Airworthiness Directives; Bell Helicopter Textron Canada Model 222, 222B, 222U, 230, and 430 Helicopters, 52777-52778 [E8-20979]
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Federal Register / Vol. 73, No. 177 / Thursday, September 11, 2008 / Rules and Regulations
Reduction Act of 1995 (44 U.S.C. 3501
et seq.).
List of Subjects in 9 CFR Part 77
Animal diseases, Bison, Cattle,
Reporting and recordkeeping
requirements, Transportation,
Tuberculosis.
I Accordingly, we are amending 9 CFR
part 77 as follows:
PART 77—TUBERCULOSIS
1. The authority citation for part 77
continues to read as follows:
I
Authority: 7 U.S.C. 8301–8317; 7 CFR 2.22,
2.80, and 371.4.
§ 77.7
[Amended]
2. Section 77.7, paragraph (b), is
amended by removing the paragraph
number ‘‘(1)’’ and by removing
paragraph (b)(2).
I
§ 77.9
[Amended]
3. Section 77.9 is amended as follows:
a. In paragraph (a), by removing the
word ‘‘None’’ and adding the words
‘‘New Mexico’’ in its place.
I b. In paragraph (b), by removing the
paragraph number ‘‘(1)’’ and by
removing paragraph (b)(2).
I
I
Done in Washington, DC, this 5th day of
September 2008.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E8–21117 Filed 9–10–08; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0449; Directorate
Identifier 2007–SW–10–AD; Amendment 39–
15669; AD 2008–19–02]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Model 222,
222B, 222U, 230, and 430 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
rmajette on PRODPC74 with RULES
AGENCY:
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
Bell Helicopter Textron Canada (Bell)
Model 222, 222B, 222U, 230, and 430
helicopters. That AD currently requires
visually inspecting the main rotor
hydraulic actuator support (support) to
verify the presence of all dowel pins
and sealant between the support and
VerDate Aug<31>2005
13:31 Sep 10, 2008
Jkt 214001
transmission and verifying the proper
torque of each attaching nut (nut). This
AD requires the same actions as the
existing AD and also requires repetitive
actions at intervals not to exceed 600
hours time-in-service (TIS) or 12
months, whichever occurs first. This AD
is prompted by the discovery that a 12month compliance requirement was
correctly included in an Emergency AD
(EAD) that we issued but was
inadvertently omitted when we
published the Final rule; request for
comments following the issuance of the
EAD. The actions specified by this AD
are intended to prevent failure of the
support and subsequent loss of control
of the helicopter.
DATES: Effective October 16, 2008.
The incorporation by reference of Bell
Helicopter Textron Alert Service
Bulletin Nos. 222–00–86, 222U–00–57,
230–00–18, and 430–00–17, all dated
May 19, 2000, was approved previously
for incorporation by reference by the
Director of the Federal Register on
March 2, 2001 (66 FR 10361, February
15, 2001).
ADDRESSES: You may examine the AD
docket on the Internet at https://
regulations.gov or in person at the
Docket Operations office, U.S.
Department of Transportation, M–30,
West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC between 9 a.m. and 5
p.m. Monday through Friday, except
Federal holidays.
You may get the service information
identified in this AD from Bell
Helicopter Textron Canada, 12,800 Rue
de l’Avenir, Mirabel, Quebec J7J1R4,
telephone (450) 437–2862 or (800) 363–
8023, fax (450) 433–0272.
Examining the AD Docket: The AD
docket contains the Notice of proposed
rulemaking (NPRM), the economic
evaluation, any comments received, and
other information. The street address
and operating hours for the Docket
Operations office (telephone (800) 647–
5527) are in the ADDRESSES section of
this AD. Comments will be available in
the AD docket shortly after they are
received.
FOR FURTHER INFORMATION CONTACT:
Tyrone Millard, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft
Standards Staff, Fort Worth, Texas
76193–0110, telephone (817) 222–5439,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: On
January 5, 2001, we issued EAD 2001–
01–51 for Bell Model 222, 222B, 222U,
230, and 430 helicopters which
requires, at specified time intervals,
visually inspecting the support for the
presence of all dowel pins and sealant
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
52777
between the support and transmission
and verifying the proper torque of each
nut. That action was prompted by the
failure of a support resulting in an
accident of a Bell Model 222U
helicopter. All retaining studs and shear
pins were found sheared or pulled out
at the junction between the support and
transmission case. The requirements of
that EAD are intended to prevent failure
of the support and subsequent loss of
control of the helicopter.
