Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) Helicopters, 40492-40495 [2016-14467]
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Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations
(e) Reason
This AD was prompted by the discovery of
a number of incorrectly calibrated angle of
attack (AOA) transducers installed in the
stall protection system. We are issuing this
AD to detect and replace incorrectly
calibrated AOA transducers; incorrect
calibration of the transducers could result in
late activation of the stick pusher.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Replacement of AOA
Transducers With No Changes
This paragraph restates the requirements
paragraph (g) of AD 2016–08–05, with no
changes. Within 2,500 flight hours or 12
months, whichever occurs first after May 18,
2016 (the effective date of AD 2016–08–05),
replace the AOA transducers identified in
paragraph 1.A., ‘‘Effectivity,’’ of Bombardier
Service Bulletin 670BA–27–069, dated March
30, 2015, with correctly calibrated AOA
transducers, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–27–069, dated March
30, 2015.
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(h) Retained Parts Installation Prohibition,
With a Change to the Affected Parts
Language
This paragraph restates the parts
installation prohibition specified in
paragraph (h) of AD 2016–08–05, with a
change to the affected parts language. As of
May 18, 2016 (the effective date of AD 2016–
08–05), no person may install, on any
airplane, an AOA transducer having a part
number and serial number listed in
paragraph 1.A., ‘‘Effectivity,’’ of Bombardier
Service Bulletin 670BA–27–069, dated March
30, 2015.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone: 516–228–7300; fax: 516–794–
5531. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, New York ACO, ANE–170,
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FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
(j) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
AD CF–2015–18, dated July 16, 2015, for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2016–7265.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on May 18, 2016, (81 FR
21709, April 13, 2016).
(i) Bombardier Service Bulletin 670BA–27–
069, dated March 30, 2015.
(ii) Reserved.
(4) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; Widebody Customer Response
Center North America toll-free telephone: 1–
866–538–1247 or direct-dial telephone: 1–
514–855–2999; fax: 514–855–7401; email:
ac.yul@aero.bombardier.com; Internet:
https://www.bombardier.com.
(5) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on June 13,
2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–14579 Filed 6–21–16; 8:45 am]
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[Docket No. FAA–2014–0105; Directorate
Identifier 2008–SW–58–AD; Amendment 39–
18562; AD 2016–12–13]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2000–05–
17 and AD 2001–04–12, which apply to
Eurocopter France (now Airbus
Helicopters) Model EC120B helicopters.
AD 2000–05–17 and AD 2001–04–12
required repetitive visual checks of the
engine-to-main gearbox (MGB) coupling
tube assembly (coupling tube) for a
crack and replacing any cracked tube
with an airworthy tube. This new AD
requires removing certain engine mount
parts from service, measuring the height
of the engine mounting base for certain
helicopters, replacing the engine mount
if a certain height is exceeded,
inspecting the flared coupling on certain
helicopters for a crack, and replacing
the coupling if it is cracked. Since we
issued AD 2000–05–17 and AD 2001–
04–12, there have been reports of
additional cracks in coupling tubes.
These actions are intended to prevent
coupling tube failure, loss of engine
drive, and a subsequent forced landing
of the helicopter.
DATES: This AD is effective July 27,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 27, 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 view this referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0105.
SUMMARY:
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov in Docket No.
FAA–2014–0105; 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 Direction
Generale de L’Aviation Civile (DGAC)
AD, any incorporated-by-reference
information, the economic evaluation,
any comments received, and other
information. The address for the Docket
Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
James Blyn, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
james.blyn@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 29, 2015, we issued a notice
of proposed rulemaking (NPRM) to
amend 14 CFR part 39 to remove AD
2000–05–17 (65 FR 13875, March 15,
2000) and AD 2001–04–12 (66 FR
13232, March 5, 2001) and add a new
AD. AD 2000–05–17 applied to Model
EC120B helicopters with engine
coupling tube part number (P/N)
C631A1002101 and required recurring
inspections of each coupling tube for a
crack and replacing any cracked
coupling tube with a reinforced
coupling tube P/N C631A1101101. AD
2001–04–12 applied to Model EC120B
helicopters with engine coupling tube
P/N C631A1101101 and required
repetitive visual checks of each
coupling tube for a crack. AD 2000–05–
17 and AD 2001–04–12 were prompted
by reports of cracks on the reinforced
coupling tube and were intended to
prevent coupling tube failure, loss of
engine drive, and a subsequent forced
landing.
