Airworthiness Directives; Cessna Aircraft Company Airplanes, 53308-53312 [2011-21210]
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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on August
2, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–21625 Filed 8–25–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27747; Directorate
Identifier 2007–CE–030–AD; Amendment
39–16782; AD 2009–10–09 R2]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are revising an existing
airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna)
Models 150F, 150G, 150H, 150J, 150K,
150L, 150M, A150K, A150L, A150M,
F150F, F150G, F150H, F150J, F150K,
F150L, F150M, FA150K, FA150L,
FRA150L, FA150M, FRA150M, 152,
A152, F152, and FA152 airplanes. That
AD currently requires either installing a
placard prohibiting spins and other
acrobatic maneuvers in the airplane or
replacing the rudder stop, the rudder
stop bumper, and the attachment
hardware with a rudder stop
modification kit. This new AD requires
a change to the modification kit and
removal of a small amount of material
from the rudder horn assembly for those
that have not yet complied with the
existing AD or for those who can not
comply with the existing AD (because
they were unable to obtain full rudder
travel with the existing kits). This AD
was prompted by operators who have
reported difficulty in obtaining full
rudder travel with the existing
modification kit. We are issuing this AD
to revise the kits to use longer rivets and
allow a small amount of material to be
removed from the rudder horn
assembly, which allows operators to
obtain full rudder travel.
DATES: This AD is effective September
12, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 12, 2011.
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SUMMARY:
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We must receive any comments on
this AD by October 11, 2011.
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 comments.
• 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.
For service information identified in
this AD, contact Cessna Aircraft
Company, Product Support, P.O. Box
7706, Wichita, KS 67277; telephone:
(316) 517–5800; fax: (316) 517–7271;
Internet: https://www.cessna.com. You
may review copies of the referenced
service information at the FAA, Small
Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call 816–329–4148.
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 street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Ann
Johnson, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4105; fax: (316) 946–4107; e-mail:
ann.johnson@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On October 27, 2009, we issued AD
2009–10–09 R1, amendment 39–16074
(74 FR 57408, November 6, 2009), for
certain Cessna Aircraft Company
(Cessna) Models 150F, 150G, 150H,
150J, 150K, 150L, 150M, A150K, A150L,
A150M, F150F, F150G, F150H, F150J,
F150K, F150L, F150M, FA150K,
FA150L, FRA150L, FA150M, FRA150M,
152, A152, F152, and FA152 airplanes.
That AD requires installation of a
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placard prohibiting spins and other
acrobatic maneuvers in the airplane or
replacement of the rudder stop, rudder
stop bumper, and attachment hardware
with a new rudder stop modification kit
and replacement of the safety wire with
jamnuts. The revision was issued to
clarify certain model and serial number
designations, remove the duplicate
requirement of replacing the safety wire
with jamnuts, and clarify the
conditional acceptability of using
modification kit part number (P/N)
SK152–25 as a terminating action to that
AD. That AD resulted from follow-on
investigations of two accidents where
the rudder was found in the over-travel
position with the stop plate hooked over
the stop bolt heads. While neither of the
accident aircraft met type design,
investigations revealed that aircraft in
full conformity with type design can
exceed the travel limits set by the
rudder stops. We issued that AD to
prevent the rudder from traveling past
the normal travel limit. Operation in
this non-certificated control position is
unacceptable and could cause
undesirable consequences, such as
contact between the rudder and the
elevator.
Actions Since AD Was Issued
Since we issued AD 2009–10–09 R1
(74 FR 57408, November 6, 2009),
compliance with the existing AD
required operators to check for full
rudder travel with the installation of the
existing kits (P/N SK152–24A and P/N
SK152–25A). Some operators have
reported difficulty in obtaining full
rudder travel with these kits. To correct
this issue, Cessna has revised the kits to
use longer rivets and allow a small
amount of material to be removed from
the rudder horn assembly, which allows
operators to obtain full rudder travel.
