Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) (Airbus Helicopters), 13526-13528 [2014-04729]
Download as PDF
<![CDATA[
13526
Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations
(e) Required Actions
Within 10 hours time-in-service, replace
the 3.2 mm rivets, part-number (P/N)
21215DC3200J, of the RH and LH
longitudinal beams Y350 of the bottom
structure with 4.8 mm rivets, P/N
21215DC4800J, as shown in Figures 2 and 3
of Eurocopter Emergency Alert Service
Bulletin No. 01.00.81, Revision 0, dated
March 19, 2012.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Gary Roach,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
gary.b.roach@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.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA)
Emergency AD No. 2012–0046–E, dated
March 21, 2012. You may view the EASA AD
on the Internet at www.regulations.gov in
Docket No. FAA–2013–0573.
mstockstill on DSK4VPTVN1PROD with RULES
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 5314: Fuselage Main, Keel.
16:00 Mar 10, 2014
Jkt 232001
Issued in Fort Worth, Texas, on February
26, 2014.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–04697 Filed 3–10–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0477; Directorate
Identifier 2011–SW–015–AD; Amendment
39–17780; AD 2014–05–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Type Certificate
Previously Held by Eurocopter France)
(Airbus Helicopters)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2010–11–
51 for Eurocopter France (Eurocopter)
Model AS350B, BA, B1, B2, C, D, and
D1 helicopters and Model AS355E, F,
F1, F2, and N helicopters with certain
part-numbered tail gearbox (TGB)
control levers installed. AD 2010–11–51
required repetitive visual inspections of
the TGB control lever for a crack and
replacing a cracked TGB control lever
with an airworthy TGB control lever.
This new AD retains the requirements of
AD 2010–11–51 and also requires
inspecting other areas of the TGB
control lever not previously inspected
and at additional inspection intervals.
This AD was prompted by several
reports of cracking in a TGB control
lever. The actions of this AD are
intended to prevent failure of the TGB
control lever, loss of tail rotor control,
and subsequent loss of control of the
helicopter.
SUMMARY:
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Emergency Alert Service
Bulletin No. 01.00.81, Revision 0, dated
March 19, 2012.
Note 1 to paragraph (i)(2): Eurocopter
Emergency Alert Service Bulletin No.
01.00.81, Revision 0, dated March 19, 2012,
is co-published as one document along with
Eurocopter Emergency Alert Service Bulletin
No. 01.00.46, Revision 0, dated March 19,
2012, which is not incorporated by reference
in this AD.
(ii) Reserved.
(3) For Eurocopter service information
identified in this AD, contact Airbus
Helicopters, Inc., 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone (972)
641–0000 or (800) 232–0323; fax (972) 641–
3775; or at https://
www.airbushelicopters.com/techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
VerDate Mar<15>2010
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
This AD is effective April 15,
2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 15, 2014.
ADDRESSES: For service information
identified in this AD, contact Airbus
DATES:
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
Helicopters, Inc., 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the European
Aviation Safety Agency (EASA) AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Robert Grant, Aviation Safety Engineer,
Rotorcraft Directorate, Safety
Management Group, 2601 Meacham
Blvd., Fort Worth, TX 76137, telephone
817–222–5110, email robert.grant@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010–11–51,
Amendment 39–16396 (75 FR 50874,
August 18, 2010). AD 2010–11–51
applied to Eurocopter Model AS350B,
BA, B1, B2, C, D, and D1 helicopters
and Model AS355E, F, F1, F2, and N
helicopters with certain part-numbered
tail gearbox (TGB) control levers
installed. The NPRM published in the
Federal Register on June 17, 2013 (78
FR 36129). The NPRM proposed to
retain the requirements in AD 2010–11–
51 to perform repetitive visual
inspections in a certain area on each
TGB control lever not marked with an
‘‘X’’ and to replace a cracked part. Also,
the NPRM proposed to require
inspecting another area of each TGB
control lever at additional intervals. The
NPRM also proposed replacing each
TGB control lever with a reworked TGB
control lever marked with an ‘‘X’’ near
the P/N or with a TGB control lever
with a P/N not listed in the applicability
of the AD. The proposed requirements
were intended to prevent failure of the
E:\FR\FM\11MRR1.SGM
11MRR1
Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations
TGB control lever, loss of tail rotor
control, and subsequent loss of control
of the helicopter.
