Airworthiness Directives; Airbus Helicopters (Formerly Eurocopter France) Helicopters, 72390-72393 [2015-29402]
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Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules
standard rating of 95 °F dry bulb
outdoor temperature) not less than the
following:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Energy
efficiency
ratio
(EER)
Product class
[Docket No. FAA–2015–5914; Directorate
Identifier 2014–SW–056–AD]
RIN 2120–AA64
(i) Split-system rated cooling
capacity less than 45,000
Btu/hr .................................
(ii) Split-system rated cooling
capacity equal to or greater than 45,000 Btu/hr ........
(iii) Single-package systems
12.2
Airworthiness Directives; Airbus
Helicopters (Formerly Eurocopter
France) Helicopters
11.7
11.0
AGENCY:
Any outdoor unit model that has a
certified combination with a rating
below 14 SEER or the applicable EER
cannot be installed in this region. An
outdoor unit model certified below 14
SEER or the applicable EER by the
outdoor unit manufacturer cannot be
installed in this region even with an
independent coil manufacturer’s indoor
unit that may have a certified rating at
or above 14 SEER and the applicable
EER.
(5) Each basic model of single-package
central air conditioners and central air
conditioning heat pumps and each
individual combination of split-system
central air conditioners and central air
conditioning heat pumps manufactured
on or after January 1, 2015, shall have
an average off mode electrical power
consumption not more than the
following:
Product class
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(i) Split-system air conditioners ...............................
(ii) Split-system heat pumps
(iii) Single-package air conditioners ...............................
(iv) Single-package heat
pumps ...............................
(v) Small-duct, high-velocity
systems .............................
(vi) Space-constrained air
conditioners .......................
(vii) Space-constrained heat
pumps ...............................
*
*
*
*
We propose to adopt a new
airworthiness directive (AD) for Airbus
Helicopters Model SA341G and SA342J
helicopters. This proposed AD would
require repetitive inspections of a
certain part-numbered main rotor hub
torsion bar (torsion bar). This proposed
AD is prompted by several cases of
corrosion in the metal strands of the
torsion bar. The proposed actions are
intended to detect corrosion and
prevent failure of the torsion bar, loss of
a main rotor blade, and subsequent loss
of control of the helicopter.
DATES: We must receive comments on
this proposed AD by January 19, 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.
Average
• Fax: 202–493–2251.
off mode
• Mail: Send comments to the U.S.
power
Department of Transportation, Docket
consumption
Operations, M–30, West Building
PW,OFF
(watts)
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
30
• Hand Delivery: Deliver to the
33
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
30
Federal holidays.
Examining the AD Docket
30
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5914; 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
30
33
*
BILLING CODE 6450–01–P
14:08 Nov 18, 2015
SUMMARY:
33
[FR Doc. 2015–29435 Filed 11–18–15; 8:45 am]
VerDate Sep<11>2014
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
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section. Comments will be available in
the AD docket shortly after receipt. For
service information identified in this
proposed AD, contact Airbus
Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT:
Robert Grant, Aviation Safety Engineer,
Safety Management Group, FAA, 10101
Hillwood Pkwy, Fort Worth, Texas
76177; telephone (817) 222–5110; email
robert.grant@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
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
EASA, which is the Technical Agent
for the Member States of the European
Union, issued EASA AD No. 2014–0216,
dated September 24, 2014, to correct an
unsafe condition for Airbus Helicopters
Model SA341G and SA342J helicopters.
EASA advises that several cases of
cracks were found on the polyurethane
(PU) coating of part-numbered
704A33633274 torsion bars installed on
military Model SA341 helicopters.
EASA states that these parts can also be
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Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules
installed on civilian Model SA341 and
SA342 helicopters. According to EASA,
analysis of the cracked torsion bars
showed small areas of superficial
corrosion on the strands inside the bars
can also develop during the
manufacturing process. EASA states that
cracking of the PU coating near these
areas and the associated penetration of
water can lead to further and deeper
development of the corrosion. EASA
advises that this condition, if not
detected and corrected, allows water to
penetrate into the torsion bar causing
corrosion and failure of the metal
strands inside the bar. Failure of the
metal strands could lead to torsion bar
failure, resulting in an in-flight loss of
a main rotor blade and consequent loss
of control of the helicopter.
