DAH indicates
that the fastener holes at FR40 of the inside and outside CWB (above
and below bottom skin) are subject to WFD.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0069, dated April 25, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A330-200, -200
Freighter, and -300 series airplanes, and Model A340-200 and -300
series airplanes. The MCAI states:
During accomplishment of A330 Airworthiness Limitation Item
(ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between
stringers (STR) 38 and STR39 on both LH [left-hand] and RH [right-
hand] sides of the fuselage, cracks were found on an adjacent hole.
After reaming at second oversize of the subject hole, the crack was
still present. As a result of a sampling inspection program,
additional crack findings were reported on this adjacent hole on
other A330 and A340 aeroplanes.
This condition, if not detected and corrected, could affect the
structural integrity of the centre fuselage of the aeroplane.
Prompted by these findings, EASA issued AD 2014-0149 [which
corresponds to FAA AD 2016-12-09] to require removal of the
fasteners and repetitive Special Detailed Inspection (SDI) of
fastener holes at FR40 vertical web above or below Centre Wing Box
(CWB) lower panel reference on both LH and RH sides of the fuselage,
and, depending on findings, accomplishment of the applicable
corrective actions. That [EASA] AD excluded certain aeroplanes from
the Applicability, on which Airbus modification (mod) 55792 or mod
55306 had been embodied in production.
Since EASA AD 2014-0149 was issued, prompted by complementary
fatigue analyses correlated with in-service findings, Airbus
published Service Bulletin (SB) A330-57-3115 Revision 01 and SB
A340-57-4124 Revision 02, which introduced revised thresholds and
intervals for the repetitive inspections of the inside CWB (above
bottom skin), and an alleviation of the number of holes to be
inspected, for post-mod 44360 and pre-mod 55306 configuration
aeroplanes.
In addition, for aeroplanes in post-mod 44360, post-mod 55306
and pre-mod 205225 configuration, Airbus developed mod 206051,
introducing reinforcement of the structural integrity of the inside
CWB (above bottom skin) area, and published associated Airbus SB
A330-57-3129 and SB A340-57-4136, as applicable, which avoids the
need for required repetitive inspections for the inside of the CWB.
Finally, Airbus published SB A330-57-3116 Revision 01 and SB
A330-57-4125 Revision 01, as applicable, to expand their Effectivity
to include aeroplanes in post-mod 44360 and post-mod 49202
configuration for inspections of the outside CWB (below bottom
skin), and introduced revised thresholds and intervals for the
repetitive inspections of the outside CWB, and to provide an
alleviation of the number of holes to be inspected. The repetitive
inspection program for aeroplanes in pre-mod 44360 configuration
remains unchanged.
For the reasons described above, this [EASA] AD partially
retains the requirements of EASA AD 2014-0149, which is superseded,
and requires new repetitive inspections of the fastener holes at
FR40 of the inside and the outside CWB (above and below bottom
skin), and the implementation of the modification of the inside CWB,
as terminating action of the repetitive SDI.
Required actions also include oversizing certain holes, installing
new fasteners, and repairing any cracking that is found.
The compliance times for the inspections range depending on
airplane operation and utilization. The earliest initial flight-cycle
compliance time is 13,500 flight cycles. The earliest initial flight-
hour compliance time is 57,000 flight hours. The latest initial flight-
cycle compliance time is 30,900 flight cycles. The latest initial
flight-hour compliance time is 162,000 flight hours. The earliest
repetitive flight-cycle compliance time is 5,950 flight cycles. The
earliest repetitive flight-hour compliance time is 24,300 flight hours.
The latest repetitive flight-cycle compliance time is 7,400 flight
cycles. The latest repetitive flight-hour compliance time is 40,400
flight hours. 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-2018-0113.
[[Page 8203]]
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information. This service
information describes procedures for removing the fasteners and doing a
repetitive rototest inspection of fastener holes at FR40 vertical web
on both sides, checking for the existence of a repair done as specified
by a repair design approval sheet (RDAS), installing new fasteners in
transition fit, oversizing the holes, and repairing any crack found.
This service information is distinct because it applies to different
airplane models and configurations.
Airbus Service Bulletin A330-57-3114, Revision 01, dated
January 13, 2017.
Airbus Service Bulletin A330-57-3115, Revision 01,
including Appendices 01 and 02, dated November 23, 2016.
Airbus Service Bulletin A330-57-3116, Revision 01,
including Appendices 01 and 02, dated November 23, 2016.
Airbus Service Bulletin A340-57-4123, Revision 01, dated
January 13, 2017.
Airbus Service Bulletin A340-57-4124, Revision 02,
including Appendices 01 and 02, dated November 23, 2016.
Airbus Service Bulletin A340-57-4125, Revision 01,
including Appendices 01 and 02, dated November 23, 2016.
