Airworthiness Directives; Various Restricted Category Helicopters, 47531-47534 [2013-18570]
Download as PDF
<![CDATA[
Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
(g) Maintenance Program Revision
Within 30 days after the effective date of
this AD, revise the maintenance program to
incorporate Tasks C27–50–111–15 and C27–
50–111–17 of Bombardier CL–600–2B19
Temporary Revision (TR) 2A–48, dated July
6, 2012, to Appendix A—Certification
Maintenance Requirements, of Part 2,
Airworthiness Requirements, of the
Bombardier CL–600–2B19 Maintenance
Requirements Manual (MRM), except as
specified in paragraph (j) of this AD. The
initial compliance times for the tasks are
specified in paragraph (h) of this AD.
Note 1 to paragraph (g) of this AD: The
maintenance program revision required by
paragraph (g) of this AD may be done by
inserting a copy of Bombardier CL–600–2B19
TR 2A–48, dated July 6, 2012, into Appendix
A—Certification Maintenance Requirements,
of Part 2, Airworthiness Requirements, of the
Bombardier CL–600–2B19 MRM. When this
TR has been included in general revisions of
the MRM, the general revisions may be
inserted in the MRM, provided the relevant
information in the general revision is
identical to that in Bombardier CL–600–2B19
TR 2A–48, dated July 6, 2012.
(h) Initial Task Compliance Times
tkelley on DSK3SPTVN1PROD with RULES
For the inboard and outboard flap actuators
identified in Bombardier CL–600–2B19 TR
2A–48, dated July 6, 2012, to Appendix A—
Certification Maintenance Requirements, of
Part 2, Airworthiness Requirements, of the
Bombardier CL–600–2B19 MRM, the initial
compliance times for the tasks specified in
Bombardier CL–600–2B19 TR 2A–48, dated
July 6, 2012, are the applicable times
specified in paragraphs (h)(1) through (h)(4)
of this AD.
(1) For flap actuators that have
accumulated less than 6,000 flight cycles as
of the effective date of this AD, before the
accumulation of 10,000 flight cycles on the
flap actuator.
(2) For flap actuators that have
accumulated 6,000 or more flight cycles but
less than 10,000 flight cycles as of the
effective date of this AD, within 4,000 flight
cycles after the effective date of this AD, but
no later than 12,000 flight cycles on the flap
actuator.
(3) For flap actuators that have
accumulated 10,000 or more flight cycles but
less than or equal to 12,000 flight cycles as
of the effective date of this AD, within 2,000
flight cycles after the effective date of this
AD, but no later than 13,000 flight cycles on
the flap actuator.
(4) For flap actuators that have
accumulated more than 12,000 flight cycles
as of the effective date of this AD, within
1,000 flight cycles after the effective date of
this AD.
(i) Repetitive Compliance Time
Where Bombardier CL–600–2B19 TR 2A–
48, dated July 6, 2012, to Appendix A—
Certification Maintenance Requirements, of
Part 2, Airworthiness Requirements, of the
Bombardier CL–600–2B19 MRM, specifies a
task interval of 10,000 flight cycles or 144
months, the task interval is 10,000 flight
cycles.
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
(j) No Alternative Actions and Intervals
After accomplishing the revision required
by paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (k) of this
AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the ACO, send it to Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
(516) 228–7300; fax (516) 794–5531. Before
using any approved AMOC, notify your
appropriate principal inspector, or lacking a
principal inspector, the manager of the local
flight standards district office/certificate
holding district office. The AMOC approval
letter must specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information Canadian
Airworthiness Directive CF–2012–26, dated
October 30, 2012, for related information,
which can be found in the AD docket on the
internet at https://www.regulations.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Bombardier CL–600–2B19 Temporary
Revision 2A–48, dated July 6, 2012, to
Appendix A—Certification Maintenance
Requirements, of Part 2, Airworthiness
Requirements, of the Bombardier CL–600–
2B19 Maintenance Requirements Manual.
(ii) Reserved.