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 Airbus Helicopters
Gazelle work card 65.12.607, dated
August 2008. This service information
describes inspecting the torsion bars for
a crack in the PU coating and for
corrosion and thickness of the bushings.
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 of
this NPRM.
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Other Related Service Information
Airbus Helicopters has issued Alert
Service Bulletin No. SA341/SA342–
05.40, Revision 0, dated April 28, 2014
(ASB), for Model SA341G and SA342J
helicopters certificated by the FAA, and
military Model SA341B, C, D, E, F, and
H and SA342K, L, L1, M, M1, and Ma
helicopters. The ASB specifies
repetitively inspecting the torsion bars
in accordance with certain work cards,
including work card 65.12.07. These
inspections are part of Airbus
Helicopters’ current maintenance
program, and the ASB revises the
compliance time interval for the
inspections.
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14:08 Nov 18, 2015
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Proposed AD Requirements
This proposed AD would require
removing and performing repetitive
inspections of each torsion bar for a
crack in the PU coating, the dimension
of the angle between the bushings,
corrosion on the inside diameter of each
bushing, the thickness of each bushing,
the size of the inside diameter of each
bushing, and missing varnish on the two
faces of each bushing. This proposed
AD would require replacing the torsion
bar before further flight if there is a
crack in the PU coating of a torsion bar
that matches or exceeds the damage
criteria, if the angle of the torsion bar is
7 degrees or more, if any corrosion on
a bushing cannot be removed by rubbing
it with an abrasive pad, if the thickness
of a bushing is less than 37.520 mm
(1.477 in), or if the diameter of a
bushing is larger than 21,040 mm (.828
in). If varnish is missing from more than
15 percent of the surface area from a
face of a bushing, this proposed AD
would require removing all varnish,
finishing with an abrasive pad, and
applying a coat of paint to the face of
the bushing.
Differences Between This Proposed AD
and the EASA AD
This proposed AD would require you
to replace a torsion bar instead of
returning it to the manufacturer for
examination.
Interim Action
We consider this proposed AD to be
an interim action. If final action is later
identified, we might consider further
rulemaking.
Costs of Compliance
We estimate that this proposed AD
would affect 33 helicopters of U.S.
Registry.
We estimate that operators may incur
the following costs in order to comply
with this AD. We estimate $85 per work
hour for labor. We estimate 8 work
hours to inspect each helicopter at an
estimated cost of $680 per helicopter
and $22,440 for the fleet per inspection
cycle. Replacing a torsion bar would
cost $7,020 for required parts; no
additional labor would be necessary.
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,
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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
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):
■
Airbus Helicopters (formerly Eurocopter
France): Docket No. FAA–2015–5914;
Directorate Identifier 2014–SW–056–AD.
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Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules
(a) Applicability
This AD applies to Model SA341G and
SA342J helicopters with a main rotor head
torsion bar (torsion bar) part number
704A33633274 installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the coating of the torsion bar
resulting in corrosion. This condition could
result in failure of a torsion bar, loss of a
main rotor blade, and subsequent loss of
control of the helicopter.
(c) Comments Due Date
We must receive comments by January 19,
2016.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) For each torsion bar with less than 5
years since the first date of installation on
any helicopter, within the compliance time
shown in Table 1 to paragraph (e)(1) of this
AD:
(i) Remove the torsion bar and, using a
magnifying glass with a maximum
magnification level of 10X, visually inspect
for a crack in the polyurethane (PU) coating
of the torsion bar as depicted in Figure 1 of
Airbus Helicopters Gazelle work card
65.12.607, dated August 2008 (work card).
Consider two cracks that are less than 5 mm
(.196 in) apart as a single crack. If there is a
crack in the PU coating that is more than 5
mm (.196 in), replace the torsion bar before
further flight. Do not rework the PU coating
of the torsion bar in any way.
(ii) Inspect the angle, dimension alpha, as
depicted in View on Arrow F of Figure 1 of
the work card. If the angle is 7 or more
degrees, replace the torsion bar before further
flight.
(iii) Inspect each bushing for corrosion on
the inside diameter. If any corrosion cannot
be removed by rubbing it with an abrasive
pad, replace the torsion bar before further
flight.
(iv) Using an outside micrometer, measure
the thickness, dimension a, of each bushing
as depicted in Detail AA of Figure 1 of the
work card. If the thickness is less than 37.520
mm (1.477 in), replace the torsion bar before
further flight.
