Airworthiness Directives; Airbus Airplanes, 26559-26564 [2018-12268]
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Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations
5313; fax: 562–627–5210; email:
payman.soltani@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (l)(3) and (l)(4) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin
737–57A1337 RB, dated September 14, 2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on May
31, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–12279 Filed 6–7–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1020; Product
Identifier 2017–NM–114–AD; Amendment
39–19306; AD 2018–12–02]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, and –115 airplanes; Model A320–
211, –212, –214, and –216 airplanes;
SUMMARY:
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and Model A321–111, –112, –211, –212,
and –213 airplanes. This AD was
prompted by a review of maintenance
instructions for a blend repair of the
snout diameter of the main beam
assembly of the forward engine mount
that would create an excessive gap
between the bearing mono-ball and the
snout. This AD requires modifying the
main beam assembly of the forward
engine mount. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective July 13,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 13, 2018.
ADDRESSES: For Airbus service
information identified in this final rule,
contact Airbus, Airworthiness Office–
EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France;
telephone: +33 5 61 93 36 96; fax: +33
5 61 93 44 51; email: account.airwortheas@airbus.com; internet: https://
www.airbus.com. For Goodrich service
information identified in this final rule,
contact Goodrich Corporation,
Aerostructures, 850 Lagoon Drive, Chula
Vista, CA 91910–2098; phone: 619–691–
2719; email: jan.lewis@goodrich.com;
internet: https://www.goodrich.com/
TechPubs. You may view this
referenced service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
1020.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
1020; 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 AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
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26559
216th St., Des Moines, WA 98198–6547;
telephone 425–227–1405; fax 425–227–
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A318–111
and –112 airplanes; Model A319–111,
–112, –113, –114, and –115 airplanes;
Model A320–211, –212, –214, and –216
airplanes; and Model A321–111, –112,
–211, –212, and –213 airplanes. The
NPRM published in the Federal
Register on October 24, 2017 (82 FR
49146) (‘‘the NPRM’’). The NPRM was
prompted by a review of maintenance
instructions for a blend repair of the
snout diameter of the main beam
assembly of the forward engine mount
that would create an excessive gap
between the bearing mono-ball and the
snout. The NPRM proposed to require
modifying the main beam assembly of
the forward engine mount. We are
issuing this AD to prevent in-flight
failure of a forward engine mount, and
consequent detachment of an engine,
which could result in reduced
controllability of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–
0132R1, dated November 22, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A318–
111 and –112 airplanes; Model A319–
111, –112, –113, –114, and –115
airplanes; Model A320–211, –212, –214,
and –216 airplanes; and Model A321–
111, –112, –211, –212, and –213
airplanes. The MCAI states:
A review of maintenance instructions
revealed that the Goodrich Aerospace
CFM56–5B, Forward Engine Mount
Component Maintenance Manual (CMM) 71–
21–08, revision (rev.) 1 up to 46 (inclusive),
repair 10 (Blend Repair-Beam Assembly
Snout Diameter), provides instructions to
blend the wear on the forward engine mount
assembly, Part Number (P/N) 642–2000–9,
642–2000–13, or 642–2000–25, creating an
excessive gap between the bearing mono-ball
and the snout of the forward engine mount
main beam assembly, P/N 642–2006–501, or
P/N 642–2006–503.
This condition, if not detected and
corrected, could lead to in-flight failure of a
forward engine mount and consequent
detachment of an engine, possibly resulting
in reduced control of the aeroplane and
injury to persons on the ground.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A320–
71–1065 and SB A320–71–1066, and
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Goodrich Aerospace issued SB RA32071–
159, providing instructions for an in-shop
inspection(s) for the main beam snout and,
depending on findings, applicable corrective
action(s) and re-identification.
Consequently, EASA issued AD 2017–
0132, requiring replacement of the affected
forward engine mount main beam
assemblies. As the same main beam
assemblies are certified for CFM56–5A
engine installation, that [EASA] AD also
applied to aeroplanes with that engine.
Since that [EASA] AD was issued, it was
determined that, for aeroplanes equipped
with an affected forward engine mount main
beam assembly, installation of an affected
assembly can still be allowed until
replacement, as required by this [EASA] AD.
For the reason described above, this
[EASA] AD is revised accordingly.
Required actions include modifying
the main beam assembly of the forward
engine mount. The modification
includes repairing, replacing, or
reworking the main beam assembly. You
may examine the MCAI in the AD
docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
1020.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
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Support for the NPRM
The Air Line Pilots Association,
International (ALPA) and Jake Watson
stated their support for the proposed
AD. American Airlines (AAL) stated
that it has no objection to the intent of
the NPRM.
Request To Use Revised Vendor Service
Information
AAL stated that the proposed AD
should require Goodrich Aerospace
Service Bulletin RA32071–159, Rev 1,
dated July 25, 2017 (‘‘SB RA32071–159
Rev 1’’), which corrects part number
references, revises illustrations, and
clarifies the procedure. Alternatively,
AAL asserted that the proposed AD
should allow the use of RA32071–159
Rev 1, or later revisions. AAL stated that
Goodrich Aerospace Service Bulletin
RA32071–159, dated November 20,
2016, is not useable due to multiple
issues.
We do not agree to require RA32071–
159 Rev 1. Goodrich Aerospace Service
Bulletin RA32071–159 is referenced as
an additional source of guidance in
Airbus Service Bulletin A320–71–1065,
Revision 01, dated July 28, 2017; and
Airbus Service Bulletin A320–71–1066,
dated December 1, 2016; for inspecting
and corrective actions. We acknowledge
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that RA32071–159 Rev 1 contains
several improvements. Therefore, we
recommend operators incorporate the
latest approved service information.
However, in paragraphs (g)(2)(ii) and (h)
of this AD, we refer to ‘‘Goodrich
Aerospace Service Bulletin RA32071–
159’’ and not to any specific revision.
Therefore, we have not changed this AD
in this regard.
Request To Exclude Certain Actions
AAL stated that Goodrich Aerospace
Service Bulletin RA32071–159 requires
operators to ‘‘fully disassemble the
engine mount assembly’’, which is not
necessary for the dimensional
inspection of the snout. AAL noted that,
as long as the mount is not installed on
the engine, the bearing assembly can be
removed to expose the snout, clean, and
measure the snout. AAL added that if an
operator is forced to fully disassemble
the mount, it will drive the mount to an
overhaul, which is time consuming and
costly.
We infer that the commenter is asking
that we exclude full disassembly of the
engine mount assembly from the
inspection specified in paragraph (h) of
the proposed AD. We do not agree.
