Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) (Airbus Helicopters), 17408-17416 [2014-06769]
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Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations
intensity deemed appropriate. Inspection
aids such as mirror, magnifying lenses, etc.,
may be necessary. Surface cleaning and
elaborate procedures may be required.
(i) Corrective Action for Cracks
If any crack is found during any inspection
required by paragraph (g) of this AD, before
further flight, do either action specified in
paragraph (i)(1) or (i)(2) of this AD.
Accomplishment of either action terminates
the requirements of paragraph (g) of this AD.
(1) Do a large repair, in accordance with
Part IV of the Accomplishment Instructions
of Boeing Service Bulletin 727–57–0112,
Revision 5, dated July 31, 1997.
(2) Do a preventive modification, in
accordance with Part V of the
Accomplishment Instructions of Boeing
Service Bulletin 727–57–0112, Revision 5,
dated July 31, 1997.
(j) Optional Terminating Action
Accomplishment of the actions specified in
either paragraph (j)(1) or (j)(2) of this AD
terminates the requirements of paragraphs (g)
and (i) of this AD.
(1) A large repair, in accordance with Part
IV of the Accomplishment Instructions of
Boeing Service Bulletin 727–57–0112,
Revision 5, dated July 31, 1997. Any crack
found must be repaired before further flight
using a method approved in accordance with
the procedures specified in paragraph (l) of
this AD.
(2) A preventive modification, in
accordance with Part V of the
Accomplishment Instructions of Boeing
Service Bulletin 727–57–0112, Revision 5,
dated July 31, 1997. Any crack found must
be repaired before further flight using a
method approved in accordance with the
procedures specified in paragraph (l) of this
AD.
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(k) Credit for Previous Actions
This paragraph provides credit for the
inspections, large repair, and modification
specified in this AD, if those actions were
performed before the effective date of this AD
using Boeing Service Bulletin 727–57–0112,
Revision 4, dated October 29, 1992.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (m) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
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Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(m) Related Information
For more information about this AD,
contact Chandraduth Ramdoss, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Blvd., Suite
100, Lakewood, CA 90712–4137, phone: 562–
627–5329; fax: 562–627–5210; email:
Chandraduth.Ramdoss@faa.gov.
(n) 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) Boeing Service Bulletin 727–57–0112,
Revision 5, dated July 31, 1997.
(ii) Reserved.
(3) For service information identified in
this 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.
(4) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on February
14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–06776 Filed 3–27–14; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0822; Directorate
Identifier 2013–SW–004–AD; Amendment
39–17783; AD 2014–05–10]
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) 2012–25–
04 for Eurocopter France Model
AS350B3 helicopters with a certain
modification (MOD) installed. AD 2012–
25–04 required installing two placards
and revising the Rotorcraft Flight
Manual (RFM). AD 2012–25–04 also
required certain checks and inspecting
and replacing, if necessary, all four
laminated half-bearings (bearings). This
new AD retains the previous AD
requirements, requires certain
modifications which would be
terminating action for the airspeed
limitations, and adds certain helicopter
models to the bearing inspection with a
different inspection interval. These
actions are intended to prevent
vibration due to a failed bearing, failure
of the tail rotor, and subsequent loss of
control of the helicopter.
DATES: This AD is effective May 2, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of May 2, 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.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov in Docket No.
FAA–2013–0822 or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the foreign
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authority’s AD, any incorporated-byreference information, the economic
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Robert Grant, Aviation Safety Engineer,
Safety Management Group, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
On September 23, 2013, at 78 FR
58256, the Federal Register published
our notice of proposed rulemaking
(NPRM), which proposed to amend 14
CFR part 39 by removing AD 2012–25–
04, Amendment 39–17285 (78 FR
24041, April 24, 2013) and adding an
AD that would apply to Eurocopter
France (now Airbus Helicopters) Model
AS350B, AS350BA, AS350B1,
AS350B2, AS350B3 (except AS350B3
helicopters with modification (MOD) 07
5606 installed), AS350C, AS350D,
AS350D1, AS355E, AS355F, AS355F1,
AS355F2, AS355N, and AS355NP
helicopters. For Model AS350B3
helicopters with MOD 07 5601 installed,
the NPRM proposed to require limiting
the velocity never exceed speed by
installing a placard and revising the
RFM, checking the bearings after each
flight for separation, a crack, or
extrusion, performing a one-time
inspection of the bearings, modifying
the chin weight support and replacing
any bearings with more than 5 hours
time-in-service (TIS), removing the
additional chin weights and installing
blanks, modifying the rotating pitchchange spider assembly, installing a
load compensator, and modifying the
electrical installation. After modifying
the helicopter, the NPRM proposed to
require removing the RFM limitations
and placards installed previously. For
Model AS350B, AS350BA, AS350B1,
AS350B2, AS350C, AS350D, AS350D1,
AS355E, AS355F, AS355F1, AS355F2,
AS355N, AS355NP helicopters, and
Model AS350B3 helicopters that do not
have MOD 07 5601 installed, the NPRM
also proposed to require checking the
bearings after the last flight of each day
and replacing the bearings if there is an
extrusion, a crack, or separation. The
proposed requirements were intended to
prevent vibration due to a failed
bearing, failure of the tail rotor, and
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subsequent loss of control of the
helicopter.
