Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes, 48143-48151 [E9-21033]
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Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations
TABLE 1—ENGINE MODELS AFFECTED
O–470–G, K, L, R, S, M, U
IO–470–C, D, E, F, H, L, M, N, S, U, V, VO
TSIO–470–B, C, D
IO–520–A, B, BA, BB, C, CB, D, E, F, J, K,
L, M, MB
TSIO–520–AF, B, BB, C, CE, D, DB, E, EB,
G, H, J, JB, K, KB, L, LB, M, N, NB, P, R,
T, UB, VB, WB
IO–550–A, B, C, D, E, F, L
IOF–550–B, C, D, E, F, L
(d) These engines are installed on, but not
limited to, Alexandria Aircraft LLC (formerly
Bellanca) model 300 Super Viking; Beech
Bonanza 33, 35 and 36 series, Beech Baron
56 and 58 series, Cessna 180, 182, 188, 205,
206, 207, 210, 303, 310, 320, 402, and 414
model series; Aero Commander 200 and 500;
certain Rockwell (formerly Meyers)
Windecker Eagle 200, and Navion airplanes.
Unsafe Condition
(e) This AD results from reports of 35 EQ3
cylinders found cracked. We are issuing this
AD to prevent loss of engine power due to
cracks in the cylinder head, possible engine
failure, and fire in the engine compartment.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Identification and Initial Visual Inspection
(g) Within 20 flight hours after the effective
date of this AD, identify EQ3 cylinders using
Step 1 of TCM MSB No. MSB09–1B, dated
July 14, 2009.
(1) Within 20 flight hours after the effective
date of this AD, for EQ3 cylinders with 400
or more hours total time of operation on the
effective date of this AD, perform an initial
visual inspection of the cylinder for cracks
using Step 2, paragraph B, of TCM MSB No.
MSB09–1B, dated July 14, 2009.
(2) For EQ3 cylinders with fewer than 400
hours total time of operation on the effective
date of this AD, perform an initial visual
inspection of the cylinder for cracks before
reaching 400 hours total time of operation,
using Step 2, paragraph B, of TCM MSB No.
MSB09–1B, dated July 14, 2009.
(3) Remove from service before flight, any
cylinders found cracked.
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Repetitive Visual Inspections
(h) Repeat the visual inspections required
by this AD every 50 hours of operation. Use
Step 2, paragraph B, of TCM MSB No.
MSB09–1B, dated July 14, 2009, to perform
the inspection.
(i) Remove from service before flight, any
cylinders found cracked.
Removal of All EQ3 Cylinders From Service
(j) Within 1,300 hours total time of
operation after the effective date of this AD,
remove all EQ3 cylinders from service.
Previous Credit
DEPARTMENT OF TRANSPORTATION
(l) Initial visual inspections done before
the effective date of this AD per TCM MSB
No. MSB09–1A, dated March 11, 2009,
comply with the initial inspection
requirements specified in this AD.
Alternative Methods of Compliance
(m) The Manager, Atlanta Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
Special Flight Permits
(n) Under 14 CFR 39.23, we are limiting
the special flight permits for this AD to
engines that have no evidence of fuel or
combustion staining in the cylinder crack
location, and for a total special flight time of
5 hours.
Related Information
(o) Contact Anthony Holton, Engineer,
Propulsion, Atlanta Aircraft Certification
Office, FAA, Small Airplane Directorate,
1701 Columbia Avenue, College Park,
Georgia 30337; e-mail
anthony.holton@faa.gov; telephone: (404)
474–5567; fax: (404) 474–5606, for more
information about this AD.
Material Incorporated by Reference
(p) You must use Teledyne Continental
Motors Mandatory Service Bulletin No.
MSB09–1B, dated July 14, 2009, to perform
the actions required by this AD. The Director
of the Federal Register approved the
incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Teledyne
Continental Motors, Inc., PO Box 90, Mobile,
AL 36601; telephone (251) 438–3411, or go
to: https://tcmlink.com/servicebulletins.cfm,
for a copy of this service information. You
may review copies at the FAA, New England
Region, 12 New England Executive Park,
Burlington, MA; 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 Burlington, Massachusetts, on
September 8, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–22287 Filed 9–21–09; 8:45 am]
BILLING CODE 4910–13–P
EQ3 Cylinder Installation Prohibition
(k) After the effective date of this AD, do
not install any EQ3 cylinder onto any engine,
or any EQ3 cylinder-equipped engine, onto
any aircraft.