Neither Airbus nor the state of design
authority, EASA, has informed the FAA
that the snout diameter can be
conclusively measured without full
disassembly of the engine mount
assembly. AAL did not provide any
justification supported by approval from
EASA; or Airbus’s EASA Design
Organization Approval (DOA) to allow
deviation from the required for
compliance section of the service
information. However, under the
provisions of paragraph (n) of this AD,
we will consider requests for approval
of an alternative method of compliance
if sufficient data are submitted to
substantiate that a deviation would
provide an acceptable level of safety.
We have made no change to this AD in
this regard.
Request To Compel Goodrich
Aerospace To Use ‘‘Required for
Compliance (RC)’’ Language in
Goodrich Aerospace Service Bulletin
RA32071–159
AAL also asked that the FAA compel
Goodrich Aerospace to incorporate FAA
Advisory Circular 20–176A, dated June
16, 2014, into Goodrich Aerospace
Service Bulletin RA32071–159 for the
purpose of ‘‘. . . distinguishing which
steps in an SB will have a direct effect
on detecting, preventing, resolving, or
eliminating the unsafe condition
identified in an AD.’’ AAL asserted that
Goodrich Aerospace has had 7 years to
evaluate and incorporate the best
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practices for drafting service bulletins
related to ADs.
We disagree with the commenter’s
request. FAA Advisory Circular 20–
176A, dated June 16, 2014, provides
best practices for drafting service
bulletins related to ADs. Although we
recommend that the original equipment
manufacturer (OEM) specify ‘‘RC’’ steps
in service information, the FAA
advisory circular is not mandatory, only
a recommendation as best practices. We
have not changed this AD in this regard.
Request To Remove Revision Level for
Vendor Service Information
Delta Airlines (Delta) asked that the
proposed AD not specify a revision level
for Goodrich Aerospace Service Bulletin
RA32071–159. Delta added that, if one
must be specified, all revisions
published prior to the effective date of
the AD should be acceptable methods of
compliance.
We agree with the commenter’s
request that the revision level of
Goodrich Aerospace Service Bulletin
RA32071–159 not be specified. As
previously explained, this AD does not
specify a revision level for Goodrich
Aerospace Service Bulletin RA32071–
159. Therefore, no change to this AD is
necessary in this regard.
Request To Specify Confirmation That
a Certain Discrepant Repair Has Never
Been Installed
Delta requested that paragraph (g)(1)
of the proposed AD be revised to specify
that maintenance records must confirm
that Repair 10 of Component
Maintenance Manual (CMM) 71–21–08,
Revisions 1 through 46, has never been
performed. Delta stated that, based on
the NPRM and service information, it is
clear that the discrepant repair is Repair
10 of CMM 71–21–08, Revisions 1
through 46. Delta added that paragraph
(g)(1) of the proposed AD does not
specify that maintenance records must
show only that forward mount main
beams have not been repaired per the
discrepant Repair 10 of CMM 71–21–08,
Revisions 1 through 46, which would
classify them as affected main beams.
We disagree with the commenter’s
request; however, we provide the
following clarification. The intent of
paragraph (g)(1) of this AD is that if no
maintenance record exists then there is
a possibility that the main beam has
been repaired using Repair 10 of CMM
71–21–08 Revisions 1 through 46, and,
therefore, qualifies as an ‘‘affected main
beam.’’ We have not changed this AD in
this regard.
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Request To Apply Exceptions to Parts
Without Maintenance Records of
Repair History
Delta asked that the exceptions in
paragraphs (g)(2)(i) through (g)(2)(iii) of
the proposed AD also apply to parts for
which maintenance records are not
available to confirm repair history. Delta
stated that this will account for mounts
that are not installed on-wing and future
spare purchases. Delta added that
paragraph (g)(2) of the proposed AD
does not permit parts with unknown
repair history to be excluded if the
criteria in paragraphs (g)(2)(i) through
(g)(2)(iii) of the proposed AD are met.
Delta noted that paragraph (g)(1) of the
proposed AD, parts with unknown
repair history, are considered ‘‘affected
main beams’’ and have the same
compliance requirements as parts that
have been repaired per discrepant
Repair 10 of CMM 71–21–08, Revisions
1 through 46.
We do not agree with the commenter’s
request. Exceptions in paragraphs
(g)(2)(i) through (g)(2)(iii) of this AD are
based on the fact that maintenance
records exist. Therefore, these
exceptions do not apply to parts with
unknown repair history in paragraph
(g)(1) of this AD. We have not changed
this AD in this regard.
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Requests To Use Later Revisions of
CMM Repairs
Delta and Lufthansa Technik
(Lufthansa) asked that we allow use of
later revisions of the CMM repairs in
paragraphs (g)(2)(ii) and (h) of the
proposed AD. Delta noted that
paragraph (g)(2)(ii) doesn’t specify that
a repair per the corrected Repair 10 of
CMM 71–21–08, Revision 47 (and later),
or Repair 21 of CMM 71–21–06,
Revision 59 (and later), excludes
forward mount main beams from the
effectivity. Delta added that the
dimensional requirements of corrected
Repair 10 and Repair 21 are equivalent
to the requirements of Goodrich
Aerospace Service Bulletin RA32071–
159, and ensure that any main beams
repaired will meet the intent of the
proposed AD.
Delta stated that paragraph (h) of the
proposed AD doesn’t specify that a
qualifying inspection can be done as
specified in the instructions of the later
revisions of CMMs 71–21–08 and 71–
21–06 that introduced the corrected
Repair 10 and Repair 21. Delta
explained that CMM 71–21–08,
Revision 48 (and later), and CMM 71–
21–06, Revision 60 (and later), contain
the correct snout diameters as specified
in Repair 10 of CMM 71–21–08,
Revision 47, and Repair 21 of CMM 71–
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21–06, Revision 59. Delta further noted
that EASA AD 2017–0132R1, dated
November 22, 2017, permits the use of
later revisions of the CMMs with
corrected Repairs 10 and 21.
We disagree with the commenters’
requests. We cannot use the phrase, ‘‘or
later approved revisions,’’ in an AD
when referring to the service document
because doing so violates Office of the
Federal Register (OFR) regulations for
approval of materials ‘‘incorporated by
reference’’ in rules. In general terms, we
are required by these OFR regulations to
either publish the service document
contents as part of the actual AD
language; or submit the service
document to the OFR for approval as
‘‘referenced’’ material, in which case we
may only refer to such material in the
text of an AD. The AD may refer to the
service document only if the OFR
approved it for ‘‘incorporation by
reference.’’ To allow operators to use
later revisions of the referenced
document (issued after publication of
the AD), either we must revise the AD
to reference specific later revisions, or
operators must request approval to use
later revisions as an alternative method
of compliance (AMOC) with this AD
under the provisions of paragraph (n) of
this AD. We have not changed this AD
in this regard.