(v) Using an inside micrometer, measure
the inside diameter, dimension b, of each
bushing as depicted in Detail AA of Figure
1 of the work card. If the diameter is larger
than 21.040 mm (.828 in), replace the torsion
bar before further flight.
(vi) Inspect the two faces of each bushing
for missing varnish. If varnish is missing
from more than 15% of the surface area on
a face of a bushing, before further flight,
remove all varnish using 400-grit abrasive
paper. Finish with an abrasive pad and apply
a coat of P05 paint to the face of the bushing.
TABLE 1 TO PARAGRAPH (e)(1)
Time accumulated on torsion bar
Compliance time
(i) Less than 320 hours time-in-service (TIS) since new and has never
been inspected in accordance with Airbus Helicopters 341G–342J
Airworthiness Limitations, Revision 18, dated June 2014 (limitations
inspection).
(ii) 320 or more hours TIS since new and has never had a limitations
inspection.
Before accumulating 420 hours TIS since new or within 24 months
since the date of first installation on any helicopter, whichever occurs
first.
(iii) Less than 320 hours TIS since the last limitations inspection ...........
(iv) 320 or more hours TIS since the last limitations inspection ..............
(2) For each torsion bar with 5 or more
years since the first date of installation on
Within 100 hours TIS, or before accumulating 600 hours TIS since
new, or within 24 months since the date of first installation on any
helicopter, whichever occurs first.
Before accumulating 420 hours TIS since the last limitations inspection
or within 24 months since the last limitations inspection, whichever
occurs first.
Within 100 hours TIS, or before accumulating 600 hours TIS since the
last limitations inspection, or within 24 months since the last limitations inspection, whichever occurs first.
any helicopter, within the compliance time
shown in Table 2 to paragraph (e)(2) of this
AD, do the inspections required by
paragraphs (e)(1)(i) through (vi) of this AD.
TABLE 2 TO PARAGRAPH (e)(2)
Compliance time
(i) Less than 320 hours TIS since new, and less than 6 months since
the date of first installation on any helicopter, and has never had a
limitations inspection.
(ii) 320 or more hours TIS since new or more than 6 months since the
date of first installation on any helicopter, and has never had a limitations inspection.
(iii) Less than 320 hours TIS since last limitations inspection and less
than 6 months since the last limitations inspection.
(iv) 320 or more hours TIS since last limitations inspection or 6 or more
months since the last limitations inspection.
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Time accumulated on torsion bar
Before accumulating 420 hours TIS since new or within 12 months
since the date of first installation on any helicopter, whichever occurs
first.
Within 100 hours TIS, or within 6 months, or before accumulating 600
hours TIS since new, or within 24 months since the date of first installation on any helicopter, whichever occurs first.
Before accumulating 420 hours TIS since last limitations inspection or
12 months since last limitations inspection, whichever occurs first.
Within 100 hours TIS, or within 6 months, or before accumulating 600
hours TIS since the last limitations inspection, or within 24 months
since the last limitations inspection, whichever occurs first.
(3) Repeat the inspections required by
paragraphs (e)(1)(i) through (vi) of this AD as
follows:
(i) For torsion bars with less than 6 years
since the date of installation on any
helicopter, at intervals not to exceed 420
hours TIS or 24 months, whichever occurs
first.
(ii) For torsion bars with 6 or more years
since the date of installation on any
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helicopter, at intervals not to exceed 420
hours TIS or 12 months, whichever comes
first.
(f) 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
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Group, 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
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Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
(1) Airbus Helicopters Alert Service
Bulletin ASB No. SA341/SA342–05.40,
Revision 0, dated April 28, 2014, which is
not incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Airbus Helicopters, 2701 N.
Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–0323;
fax (972) 641–3775; or at https://
www.airbushelicopters.com/techpub. You
may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N–321, Fort Worth,
TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2014–0216, dated September 24, 2014.
You may view the EASA AD on the Internet
at https://www.regulations.gov in the AD
Docket.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6700 Main Rotor.