The NPRM was prompted by
Emergency AD No. 2012–0257–E, dated
December 5, 2012 (EAD 2012–0257–E)
issued by the European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Union. EASA EAD 2012–
0257–E advises of premature failures of
bearings on AS350B3 helicopters, and
states that the criticality of the bearing
failures should apply to all AS355 and
AS350 helicopters. As a result, EAD
2012–0257–E requires repetitive postflight checks of the bearings.
EASA then superseded EAD 2012–
0217–E with EASA AD No. 2013–0029,
dated February 8, 2013 (AD 2013–0029),
to correct an unsafe condition for
Eurocopter Model AS 350 B3
helicopters modified by MOD 07 5601,
except for helicopters modified by MOD
07 5606 in production. EASA advises
that MOD 07 5606 restores the tail rotor
dynamic load level to that on
helicopters before installation of MOD
07 5601 and eliminates the modified
loading conditions of bearings which
caused the intensified deterioration and
reported failures. For these reasons,
EASA AD 2013–0029 requires
incorporation of MOD 07 5606 as a
terminating action.
Since we issued the NPRM,
Eurocopter France has 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 58256, September 23,
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 helicopter of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed, except for the minor change
previously described and formatting
changes. These changes are consistent
with the intent of the proposals in the
NPRM (78 FR 58256, September 23,
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17409
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
The EASA AD requires removing the
placard and RFM changes with the true
airspeed limitation (TAS) and replacing
it with an indicated airspeed limitation.
Since AD 2012–25–04 did not include
the TAS limitation, this AD does not
require removing it.
Related Service Information
We reviewed Eurocopter Service
Bulletin (SB) No. AS350–01.00.66,
Revision 1, dated February 15, 2013 (SB
AS350–01.00.66), which describes
procedures for removing the additional
chin weights installed on the tail rotor,
installing a load compensator, and
modifying the electrical system
installation, to reduce the dynamic
loads on the tail rotor. Eurocopter refers
to the procedures in this SB as MOD 07
5606. SB AS350–01.00.66 only applies
to helicopters with MOD 07 5601
installed.
We reviewed one Eurocopter
Emergency Alert Service Bulletin
(EASB) with two numbers: No. 01.00.65
for the Model AS350B3 helicopters and
No. 01.00.24 for the non-FAA type
certificated Model AS550C3 helicopters
(EASB 01.00.65). EASB 01.00.65 is
Revision 3, dated February 4, 2013.
EASB 01.00.65 specifies installing a
placard on the instrument panel and
revising the RFM to limit airspeed to
100 knots IAS, revising the RFM to
include a procedure in case of in-flight
vibrations originating in the tail rotor
and an ‘‘engine health check,’’ checking
the bearings after each flight, and
performing a one-time inspection of the
bearings. EASB 01.00.65 does not apply
to helicopters with MOD 07 5606
installed.
We also reviewed one Eurocopter
EASB with four numbers: No 05.00.71
for Model AS350B, BA, BB, D, B1, B2,
B3, and the non-FAA type certificated
L1 helicopters; No. 05.00.63 for Model
AS355E, F, F1, F2, N, and NP
helicopters; No. 05.00.46 for the nonFAA type certificated Model AS550A2,
C2, C3, and U2 helicopters; and No.
05.00.42 for the non-FAA type
certificated Model AS555AF, AN, SN,
UF, and UN helicopters (EASB
05.00.71). EASB 05.00.71 is Revision 2,
dated December 19, 2012. EASB
05.00.71 specifies procedures for
checking the bearings for deterioration
or damage after the last flight of each
day. EASB 05.00.71 does not apply to
helicopters with MOD 07 5601 installed.
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We also reviewed Eurocopter SB No.
AS350–64.00.11, Revision 0, dated
December 19, 2012 (SB AS350–
64.00.11), which describes procedures
for modifying the tail rotor chin weight
support to prevent interference with the
bearings. The manufacturer refers to the
procedures in this SB as MOD 07 6604.
SB AS350–64.00.11 only applies to
helicopters with MOD 07 5601 installed.
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Costs of Compliance
We estimate that the pilot checks of
the bearings in this AD will affect 938
helicopters of U.S. Registry, and that 50
helicopters will be affected by the
remaining requirements. The cost for
the pilot checks is minimal.
We estimate that operators may incur
the following costs in order to comply
with this AD. At an average labor rate
of $85 per hour, installing a placard and
revising the RFM requires about .5
work-hour, for a cost per helicopter of
$43 and a total cost to U.S. operators of
$2,150. Disassembling and inspecting
the bearings requires about 6 workhours, for a cost per helicopter of $510
and a total cost to U.S. operators of
$25,500. Modifying the chin weight
support requires about 8 work-hours, for
a cost per helicopter of $680, and a total
cost to U.S. operators of $34,000.
Removing the additional chin weights
installed on the tail rotor, modifying the
rotating pitch-change spider assembly,
installing a load compensator, and
modifying the electrical system
installation requires about 200 workhours, and required parts will cost
$18,343, for a cost per helicopter of
$35,343, and a total cost to U.S.
operators of $1,767,150.
If necessary, replacing the bearings
installed on the aircraft requires about 6
work-hours, at an average labor rate of
$85, and required parts will cost $2,415,
for a cost per helicopter of $2,925.
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
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because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(b) Unsafe Condition
This AD defines the unsafe condition as
severe vibrations due to failure of laminated
half-bearings (bearings). This condition could
result in failure of the tail rotor and
subsequent loss of control of the helicopter.
