Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France), 74362-74364 [2016-25748]
Download as PDF
<![CDATA[
74362
Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
any category, serial numbers 003 through 672
inclusive, on which Bombardier ModSum
8Q100813 or Bombardier Service Bulletin 8–
74–02 is incorporated.
(1) Model DHC–8–102, –103, and –106
airplanes.
(2) Model DHC–8–201 and –202 airplanes.
(3) Model DHC–8–301, –311, and –315
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 74, Ignition.
(e) Reason
This AD was prompted by reports of
incorrect installation of the auto-ignition
system due to crossed wires at one of the
splices in the auto-relight system. We are
issuing this AD to detect and correct
incorrect wiring of the auto-ignition system,
which could result in inability to restart the
engine in flight and consequent reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Corrective Actions
Within 2,000 flight hours or 12 months
after the effective date of this AD, whichever
occurs first: Inspect the auto-ignition system
for correct wiring and do all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–74–05, Revision B, dated
April 14, 2014. All applicable corrective
actions must be done before further flight.
Lhorne on DSK30JT082PROD with PROPOSALS
(h) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Bombardier
Service Bulletin 8–74–05, dated July 12,
2013; or Revision A, dated January 27, 2014.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York 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.
(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
VerDate Sep<11>2014
15:05 Oct 25, 2016
Jkt 241001
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–36, dated
November 19, 2013, 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–2016–9299.
(2) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com. 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.
Issued in Renton, Washington, on October
14, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–25664 Filed 10–25–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3343; Directorate
Identifier 2015–SW–078–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France)
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2014–12–
12 for Airbus Helicopters (previously
Eurocopter France) Model EC130B4 and
Model EC120B helicopters. AD 2014–
12–12 currently requires inspecting and,
if necessary, replacing parts of the
sliding door star support attachment
assembly. This proposed AD would
expand the applicability and provide
revised instructions for reinforcing the
sliding door. These proposed actions are
intended to prevent failure of the sliding
door star support attachment, which
could inhibit the operation of the
sliding door from the inside, delaying
the evacuation of passengers during an
emergency.
SUMMARY:
PO 00000
Frm 00048
Fmt 4702
Sfmt 4702
We must receive comments on
this proposed AD by December 27,
2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
3343; 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 proposed AD, the
European Aviation Safety Agency
(EASA) AD, the economic evaluation,
any comments received and other
information. The street address for the
Docket Operations Office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
For service information identified in
this proposed 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 service information at
the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177.
FOR FURTHER INFORMATION CONTACT:
David Hatfield, Aviation Safety
Engineer, Safety Management Group,
Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5116; email
david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
E:\FR\FM\26OCP1.SGM
26OCP1
Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Lhorne on DSK30JT082PROD with PROPOSALS
Discussion
On June 13, 2014, we issued AD
2014–12–12, Amendment 39–17873 (79
FR 36638, June 30, 2014) for Airbus
Helicopters Model EC120B helicopters
with serial numbers up to and including
1367 and with a sliding door part
number (P/N) C526A2370101 installed
and Model EC130B4 helicopters with
sliding door P/N C526S1101051
installed. AD 2014–12–12 does not
apply to helicopters with modification
(MOD) 07 3796 or 07 2921 installed. AD
2014–12–12 requires inspecting the
upper and lower locking pin control rod
fittings and the star support pin for a
crack and reinforcing the sliding door
star support stringer by installing three
carbon fabric plies.
AD 2014–12–12 was prompted by AD
No. 2013–0093, dated April 15, 2013,
and corrected on April 17, 2013, issued
by EASA, which is the Technical Agent
for the Member States of the European
Union. EASA AD No. 2013–0093 was
issued to correct an unsafe condition for
Model EC120B and EC130B4 helicopters
after a case was reported where
passengers could not open a helicopter’s
sliding door after landing. EASA advises
that an investigation revealed a failure
of the sliding door star axle support.
Actions Since AD 2014–12–12 Was
Issued
Since we issued AD 2014–12–12,
EASA has issued EASA AD No. 2015–
0020, dated February 11, 2015, to
correct an unsafe condition for Model
EC120B helicopters with sliding door P/
N C526A2370101 and Model EC130B4
helicopters sliding door P/N
C526S1101051. EASA AD No. 2015–
0020 does not apply to helicopters with
VerDate Sep<11>2014
15:05 Oct 25, 2016
Jkt 241001
MOD A00565, 07 3796, or 07 2921.
