Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) Model 407 and Model 427 Helicopters, 65684-65686 [E9-29427]
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65684
Federal Register / Vol. 74, No. 237 / Friday, December 11, 2009 / Rules and Regulations
and failure of the lights to illuminate
properly. These actions are intended to
prohibit flight over water if a functional test
indicates that the emergency floatation gear
cannot be armed, which would preclude
deployment of the floats in an emergency
water ditching that could result in helicopter
damage or a fatality.
Actions and Compliance
(e) Required as indicated, unless already
accomplished.
(1) Before further flight, amend the EC120B
Rotorcraft Flight Manual Supplement
(RFMS), Document #9–17 for the Emergency
Floatation Gear Aerazur, by inserting a copy
of this AD into the Limitations section of the
RFMS or making pen and ink changes to that
section as follows:
‘‘Arm the emergency floatation gear by
pressing the LACU ‘FLOAT ARM’
pushbutton.
—If both lights of the pushbutton remain lit,
flight over water is permitted.
—If one or both lights of the pushbutton do
not remain lit, FLIGHT OVER WATER IS
PROHIBITED.’’
(2) Before each flight over water, perform
a functional check to determine whether
flight over water is permitted under the
Limitations section in paragraph (e)(1) of this
AD. For purposes of this AD, ‘‘flight over
water’’ means flight beyond the power-off
gliding distance from shore. ‘‘Shore’’ is an
area of land adjacent to the water and above
the high water mark but does not include
land area that is intermittently under water.
(3) If the LACU fails the functional check
required by paragraph (e)(2) of this AD, place
a placard over the ‘‘FLOAT ARM’’
pushbutton that reads ‘‘INOP.’’
(4) The functional check required by
paragraph (e)(2) may be performed by an
owner/operator (pilot) holding at least a
private pilot certificate because no special
tools are required. The check must be entered
into the aircraft records showing compliance
with paragraph (e)(2) of this AD in
accordance with the requirements of 14 CFR
sections 43.11 and 91.417(a)(2)(v).
WReier-Aviles on DSKGBLS3C1PROD with RULES
Differences Between This AD and the MCAI
AD
(f) We require adding the limitations to the
Limitations section of the RFMS not the basic
RFM. We also allow inserting a copy of this
AD in the RFMS or making pen and ink
changes to the language in the RFMS. We
changed the wording used to describe the
functional check.
Other Information
(g) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, ATTN: DOT/FAA Southwest Region,
J. R. Holton, Jr., ASW–112, Aviation Safety
Engineer, Rotorcraft Directorate, 2601
Meacham Blvd., Fort Worth, Texas 76137,
telephone (817) 222–4964, fax (817) 222–
5961, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
(h) Special flight permits may be issued for
a single flight in accordance with sections 14
CFR 21.197 and 21.199 to operate the
helicopter to a location where the
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15:09 Dec 10, 2009
Jkt 220001
requirements of this AD can be accomplished
provided there are no passengers on board
and the helicopter is not flown over water.
Related Information
(i) The European Aviation Safety Agency
(EASA), which is the Technical Agent for the
Member States of the European Community,
EASA AD No. 2008–0177–E, dated
September 19, 2008, and Eurocopter France
Emergency Alert Service Bulletin No.
04A007, dated September 18, 2008, contain
related information.
Joint Aircraft System/Component (JASC)
Tracking Code
(j) JASC Code 2560: Emergency Equipment.
Issued in Fort Worth, Texas, on November
18, 2009.
Gary B. Roach,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E9–29426 Filed 12–10–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1123; Directorate
Identifier 2009–SW–03–AD; Amendment 39–
16127; AD 2009–25–08]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada (BHTC)
Model 407 and Model 427 Helicopters
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
BHTC Model 407 and Model 427
helicopters. This AD results from
mandatory continuing airworthiness
information (MCAI) ADs issued by the
aviation authority of Canada. The MCAI
ADs state that some hydraulic pump
driveshaft assemblies may have been
delivered with a missing internal plug
or fastening rivet. This condition, if not
corrected, could result in a loss of
hydraulic pressure and subsequent loss
of control of the helicopter.
DATES: This AD becomes effective on
December 28, 2009.
We must receive comments on this
AD by February 9, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting your
comments electronically.
