Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France), 26103-26106 [2016-09235]
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and 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, 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
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):
■
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2016–09–04 Bombardier, Inc.: Amendment
39–18502; Docket No. FAA–2015–4814;
Directorate Identifier 2015–NM–105–AD.
(a) Effective Date
This AD is effective June 6, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model
CL–600–2B19 (Regional Jet Series 100 & 440)
airplanes, certificated in any category, serial
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numbers 7003 through 7067 inclusive, 7069
through 7990 inclusive, and 8000 through
8999 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(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) Replacement
For AOA transducers identified in
paragraph 1.A., ‘‘Effectivity,’’ of Bombardier
Service Bulletin 601R–27–164, dated March
30, 2015: Within 2,500 flight hours or 12
months, whichever occurs first after the
effective date of this AD, replace the AOA
transducers with correctly calibrated AOA
transducers, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 601R–27–164, dated March
30, 2015.
(h) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane, an AOA
transducer having a part number or serial
number listed in paragraph 1.A.,
‘‘Effectivity,’’ of Bombardier Service Bulletin
601R–27–164, 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: 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,
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.
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26103
(j) Related Information
For more information about this AD,
contact Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch,
ANE–171, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7318; fax 516–
794–5531.
(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 the AD specifies otherwise.
(i) Bombardier Service Bulletin 601R–27–
164, dated March 30, 2015.
(ii) Reserved.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may view this service information
at 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.
(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 Renton, Washington, on April 20,
2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–09791 Filed 4–29–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3970; Directorate
Identifier 2015–SW–006–AD; Amendment
39–18497; AD 2016–08–20]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2014–12–
51 for Airbus Helicopters (previously
Eurocopter France) Model EC130B4 and
SUMMARY:
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
EC130T2 helicopters. AD 2014–12–51
required repetitively inspecting the
tailboom to Fenestron junction frame
(junction frame) for a crack. This new
AD retains the requirements of AD
2014–12–51, changes the applicability
from helicopters with certain hours
time-in-service (TIS) to junction frames
with certain hours TIS, and adds a
compliance time for sling cycles to the
junction frame inspection interval. The
actions of this AD are intended to detect
a crack and to prevent failure of the
junction frame, which could result in
loss of the Fenestron and subsequent
loss of control of the helicopter.
This AD is effective June 6, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of June 6, 2016.
DATES:
For service information
identified in this final rule, contact
Airbus Helicopters, Inc., 2701 N. Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177. It is also on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–3970.
ADDRESSES:
Examining the AD Docket
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You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3970; 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, any
incorporated-by-reference service
information, 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:
Robert Grant, Aviation Safety Engineer,
Safety Management Group, FAA,
Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy, Fort Worth, TX 76177;
email robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
On September 25, 2015, at 80 FR
57742, the Federal Register published
our notice of proposed rulemaking
(NPRM) to amend 14 CFR part 39 to
remove AD 2014–12–51, Amendment
39–17921 (79 FR 45335, August 5,
2014), and add a new AD. AD 2014–12–
51 applied to Airbus Helicopters Model
EC130B4 and EC130T2 helicopters with
690 or more hours TIS and required,
within 10 hours TIS, dye-penetrant
inspecting certain areas of the junction
frame for a crack. AD 2014–12–51 also
required, at intervals not exceeding 25
hours TIS, either repeating the dyepenetrant inspection or performing a
borescope inspection of certain areas of
the junction frame for a crack. If there
was a crack, AD 2014–12–51 required
replacing the junction frame. AD 2014–
12–51 was prompted by two incidents
of crack propagation through the
junction frame that initiated in the
lower right-hand side between the web
and the flange where the lower spar of
the tailboom is joined. The cracks were
significant in length and not visible
from the outside of the helicopter.
The NPRM was prompted by AD No.
2015–0033–E dated February 24, 2015
(AD 2015–0033–E), issued by EASA,
which is the Technical Agent for the
Member States of the European Union,
to correct an unsafe condition on Airbus
Helicopters EC130B4 and EC130T2
helicopters. The NPRM proposed to
require retaining the dye penetrant and
borescope inspections in AD 2014–12–
51 but with revised compliance times.
The NRPM also proposed to change the
applicability to helicopters with 690
hours TIS accumulated on the junction
frame instead of on the helicopter, and
proposed including an inspection
interval defined in sling cycles. These
actions were intended to detect a crack
and to prevent failure of the junction
frame, which could result in loss of the
Fenestron and subsequent loss of
control of the helicopter.
