Airworthiness Directives; Airbus Helicopters Deutschland GmbH (Previously Eurocopter Deutschland GmbH) (Airbus Helicopters), 36137-36139 [2016-13103]
Download as PDF
36137
Rules and Regulations
Federal Register
Vol. 81, No. 108
Monday, June 6, 2016
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. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0903; Directorate
Identifier 2013–SW–043–AD; Amendment
39–18548; AD 2016–11–21]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH
(Previously Eurocopter Deutschland
GmbH) (Airbus Helicopters)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Airbus
Helicopters Model EC135P1, EC135P2,
EC135P2+, EC135T1, EC135T2, and
EC135T2+ helicopters. This AD requires
reducing the life limit of certain parts
and removing each part that has reached
its life limit. The actions of this AD are
intended to reduce the life limits of
certain critical parts to prevent failure of
a part and subsequent loss of control of
the helicopter.
DATES: This AD is effective July 11,
2016.
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 the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
mstockstill on DSK3G9T082PROD with RULES
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
VerDate Sep<11>2014
16:21 Jun 03, 2016
Jkt 238001
and locating Docket No. FAA–2014–
0903; 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
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 13, 2014, at 79 FR
67382, 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 EC135P1, EC135P2, EC135P2+,
EC135T1, EC135T2, and EC135T2+
helicopters. The NPRM proposed to
require, before further flight, revising
the Airworthiness Limitations Section
(ALS) of the applicable maintenance
manual and the component history card
or equivalent record by reducing the life
limit for various parts and removing
from service any part that has reached
its life limit. The proposed requirements
were intended to reduce the life limits
of certain critical parts to prevent failure
of a part and subsequent loss of control
of the helicopter.
The NPRM was prompted by AD No.
2013–0178, dated August 7, 2013,
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for Eurocopter Deutschland
GmbH (ECD) (now Airbus Helicopters)
Model EC135P1, EC135P2, EC135P2+,
EC135T1, EC135T2, EC135T2+,
EC635T1, EC635P2+, and EC635T2+
helicopters. EASA advises that ECD has
revised the airworthiness limitations for
the EC135 and EC635 type design as
published in the Master Servicing
Manual (MSM) EC135 Chapter 04—ALS
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
documents. Revision 14 of the MSM
contains these new airworthiness
limitations. EASA states that failure to
comply with these limitations could
result in an unsafe condition. For these
reasons, EASA AD No. 2013–0178
requires revising the ALS to include the
new life limits and replacing each part
that has reached its life limit.
Since the NPRM was issued, the FAA
Southwest Regional Office has relocated
and a group email address has been
established for requesting an FAA
Alternative Method of Compliance for a
helicopter of foreign design. We have
updated this information throughout
this Final Rule.
Comments
After our NPRM (79 FR 67382,
November 13, 2014) was published, we
received comments from three
commenters.
Request
Three commenters requested that the
FAA not issue this AD. The commenters
stated an AD to revise the airworthiness
limitations of an aircraft manual is
unnecessary because operators are
required to use the most current
revision of the manual.
We disagree. The FAA must issue an
AD to mandate an airworthiness
limitations revision, such as a new life
limit, for all operators.
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, considered the
comments received, 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
This AD does not apply to Airbus
Helicopters Model EC635T1, P2+, or
EC635T2+ helicopters because those
helicopters are not type certificated in
the U.S.
E:\FR\FM\06JNR1.SGM
06JNR1
36138
Federal Register / Vol. 81, No. 108 / Monday, June 6, 2016 / Rules and Regulations
Related Service Information
The airworthiness limitations and
maintenance procedures for certain
parts are contained in the Airworthiness
Limitations section, Chapter 4, of
Eurocopter’s MSM EC135, dated
December 1, 2001. Revision 14 of the
MSM, dated July 1, 2012, establishes a
life limit for certain part-numbered
main rotor blades and reduces the life
limits for swashplate and mixing lever
gear unit parts.
Costs of Compliance
We estimate that this AD affects 267
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
Labor costs are estimated at $85 per
work-hour. We estimate 2 work-hours to
update the maintenance manual for a
total cost of $170 for each helicopter
and $45,390 for the U.S. fleet.
mstockstill on DSK3G9T082PROD with RULES
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
VerDate Sep<11>2014
16:21 Jun 03, 2016
Jkt 238001
(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):
■
2016–11–21 Airbus Helicopters
Deutschland GmbH (Previously
Eurocopter Deutschland GmbH):
Amendment 39–18548; Docket No.
FAA–2014–0903; Directorate Identifier
2013–SW–043–AD.
(a) Applicability
This AD applies to Model EC135P1,
EC135P2, EC135P2+, EC135T1, EC135T2,
and EC135T2+ helicopters, certificated in
any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
failure of a critical part, which could result
in loss of control of the helicopter.
