Airworthiness Directives; Bell Helicopter Textron Canada Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters, 60203-60205 [05-20677]
Download as PDF
<![CDATA[
60203
Rules and Regulations
Federal Register
Vol. 70, No. 199
Monday, October 17, 2005
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21680; Directorate
Identifier 2004–SW–48–AD; Amendment 39–
14341; AD 2005–21–03]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Model
206A, A–1, B, B–1, L, L–1, L–3, L–4
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for the
specified Bell Helicopter Textron
Canada (BHTC) model helicopters that
requires, before the first flight of each
day, checking the tail rotor blade (blade)
root doublers (doublers) for an edge
void or de-bond on both sides of each
blade, and if an edge void or de-bond is
found, replacing the unairworthy blade
with an airworthy blade. This AD also
requires replacing any affected serialnumbered blade with an airworthy
blade. This amendment is prompted by
reports of de-bond of the doublers due
to inadequate surface preparation
resulting in poor adherence of the
doublers. The actions specified by this
AD are intended to prevent loss of a
blade, loss of tail rotor control, and
subsequent loss of control of the
helicopter.
Effective November 21, 2005.
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.
DATES:
ADDRESSES:
VerDate Aug<31>2005
14:06 Oct 14, 2005
Jkt 208001
Examining the Docket
You may examine the docket that
contains this AD, any comments, and
other information on the Internet at
https://dms.dot.gov, or at the Docket
Management System (DMS), U.S.
Department of Transportation, 400
Seventh Street, SW., Room PL–401, on
the plaza level of the Nassif Building,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: A
proposal to amend 14 CFR part 39 to
include an AD for the specified BHTC
model helicopters was published in the
Federal Register on June 28, 2005 (70
FR 37060). That action proposed to
require, before the first flight of each
day, checking the blade doublers for an
edge void or de-bond on both sides of
each blade, and if an edge void or debond is found, replacing the
unairworthy blade with an airworthy
blade. Also, that action proposed to
require replacing any affected serialnumbered blade with an airworthy
blade.
Transport Canada, the airworthiness
authority for Canada, notified the FAA
that an unsafe condition may exist on
Model 206A, B, and L series helicopters.
Transport Canada advises that an
inadequate surface preparation on a
limited number of blades resulted in
two reported instances of blade root
doubler de-bond. They also advise that
to ensure blade integrity all suspected
blades are to be checked daily until
removed from service.
BHTC has issued Alert Service
Bulletin Nos. 206–04–101 and 206L–04–
131, both dated September 13, 2004,
which specify a daily check of the
doubler area to verify integrity of the
doubler by a pilot as part of the daily
pre-flight check. The service bulletins
also specify a retirement from service of
affected blades, which constitutes
terminating action. Transport Canada
classified these service bulletins as
mandatory and issued AD No. CF–
2004–25, dated November 23, 2004, to
ensure the continued airworthiness of
these helicopters in Canada.
These helicopter models are now
manufactured in Canada and are type
certificated for operation in the United
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, Transport Canada
has kept the FAA informed of the
situation described above. The FAA has
examined the findings of Transport
Canada, reviewed all available
information, and determined that AD
action is necessary for products of these
type designs that are certificated for
operation in the United States.
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. No
comments were received on the
proposal or the FAA’s determination of
the cost to the public. The FAA has
determined that air safety and the
public interest require the adoption of
the rule as proposed.
The FAA estimates that this AD will
affect 2,194 helicopters of U.S. registry.
The required actions will:
• Take about 1⁄4 work hour to do a
daily check for blade edge voids and debonds; and
• Take about 4 work hours to replace
a blade at an average labor rate of $65
per work hour.
• Cost about $5,848 for a replacement
blade.
Based on these figures, we estimate
the total cost impact of the AD on U.S.
operators to be $201,058, assuming 26
blades are affected and replaced and
assuming 100 daily checks are done.
Regulatory Findings
We have 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.
For the reasons discussed above, I
certify that the 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); 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
E:\FR\FM\17OCR1.SGM
17OCR1
Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Rules and Regulations
this AD. See the DMS to examine the
economic evaluation.
products identified in this rulemaking
action.
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
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
Air transportation, Aircraft, Aviation
safety, Safety.
BILLING CODE 4910–13–C
(b) If an edge void or a de-bond is found,
before further flight, replace the blade with
an airworthy blade with a serial number
other than those to which this AD applies.