The NPRM published in the Federal
Register on June 16, 2015 (80 FR 34335).
The NPRM was prompted by reports of
additional cracks in coupling tubes.
Eurocopter France (now Airbus
Helicopters) determined that the
washer-type engine mount may, in
certain cases, induce excessive loading
on the coupling tube, which results in
binding that increases component wear
of the inner diameter of the mounting
base. Because of this, the DGAC, on
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behalf of the European Aviation Safety
Agency (EASA), issued AD No. F–2003–
325 R1, dated May 12, 2004, for Model
EC120B helicopters with engine
coupling tube, P/N C631A1101101, and
with an engine mount containing
certain parts listed in Eurocopter Alert
Service Bulletin (ASB) No. 04A005,
dated July 16, 2003. DGAC AD No. F–
2003–325 R1 requires inspections for
helicopters with an engine mount block
modified in accordance with Eurocopter
Service Bulletin (SB) No. 71–003,
Revision 1, dated July 18, 2002;
replacing any coupling tube that has a
crack; and increasing the life limit of the
coupling tube from 1,000 flight hours to
20,000 flight hours. Also, DGAC AD No.
F–2003–325 R1 requires, for helicopters
with a new spring-loaded engine
suspension modification in accordance
with Eurocopter SB No. 71–005,
Revision 0, dated May 14, 2004,
increasing the life limit of the coupling
tube to 20,000 flight hours and
canceling the repetitive inspections of
the coupling tube.
The NPRM proposed to require, for
helicopters with certain engine mounts,
before further flight, removing from
service certain engine mount parts and
measuring the height of the engine
mounting base. If the height is more
than 10.5 millimeters, the NPRM
proposed replacing the engine mount
with an engine mount that does not
have the affected parts. For certain other
helicopters, the NPRM proposed to
require within 25 hours time-in-serice
(TIS) replacing the spring-type engine
suspension system, dye-penetrant
inspecting the flared coupling for a
crack, and replacing any cracked flared
coupling. The NPRM also proposed
removing coupling tube P/N
C631A1002101 from service and
prohibiting installation of that coupling
tube on any helicopter.
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
revised the contact information
throughout this final rule to reflect the
new address and new email address.
Comments
After our NPRM (80 FR 34335, June
16, 2015) was published, we received
comments from one commenter.
Request
Airbus Helicopters disagrees with the
proposed requirement to replace the
spring-type engine suspension system in
accordance with Eurocopter SB No. 71–
005 for helicopters with an improved
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engine mount under Eurocopter SB No.
71–003. Airbus Helicopters states there
have been no coupling tube failures
since incorporation of Eurocopter SB
No. 71–003, and therefore the proposed
requirement would not increase safety
levels.
We disagree. Installing the improved
engine mount specified in Eurocopter
SB No. 71–003 extends the compliance
time for a recurring visual inspection of
the coupling tube from 5 hours TIS to
25 hours TIS. When issued, that
recurring inspection was considered a
short-term interim action until an
effective modification or action was
developed, approved, and available.
Eurocopter SB No. 71–005 contained
such an effective action to cancel that
interim action and was developed and
approved in May 2004.
Airbus Helicopters requested that, if
we mandate the proposed requirement
to replace the spring-type engine
suspension system in accordance with
Eurocopter SB No. 71–005, we change
the proposed compliance time from 25
hours TIS to 18 months to allow for
availability of parts.
