Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) Model 430 Helicopters, 44140-44142 [E8-17275]
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44140
Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations
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 AD docket 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, 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.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
rwilkins on PROD1PC63 with RULES
2008–15–03 MD Helicopters, Inc. (MDHI):
Amendment 39–15615. Docket No.
FAA–2008–0287; Directorate Identifier
2006–SW–15–AD.
Applicability: Model 369A, OH–6A, 369D,
369E, 369F, 369FF, 369H, 369HE, 369HM,
and 369HS, certificated in any category, with
a tail rotor (T/R) blade installed as follows
including all serial numbers and those T/R
blades with an ‘‘M’’ or an ‘‘I’’ painted on the
T/R blade root:
VerDate Aug<31>2005
16:51 Jul 29, 2008
Jkt 214001
• Helicopter Technology Company, LLC
(HTC) part number (P/N) 500P3100–101 and
–103, or MDHI P/N 369D21640–501, –503,
and –505.
• HTC P/N 500P3100–301 and –303, or
MDHI P/N 369D21641–501, –503, and –505.
• HTC P/N 500P3300–501 and –503, or
MDHI P/N 369D21643–501, –503, and –505.
• HTC P/N 500P3500–701 and –703, or
MDHI P/N 369D21642–501, –503, and –505.
Note 1: An ‘‘M’’ or an ‘‘I’’ painted on the
root of the T/R blade indicates compliance to
an Alternate Method of Compliance (AMOC)
to Emergency AD 2003–08–51 (Docket No.
2003–SW–17–AD, Amendment 39–13215,
April 15, 2003), issued by the FAA, Los
Angeles Aircraft Certification Office
(LAACO) on June 13, 2003 to HTC. The
AMOC addressed shot peening of the pitch
horn of the T/R assembly.
Compliance: Required as indicated.
To prevent disbonding and subsequent
separation of an abrasion strip from a T/R
blade, which could result in vibration, loss
of the T/R, and subsequent loss of control of
the helicopter, accomplish the following:
(a) Within 25 hours time-in-service (TIS),
unless accomplished previously, and
thereafter at intervals not to exceed 25 hours
TIS, inspect the abrasion strip-to-skin bond
integrity on each T/R blade using a tap test
method in accordance with Part 1—
Inspection, in Helicopter Technology
Company, LLC (HTC) Mandatory Service
Bulletin Notice No. 3100–4R4, dated May 10,
2006 (SB).
Note 2: MD Helicopters Service Bulletin
SB369D–203R1, SB369E–097R1, SB369F–
082R1, and SB369H–246R1, dated January
23, 2006, pertain to the subject of this AD.
(b) Modifying each T/R blade in
accordance with FAA-approved data by
installing a titanium rivet at the outboard end
and painting the letter ‘‘T’’ on the root-end
of the T/R blade to indicate the modification
has been accomplished is considered a
terminating action for the requirements 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, Los Angeles
Aircraft Certification Office, FAA, ATTN:
John Cecil, Aviation Safety Engineer, 3960
Paramount Blvd., Lakewood, California
90712–4137, telephone (562) 627–5228, fax
(562) 627–5210, for information about
previously approved alternative methods of
compliance.
(d) Special flight permits will not be
issued.
(e) The inspection shall be done in
accordance with the specified portions of
Helicopter Technology Company, LLC (HTC)
Mandatory Service Bulletin Notice No. 3100–
4R4, dated May 10, 2006. The Director of the
Federal Register approved this incorporation
by reference in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Copies may be
obtained from HTC, 12902 South Broadway,
Los Angeles, California, 90061, telephone
(310) 523–2750, fax (310) 523–2745, or on the
Internet at https://www.helicoptertech.com.
Copies may be inspected at the FAA, Office
of the Regional Counsel, Southwest Region,
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
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/
code_of_federal_regulations/ibr_locations.
html.
(f) This amendment becomes effective on
September 3, 2008.
