Document ID: FAA-2013-0822-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Eurocopter France Helicopters
Posted Date: 2013-09-23T04:00Z

[Federal Register Volume 78, Number 184 (Monday, September 23, 2013)]
[Proposed Rules]
[Pages 58256-58264]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23102]

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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]
RIN 2120-AA64

Airworthiness Directives; Eurocopter France Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) for Eurocopter France (Eurocopter) Model AS350B3 helicopters with 
a certain modification (MOD) installed. The existing AD currently 
requires installing two placards and revising the Rotorcraft Flight 
Manual (RFM). The AD also requires certain checks and inspecting and 
replacing, if necessary, all four laminated half-bearings (bearings). 
Since we issued that AD, we have determined that the unsafe condition 
applies to additional model helicopters, and that a recently developed 
Eurocopter modification should be a required terminating action for the 
repetitive checks required by the AD. This proposed AD would retain the 
existing AD requirements, require certain modifications which would be 
terminating action for the airspeed limitations, and would add certain 
helicopter models to the bearing inspection with a different inspection 
interval. The proposed 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: We must receive comments on this proposed AD by November 22, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the foreign 
authority's AD, the economic evaluation, any comments received and 
other information. The street address for the Docket Operations Office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed AD, contact 
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.eurocopter.com/techpub. You may review service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

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:

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will

[[Page 58257]]

consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    On April 24, 2013, we issued AD 2012-25-04, Amendment 39-17285 (78 
FR 24041) for Eurocopter Model AS350B3 helicopters with MOD 07 5601 
installed. AD 2012-25-04 requires, before further flight, installing 
two placards on the instrument panel and revising the RFM to reduce the 
Velocity Never Exceed (VNE) indicated airspeed (IAS) 
limitation. It also requires, before further flight and thereafter 
after each flight, visually checking all visible faces of the pressure 
side of the bearings for separation, a crack, or an extrusion, and 
replacing the four bearings if there is an extrusion or if there is a 
separation or a crack greater than 5 millimeters (.196 inches). AD 
2012-25-04 also requires checking the suction side of the bearings for 
extrusions and replacing all four bearings if an extrusion is present. 
Lastly, AD 2012-25-04 requires performing a one-time disassembly and 
inspection of the bearings for a separation, a crack, or an extrusion, 
and replacing the four bearings if there is a separation, crack, or 
extrusion. AD 2012-25-04 superseded Emergency AD (EAD) No. 2012-21-51, 
dated October 17, 2012 (EAD 2012-21-51), which had the same 
requirements but which only applied to helicopters with certain part-
numbered half-bearings and tail rotor blades.
    AD 2012-25-04 and EAD 2012-21-51 were prompted by Emergency AD No. 
2012-0207-E, dated October 5, 2012 (EAD 2012-0207-E), and Emergency AD 
No. 2012-0217-E, dated October 19, 2012 (EAD 2012-0217-E), issued by 
the European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union. EASA advised of 
premature failures of the bearings, three cases of vibrations 
originating from the tail rotor due to premature failure of the 
bearings installed with certain tail rotor blades, and an accident. EAD 
2012-0217-E supersedes EAD 2012-0207-E to correct an inconsistency 
where the new airspeed limitation defined in the placards and the RFM 
were stated in both true airspeed (TAS) and indicated airspeed (IAS). 
EAD 2012-0217-E retains some of the requirements of EAD 2012-0207-E, 
removes the airspeed limitations defined in TAS, and requires inserting 
a temporary engine health check procedure into the RFM. The actions 
required by AD 2012-25-04 and EAD 2012-21-51 are intended to prevent 
vibration due to a failed bearing, failure of the T/R, and subsequent 
loss of control of the helicopter.

Actions Since Existing AD Was Issued

    After we issued EAD No. 2012-21-51, dated October 17, 2012, EASA 
issued EAD No. 2012-0257-E, dated December 5, 2012 (EAD 2012-0257-E), 
for Model AS350B, AS350BA, AS350BB, AS350B1, AS350B2, AS350B3 without 
Modification (MOD) 07 5601, AS350D, AS355E, AS355F, AS355F1, AS355F2, 
AS355N, and AS355NP helicopters. EAD 2012-0257-E describes the previous 
issues with the bearings on the AS350B3 helicopters, and states that 
the criticality of the bearing failures should apply to all AS355 and 
AS350 helicopters, although service experience has not demonstrated 
premature deterioration of the bearings on these model helicopters. EAD 
2012-0257-E requires repetitive post-flight checks of the bearings, 
similar to the checks required by EAD 2012-0217-E.
    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 Eurocopter has designed MOD 07 5606, which 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.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other helicopters of the same type design.

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.
    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. Eurocopter 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.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2012-25-04, 
Amendment 39-17285 (78 FR 24041, April 24, 2013). Additionally, this 
proposed AD would require, for AS350B3 helicopters with MOD 07 5601 
installed:

[[Page 58258]]

     Modifying the chin weight support and replacing any 
bearings with more than 5 hours time-in-service (TIS) by following the 
procedures specified in SB AS350-64.00.11;
     Following certain procedures specified in SB AS350-
01.00.66 for 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, removing the RFM 
limitations and placards required to be installed by AD 2012-25-04, 
Amendment 39-17285 (78 FR 24041, April 24, 2013). Modifying the 
helicopter would be terminating action for the repetitive checks and 
inspections.
    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 proposed AD would also require:
     After the last flight of each day, without exceeding 10 
hours TIS between two checks, checking the bearings for separation or a 
crack. These checks may be performed by the owner/operator (pilot) 
holding at least a private pilot certificate as it only requires a 
visual check of the bearings. This authorization is an exception to our 
standard maintenance regulations and must be entered into the aircraft 
records showing compliance with the proposed AD; and
     If there is separation or a crack over a specific size, 
replacing the bearings before further flight.

Differences Between the Proposed AD and the EASA ADs

    The EASA AD requires removing the placard and RFM changes with the 
TAS limitation and replacing it with an IAS limitation. Since the FAA 
EAD did not include the TAS limitation, this proposed AD would not 
require removing it. This proposed AD would not require inserting the 
temporary engine health check procedure in the RFM.

Costs of Compliance

    We estimate that the pilot checks of the bearings in the proposed 
AD would affect 938 helicopters of U.S. Registry, and that 50 
helicopters would 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 will require 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 will 
require 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 will require 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 will require 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 will 
require 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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed, I certify this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2012-25-04, Amendment 39-17285 (78 FR 24041, April 24, 2013), and 
adding the following new (AD):

Eurocopter France: 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 ADs

    This AD supersedes AD No. 2012-25-04, Amendment 39-17285 (78 FR 
24041, April 24, 2013).

(d) Comments Due Date

    We must receive comments by November 22, 2013.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the

[[Page 58259]]

specified compliance time unless it has already been accomplished 
prior to that time.

(f) Required Actions

    (1) For Model AS350B3 helicopters with MOD 07 5601 installed:
    Note 1 to paragraph (f): 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 Table 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
------------------------------------------------------------------------

    Table 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 Table 2 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
------------------------------------------------------------------------

    Table 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 1 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 
1 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 2 to paragraph (f) of this AD). A flashlight may 
be used to enhance the check.
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[GRAPHIC] [TIFF OMITTED] TR23SE13.001

[[Page 58261]]

[GRAPHIC] [TIFF OMITTED] TR23SE13.002

    (D) Repeat paragraphs (f)(1)(iii)(A) through (f)(1)(iii)(C) 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 3 to paragraph (f) of this 
AD. The load will deflect the tail rotor blade away from the tail 
boom.

[[Page 58262]]

[GRAPHIC] [TIFF OMITTED] TR23SE13.003

    (F) While maintaining the load, check visible faces of Area C as 
shown in Figure 3 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) 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 4 to paragraph (f) of this AD, before 
further flight, replace the four bearings with airworthy bearings.

[[Page 58263]]

[GRAPHIC] [TIFF OMITTED] TR23SE13.004

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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 4 to paragraph (f):  The manufacturer refers to the actions 
in paragraphs (f)(1)(viii)(B) through (f)(1)(viii)(E) 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.
    (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 required for 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 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 Permit

    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. 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 Emergency AD No. 2013-0029, dated February 8, 2013, 
which can be found in the AD Docket on the Internet at http://www.regulations.gov.

 (k) Subject

    Joint Aircraft Service Component (JASC) Code: 6400: Tail Rotor.

[[Page 58264]]

    Issued in Fort Worth, Texas, on September 13, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-23102 Filed 9-20-13; 8:45 am]
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