Comments
After our NPRM (80 FR 57742,
September 25, 2015) was published, we
received a comment from one
commenter.
Request
One commenter requested the
addition of a 10-hour or 250-sling cycle
visual pilot check for helicopters with
Modification 350A087421 or that have
complied with Airbus Helicopters
Service Bulletin No. EC130–53–029,
Revision 0, dated February 20, 2015 (SB
EC130–53–029). The commenter stated
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this pilot check would benefit operators
and provide the same level of safety.
We disagree. While the EASA AD
allows the check requested by the
commenter as an alternative method,
because the cause of the fatigue cracking
is still under investigation, we cannot
determine that this method would
correct the unsafe condition.
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, 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, reviewed the
relevant information, considered the
comment received, and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
the same type designs and that air safety
and the public interest require adopting
the AD requirements as proposed.
Interim Action
We consider this AD to be an interim
action. If final action is later identified,
we might consider further rulemaking
then.
Differences Between This AD and the
EASA AD
The EASA AD includes alternate
compliance instructions for helicopters
modified with a cut-out in production
by Airbus Helicopters Modification
350A087421 or in service by
compliance with SB EC130–53–029.
This AD does not.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Helicopters
Emergency Alert Service Bulletin No.
05A017, Revision 2, dated February 20,
2015 (EASB 05A017), for Model
EC130B4 and EC130T2 helicopters.
EASB 05A017 describes alternate
procedures for inspecting outside the
tailboom for a crack at reduced
inspection intervals in combination
with the internal inspections at
extended intervals. EASB 05A017 also
specifies adding sling cycles to the
existing flight hour inspection interval
for helicopters that perform external
load-carrying operations. EASA issued
AD No. 2015–0033–E mandating the
requirements in EASB 05A017 to ensure
the continued airworthiness of these
helicopters.
This service information is reasonably
available because the interested parties
have access to it through their normal
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
course of business or by the means
identified in the ADDRESSES section.
Other Related Service Information
Airbus Helicopters also issued SB
EC130–53–029, which contains
procedures to cut out the skin and
splice at the junction frame to facilitate
the external inspection specified in
EASB 05A017.
Costs of Compliance
We estimate that this AD affects 208
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
At an average labor rate of $85 per workhour, dye-penetrant inspecting the
junction frame will require 1 work-hour,
for a cost of $85 per helicopter and a
total cost of $17,680 for the U.S. fleet,
per inspection cycle. Borescope
inspecting the junction frame will
require 0.5 work-hour, for a cost of $43
per helicopter and a total cost of $8,944
for the U.S. fleet, per inspection cycle.
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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);
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(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
removing Airworthiness Directive (AD)
2014–12–51, Amendment 39–17921 (79
FR 45335, August 5, 2014), and adding
the following new AD:
■
2016–08–20 Airbus Helicopters (Previously
Eurocopter France): Amendment 39–
18497; Docket No. FAA–2015–3970;
Directorate Identifier 2015–SW–006–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model EC130B4 and EC130T2 helicopters
with a tailboom to fenestron junction frame
(junction frame) that has 690 or more hours
time-in-service (TIS), certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the junction frame. This condition
could result in failure of the junction frame,
which could result in loss of the Fenestron
and subsequent loss of control of the
helicopter.
(c) Affected ADs
This AD supersedes AD 2014–12–51,
Amendment 39–17921 (79 FR 45335, August
5, 2014).
(d) Effective Date
This AD becomes effective June 6, 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.
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26105
(f) Required Actions
(1) Before the junction frame reaches 700
hours TIS or within 10 hours TIS, whichever
occurs later, remove the horizontal stabilizer,
clean the junction frame, and dye-penetrant
inspect around the circumference of the
junction frame for a crack in the areas shown
in Figure 1 of Airbus Helicopters EC130
Emergency Alert Service Bulletin No.
05A017, Revision 2, dated February 20, 2015
(EASB 05A017). Pay particular attention to
the area around the 4 spars (item b) of Figure
1 of EASB 05A017. An example of a crack
is shown in Figure 3 of EASB 05A017.
