Airworthiness Directives; Airbus Airplanes, 15985-15988 [2017-06098]
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Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) M7 Aerospace LLC SA226 Series
Service Bulletin 226–76–012, dated March
17, 2015.
(ii) M7 Aerospace LLC SA227 Series
Service Bulletin 227–76–007, dated March
17, 2015.
(iii) M7Aerospace LLC SA227 Series
Commuter Category Service Bulletin CC7–
76–004, dated March 17, 2015.
(iv) M7 Aerospace SA226 Series
Maintenance Manual Temporary Revision
71–02, dated March 15, 2016.
(v) M7 Aerospace SA227 Series
Maintenance Manual Temporary Revision
71–03, dated March 15, 2016.
(vi) M7 Aerospace SA227 Series Commuter
Category Maintenance Manual Temporary
Revision 71–02, dated March 15, 2016.
(vii) Honeywell International Inc. Service
Bulletin TPE331–72–2190, dated December
21, 2011.
(3) For service information identified in
this AD, contact M7 Aerospace LLC, 10823
NE Entrance Road, San Antonio, Texas
78216; phone: (210) 824–9421; fax: (210)
804–7766; Internet: https://www.elbitsystemsus.com; email: MetroTech@
M7Aerospace.com; or Honeywell
International Inc. 111 S. 34th Street, Phoenix,
Arizona 85034–2802; phone: (855) 808–6500;
email: AeroTechSupport@honeywell.com;
Internet: https://aerospace.honeywell.com/
en/services/maintenance-and-monitoring.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call 816–329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri on March
17, 2017.
William Schinstock,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–05857 Filed 3–30–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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14 CFR Part 39
[Docket No. FAA–2017–0245; Directorate
Identifier 2017–NM–023–AD; Amendment
39–18841; AD 2017–07–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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14:25 Mar 30, 2017
Jkt 241001
Final rule; request for
comments.
ACTION:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A330–243, –243F, –341,
–342, and –343 airplanes. This AD
requires an inspection to determine if
affected hydraulic pressure tube
assemblies are installed, and
replacement with serviceable hydraulic
pressure tube assemblies if necessary.
This AD also requires repetitive
replacements of serviceable hydraulic
pressure tube assemblies. This AD was
prompted by a determination that cracks
can develop on the ripple damper of the
hydraulic pressure tube assembly and
reports of failure of the ripple damper
of the hydraulic pressure tube assembly.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD becomes effective April
17, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 17, 2017.
We must receive comments on this
AD by May 15, 2017.
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.
For service information identified in
this final rule, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0245.
SUMMARY:
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15985
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0245; 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 Branch, ANM–116,
Transport Airplane Directorate, 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 Airworthiness
Directive 2017–0041, dated February 24,
2017; corrected February 28, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A330–
243, –243F, –341, –342, and –343
airplanes. The MCAI states:
Following introduction in-service of
Airbus modification (mod) 205242, a new
hydraulic pressure tube assembly Part
Number (P/N) AE711121–18 was installed,
one on each engine, with an integral ripple
damper. It was determined that, at a
relatively low number of cycles, cracks can
develop on the ripple damper weld of this
new hydraulic pressure tube, which could
lead to hydraulic leakage and consequent
loss of the green hydraulic system. Recently,
there has been a high rate of failure of the
affected dampers that, if continued, may
exceed the overall safety objective of the
certified design.
This condition, if not corrected, could, in
combination with other system failures,
result in reduced control of the aeroplane.
Prompted by these findings, Airbus issued
Alert Operators Transmission (AOT)
A71L012–16 Revision 01, to provide
instructions to replace the hydraulic pressure
tube assembly P/N AE711121–18 with an
improved assembly, P/N AE711121–18 Rev
A, equipped with a double-welded ripple
damper.
