Airworthiness Directives; Airbus Airplanes, 7117-7120 [2018-03212]
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7117
Proposed Rules
Federal Register
Vol. 83, No. 34
Tuesday, February 20, 2018
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0111; Product
Identifier 2017–NM–059–AD]
Examining the AD Docket
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) 2017–07–
07, for certain Airbus Model A330–200,
A330–300, A340–200, and A340–300
series airplanes. AD 2017–07–07
requires repetitive inspections of certain
fastener holes, and related investigative
and corrective actions if necessary.
Since we issued AD 2017–07–07, we
have determined that certain other
airplanes could also be affected by the
unsafe condition specified in AD 2017–
07–07. This proposed AD would retain
the requirements of AD 2017–07–07 and
expand the applicability. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by April 6, 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.
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SUMMARY:
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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, 1601 Lind Avenue
SW, Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0111; 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, 1601 Lind
Avenue SW, Renton, WA 98057–3356;
telephone: 425–227–1138; fax: 425–
227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0111; Product Identifier 2017–
NM–059–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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substantive verbal contact we receive
about this proposed AD.
Discussion
We issued AD 2017–07–07,
Amendment 39–18845 (82 FR 18547,
April 20, 2017) (‘‘AD 2017–07–07’’), for
certain Airbus Model A330–200, A330–
300, A340–200, and A340–300 series
airplanes with manufacturer serial
numbers (MSN) 0176 through 0915
inclusive. These airplanes have Airbus
modification 44360 embodied in
production. AD 2017–07–07 was
prompted by a report of cracking at
fastener holes located at frame (FR) 40
on the lower shell panel junction. AD
2017–07–07 requires repetitive
inspections of certain fastener holes,
and related investigative and corrective
actions if necessary. Airbus then
introduced the modification 55792 to
reinforce the fuselage at FR40. We
issued AD 2017–07–07 to detect and
correct cracking at FR40 on the lower
shell panel junction; such cracking
could lead to reduced structural
integrity of the fuselage.
Since we issued AD 2017–07–07, we
have determined that airplanes in the
post-modification 55792 configuration
could be also affected by crack initiation
and propagation at fastener holes
located at FR40 on the lower shell panel
junction.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0063,
dated April 12, 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,
A330–300, and A340–200 series
airplanes, and Model A340–312 and
–313 airplanes. The MCAI states:
During full scale fatigue test of the Frame
(FR) 40 to fuselage skin panel junction,
fatigue damage was found. Corrective actions
consisted of in-service installation of an
internal reinforcing strap on the related
junction, as currently required by DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France AD 1999–448–126(B), which refers to
Airbus Service Bulletin (SB) A340–53–4104
Revision 02, and [DGAC] AD 2001–070(B),
which refers to Airbus SB A330–53–3093
Revision 04; retrofit improvement of internal
reinforcing strap fatigue life through
recommended Airbus SB A330–53–3145; and
introducing a design improvement in
production through Airbus mod 44360.
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Federal Register / Vol. 83, No. 34 / Tuesday, February 20, 2018 / Proposed Rules
After those actions were implemented,
cracks were found on both left-hand (LH) and
right-hand (RH) sides on internal strap, butt
strap, keel beam fitting, or forward fitting
FR40 flange. These findings were made
during embodiment of a FR40 web repair on
an A330 aeroplane, and during keel beam
replacement on an A340 aeroplane, where
the internal strap was removed and a special
detailed inspection (SDI) was performed on
several holes.
This condition, if not detected and
corrected, could affect the structural integrity
of the centre fuselage of the aeroplane.
Prompted by these findings, Airbus issued
SB A330–53–3215 and SB A340–53–4215,
providing inspection instructions.
Consequently, EASA issued AD 2014–0136
[which corresponds to FAA AD 2017–07–07]
to require repetitive SDI (rototest) of 10
fastener holes located at the FR40 lower shell
panel junction on both LH and RH sides and,
depending on findings, accomplishment of
applicable corrective action(s).