Relevant Service Information
We reviewed Cessna Aircraft
Company Service Bulletin SEB01–1,
Revision 1, dated March 22, 2011;
Cessna Aircraft Company Service Kit
SK152–24B, dated March 22, 2011; and
Cessna Aircraft Company Service Kit
SK152–25B, dated March 22, 2011. The
service information describes
procedures for replacement of the
rudder stop, rudder stop bumper, and
attachment hardware with a new rudder
stop modification kit.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations
AD Requirements
This AD requires installation of a
placard prohibiting spins and other
acrobatic maneuvers in the airplane or
replacement of the rudder stop, rudder
stop bumper, and attachment hardware
with a new rudder stop modification kit.
Change to Existing AD
This AD would retain certain
requirements of AD 2009–10–09 R1 (74
FR 57408, November 6, 2009). Since AD
2009–10–09 R1 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIER
Requirement in AD
2009–10–09 R1
Corresponding
requirement in this
AD
paragraph (e)
paragraph (f)
paragraph (g)
paragraph (h)
FAA’s Justification and Determination
of the Effective Date
This action incorporates revised
modification kits that can be used by all
airplanes that would need the
modification incorporated in the future
and does not require any additional
work for those airplanes with the
modification already incorporated (see
table 3). Therefore, we find that notice
and opportunity for prior public
comment are unnecessary and that good
cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2007–27747 and directorate
identifier 2007–CE–030–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.
Costs of Compliance
We estimate that this AD affects
17,090 airplanes of U.S. registry.
Estimated Costs
We estimate the following costs to do
the insertion of the operational
limitation:
Action
Labor cost
Parts cost
Insert limitations and placard ........................
1 work-hour × $85 per hour = $85 ...............
Not applicable ..
Cost per
product
Cost on U.S.
operators
$85
$1,452,650
We estimate the following costs to do
the modification:
Action
Labor cost
Install a rudder stop modification kit ............
4 work-hours × $85 per hour = $340 ..........
The new requirements of this AD add
no additional economic burden. The
increased estimated cost of this AD is
due to increased labor cost from 2009
when AD 2009–10–09 R1 (74 FR 57408,
November 6, 2009) was issued.
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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
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
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Cost per
product
Parts cost
$90
Cost on U.S.
operators
$430
$7,348,700
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.
(4) 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.
Regulatory Findings
List of Subjects in 14 CFR Part 39
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),
(3) Will not affect intrastate aviation
in Alaska, and
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA 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.
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§ 39.13
Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations
FAA–2007–27747; Directorate Identifier
2007–CE–030–AD.
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2009–10–09 R1, Amendment 39–16074
(74 FR 57408, November 6, 2009), and
adding the following new AD:
■
(a) Effective Date
This AD is effective September 12, 2011.
(b) Affected ADs
This AD revises AD 2009–10–09 R1,
Amendment 39–16074 (74 FR 57408,
November 6, 2009).
(c) Applicability
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
2009–10–09 R2 Cessna Aircraft Company:
Amendment 39–16782; Docket No.
TABLE 1—APPLICABILITY
Models
Serial Nos.
(1) 150F .......................................
(2) 150G ......................................
(3) 150H ......................................
(4) 150J .......................................
(5) 150K .......................................
(6) 150L .......................................
(7) 150M ......................................
(8) A150K ....................................
(9) A150L .....................................
(10) A150M ..................................
(11) F150F ...................................
(12) F150G ..................................
(13) F150H ..................................
(14) F150J ...................................
(15) F150K ..................................
(16) F150L ...................................
(17) F150M ..................................
(18) FA150K ................................
(19) FA150L ................................
(20) FA150L or FRA150L ............
15061533 through 15064532.
15064533 through 15064969 and 15064971 through 15067198.
15067199 through 15069308 and 649.
15069309 through 15071128.
15071129 through 15072003.
15072004 through 15075781.
