Airworthiness Directives; Airbus Airplanes, 10411-10415 [2018-04727]
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Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules
paragraph (g) of this AD and all applicable
corrective actions required by paragraph (h)
of this AD, check the bolt preload, and do all
applicable corrective actions, in accordance
with paragraph 3.B., ‘‘Procedure,’’ of the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A84–55–04, Revision
C, dated May 3, 2016. Do all applicable
corrective actions before further flight.
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
this paragraph.
(j) Retained Repetitive Inspection Interval,
With New Terminating Action
This paragraph restates the requirements of
paragraph (j) of AD 2016–24–03, with new
terminating action. Repeat the inspection and
preload check required by paragraphs (g) and
(i) of this AD at intervals not to exceed 3,600
flight hours or 18 months, whichever occurs
first, except as provided by paragraph (k) of
this AD. Accomplishment of the actions
required by paragraphs (l) and (m) of this AD,
as applicable, terminates the requirements of
this paragraph.
(k) Retained Optional Barrel Nut
Replacement, With New Service Information
This paragraph restates the provisions of
paragraph (k) of AD 2016–24–03, with new
service information. Inspection and
replacement of all barrel nuts at the
horizontal-stabilizer-to-vertical-stabilizer
attachment joints, in accordance with
paragraph 3.B., ‘‘Procedure,’’ of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–55–08, Revision A, dated
August 2, 2017, extends the next inspection
required by paragraph (j) of this AD to within
6,000 flight hours or 36 months, whichever
occurs first, after accomplishing the
replacement.
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(l) New Requirement of This AD: Sealing
Disk Installation
Within 8,000 flight hours or 48 months,
whichever occurs first, after the effective date
of this AD, install a sealing disk at the midspar location of the vertical stabilizer in
accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–06, dated January 31, 2017.
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
paragraphs (h), (i), and (j) of this AD.
(m) New Requirement of This AD:
Replacement of DSC228 Series Barrel Nuts
For Bombardier, Inc., Model DHC–8–400,
–401 and –402 airplanes, serial numbers
4001 through 4524 inclusive: Within 8,000
flight hours or 48 months, whichever occurs
first, after the effective date of this AD,
replace all DSC228 series barrel nuts at the
horizontal-stabilizer-to-vertical-stabilizer
attachment joints with B0203073 series barrel
nuts in accordance with paragraph 3.B.,
‘‘Procedure,’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
84–55–08, Revision A, dated August 2, 2017.
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
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applicable, terminates the requirements of
paragraphs (h), (i), and (j) of this AD.
(n) Parts Installation Prohibition
After modification of an airplane as
required by paragraphs (l) and (m) of this AD,
no person may install a DSC228 series barrel
nut at the horizontal-stabilizer-to-verticalstabilizer attachment joint on the modified
airplane.
(o) Terminating Actions
Accomplishment of the actions required by
paragraphs (l) and (m) of this AD, as
applicable, terminates the requirements of
paragraphs (h), (i), and (j) of this AD.
(p) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraphs (g)(1), (g)(2),
(h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), (h)(3), (h)(4),
(i), and (k) of this AD, if those actions were
performed before the effective date of this AD
using the service information identified in
paragraphs (p)(1)(i) through (p)(1)(iii) of this
AD.
(i) Bombardier Alert Service Bulletin A84–
55–04, dated May 21, 2015, which is not
incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84–
55–04, Revision A, dated June 2, 2015, which
is not incorporated by reference in this AD.
(iii) Bombardier Alert Service Bulletin
A84–55–04, Revision B, dated July 30, 2015,
which is not incorporated by reference in this
AD.
(2) This paragraph provides credit for
actions required by paragraphs (h)(1),
(h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this AD,
if those actions were performed before the
effective date of this AD using the service
information identified in paragraphs (p)(2)(i)
and (p)(2)(ii) of this AD.
(i) Bombardier Service Bulletin 84–55–08,
dated January 27, 2017, which is not
incorporated by reference in this AD.
(ii) Bombardier Alert Service Bulletin A84–
55–04, Revision C, dated May 3, 2016, which
was incorporated by reference in AD 2016–
24–03.