PO 00000
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• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
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 Limited,
12,800 Rue de l’Avenir, Mirabel, Quebec
J7J1R4, telephone (450) 437–2862 or
(800) 363–8023, fax (450) 433–0272, or
at https://www.bellcustomer.com/files/.
Examining the 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, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is
stated in the ADDRESSES section of this
AD. Comments will be available in the
AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
DOT/FAA Southwest Region, Uday
Garadi, ASW–111, Aviation Safety
Engineer, Rotorcraft Directorate,
Regulations and Guidance Group, 2601
Meacham Blvd., Fort Worth, Texas
76137, telephone (817) 222–5123, fax
(817) 222–5961.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada, which is the
aviation authority for Canada, has
issued Canadian AD No. CF–2009–03,
dated January 22, 2009, to correct an
unsafe condition for BHTC Model 407
helicopters, serial numbers (S/N) 53000
through 53408, and S/N 53421 through
53459. Transport Canada has also issued
Canadian AD No. CF–2009–04, dated
January 22, 2009, to correct an unsafe
condition for Model 427 helicopters, S/
N 56001 through 56046. These MCAI
ADs state that helicopters with
hydraulic pump input shaft, part
number
(P/N) 407–340–107–101, and
interconnect adapter, P/N 407–340–
108–101, that were installed in
accordance with BHTC Technical
Bulletin (TB) No. 407–01–30, Revision
A, dated May 21, 2003 (for Model 407
helicopters), or TB No. 427–05–19,
dated January 7, 2005 (for Model 427
E:\FR\FM\11DER1.SGM
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Federal Register / Vol. 74, No. 237 / Friday, December 11, 2009 / Rules and Regulations
helicopters), are not affected by the
MCAI ADs. The MCAI ADs further state
that some hydraulic pump driveshaft
assemblies, P/N 406–040–072–105, may
have been delivered with a missing
internal plug or fastening rivet. This
condition, if not corrected, could result
in a loss of hydraulic pressure and
subsequent loss of control of the
helicopter.
You may obtain further information
by examining the MCAI ADs and any
related service information in the AD
docket.
FAA’s Evaluation and Unsafe Condition
Determination
These helicopters have been approved
by the aviation authority of Canada, and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with Canada, they have
notified us of the unsafe condition
described in the MCAI ADs. We are
issuing this AD because we evaluated
all information provided by Transport
Canada and determined the unsafe
condition exists and is likely to exist or
develop on other helicopters of these
same type designs.
WReier-Aviles on DSKGBLS3C1PROD with RULES
Differences Between This AD and the
MCAI ADs
This AD differs from MCAI AD No.
CF–2009–03, applicable to Model 407
helicopters, and MCAI AD No. CF–
2009–04, applicable to Model 427
helicopters, both dated January 22,
2009, which require compliance with a
part of the BHTC service information
that specifies inspecting ‘‘spares stock’’,
and also require attaching a
‘‘serviceable’’ tag to parts in inventory.
This AD does not require either of those
actions. Also, the compliance section of
this AD refers to ‘‘50 hours time-inservice’’ instead of ‘‘50 hours air time,’’
which is used in both of the MCAI ADs.
Further, the MCAI ADs require
performing actions in accordance with
the BHTC alert service and technical
bulletins or later revisions approved by
the Chief, Continuing Airworthiness,
Transport Canada. The BHTC alert
service and technical bulletins describe
additional inspections for wear that are
not required by this AD; we have listed
those bulletins in the ‘‘Related
Information’’ section of this AD. Finally,
the MCAI AD for the Model 427
helicopter applies to S/N 58001 and S/
N 58002. Per U.S. Type Certificate
R00001RC, neither of these helicopters
is eligible for an FAA Airworthiness
Certificate and thus, this AD does not
apply to them.
VerDate Nov<24>2008
15:09 Dec 10, 2009
Jkt 220001
Costs of Compliance
We estimate that this AD will affect
about 259 BHTC Model 407 helicopters
and 16 BHTC Model 427 helicopters of
U.S. registry. We also estimate that it
will take about 1.5 work-hours per
helicopter to perform a one-time
inspection of the hydraulic pump
driveshaft assembly, P/N 406–040–072–
105, to determine the presence of the
internal plug in the center of the
driveshaft, as well as the fastening rivet
that holds the internal plug in place,
and 1 work-hour to install a
replacement shaft and adapter, if
necessary. The average labor rate is $80
per work-hour. Required parts will cost
about $1,850 per helicopter, to install an
input shaft and adapter, if needed.
