Airworthiness Directives; Airbus Airplanes, 5301-5304 [2018-02350]
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Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this 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:
■
sradovich on DSK3GMQ082PROD with RULES
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):
■
2018–03–09 Airbus: Amendment 39–19182;
Docket No. FAA–2018–0070; Product
Identifier 2015–NM–146–AD.
VerDate Sep<11>2014
17:31 Feb 06, 2018
Jkt 244001
(a) Effective Date
This AD becomes effective February 22,
2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A321–
211 and –231 airplanes, certificated in any
category, manufacturer serial numbers 3191,
3217, 3241, 3251, 3267, 3334, 3459, 3493,
3507, 3552, 3566, 3587, 3645, 3681, 3764,
3784, 3847, 3867, 3920, 3934, 3938, 3951,
3981, 4058, 4074, 4099, 4103, 4116, 4148,
4184, 4189, 4194, 4217, 4224, 4230, 4266,
4271, 4274, 4292, 4299, 4338, 4341, 4369,
4387, 4416, 4430, 4461, and 4500.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/furnishings.
(e) Reason
This AD was prompted by a determination
that the flat-headed pin at the upper
attachment point of the overhead stowage
compartments (OHSCs) at a certain frame
may not sustain the maximum weight load
for each flight phase. We are issuing this AD
to prevent OHSC detachment during flight,
which could cause injury to the crew or
passengers.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Action(s)
Within 30 days after the effective date of
this AD, request instructions from the
Manager, International Section, Transport
Standards Branch, FAA, to address the
unsafe condition specified in paragraph (e) of
this AD; and accomplish the action(s) at the
times specified in, and in accordance with,
those instructions. Guidance can be found in
Mandatory Continuing Airworthiness
Information (MCAI) European Aviation
Safety Agency (EASA) AD 2015–0164, dated
August 10, 2015.
(h) 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 (i)(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.
(i) Related Information
(1) Refer to MCAI EASA AD 2015–0164,
dated August 10, 2015, for related
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
5301
information. You may examine the MCAI on
the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2018–0070.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW,
Renton, WA 98057–3356; telephone: 425–
227–1405; fax: 425–227–1149.
(j) Material Incorporated by Reference
None.
Issued in Renton, Washington, on January
26, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–02357 Filed 2–6–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0029; Product
Identifier 2015–NM–132–AD; Amendment
39–19179; AD 2018–03–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–02–
18, which applied to all Airbus Model
A330–201, –202, –203, –301, –302, and
–303 airplanes. AD 2015–02–18
required a one-time ultrasonic
inspection for fractures of all aft mountpylon bolts of each engine. This new AD
was prompted by the failure of a bolt on
the aft engine mount upper beam, which
was found to be caused by inappropriate
in-production upper beam installation.
This AD requires contacting the FAA to
obtain instructions for addressing the
unsafe condition on these products, and
doing the actions specified in those
instructions. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD becomes effective
February 22, 2018.
We must receive comments on this
AD by March 26, 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.
SUMMARY:
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Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations
• 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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–
0029; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057–3356;
telephone: 425–227–1138; fax: 425–
227–1149.
SUPPLEMENTARY INFORMATION:
sradovich on DSK3GMQ082PROD with RULES
Discussion
We issued AD 2015–02–18,
Amendment 39–18085 (80 FR 5020,
January 30, 2015) (‘‘AD 2015–02–18’’),
which applied to all Airbus Model
A330–201, –202, –203, –301, –302, and
–303 airplanes. AD 2015–02–18 was
prompted by a report of one bolt on the
aft engine mount upper beam found
totally broken. AD 2015–02–18 required
a one-time ultrasonic inspection for
fractures of all aft mount-pylon bolts of
each engine. We issued AD 2015–02–18
to detect and correct fracture of the aft
mount-pylon bolts, which could result
in failure of the engine mount and
consequent detachment of the engine.
Since we issued AD 2015–02–18,
further investigation showed that the
pylon bolt failure was caused by
inappropriate upper beam installation
during production. We have determined
that repetitive inspections are necessary
to address the unsafe condition.
VerDate Sep<11>2014
17:31 Feb 06, 2018
Jkt 244001
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2015–0126,
dated July 1, 2015 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A330–200 and
–300 series airplanes. The MCAI states:
During a scheduled replacement of a CF6–
80E1 engine on an A330 aeroplane, a bolt on
the aft engine mount upper beam was found
sheared. The affected bolt is one out of four
bolts that attach the upper beam to the pylon.
Investigation results revealed an unusual
contact with the counter-bore edge of the
beam which induced a significant groove on
the bolt during its installation in production.