We disagree. Eurocopter SB No. 71–
005 was approved May 13, 2004. The
NPRM was published June 16, 2015.
The substantial amount of time that has
passed since the approval of the service
information and publication of our
NPRM provided operators with enough
notice of our proposal to mandate that
procedure such that availability of parts
should not be an issue.
FAA’s Determination
This helicopter has been approved by
the aviation authority of France and is
approved for operation in the United
States. Pursuant to our bilateral
agreement with France, the DGAC on
behalf of EASA, has kept the FAA
informed of the situation described
above. We are issuing this AD because
we evaluated all information provided
by the DGAC, reviewed the relevant
information, considered the comments
received, and determined the unsafe
condition exists and is likely to exist or
develop on other helicopters of this
same type design and that air safety and
the public interest require adopting the
AD requirements as proposed.
Related Service Information Under 1
CFR Part 51
Eurocopter issued ASB No. 04A005,
Revision 0, dated July 16, 2003, which
prohibits, after June 30, 2004, operating
an engine mount made up of the
following parts: Support arm, P/N
C714A1107201; swaged support arm, P/
N C714A1106201; left-hand support
bracket, P/N C714A1101102; and right-
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hand support bracket, P/N
C714A1101103. ASB No. 04A005 also
specifies measuring the height of the
engine mounting base and, if the height
is more than 10.5 millimeters, replacing
the engine mount with an engine mount
that does not have the specified P/N.
ASB No. 04A005 does not apply to
helicopters modified with an improved
engine mount in accordance with SB
No. 71–003. ASB No. 04A005 also does
not apply to helicopters with a serial
number 1170 or larger, as the specified
engine mounts are not installed on those
helicopters.
Eurocopter also issued SB No. 71–
005, Revision 0, dated May 14, 2004,
which contains procedures to modify
the spring-type engine suspension
system and dye-penetrant inspect the
flared coupling assembly.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Other Related Service Information
Eurocopter issued SB No. 71–003,
Revision 1, dated July 18, 2002, which
contains procedures to improve the
engine mount. Eurocopter also issued
ASB No. 05A003, Revision 2, dated July
16, 2003, for helicopters that have not
been modified with an improved engine
mount in accordance with SB No. 71–
003, which specifies inspecting the
coupling tube for a crack every 5 hours
and establishing a coupling tube life
limit of 1,000 hours. For helicopters that
have been modified with an improved
engine mount, ASB No. 05A003
specifies inspecting the coupling tube
for a crack every 25 hours and
increasing the coupling tube life limit to
20,000 hours. ASB No. 05A003 was
revised to Revision 3, dated May 11,
2004, to specify an optional spring-type
engine suspension modification and
cancel the repetitive inspection for this
modified configuration.
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Differences Between This AD and the
DGAC AD
This AD requires the installation of
the spring-type engine suspension
modification specified in Eurocopter SB
No. 71–005 and does not require the
repetitive inspection of the coupling
tube and the engine mount base. This
AD also does not require you to contact
the manufacturer.
Costs of Compliance
We estimate that this AD will affect
23 helicopters of the 115 helicopters of
U.S. Registry. At an average labor rate of
$85 per work-hour, we estimate that
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operators may incur the following costs
in order to comply with this AD.
Installing new mounting arms and
brackets requires about 12 work-hours
and required parts cost $9,194, for a
total cost per helicopter of $10,214 and
$234,922 for the U.S. fleet. Installing the
mounting spring kit requires about 14
work-hours and required parts cost
$14,621, for a total cost per helicopter
of $15,811 and $363,653 for the U.S.
fleet. Dye-penetrant inspecting the
coupling tube requires about 1 workhour for a cost per helicopter of $85 and
$1,955 for the U.S. fleet.
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 for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska to the extent that a regulatory,
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.