Request To Define Airplane Group
Delta asked that paragraph (i) of the
proposed AD clarify that airplanes on
which the main beams have never been
replaced are considered Group 2
airplanes. Delta stated that paragraph (i)
of the proposed AD doesn’t specify that
airplanes on which the main beams
have never been replaced (and thus
never repaired) since aircraft delivery
should be considered Group 2 airplanes.
Delta added that an airplane on which
the forward mounts have never been
replaced since aircraft delivery will not
have the discrepant Repair 10 of CMM
71–21–08, Revisions 1 through 46.
We do not agree to revise paragraph
(i) of this AD; however, we have
clarified the airplane group as follows.
Paragraph (i) of this AD specifies Group
2 airplanes are airplanes on which an
affected main beam has not been
installed as of the effective date of this
AD. Therefore, airplanes with main
beams that have never been replaced
since aircraft delivery might be
considered Group 2 airplanes, if the
original main beam is not an affected
main beam as defined in paragraph (g)
of this AD. However, if for example, an
airplane with main beams that have
never been replaced does not have
maintenance records to conclusively
confirm the part has never been
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26561
repaired, as specified in paragraph (g)(1)
of this AD, then it is a Group 1 airplane.
We have not changed this AD in this
regard.
Request To Change ‘‘Modify’’ to
‘‘Inspect and Disposition’’
Delta asked that the proposed AD use
the language ‘‘inspect and disposition’’
instead of ‘‘modify’’ to describe the
action required by paragraph (j) of the
proposed AD. Additionally, Delta asked
that the proposed AD specify that
replacement of a forward mount
assembly containing an affected main
beam with a forward mount assembly
that contains an AD-compliant main
beam is an acceptable means of
compliance. Delta stated that paragraph
(j) of the proposed AD uses the term
‘‘modify’’ to describe compliance with
the requirements of the inspection and
repair of the mounts. Delta added that,
based on the instructions in the service
information, the intent of the work
instructions is to inspect affected main
beams and disposition based on
inspection findings; the dispositions
range from scrapping the main beam to
blending, based on measured snout
diameter. Delta noted that the
replacement of a forward mount
assembly that contains an affected main
beam with a forward mount assembly
with an AD-compliant main beam meets
the intent of the proposed AD to remove
affected main beams from service.
We partially agree. We do not agree to
replace ‘‘modify’’ with ‘‘inspect and
disposition,’’ because corrective action
cannot be defined by the term
‘‘disposition,’’ which is open to
interpretation. Operators must follow
the instructions in the Airbus service
information referenced in paragraph (j)
of this AD for the applicable method of
compliance. However, we acknowledge
that, while the Accomplishment
Instructions of Airbus Service Bulletin
A320–71–1066, dated December 1,
2016, specify to do a ‘‘Modification of
the FWD Engine Mount Assembly on
Engine 1 and Engine 2,’’ the
Accomplishment Instructions of Airbus
Service Bulletin A320–71–1065,
Revision 01, dated July 28, 2017, specify
to do inspections and applicable
corrective actions. Therefore, we have
changed paragraph (j) of this AD to
replace ‘‘modify’’ with ‘‘modify,
including doing all applicable
inspections and corrective actions.’’
Request To Include Goodrich
Aerospace Service Bulletin for the
Required Modification
Lufthansa requested that we include
Goodrich Aerospace Service Bulletin
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RA32071–159 in paragraph (j) of the
proposed AD to ‘‘make it more clear.’’
We do not agree. The commenter
provided no explanation of what is
unclear in paragraph (j) or how adding
the Goodrich Aerospace service bulletin
will clarify the requirements of
paragraph (j). Therefore, we have not
changed this AD in this regard.
Requests To Provide Credit for Previous
Actions Done Using Other Service
Information
Delta and Lufthansa asked that the
proposed AD include credit for doing
previous actions by accomplishing
Goodrich Aerospace Service Bulletin
RA32071–159; Repair 10 of CMM 71–
21–08, Revision 47 (and later); or Repair
21 of CMM 71–21–06, Revision 59 (and
later). Delta stated that paragraph (l) of
the proposed AD includes credit for
previous actions only for compliance
with Airbus Service Bulletin A320–71–
1065, Revision 01, dated July 28, 2017.
Delta asserted that the intent of the
proposed AD is met by the
accomplishment of Goodrich Aerospace
Service Bulletin RA32071–159; Repair
10 of CMM 71–21–08, Revision 47 (and
later); or Repair 21 of CMM 71–21–06,
Revision 59 (and later); due to the
correction of the inspection and repair
requirements.
We do not agree with the commenter’s
request. Goodrich Aerospace Service
Bulletin RA32071–159 is referenced in
the airplane level Airbus service
information as a secondary document;
therefore, it is not an alternate for the
instructions in the airplane level service
information. All of the steps in
paragraph 3.C. of Airbus Service
Bulletin A320–71–1065, Revision 01,
dated July 28, 2017, are required for
compliance and must be done to comply
with this AD. If not done before the
effective date of this AD, paragraph (f)
of this AD states that you must comply
with the actions in the AD, ‘‘unless
already done.’’
Regarding future revisions of CMM
repairs, we may not refer to any
document that does not yet exist. To
allow operators to use later revisions of
a required document (issued after
publication of the AD), either we must
revise the AD to reference specific later
revisions, or operators must request
approval to use later revisions as an
alternative method of compliance with
the requirements of an AD under the
provisions of the AMOC paragraph of
the AD. However, as explained
previously, the identified CMM repairs
are not required for accomplishment of
any action in this AD; therefore, no
change to this AD is necessary in this
regard.
Request To Change Parts Installation
Prohibition
Delta asked that paragraph (m) of the
proposed AD, ‘‘Parts Installation
Prohibition,’’ be changed to permit the
same allowance to install an affected
main beam onto an aircraft equipped
with an affected forward engine mount
assembly within the compliance
windows defined in paragraph (j) of the
proposed AD. Delta stated that
paragraph (m) of the proposed AD
prohibits the installation of an affected
main beam on any airplane after the
effective date of the AD. Delta further
points out that the parallel EASA AD
2017–0132R1, dated November 22,
2017, permits the installation of an
affected main beam onto an aircraft
equipped with an affected forward
engine mount assembly within the
compliance times defined in paragraph
(j) of the proposed AD.