(3) For service information identified in
ˆ
this AD, Bombardier, Inc., 400 Cote-Vertu
´
Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
47531
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 12,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–18488 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0564; Directorate
Identifier 2010–SW–013–AD; Amendment
39–17494; AD 2013–13–06]
RIN 2120–AA64
Airworthiness Directives; Various
Restricted Category Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Arrow
Falcon Exporters, Inc. (previously Utah
State University); Firefly Aviation
Helicopter Services (previously
Erickson Air-Crane Co.); California
Department of Forestry; Garlick
Helicopters, Inc.; Global Helicopter
Technology, Inc.; Hagglund Helicopters,
LLC (previously Western International
Aviation, Inc.); International
Helicopters, Inc.; Precision Helicopters,
LLC; Robinson Air Crane, Inc.; San
Joaquin Helicopters (previously
Hawkins and Powers Aviation, Inc.);
S.M.&T. Aircraft (previously US
Helicopters, Inc., UNC Helicopter, Inc.,
Southern Aero Corporation, and Wilco
Aviation); Smith Helicopters; Southern
Helicopter, Inc.; Southwest Florida
Aviation International, Inc. (previously
Jamie R. Hill and Southwest Florida
Aviation); Tamarack Helicopters, Inc.
(previously Ranger Helicopter Services,
Inc.); US Helicopter, Inc. (previously
UNC Helicopter, Inc.); West Coast
Fabrication; and Williams Helicopter
Corporation (previously Scott Paper Co.)
Model HH–1K, TH–1F, TH–1L, UH–1A,
UH–1B, UH–1E, UH–1F, UH–1H, UH–
1L, and UH–1P Helicopters; and
Southwest Florida Aviation Model UH–
SUMMARY:
E:\FR\FM\06AUR1.SGM
06AUR1
47532
Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
1B (SW204 and SW204HP) and UH–1H
(SW205) Helicopters. This AD requires
creating a component history card or
equivalent record for each main rotor
grip (grip); determining and recording
the total hours time-in-service (TIS) for
each grip; visually inspecting the upper
and lower tangs of the grip for a crack;
inspecting the grip buffer pads for
delamination and if delamination is
present, inspecting the grip surface for
corrosion or other damage; inspecting
the grip for a crack using ultrasonic (UT)
and fluorescent penetrant inspection
methods; and establishing a retirement
life for certain grips. This AD was
prompted by three in-flight failures of
grips installed on Bell Helicopter
Textron (Bell) Model 212 helicopters,
which resulted from cracks originating
in the lower main rotor blade bolt lug.
The actions are intended to prevent
failure of the grip, separation of a main
rotor blade, and subsequent loss of
control of the helicopter.
DATES: This AD is effective September
10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of September 10, 2013.
ADDRESSES: For service information
identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, TX 76101; telephone (817)
280–3391; fax (817) 280–6466; or at
https://www.bellcustomer.com/files/.
You may review a copy of the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas
76137.
tkelley on DSK3SPTVN1PROD with RULES
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 AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Michael Kohner, Aviation Safety
Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
76137; telephone (817) 222–5170; email
7-avs-asw-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 8, 2010, at 75 FR 39192, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 to
include an AD that would apply to
Arrow Falcon Exporters, Inc.
(previously Utah State University);
Firefly Aviation Helicopter Services
(previously Erickson Air-Crane Co.);
California Department of Forestry;
Garlick Helicopters, Inc.; Global
Helicopter Technology, Inc.; Hagglund
Helicopters, LLC (previously Western
International Aviation, Inc.);
International Helicopters, Inc.; Precision
Helicopters, LLC; Robinson Air Crane,
Inc.; San Joaquin Helicopters
(previously Hawkins and Powers
Aviation, Inc.); S.M.&T. Aircraft
(previously US Helicopters, Inc., UNC
Helicopter, Inc., Southern Aero
Corporation, and Wilco Aviation);
Smith Helicopters; Southern Helicopter,
Inc.; Southwest Florida Aviation
International, Inc. (previously Jamie R.
Hill and Southwest Florida Aviation);
Tamarack Helicopters, Inc. (previously
Ranger Helicopter Services, Inc.); US
Helicopter, Inc. (previously UNC
Helicopter, Inc.); West Coast
Fabrication; and Williams Helicopter
Corporation (previously Scott Paper Co.)
Model HH–1K, TH–1F, TH–1L, UH–1A,
UH–1B, UH–1E, UH–1F, UH–1H, UH–
1L, and UH–1P Helicopters; and
Southwest Florida Aviation Model UH–
1B (SW204 and SW204HP) and UH–1H
(SW205) Helicopters with certain grips
installed. The NPRM proposed to
require creating a component history
card or equivalent record for each grip;
determining and recording the total
hours TIS for each grip; visually
inspecting the upper and lower tangs of
the grip for a crack; inspecting the grip
buffer pads for delamination and if
delamination is present, inspecting the
grip surface for corrosion or other
damage; inspecting the grip for a crack
using UT and fluorescent penetrant
inspection methods; and establishing a
retirement life for certain grips. The
NPRM was prompted by reports of three
in-flight failures of grips, P/N 204–011–
121–009 and 204–011–121–121,
installed on Bell Model 212 helicopters.