(q) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to ATTN: Program Manager,
Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531.
(i) 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.
(ii) AMOCs approved previously for AD
2016–24–03 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
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10411
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO Branch,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) TCCA
Airworthiness Directive CF–2015–13R1,
dated June 26, 2017, for related information.
This MCAI may be found in the AD docket
on the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0160.
(2) For more information about this AD,
contact Aziz Ahmed, Aerospace Engineer,
Airframe and Mechanical Systems Section,
FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7329; fax 516–794–5531.
(3) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
internet https://www.bombardier.com. You
may view this service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
Issued in Renton, Washington, on March 2,
2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–04720 Filed 3–8–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0165; Product
Identifier 2017–NM–122–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for 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 proposed AD
was prompted by a report of a
production quality deficiency on the
SUMMARY:
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Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules
inner retainer installed on link
assemblies of the aft engine mount,
which could result in failure of the
retainer. This proposed AD would
require modifying and re-identifying the
aft engine mount assemblies. We are
proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by April 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 Airbus service information
identified in this NPRM, 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.airworth-eas@airbus.com;
internet https://www.airbus.com.
For Goodrich Aerospace service
information identified in this NPRM,
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 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.
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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–
0165; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
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International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone 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–
2018–0165; Product Identifier 2017–
NM–122–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM based
on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0251, dated December
15, 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:
During in-service inspections, several aft
engine mount inner retainers, fitted on
aeroplanes equipped with CFM56–5A/5B
engines, were found broken. Investigation
identified that the main cause of crack
initiation was the vibration dynamic effect
that affects the retainers, and that the ‘‘dull’’
surface finish pitting is an aggravating factor
when compared with the ‘‘bright’’ surface
finishing.
This condition, if not detected and
corrected, could lead to in-flight loss of an aft
engine mount link, possibly resulting in
damage to the aeroplane and/or injury to
persons on the ground.
To address this potential unsafe condition,
Airbus issued Alert Operators Transmission
(AOT) A71N001–12 (later revised) and EASA
issued AD 2013–0050 [which corresponds to
FAA AD 2014–14–06, Amendment 39–17901
(79 FR 42655, July 23, 2014)], later
superseded by EASA AD 2015–0021 [which
corresponds to FAA AD 2016–14–09,
Amendment 39–18590 (81 FR 44989, July 12,
2016) (‘‘AD 2016–14–09’’)], requiring
repetitive detailed inspections (DET) of all aft
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engine mount inner retainers and, depending
on findings, their replacement.
After EASA AD 2015–0021 was issued, a
production quality deficiency was identified
by Airbus and Goodrich Aerostructures, the
engine mount retainer manufacturer, on the
inner retainer, Part Number (P/N) 238–0252–
505, installed in the three link assemblies of
the engine mount fitted on CFM56–5A/5B
engines. Airbus issued AOT A71N011–15
and Service Bulletin (SB) A320–71–1070,
providing a list of affected parts and
applicable corrective actions.
Consequently, EASA issued AD 2016–0010
(later revised), retaining the requirements of
EASA AD 2015–0021, which was
superseded, and in addition requiring the
identification and replacement of all nonconforming aft engine mount inner retainers
[EASA AD 2016–0010 R1 corresponds to
FAA AD 2017–04–10, Amendment 39–18805
(82 FR 11791, February 27, 2017) (‘‘AD 2017–
04–10’’)].
After that [EASA] AD was issued, a new
engine mount retainer was developed by
Goodrich Aerostructures to improve the
retainer efficiency. For retrofit purposes,
Goodrich Aerostructures issued SB
RA32071–164, and Airbus issued SB A320–
71–1071, providing instructions to modify
and re-identify the engine mount assemblies
as instructed in the Goodrich Aerostructures
SB. Subsequently, it was observed that, on
aeroplanes equipped with certain engines
fitted with a Turbine Rear Frame (TRF) with
4 lugs configuration, the installation of the
new engine mount retainers can lead to
interference, and Goodrich Aerostructures
revised SB RA32071–164, providing
instructions not to install the new engine
retainers on affected engines. Airbus SB
A320–71–1071 is expected to be revised
accordingly. For engines fitted with a TRF
with 4 lugs, a new installation (potentially
requiring different engine mount retainers) is
being developed by Goodrich Aerospace and
Airbus.