15075782 through 15079405.
A1500001 through A1500226.
A1500227 through A1500432 and A1500434 through A1500523.
A1500524 through A1500734 and 15064970.
F150–0001 through F150–0067.
F150–0068 through F150–0219.
F150–0220 through F150–0389.
F150–0390 through F150–0529.
F15000530 through F15000658.
F15000659 through F15001143.
F15001144 through F15001428.
FA1500001 through FA1500081.
FA1500082 through FA1500120.
FA1500121 through FA1500261 that are equipped with FKA150–2311 and FKA150–2316, or FRA1500121
through FRA1500261.
FA1500262 through FA1500336 that are equipped with FKA150–2311 and FKA150–2316, or FRA1500262
through FRA1500336.
15279406 through 15286033.
A1520735 through A1521049, A1500433, and 681.
F15201429 through F15201980.
FA1520337 through FA1520425.
(21) FA150M or FRA150M ..........
(22)
(23)
(24)
(25)
152 .......................................
A152 .....................................
F152 .....................................
FA152 ..................................
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Note: AD 2009–10–09 R1 (74 FR 57408,
November 6, 2009) clarified the applicability
of AD 2009–10–09 (74 FR 22429, May 3,
2009), eliminated a duplicate requirement for
replacement of safety wire with jamnuts, and
clarified the intent of the conditional
acceptability of using modification kit part
number (P/N) SK152–25 as a terminating
requirement to the AD. No further action is
required for those already in compliance
with AD 2009–10–09 R1, which included
verification of full rudder travel as part of the
kit work.
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(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 2720, Rudder Control System.
cause undesirable consequences, such as
contact between the rudder and the elevator.
(f) Compliance
(e) Unsafe Condition
Aircraft in full conformity with type design
can exceed the travel limits set by the rudder
stops. We are issuing this AD to prevent the
rudder from traveling past the normal travel
limit. Operation in this non-certificated
control position is unacceptable and could
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Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions
To address this problem, you must do
either the actions in option 1 or option 2 of
this AD, unless already done:
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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations
53311
TABLE 2—ACTIONS, COMPLIANCE AND PROCEDURES
Actions
Compliance
Procedures
(1) Option 1: For all airplanes that do not have
modification kits P/N SK152–25B or P/N
SK152–24B installed (or the other kits allowed by Table 3), do the following:
(i) Insert the following text into the Limitations section of the FAA-approved airplane flight manual (AFM), and pilot’s
operating handbook (POH): ‘‘INTENTIONAL SPINS AND OTHER ACROBATIC/AEROBATIC MANEUVERS PROHIBITED PER AD 2009–10–09. NOTE:
THIS AD DOES NOT PROHIBIT PERFORMING INTENTIONAL STALLS.’’
(ii) Fabricate a placard (using at least 1⁄8inch letters) with the following words and
install the placard on the instrument
panel within the pilot’s clear view: ‘‘INTENTIONAL SPINS AND OTHER ACROBATIC/AEROBATIC
MANEUVERS
PROHIBITED PER AD 2009–10–09.’’
(iii) The AFM and POH limitations in paragraph (g)(1)(i) of the AD and the placard
in paragraph (g)(1)(ii) of this AD may be
removed after either paragraph (g)(2)(i)
or paragraph (g)(2)(ii) of this AD is done.
(2) Option 2: Install a rudder stop modification
kit:
(i) For airplanes with a forged bulkhead, replace the rudder stops, rudder stop
bumpers, and attachment hardware with
the new rudder stop modification kit P/N
SK152–25B.
(ii) For airplanes with a sheet metal bulkhead, replace the rudder stops, rudder
stop bumpers, and attachment hardware
with the new rudder stop modification kit
P/N SK152–24B.
(iii) Refer to Table 3 in paragraph (g) of
this AD for other applicable kit P/Ns.