We agree with the commenter’s
request. After the NPRM was issued,
EASA issued AD 2017–0132R1, dated
November 22, 2017, which revised its
parts installation requirement. We have
revised paragraph (m) of this AD to
match the EASA AD. In addition, we
have revised this AD to refer to EASA
AD 2017–0132R1, dated November 22,
2017.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously,
with minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–71–1065, Revision 01, dated July
28, 2017. This service information
describes procedures for modifying the
main beam assembly of the forward
engine mount. The modification
includes, among other things, repair or
replacement of the main beam assembly.
Airbus has also issued Service
Bulletin A320–71–1066, dated
December 1, 2016. This service
information describes procedures for
modifying the main beam assembly of
the forward engine mount. The
modification includes, among other
things, rework of the main beam
assembly.
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.
Costs of Compliance
We estimate that this AD affects 500
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Modification ............
Up to 76 work-hours × $85 per hour = $6,460 ..
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
VerDate Sep<11>2014
16:08 Jun 07, 2018
Jkt 244001
Parts cost
$778
Cost per product
Up to $7,238 ................
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
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Fmt 4700
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Cost on U.S. operators
Up to $3,619,000.
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.
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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 AD will not
have federalism implications under
Executive Order 13132. This AD will
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 that this AD:
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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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):
amozie on DSK3GDR082PROD with RULES
■
2018–12–02 Airbus: Amendment 39–19306;
Docket No. FAA–2017–1020; Product
Identifier 2017–NM–114–AD.
(a) Effective Date
This AD is effective July 13, 2018.
(b) Affected ADs
None.
VerDate Sep<11>2014
16:08 Jun 07, 2018
Jkt 244001
(c) Applicability
This AD applies to all Airbus Model A318–
111 and –112 airplanes; Model A319–111,
–112, –113, –114, and –115 airplanes; Model
A320–211, –212, –214, and –216 airplanes;
and Model A321–111, –112, –211, –212, and
–213 airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
(e) Reason
This AD was prompted by a review of
maintenance instructions for a blend repair
of the diameter of the snout of the main beam
assembly of the forward engine mount that
would create an excessive gap between the
bearing mono-ball and the snout. We are
issuing this AD to prevent in-flight failure of
a forward engine mount, and consequent
detachment of an engine, which could result
in reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definition of Affected Parts
For the purposes of this AD: An ‘‘affected
main beam’’ is any main beam assembly of
the forward engine mount, part number (P/
N) 642–2006–501 or P/N 642–2006–503,
identified in paragraph (g)(1) or (g)(2) of this
AD.
(1) Any part for which no maintenance
records are available to confirm the part has
never been repaired.
(2) Any part that was repaired as specified
in Repair 10, of Goodrich Aerospace
Component Maintenance Manual (CMM) 71–
21–08, Revisions 1 through 46, except for
parts identified in paragraphs (g)(2)(i),
(g)(2)(ii), and (g)(2)(iii) of this AD.
(i) Any part on which a qualifying
inspection identified in paragraph (h) of this
AD has been done and there were no findings
(the inspection was passed).
(ii) Any part on which a qualifying
inspection identified in paragraph (h) of this
AD has been done and that part has been
repaired as specified in Goodrich Aerospace
Service Bulletin RA32071–159.
(iii) Any part that has been repaired in
accordance with other instructions approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA).
(h) Definition of Qualifying Inspection
For the purposes of this AD: ‘‘A qualifying
inspection’’ is an inspection done as
specified in Goodrich Aerospace Service
Bulletin RA32071–159; or for CFM56–5B
engines, an inspection done as specified in
Repair 10 of Goodrich Aerospace CMM 71–
21–08, Revision 47; or for CFM56–5A
engines, an inspection done as specified in
Repair 21 of Goodrich Aerospace CMM 71–
21–06, Revision 59.
(i) Definition of Airplane Groups
For the purposes of this AD: ‘‘Group 1
airplanes’’ are airplanes on which an affected
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
26563
main beam has been installed as of the
effective date of this AD. ‘‘Group 2 airplanes’’
are airplanes on which an affected main
beam has not been installed as of the
effective date of this AD; this includes
airplanes with an original certificate of
airworthiness or original export certificate of
airworthiness that was issued after the
effective date of this AD.
(j) Modification of Affected Main Beam
Assemblies
For Group 1 airplanes as identified in
paragraph (i) of this AD: At the earliest of the
compliance times specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, modify,
including doing all applicable inspections
and corrective actions, for each affected main
beam identified in paragraph (g) of this AD,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
71–1065, Revision 01, dated July 28, 2017; or
Airbus Service Bulletin A320–71–1066,
dated December 1, 2016; as applicable;
except as required by paragraph (k) of this
AD.
(1) Within 48 months after the effective
date of this AD.
(2) Within 10,000 flight cycles after the
effective date of this AD.
(3) Within 15,000 flight hours after the
effective date of this AD.
(k) Exception to Service Information
Where Airbus Service Bulletin A320–71–
1065, Revision 01, dated July 28, 2017,
specifies to contact a manufacturer for
appropriate action, and specifies that action
as ‘‘RC’’ (Required for Compliance): Before
further flight, accomplish corrective actions
in accordance with the procedures specified
in paragraph (n)(2) of this AD.
(l) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (j) of this AD
involving Airbus Service Bulletin A320–71–
1065, Revision 01, dated July 28, 2017, if
those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–71–1065, dated December 1,
2016.
(m) Parts Installation Prohibition
Do not install on any airplane an affected
main beam or a forward engine mount
assembly equipped with an affected main
beam, as specified in paragraph (m)(1) or
(m)(2) of this AD, as applicable.
(1) For Group 1 airplanes: After
modification of the airplane as required by
paragraph (j) of this AD.
(2) For Group 2 airplanes: As of the
effective date of this AD.
(n) 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
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26564
Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations
directly to the manager of the International
Section, send it to the attention of the person
identified in paragraph (o)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: 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 paragraph (k) of this AD: If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
amozie on DSK3GDR082PROD with RULES
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0132R1, dated November 22, 2017, for
related information. This MCAI may be
found in the AD docket on the internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2017–1020.
(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 98198–6547; telephone 425–
227–1405; fax 425–227–1149.
(3) Airbus service information identified in
this AD that is not incorporated by reference
is available at the addresses specified in
paragraphs (p)(4) and (p)(5) of this AD.
(4) Goodrich service information identified
in this AD that is not incorporated by
reference is available at Goodrich
Corporation, Aerostructures, 850 Lagoon
Drive, Chula Vista, CA 91910–2098; phone:
619–691–2719; email: jan.lewis@
goodrich.com; internet: https://
www.goodrich.com/TechPubs.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–71–1065,
Revision 01, dated July 28, 2017.