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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2000–05–17, Amendment 39–
11627 (65 FR 13875, March 15, 2000);
and AD 2001–04–12, Amendment 39–
12131 (66 FR 13232, March 5, 2001);
and
■ b. Adding the following new AD:
■
■
2016–12–13 Airbus Helicopters (Previously
Eurocopter France): Amendment 39–
18562; Docket No. FAA–2014–0105;
Directorate Identifier 2008–SW–58–AD.
(a) Applicability
This AD applies to Model EC120B
helicopters with an engine-to-main gearbox
coupling tube assembly (coupling tube), part
number (P/N) C631A1101101 or P/N
C631A1002101, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in a coupling tube. This condition
could result in coupling tube failure, loss of
engine drive, and a subsequent forced
landing of the helicopter.
(c) Affected ADs
This AD supersedes AD 2000–05–17,
Amendment 39–11627 (65 FR 13875, March
15, 2000) and AD 2001–04–12, Amendment
39–12131 (66 FR 13232, March 5, 2001).
(d) Effective Date
This AD becomes effective July 27, 2016.
(e) 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.
(f) Required Actions
(1) For helicopters with a serial number up
to and including 1169, not modified with an
improvement of the engine mount in
accordance with Eurocopter Service Bulletin
(SB) No. 71–003, Revision 1, dated July 18,
2002 (SB 71–003), or not modified by
installing a spring-type engine suspension
system in accordance with Eurocopter SB No.
71–005, Revision 0, dated May 14, 2004 (SB
71–005), before further flight:
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(i) Remove from service the following
engine mount parts:
(A) Support arm, P/N C714A1107201;
(B) Swaged support arm, P/N
C714A1106201;
(C) Left-hand support bracket, P/N
C714A1101102; and
(D) Right-hand support bracket, P/N
C714A1101103.
(ii) Measure the height of the engine
mounting base as depicted in Figure 1 of
Eurocopter Alert SB No. 04A005, Revision 0,
dated July 16, 2003. If the height is more than
10.5 millimeters, replace the engine mount
with an engine mount that does not have the
parts identified in paragraph (f)(1)(i) of this
AD.
(2) For helicopters with a serial number
1170 and larger or helicopters modified with
an improvement of the engine mount in
accordance with SB 71–003:
(i) Within 25 hours TIS, replace the springtype engine suspension system and perform
a dye-penetrant inspection of the flared
coupling for a crack by following the
Accomplishment Instructions, paragraphs
2.B.2.a through 2.B.2.c of SB 71–005.
(ii) If there is a crack in the flared coupling,
before further flight, replace the coupling
with an airworthy coupling.
(3) For helicopters with coupling tube, P/
N C631A1002101, installed, before further
flight, remove coupling tube, P/N
C631A1002101, from service. Do not install
coupling tube, P/N C631A1002101, on any
helicopter.
(g) Special Flight Permits
Special flight permits may be issued
provided there are no cracks in the coupling
tube attachment fitting.
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(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: James Blyn,
Aviation Safety Engineer, Regulations and
Policy 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.
(i) Additional Information
(1) Eurocopter Alert Service Bulletin (ASB)
No. 05A003, Revision 2, dated July 16, 2003;
Eurocopter ASB No. 05A003, Revision 3,
dated May 11, 2004; and Eurocopter Service
Bulletin No. 71–003, Revision 1, dated July
18, 2002; which are not incorporated by
reference, contain additional information
about the subject of this final rule. For
Eurocopter 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
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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
Direction Generale de L’Aviation Civile
(DGAC) AD No. F–2003–325 R1, Revision 1,
dated May 12, 2004. You may view the
DGAC AD on the Internet at https://
www.regulations.gov in Docket No. FAA–
2014–0105.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6310, Engine/Transmission Coupling—
Coupling Tube, Engine Mount, and Engine
Mount Base.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No.
04A005, Revision 0, dated July 16, 2003.
(ii) Eurocopter Service Bulletin No. 71–
005, Revision 0, dated May 14, 2004.