Airbus has also issued the following service information. This
service information describes procedures for modification of certain
fastener holes. The modification includes a rotating probe inspection
for cracking, related investigative actions (checks of the hole
diameter), and corrective actions (repair). This service information is
distinct because it applies to different airplane models and
configurations.
Airbus Service Bulletin A330-57-3129, dated October 5,
2016.
Airbus Service Bulletin A330-57-3130, dated November 23,
2016.
Airbus Service Bulletin A330-57-3131, dated November 23,
2016.
Airbus Service Bulletin A330-57-3132, including Appendices
01 and 02, dated November 23, 2016.
Airbus Service Bulletin A340-57-4136, dated October 5,
2016.
Airbus Service Bulletin A340-57-4137, dated November 23,
2016.
Airbus Service Bulletin A340-57-4138, dated November 23,
2016.
Airbus Service Bulletin A340-57-4139, including Appendices
01 and 02, dated November 23, 2016.
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 these
same type designs.
Explanation of a Certain Compliance Time
The compliance time for the replacement specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 99 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained actions 78 work-hours x $85 $0.................. $6,630 per $232,050 per
from AD 2016-12-09) (35 per hour = $6,630 per inspection inspection
airplanes). inspection cycle. cycle. cycle.
Inspection (new proposed Up to 257 work-hours x $0.................. Up to $21,845 Up to $2,162,655
action) (99 airplanes). $85 per hour = per inspection per inspection
$21,845 per cycle. cycle.
inspection cycle.
Modification (new proposed Up to 136 work-hours x Up to $1,070........ Up to $12,630... Up to
action) (Up to 99 airplanes). $85 per hour = $1,250,370.
$11,560.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
actions that would be required based on the results of the proposed
inspection. We have no way of determining the number of aircraft that
might need these actions:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
---------------------------------------------------------------------------------------------------------------
Oversize, installation, and Up to 105 work-hours Up to $21,560............ Up to $30,485............
inspection. x $85 per hour =
$8,925.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs specified in this proposed
AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
[[Page 8204]]
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 removing Airworthiness Directive (AD)
2016-12-09, Amendment 39-18558 (81 FR 38573, June 14, 2016), and adding
the following new AD:
Airbus: Docket No. FAA-2018-0113; Product Identifier 2017-NM-060-AD.
(a) Comments Due Date
We must receive comments by April 12, 2018.
(b) Affected ADs
This AD replaces AD 2016-12-09, Amendment 39-18558 (81 FR 38573,
June 14, 2016) (``AD 2016-12-09'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(5) of this AD, certificated in any category, all
manufacturer serial numbers, except those on which Airbus Repair
Instructions R57115092 have been embodied in service on both right-
hand (RH) and left-hand (LH) sides.
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
(4) Model A340-211, -212, and -213 airplanes.
(5) Model A340-311, -312, and -313 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports that cracks were found on an
adjacent hole of certain frames of the center wing box (CWB). We are
issuing this AD to detect and correct cracking of certain holes of
certain frames of the CWB, which could affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Service Information
(1) For the actions required by paragraphs (h), (i), and (j) of
this AD, use the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(vi) of this AD.
(i) Airbus Service Bulletin A330-57-3114, Revision 01, dated
January 13, 2017 (CWB inspection area: Below) (for Model A330-300
series airplanes in pre-modification 44360 configuration).
(ii) Airbus Service Bulletin A330-57-3115, Revision 01,
including Appendices 01 and 02, dated November 23, 2016 (CWB
inspection area: Above) (for Model A330-200 and -300 series
airplanes in pre-modification 55306 and pre-modification 55792
configuration).
(iii) Airbus Service Bulletin A330-57-3116, Revision 01,
including Appendices 01 and 02, dated November 23, 2016 (CWB
inspection area: Below) (for Model A330-200 and -300 series
airplanes in post-modification 44360 configuration).
(iv) Airbus Service Bulletin A340-57-4123, Revision 01, dated
January 13, 2017 (CWB inspection area: Below) (for Model A340-200
and -300 series airplanes in pre-modification 44360 configuration).
(v) Airbus Service Bulletin A340-57-4124, Revision 02, including
Appendices 01 and 02, dated November 23, 2016 (CWB inspection area:
Above) (for Model A340-200 and -300 series airplanes in pre-
modification 55306 and pre-modification 55792 configuration).
(vi) Airbus Service Bulletin A340-57-4125, Revision 01,
including Appendices 01 and 02, dated November 23, 2016 (CWB
inspection area: Below) (for Model A340-200 and -300 series
airplanes in post-modification 44360 configuration).
(2) For the modification required by paragraph (o)(1) of this
AD, use the applicable service information specified in paragraphs
(g)(2)(i) through (g)(2)(vi) of this AD.