The failures resulted from cracks
originating in the lower blade bolt lug.
The cracking was attributed to
subsurface fatigue, corrosion and
mechanical damage. Grips with these
same P/Ns are eligible for installation on
certain restricted category helicopters.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Grips, P/N 204–044–121–005 and 204–
044–121–113, are also affected if they
were ever installed on a Model 205B or
UH–1N helicopter. The proposed
requirements were intended to prevent
failure of the grip, separation of a main
rotor blade, and subsequent loss of
control of the helicopter.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (75 FR 39192, July 8, 2010).
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other products of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed except for we are
incorporating the figure by reference
instead of including it in our AD and
other minor changes to meet current
publication requirements. These
changes are consistent with the intent of
the proposals in the NPRM (75 FR
39192, July 8, 2010) and will not
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
We estimate that this AD will affect
20 helicopters of U.S. registry and that
labor costs will average $85 per workhour. Based on these estimates, we
expect the following costs:
• Creating new component history
cards or the equivalent will require two
work-hours for a labor cost of $170 per
helicopter, $3,400 for the U.S. fleet.
• Maintaining records will require
five work-hours per year for a labor cost
of $425.
• Conducting 24 visual inspections
using a magnifying glass will require 12
work-hours per year for a labor cost of
$1,020.
• 1⁄2 of a buffer pad inspection: 1.5
hours per year for a labor cost of $128.
• 1⁄4 of a fluorescent penetrant
inspection: .5 work hour per year for a
labor cost of $43.
• 4 UT inspections: 4 work hours per
year for a labor cost of $340.
• Removing and replacing a grip set
will require 20 work hours per year. A
set of grips will cost $37,590, for total
cost of $39,290 per helicopter.
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
E:\FR\FM\06AUR1.SGM
06AUR1
Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska 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 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
47533
the FAA amends 14 CFR part 39 as
follows:
This condition could result in failure of a
grip, separation of a main rotor blade, and
subsequent loss of control of the helicopter.
PART 39—AIRWORTHINESS
DIRECTIVES
(c) Effective Date
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 adding
the following new airworthiness
directive (AD):
■
2013–13–06 Various Restricted Category
Helicopters: Amendment 39–17494;
Docket No. FAA–2010–0564; Directorate
Identifier 2010–SW–013–AD.
(a) Applicability
This AD applies to Arrow Falcon
Exporters, Inc. (previously Utah State
University); Firefly Aviation Helicopter
Services (previously Erickson Air-Crane Co.);
California Department of Forestry; Garlick
Helicopters, Inc.; Global Helicopter
Technology, Inc.; Hagglund Helicopters, LLC
(previously Western International Aviation,
Inc.); International Helicopters, Inc.;
Precision Helicopters, LLC; Robinson Air
Crane, Inc.; San Joaquin Helicopters
(previously Hawkins and Powers Aviation,
Inc.); S.M.&T. Aircraft (previously US
Helicopters, Inc., UNC Helicopter, Inc.,
Southern Aero Corporation, and Wilco
Aviation); Smith Helicopters; Southern
Helicopter, Inc.; Southwest Florida Aviation
International, Inc. (previously Jamie R. Hill
and Southwest Florida Aviation); Tamarack
Helicopters, Inc. (previously Ranger
Helicopter Services, Inc.); US Helicopter, Inc.
(previously UNC Helicopter, Inc.); West
Coast Fabrication; and Williams Helicopter
Corporation (previously Scott Paper Co.)
Model HH–1K, TH–1F, TH–1L, UH–1A, UH–
1B, UH–1E, UH–1F, UH–1H, UH–1L, and
UH–1P Helicopters; and Southwest Florida
Aviation Model UH–1B (SW204 and
SW204HP) and UH–1H (SW205) Helicopters
with main rotor grip (grip) part number (P/
N) 204–011–121–009, 204–011–121–121, or
ASI–4011–121–9, installed, or with grip P/N
204–011–121–005 or 204–011–121–113, if
the grip was ever installed on a Model 205B
or a Model UH–1N helicopter, or P/N 204–
011–121–117, installed, if the grip was ever
installed on a Model 205B helicopter,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the lower main rotor blade bolt lug.
