Airworthiness Directives; Hawker Beechcraft Corporation Model 390 Airplanes, 67714-67716 [E8-26879]
Download as PDF
<![CDATA[
67714
Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Rules and Regulations
publish a regulatory flexibility analysis
if the agency certifies that the final rule
will not have a significant economic
impact on a substantial number of small
entities. 5 U.S.C. 605(b).
Pursuant to section 605(b), the Board
certifies that this interim final rule will
not have a significant economic impact
on a substantial number of small
entities. The rule increases the interest
paid on certain balances held by eligible
institutions at the Federal Reserve
Banks and will benefit all institutions,
small and large, that receive such
interest. There are no new reporting,
record-keeping, or other compliance
requirements associated with this rule.
Paperwork Reduction Act
In accordance with the Paperwork
Reduction Act (44 U.S.C. 3506; 5 CFR
1320 Appendix A.1), the Board has
reviewed the interim final rule under
authority delegated to the Board by the
Office of Management and Budget. The
rule contains no collections of
information pursuant to the Paperwork
Reduction Act.
List of Subjects in 12 CFR Part 204
Banks, Banking, Reporting and
recordkeeping requirements.
Authority and Issuance
For the reasons set forth in the
preamble, the Board is amending 12
CFR part 204 as follows:
■
PART 204—RESERVE
REQUIREMENTS OF DEPOSITORY
INSTITUTIONS (REGULATION D)
1. The authority citation for part 204
continues to read as follows:
■
Authority: 12 U.S.C. 248(a), 248(c), 371a,
461, 601, 611, and 3105.
2. In § 204.10, paragraphs (b)(1) and
(b)(2) are revised to read as follows:
■
§ 204.10
Payment of interest on balances.
*
*
*
*
(b) * * *
(1) For required reserve balances, at
the average targeted federal funds rate
over the reserve maintenance period;
and
(2) For excess balances, at the lowest
targeted federal funds rate during the
reserve maintenance period.
*
*
*
*
*
hsrobinson on PROD1PC76 with RULES
*
By order of the Board of Governors of the
Federal Reserve System, November 5, 2008.
Robert deV. Frierson,
Deputy Secretary of the Board.
[FR Doc. E8–26727 Filed 11–14–08; 8:45 am]
BILLING CODE 6210–01–P
VerDate Aug<31>2005
17:35 Nov 14, 2008
Jkt 217001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0492; Directorate
Identifier 2008–CE–023–AD; Amendment
39–15734; AD 2008–23–13]
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation Model 390
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Hawker Beechcraft Corporation (HBC)
Model 390 airplanes. This AD requires
you to remove the current preformed
packing, elbow fitting, and jam nut from
the left and right hydraulic pump
pressure output port and replace with
new parts. This AD also requires you to
install a hydraulic pump case drain
check valve. This AD results from nine
occurrences of hydraulic fluid leaking
from the engine hydraulic pump output
fitting as a result of an improperly
installed elbow connecting the output
port to the pulse dampener hose. We are
issuing this AD to prevent hydraulic
fluid leaks from the left and right
hydraulic fluid pump and to prevent the
flow of hydraulic fluid into the engine
compartment. The loss of hydraulic
fluid can result in loss of airplane
hydraulic system pressure and the
consequent loss of hydraulic system
functions including gear extension/
retraction, spoiler functions, and antiskid braking system actuation. The
inability of the hydraulic installation to
isolate flow of hydraulic fluid could
result in a hazardous amount of
flammable fluid in the corresponding
engine compartment. These conditions,
if not corrected, could result in loss of
system functions and/or fire in the
engine compartment.
DATES: This AD becomes effective on
December 22, 2008.
On December 22, 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 67201;
telephone: (316) 676–5034; fax: (316)
SUMMARY:
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
676–6614; Internet: https://
www.hawkerbeechcraft.com/
service_support/pubs/.
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–2008–0492; Directorate
Identifier 2008–CE–023–AD.
FOR FURTHER INFORMATION CONTACT:
Aaron Waters, Aerospace Engineer,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4174; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
Discussion
On April 24, 2008, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Model 390 airplanes. This
proposal was published in the Federal
Register as a notice of proposed
rulemaking (NPRM) on May 1, 2008 (73
FR 23988). The NPRM proposed to
require you to remove the current
preformed packing, elbow fitting, and
jam nut from the left and right hydraulic
pump pressure output port and replace
with new parts. The NPRM also
proposed to require you to install a
hydraulic pump case drain check valve.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 182
airplanes in the U.S. registry.