(c) Affected AD
This AD supersedes AD No. 2012–25–04,
Amendment 39–17285 (78 FR 24041, April
24, 2013).
(d) Effective Date
This AD becomes effective May 2, 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 Action
(1) For Model AS350B3 helicopters with
MOD 07 5601 installed:
Note 1 to paragraph (f) of this AD: MOD
075601 is an integral part of a specific Model
AS350B3 configuration, commercially
identified as ‘‘AS350B3e’’ and is not fitted on
Model AS350B3 helicopters of other
configurations.
(i) Before further flight:
(A) Install a velocity never exceed (VNE)
placard that reads as follows on the
instrument panel in full view of the pilot and
co-pilot with 6-millimeter red letters on a
white background:
VNE LIMITED TO 100 KTS IAS.
(B) Replace the IAS limit versus the flight
altitude placard located inside the cabin on
the center post with the placard as depicted
in Figure 1 to paragraph (f) of this AD:
VNE
POWER ON
PART 39—AIRWORTHINESS
DIRECTIVES
Hp (ft)
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2012–25–04, Amendment 39–17285 (78
FR 24041, April 24, 2013), and adding
the following new (AD):
■
2014–05–10 Airbus Helicopters (Type
Certificate Previously Held By
Eurocopter France): Amendment 39–
17783; Docket No. FAA–2013–0822;
Directorate Identifier 2013–SW–004–AD.
(a) Applicability
This AD applies to Model AS350B,
AS350BA, AS350B1, AS350B2, AS350B3
(except AS350B3 helicopters with
modification (MOD) 07 5606 installed),
AS350C, AS350D, AS350D1, AS355E,
AS355F, AS355F1, AS355F2, AS355N, and
AS355NP helicopters, certificated in any
category.
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0 ................................................
2000 ..........................................
4000 ..........................................
6000 ..........................................
8000 ..........................................
10000 ........................................
12000 ........................................
14000 ........................................
16000 ........................................
18000 ........................................
20000 ........................................
22000 ........................................
IAS (kts)
100
97
94
91
88
85
82
79
76
73
70
67
Valid for VNE
POWER OFF
Figure 1 to paragraph (f)
(ii) Before further flight, revise the
Rotorcraft Flight Manual (RFM) by inserting
a copy of this AD into the RFM or by making
pen and ink changes as follows:
(A) Revise paragraph 2.3 of the RFM by
inserting the following:
VNE limited to 100 kts IAS.
(B) Revise paragraph 2.6 of the RFM by
inserting Figure 2 to paragraph (f) of this AD.
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VNE
POWER ON
Hp (ft)
IAS (kts)
0 ................................................
2000 ..........................................
4000 ..........................................
6000 ..........................................
8000 ..........................................
10000 ........................................
12000 ........................................
14000 ........................................
16000 ........................................
18000 ........................................
20000 ........................................
22000 ........................................
100
97
94
91
88
85
82
79
76
73
70
67
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Valid for VNE
POWER OFF
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Figure 2 to paragraph (f)
(C) Add the following as paragraph 3.3.3 to
the RFM:
3.3.3 IN–FLIGHT VIBRATIONS FELT IN
THE PEDALS
Symptom:
IN–FLIGHT VIBRATIONS FELT IN THE
PEDALS
1. CHECK PEDAL EFFECTIVENESS
2. SMOOTHLY REDUCE THE SPEED TO VY
3. AVOID SIDESLIP AS MUCH AS
POSSIBLE
LAND AS SOON AS POSSIBLE
(iii) Before further flight, and thereafter
after each flight, without exceeding 3 hours
time-in-service (TIS) between two checks,
visually check each bearing as follows:
(A) Position both tail rotor blades
horizontally.
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(B) Apply load (F) by hand, perpendicular
to the pressure face of one tail rotor blade (a),
as shown in Figure 3 to paragraph (f) of this
AD, taking care not to reach the extreme
position against the tail rotor hub. The load
will deflect the tail rotor blade towards the
tail boom.
(C) While maintaining the load, check all
the visible faces of the bearings (front and
side faces) in area B of DETAIL A of Figure
3 to paragraph (f) of this AD for separation
between the elastomer and metal parts, a
crack in the elastomer, or an extrusion (see
example in Figure 4 to paragraph (f) of this
AD). A flashlight may be used to enhance the
check.
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DETAIL A
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Figure 3 to paragraph (t)
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Figure 4 to paragraph (f)
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(D) Repeat paragraphs (f)(1)(iii)(A) through
(f)(1)(iii)(C) of this AD on the other tail rotor
blade.
(E) Apply load (G) by hand perpendicular
to the suction face of one tail rotor blade as
shown in Figure 5 to paragraph (f) of this AD.
The load will deflect the tail rotor blade away
from the tail boom.
II
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Figure 5 to paragraph (f)
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(vi) If there is a separation or a crack on
the pressure side bearing, measure the
separation or the crack. If the separation or
crack is greater than 5 millimeters (.196
inches) as indicated by dimension ‘‘L’’ in
Figure 6 to paragraph (f) of this AD, before
further flight, replace the four bearings with
airworthy bearings.
3.B.2.a., of Eurocopter SB No. AS350–
01.00.66, Revision 1, dated February 15, 2013
(SB AS350–01.00.66).