For the reasons described above, this
[EASA] AD requires [inspection for and]
replacement of each affected hydraulic
pressure tube assembly with a [serviceable]
tube assembly having the double welded
ripple damper installed. This [EASA] AD
also requires implementation of a life limit
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on the new part [i.e., repetitive replacements
of serviceable hydraulic pressure tube
assemblies]. This [EASA] AD is considered as
interim measure and further AD action may
follow.
This [EASA] AD is republished to correct
the TCDS number and add a previous
manufacturer name.
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2017–0245.
Related Service Information Under 1
CFR Part 51
Airbus has issued Alert Operators
Transmission (AOT) A71L012–16,
Revision 01, dated February 24, 2017.
The service information describes
procedures for replacing hydraulic
pressure tube assembly, part number (P/
N) AE711121–18, and hydraulic
pressure tube assembly, P/N AE711121–
18 Rev A. 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.
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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 and service information
referenced above. 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 design.
Difference Between This AD and the
MCAI
The MCAI mandates replacement of
the hydraulic pressure tube assembly,
using Airbus AOT A71L012–16,
Revision 01, dated February 24, 2017.
However, Airbus AOT A71L012–16,
Revision 01, dated February 24, 2017,
also specifies to first inspect or do a
records review to determine the part
number of the hydraulic pressure tube
assembly. Therefore, paragraph (i) of
this AD requires the inspection or
records review.
The MCAI includes a compliance
time of ‘‘within 5 months’’ for the
replacement of the affected part. We
have determined that a compliance time
of ‘‘within 4 months’’ is necessary to
adequately address the identified unsafe
condition. We have included the 4month compliance time in paragraphs
(j), (l), and (m) of this AD.
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We have coordinated these
differences with EASA.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because cracks can develop on the
ripple damper of the hydraulic pressure
tube assembly, which could lead to
hydraulic leakage and consequent loss
of the green hydraulic system and
because of reports of failure of the ripple
damper of the hydraulic pressure tube
assembly. This condition could, in
combination with other system failures,
result in reduced control of the airplane.
Therefore, we determined that notice
and opportunity for public comment
before issuing this AD are impracticable
and that good cause exists for making
this amendment effective in fewer 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–2017–0245;
Directorate Identifier 2017–NM–023–
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
We estimate that this AD affects 53
airplanes of U.S. registry.
We also estimate that it will take
about 5 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts will cost
about $20,000 per product. Based on
these figures, we estimate the cost of
this AD on U.S. operators to be
$1,082,525, or $20,425 per product.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
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cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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.
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:
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Federal Register / Vol. 82, No. 61 / Friday, March 31, 2017 / Rules and Regulations
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):
■
2017–07–05 Airbus: Amendment 39–18841;
Docket No. FAA–2017–0245; Directorate
Identifier 2017–NM–023–AD.
(a) Effective Date
This AD becomes effective April 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330–
243, –243F, –341, –342, and –343 airplanes,
certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
(e) Reason
This AD was prompted by a determination
that cracks can develop on the ripple damper
of the hydraulic pressure tube assembly,
which could lead to hydraulic leakage and
consequent loss of the green hydraulic
system. This AD was also prompted by
reports of failure of the ripple damper of the
hydraulic pressure tube assembly. We are
issuing this AD to prevent cracking and
failure of the ripple damper of the hydraulic
pressure tube assembly, which could, in
combination with other system failures,
result in reduced control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Definition of Affected Part
For the purpose of this AD, a hydraulic
pressure tube assembly, part number (P/N)
AE711121–18, as introduced by Airbus mod
205242, is hereafter referred to as an
‘‘affected part’’ in this AD.
(h) Definition of Serviceable Part
For the purpose of this AD, a ‘‘serviceable
part’’ is a hydraulic pressure tube assembly
(which has a double-welded ripple damper
15987
installed), P/N AE711121–18 Rev A, that has
accumulated fewer than 800 total flight
cycles since first installation on an airplane.
The hydraulic pressure tube assembly, P/N
AE711121–18 Rev A, is introduced by Airbus
mod 206979 on the production line.