(c) Effective Date
This AD becomes effective July 11, 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
Before further flight:
(1) Revise the life limit of each part listed
in paragraphs (e)(1)(i) and (ii) in the
Airworthiness Limitations Section of the
applicable maintenance manual and record
the revised life limit on the component
history card or equivalent record as follows:
(i) For swashplate parts:
(A) Ring (bearing ring), part number (P/N)
L623M2001214, reduce the life limit from
8,300 hours time-in-service (TIS) to 8,000
hours TIS.
(B) Ring (control ring), P/N
L623M2001213, reduce the life limit from
8,300 hours TIS to 8,000 hours TIS.
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
(C) Cardan ring (two-part), P/N
L623M2005205, reduce the life limit from
14,400 hours TIS to 12,900 hours TIS.
(D) Bolt (control ring), P/N L671M7001215,
reduce the life limit from 14,400 hours TIS
to 12,900 hours TIS.
(E) Bolt (sliding sleeve), P/N
L623M2006206 and P/N L623M2006213,
reduce the life limit from 14,400 hours TIS
to 12,900 hours TIS.
(ii) For mixing lever gear unit parts:
(A) Forked lever assembly, P/N
L671M3012102, reduce the life limit from
9,000 hours TIS to 8,700 hours TIS.
(B) Hinged support, P/N L671M7003210,
reduce the life limit from 8,700 hours TIS to
8,400 hours TIS.
(C) Bolt, P/N L671M7001220, reduce the
life limit from 8,700 hours TIS to 8,400 hours
TIS.
(2) Remove from service any part listed in
paragraph (e)(1) of this AD that has reached
or exceeded its newly revised life limit.
(f) Special Flight Permits
Special flight permits are limited to a onetime flight to a maintenance facility to
replace a part that has reached its life limit.
(g) 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.
(h) Additional Information
(1) Eurocopter Master Servicing Manual
EC135 Chapter 04—Airworthiness
Limitations Section, Revision 14, dated July
1, 2012, which is not incorporated by
reference, contains additional information
about the subject of this final rule. For
service information identified in this 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 a copy of the 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. 2013–0178, dated August 7, 2013. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2014–0903.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6300, 2700 Swashplate Ring, Cardan
E:\FR\FM\06JNR1.SGM
06JNR1
36139
Federal Register / Vol. 81, No. 108 / Monday, June 6, 2016 / Rules and Regulations
Ring, Bolt, Mixing Lever Gear Unit (flight
controls).
This final rule is effective June
6, 2016.
DATES:
Issued in Fort Worth, Texas, on May 23,
2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0338; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
ADDRESSES:
[FR Doc. 2016–13103 Filed 6–3–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0338; Directorate
Identifier 2014–CE–010–AD; Amendment
39–18495; AD 2016–08–18]
RIN 2120–AA64
Gary
Wechsler, Aerospace Engineer, FAA,
Atlanta Aircraft Certification Office,
1701 Columbia Avenue, College Park,
Georgia 30337; telephone: (404) 474–
5575; fax: (404) 474–5606; email:
gary.wechsler@faa.gov.
FOR FURTHER INFORMATION CONTACT:
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to certain Piper Aircraft, Inc.
Model PA–31–350 airplanes. The wing
locations of engine TIO–540–J2B and
LTIO–540–J2B in table 1 of the
Applicability, paragraph (c), section are
incorrect. This document corrects that
error. In all other respects, the original
document remains the same; however
we are publishing the entire rule in the
Federal Register.
SUMMARY:
SUPPLEMENTARY INFORMATION:
Airworthiness Directive 2016–08–18,
Amendment 39–18495 (81 FR 26106,
May 2, 2016), currently requires
inspecting the fuel hose assembly and
the turbocharger support assembly for
proper clearance between them,
inspecting each assembly for any sign of
damage, and making any necessary
repairs or replacements for certain Piper
Aircraft, Inc. Model PA–31–350
airplanes.
As published, the wing locations of
engine TIO–540–JJ2B and LTIO–540–
J2B in table 1 of the Applicability,
paragraph (c), section are incorrect. This
document corrects that error.
Although no other part of the
preamble or regulatory information has
been corrected, we are publishing the
entire rule in the Federal Register.
The effective date of this AD remains
June 6, 2016.
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):
■
2016–08–18 Piper Aircraft, Inc.:
Amendment 39–18495; Docket No.
FAA–2014–0338; Directorate Identifier
2014–CE–010–AD.
(a) Effective Date
This AD is effective June 6, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Piper Aircraft, Inc.