(C) Modify and re-identify the rotating
pitch-change spider assembly as described in
the Accomplishment Instructions, paragraph
3.B.2.b., of SB AS350–01.00.66.
(D) Install a load compensator as described
in the Accomplishment Instructions,
paragraph 3.B.3.b., of SB AS350–01.00.66.
(E) Modify the electrical installation as
described in the Accomplishment
Instructions, section 3.B.4., of SB AS350–
01.00.66.
Note 2 to paragraph (f) of this AD: The
manufacturer refers to the actions in
paragraphs (f)(1)(viii)(B) through (f)(1)(viii)(E)
of this AD as MOD 07 5606.
(ix) After modification of a helicopter as
required by paragraphs (f)(1)(viii)(A) through
(f)(1)(viii)(E) of this AD, the actions of
paragraph (f)(1)(iii) through (f)(1)(vii) of this
AD are no longer required and the operating
limitation placards and RFM procedures
required by paragraphs (f)(1)(i) through
(f)(1)(ii)(C) of this AD may be removed.
(2) For Model AS350B, AS350BA,
AS350B1, AS350B2, AS350C, AS350D,
AS350D1, AS355E, AS355F, AS355F1,
AS355F2, AS355N, AS355NP helicopters,
and Model AS350B3 helicopters that do not
have MOD 07 5601 installed:
(i) No later than after the last flight of the
day, and thereafter during each last flight of
the day check, without exceeding 10 hours
TIS between two checks, visually check each
bearing as described in paragraphs
(f)(1)(iii)(A) through (f)(1)(vi) of this AD.
(ii) If there is an extrusion on any bearing,
before further flight, replace the bearing with
an airworthy bearing.
(vii) No later than after the last flight of the
day, perform a one-time inspection by
removing the bearings and inspecting for a
separation, a crack, or an extrusion. This
inspection is not a daily inspection. If there
is a separation, crack, or extrusion, before
further flight, replace the four bearings with
airworthy bearings.
(viii) Within 130 hours TIS:
(A) Modify the chin weight support as
described in the Accomplishment
Instructions, paragraphs 3.B.2.a through
3.B.2.h, of Eurocopter Service Bulletin (SB)
No. AS350–64.00.11, Revision 0, dated
December 19, 2012.
(B) Remove the additional chin weights,
install blanks on the chin weights, replace
bearings with more than 5 hours TIS, and reidentify the blade assembly as described in
the Accomplishment Instructions, paragraph
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(pilot) holding at least a private pilot
certificate, and must be entered into the
aircraft records showing compliance with
this AD in accordance with 14 CFR §§ 43.9
(a)(1)–(4) and 14 CFR 91.417(a)(2)(v). The
record must be maintained as required by 14
CFR §§ 91.417, 121.380, or 135.439.
(v) If there is an extrusion on any bearing,
before further flight, replace the four bearings
with airworthy bearings.
BILLING CODE 4910–13–C
tkelley on DSK3SPTVN1PROD with RULES
(F) While maintaining the load, check
visible faces of Area C as shown in Figure 5
to paragraph (f) of this AD for any extrusion.
A flashlight may be used to enhance the
check.
(G) Repeat paragraphs (f)(1)(iii)(E) and
(f)(1)(iii)(F) of this AD on the other tail rotor
blade.
(iv) The actions required by paragraphs
(f)(1)(iii)(A) through (f)(1)(iii)(G) of this AD
may be performed by the owner/operator
17416
Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations
(iii) If there is a separation or a crack on
the bearing, measure the separation or the
crack. If the separation or crack is greater
than 5 mm (.196 inches) as indicated by
dimension ‘‘L’’ and greater than 2 mm (.078
inches) as indicated by dimension ‘‘P’’ in
Figure 3 of Eurocopter Emergency Alert
Service Bulletin (EASB) No. 05.00.71 or No.
05.00.63, both Revision 2 and both dated
December 19, 2012, as applicable to your
model helicopter, before further flight,
replace the bearing.
(g) Credit for Actions Previously Completed
Actions accomplished before the effective
date of this AD in accordance with
Emergency AD No. 2012–21–51, dated
October 19, 2012, or AD No. 2012–25–04,
Amendment 39–17285 (78 FR 24041, April
24, 2013) are considered acceptable for
compliance with the corresponding actions
of this AD.
(h) Special Flight Permits
Special flight permits are prohibited.
(i) 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, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222–
5328; 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.
tkelley on DSK3SPTVN1PROD with RULES
(j) Additional Information
(1) Eurocopter EASB No. 01.00.65 and No.
01.00.24, both Revision 3 and both dated
February 4, 2013, which are co-published as
one document and which are not
incorporated by reference, contain additional
information about the subject of this AD. For
this service information, 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 this service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in
European Aviation Safety Agency AD No.
2013–0029, dated February 8, 2013, which
can be found on the Internet at https://
www.regulations.gov in Docket number
2013–0822.
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 Service Bulletin No. AS350–
64.00.11, Revision 0, dated December 19,
2012.
(ii) Eurocopter Service Bulletin No. AS350–
01.00.66, Revision 1, dated February 15,
2013.
(iii) Eurocopter Emergency Alert Service
Bulletin No. 05.00.71, Revision 2, dated
December 19, 2012.
(iv) Eurocopter Emergency Alert Service
Bulletin No. 05.00.63, Revision 2, dated
December 19, 2012.