(ii) Airbus Service Bulletin A320–71–1066,
dated December 1, 2016.
VerDate Sep<11>2014
16:08 Jun 07, 2018
Jkt 244001
(3) For Airbus service information
identified in this AD, contact Airbus,
Airworthiness Office–EIAS, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone: +33 5 61 93 36 96; fax:
+33 5 61 93 44 51; email: account.airwortheas@airbus.com; internet: https://
www.airbus.com.
(4) For Goodrich service information
identified in this final rule, contact Goodrich
Corporation, Aerostructures, 850 Lagoon
Drive, Chula Vista, CA 91910–2098; phone:
619–691–2719; email: jan.lewis@
goodrich.com; internet: https://
www.goodrich.com/TechPubs.
(5) 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.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on May
29, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2018–12268 Filed 6–7–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
of a certain publication listed in this AD
as of June 25, 2018.
We must receive comments on this
AD by July 23, 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 final rule, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110 SK57,
Seal Beach, CA 90740–5600; telephone
562 797 1717; internet https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0507.
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2018–0507; Product
Identifier 2018–NM–027–AD; Amendment
39–19308; AD 2018–12–04]
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0507; 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 final rule,
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:
Stanley Chen, Aerospace Engineer,
Cabin Safety and Environmental
Systems Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3565; email: stanley.chen@faa.gov.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 777–300ER
series airplanes. This AD requires
replacing the water filter assembly in
certain steam ovens. This AD was
prompted by a report that water can
enter the steam oven cavity and become
heated and then released when the oven
door is opened. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective June 25,
2018.
The Director of the Federal Register
approved the incorporation by reference
SUMMARY:
PO 00000
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Fmt 4700
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Discussion
We have received a report that
members of the cabincrew on a Model
787 airplane were injured when hot
E:\FR\FM\08JNR1.SGM
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]]>Agencies
[Federal Register Volume 83, Number 111 (Friday, June 8, 2018)]
[Rules and Regulations]
[Pages 26559-26564]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12268]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD; Amendment
39-19306; AD 2018-12-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -
114, and -115 airplanes; Model A320-211, -212, -214, and -216
airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes.
This AD was prompted by a review of maintenance instructions for a
blend repair of the snout diameter of the main beam assembly of the
forward engine mount that would create an excessive gap between the
bearing mono-ball and the snout. This AD requires modifying the main
beam assembly of the forward engine mount. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective July 13, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 13,
2018.
ADDRESSES: For Airbus service information identified in this final
rule, contact Airbus, Airworthiness Office-EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 44 51; email: [email protected];
internet: https://www.airbus.com. For Goodrich service information
identified in this final rule, contact Goodrich Corporation,
Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone:
619-691-2719; email: [email protected]; internet: https://www.goodrich.com/TechPubs. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2017-1020.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1020; 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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198-6547; telephone 425-227-1405; fax 425-
227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A318-111
and -112 airplanes; Model A319-111, -112, -113, -114, and -115
airplanes; Model A320-211, -212, -214, and -216 airplanes; and Model
A321-111, -112, -211, -212, and -213 airplanes. The NPRM published in
the Federal Register on October 24, 2017 (82 FR 49146) (``the NPRM'').
The NPRM was prompted by a review of maintenance instructions for a
blend repair of the snout diameter of the main beam assembly of the
forward engine mount that would create an excessive gap between the
bearing mono-ball and the snout. The NPRM proposed to require modifying
the main beam assembly of the forward engine mount. We are issuing this
AD to prevent in-flight failure of a forward engine mount, and
consequent detachment of an engine, which could result in reduced
controllability of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0132R1, dated November 22, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for all Airbus Model A318-111 and -112
airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model
A320-211, -212, -214, and -216 airplanes; and Model A321-111, -112, -
211, -212, and -213 airplanes. The MCAI states:
A review of maintenance instructions revealed that the Goodrich
Aerospace CFM56-5B, Forward Engine Mount Component Maintenance
Manual (CMM) 71-21-08, revision (rev.) 1 up to 46 (inclusive),
repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides
instructions to blend the wear on the forward engine mount assembly,
Part Number (P/N) 642-2000-9, 642-2000-13, or 642-2000-25, creating
an excessive gap between the bearing mono-ball and the snout of the
forward engine mount main beam assembly, P/N 642-2006-501, or P/N
642-2006-503.
This condition, if not detected and corrected, could lead to in-
flight failure of a forward engine mount and consequent detachment
of an engine, possibly resulting in reduced control of the aeroplane
and injury to persons on the ground.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-71-1065 and SB A320-71-1066, and
[[Page 26560]]
Goodrich Aerospace issued SB RA32071-159, providing instructions for
an in-shop inspection(s) for the main beam snout and, depending on
findings, applicable corrective action(s) and re-identification.
Consequently, EASA issued AD 2017-0132, requiring replacement of
the affected forward engine mount main beam assemblies. As the same
main beam assemblies are certified for CFM56-5A engine installation,
that [EASA] AD also applied to aeroplanes with that engine.
Since that [EASA] AD was issued, it was determined that, for
aeroplanes equipped with an affected forward engine mount main beam
assembly, installation of an affected assembly can still be allowed
until replacement, as required by this [EASA] AD.
For the reason described above, this [EASA] AD is revised
accordingly.
Required actions include modifying the main beam assembly of the
forward engine mount. The modification includes repairing, replacing,
or reworking the main beam assembly. You may examine the MCAI in the AD
docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2017-1020.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Support for the NPRM
The Air Line Pilots Association, International (ALPA) and Jake
Watson stated their support for the proposed AD. American Airlines
(AAL) stated that it has no objection to the intent of the NPRM.
Request To Use Revised Vendor Service Information
AAL stated that the proposed AD should require Goodrich Aerospace
Service Bulletin RA32071-159, Rev 1, dated July 25, 2017 (``SB RA32071-
159 Rev 1''), which corrects part number references, revises
illustrations, and clarifies the procedure. Alternatively, AAL asserted
that the proposed AD should allow the use of RA32071-159 Rev 1, or
later revisions. AAL stated that Goodrich Aerospace Service Bulletin
RA32071-159, dated November 20, 2016, is not useable due to multiple
issues.