Consequently, EASA issued AD 2017–
0138, retaining the requirements of EASA AD
2016–0010R1, which was superseded, and,
except for aeroplanes equipped with engines
fitted with a TRF with 4 lugs configuration,
requiring modification and identification of
aft engine mount assemblies as terminating
action for the repetitive inspections of the
retainers. That [EASA] AD also included
additional instructions applicable to
installation of engines fitted with a TRF with
4 lugs configuration.
Since EASA AD 2017–0138 was issued, it
was determined that installation of new
engine mount assemblies must not be
allowed for some specific engine
configurations, and that installation of
Goodrich Aerostructures SB RA32071–164
alone can be referred to, in order to
accomplish the terminating action as
required by that [EASA] AD.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2017–0138, which is superseded, adds
reference to Goodrich Aerostructures SB
RA32071–164 * * *, and introduces new
requirement for aeroplanes equipped with
engines fitted with a TRF with 4 lugs
configuration.
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This NPRM would not supersede AD
2017–04–10. Rather, we have
determined that a stand-alone AD
would be more appropriate to address
the changes in the MCAI. This NPRM
would require modifying and reidentifying the aft engine mount
assemblies. Accomplishment of the
proposed actions would then terminate
the repetitive detailed inspections
required by paragraph (l) of AD 2016–
14–09, and serve as a method of
compliance for the requirements of
paragraph (g) of AD 2017–04–10. 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–
0165.
Related Service Information Under 1
CFR Part 51
FAA’s Determination and Requirements
of This Proposed AD
Airbus has issued Service Bulletin
A320–71–1071, dated November 8,
2016. Goodrich Aerostructures has
issued Service Bulletin RA32071–164,
Revision 1, dated July 19, 2017. The
service information describes
procedures for modifying and reidentifying the aft engine mount retainer
assembly. These documents are distinct
since they apply to different airplane
models in different configurations.
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.
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 500 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Modification and re-identification ....................
20 work-hours × $85 per hour = $1,700 ........
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Authority for This Rulemaking
Regulatory Findings
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.
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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Cost per
product
$3,152
Cost on U.S.
operators
$4,852
$2,426,000
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2018–0165; Product
Identifier 2017–NM–122–AD.
(a) Comments Due Date
We must receive comments by April 23,
2018.
(b) Affected ADs
This AD affects AD 2016–14–09,
Amendment 39–18590 (81 FR 44989, July 12,
2016) (‘‘AD 2016–14–09’’); and AD 2017–04–
10, Amendment 39–18805 (82 FR 11791,
February 27, 2017) (‘‘AD 2017–04–10’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Model A318–111 and –112 airplanes.
(2) Model A319–111, –112, –113, –114, and
–115 airplanes.
(3) Model A320–211, –212, –214, and –216
airplanes.
(4) Model A321–111, –112, –211, –212, and
–213 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
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(e) Reason
This AD was prompted by a report of a
production quality deficiency on the inner
retainer installed on link assemblies of the aft
engine mount, which could result in failure
of the retainer. We are issuing this AD to
address non-conforming retainers of the aft
engine mount. This condition could result in
loss of the locking feature of the nuts of the
inner and outer pins; loss of the pins will
result in the aft mount engine link no longer
being secured to the aft engine mount,
possibly resulting in damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definitions
(1) For the purpose of this AD: A Group 1
airplane has an aft engine mount assembly
installed, having a part number (P/N)
identified as ‘‘Old P/N’’ in figure 1 to
paragraphs (g), (h), (i), (j), (k), and (l) of this
AD. A Group 2 airplane does not have any
aft engine mount assembly installed having
a part number identified as ‘‘Old P/N’’ in
figure 1 to paragraphs (g), (h), (i), (j), (k), and
(l) of this AD.