Note 3 to paragraph (l)(2): Eurocopter
Emergency Alert Service Bulletin No.
05.00.71, Revision 2, dated December 19,
2012, and Eurocopter Emergency Alert
Service Bulletin No. 05.00.63, Revision 2,
dated December 19, 2012, are co-published as
one document along with Eurocopter
Emergency Alert Service Bulletin No.
05.00.46, Revision 2, dated December 19,
2012, and Eurocopter Emergency Alert
Service Bulletin No. 05.00.42, Revision 2,
dated December 19, 2012, 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
20, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–06769 Filed 3–27–14; 8:45 am]
BILLING CODE 4910–13–P
(k) Subject
Joint Aircraft Service Component (JASC)
Code: 6400: Tail Rotor.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1253; Directorate
Identifier 2011–NM–079–AD; Amendment
39–17723; AD 2013–26–14]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2008–08–
04 for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2008–08–04 required repetitive
inspections for cracking in the forward
lug of the support rib 5 fitting of the left
and right main landing gear (MLG), and
repair or replacement of any cracked
MLG fitting if necessary. AD 2008–08–
04 also required modification of the rib
bushings of the left and right MLG,
which ended the repetitive inspections.
This new AD requires, for airplanes on
which certain modifications or repairs
have been done, repetitive inspections
for cracks of the forward lug of each lefthand and right-hand MLG support rib 5
fitting, and repair if necessary; and adds
Model A318 series airplanes to the
applicability. Replacement of an MLG
support rib 5 fitting terminates the
repetitive inspection requirements for
the MLG support rib 5 fitting at that
position. This AD was prompted by
reports of cracks found in the forward
lug of the MLG support rib 5 fitting. We
are issuing this AD to prevent cracking
in the forward lug of the MLG, which
could result in failure of the lug and
consequent collapse of the MLG during
takeoff or landing.
DATES: This AD becomes effective May
2, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 2, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of May 19, 2008 (73 FR
19975, April 14, 2008).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2011-1253; or in
person at the U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
SUMMARY:
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[Federal Register Volume 79, Number 60 (Friday, March 28, 2014)]
[Rules and Regulations]
[Pages 17408-17416]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06769]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0822; Directorate Identifier 2013-SW-004-AD;
Amendment 39-17783; AD 2014-05-10]
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) 2012-25-04 for
Eurocopter France Model AS350B3 helicopters with a certain modification
(MOD) installed. AD 2012-25-04 required installing two placards and
revising the Rotorcraft Flight Manual (RFM). AD 2012-25-04 also
required certain checks and inspecting and replacing, if necessary, all
four laminated half-bearings (bearings). This new AD retains the
previous AD requirements, requires certain modifications which would be
terminating action for the airspeed limitations, and adds certain
helicopter models to the bearing inspection with a different inspection
interval. These actions are intended to prevent vibration due to a
failed bearing, failure of the tail rotor, and subsequent loss of
control of the helicopter.
DATES: This AD is effective May 2, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of May 2, 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 in Docket No. FAA-2013-0822 or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this AD, the
foreign
[[Page 17409]]
authority's AD, any incorporated-by-reference information, the economic
evaluation, any comments received, and other information. The address
for the Docket Office (phone: 800-647-5527) is Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On September 23, 2013, at 78 FR 58256, the Federal Register
published our notice of proposed rulemaking (NPRM), which proposed to
amend 14 CFR part 39 by removing AD 2012-25-04, Amendment 39-17285 (78
FR 24041, April 24, 2013) and adding an AD that would apply to
Eurocopter France (now Airbus Helicopters) Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3 (except AS350B3 helicopters with modification
(MOD) 07 5606 installed), AS350C, AS350D, AS350D1, AS355E, AS355F,
AS355F1, AS355F2, AS355N, and AS355NP helicopters. For Model AS350B3
helicopters with MOD 07 5601 installed, the NPRM proposed to require
limiting the velocity never exceed speed by installing a placard and
revising the RFM, checking the bearings after each flight for
separation, a crack, or extrusion, performing a one-time inspection of
the bearings, modifying the chin weight support and replacing any
bearings with more than 5 hours time-in-service (TIS), removing the
additional chin weights and installing blanks, modifying the rotating
pitch-change spider assembly, installing a load compensator, and
modifying the electrical installation. After modifying the helicopter,
the NPRM proposed to require removing the RFM limitations and placards
installed previously. For Model AS350B, AS350BA, AS350B1, AS350B2,
AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N,
AS355NP helicopters, and Model AS350B3 helicopters that do not have MOD
07 5601 installed, the NPRM also proposed to require checking the
bearings after the last flight of each day and replacing the bearings
if there is an extrusion, a crack, or separation. The proposed
requirements were intended to prevent vibration due to a failed
bearing, failure of the tail rotor, and subsequent loss of control of
the helicopter.
The NPRM was prompted by Emergency AD No. 2012-0257-E, dated
December 5, 2012 (EAD 2012-0257-E) issued by the European Aviation
Safety Agency (EASA), which is the Technical Agent for the Member
States of the European Union. EASA EAD 2012-0257-E advises of premature
failures of bearings on AS350B3 helicopters, and states that the
criticality of the bearing failures should apply to all AS355 and AS350
helicopters. As a result, EAD 2012-0257-E requires repetitive post-
flight checks of the bearings.