Issued in Fort Worth, Texas, on June 25,
2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. E8–17274 Filed 7–29–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0177; Directorate
Identifier 2007–SW–19–AD; Amendment
39–15616; AD 2008–15–04]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada (BHTC)
Model 430 Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for BHTC
Model 430 helicopters. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The aviation authority of
Canada, with which we have a bilateral
agreement, states in the MCAI: ‘‘It has
been determined that the existing
rigging procedures for the tail rotor
pitch change mechanism have to be
changed due to possibility of parts
interference.’’ The cumulative effect of
individual part tolerances resulting in
the total assemblage of those parts being
out of tolerance could result in the tail
rotor yoke striking another part other
than the flapping stop (parts
interference) cited in the MCAI. Also,
the misalignment of the tail rotor
counterweight bellcrank may result in
higher tail rotor pedal forces and a
higher pilot workload after failure of the
#1 hydraulic system. Both parts
interference and the misaligned
counterweight bellcrank create an
unsafe condition. This AD require
actions that are intended to address
these unsafe conditions.
E:\FR\FM\30JYR1.SGM
30JYR1
Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations
This AD becomes effective on
September 3, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 3, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.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–
5227) 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, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Rotorcraft Standards Staff, Fort Worth,
Texas 76193–0111, telephone (817)
222–5439, fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
rwilkins on PROD1PC63 with RULES
DATES:
Discussion
We issued an NPRM to amend 14 CFR
part 39 to include an AD that would
apply to BHTC Model 430 helicopters,
serial numbers 49001 through 49122, on
November 2, 2007. That NPRM was
published in the Federal Register on
November 16, 2007 (72 FR 64540). That
NPRM proposed to correct an unsafe
condition for the specified products.
The MCAI states: ‘‘It has been
determined that the existing rigging
procedures for the tail rotor pitch
change mechanism have to be changed
due to possibility of parts interference.’’
Because the cumulative effect of the
tolerances on the various parts may
result in the total assemblage outboard
of the counterweight bellcrank being out
of tolerance, the tail rotor yoke may
contact the nut, part number (P/N)
222–012–731–001, before contacting the
flapping stop, resulting in less tail rotor
travel. Additionally, the manufacturer
has indicated that the tail rotor
counterweight bellcranks may be
misaligned, resulting in higher tail rotor
VerDate Aug<31>2005
16:51 Jul 29, 2008
Jkt 214001
pedal forces and higher pilot workload
after failure of the #1 hydraulic system.
Both the parts interference and the
higher pedal forces constitute unsafe
conditions. You may obtain further
information by examining the MCAI and
any related service information in the
AD docket.
Comments
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.
Relevant Service Information
Bell Helicopter Textron has issued
Alert Service Bulletin No. 430–07–39,
dated January 9, 2007, that describes
revised rigging procedures for the tail
rotor pitch change mechanism. The
actions described in the MCAI are
intended to correct the same unsafe
condition as that identified in the
service information.
Differences Between This AD and the
MCAI
We have reviewed the MCAI and
related service information and, in
general, agree with their substance.
However, this AD requires compliance
within the next 150 hours time-inservice or at the next annual inspection,
whichever occurs first, instead of ‘‘at the
next 150 hour or annual inspection, but
no later than 31 December 2007.’’ In
making this change, we do not intend to
differ substantively from the
information provided in the MCAI. This
difference is highlighted in the
‘‘Differences Between this AD and the
MCAI’’ section in the AD.
Costs of Compliance
We estimate that this AD will affect
58 helicopters of U.S. registry. We also
estimate that it will take about 2 workhours per helicopter to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
A replacement yoke will cost about
$21,218, assuming the part is no longer
under warranty. However, because the
service information lists this part as
covered under warranty, we have
assumed that there will be no charge for
this part. Therefore, as we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these assumptions and figures, we
estimate the cost of this AD on U.S.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
44141
operators to be $9,280, or $160 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
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this 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.