This AD becomes effective September 10,
2013.
(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) Within 10 hours time-in-service (TIS),
create a component history card or
equivalent record and determine and record
the total hours TIS for each grip. If the total
hours TIS cannot be determined from the
helicopter records, assume and record 50
hours TIS for each month for which the
hours cannot be determined with the grip
installed on any helicopter. Continue to
count and record the hours TIS and begin to
count and record the number of times the
helicopter engine(s) are started (engine start/
stop cycles).
(2) Within 10 hours TIS, and then at
intervals not to exceed 25 hours TIS, without
removing the main rotor blades:
(i) Clean the exposed surfaces of the upper
and lower tangs of each grip with denatured
alcohol and wipe dry.
(ii) Using a 10X or higher magnifying glass,
visually inspect the exposed surfaces of the
upper and lower tangs of each grip for a
crack. Pay particular attention to the lower
surface of each lower grip tang from the main
rotor blade bolt-bushing flange to the leading
and trailing edge of each grip tang as
depicted in Figure 5–7, Inspection of Main
Rotor Hub Grip (1200 Hours), Revision 9,
dated August 8, 2008, of Chapter 5,
Inspections and Component Overhaul
Schedule, Revision 11, dated April 30, 2010,
of Bell Helicopter Textron, Inc. (BHTI), BHT–
212–MM–1, Revision 13, dated September
16, 2010.
(iii) At the intervals shown in Table 1 to
Paragraph (e) of this AD, ultrasonic (UT)
inspect each grip for a crack in accordance
with the BHTI Nondestructive Inspection
Procedure, Log No. 00–340, Revision E, dated
April 9, 2002. The UT inspection of the grip
must be performed by a Nondestructive
Testing (NDT) UT Level I Special, Level II,
or Level III inspector who is qualified under
the guidelines established by MIL–STD–
410E, ATA Specification 105, AIA–NAS–410,
or an FAA-accepted equivalent for
qualification standards of NDT Inspection/
Evaluation Personnel.
tkelley on DSK3SPTVN1PROD with RULES
TABLE 1 TO PARAGRAPH (e)
Within 30 days,
for a grip with
the following or
more hours TIS:
UT inspect grip, P/N
204–011–121–009 or ASI–4011–121–9 ..........................................................................
204–011–121–121 ...........................................................................................................
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
Thereafter, at intervals not to exceed the following number of hours
TIS or the engine start/stop cycles,
whichever occurs first:
Hours TIS
4,000
500
E:\FR\FM\06AUR1.SGM
400
150
06AUR1
Engine start/stop
cycles
1,600
600
47534
Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
TABLE 1 TO PARAGRAPH (e)—Continued
UT inspect grip, P/N
tkelley on DSK3SPTVN1PROD with RULES
204–011–121–005 or –113, if the grip was EVER installed on a Model 205B or Model
UH–1N helicopter .........................................................................................................
204–011–121–117, if the grip was EVER installed on a Model 205B helicopter ...........
(3) At intervals not to exceed 1,200 hours
TIS or 24 months, whichever occurs first:
(i) Remove each main rotor blade, and
(ii) Inspect each grip buffer pad on the
inner surfaces of each grip tang for
delamination as depicted in Figure 5–7,
Inspection of Main Rotor Hub Grip (1200
Hours), Revision 9, dated August 8, 2008, of
Chapter 5, Inspections and Component
Overhaul Schedule, Revision 11, dated April
30, 2010, of Bell Helicopter Textron, Inc.,
BHT–212–MM–1, Revision 13, dated
September 16, 2010. If there is any
delamination, remove the buffer pad and
inspect the grip surface for corrosion or other
damage.
(4) Within 2,400 hours TIS or at the next
overhaul of the main rotor hub, whichever
occurs first, and then at intervals not to
exceed 2,400 hours TIS:
(i) Remove each main rotor blade.
(ii) Remove each grip buffer pad (if
installed) from the inner surfaces of each grip
tang.
(iii) Visually inspect the grip surfaces for
corrosion or other damage.
(iv) Fluorescent-penetrant inspect (FPI) the
grip for a crack, paying particular attention
to the upper and lower grip tangs. When
inspecting a grip, P/N 204–011–121–005,
204–011–121–009, or 204–011–121–113, or
ASI–4011–121–9, pay particular attention to
the leading and trailing edges of the grip
barrel.