We estimate the following costs to do
the modifications:
E:\FR\FM\17NOR1.SGM
17NOR1
Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Rules and Regulations
Labor cost
Hydraulic pressure output fitting assembly: 8 work-hours × $80 per hour = $640 .................................
Hydraulic pump case drain check valve: 16 work-hours × $80 per hour = $1,280 ................................
HBC will provide warranty credit as
specified in Hawker Beechcraft
Mandatory Service Bulletin SB 29–3869,
dated January 2008; and Hawker
Beechcraft Mandatory Service Bulletin
SB 29–3851, dated January 2008.
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 AD.
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 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 a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2008–0492;
Directorate Identifier 2008–CE–023–
AD’’ in your request.
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 Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Total cost
per airplane
Parts cost
[Amended]
$100
4,353
$740
5,633
67715
Total cost
on U.S.
operators
$134,680
1,025,206
2008–23–13 Hawker Beechcraft
Corporation: Amendment 39–15734;
Docket No. FAA–2008–0492; Directorate
Identifier 2008–CE–023–AD.
Effective Date
(a) This AD becomes effective on December
22, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 390 airplanes,
serial numbers RB–4 through RB–224, that
are certificated in any category.
Unsafe Condition
(d) This AD results from nine occurrences
of hydraulic fluid leaking from the engine
hydraulic pump output fitting as a result of
an improperly installed elbow connecting the
output port to the pulse dampener hose. We
are issuing this AD to prevent hydraulic fluid
leaking from the left and right hydraulic fluid
pump and to prevent the flow of hydraulic
fluid into the engine compartment. The loss
of hydraulic fluid can result in loss of
airplane hydraulic system pressure and the
consequent loss of hydraulic system
functions including gear extension/
retraction, spoiler functions, and anti-skid
braking system actuation. The inability of the
hydraulic installation to isolate flow of
hydraulic fluid could result in a hazardous
amount of flammable fluid in the
corresponding engine compartment. These
conditions, if not corrected, could result in
loss of system functions and/or fire in the
engine compartment.
Compliance
2. FAA amends § 39.13 by adding the
following new AD:
■
(e) To address this problem, you must do
the following, unless already done:
hsrobinson on PROD1PC76 with RULES
Actions
Compliance
Procedures
(1) Remove current preformed packing (part
number (P/N) MS28778–6), elbow fitting (P/N
MS21908J6), and jam nut (P/N AN924–6J)
from the left and right hydraulic pump pressure output port and install new preformed
packing (P/N MS28778–6), union (P/N
MS21902J6), and swivel fitting (P/N
NAS1762J0606) in the left and right hydraulic
pressure pump output port.
(2) Install hydraulic pump case drain check
valve Kit No. 390–5803–0001.
Within the next 200 hours time-in-service
(TIS) after December 22, 2008 (the effective date of this AD) or within the next 6
months after December 22, 2008 (the effective date of this AD), whichever occurs first.
Follow Hawker Beechcraft Mandatory Service
Bulletin SB 29–3869, dated January 2008.
Within the next 200 hours TIS after December
22, 2008 (the effective date of this AD) or
within the next 6 months after December
22, 2008 (the effective date of this AD),
whichever occurs first.
Hawker Beechcraft Mandatory Service Bulletin SB 29–3851, dated January 2008.
VerDate Aug<31>2005
17:35 Nov 14, 2008
Jkt 217001
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
E:\FR\FM\17NOR1.SGM
17NOR1
67716
Federal Register / Vol. 73, No. 222 / Monday, November 17, 2008 / Rules and Regulations
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Aaron Waters, Aerospace Engineer, Wichita
ACO, 1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–4174;
fax: (316) 946–4107. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
Material Incorporated by Reference
(g) You must use Hawker Beechcraft
Mandatory Service Bulletin SB 29–3869,
dated January 2008; and Hawker Beechcraft
Mandatory Service Bulletin SB 29–3851,
dated January 2008, to do the actions
required by this AD, unless the AD specifies
otherwise.
(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 Hawker Beechcraft
Corporation, 9709 East Central, Wichita,
Kansas 67201; telephone: (316) 676–5034;
fax: (316) 676–6614; Internet: https://
www.hawkerbeechcraft.com/service_support/
pubs/.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; 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.