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0292; Directorate
Identifier 2008–NM–011–AD; Amendment
39–16011; AD 2009–18–15]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300, A310, and A300–600 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A300 and A310 series airplanes. That
AD currently requires replacement of
the nose landing gear drag strut upper
attachment pin. This new AD requires
revising the Airworthiness Limitations
section (ALS) of the Instructions for
Continued Airworthiness (ICA) to
require additional life limits and/or
replacements for certain main landing
gear and nose landing gear components,
and also expands the applicability. This
AD results from revisions to the ALS of
the ICA to include new or more
restrictive life limits and/or
replacements. We are issuing this AD to
ensure the continued structural integrity
of these airplanes.
DATES: This AD becomes effective
October 27, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 27, 2009.
ADDRESSES: For service information
identified in this AD, contact Airbus
SAS—EAW (Airworthiness Office), 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
61 93 36 96; fax +33 5 61 93 44 51; email: account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
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Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Tom
Stafford, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1622; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 87–16–06, amendment
39–5692 (52 FR 28241, July 29, 1987).
The existing AD applies to certain
Airbus Model A300 and A310 series
airplanes. That NPRM was published in
the Federal Register on April 1, 2009
(74 FR 14751). That NPRM proposed to
continue to require replacement of the
nose landing gear drag strut upper
attachment pin. That NPRM also
proposed to require revising the
Airworthiness Limitations section (ALS)
of the Instructions for Continued
Airworthiness (ICA) to require
additional life limits and/or
replacements for certain main landing
gear and nose landing gear components,
and would also expand the
applicability.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request To Add Grace Period
TradeWinds Airlines requests that we
add a ‘‘grace period’’ to the life limit
placed on the nose landing gear (NLG)
shock absorber bottom, part number
(P/N) C62037–1, listed in Table 1 of the
NPRM, as referenced in paragraph
(h)(1)(i) of the NPRM. TradeWinds
explains that this component was not
listed in Chapter 5 of the Airbus A300
Airplane Maintenance Manual (AMM)
and had no corresponding FAA AD
issued against it. Therefore, for U.S.
operators, there was never a
requirement to track the life limit.
TradeWinds suggests a grace period of
the next NLG overhaul or restoration be
added so this internal component can be
replaced without unscheduled removal
from the airplane.
We do not agree that it is necessary
to add a grace period based on the
operator’s next overhaul or restoration.
Maintenance schedules vary among
operators; there is no assurance that the
overhaul or restoration would occur
within the maximum interval of time
allowable for the affected airplanes to
operate safely. However, under the
provisions of paragraph (l) of this AD,
we will consider requests for
adjustments to the compliance time if
data are submitted to substantiate that
such an adjustment would provide an
acceptable level of safety. We have not
changed the AD in this regard.
Information Letter (SIL) 32–118,
Revision 02, dated October 24, 2007, as
referenced in paragraph (j) of the NPRM.
TradeWinds requests a note or some
clarification to describe the use or
application of the SIL as it pertains to
the AD.
We agree with the request to clarify
the purpose of the SIL. We have added
Note 2 to the AD to include the
following information from page 1 of the
SIL:
Note 2: Airbus Service Information Letter
32–118, Revision 02, dated October 24, 2007,
provides operators with guidance on the
means to assign a conservative calculated life
to parts whose history of accumulated
landings is partial or unknown; and to select
the limitations applicable to parts whose
history of application details (aircraft type,
aircraft model, weight variant, etc.) is partial
or unknown.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, and determined
that air safety and the public interest
require adopting the AD with the
change described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
Request To Clarify Purpose of Service
Information Letter (SIL)
TradeWinds Airlines requests that we
clarify the purpose of Airbus Service
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Work
hours
Action
Replacement (required by AD 87–16–06) ...............................
Revision (new action) ..............................................................
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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
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7
1
Average
labor rate
per hour
$80
80
$3,300
0
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 have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
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Cost per
airplane
Parts
$3,860
80
Number
of U.S.registered
airplanes
94
238
Fleet cost
$362,840
19,040
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
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
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Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
Affected ADs
List of Subjects in 14 CFR Part 39
Subject
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Applicability
(c) This AD applies to all Airbus Model
A300, A310, and A300–600 series airplanes,
certificated in any category.