(i) Identification of Affected Parts
Within 15 days after the effective date of
this AD, inspect to determine the part
number of the hydraulic pressure tube
assembly that is installed on each engine. A
review of airplane maintenance records is
acceptable in lieu of this inspection if the
part number of the hydraulic pressure tube
assembly can be conclusively determined
from that review.
(j) Replacement of Affected Parts
Within the compliance time specified in
table 1 to paragraph (j) of this AD, as
applicable, or within 4 months after the
effective date of this AD, whichever occurs
first, replace each affected part (see
paragraph (g) of this AD) with a serviceable
part (see paragraph (h) of this AD), in
accordance with the instructions of Airbus
Alert Operators Transmission (AOT)
A71L012–16, Revision 01, dated February 24,
2017.
TABLE 1 TO PARAGRAPH (j) OF THIS AD—REPLACEMENT COMPLIANCE TIMES
Flight cycles accumulated *
Compliance time
Fewer than 775 total flight cycles .................................................
Before exceeding 800 total flight cycles on the affected hydraulic pressure
tube assembly since first installation on an airplane.
Within 25 flight cycles after the effective date of this AD.
Within 25 flight cycles after the effective date of this AD.
775 total flight cycles or more ......................................................
An unknown number of flight cycles accumulated .......................
* Unless specified otherwise, the flight cycles in the ‘‘flight cycles accumulated’’ column of table 1 to paragraph (j) of this AD are those accumulated by an affected hydraulic pressure tube assembly, on the effective date of this AD, since first installation on an airplane.
(n) Credit for Previous Actions
(k) Repetitive Replacement of Serviceable
Parts—Life Limit
Before a serviceable part (see paragraph (h)
of this AD) exceeds 800 total flight cycles
since first installation on an airplane, replace
it with a serviceable part, in accordance with
the instructions of Airbus AOT A71L012–16,
Revision 01, dated February 24, 2017.
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(l) Engine Installation Limitation
As of the effective date of this AD, except
as required by paragraph (m) of this AD, it
is allowed to install on any airplane a
replacement engine having an affected part
(see paragraph (g) of this AD) installed,
provided that, before that affected part
exceeds 800 total flight cycles since first
installation on an airplane, or within 4
months after the effective date of this AD,
whichever occurs first, the part is replaced
with a serviceable part (see paragraph (h) of
this AD), in accordance with the instructions
of Airbus AOT A71L012–16, Revision 01,
dated February 24, 2017.
(m) Parts and Engine Installation Prohibition
As of 4 months after the effective date of
this AD: Do not install on any airplane an
affected part (see paragraph (g) of this AD),
or an engine having an affected part installed.
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This paragraph provides credit for actions
required by paragraph (j) of this AD, if those
actions were performed before the effective
date of this AD using Airbus AOT A71L012–
16, dated December 22, 2016.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
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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 Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2017–0041, dated
February 24, 2017; corrected February 28,
2017, for related information. This MCAI
may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2017–0245.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Branch, ANM–116,
Transport Airplane Directorate, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
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(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Alert Operators Transmission
(AOT) A71L012–16, Revision 01, dated
February 24, 2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–06098 Filed 3–30–17; 8:45 am]
Examining the AD Docket
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0603; Directorate
Identifier 2013–CE–026–AD; Amendment
39–18827; AD 2017–06–03]
RIN 2120–AA64
Airworthiness Directives; Meggitt
(Troy), Inc. Combustion Heaters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 81–09–09
for certain Meggitt (Troy), Inc.
