Airworthiness Directives; Airbus Helicopters Deutschland GmbH, 16895-16897 [2017-06706]
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Federal Register / Vol. 82, No. 66 / Friday, April 7, 2017 / Rules and Regulations
prior opportunities for comment
described above.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the following special conditions are
issued as part of the type certification
basis for Boeing Model 777–200
airplanes modified by VT DRB Aviation
Consultants.
1. For seats with an airbag system in
the shoulder belts, show that the airbag
system in the shoulder belt will deploy
and provide protection under crash
conditions where it is necessary to
prevent serious injury. The means of
protection must take into consideration
a range of stature from a 2-year-old child
to a 95th percentile male. The airbag
system in the shoulder belt must
provide a consistent approach to energy
absorption throughout that range of
occupants. When the seat system
includes an airbag system, that system
must be included in each of the
certification tests as it would be
installed in the airplane. In addition, the
following situations must be considered:
a. The seat occupant is holding an
infant.
b. The seat occupant is a pregnant
woman.
2. The airbag system in the shoulder
belt must provide adequate protection
for each occupant regardless of the
number of occupants of the seat
assembly, considering that unoccupied
seats may have an active airbag system
in the shoulder belt.
3. The design must prevent the airbag
system in the shoulder belt from being
either incorrectly buckled or incorrectly
installed, such that the airbag system in
the shoulder belt would not properly
deploy. Alternatively, it must be shown
that such deployment is not hazardous
to the occupant, and will provide the
required injury protection.
4. It must be shown that the airbag
system in the shoulder belt is not
susceptible to inadvertent deployment
as a result of wear and tear, or inertial
loads resulting from in-flight or ground
maneuvers (including gusts and hard
landings), and other operating and
environmental conditions (vibrations,
moisture, etc.) likely to occur in service.
5. Deployment of the airbag system in
the shoulder belt must not injure the
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■
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14:50 Apr 06, 2017
Jkt 241001
seated occupant, including injuries that
could impede rapid egress. This
assessment should include an occupant
whose belt is loosely fastened.
6. It must be shown that inadvertent
deployment of the airbag system in the
shoulder belt, during the most critical
part of the flight, will either meet the
requirement of § 25.1309(b) or not cause
a hazard to the airplane or its occupants.
7. It must be shown that the airbag
system in the shoulder belt will not
impede rapid egress of occupants 10
seconds after airbag deployment.
8. The airbag system must be
protected from lightning and highintensity radiated fields (HIRF). The
threats to the airplane specified in
existing regulations regarding lighting,
§ 25.1316, and HIRF, § 25.1317, are
incorporated by reference for the
purpose of measuring lightning and
HIRF protection.
9. The airbag system in the shoulder
belt must function properly after loss of
normal aircraft electrical power, and
after a transverse separation of the
fuselage at the most critical location. A
separation at the location of the airbag
system in the shoulder belt does not
have to be considered.
10. It must be shown that the airbag
system in the shoulder belt will not
release hazardous quantities of gas or
particulate matter into the cabin.
11. The airbag system in the shoulderbelt installation must be protected from
the effects of in-flight fire such that no
hazard to occupants will result.
12. A means must be available for a
crewmember to verify the integrity of
the airbag system in the shoulder-belt
activation system prior to each flight, or
it must be demonstrated to reliably
operate between inspection intervals.
The FAA considers that the loss of the
airbag-system deployment function
alone (i.e., independent of the
conditional event that requires the
airbag-system deployment) is a majorfailure condition.
13. The inflatable material may not
have an average burn rate of greater than
2.5 inches/minute when tested using the
horizontal flammability test defined in
part 25, appendix F, part I, paragraph
(b)(5).
14. The airbag system in the shoulder
belt, once deployed, must not adversely
affect the emergency-lighting system
(i.e., block floor proximity lights to the
extent that the lights no longer meet
their intended function).
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16895
Issued in Renton, Washington, on March
31, 2017.
Michael Kaszycki,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–06930 Filed 4–6–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3257; Directorate
Identifier 2015–SW–072–AD; Amendment
39–18846; AD 2017–07–08]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters Deutschland GmbH (Airbus
Helicopters) Model MBB–BK 117 D–2
helicopters. This AD requires
repetitively inspecting the engine mount
bushings. This AD was prompted by
reports of delaminated and worn
bushings. The actions of this AD are
intended to prevent an unsafe condition
on these products.
