Airworthiness Directives; Airbus SAS Airplanes, 39377-39380 [2018-16733]
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Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0705; Product
Identifier 2018–NM–077–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus SAS Model A321–111, –112,
–131, –211, –212, –213, –231, and –232
airplanes. This proposed AD was
prompted by a report that during
removal of left-hand (LH) gear rib 5, four
failed fasteners were discovered. This
proposed AD would require a one-time
ultrasonic inspection of the LH and
right-hand (RH) wing rib 5-to-rear spar
attachments for cracked or failed
fasteners, and if necessary, a detailed
inspection of the gear rib 5 and spar web
for cracks and damage, a rotating probe
test of the gear rib and spar web bolt
holes for cracks and damage, reaming
the gear rib and the spar web bolt holes,
and replacement of cracked or failed
fasteners. We are proposing this AD to
address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by September 24,
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, Rond-Point
Emile Dewoitine No: 2, 31700 Blagnac
Cedex, France; phone: +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
sradovich on DSK3GMQ082PROD with PROPOSALS
SUMMARY:
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16:04 Aug 08, 2018
Jkt 244001
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–
0705; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
phone and fax: 206–231–3223.
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–
2018–0705; Product Identifier 2018–
NM–077–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
39377
separated from the bolt shanks when the
overcoat sealant was being removed, and the
other two bolt heads broke away during
removal.
This condition, if not detected and
corrected, could reduce the structural
integrity of the wing.
To address this possible unsafe condition,
Airbus issued [Service Bulletin] SB A320–
57–1167 to provide inspection instructions.
After that SB was issued, a potential
manufacturing issue was identified on early
production A321 [airplanes] concerning
reports of fasteners ‘‘jamming’’ during
installation on spar assemblies. A process
change was introduced in production line,
and SB A320–57–1167 was revised, changing
the affected population to include all A321
aeroplanes delivered before the introduction
of that process change.
For the reasons described above, this
[EASA] AD requires a one-time special
detailed [ultrasonic] inspection (SDI) of the
wing rib 5-to-rear spar attachments, both LH
and right hand (RH) wings, [and if necessary,
a detailed inspection of the gear rib 5 and
spar web for cracks and damage (cracks along
the length of the bolt or broken bolt), a
rotating probe test of the gear rib and spar
web bolt holes for cracks and damage (cracks
in the bolt holes), reaming the gear rib and
the spar web bolt holes] and, depending on
findings, accomplishment of a repair
[replacement of cracked or failed (broken)
fasteners (bolts)]. This [EASA] AD also
requires the reporting of findings.
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–
0705.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0102,
dated April 27, 2018 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A321–
111, –112, –131, –211, –212, –213, –231,
and –232 airplanes. The MCAI states:
Related Service Information Under 1
CFR Part 51
Airbus SAS has issued Service
Bulletin A320–57–1167, Revision 01,
dated January 16, 2018. This service
information describes procedures for a
one-time special detailed (ultrasonic)
inspection of the LH and RH wing rib
5-to-rear spar attachments for cracked or
failed (broken) fasteners (bolts), and if
necessary, a detailed inspection of the
gear-rib-5 and spar web for cracks and
damage (cracks along the length of the
bolt or broken bolt), a rotating probe test
of the gear rib and spar web bolt holes
for cracks and damage (cracks in the
bolt holes), reaming the gear rib and the
spar web bolt holes, and replacement of
the cracked or damaged (broken)
fasteners (bolts). 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.
During removal of the left hand (LH) rib 5,
two of the fasteners (bolts) attaching the rib
to the wing inner rear spar were found to
have failed and two more failed during their
removal. Two of the bolts were found
FAA’s Determination
This product has been approved by
the aviation authority of another
country, and is approved for operation
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Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules
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 the
relevant information and determined
the unsafe condition described
previously is likely to exist or develop
on other products of the same type
design.
Proposed Requirements of This NPRM
This proposed AD would require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between this Proposed AD
and the MCAI or Service Information.’’
This proposed AD also would require
sending the inspection results to Airbus
SAS.
Differences Between This Proposed AD
and the MCAI or Service Information
The MCAI specifies credit for actions
accomplished in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1167, dated
August 10, 2011. The MCAI also
discusses a potential manufacturing
issue that was identified on early
production Model A321 airplanes
concerning reports of fasteners
‘‘jamming’’ during installation on spar
assemblies. The corrective action
specified in Airbus Service Bulletin
A320–57–1167, dated August 10, 2011,
includes the same process that
produced ‘‘jamming’’ previously.