Within the next 100 hours time-in-service
(TIS) after December 11, 2009 (the effective date retained from AD 2009–10–09 R1
(74 FR 57408, November 6, 2009)), or within the next 12 months after December 11,
2009 (the effective date retained from AD
2009–10–09 R1), whichever occurs first.
A person authorized to perform maintenance
as specified in 14 CFR section 43.3 of the
Federal Aviation Administration Regulations
(14 CFR 43.3) is required to make the AFM
and POH changes, fabricate the placard required in paragraph (g)(1)(i) of this AD, and
make an entry into the aircraft logbook
showing compliance with the portion of the
AD per compliance with 14 CFR 43.9.
Within the next 100 hours TIS after December
11, 2009 (the effective date retained from
AD 2009–10–09 R1 (74 FR 57408, November 6, 2009)), or within the next 12 months
after December 11, 2009 (the effective date
retained from AD 2009–10–09 R1), whichever occurs first.
Follow Cessna Aircraft Company Service Bulletin SEB01–1, Revision 1, dated March 22,
2011; and, as applicable, either Cessna Aircraft Company Service Kit SK152–25B,
dated March 22, 2011, or Cessna Aircraft
Company Service Kit SK152–24B, dated
March 22, 2011.
(h) Kit Part Number Applicability
Table 3 of this AD identifies when a kit
P/N that has already been ordered may be
used to comply with this AD. All future
orders received by Cessna for kits P/Ns
SK152–24, SK152–25, SK152–24A, and SK
152–25A will automatically be filled with
P/Ns SK152–24B and SK152–25B,
respectively.
TABLE 3—KIT APPLICABILITY
Type of bulkhead
Can it be installed to comply with this AD, or will credit be given for compliance with
previous revisions of this AD?
(1) SK152–24 ......................
(2) SK152–25 ......................
sheet metal .........................
forged .................................
(3)
(4)
(5)
(6)
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Kit P/N
sheet metal .........................
forged .................................
sheet metal .........................
forged .................................
NO.
ONLY if washer P/N NAS1149F0332P is used (and this is recorded in the maintenance log), AND full rudder travel can be verified.
ONLY if full rudder travel can be verified.
ONLY if full rudder travel can be verified.
YES.
YES.
SK152–24A
SK152–25A
SK152–24B
SK152–25B
...................
...................
...................
...................
(i) Credit for Actions Accomplished Using
Previous Service Information
Credit will be given for the actions in
paragraphs (g)(1) and (g)(2) of this AD if
already done and you were able to verify full
rudder travel before the effective date of this
AD per AD 2009–10–09 R1, Amendment 39–
16074 (74 FR 57408, November 6, 2009);
Cessna Aircraft Company Service Bulletin
SEB01–1, dated January 22, 2001; and, as
applicable, either Cessna Aircraft Company
Service Kit SK152–25A, Revision A, dated
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February 9, 2001, or Cessna Aircraft
Company Service Kit SK152–24A, Revision
A, dated March 9, 2001.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
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appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) AMOCs approved for AD 2009–10–09
(74 FR 22429, May 3, 2009) and AD 2009–
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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations
10–09 R1 (74 FR 57408, November 6, 2009)
are approved as AMOCs for this AD.
ACTION:
(k) Related Information
For more information about this AD,
contact Ann Johnson, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–4105;
fax: (316) 946–4107; e-mail:
ann.johnson@faa.gov.
SUMMARY:
(l) Material Incorporated by Reference
(1) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) under 5
U.S.C. 552(a) and 1 CFR part 51 of the
following service information on September
12, 2011:
(i) Cessna Aircraft Company Service
Bulletin SEB01–1, Revision 1, dated March
22, 2011;
(ii) Cessna Aircraft Company Service Kit
SK152–25B, dated March 22, 2011; and
(iii) Cessna Aircraft Company Service Kit
SK152–24B, dated March 22, 2011.
