Airworthiness Directives; Eurocopter France Helicopters, 58256-58264 [2013-23102]
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burden by requiring investigations to be
continually reinvestigated. In addition,
permitting access and amendment to such
information could disclose security-sensitive
information that could be detrimental to
homeland security.
(3) From subsection (e)(1) (Relevancy and
Necessity of Information) because in the
course of investigations into potential
violations of federal law, the accuracy of
information obtained or introduced
occasionally may be unclear, or the
information may not be strictly relevant or
necessary to a specific investigation. In the
interests of effective law enforcement, it is
appropriate to retain all information that may
aid in establishing patterns of unlawful
activity.
(4) From subsection (e)(2) (Collection of
Information from Individuals) because
requiring that information be collected from
the subject of an investigation would alert the
subject to the nature or existence of the
investigation, thereby interfering with that
investigation and related law enforcement
activities.
(5) From subsection (e)(3) (Notice to
Subjects) because providing such detailed
information could impede law enforcement
by compromising the existence of a
confidential investigation or reveal the
identity of witnesses or confidential
informants.
(6) From subsections (e)(4)(G), (e)(4)(H),
and (e)(4)(I) (Agency Requirements) and (f)
(Agency Rules), because portions of this
system are exempt from the individual access
provisions of subsection (d) for the reasons
noted above, and therefore DHS is not
required to establish requirements, rules, or
procedures with respect to such access.
Providing notice to individuals with respect
to existence of records pertaining to them in
the system of records or otherwise setting up
procedures pursuant to which individuals
may access and view records pertaining to
themselves in the system would undermine
investigative efforts and reveal the identities
of witnesses, potential witnesses, and
confidential informants.
(7) From subsection (e)(5) (Collection of
Information) because with the collection of
information for law enforcement purposes, it
is impossible to determine in advance what
information is accurate, relevant, timely, and
complete. Compliance with subsection (e)(5)
would preclude DHS agents from using their
investigative training and exercise of good
judgment to both conduct and report on
investigations.
(8) From subsection (e)(8) (Notice on
Individuals) because compliance would
interfere with DHS’s ability to obtain, serve,
and issue subpoenas, warrants, and other law
enforcement mechanisms that may be filed
under seal and could result in disclosure of
investigative techniques, procedures, and
evidence.
(9) From subsection (g)(1) (Civil Remedies)
to the extent that the system is exempt from
other specific subsections of the Privacy Act.
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Dated: August 6, 2013.
Jonathan R. Cantor,
Acting Chief Privacy Officer, Department of
Homeland Security.
[FR Doc. 2013–22691 Filed 9–20–13; 8:45 am]
BILLING CODE 4411–14–P
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
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Federal holidays.
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this 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 https://
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.
14 CFR Part 39
[Docket No. FAA–2013–0822; Directorate
Identifier 2013–SW–004–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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.
SUMMARY:
We must receive comments on
this proposed AD by November 22,
2013.
DATES:
You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://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
ADDRESSES:
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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
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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 partnumbered 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
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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
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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.
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:
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• 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.
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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
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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 workhours, 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 workhours, 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;
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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
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):
■
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
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specified compliance time unless it has
already been accomplished prior to that time.
VNE POWER ON—Continued
Hp
(ft)
(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:
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.
100
97
94
91
88
85
82
79
76
73
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IAS
(kts)
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
IAS
(kts)
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
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VNE POWER ON
Hp
(ft)
Hp
(ft)
19:59 Sep 20, 2013
67
Valid for VNE POWER OFF
VNE POWER ON
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IAS
(kts)
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(f) Required Actions
100
97
94
91
88
85
82
79
76
73
70
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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(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.
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The load will deflect the tail rotor blade away
from the tail boom.
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(D) Repeat paragraphs (f)(1)(iii)(A) through
(f)(1)(iii)(C) on the other tail rotor blade.
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(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
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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.
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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 4 to paragraph (f) of this AD, before
further flight, replace the four bearings with
airworthy bearings.
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Federal Register / Vol. 78, No. 184 / Monday, September 23, 2013 / Proposed Rules
(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
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
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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.
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Fmt 4702
Sfmt 4702
(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 https://www.regulations.gov.
(k) Subject
Joint Aircraft Service Component (JASC)
Code: 6400: Tail Rotor.
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emcdonald on DSK67QTVN1PROD with PROPOSALS
BILLING CODE 4910–13–C
58263
58264
Federal Register / Vol. 78, No. 184 / Monday, September 23, 2013 / Proposed Rules
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]
BILLING CODE 4910–13–P
DEPARTMENT OF LABOR
Mine Safety and Health Administration
30 CFR Parts 7 and 75
RIN 1219–AB79
Refuge Alternatives for Underground
Coal Mines
Mine Safety and Health
Administration, Labor.
ACTION: Request for information;
extension of comment period.
AGENCY:
In response to requests from
interested parties, the Mine Safety and
Health Administration (MSHA) is
extending the comment period on the
Agency’s Request for Information (RFI)
on Refuge Alternatives for Underground
Coal Mines. This extension gives
interested parties additional time to
review new information on refuge
alternatives.
SUMMARY:
Comments must be received by
midnight Eastern Standard Time on
December 6, 2013.
ADDRESSES: Submit comments and
supporting documentation by any of the
following methods:
• Federal E-Rulemaking Portal:
https://www.regulations.gov. Follow the
on-line instructions for submitting
comments for Docket Number MSHA–
2013–0033.