(2) For the purpose of this AD, a 4-lugs
engine is a CFM56–5A1, CFM56–5A3,
CFM56–5A4, CFM56–5A4/F, CFM56–5A5, or
CFM56–5A5/F engine, fitted with a turbine
rear frame (TRF) having a part number as
identified in figure 2 to paragraph (g) of this
AD.
FIGURE 1 TO PARAGRAPHS (g), (h), (i),
(j), (k), AND (l) OF THIS AD—PART
RE-IDENTIFICATION
Old P/N
New P/N
238–0230–11 .....................
238–0230–15 .....................
238–0230–5 .......................
642–2300–3 .......................
238M0230–11
238M0230–15
238M0230–5
642–2300–11
FIGURE 2 TO PARAGRAPH (g) OF THIS
AD—TRF WITH 4-LUGS CONFIGURATION
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Part No.
336–031–615–0
336–031–617–0
336–031–618–0
336–031–621–0
336–031–650–0
336–031–651–0
336–031–652–0
336–031–653–0
336–031–660–0
336–031–661–0
336–031–662–0
336–031–663–0
336–031–670–0
336–031–671–0
336–031–672–0
336–031–673–0
336–031–640–0
336–031–642–0
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(h) Modification
For Group 1 airplanes: Within 48 months
after the effective date of this AD, except for
4-lugs engines, modify the aft engine mount
assembly, having a part number identified as
‘‘Old P/N’’ in figure 1 to paragraphs (g), (h),
(i), (j), (k), and (l) of this AD, and re-identify
it with the corresponding part number
identified as ‘‘New P/N’’ in figure 1 to
paragraphs (g), (h), (i), (j), (k), and (l) of this
AD, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
71–1071, dated November 8, 2016; or
Goodrich Aerostructures Service Bulletin
RA32071–164, Revision 1, dated July 19,
2017.
(i) Other Acceptable Method of Compliance
Replacement on an airplane of each aft
engine mount assembly, identified as ‘‘Old
P/N’’ in figure 1 to paragraphs (g), (h), (i), (j),
(k), and (l) of this AD, with a corresponding
aft engine mount assembly, identified as
‘‘New P/N’’ in figure 1 to paragraphs (g), (h),
(i), (j), (k), and (l) of this AD, is an acceptable
method to comply with the requirements of
paragraph (h) of this AD for that airplane.
(j) Identification of Certain Airplanes That
Do Not Have Affected Parts
An airplane on which Airbus modification
158435 has been embodied in production
and on which it can be positively determined
that no aft engine mount assembly, identified
as ‘‘Old P/N’’ in figure 1 to paragraphs (g),
(h), (i), (j), (k), and (l) of this AD, is installed,
is considered a Group 2 airplane. A review
of airplane maintenance records is acceptable
to make this determination, if it can be
conclusively determined that no aft engine
mount assembly identified as ‘‘Old P/N’’ in
figure 1 to paragraphs (g), (h), (i), (j), (k), and
(l) of this AD is installed. Group 2 airplanes
are not affected by the requirements of
paragraph (h) of this AD.
(k) Parts Installation Prohibition
(1) For Group 1 airplanes: Do not install an
aft engine mount assembly identified as ‘‘Old
P/N’’ in figure 1 to paragraphs (g), (h), (i), (j),
(k), and (l) of this AD on any airplane after
modification of the airplane as required by
paragraph (h) of this AD, or after any
replacement specified in paragraph (i) of this
AD.
(2) For Group 2 airplanes: As of the
effective date of this AD, do not install an aft
engine mount assembly identified as ‘‘Old
P/N’’ in figure 1 to paragraphs (g), (h), (i), (j),
(k), and (l) of this AD on any airplane.
(3) For airplanes equipped with a 4-lugs
engine (left-hand (LH) or right-hand (RH)
side): As of the effective date of this AD, do
not modify any aft engine mount assembly
identified as ‘‘Old P/N’’ in figure 1 to
paragraphs (g), (h), (i), (j), (k), and (l) of this
AD, as required by paragraph (h) of this AD,
and do not install on an affected engine
pylon (LH or RH) any aft engine mount
assembly identified as ‘‘New P/N’’ in figure
1 to paragraphs (g), (h), (i), (j), (k), and (l) of
this AD.