EASA then superseded EAD 2012-0217-E with EASA AD No. 2013-0029,
dated February 8, 2013 (AD 2013-0029), to correct an unsafe condition
for Eurocopter Model AS 350 B3 helicopters modified by MOD 07 5601,
except for helicopters modified by MOD 07 5606 in production. EASA
advises that MOD 07 5606 restores the tail rotor dynamic load level to
that on helicopters before installation of MOD 07 5601 and eliminates
the modified loading conditions of bearings which caused the
intensified deterioration and reported failures. For these reasons,
EASA AD 2013-0029 requires incorporation of MOD 07 5606 as a
terminating action.
Since we issued the NPRM, Eurocopter France has 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 58256,
September 23, 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 helicopter of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed, except for the minor change
previously described and formatting changes. These changes are
consistent with the intent of the proposals in the NPRM (78 FR 58256,
September 23, 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
The EASA AD requires removing the placard and RFM changes with the
true airspeed limitation (TAS) and replacing it with an indicated
airspeed limitation. Since AD 2012-25-04 did not include the TAS
limitation, this AD does not require removing it.
Related Service Information
We reviewed Eurocopter Service Bulletin (SB) No. AS350-01.00.66,
Revision 1, dated February 15, 2013 (SB AS350-01.00.66), which
describes procedures for removing the additional chin weights installed
on the tail rotor, installing a load compensator, and modifying the
electrical system installation, to reduce the dynamic loads on the tail
rotor. Eurocopter refers to the procedures in this SB as MOD 07 5606.
SB AS350-01.00.66 only applies to helicopters with MOD 07 5601
installed.
We reviewed one Eurocopter Emergency Alert Service Bulletin (EASB)
with two numbers: No. 01.00.65 for the Model AS350B3 helicopters and
No. 01.00.24 for the non-FAA type certificated Model AS550C3
helicopters (EASB 01.00.65). EASB 01.00.65 is Revision 3, dated
February 4, 2013. EASB 01.00.65 specifies installing a placard on the
instrument panel and revising the RFM to limit airspeed to 100 knots
IAS, revising the RFM to include a procedure in case of in-flight
vibrations originating in the tail rotor and an ``engine health
check,'' checking the bearings after each flight, and performing a one-
time inspection of the bearings. EASB 01.00.65 does not apply to
helicopters with MOD 07 5606 installed.
We also reviewed one Eurocopter EASB with four numbers: No 05.00.71
for Model AS350B, BA, BB, D, B1, B2, B3, and the non-FAA type
certificated L1 helicopters; No. 05.00.63 for Model AS355E, F, F1, F2,
N, and NP helicopters; No. 05.00.46 for the non-FAA type certificated
Model AS550A2, C2, C3, and U2 helicopters; and No. 05.00.42 for the
non-FAA type certificated Model AS555AF, AN, SN, UF, and UN helicopters
(EASB 05.00.71). EASB 05.00.71 is Revision 2, dated December 19, 2012.
EASB 05.00.71 specifies procedures for checking the bearings for
deterioration or damage after the last flight of each day. EASB
05.00.71 does not apply to helicopters with MOD 07 5601 installed.
[[Page 17410]]
We also reviewed Eurocopter SB No. AS350-64.00.11, Revision 0,
dated December 19, 2012 (SB AS350-64.00.11), which describes procedures
for modifying the tail rotor chin weight support to prevent
interference with the bearings. The manufacturer refers to the
procedures in this SB as MOD 07 6604. SB AS350-64.00.11 only applies to
helicopters with MOD 07 5601 installed.
Costs of Compliance
We estimate that the pilot checks of the bearings in this AD will
affect 938 helicopters of U.S. Registry, and that 50 helicopters will
be affected by the remaining requirements. The cost for the pilot
checks is minimal.
We estimate that operators may incur the following costs in order
to comply with this AD. At an average labor rate of $85 per hour,
installing a placard and revising the RFM requires about .5 work-hour,
for a cost per helicopter of $43 and a total cost to U.S. operators of
$2,150. Disassembling and inspecting the bearings requires about 6
work-hours, for a cost per helicopter of $510 and a total cost to U.S.
operators of $25,500. Modifying the chin weight support requires about
8 work-hours, for a cost per helicopter of $680, and a total cost to
U.S. operators of $34,000. Removing the additional chin weights
installed on the tail rotor, modifying the rotating pitch-change spider
assembly, installing a load compensator, and modifying the electrical
system installation requires about 200 work-hours, and required parts
will cost $18,343, for a cost per helicopter of $35,343, and a total
cost to U.S. operators of $1,767,150.
If necessary, replacing the bearings installed on the aircraft
requires about 6 work-hours, at an average labor rate of $85, and
required parts will cost $2,415, for a cost per helicopter of $2,925.
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 have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2012-25-04, Amendment 39-17285 (78 FR 24041, April 24, 2013), and
adding the following new (AD):
2014-05-10 Airbus Helicopters (Type Certificate Previously Held By
Eurocopter France): Amendment 39-17783; Docket No. FAA-2013-0822;
Directorate Identifier 2013-SW-004-AD.
(a) Applicability
This AD applies to Model AS350B, AS350BA, AS350B1, AS350B2,
AS350B3 (except AS350B3 helicopters with modification (MOD) 07 5606
installed), AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1,
AS355F2, AS355N, and AS355NP helicopters, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as severe vibrations due to
failure of laminated half-bearings (bearings). This condition could
result in failure of the tail rotor and subsequent loss of control
of the helicopter.