(2) For service information identified in
this AD, contact Cessna Aircraft Company,
Product Support, P.O. Box 7706, Wichita, KS
67277; telephone: (316) 517–5800; fax: (316)
517–7271; Internet: https://www.cessna.com.
(3) You may review copies of the service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
(816) 329–4148.
(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 an NARA facility, 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 August
11, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–21210 Filed 8–25–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
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[Docket No. FAA–2011–0861; Directorate
Identifier 2010–SW–092–AD; Amendment
39–16778; AD 2011–17–14]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Model A109A and A109AII
Helicopters
Federal Aviation
Administration, DOT.
AGENCY:
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15:41 Aug 25, 2011
Jkt 223001
Final rule; request for
comments.
This amendment adopts a
new airworthiness directive (AD) for the
specified Agusta S.p.A. (Agusta)
helicopters with a certain tail rotor
special hub plug (hub plug) installed.
This action requires a one-time
inspection to determine the tightening
torque value of the hub plug, and
depending on the inspection results,
replacing certain parts or disassembling
the tail rotor hub and blades assembly
and inspecting for damage. If the
tightening torque value is between 600
kgcm and 700 kgcm, the lock washer
and o-ring must be replaced with
airworthy parts, and no further action is
required. If the tightening torque value
is greater than 700 kgcm, the hub plug
must be replaced with an airworthy
part. Torque the new hub plug to the
specified tightening torque between 600
and 700 kgcm. If the tightening torque
value of the hub plug is less than 600
kgcm, the tail rotor hub and blades
assembly must be disassembled and
inspected for damage. If a part is found
that is outside allowable damage
tolerances, that part must be replaced
with an airworthy part. This
amendment is prompted by the
discovery that a wrong tightening torque
value for the hub plug was contained in
a revision to the helicopter maintenance
manual. The actions specified in this
AD are intended to detect an improperly
torqued hub plug that could lead to tail
rotor failure and subsequent loss of
control of the helicopter.
DATES: Effective September 12, 2011.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of September
12, 2011.
Comments for inclusion in the Rules
Docket must be received on or before
October 25, 2011.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• 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.
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
You may get the service information
identified in this AD from Agusta
Westland, Customer Support & Services,
Via Per Tornavento 15, 21019 Somma
Lombardo (VA) Italy, ATTN: Giovanni
Cecchelli; telephone 39-0331–711133;
fax 39 0331 711180; or at https://
www.agustawestland.com/technicalbullettins.
Examining the Docket: You may
examine the docket that contains the
AD, any comments, and other
information 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 Docket
Operations office (telephone (800) 647–
5527) is located in Room W12–140 on
the ground floor of the West Building at
the street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aerospace Engineer,
FAA, Rotorcraft Directorate, Regulations
and Policy Group, 2601 Meacham Blvd.,
Fort Worth, Texas 76137; telephone:
(817) 222–5122; fax: (817) 222–5961.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Emergency AD
No. 2010–0222–E, dated October 22,
2010 (EAD 2010–0222–E), to correct an
unsafe condition for the specified
Agusta model helicopters with a hub
plug, part number (P/N) 109–0133–18–
103, installed. EASA advises that a
mistaken value of the tightening torque
of the hub plug has been discovered in
the maintenance manual of A109A and
A109AII helicopters. The investigation
carried out by Agusta has revealed that
the wrong value of the tightening torque
of the hub plug was introduced with
Revision 9 of the A109A and A109AII
Helicopter Maintenance Manual, dated
June 15, 2009. EASA states that this
condition could ultimately lead to a tail
rotor malfunction. The actions specified
in this AD are intended to detect an
improperly torqued hub plug that could
lead to tail rotor failure and subsequent
loss of control of the helicopter.