(d) Air Transport Association (ATA) of
America Code 32: Landing Gear.
Unsafe Condition
(e) This AD results from revisions to the
Airworthiness Limitations section (ALS) of
the Instructions for Continued Airworthiness
(ICA) to include new or more restrictive life
limits and/or replacements. We are issuing
this AD to ensure the continued structural
integrity of these airplanes.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
Compliance
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
(b) This AD supersedes AD 87–16–06.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–5692 (52
FR 28241, July 29, 1987) and by adding
the following new airworthiness
directive (AD):
■
2009–18–15 Airbus: Amendment 39–16011.
Docket No. FAA–2009–0292; Directorate
Identifier 2008–NM–011–AD.
Effective Date
(a) This AD becomes effective October 27,
2009.
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new replacements. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these replacements,
the operator may not be able to accomplish
the replacements described in the revisions.
In this situation, to comply with 14 CFR
91.403(c), the operator must request approval
for an alternative method of compliance
according to paragraph (l) of this AD. The
request should include a description of
changes to the required replacements that
will ensure the continued operational safety
of the airplane.
48145
Restatement of the Requirements of AD 87–
16–06
(g) For Model A300 and A310 series
airplanes: Prior to the accumulation of 16,000
landings, or within the next 2,000 landings
after September 3, 1987 (the effective date of
AD 87–16–06), whichever occurs later,
replace the nose landing gear drag strut
upper attachment pin in accordance with
Airbus Service Bulletin A300–32–374,
Revision 1, dated July 15, 1986 (applicable to
Model A300 airplanes); or A310–32–2023,
Revision 2, dated November 14, 1986
(applicable to Model A310 airplanes).
New Requirements of This AD
ALS Revision
(h) For Model A300, A310, and A300–600
series airplanes: Within 3 months after the
effective date of this AD, revise the ALS of
the ICA to incorporate the applicable
document listed in paragraph (h)(1), (h)(2), or
(h)(3) of this AD. Accomplishing the actions
specified in the applicable document satisfies
the requirements of paragraph A. of AD 84–
02–04, amendment 39–4795.
(1) For Model A300 series airplanes:
Incorporate the applicable document listed in
paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
(i) Section 05–10–00, Revision 28, dated
February 27, 1998, of Chapter 05, ‘‘Service
Life Limits and Maintenance Checks,’’ of the
Airbus A300 Aircraft Maintenance Manual,
except that the parts listed in Table 1 of this
AD are subject to the life limits defined in
the document listed in paragraph (h)(1)(ii) of
this AD.
(ii) ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated Fatigue Lives’’ of Part
1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated September 6, 2007, of the
Airbus A300 ALS.
TABLE 1—PARTS SUBJECT TO THE LIFE LIMITS SPECIFIED IN THE DOCUMENT IDENTIFIED IN PARAGRAPH (H)(1)(II) OF THIS
AD
Part No. (P/N)
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P/N
P/N
P/N
P/N
Part name
C61643–2, P/N C61643–4, P/N C61643–5 ...............................................................
A32210001205xx ........................................................................................................
C62037–1 ...................................................................................................................
196–0328–501 ............................................................................................................
(2) For Model A310 series airplanes:
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated December 21, 2006, of the
Airbus A310 ALS.
(3) For Model A300–600 series airplanes:
Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and
‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’
of Part 1, ‘‘Safe Life Airworthiness Limitation
Items,’’ dated December 21, 2006, of the
Airbus A300–600 ALS.
Initial Compliance Times and Repetitive
Inspections
(i) Do the replacement at the applicable
time specified in paragraph (i)(1) or (i)(2) of
this AD, except as provided by paragraph (j)
of this AD. The replacement must be done
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Main landing gear (MLG) shock absorber end fitting.
Nose landing gear (NLG) pintle pin.
NLG shock absorber bottom.
Cross beam (Pratt & Whitney forward engine mount).
thereafter within the interval specified in the
applicable document identified in paragraph
(h)(1), (h)(2), or (h)(3) of this AD.
(1) For any life limitation/task that has
been complied with before the effective date
of this AD in accordance with the applicable
document listed in paragraph (h)(1), (h)(2), or
(h)(3) of this AD, or in accordance with
paragraph (g) of this AD, use the last
accomplishment of each limitation/task as a
starting point for accomplishing each
corresponding limitation/task required by
this AD.