EASA AD No. 2015–0020 supersedes
EASA AD No. 2013–0093. EASA
advises that after it issued AD No. 2013–
0093, it discovered that the doors could
be installed on all serial-numbered
EC120B helicopters. Also, Eurocopter
(now Airbus Helicopters) learned of
difficulties with installing the angle
bracket and plate used to reinforce the
sliding door star support. Because of the
distance between the star support pin
and the bottom of the stringer on
composite sliding doors, installation of
the angle bracket and plate is not
possible in a small number of sliding
doors. Eurocopter subsequently revised
its repair procedures to provide an
alternate method for reinforcing the
sliding door star support.
EASA advises that it consequently
issued AD No. 2015–0020 to extend the
applicability to all serial-numbered
EC120B helicopters with the affected
sliding doors. EASA AD No. 2015–0020
also requires compliance with the
revised service information.
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 its
AD. We are proposing this AD because
we evaluated all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other products of the same
type design.
Related Service Information Under 1
CFR Part 51
We reviewed Eurocopter (now Airbus
Helicopters) Alert Service Bulletin
(ASB) No. EC120–52A014, Revision 2,
dated October 28, 2013, for Model
EC120B helicopters and ASB No. 130–
52A009, Revision 1, dated January 25,
2013, for Model EC130B4 helicopters.
This service information specifies visual
and dye penetrant inspections of
sections of the sliding door attachment
assembly and reinforcement of the
sliding door star support. ASB EC120–
52A014 was changed at Revision 2 to
expand the applicability for all serialnumbered Model 120B helicopters and
provides an alternative procedure for
reinforcing the sliding door star support.
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.
PO 00000
Frm 00049
Fmt 4702
Sfmt 4702
74363
Proposed AD Requirements
This proposed AD would require,
within 165 hours time-in-service (TIS):
• Visually inspecting each upper and
lower locking pin control rod end fitting
(control end fitting) and replacing it
before further flight if it is bent, twisted,
or broken.
• Cleaning and dye-penetrant
inspecting the star support pin for a
crack and replacing it before further
flight if it is cracked.
• Reinforcing the sliding door star
support stringer by installing three
carbon fabric plies.
This proposed AD would also
prohibit installing a sliding door P/N
C526A2370101 on a Model EC120B
helicopter, or a sliding door P/N
C526S1101051 on a Model EC130B4
helicopter, unless the sliding door star
support stringer is reinforced as
required by this proposed AD.
Costs of Compliance
We estimate that this proposed AD
would affect 261 helicopters of U.S.
Registry and that labor costs average $85
a work hour. Based on these estimates,
we expect the following costs:
• Visually inspecting the control rod
end fittings would require 1 work-hour
and a minimal amount for consumable
materials for an estimated cost of $85
per helicopter, or $22,185 for the U.S.
fleet.
• Replacing the control rod end
fittings with airworthy fittings would
require 5 work-hours for a labor cost of
$425. Parts would cost about $242 for an
estimated total cost of $667 per
helicopter.
• Dye-penetrant inspecting the star
support pin for a crack would require 2
work-hours and no parts for an
estimated cost of $170 per helicopter
and $44,370 for the U.S. fleet.
• Replacing the star support pin
would require 5 work-hours. Parts
would cost about $200 for an estimated
total cost of $625 per helicopter.
• Installing three carbon fabric plies
to reinforce the sliding door star support
would require 5 work-hours. Parts
would cost $200 for an estimated total
cost of $625 per helicopter and $163,125
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,
E:\FR\FM\26OCP1.SGM
26OCP1
74364
Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
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.
Airbus Helicopters (Previously Eurocopter
France): Docket No. FAA–2016–3343;
Directorate Identifier 2015–SW–078–AD.