(3) For Eurocopter 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.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on June 9,
2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–14467 Filed 6–21–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 95
[Docket No. 31084; Amdt. No. 527]
IFR Altitudes; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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This amendment adopts
miscellaneous amendments to the
required IFR (instrument flight rules)
altitudes and changeover points for
certain Federal airways, jet routes, or
direct routes for which a minimum or
maximum en route authorized IFR
altitude is prescribed. This regulatory
action is needed because of changes
occurring in the National Airspace
System. These changes are designed to
provide for the safe and efficient use of
the navigable airspace under instrument
conditions in the affected areas.
DATES: Effective 0901 UTC, July 21,
2016.
FOR FURTHER INFORMATION CONTACT:
Richard A. Dunham, Flight Procedure
Standards Branch (AMCAFS–420),
Flight Technologies and Programs
Division, Flight Standards Service,
Federal Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd., Oklahoma City,
OK 73169 (Mail Address: P.O. Box
25082 Oklahoma City, OK 73125)
telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This
amendment to part 95 of the Federal
Aviation Regulations (14 CFR part 95)
amends, suspends, or revokes IFR
altitudes governing the operation of all
aircraft in flight over a specified route
or any portion of that route, as well as
the changeover points (COPs) for
Federal airways, jet routes, or direct
routes as prescribed in part 95.
SUMMARY:
The Rule
The specified IFR altitudes, when
used in conjunction with the prescribed
changeover points for those routes,
ensure navigation aid coverage that is
adequate for safe flight operations and
free of frequency interference. The
reasons and circumstances that create
the need for this amendment involve
matters of flight safety and operational
efficiency in the National Airspace
System, are related to published
aeronautical charts that are essential to
the user, and provide for the safe and
efficient use of the navigable airspace.
In addition, those various reasons or
circumstances require making this
amendment effective before the next
scheduled charting and publication date
of the flight information to assure its
timely availability to the user. The
effective date of this amendment reflects
those considerations. In view of the
close and immediate relationship
between these regulatory changes and
safety in air commerce, I find that notice
and public procedure before adopting
this amendment are impracticable and
contrary to the public interest and that
good cause exists for making the
E:\FR\FM\22JNR1.SGM
22JNR1
]]>Agencies
[Federal Register Volume 81, Number 120 (Wednesday, June 22, 2016)]
[Rules and Regulations]
[Pages 40492-40495]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14467]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0105; Directorate Identifier 2008-SW-58-AD;
Amendment 39-18562; AD 2016-12-13]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Previously
Eurocopter France) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2000-05-17 and
AD 2001-04-12, which apply to Eurocopter France (now Airbus
Helicopters) Model EC120B helicopters. AD 2000-05-17 and AD 2001-04-12
required repetitive visual checks of the engine-to-main gearbox (MGB)
coupling tube assembly (coupling tube) for a crack and replacing any
cracked tube with an airworthy tube. This new AD requires removing
certain engine mount parts from service, measuring the height of the
engine mounting base for certain helicopters, replacing the engine
mount if a certain height is exceeded, inspecting the flared coupling
on certain helicopters for a crack, and replacing the coupling if it is
cracked. Since we issued AD 2000-05-17 and AD 2001-04-12, there have
been reports of additional cracks in coupling tubes. These actions are
intended to prevent coupling tube failure, loss of engine drive, and a
subsequent forced landing of the helicopter.
DATES: This AD is effective July 27, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 27,
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 view this
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0105.
[[Page 40493]]
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov in Docket No. FAA-2014-0105; 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
Direction Generale de L'Aviation Civile (DGAC) AD, any incorporated-by-
reference information, the economic evaluation, any comments received,
and other information. The address for the Docket Office (phone: 800-
647-5527) is Document Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: James Blyn, Aviation Safety Engineer,
Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email
james.blyn@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 29, 2015, we issued a notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to remove AD 2000-05-17 (65 FR 13875, March 15,
2000) and AD 2001-04-12 (66 FR 13232, March 5, 2001) and add a new AD.