Issued in Fort Worth, Texas, on November
9, 2015.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015–29402 Filed 11–18–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–5808; Directorate
Identifier 2015–NM–111–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This proposed AD was
prompted by reports of water leakage
from the potable water system due to
improperly installed waterline
couplings, and water leaking into the
electronics equipment (EE) bays from
above the floor in the main cabin,
resulting in water on the equipment in
the EE bays. This proposed AD would
require replacing the potable waterline
couplings above the forward and aft EE
bays with new, improved couplings.
rmajette on DSK2TPTVN1PROD with PROPOSALS
SUMMARY:
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14:08 Nov 18, 2015
Jkt 238001
This proposed AD would also require
sealing the main cabin floor areas above
the aft EE bay, installing drip shields
and foam blocks, and rerouting the wire
bundles near the drip shields above the
equipment in the aft EE bay. We are
proposing this AD to prevent a water
leak from an improperly installed
potable water system coupling, or main
cabin water source, which could cause
the equipment in the EE bays to become
wet, resulting in an electrical short and
potential loss of system functions
essential for safe flight.
DATES: We must receive comments on
this proposed AD by January 4, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
5808.
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–
5808; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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FOR FURTHER INFORMATION CONTACT:
Susan L. Monroe, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6457;
fax: 425–917–6590; email:
susan.l.monroe@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2015–5808; Directorate Identifier 2015–
NM–111–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We received reports of water leakage
from the potable water system due to
improperly installed waterline
couplings, and water leaking into the EE
bays from above the floor in the main
cabin, resulting in water on the
equipment in the EE bays. Such leakage
could result in an electrical short and
potential loss of system functions
essential for safe flight.
Related Service Information Under 1
CFR Part 51
We reviewed the following service
information:
• Boeing Alert Service Bulletin B787–
81205–SB380009–00, Issue 001, dated
March 26, 2015.
• Boeing Alert Service Bulletin B787–
81205–SB530029–00, Issue 001, dated
March 26, 2015.
• Boeing Alert Service Bulletin B787–
81205–SB530031–00, Issue 001, dated
March 26, 2015.
This service information describes
procedures for replacing the potable
waterline couplings above the forward
and aft EE bays with new, improved
couplings; sealing the floors, seat tracks,
and lavatories above the aft EE bay;
installing drip shields and foam blocks;
and rerouting the wire bundles adjacent
to the drip shields above the aft EE bay.
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]]>Agencies
[Federal Register Volume 80, Number 223 (Thursday, November 19, 2015)]
[Proposed Rules]
[Pages 72390-72393]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29402]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-5914; Directorate Identifier 2014-SW-056-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Formerly Eurocopter
France) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
Airbus Helicopters Model SA341G and SA342J helicopters. This proposed
AD would require repetitive inspections of a certain part-numbered main
rotor hub torsion bar (torsion bar). This proposed AD is prompted by
several cases of corrosion in the metal strands of the torsion bar. The
proposed actions are intended to detect corrosion and prevent failure
of the torsion bar, loss of a main rotor blade, and subsequent loss of
control of the helicopter.
DATES: We must receive comments on this proposed AD by January 19,
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-2015-
5914; 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 AD, contact Airbus Helicopters,
2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000
or (800) 232-0323; fax (972) 641-3775; or at https://www.airbushelicopters.com/techpub. You may review the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX
76177.
FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy, Fort
Worth, Texas 76177; telephone (817) 222-5110; email
robert.grant@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 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
EASA, which is the Technical Agent for the Member States of the
European Union, issued EASA AD No. 2014-0216, dated September 24, 2014,
to correct an unsafe condition for Airbus Helicopters Model SA341G and
SA342J helicopters. EASA advises that several cases of cracks were
found on the polyurethane (PU) coating of part-numbered 704A33633274
torsion bars installed on military Model SA341 helicopters. EASA states
that these parts can also be
[[Page 72391]]
installed on civilian Model SA341 and SA342 helicopters. According to
EASA, analysis of the cracked torsion bars showed small areas of
superficial corrosion on the strands inside the bars can also develop
during the manufacturing process. EASA states that cracking of the PU
coating near these areas and the associated penetration of water can
lead to further and deeper development of the corrosion. EASA advises
that this condition, if not detected and corrected, allows water to
penetrate into the torsion bar causing corrosion and failure of the
metal strands inside the bar. Failure of the metal strands could lead
to torsion bar failure, resulting in an in-flight loss of a main rotor
blade and consequent loss of control of the helicopter.