(2) Within 25 hours TIS or 390 sling cycles,
whichever occurs first after the inspection
required by paragraph (f)(1) of this AD, and
thereafter at intervals not exceeding 25 hours
TIS or 390 sling cycles, whichever occurs
first, either perform the actions of paragraph
(f)(1) of this AD or, if the area is clean, using
a borescope, inspect around the
circumference of the junction frame for a
crack in the areas shown in Figure 2 of EASB
05A017. Pay particular attention to the area
around the 4 spars (item b) of Figure 2 of
EASB 05A017. An example of a crack is
shown in Figure 3 of EASB 05A017. For
purposes of this AD, a sling cycle is defined
as one landing with or without stopping the
rotor or one external load-carrying operation;
an external load-carrying operation occurs
each time a helicopter picks up an external
load and drops it off.
(3) If there is a crack, before further flight,
replace the junction frame.
(g) Special Flight Permits
Special flight permits are prohibited.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-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) Airbus Helicopters Service Bulletin No.
EC130–53–029, Revision 0, dated February
20, 2015, which is not incorporated by
reference, contains additional information
about the subject of this final rule. For
service information identified in this final
rule, contact Airbus Helicopters, Inc., 2701
N. Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub. You
may review a copy of the service information
at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2015–0033–E, dated February 24, 2015.
You may view the EASA AD on the Internet
at https://www.regulations.gov in Docket No.
FAA–2015–3970.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 5302: Rotorcraft Tailboom.
(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) Airbus Helicopters Emergency Alert
Service Bulletin No. 05A017, Revision 2,
dated February 20, 2015.
(ii) Reserved.
(3) For Airbus Helicopters service
information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N.
Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
(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 April 15,
2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–09235 Filed 4–29–16; 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]
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RIN 2120–AA64
Airworthiness Directives; Piper
Aircraft, Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
SUMMARY:
VerDate Sep<11>2014
17:39 Apr 29, 2016
Jkt 238001
Piper Aircraft, Inc. Model PA–31–350
airplanes. This AD was prompted by a
report of an engine fire caused by a leak
in the fuel pump inlet hose. This AD
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. We
are issuing this AD to correct the unsafe
condition on these products.
DATES: This AD is effective June 6, 2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 6, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Piper Aircraft, Inc., 2926 Piper Drive,
Vero Beach, Florida 32960; telephone:
(772) 567–4361; fax: (772) 978–6573;
Internet: www.piper.com/home/pages/
Publications.cfm. You may view this
referenced service information at the
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2014–0338.
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–
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.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain Piper
Aircraft, Inc. Model PA–31–350
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Fmt 4700
Sfmt 4700
airplanes. The SNPRM published in the
Federal Register on January 26, 2016
(81 FR 4214). We preceded the SNPRM
with a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on June 3, 2014 (79 FR 31888).
The NPRM proposed to require
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. The NPRM was
prompted by a report of an engine fire
on a Piper Aircraft, Inc. (Piper) Model
PA–31–350 airplane. Investigation
revealed that the fire was caused by a
leak in the fuel pump inlet hose that
resulted from repeated contact with an
adjacent turbocharger support assembly
caused by inadequate clearance between
the two assemblies. The SNPRM
proposed to require the same actions as
proposed in the NPRM using revised
service information issued by the
manufacturer to clarify which engines
are part of the airplane applicability and
to revise the instructions for
accomplishing the proposed actions.
This condition, if not corrected, could
result in damage to the fuel inlet hose
assembly, which could cause the fuel
pump inlet hose to fail and leak fuel in
the engine compartment. This condition
could also cause damage to the
turbocharger support assembly, which
could require the turbocharger support
assembly to be repaired or replaced.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM
(81 FR 4214, January 26, 2016) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (81 FR
4214, January 26, 2016) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (81 FR 4214,
January 26, 2016).
Related Service Information Under 1
CFR Part 51
We reviewed Piper Aircraft, Inc.
Service Bulletin No. 1257A, dated
August 4, 2015. The service information
describes procedures for the following.
