Airworthiness Directives; Agusta S.p.A. Helicopters, 12651-12655 [2013-04220]
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Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules
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 Amendment 39–16717 (76 FR
35330, June 17, 2011), and adding the
following new AD:
■
Robinson Helicopter Company: Docket No.
FAA–2013–0159; Directorate Identifier
2012–SW–010–AD.
(a) Applicability
This AD applies to Model R22, R22 Alpha,
R22 Beta, and R22 Mariner helicopters with
main rotor blade (blade), part number (P/N)
A016–2 or A016–4; and Model R44 and R44
II helicopters with blade, P/N C016–2 or C–
016–5, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
blade skin debonding, which could result in
blade failure and subsequent loss of control
of the helicopter.
(c) Affected ADs
This AD supersedes AD 2011–12–10,
Amendment 39–16717 (76 FR 35330, June
17, 2011).
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(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) Before the first flight of each day,
visually check for any exposed (bare metal)
skin-to-spar joint area on the lower surface of
each blade. The actions required by this
paragraph 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
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.
(2) If there is any bare metal in the area of
the skin-to-spar bond line, before further
flight, inspect the blade by following the
requirements of paragraph (e)(3) of this AD.
(3) Within 10 hours time-in-service (TIS),
and at intervals not to exceed 100 hours TIS
or at each annual inspection, whichever
occurs first, inspect each blade for corrosion,
separation, a gap, or a dent by following the
Compliance Procedure, paragraphs 1 through
6 and 8, of Robinson R22 Service Bulletin
SB–103, dated April 30, 2010 (SB103), or
Robinson Service Bulletin SB–72, dated
April 30, 2010 (SB72), as appropriate for your
model helicopter. Although the Robinson
service information limits the magnification
to 10 x, a higher magnification is acceptable
for this inspection. Also, an appropriate tap
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test tool which provides similar performance,
weight, and consistency of tone may be
substituted for the ‘‘1965 or later United
States Quarter-dollar coin,’’ which is
specified in the Compliance Procedure,
paragraph 2, of SB72 and SB103.
(4) Before further flight, refinish any
exposed area of a blade by following the
Compliance Procedure, paragraphs 2 through
6, of Robinson R22 Service Letter SL–56B or
R44 Service Letter SL–32B, both dated April
30, 2010, as appropriate for your model
helicopter.
(5) Before further flight, replace any
unairworthy blade with an airworthy blade.
(6) Within 5 years of the effective date of
this AD:
(i) For Model R22 series helicopters,
replace blade P/N A016–2 or A016–4 with a
blade, P/N A016–6.
(ii) For Model R44 series helicopters fitted
with hydraulically boosted main rotor flight
controls, replace blade P/N C016–2 or C016–
5 with a blade, P/N C016–7.
(iii) For Model R44 series helicopters
without hydraulically boosted main rotor
flight controls, replace blade P/N C016–2 or
C016–5 with a blade, P/N C016–7. Prior to
installing a blade P/N C016–7, verify the
helicopter has been modified as required by
Robinson R44 Service Letter SL–37, dated
June 18, 2010, Compliance Procedures,
paragraphs 1. through 10.
(iv) Installing blades, P/N A016–6 or P/N
C016–7, is terminating action for the
inspection requirements of paragraphs (e)(1)
through (e)(4) of this AD.
(f) Special Flight Permit
Special flight permits will not be issued.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Fred Guerin, Aviation Safety Engineer, Los
Angeles Aircraft Certification Office,
Transport Airplane Directorate, FAA, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone (562) 627–5232; email
fred.guerin@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.
(h) Additional Information
The Robinson letter titled ‘‘Additional
Information Regarding Main Rotor Blade
Skin Debonding,’’ dated May 25, 2007, which
is not incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Robinson Helicopter
Company, 2901 Airport Drive, Torrance, CA
90505; telephone (310) 539–0508; fax (310)
539–5198; or at https://
www.robinsonheli.com/servelib.htm. You
may review a copy of this information at the
FAA, Office of the Regional Counsel,
PO 00000
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12651
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137.
(i) Subject.
Joint Aircraft Service Component (JASC)
Code: 6210: Main Rotor Blades.
Issued in Fort Worth, Texas, on February
12, 2013.
Bruce Cain,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–04217 Filed 2–22–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0146; Directorate
Identifier 2012–SW–060–AD]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD) for
Agusta S.p.A. (Agusta) Model A109E
helicopters that requires reducing the
tail rotor (T/R) blade life limit,
modifying a T/R hub and grip assembly,
re-identifying two T/R assemblies,
clarifying the never-exceed speed (Vne)
limitation and reducing the inspection
interval. Since we issued that AD, the
manufacturer has redesigned a T/R grip
bushing (bushing) that reduces the
loads, which caused the T/R cracking,
on the T/R blades. This action would
require installing the new bushing and
re-identifying the T/R hub-and-grip and
hub-and-blade assemblies and require a
recurring inspection of each bushing.