It is suspected that the induced groove led to
a fatigue crack initiation and subsequent
quick propagation leading to the complete
fracture of the bolt. In case of multiple bolt
fractures, the remaining bolts would be
insufficient to sustain the residual fatigue
and limit loads.
This condition, if not detected and
corrected, could lead, in case of multiple bolt
fracture, to loss of an engine mount structural
integrity and possible in-flight engine
detachment, resulting in reduced control of
the aeroplane and/or injury to persons on the
ground.
To address this potential unsafe condition,
EASA issued AD 2013–0094 to require a onetime ultrasonic (US) inspection of the four aft
mount-pylon bolts of both engines to detect
sheared bolts and, depending on findings,
accomplishment of applicable corrective
actions.
Since EASA AD 2013–0094 was issued,
further investigation results revealed that the
pylon bolt failure was caused by
inappropriate upper beam installation during
production. An abnormal bending load
applied on the bolt during installation of the
upper beam could have increased the stress
close to or beyond the limit strength, high
enough to fracture the bolt.
Prompted by these findings, Airbus issued
Service Bulletin (SB) A330–71–3031
providing instructions for repetitive
inspections and the applicable corrective
actions.
For the reasons described above, this
[EASA] AD, which supersedes EASA AD
2013–0094, requires repetitive US
inspections of the aft mount-pylons bolts of
each engine and, depending on findings,
corrective actions.
You may examine the MCAI on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0029.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
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. We are issuing this AD because
we evaluated all pertinent information
and determined the unsafe condition
exists and is likely to exist or develop
on other products of the same type
design.
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this product, we find good
cause that notice and opportunity for
prior public comment are unnecessary.
In addition, for the reason(s) stated
above, we find that good cause exists for
making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2018–0029;
Product Identifier 2015–NM–132–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this 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 AD.
Costs of Compliance
Currently, there are no affected U.S.registered airplanes. This AD requires
contacting the FAA to obtain
instructions for addressing the unsafe
condition, and doing the actions
specified in those instructions. Based on
the actions specified in the MCAI AD,
we are providing the following cost
estimates for an affected airplane that is
placed on the U.S. Register in the future:
E:\FR\FM\07FER1.SGM
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Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations
ESTIMATED COSTS
Action
Labor cost
Inspections (new action) ..........................
8 work-hours × $85 per hour = $680 per
inspection cycle..
We estimate the following costs to do
any necessary on-condition repairs that
Parts cost
Cost per product
$0
$680 per inspection cycle.
would be required based on the results
of the required actions:
ON-CONDITION COSTS
Action
Labor cost
Repair (new action) .........................................
Up to 337 work-hours × $85 per hour = $28,645 ....................
1We
(1)
Up to $28,645.
have received no definitive data that would enable us to provide parts cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
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 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
sradovich on DSK3GMQ082PROD with RULES
Cost per
product
Parts cost
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.
VerDate Sep<11>2014
17:31 Feb 06, 2018
Jkt 244001
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
removing airworthiness directive (AD)
2015–02–18, Amendment 39–18085 (80
FR 5020, January 30, 2015), and adding
the following new AD:
■
2018–03–06 Airbus: Amendment 39–19179;
Docket No. FAA–2018–0029; Product
Identifier 2015–NM–132–AD.
(a) Effective Date
This AD becomes effective February 22,
2018.
(b) Affected ADs
This AD replaces AD 2015–02–18,
Amendment 39–18085 (80 FR 5020, January
30, 2015) (‘‘AD 2015–02–18’’).
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
(c) Applicability
This AD applies to Airbus Model A330–
201, –202, –203, –301, –302, and –303
airplanes, certificated in any category, all
manufacturer serial numbers, except those on
which Airbus modification 203947 has been
embodied in production.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
(e) Reason
This AD was prompted by the failure of a
bolt on the aft engine mount upper beam,
which was found to be caused by
inappropriate in-production upper beam
installation. We are issuing this AD to detect
and correct fracture of the aft mount-pylon
bolts, which could result in loss of engine
mount structural integrity, consequent
detachment of the engine and reduced
control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Action(s)
Within 30 days after the effective date of
this AD, request instructions from the
Manager, International Section, Transport
Standards Branch, FAA, to address the
unsafe condition specified in paragraph (e) of
this AD; and accomplish the action(s) at the
times specified in, and in accordance with,
those instructions. Guidance can be found in
Mandatory Continuing Airworthiness
Information (MCAI) European Aviation
Safety Agency (EASA) AD 2015–0126, dated
July 1, 2015.
(h) 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
E:\FR\FM\07FER1.SGM
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5304
Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations
paragraph (i)(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.
(i) Related Information
(1) Refer to MCAI EASA AD 2015–0126,
dated July 1, 2015, for related information.