Regulatory Findings
(b) Unsafe Condition
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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, I certify
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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 proposed 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Lhorne on DSK30JT082PROD with PROPOSALS
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2014–12–12, Amendment 39–17873 (79
FR 36638, June 30, 2014), and adding
the following new AD:
■
VerDate Sep<11>2014
15:05 Oct 25, 2016
Jkt 241001
(a) Applicability
This AD applies to the following
helicopters, certificated in any category,
except those with modification A00565, 07
3796, or 07 2921 installed:
(1) Model EC120B helicopters with a
sliding door part number (P/N)
C526A2370101 installed; and
(2) Model EC130B4 helicopters with a
sliding door P/N C526S1101051 installed.
This AD defines the unsafe condition as a
failure of the sliding door star axle support.
This condition could prevent operation of a
sliding door from inside, which could delay
evacuation of passengers during an
emergency.
(c) Affected ADs
This AD supersedes AD 2014–12–12,
Amendment 39–17873 (79 FR 36638, June
30, 2014).
(d) Comments Due Date
We must receive comments by December
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) Within 165 hours time-in-service:
(i) Visually inspect each upper and lower
locking pin control rod end fitting (control
end fitting) for a bend, twist, or breakage. If
a control end fitting is bent, twisted, or
broken, before further flight, replace the
control end fitting with an airworthy control
end fitting.
(ii) Clean and dye penetrant inspect the
star support pin for a crack in the areas
identified as Zone X and Zone Y in Figure
3 of Eurocopter Alert Service Bulletin No.
EC120–52A014, Revision 2, dated October
28, 2013 (ASB No. EC120–52A014) or
Eurocopter Alert Service Bulletin No. EC130–
52A009, Revision 1, dated January 25, 2013
(ASB No. EC130–52A009), as applicable to
your model helicopter. If there is a crack in
the star support pin, before further flight,
replace the star support pin with an
airworthy star support pin.
(iii) Reinforce the sliding door star support
stringer by installing three carbon fiber plies
and re-identify the sliding door by following
the Accomplishment Instructions, paragraphs
3.B.2.d. and 3.B.2.e of ASB No. EC120–
52A014, or paragraph 3.B.2.d. and the table
under paragraph 3.C of ASB No. EC130–
52A009, whichever is applicable to your
model helicopter.
(2) After the effective date of this AD, do
not install a sliding door P/N C526A2370101
on an EC120B helicopter, or a sliding door
P/N C526S1101051 on an EC130B4
helicopter, unless the sliding door has been
reinforced as required by paragraph (f)(1)(iii)
of this AD.
PO 00000
Frm 00050
Fmt 4702
Sfmt 4702
(g) Credit for Actions Previously Completed
Compliance with AD 2014–12–12 (79 FR
366838, June 30, 2014) before the effective
date of this AD is considered acceptable for
compliance with the corresponding actions
specified in paragraph (f)(1) of this AD.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: David Hatfield,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5116; 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
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2015–0020, dated February 11, 2015. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2016–3343.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 5220, Emergency Exits.
Issued in Fort Worth, Texas, on October 18,
2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–25748 Filed 10–25–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 2
[Docket No. FDA–2015–N–1355]
RIN 0910–AH36
Use of Ozone-Depleting Substances
AGENCY:
Food and Drug Administration,
HHS.
ACTION:
Proposed rule.
The Food and Drug
Administration (FDA, the Agency, or
we) is proposing to amend its regulation
on uses of ozone-depleting substances
(ODSs), including chlorofluorocarbons
(CFCs), to remove the designation for
certain products as ‘‘essential uses’’
under the Clean Air Act. Essential-use
products are exempt from the ban by
SUMMARY:
E:\FR\FM\26OCP1.SGM
26OCP1
]]>Agencies
[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)]
[Proposed Rules]
[Pages 74362-74364]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25748]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-3343; Directorate Identifier 2015-SW-078-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Previously
Eurocopter France)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-12-
12 for Airbus Helicopters (previously Eurocopter France) Model EC130B4
and Model EC120B helicopters. AD 2014-12-12 currently requires
inspecting and, if necessary, replacing parts of the sliding door star
support attachment assembly. This proposed AD would expand the
applicability and provide revised instructions for reinforcing the
sliding door. These proposed actions are intended to prevent failure of
the sliding door star support attachment, which could inhibit the
operation of the sliding door from the inside, delaying the evacuation
of passengers during an emergency.