DATES: This AD is effective May 12,
2017.
SUMMARY:
For service information
identified in this final rule, contact
Airbus Helicopters, 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
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX
76177.
ADDRESSES:
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–2016–
3257; 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.
E:\FR\FM\07APR1.SGM
07APR1
16896
Federal Register / Vol. 82, No. 66 / Friday, April 7, 2017 / Rules and Regulations
Department of Transportation, Docket
Operations Office, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Group, Rotorcraft
Directorate, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone
(817) 222–5110; email matthew.fuller@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On November 21, 2016, at 81 FR
83182, 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 D–2 helicopters
with a bushing part number 105–60386
installed. The NPRM proposed to
require repetitively inspecting the
bushings of the inner and outer forward
trusses of both engines and repairing or
replacing the bushings, depending on
the outcome of the inspections. The
proposed requirements were intended to
detect delaminated engine mount
bushings, which can lead to excessive
vibration, cracking, failure of the engine
mount front support pins, and loss of
helicopter control.
The NPRM was prompted by AD No.
2015–0198, dated September 30, 2015,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union. EASA advises of
delaminated engine mount bushings.
According to EASA, this condition
could lead to cracks and eventually
failure of the engine mount front
support pins, possibly resulting in loss
of helicopter control.
The EASA AD consequently requires
repetitive inspections of the engine
mount bushings and depending of the
findings, repairing or replacing the
bushings.
Comments
nlaroche on DSK30NT082PROD with RULES
We gave the public the opportunity to
participate in developing this AD. We
received one comment. However, the
comment addressed neither the
proposed actions nor the determination
of the cost to the public. Therefore, we
have made no changes to this AD.
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
VerDate Sep<11>2014
14:50 Apr 06, 2017
Jkt 241001
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.
Differences Between This AD and the
EASA AD
The EASA AD allows for a 10 hour
time-in-service, non-cumulative
tolerance for its required compliance
times. This AD does not.
Related Service Information
We reviewed Airbus Helicopters Alert
Service Bulletin (ASB) MBB–BK117 D–
2–71A–002, Revision 0, dated
September 28, 2015, for Model MBB–BK
117 D–2 helicopters. The ASB
introduces repetitive visual inspections
of the engine mount bushings for
defects, deformation, separation of the
rubber, and missing rubber after reports
of delaminated engine mount bushings
and bushings with damage to the metal
inner sleeve. If there is any deformation
or separation of the rubber, the ASB
specifies performing a detailed
inspection of the bushing in accordance
with the aircraft maintenance manual.
Costs of Compliance
We estimate that this AD affects 5
helicopters of U.S. Registry and that
labor costs average $85 per work hour.
Based on these estimates, we expect the
following costs:
• Inspecting the bushings requires 1
work hour. No parts are needed, for a
total cost of $85 per helicopter and $425
for the U.S. fleet.
• Replacing a bushing requires 1
work hour and $373 for parts, for a total
cost of $458 per bushing.
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
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Frm 00006
Fmt 4700
Sfmt 4700
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
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,
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):
■
2017–07–08 Airbus Helicopters
Deutschland GmbH: Amendment 39–
18846; Docket No. FAA–2016–3257;
Directorate Identifier 2015–SW–072–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Deutschland GmbH Model MBB–BK 117 D–
2 helicopters with a bushing part number
105–60386 installed, certificated in any
category.
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07APR1
Federal Register / Vol. 82, No. 66 / Friday, April 7, 2017 / Rules and Regulations
(b) Unsafe Condition
This AD defines the unsafe condition as a
delaminated engine mount bushing. This
condition could result in excessive vibration,
which could lead to cracking and failure of
the engine mount front support pins, and loss
of helicopter control.
(c) Effective Date
This AD becomes effective May 12, 2017.
(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
Within 50 hours time-in-service (TIS) and
thereafter at intervals not to exceed 50 hours
TIS:
(1) Visually inspect each engine mount
bushing (bushing) for separation of the
rubber from the metal or missing rubber.
(2) If any rubber has separated from the
metal or if there is missing rubber, inspect
the bushing for deformation, corrosion, and
mechanical damage.
