Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters, 72505-72507 [2016-24860]
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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
compact fluorescent lamps, or integrated LED
lamps.
2. Definitions:
Measured initial input power means the
input power to the lamp, measured after the
lamp is stabilized and seasoned (if
applicable), and expressed in watts (W).
Measured initial lumen output means the
lumen output of the lamp, measured after the
lamp is stabilized and seasoned (if
applicable), and expressed in lumens (lm).
Power factor means the measured initial
input power (watts) divided by the product
of the input voltage (volts) and the input
current (amps) measured at the same time as
the initial input power.
3. Active Mode Test Procedures
3.1. Take measurements at full light
output.
3.2. Do not use a goniophotometer.
3.3. For single base OLED and nonintegrated LED lamps, position a lamp in
either the base-up and base-down orientation
throughout testing. Test an equal number of
lamps in the sample in the base-up and basedown orientations, except that, if the
manufacturer restricts the orientation, test all
of the units in the sample in the
manufacturer-specified orientation. For
double base OLED and non-integrated LED
lamps, test all units in the horizontal
orientation except that, if the manufacturer
restricts the orientation, test all of the units
in the sample in the manufacturer-specified
orientation.
3.4. Operate the lamp at the rated voltage
throughout testing. For lamps with multiple
rated voltages including 120 volts, operate
the lamp at 120 volts. If a lamp is not rated
for 120 volts, operate the lamp at the highest
72505
rated input voltage. For non-integrated LED
lamps, operate the lamp at the manufacturerdeclared input voltage and current.
3.5. Operate the lamp at the maximum
input power. If multiple modes occur at the
same maximum input power (such as
variable CCT or CRI), the manufacturer may
select any of these modes for testing;
however, all measurements must be taken at
the same selected mode. The manufacturer
must indicate in the test report which mode
was selected for testing and include detail
such that another laboratory could operate
the lamp in the same mode.
3.6. To measure initial lumen output, input
power, input voltage, and input current use
the test procedures in the table in this
section.
TABLE 3.1—REFERENCES TO INDUSTRY STANDARD TEST PROCEDURES
Lamp type
Referenced test procedure
General service incandescent lamps .......................................................
Compact fluorescent lamps ......................................................................
Integrated LED lamps ...............................................................................
Other incandescent lamps that are not reflector lamps ...........................
Other incandescent lamps that are reflector lamps .................................
Other fluorescent lamps ...........................................................................
OLED lamps .............................................................................................
Appendix R to subpart B of 10 CFR part 430.
Appendix W to subpart B of 10 CFR part 430.
Appendix BB to subpart B of 10 CFR part 430.
IES LM–45–15, sections 4–6, and section 7.1.*
IES LM–20–13, sections 4–6, and section 8.*
IES LM–9–09–DD, sections 4–6, and section 7.5.*
IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0,
9.1 and 9.2.*
IES LM–79–08–DD, sections 1.3 (except 1.3f), 2.0, 3.0, 5.0, 7.0, 8.0,
9.1 and 9.2.*
Non-integrated LED lamps .......................................................................
asabaliauskas on DSK3SPTVN1PROD with RULES
* Incorporated by reference, see § 430.3.
3.7. Determine initial lamp efficacy by
dividing the measured initial lumen output
(lumens) by the measured initial input power
(watts).
3.8. Determine power factor by dividing
the measured initial input power (watts) by
the product of the measured input voltage
(volts) and measured input current (amps).
4. Standby Mode Test Procedure
4.1. Measure standby mode power only for
lamps that are capable of standby mode
operation.
4.2. Maintain lamp orientation as specified
in section 3.3 of this appendix.
4.3. Connect the lamp to the manufacturerspecified wireless control network (if
applicable) and configure the lamp in
standby mode by sending a signal to the lamp
instructing it to have zero light output. Lamp
must remain connected to the network
throughout testing.
4.4. Operate the lamp at the rated voltage
throughout testing. For lamps with multiple
rated voltages including 120 volts, operate
the lamp at 120 volts. If a lamp is not rated
for 120 volts, operate the lamp at the highest
rated input voltage.