The proposed actions are intended to
prevent fatigue failure of a T/R blade
and subsequent loss of control of the
helicopter.
DATES: We must receive comments on
this proposed AD by April 26, 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.
SUMMARY:
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Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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.
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
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 Agusta
Westland, Customer Support & Services,
Via Per Tornavento 15, 21019 Somma
Lombardo (VA) Italy, ATTN: Giovanni
Cecchelli; telephone 39–0331–711133;
fax 39–0331–711180; or at https://
www.agustawestland.com/technicalbullettins. You may review a copy of the
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:
Sharon Miles, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, TX 76137;
telephone (817) 222–5110; email
sharon.y.miles@faa.gov.
SUPPLEMENTARY INFORMATION
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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
consider all comments we receive on or
before the closing date for comments.
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Discussion
On June 12, 2002, a T/R blade on an
Agusta Model 119 helicopter failed and
resulted in an autorotative landing. As
a result of this failure, based on the
commonality of the T/R blades on the
model 109E helicopter, Agusta issued
Alert Bollettino Tecnico (ABT) No.
109EP–30, dated June 21, 2002, for the
Model 109E helicopter. The aviation
authority for Italy, Ente Nazionale per
L’Aviazione Civile (ENAC), issued
Emergency AD No. 2002–340, dated
June 28, 2002, for the Model 109E
helicopters. On July 9, 2002, we issued
Emergency AD 2002–14–51 to require a
pilot-check before each flight, and
initial and repetitive inspections of the
T/R blades for a crack.
‘‘As a precautionary measure,’’ Agusta
issued Revision A, dated July 25, 2002,
to ABT 109EP–30. On July 29, 2002,
ENAC issued AD No. 2002–384,
adopting the requirements of Revision A
of this Agusta ABT. On October 17,
2002, we issued immediately adopted
AD 2002–17–51 (67 FR 67510,
November 6, 2002) to require a
reduction in VNE, a pilot-check of each
T/R blade before each start of the
helicopter engines, and initial and
recurring inspections of each T/R blade
for a crack.
Following increased ground
vibrations in a Model A 109E helicopter,
another crack was discovered in a T/R
blade, which prompted Agusta to issue
Revision B, dated November 17, 2002, to
ABT 109EP–30. Analysis and tests had
shown that the fatigue failure of the T/
R blade was caused by unanticipated
loads on the T/R blade. Revision B to
that ABT specified maintaining the VNE
reduction until a new bushing was
installed in the T/R grip assembly.
Further, that ABT established, for T/R
blade P/N 109–8132–01–111 on grip
assembly P/N 109–8131–02–127, a
retirement life of 200 hours TIS. ENAC
adopted the provisions of Revision B of
the Agusta ABT in ENAC AD No. 2002–
592, dated November 28, 2002.
On February 14, 2003, we issued AD
2002–25–51, Amendment 39–13060 (68
FR 9504, February 28, 2003), to require:
For helicopters with T/R hub and
blade assembly, part number (P/N) 109–
8131–02–151 (the T/R hub and blade
assembly consists of two T/R blades, P/
N 109–8132–01–111, and one T/R hub
and grip assembly, P/N 109–8131–02–
127):
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• Before further flight, installing a
placard and marking the airspeed
indicator to reduce the helicopter VNE
by 28 knots-indicated air speed (KIAS)
in addition to any additional reduction
in VNE caused by optional equipment.
• Before each start of the helicopter
engines, allowing an owner/operator
(pilot) to check the T/R blade for a crack
so long as the pilot records that AD
compliance in the maintenance records
in accordance with 14 CFR 43.9(a)(1)-(4)
and 91.417(a)(2)(v).
• Within 5 hours time-in-service
(TIS), and thereafter at intervals not to
exceed 5 hours TIS, and before further
flight any time there is an increase in
vibration levels, inspecting each T/R
blade for a crack using a 5x or higher
magnifying glass.
• Establishing a new life limit for T/
R blade, P/N 109–8132–01–111, of 200
hours TIS and requiring T/R blades with
190 hours or more TIS to be replaced
within 10 hours TIS.
• On or before May 31, 2003,
modifying and re-identifying the T/R
hub and grip assembly and the T/R hub
and blade assembly, which removes the
VNE restriction and restores the T/R
blade life limit to 1,000 hours TIS.
For helicopters with T/R hub and
blade assembly, P/N 109–8131–02–157
(the T/R hub and blade assembly
consists of two T/R blades, P/N 109–
8132–01–111, and one T/R hub and grip
assembly, P/N 109–8131–02–159):
• Before each start of the helicopter
engines, allowing an owner/operator
(pilot) to check the T/R blade for a crack
so long as the pilot records that AD
compliance in the maintenance records
in accordance with 14 CFR 43.9(a)(1)-(4)
and 91.417(a)(2)(v).
