80 FR 72390 - Airworthiness Directives; Airbus Helicopters (Formerly Eurocopter France) Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 223 (November 19, 2015)

Page Range		72390-72393
FR Document		2015-29402

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.

Federal Register, Volume 80 Issue 223 (Thursday, November 19, 2015)

[Federal Register Volume 80, Number 223 (Thursday, November 19, 2015)]
[Proposed Rules]
[Pages 72390-72393]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2015-29402]

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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 http://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 http://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 http://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.

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 http://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 http://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

Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 72391

installed on civilian Model SA341 and Proposed AD Requirements Part A, Subpart III, Section 44701:
SA342 helicopters. According to EASA, This proposed AD would require General requirements.’’ Under that
analysis of the cracked torsion bars removing and performing repetitive section, Congress charges the FAA with
showed small areas of superficial inspections of each torsion bar for a promoting safe flight of civil aircraft in
corrosion on the strands inside the bars crack in the PU coating, the dimension air commerce by prescribing regulations
can also develop during the of the angle between the bushings, for practices, methods, and procedures
manufacturing process. EASA states that corrosion on the inside diameter of each the Administrator finds necessary for
cracking of the PU coating near these bushing, the thickness of each bushing, safety in air commerce. This regulation
areas and the associated penetration of the size of the inside diameter of each is within the scope of that authority
water can lead to further and deeper bushing, and missing varnish on the two because it addresses an unsafe condition
development of the corrosion. EASA faces of each bushing. This proposed that is likely to exist or develop on
advises that this condition, if not AD would require replacing the torsion products identified in this rulemaking
detected and corrected, allows water to bar before further flight if there is a action.
penetrate into the torsion bar causing crack in the PU coating of a torsion bar Regulatory Findings
corrosion and failure of the metal that matches or exceeds the damage
strands inside the bar. Failure of the We determined that this proposed AD
criteria, if the angle of the torsion bar is
metal strands could lead to torsion bar would not have federalism implications
7 degrees or more, if any corrosion on
failure, resulting in an in-flight loss of under Executive Order 13132. This
a bushing cannot be removed by rubbing
a main rotor blade and consequent loss proposed AD would not have a
it with an abrasive pad, if the thickness
of control of the helicopter. substantial direct effect on the States, on
of a bushing is less than 37.520 mm
the relationship between the national
FAA’s Determination (1.477 in), or if the diameter of a
Government and the States, or on the
bushing is larger than 21,040 mm (.828 distribution of power and
These helicopters have been approved in). If varnish is missing from more than
by the aviation authority of France and responsibilities among the various
15 percent of the surface area from a levels of government.
are approved for operation in the United face of a bushing, this proposed AD For the reasons discussed, I certify
States. Pursuant to our bilateral would require removing all varnish, this proposed regulation:
agreement with France, EASA, its finishing with an abrasive pad, and 1. Is not a ‘‘significant regulatory
technical representative, has notified us applying a coat of paint to the face of action’’ under Executive Order 12866;
of the unsafe condition described in its the bushing. 2. Is not a ‘‘significant rule’’ under the
AD. We are proposing this AD because DOT Regulatory Policies and Procedures
we evaluated all known relevant Differences Between This Proposed AD
and the EASA AD (44 FR 11034, February 26, 1979);
information and determined that an 3. Will not affect intrastate aviation in
unsafe condition is likely to exist or This proposed AD would require you Alaska to the extent that it justifies
develop on other products of the same to replace a torsion bar instead of making a regulatory distinction; and
type design. returning it to the manufacturer for 4. Will not have a significant
examination. economic impact, positive or negative,
Related Service Information Under 1
CFR Part 51 Interim Action on a substantial number of small entities
under the criteria of the Regulatory
We reviewed Airbus Helicopters We consider this proposed AD to be Flexibility Act.
Gazelle work card 65.12.607, dated an interim action. If final action is later We prepared an economic evaluation
August 2008. This service information identified, we might consider further of the estimated costs to comply with
describes inspecting the torsion bars for rulemaking. this proposed AD and placed it in the
a crack in the PU coating and for Costs of Compliance AD docket.
corrosion and thickness of the bushings.
We estimate that this proposed AD List of Subjects in 14 CFR Part 39
This service information is reasonably would affect 33 helicopters of U.S.
available because the interested parties Air transportation, Aircraft, Aviation
Registry. safety, Incorporation by reference,
have access to it through their normal We estimate that operators may incur
course of business or by the means Safety.
the following costs in order to comply
identified in the ADDRESSES section of with this AD. We estimate $85 per work The Proposed Amendment
this NPRM. hour for labor. We estimate 8 work Accordingly, under the authority
Other Related Service Information hours to inspect each helicopter at an delegated to me by the Administrator,
estimated cost of $680 per helicopter the FAA proposes to amend 14 CFR part
Airbus Helicopters has issued Alert and $22,440 for the fleet per inspection 39 as follows:
Service Bulletin No. SA341/SA342– cycle. Replacing a torsion bar would
05.40, Revision 0, dated April 28, 2014 cost $7,020 for required parts; no PART 39—AIRWORTHINESS
(ASB), for Model SA341G and SA342J additional labor would be necessary. DIRECTIVES
helicopters certificated by the FAA, and
military Model SA341B, C, D, E, F, and Authority for This Rulemaking ■ 1. The authority citation for part 39
H and SA342K, L, L1, M, M1, and Ma Title 49 of the United States Code continues to read as follows:
helicopters. The ASB specifies specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701.
rmajette on DSK2TPTVN1PROD with PROPOSALS