(c) Within 100 hours time-in-service,
replace all affected, serial-numbered blades
with airworthy blades with a serial number
other than those to which this AD applies.
Note 1: Bell Helicopter Textron Alert
Service Bulletin Nos. 206–04–101 and 206L–
04–131, both dated September 13, 2004,
pertain to the subject of this AD.
VerDate Aug<31>2005
14:06 Oct 14, 2005
Jkt 208001
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.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
(d) Replacing an affected, serial-numbered
blade with an airworthy blade without an
affected serial number contained in the
applicability section of this AD constitutes
terminating action for the requirements of
this AD for that blade.
(e) 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 Safety Management Group,
Rotorcraft Directorate, FAA, for information
about previously approved alternative
methods of compliance.
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
2005–21–03 Bell Helicopter Textron
Canada: Amendment 39–14341. Docket
No. FAA–2005–21680; Directorate
Identifier 2004–SW–48–AD.
Applicability: Model 206A, A–1, B, B–1, L,
L–1, L–3, L–4 helicopters, with tail rotor
blade (blade), part number (P/N) 206–016–
201–131, serial numbers with a prefix of
‘‘CS’’ and 4820 through 4845, installed,
certificated in any category.
Compliance: Required as indicated, unless
accomplished previously.
To prevent loss of a blade, loss of tail rotor
control, and subsequent loss of control of the
helicopter, accomplish the following:
(a) Before the first flight of each day, clean
each blade and visually check the blade root
doublers for an edge void or de-bond on both
sides of each blade as depicted in Figure 1
of this AD. An owner/operator (pilot),
holding at least a private pilot certificate,
may perform this visual check and must
enter compliance with this paragraph into
the helicopter maintenance records by
following 14 CFR sections 43.11 and
91.417(a)(2)(v).
BILLING CODE 4910–13–P
(f) Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the helicopter to a location where
the blade may be replaced provided that no
doubler edge void or de-bond is found during
any check or inspection.
(g) This amendment becomes effective on
November 21, 2005.
Note 2: The subject of this AD is addressed
in Transport Canada, Canada AD No. CF–
2004–25, dated November 23, 2004.
E:\FR\FM\17OCR1.SGM
17OCR1
ER17OC05.000</GPH>
60204
Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 / Rules and Regulations
Issued in Fort Worth, Texas, on October 7,
2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 05–20677 Filed 10–14–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21725; Directorate
Identifier 2004–SW–45–AD; Amendment 39–
14342; AD 2005–21–04]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Model 47D1, 47G,
47G–2, 47G–2A, 47G–2A–1, 47G–3,
47G–3B, 47G–3B–1, 47G–3B–2, 47G–
3B–2A, 47G–4, 47G–4A, 47G–5, 47G–
5A and Coastal Helicopters, Inc. Model
OH–13H (Tomcat Mark 5A, 6B, 6C)
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for
Bell Helicopter Textron (Bell) Model
47D1, 47G, 47G–2, 47G–2A, 47G–2A–1,
47G–3, 47G–3B, 47G–3B–1, 47G–3B–2,
47G–3B–2A, 47G–4, 47G–4A, 47G–5,
47G–5A and Coastal Helicopters, Inc.
Model OH–13H (Tomcat Mark 5A, 6B,
6C) helicopters that have a certain
scissors assembly or weld assembly
scissors bracket installed. The AD
requires, within 60 days, determining
and recording the total hours time-inservice (TIS) for each Parts
Manufacturer Approval (PMA)produced scissors assembly and weld
assembly scissors bracket and
establishes a life limit for each affected
part. This amendment is prompted by
the need to establish a life limit on
scissors assemblies and weld assembly
scissors brackets produced under PMA
No. PQ808SW or installed per
Supplemental Type Certificate (STC)
No. SH2772SW. The actions specified
by this AD are intended to establish a
life limit to prevent using a scissors
assembly or weld assembly scissors
bracket past it’s life limit, which could
result in failure of the part and
subsequent loss of control of the
helicopter.
Effective November 21, 2005.
You may get the service
information identified in this AD from
Texas Helicopter Co., Inc., P.O. Box
DATES:
ADDRESSES:
VerDate Aug<31>2005
14:06 Oct 14, 2005
Jkt 208001
177686, Irving, Texas 75017, phone
(972) 399–1045, fax (972) 790–6397.