(l) 4-Lugs Engine Installation
(1) From the effective date of this AD, it is
allowed to install or reinstall a 4-lugs engine
Jkt 244001
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Frm 00008
Fmt 4702
Sfmt 4702
on an airplane (LH or RH) provided that the
airplane is equipped with an aft engine
mount assembly identified as ‘‘Old P/N’’ in
figure 1 to paragraphs (g), (h), (i), (j), (k), and
(l) of this AD on the affected engine pylon
(LH or RH).
(2) For airplanes equipped with a 4-lugs
engine (LH or RH), and on which, prior to the
effective date of this AD, an aft engine mount
assembly identified as ‘‘New P/N’’ in figure
1 to paragraphs (g), (h), (i), (j), (k), and (l) of
this AD has been installed on the affected
engine pylon (LH or RH), or on which the aft
engine part assembly has been modified as
specified in paragraph (h) of this AD: Within
30 days after the effective date of this AD,
obtain repair instructions using a method
approved by the Manager, International
Section, Transport Standards Branch, FAA;
or the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA), and
accomplish those instructions accordingly. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(m) Terminating Action and Method of
Compliance
(1) Modification of an airplane as required
by paragraph (h) of this AD, or as specified
in paragraph (i) of this AD, constitutes
terminating action for the repetitive detailed
inspections required by paragraph (l) of AD
2016–14–09 for that airplane.
(2) Modification of an airplane as required
by paragraph (h) of this AD, or as specified
in paragraph (i) of this AD, is a method of
compliance with the requirements of
paragraph (g) of AD 2017–04–10 for that
airplane.
(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
directly to the International Section, send it
to the attention of the person identified in
paragraph (p)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
E:\FR\FM\09MRP1.SGM
09MRP1
Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules
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.
DEPARTMENT OF TRANSPORTATION
(o) Special Flight Permits
AGENCY:
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2017–0251 dated
December 15, 2017, for related information.
This MCAI may be found in the AD docket
on the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0165.
(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; telephone and fax 206–
231–3223.
(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.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) For Goodrich Aerospace service
information identified in this AD, 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 service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
Issued in Renton, Washington, on March 5,
2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–04727 Filed 3–8–18; 8:45 am]
amozie on DSK30RV082PROD with PROPOSALS
BILLING CODE 4910–13–P
VerDate Sep<11>2014
15:54 Mar 08, 2018
Jkt 244001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0161; Product
Identifier 2017–NM–088–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to supersede
Airworthiness Directive (AD) 2013–11–
12, which applies to certain
Bombardier, Inc., Model BD–100–1A10
airplanes. AD 2013–11–12 requires
inspecting for the correct serial number
of a certain hydraulic system
accumulator, and replacing affected
hydraulic system accumulators with
new or serviceable accumulators. Since
we issued AD 2013–11–12, we have
determined that certain other hydraulic
system accumulators must be modified
or replaced and life limits must be
added. This proposed AD would expand
the applicability and require modifying
or replacing certain hydraulic brake
system accumulators. This proposed AD
would also require revising the
maintenance or inspection program to
add life limits for the accumulators. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by April 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 NPRM, contact Bombardier, Inc.,
ˆ
400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401; email
thd.crj@aero.bombardier.com; internet
https://www.bombardier.com. You may
view this referenced service information
at the FAA, Transport Standards
SUMMARY:
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
10415
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–
0161; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7318; fax 516–794–5531.
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–
2018–0161; Product Identifier 2017–
NM–088–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We issued AD 2013–11–12,
Amendment 39–17472 (78 FR 33206,
June 4, 2013) (‘‘AD 2013–11–12’’), for
certain Bombardier, Inc., Model BD–
100–1A10 airplanes. AD 2013–11–12
requires inspecting for the correct serial
number of a certain hydraulic system
accumulator, and replacing affected
hydraulic system accumulators with
new or serviceable accumulators. AD
2013–11–12 resulted from reports of
failure of a screw cap or end cap of the
hydraulic system accumulator while on
the ground, which resulted in loss of
E:\FR\FM\09MRP1.SGM
09MRP1
]]>Agencies
[Federal Register Volume 83, Number 47 (Friday, March 9, 2018)]
[Proposed Rules]
[Pages 10411-10415]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-04727]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0165; Product Identifier 2017-NM-122-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for 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 proposed AD was prompted by a report of a production quality
deficiency on the
[[Page 10412]]
inner retainer installed on link assemblies of the aft engine mount,
which could result in failure of the retainer. This proposed AD would
require modifying and re-identifying the aft engine mount assemblies.