You may examine the MCAI on the internet
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–0029.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 1601 Lind Avenue
SW, Renton, WA 98057–3356; telephone:
425–227–1138; fax: 425–227–1149.
(j) Material Incorporated by Reference
None.
Issued in Renton, Washington, on January
25, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–02350 Filed 2–6–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0030; Product
Identifier 2014–NM–161–AD; Amendment
39–19180; AD 2018–03–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–202, –203, –223,
and –243 airplanes; and Model A340–
211, –212, –311, and –313 airplanes.
This AD requires contacting the FAA to
obtain instructions for addressing the
unsafe condition on these products, and
doing the actions specified in those
instructions. This AD was prompted by
a report of a hard contact that was found
between the constant speed motor/
generator feeder line route 6G/6E and
the optional cabin temperature control
pipe on the upper shell between certain
frames. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD becomes effective
February 22, 2018.
sradovich on DSK3GMQ082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
17:31 Feb 06, 2018
Jkt 244001
We must receive comments on this
AD by March 26, 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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–
0030; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057–3356;
telephone: 425–227–1138; fax: 425–
227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2014–0161,
dated July 10, 2014 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A330–202,
–203, –223, and –243 airplanes; and
Model A340–211, –212, –311, and –313
airplanes. The MCAI states:
A hard contact was found on an A330
aeroplane during production between the
Constant Speed Motor/Generator (CSM/G)
feeder line route 6G/6E (Functional Item
Number 1526VB) and the optional cabin
temperature control pipe on the upper shell
between Frame (FR)37.4 and FR38 on
stringer 5, right hand (RH) side.
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Fmt 4700
Sfmt 4700
This condition, if not corrected, may lead
to chafing and, consequently, a short circuit
when the emergency generation is activated,
resulting in the loss of emergency generation.
The loss of normal generation combined with
the loss of emergency generation jeopardizes
the aeroplane safe flight.
To address this potential unsafe condition,
Airbus developed a modification to provide
adequate clearance between harness 1526VB
and the affected (optional) air-conditioning
temperature control pipe. A340–200/–300
aeroplanes equipped with this optional cabin
temperature control pipe are also affected by
this issue. The modification can be embodied
in service through Airbus Service Bulletin
(SB) A330–92–3125, or SB A340–92–4097, as
applicable.
For the reasons described above, this
[EASA] AD requires modification of the
CSM/G mounting with installation of new
stacking and/or longer bracket, depending on
aeroplane configuration.
You may examine the MCAI on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2018–0030.
FAA’s Determination and Requirements
of This 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. We are issuing this AD because
we evaluated all pertinent information
and determined the unsafe condition
exists and is likely to exist or develop
on other products of these same type
designs.
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this product, we find good
cause that notice and opportunity for
prior public comment are unnecessary.
In addition, for the reason(s) stated
above, we find that good cause exists for
making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2018–0030;
Product Identifier 2014–NM–161–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
E:\FR\FM\07FER1.SGM
07FER1
]]>Agencies
[Federal Register Volume 83, Number 26 (Wednesday, February 7, 2018)]
[Rules and Regulations]
[Pages 5301-5304]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02350]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0029; Product Identifier 2015-NM-132-AD; Amendment
39-19179; AD 2018-03-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2015-02-18,
which applied to all Airbus Model A330-201, -202, -203, -301, -302, and
-303 airplanes. AD 2015-02-18 required a one-time ultrasonic inspection
for fractures of all aft mount-pylon bolts of each engine. This new AD
was prompted by the failure of a bolt on the aft engine mount upper
beam, which was found to be caused by inappropriate in-production upper
beam installation. This AD requires contacting the FAA to obtain
instructions for addressing the unsafe condition on these products, and
doing the actions specified in those instructions. We are issuing this
AD to address the unsafe condition on these products.
DATES: This AD becomes effective February 22, 2018.
We must receive comments on this AD by March 26, 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.
[[Page 5302]]
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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-
0029; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Operations office
(telephone: 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-
227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued AD 2015-02-18, Amendment 39-18085 (80 FR 5020, January
30, 2015) (``AD 2015-02-18''), which applied to all Airbus Model A330-
201, -202, -203, -301, -302, and -303 airplanes. AD 2015-02-18 was
prompted by a report of one bolt on the aft engine mount upper beam
found totally broken. AD 2015-02-18 required a one-time ultrasonic
inspection for fractures of all aft mount-pylon bolts of each engine.
We issued AD 2015-02-18 to detect and correct fracture of the aft
mount-pylon bolts, which could result in failure of the engine mount
and consequent detachment of the engine.