(previously known as Stewart Warner
South Wind Corporation and as Stewart
Warner South Wind Division) Model
Series (to include all the variants) 921,
930, 937, 940, 944, 945, 977, 978, 979,
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SUMMARY:
VerDate Sep<11>2014
14:25 Mar 30, 2017
Jkt 241001
8240, 8253, 8259, and 8472 combustion
heaters. AD 81–09–09 required
repetitive inspections of the combustion
heater; repetitive installation
inspections of the combustion heater;
and, for combustion heaters having
1,000 hours or more time-in-service
(TIS), overhaul of the combustion
heater. This new AD requires detailed
repetitive inspections, repetitive
pressure decay tests, and disable/
removal of the combustion heater if
necessary. This AD was prompted by an
airplane accident and reports that the
heater was malfunctioning. We are
issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective May 5, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 5, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Meggitt Control Systems, 3 Industrial
Drive, Troy, Indiana 47588; telephone:
(812) 547–7071; fax: (812) 547–2488;
email: infotroy@meggitt.com; Internet:
www.stewart-warner.com. You may
view this referenced service information
at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri
64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0603.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0603; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Chung-Der Young, Aerospace Engineer,
FAA, Chicago Aircraft Certification
Office, 2300 East Devon Avenue, Des
Plaines, IL 60018–4696; telephone (847)
294–7309; fax (847) 294–7834 email:
chung-der.young@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
81–09–09, Amendment 39- 4102 (46 FR
24936, May 4, 1981) (‘‘AD 81–09–09’’).
The SNPRM published in the Federal
Register on November 3, 2016 (81 FR
76532). We preceded the SNPRM with
a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on August 20, 2014 (79 FR
49249). The NPRM proposed to retain
most actions from AD 81–09–09, add a
calendar time to the repetitive
inspections, add more detailed actions
to the inspections, and add a pressure
decay test (PDT). The NPRM was
prompted by an airplane accident and
reports we received of the heater
malfunctioning. The SNPRM proposed
to retain the actions proposed in the
NPRM, add combustion heater models
series to the applicability, and modify
the compliance times. We also
completed and included in the SNPRM
an initial regulatory flexibility analysis.
We are issuing this AD to correct the
unsafe condition on these products.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM and the FAA’s
response to each comment.
Request
The European Aviation Safety Agency
(EASA) requested we change the
wording in paragraph (k) of this AD,
Removal or Disable of the Combustion
Heater. If an operator installs or reenables an applicable combustion
heater, the SNPRM requires the operator
to do either the inspections required by
the AD, disable the heater, or remove
the heater. However, the actions of
remove or disable would not apply to an
operator installing or re-enabling a
heater. EASA requested we only require
the inspections for a heater that has
been re-enabled and only require the
inspections or disable options for a
heater that has been installed.
We partially agree with this comment.
We agree that the wording of the
SNPRM may be confusing—re-enable
the heater and then disable or remove it.
However, we do not agree with
completely omitting the disable or
removal options. If an operator installs
or re-enables an applicable heater, that
heater must be inspected as required by
the AD, and, if it fails the inspections,
the heater must be disabled or removed.
We changed the language in
paragraph (k) of this AD, Removal or
E:\FR\FM\31MRR1.SGM
31MRR1
]]>Agencies
[Federal Register Volume 82, Number 61 (Friday, March 31, 2017)]
[Rules and Regulations]
[Pages 15985-15988]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06098]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0245; Directorate Identifier 2017-NM-023-AD;
Amendment 39-18841; AD 2017-07-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. This AD
requires an inspection to determine if affected hydraulic pressure tube
assemblies are installed, and replacement with serviceable hydraulic
pressure tube assemblies if necessary. This AD also requires repetitive
replacements of serviceable hydraulic pressure tube assemblies. This AD
was prompted by a determination that cracks can develop on the ripple
damper of the hydraulic pressure tube assembly and reports of failure
of the ripple damper of the hydraulic pressure tube assembly. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD becomes effective April 17, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 17,
2017.
We must receive comments on this AD by May 15, 2017.
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.