(i) Replace the bushing with an airworthy
bushing if there is any deformation,
separation of the rubber from the metal,
corrosion, or mechanical damage, or repair
the bushing if the deformation, separation of
the rubber, corrosion, or mechanical damage
is within the maximum repair damage
limitations.
(ii) If the inner and outer parts of the
bushing are separated with missing rubber,
replace the bushing with an airworthy
bushing.
nlaroche on DSK30NT082PROD with RULES
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Fuller,
Senior Aviation Safety Engineer, Safety
Management Group, Rotorcraft Directorate,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email 9ASW-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) Airbus Helicopters Alert Service
Bulletin ASB MBB–BK117 D–2–71A–002,
Revision 0, dated September 28, 2015, which
is not incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
AD, contact Airbus Helicopters, 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
VerDate Sep<11>2014
14:50 Apr 06, 2017
Jkt 241001
Hillwood Pkwy., Room 6N–321, Fort Worth,
TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2015–0198, dated September 30, 2015.
You may view the EASA AD on the Internet
at https://www.regulations.gov in Docket No.
FAA–2016–3257.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 7200, Engine (Turbine, Turboprop).
Issued in Fort Worth, Texas, on March 29,
2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2017–06706 Filed 4–6–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
16897
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
7095; 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 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 Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kristopher Greer, Aerospace Engineer,
Boston Aircraft Certification Office,
Engine & Propeller Directorate, FAA,
1200 District Avenue, Burlington,
Massachusetts 01803; telephone 781–
238–7799; email Kristopher.Greer@
faa.gov.
14 CFR Part 39
SUPPLEMENTARY INFORMATION:
[Docket No. FAA–2015–7095; Directorate
Identifier 2015–SW–085–AD; Amendment
39–18848; AD 2017–07–09]
Discussion
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Sikorsky Aircraft Corporation (Sikorsky)
Model S–92A helicopters. This AD
requires removing from service the tail
gearbox center housing (housing) when
it has 12,200 or more hours time-inservice (TIS). This AD was prompted by
fatigue analysis conducted by Sikorsky
that determined the housing required a
retirement life. The actions are intended
to prevent an unsafe condition on these
products.
DATES: This AD is effective May 12,
2017.
SUMMARY:
For service information
identified in this final rule, contact
Sikorsky Aircraft Corporation, Customer
Service Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1–800Winged-S or 203–416–4299; email: wcs_
cust_service_eng.gr-sik@lmco.com. You
may review a copy of the referenced
service information at the FAA, Office
of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room
6N–321, Fort Worth, TX 76177.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
On August 30, 2016, at 81 FR 59526,
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 Sikorsky Model S–92A helicopters
with a housing part number (P/N)
92358–06107–043 installed. The NPRM
proposed to require removing from
service any housing with 12,200 or more
hours TIS. The NPRM was prompted by
fatigue analysis conducted by Sikorsky
that determined the housing required a
retirement life. The proposed actions
were intended to prevent a crack in the
housing, which could lead to loss of tail
rotor drive and loss of helicopter
control.
Comments
After our NPRM was published, we
received a comment from Sikorsky.
Request
Sikorsky requested a minimum 45day extension of the comment period. In
support of this request, Sikorsky stated
it is re-evaluating the housing’s 12,200hour life limit due to an error in the
measured flight test loads used in the
structural fatigue substantiation. When
asked for additional information,
Sikorsky advised that it had completed
its re-evaluation and determined that
the 12,200-hour life limit was, in fact,
correct.
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other products of
E:\FR\FM\07APR1.SGM
07APR1
Agencies
[Federal Register Volume 82, Number 66 (Friday, April 7, 2017)]
[Rules and Regulations]
[Pages 16895-16897]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06706]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-3257; Directorate Identifier 2015-SW-072-AD;
Amendment 39-18846; AD 2017-07-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 D-2
helicopters. This AD requires repetitively inspecting the engine mount
bushings. This AD was prompted by reports of delaminated and worn
bushings. The actions of this AD are intended to prevent an unsafe
condition on these products.
DATES: This AD is effective May 12, 2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, 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 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 by searching for and locating Docket No. FAA-2016-
3257; 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.