(5) Before further flight:
(i) Replace any cracked grip with an
airworthy grip.
(ii) Replace any grip with any corrosion or
other damage with an airworthy grip, or
repair the grip if the corrosion or other
damage is within the maximum repair
limitations.
(iii) Remove any grip, P/N 204–011–121–
009 or ASI–4011–121–9, that has been in
service for 15,000 or more hours TIS.
(iv) Remove any grip, P/N 204–011–121–
121, that has been in service for 25,000 or
more hours TIS.
(6) Revise the Airworthiness Limitations
section of the applicable maintenance
manual or the Instructions for Continued
Airworthiness (ICA) by establishing a new
retirement life of 15,000 hours TIS for grip,
P/N 204–011–121–009 or ASI–4011–121–9,
and 25,000 hours TIS for grip, P/N 204–011–
121–121, by marking pen and ink changes or
inserting a copy of this AD into the
maintenance manual or ICA.
(7) Record a 15,000 hour TIS life limit for
each grip, P/N 204–011–121–009 or ASI–
4011–121–9, and a 25,000 hour life limit for
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
each grip, P/N 204–011–121–121, on the
applicable component history card or
equivalent record.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, Rotorcraft
Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5170;
email 7-avs-asw-170@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.
(g) Additional Information
BHTI Alert Service Bulletin (ASB) 212–94–
92, Revision A, dated March 13, 1995; BHTI
Operations Safety Notice (OSN) 204–85–6,
OSN 205–85–9, and OSN 212–85–13, all
dated November 14, 1985 and co-published
as one document; BHTI ASB 205B–02–39,
Revision B, dated November 22, 2002; and
BHTI ASB 212–02–116, Revision A, dated
October 30, 2002, which are not incorporated
by reference, contain additional information
about the subject of this AD.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6220, Main rotor head.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Bell Helicopter Textron, Inc.
Nondestructive Inspection Procedure, Log
No. 00–340, Revision E, dated April 9, 2002.
(ii) Figure 5–7, Inspection of Main Rotor
Hub Grip (1200 Hours), Revision 9, dated
August 8, 2008, of Chapter 5, Inspections and
Component Overhaul Schedule, Revision 11,
dated April 30, 2010, of Bell Helicopter
Textron, Inc., BHT–212–MM–1, Revision 13,
dated September 16, 2010.
(3) For BHTI service information identified
in this AD, contact Bell Helicopter Textron,
PO 00000
Thereafter, at intervals not to exceed the following number of hours
TIS or the engine start/stop cycles,
whichever occurs first:
Within 30 days,
for a grip with
the following or
more hours TIS:
Frm 00008
Fmt 4700
Sfmt 4700
Hours TIS
4,000
500
Engine start/stop
cycles
400
150
1,600
600
Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280–3391; fax (817) 280–
6466; or at https://www.bellcustomer.com/
files/.
(4) You may review a copy of this service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(5) You may also review a copy of this
service information at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on June 18,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–18570 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0447; Directorate
Identifier 2013–NE–17–AD; Amendment 39–
17536; AD 2013–15–20]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
emergency airworthiness directive (AD)
2013–14–51 for General Electric
Company (GE) GE90–110B1 and GE90–
115B turbofan engines with affected
transfer gearbox assembly (TGB) radial
gearshafts installed. AD 2013–14–51
was sent previously to all known U.S.
owners and operators of GE90–110B1
and GE90–115B turbofan engines. AD
2013–14–51 prohibited operation of an
airplane if more than one installed
engine has an affected TGB radial
SUMMARY:
E:\FR\FM\06AUR1.SGM
06AUR1
]]>Agencies
[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47531-47534]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18570]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0564; Directorate Identifier 2010-SW-013-AD;
Amendment 39-17494; AD 2013-13-06]
RIN 2120-AA64
Airworthiness Directives; Various Restricted Category Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Arrow
Falcon Exporters, Inc. (previously Utah State University); Firefly
Aviation Helicopter Services (previously Erickson Air-Crane Co.);
California Department of Forestry; Garlick Helicopters, Inc.; Global
Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously
Western International Aviation, Inc.); International Helicopters, Inc.;
Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin
Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T.
Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc.,
Southern Aero Corporation, and Wilco Aviation); Smith Helicopters;
Southern Helicopter, Inc.; Southwest Florida Aviation International,
Inc. (previously Jamie R. Hill and Southwest Florida Aviation);
Tamarack Helicopters, Inc. (previously Ranger Helicopter Services,
Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West
Coast Fabrication; and Williams Helicopter Corporation (previously
Scott Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F,
UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation
Model UH-
[[Page 47532]]
1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters. This AD requires
creating a component history card or equivalent record for each main
rotor grip (grip); determining and recording the total hours time-in-
service (TIS) for each grip; visually inspecting the upper and lower
tangs of the grip for a crack; inspecting the grip buffer pads for
delamination and if delamination is present, inspecting the grip
surface for corrosion or other damage; inspecting the grip for a crack
using ultrasonic (UT) and fluorescent penetrant inspection methods; and
establishing a retirement life for certain grips. This AD was prompted
by three in-flight failures of grips installed on Bell Helicopter
Textron (Bell) Model 212 helicopters, which resulted from cracks
originating in the lower main rotor blade bolt lug. The actions are
intended to prevent failure of the grip, separation of a main rotor
blade, and subsequent loss of control of the helicopter.
DATES: This AD is effective September 10, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of September 10,
2013.
ADDRESSES: For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone
(817) 280-3391; fax (817) 280-6466; or at https://www.bellcustomer.com/files/. You may review a copy of the referenced service information at
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
Examining the AD Docket
You may examine the AD docket on the Internet at 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 AD, any incorporated-by-reference
service information, the economic evaluation, any comments received,
and other information. The street address for the Docket Operations
Office (phone: 800-647-5527) is U.S. Department of Transportation,
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170;
email 7-avs-asw-170@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 8, 2010, at 75 FR 39192, the Federal Register published our
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR
part 39 to include an AD that would apply to Arrow Falcon Exporters,
Inc. (previously Utah State University); Firefly Aviation Helicopter
Services (previously Erickson Air-Crane Co.); California Department of
Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology,
Inc.; Hagglund Helicopters, LLC (previously Western International
Aviation, Inc.); International Helicopters, Inc.; Precision
Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters
(previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft
(previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero
Corporation, and Wilco Aviation); Smith Helicopters; Southern
Helicopter, Inc.; Southwest Florida Aviation International, Inc.
(previously Jamie R. Hill and Southwest Florida Aviation); Tamarack
Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US
Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast
Fabrication; and Williams Helicopter Corporation (previously Scott
Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-
1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation Model
UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters with certain
grips installed. The NPRM proposed to require creating a component
history card or equivalent record for each grip; determining and
recording the total hours TIS for each grip; visually inspecting the
upper and lower tangs of the grip for a crack; inspecting the grip
buffer pads for delamination and if delamination is present, inspecting
the grip surface for corrosion or other damage; inspecting the grip for
a crack using UT and fluorescent penetrant inspection methods; and
establishing a retirement life for certain grips. The NPRM was prompted
by reports of three in-flight failures of grips, P/N 204-011-121-009
and 204-011-121-121, installed on Bell Model 212 helicopters. The
failures resulted from cracks originating in the lower blade bolt lug.
The cracking was attributed to subsurface fatigue, corrosion and
mechanical damage. Grips with these same P/Ns are eligible for
installation on certain restricted category helicopters. Grips, P/N
204-044-121-005 and 204-044-121-113, are also affected if they were
ever installed on a Model 205B or UH-1N helicopter. The proposed
requirements were intended to prevent failure of the grip, separation
of a main rotor blade, and subsequent loss of control of the
helicopter.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (75 FR 39192,
July 8, 2010).
FAA's Determination
We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
products of these same type designs and that air safety and the public
interest require adopting the AD requirements as proposed except for we
are incorporating the figure by reference instead of including it in
our AD and other minor changes to meet current publication
requirements. These changes are consistent with the intent of the
proposals in the NPRM (75 FR 39192, July 8, 2010) and will not increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 20 helicopters of U.S.
registry and that labor costs will average $85 per work-hour. Based on
these estimates, we expect the following costs:
Creating new component history cards or the equivalent
will require two work-hours for a labor cost of $170 per helicopter,
$3,400 for the U.S. fleet.
Maintaining records will require five work-hours per year
for a labor cost of $425.
Conducting 24 visual inspections using a magnifying glass
will require 12 work-hours per year for a labor cost of $1,020.