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
E:\FR\FM\30JYR1.SGM
30JYR1
44142
Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–15–04 Bell Helicopter Textron
Canada: Amendment 39–15616. Docket
No. FAA–2007–0177; Directorate
Identifier 2007–SW–19–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective on September 3, 2008.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 430
helicopters, serial numbers 49001 through
49122, certificated in any category.
rwilkins on PROD1PC63 with RULES
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states: ‘‘It
has been determined that the existing rigging
procedures for the tail rotor pitch change
mechanism have to be changed due to
possibility of parts interference.’’
This ‘‘possibility of parts interference’’
occurs because the cumulative effect of the
tolerances on the various parts may result in
the total assemblage outboard of the
counterweight bellcrank being out of
tolerance and the tail rotor yoke may contact
the nut, part number (P/N ) 222–012–731–
001, before contacting the flapping stop.
Further, the manufacturer has indicated that
the tail rotor counterweight bellcranks may
be misaligned, resulting in higher tail rotor
pedal forces and higher pilot workload after
failure of the #1 hydraulic system. Both the
parts interference and the higher pedal forces
constitute unsafe conditions. This AD
requires actions that are intended to address
these unsafe conditions.
Actions and Compliance
(e) Within the next 150 hours time-inservice (TIS) or at the next annual inspection,
whichever occurs first, unless already
accomplished, do the following:
(1) Adjust the rigging of the tail rotor pitch
change mechanism in accordance with the
Accomplishment Instructions, paragraphs 1
and 2, in Bell Helicopter Textron Alert
Service Bulletin 430–07–39, dated January 9,
2007 (ASB).
(2) If either at full left pedal position or full
right pedal position a gap exists between the
tail rotor yoke and the flapping stop, replace
the tail rotor yoke with an airworthy tail rotor
yoke.
(3) If no gap exists between the tail rotor
yoke and the flapping stop at either full right
or full left pedal position, measure the gap
between the tail rotor yoke and nut, P/N 222–
012–731–001, adjust the tail rotor pitch
change mechanism, and adjust the tail rotor
pedal forces in accordance with the
Accomplishment Instruction, paragraphs 4
through 6 of the ASB.
hours TIS or at the next annual inspection,
whichever occurs first, instead of ‘‘at the next
150 hour or annual inspection, but no later
than 31 December 2007.’’
DEPARTMENT OF TRANSPORTATION
Other Information
14 CFR Part 39
(g) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, FAA, ATTN: Tyrone Millard,
Aviation Safety Engineer, FAA, Rotorcraft
Directorate, Rotorcraft Standards Staff, Fort
Worth, Texas 76193–0111, telephone (817)
222–5439, fax (817) 222–5961 has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
[Docket No. FAA–2008–0353; Directorate
Identifier 2007–CE–101–AD; Amendment
39–15620; AD 2008–16–02]
Related Information
(h) MCAI Transport Canada Airworthiness
Directive No. CF–2007–04, dated April 5,
2007, contains related information.
Air Transport Association of America (ATA)
Tracking Code
(i) ATA Code JASC 6720: Tail Rotor
Control System, Tail Rotor Pitch Change.
Material Incorporated by Reference
(j) You must use the specified portions of
Bell Helicopter Textron Alert Service
Bulletin No. 430–07–39, dated January 9,
2007, to do the actions required.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(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., Fort Worth,
Texas, 76193; 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.
Issued in Fort Worth, Texas, on July 9,
2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–17275 Filed 7–29–08; 8:45 am]
BILLING CODE 4910–13–P
Differences Between This AD and the MCAI
(f) This AD differs from the MCAI in that
it requires compliance within the next 150
VerDate Aug<31>2005
16:51 Jul 29, 2008
Jkt 214001
PO 00000
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Fmt 4700
Sfmt 4700
Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation Model 390
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Hawker Beechcraft Corporation Model
390 airplanes. This AD requires you to
repetitively do a post-flight check
(owner/operator holding at least a
private pilot certificate checking for
residual heat in the angle-of-attack
(AOA) probes or an appropriately-rated
mechanic doing a maintenance manual
operational test of the heat of the AOA
probes) after every flight and replace or
modify (upload software) the stall
warning AOA transmitters. This AD
results from reports of the potential for
unannunciated loss of the heating
function in the left-hand (LH) and righthand (RH) stall warning AOA
transmitters of Model 390 airplanes. We
are issuing this AD to correct potentially
inadequate stall warning with loss of
stick pusher function.