[[Page 16896]]
Department of Transportation, Docket Operations Office, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On November 21, 2016, at 81 FR 83182, 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 D-2 helicopters with a bushing part number
105-60386 installed. The NPRM proposed to require repetitively
inspecting the bushings of the inner and outer forward trusses of both
engines and repairing or replacing the bushings, depending on the
outcome of the inspections. The proposed requirements were intended to
detect delaminated engine mount bushings, which can lead to excessive
vibration, cracking, failure of the engine mount front support pins,
and loss of helicopter control.
The NPRM was prompted by AD No. 2015-0198, dated September 30,
2015, issued by EASA, which is the Technical Agent for the Member
States of the European Union. EASA advises of delaminated engine mount
bushings. According to EASA, this condition could lead to cracks and
eventually failure of the engine mount front support pins, possibly
resulting in loss of helicopter control.
The EASA AD consequently requires repetitive inspections of the
engine mount bushings and depending of the findings, repairing or
replacing the bushings.
Comments
We gave the public the opportunity to participate in developing
this AD. We received one comment. However, the comment addressed
neither the proposed actions nor the determination of the cost to the
public. Therefore, we have made no changes to this AD.
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.
Differences Between This AD and the EASA AD
The EASA AD allows for a 10 hour time-in-service, non-cumulative
tolerance for its required compliance times. This AD does not.
Related Service Information
We reviewed Airbus Helicopters Alert Service Bulletin (ASB) MBB-
BK117 D-2-71A-002, Revision 0, dated September 28, 2015, for Model MBB-
BK 117 D-2 helicopters. The ASB introduces repetitive visual
inspections of the engine mount bushings for defects, deformation,
separation of the rubber, and missing rubber after reports of
delaminated engine mount bushings and bushings with damage to the metal
inner sleeve. If there is any deformation or separation of the rubber,
the ASB specifies performing a detailed inspection of the bushing in
accordance with the aircraft maintenance manual.
Costs of Compliance
We estimate that this AD affects 5 helicopters of U.S. Registry and
that labor costs average $85 per work hour. Based on these estimates,
we expect the following costs:
Inspecting the bushings requires 1 work hour. No parts are
needed, for a total cost of $85 per helicopter and $425 for the U.S.
fleet.
Replacing a bushing requires 1 work hour and $373 for
parts, for a total cost of $458 per bushing.
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
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, 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):
2017-07-08 Airbus Helicopters Deutschland GmbH: Amendment 39-18846;
Docket No. FAA-2016-3257; Directorate Identifier 2015-SW-072-AD.
(a) Applicability
This AD applies to Airbus Helicopters Deutschland GmbH Model
MBB-BK 117 D-2 helicopters with a bushing part number 105-60386
installed, certificated in any category.
[[Page 16897]]
(b) Unsafe Condition
This AD defines the unsafe condition as a delaminated engine
mount bushing. This condition could result in excessive vibration,
which could lead to cracking and failure of the engine mount front
support pins, and loss of helicopter control.
(c) Effective Date
This AD becomes effective May 12, 2017.
(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
Within 50 hours time-in-service (TIS) and thereafter at
intervals not to exceed 50 hours TIS:
(1) Visually inspect each engine mount bushing (bushing) for
separation of the rubber from the metal or missing rubber.
(2) If any rubber has separated from the metal or if there is
missing rubber, inspect the bushing for deformation, corrosion, and
mechanical damage.
(i) Replace the bushing with an airworthy bushing if there is
any deformation, separation of the rubber from the metal, corrosion,
or mechanical damage, or repair the bushing if the deformation,
separation of the rubber, corrosion, or mechanical damage is within
the maximum repair damage limitations.
(ii) If the inner and outer parts of the bushing are separated
with missing rubber, replace the bushing with an airworthy bushing.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Group, Rotorcraft Directorate,
FAA, 10101 Hillwood Pkwy., 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) Airbus Helicopters Alert Service Bulletin ASB MBB-BK117 D-2-
71A-002, Revision 0, dated September 28, 2015, which is not
incorporated by reference, contains additional information about the
subject of this AD. For service information identified in AD,
contact Airbus Helicopters, 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.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2015-0198, dated September 30, 2015. You
may view the EASA AD on the Internet at https://www.regulations.gov
in Docket No. FAA-2016-3257.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 7200, Engine
(Turbine, Turboprop).
Issued in Fort Worth, Texas, on March 29, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-06706 Filed 4-6-17; 8:45 am]
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