We do not agree to require RA32071-159 Rev 1. Goodrich Aerospace
Service Bulletin RA32071-159 is referenced as an additional source of
guidance in Airbus Service Bulletin A320-71-1065, Revision 01, dated
July 28, 2017; and Airbus Service Bulletin A320-71-1066, dated December
1, 2016; for inspecting and corrective actions. We acknowledge that
RA32071-159 Rev 1 contains several improvements. Therefore, we
recommend operators incorporate the latest approved service
information. However, in paragraphs (g)(2)(ii) and (h) of this AD, we
refer to ``Goodrich Aerospace Service Bulletin RA32071-159'' and not to
any specific revision. Therefore, we have not changed this AD in this
regard.
Request To Exclude Certain Actions
AAL stated that Goodrich Aerospace Service Bulletin RA32071-159
requires operators to ``fully disassemble the engine mount assembly'',
which is not necessary for the dimensional inspection of the snout. AAL
noted that, as long as the mount is not installed on the engine, the
bearing assembly can be removed to expose the snout, clean, and measure
the snout. AAL added that if an operator is forced to fully disassemble
the mount, it will drive the mount to an overhaul, which is time
consuming and costly.
We infer that the commenter is asking that we exclude full
disassembly of the engine mount assembly from the inspection specified
in paragraph (h) of the proposed AD. We do not agree. Neither Airbus
nor the state of design authority, EASA, has informed the FAA that the
snout diameter can be conclusively measured without full disassembly of
the engine mount assembly. AAL did not provide any justification
supported by approval from EASA; or Airbus's EASA Design Organization
Approval (DOA) to allow deviation from the required for compliance
section of the service information. However, under the provisions of
paragraph (n) of this AD, we will consider requests for approval of an
alternative method of compliance if sufficient data are submitted to
substantiate that a deviation would provide an acceptable level of
safety. We have made no change to this AD in this regard.
Request To Compel Goodrich Aerospace To Use ``Required for Compliance
(RC)'' Language in Goodrich Aerospace Service Bulletin RA32071-159
AAL also asked that the FAA compel Goodrich Aerospace to
incorporate FAA Advisory Circular 20-176A, dated June 16, 2014, into
Goodrich Aerospace Service Bulletin RA32071-159 for the purpose of ``.
. . distinguishing which steps in an SB will have a direct effect on
detecting, preventing, resolving, or eliminating the unsafe condition
identified in an AD.'' AAL asserted that Goodrich Aerospace has had 7
years to evaluate and incorporate the best practices for drafting
service bulletins related to ADs.
We disagree with the commenter's request. FAA Advisory Circular 20-
176A, dated June 16, 2014, provides best practices for drafting service
bulletins related to ADs. Although we recommend that the original
equipment manufacturer (OEM) specify ``RC'' steps in service
information, the FAA advisory circular is not mandatory, only a
recommendation as best practices. We have not changed this AD in this
regard.
Request To Remove Revision Level for Vendor Service Information
Delta Airlines (Delta) asked that the proposed AD not specify a
revision level for Goodrich Aerospace Service Bulletin RA32071-159.
Delta added that, if one must be specified, all revisions published
prior to the effective date of the AD should be acceptable methods of
compliance.
We agree with the commenter's request that the revision level of
Goodrich Aerospace Service Bulletin RA32071-159 not be specified. As
previously explained, this AD does not specify a revision level for
Goodrich Aerospace Service Bulletin RA32071-159. Therefore, no change
to this AD is necessary in this regard.
Request To Specify Confirmation That a Certain Discrepant Repair Has
Never Been Installed
Delta requested that paragraph (g)(1) of the proposed AD be revised
to specify that maintenance records must confirm that Repair 10 of
Component Maintenance Manual (CMM) 71-21-08, Revisions 1 through 46,
has never been performed. Delta stated that, based on the NPRM and
service information, it is clear that the discrepant repair is Repair
10 of CMM 71-21-08, Revisions 1 through 46. Delta added that paragraph
(g)(1) of the proposed AD does not specify that maintenance records
must show only that forward mount main beams have not been repaired per
the discrepant Repair 10 of CMM 71-21-08, Revisions 1 through 46, which
would classify them as affected main beams.
We disagree with the commenter's request; however, we provide the
following clarification. The intent of paragraph (g)(1) of this AD is
that if no maintenance record exists then there is a possibility that
the main beam has been repaired using Repair 10 of CMM 71-21-08
Revisions 1 through 46, and, therefore, qualifies as an ``affected main
beam.'' We have not changed this AD in this regard.
[[Page 26561]]
Request To Apply Exceptions to Parts Without Maintenance Records of
Repair History
Delta asked that the exceptions in paragraphs (g)(2)(i) through
(g)(2)(iii) of the proposed AD also apply to parts for which
maintenance records are not available to confirm repair history. Delta
stated that this will account for mounts that are not installed on-wing
and future spare purchases. Delta added that paragraph (g)(2) of the
proposed AD does not permit parts with unknown repair history to be
excluded if the criteria in paragraphs (g)(2)(i) through (g)(2)(iii) of
the proposed AD are met. Delta noted that paragraph (g)(1) of the
proposed AD, parts with unknown repair history, are considered
``affected main beams'' and have the same compliance requirements as
parts that have been repaired per discrepant Repair 10 of CMM 71-21-08,
Revisions 1 through 46.
We do not agree with the commenter's request. Exceptions in
paragraphs (g)(2)(i) through (g)(2)(iii) of this AD are based on the
fact that maintenance records exist. Therefore, these exceptions do not
apply to parts with unknown repair history in paragraph (g)(1) of this
AD. We have not changed this AD in this regard.
Requests To Use Later Revisions of CMM Repairs
Delta and Lufthansa Technik (Lufthansa) asked that we allow use of
later revisions of the CMM repairs in paragraphs (g)(2)(ii) and (h) of
the proposed AD. Delta noted that paragraph (g)(2)(ii) doesn't specify
that a repair per the corrected Repair 10 of CMM 71-21-08, Revision 47
(and later), or Repair 21 of CMM 71-21-06, Revision 59 (and later),
excludes forward mount main beams from the effectivity. Delta added
that the dimensional requirements of corrected Repair 10 and Repair 21
are equivalent to the requirements of Goodrich Aerospace Service
Bulletin RA32071-159, and ensure that any main beams repaired will meet
the intent of the proposed AD.
Delta stated that paragraph (h) of the proposed AD doesn't specify
that a qualifying inspection can be done as specified in the
instructions of the later revisions of CMMs 71-21-08 and 71-21-06 that
introduced the corrected Repair 10 and Repair 21. Delta explained that
CMM 71-21-08, Revision 48 (and later), and CMM 71-21-06, Revision 60
(and later), contain the correct snout diameters as specified in Repair
10 of CMM 71-21-08, Revision 47, and Repair 21 of CMM 71-21-06,
Revision 59. Delta further noted that EASA AD 2017-0132R1, dated
November 22, 2017, permits the use of later revisions of the CMMs with
corrected Repairs 10 and 21.