Related Service Information
Agusta has issued Mandatory Alert
Bollettino Tecnico No. 109–132, dated
October 22, 2010 (BT), which specifies
performing a one-time inspection of the
hub plug to verify the right tightening
torque value, and provides instruction
to restore the correct installation. If the
E:\FR\FM\26AUR1.SGM
26AUR1
]]>Agencies
[Federal Register Volume 76, Number 166 (Friday, August 26, 2011)]
[Rules and Regulations]
[Pages 53308-53312]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-21210]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27747; Directorate Identifier 2007-CE-030-AD;
Amendment 39-16782; AD 2009-10-09 R2]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are revising an existing airworthiness directive (AD) for
certain Cessna Aircraft Company (Cessna) Models 150F, 150G, 150H, 150J,
150K, 150L, 150M, A150K, A150L, A150M, F150F, F150G, F150H, F150J,
F150K, F150L, F150M, FA150K, FA150L, FRA150L, FA150M, FRA150M, 152,
A152, F152, and FA152 airplanes. That AD currently requires either
installing a placard prohibiting spins and other acrobatic maneuvers in
the airplane or replacing the rudder stop, the rudder stop bumper, and
the attachment hardware with a rudder stop modification kit. This new
AD requires a change to the modification kit and removal of a small
amount of material from the rudder horn assembly for those that have
not yet complied with the existing AD or for those who can not comply
with the existing AD (because they were unable to obtain full rudder
travel with the existing kits). This AD was prompted by operators who
have reported difficulty in obtaining full rudder travel with the
existing modification kit. We are issuing this AD to revise the kits to
use longer rivets and allow a small amount of material to be removed
from the rudder horn assembly, which allows operators to obtain full
rudder travel.
DATES: This AD is effective September 12, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 12,
2011.
We must receive any comments on this AD by October 11, 2011.
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 comments.
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.
For service information identified in this AD, contact Cessna
Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 67277;
telephone: (316) 517-5800; fax: (316) 517-7271; Internet: https://www.cessna.com. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this
material at the FAA, call 816-329-4148.
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 street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Ann Johnson, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4105; fax: (316) 946-4107;
e-mail: ann.johnson@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On October 27, 2009, we issued AD 2009-10-09 R1, amendment 39-16074
(74 FR 57408, November 6, 2009), for certain Cessna Aircraft Company
(Cessna) Models 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150K, A150L,
A150M, F150F, F150G, F150H, F150J, F150K, F150L, F150M, FA150K, FA150L,
FRA150L, FA150M, FRA150M, 152, A152, F152, and FA152 airplanes. That AD
requires installation of a placard prohibiting spins and other
acrobatic maneuvers in the airplane or replacement of the rudder stop,
rudder stop bumper, and attachment hardware with a new rudder stop
modification kit and replacement of the safety wire with jamnuts. The
revision was issued to clarify certain model and serial number
designations, remove the duplicate requirement of replacing the safety
wire with jamnuts, and clarify the conditional acceptability of using
modification kit part number (P/N) SK152-25 as a terminating action to
that AD. That AD resulted from follow-on investigations of two
accidents where the rudder was found in the over-travel position with
the stop plate hooked over the stop bolt heads. While neither of the
accident aircraft met type design, investigations revealed that
aircraft in full conformity with type design can exceed the travel
limits set by the rudder stops. We issued that AD to prevent the rudder
from traveling past the normal travel limit. Operation in this non-
certificated control position is unacceptable and could cause
undesirable consequences, such as contact between the rudder and the
elevator.
Actions Since AD Was Issued
Since we issued AD 2009-10-09 R1 (74 FR 57408, November 6, 2009),
compliance with the existing AD required operators to check for full
rudder travel with the installation of the existing kits (P/N SK152-24A
and P/N SK152-25A). Some operators have reported difficulty in
obtaining full rudder travel with these kits. To correct this issue,
Cessna has revised the kits to use longer rivets and allow a small
amount of material to be removed from the rudder horn assembly, which
allows operators to obtain full rudder travel.