\1/2\ of a buffer pad inspection: 1.5 hours per year for a
labor cost of $128.
\1/4\ of a fluorescent penetrant inspection: .5 work hour
per year for a labor cost of $43.
4 UT inspections: 4 work hours per year for a labor cost
of $340.
Removing and replacing a grip set will require 20 work
hours per year. A set of grips will cost $37,590, for total cost of
$39,290 per helicopter.
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
[[Page 47533]]
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska 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 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2013-13-06 Various Restricted Category Helicopters: Amendment 39-
17494; Docket No. FAA-2010-0564; Directorate Identifier 2010-SW-013-
AD.
(a) Applicability
This AD applies to Arrow Falcon Exporters, Inc. (previously Utah
State University); Firefly Aviation Helicopter Services (previously
Erickson Air-Crane Co.); California Department of Forestry; Garlick
Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund
Helicopters, LLC (previously Western International Aviation, Inc.);
International Helicopters, Inc.; Precision Helicopters, LLC;
Robinson Air Crane, Inc.; San Joaquin Helicopters (previously
Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US
Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation,
and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.;
Southwest Florida Aviation International, Inc. (previously Jamie R.
Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc.
(previously Ranger Helicopter Services, Inc.); US Helicopter, Inc.
(previously UNC Helicopter, Inc.); West Coast Fabrication; and
Williams Helicopter Corporation (previously Scott Paper Co.) Model
HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and
UH-1P Helicopters; and Southwest Florida Aviation Model UH-1B (SW204
and SW204HP) and UH-1H (SW205) Helicopters with main rotor grip
(grip) part number (P/N) 204-011-121-009, 204-011-121-121, or ASI-
4011-121-9, installed, or with grip P/N 204-011-121-005 or 204-011-
121-113, if the grip was ever installed on a Model 205B or a Model
UH-1N helicopter, or P/N 204-011-121-117, installed, if the grip was
ever installed on a Model 205B helicopter, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the lower
main rotor blade bolt lug. This condition could result in failure of
a grip, separation of a main rotor blade, and subsequent loss of
control of the helicopter.
(c) Effective Date
This AD becomes effective September 10, 2013.
(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) Within 10 hours time-in-service (TIS), create a component
history card or equivalent record and determine and record the total
hours TIS for each grip. If the total hours TIS cannot be determined
from the helicopter records, assume and record 50 hours TIS for each
month for which the hours cannot be determined with the grip
installed on any helicopter. Continue to count and record the hours
TIS and begin to count and record the number of times the helicopter
engine(s) are started (engine start/stop cycles).
(2) Within 10 hours TIS, and then at intervals not to exceed 25
hours TIS, without removing the main rotor blades:
(i) Clean the exposed surfaces of the upper and lower tangs of
each grip with denatured alcohol and wipe dry.
(ii) Using a 10X or higher magnifying glass, visually inspect
the exposed surfaces of the upper and lower tangs of each grip for a
crack. Pay particular attention to the lower surface of each lower
grip tang from the main rotor blade bolt-bushing flange to the
leading and trailing edge of each grip tang as depicted in Figure 5-
7, Inspection of Main Rotor Hub Grip (1200 Hours), Revision 9, dated
August 8, 2008, of Chapter 5, Inspections and Component Overhaul
Schedule, Revision 11, dated April 30, 2010, of Bell Helicopter
Textron, Inc. (BHTI), BHT-212-MM-1, Revision 13, dated September 16,
2010.
(iii) At the intervals shown in Table 1 to Paragraph (e) of this
AD, ultrasonic (UT) inspect each grip for a crack in accordance with
the BHTI Nondestructive Inspection Procedure, Log No. 00-340,
Revision E, dated April 9, 2002. The UT inspection of the grip must
be performed by a Nondestructive Testing (NDT) UT Level I Special,
Level II, or Level III inspector who is qualified under the
guidelines established by MIL-STD-410E, ATA Specification 105, AIA-
NAS-410, or an FAA-accepted equivalent for qualification standards
of NDT Inspection/Evaluation Personnel.