We disagree with the commenters' requests. We cannot use the
phrase, ``or later approved revisions,'' in an AD when referring to the
service document because doing so violates Office of the Federal
Register (OFR) regulations for approval of materials ``incorporated by
reference'' in rules. In general terms, we are required by these OFR
regulations to either publish the service document contents as part of
the actual AD language; or submit the service document to the OFR for
approval as ``referenced'' material, in which case we may only refer to
such material in the text of an AD. The AD may refer to the service
document only if the OFR approved it for ``incorporation by
reference.'' To allow operators to use later revisions of the
referenced document (issued after publication of the AD), either we
must revise the AD to reference specific later revisions, or operators
must request approval to use later revisions as an alternative method
of compliance (AMOC) with this AD under the provisions of paragraph (n)
of this AD. We have not changed this AD in this regard.
Request To Define Airplane Group
Delta asked that paragraph (i) of the proposed AD clarify that
airplanes on which the main beams have never been replaced are
considered Group 2 airplanes. Delta stated that paragraph (i) of the
proposed AD doesn't specify that airplanes on which the main beams have
never been replaced (and thus never repaired) since aircraft delivery
should be considered Group 2 airplanes. Delta added that an airplane on
which the forward mounts have never been replaced since aircraft
delivery will not have the discrepant Repair 10 of CMM 71-21-08,
Revisions 1 through 46.
We do not agree to revise paragraph (i) of this AD; however, we
have clarified the airplane group as follows. Paragraph (i) of this AD
specifies Group 2 airplanes are airplanes on which an affected main
beam has not been installed as of the effective date of this AD.
Therefore, airplanes with main beams that have never been replaced
since aircraft delivery might be considered Group 2 airplanes, if the
original main beam is not an affected main beam as defined in paragraph
(g) of this AD. However, if for example, an airplane with main beams
that have never been replaced does not have maintenance records to
conclusively confirm the part has never been repaired, as specified in
paragraph (g)(1) of this AD, then it is a Group 1 airplane. We have not
changed this AD in this regard.
Request To Change ``Modify'' to ``Inspect and Disposition''
Delta asked that the proposed AD use the language ``inspect and
disposition'' instead of ``modify'' to describe the action required by
paragraph (j) of the proposed AD. Additionally, Delta asked that the
proposed AD specify that replacement of a forward mount assembly
containing an affected main beam with a forward mount assembly that
contains an AD-compliant main beam is an acceptable means of
compliance. Delta stated that paragraph (j) of the proposed AD uses the
term ``modify'' to describe compliance with the requirements of the
inspection and repair of the mounts. Delta added that, based on the
instructions in the service information, the intent of the work
instructions is to inspect affected main beams and disposition based on
inspection findings; the dispositions range from scrapping the main
beam to blending, based on measured snout diameter. Delta noted that
the replacement of a forward mount assembly that contains an affected
main beam with a forward mount assembly with an AD-compliant main beam
meets the intent of the proposed AD to remove affected main beams from
service.
We partially agree. We do not agree to replace ``modify'' with
``inspect and disposition,'' because corrective action cannot be
defined by the term ``disposition,'' which is open to interpretation.
Operators must follow the instructions in the Airbus service
information referenced in paragraph (j) of this AD for the applicable
method of compliance. However, we acknowledge that, while the
Accomplishment Instructions of Airbus Service Bulletin A320-71-1066,
dated December 1, 2016, specify to do a ``Modification of the FWD
Engine Mount Assembly on Engine 1 and Engine 2,'' the Accomplishment
Instructions of Airbus Service Bulletin A320-71-1065, Revision 01,
dated July 28, 2017, specify to do inspections and applicable
corrective actions. Therefore, we have changed paragraph (j) of this AD
to replace ``modify'' with ``modify, including doing all applicable
inspections and corrective actions.''
Request To Include Goodrich Aerospace Service Bulletin for the Required
Modification
Lufthansa requested that we include Goodrich Aerospace Service
Bulletin
[[Page 26562]]
RA32071-159 in paragraph (j) of the proposed AD to ``make it more
clear.''
We do not agree. The commenter provided no explanation of what is
unclear in paragraph (j) or how adding the Goodrich Aerospace service
bulletin will clarify the requirements of paragraph (j). Therefore, we
have not changed this AD in this regard.
Requests To Provide Credit for Previous Actions Done Using Other
Service Information
Delta and Lufthansa asked that the proposed AD include credit for
doing previous actions by accomplishing Goodrich Aerospace Service
Bulletin RA32071-159; Repair 10 of CMM 71-21-08, Revision 47 (and
later); or Repair 21 of CMM 71-21-06, Revision 59 (and later). Delta
stated that paragraph (l) of the proposed AD includes credit for
previous actions only for compliance with Airbus Service Bulletin A320-
71-1065, Revision 01, dated July 28, 2017. Delta asserted that the
intent of the proposed AD is met by the accomplishment of Goodrich
Aerospace Service Bulletin RA32071-159; Repair 10 of CMM 71-21-08,
Revision 47 (and later); or Repair 21 of CMM 71-21-06, Revision 59 (and
later); due to the correction of the inspection and repair
requirements.
We do not agree with the commenter's request. Goodrich Aerospace
Service Bulletin RA32071-159 is referenced in the airplane level Airbus
service information as a secondary document; therefore, it is not an
alternate for the instructions in the airplane level service
information. All of the steps in paragraph 3.C. of Airbus Service
Bulletin A320-71-1065, Revision 01, dated July 28, 2017, are required
for compliance and must be done to comply with this AD. If not done
before the effective date of this AD, paragraph (f) of this AD states
that you must comply with the actions in the AD, ``unless already
done.''
Regarding future revisions of CMM repairs, we may not refer to any
document that does not yet exist. To allow operators to use later
revisions of a required document (issued after publication of the AD),
either we must revise the AD to reference specific later revisions, or
operators must request approval to use later revisions as an
alternative method of compliance with the requirements of an AD under
the provisions of the AMOC paragraph of the AD. However, as explained
previously, the identified CMM repairs are not required for
accomplishment of any action in this AD; therefore, no change to this
AD is necessary in this regard.