• Within 25 hours TIS, and thereafter
at intervals not to exceed 25 hours TIS,
and before further flight any time there
is an increase in vibration levels,
inspecting each T/R blade for a crack
using a 5x or higher magnifying glass.
• On or before accumulating 150
hours TIS on the T/R hub assembly, P/
N 109–8131–02–159, and thereafter at
intervals not to exceed 150 hours TIS,
inspecting the bushings, P/N 109–8131–
30–109, linings for wear, and replacing
any unairworthy bushing.
Also, the existing AD states that T/R
blades, P/N 109–8132–01–111, which
have been operated as part of the T/R
hub and blade assembly, P/N 109–8131–
02–151, are considered unairworthy
components of the T/R hub and blade
assembly, P/N 109–8131–02–157,
regardless of TIS.
Finally, AD 2002–25–51 requires
replacing any unairworthy T/R blade
before further flight.
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Actions Since Existing AD Was Issued
Since we issued AD 2002–25–51,
Agusta has issued Revision C, dated
September 29, 2006, to ABT No. 109EP–
30, and states that the service
experience of T/R hub and blade
assemblies with the newly-designed
bushings that reduce T/R blade loading
has shown improvement and has
determined that increasing the amount
of time between inspections is
appropriate, based upon the service
history and the results of the
maintenance performed.
In response to Revision C of the ABT,
the European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2006–
0353, dated December 4, 2006, which
supersedes ENAC AD 2002–597 to
extend the inspection interval ‘‘from
150 to 200 FH.’’ Subsequently, EASA
AD No. 2007–0010, dated January 31,
2007, was issued to supersede AD No.
2006–0353 to restore the initial
requirements of ABT 109EP–30,
Revision C, which were unintentionally
omitted from AD No. 2006–0353.
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FAA’s Determination
These helicopters have been approved
by the aviation authority of Italy and are
approved for operation in the United
States. Pursuant to our bilateral
agreement with Italy, 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 products of the same
type design.
Related Service Information
We reviewed ABT No. 109EP–30,
Revision C, dated September 29, 2006,
which describes procedures for
checking/inspecting for cracks on both
the upper and lower surfaces of T/R
blades, P/N 109–8132–01–111;
replacing each bushing, P/N 109–0132–
55 and spacer P/N 109–0132–13, with
bushing, P/N 109–8131–30–109, and
instituting a recurring inspection of
each bushing; and cancelling the VNE
limitations when the newly-designed
bushing is installed on each T/R grip
assembly, P/N 109–8131–29–101, a
‘‘new’’ pair of T/R blades, P/N 109–
8132–01–111, is installed, and the T/R
hub-and-grip and hub-and-blade
assemblies are re-identified.
Proposed AD Requirements
This proposed AD would require:
• Before each start of the helicopter
engines, visually checking both sides of
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each T/R blade for a crack. An owner/
operator (pilot) may perform this check
and must enter compliance into the
aircraft records in accordance with 14
CFR 43.9 (a)(1)-(4) and 14 CFR
91.417(a)(2)(v). A pilot may perform this
check because it involves only a visual
check for a crack and can be performed
equally well by a pilot or a mechanic.
This procedure is an exception to our
standard maintenance regulations.
• For helicopters with T/R hub and
blade assembly, P/N 109–8131–02–151,
before further flight, modifying each T/
R hub and blade assembly by installing
a new bushing in each grip assembly
and two zero-TIS T/R blades; and reidentifying the hub and grip assembly
and the T/R hub and blade assembly
with different P/Ns.
• For helicopters with T/R hub and
blade assembly, P/N 109–8131–02–157,
within 25 hours TIS and thereafter at
intervals not to exceed 25 hours TIS,
and before further flight any time there
is an increase in vibration levels, using
a 5x or higher power magnifying glass,
visually inspecting each T/R blade for a
crack.
• On or before accumulating 200
hours TIS on the T/R hub and grip
assembly, and thereafter at intervals not
to exceed 200 hours TIS, inspecting the
linings and measuring the internal
diameter of the bushings. If the internal
diameter of the bushing exceeds 41.35
millimeters, replacing the bushing.
• If there is a crack, before further
flight, replacing the T/R blade.
• Revising the Airworthiness
Limitations section of the maintenance
manual to reflect that a T/R blade, P/N
109–8132–01–111, which has not been
operated as part of T/R hub and blade
assembly, P/N 109–8131–02–151, has a
retirement life of 1,000 hours TIS.
Costs of Compliance
We estimate that this proposed AD
would affect 75 helicopters of U.S.
Registry. Based on an average labor rate
of $85 per hour, we estimate that
operators may incur the following costs
in order to comply with this AD:
• Visually inspecting the T/R blades
would require about 0.5 work hours for
a cost per helicopter of $43 and a total
cost to U.S. operators of $3,225 per
inspection cycle.