Model PA–31–350 airplanes, serial numbers
31–5001 through 31–5004, 31–7305005
through 31–8452024, and 31–8253001
through 31–8553002, certificated in any
category, that are equipped with the
following engines and fuel pump hose
assemblies:
TABLE 1 TO PARAGRAPH (c) OF THIS AD—APPLICABLE ENGINES AND FUEL PUMP HOSE ASSEMBLIES
Engine
Manufacturer’s hose name
Manufacturer’s part No.
(P/N)
LTIO–540–J2B (right wing) ............
Hose Assembly—Fuel ..................
Piper 39995–034 ..........................
TIO–540–J2B (left wing) ................
Hose, Fuel pump to Injector .........
Lycoming LW–12877–6S142 .......
LTIO–540–J2BD (right wing) .........
Hose, Fuel pump to Injector .........
Lycoming LW–12877–6S142 .......
TIO–540–J2BD (left wing) .............
Hose Assembly—Fuel ..................
Piper 39995–034 ..........................
mstockstill on DSK3G9T082PROD with RULES
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 73: Engine Fuel and Control.
(e) Unsafe Condition
This AD was prompted by a report of an
engine fire caused by a leak in the fuel pump
inlet hose. We are issuing this AD to correct
the unsafe condition on these products.
(f) Compliance
Comply with this AD within the
compliance times specified in paragraphs
VerDate Sep<11>2014
16:21 Jun 03, 2016
Jkt 238001
(g)(1) through (j)(2) of this AD, unless already
done.
(g) Ensure Proper Clearance Between the
Fuel Hose Assembly and the Turbocharger
Support Assembly
(1) Within the next 60 hours time-inservice (TIS) after June 6, 2016 (the effective
date of this AD) or within the next 6 months
after June 6, 2016 (the effective date of this
AD), whichever occurs first, inspect to
determine the clearance between the inlet
and exit fuel hose assemblies listed in table
1 to paragraph (c) of this AD, and each
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
Hose description
Inlet fuel hose to
pump.
Exit fuel hose from
pump.
Exit fuel hose from
pump.
Inlet fuel hose to
pump.
engine fuel
engine fuel
engine fuel
engine fuel
turbocharger support assembly, Lycoming
P/N LW–18302. There should be a minimum
3/16-inch clearance. Do the inspection
following the INSTRUCTIONS section of
Piper Aircraft, Inc. Service Bulletin No.
1257A, dated August 4, 2015.
(2) Before further flight after the inspection
required in paragraph (g)(1) of this AD, if the
measured clearance is less than 3/16-inch,
make all necessary adjustments to make the
clearance a minimum of 3/16-inch between
the inlet and exit fuel hose assemblies listed
in table 1 to paragraph (c) of this AD and
each turbocharger support assembly,
E:\FR\FM\06JNR1.SGM
06JNR1
Agencies
[Federal Register Volume 81, Number 108 (Monday, June 6, 2016)]
[Rules and Regulations]
[Pages 36137-36139]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-13103]
========================================================================
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.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 81, No. 108 / Monday, June 6, 2016 / Rules
and Regulations
[[Page 36137]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0903; Directorate Identifier 2013-SW-043-AD;
Amendment 39-18548; AD 2016-11-21]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters Deutschland GmbH
(Previously Eurocopter Deutschland GmbH) (Airbus Helicopters)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus
Helicopters Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and
EC135T2+ helicopters. This AD requires reducing the life limit of
certain parts and removing each part that has reached its life limit.
The actions of this AD are intended to reduce the life limits of
certain critical parts to prevent failure of a part and subsequent loss
of control of the helicopter.
DATES: This AD is effective July 11, 2016.
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 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-2014-
0903; 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 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 13, 2014, at 79 FR 67382, 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 EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and
EC135T2+ helicopters. The NPRM proposed to require, before further
flight, revising the Airworthiness Limitations Section (ALS) of the
applicable maintenance manual and the component history card or
equivalent record by reducing the life limit for various parts and
removing from service any part that has reached its life limit. The
proposed requirements were intended to reduce the life limits of
certain critical parts to prevent failure of a part and subsequent loss
of control of the helicopter.
The NPRM was prompted by AD No. 2013-0178, dated August 7, 2013,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to correct an unsafe condition for Eurocopter
Deutschland GmbH (ECD) (now Airbus Helicopters) Model EC135P1, EC135P2,
EC135P2+, EC135T1, EC135T2, EC135T2+, EC635T1, EC635P2+, and EC635T2+
helicopters. EASA advises that ECD has revised the airworthiness
limitations for the EC135 and EC635 type design as published in the
Master Servicing Manual (MSM) EC135 Chapter 04--ALS documents. Revision
14 of the MSM contains these new airworthiness limitations. EASA states
that failure to comply with these limitations could result in an unsafe
condition. For these reasons, EASA AD No. 2013-0178 requires revising
the ALS to include the new life limits and replacing each part that has
reached its life limit.
