Airworthiness Directives; Safran Helicopter Engines, S.A., Turboshaft Engines, 38951-38953 [2018-16652]
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38951
Rules and Regulations
Federal Register
Vol. 83, No. 153
Wednesday, August 8, 2018
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0889; Product
Identifier 2009–NE–35–AD; Amendment 39–
19305; AD 2018–12–01]
RIN 2120–AA64
Airworthiness Directives; Safran
Helicopter Engines, S.A., Turboshaft
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–03–
11 for all Safran Helicopter Engines,
S.A., Arriel 2B and 2B1 turboshaft
engines. AD 2012–03–11 required
checking the transmissible torque
between the low-pressure (LP) pump
impeller and the high-pressure (HP)
pump shaft on the HP/LP pump and
metering valve assembly, hereafter
referred to as the hydro-mechanical
metering unit (HMU). Since we issued
AD 2012–03–11, the manufacturer
determined that incorporating
Modification TU 178 is a more effective
method to reduce the risk of uncoupling
between the LP fuel pump impeller and
the HP fuel pump shaft than the prior
Modification TU 147. This AD requires
inspection and possible replacement of
the HMU. This AD was prompted by
three cases of uncoupling of the HMU
LP fuel pump impeller and the HP fuel
pump shaft since AD 2012–03–11 was
issued. We are issuing this AD to
address the unsafe condition on these
products.
amozie on DSK3GDR082PROD with RULES
SUMMARY:
This AD is effective September
12, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 11, 2010 (75 FR 5689,
February 4, 2010).
DATES:
VerDate Sep<11>2014
16:30 Aug 07, 2018
Jkt 244001
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 20, 2012 (77 FR 8092,
February 14, 2012).
ADDRESSES: For service information
identified in this final rule, contact
Safran Helicopter Engines, S.A., 40220
Tarnos, France; phone: (33) 05 59 74 40
00; fax: (33) 05 59 74 45 15. You may
view this service information at the
FAA, Engine and Propeller Standards
Branch, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call 781–238–7759. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2009–
0889.
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–2009–
0889; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the mandatory continuing airworthiness
information, regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
Document Operations, 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: John
Frost, Aerospace Engineer, ECO Branch,
FAA, 1200 District Avenue, Burlington,
MA 01803; phone: 781–238–7756; fax:
781–238–7199; email: john.frost@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–03–11,
Amendment 39–16953 (77 FR 8092,
February 14, 2012), (‘‘AD 2012–03–11’’).
AD 2012–03–11 applied to all Safran
Helicopter Engines, S.A., Arriel 2B and
2B1 turboshaft engines. The NPRM
published in the Federal Register on
October 6, 2017 (82 FR 46727). The
NPRM was prompted by instances of
uncoupling between the LP fuel pump
impeller and the HP fuel pump shaft.
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
The NPRM proposed to require
inspection and, depending on the
results of the inspection, possible
replacement of the HMU. The NPRM
also proposed to require replacement of
pre-Modification TU 178 HMUs with an
HMU incorporating Modification TU
178 within 2,200 engine flight hours or
72 months, whichever occurs first, after
the effective date of this AD. We are
issuing this AD to address 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 NPRM and the FAA’s
response to the comment.
Request To Clarify Reason for AD
An individual commenter questioned
how the new modification in this AD is
better and different from the actions
required by the previous AD 2012–03–
11.
AD 2012–03–11 required a check of
the transmissible torque between the LP
fuel pump impeller and the HP fuel
pump shaft and replacement of the
HMU if it does not pass the torque
check. Since we issued AD 2012–03–11,
Safran Service Bulletin (SB) 292 73
2178, Version A, dated April 1, 2015
introduced Modification TU 178. This
AD accepts Modification TU 178 as a
more robust drive link between the LP
fuel pump impeller and the HP fuel
pump shaft that ensures the LP impeller
pump is driven even if the link with the
drive shaft loosens. This AD requires
installation of a Modification TU 178
HMU for any HMU that fails the torque
sensor check and as a mandatory
terminating action for the inspections
required by this AD, as well as purging
the fleet of the pre- and post-TU 147
configuration parts. We did not change
this AD.