Therefore, this proposed AD does not
include credit for actions accomplished
using the Accomplishment Instructions
of Airbus Service Bulletin A320–57–
1167, dated August 10, 2011.
Explanation of Change to Applicability
We have revised the applicability of
this AD to identify model designations
as published in the most recent type
certificate data sheet for the affected
model.
Costs of Compliance
We estimate that this proposed AD
affects 29 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
16 work-hours × $85 per hour = $1,360 .....................................................................................
$0
$1,360
$39,440
We estimate that it would take about
1 work-hour per product to comply with
the proposed reporting requirement in
this proposed AD. The average labor
rate is $85 per hour. Based on these
figures, we estimate the cost of reporting
the inspection results on U.S. operators
to be $2,465, or $85 per product.
We estimate the following costs to do
any necessary on-condition actions that
would be required based on the results
of any required actions. We have no way
of determining the number of aircraft
that might need these on-condition
actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts
cost
Cost per
product
20 work-hours × $85 per hour = $1,700 .................................................................................................................
$0
$1,700
sradovich on DSK3GMQ082PROD with PROPOSALS
Paperwork Reduction Act
Authority for This Rulemaking
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this NPRM is 2120–0056.
The paperwork cost associated with this
NPRM has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this NPRM is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW, Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
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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;
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Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus SAS: Docket No. FAA–2018–0705;
Product Identifier 2018–NM–077–AD.
(a) Comments Due Date
We must receive comments by September
24, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model
A321–111, –112, –131, –211, –212, –213,
–231, and –232 airplanes, certificated in any
category, as identified in Airbus Service
Bulletin A320–57–1167, Revision 01, dated
January 16, 2018.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
sradovich on DSK3GMQ082PROD with PROPOSALS
(e) Reason
This AD was prompted by a report that
during removal of left-hand (LH) gear rib 5,
four failed fasteners (bolts attaching the gear
rib to the wing inner rear spar) were
discovered. We are issuing this AD to detect
and correct cracked or failed (broken)
fasteners (bolts) of the rib 5-to-rear spar
attachment, which could lead to reduced
structural integrity of the wing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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16:04 Aug 08, 2018
Jkt 244001
(g) Inspection of the Rib 5-to-Rear Spar
Attachment Fasteners (Bolts)
Within 30 months after the effective date
of this AD, do a special detailed (ultrasonic)
inspection of the LH and right-hand (RH)
wing rib 5-to-rear spar attachment fasteners
(bolts) for cracked or failed (broken) fasteners
(bolts), in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1167, Revision 01,
dated January 16, 2018.
(h) Replacement of Cracked or Failed
Fasteners (Bolts)
If any cracked or failed (broken) fastener
(bolt) is found during any inspection
required by paragraph (g) of this AD, before
further flight, do the actions specified in
paragraph (h)(1), (h)(2), (h)(3) and (h)(4) of
this AD, as applicable.
(1) Do a detailed inspection of the gear rib
5 and spar web for cracks and damage (cracks
along the length of the bolt or broken bolt),
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
57–1167, Revision 01, dated January 16,
2018. If any crack or damage is found during
any inspection required by this paragraph,
before further flight, obtain corrective actions
approved by the Manager, International
Section, Transport Standards Branch, FAA;
or the European Aviation Safety Agency
(EASA); or Airbus SAS’s EASA Design
Organization Approval (DOA); and
accomplish the corrective actions within the
compliance time specified therein. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(2) If no cracks or damage are found during
any inspection required by paragraph (h)(1)
of this AD: Do a rotating probe test of the gear
rib and spar web bolt holes for cracks and
damage (cracks in the bolt holes), in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
57–1167, Revision 01, dated January 16,
2018. If any crack or damage is found during
any inspection required by this paragraph,
before further flight, obtain corrective actions
approved by the Manager, International
Section, Transport Standards Branch, FAA;
or EASA; or Airbus SAS’s EASA DOA; and
accomplish the corrective actions within the
compliance time specified therein. If
approved by the DOA, the approval must
include the DOA authorized signature.