(2) For any life limitation/task that has not
been complied with before the effective date
of this AD in accordance with the applicable
document listed in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD, or in accordance with
paragraph (g) of this AD, the initial
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compliance time starts from the date of initial
entry into service as defined in the applicable
document.
Special Compliance Times
(j) For any airplane on which the history
of accumulated landings is partial or
unknown, or where the history of application
details (airplane type, model, weight variant,
etc.) is partial or unknown, with or without
using the information in Airbus Service
Information Letter 32–118, Revision 02,
dated October 24, 2007: Parts listed in Figure
1 of this AD must be replaced at the
associated compliance time. The replacement
must be done thereafter at the interval
specified in the applicable document(s)
specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD.
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Note 2: Airbus Service Information Letter
32–118, Revision 02, dated October 24, 2007,
provides operators with guidance on the
means to assign a conservative calculated life
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to parts whose history of accumulated
landings is partial or unknown; and to select
the limitations applicable to parts whose
history of application details (aircraft type,
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aircraft model, weight variant, etc.) is partial
or unknown.
BILLING CODE 4910–13–P
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BILLING CODE 4910–13–C
Alternative Intervals or Limits
(k) Except as provided by paragraph (l) of
this AD, after accomplishing the actions
specified in paragraphs (h), (i), and (j) of this
AD, no alternative replacements, replacement
intervals, or limitations may be used.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, 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: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; fax (425) 227–1149.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
Related Information
(m) European Aviation Safety Agency
(EASA) Airworthiness Directive 2007–0293,
dated November 29, 2007, also addresses the
subject of this AD.
Material Incorporated by Reference
(n) You must use the service information
contained in Table 2 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise.
TABLE 2—MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Section 05–10–00 of Chapter 05, ‘‘Service Life Limits and Maintenance Checks,’’ of the Airbus A300 Aircraft Maintenance Manual.
Airbus A300 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitations Items’’ ......
Airbus A300–600 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitations
Items’’.
Airbus A310 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items’’ ........
Airbus Service Bulletin A300–32–374 ...............................................................................................................
Airbus Service Bulletin A310–32–2023 .............................................................................................................
28 .............
February 27, 1998.
Original ....
Original ....
September 6, 2007.
December 21, 2006.
Original ....
1 ...............
2 ..............
December 21, 2006.
July 15, 1986.
November 14, 1986.
Airbus Service Bulletin A300–32–374,
Revision 1, dated July 15, 1986, has the
following effective pages:
Revision
level
shown on
page
1, 3–8, 11
2 .............
1 ..............
Original ...
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page
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Revision
level
shown on
page
Date shown on
page
1, 5–9 .....
2, 4 .........
3 .............
2 ..............
1 ..............
Original ...
November 14, 1986
July 15, 1986
April 16, 1986
Chapter 05 of Airbus A300 Aircraft
Maintenance Manual has the following
effective pages:
July 15, 1986.
April 16, 1986.
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Page No.
(Airbus Service Bulletin A300–32–374,
Revision 1, dated July 15, 1986 does not
contain pages 9 and 10.)
Airbus Service Bulletin A310–32–2023,
Revision 2, dated November 14, 1986, has the
following effective pages:
Date
Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations
48151
LIST OF EFFECTIVE PAGES
Page title/description
Page No.(s)
Revision No.
AMM Title Page ....................................................................
Chapter 05 Record of Revisions ..........................................
Chapter 05 Effective Pages ..................................................
Chapter 05 Table of Contents ..............................................
Section 05–10–00 .................................................................
None shown ..........................
1–2 ........................................
1–4 ........................................
1–4 ........................................
1 ............................................
None shown * ........................
28 ..........................................
None shown * ........................
None shown * ........................
None shown * ........................
Date shown on
page(s)
February
February
February
February
February
27,
27,
27,
27,
27,
1998.
1998.
1998.
1998.
1998.
* The revision number is indicated only in the Record of Revisions section of Chapter 05.