Clarification to Service Information for
Torque Check
We updated paragraphs (g)(1)(i) and
(ii) of this AD to clarify that only
paragraph 2.A, rather than paragraph 2,
in Turbomeca Alert Mandatory SB
(MSB) A292 73 2830, Version B, dated
July 10, 2009, and Turbomeca Alert
MSB A292 73 2836, Version A, dated
August 17, 2010, is used to perform the
torque check.
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38952
Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
2836, Version A, dated August 17, 2010.
Turbomeca Alert MSB A292 73 2830,
Version B, describes procedures for
inspecting pre-Modification TU 147
HMUs. Turbomeca Alert MSB A292 73
2836, Version A, dated August 17, 2010,
describes procedures for inspecting
HMUs that have incorporated
Modification TU 147. 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.
describes HMU improvements that
includes a reinforced drive link between
the LP impeller and HP fuel pump shaft
(Modification TU 178). Safran
Helicopter Engines has also issued MSB
A292 73 2830, Version C; and A292 73
2836, Version B, both dated April 5,
2017, which exempt HMUs
incorporating Modification TU 178 from
the inspections previously
recommended by Safran Helicopter
Engines.
Related Service Information Under 1
CFR Part 51
We reviewed Turbomeca, S.A., Alert
MSB A292 73 2830, Version B, dated
July 10, 2009, and Alert MSB A292 73
Other Related Service Information
We estimate that this AD affects 417
engines installed on helicopters of U.S.
registry.
We estimate the following costs to
comply with this AD:
We reviewed Safran Helicopter
Engines MSB 292 73 2178, Version B,
dated March 23, 2017. Safran Helicopter
Engines MSB 292 73 2178, Version B,
Costs of Compliance
ESTIMATED COSTS
Action
Labor cost
Parts cost
Remove and replace the HP/LP fuel pump
metering unit.
2 work-hours × $85 per hour = $170 .............
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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 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 engines, propellers, and
associated appliances to the Manager,
Engine and Propeller Standards Branch,
Policy and Innovation Division.
We have 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
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.
VerDate Sep<11>2014
16:30 Aug 07, 2018
Jkt 244001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Cost per
product
$17,400
Cost on U.S.
operators
$17,570
$7,326,690
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)
2012–03–11, Amendment 39–16953 (77
FR 8092, February 14, 2012), and adding
the following new AD:
■
2018–12–01 Safran Helicopter Engines
(Type Certificate previously held by
Turbomeca, S.A.): Amendment 39–
19305; Docket No. FAA–2009–0889;
Product Identifier 2009–NE–35–AD.
(a) Effective Date
This AD is effective September 12, 2018.
(b) Affected ADs
This AD replaces AD 2012–03–11,
Amendment 39–16953 (77 FR 8092, February
14, 2012).
(c) Applicability
This AD applies to Safran Helicopter
Engines, S.A., Arriel 2B and 2B1 turboshaft
engines, except those incorporating
Modification TU 178.
Adoption of the Amendment
(d) Subject
Joint Aircraft System Component (JASC)
Code 7300, Engine Fuel and Control.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(e) Unsafe Condition
This AD was prompted by analysis that
indicated the modification of an engine to
incorporate Modification TU 178 provides a
more effective method than Modification TU
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Fmt 4700
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E:\FR\FM\08AUR1.SGM
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Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations
147 to reduce the risk of uncoupling between
the low-pressure (LP) fuel pump impeller
and the high-pressure (HP) fuel pump shaft
of the HP/LP pump and hydro-mechanical
metering unit (HMU). We are issuing this AD
to prevent failure of the HMU. The unsafe
condition, if not corrected, could result in
failure of the engine, in-flight shutdown, and
loss of the helicopter.
(k) Related Information
DEPARTMENT OF TRANSPORTATION
Comply with this AD within the
compliance times specified, unless already
done.
(1) For more information about this AD,
contact John Frost, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7756; fax: 781–238–7199; email: john.frost@
faa.gov.
(2) Refer to European Aviation Safety
Agency (EASA) AD 2017–0102, dated June
13, 2017, for more information. You may
examine the EASA AD on the internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2009–0889.