DATES: This AD becomes effective on
September 3, 2008.
On September 3, 2008, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Hawker
Beechcraft Corporation, 9709 East
Central, Wichita, Kansas 67291;
telephone: (800) 429–5372 or (316) 676–
3140.
To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2008–0353; Directorate
Identifier 2007–CE–101–AD.
FOR FURTHER INFORMATION CONTACT:
Philip Petty, Aerospace Engineer,
Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4139; fax: (316) 946–4107.
E:\FR\FM\30JYR1.SGM
30JYR1
]]>Agencies
[Federal Register Volume 73, Number 147 (Wednesday, July 30, 2008)]
[Rules and Regulations]
[Pages 44140-44142]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17275]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0177; Directorate Identifier 2007-SW-19-AD;
Amendment 39-15616; AD 2008-15-04]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada (BHTC)
Model 430 Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for BHTC
Model 430 helicopters. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The aviation authority of Canada, with which we have
a bilateral agreement, states in the MCAI: ``It has been determined
that the existing rigging procedures for the tail rotor pitch change
mechanism have to be changed due to possibility of parts
interference.'' The cumulative effect of individual part tolerances
resulting in the total assemblage of those parts being out of tolerance
could result in the tail rotor yoke striking another part other than
the flapping stop (parts interference) cited in the MCAI. Also, the
misalignment of the tail rotor counterweight bellcrank may result in
higher tail rotor pedal forces and a higher pilot workload after
failure of the 1 hydraulic system. Both parts interference and
the misaligned counterweight bellcrank create an unsafe condition. This
AD require actions that are intended to address these unsafe
conditions.
[[Page 44141]]
DATES: This AD becomes effective on September 3, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 3,
2008.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.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) 647-5227) 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, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort
Worth, Texas 76193-0111, telephone (817) 222-5439, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Discussion
We issued an NPRM to amend 14 CFR part 39 to include an AD that
would apply to BHTC Model 430 helicopters, serial numbers 49001 through
49122, on November 2, 2007. That NPRM was published in the Federal
Register on November 16, 2007 (72 FR 64540). That NPRM proposed to
correct an unsafe condition for the specified products. The MCAI
states: ``It has been determined that the existing rigging procedures
for the tail rotor pitch change mechanism have to be changed due to
possibility of parts interference.'' Because the cumulative effect of
the tolerances on the various parts may result in the total assemblage
outboard of the counterweight bellcrank being out of tolerance, the
tail rotor yoke may contact the nut, part number (P/N) 222-012-731-001,
before contacting the flapping stop, resulting in less tail rotor
travel. Additionally, the manufacturer has indicated that the tail
rotor counterweight bellcranks may be misaligned, resulting in higher
tail rotor pedal forces and higher pilot workload after failure of the
1 hydraulic system. Both the parts interference and the higher
pedal forces constitute unsafe conditions. You may obtain further
information by examining the MCAI and any related service information
in the AD docket.
Comments
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.
Relevant Service Information
Bell Helicopter Textron has issued Alert Service Bulletin No. 430-
07-39, dated January 9, 2007, that describes revised rigging procedures
for the tail rotor pitch change mechanism. The actions described in the
MCAI are intended to correct the same unsafe condition as that
identified in the service information.
Differences Between This AD and the MCAI
We have reviewed the MCAI and related service information and, in
general, agree with their substance. However, this AD requires
compliance within the next 150 hours time-in-service or at the next
annual inspection, whichever occurs first, instead of ``at the next 150
hour or annual inspection, but no later than 31 December 2007.'' In
making this change, we do not intend to differ substantively from the
information provided in the MCAI. This difference is highlighted in the
``Differences Between this AD and the MCAI'' section in the AD.