The NPRM was prompted by
Emergency AD No. 2011–0038–E, dated
March 4, 2011 (AD No. 2011–0038–E),
issued by EASA, which is the Technical
Agent for the Member States of the
European Union, to correct an unsafe
condition for the Eurocopter Model
AS350B, BA, BB, B1, B2, and D, and
AS355E, F, F1, F2, and N helicopters.
Emergency AD No. 2011–0038–E
superseded EASA Emergency AD No.
2010–0082–E, dated April 27, 2010 (AD
No. 2010–0082–E). EASA advises that
since issuing its Emergency AD No.
2010–0082–E, Eurocopter found
additional cracks opposite the required
inspection area on the affected control
levers. EASA Emergency AD No. 2011–
0038–E retains the requirements of
EASA Emergency AD No. 2010–082–E
and adds repetitive inspections for the
area opposite the control levers.
Since we issued the NPRM,
Eurocopter France changed its name to
Airbus Helicopters. This AD reflects
that change and updates the contact
information to obtain service
documentation.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (78 FR 36129, June 17, 2013).
mstockstill on DSK4VPTVN1PROD with RULES
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed except for the name change
previously described and correcting the
date referenced for Revision 2 of the
Eurocopter Emergency Alert Service
Bulletin (EASB). These changes are
consistent with the intent of the
proposals in the NPRM (78 FR 36129,
June 17, 2013) and will not increase the
economic burden on any operator nor
increase the scope of the AD.
VerDate Mar<15>2010
16:00 Mar 10, 2014
Jkt 232001
Differences Between This AD and the
EASA AD
This AD differs from EASA
Emergency AD No. 2011–0038–E as
follows:
• We include the Model AS350C and
AS350D1 helicopters that may contain
the affected TGB control lever. We do
not include the Model AS350BB
helicopter because it is not typecertificated in the United States.
• We do not require an ‘‘after last
flight’’of the day inspection.
• We do not allow a pilot to inspect
for a crack.
• We do not require reworking
noninstalled control levers.
• We do not include a calendar
compliance time for reworking the TGB
control lever if there is not a crack.
• We do not require you to contact
Eurocopter (now Airbus Helicopters) if
a crack is found during any inspection.
Related Service Information
Eurocopter issued one EASB,
Revision 2, dated March 1, 2011, with
four different numbers. EASB No.
05.00.62 is for Model AS350
helicopters; EASB No. 05.00.57 is for
Model AS355 helicopters; EASB No.
05.00.38 is for military Model AS550
helicopters; and EASB No. 05.00.35 is
for military Model AS555 helicopters.
The military models are not typecertificated in the United States. The
EASB specifies visually inspecting the
TGB control lever for a crack at the last
flight of each day, without exceeding 10
flying hours between inspections. The
EASB also specifies a rework procedure
for affected TGB control levers, to be
done within 660 flying hours and no
later than June 30, 2011, indicated by
marking the control lever with a letter
‘‘X.’’ EASA classified this EASB as
mandatory and issued AD No. 2011–
0038–E to ensure the continued
airworthiness of these helicopters.
Costs of Compliance
We estimate that this AD will affect
791 helicopters of U.S. registry. We
estimate that operators may incur the
following costs in order to comply with
this AD. The inspections for a crack in
the TGB control lever will take a
minimal amount of time. Replacing a
control lever will take about 3 work
hours at an average labor rate of $85 per
work hour. Required parts will cost
about $2,103 per helicopter. Based on
these figures, we estimate the total cost
of the AD on U.S. operators to be $2,358
per helicopter to replace the control
lever.