(3) If no cracks or damage are found during
any inspection required by paragraph (h)(2)
of this AD: Ream the gear rib and the spar
web bolt holes, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1167, Revision 01,
dated January 16, 2018. If an oversize larger
than 0.794 millimeter (0.0313 inch) is
required, before further flight, obtain
corrective actions approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus SAS’s
EASA DOA; and accomplish the corrective
actions within the compliance time specified
therein. If approved by the DOA, the
approval must include the DOA authorized
signature.
(4) Replace any cracked or failed fasteners
(bolts) in accordance with the
Accomplishment Instructions of Airbus
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39379
Service Bulletin A320–57–1167, Revision 01,
dated January 16, 2018.
(i) Reporting
Within 90 days after the special detailed
inspection required by paragraph (g) of this
AD, or within 30 days after the effective date
of this AD, whichever occurs later, report the
inspection results (both positive and
negative) to Airbus SAS in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–57–1167, Revision 01,
dated January 16, 2018. If operators have
reported findings as part of obtaining any
corrective actions approved by the EASA
DOA, operators are not required to report
those findings as specified in this paragraph.
(j) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW, Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(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: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
EASA; or Airbus SAS’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 paragraph (i) of this AD: If any
service information contains procedures or
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Federal Register / Vol. 83, No. 154 / Thursday, August 9, 2018 / Proposed Rules
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
2018–0102, dated April 27, 2018, 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–2018–0705.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3223.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; phone:
+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 Des Moines, Washington, on July
27, 2018.
James Cashdollar,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–16733 Filed 8–8–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0611; Product
Identifier 2018–NE–21–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
sradovich on DSK3GMQ082PROD with PROPOSALS
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Rolls-Royce plc (RR) Trent 1000–A2,
Trent 1000–C2, Trent 1000–D2, Trent
1000–E2, Trent 1000–G2, Trent 1000–
SUMMARY:
VerDate Sep<11>2014
16:04 Aug 08, 2018
Jkt 244001
H2, Trent 1000–J2, Trent 1000–K2, and
Trent 1000–L2 turbofan engine models.
This proposed AD was prompted by
reports of intermediate-pressure
compressor (IPC) rotor seal failures.
This proposed AD would require initial
and repetitive on-wing borescope
inspections (BSI) of affected IPC rotor
seals, and removing any cracked parts
from service. We are proposing this AD
to address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by September 24,
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 Rolls-Royce plc,
Corporate Communications, P.O. Box
31, Derby, England, DE24 8BJ; phone:
011–44–1332–242424; fax: 011–44–
1332–249936; email: corporate.care@
rolls-royce.com; internet: https://
customers.rolls-royce.com/public/
rollsroycecare. You may view this
service information at the FAA, Engine
& Propeller Standards Branch, 1200
District Avenue, Burlington, MA 01803.
For information on the availability of
this material at the FAA, call 781–238–
7759.
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–
0611; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this NPRM, the mandatory
continuing airworthiness information
(MCAI), the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
listed above. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Kevin M. Clark, Aerospace Engineer,
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7088; fax: 781–238–7199;
email: kevin.m.clark@faa.gov.
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–
2018–0611; Product Identifier 2018–
NE–21–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2018–
0095, dated April 24, 2018 (referred to
hereinafter as ‘‘the MCAI’’), to address
the unsafe condition on these products.
The MCAI states:
During an engine shop visit, an affected
seal was found with cracking at the seal
head. Propagation of such cracking may lead
to failure, causing secondary impact damage
to the IPC module.
This condition, if not detected and
corrected, could lead to engine power loss,
possibly resulting in reduced control of the
aeroplane.
To address this potential unsafe condition,
RR published the NMSB, providing
instructions for on-wing borescope
inspections. RR previously issued NMSB
TRENT 1000 72–J353, which contains
instructions for in-shop inspections.
For the reasons described above, this
[EASA] AD requires repetitive borescope
inspections of the front face of the affected
seals and, depending on the findings,
accomplishment of applicable corrections
action(s).
You may obtain further information
by examining the MCAI in the AD
docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0611.