For service information identified in this final rule, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0245.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0245; 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 Branch, ANM-116, Transport Airplane Directorate, 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
Airworthiness Directive 2017-0041, dated February 24, 2017; corrected
February 28, 2017 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Airbus Model A330-243, -243F, -341, -342, and -343
airplanes. The MCAI states:
Following introduction in-service of Airbus modification (mod)
205242, a new hydraulic pressure tube assembly Part Number (P/N)
AE711121-18 was installed, one on each engine, with an integral
ripple damper. It was determined that, at a relatively low number of
cycles, cracks can develop on the ripple damper weld of this new
hydraulic pressure tube, which could lead to hydraulic leakage and
consequent loss of the green hydraulic system. Recently, there has
been a high rate of failure of the affected dampers that, if
continued, may exceed the overall safety objective of the certified
design.
This condition, if not corrected, could, in combination with
other system failures, result in reduced control of the aeroplane.
Prompted by these findings, Airbus issued Alert Operators
Transmission (AOT) A71L012-16 Revision 01, to provide instructions
to replace the hydraulic pressure tube assembly P/N AE711121-18 with
an improved assembly, P/N AE711121-18 Rev A, equipped with a double-
welded ripple damper.
For the reasons described above, this [EASA] AD requires
[inspection for and] replacement of each affected hydraulic pressure
tube assembly with a [serviceable] tube assembly having the double
welded ripple damper installed. This [EASA] AD also requires
implementation of a life limit
[[Page 15986]]
on the new part [i.e., repetitive replacements of serviceable
hydraulic pressure tube assemblies]. This [EASA] AD is considered as
interim measure and further AD action may follow.
This [EASA] AD is republished to correct the TCDS number and add
a previous manufacturer name.
You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0245.
Related Service Information Under 1 CFR Part 51
Airbus has issued Alert Operators Transmission (AOT) A71L012-16,
Revision 01, dated February 24, 2017. The service information describes
procedures for replacing hydraulic pressure tube assembly, part number
(P/N) AE711121-18, and hydraulic pressure tube assembly, P/N AE711121-
18 Rev A. 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 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 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 design.
Difference Between This AD and the MCAI
The MCAI mandates replacement of the hydraulic pressure tube
assembly, using Airbus AOT A71L012-16, Revision 01, dated February 24,
2017. However, Airbus AOT A71L012-16, Revision 01, dated February 24,
2017, also specifies to first inspect or do a records review to
determine the part number of the hydraulic pressure tube assembly.
Therefore, paragraph (i) of this AD requires the inspection or records
review.
The MCAI includes a compliance time of ``within 5 months'' for the
replacement of the affected part. We have determined that a compliance
time of ``within 4 months'' is necessary to adequately address the
identified unsafe condition. We have included the 4-month compliance
time in paragraphs (j), (l), and (m) of this AD.
We have coordinated these differences with EASA.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
cracks can develop on the ripple damper of the hydraulic pressure tube
assembly, which could lead to hydraulic leakage and consequent loss of
the green hydraulic system and because of reports of failure of the
ripple damper of the hydraulic pressure tube assembly. This condition
could, in combination with other system failures, result in reduced
control of the airplane. Therefore, we determined that notice and
opportunity for public comment before issuing this AD are impracticable
and that good cause exists for making this amendment effective in fewer
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-2017-0245; Directorate
Identifier 2017-NM-023-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
We estimate that this AD affects 53 airplanes of U.S. registry.
We also estimate that it will take about 5 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $20,000 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $1,082,525, or $20,425 per product.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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.
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:
[[Page 15987]]
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):
2017-07-05 Airbus: Amendment 39-18841; Docket No. FAA-2017-0245;
Directorate Identifier 2017-NM-023-AD.