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
13527
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
helicopters identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
E:\FR\FM\11MRR1.SGM
11MRR1
13528
Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2010–11–51, Amendment 39–16396 (75
FR 50874, August 18, 2010), and adding
the following new AD:
■
2014–05–07 Airbus Helicopters (Type
Certificate Previously Held by
Eurocopter France): Amendment 39–
17780; FAA–2013–0477; Directorate
Identifier 2011–SW–015–AD.
(a) Applicability
This AD applies to Model AS350B, BA, B1,
B2, C, D, and D1 helicopters and Model
AS355E, F, F1, F2, and N helicopters, with
a tail gearbox (TGB) control lever, part
number (P/N) 350A33–1058–00, P/N
350A33–1058–01, P/N 350A33–1058–02, or
P/N 350A33–1058–03, both with and without
an ‘‘X’’ marked near the P/N, installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the TGB control lever. This
condition could result in failure of the TGB
control lever, loss of tail rotor control, and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2010–11–51,
Amendment 39–16396 (75 FR 50874, August
18, 2010).
(d) Effective Date
This AD becomes effective April 15, 2014.
mstockstill on DSK4VPTVN1PROD with RULES
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) For helicopters with a lever not marked
with an ‘‘X’’ near the P/N, within 10 hours
time-in-service (TIS), and thereafter at
intervals not to exceed 10 hours TIS, using
a mirror and appropriate light source,
visually inspect the TGB control lever for a
crack as shown in area ‘‘A’’ of Figure 2 of
Eurocopter Emergency Alert Service Bulletin
No. 05.00.62, Revision 2, dated March 1,
2011 (EASB No. 05.00.62), for Model AS350
helicopters, and Eurocopter Emergency Alert
Service Bulletin No. 05.00.57, Revision 2,
dated March 1, 2011 (EASB No. 05.00.57), for
Model AS355 helicopters. If there is a crack,
before further flight, replace each cracked
TGB control lever with a TGB control lever
with a P/N not listed in paragraph (a) of this
AD.
(2) For Model AS355N helicopters, within
110 hours TIS, or if the helicopter has
reached 100 or more hours TIS, within the
next 10 hours TIS, and thereafter at intervals
not to exceed 110 hours TIS, using a mirror
and appropriate light source, inspect each
TGB control lever for a crack as shown in
area ‘‘C’’ of Figure 8 of EASB No. 05.00.62
or EASB No. 05.00.57, as applicable to your
model helicopter.
VerDate Mar<15>2010
16:00 Mar 10, 2014
Jkt 232001
(3) Within 660 hours TIS, replace each
TGB control lever with a reworked TGB
control lever marked with an ‘‘X’’ near the P/
N or with a TGB control lever with a P/N not
listed in paragraph (a) of this AD.
(4) For all model helicopters except Model
AS355N, within 660 hours TIS, or if the
helicopter has reached 605 or more hours TIS
within the next 55 hours TIS, and thereafter
at intervals not to exceed 660 hours TIS,
using a mirror and appropriate light source,
inspect each TGB control lever for a crack as
shown in area ‘‘C’’ of Figure 8 of EASB No.
05.00.62 or EASB No. 05.00.57, as applicable
to your model helicopter.
(5) If there is a crack, before further flight,
replace each cracked TGB control lever with
a TGB control lever with a P/N not listed in
paragraph (a) of this AD.
(g) 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, FAA, Rotorcraft
Directorate, Safety Management Group, 2601
Meacham Blvd., Fort Worth, TX 76137,
telephone (817) 222–5110, email
robert.grant@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.
(h) Related Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA)
Emergency AD No. 2011–0038–E, dated
March 4, 2011, and superseded EASA
Emergency AD No. 2010–0082–E, dated April
27, 2010. You may view the EASA AD on the
Internet at https://www.regulations.gov in
Docket No. FAA–2013–0477.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6720 Tail Rotor Control System.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Emergency Alert Service
Bulletin (EASB), No. 05.00.62,
Revision 2, dated March 1, 2011.