DATES: We must receive comments on this proposed AD by December 27,
2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3343; 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 proposed AD, the European Aviation Safety Agency (EASA)
AD, the economic evaluation, any comments received and other
information. The street address for the Docket Operations Office
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this proposed 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 service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: David Hatfield, Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5116; email
david.hatfield@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this
[[Page 74363]]
document. The most helpful comments reference a specific portion of the
proposal, explain the reason for any recommended change, and include
supporting data. To ensure the docket does not contain duplicate
comments, commenters should send only one copy of written comments, or
if comments are filed electronically, commenters should submit only one
time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
On June 13, 2014, we issued AD 2014-12-12, Amendment 39-17873 (79
FR 36638, June 30, 2014) for Airbus Helicopters Model EC120B
helicopters with serial numbers up to and including 1367 and with a
sliding door part number (P/N) C526A2370101 installed and Model EC130B4
helicopters with sliding door P/N C526S1101051 installed. AD 2014-12-12
does not apply to helicopters with modification (MOD) 07 3796 or 07
2921 installed. AD 2014-12-12 requires inspecting the upper and lower
locking pin control rod fittings and the star support pin for a crack
and reinforcing the sliding door star support stringer by installing
three carbon fabric plies.
AD 2014-12-12 was prompted by AD No. 2013-0093, dated April 15,
2013, and corrected on April 17, 2013, issued by EASA, which is the
Technical Agent for the Member States of the European Union. EASA AD
No. 2013-0093 was issued to correct an unsafe condition for Model
EC120B and EC130B4 helicopters after a case was reported where
passengers could not open a helicopter's sliding door after landing.
EASA advises that an investigation revealed a failure of the sliding
door star axle support.
Actions Since AD 2014-12-12 Was Issued
Since we issued AD 2014-12-12, EASA has issued EASA AD No. 2015-
0020, dated February 11, 2015, to correct an unsafe condition for Model
EC120B helicopters with sliding door P/N C526A2370101 and Model EC130B4
helicopters sliding door P/N C526S1101051. EASA AD No. 2015-0020 does
not apply to helicopters with MOD A00565, 07 3796, or 07 2921. EASA AD
No. 2015-0020 supersedes EASA AD No. 2013-0093. EASA advises that after
it issued AD No. 2013-0093, it discovered that the doors could be
installed on all serial-numbered EC120B helicopters. Also, Eurocopter
(now Airbus Helicopters) learned of difficulties with installing the
angle bracket and plate used to reinforce the sliding door star
support. Because of the distance between the star support pin and the
bottom of the stringer on composite sliding doors, installation of the
angle bracket and plate is not possible in a small number of sliding
doors. Eurocopter subsequently revised its repair procedures to provide
an alternate method for reinforcing the sliding door star support.
EASA advises that it consequently issued AD No. 2015-0020 to extend
the applicability to all serial-numbered EC120B helicopters with the
affected sliding doors. EASA AD No. 2015-0020 also requires compliance
with the revised service information.
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
its AD. We are proposing this AD because we evaluated all known
relevant information and determined that an unsafe condition is likely
to exist or develop on other products of the same type design.
Related Service Information Under 1 CFR Part 51
We reviewed Eurocopter (now Airbus Helicopters) Alert Service
Bulletin (ASB) No. EC120-52A014, Revision 2, dated October 28, 2013,
for Model EC120B helicopters and ASB No. 130-52A009, Revision 1, dated
January 25, 2013, for Model EC130B4 helicopters. This service
information specifies visual and dye penetrant inspections of sections
of the sliding door attachment assembly and reinforcement of the
sliding door star support. ASB EC120-52A014 was changed at Revision 2
to expand the applicability for all serial-numbered Model 120B
helicopters and provides an alternative procedure for reinforcing the
sliding door star support.
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.
Proposed AD Requirements
This proposed AD would require, within 165 hours time-in-service
(TIS):
Visually inspecting each upper and lower locking pin
control rod end fitting (control end fitting) and replacing it before
further flight if it is bent, twisted, or broken.
Cleaning and dye-penetrant inspecting the star support pin
for a crack and replacing it before further flight if it is cracked.
Reinforcing the sliding door star support stringer by
installing three carbon fabric plies.
This proposed AD would also prohibit installing a sliding door P/N
C526A2370101 on a Model EC120B helicopter, or a sliding door P/N
C526S1101051 on a Model EC130B4 helicopter, unless the sliding door
star support stringer is reinforced as required by this proposed AD.