We are proposing this AD to address the unsafe condition on these
products.
DATES: We must receive comments on this proposed AD by April 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 Airbus service information identified in this NPRM, 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 Aerospace service information identified in this NPRM,
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 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-
0165; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this NPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Operations
office (telephone 800-647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone 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-2018-0165;
Product Identifier 2017-NM-122-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM based on
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this NPRM.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0251, dated December 15, 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:
During in-service inspections, several aft engine mount inner
retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines,
were found broken. Investigation identified that the main cause of
crack initiation was the vibration dynamic effect that affects the
retainers, and that the ``dull'' surface finish pitting is an
aggravating factor when compared with the ``bright'' surface
finishing.
This condition, if not detected and corrected, could lead to in-
flight loss of an aft engine mount link, possibly resulting in
damage to the aeroplane and/or injury to persons on the ground.
To address this potential unsafe condition, Airbus issued Alert
Operators Transmission (AOT) A71N001-12 (later revised) and EASA
issued AD 2013-0050 [which corresponds to FAA AD 2014-14-06,
Amendment 39-17901 (79 FR 42655, July 23, 2014)], later superseded
by EASA AD 2015-0021 [which corresponds to FAA AD 2016-14-09,
Amendment 39-18590 (81 FR 44989, July 12, 2016) (``AD 2016-14-
09'')], requiring repetitive detailed inspections (DET) of all aft
engine mount inner retainers and, depending on findings, their
replacement.
After EASA AD 2015-0021 was issued, a production quality
deficiency was identified by Airbus and Goodrich Aerostructures, the
engine mount retainer manufacturer, on the inner retainer, Part
Number (P/N) 238-0252-505, installed in the three link assemblies of
the engine mount fitted on CFM56-5A/5B engines. Airbus issued AOT
A71N011-15 and Service Bulletin (SB) A320-71-1070, providing a list
of affected parts and applicable corrective actions.
Consequently, EASA issued AD 2016-0010 (later revised),
retaining the requirements of EASA AD 2015-0021, which was
superseded, and in addition requiring the identification and
replacement of all non-conforming aft engine mount inner retainers
[EASA AD 2016-0010 R1 corresponds to FAA AD 2017-04-10, Amendment
39-18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'')].
After that [EASA] AD was issued, a new engine mount retainer was
developed by Goodrich Aerostructures to improve the retainer
efficiency. For retrofit purposes, Goodrich Aerostructures issued SB
RA32071-164, and Airbus issued SB A320-71-1071, providing
instructions to modify and re-identify the engine mount assemblies
as instructed in the Goodrich Aerostructures SB. Subsequently, it
was observed that, on aeroplanes equipped with certain engines
fitted with a Turbine Rear Frame (TRF) with 4 lugs configuration,
the installation of the new engine mount retainers can lead to
interference, and Goodrich Aerostructures revised SB RA32071-164,
providing instructions not to install the new engine retainers on
affected engines. Airbus SB A320-71-1071 is expected to be revised
accordingly. For engines fitted with a TRF with 4 lugs, a new
installation (potentially requiring different engine mount
retainers) is being developed by Goodrich Aerospace and Airbus.
Consequently, EASA issued AD 2017-0138, retaining the
requirements of EASA AD 2016-0010R1, which was superseded, and,
except for aeroplanes equipped with engines fitted with a TRF with 4
lugs configuration, requiring modification and identification of aft
engine mount assemblies as terminating action for the repetitive
inspections of the retainers. That [EASA] AD also included
additional instructions applicable to installation of engines fitted
with a TRF with 4 lugs configuration.