Request To Change Parts Installation Prohibition
Delta asked that paragraph (m) of the proposed AD, ``Parts
Installation Prohibition,'' be changed to permit the same allowance to
install an affected main beam onto an aircraft equipped with an
affected forward engine mount assembly within the compliance windows
defined in paragraph (j) of the proposed AD. Delta stated that
paragraph (m) of the proposed AD prohibits the installation of an
affected main beam on any airplane after the effective date of the AD.
Delta further points out that the parallel EASA AD 2017-0132R1, dated
November 22, 2017, permits the installation of an affected main beam
onto an aircraft equipped with an affected forward engine mount
assembly within the compliance times defined in paragraph (j) of the
proposed AD.
We agree with the commenter's request. After the NPRM was issued,
EASA issued AD 2017-0132R1, dated November 22, 2017, which revised its
parts installation requirement. We have revised paragraph (m) of this
AD to match the EASA AD. In addition, we have revised this AD to refer
to EASA AD 2017-0132R1, dated November 22, 2017.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously, with minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-71-1065, Revision 01, dated
July 28, 2017. This service information describes procedures for
modifying the main beam assembly of the forward engine mount. The
modification includes, among other things, repair or replacement of the
main beam assembly.
Airbus has also issued Service Bulletin A320-71-1066, dated
December 1, 2016. This service information describes procedures for
modifying the main beam assembly of the forward engine mount. The
modification includes, among other things, rework of the main beam
assembly.
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.
Costs of Compliance
We estimate that this AD affects 500 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Modification.................. Up to 76 work-hours $778 Up to $7,238........ Up to $3,619,000.
x $85 per hour =
$6,460.
----------------------------------------------------------------------------------------------------------------
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.
[[Page 26563]]
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 AD will not have federalism implications
under Executive Order 13132. This AD will 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 that this AD:
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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2018-12-02 Airbus: Amendment 39-19306; Docket No. FAA-2017-1020;
Product Identifier 2017-NM-114-AD.
(a) Effective Date
This AD is effective July 13, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A318-111 and -112 airplanes;
Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-
211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211,
-212, and -213 airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by a review of maintenance instructions for
a blend repair of the diameter of the snout of the main beam
assembly of the forward engine mount that would create an excessive
gap between the bearing mono-ball and the snout. We are issuing this
AD to prevent in-flight failure of a forward engine mount, and
consequent detachment of an engine, which could result in reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definition of Affected Parts
For the purposes of this AD: An ``affected main beam'' is any
main beam assembly of the forward engine mount, part number (P/N)
642-2006-501 or P/N 642-2006-503, identified in paragraph (g)(1) or
(g)(2) of this AD.
(1) Any part for which no maintenance records are available to
confirm the part has never been repaired.
(2) Any part that was repaired as specified in Repair 10, of
Goodrich Aerospace Component Maintenance Manual (CMM) 71-21-08,
Revisions 1 through 46, except for parts identified in paragraphs
(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD.
(i) Any part on which a qualifying inspection identified in
paragraph (h) of this AD has been done and there were no findings
(the inspection was passed).
(ii) Any part on which a qualifying inspection identified in
paragraph (h) of this AD has been done and that part has been
repaired as specified in Goodrich Aerospace Service Bulletin
RA32071-159.
(iii) Any part that has been repaired in accordance with other
instructions approved by the Manager, International Section,
Transport Standards Branch, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(h) Definition of Qualifying Inspection
For the purposes of this AD: ``A qualifying inspection'' is an
inspection done as specified in Goodrich Aerospace Service Bulletin
RA32071-159; or for CFM56-5B engines, an inspection done as
specified in Repair 10 of Goodrich Aerospace CMM 71-21-08, Revision
47; or for CFM56-5A engines, an inspection done as specified in
Repair 21 of Goodrich Aerospace CMM 71-21-06, Revision 59.
(i) Definition of Airplane Groups
For the purposes of this AD: ``Group 1 airplanes'' are airplanes
on which an affected main beam has been installed as of the
effective date of this AD. ``Group 2 airplanes'' are airplanes on
which an affected main beam has not been installed as of the
effective date of this AD; this includes airplanes with an original
certificate of airworthiness or original export certificate of
airworthiness that was issued after the effective date of this AD.
(j) Modification of Affected Main Beam Assemblies
For Group 1 airplanes as identified in paragraph (i) of this AD:
At the earliest of the compliance times specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, modify, including doing all
applicable inspections and corrective actions, for each affected
main beam identified in paragraph (g) of this AD, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-71-
1065, Revision 01, dated July 28, 2017; or Airbus Service Bulletin
A320-71-1066, dated December 1, 2016; as applicable; except as
required by paragraph (k) of this AD.
(1) Within 48 months after the effective date of this AD.
(2) Within 10,000 flight cycles after the effective date of this
AD.
(3) Within 15,000 flight hours after the effective date of this
AD.
(k) Exception to Service Information
Where Airbus Service Bulletin A320-71-1065, Revision 01, dated
July 28, 2017, specifies to contact a manufacturer for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (n)(2) of this
AD.
(l) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (j) of this AD involving Airbus Service Bulletin A320-71-
1065, Revision 01, dated July 28, 2017, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A320-71-1065, dated December 1, 2016.
(m) Parts Installation Prohibition
Do not install on any airplane an affected main beam or a
forward engine mount assembly equipped with an affected main beam,
as specified in paragraph (m)(1) or (m)(2) of this AD, as
applicable.
(1) For Group 1 airplanes: After modification of the airplane as
required by paragraph (j) of this AD.
(2) For Group 2 airplanes: As of the effective date of this AD.
(n) 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
[[Page 26564]]
directly to the manager of the International Section, send it to the
attention of the person identified in paragraph (o)(2) of this AD.
Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (k) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0132R1, dated November 22, 2017, for related
information. This MCAI may be found in the AD docket on the internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2017-1020.
(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 98198-6547;
telephone 425-227-1405; fax 425-227-1149.
(3) Airbus service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(4) and (p)(5) of this AD.
(4) Goodrich service information identified in this AD that is
not incorporated by reference is available at Goodrich Corporation,
Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone:
619-691-2719; email: [email protected]; internet: https://www.goodrich.com/TechPubs.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-71-1065, Revision 01, dated
July 28, 2017.
(ii) Airbus Service Bulletin A320-71-1066, dated December 1,
2016.
(3) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office-EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 44 51; email: [email protected];
internet: https://www.airbus.com.
(4) For Goodrich service information identified in this final
rule, contact Goodrich Corporation, Aerostructures, 850 Lagoon
Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email:
[email protected]; internet: https://www.goodrich.com/TechPubs.
(5) 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.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on May 29, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-12268 Filed 6-7-18; 8:45 am]
BILLING CODE 4910-13-P