(c) Affected AD
This AD supersedes AD No. 2012-25-04, Amendment 39-17285 (78 FR
24041, April 24, 2013).
(d) Effective Date
This AD becomes effective May 2, 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 Action
(1) For Model AS350B3 helicopters with MOD 07 5601 installed:
Note 1 to paragraph (f) of this AD: MOD 075601 is an integral
part of a specific Model AS350B3 configuration, commercially
identified as ``AS350B3e'' and is not fitted on Model AS350B3
helicopters of other configurations.
(i) Before further flight:
(A) Install a velocity never exceed (VNE) placard
that reads as follows on the instrument panel in full view of the
pilot and co-pilot with 6-millimeter red letters on a white
background:
VNE LIMITED TO 100 KTS IAS.
(B) Replace the IAS limit versus the flight altitude placard
located inside the cabin on the center post with the placard as
depicted in Figure 1 to paragraph (f) of this AD:
------------------------------------------------------------------------
------------------------------------------------------------------------
VNE
POWER ON
------------------------------------------------------------------------
Hp (ft) IAS (kts)
------------------------------------------------------------------------
0.......................................................... 100
2000....................................................... 97
4000....................................................... 94
6000....................................................... 91
8000....................................................... 88
10000...................................................... 85
12000...................................................... 82
14000...................................................... 79
16000...................................................... 76
18000...................................................... 73
20000...................................................... 70
22000...................................................... 67
------------------------------------------------------------------------
Valid for VNE
POWER OFF
------------------------------------------------------------------------
Figure 1 to paragraph (f)
(ii) Before further flight, revise the Rotorcraft Flight Manual
(RFM) by inserting a copy of this AD into the RFM or by making pen
and ink changes as follows:
(A) Revise paragraph 2.3 of the RFM by inserting the following:
VNE limited to 100 kts IAS.
(B) Revise paragraph 2.6 of the RFM by inserting Figure 2 to
paragraph (f) of this AD.
[[Page 17411]]
------------------------------------------------------------------------
------------------------------------------------------------------------
VNE
POWER ON
------------------------------------------------------------------------
Hp (ft) IAS (kts)
------------------------------------------------------------------------
0.......................................................... 100
2000....................................................... 97
4000....................................................... 94
6000....................................................... 91
8000....................................................... 88
10000...................................................... 85
12000...................................................... 82
14000...................................................... 79
16000...................................................... 76
18000...................................................... 73
20000...................................................... 70
22000...................................................... 67
------------------------------------------------------------------------
Valid for VNE
POWER OFF
------------------------------------------------------------------------
Figure 2 to paragraph (f)
(C) Add the following as paragraph 3.3.3 to the RFM:
3.3.3 IN-FLIGHT VIBRATIONS FELT IN THE PEDALS
Symptom:
IN-FLIGHT VIBRATIONS FELT IN THE PEDALS
1. CHECK PEDAL EFFECTIVENESS
2. SMOOTHLY REDUCE THE SPEED TO VY
3. AVOID SIDESLIP AS MUCH AS POSSIBLE
LAND AS SOON AS POSSIBLE
(iii) Before further flight, and thereafter after each flight,
without exceeding 3 hours time-in-service (TIS) between two checks,
visually check each bearing as follows:
(A) Position both tail rotor blades horizontally.
(B) Apply load (F) by hand, perpendicular to the pressure face
of one tail rotor blade (a), as shown in Figure 3 to paragraph (f)
of this AD, taking care not to reach the extreme position against
the tail rotor hub. The load will deflect the tail rotor blade
towards the tail boom.
(C) While maintaining the load, check all the visible faces of
the bearings (front and side faces) in area B of DETAIL A of Figure
3 to paragraph (f) of this AD for separation between the elastomer
and metal parts, a crack in the elastomer, or an extrusion (see
example in Figure 4 to paragraph (f) of this AD). A flashlight may
be used to enhance the check.
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[[Page 17414]]
(D) Repeat paragraphs (f)(1)(iii)(A) through (f)(1)(iii)(C) of
this AD on the other tail rotor blade.
(E) Apply load (G) by hand perpendicular to the suction face of
one tail rotor blade as shown in Figure 5 to paragraph (f) of this
AD. The load will deflect the tail rotor blade away from the tail
boom.
[GRAPHIC] [TIFF OMITTED] TR28MR14.038
[[Page 17415]]
(F) While maintaining the load, check visible faces of Area C as
shown in Figure 5 to paragraph (f) of this AD for any extrusion. A
flashlight may be used to enhance the check.
(G) Repeat paragraphs (f)(1)(iii)(E) and (f)(1)(iii)(F) of this
AD on the other tail rotor blade.
(iv) The actions required by paragraphs (f)(1)(iii)(A) through
(f)(1)(iii)(G) of this AD may be performed by the owner/operator
(pilot) holding at least a private pilot certificate, and must be
entered into the aircraft records showing compliance with this AD in
accordance with 14 CFR Sec. Sec. 43.9 (a)(1)-(4) and 14 CFR
91.417(a)(2)(v). The record must be maintained as required by 14 CFR
Sec. Sec. 91.417, 121.380, or 135.439.
(v) If there is an extrusion on any bearing, before further
flight, replace the four bearings with airworthy bearings.