Relevant Service Information
We reviewed Cessna Aircraft Company Service Bulletin SEB01-1,
Revision 1, dated March 22, 2011; Cessna Aircraft Company Service Kit
SK152-24B, dated March 22, 2011; and Cessna Aircraft Company Service
Kit SK152-25B, dated March 22, 2011. The service information describes
procedures for replacement of the rudder stop, rudder stop bumper, and
attachment hardware with a new rudder stop modification kit.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
[[Page 53309]]
AD Requirements
This AD requires installation of a placard prohibiting spins and
other acrobatic maneuvers in the airplane or replacement of the rudder
stop, rudder stop bumper, and attachment hardware with a new rudder
stop modification kit.
Change to Existing AD
This AD would retain certain requirements of AD 2009-10-09 R1 (74
FR 57408, November 6, 2009). Since AD 2009-10-09 R1 was issued, the AD
format has been revised, and certain paragraphs have been rearranged.
As a result, the corresponding paragraph identifiers have changed in
this AD, as listed in the following table:
Revised Paragraph Identifier
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2009-10-09 R1 AD
------------------------------------------------------------------------
paragraph (e) paragraph (g)
paragraph (f) paragraph (h)
------------------------------------------------------------------------
FAA's Justification and Determination of the Effective Date
This action incorporates revised modification kits that can be used
by all airplanes that would need the modification incorporated in the
future and does not require any additional work for those airplanes
with the modification already incorporated (see table 3). Therefore, we
find that notice and opportunity for prior public comment are
unnecessary and that good cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2007-27747 and directorate identifier 2007-CE-
030-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.
Costs of Compliance
We estimate that this AD affects 17,090 airplanes of U.S. registry.
Estimated Costs
We estimate the following costs to do the insertion of the
operational limitation:
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Insert limitations and placard... 1 work-hour x $85 Not applicable.......... $85 $1,452,650
per hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do the modification:
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Install a rudder stop modification 4 work-hours x $85 per $90 $430 $7,348,700
kit. hour = $340.
----------------------------------------------------------------------------------------------------------------
The new requirements of this AD add no additional economic burden.
The increased estimated cost of this AD is due to increased labor cost
from 2009 when AD 2009-10-09 R1 (74 FR 57408, November 6, 2009) was
issued.
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
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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.
[[Page 53310]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2009-10-09 R1, Amendment 39-16074 (74 FR 57408, November 6, 2009), and
adding the following new AD:
2009-10-09 R2 Cessna Aircraft Company: Amendment 39-16782; Docket
No. FAA-2007-27747; Directorate Identifier 2007-CE-030-AD.
(a) Effective Date
This AD is effective September 12, 2011.
(b) Affected ADs
This AD revises AD 2009-10-09 R1, Amendment 39-16074 (74 FR
57408, November 6, 2009).
(c) Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
Table 1--Applicability
------------------------------------------------------------------------
Models Serial Nos.
------------------------------------------------------------------------
(1) 150F..................................... 15061533 through
15064532.
(2) 150G..................................... 15064533 through 15064969
and 15064971 through
15067198.
(3) 150H..................................... 15067199 through 15069308
and 649.
(4) 150J..................................... 15069309 through
15071128.
(5) 150K..................................... 15071129 through
15072003.
(6) 150L..................................... 15072004 through
15075781.
(7) 150M..................................... 15075782 through
15079405.
(8) A150K.................................... A1500001 through
A1500226.
(9) A150L.................................... A1500227 through A1500432
and A1500434 through
A1500523.
(10) A150M................................... A1500524 through A1500734
and 15064970.
(11) F150F................................... F150-0001 through F150-
0067.
(12) F150G................................... F150-0068 through F150-
0219.
(13) F150H................................... F150-0220 through F150-
0389.
(14) F150J................................... F150-0390 through F150-
0529.
(15) F150K................................... F15000530 through
F15000658.
(16) F150L................................... F15000659 through
F15001143.
(17) F150M................................... F15001144 through
F15001428.
(18) FA150K.................................. FA1500001 through
FA1500081.