(The List of Effective Pages (LOEP) for
Chapter 05 of the Airbus A300 Aircraft
Maintenance Manual contains the following
errors: Transmittal Letter page, page 4 of the
LOEP and Table of Contents sections, page 2
of Subsection 05–00–01, page 1 of Subsection
05–11–11, and Subsection 05–10–00, are not
listed in the LOEP; and the LOEP also does
not specify a date for the Record of Revisions
page. In addition, the LOEP identifies three
pages for Subsection 05–11–00,
Configuration 5; however, only one page
exists. The LOEP identifies three pages for
Subsection 05–11–00, Configuration 9;
however, those pages do not exist.)
(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 Airbus SAS—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference 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 Renton, Washington, on August
24, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–21033 Filed 9–21–09; 8:45 am]
erowe on DSK5CLS3C1PROD with RULES
BILLING CODE 4910–13–P
DEPARTMENT OF THE TREASURY
PART 1—INCOME TAXES
Internal Revenue Service
■
26 CFR Part 1
Paragraph 1. The authority citation
for part 1 continues to read in part as
follows:
[TD 9452]
■
Authority: 26 U.S.C. 7805 * * *
RIN 1545–BB28
Application of Separate Limitations to
Dividends From Noncontrolled Section
902 Corporations; Correction
Par. 2. Section 1.964–1 is amended by
revising the last sentence of paragraph
(c)(2) and paragraph (c)(4)(i)(D) to read
as follows:
§ 1.964–1 Determination of the earnings
and profits of a foreign corporation.
AGENCY: Internal Revenue Service (IRS),
Treasury.
ACTION: Correcting amendment.
SUMMARY: This document contains
corrections to final regulations (TD
9452) that were published in the
Federal Register on Thursday, June 11,
2009, regarding the application of
separate foreign tax credit limitations to
dividends received from noncontrolled
section 902 corporations.
DATES: This correction is effective on
September 22, 2009 and is applicable in
taxable years ending on or after April
20, 2009.
FOR FURTHER INFORMATION CONTACT:
Richard Chewning, (202) 622–3850 (not
a toll-free number).
SUPPLEMENTARY INFORMATION:
The final regulations that are the
subject of this document are under
section 964 of the Internal Revenue
Code.
DEPARTMENT OF DEFENSE
Department of the Army, Corps of
Engineers
Need for Correction
As published on Thursday, June 11,
2009 (74 FR 27886), the final regulations
(TD 9452) contain errors that may prove
to be misleading and are in need of
clarification.
33 CFR Part 334
List of Subjects in 26 CFR Part 1
AGENCY: U.S. Army Corps of Engineers,
Department of Defense.
ACTION: Final rule.
Income taxes, Reporting and
recordkeeping requirements.
Accordingly, 26 CFR part 1 is
corrected by making the following
correcting amendments:
Jkt 217001
LaNita VanDyke,
Chief, Publications and Regulations Branch,
Legal Processing Division, Associate Chief
Counsel, (Procedure and Administration).
[FR Doc. E9–22694 Filed 9–21–09; 8:45 am]
BILLING CODE 4830–01–P
■
15:26 Sep 21, 2009
*
*
*
*
(c) * * *
(2) * * * See also §§ 1.985–5, 1.985–
6, and 1.985–7 relating to adjustments to
earnings and profits of a QBU required
when the QBU changes its functional
currency or begins to use the dollar
approximate separate transactions
method of accounting.
(4) * * *
(i) * * *
(D) Whether the domestic shareholder
received the written notice required by
paragraph (c)(3)(iii) of this section.
*
*
*
*
*
Background
Correction of Publication
VerDate Nov<24>2008
*
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
United States Navy Restricted Area,
SUPSHIP Bath Detachment Mobile,
Mobile, AL
SUMMARY: The U.S. Army Corps of
Engineers (Corps) is adding regulations
to establish a restricted area around the
AUSTAL, USA shipbuilding facility
located in Mobile, Alabama, because of
E:\FR\FM\22SER1.SGM
22SER1
]]>Agencies
[Federal Register Volume 74, Number 182 (Tuesday, September 22, 2009)]
[Rules and Regulations]
[Pages 48143-48151]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-21033]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0292; Directorate Identifier 2008-NM-011-AD;
Amendment 39-16011; AD 2009-18-15]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A300 and A310 series
airplanes. That AD currently requires replacement of the nose landing
gear drag strut upper attachment pin. This new AD requires revising the
Airworthiness Limitations section (ALS) of the Instructions for
Continued Airworthiness (ICA) to require additional life limits and/or
replacements for certain main landing gear and nose landing gear
components, and also expands the applicability. This AD results from
revisions to the ALS of the ICA to include new or more restrictive life
limits and/or replacements. We are issuing this AD to ensure the
continued structural integrity of these airplanes.