Table 1 to Paragraph (e)
----------------------------------------------------------------------------------------------------------------
Thereafter, at intervals not to
exceed the following number of
Within 30 days, hours TIS or the engine start/stop
UT inspect grip, P/N for a grip with cycles, whichever occurs first:
the following or -----------------------------------
more hours TIS: Engine start/
Hours TIS stop cycles
----------------------------------------------------------------------------------------------------------------
204-011-121-009 or ASI-4011-121-9......................... 4,000 400 1,600
204-011-121-121........................................... 500 150 600
[[Page 47534]]
204-011-121-005 or -113, if the grip was EVER installed on 4,000 400 1,600
a Model 205B or Model UH-1N helicopter...................
204-011-121-117, if the grip was EVER installed on a Model 500 150 600
205B helicopter..........................................
----------------------------------------------------------------------------------------------------------------
(3) At intervals not to exceed 1,200 hours TIS or 24 months,
whichever occurs first:
(i) Remove each main rotor blade, and
(ii) Inspect each grip buffer pad on the inner surfaces of each
grip tang for delamination as depicted in Figure 5-7, Inspection of
Main Rotor Hub Grip (1200 Hours), Revision 9, dated August 8, 2008,
of Chapter 5, Inspections and Component Overhaul Schedule, Revision
11, dated April 30, 2010, of Bell Helicopter Textron, Inc., BHT-212-
MM-1, Revision 13, dated September 16, 2010. If there is any
delamination, remove the buffer pad and inspect the grip surface for
corrosion or other damage.
(4) Within 2,400 hours TIS or at the next overhaul of the main
rotor hub, whichever occurs first, and then at intervals not to
exceed 2,400 hours TIS:
(i) Remove each main rotor blade.
(ii) Remove each grip buffer pad (if installed) from the inner
surfaces of each grip tang.
(iii) Visually inspect the grip surfaces for corrosion or other
damage.
(iv) Fluorescent-penetrant inspect (FPI) the grip for a crack,
paying particular attention to the upper and lower grip tangs. When
inspecting a grip, P/N 204-011-121-005, 204-011-121-009, or 204-011-
121-113, or ASI-4011-121-9, pay particular attention to the leading
and trailing edges of the grip barrel.
(5) Before further flight:
(i) Replace any cracked grip with an airworthy grip.
(ii) Replace any grip with any corrosion or other damage with an
airworthy grip, or repair the grip if the corrosion or other damage
is within the maximum repair limitations.
(iii) Remove any grip, P/N 204-011-121-009 or ASI-4011-121-9,
that has been in service for 15,000 or more hours TIS.
(iv) Remove any grip, P/N 204-011-121-121, that has been in
service for 25,000 or more hours TIS.
(6) Revise the Airworthiness Limitations section of the
applicable maintenance manual or the Instructions for Continued
Airworthiness (ICA) by establishing a new retirement life of 15,000
hours TIS for grip, P/N 204-011-121-009 or ASI-4011-121-9, and
25,000 hours TIS for grip, P/N 204-011-121-121, by marking pen and
ink changes or inserting a copy of this AD into the maintenance
manual or ICA.
(7) Record a 15,000 hour TIS life limit for each grip, P/N 204-
011-121-009 or ASI-4011-121-9, and a 25,000 hour life limit for each
grip, P/N 204-011-121-121, on the applicable component history card
or equivalent record.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222-5170; email 7-avs-asw-170@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.
(g) Additional Information
BHTI Alert Service Bulletin (ASB) 212-94-92, Revision A, dated
March 13, 1995; BHTI Operations Safety Notice (OSN) 204-85-6, OSN
205-85-9, and OSN 212-85-13, all dated November 14, 1985 and co-
published as one document; BHTI ASB 205B-02-39, Revision B, dated
November 22, 2002; and BHTI ASB 212-02-116, Revision A, dated
October 30, 2002, which are not incorporated by reference, contain
additional information about the subject of this AD.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6220, Main rotor
head.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Bell Helicopter Textron, Inc. Nondestructive Inspection
Procedure, Log No. 00-340, Revision E, dated April 9, 2002.
(ii) Figure 5-7, Inspection of Main Rotor Hub Grip (1200 Hours),
Revision 9, dated August 8, 2008, of Chapter 5, Inspections and
Component Overhaul Schedule, Revision 11, dated April 30, 2010, of
Bell Helicopter Textron, Inc., BHT-212-MM-1, Revision 13, dated
September 16, 2010.
(3) For BHTI service information identified in this AD, contact
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280-3391; fax (817) 280-6466; or at https://www.bellcustomer.com/files/.
(4) You may review a copy of this service information at the
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
(5) You may also review a copy of this service information at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call (202)
741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on June 18, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18570 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P