4.5. Stabilize the lamp prior to
measurement as specified in section 5 of IEC
62301–DD (incorporated by reference; see
§ 430.3).
4.6. Measure the standby mode power in
watts as specified in section 5 of IEC 62301–
DD (incorporated by reference; see § 430.3).
[FR Doc. 2016–25180 Filed 10–19–16; 8:45 am]
BILLING CODE 6450–01–P
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15:55 Oct 19, 2016
Jkt 241001
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
movement of the output lever in an
axial direction, contact of a bolt
connecting the control rod to an output
lever with the actuator housing, and
subsequent loss of helicopter control.
DATES: This AD is effective November
25, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Airbus Helicopters, Inc., 2701 N. Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model MBB–BK 117 C–2
helicopters with certain duplex trim
actuators installed. This AD requires
repetitively inspecting the lateral and
longitudinal trim actuator output levers
for correct torque of the nuts. This AD
was prompted by a design review that
indicated the attachment screws can
become loose under certain
circumstances. These actions are
intended to prevent the loss of an
attachment screw, which could result in
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov 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 European
Aviation Safety Agency (EASA) AD, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (phone: 800–647–5527) is U.S.
Department of Transportation, Docket
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0578; Directorate
Identifier 2013–SW–048–AD; Amendment
39–18684; AD 2016–21–03]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
(Previously Eurocopter Deutschland
GmbH) (Airbus Helicopters)
Helicopters
AGENCY:
SUMMARY:
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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
Operations Office, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt
Wilbanks, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Room 6N–321, Fort
Worth, TX 76177; telephone (817) 222–
5110; email matt.wilbanks@faa.gov.
SUPPLEMENTARY INFORMATION:
asabaliauskas on DSK3SPTVN1PROD with RULES
Discussion
On August 18, 2014, at 79 FR 48696,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 by adding an AD that would apply
to Airbus Helicopters Model MBB–BK
117 C–2 helicopters with a lateral
duplex trim actuator, part number (P/N)
418–00878–050 or P/N 418–00878–051,
or a longitudinal duplex trim actuator,
P/N 418–00878–000 or P/N 418–00878–
001, installed. The NPRM proposed to
require repetitively inspecting the
lateral and longitudinal trim actuator
output levers for correct torque of the
nuts. The proposed requirements were
intended to prevent a loose attachment
screw, which could result in movement
of the output lever in an axial direction,
contact of a bolt connecting the control
rod to an output lever with the actuator
housing, and subsequent loss of
helicopter control.
The NPRM was prompted by AD No.
2013–0182, dated August 12, 2013,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for Airbus Helicopters Model
MBB–BK 117 C–2 helicopters with a
lateral duplex trim actuator, P/N 418–
00878–050 or P/N 418–00878–051, or
with a longitudinal duplex trim
actuator, P/N 418–00878–000 or P/N
418–00878–001. EASA advises that
under unfavorable circumstances, a total
loss of the trim actuator output lever
attachment screw could lead to a
restriction of the lateral and
longitudinal control range. According to
EASA, without the attachment screw,
the output lever can move in the axial
direction. This condition, if not
detected, could cause the bolt that
connects the control rod to the output
lever to make contact with actuator
housing, possibly resulting in reduced
control of the helicopter.
To prevent this condition, EASA
requires an initial torque check of the
lateral and longitudinal trim actuator
output lever attachment screws, the
application of a torque marking, and
repetitive inspections for correct torque
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15:55 Oct 19, 2016
Jkt 241001
thereafter. The EASA AD’s requirements
are considered an interim solution,
pending a terminating modification.
Since the issuance of EASA AD No.
2013–0182, Eurocopter Deutschland
GmbH has changed its name to Airbus
Helicopters Deutschland GmbH.
parts are needed, so the cost for the U.S.
fleet totals $8,500.
• Visually inspecting for correct
torque requires 0.5 work-hour for a labor
cost of about $43. No parts are needed,
so the total cost for the U.S. fleet is
$4,300 per inspection cycle.