• Replacing a cracked T/R blade
would require about 2 work hours, and
required parts would cost about
$25,320, for a total cost per helicopter
of $25,490.
• Modifying the hub assembly with
new T/R blades and bushings would
require about 16 work hours, and
required parts would cost about
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$58,690, for a total cost per helicopter
of $60,050.
• Inspecting the T/R bushings would
require about 7 work hours, for a cost
per helicopter of $595 and a total cost
to U.S. operators of $44,625 per
inspection cycle.
• Revising the Airworthiness
Limitations section of the maintenance
manual would require about .25 work
hour, for a cost per helicopter of $22
and a total cost to U.S. operators of
$1,650.
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.
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The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 to read as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
(d) Reserved
AGUSTA S.p.A. (Agusta): Docket No. FAA–
2013–0146; Directorate Identifier 2012–
SW–060–AD.
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(a) Applicability
This AD applies to Agusta Model 109E
helicopters with tail rotor (T/R) hub and
blade assembly, part number (P/N) 109–
8131–02–151 and P/N 109–8131–02–157,
certificated in any category.
(b) Unsafe Condition
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
the following new Airworthiness
Directive (AD):
[Amended]
This AD defines the unsafe condition as a
fatigue crack in a T/R blade. This condition
could result in failure of the T/R blade and
subsequent loss of control of the helicopter.
(c) Affected ADs
2. The FAA amends § 39.13 by
removing Amendment 39–13060 (68 FR
9504, February 28, 2003), and adding
This AD supersedes AD 2002–25–51,
Docket No. 2002–SW–55–AD, Amendment
39–13060 (68 FR 9504, February 28, 2003).
BILLING CODE 4910–03–C
the Compliance Instructions, Part V,
paragraphs 2. through 13., of Agusta
Bollettino Tecnico No. 109EP–30, Revision C,
dated September 29, 2006 (BT). A T/R blade,
P/N 109–8132–01–111, which has been
operated as part of T/R hub and blade
assembly, P/N 109–8131–02–151, must be
retired regardless of TIS and may not be used
as part of the T/R hub and blade assembly,
P/N 109–8131–02–157. Returning the
removed T/R blades, grips, or bushings to
Agusta is not required.
(3) For helicopters with T/R hub and blade
assembly, P/N 109–8131–02–157 (consisting
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■
(2) For helicopters with T/R hub and blade
assembly, P/N 109–8131–02–151 (consisting
of two T/R blades, P/N 109–8132–01–111,
and one T/R hub and grip assembly, P/N
109–8131–02–127), before further flight,
modify each T/R hub and blade assembly by
installing a new bushing, P/N 109–8131–30–
109, in each grip assembly and two zero-hour
time-in-service (TIS) T/R blades, P/N 109–
8132–01–111; re-identifying the hub and grip
assembly as P/N 109–8131–02–159; and reidentifying the T/R hub and blade assembly
as P/N 109–8131–02–157 in accordance with
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(e) Compliance
(f) Required Actions
(1) Before each start of the helicopter
engines, visually check both sides of each
T/R blade for a crack in the inspection area
depicted in Figure 1 to paragraph (f) of this
AD. This action 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 43.9
(a)(1)–(4) and 14 CFR 91.417(a)(2)(v). The
record must be maintained as required by 14
CFR 91.173, 121.380, or 135.439.
BILLING CODE 4910–13–P
of two T/R blades, P/N 109–8132–01–111,
and one T/R hub and grip assembly, P/N
109–8131–02–159), within 25 hours TIS, and
thereafter at intervals not to exceed 25 hours
TIS, and before further flight any time there
is an increase in vibration levels, using a 5x
or higher power magnifying glass, visually
inspect each T/R blade for a crack in
accordance with the Compliance
Instructions, Part III, paragraphs 1. through 5.
of the BT. Reporting to Agusta is not
required.
(4) On or before accumulating 200 hours
TIS on the T/R hub and grip assembly, P/N
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Federal Register / Vol. 78, No. 37 / Monday, February 25, 2013 / Proposed Rules
109–8131–02–159, and thereafter at intervals
not to exceed 200 hours TIS, inspect the
linings and measure the internal diameter of
the bushings, P/N 109–8131–30–109, by
referring to Figure 2 of the BT. If the internal
diameter of the bushing exceeds 41.35
millimeters, replace the bushing.
(5) If there is a crack in a T/R blade, before
further flight, replace the cracked T/R blade.
(6) Revise the Airworthiness Limitations
section of the maintenance manual to reflect
that a T/R blade, P/N 109–8132–01–111,
which has not been operated as part of T/R
hub and blade assembly, P/N 109–8131–02–
151, has retirement life of 1,000 hours TIS.
(g) Special Flight Permit
Special flight permits will not be issued.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Sharon Miles,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas,
76137; telephone (817) 222–5110; email
sharon.y.miles@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.