Based on these figures, we estimate the
cost of this AD on U.S. operators will be
$563,750 or $2,050 per helicopter to
inspect and replace parts.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. We find that the risk to the flying
public justifies waiving notice and
comment prior to adoption of this rule
because a hydraulic pump driveshaft
assembly with a missing internal plug or
fastening rivet could result in a loss of
hydraulic pressure and subsequent loss
of control of the helicopter. Because the
compliance time to correct this unsafe
condition is short, we have determined
that notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
for making this amendment effective in
fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment.
However, we invite you to send us any
written data, views, or arguments
concerning this AD. Send your
comments to an address listed under the
ADDRESSES section of this AD. Include
‘‘Docket No. FAA–2009–1123;
Directorate Identifier 2009–SW–03–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov including any
personal information you provide. We
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65685
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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, 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
1. The authority citation for part 39
continues to read as follows:
■
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65686
Federal Register / Vol. 74, No. 237 / Friday, December 11, 2009 / 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:
■
2009–25–08 Bell Helicopter Transport
Canada: Amendment 39–16127. Docket
No. FAA–2009–1123; Directorate
Identifier 2009–SW–03–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective on December 28, 2009.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 407
helicopters, serial numbers (S/N) 53000
through 53408, and S/N 53421 through
53459, and Model 427 helicopters, S/N 56001
through 56046, certificated in any category.
This AD does not apply to helicopters with
hydraulic pump input shaft, part number
(P/N) 407–340–107–101, and interconnect
adapter, P/N 407–340–108–101, which is a
direct replacement for hydraulic pump
driveshaft assembly, P/N 406–040–072–105,
and the subject of this AD.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) ADs state
that some hydraulic pump driveshaft
assemblies, P/N 406–040–072–105, may have
been delivered with a missing internal plug
or fastening rivet. This condition, if not
corrected, could result in a loss of hydraulic
pressure and subsequent loss of control of the
helicopter.
WReier-Aviles on DSKGBLS3C1PROD with RULES
Actions and Compliance
(e) During the next driveshaft lubrication,
or within 50 hours time-in-service or 30
calendar days, whichever occurs first, unless
already accomplished, do the following:
(1) Perform a one-time inspection of the
hydraulic pump driveshaft assembly, P/N
406–040–072–105, to determine if an internal
plug and a fastening rivet are correctly
installed.
(2) If either the internal plug, P/N 406–
040–094–101, or the fastening rivet, P/N
MS20613–3P10, is not installed, replace the
hydraulic pump driveshaft assembly, P/N
406–040–072–105, with an airworthy
hydraulic pump input shaft, P/N 407–340–
107–101, and interconnect adapter, P/N 407–
340–108–101.
Differences Between This AD and the MCAI
ADs
(f) This AD differs from MCAI AD No.
CF–2009–03, applicable to Model 407
helicopters, and MCAI AD No. CF–2009–04,
applicable to Model 427 helicopters, both
dated January 22, 2009, which require
compliance with a part of the BHTC service
information that specifies inspecting ‘‘spares
stock’’, and also require attaching a
‘‘serviceable’’ tag to parts in inventory. This
AD does not require either of those actions.
Also, the compliance section of this AD
refers to ‘‘50 hours time-in-service’’ instead
of ‘‘50 hours air time,’’ which is used in both
VerDate Nov<24>2008
15:09 Dec 10, 2009
Jkt 220001
of the MCAI ADs. Further, the MCAI ADs
require performing actions in accordance
with the BHTC alert service and technical
bulletins or later revisions approved by the
Chief, Continuing Airworthiness, Transport
Canada. The BHTC alert service and
technical bulletins describe additional
inspections for wear that are not required by
this AD; we have listed those bulletins in the
‘‘Related Information’’ section of this AD.
Finally, the MCAI AD for the Model 427
helicopter applies to S/N 58001 and S/N
58002. Per U.S. Type Certificate R00001RC,
neither of these helicopters is eligible for an
FAA Airworthiness Certificate and thus, this
AD does not apply to them.