This service information is reasonably
E:\FR\FM\02MYR1.SGM
02MYR1
]]>Agencies
[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)]
[Rules and Regulations]
[Pages 26103-26106]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09235]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3970; Directorate Identifier 2015-SW-006-AD;
Amendment 39-18497; AD 2016-08-20]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Previously
Eurocopter France)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directive (AD) 2014-12-51 for
Airbus Helicopters (previously Eurocopter France) Model EC130B4 and
[[Page 26104]]
EC130T2 helicopters. AD 2014-12-51 required repetitively inspecting the
tailboom to Fenestron junction frame (junction frame) for a crack. This
new AD retains the requirements of AD 2014-12-51, changes the
applicability from helicopters with certain hours time-in-service (TIS)
to junction frames with certain hours TIS, and adds a compliance time
for sling cycles to the junction frame inspection interval. The actions
of this AD are intended to detect a crack and to prevent failure of the
junction frame, which could result in loss of the Fenestron and
subsequent loss of control of the helicopter.
DATES: This AD is effective June 6, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of June 6, 2016.
ADDRESSES: For service information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie,
TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at https://www.airbushelicopters.com/techpub. You may review
the referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort
Worth, TX 76177. It is also on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3970.
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-2015-
3970; 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, any
incorporated-by-reference service information, 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: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, Rotorcraft Directorate, FAA,
10101 Hillwood Pkwy, Fort Worth, TX 76177; email robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On September 25, 2015, at 80 FR 57742, the Federal Register
published our notice of proposed rulemaking (NPRM) to amend 14 CFR part
39 to remove AD 2014-12-51, Amendment 39-17921 (79 FR 45335, August 5,
2014), and add a new AD. AD 2014-12-51 applied to Airbus Helicopters
Model EC130B4 and EC130T2 helicopters with 690 or more hours TIS and
required, within 10 hours TIS, dye-penetrant inspecting certain areas
of the junction frame for a crack. AD 2014-12-51 also required, at
intervals not exceeding 25 hours TIS, either repeating the dye-
penetrant inspection or performing a borescope inspection of certain
areas of the junction frame for a crack. If there was a crack, AD 2014-
12-51 required replacing the junction frame. AD 2014-12-51 was prompted
by two incidents of crack propagation through the junction frame that
initiated in the lower right-hand side between the web and the flange
where the lower spar of the tailboom is joined. The cracks were
significant in length and not visible from the outside of the
helicopter.
The NPRM was prompted by AD No. 2015-0033-E dated February 24, 2015
(AD 2015-0033-E), issued by EASA, which is the Technical Agent for the
Member States of the European Union, to correct an unsafe condition on
Airbus Helicopters EC130B4 and EC130T2 helicopters. The NPRM proposed
to require retaining the dye penetrant and borescope inspections in AD
2014-12-51 but with revised compliance times. The NRPM also proposed to
change the applicability to helicopters with 690 hours TIS accumulated
on the junction frame instead of on the helicopter, and proposed
including an inspection interval defined in sling cycles. These actions
were intended to detect a crack and to prevent failure of the junction
frame, which could result in loss of the Fenestron and subsequent loss
of control of the helicopter.
Comments
After our NPRM (80 FR 57742, September 25, 2015) was published, we
received a comment from one commenter.
Request
One commenter requested the addition of a 10-hour or 250-sling
cycle visual pilot check for helicopters with Modification 350A087421
or that have complied with Airbus Helicopters Service Bulletin No.
EC130-53-029, Revision 0, dated February 20, 2015 (SB EC130-53-029).
The commenter stated this pilot check would benefit operators and
provide the same level of safety.
We disagree. While the EASA AD allows the check requested by the
commenter as an alternative method, because the cause of the fatigue
cracking is still under investigation, we cannot determine that this
method would correct the unsafe condition.
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, 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, reviewed the relevant information,
considered the comment received, and determined the unsafe condition
exists and is likely to exist or develop on other helicopters of the
same type designs and that air safety and the public interest require
adopting the AD requirements as proposed.
Interim Action
We consider this AD to be an interim action. If final action is
later identified, we might consider further rulemaking then.
Differences Between This AD and the EASA AD
The EASA AD includes alternate compliance instructions for
helicopters modified with a cut-out in production by Airbus Helicopters
Modification 350A087421 or in service by compliance with SB EC130-53-
029. This AD does not.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Helicopters Emergency Alert Service Bulletin No.
05A017, Revision 2, dated February 20, 2015 (EASB 05A017), for Model
EC130B4 and EC130T2 helicopters. EASB 05A017 describes alternate
procedures for inspecting outside the tailboom for a crack at reduced
inspection intervals in combination with the internal inspections at
extended intervals. EASB 05A017 also specifies adding sling cycles to
the existing flight hour inspection interval for helicopters that
perform external load-carrying operations. EASA issued AD No. 2015-
0033-E mandating the requirements in EASB 05A017 to ensure the
continued airworthiness of these helicopters.