(i) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency AD No.
2007–0010, dated January 31, 2007.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6410, Tail Rotor Blades.
Issued in Fort Worth, Texas, on February
11, 2013.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013–04220 Filed 2–22–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF LABOR
Employment and Training
Administration
20 CFR Part 619
erowe on DSK2VPTVN1PROD with PROPOSALS-1
RIN 1205–AB64
Federal-State Unemployment
Insurance (UI) Program; Data
Exchange Standardization as Required
by Section 2104 of the Middle Class
Tax Relief and Job Creation Act of
2012
Employment and Training
Administration, Labor.
AGENCY:
VerDate Mar<15>2010
14:27 Feb 22, 2013
Jkt 229001
ACTION:
Notice of proposed rulemaking.
The Department of Labor’s
(Department’s) Employment and
Training Administration proposes to
designate in regulation data exchange
standards, developed in consultation
with an interagency work group
established by the Office of Management
and Budget (OMB), for Unemployment
Insurance (UI) administration as
required by amendments to Title IX of
the Social Security Act (SSA) made by
the Middle Class Tax Relief and Job
Creation Act of 2012 (the Act). This
proposed regulation would establish
data exchange standards for three
categories of information: real-time
applications on the Interstate
Connection Network (ICON); the State
Information Data Exchange System
(SIDES); and implementation of the
standards identified for ICON and
SIDES in major Information Technology
(IT) modernization projects to upgrade
UI Benefits and Tax systems by State
Workforce Agencies (SWAs) using
Federal funds.
DATES: Submit comments on or before
April 26, 2013.
ADDRESSES: You may submit comments,
identified by Regulatory Information
Number (RIN) 1205–AB64, by one of the
following methods:
Federal e-Rulemaking Portal: https://
www.regulations.gov. Follow the Web
site instructions for submitting
comments.
Mail and hand delivery/courier:
Written comments, disk, and CD–ROM
submissions may be mailed to Michael
S. Jones, Acting Administrator, Office of
Policy Development and Research, U.S.
Department of Labor, 200 Constitution
Avenue NW., Room N–5641, and
Washington, DC 20210.
Instructions: Label all submissions
with ‘‘RIN 1205–AB64.’’
Please submit your comments by only
one method. Please be advised that the
Department will post all comments
received that relate to the proposed data
exchange standardization on https://
www.regulations.gov without making
any change to the comments or
redacting any information. The https://
www.regulations.gov Web site is the
Federal e-rulemaking portal and all
comments posted there are available
and accessible to the public. Therefore,
the Department recommends that
commenters remove personal
information such as Social Security
Numbers, personal addresses, telephone
numbers, and email addresses included
in their comments as such information
may become easily available to the
public via the https://
www.regulations.gov Web site. It is the
SUMMARY:
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
12655
responsibility of the commenter to
safeguard personal information.
Also, please note that due to security
concerns, postal mail delivery in
Washington, DC may be delayed.
Therefore, the Department encourages
the public to submit comments on
https://www.regulations.gov.
Docket: All comments on this
proposed rule will be available on the
https://www.regulations.gov Web site
and can be found using RIN 1205–AB64.
The Department also will make all the
comments it receives available for
public inspection by appointment
during normal business hours at the
above address. If you need assistance to
review the comments, the Department
will provide appropriate aids such as
readers or print magnifiers. The
Department will make copies of this
proposed rule available, upon request,
in large print and electronic file on
computer disk. To schedule an
appointment to review the comments
and/or obtain the proposed rule in an
alternative format, contact the Office of
Policy Development and Research at
(202) 693–3700 (this is not a toll-free
number). You may also contact this
office at the address listed below.
Instructions for Submitting Comments
on Paperwork Burden: Submit any
comments that concern the information
collection request to the Office of
Information and Regulatory Affairs,
Attn: OMB Desk Officer for DOL–ETA,
Office of Management and Budget,
Room 10235, 725 17th Street NW.,
Washington, DC 20503, Fax: 202–395–
6881 (this is not a toll-free number),
email: OIRA_submission@omb.eop.gov.
OMB recommends that comments on
the information collection requirements
be submitted within 30 days of
publication of this NPRM. Comments on
the information collections may also be
submitted to the ETA in the same
manner as any other issue addressed in
this NPRM.
FOR FURTHER INFORMATION CONTACT:
Michael S. Jones, Acting Administrator,
Office of Policy Development and
Research, U.S. Department of Labor, 200
Constitution Avenue NW., Room N–
5641, Washington, DC 20210; telephone
(202) 693–3700 (this is not a toll-free
number).
Individuals with hearing or speech
impairments may access the telephone
number above via TTY by calling the
toll-free Federal Information Relay
Service at 1–800–877–8339.