Comments
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
helicopters identified in this rulemaking
action.
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(79 FR 48696, August 18, 2014).
FAA’s Determination
These helicopters have been approved
by the aviation authority of Germany
and are approved for operation in the
United States. Pursuant to our bilateral
agreement with Germany, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Interim Action
We consider this AD to be an interim
action because Airbus Helicopters is
currently developing a modification that
will address the unsafe condition
identified in this AD. Once this
modification is developed, approved
and available, we might consider
additional rulemaking.
Related Service Information
We reviewed Eurocopter (now Airbus
Helicopters) Alert Service Bulletin
MBB–BK117 C–2–67A–020, Revision 0,
dated June 18, 2013 (ASB), which
advises of a design review that showed
that a loss of the attachment screw of
the trim actuator output lever could
restrict the lateral and longitudinal
control range. The ASB consequently
calls for an initial torque check and
application of torque markings of the
self-locking nuts, and subsequent
repetitive inspections to maintain the
proper torque.
Costs of Compliance
We estimate that this AD affects 100
helicopters of U.S. Registry and that
labor costs average $85 per work-hour.
Based on these estimates, we expect the
following costs:
• Applying torque and torque
marking to the lateral and longitudinal
trim actuator output levers requires 1
work-hour for a labor cost of $85. No
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Regulatory Findings
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 to the extent that it justifies
making a regulatory distinction; 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.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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,
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Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–21–03 Airbus Helicopters
Deutschland GmbH (Previously
Eurocopter Deutschland GmbH) (Airbus
Helicopters) Helicopters: Amendment
39–18684; Docket No. FAA–2014–0578;
Directorate Identifier 2013–SW–048–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model MBB–BK 117 C–2 helicopters with a
lateral duplex trim actuator, part number (P/
N) 418–00878–050 or P/N 418–00878–051, or
a longitudinal duplex trim actuator, P/N 418–
00878–000 or P/N 418–00878–001, installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
loss of a trim actuator output lever
attachment screw. This condition could
result in movement of the output lever in an
axial direction, contact of a bolt connecting
the control rod to an output lever with the
actuator housing, and subsequent loss of
control of the helicopter.
(c) Effective Date
This AD becomes effective November 25,
2016.
asabaliauskas on DSK3SPTVN1PROD with RULES
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Within 300 hours time-in-service (TIS),
apply a torque of 31.0 inch-pounds (3.5 Nm)
to the self-locking nut (nut) on each lateral
and longitudinal trim actuator output lever
and apply a torque marking between the nut
and the screw.
(2) Thereafter at intervals not to exceed 400
hours TIS, visually inspect each nut on each
lateral and longitudinal trim actuator output
lever to determine whether the torque is at
31.0 inch-pounds (3.5 Nm). If the torque is
not at 31.0 inch-pounds, apply a torque of
31.0 inch-pounds (3.5 Nm), remove the
previous torque marking, and apply a new
torque marking between the nut and the
screw.
(3) Do not install a lateral duplex trim
actuator, part number (P/N) 418–00878–050
or P/N 418–00878–051, or a longitudinal
duplex trim actuator, P/N 418–00878–000 or
P/N 418–00878–001, on any helicopter
unless each nut has been inspected for
proper torque in accordance with the
requirements of this AD.
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Jkt 241001
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Wilbanks,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
10101 Hillwood Pkwy., Room 6N–321, Fort
Worth, TX 76177; telephone (817) 222–5110;
email 9-ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
(1) Eurocopter Alert Service Bulletin MBB–
BK117 C–2–67A–020, Revision 0, dated June
18, 2013, which is not incorporated by
reference, contains additional information
about the subject of this AD. For service
information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N.
Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub. You
may review a copy of the service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Parkway,
Room 6N–321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
the European Aviation Agency (EASA) AD
No. 2013–0182, dated August 12, 2013. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2014–0578.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6700, Rotorcraft Flight Control.