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 Airbus Helicopters Gazelle work card 65.12.607, dated
August 2008. This service information describes inspecting the torsion
bars for a crack in the PU coating and for corrosion and thickness of
the bushings.
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 of this
NPRM.
Other Related Service Information
Airbus Helicopters has issued Alert Service Bulletin No. SA341/
SA342-05.40, Revision 0, dated April 28, 2014 (ASB), for Model SA341G
and SA342J helicopters certificated by the FAA, and military Model
SA341B, C, D, E, F, and H and SA342K, L, L1, M, M1, and Ma helicopters.
The ASB specifies repetitively inspecting the torsion bars in
accordance with certain work cards, including work card 65.12.07. These
inspections are part of Airbus Helicopters' current maintenance
program, and the ASB revises the compliance time interval for the
inspections.
Proposed AD Requirements
This proposed AD would require removing and performing repetitive
inspections of each torsion bar for a crack in the PU coating, the
dimension of the angle between the bushings, corrosion on the inside
diameter of each bushing, the thickness of each bushing, the size of
the inside diameter of each bushing, and missing varnish on the two
faces of each bushing. This proposed AD would require replacing the
torsion bar before further flight if there is a crack in the PU coating
of a torsion bar that matches or exceeds the damage criteria, if the
angle of the torsion bar is 7 degrees or more, if any corrosion on a
bushing cannot be removed by rubbing it with an abrasive pad, if the
thickness of a bushing is less than 37.520 mm (1.477 in), or if the
diameter of a bushing is larger than 21,040 mm (.828 in). If varnish is
missing from more than 15 percent of the surface area from a face of a
bushing, this proposed AD would require removing all varnish, finishing
with an abrasive pad, and applying a coat of paint to the face of the
bushing.
Differences Between This Proposed AD and the EASA AD
This proposed AD would require you to replace a torsion bar instead
of returning it to the manufacturer for examination.
Interim Action
We consider this proposed AD to be an interim action. If final
action is later identified, we might consider further rulemaking.
Costs of Compliance
We estimate that this proposed AD would affect 33 helicopters of
U.S. Registry.
We estimate that operators may incur the following costs in order
to comply with this AD. We estimate $85 per work hour for labor. We
estimate 8 work hours to inspect each helicopter at an estimated cost
of $680 per helicopter and $22,440 for the fleet per inspection cycle.
Replacing a torsion bar would cost $7,020 for required parts; no
additional labor would be necessary.
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 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 adding the following new airworthiness
directive (AD):
Airbus Helicopters (formerly Eurocopter France): Docket No. FAA-
2015-5914; Directorate Identifier 2014-SW-056-AD.
[[Page 72392]]
(a) Applicability
This AD applies to Model SA341G and SA342J helicopters with a
main rotor head torsion bar (torsion bar) part number 704A33633274
installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the coating
of the torsion bar resulting in corrosion. This condition could
result in failure of a torsion bar, loss of a main rotor blade, and
subsequent loss of control of the helicopter.
(c) Comments Due Date
We must receive comments by January 19, 2016.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) For each torsion bar with less than 5 years since the first
date of installation on any helicopter, within the compliance time
shown in Table 1 to paragraph (e)(1) of this AD:
(i) Remove the torsion bar and, using a magnifying glass with a
maximum magnification level of 10X, visually inspect for a crack in
the polyurethane (PU) coating of the torsion bar as depicted in
Figure 1 of Airbus Helicopters Gazelle work card 65.12.607, dated
August 2008 (work card). Consider two cracks that are less than 5 mm
(.196 in) apart as a single crack. If there is a crack in the PU
coating that is more than 5 mm (.196 in), replace the torsion bar
before further flight. Do not rework the PU coating of the torsion
bar in any way.
(ii) Inspect the angle, dimension alpha, as depicted in View on
Arrow F of Figure 1 of the work card. If the angle is 7 or more
degrees, replace the torsion bar before further flight.
(iii) Inspect each bushing for corrosion on the inside diameter.
If any corrosion cannot be removed by rubbing it with an abrasive
pad, replace the torsion bar before further flight.
(iv) Using an outside micrometer, measure the thickness,
dimension a, of each bushing as depicted in Detail AA of Figure 1 of
the work card. If the thickness is less than 37.520 mm (1.477 in),
replace the torsion bar before further flight.