(g) Required Actions
(l) Material Incorporated by Reference
(1) Check the transmissible torque between
the LP fuel pump impeller and the HP fuel
pump shaft as follows:
(i) For pre-Modification TU 147 HMUs,
check the torque before accumulating 500
engine flight hours (FHs) since March 11,
2010 or before the next flight after the
effective date of this AD, whichever occurs
later. Use Paragraph 2.A. of Turbomeca Alert
Mandatory Service Bulletin (MSB) A292 73
2830, Version B, dated July 10, 2009 to do
the check.
(ii) For HMUs that incorporated
Modification TU 147 on or before March 31,
2010, and those HMUs not listed in Figure
2 or 3 of Turbomeca Alert MSB A292 73
2836, Version A, dated August 17, 2010,
check the torque before the next flight after
the effective date of this AD. Use Paragraph
2.A. of Turbomeca Alert MSB A292 73 2836,
Version A, dated August 17, 2010, to do the
check.
(2) If the HMU does not pass the torque
check, replace the HMU with a postModification TU 178 HMU before the next
flight after the effective date of this AD.
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on March 11, 2010 (75 FR
5689, February 4, 2010).
(i) Turbomeca Alert Mandatory Service
Bulletin (MSB) No. A292 73 2830, Version B,
dated July 10, 2009.
(ii) Reserved.
(4) The following service information was
approved for IBR on March 20, 2012 (77 FR
8092, February 14, 2012).
(i) Turbomeca Alert MSB No. A292 73
2836, Version A, dated August 17, 2010.
(ii) Reserved.
(5) For Safran Helicopter Engines, S.A,
service information identified in this AD,
contact Safran Helicopter Engines, S.A.,
40220 Tarnos, France; phone: (33) 05 59 74
40 00; fax: (33) 05 59 74 45 15.
(6) You may view this service information
at FAA, Engine and Propeller Standards
Branch, 1200 District Avenue, Burlington,
MA 01803. For information on the
availability of this material at the FAA, call
781–238–7759.
(7) 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.
(f) Compliance
(h) Mandatory Terminating Action
Within 2,200 engine FHs or 72 months
after the effective date of this AD, whichever
occurs first, replace any pre-Modification TU
178 HMU with a post-Modification TU 178
configuration HMU.
(i) Installation Prohibition
After the effective date of this AD, do not
install a pre-Modification TU 178 HMU on
engines incorporating a post-Modification TU
178 HMU.
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(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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 the attention of the person
identified in paragraph (k)(1) of this AD. You
may email your request to: ANE-AD-AMOC@
faa.gov.
(2) 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.
VerDate Sep<11>2014
16:30 Aug 07, 2018
Jkt 244001
Issued in Burlington, Massachusetts, on
July 31, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards
Branch, Aircraft Certification Service.
[FR Doc. 2018–16652 Filed 8–7–18; 8:45 am]
BILLING CODE 4910–13–P
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38953
Sfmt 4700
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0640; Product
Identifier 2018–NM–075–AD; Amendment
39–19343; AD 2018–16–03]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A319–133 airplanes
and Model A321–232 airplanes. This
AD requires modification and reidentification, or replacement, of certain
engine fan cowl doors (FCDs) and
installation of a placard in the flight
deck. This AD was prompted by reports
of in-service engine FCD losses, and the
development of a new FCD front latch
and keeper assembly that addresses this
unsafe condition. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD becomes effective
August 23, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 3, 2017 (82 FR 29371, June
29, 2017).
We must receive comments on this
AD by September 24, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: 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—EIAS, RondPoint Emile Dewoitine No: 2, 31700
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
SUMMARY:
E:\FR\FM\08AUR1.SGM
08AUR1
Agencies
[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Rules and Regulations]
[Pages 38951-38953]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16652]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
========================================================================
Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 /
Rules and Regulations
[[Page 38951]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0889; Product Identifier 2009-NE-35-AD; Amendment
39-19305; AD 2018-12-01]
RIN 2120-AA64
Airworthiness Directives; Safran Helicopter Engines, S.A.,
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2012-03-11 for
all Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft
engines. AD 2012-03-11 required checking the transmissible torque
between the low-pressure (LP) pump impeller and the high-pressure (HP)
pump shaft on the HP/LP pump and metering valve assembly, hereafter
referred to as the hydro-mechanical metering unit (HMU). Since we
issued AD 2012-03-11, the manufacturer determined that incorporating
Modification TU 178 is a more effective method to reduce the risk of
uncoupling between the LP fuel pump impeller and the HP fuel pump shaft
than the prior Modification TU 147. This AD requires inspection and
possible replacement of the HMU. This AD was prompted by three cases of
uncoupling of the HMU LP fuel pump impeller and the HP fuel pump shaft
since AD 2012-03-11 was issued. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective September 12, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 11,
2010 (75 FR 5689, February 4, 2010).