On February 2, 2001, we issued AD
2001–01–51, Amendment 39–12105,
Docket No. 2000–SW–54–AD as a Final
rule; request for comments (66 FR
10361, February 15, 2001). Since issuing
that AD, we discovered that we
inadvertently omitted the phrase ‘‘or 12
months, whichever occurs first,’’ from
compliance paragraph (a) of the
published final rule AD. Because the
two versions of AD 2001–01–51 have
different compliance times, we issued
an NPRM on April 14, 2008 (73 FR
21853, April 23, 2008) proposing to
supersede AD 2001–01–51 and require
the following:
• Within 25 hours TIS, and thereafter
at intervals not to exceed 600 hours TIS
or 12 months, whichever occurs first:
• Visually inspecting the support
and, if any pin is missing or if there is
no sealant visible, further inspecting the
support, the transmission case, studs,
and dowel pins and repairing or
replacing any unairworthy part before
further flight;
• Verifying the torque of the nuts and,
depending on the location and number
of loose nuts, before further flight:
• Removing the support and further
inspecting the support, transmission
case, studs, and dowel pins and
repairing or replacing any unairworthy
part; and
• Retorqueing certain nuts;
• At not less than 20 hours TIS nor
more than 30 hours TIS after reinstalling
a support for any reason, verifying the
torque of the nuts.
By publishing the NPRM, we gave the
public an opportunity to participate in
developing this AD. However, we
received no comment on the NPRM or
on our determination of the cost to the
public. Therefore, based on our review
and evaluation of the available data, we
have determined that air safety and the
public interest require adopting the AD
as proposed.
We have reviewed Bell Alert Service
Bulletin Nos. 222–00–86, 222U–00–57,
230–00–18, and 430–00–17, all dated
May 19, 2000 (ASB’s), which specify,
within 25 hours TIS, conducting a onetime inspection of the support
installation by accomplishing a torque
check of the support attaching nuts. In
E:\FR\FM\11SER1.SGM
11SER1
52778
Federal Register / Vol. 73, No. 177 / Thursday, September 11, 2008 / Rules and Regulations
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 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.
Therefore, I certify this AD:
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); and
3. 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.
rmajette on PRODPC74 with RULES
addition, a revision to the maintenance
manual will introduce a recurring
torque check of the nuts. Transport
Canada classified these ASB’s as
mandatory and issued AD No. CF–
2000–29, dated September 6, 2000, to
ensure the continued airworthiness of
these helicopters in Canada.
We estimate that this AD will affect
145 helicopters of U.S. registry. It will
take approximately 1⁄2 work hour per
helicopter to inspect for proper torque,
and the average labor rate is $80 per
work hour. The cost for the inspection
is estimated to be $5,800. Assuming 15
helicopters require removing the
support for additional inspections, it
will take approximately 6 additional
work hours at $80 per work hour and
$50 for parts at an additional total cost
of $7,950. Based on these figures, we
estimate the total cost impact of this AD
on U.S. operators to be $13,750,
assuming no supports are replaced.
§ 39.13
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
VerDate Aug<31>2005
13:31 Sep 10, 2008
Jkt 214001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. Section 39.13 is amended by
removing Amendment 39–12105 (66 FR
10361, February 15, 2001), and by
adding a new airworthiness directive
(AD), Amendment 39–15669, to read as
follows:
I
2008–19–02 Bell Helicopter Textron
Canada: Amendment 39–15669, Docket
No. FAA–2008–0449; Directorate
Identifier 2007–SW–10–AD. Supersedes
AD 2001–01–51, Amendment 39–12105,
Docket No. 2000–SW–54–AD.
Applicability: Model 222, 222B, 222U, 230,
and 430 helicopters, with a main rotor
hydraulic actuator support (support), part
number (P/N) 222–040–125–001, installed,
certificated in any category.