(v) Using an inside micrometer, measure the inside diameter,
dimension b, of each bushing as depicted in Detail AA of Figure 1 of
the work card. If the diameter is larger than 21.040 mm (.828 in),
replace the torsion bar before further flight.
(vi) Inspect the two faces of each bushing for missing varnish.
If varnish is missing from more than 15% of the surface area on a
face of a bushing, before further flight, remove all varnish using
400-grit abrasive paper. Finish with an abrasive pad and apply a
coat of P05 paint to the face of the bushing.
Table 1 to Paragraph (e)(1)
------------------------------------------------------------------------
Time accumulated on torsion bar Compliance time
------------------------------------------------------------------------
(i) Less than 320 hours time-in-service Before accumulating 420 hours
(TIS) since new and has never been TIS since new or within 24
inspected in accordance with Airbus months since the date of first
Helicopters 341G-342J Airworthiness installation on any
Limitations, Revision 18, dated June helicopter, whichever occurs
2014 (limitations inspection). first.
(ii) 320 or more hours TIS since new Within 100 hours TIS, or before
and has never had a limitations accumulating 600 hours TIS
inspection. since new, or within 24 months
since the date of first
installation on any
helicopter, whichever occurs
first.
(iii) Less than 320 hours TIS since the Before accumulating 420 hours
last limitations inspection. TIS since the last limitations
inspection or within 24 months
since the last limitations
inspection, whichever occurs
first.
(iv) 320 or more hours TIS since the Within 100 hours TIS, or before
last limitations inspection. accumulating 600 hours TIS
since the last limitations
inspection, or within 24
months since the last
limitations inspection,
whichever occurs first.
------------------------------------------------------------------------
(2) For each torsion bar with 5 or more years since the first
date of installation on any helicopter, within the compliance time
shown in Table 2 to paragraph (e)(2) of this AD, do the inspections
required by paragraphs (e)(1)(i) through (vi) of this AD.
Table 2 to Paragraph (e)(2)
------------------------------------------------------------------------
Time accumulated on torsion bar Compliance time
------------------------------------------------------------------------
(i) Less than 320 hours TIS since new, Before accumulating 420 hours
and less than 6 months since the date TIS since new or within 12
of first installation on any months since the date of first
helicopter, and has never had a installation on any
limitations inspection. helicopter, whichever occurs
first.
(ii) 320 or more hours TIS since new or Within 100 hours TIS, or within
more than 6 months since the date of 6 months, or before
first installation on any helicopter, accumulating 600 hours TIS
and has never had a limitations since new, or within 24 months
inspection. since the date of first
installation on any
helicopter, whichever occurs
first.
(iii) Less than 320 hours TIS since Before accumulating 420 hours
last limitations inspection and less TIS since last limitations
than 6 months since the last inspection or 12 months since
limitations inspection. last limitations inspection,
whichever occurs first.
(iv) 320 or more hours TIS since last Within 100 hours TIS, or within
limitations inspection or 6 or more 6 months, or before
months since the last limitations accumulating 600 hours TIS
inspection. since the last limitations
inspection, or within 24
months since the last
limitations inspection,
whichever occurs first.
------------------------------------------------------------------------
(3) Repeat the inspections required by paragraphs (e)(1)(i)
through (vi) of this AD as follows:
(i) For torsion bars with less than 6 years since the date of
installation on any helicopter, at intervals not to exceed 420 hours
TIS or 24 months, whichever occurs first.
(ii) For torsion bars with 6 or more years since the date of
installation on any helicopter, at intervals not to exceed 420 hours
TIS or 12 months, whichever comes first.
(f) 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, 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
[[Page 72393]]
operating any aircraft complying with this AD through an AMOC.
(g) Additional Information
(1) Airbus Helicopters Alert Service Bulletin ASB No. SA341/
SA342-05.40, Revision 0, dated April 28, 2014, which is not
incorporated by reference, contains additional information about the
subject of this AD. For service information identified in this AD,
contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at https://www.airbushelicopters.com/techpub. You may review
the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2014-0216, dated September 24, 2014. You
may view the EASA AD on the Internet at https://www.regulations.gov
in the AD Docket.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6700 Main Rotor.
Issued in Fort Worth, Texas, on November 9, 2015.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015-29402 Filed 11-18-15; 8:45 am]
BILLING CODE 4910-13-P