Other Information
(g) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, FAA, ATTN: Uday Garadi, Aviation
Safety Engineer, Rotorcraft Directorate,
Regulations and Guidance Group, 2601
Meacham Blvd., Fort Worth, Texas 76137,
telephone (817) 222–5123, fax (817) 222–
5961, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
(h) For service information identified in
this AD, contact Bell Helicopter Textron
Canada Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J1R4, telephone (450)
437–2862 or (800) 363–8023, fax (450) 433–
0272, or at https://www.bellcustomer.com/
files/.
Related Information
(i) Transport Canada MCAI Airworthiness
Directive AD No. CF–2009–03 and No. CF–
2009–04, both dated January 22, 2009; and
Bell Helicopter Textron Canada Alert Service
Bulletin No. 407–08–83, dated May 22, 2008,
Alert Service Bulletin No. 427–08–22, dated
June 26, 2008, Technical Bulletin No. 407–
01–30, Revision A, dated May 21, 2003, and
Technical Bulletin No. 427–05–19, dated
January 7, 2005 contain related information.
Joint Aircraft System/Component (JASC)
Code
(j) JASC Code 2913: Hydraulic Pump,
main.
Issued in Fort Worth, Texas, on November
19, 2009.
Gary B. Roach,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E9–29427 Filed 12–10–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2009–0888; Airspace
Docket No. 09–ASO–23]
Modification of Jet Route J–20; Florida
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: This action modifies Jet Route
J–20 by terminating the route at the
Orlando, FL, very high frequency
omnidirectional range/tactical air
navigation (VORTAC) facility, thereby
eliminating a portion of J–20 that is no
longer needed. This action will ensure
the efficient use of airspace within the
National Airspace System (NAS).
DATES: Effective 0901 UTC, February 11,
2010. The Director of the Federal
Register approves this incorporation by
reference action under 1 CFR part 51,
subject to the annual revision of FAA
Order 7400.9 and publication of
conforming amendments.
FOR FURTHER INFORMATION CONTACT: Paul
Gallant, Airspace and Rules Group,
Office of System Operations Airspace
and AIM, Federal Aviation
Administration, 800 Independence
Avenue, SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
History
On Friday, October 23, 2009, the FAA
published in the Federal Register a
notice of proposed rulemaking to
modify jet route J–20 (74 FR 54765).
Interested parties were invited to
participate in this rulemaking effort by
submitting written comments on the
proposal. No comments were received.
The Rule
The FAA is amending Title 14, Code
of Federal Regulations (14 CFR) part 71
to eliminate the segment of J–20 that
extends between the Orlando VORTAC
and the Virginia Key very high
frequency omnidirectional range/
distance measuring equipment (VOR/
DME). The FAA has determined that
this portion of J–20 is no longer
required. Currently, J–20 parallels jet
route J–53, between the Miami area and
DEARY intersection (southeast of the
Orlando VORTAC). At DREARY, J–20
makes a left turn to the Orlando
VORTAC where it converges with J–53.
This can cause a problem when aircraft
are parallel on both J–20 and J–53. Jet
route J–113 provides a suitable
northbound replacement route for the
J–20 segment. In addition, this change
provides air traffic control with more
time to get climbing aircraft to their
requested altitudes, thereby enhancing
system efficiency.
Jet routes are published in paragraph
2004 of FAA Order 7400.9T dated
August 27, 2009 and effective
September 15, 2009, which is
incorporated by reference in 14 CFR
71.1. The jet route listed in this
document will be subsequently
published in the Order.
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Agencies
[Federal Register Volume 74, Number 237 (Friday, December 11, 2009)]
[Rules and Regulations]
[Pages 65684-65686]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-29427]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1123; Directorate Identifier 2009-SW-03-AD;
Amendment 39-16127; AD 2009-25-08]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada (BHTC)
Model 407 and Model 427 Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
BHTC Model 407 and Model 427 helicopters. This AD results from
mandatory continuing airworthiness information (MCAI) ADs issued by the
aviation authority of Canada. The MCAI ADs state that some hydraulic
pump driveshaft assemblies may have been delivered with a missing
internal plug or fastening rivet. This condition, if not corrected,
could result in a loss of hydraulic pressure and subsequent loss of
control of the helicopter.
DATES: This AD becomes effective on December 28, 2009.
We must receive comments on this AD by February 9, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting your
comments electronically.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, 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 Limited, 12,800 Rue de l'Avenir, Mirabel,
Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450)
433-0272, or at https://www.bellcustomer.com/files/.