Since that [EASA] AD was issued,
prompted by the results of complementary
fatigue analyses, it was determined that postmod 55792 aeroplanes could be also affected
by crack initiation and propagation at this
area of the fuselage. These analyses
demonstrated that post-mod 55792
aeroplanes must follow the same
maintenance program as aeroplanes in postmod 55306 and pre-mod 55792
configuration. Consequently, Airbus
published SB A330–53–3215 Revision 02 and
SB A340–53–4215 Revision 02 to expand the
Effectivity accordingly.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0136, which is superseded, which
now also apply to aeroplanes in post-mod
55792 configuration [the applicability
identifies airplanes in post-mod 44360
configuration].
AD 2017–07–07 includes Model
A340–311 airplanes in its applicability.
Airbus Model A340–311 airplanes are
not identified in the applicability of this
proposed AD because those airplanes
are not affected by the identified unsafe
condition. All of those airplanes are in
the pre-Airbus modification 44360
configuration. The MCAI does not
include Model A340–311 airplanes in
its applicability.
The compliance time ranges between
20,000 flight cycles or 65,400 flight
hours and 20,800 flight cycles or 68,300
flight hours, depending on airplane
utilization and configuration. The
repetitive inspection interval ranges
between 14,000 flight cycles or 95,200
flight hours and 24,600 flight cycles or
98,700 flight hours, depending on
airplane utilization and configuration.
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–
0111.
Related Service Information Under 1
CFR Part 51
Airbus has issued Airbus Service
Bulletin A330–53–3215, Revision 02,
dated November 23, 2016 (‘‘A330–53–
3215, R2’’); and Airbus Service Bulletin
A340–53–4215, Revision 02, dated
November 23, 2016. This service
information describes procedures for
repetitive rototest inspections of certain
fastener holes, and related investigative
and corrective actions if necessary.
These documents are distinct since they
apply to different airplane models. This
service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
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.
Differences Between This Proposed AD
and the MCAI or Service Information
The MCAI includes Model A340–211
airplanes in its applicability. Airbus
Model A340–211 airplanes are not
identified in the applicability of this
proposed AD because those airplanes
are not affected by the identified unsafe
condition. All of those airplanes are in
the pre-Airbus modification 44360
configuration. We have coordinated this
difference with EASA.
Paragraph 1.E. ‘‘Compliance,’’ of
A330–53–3215, R2, specifies weight
variant (WV) 050 in the condition
column of table 1, configuration 003.
We have determined that for the
purposes of this AD, WV060 and
WV080 are also affected.
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
Inspection ..........
42 work-hours × $85 per hour = $3,570
per inspection cycle.
We estimate the following costs to do
any necessary repairs that are required
Parts cost
Cost per product
$0
Cost on U.S. operators
$3,570 per inspection cycle ......
based on the results of the required
inspection. We have no way of
$353,430 per inspection cycle.
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
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Action
Labor cost
Repair ...........................................................................
46 work-hours × $85 per hour = $3,910 ......................
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
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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,
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Parts cost
$2,358
Cost per
product
$6,268
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
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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
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under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2017–07–07, Amendment 39–18845 (82
FR 18547, April 20, 2017), and adding
the following new AD:
■
Airbus: Docket No. FAA–2018–0111; Product
Identifier 2017–NM–059–AD.
(a) Comments Due Date
We must receive comments by April 6,
2018.
(b) Affected ADs
This AD replaces AD 2017–07–07,
Amendment 39–18845 (82 FR 18547, April
20, 2017) (‘‘AD 2017–07–07’’).
(c) Applicability
This AD applies to the airplanes,
certificated in any category, identified in
paragraphs (c)(1) and (c)(2) of this AD, all
manufacturer serial numbers on which
Airbus Modification 44360 has been
embodied in production.
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(1) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes.
(2) Airbus Model A340–212, –213, –312,
and –313 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of
cracking at fastener holes located at frame
(FR) 40 on the lower shell panel junction. We
are issuing this AD to detect and correct
cracking at FR40 on the lower shell panel
junction; such cracking could lead to reduced
structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Compliance Times for the Actions
Required by Paragraph (h) of This AD
Accomplish the actions required by
paragraph (h) of this AD at the times
specified in paragraphs (g)(1) and (g)(2) of
this AD, as applicable.