AD 2000-05-17 applied to Model EC120B helicopters with engine coupling
tube part number (P/N) C631A1002101 and required recurring inspections
of each coupling tube for a crack and replacing any cracked coupling
tube with a reinforced coupling tube P/N C631A1101101. AD 2001-04-12
applied to Model EC120B helicopters with engine coupling tube P/N
C631A1101101 and required repetitive visual checks of each coupling
tube for a crack. AD 2000-05-17 and AD 2001-04-12 were prompted by
reports of cracks on the reinforced coupling tube and were intended to
prevent coupling tube failure, loss of engine drive, and a subsequent
forced landing.
The NPRM published in the Federal Register on June 16, 2015 (80 FR
34335). The NPRM was prompted by reports of additional cracks in
coupling tubes. Eurocopter France (now Airbus Helicopters) determined
that the washer-type engine mount may, in certain cases, induce
excessive loading on the coupling tube, which results in binding that
increases component wear of the inner diameter of the mounting base.
Because of this, the DGAC, on behalf of the European Aviation Safety
Agency (EASA), issued AD No. F-2003-325 R1, dated May 12, 2004, for
Model EC120B helicopters with engine coupling tube, P/N C631A1101101,
and with an engine mount containing certain parts listed in Eurocopter
Alert Service Bulletin (ASB) No. 04A005, dated July 16, 2003. DGAC AD
No. F-2003-325 R1 requires inspections for helicopters with an engine
mount block modified in accordance with Eurocopter Service Bulletin
(SB) No. 71-003, Revision 1, dated July 18, 2002; replacing any
coupling tube that has a crack; and increasing the life limit of the
coupling tube from 1,000 flight hours to 20,000 flight hours. Also,
DGAC AD No. F-2003-325 R1 requires, for helicopters with a new spring-
loaded engine suspension modification in accordance with Eurocopter SB
No. 71-005, Revision 0, dated May 14, 2004, increasing the life limit
of the coupling tube to 20,000 flight hours and canceling the
repetitive inspections of the coupling tube.
The NPRM proposed to require, for helicopters with certain engine
mounts, before further flight, removing from service certain engine
mount parts and measuring the height of the engine mounting base. If
the height is more than 10.5 millimeters, the NPRM proposed replacing
the engine mount with an engine mount that does not have the affected
parts. For certain other helicopters, the NPRM proposed to require
within 25 hours time-in-serice (TIS) replacing the spring-type engine
suspension system, dye-penetrant inspecting the flared coupling for a
crack, and replacing any cracked flared coupling. The NPRM also
proposed removing coupling tube P/N C631A1002101 from service and
prohibiting installation of that coupling tube on any helicopter.
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 revised the contact information throughout this final
rule to reflect the new address and new email address.
Comments
After our NPRM (80 FR 34335, June 16, 2015) was published, we
received comments from one commenter.
Request
Airbus Helicopters disagrees with the proposed requirement to
replace the spring-type engine suspension system in accordance with
Eurocopter SB No. 71-005 for helicopters with an improved engine mount
under Eurocopter SB No. 71-003. Airbus Helicopters states there have
been no coupling tube failures since incorporation of Eurocopter SB No.
71-003, and therefore the proposed requirement would not increase
safety levels.
We disagree. Installing the improved engine mount specified in
Eurocopter SB No. 71-003 extends the compliance time for a recurring
visual inspection of the coupling tube from 5 hours TIS to 25 hours
TIS. When issued, that recurring inspection was considered a short-term
interim action until an effective modification or action was developed,
approved, and available. Eurocopter SB No. 71-005 contained such an
effective action to cancel that interim action and was developed and
approved in May 2004.
Airbus Helicopters requested that, if we mandate the proposed
requirement to replace the spring-type engine suspension system in
accordance with Eurocopter SB No. 71-005, we change the proposed
compliance time from 25 hours TIS to 18 months to allow for
availability of parts.