(a) Effective Date
This AD becomes effective April 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330-243, -243F, -341, -342, and
-343 airplanes, certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by a determination that cracks can develop
on the ripple damper of the hydraulic pressure tube assembly, which
could lead to hydraulic leakage and consequent loss of the green
hydraulic system. This AD was also prompted by reports of failure of
the ripple damper of the hydraulic pressure tube assembly. We are
issuing this AD to prevent cracking and failure of the ripple damper
of the hydraulic pressure tube assembly, which could, in combination
with other system failures, result in reduced control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definition of Affected Part
For the purpose of this AD, a hydraulic pressure tube assembly,
part number (P/N) AE711121-18, as introduced by Airbus mod 205242,
is hereafter referred to as an ``affected part'' in this AD.
(h) Definition of Serviceable Part
For the purpose of this AD, a ``serviceable part'' is a
hydraulic pressure tube assembly (which has a double-welded ripple
damper installed), P/N AE711121-18 Rev A, that has accumulated fewer
than 800 total flight cycles since first installation on an
airplane. The hydraulic pressure tube assembly, P/N AE711121-18 Rev
A, is introduced by Airbus mod 206979 on the production line.
(i) Identification of Affected Parts
Within 15 days after the effective date of this AD, inspect to
determine the part number of the hydraulic pressure tube assembly
that is installed on each engine. A review of airplane maintenance
records is acceptable in lieu of this inspection if the part number
of the hydraulic pressure tube assembly can be conclusively
determined from that review.
(j) Replacement of Affected Parts
Within the compliance time specified in table 1 to paragraph (j)
of this AD, as applicable, or within 4 months after the effective
date of this AD, whichever occurs first, replace each affected part
(see paragraph (g) of this AD) with a serviceable part (see
paragraph (h) of this AD), in accordance with the instructions of
Airbus Alert Operators Transmission (AOT) A71L012-16, Revision 01,
dated February 24, 2017.
Table 1 to Paragraph (j) of This AD--Replacement Compliance Times
------------------------------------------------------------------------
Flight cycles accumulated * Compliance time
------------------------------------------------------------------------
Fewer than 775 total flight cycles... Before exceeding 800 total flight
cycles on the affected hydraulic
pressure tube assembly since
first installation on an
airplane.
775 total flight cycles or more...... Within 25 flight cycles after the
effective date of this AD.
An unknown number of flight cycles Within 25 flight cycles after the
accumulated. effective date of this AD.
------------------------------------------------------------------------
* Unless specified otherwise, the flight cycles in the ``flight cycles
accumulated'' column of table 1 to paragraph (j) of this AD are those
accumulated by an affected hydraulic pressure tube assembly, on the
effective date of this AD, since first installation on an airplane.
(k) Repetitive Replacement of Serviceable Parts--Life Limit
Before a serviceable part (see paragraph (h) of this AD) exceeds
800 total flight cycles since first installation on an airplane,
replace it with a serviceable part, in accordance with the
instructions of Airbus AOT A71L012-16, Revision 01, dated February
24, 2017.
(l) Engine Installation Limitation
As of the effective date of this AD, except as required by
paragraph (m) of this AD, it is allowed to install on any airplane a
replacement engine having an affected part (see paragraph (g) of
this AD) installed, provided that, before that affected part exceeds
800 total flight cycles since first installation on an airplane, or
within 4 months after the effective date of this AD, whichever
occurs first, the part is replaced with a serviceable part (see
paragraph (h) of this AD), in accordance with the instructions of
Airbus AOT A71L012-16, Revision 01, dated February 24, 2017.
(m) Parts and Engine Installation Prohibition
As of 4 months after the effective date of this AD: Do not
install on any airplane an affected part (see paragraph (g) of this
AD), or an engine having an affected part installed.
(n) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(j) of this AD, if those actions were performed before the effective
date of this AD using Airbus AOT A71L012-16, dated December 22,
2016.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0041, dated February 24,
2017; corrected February 28, 2017, for related information. This
MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2017-0245.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
[[Page 15988]]
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Alert Operators Transmission (AOT) A71L012-16,
Revision 01, dated February 24, 2017.
(ii) Reserved.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-06098 Filed 3-30-17; 8:45 am]
BILLING CODE 4910-13-P