(1) For airplanes having serial numbers
0176 through 0915 inclusive: Within the
compliance times defined in table 1 to
paragraph (g)(1) of this AD, and, thereafter,
at intervals not to exceed the compliance
times defined in Airbus Service Bulletin
A330–53–3215, Revision 02, dated November
23, 2016 (‘‘A330–53–3215, R2’’); or Airbus
Service Bulletin A340–53–4215, Revision 02,
dated November 23, 2016 (‘‘A340–53–4215,
R2’’); as applicable, depending on airplane
utilization and configuration. As of the
effective date of this AD, where paragraph
1.E. ‘‘Compliance,’’ of A330–53–3215, R2
specifies weight variant (WV) 050 in the
condition column of table 1, configuration
003, for the purposes of this AD, WV060 and
WV080 are also included.
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the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
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(2) For all airplanes except those identified
in paragraph (g)(1) of this AD: Before
exceeding the applicable compliance time
‘‘threshold’’ defined in paragraph 1.E.,
‘‘Compliance,’’ of A330–53–3215, R2; or
A340–53–4215, R2; as applicable, depending
on airplane utilization and configuration and
to be counted from airplane first flight, and,
thereafter, at intervals not to exceed the
compliance times specified in paragraph 1.E.,
‘‘Compliance’’ of A330–53–3215, R2; or
A340–53–4215, R2; as applicable, depending
on airplane utilization and configuration.
Where paragraph 1.E. ‘‘Compliance,’’ of
A330–53–3215, R2 specifies weight variant
WV050 in the condition column of table 1,
configuration 003, for the purposes of this
AD, WV060 and WV080 are also included.
(h) Repetitive Inspections and Related
Investigative and Corrective Actions
At the applicable compliance times
specified in paragraph (g) of this AD:
Accomplish a special detailed inspection of
the 10 fastener holes located at FR40 lower
shell panel junction on both left-hand and
right-hand sides, in accordance with the
Accomplishment Instructions of A330–53–
3215, R2; or A340–53–4215, R2; as
applicable.
(1) If, during any inspection required by
the introductory text of paragraph (h) of this
AD, any crack is detected, before further
flight, accomplish all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of A330–53–3215, R2; or A340–
53–4215, R2; as applicable, except where
A330–53–3215, R2; or A340–53–4215, R2;
specifies to contact Airbus for repair
instructions, and specifies that action as
‘‘RC,’’ this AD requires repair before further
flight using a method approved by the
Manager, International Section, Transport
Standards Branch, FAA; or 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.
(2) If, during any inspection required by
the introductory text of paragraph (h) of this
AD, the diameter of a fastener hole is found
to be outside the tolerances of the transition
fit as specified in A330–53–3215, R2; or
A340–53–4215, R2; as applicable; and A330–
53–3215, R2; or A340–53–4215, R2; specifies
to contact Airbus for repair instructions, and
specifies that action as ‘‘RC,’’ 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.
(3) Accomplishment of corrective actions,
as required by paragraph (h)(1) of this AD,
does not constitute terminating action for the
repetitive inspections required by the
introductory text of paragraph (h) of this AD.
(4) Accomplishment of a repair on an
airplane, as required by paragraph (h)(2) of
this AD, does not constitute terminating
action for the repetitive inspections required
by the introductory text of paragraph (h) of
this AD for that airplane, unless the method
approved by the Manager, International
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Section, Transport Standards Branch, FAA;
or EASA; or Airbus’s EASA DOA indicates
otherwise.
(i) No Reporting Requirement
Although A330–53–3215, R2 and A340–
53–4215, R2, specify to submit certain
information to the manufacturer, and specify
that action as ‘‘RC,’’ this AD does not include
that requirement.
(j) Credit for Previous Actions
This paragraph provides credit for the
inspections required by the introductory text
of (h) of this AD and the related investigative
and corrective actions required by paragraph
(h)(1) of this AD, if those actions were
performed before May 25, 2017 (the effective
date of AD 2017–07–07), using Airbus
Service Bulletin A330–53–3215, dated June
21, 2013; or Revision 01, dated April 17,
2014; or Airbus Service Bulletin A340–53–
4215, dated June 21, 2013; or Revision 01,
dated April 17, 2014; as applicable.
(k) 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 (l)(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: 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 (g)(1), (g)(2), (h)(1),
(h)(2), and (i) 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.
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(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0063, dated April 12, 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–2018–0111.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 1601 Lind Avenue
SW, Renton, WA 98057–3356; telephone:
425–227–1138; fax: 425–227–1149.