We disagree. Eurocopter SB No. 71-005 was approved May 13, 2004.
The NPRM was published June 16, 2015. The substantial amount of time
that has passed since the approval of the service information and
publication of our NPRM provided operators with enough notice of our
proposal to mandate that procedure such that availability of parts
should not be an issue.
FAA's Determination
This helicopter has been approved by the aviation authority of
France and is approved for operation in the United States. Pursuant to
our bilateral agreement with France, the DGAC on behalf of EASA, has
kept the FAA informed of the situation described above. We are issuing
this AD because we evaluated all information provided by the DGAC,
reviewed the relevant information, considered the comments received,
and determined the unsafe condition exists and is likely to exist or
develop on other helicopters of this same type design and that air
safety and the public interest require adopting the AD requirements as
proposed.
Related Service Information Under 1 CFR Part 51
Eurocopter issued ASB No. 04A005, Revision 0, dated July 16, 2003,
which prohibits, after June 30, 2004, operating an engine mount made up
of the following parts: Support arm, P/N C714A1107201; swaged support
arm, P/N C714A1106201; left-hand support bracket, P/N C714A1101102; and
right-
[[Page 40494]]
hand support bracket, P/N C714A1101103. ASB No. 04A005 also specifies
measuring the height of the engine mounting base and, if the height is
more than 10.5 millimeters, replacing the engine mount with an engine
mount that does not have the specified P/N. ASB No. 04A005 does not
apply to helicopters modified with an improved engine mount in
accordance with SB No. 71-003. ASB No. 04A005 also does not apply to
helicopters with a serial number 1170 or larger, as the specified
engine mounts are not installed on those helicopters.
Eurocopter also issued SB No. 71-005, Revision 0, dated May 14,
2004, which contains procedures to modify the spring-type engine
suspension system and dye-penetrant inspect the flared coupling
assembly.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Other Related Service Information
Eurocopter issued SB No. 71-003, Revision 1, dated July 18, 2002,
which contains procedures to improve the engine mount. Eurocopter also
issued ASB No. 05A003, Revision 2, dated July 16, 2003, for helicopters
that have not been modified with an improved engine mount in accordance
with SB No. 71-003, which specifies inspecting the coupling tube for a
crack every 5 hours and establishing a coupling tube life limit of
1,000 hours. For helicopters that have been modified with an improved
engine mount, ASB No. 05A003 specifies inspecting the coupling tube for
a crack every 25 hours and increasing the coupling tube life limit to
20,000 hours. ASB No. 05A003 was revised to Revision 3, dated May 11,
2004, to specify an optional spring-type engine suspension modification
and cancel the repetitive inspection for this modified configuration.
Differences Between This AD and the DGAC AD
This AD requires the installation of the spring-type engine
suspension modification specified in Eurocopter SB No. 71-005 and does
not require the repetitive inspection of the coupling tube and the
engine mount base. This AD also does not require you to contact the
manufacturer.
Costs of Compliance
We estimate that this AD will affect 23 helicopters of the 115
helicopters of U.S. Registry. At an average labor rate of $85 per work-
hour, we estimate that operators may incur the following costs in order
to comply with this AD.
Installing new mounting arms and brackets requires about 12 work-
hours and required parts cost $9,194, for a total cost per helicopter
of $10,214 and $234,922 for the U.S. fleet. Installing the mounting
spring kit requires about 14 work-hours and required parts cost
$14,621, for a total cost per helicopter of $15,811 and $363,653 for
the U.S. fleet. Dye-penetrant inspecting the coupling tube requires
about 1 work-hour for a cost per helicopter of $85 and $1,955 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 products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that a regulatory, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) 2000-05-17, Amendment 39-11627
(65 FR 13875, March 15, 2000); and AD 2001-04-12, Amendment 39-12131
(66 FR 13232, March 5, 2001); and
0
b. Adding the following new AD:
2016-12-13 Airbus Helicopters (Previously Eurocopter France):
Amendment 39-18562; Docket No. FAA-2014-0105; Directorate Identifier
2008-SW-58-AD.