repetitively inspecting the torsion bars rules on aviation safety. Subtitle I,
in accordance with certain work cards, section 106, describes the authority of § 39.13 [Amended]
including work card 65.12.07. These the FAA Administrator. ‘‘Subtitle VII: ■ 2. The FAA amends § 39.13 by adding
inspections are part of Airbus Aviation Programs,’’ describes in more the following new airworthiness
Helicopters’ current maintenance detail the scope of the Agency’s directive (AD):
program, and the ASB revises the authority. Airbus Helicopters (formerly Eurocopter
compliance time interval for the We are issuing this rulemaking under France): Docket No. FAA–2015–5914;
inspections. the authority described in ‘‘Subtitle VII, Directorate Identifier 2014–SW–056–AD.

VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 PO 00000 Frm 00034 Fmt 4702 Sfmt 4702 E:\FR\FM\19NOP1.SGM 19NOP1

Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 72393

operating any aircraft complying with this This proposed AD would also require FOR FURTHER INFORMATION CONTACT:
AD through an AMOC. sealing the main cabin floor areas above Susan L. Monroe, Aerospace Engineer,
(g) Additional Information the aft EE bay, installing drip shields Cabin Safety and Environmental
(1) Airbus Helicopters Alert Service
and foam blocks, and rerouting the wire Systems Branch, ANM–150S, FAA,
Bulletin ASB No. SA341/SA342–05.40, bundles near the drip shields above the Seattle Aircraft Certification Office
Revision 0, dated April 28, 2014, which is equipment in the aft EE bay. We are (ACO), 1601 Lind Avenue SW., Renton,
not incorporated by reference, contains proposing this AD to prevent a water WA 98057–3356; phone: 425–917–6457;
additional information about the subject of leak from an improperly installed fax: 425–917–6590; email:
this AD. For service information identified in potable water system coupling, or main susan.l.monroe@faa.gov.
this AD, contact Airbus Helicopters, 2701 N. cabin water source, which could cause SUPPLEMENTARY INFORMATION:
Forum Drive, Grand Prairie, TX 75052; the equipment in the EE bays to become
telephone (972) 641–0000 or (800) 232–0323; wet, resulting in an electrical short and Comments Invited
fax (972) 641–3775; or at http:// potential loss of system functions We invite you to send any written
www.airbushelicopters.com/techpub. You
may review the referenced service
essential for safe flight. relevant data, views, or arguments about
information at the FAA, Office of the DATES: We must receive comments on this proposal. Send your comments to
Regional Counsel, Southwest Region, 10101 this proposed AD by January 4, 2016. an address listed under the ADDRESSES
Hillwood Pkwy., Room 6N–321, Fort Worth, ADDRESSES: You may send comments, section. Include ‘‘Docket No. FAA–
TX 76177. using the procedures found in 14 CFR 2015–5808; Directorate Identifier 2015–
(2) The subject of this AD is addressed in 11.43 and 11.45, by any of the following NM–111–AD’’ at the beginning of your
European Aviation Safety Agency (EASA) AD methods: comments. We specifically invite
No. 2014–0216, dated September 24, 2014. • Federal eRulemaking Portal: Go to comments on the overall regulatory,
You may view the EASA AD on the Internet
http://www.regulations.gov. Follow the economic, environmental, and energy
at http://www.regulations.gov in the AD
Docket. instructions for submitting comments. aspects of this proposed AD. We will
• Fax: 202–493–2251. consider all comments received by the
(h) Subject • Mail: U.S. Department of closing date and may amend this
Joint Aircraft Service Component (JASC) Transportation, Docket Operations, M– proposed AD because of those
Code: 6700 Main Rotor. 30, West Building Ground Floor, Room comments.
Issued in Fort Worth, Texas, on November W12–140, 1200 New Jersey Avenue SE., We will post all comments we
9, 2015. Washington, DC 20590. receive, without change, to http://
Lance T. Gant,
• Hand Delivery: Deliver to Mail www.regulations.gov, including any
address above between 9 a.m. and 5 personal information you provide. We