Since EASA AD 2017-0138 was issued, it was determined that
installation of new engine mount assemblies must not be allowed for
some specific engine configurations, and that installation of
Goodrich Aerostructures SB RA32071-164 alone can be referred to, in
order to accomplish the terminating action as required by that
[EASA] AD.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2017-0138, which is superseded, adds
reference to Goodrich Aerostructures SB RA32071-164 * * *, and
introduces new requirement for aeroplanes equipped with engines
fitted with a TRF with 4 lugs configuration.
[[Page 10413]]
This NPRM would not supersede AD 2017-04-10. Rather, we have
determined that a stand-alone AD would be more appropriate to address
the changes in the MCAI. This NPRM would require modifying and re-
identifying the aft engine mount assemblies. Accomplishment of the
proposed actions would then terminate the repetitive detailed
inspections required by paragraph (l) of AD 2016-14-09, and serve as a
method of compliance for the requirements of paragraph (g) of AD 2017-
04-10. 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-2018-0165.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-71-1071, dated November 8,
2016. Goodrich Aerostructures has issued Service Bulletin RA32071-164,
Revision 1, dated July 19, 2017. The service information describes
procedures for modifying and re-identifying the aft engine mount
retainer assembly. These documents are distinct since they apply to
different airplane models in different configurations.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 500 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Modification and re-identification. 20 work-hours x $85 per $3,152 $4,852 $2,426,000
hour = $1,700.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2018-0165; Product Identifier 2017-NM-122-AD.
(a) Comments Due Date
We must receive comments by April 23, 2018.
(b) Affected ADs
This AD affects AD 2016-14-09, Amendment 39-18590 (81 FR 44989,
July 12, 2016) (``AD 2016-14-09''); and AD 2017-04-10, Amendment 39-
18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Model A318-111 and -112 airplanes.
(2) Model A319-111, -112, -113, -114, and -115 airplanes.
(3) Model A320-211, -212, -214, and -216 airplanes.
(4) Model A321-111, -112, -211, -212, and -213 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
[[Page 10414]]
(e) Reason
This AD was prompted by a report of a production quality
deficiency on the inner retainer installed on link assemblies of the
aft engine mount, which could result in failure of the retainer. We
are issuing this AD to address non-conforming retainers of the aft
engine mount. This condition could result in loss of the locking
feature of the nuts of the inner and outer pins; loss of the pins
will result in the aft mount engine link no longer being secured to
the aft engine mount, possibly resulting in damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
(1) For the purpose of this AD: A Group 1 airplane has an aft
engine mount assembly installed, having a part number (P/N)
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i),
(j), (k), and (l) of this AD. A Group 2 airplane does not have any
aft engine mount assembly installed having a part number identified
as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k),
and (l) of this AD.
(2) For the purpose of this AD, a 4-lugs engine is a CFM56-5A1,
CFM56-5A3, CFM56-5A4, CFM56-5A4/F, CFM56-5A5, or CFM56-5A5/F engine,
fitted with a turbine rear frame (TRF) having a part number as
identified in figure 2 to paragraph (g) of this AD.
Figure 1 to Paragraphs (g), (h), (i), (j), (k), and (l) of this AD--Part
Re-Identification
------------------------------------------------------------------------
Old P/N New P/N
------------------------------------------------------------------------
238-0230-11............................ 238M0230-11
238-0230-15............................ 238M0230-15
238-0230-5............................. 238M0230-5
642-2300-3............................. 642-2300-11
------------------------------------------------------------------------
Figure 2 to Paragraph (g) of This AD--TRF With 4-Lugs Configuration
------------------------------------------------------------------------
Part No.
-------------------------------------------------------------------------
336-031-615-0
336-031-617-0
336-031-618-0
336-031-621-0
336-031-650-0
336-031-651-0
336-031-652-0
336-031-653-0
336-031-660-0
336-031-661-0
336-031-662-0
336-031-663-0
336-031-670-0
336-031-671-0
336-031-672-0
336-031-673-0
336-031-640-0
336-031-642-0
------------------------------------------------------------------------
(h) Modification
For Group 1 airplanes: Within 48 months after the effective date
of this AD, except for 4-lugs engines, modify the aft engine mount
assembly, having a part number identified as ``Old P/N'' in figure 1
to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, and re-
identify it with the corresponding part number identified as ``New
P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of
this AD, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-71-1071, dated November 8, 2016; or
Goodrich Aerostructures Service Bulletin RA32071-164, Revision 1,
dated July 19, 2017.