(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, 1601 Lind
Avenue SW, Renton, WA. For information on
the availability of this material at the FAA,
call 425–227–1221.
Issued in Renton, Washington, on February
9, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–03212 Filed 2–16–18; 8:45 am]
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FEDERAL TRADE COMMISSION
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Regulatory Review Schedule
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Intent to request public
comments.
AGENCY:
ACTION:
As part of its ongoing,
systematic review of all Federal Trade
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Commission announces a modified tenyear regulatory review schedule. No
Commission determination on the need
for, or the substance of, the rules and
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from this notice.
DATES: February 20, 2018.
FOR FURTHER INFORMATION CONTACT:
Further details about particular rules or
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Agencies
[Federal Register Volume 83, Number 34 (Tuesday, February 20, 2018)]
[Proposed Rules]
[Pages 7117-7120]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-03212]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 83, No. 34 / Tuesday, February 20, 2018 /
Proposed Rules
[[Page 7117]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0111; Product Identifier 2017-NM-059-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) 2017-07-
07, for certain Airbus Model A330-200, A330-300, A340-200, and A340-300
series airplanes. AD 2017-07-07 requires repetitive inspections of
certain fastener holes, and related investigative and corrective
actions if necessary. Since we issued AD 2017-07-07, we have determined
that certain other airplanes could also be affected by the unsafe
condition specified in AD 2017-07-07. This proposed AD would retain the
requirements of AD 2017-07-07 and expand the applicability. We are
proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 6, 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, 1601 Lind Avenue SW, Renton, WA. For
information on the availability of this material at the FAA, call 425-
227-1221.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0111; 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, 1601 Lind
Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-
227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0111;
Product Identifier 2017-NM-059-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We issued AD 2017-07-07, Amendment 39-18845 (82 FR 18547, April 20,
2017) (``AD 2017-07-07''), for certain Airbus Model A330-200, A330-300,
A340-200, and A340-300 series airplanes with manufacturer serial
numbers (MSN) 0176 through 0915 inclusive. These airplanes have Airbus
modification 44360 embodied in production. AD 2017-07-07 was prompted
by a report of cracking at fastener holes located at frame (FR) 40 on
the lower shell panel junction. AD 2017-07-07 requires repetitive
inspections of certain fastener holes, and related investigative and
corrective actions if necessary. Airbus then introduced the
modification 55792 to reinforce the fuselage at FR40. We issued AD
2017-07-07 to detect and correct cracking at FR40 on the lower shell
panel junction; such cracking could lead to reduced structural
integrity of the fuselage.
Since we issued AD 2017-07-07, we have determined that airplanes in
the post-modification 55792 configuration could be also affected by
crack initiation and propagation at fastener holes located at FR40 on
the lower shell panel junction.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0063, dated April 12, 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, A330-
300, and A340-200 series airplanes, and Model A340-312 and -313
airplanes. The MCAI states:
During full scale fatigue test of the Frame (FR) 40 to fuselage
skin panel junction, fatigue damage was found. Corrective actions
consisted of in-service installation of an internal reinforcing
strap on the related junction, as currently required by DGAC
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France AD
1999-448-126(B), which refers to Airbus Service Bulletin (SB) A340-
53-4104 Revision 02, and [DGAC] AD 2001-070(B), which refers to
Airbus SB A330-53-3093 Revision 04; retrofit improvement of internal
reinforcing strap fatigue life through recommended Airbus SB A330-
53-3145; and introducing a design improvement in production through
Airbus mod 44360.
[[Page 7118]]
After those actions were implemented, cracks were found on both
left-hand (LH) and right-hand (RH) sides on internal strap, butt
strap, keel beam fitting, or forward fitting FR40 flange. These
findings were made during embodiment of a FR40 web repair on an A330
aeroplane, and during keel beam replacement on an A340 aeroplane,
where the internal strap was removed and a special detailed
inspection (SDI) was performed on several holes.
This condition, if not detected and corrected, could affect the
structural integrity of the centre fuselage of the aeroplane.
Prompted by these findings, Airbus issued SB A330-53-3215 and SB
A340-53-4215, providing inspection instructions. Consequently, EASA
issued AD 2014-0136 [which corresponds to FAA AD 2017-07-07] to
require repetitive SDI (rototest) of 10 fastener holes located at
the FR40 lower shell panel junction on both LH and RH sides and,
depending on findings, accomplishment of applicable corrective
action(s).