Compliance: Required as indicated, unless
accomplished previously.
To prevent failure of the support and
subsequent loss of control of the helicopter,
accomplish the following:
(a) Within 25 hours time-in-service (TIS)
and thereafter at intervals not to exceed 600
hours TIS or 12 months, whichever occurs
first, accomplish the following:
(1) Visually inspect the support for the
presence of all dowel pins and for sealant
between the support and transmission. If any
pin is missing, or if no sealant is visible,
before further flight, remove the support and
further inspect the support, transmission
case, studs, and dowel pins in accordance
with the Accomplishment Instructions,
paragraphs 5 through 7, of the applicable Bell
Helicopter Textron Alert Service Bulletin
Nos. 222–00–86, 222U–00–57, 230–00–18, or
430–00–17, all dated May 19, 2000 (ASB’s).
Repair or replace any unairworthy support,
transmission case, stud, or dowel pin before
further flight.
(2) Verify the torque of the support
attaching nuts (nuts). Upper nuts must not
rotate at a torque less than 40 in-lbs. Lower
nuts must not rotate at a torque less than 90
in-lbs.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
(i) If two or more upper nuts rotate at a
torque less than 40 in-lbs. or two or more
lower nuts rotate at a torque less than 90 inlbs., before further flight, remove the support
and further inspect the support, transmission
case, studs, and dowel pins in accordance
with the Accomplishment Instructions,
paragraph 5 through 7, of the applicable
ASB’s. Repair or replace any unairworthy
support, transmission case, stud, or dowel
pin before further flight.
(ii) If less than two upper nuts rotate at a
torque less than 40 in-lbs. or less than two
lower nuts rotate at a torque less than 90 inlbs., before further flight, retorque the upper
nut to 50 to 70 in-lbs. plus tare and the lower
nut to 100 to 140 in-lbs. plus tare.
(b) At not less than 20 hours TIS nor more
than 30 hours TIS after reinstalling a support
for any reason, verify the torque of the nuts
in accordance with paragraph (a)(2) of this
AD.
(c) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Rotorcraft
Standards Staff, FAA, ATTN: Tyrone Millard,
telephone (817) 222–5439, fax (817) 222–
5961, for information about previously
approved alternative methods of compliance.
(d) You must use the specified portions of
Bell Helicopter Textron Alert Service
Bulletin Nos. 222–00–86, 222U–00–57, 230–
00–18, or 430–00–17, all dated May 19, 2000,
to do the required inspections.
(1) The Director of the Federal Register
previously approved the incorporation by
reference of these service bulletins on March
2, 2001 (66 FR 10361, February 15, 2001).
(2) For service information identified in
this AD, contact Bell Helicopter Textron
Canada, 12,800 Rue de l’Avenir, Mirabel,
Quebec J7J1R4, telephone (450) 437–2862 or
(800) 363–8023, fax (450) 433–0272.
(3) You may review copies at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas; or 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.
(e) This amendment becomes effective on
October 16, 2008.
Note: The subject of this AD is addressed
in Transport Canada (Canada) AD CF–2000–
29, dated September 6, 2000.
Issued in Fort Worth, Texas, on August 13,
2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–20979 Filed 9–10–08; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\11SER1.SGM
11SER1
]]>Agencies
[Federal Register Volume 73, Number 177 (Thursday, September 11, 2008)]
[Rules and Regulations]
[Pages 52777-52778]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-20979]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0449; Directorate Identifier 2007-SW-10-AD;
Amendment 39-15669; AD 2008-19-02]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
222, 222B, 222U, 230, and 430 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for Bell Helicopter Textron Canada (Bell) Model 222, 222B, 222U, 230,
and 430 helicopters. That AD currently requires visually inspecting the
main rotor hydraulic actuator support (support) to verify the presence
of all dowel pins and sealant between the support and transmission and
verifying the proper torque of each attaching nut (nut). This AD
requires the same actions as the existing AD and also requires
repetitive actions at intervals not to exceed 600 hours time-in-service
(TIS) or 12 months, whichever occurs first. This AD is prompted by the
discovery that a 12-month compliance requirement was correctly included
in an Emergency AD (EAD) that we issued but was inadvertently omitted
when we published the Final rule; request for comments following the
issuance of the EAD. The actions specified by this AD are intended to
prevent failure of the support and subsequent loss of control of the
helicopter.