(i) Other Acceptable Method of Compliance
Replacement on an airplane of each aft engine mount assembly,
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i),
(j), (k), and (l) of this AD, with a corresponding aft engine mount
assembly, identified as ``New P/N'' in figure 1 to paragraphs (g),
(h), (i), (j), (k), and (l) of this AD, is an acceptable method to
comply with the requirements of paragraph (h) of this AD for that
airplane.
(j) Identification of Certain Airplanes That Do Not Have Affected Parts
An airplane on which Airbus modification 158435 has been
embodied in production and on which it can be positively determined
that no aft engine mount assembly, identified as ``Old P/N'' in
figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD,
is installed, is considered a Group 2 airplane. A review of airplane
maintenance records is acceptable to make this determination, if it
can be conclusively determined that no aft engine mount assembly
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i),
(j), (k), and (l) of this AD is installed. Group 2 airplanes are not
affected by the requirements of paragraph (h) of this AD.
(k) Parts Installation Prohibition
(1) For Group 1 airplanes: Do not install an aft engine mount
assembly identified as ``Old P/N'' in figure 1 to paragraphs (g),
(h), (i), (j), (k), and (l) of this AD on any airplane after
modification of the airplane as required by paragraph (h) of this
AD, or after any replacement specified in paragraph (i) of this AD.
(2) For Group 2 airplanes: As of the effective date of this AD,
do not install an aft engine mount assembly identified as ``Old P/
N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of
this AD on any airplane.
(3) For airplanes equipped with a 4-lugs engine (left-hand (LH)
or right-hand (RH) side): As of the effective date of this AD, do
not modify any aft engine mount assembly identified as ``Old P/N''
in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this
AD, as required by paragraph (h) of this AD, and do not install on
an affected engine pylon (LH or RH) any aft engine mount assembly
identified as ``New P/N'' in figure 1 to paragraphs (g), (h), (i),
(j), (k), and (l) of this AD.
(l) 4-Lugs Engine Installation
(1) From the effective date of this AD, it is allowed to install
or reinstall a 4-lugs engine on an airplane (LH or RH) provided that
the airplane is equipped with an aft engine mount assembly
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i),
(j), (k), and (l) of this AD on the affected engine pylon (LH or
RH).
(2) For airplanes equipped with a 4-lugs engine (LH or RH), and
on which, prior to the effective date of this AD, an aft engine
mount assembly identified as ``New P/N'' in figure 1 to paragraphs
(g), (h), (i), (j), (k), and (l) of this AD has been installed on
the affected engine pylon (LH or RH), or on which the aft engine
part assembly has been modified as specified in paragraph (h) of
this AD: Within 30 days after the effective date of this AD, obtain
repair instructions using a method approved by the Manager,
International Section, Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA), and accomplish those instructions
accordingly. If approved by the DOA, the approval must include the
DOA-authorized signature.
(m) Terminating Action and Method of Compliance
(1) Modification of an airplane as required by paragraph (h) of
this AD, or as specified in paragraph (i) of this AD, constitutes
terminating action for the repetitive detailed inspections required
by paragraph (l) of AD 2016-14-09 for that airplane.
(2) Modification of an airplane as required by paragraph (h) of
this AD, or as specified in paragraph (i) of this AD, is a method of
compliance with the requirements of paragraph (g) of AD 2017-04-10
for that airplane.
(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
directly to the International Section, send it to the attention of
the person identified in paragraph (p)(2) of this AD. Information
may be emailed to: [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): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply
[[Page 10415]]
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) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0251 dated December 15,
2017, for related information. This MCAI may be found in the AD
docket on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0165.
(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; telephone
and fax 206-231-3223.
(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 Aerospace service information identified in
this AD, 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 service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
Issued in Renton, Washington, on March 5, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-04727 Filed 3-8-18; 8:45 am]
BILLING CODE 4910-13-P