Since we issued AD 2015-02-18, further investigation showed that
the pylon bolt failure was caused by inappropriate upper beam
installation during production. We have determined that repetitive
inspections are necessary to address the unsafe condition.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2015-0126, dated July 1, 2015 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Airbus Model A330-200 and -300 series
airplanes. The MCAI states:
During a scheduled replacement of a CF6-80E1 engine on an A330
aeroplane, a bolt on the aft engine mount upper beam was found
sheared. The affected bolt is one out of four bolts that attach the
upper beam to the pylon.
Investigation results revealed an unusual contact with the
counter-bore edge of the beam which induced a significant groove on
the bolt during its installation in production. It is suspected that
the induced groove led to a fatigue crack initiation and subsequent
quick propagation leading to the complete fracture of the bolt. In
case of multiple bolt fractures, the remaining bolts would be
insufficient to sustain the residual fatigue and limit loads.
This condition, if not detected and corrected, could lead, in
case of multiple bolt fracture, to loss of an engine mount
structural integrity and possible in-flight engine detachment,
resulting in reduced control of the aeroplane and/or injury to
persons on the ground.
To address this potential unsafe condition, EASA issued AD 2013-
0094 to require a one-time ultrasonic (US) inspection of the four
aft mount-pylon bolts of both engines to detect sheared bolts and,
depending on findings, accomplishment of applicable corrective
actions.
Since EASA AD 2013-0094 was issued, further investigation
results revealed that the pylon bolt failure was caused by
inappropriate upper beam installation during production. An abnormal
bending load applied on the bolt during installation of the upper
beam could have increased the stress close to or beyond the limit
strength, high enough to fracture the bolt.
Prompted by these findings, Airbus issued Service Bulletin (SB)
A330-71-3031 providing instructions for repetitive inspections and
the applicable corrective actions.
For the reasons described above, this [EASA] AD, which
supersedes EASA AD 2013-0094, requires repetitive US inspections of
the aft mount-pylons bolts of each engine and, depending on
findings, corrective actions.
You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0029.
FAA's Determination and Requirements of This 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. We are
issuing this AD because we evaluated all pertinent information and
determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this product, we
find good cause that notice and opportunity for prior public comment
are unnecessary. In addition, for the reason(s) stated above, we find
that good cause exists for making this amendment effective in less than
30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2018-0029; Product
Identifier 2015-NM-132-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this 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 AD.
Costs of Compliance
Currently, there are no affected U.S.-registered airplanes. This AD
requires contacting the FAA to obtain instructions for addressing the
unsafe condition, and doing the actions specified in those
instructions. Based on the actions specified in the MCAI AD, we are
providing the following cost estimates for an affected airplane that is
placed on the U.S. Register in the future:
[[Page 5303]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Inspections (new action)................ 8 work-hours x $85 per $0 $680 per inspection cycle.
hour = $680 per
inspection cycle..
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
repairs that would be required based on the results of the required
actions:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair (new action).................. Up to 337 work-hours x $85 \(1)\ Up to $28,645.
per hour = $28,645.
----------------------------------------------------------------------------------------------------------------
\1\We have received no definitive data that would enable us to provide parts cost estimates for the on-condition
actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
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 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 removing airworthiness directive (AD)
2015-02-18, Amendment 39-18085 (80 FR 5020, January 30, 2015), and
adding the following new AD:
2018-03-06 Airbus: Amendment 39-19179; Docket No. FAA-2018-0029;
Product Identifier 2015-NM-132-AD.
(a) Effective Date
This AD becomes effective February 22, 2018.
(b) Affected ADs
This AD replaces AD 2015-02-18, Amendment 39-18085 (80 FR 5020,
January 30, 2015) (``AD 2015-02-18'').
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -301, -
302, and -303 airplanes, certificated in any category, all
manufacturer serial numbers, except those on which Airbus
modification 203947 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by the failure of a bolt on the aft engine
mount upper beam, which was found to be caused by inappropriate in-
production upper beam installation. We are issuing this AD to detect
and correct fracture of the aft mount-pylon bolts, which could
result in loss of engine mount structural integrity, consequent
detachment of the engine and reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Action(s)
Within 30 days after the effective date of this AD, request
instructions from the Manager, International Section, Transport
Standards Branch, FAA, to address the unsafe condition specified in
paragraph (e) of this AD; and accomplish the action(s) at the times
specified in, and in accordance with, those instructions. Guidance
can be found in Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) AD 2015-0126, dated
July 1, 2015.
(h) 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
[[Page 5304]]
paragraph (i)(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.
(i) Related Information
(1) Refer to MCAI EASA AD 2015-0126, dated July 1, 2015, for
related information. You may examine the MCAI on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2018-0029.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356;
telephone: 425-227-1138; fax: 425-227-1149.
(j) Material Incorporated by Reference
None.
Issued in Renton, Washington, on January 25, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-02350 Filed 2-6-18; 8:45 am]
BILLING CODE 4910-13-P