Issued in Kansas City, Missouri, on
November 5, 2008.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–26879 Filed 11–14–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0115; Directorate
Identifier 2007–NM–240–AD; Amendment
39–15723; AD 2008–23–02]
hsrobinson on PROD1PC76 with RULES
RIN 2120–AA64
Airworthiness Directives; Saab Model
SAAB 2000 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate Aug<31>2005
17:35 Nov 14, 2008
Jkt 217001
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. 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 MCAI describes the unsafe
condition as:
One Part Number (P/N) LM–219–92 Centre
Bracket from a P/N LM–219–SA28 Aft Engine
Mounting assembly was found to be cracked
while installed on the aircraft.
This reduces the effectiveness of the
mounting assembly and could eventually
cause it to fail.
*
*
*
*
*
A failed mounting assembly, if not
corrected, could result in loss of the
engine. We are issuing this AD to
require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective
December 22, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 22, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM–
116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1112; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (NPRM) to amend
14 CFR part 39 to include an AD that
would apply to the specified products.
That supplemental NPRM was
published in the Federal Register on
August 29, 2008 (73 FR 50903). That
supplemental NPRM proposed to
correct an unsafe condition for the
specified products. The MCAI states:
One Part Number (P/N) LM–219–92 Centre
Bracket from a P/N LM–219–SA28 Aft Engine
Mounting assembly was found to be cracked
while installed on the aircraft.
This reduces the effectiveness of the
mounting assembly and could eventually
cause it to fail.
EASA Airworthiness Directive (AD) was
issued to require inspection and rework in
order to make the centre bracket less
sensitive to external damage that may result
in a crack.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
This AD, superseding AD 2007–0204, has
been issued to introduce an alternative
repeatable inspection procedure.
A failed mounting assembly, if not
corrected, could result in loss of the
engine. The corrective actions include
an inspection to determine if there are
any sharp edges on the aft engine
mounting assembly; repetitive visual
inspections, or a combination of visual
and fluorescent penetrant inspection,
for cracking of the center bracket of the
aft engine mounting assembly for both
engines; rework of sharp edges;
replacement of the aft engine mounting
assemblies; and re-identification of
engine mounting assemblies and
reworked center bracket. You may
obtain further information by examining
the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the
supplemental NPRM or on the
determination of the cost to the public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed in the supplemental NPRM.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 6 products of U.S. registry. We
also estimate that it will take about 8
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $3,840, or $640 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
E:\FR\FM\17NOR1.SGM
17NOR1
]]>Agencies
[Federal Register Volume 73, Number 222 (Monday, November 17, 2008)]
[Rules and Regulations]
[Pages 67714-67716]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-26879]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0492; Directorate Identifier 2008-CE-023-AD;
Amendment 39-15734; AD 2008-23-13]
RIN 2120-AA64
Airworthiness Directives; Hawker Beechcraft Corporation Model 390
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Hawker Beechcraft Corporation (HBC) Model 390 airplanes. This AD
requires you to remove the current preformed packing, elbow fitting,
and jam nut from the left and right hydraulic pump pressure output port
and replace with new parts. This AD also requires you to install a
hydraulic pump case drain check valve. This AD results from nine
occurrences of hydraulic fluid leaking from the engine hydraulic pump
output fitting as a result of an improperly installed elbow connecting
the output port to the pulse dampener hose. We are issuing this AD to
prevent hydraulic fluid leaks from the left and right hydraulic fluid
pump and to prevent the flow of hydraulic fluid into the engine
compartment. The loss of hydraulic fluid can result in loss of airplane
hydraulic system pressure and the consequent loss of hydraulic system
functions including gear extension/retraction, spoiler functions, and
anti-skid braking system actuation. The inability of the hydraulic
installation to isolate flow of hydraulic fluid could result in a
hazardous amount of flammable fluid in the corresponding engine
compartment. These conditions, if not corrected, could result in loss
of system functions and/or fire in the engine compartment.
DATES: This AD becomes effective on December 22, 2008.
On December 22, 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
67201; telephone: (316) 676-5034; fax: (316) 676-6614; Internet:
https://www.hawkerbeechcraft.com/service_support/pubs/.
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-2008-0492;
Directorate Identifier 2008-CE-023-AD.