(i) Airbus Service Bulletin A330-57-3130, dated November 23,
2016 (for Model A330-200 and -300 series airplanes in post-
modification 44360, post-Airbus Service Bulletin A330-57-3131, and
pre-modification 49202 configuration).
(ii) Airbus Service Bulletin A330-57-3131, dated November 23,
2016 (for Model A330-200 and -300 series airplanes in post-
modification 44360 and pre-modification 55306 configuration).
(iii) Airbus Service Bulletin A330-57-3132, including Appendices
01 and 02, dated November 23, 2016 (for Model A330-200 and -300
series airplanes in post-modification 44360 configuration).
(iv) Airbus Service Bulletin A340-57-4137, dated November 23,
2016 (for Model A340-200 and -300 series airplanes in post-
modification 44360, post-Airbus Service Bulletin A340-57-4138, and
pre-modification 49202 configuration).
(v) Airbus Service Bulletin A340-57-4138, dated November 23,
2016 (for Model A340-200 and -300 series airplanes in post-
modification 44360 and pre-modification 55306 configuration).
(vi) Airbus Service Bulletin A340-57-4139, including Appendices
01 and 02, dated November 23, 2016 (for Model A340-200 and -300
series airplanes in post-modification 44360 configuration).
(h) Repetitive Inspections and Certain Repairs
Except as specified in paragraphs (l)(2), (l)(3), (p) of this
AD: Before exceeding the applicable threshold specified in paragraph
1.E., ``Compliance'' of the applicable service information specified
in paragraph (g)(1) of this AD, or within the compliance time
specified in table 1 to paragraph (h) of this AD, whichever occurs
later; remove the fasteners and accomplish a special detailed
inspection (SDI) of the fastener holes at frame (FR) 40 vertical
web, on both LH and RH sides, of the affected CWB lower panel area,
and, as applicable, check for the existence of a repair done as
specified by a repair design approval sheet (RDAS), in accordance
with the Accomplishment Instructions of the
[[Page 8205]]
applicable service information specified in paragraph (g)(1) of this
AD, and if any RDAS repair is found 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. Repeat the SDI thereafter at the applicable intervals
specified in paragraph 1.E., ``Compliance,'' of the applicable
service information identified in paragraph (g)(1) of this AD.
[GRAPHIC] [TIFF OMITTED] TP26FE18.000
(i) Follow-On Actions: No Cracking
If no crack is found during any inspection required by paragraph
(h) of this AD: Before further flight, install new fasteners in the
transition fit, in accordance with the Accomplishment Instructions
of the applicable service information specified in paragraph (g)(1)
of this AD.
(j) Follow-On Actions: Cracking
If any crack is found during any inspection required by
paragraph (h) of this AD: Before further flight, oversize the holes
to the first oversize in comparison with the current hole diameter,
and do an SDI for cracks, in accordance with the Accomplishment
Instructions of the applicable service information identified in
paragraph (g)(1) of this AD.
(1) If no cracking is found during the SDI required by the
introductory text of paragraph (j) of this AD: Before further
flight, install new fasteners in the transition fit, in accordance
with the Accomplishment Instructions of the applicable service
information identified in paragraph (g)(1) of this AD.
(2) If any cracking is found during the SDI required by the
introductory text of paragraph (j) of this AD: Before further
flight, repair 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.
(k) No Reporting Required
Although the applicable service information specified in
paragraph (g)(1) of this AD specifies to submit certain information
to the manufacturer, and specifies that action as ``RC'' (Required
for Compliance), this AD does not include that requirement.
(l) Exceptions to Service Information
(1) Where the applicable service information identified in
paragraphs (g) and (m) of this AD specifies contacting Airbus for
appropriate action: Before further flight, repair 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.
(2) Where paragraph 1.E., ``Compliance,'' of the applicable
service information specified in paragraph (g)(1) of this AD
specifies a compliance time in terms of a ``Threshold'' and ``Grace
Period,'' this AD requires compliance at the later of the applicable
threshold and grace period.
(3) When it is determined that no RDAS is found to exist for the
FR40 area it is acceptable to accomplish the first SDI before
exceeding the applicable threshold, instead of ``before next
flight'', as specified in the applicable service information
specified in paragraph (g)(1)(ii), (g)(1)(iii), (g)(1)(v) and
(g)(1)(vi) of this AD.
(m) Modification for Airplanes in Post-Modification 55306 and Pre-
Modification 205225 Configuration
For airplanes in post-modification 55306 and pre-modification
205225 configuration: Before exceeding the applicable compliance
time specified in table 2 to paragraph (m) of this AD, as
applicable, or within 18 months after the effective date of this AD,
whichever occurs later; modify the inside CWB (above bottom skin),
including doing a rotating probe inspection for cracking and all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-57-3129, dated October 5, 2016; or Airbus Service
Bulletin A340-57-4136, dated October 5, 2016; as applicable; except
as required by paragraph (l)(1) of this AD. Do all applicable
related investigative and corrective actions before further flight.