Examining the Docket
You may examine the docket that
contains this AD, any comments, and
other information on the Internet at
https://dms.dot.gov, or at the Docket
Management System (DMS), U.S.
Department of Transportation, 400
Seventh Street, SW., Room PL–401, on
the plaza level of the Nassif Building,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Marc Belhumeur, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Rotorcraft Certification Office, Fort
Worth, Texas 76193–0170, telephone
(817) 222–5177, fax (817) 222–5783.
SUPPLEMENTARY INFORMATION: A
proposal to amend 14 CFR part 39 to
include an AD for the specified model
helicopters was published in the
Federal Register on July 6, 2005 (70 FR
38817). That action proposed to require,
within 60 days, determining and
recording the total hours TIS for each
PMA-produced scissors assembly and
weld assembly scissors bracket and
establishing a life limit for each affected
part.
We have reviewed Texas Helicopter
Co., Inc. (THC) Service Bulletin No. SB
003, dated December 1, 2002. THC
holds STC No. SH2772SW and produces
parts under PMA No. PQ808SW. That
service bulletin was issued to clarify
maintenance inspections and retirement
schedules. The service bulletin specifies
maintaining Bell Model 47 series and all
other helicopters utilizing a 74–150–
259–1M or 74–150–259–3M control
installation per STC SH2772SW or 74–
150–117–13M scissors bracket weld
assembly as PMA replacement, in
accordance with THC Instructions For
Continued Airworthiness (ICA), Doc.
No. THC 2002–22 Rev. 0, dated
December 1, 2002. Those ICAs refer to
STC SH2772SW and contain the
mandatory retirement times for the
scissor assembly and weld assembly
scissors bracket in the Airworthiness
Limitations section.
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. No
comments were received on the
proposal or the FAA’s determination of
the cost to the public. The FAA has
determined that air safety and the
public interest require the adoption of
the rule as proposed.
Based on the manufacturer’s
production estimate, this AD will affect
350 helicopters of U.S. registry.
Determining and recording the initial
hours TIS of each scissors assembly will
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
60205
take 1 hour, replacing a scissors
assembly will take 2 hours, and
replacing a weld assembly scissors
bracket will take 8 hours. The average
labor rate is $65 per work hour.
Required parts will cost approximately
$1,300 for the 2 scissors assemblies
required per helicopter and $2,500 for
each weld assembly scissors bracket
required per helicopter. Based on these
figures, the total cost impact of the AD
on U.S. operators is $1,580,250,
assuming all operators determine and
record the hours TIS once, and replace
the scissors assembly and weld
assembly scissors bracket once.
Regulatory Findings
We have 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.
For the reasons discussed above, I
certify that the 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); 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. See the DMS to examine the
economic evaluation.
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.
E:\FR\FM\17OCR1.SGM
17OCR1
]]>Agencies
[Federal Register Volume 70, Number 199 (Monday, October 17, 2005)]
[Rules and Regulations]
[Pages 60203-60205]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20677]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 70, No. 199 / Monday, October 17, 2005 /
Rules and Regulations
[[Page 60203]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21680; Directorate Identifier 2004-SW-48-AD;
Amendment 39-14341; AD 2005-21-03]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the specified Bell Helicopter Textron Canada (BHTC) model helicopters
that requires, before the first flight of each day, checking the tail
rotor blade (blade) root doublers (doublers) for an edge void or de-
bond on both sides of each blade, and if an edge void or de-bond is
found, replacing the unairworthy blade with an airworthy blade. This AD
also requires replacing any affected serial-numbered blade with an
airworthy blade. This amendment is prompted by reports of de-bond of
the doublers due to inadequate surface preparation resulting in poor
adherence of the doublers. The actions specified by this AD are
intended to prevent loss of a blade, loss of tail rotor control, and
subsequent loss of control of the helicopter.
DATES: Effective November 21, 2005.
ADDRESSES: 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 Docket
You may examine the docket that contains this AD, any comments, and
other information on the Internet at https://dms.dot.gov, or at the
Docket Management System (DMS), U.S. Department of Transportation, 400
Seventh Street, SW., Room PL-401, on the plaza level of the Nassif
Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for the specified BHTC model helicopters was published in
the Federal Register on June 28, 2005 (70 FR 37060). That action
proposed to require, before the first flight of each day, checking the
blade doublers for an edge void or de-bond on both sides of each blade,
and if an edge void or de-bond is found, replacing the unairworthy
blade with an airworthy blade. Also, that action proposed to require
replacing any affected serial-numbered blade with an airworthy blade.