Costs of Compliance
We estimate that this proposed AD would affect 261 helicopters of
U.S. Registry and that labor costs average $85 a work hour. Based on
these estimates, we expect the following costs:
Visually inspecting the control rod end fittings would
require 1 work-hour and a minimal amount for consumable materials for
an estimated cost of $85 per helicopter, or $22,185 for the U.S. fleet.
Replacing the control rod end fittings with airworthy
fittings would require 5 work-hours for a labor cost of $425. Parts
would cost about $242 for an estimated total cost of $667 per
helicopter.
Dye-penetrant inspecting the star support pin for a crack
would require 2 work-hours and no parts for an estimated cost of $170
per helicopter and $44,370 for the U.S. fleet.
Replacing the star support pin would require 5 work-hours.
Parts would cost about $200 for an estimated total cost of $625 per
helicopter.
Installing three carbon fabric plies to reinforce the
sliding door star support would require 5 work-hours. Parts would cost
$200 for an estimated total cost of $625 per helicopter and $163,125
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,
[[Page 74364]]
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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)
2014-12-12, Amendment 39-17873 (79 FR 36638, June 30, 2014), and adding
the following new AD:
Airbus Helicopters (Previously Eurocopter France): Docket No. FAA-
2016-3343; Directorate Identifier 2015-SW-078-AD.
(a) Applicability
This AD applies to the following helicopters, certificated in
any category, except those with modification A00565, 07 3796, or 07
2921 installed:
(1) Model EC120B helicopters with a sliding door part number (P/
N) C526A2370101 installed; and
(2) Model EC130B4 helicopters with a sliding door P/N
C526S1101051 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a failure of the sliding
door star axle support. This condition could prevent operation of a
sliding door from inside, which could delay evacuation of passengers
during an emergency.
(c) Affected ADs
This AD supersedes AD 2014-12-12, Amendment 39-17873 (79 FR
36638, June 30, 2014).
(d) Comments Due Date
We must receive comments by December 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) Within 165 hours time-in-service:
(i) Visually inspect each upper and lower locking pin control
rod end fitting (control end fitting) for a bend, twist, or
breakage. If a control end fitting is bent, twisted, or broken,
before further flight, replace the control end fitting with an
airworthy control end fitting.
(ii) Clean and dye penetrant inspect the star support pin for a
crack in the areas identified as Zone X and Zone Y in Figure 3 of
Eurocopter Alert Service Bulletin No. EC120-52A014, Revision 2,
dated October 28, 2013 (ASB No. EC120-52A014) or Eurocopter Alert
Service Bulletin No. EC130-52A009, Revision 1, dated January 25,
2013 (ASB No. EC130-52A009), as applicable to your model helicopter.
If there is a crack in the star support pin, before further flight,
replace the star support pin with an airworthy star support pin.
(iii) Reinforce the sliding door star support stringer by
installing three carbon fiber plies and re-identify the sliding door
by following the Accomplishment Instructions, paragraphs 3.B.2.d.
and 3.B.2.e of ASB No. EC120-52A014, or paragraph 3.B.2.d. and the
table under paragraph 3.C of ASB No. EC130-52A009, whichever is
applicable to your model helicopter.
(2) After the effective date of this AD, do not install a
sliding door P/N C526A2370101 on an EC120B helicopter, or a sliding
door P/N C526S1101051 on an EC130B4 helicopter, unless the sliding
door has been reinforced as required by paragraph (f)(1)(iii) of
this AD.
(g) Credit for Actions Previously Completed
Compliance with AD 2014-12-12 (79 FR 366838, June 30, 2014)
before the effective date of this AD is considered acceptable for
compliance with the corresponding actions specified in paragraph
(f)(1) of this AD.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: David Hatfield, Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5116; 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
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2015-0020, dated February 11, 2015. You may
view the EASA AD on the Internet at https://www.regulations.gov in
Docket No. FAA-2016-3343.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 5220, Emergency
Exits.
Issued in Fort Worth, Texas, on October 18, 2016.
James A. Grigg,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-25748 Filed 10-25-16; 8:45 am]
BILLING CODE 4910-13-P