Examining the 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, the economic evaluation, any
comments received, and other information. The street address for the
Docket Operations office (telephone (800) 647-5527) is stated in the
ADDRESSES section of this AD. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Uday Garadi,
ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations
and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137,
telephone (817) 222-5123, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada, which is the aviation authority for Canada, has
issued Canadian AD No. CF-2009-03, dated January 22, 2009, to correct
an unsafe condition for BHTC Model 407 helicopters, serial numbers (S/
N) 53000 through 53408, and S/N 53421 through 53459. Transport Canada
has also issued Canadian AD No. CF-2009-04, dated January 22, 2009, to
correct an unsafe condition for Model 427 helicopters, S/N 56001
through 56046. These MCAI ADs state that helicopters with hydraulic
pump input shaft, part number (P/N) 407-340-107-101, and interconnect
adapter, P/N 407-340-108-101, that were installed in accordance with
BHTC Technical Bulletin (TB) No. 407-01-30, Revision A, dated May 21,
2003 (for Model 407 helicopters), or TB No. 427-05-19, dated January 7,
2005 (for Model 427
[[Page 65685]]
helicopters), are not affected by the MCAI ADs. The MCAI ADs further
state that some hydraulic pump driveshaft assemblies, P/N 406-040-072-
105, may have been delivered with a missing internal plug or fastening
rivet. This condition, if not corrected, could result in a loss of
hydraulic pressure and subsequent loss of control of the helicopter.
You may obtain further information by examining the MCAI ADs and
any related service information in the AD docket.
FAA's Evaluation and Unsafe Condition Determination
These helicopters have been approved by the aviation authority of
Canada, and are approved for operation in the United States. Pursuant
to our bilateral agreement with Canada, they have notified us of the
unsafe condition described in the MCAI ADs. We are issuing this AD
because we evaluated all information provided by Transport Canada and
determined the unsafe condition exists and is likely to exist or
develop on other helicopters of these same type designs.
Differences Between This AD and the MCAI ADs
This AD differs from MCAI AD No. CF-2009-03, applicable to Model
407 helicopters, and MCAI AD No. CF-2009-04, applicable to Model 427
helicopters, both dated January 22, 2009, which require compliance with
a part of the BHTC service information that specifies inspecting
``spares stock'', and also require attaching a ``serviceable'' tag to
parts in inventory. This AD does not require either of those actions.
Also, the compliance section of this AD refers to ``50 hours time-in-
service'' instead of ``50 hours air time,'' which is used in both of
the MCAI ADs. Further, the MCAI ADs require performing actions in
accordance with the BHTC alert service and technical bulletins or later
revisions approved by the Chief, Continuing Airworthiness, Transport
Canada. The BHTC alert service and technical bulletins describe
additional inspections for wear that are not required by this AD; we
have listed those bulletins in the ``Related Information'' section of
this AD. Finally, the MCAI AD for the Model 427 helicopter applies to
S/N 58001 and S/N 58002. Per U.S. Type Certificate R00001RC, neither of
these helicopters is eligible for an FAA Airworthiness Certificate and
thus, this AD does not apply to them.
Costs of Compliance
We estimate that this AD will affect about 259 BHTC Model 407
helicopters and 16 BHTC Model 427 helicopters of U.S. registry. We also
estimate that it will take about 1.5 work-hours per helicopter to
perform a one-time inspection of the hydraulic pump driveshaft
assembly, P/N 406-040-072-105, to determine the presence of the
internal plug in the center of the driveshaft, as well as the fastening
rivet that holds the internal plug in place, and 1 work-hour to install
a replacement shaft and adapter, if necessary. The average labor rate
is $80 per work-hour. Required parts will cost about $1,850 per
helicopter, to install an input shaft and adapter, if needed. Based on
these figures, we estimate the cost of this AD on U.S. operators will
be $563,750 or $2,050 per helicopter to inspect and replace parts.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. We find that the risk to the flying public justifies waiving
notice and comment prior to adoption of this rule because a hydraulic
pump driveshaft assembly with a missing internal plug or fastening
rivet could result in a loss of hydraulic pressure and subsequent loss
of control of the helicopter. Because the compliance time to correct
this unsafe condition is short, we have determined that notice and
opportunity for public comment before issuing this AD are impracticable
and that good cause exists for making this amendment effective in fewer
than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. However, we invite you to send us any written data, views, or
arguments concerning this AD. Send your comments to an address listed
under the ADDRESSES section of this AD. Include ``Docket No. FAA-2009-
1123; Directorate Identifier 2009-SW-03-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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, 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 65686]]
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:
2009-25-08 Bell Helicopter Transport Canada: Amendment 39-16127.