This service information is reasonably available because the
interested parties have access to it through their normal
[[Page 26105]]
course of business or by the means identified in the ADDRESSES section.
Other Related Service Information
Airbus Helicopters also issued SB EC130-53-029, which contains
procedures to cut out the skin and splice at the junction frame to
facilitate the external inspection specified in EASB 05A017.
Costs of Compliance
We estimate that this AD affects 208 helicopters of U.S. Registry.
We estimate that operators may incur the following costs in order to
comply with this AD. At an average labor rate of $85 per work-hour,
dye-penetrant inspecting the junction frame will require 1 work-hour,
for a cost of $85 per helicopter and a total cost of $17,680 for the
U.S. fleet, per inspection cycle. Borescope inspecting the junction
frame will require 0.5 work-hour, for a cost of $43 per helicopter and
a total cost of $8,944 for the U.S. fleet, per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2014-12-51, Amendment 39-17921 (79 FR 45335, August 5, 2014), and
adding the following new AD:
2016-08-20 Airbus Helicopters (Previously Eurocopter France):
Amendment 39-18497; Docket No. FAA-2015-3970; Directorate Identifier
2015-SW-006-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model EC130B4 and EC130T2
helicopters with a tailboom to fenestron junction frame (junction
frame) that has 690 or more hours time-in-service (TIS),
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the junction
frame. This condition could result in failure of the junction frame,
which could result in loss of the Fenestron and subsequent loss of
control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2014-12-51, Amendment 39-17921 (79 FR
45335, August 5, 2014).
(d) Effective Date
This AD becomes effective June 6, 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) Before the junction frame reaches 700 hours TIS or within 10
hours TIS, whichever occurs later, remove the horizontal stabilizer,
clean the junction frame, and dye-penetrant inspect around the
circumference of the junction frame for a crack in the areas shown
in Figure 1 of Airbus Helicopters EC130 Emergency Alert Service
Bulletin No. 05A017, Revision 2, dated February 20, 2015 (EASB
05A017). Pay particular attention to the area around the 4 spars
(item b) of Figure 1 of EASB 05A017. An example of a crack is shown
in Figure 3 of EASB 05A017.
(2) Within 25 hours TIS or 390 sling cycles, whichever occurs
first after the inspection required by paragraph (f)(1) of this AD,
and thereafter at intervals not exceeding 25 hours TIS or 390 sling
cycles, whichever occurs first, either perform the actions of
paragraph (f)(1) of this AD or, if the area is clean, using a
borescope, inspect around the circumference of the junction frame
for a crack in the areas shown in Figure 2 of EASB 05A017. Pay
particular attention to the area around the 4 spars (item b) of
Figure 2 of EASB 05A017. An example of a crack is shown in Figure 3
of EASB 05A017. For purposes of this AD, a sling cycle is defined as
one landing with or without stopping the rotor or one external load-
carrying operation; an external load-carrying operation occurs each
time a helicopter picks up an external load and drops it off.
(3) If there is a crack, before further flight, replace the
junction frame.
(g) Special Flight Permits
Special flight permits are prohibited.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Robert Grant, 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.
(i) Additional Information
(1) Airbus Helicopters Service Bulletin No. EC130-53-029,
Revision 0, dated February 20, 2015, which is not incorporated by
reference, contains additional information about the subject of this
final rule. For service information identified in this final rule,
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972) 641-3775; or at https://www.airbushelicopters.com/techpub. You
may review a copy of the service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177.
[[Page 26106]]
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2015-0033-E, dated February 24, 2015.
You may view the EASA AD on the Internet at https://www.regulations.gov in Docket No. FAA-2015-3970.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 5302: Rotorcraft
Tailboom.
(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) Airbus Helicopters Emergency Alert Service Bulletin No.
05A017, Revision 2, dated February 20, 2015.
(ii) Reserved.
(3) For Airbus Helicopters service information identified in
this final rule, contact Airbus Helicopters, Inc., 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800)
232-0323; fax (972) 641-3775; or at https://www.airbushelicopters.com/techpub.
(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 April 15, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-09235 Filed 4-29-16; 8:45 am]
BILLING CODE 4910-13-P