DATES: This AD becomes effective October 27, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 27,
2009.
ADDRESSES: For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail: account.airworth-eas@airbus.com; Internet https://www.airbus.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West
[[Page 48144]]
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 87-16-06, amendment 39-
5692 (52 FR 28241, July 29, 1987). The existing AD applies to certain
Airbus Model A300 and A310 series airplanes. That NPRM was published in
the Federal Register on April 1, 2009 (74 FR 14751). That NPRM proposed
to continue to require replacement of the nose landing gear drag strut
upper attachment pin. That NPRM also proposed to require revising the
Airworthiness Limitations section (ALS) of the Instructions for
Continued Airworthiness (ICA) to require additional life limits and/or
replacements for certain main landing gear and nose landing gear
components, and would also expand the applicability.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Add Grace Period
TradeWinds Airlines requests that we add a ``grace period'' to the
life limit placed on the nose landing gear (NLG) shock absorber bottom,
part number (P/N) C62037-1, listed in Table 1 of the NPRM, as
referenced in paragraph (h)(1)(i) of the NPRM. TradeWinds explains that
this component was not listed in Chapter 5 of the Airbus A300 Airplane
Maintenance Manual (AMM) and had no corresponding FAA AD issued against
it. Therefore, for U.S. operators, there was never a requirement to
track the life limit. TradeWinds suggests a grace period of the next
NLG overhaul or restoration be added so this internal component can be
replaced without unscheduled removal from the airplane.
We do not agree that it is necessary to add a grace period based on
the operator's next overhaul or restoration. Maintenance schedules vary
among operators; there is no assurance that the overhaul or restoration
would occur within the maximum interval of time allowable for the
affected airplanes to operate safely. However, under the provisions of
paragraph (l) of this AD, we will consider requests for adjustments to
the compliance time if data are submitted to substantiate that such an
adjustment would provide an acceptable level of safety. We have not
changed the AD in this regard.
Request To Clarify Purpose of Service Information Letter (SIL)
TradeWinds Airlines requests that we clarify the purpose of Airbus
Service Information Letter (SIL) 32-118, Revision 02, dated October 24,
2007, as referenced in paragraph (j) of the NPRM. TradeWinds requests a
note or some clarification to describe the use or application of the
SIL as it pertains to the AD.
We agree with the request to clarify the purpose of the SIL. We
have added Note 2 to the AD to include the following information from
page 1 of the SIL:
Note 2:
Airbus Service Information Letter 32-118, Revision 02, dated
October 24, 2007, provides operators with guidance on the means to
assign a conservative calculated life to parts whose history of
accumulated landings is partial or unknown; and to select the
limitations applicable to parts whose history of application details
(aircraft type, aircraft model, weight variant, etc.) is partial or
unknown.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work Average Cost per U.S.-
Action hours labor rate Parts airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Replacement (required by AD 87-16-06). 7 $80 $3,300 $3,860 94 $362,840
Revision (new action)................. 1 80 0 80 238 19,040
----------------------------------------------------------------------------------------------------------------
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 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 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
[[Page 48145]]
under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-5692 (52 FR 28241, July 29, 1987) and by adding
the following new airworthiness directive (AD):
2009-18-15 Airbus: Amendment 39-16011. Docket No. FAA-2009-0292;
Directorate Identifier 2008-NM-011-AD.
Effective Date
(a) This AD becomes effective October 27, 2009.
Affected ADs
(b) This AD supersedes AD 87-16-06.
Applicability
(c) This AD applies to all Airbus Model A300, A310, and A300-600
series airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Unsafe Condition
(e) This AD results from revisions to the Airworthiness
Limitations section (ALS) of the Instructions for Continued
Airworthiness (ICA) to include new or more restrictive life limits
and/or replacements. We are issuing this AD to ensure the continued
structural integrity of these airplanes.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new replacements. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these replacements, the operator may not be able
to accomplish the replacements described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (l) of this AD. The request should include a
description of changes to the required replacements that will ensure
the continued operational safety of the airplane.