(ii) Eurocopter EASB No. 05.00.57,
Revision 2, dated March 1, 2011.
Note 1 to paragraph (j)(2): Eurocopter
EASB No. 05.00.62, Revision 2, dated March
1, 2011, and Eurocopter EASB No. 05.00.57,
Revision 2, dated March 1, 2011, are copublished as one document along with
Eurocopter EASB No. 05.00.38, Revision 2,
dated March 1, 2011, and Eurocopter EASB
No. 05.00.35, Revision 2, dated March 1,
PO 00000
Frm 00032
Fmt 4700
Sfmt 4700
2011, which are not incorporated by
reference in this AD.
(3) For Eurocopter service information
identified in this AD, contact Airbus
Helicopters, Inc., 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone (972)
641–0000 or (800) 232–0323; fax (972) 641–
3775; or at https://
www.airbushelicopters.com/techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on February
26, 2014.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–04729 Filed 3–10–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0798; Directorate
Identifier 2013–NM–087–AD; Amendment
39–17796; AD 2014–05–23]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model BD–100–1A10
(Challenger 300) airplanes. This AD was
prompted by multiple reports of erratic
electrical status indications on the push
button annunciators and the engine
instrument and crew alerting system.
Certain of those reported incidents
resulted in the airplane experiencing a
momentary loss of electrical power and
loss of flight displays. This AD requires
modification of the direct current power
centers. We are issuing this AD to
prevent loss of electrical power, which
could result in the loss of flight displays
and reduced controllability of the
airplane.
DATES: This AD becomes effective April
15, 2014.
SUMMARY:
E:\FR\FM\11MRR1.SGM
11MRR1
]]>Agencies
[Federal Register Volume 79, Number 47 (Tuesday, March 11, 2014)]
[Rules and Regulations]
[Pages 13526-13528]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04729]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0477; Directorate Identifier 2011-SW-015-AD;
Amendment 39-17780; AD 2014-05-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France) (Airbus Helicopters)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directive (AD) 2010-11-51 for
Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, C, D, and D1
helicopters and Model AS355E, F, F1, F2, and N helicopters with certain
part-numbered tail gearbox (TGB) control levers installed. AD 2010-11-
51 required repetitive visual inspections of the TGB control lever for
a crack and replacing a cracked TGB control lever with an airworthy TGB
control lever. This new AD retains the requirements of AD 2010-11-51
and also requires inspecting other areas of the TGB control lever not
previously inspected and at additional inspection intervals. This AD
was prompted by several reports of cracking in a TGB control lever. The
actions of this AD are intended to prevent failure of the TGB control
lever, loss of tail rotor control, and subsequent loss of control of
the helicopter.
DATES: This AD is effective April 15, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 15,
2014.
ADDRESSES: For service information identified in this AD, contact
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
https://www.airbushelicopters.com/techpub. You may review the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the European Aviation Safety
Agency (EASA) AD, any incorporated-by-reference service information,
the economic evaluation, any comments received, and other information.
The street address for the Docket Operations Office (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations Office,
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety
Engineer, Rotorcraft Directorate, Safety Management Group, 2601 Meacham
Blvd., Fort Worth, TX 76137, telephone 817-222-5110, email
robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010-11-51, Amendment 39-16396 (75 FR 50874,
August 18, 2010). AD 2010-11-51 applied to Eurocopter Model AS350B, BA,
B1, B2, C, D, and D1 helicopters and Model AS355E, F, F1, F2, and N
helicopters with certain part-numbered tail gearbox (TGB) control
levers installed. The NPRM published in the Federal Register on June
17, 2013 (78 FR 36129). The NPRM proposed to retain the requirements in
AD 2010-11-51 to perform repetitive visual inspections in a certain
area on each TGB control lever not marked with an ``X'' and to replace
a cracked part. Also, the NPRM proposed to require inspecting another
area of each TGB control lever at additional intervals. The NPRM also
proposed replacing each TGB control lever with a reworked TGB control
lever marked with an ``X'' near the P/N or with a TGB control lever
with a P/N not listed in the applicability of the AD. The proposed
requirements were intended to prevent failure of the
[[Page 13527]]
TGB control lever, loss of tail rotor control, and subsequent loss of
control of the helicopter.