SUPPLEMENTARY INFORMATION: The
preamble to this proposed rule is
organized as follows:
I. Background—provides a brief description
of the development of the proposed rule.
E:\FR\FM\25FEP1.SGM
25FEP1
]]>Agencies
[Federal Register Volume 78, Number 37 (Monday, February 25, 2013)]
[Proposed Rules]
[Pages 12651-12655]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-04220]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0146; Directorate Identifier 2012-SW-060-AD]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that requires
reducing the tail rotor (T/R) blade life limit, modifying a T/R hub and
grip assembly, re-identifying two T/R assemblies, clarifying the never-
exceed speed (Vne) limitation and reducing the inspection interval.
Since we issued that AD, the manufacturer has redesigned a T/R grip
bushing (bushing) that reduces the loads, which caused the T/R
cracking, on the T/R blades. This action would require installing the
new bushing and re-identifying the T/R hub-and-grip and hub-and-blade
assemblies and require a recurring inspection of each bushing. The
proposed actions are intended to prevent fatigue failure of a T/R blade
and subsequent loss of control of the helicopter.
DATES: We must receive comments on this proposed AD by April 26, 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.
[[Page 12652]]
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 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
Agusta Westland, Customer Support & Services, Via Per Tornavento 15,
21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone
39-0331-711133; fax 39-0331-711180; or at https://www.agustawestland.com/technical-bullettins. You may review a copy of
the 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: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5110;
email sharon.y.miles@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 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 June 12, 2002, a T/R blade on an Agusta Model 119 helicopter
failed and resulted in an autorotative landing. As a result of this
failure, based on the commonality of the T/R blades on the model 109E
helicopter, Agusta issued Alert Bollettino Tecnico (ABT) No. 109EP-30,
dated June 21, 2002, for the Model 109E helicopter. The aviation
authority for Italy, Ente Nazionale per L'Aviazione Civile (ENAC),
issued Emergency AD No. 2002-340, dated June 28, 2002, for the Model
109E helicopters. On July 9, 2002, we issued Emergency AD 2002-14-51 to
require a pilot-check before each flight, and initial and repetitive
inspections of the T/R blades for a crack.
``As a precautionary measure,'' Agusta issued Revision A, dated
July 25, 2002, to ABT 109EP-30. On July 29, 2002, ENAC issued AD No.
2002-384, adopting the requirements of Revision A of this Agusta ABT.
On October 17, 2002, we issued immediately adopted AD 2002-17-51 (67 FR
67510, November 6, 2002) to require a reduction in VNE, a
pilot-check of each T/R blade before each start of the helicopter
engines, and initial and recurring inspections of each T/R blade for a
crack.
Following increased ground vibrations in a Model A 109E helicopter,
another crack was discovered in a T/R blade, which prompted Agusta to
issue Revision B, dated November 17, 2002, to ABT 109EP-30. Analysis
and tests had shown that the fatigue failure of the T/R blade was
caused by unanticipated loads on the T/R blade. Revision B to that ABT
specified maintaining the VNE reduction until a new bushing
was installed in the T/R grip assembly. Further, that ABT established,
for T/R blade P/N 109-8132-01-111 on grip assembly P/N 109-8131-02-127,
a retirement life of 200 hours TIS. ENAC adopted the provisions of
Revision B of the Agusta ABT in ENAC AD No. 2002-592, dated November
28, 2002.
On February 14, 2003, we issued AD 2002-25-51, Amendment 39-13060
(68 FR 9504, February 28, 2003), to require:
For helicopters with T/R hub and blade assembly, part number (P/N)
109-8131-02-151 (the T/R hub and blade assembly consists of two T/R
blades, P/N 109-8132-01-111, and one T/R hub and grip assembly, P/N
109-8131-02-127):
Before further flight, installing a placard and marking
the airspeed indicator to reduce the helicopter VNE by 28
knots-indicated air speed (KIAS) in addition to any additional
reduction in VNE caused by optional equipment.
Before each start of the helicopter engines, allowing an
owner/operator (pilot) to check the T/R blade for a crack so long as
the pilot records that AD compliance in the maintenance records in
accordance with 14 CFR 43.9(a)(1)-(4) and 91.417(a)(2)(v).
Within 5 hours time-in-service (TIS), and thereafter at
intervals not to exceed 5 hours TIS, and before further flight any time
there is an increase in vibration levels, inspecting each T/R blade for
a crack using a 5x or higher magnifying glass.
Establishing a new life limit for T/R blade, P/N 109-8132-
01-111, of 200 hours TIS and requiring T/R blades with 190 hours or
more TIS to be replaced within 10 hours TIS.
On or before May 31, 2003, modifying and re-identifying
the T/R hub and grip assembly and the T/R hub and blade assembly, which
removes the VNE restriction and restores the T/R blade life
limit to 1,000 hours TIS.