Since that [EASA] AD was issued, prompted by the results of
complementary fatigue analyses, it was determined that post-mod
55792 aeroplanes could be also affected by crack initiation and
propagation at this area of the fuselage. These analyses
demonstrated that post-mod 55792 aeroplanes must follow the same
maintenance program as aeroplanes in post-mod 55306 and pre-mod
55792 configuration. Consequently, Airbus published SB A330-53-3215
Revision 02 and SB A340-53-4215 Revision 02 to expand the
Effectivity accordingly.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0136, which is superseded, which now
also apply to aeroplanes in post-mod 55792 configuration [the
applicability identifies airplanes in post-mod 44360 configuration].
AD 2017-07-07 includes Model A340-311 airplanes in its
applicability. Airbus Model A340-311 airplanes are not identified in
the applicability of this proposed AD because those airplanes are not
affected by the identified unsafe condition. All of those airplanes are
in the pre-Airbus modification 44360 configuration. The MCAI does not
include Model A340-311 airplanes in its applicability.
The compliance time ranges between 20,000 flight cycles or 65,400
flight hours and 20,800 flight cycles or 68,300 flight hours, depending
on airplane utilization and configuration. The repetitive inspection
interval ranges between 14,000 flight cycles or 95,200 flight hours and
24,600 flight cycles or 98,700 flight hours, depending on airplane
utilization and configuration. 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-2018-0111.
Related Service Information Under 1 CFR Part 51
Airbus has issued Airbus Service Bulletin A330-53-3215, Revision
02, dated November 23, 2016 (``A330-53-3215, R2''); and Airbus Service
Bulletin A340-53-4215, Revision 02, dated November 23, 2016. This
service information describes procedures for repetitive rototest
inspections of certain fastener holes, and related investigative and
corrective actions if necessary. These documents are distinct since
they apply to different airplane models. This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section.
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.
Differences Between This Proposed AD and the MCAI or Service
Information
The MCAI includes Model A340-211 airplanes in its applicability.
Airbus Model A340-211 airplanes are not identified in the applicability
of this proposed AD because those airplanes are not affected by the
identified unsafe condition. All of those airplanes are in the pre-
Airbus modification 44360 configuration. We have coordinated this
difference with EASA.
Paragraph 1.E. ``Compliance,'' of A330-53-3215, R2, specifies
weight variant (WV) 050 in the condition column of table 1,
configuration 003. We have determined that for the purposes of this AD,
WV060 and WV080 are also affected.
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................. 42 work-hours x $85 $0 $3,570 per inspection $353,430 per
per hour = $3,570 cycle. inspection cycle.
per inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
are required based on the results of the required inspection. We have
no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair........................................ 46 work-hours x $85 per hour = $2,358 $6,268
$3,910.
----------------------------------------------------------------------------------------------------------------
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
[[Page 7119]]
the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses
an unsafe condition that is likely to exist or develop on products
identified in this rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2017-07-07, Amendment 39-18845 (82 FR 18547, April 20, 2017), and
adding the following new AD:
Airbus: Docket No. FAA-2018-0111; Product Identifier 2017-NM-059-AD.
(a) Comments Due Date
We must receive comments by April 6, 2018.
(b) Affected ADs
This AD replaces AD 2017-07-07, Amendment 39-18845 (82 FR 18547,
April 20, 2017) (``AD 2017-07-07'').
(c) Applicability
This AD applies to the airplanes, certificated in any category,
identified in paragraphs (c)(1) and (c)(2) of this AD, all
manufacturer serial numbers on which Airbus Modification 44360 has
been embodied in production.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-212, -213, -312, and -313 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report of cracking at fastener holes
located at frame (FR) 40 on the lower shell panel junction. We are
issuing this AD to detect and correct cracking at FR40 on the lower
shell panel junction; such cracking could lead to reduced structural
integrity of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Compliance Times for the Actions Required by Paragraph (h) of This
AD
Accomplish the actions required by paragraph (h) of this AD at
the times specified in paragraphs (g)(1) and (g)(2) of this AD, as
applicable.