• Electronic mail: zzMSHAcomments@dol.gov. Include ‘‘RIN 1219–
AB79’’ in the subject line of the
message.
• Mail: Send comments to MSHA,
Office of Standards, Regulations, and
Variances, 1100 Wilson Boulevard,
Room 2350, Arlington, Virginia 22209–
3939.
• Hand Delivery or Courier: MSHA,
Office of Standards, Regulations, and
Variances, 1100 Wilson Boulevard,
Room 2350, Arlington, Virginia,
between 9:00 a.m. and 5:00 p.m.
Monday through Friday, except Federal
holidays. Sign in at the receptionist’s
desk on the 21st floor.
Instructions: Clearly identify all
submissions with ‘‘RIN 1219–AB79’’.
Because comments will not be edited to
remove any identifying or contact
information, MSHA cautions the
commenter against including
emcdonald on DSK67QTVN1PROD with PROPOSALS
DATES:
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information in the submission that
should not be publicly disclosed.
FOR FURTHER INFORMATION CONTACT:
George F. Triebsch, Director, Office of
Standards, Regulations, and Variances,
MSHA, at triebsch.george@dol.gov
(email); 202–693–9440 (voice); or 202–
693–9441 (facsimile). These are not tollfree numbers.
SUPPLEMENTARY INFORMATION: On August
8, 2013 (78 FR 48593), MSHA published
a Request for Information on Refuge
Alternatives for Underground Coal
Mines. The RFI comment period had
been scheduled to close on October 7,
2013. In response to requests, MSHA is
extending the comment period to
December 6, 2013 to allow interested
parties additional time to review
National Institute for Occupational
Safety and Health information.
Dated: September 18, 2013.
Joseph A. Main,
Assistant Secretary of Labor for Mine Safety
and Health.
[FR Doc. 2013–23031 Filed 9–20–13; 8:45 am]
BILLING CODE 4510–43–P
DEPARTMENT OF VETERANS
AFFAIRS
38 CFR Part 9
RIN 2900–AO42
Servicemembers’ Group Life Insurance
and Veterans’ Group Life Insurance
Information Access
Department of Veterans Affairs.
Proposed rule.
AGENCY:
ACTION:
The Department of Veterans
Affairs (VA) proposes to amend its
regulations governing Servicemembers’
Group Life Insurance (SGLI), Family
SGLI, SGLI Traumatic Injury Protection,
and Veterans’ Group Life Insurance (all
hereafter referred to as SGLI). The
purpose is to acknowledge and clarify
what is implicit in the law: That VA,
which has the responsibility under the
law to oversee the SGLI program and
ensure its proper operation, also has the
right to full access to records held by the
insurer or on behalf of the insurer from
whom VA has purchased a policy.
These records include all of the
insurer’s records related to the operation
and administration of the SGLI
programs necessary to protect the legal
and financial rights of the Government
and of the persons affected by the
activities of the agency and its agents.
DATES: Comments must be received by
VA on or before November 22, 2013.
ADDRESSES: Written comments may be
submitted through https://
SUMMARY:
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www.Regulations.gov; by mail or hand
delivery to Director, Regulation Policy
and Management (02REG), Department
of Veterans Affairs, 810 Vermont Ave.
NW., Room 1068, Washington, DC
20420; or by fax to (202) 273–9026.
Comments should indicate that they are
submitted in response to ‘‘RIN 2900–
AO42 Servicemembers’ Group Life
Insurance and Veterans’ Group Life
Insurance Information Access.’’ Copies
of comments received will be available
for public inspection in the Office of
Regulation Policy and Management,
Room 1068, between the hours of 8:00
a.m. and 4:30 p.m., Monday through
Friday (except holidays). Please call
(202) 461–4902 for an appointment.
(This is not a toll-free number.) In
addition, during the comment period,
comments may be viewed online
through the Federal Docket Management
System at https://www.Regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Monica Keitt, Attorney/Advisor,
Department of Veterans Affairs Regional
Office and Insurance Center (310/290B),
5000 Wissahickon Avenue, P.O. Box
8079, Philadelphia, PA 19101, (215)
842–2000, ext. 2905. This is not a tollfree number.
SUPPLEMENTARY INFORMATION: Section
1966(a) of title 38, United States Code,
authorizes the Secretary of Veterans
Affairs (Secretary) to purchase one or
more group life insurance policies from
one or more life insurance companies
for the purposes of providing the
benefits specified in 38 U.S.C. 1965–
1980A, namely the Servicemembers’
Group Life Insurance (SGLI), Family
SGLI, SGLI Traumatic Injury Protection,
and Veterans’ Group Life Insurance
programs (all hereafter referred to as
SGLI). Under 38 U.S.C. 1966 and the
terms of the policy purchased by VA
pursuant to section 1966(a), the insurer
has the responsibility of administering
the SGLI programs on a day-to-day basis
with VA retaining oversight
responsibility to ensure that the SGLI
programs are managed in an effective
and efficient manner that allows the
Secretary to fulfill his responsibilities
under the law.
Section 3101 of title 44, United States
Code, requires the head of each Federal
agency to make and preserve records
containing adequate and proper
documentation of the organization,
functions, policies, decisions,
procedures, and essential transactions of
the agency and designed to furnish the
information necessary to ‘‘protect the
legal and financial rights of the
Government and of persons directly
affected by the agency’s activities.’’ The
records that are created and maintained
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]]>Agencies
[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]
=======================================================================
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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 https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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 https://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
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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
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 https://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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