For helicopters with T/R hub and blade assembly, P/N 109-8131-02-
157 (the T/R hub and blade assembly consists of two T/R blades, P/N
109-8132-01-111, and one T/R hub and grip assembly, P/N 109-8131-02-
159):
Before each start of the helicopter engines, allowing an
owner/operator (pilot) to check the T/R blade for a crack so long as
the pilot records that AD compliance in the maintenance records in
accordance with 14 CFR 43.9(a)(1)-(4) and 91.417(a)(2)(v).
Within 25 hours TIS, and thereafter at intervals not to
exceed 25 hours TIS, and before further flight any time there is an
increase in vibration levels, inspecting each T/R blade for a crack
using a 5x or higher magnifying glass.
On or before accumulating 150 hours TIS on the T/R hub
assembly, P/N 109-8131-02-159, and thereafter at intervals not to
exceed 150 hours TIS, inspecting the bushings, P/N 109-8131-30-109,
linings for wear, and replacing any unairworthy bushing.
Also, the existing AD states that T/R blades, P/N 109-8132-01-111,
which have been operated as part of the T/R hub and blade assembly, P/N
109-8131-02-151, are considered unairworthy components of the T/R hub
and blade assembly, P/N 109-8131-02-157, regardless of TIS.
Finally, AD 2002-25-51 requires replacing any unairworthy T/R blade
before further flight.
[[Page 12653]]
Actions Since Existing AD Was Issued
Since we issued AD 2002-25-51, Agusta has issued Revision C, dated
September 29, 2006, to ABT No. 109EP-30, and states that the service
experience of T/R hub and blade assemblies with the newly-designed
bushings that reduce T/R blade loading has shown improvement and has
determined that increasing the amount of time between inspections is
appropriate, based upon the service history and the results of the
maintenance performed.
In response to Revision C of the ABT, the European Aviation Safety
Agency (EASA), which is the Technical Agent for the Member States of
the European Union, has issued EASA AD No. 2006-0353, dated December 4,
2006, which supersedes ENAC AD 2002-597 to extend the inspection
interval ``from 150 to 200 FH.'' Subsequently, EASA AD No. 2007-0010,
dated January 31, 2007, was issued to supersede AD No. 2006-0353 to
restore the initial requirements of ABT 109EP-30, Revision C, which
were unintentionally omitted from AD No. 2006-0353.
FAA's Determination
These helicopters have been approved by the aviation authority of
Italy and are approved for operation in the United States. Pursuant to
our bilateral agreement with Italy, 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 products of the same type design.
Related Service Information
We reviewed ABT No. 109EP-30, Revision C, dated September 29, 2006,
which describes procedures for checking/inspecting for cracks on both
the upper and lower surfaces of T/R blades, P/N 109-8132-01-111;
replacing each bushing, P/N 109-0132-55 and spacer P/N 109-0132-13,
with bushing, P/N 109-8131-30-109, and instituting a recurring
inspection of each bushing; and cancelling the VNE
limitations when the newly-designed bushing is installed on each T/R
grip assembly, P/N 109-8131-29-101, a ``new'' pair of T/R blades, P/N
109-8132-01-111, is installed, and the T/R hub-and-grip and hub-and-
blade assemblies are re-identified.
Proposed AD Requirements
This proposed AD would require:
Before each start of the helicopter engines, visually
checking both sides of each T/R blade for a crack. An owner/operator
(pilot) may perform this check and must enter compliance into the
aircraft records in accordance with 14 CFR 43.9 (a)(1)-(4) and 14 CFR
91.417(a)(2)(v). A pilot may perform this check because it involves
only a visual check for a crack and can be performed equally well by a
pilot or a mechanic. This procedure is an exception to our standard
maintenance regulations.
For helicopters with T/R hub and blade assembly, P/N 109-
8131-02-151, before further flight, modifying each T/R hub and blade
assembly by installing a new bushing in each grip assembly and two
zero-TIS T/R blades; and re-identifying the hub and grip assembly and
the T/R hub and blade assembly with different P/Ns.
For helicopters with T/R hub and blade assembly, P/N 109-
8131-02-157, within 25 hours TIS and thereafter at intervals not to
exceed 25 hours TIS, and before further flight any time there is an
increase in vibration levels, using a 5x or higher power magnifying
glass, visually inspecting each T/R blade for a crack.
On or before accumulating 200 hours TIS on the T/R hub and
grip assembly, and thereafter at intervals not to exceed 200 hours TIS,
inspecting the linings and measuring the internal diameter of the
bushings. If the internal diameter of the bushing exceeds 41.35
millimeters, replacing the bushing.
If there is a crack, before further flight, replacing the
T/R blade.
Revising the Airworthiness Limitations section of the
maintenance manual to reflect that a T/R blade, P/N 109-8132-01-111,
which has not been operated as part of T/R hub and blade assembly, P/N
109-8131-02-151, has a retirement life of 1,000 hours TIS.