Costs of Compliance
We estimate that this AD will affect 58 helicopters of U.S.
registry. We also estimate that it will take about 2 work-hours per
helicopter to comply with the basic requirements of this AD. The
average labor rate is $80 per work-hour. A replacement yoke will cost
about $21,218, assuming the part is no longer under warranty. However,
because the service information lists this part as covered under
warranty, we have assumed that there will be no charge for this part.
Therefore, as we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
assumptions and figures, we estimate the cost of this AD on U.S.
operators to be $9,280, or $160 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 the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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:
[[Page 44142]]
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 AD:
2008-15-04 Bell Helicopter Textron Canada: Amendment 39-15616.
Docket No. FAA-2007-0177; Directorate Identifier 2007-SW-19-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective on
September 3, 2008.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 430 helicopters, serial numbers
49001 through 49122, certificated in any category.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states: ``It has been determined that the existing rigging
procedures for the tail rotor pitch change mechanism have to be
changed due to possibility of parts interference.''
This ``possibility of parts interference'' occurs because the
cumulative effect of the tolerances on the various parts may result
in the total assemblage outboard of the counterweight bellcrank
being out of tolerance and the tail rotor yoke may contact the nut,
part number (P/N ) 222-012-731-001, before contacting the flapping
stop. Further, the manufacturer has indicated that the tail rotor
counterweight bellcranks may be misaligned, resulting in higher tail
rotor pedal forces and higher pilot workload after failure of the
1 hydraulic system. Both the parts interference and the
higher pedal forces constitute unsafe conditions. This AD requires
actions that are intended to address these unsafe conditions.
Actions and Compliance
(e) Within the next 150 hours time-in-service (TIS) or at the
next annual inspection, whichever occurs first, unless already
accomplished, do the following:
(1) Adjust the rigging of the tail rotor pitch change mechanism
in accordance with the Accomplishment Instructions, paragraphs 1 and
2, in Bell Helicopter Textron Alert Service Bulletin 430-07-39,
dated January 9, 2007 (ASB).
(2) If either at full left pedal position or full right pedal
position a gap exists between the tail rotor yoke and the flapping
stop, replace the tail rotor yoke with an airworthy tail rotor yoke.
(3) If no gap exists between the tail rotor yoke and the
flapping stop at either full right or full left pedal position,
measure the gap between the tail rotor yoke and nut, P/N 222-012-
731-001, adjust the tail rotor pitch change mechanism, and adjust
the tail rotor pedal forces in accordance with the Accomplishment
Instruction, paragraphs 4 through 6 of the ASB.
Differences Between This AD and the MCAI
(f) This AD differs from the MCAI in that it requires compliance
within the next 150 hours TIS or at the next annual inspection,
whichever occurs first, instead of ``at the next 150 hour or annual
inspection, but no later than 31 December 2007.''
Other Information
(g) Alternative Methods of Compliance (AMOCs): The Manager,
Safety Management Group, FAA, ATTN: Tyrone Millard, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff,
Fort Worth, Texas 76193-0111, telephone (817) 222-5439, fax (817)
222-5961 has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
Related Information
(h) MCAI Transport Canada Airworthiness Directive No. CF-2007-
04, dated April 5, 2007, contains related information.
Air Transport Association of America (ATA) Tracking Code
(i) ATA Code JASC 6720: Tail Rotor Control System, Tail Rotor
Pitch Change.
Material Incorporated by Reference
(j) You must use the specified portions of Bell Helicopter
Textron Alert Service Bulletin No. 430-07-39, dated January 9, 2007,
to do the actions required.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(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., Fort Worth, Texas,
76193; 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.
Issued in Fort Worth, Texas, on July 9, 2008.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-17275 Filed 7-29-08; 8:45 am]
BILLING CODE 4910-13-P