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 20,
2012 (77 FR 8092, February 14, 2012).
ADDRESSES: For service information identified in this final rule,
contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone:
(33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. You may view this
service information at the FAA, Engine and Propeller Standards Branch,
1200 District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call 781-238-7759. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2009-0889.
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-2009-
0889; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the mandatory continuing airworthiness information,
regulatory evaluation, any comments received, and other information.
The address for Docket Operations (phone: 800-647-5527) is Document
Operations, 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: John Frost, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7756; fax: 781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-03-11, Amendment 39-16953 (77 FR 8092,
February 14, 2012), (``AD 2012-03-11''). AD 2012-03-11 applied to all
Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines.
The NPRM published in the Federal Register on October 6, 2017 (82 FR
46727). The NPRM was prompted by instances of uncoupling between the LP
fuel pump impeller and the HP fuel pump shaft. The NPRM proposed to
require inspection and, depending on the results of the inspection,
possible replacement of the HMU. The NPRM also proposed to require
replacement of pre-Modification TU 178 HMUs with an HMU incorporating
Modification TU 178 within 2,200 engine flight hours or 72 months,
whichever occurs first, after the effective date of this AD. We are
issuing this AD to address 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 NPRM and
the FAA's response to the comment.
Request To Clarify Reason for AD
An individual commenter questioned how the new modification in this
AD is better and different from the actions required by the previous AD
2012-03-11.
AD 2012-03-11 required a check of the transmissible torque between
the LP fuel pump impeller and the HP fuel pump shaft and replacement of
the HMU if it does not pass the torque check. Since we issued AD 2012-
03-11, Safran Service Bulletin (SB) 292 73 2178, Version A, dated April
1, 2015 introduced Modification TU 178. This AD accepts Modification TU
178 as a more robust drive link between the LP fuel pump impeller and
the HP fuel pump shaft that ensures the LP impeller pump is driven even
if the link with the drive shaft loosens. This AD requires installation
of a Modification TU 178 HMU for any HMU that fails the torque sensor
check and as a mandatory terminating action for the inspections
required by this AD, as well as purging the fleet of the pre- and post-
TU 147 configuration parts. We did not change this AD.
Clarification to Service Information for Torque Check
We updated paragraphs (g)(1)(i) and (ii) of this AD to clarify that
only paragraph 2.A, rather than paragraph 2, in Turbomeca Alert
Mandatory SB (MSB) A292 73 2830, Version B, dated July 10, 2009, and
Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, is
used to perform the torque check.
[[Page 38952]]
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed Turbomeca, S.A., Alert MSB A292 73 2830, Version B,
dated July 10, 2009, and Alert MSB A292 73 2836, Version A, dated
August 17, 2010. Turbomeca Alert MSB A292 73 2830, Version B, describes
procedures for inspecting pre-Modification TU 147 HMUs. Turbomeca Alert
MSB A292 73 2836, Version A, dated August 17, 2010, describes
procedures for inspecting HMUs that have incorporated Modification TU
147. 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.
Other Related Service Information
We reviewed Safran Helicopter Engines MSB 292 73 2178, Version B,
dated March 23, 2017. Safran Helicopter Engines MSB 292 73 2178,
Version B, describes HMU improvements that includes a reinforced drive
link between the LP impeller and HP fuel pump shaft (Modification TU
178). Safran Helicopter Engines has also issued MSB A292 73 2830,
Version C; and A292 73 2836, Version B, both dated April 5, 2017, which
exempt HMUs incorporating Modification TU 178 from the inspections
previously recommended by Safran Helicopter Engines.
Costs of Compliance
We estimate that this AD affects 417 engines installed on
helicopters of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Remove and replace the HP/LP fuel pump 2 work-hours x $85 per $17,400 $17,570 $7,326,690
metering unit. hour = $170.