DATES: Effective October 16, 2008.
The incorporation by reference of Bell Helicopter Textron Alert
Service Bulletin Nos. 222-00-86, 222U-00-57, 230-00-18, and 430-00-17,
all dated May 19, 2000, was approved previously for incorporation by
reference by the Director of the Federal Register on March 2, 2001 (66
FR 10361, February 15, 2001).
ADDRESSES: You may examine the AD docket on the Internet at https://
regulations.gov or in person at the Docket Operations office, U.S.
Department of Transportation, M-30, West Building Ground Floor, Room
W12-140, 1200 New Jersey Avenue, SE., Washington, DC between 9 a.m. and
5 p.m. Monday through Friday, except Federal holidays.
You may get the service information identified in this AD from Bell
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272.
Examining the AD Docket: The AD docket contains the Notice of
proposed rulemaking (NPRM), the economic evaluation, any comments
received, and other information. The street address and operating hours
for the Docket Operations office (telephone (800) 647-5527) are in the
ADDRESSES section of this AD. Comments will be available in the AD
docket shortly after they are received.
FOR FURTHER INFORMATION CONTACT: Tyrone Millard, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth,
Texas 76193-0110, telephone (817) 222-5439, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: On January 5, 2001, we issued EAD 2001-01-51
for Bell Model 222, 222B, 222U, 230, and 430 helicopters which
requires, at specified time intervals, visually inspecting the support
for the presence of all dowel pins and sealant between the support and
transmission and verifying the proper torque of each nut. That action
was prompted by the failure of a support resulting in an accident of a
Bell Model 222U helicopter. All retaining studs and shear pins were
found sheared or pulled out at the junction between the support and
transmission case. The requirements of that EAD are intended to prevent
failure of the support and subsequent loss of control of the
helicopter.
On February 2, 2001, we issued AD 2001-01-51, Amendment 39-12105,
Docket No. 2000-SW-54-AD as a Final rule; request for comments (66 FR
10361, February 15, 2001). Since issuing that AD, we discovered that we
inadvertently omitted the phrase ``or 12 months, whichever occurs
first,'' from compliance paragraph (a) of the published final rule AD.
Because the two versions of AD 2001-01-51 have different compliance
times, we issued an NPRM on April 14, 2008 (73 FR 21853, April 23,
2008) proposing to supersede AD 2001-01-51 and require the following:
Within 25 hours TIS, and thereafter at intervals not to
exceed 600 hours TIS or 12 months, whichever occurs first:
Visually inspecting the support and, if any pin is missing
or if there is no sealant visible, further inspecting the support, the
transmission case, studs, and dowel pins and repairing or replacing any
unairworthy part before further flight;
Verifying the torque of the nuts and, depending on the
location and number of loose nuts, before further flight:
Removing the support and further inspecting the support,
transmission case, studs, and dowel pins and repairing or replacing any
unairworthy part; and
Retorqueing certain nuts;
At not less than 20 hours TIS nor more than 30 hours TIS
after reinstalling a support for any reason, verifying the torque of
the nuts.
By publishing the NPRM, we gave the public an opportunity to
participate in developing this AD. However, we received no comment on
the NPRM or on our determination of the cost to the public. Therefore,
based on our review and evaluation of the available data, we have
determined that air safety and the public interest require adopting the
AD as proposed.
We have reviewed Bell Alert Service Bulletin Nos. 222-00-86, 222U-
00-57, 230-00-18, and 430-00-17, all dated May 19, 2000 (ASB's), which
specify, within 25 hours TIS, conducting a one-time inspection of the
support installation by accomplishing a torque check of the support
attaching nuts. In
[[Page 52778]]
addition, a revision to the maintenance manual will introduce a
recurring torque check of the nuts. Transport Canada classified these
ASB's as mandatory and issued AD No. CF-2000-29, dated September 6,
2000, to ensure the continued airworthiness of these helicopters in
Canada.