FOR FURTHER INFORMATION CONTACT: Aaron Waters, Aerospace Engineer, 1801
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4174; fax: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
On April 24, 2008, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Model 390 airplanes. This proposal was published
in the Federal Register as a notice of proposed rulemaking (NPRM) on
May 1, 2008 (73 FR 23988). The NPRM proposed to require you to remove
the current preformed packing, elbow fitting, and jam nut from the left
and right hydraulic pump pressure output port and replace with new
parts. The NPRM also proposed to require you to install a hydraulic
pump case drain check valve.
Comments
We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 182 airplanes in the U.S.
registry.
We estimate the following costs to do the modifications:
[[Page 67715]]
------------------------------------------------------------------------
Total cost Total cost
Labor cost Parts cost per on U.S.
airplane operators
------------------------------------------------------------------------
Hydraulic pressure output fitting $100 $740 $134,680
assembly: 8 work-hours x $80 per
hour = $640.....................
Hydraulic pump case drain check 4,353 5,633 1,025,206
valve: 16 work-hours x $80 per
hour = $1,280...................
------------------------------------------------------------------------
HBC will provide warranty credit as specified in Hawker Beechcraft
Mandatory Service Bulletin SB 29-3869, dated January 2008; and Hawker
Beechcraft Mandatory Service Bulletin SB 29-3851, dated January 2008.
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 AD.
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 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 a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2008-0492; Directorate Identifier 2008-CE-023-AD'' in your
request.
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 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. FAA amends Sec. 39.13 by adding the following new AD:
2008-23-13 Hawker Beechcraft Corporation: Amendment 39-15734; Docket
No. FAA-2008-0492; Directorate Identifier 2008-CE-023-AD.
Effective Date
(a) This AD becomes effective on December 22, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 390 airplanes, serial numbers RB-4
through RB-224, that are certificated in any category.
Unsafe Condition
(d) This AD results from nine occurrences of hydraulic fluid
leaking from the engine hydraulic pump output fitting as a result of
an improperly installed elbow connecting the output port to the
pulse dampener hose. We are issuing this AD to prevent hydraulic
fluid leaking from the left and right hydraulic fluid pump and to
prevent the flow of hydraulic fluid into the engine compartment. The
loss of hydraulic fluid can result in loss of airplane hydraulic
system pressure and the consequent loss of hydraulic system
functions including gear extension/retraction, spoiler functions,
and anti-skid braking system actuation. The inability of the
hydraulic installation to isolate flow of hydraulic fluid could
result in a hazardous amount of flammable fluid in the corresponding
engine compartment. These conditions, if not corrected, could result
in loss of system functions and/or fire in the engine compartment.
Compliance
(e) To address this problem, you must do the following, unless
already done:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Remove current preformed Within the next 200 Follow Hawker
packing (part number (P/N) hours time-in- Beechcraft
MS28778-6), elbow fitting service (TIS) after Mandatory Service
(P/N MS21908J6), and jam December 22, 2008 Bulletin SB 29-
nut (P/N AN924-6J) from the (the effective date 3869, dated January
left and right hydraulic of this AD) or 2008.
pump pressure output port within the next 6
and install new preformed months after
packing (P/N MS28778-6), December 22, 2008
union (P/N MS21902J6), and (the effective date
swivel fitting (P/N of this AD),
NAS1762J0606) in the left whichever occurs
and right hydraulic first.
pressure pump output port.
(2) Install hydraulic pump Within the next 200 Hawker Beechcraft
case drain check valve Kit hours TIS after Mandatory Service
No. 390-5803-0001. December 22, 2008 Bulletin SB 29-
(the effective date 3851, dated January
of this AD) or 2008.
within the next 6
months after
December 22, 2008
(the effective date
of this AD),
whichever occurs
first.
------------------------------------------------------------------------
[[Page 67716]]
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Aaron Waters, Aerospace Engineer, Wichita ACO, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4174;
fax: (316) 946-4107. Before using any approved AMOC on any airplane
to which the AMOC applies, notify your appropriate principal
inspector (PI) in the FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
Material Incorporated by Reference
(g) You must use Hawker Beechcraft Mandatory Service Bulletin SB
29-3869, dated January 2008; and Hawker Beechcraft Mandatory Service
Bulletin SB 29-3851, dated January 2008, to do the actions required
by this AD, unless the AD specifies otherwise.
(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
Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas
67201; telephone: (316) 676-5034; fax: (316) 676-6614; Internet:
https://www.hawkerbeechcraft.com/service_support/pubs/.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; 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.
Issued in Kansas City, Missouri, on November 5, 2008.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-26879 Filed 11-14-08; 8:45 am]
BILLING CODE 4910-13-P