Related Service Information Under 1
CFR Part 51
We reviewed RR Non-Modification
Service Bulletin (NMSB) Trent 1000 72–
E:\FR\FM\09AUP1.SGM
09AUP1
]]>Agencies
[Federal Register Volume 83, Number 154 (Thursday, August 9, 2018)]
[Proposed Rules]
[Pages 39377-39380]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16733]
[[Page 39377]]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0705; Product Identifier 2018-NM-077-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes. This proposed AD was prompted by a report that
during removal of left-hand (LH) gear rib 5, four failed fasteners were
discovered. This proposed AD would require a one-time ultrasonic
inspection of the LH and right-hand (RH) wing rib 5-to-rear spar
attachments for cracked or failed fasteners, and if necessary, a
detailed inspection of the gear rib 5 and spar web for cracks and
damage, a rotating probe test of the gear rib and spar web bolt holes
for cracks and damage, reaming the gear rib and the spar web bolt
holes, and replacement of cracked or failed fasteners. We are proposing
this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by September 24,
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, Rond-Point Emile Dewoitine No: 2, 31700
Blagnac Cedex, France; phone: +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.
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-
0705; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; phone and fax: 206-231-3223.
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-2018-0705;
Product Identifier 2018-NM-077-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM because
of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this NPRM.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0102, dated April 27, 2018 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus SAS Model A321-111, -
112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states:
During removal of the left hand (LH) rib 5, two of the fasteners
(bolts) attaching the rib to the wing inner rear spar were found to
have failed and two more failed during their removal. Two of the
bolts were found separated from the bolt shanks when the overcoat
sealant was being removed, and the other two bolt heads broke away
during removal.
This condition, if not detected and corrected, could reduce the
structural integrity of the wing.
To address this possible unsafe condition, Airbus issued
[Service Bulletin] SB A320-57-1167 to provide inspection
instructions. After that SB was issued, a potential manufacturing
issue was identified on early production A321 [airplanes] concerning
reports of fasteners ``jamming'' during installation on spar
assemblies. A process change was introduced in production line, and
SB A320-57-1167 was revised, changing the affected population to
include all A321 aeroplanes delivered before the introduction of
that process change.
For the reasons described above, this [EASA] AD requires a one-
time special detailed [ultrasonic] inspection (SDI) of the wing rib
5-to-rear spar attachments, both LH and right hand (RH) wings, [and
if necessary, a detailed inspection of the gear rib 5 and spar web
for cracks and damage (cracks along the length of the bolt or broken
bolt), a rotating probe test of the gear rib and spar web bolt holes
for cracks and damage (cracks in the bolt holes), reaming the gear
rib and the spar web bolt holes] and, depending on findings,
accomplishment of a repair [replacement of cracked or failed
(broken) fasteners (bolts)]. This [EASA] AD also requires the
reporting of findings.
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-
0705.
Related Service Information Under 1 CFR Part 51
Airbus SAS has issued Service Bulletin A320-57-1167, Revision 01,
dated January 16, 2018. This service information describes procedures
for a one-time special detailed (ultrasonic) inspection of the LH and
RH wing rib 5-to-rear spar attachments for cracked or failed (broken)
fasteners (bolts), and if necessary, a detailed inspection of the gear-
rib-5 and spar web for cracks and damage (cracks along the length of
the bolt or broken bolt), a rotating probe test of the gear rib and
spar web bolt holes for cracks and damage (cracks in the bolt holes),
reaming the gear rib and the spar web bolt holes, and replacement of
the cracked or damaged (broken) fasteners (bolts). 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
This product has been approved by the aviation authority of another
country, and is approved for operation
[[Page 39378]]
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 the relevant
information and determined the unsafe condition described previously is
likely to exist or develop on other products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the MCAI or Service
Information.'' This proposed AD also would require sending the
inspection results to Airbus SAS.
Differences Between This Proposed AD and the MCAI or Service
Information
The MCAI specifies credit for actions accomplished in accordance
with the Accomplishment Instructions of Airbus Service Bulletin A320-
57-1167, dated August 10, 2011. The MCAI also discusses a potential
manufacturing issue that was identified on early production Model A321
airplanes concerning reports of fasteners ``jamming'' during
installation on spar assemblies. The corrective action specified in
Airbus Service Bulletin A320-57-1167, dated August 10, 2011, includes
the same process that produced ``jamming'' previously. Therefore, this
proposed AD does not include credit for actions accomplished using the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1167,
dated August 10, 2011.
Explanation of Change to Applicability
We have revised the applicability of this AD to identify model
designations as published in the most recent type certificate data
sheet for the affected model.