Restatement of the Requirements of AD 87-16-06
(g) For Model A300 and A310 series airplanes: Prior to the
accumulation of 16,000 landings, or within the next 2,000 landings
after September 3, 1987 (the effective date of AD 87-16-06),
whichever occurs later, replace the nose landing gear drag strut
upper attachment pin in accordance with Airbus Service Bulletin
A300-32-374, Revision 1, dated July 15, 1986 (applicable to Model
A300 airplanes); or A310-32-2023, Revision 2, dated November 14,
1986 (applicable to Model A310 airplanes).
New Requirements of This AD
ALS Revision
(h) For Model A300, A310, and A300-600 series airplanes: Within
3 months after the effective date of this AD, revise the ALS of the
ICA to incorporate the applicable document listed in paragraph
(h)(1), (h)(2), or (h)(3) of this AD. Accomplishing the actions
specified in the applicable document satisfies the requirements of
paragraph A. of AD 84-02-04, amendment 39-4795.
(1) For Model A300 series airplanes: Incorporate the applicable
document listed in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
(i) Section 05-10-00, Revision 28, dated February 27, 1998, of
Chapter 05, ``Service Life Limits and Maintenance Checks,'' of the
Airbus A300 Aircraft Maintenance Manual, except that the parts
listed in Table 1 of this AD are subject to the life limits defined
in the document listed in paragraph (h)(1)(ii) of this AD.
(ii) ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3:
Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness
Limitation Items,'' dated September 6, 2007, of the Airbus A300 ALS.
Table 1--Parts Subject to the Life Limits Specified in the Document Identified in Paragraph (h)(1)(ii) of This
AD
----------------------------------------------------------------------------------------------------------------
Part No. (P/N) Part name
----------------------------------------------------------------------------------------------------------------
P/N C61643-2, P/N C61643-4, P/N Main landing gear (MLG) shock absorber end fitting.
C61643-5.
P/N A32210001205xx.................. Nose landing gear (NLG) pintle pin.
P/N C62037-1........................ NLG shock absorber bottom.
P/N 196-0328-501.................... Cross beam (Pratt & Whitney forward engine mount).
----------------------------------------------------------------------------------------------------------------
(2) For Model A310 series airplanes: Incorporate ``Sub-part 1-
2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives''
of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated
December 21, 2006, of the Airbus A310 ALS.
(3) For Model A300-600 series airplanes: Incorporate ``Sub-part
1-2: Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives''
of Part 1, ``Safe Life Airworthiness Limitation Items,'' dated
December 21, 2006, of the Airbus A300-600 ALS.
Initial Compliance Times and Repetitive Inspections
(i) Do the replacement at the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD, except as provided by
paragraph (j) of this AD. The replacement must be done thereafter
within the interval specified in the applicable document identified
in paragraph (h)(1), (h)(2), or (h)(3) of this AD.
(1) For any life limitation/task that has been complied with
before the effective date of this AD in accordance with the
applicable document listed in paragraph (h)(1), (h)(2), or (h)(3) of
this AD, or in accordance with paragraph (g) of this AD, use the
last accomplishment of each limitation/task as a starting point for
accomplishing each corresponding limitation/task required by this
AD.
(2) For any life limitation/task that has not been complied with
before the effective date of this AD in accordance with the
applicable document listed in paragraphs (h)(1), (h)(2), and (h)(3)
of this AD, or in accordance with paragraph (g) of this AD, the
initial compliance time starts from the date of initial entry into
service as defined in the applicable document.
Special Compliance Times
(j) For any airplane on which the history of accumulated
landings is partial or unknown, or where the history of application
details (airplane type, model, weight variant, etc.) is partial or
unknown, with or without using the information in Airbus Service
Information Letter 32-118, Revision 02, dated October 24, 2007:
Parts listed in Figure 1 of this AD must be replaced at the
associated compliance time. The replacement must be done thereafter
at the interval specified in the applicable document(s) specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
[[Page 48146]]
Note 2: Airbus Service Information Letter 32-118, Revision 02,
dated October 24, 2007, provides operators with guidance on the
means to assign a conservative calculated life to parts whose
history of accumulated landings is partial or unknown; and to select
the limitations applicable to parts whose history of application
details (aircraft type, aircraft model, weight variant, etc.) is
partial or unknown.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR22SE09.000
[[Page 48147]]
[GRAPHIC] [TIFF OMITTED] TR22SE09.001
[[Page 48148]]
[GRAPHIC] [TIFF OMITTED] TR22SE09.002
[[Page 48149]]
[GRAPHIC] [TIFF OMITTED] TR22SE09.003
[[Page 48150]]
[GRAPHIC] [TIFF OMITTED] TR22SE09.004
BILLING CODE 4910-13-C
Alternative Intervals or Limits
(k) Except as provided by paragraph (l) of this AD, after
accomplishing the actions specified in paragraphs (h), (i), and (j)
of this AD, no alternative replacements, replacement intervals, or
limitations may be used.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, ANM-116, International Branch, Transport
Airplane Directorate, 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: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-1622; fax (425) 227-1149.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Related Information
(m) European Aviation Safety Agency (EASA) Airworthiness
Directive 2007-0293, dated November 29, 2007, also addresses the
subject of this AD.