[[Page 8206]]
[GRAPHIC] [TIFF OMITTED] TP26FE18.001
(n) Terminating Action for Certain Airworthiness Limitation Item (ALI)
Tasks
(1) Accomplishment on an airplane of the initial and repetitive
inspections required by paragraph (h) of this AD terminates the
requirements of ALI task 57-11-02 and task 57-11-04 of the
applicable Airbus Airworthiness Limitation Section (ALS) Part 2,
Damage Tolerant (DT) ALI, for that airplane.
(2) Modification of an airplane as required by paragraph (m) of
this AD terminates the requirements of ALI task 57-11-02 of the
applicable Airbus ALS Part 2, DT ALI, for that airplane.
(o) Terminating Action for Repetitive SDI Inspections
(1) Modification of a post-modification 44360 airplane by
multiple cold working, including doing a rotating probe inspection
for cracking and all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of the
applicable Airbus service information specified in paragraph (g)(2)
of this AD, except as required by paragraph (l)(1) of this AD,
constitutes terminating action for the repetitive SDI required by
paragraph (h) of this AD for that airplane, provided the
modification is accomplished within the applicable compliance times
specified in the applicable Airbus service information specified in
paragraph (g)(1) of this AD.
(2) If, during any inspection of a post-modification 44360
airplane, as required by paragraph (h) of this AD, a crack
previously repaired by an Airbus RDAS is detected only on the LH or
RH side, it is permitted to do the modification specified in
paragraph (o)(1) of this AD on the non-repaired side. Doing the
modification constitutes terminating action for the repetitive SDI
required by paragraph (h) of this AD on the modified side only.
(p) Extension to Compliance Time for Certain Airplanes
For post-modification 44360 airplanes and pre-modification 55306
airplanes that have been inspected before the effective date of this
AD as required by AD 2016-12-09: It is permitted to defer the next
due inspection to 18 months after the effective date of this AD,
provided the previous inspection interval, as applicable, depending
on airplane configuration and utilization, as specified in the
service information used in the previous inspection is not exceeded.
(q) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (h) through (j) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service information specified in paragraphs (q)(1)(i) through
(q)(1)(vi) of this AD. This service information was incorporated by
reference in AD 2016-09-11, Amendment 39-18509 (81 FR 27986, May 9,
2016).
(i) Airbus Service Bulletin A330-57-3114, dated March 12, 2013.
(ii) Airbus Service Bulletin A330-57-3115, April 4, 2013.
(iii) Airbus Service Bulletin A330-57-3116, dated March 12,
2013.
(iv) Airbus Service Bulletin A340-57-4123, dated March 12, 2013.
(v) Airbus Service Bulletin A340-57-4124, Revision 01, dated
August 22, 2013.
(vi) Airbus Service Bulletin A340-57-4125, dated March 12, 2013.
(2) This paragraph provides credit for the actions required by
paragraphs (h) through (j) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A340-57-4124, dated April 4, 2013. This service information
is not incorporated by reference in this AD.
(3) This paragraph provides credit for the actions required by
paragraphs (h) through (j) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service information specified in paragraphs (q)(3)(i) through
(q)(3)(viii) of this AD. This service information is not
incorporated by reference in this AD.
(i) Airbus Technical Disposition LR57D11023270, Issue B, dated
July 12, 2011.
(ii) Airbus Technical Disposition LR57D11029170, Issue C, dated
September 6, 2011.
(iii) Airbus Technical Disposition LR57D11029171, Issue B, dated
September 6, 2011.
(iv) Airbus Technical Disposition LR57D11029172, Issue B, dated
September 6, 2011.
(v) Airbus Technical Disposition LR57D11029173, Issue B, dated
September 6, 2011.
(vi) Airbus Technical Disposition LR57D11023714, Issue B, dated
July 12, 2011.
(vii) Airbus Technical Disposition LR57D11030740, Issue C, dated
September 22, 2011.
(viii) Airbus Technical Disposition LR57D11030741, Issue B,
dated September 22, 2011.
(r) 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 manager of the International Section, send it to the
attention of the person identified in paragraph (s)(2) of this AD.
Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate
[[Page 8207]]
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 EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (k) and (l)(1) 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.
(s) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0069, dated April 25, 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-2018-0113.
(2) For more information about this AD, 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.
(3) For service information identified in this AD, 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: [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 Renton, Washington, on February 14, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-03599 Filed 2-23-18; 8:45 am]
BILLING CODE 4910-13-P