Costs of Compliance
We estimate that this proposed AD affects 29 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
16 work-hours x $85 per hour = $1,360........................ $0 $1,360 $39,440
----------------------------------------------------------------------------------------------------------------
We estimate that it would take about 1 work-hour per product to
comply with the proposed reporting requirement in this proposed AD. The
average labor rate is $85 per hour. Based on these figures, we estimate
the cost of reporting the inspection results on U.S. operators to be
$2,465, or $85 per product.
We estimate the following costs to do any necessary on-condition
actions that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need these on-condition actions:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
20 work-hours x $85 per hour = $1,700. $0 $1,700
------------------------------------------------------------------------
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this NPRM is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
[[Page 39379]]
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus SAS: Docket No. FAA-2018-0705; Product Identifier 2018-NM-
077-AD.
(a) Comments Due Date
We must receive comments by September 24, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A321-111, -112, -131, -211,
-212, -213, -231, and -232 airplanes, certificated in any category,
as identified in Airbus Service Bulletin A320-57-1167, Revision 01,
dated January 16, 2018.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by a report that during removal of left-
hand (LH) gear rib 5, four failed fasteners (bolts attaching the
gear rib to the wing inner rear spar) were discovered. We are
issuing this AD to detect and correct cracked or failed (broken)
fasteners (bolts) of the rib 5-to-rear spar attachment, which could
lead to reduced structural integrity of the wing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection of the Rib 5-to-Rear Spar Attachment Fasteners (Bolts)
Within 30 months after the effective date of this AD, do a
special detailed (ultrasonic) inspection of the LH and right-hand
(RH) wing rib 5-to-rear spar attachment fasteners (bolts) for
cracked or failed (broken) fasteners (bolts), in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1167,
Revision 01, dated January 16, 2018.
(h) Replacement of Cracked or Failed Fasteners (Bolts)
If any cracked or failed (broken) fastener (bolt) is found
during any inspection required by paragraph (g) of this AD, before
further flight, do the actions specified in paragraph (h)(1),
(h)(2), (h)(3) and (h)(4) of this AD, as applicable.
(1) Do a detailed inspection of the gear rib 5 and spar web for
cracks and damage (cracks along the length of the bolt or broken
bolt), in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-57-1167, Revision 01, dated January 16, 2018.
If any crack or damage is found during any inspection required by
this paragraph, before further flight, obtain corrective actions
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus SAS's EASA Design Organization Approval (DOA); and accomplish
the corrective actions within the compliance time specified therein.
If approved by the DOA, the approval must include the DOA-authorized
signature.
(2) If no cracks or damage are found during any inspection
required by paragraph (h)(1) of this AD: Do a rotating probe test of
the gear rib and spar web bolt holes for cracks and damage (cracks
in the bolt holes), in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1167, Revision 01,
dated January 16, 2018. If any crack or damage is found during any
inspection required by this paragraph, before further flight, obtain
corrective actions approved by the Manager, International Section,
Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA;
and accomplish the corrective actions within the compliance time
specified therein. If approved by the DOA, the approval must include
the DOA authorized signature.
(3) If no cracks or damage are found during any inspection
required by paragraph (h)(2) of this AD: Ream the gear rib and the
spar web bolt holes, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1167, Revision 01,
dated January 16, 2018. If an oversize larger than 0.794 millimeter
(0.0313 inch) is required, before further flight, obtain corrective
actions approved by the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; and
accomplish the corrective actions within the compliance time
specified therein. If approved by the DOA, the approval must include
the DOA authorized signature.
(4) Replace any cracked or failed fasteners (bolts) in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-57-1167, Revision 01, dated January 16, 2018.
(i) Reporting
Within 90 days after the special detailed inspection required by
paragraph (g) of this AD, or within 30 days after the effective date
of this AD, whichever occurs later, report the inspection results
(both positive and negative) to Airbus SAS in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1167,
Revision 01, dated January 16, 2018. If operators have reported
findings as part of obtaining any corrective actions approved by the
EASA DOA, operators are not required to report those findings as
specified in this paragraph.
(j) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 1 hour per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(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: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the EASA; or Airbus
SAS'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
paragraph (i) of this AD: If any service information contains
procedures or
[[Page 39380]]
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 2018-0102, dated April 27, 2018, 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-2018-0705.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and
fax: 206-231-3223.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; phone: +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 Des Moines, Washington, on July 27, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-16733 Filed 8-8-18; 8:45 am]
BILLING CODE 4910-13-P