Material Incorporated by Reference
(n) You must use the service information contained in Table 2 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
Table 2--Material Incorporated by Reference
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Section 05-10-00 of Chapter 28........... February 27, 1998.
05, ``Service Life Limits
and Maintenance Checks,'' of
the Airbus A300 Aircraft
Maintenance Manual.
Airbus A300 Airworthiness Original..... September 6, 2007.
Limitations Section, ALS
Part 1, ``Safe Life
Airworthiness Limitations
Items''.
Airbus A300-600 Airworthiness Original..... December 21, 2006.
Limitations Section, ALS
Part 1, ``Safe Life
Airworthiness Limitations
Items''.
Airbus A310 Airworthiness Original..... December 21, 2006.
Limitations Section, ALS
Part 1, ``Safe Life
Airworthiness Limitation
Items''.
Airbus Service Bulletin A300- 1............ July 15, 1986.
32-374.
Airbus Service Bulletin A310- 2............ November 14, 1986.
32-2023.
------------------------------------------------------------------------
Airbus Service Bulletin A300-32-374, Revision 1, dated July 15,
1986, has the following effective pages:
------------------------------------------------------------------------
Revision
Page No. level shown Date shown on page
on page
------------------------------------------------------------------------
1, 3-8, 11.................... 1............ July 15, 1986.
2............................. Original..... April 16, 1986.
------------------------------------------------------------------------
(Airbus Service Bulletin A300-32-374, Revision 1, dated July 15,
1986 does not contain pages 9 and 10.)
Airbus Service Bulletin A310-32-2023, Revision 2, dated November
14, 1986, has the following effective pages:
------------------------------------------------------------------------
Revision
Page No. level shown Date shown on page
on page
------------------------------------------------------------------------
1, 5-9........................ 2............ November 14, 1986
2, 4.......................... 1............ July 15, 1986
3............................. Original..... April 16, 1986
------------------------------------------------------------------------
Chapter 05 of Airbus A300 Aircraft Maintenance Manual has the
following effective pages:
[[Page 48151]]
List of Effective Pages
----------------------------------------------------------------------------------------------------------------
Page title/description Page No.(s) Revision No. Date shown on page(s)
----------------------------------------------------------------------------------------------------------------
AMM Title Page.................... None shown........... None shown *......... February 27, 1998.
Chapter 05 Record of Revisions.... 1-2.................. 28................... February 27, 1998.
Chapter 05 Effective Pages........ 1-4.................. None shown *......... February 27, 1998.
Chapter 05 Table of Contents...... 1-4.................. None shown *......... February 27, 1998.
Section 05-10-00.................. 1.................... None shown *......... February 27, 1998.
----------------------------------------------------------------------------------------------------------------
* The revision number is indicated only in the Record of Revisions section of Chapter 05.
(The List of Effective Pages (LOEP) for Chapter 05 of the Airbus
A300 Aircraft Maintenance Manual contains the following errors:
Transmittal Letter page, page 4 of the LOEP and Table of Contents
sections, page 2 of Subsection 05-00-01, page 1 of Subsection 05-11-
11, and Subsection 05-10-00, are not listed in the LOEP; and the
LOEP also does not specify a date for the Record of Revisions page.
In addition, the LOEP identifies three pages for Subsection 05-11-
00, Configuration 5; however, only one page exists. The LOEP
identifies three pages for Subsection 05-11-00, Configuration 9;
however, those pages do not exist.)
(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
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference 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 Renton, Washington, on August 24, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-21033 Filed 9-21-09; 8:45 am]
BILLING CODE 4910-13-P