Since the NPRM was issued, the FAA Southwest Regional Office has
relocated and a group email address has been established for requesting
an FAA Alternative Method of Compliance for a helicopter of foreign
design. We have updated this information throughout this Final Rule.
Comments
After our NPRM (79 FR 67382, November 13, 2014) was published, we
received comments from three commenters.
Request
Three commenters requested that the FAA not issue this AD. The
commenters stated an AD to revise the airworthiness limitations of an
aircraft manual is unnecessary because operators are required to use
the most current revision of the manual.
We disagree. The FAA must issue an AD to mandate an airworthiness
limitations revision, such as a new life limit, for all operators.
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, considered the comments received, 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
This AD does not apply to Airbus Helicopters Model EC635T1, P2+, or
EC635T2+ helicopters because those helicopters are not type
certificated in the U.S.
[[Page 36138]]
Related Service Information
The airworthiness limitations and maintenance procedures for
certain parts are contained in the Airworthiness Limitations section,
Chapter 4, of Eurocopter's MSM EC135, dated December 1, 2001. Revision
14 of the MSM, dated July 1, 2012, establishes a life limit for certain
part-numbered main rotor blades and reduces the life limits for
swashplate and mixing lever gear unit parts.
Costs of Compliance
We estimate that this AD affects 267 helicopters of U.S. Registry.
We estimate that operators may incur the following costs in order to
comply with this AD. Labor costs are estimated at $85 per work-hour. We
estimate 2 work-hours to update the maintenance manual for a total cost
of $170 for each helicopter and $45,390 for the U.S. fleet.
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, 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):
2016-11-21 Airbus Helicopters Deutschland GmbH (Previously
Eurocopter Deutschland GmbH): Amendment 39-18548; Docket No. FAA-
2014-0903; Directorate Identifier 2013-SW-043-AD.
(a) Applicability
This AD applies to Model EC135P1, EC135P2, EC135P2+, EC135T1,
EC135T2, and EC135T2+ helicopters, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of a critical
part, which could result in loss of control of the helicopter.
(c) Effective Date
This AD becomes effective July 11, 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
Before further flight:
(1) Revise the life limit of each part listed in paragraphs
(e)(1)(i) and (ii) in the Airworthiness Limitations Section of the
applicable maintenance manual and record the revised life limit on
the component history card or equivalent record as follows:
(i) For swashplate parts:
(A) Ring (bearing ring), part number (P/N) L623M2001214, reduce
the life limit from 8,300 hours time-in-service (TIS) to 8,000 hours
TIS.
(B) Ring (control ring), P/N L623M2001213, reduce the life limit
from 8,300 hours TIS to 8,000 hours TIS.
(C) Cardan ring (two-part), P/N L623M2005205, reduce the life
limit from 14,400 hours TIS to 12,900 hours TIS.
(D) Bolt (control ring), P/N L671M7001215, reduce the life limit
from 14,400 hours TIS to 12,900 hours TIS.
(E) Bolt (sliding sleeve), P/N L623M2006206 and P/N
L623M2006213, reduce the life limit from 14,400 hours TIS to 12,900
hours TIS.
(ii) For mixing lever gear unit parts:
(A) Forked lever assembly, P/N L671M3012102, reduce the life
limit from 9,000 hours TIS to 8,700 hours TIS.
(B) Hinged support, P/N L671M7003210, reduce the life limit from
8,700 hours TIS to 8,400 hours TIS.
(C) Bolt, P/N L671M7001220, reduce the life limit from 8,700
hours TIS to 8,400 hours TIS.
(2) Remove from service any part listed in paragraph (e)(1) of
this AD that has reached or exceeded its newly revised life limit.
(f) Special Flight Permits
Special flight permits are limited to a one-time flight to a
maintenance facility to replace a part that has reached its life
limit.
(g) 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.
(h) Additional Information
(1) Eurocopter Master Servicing Manual EC135 Chapter 04--
Airworthiness Limitations Section, Revision 14, dated July 1, 2012,
which is not incorporated by reference, contains additional
information about the subject of this final rule. For service
information identified in this 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 a copy of the
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. 2013-0178, dated August 7, 2013. You may
view the EASA AD on the Internet at https://www.regulations.gov in
Docket No. FAA-2014-0903.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6300, 2700
Swashplate Ring, Cardan
[[Page 36139]]
Ring, Bolt, Mixing Lever Gear Unit (flight controls).
Issued in Fort Worth, Texas, on May 23, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-13103 Filed 6-3-16; 8:45 am]
BILLING CODE 4910-13-P