The NPRM was prompted by Emergency AD No. 2011-0038-E, dated March
4, 2011 (AD No. 2011-0038-E), issued by EASA, which is the Technical
Agent for the Member States of the European Union, to correct an unsafe
condition for the Eurocopter Model AS350B, BA, BB, B1, B2, and D, and
AS355E, F, F1, F2, and N helicopters. Emergency AD No. 2011-0038-E
superseded EASA Emergency AD No. 2010-0082-E, dated April 27, 2010 (AD
No. 2010-0082-E). EASA advises that since issuing its Emergency AD No.
2010-0082-E, Eurocopter found additional cracks opposite the required
inspection area on the affected control levers. EASA Emergency AD No.
2011-0038-E retains the requirements of EASA Emergency AD No. 2010-082-
E and adds repetitive inspections for the area opposite the control
levers.
Since we issued the NPRM, Eurocopter France changed its name to
Airbus Helicopters. This AD reflects that change and updates the
contact information to obtain service documentation.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 36129,
June 17, 2013).
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed except for the name change
previously described and correcting the date referenced for Revision 2
of the Eurocopter Emergency Alert Service Bulletin (EASB). These
changes are consistent with the intent of the proposals in the NPRM (78
FR 36129, June 17, 2013) and will not increase the economic burden on
any operator nor increase the scope of the AD.
Differences Between This AD and the EASA AD
This AD differs from EASA Emergency AD No. 2011-0038-E as follows:
We include the Model AS350C and AS350D1 helicopters that
may contain the affected TGB control lever. We do not include the Model
AS350BB helicopter because it is not type-certificated in the United
States.
We do not require an ``after last flight''of the day
inspection.
We do not allow a pilot to inspect for a crack.
We do not require reworking noninstalled control levers.
We do not include a calendar compliance time for reworking
the TGB control lever if there is not a crack.
We do not require you to contact Eurocopter (now Airbus
Helicopters) if a crack is found during any inspection.
Related Service Information
Eurocopter issued one EASB, Revision 2, dated March 1, 2011, with
four different numbers. EASB No. 05.00.62 is for Model AS350
helicopters; EASB No. 05.00.57 is for Model AS355 helicopters; EASB No.
05.00.38 is for military Model AS550 helicopters; and EASB No. 05.00.35
is for military Model AS555 helicopters. The military models are not
type-certificated in the United States. The EASB specifies visually
inspecting the TGB control lever for a crack at the last flight of each
day, without exceeding 10 flying hours between inspections. The EASB
also specifies a rework procedure for affected TGB control levers, to
be done within 660 flying hours and no later than June 30, 2011,
indicated by marking the control lever with a letter ``X.'' EASA
classified this EASB as mandatory and issued AD No. 2011-0038-E to
ensure the continued airworthiness of these helicopters.
Costs of Compliance
We estimate that this AD will affect 791 helicopters of U.S.
registry. We estimate that operators may incur the following costs in
order to comply with this AD. The inspections for a crack in the TGB
control lever will take a minimal amount of time. Replacing a control
lever will take about 3 work hours at an average labor rate of $85 per
work hour. Required parts will cost about $2,103 per helicopter. Based
on these figures, we estimate the total cost of the AD on U.S.
operators to be $2,358 per helicopter to replace the control lever.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
[[Page 13528]]
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)
2010-11-51, Amendment 39-16396 (75 FR 50874, August 18, 2010), and
adding the following new AD:
2014-05-07 Airbus Helicopters (Type Certificate Previously Held by
Eurocopter France): Amendment 39-17780; FAA-2013-0477; Directorate
Identifier 2011-SW-015-AD.