Issued in Fort Worth, Texas, on October 5,
2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2016–24860 Filed 10–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5589; Directorate
Identifier 2014–NM–252–AD; Amendment
39–18678; AD 2016–20–12]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
PO 00000
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72507
We are superseding
Airworthiness Directive (AD) 2012–20–
07 for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2012–20–07 required revising the
Airworthiness Limitations section (ALS)
of the Instructions for Continued
Airworthiness (ICA) to incorporate new
limitations for fuel tank systems, and
revising the maintenance program to
incorporate revised fuel maintenance
and inspection tasks. This new AD
requires revising the maintenance or
inspection program to incorporate
revised fuel airworthiness limitations.
This AD was prompted by Airbus
issuing more restrictive maintenance
requirements and/or airworthiness
limitations. We are issuing this AD to
prevent the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in a fuel tank explosion and consequent
loss of the airplane.
DATES: This AD is effective November
25, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 25, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 21, 2012 (77 FR
63716, October 17, 2012).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of December 14, 2009 (74 FR
62219, November 27, 2009).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of August 28, 2007 (72 FR
40222, July 24, 2007).
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@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–2016–
5589.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
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20OCR1
]]>Agencies
[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)]
[Rules and Regulations]
[Pages 72505-72507]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24860]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0578; Directorate Identifier 2013-SW-048-AD;
Amendment 39-18684; AD 2016-21-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(Previously Eurocopter Deutschland GmbH) (Airbus Helicopters)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Model MBB-BK 117 C-2 helicopters with certain duplex trim
actuators installed. This AD requires repetitively inspecting the
lateral and longitudinal trim actuator output levers for correct torque
of the nuts. This AD was prompted by a design review that indicated the
attachment screws can become loose under certain circumstances. These
actions are intended to prevent the loss of an attachment screw, which
could result in movement of the output lever in an axial direction,
contact of a bolt connecting the control rod to an output lever with
the actuator housing, and subsequent loss of helicopter control.
DATES: This AD is effective November 25, 2016.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie,
TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at https://www.airbushelicopters.com/techpub. You may review
the referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort
Worth, TX 76177.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov 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 European Aviation Safety
Agency (EASA) AD, the economic evaluation, any comments received, and
other information. The street address for the Docket Operations Office
(phone: 800-647-5527) is U.S. Department of Transportation, Docket
[[Page 72506]]
Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177; telephone
(817) 222-5110; email matt.wilbanks@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On August 18, 2014, at 79 FR 48696, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Airbus Helicopters
Model MBB-BK 117 C-2 helicopters with a lateral duplex trim actuator,
part number (P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal
duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-001,
installed. The NPRM proposed to require repetitively inspecting the
lateral and longitudinal trim actuator output levers for correct torque
of the nuts. The proposed requirements were intended to prevent a loose
attachment screw, which could result in movement of the output lever in
an axial direction, contact of a bolt connecting the control rod to an
output lever with the actuator housing, and subsequent loss of
helicopter control.
The NPRM was prompted by AD No. 2013-0182, dated August 12, 2013,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Airbus
Helicopters Model MBB-BK 117 C-2 helicopters with a lateral duplex trim
actuator, P/N 418-00878-050 or P/N 418-00878-051, or with a
longitudinal duplex trim actuator, P/N 418-00878-000 or P/N 418-00878-
001. EASA advises that under unfavorable circumstances, a total loss of
the trim actuator output lever attachment screw could lead to a
restriction of the lateral and longitudinal control range. According to
EASA, without the attachment screw, the output lever can move in the
axial direction. This condition, if not detected, could cause the bolt
that connects the control rod to the output lever to make contact with
actuator housing, possibly resulting in reduced control of the
helicopter.
To prevent this condition, EASA requires an initial torque check of
the lateral and longitudinal trim actuator output lever attachment
screws, the application of a torque marking, and repetitive inspections
for correct torque thereafter. The EASA AD's requirements are
considered an interim solution, pending a terminating modification.
Since the issuance of EASA AD No. 2013-0182, Eurocopter Deutschland
GmbH has changed its name to Airbus Helicopters Deutschland GmbH.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (79 FR 48696, August
18, 2014).
FAA's Determination
These helicopters have been approved by the aviation authority of
Germany and are approved for operation in the United States. Pursuant
to our bilateral agreement with Germany, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed.
Interim Action
We consider this AD to be an interim action because Airbus
Helicopters is currently developing a modification that will address
the unsafe condition identified in this AD. Once this modification is
developed, approved and available, we might consider additional
rulemaking.
Related Service Information
We reviewed Eurocopter (now Airbus Helicopters) Alert Service
Bulletin MBB-BK117 C-2-67A-020, Revision 0, dated June 18, 2013 (ASB),
which advises of a design review that showed that a loss of the
attachment screw of the trim actuator output lever could restrict the
lateral and longitudinal control range. The ASB consequently calls for
an initial torque check and application of torque markings of the self-
locking nuts, and subsequent repetitive inspections to maintain the
proper torque.
Costs of Compliance
We estimate that this AD affects 100 helicopters of U.S. Registry
and that labor costs average $85 per work-hour. Based on these
estimates, we expect the following costs:
Applying torque and torque marking to the lateral and
longitudinal trim actuator output levers requires 1 work-hour for a
labor cost of $85. No parts are needed, so the cost for the U.S. fleet
totals $8,500.
Visually inspecting for correct torque requires 0.5 work-
hour for a labor cost of about $43. No parts are needed, so the total
cost for the U.S. fleet is $4,300 per inspection cycle.
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 helicopters identified in this
rulemaking action.
Regulatory Findings
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 to the extent
that it justifies making a regulatory distinction; 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.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
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,
[[Page 72507]]
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-21-03 Airbus Helicopters Deutschland GmbH (Previously
Eurocopter Deutschland GmbH) (Airbus Helicopters) Helicopters:
Amendment 39-18684; Docket No. FAA-2014-0578; Directorate Identifier
2013-SW-048-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model MBB-BK 117 C-2
helicopters with a lateral duplex trim actuator, part number (P/N)
418-00878-050 or P/N 418-00878-051, or a longitudinal duplex trim
actuator, P/N 418-00878-000 or P/N 418-00878-001, installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as loss of a trim actuator
output lever attachment screw. This condition could result in
movement of the output lever in an axial direction, contact of a
bolt connecting the control rod to an output lever with the actuator
housing, and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective November 25, 2016.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) Within 300 hours time-in-service (TIS), apply a torque of
31.0 inch-pounds (3.5 Nm) to the self-locking nut (nut) on each
lateral and longitudinal trim actuator output lever and apply a
torque marking between the nut and the screw.
(2) Thereafter at intervals not to exceed 400 hours TIS,
visually inspect each nut on each lateral and longitudinal trim
actuator output lever to determine whether the torque is at 31.0
inch-pounds (3.5 Nm). If the torque is not at 31.0 inch-pounds,
apply a torque of 31.0 inch-pounds (3.5 Nm), remove the previous
torque marking, and apply a new torque marking between the nut and
the screw.
(3) Do not install a lateral duplex trim actuator, part number
(P/N) 418-00878-050 or P/N 418-00878-051, or a longitudinal duplex
trim actuator, P/N 418-00878-000 or P/N 418-00878-001, on any
helicopter unless each nut has been inspected for proper torque in
accordance with the requirements of this AD.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177; telephone
(817) 222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(g) Additional Information
(1) Eurocopter Alert Service Bulletin MBB-BK117 C-2-67A-020,
Revision 0, dated June 18, 2013, which is not incorporated by
reference, contains additional information about the subject of this
AD. For service information identified in this final rule, contact
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at https://www.airbushelicopters.com/techpub. You may review
a copy of the service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-321, Fort
Worth, TX 76177.
(2) The subject of this AD is addressed in the European Aviation
Agency (EASA) AD No. 2013-0182, dated August 12, 2013. You may view
the EASA AD on the Internet at https://www.regulations.gov in Docket
No. FAA-2014-0578.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft
Flight Control.
Issued in Fort Worth, Texas, on October 5, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-24860 Filed 10-19-16; 8:45 am]
BILLING CODE 4910-13-P