----------------------------------------------------------------------------------------------------------------
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 engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
Regulatory Findings
We have 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 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)
2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012), and
adding the following new AD:
2018-12-01 Safran Helicopter Engines (Type Certificate previously
held by Turbomeca, S.A.): Amendment 39-19305; Docket No. FAA-2009-
0889; Product Identifier 2009-NE-35-AD.
(a) Effective Date
This AD is effective September 12, 2018.
(b) Affected ADs
This AD replaces AD 2012-03-11, Amendment 39-16953 (77 FR 8092,
February 14, 2012).
(c) Applicability
This AD applies to Safran Helicopter Engines, S.A., Arriel 2B
and 2B1 turboshaft engines, except those incorporating Modification
TU 178.
(d) Subject
Joint Aircraft System Component (JASC) Code 7300, Engine Fuel
and Control.
(e) Unsafe Condition
This AD was prompted by analysis that indicated the modification
of an engine to incorporate Modification TU 178 provides a more
effective method than Modification TU
[[Page 38953]]
147 to reduce the risk of uncoupling between the low-pressure (LP)
fuel pump impeller and the high-pressure (HP) fuel pump shaft of the
HP/LP pump and hydro-mechanical metering unit (HMU). We are issuing
this AD to prevent failure of the HMU. The unsafe condition, if not
corrected, could result in failure of the engine, in-flight
shutdown, and loss of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Check the transmissible torque between the LP fuel pump
impeller and the HP fuel pump shaft as follows:
(i) For pre-Modification TU 147 HMUs, check the torque before
accumulating 500 engine flight hours (FHs) since March 11, 2010 or
before the next flight after the effective date of this AD,
whichever occurs later. Use Paragraph 2.A. of Turbomeca Alert
Mandatory Service Bulletin (MSB) A292 73 2830, Version B, dated July
10, 2009 to do the check.
(ii) For HMUs that incorporated Modification TU 147 on or before
March 31, 2010, and those HMUs not listed in Figure 2 or 3 of
Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010,
check the torque before the next flight after the effective date of
this AD. Use Paragraph 2.A. of Turbomeca Alert MSB A292 73 2836,
Version A, dated August 17, 2010, to do the check.
(2) If the HMU does not pass the torque check, replace the HMU
with a post-Modification TU 178 HMU before the next flight after the
effective date of this AD.
(h) Mandatory Terminating Action
Within 2,200 engine FHs or 72 months after the effective date of
this AD, whichever occurs first, replace any pre-Modification TU 178
HMU with a post-Modification TU 178 configuration HMU.
(i) Installation Prohibition
After the effective date of this AD, do not install a pre-
Modification TU 178 HMU on engines incorporating a post-Modification
TU 178 HMU.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, ECO 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 the attention of the person
identified in paragraph (k)(1) of this AD. You may email your
request to: [email protected].
(2) 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.
(k) Related Information
(1) For more information about this AD, contact John Frost,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email:
[email protected].
(2) Refer to European Aviation Safety Agency (EASA) AD 2017-
0102, dated June 13, 2017, for more information. You may examine the
EASA AD on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2009-0889.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
March 11, 2010 (75 FR 5689, February 4, 2010).
(i) Turbomeca Alert Mandatory Service Bulletin (MSB) No. A292 73
2830, Version B, dated July 10, 2009.
(ii) Reserved.
(4) The following service information was approved for IBR on
March 20, 2012 (77 FR 8092, February 14, 2012).
(i) Turbomeca Alert MSB No. A292 73 2836, Version A, dated
August 17, 2010.
(ii) Reserved.
(5) For Safran Helicopter Engines, S.A, service information
identified in this AD, contact Safran Helicopter Engines, S.A.,
40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74
45 15.
(6) You may view this service information at FAA, Engine and
Propeller Standards Branch, 1200 District Avenue, Burlington, MA
01803. For information on the availability of this material at the
FAA, call 781-238-7759.
(7) 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 Burlington, Massachusetts, on July 31, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification
Service.
[FR Doc. 2018-16652 Filed 8-7-18; 8:45 am]
BILLING CODE 4910-13-P