(a) Applicability
This AD applies to Model AS350B, BA, B1, B2, C, D, and D1
helicopters and Model AS355E, F, F1, F2, and N helicopters, with a
tail gearbox (TGB) control lever, part number (P/N) 350A33-1058-00,
P/N 350A33-1058-01, P/N 350A33-1058-02, or P/N 350A33-1058-03, both
with and without an ``X'' marked near the P/N, installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the TGB
control lever. This condition could result in failure of the TGB
control lever, loss of tail rotor control, and subsequent loss of
control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2010-11-51, Amendment 39-16396 (75 FR
50874, August 18, 2010).
(d) Effective Date
This AD becomes effective April 15, 2014.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) For helicopters with a lever not marked with an ``X'' near
the P/N, within 10 hours time-in-service (TIS), and thereafter at
intervals not to exceed 10 hours TIS, using a mirror and appropriate
light source, visually inspect the TGB control lever for a crack as
shown in area ``A'' of Figure 2 of Eurocopter Emergency Alert
Service Bulletin No. 05.00.62, Revision 2, dated March 1, 2011 (EASB
No. 05.00.62), for Model AS350 helicopters, and Eurocopter Emergency
Alert Service Bulletin No. 05.00.57, Revision 2, dated March 1, 2011
(EASB No. 05.00.57), for Model AS355 helicopters. If there is a
crack, before further flight, replace each cracked TGB control lever
with a TGB control lever with a P/N not listed in paragraph (a) of
this AD.
(2) For Model AS355N helicopters, within 110 hours TIS, or if
the helicopter has reached 100 or more hours TIS, within the next 10
hours TIS, and thereafter at intervals not to exceed 110 hours TIS,
using a mirror and appropriate light source, inspect each TGB
control lever for a crack as shown in area ``C'' of Figure 8 of EASB
No. 05.00.62 or EASB No. 05.00.57, as applicable to your model
helicopter.
(3) Within 660 hours TIS, replace each TGB control lever with a
reworked TGB control lever marked with an ``X'' near the P/N or with
a TGB control lever with a P/N not listed in paragraph (a) of this
AD.
(4) For all model helicopters except Model AS355N, within 660
hours TIS, or if the helicopter has reached 605 or more hours TIS
within the next 55 hours TIS, and thereafter at intervals not to
exceed 660 hours TIS, using a mirror and appropriate light source,
inspect each TGB control lever for a crack as shown in area ``C'' of
Figure 8 of EASB No. 05.00.62 or EASB No. 05.00.57, as applicable to
your model helicopter.
(5) If there is a crack, before further flight, replace each
cracked TGB control lever with a TGB control lever with a P/N not
listed in paragraph (a) of this AD.
(g) 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, FAA, Rotorcraft Directorate, Safety Management Group, 2601
Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222-5110, email
robert.grant@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.
(h) Related Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) Emergency AD No. 2011-0038-E, dated March 4, 2011, and
superseded EASA Emergency AD No. 2010-0082-E, dated April 27, 2010.
You may view the EASA AD on the Internet at https://www.regulations.gov in Docket No. FAA-2013-0477.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor
Control System.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Eurocopter Emergency Alert Service Bulletin (EASB), No.
05.00.62,
Revision 2, dated March 1, 2011.
(ii) Eurocopter EASB No. 05.00.57, Revision 2, dated March 1,
2011.
Note 1 to paragraph (j)(2): Eurocopter EASB No. 05.00.62,
Revision 2, dated March 1, 2011, and Eurocopter EASB No. 05.00.57,
Revision 2, dated March 1, 2011, are co-published as one document
along with Eurocopter EASB No. 05.00.38, Revision 2, dated March 1,
2011, and Eurocopter EASB No. 05.00.35, Revision 2, dated March 1,
2011, which are not incorporated by reference in this AD.
(3) For Eurocopter service information identified in this AD,
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972) 641-3775; or at https://www.airbushelicopters.com/techpub.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on February 26, 2014.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-04729 Filed 3-10-14; 8:45 am]
BILLING CODE 4910-13-P