(a) Applicability
This AD applies to Model EC120B helicopters with an engine-to-
main gearbox coupling tube assembly (coupling tube), part number (P/
N) C631A1101101 or P/N C631A1002101, installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a coupling
tube. This condition could result in coupling tube failure, loss of
engine drive, and a subsequent forced landing of the helicopter.
(c) Affected ADs
This AD supersedes AD 2000-05-17, Amendment 39-11627 (65 FR
13875, March 15, 2000) and AD 2001-04-12, Amendment 39-12131 (66 FR
13232, March 5, 2001).
(d) Effective Date
This AD becomes effective July 27, 2016.
(e) 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.
(f) Required Actions
(1) For helicopters with a serial number up to and including
1169, not modified with an improvement of the engine mount in
accordance with Eurocopter Service Bulletin (SB) No. 71-003,
Revision 1, dated July 18, 2002 (SB 71-003), or not modified by
installing a spring-type engine suspension system in accordance with
Eurocopter SB No. 71-005, Revision 0, dated May 14, 2004 (SB 71-
005), before further flight:
[[Page 40495]]
(i) Remove from service the following engine mount parts:
(A) Support arm, P/N C714A1107201;
(B) Swaged support arm, P/N C714A1106201;
(C) Left-hand support bracket, P/N C714A1101102; and
(D) Right-hand support bracket, P/N C714A1101103.
(ii) Measure the height of the engine mounting base as depicted
in Figure 1 of Eurocopter Alert SB No. 04A005, Revision 0, dated
July 16, 2003. If the height is more than 10.5 millimeters, replace
the engine mount with an engine mount that does not have the parts
identified in paragraph (f)(1)(i) of this AD.
(2) For helicopters with a serial number 1170 and larger or
helicopters modified with an improvement of the engine mount in
accordance with SB 71-003:
(i) Within 25 hours TIS, replace the spring-type engine
suspension system and perform a dye-penetrant inspection of the
flared coupling for a crack by following the Accomplishment
Instructions, paragraphs 2.B.2.a through 2.B.2.c of SB 71-005.
(ii) If there is a crack in the flared coupling, before further
flight, replace the coupling with an airworthy coupling.
(3) For helicopters with coupling tube, P/N C631A1002101,
installed, before further flight, remove coupling tube, P/N
C631A1002101, from service. Do not install coupling tube, P/N
C631A1002101, on any helicopter.
(g) Special Flight Permits
Special flight permits may be issued provided there are no
cracks in the coupling tube attachment fitting.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: James Blyn, Aviation Safety
Engineer, Regulations and Policy 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.
(i) Additional Information
(1) Eurocopter Alert Service Bulletin (ASB) No. 05A003, Revision
2, dated July 16, 2003; Eurocopter ASB No. 05A003, Revision 3, dated
May 11, 2004; and Eurocopter Service Bulletin No. 71-003, Revision
1, dated July 18, 2002; which are not incorporated by reference,
contain additional information about the subject of this final rule.
For Eurocopter 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 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 Direction Generale de
L'Aviation Civile (DGAC) AD No. F-2003-325 R1, Revision 1, dated May
12, 2004. You may view the DGAC AD on the Internet at https://www.regulations.gov in Docket No. FAA-2014-0105.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6310, Engine/
Transmission Coupling--Coupling Tube, Engine Mount, and Engine Mount
Base.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No. 04A005, Revision 0,
dated July 16, 2003.
(ii) Eurocopter Service Bulletin No. 71-005, Revision 0, dated
May 14, 2004.
(3) For Eurocopter 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.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on June 9, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-14467 Filed 6-21-16; 8:45 am]
BILLING CODE 4910-13-P