Docket No. FAA-2009-1123; Directorate Identifier 2009-SW-03-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective on
December 28, 2009.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 407 helicopters, serial numbers (S/
N) 53000 through 53408, and S/N 53421 through 53459, and Model 427
helicopters, S/N 56001 through 56046, certificated in any category.
This AD does not apply to helicopters with hydraulic pump input
shaft, part number (P/N) 407-340-107-101, and interconnect adapter,
P/N 407-340-108-101, which is a direct replacement for hydraulic
pump driveshaft assembly, P/N 406-040-072-105, and the subject of
this AD.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
ADs state that some hydraulic pump driveshaft assemblies, P/N 406-
040-072-105, may have been delivered with a missing internal plug or
fastening rivet. This condition, if not corrected, could result in a
loss of hydraulic pressure and subsequent loss of control of the
helicopter.
Actions and Compliance
(e) During the next driveshaft lubrication, or within 50 hours
time-in-service or 30 calendar days, whichever occurs first, unless
already accomplished, do the following:
(1) Perform a one-time inspection of the hydraulic pump
driveshaft assembly, P/N 406-040-072-105, to determine if an
internal plug and a fastening rivet are correctly installed.
(2) If either the internal plug, P/N 406-040-094-101, or the
fastening rivet, P/N MS20613-3P10, is not installed, replace the
hydraulic pump driveshaft assembly, P/N 406-040-072-105, with an
airworthy hydraulic pump input shaft, P/N 407-340-107-101, and
interconnect adapter, P/N 407-340-108-101.
Differences Between This AD and the MCAI ADs
(f) This AD differs from MCAI AD No. CF-2009-03, applicable to
Model 407 helicopters, and MCAI AD No. CF-2009-04, applicable to
Model 427 helicopters, both dated January 22, 2009, which require
compliance with a part of the BHTC service information that
specifies inspecting ``spares stock'', and also require attaching a
``serviceable'' tag to parts in inventory. This AD does not require
either of those actions. Also, the compliance section of this AD
refers to ``50 hours time-in-service'' instead of ``50 hours air
time,'' which is used in both of the MCAI ADs. Further, the MCAI ADs
require performing actions in accordance with the BHTC alert service
and technical bulletins or later revisions approved by the Chief,
Continuing Airworthiness, Transport Canada. The BHTC alert service
and technical bulletins describe additional inspections for wear
that are not required by this AD; we have listed those bulletins in
the ``Related Information'' section of this AD. Finally, the MCAI AD
for the Model 427 helicopter applies to S/N 58001 and S/N 58002. Per
U.S. Type Certificate R00001RC, neither of these helicopters is
eligible for an FAA Airworthiness Certificate and thus, this AD does
not apply to them.
Other Information
(g) Alternative Methods of Compliance (AMOCs): The Manager,
Safety Management Group, FAA, ATTN: Uday Garadi, Aviation Safety
Engineer, Rotorcraft Directorate, Regulations and Guidance Group,
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-
5123, fax (817) 222-5961, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
(h) For service information identified in this AD, contact Bell
Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel,
Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450)
433-0272, or at https://www.bellcustomer.com/files/.
Related Information
(i) Transport Canada MCAI Airworthiness Directive AD No. CF-
2009-03 and No. CF-2009-04, both dated January 22, 2009; and Bell
Helicopter Textron Canada Alert Service Bulletin No. 407-08-83,
dated May 22, 2008, Alert Service Bulletin No. 427-08-22, dated June
26, 2008, Technical Bulletin No. 407-01-30, Revision A, dated May
21, 2003, and Technical Bulletin No. 427-05-19, dated January 7,
2005 contain related information.
Joint Aircraft System/Component (JASC) Code
(j) JASC Code 2913: Hydraulic Pump, main.
Issued in Fort Worth, Texas, on November 19, 2009.
Gary B. Roach,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E9-29427 Filed 12-10-09; 8:45 am]
BILLING CODE 4910-13-P