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
p.m., Monday through Friday, except will also post a report summarizing each
Federal holidays. substantive verbal contact we receive
[FR Doc. 2015–29402 Filed 11–18–15; 8:45 am]
For service information identified in about this proposed AD.
BILLING CODE 4910–13–P this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data Discussion
& Services Management, P.O. Box 3707, We received reports of water leakage
DEPARTMENT OF TRANSPORTATION MC 2H–65, Seattle, WA 98124–2207; from the potable water system due to
Federal Aviation Administration telephone 206–544–5000, extension 1; improperly installed waterline
fax 206–766–5680; Internet https:// couplings, and water leaking into the EE
14 CFR Part 39 www.myboeingfleet.com. You may view bays from above the floor in the main
this referenced service information at cabin, resulting in water on the
[Docket No. FAA–2015–5808; Directorate the FAA, Transport Airplane equipment in the EE bays. Such leakage
Identifier 2015–NM–111–AD] Directorate, 1601 Lind Avenue SW., could result in an electrical short and
RIN 2120–AA64
Renton, WA. For information on the potential loss of system functions
availability of this material at the FAA, essential for safe flight.
Airworthiness Directives; The Boeing call 425–227–1221. It is also available
on the Internet at http:// Related Service Information Under 1
Company Airplanes
www.regulations.gov by searching for CFR Part 51
AGENCY: Federal Aviation and locating Docket No. FAA–2015– We reviewed the following service
Administration (FAA), DOT. 5808. information:
ACTION: Notice of proposed rulemaking • Boeing Alert Service Bulletin B787–
Examining the AD Docket
(NPRM). 81205–SB380009–00, Issue 001, dated
You may examine the AD docket on March 26, 2015.
SUMMARY: We propose to adopt a new the Internet at http:// • Boeing Alert Service Bulletin B787–
airworthiness directive (AD) for certain www.regulations.gov by searching for 81205–SB530029–00, Issue 001, dated
The Boeing Company Model 787–8 and locating Docket No. FAA–2015– March 26, 2015.
airplanes. This proposed AD was 5808; or in person at the Docket • Boeing Alert Service Bulletin B787–
prompted by reports of water leakage Management Facility between 9 a.m. 81205–SB530031–00, Issue 001, dated
from the potable water system due to and 5 p.m., Monday through Friday, March 26, 2015.
improperly installed waterline except Federal holidays. The AD docket This service information describes
rmajette on DSK2TPTVN1PROD with PROPOSALS

couplings, and water leaking into the contains this proposed AD, the procedures for replacing the potable
electronics equipment (EE) bays from regulatory evaluation, any comments waterline couplings above the forward
above the floor in the main cabin, received, and other information. The and aft EE bays with new, improved
resulting in water on the equipment in street address for the Docket Office couplings; sealing the floors, seat tracks,
the EE bays. This proposed AD would (phone: 800–647–5527) is in the and lavatories above the aft EE bay;
require replacing the potable waterline ADDRESSES section. Comments will be installing drip shields and foam blocks;
couplings above the forward and aft EE available in the AD docket shortly after and rerouting the wire bundles adjacent
bays with new, improved couplings. receipt. to the drip shields above the aft EE bay.

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Document Created: 2015-12-14 13:57:23
Document Modified: 2015-12-14 13:57:23

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by January 19, 2016.
Contact		Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy, Fort Worth, Texas 76177; telephone (817) 222-5110; email [email protected]
FR Citation		80 FR 72390
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 72390 - Airworthiness Directives; Airbus Helicopters (Formerly Eurocopter France) Helicopters

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 223 (November 19, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration