[Federal Register Volume 78, Number 184 (Monday, September 23, 2013)]
[Proposed Rules]
[Pages 58256-58264]
From the Federal Register Online via the Government Publishing 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 [email protected].
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] TR23SE13.002
(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
[email protected].
(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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