
[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]


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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)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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 
http://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 http://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 17412]]

[GRAPHIC] [TIFF OMITTED] TR28MR14.036


[[Page 17413]]


[GRAPHIC] [TIFF OMITTED] TR28MR14.037


[[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.
[GRAPHIC] [TIFF OMITTED] TR28MR14.039

BILLING CODE 4910-13-C
    (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 http://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 http://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 http://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: http://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]
BILLING CODE 4910-13-P