(1) For airplanes having serial numbers 0176 through 0915
inclusive: Within the compliance times defined in table 1 to
paragraph (g)(1) of this AD, and, thereafter, at intervals not to
exceed the compliance times defined in Airbus Service Bulletin A330-
53-3215, Revision 02, dated November 23, 2016 (``A330-53-3215,
R2''); or Airbus Service Bulletin A340-53-4215, Revision 02, dated
November 23, 2016 (``A340-53-4215, R2''); as applicable, depending
on airplane utilization and configuration. As of the effective date
of this AD, where paragraph 1.E. ``Compliance,'' of A330-53-3215, R2
specifies weight variant (WV) 050 in the condition column of table
1, configuration 003, for the purposes of this AD, WV060 and WV080
are also included.
[GRAPHIC] [TIFF OMITTED] TP20FE18.000
[[Page 7120]]
(2) For all airplanes except those identified in paragraph
(g)(1) of this AD: Before exceeding the applicable compliance time
``threshold'' defined in paragraph 1.E., ``Compliance,'' of A330-53-
3215, R2; or A340-53-4215, R2; as applicable, depending on airplane
utilization and configuration and to be counted from airplane first
flight, and, thereafter, at intervals not to exceed the compliance
times specified in paragraph 1.E., ``Compliance'' of A330-53-3215,
R2; or A340-53-4215, R2; as applicable, depending on airplane
utilization and configuration. Where paragraph 1.E. ``Compliance,''
of A330-53-3215, R2 specifies weight variant WV050 in the condition
column of table 1, configuration 003, for the purposes of this AD,
WV060 and WV080 are also included.
(h) Repetitive Inspections and Related Investigative and Corrective
Actions
At the applicable compliance times specified in paragraph (g) of
this AD: Accomplish a special detailed inspection of the 10 fastener
holes located at FR40 lower shell panel junction on both left-hand
and right-hand sides, in accordance with the Accomplishment
Instructions of A330-53-3215, R2; or A340-53-4215, R2; as
applicable.
(1) If, during any inspection required by the introductory text
of paragraph (h) of this AD, any crack is detected, before further
flight, accomplish all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of A330-53-3215, R2; or A340-53-4215, R2; as
applicable, except where A330-53-3215, R2; or A340-53-4215, R2;
specifies to contact Airbus for repair instructions, and specifies
that action as ``RC,'' this AD requires repair before further flight
using a method approved by the Manager, International Section,
Transport Standards Branch, FAA; or 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.
(2) If, during any inspection required by the introductory text
of paragraph (h) of this AD, the diameter of a fastener hole is
found to be outside the tolerances of the transition fit as
specified in A330-53-3215, R2; or A340-53-4215, R2; as applicable;
and A330-53-3215, R2; or A340-53-4215, R2; specifies to contact
Airbus for repair instructions, and specifies that action as ``RC,''
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.
(3) Accomplishment of corrective actions, as required by
paragraph (h)(1) of this AD, does not constitute terminating action
for the repetitive inspections required by the introductory text of
paragraph (h) of this AD.
(4) Accomplishment of a repair on an airplane, as required by
paragraph (h)(2) of this AD, does not constitute terminating action
for the repetitive inspections required by the introductory text of
paragraph (h) of this AD for that airplane, unless the method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA indicates otherwise.
(i) No Reporting Requirement
Although A330-53-3215, R2 and A340-53-4215, R2, specify to
submit certain information to the manufacturer, and specify that
action as ``RC,'' this AD does not include that requirement.
(j) Credit for Previous Actions
This paragraph provides credit for the inspections required by
the introductory text of (h) of this AD and the related
investigative and corrective actions required by paragraph (h)(1) of
this AD, if those actions were performed before May 25, 2017 (the
effective date of AD 2017-07-07), using Airbus Service Bulletin
A330-53-3215, dated June 21, 2013; or Revision 01, dated April 17,
2014; or Airbus Service Bulletin A340-53-4215, dated June 21, 2013;
or Revision 01, dated April 17, 2014; as applicable.
(k) 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 (l)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (i) 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.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0063, dated April 12, 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-2018-0111.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356;
telephone: 425-227-1138; fax: 425-227-1149.
(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, 1601 Lind Avenue
SW, Renton, WA. For information on the availability of this material
at the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 9, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-03212 Filed 2-16-18; 8:45 am]
BILLING CODE 4910-13-P