(vi) If there is a separation or a crack on the pressure side
bearing, measure the separation or the crack. If the separation or
crack is greater than 5 millimeters (.196 inches) as indicated by
dimension ``L'' in Figure 6 to paragraph (f) of this AD, before
further flight, replace the four bearings with airworthy bearings.
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(vii) No later than after the last flight of the day, perform a
one-time inspection by removing the bearings and inspecting for a
separation, a crack, or an extrusion. This inspection is not a daily
inspection. If there is a separation, crack, or extrusion, before
further flight, replace the four bearings with airworthy bearings.
(viii) Within 130 hours TIS:
(A) Modify the chin weight support as described in the
Accomplishment Instructions, paragraphs 3.B.2.a through 3.B.2.h, of
Eurocopter Service Bulletin (SB) No. AS350-64.00.11, Revision 0,
dated December 19, 2012.
(B) Remove the additional chin weights, install blanks on the
chin weights, replace bearings with more than 5 hours TIS, and re-
identify the blade assembly as described in the Accomplishment
Instructions, paragraph 3.B.2.a., of Eurocopter SB No. AS350-
01.00.66, Revision 1, dated February 15, 2013 (SB AS350-01.00.66).
(C) Modify and re-identify the rotating pitch-change spider
assembly as described in the Accomplishment Instructions, paragraph
3.B.2.b., of SB AS350-01.00.66.
(D) Install a load compensator as described in the
Accomplishment Instructions, paragraph 3.B.3.b., of SB AS350-
01.00.66.
(E) Modify the electrical installation as described in the
Accomplishment Instructions, section 3.B.4., of SB AS350-01.00.66.
Note 2 to paragraph (f) of this AD: The manufacturer refers to
the actions in paragraphs (f)(1)(viii)(B) through (f)(1)(viii)(E) of
this AD as MOD 07 5606.
(ix) After modification of a helicopter as required by
paragraphs (f)(1)(viii)(A) through (f)(1)(viii)(E) of this AD, the
actions of paragraph (f)(1)(iii) through (f)(1)(vii) of this AD are
no longer required and the operating limitation placards and RFM
procedures required by paragraphs (f)(1)(i) through (f)(1)(ii)(C) of
this AD may be removed.
(2) For Model AS350B, AS350BA, AS350B1, AS350B2, AS350C, AS350D,
AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS355NP
helicopters, and Model AS350B3 helicopters that do not have MOD 07
5601 installed:
(i) No later than after the last flight of the day, and
thereafter during each last flight of the day check, without
exceeding 10 hours TIS between two checks, visually check each
bearing as described in paragraphs (f)(1)(iii)(A) through (f)(1)(vi)
of this AD.
(ii) If there is an extrusion on any bearing, before further
flight, replace the bearing with an airworthy bearing.
[[Page 17416]]
(iii) If there is a separation or a crack on the bearing,
measure the separation or the crack. If the separation or crack is
greater than 5 mm (.196 inches) as indicated by dimension ``L'' and
greater than 2 mm (.078 inches) as indicated by dimension ``P'' in
Figure 3 of Eurocopter Emergency Alert Service Bulletin (EASB) No.
05.00.71 or No. 05.00.63, both Revision 2 and both dated December
19, 2012, as applicable to your model helicopter, before further
flight, replace the bearing.
(g) Credit for Actions Previously Completed
Actions accomplished before the effective date of this AD in
accordance with Emergency AD No. 2012-21-51, dated October 19, 2012,
or AD No. 2012-25-04, Amendment 39-17285 (78 FR 24041, April 24,
2013) are considered acceptable for compliance with the
corresponding actions of this AD.
(h) Special Flight Permits
Special flight permits are prohibited.
(i) 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, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222-5328; 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.
(j) Additional Information
(1) Eurocopter EASB No. 01.00.65 and No. 01.00.24, both Revision
3 and both dated February 4, 2013, which are co-published as one
document and which are not incorporated by reference, contain
additional information about the subject of this AD. For this
service information, 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 this service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in European Aviation
Safety Agency AD No. 2013-0029, dated February 8, 2013, which can be
found on the Internet at https://www.regulations.gov in Docket number
2013-0822.
(k) Subject
Joint Aircraft Service Component (JASC) Code: 6400: Tail Rotor.
(l) 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 Service Bulletin No. AS350-64.00.11, Revision 0,
dated December 19, 2012.
(ii) Eurocopter Service Bulletin No. AS350-01.00.66, Revision 1,
dated February 15, 2013.
(iii) Eurocopter Emergency Alert Service Bulletin No. 05.00.71,
Revision 2, dated December 19, 2012.
(iv) Eurocopter Emergency Alert Service Bulletin No. 05.00.63,
Revision 2, dated December 19, 2012.
Note 3 to paragraph (l)(2): Eurocopter Emergency Alert Service
Bulletin No. 05.00.71, Revision 2, dated December 19, 2012, and
Eurocopter Emergency Alert Service Bulletin No. 05.00.63, Revision
2, dated December 19, 2012, are co-published as one document along
with Eurocopter Emergency Alert Service Bulletin No. 05.00.46,
Revision 2, dated December 19, 2012, and Eurocopter Emergency Alert
Service Bulletin No. 05.00.42, Revision 2, dated December 19, 2012,
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 20, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-06769 Filed 3-27-14; 8:45 am]
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