Transport Canada, the airworthiness authority for Canada, notified
the FAA that an unsafe condition may exist on Model 206A, B, and L
series helicopters. Transport Canada advises that an inadequate surface
preparation on a limited number of blades resulted in two reported
instances of blade root doubler de-bond. They also advise that to
ensure blade integrity all suspected blades are to be checked daily
until removed from service.
BHTC has issued Alert Service Bulletin Nos. 206-04-101 and 206L-04-
131, both dated September 13, 2004, which specify a daily check of the
doubler area to verify integrity of the doubler by a pilot as part of
the daily pre-flight check. The service bulletins also specify a
retirement from service of affected blades, which constitutes
terminating action. Transport Canada classified these service bulletins
as mandatory and issued AD No. CF-2004-25, dated November 23, 2004, to
ensure the continued airworthiness of these helicopters in Canada.
These helicopter models are now manufactured in Canada and are type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, Transport Canada has kept the FAA
informed of the situation described above. The FAA has examined the
findings of Transport Canada, reviewed all available information, and
determined that AD action is necessary for products of these type
designs that are certificated for operation in the United States.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
The FAA estimates that this AD will affect 2,194 helicopters of
U.S. registry. The required actions will:
Take about \1/4\ work hour to do a daily check for blade
edge voids and de-bonds; and
Take about 4 work hours to replace a blade at an average
labor rate of $65 per work hour.
Cost about $5,848 for a replacement blade.
Based on these figures, we estimate the total cost impact of the AD
on U.S. operators to be $201,058, assuming 26 blades are affected and
replaced and assuming 100 daily checks are done.
Regulatory Findings
We have 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.
For the reasons discussed above, I certify that the 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); 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
[[Page 60204]]
this AD. See the DMS to examine the economic evaluation.
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, 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 adding a new airworthiness directive to
read as follows:
2005-21-03 Bell Helicopter Textron Canada: Amendment 39-14341.
Docket No. FAA-2005-21680; Directorate Identifier 2004-SW-48-AD.
Applicability: Model 206A, A-1, B, B-1, L, L-1, L-3, L-4
helicopters, with tail rotor blade (blade), part number (P/N) 206-
016-201-131, serial numbers with a prefix of ``CS'' and 4820 through
4845, installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of a blade, loss of tail rotor control, and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Before the first flight of each day, clean each blade and
visually check the blade root doublers for an edge void or de-bond
on both sides of each blade as depicted in Figure 1 of this AD. An
owner/operator (pilot), holding at least a private pilot
certificate, may perform this visual check and must enter compliance
with this paragraph into the helicopter maintenance records by
following 14 CFR sections 43.11 and 91.417(a)(2)(v).
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR17OC05.000
BILLING CODE 4910-13-C
(b) If an edge void or a de-bond is found, before further
flight, replace the blade with an airworthy blade with a serial
number other than those to which this AD applies.
(c) Within 100 hours time-in-service, replace all affected,
serial-numbered blades with airworthy blades with a serial number
other than those to which this AD applies.
Note 1: Bell Helicopter Textron Alert Service Bulletin Nos. 206-
04-101 and 206L-04-131, both dated September 13, 2004, pertain to
the subject of this AD.
(d) Replacing an affected, serial-numbered blade with an
airworthy blade without an affected serial number contained in the
applicability section of this AD constitutes terminating action for
the requirements of this AD for that blade.
(e) 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 Safety Management Group, Rotorcraft Directorate, FAA,
for information about previously approved alternative methods of
compliance.
(f) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the helicopter to a location where
the blade may be replaced provided that no doubler edge void or de-
bond is found during any check or inspection.
(g) This amendment becomes effective on November 21, 2005.
Note 2: The subject of this AD is addressed in Transport Canada,
Canada AD No. CF-2004-25, dated November 23, 2004.
[[Page 60205]]
Issued in Fort Worth, Texas, on October 7, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-20677 Filed 10-14-05; 8:45 am]
BILLING CODE 4910-13-P