Costs of Compliance
We estimate that this proposed AD would affect 75 helicopters of
U.S. Registry. Based on an average labor rate of $85 per hour, we
estimate that operators may incur the following costs in order to
comply with this AD:
Visually inspecting the T/R blades would require about 0.5
work hours for a cost per helicopter of $43 and a total cost to U.S.
operators of $3,225 per inspection cycle.
Replacing a cracked T/R blade would require about 2 work
hours, and required parts would cost about $25,320, for a total cost
per helicopter of $25,490.
Modifying the hub assembly with new T/R blades and
bushings would require about 16 work hours, and required parts would
cost about $58,690, for a total cost per helicopter of $60,050.
Inspecting the T/R bushings would require about 7 work
hours, for a cost per helicopter of $595 and a total cost to U.S.
operators of $44,625 per inspection cycle.
Revising the Airworthiness Limitations section of the
maintenance manual would require about .25 work hour, for a cost per
helicopter of $22 and a total cost to U.S. operators of $1,650.
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.
[[Page 12654]]
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 to read 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 Amendment 39-13060 (68 FR
9504, February 28, 2003), and adding the following new Airworthiness
Directive (AD):
AGUSTA S.p.A. (Agusta): Docket No. FAA-2013-0146; Directorate
Identifier 2012-SW-060-AD.
(a) Applicability
This AD applies to Agusta Model 109E helicopters with tail rotor
(T/R) hub and blade assembly, part number (P/N) 109-8131-02-151 and
P/N 109-8131-02-157, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a fatigue crack in a T/R
blade. This condition could result in failure of the T/R blade and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2002-25-51, Docket No. 2002-SW-55-AD,
Amendment 39-13060 (68 FR 9504, February 28, 2003).
(d) Reserved
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Before each start of the helicopter engines, visually check
both sides of each T/R blade for a crack in the inspection area
depicted in Figure 1 to paragraph (f) of this AD. This action 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 43.9
(a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained
as required by 14 CFR 91.173, 121.380, or 135.439.
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(2) For helicopters with T/R hub and blade assembly, P/N 109-
8131-02-151 (consisting of two T/R blades, P/N 109-8132-01-111, and
one T/R hub and grip assembly, P/N 109-8131-02-127), before further
flight, modify each T/R hub and blade assembly by installing a new
bushing, P/N 109-8131-30-109, in each grip assembly and two zero-
hour time-in-service (TIS) T/R blades, P/N 109-8132-01-111; re-
identifying the hub and grip assembly as P/N 109-8131-02-159; and
re-identifying the T/R hub and blade assembly as P/N 109-8131-02-157
in accordance with the Compliance Instructions, Part V, paragraphs
2. through 13., of Agusta Bollettino Tecnico No. 109EP-30, Revision
C, dated September 29, 2006 (BT). A T/R blade, P/N 109-8132-01-111,
which has been operated as part of T/R hub and blade assembly, P/N
109-8131-02-151, must be retired regardless of TIS and may not be
used as part of the T/R hub and blade assembly, P/N 109-8131-02-157.
Returning the removed T/R blades, grips, or bushings to Agusta is
not required.
(3) For helicopters with T/R hub and blade assembly, P/N 109-
8131-02-157 (consisting of two T/R blades, P/N 109-8132-01-111, and
one T/R hub and grip assembly, P/N 109-8131-02-159), within 25 hours
TIS, and thereafter at intervals not to exceed 25 hours TIS, and
before further flight any time there is an increase in vibration
levels, using a 5x or higher power magnifying glass, visually
inspect each T/R blade for a crack in accordance with the Compliance
Instructions, Part III, paragraphs 1. through 5. of the BT.
Reporting to Agusta is not required.
(4) On or before accumulating 200 hours TIS on the T/R hub and
grip assembly, P/N
[[Page 12655]]
109-8131-02-159, and thereafter at intervals not to exceed 200 hours
TIS, inspect the linings and measure the internal diameter of the
bushings, P/N 109-8131-30-109, by referring to Figure 2 of the BT.
If the internal diameter of the bushing exceeds 41.35 millimeters,
replace the bushing.
(5) If there is a crack in a T/R blade, before further flight,
replace the cracked T/R blade.
(6) Revise the Airworthiness Limitations section of the
maintenance manual to reflect that a T/R blade, P/N 109-8132-01-111,
which has not been operated as part of T/R hub and blade assembly,
P/N 109-8131-02-151, has retirement life of 1,000 hours TIS.
(g) Special Flight Permit
Special flight permits will not be issued.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Sharon Miles, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas, 76137; telephone (817) 222-
5110; email sharon.y.miles@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.
(i) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency AD No. 2007-0010, dated January 31, 2007.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor
Blades.
Issued in Fort Worth, Texas, on February 11, 2013.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013-04220 Filed 2-22-13; 8:45 am]
BILLING CODE 4910-13-P