We estimate that this AD will affect 145 helicopters of U.S.
registry. It will take approximately \1/2\ work hour per helicopter to
inspect for proper torque, and the average labor rate is $80 per work
hour. The cost for the inspection is estimated to be $5,800. Assuming
15 helicopters require removing the support for additional inspections,
it will take approximately 6 additional work hours at $80 per work hour
and $50 for parts at an additional total cost of $7,950. Based on these
figures, we estimate the total cost impact of this AD on U.S. operators
to be $13,750, assuming no supports are replaced.
Regulatory Findings
We determined that 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.
Therefore, I certify this AD:
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); and
3. 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.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-12105 (66 FR
10361, February 15, 2001), and by adding a new airworthiness directive
(AD), Amendment 39-15669, to read as follows:
2008-19-02 Bell Helicopter Textron Canada: Amendment 39-15669,
Docket No. FAA-2008-0449; Directorate Identifier 2007-SW-10-AD.
Supersedes AD 2001-01-51, Amendment 39-12105, Docket No. 2000-SW-54-
AD.
Applicability: Model 222, 222B, 222U, 230, and 430 helicopters,
with a main rotor hydraulic actuator support (support), part number
(P/N) 222-040-125-001, installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the support and subsequent loss of control
of the helicopter, accomplish the following:
(a) Within 25 hours time-in-service (TIS) and thereafter at
intervals not to exceed 600 hours TIS or 12 months, whichever occurs
first, accomplish the following:
(1) Visually inspect the support for the presence of all dowel
pins and for sealant between the support and transmission. If any
pin is missing, or if no sealant is visible, before further flight,
remove the support and further inspect the support, transmission
case, studs, and dowel pins in accordance with the Accomplishment
Instructions, paragraphs 5 through 7, of the applicable Bell
Helicopter Textron Alert Service Bulletin Nos. 222-00-86, 222U-00-
57, 230-00-18, or 430-00-17, all dated May 19, 2000 (ASB's). Repair
or replace any unairworthy support, transmission case, stud, or
dowel pin before further flight.
(2) Verify the torque of the support attaching nuts (nuts).
Upper nuts must not rotate at a torque less than 40 in-lbs. Lower
nuts must not rotate at a torque less than 90 in-lbs.
(i) If two or more upper nuts rotate at a torque less than 40
in-lbs. or two or more lower nuts rotate at a torque less than 90
in-lbs., before further flight, remove the support and further
inspect the support, transmission case, studs, and dowel pins in
accordance with the Accomplishment Instructions, paragraph 5 through
7, of the applicable ASB's. Repair or replace any unairworthy
support, transmission case, stud, or dowel pin before further
flight.
(ii) If less than two upper nuts rotate at a torque less than 40
in-lbs. or less than two lower nuts rotate at a torque less than 90
in-lbs., before further flight, retorque the upper nut to 50 to 70
in-lbs. plus tare and the lower nut to 100 to 140 in-lbs. plus tare.
(b) At not less than 20 hours TIS nor more than 30 hours TIS
after reinstalling a support for any reason, verify the torque of
the nuts in accordance with paragraph (a)(2) of this AD.
(c) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Rotorcraft Standards Staff, FAA, ATTN: Tyrone
Millard, telephone (817) 222-5439, fax (817) 222-5961, for
information about previously approved alternative methods of
compliance.
(d) You must use the specified portions of Bell Helicopter
Textron Alert Service Bulletin Nos. 222-00-86, 222U-00-57, 230-00-
18, or 430-00-17, all dated May 19, 2000, to do the required
inspections.
(1) The Director of the Federal Register previously approved the
incorporation by reference of these service bulletins on March 2,
2001 (66 FR 10361, February 15, 2001).
(2) For service information identified in this AD, contact Bell
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-
0272.
(3) You may review copies at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas; or 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.
(e) This amendment becomes effective on October 16, 2008.
Note: The subject of this AD is addressed in Transport Canada
(Canada) AD CF-2000-29, dated September 6, 2000.
Issued in Fort Worth, Texas, on August 13, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-20979 Filed 9-10-08; 8:45 am]
BILLING CODE 4910-13-P