(19) FA150L.................................. FA1500082 through
FA1500120.
(20) FA150L or FRA150L....................... FA1500121 through
FA1500261 that are
equipped with FKA150-
2311 and FKA150-2316, or
FRA1500121 through
FRA1500261.
(21) FA150M or FRA150M....................... FA1500262 through
FA1500336 that are
equipped with FKA150-
2311 and FKA150-2316, or
FRA1500262 through
FRA1500336.
(22) 152..................................... 15279406 through
15286033.
(23) A152.................................... A1520735 through
A1521049, A1500433, and
681.
(24) F152.................................... F15201429 through
F15201980.
(25) FA152................................... FA1520337 through
FA1520425.
------------------------------------------------------------------------
Note: AD 2009-10-09 R1 (74 FR 57408, November 6, 2009) clarified
the applicability of AD 2009-10-09 (74 FR 22429, May 3, 2009),
eliminated a duplicate requirement for replacement of safety wire
with jamnuts, and clarified the intent of the conditional
acceptability of using modification kit part number (P/N) SK152-25
as a terminating requirement to the AD. No further action is
required for those already in compliance with AD 2009-10-09 R1,
which included verification of full rudder travel as part of the kit
work.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 2720, Rudder Control System.
(e) Unsafe Condition
Aircraft in full conformity with type design can exceed the
travel limits set by the rudder stops. We are issuing this AD to
prevent the rudder from traveling past the normal travel limit.
Operation in this non-certificated control position is unacceptable
and could cause undesirable consequences, such as contact between
the rudder and the elevator.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions
To address this problem, you must do either the actions in
option 1 or option 2 of this AD, unless already done:
[[Page 53311]]
Table 2--Actions, Compliance and Procedures
----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(1) Option 1: For all airplanes that Within the next 100 hours time-in- A person authorized to perform
do not have modification kits P/N service (TIS) after December 11, maintenance as specified in 14 CFR
SK152-25B or P/N SK152-24B 2009 (the effective date retained section 43.3 of the Federal
installed (or the other kits from AD 2009-10-09 R1 (74 FR 57408, Aviation Administration Regulations
allowed by Table 3), do the November 6, 2009)), or within the (14 CFR 43.3) is required to make
following: next 12 months after December 11, the AFM and POH changes, fabricate
(i) Insert the following text into 2009 (the effective date retained the placard required in paragraph
the Limitations section of the FAA- from AD 2009-10-09 R1), whichever (g)(1)(i) of this AD, and make an
approved airplane flight manual occurs first. entry into the aircraft logbook
(AFM), and pilot's operating showing compliance with the portion
handbook (POH): ``INTENTIONAL SPINS of the AD per compliance with 14
AND OTHER ACROBATIC/AEROBATIC CFR 43.9.
MANEUVERS PROHIBITED PER AD 2009-10-
09. NOTE: THIS AD DOES NOT PROHIBIT
PERFORMING INTENTIONAL STALLS.''
(ii) Fabricate a placard (using at
least \1/8\-inch letters) with the
following words and install the
placard on the instrument panel
within the pilot's clear view:
``INTENTIONAL SPINS AND OTHER
ACROBATIC/AEROBATIC MANEUVERS
PROHIBITED PER AD 2009-10-09.''
(iii) The AFM and POH limitations in
paragraph (g)(1)(i) of the AD and
the placard in paragraph (g)(1)(ii)
of this AD may be removed after
either paragraph (g)(2)(i) or
paragraph (g)(2)(ii) of this AD is
done.
(2) Option 2: Install a rudder stop Within the next 100 hours TIS after Follow Cessna Aircraft Company
modification kit: December 11, 2009 (the effective Service Bulletin SEB01-1, Revision
(i) For airplanes with a forged date retained from AD 2009-10-09 R1 1, dated March 22, 2011; and, as
bulkhead, replace the rudder stops, (74 FR 57408, November 6, 2009)), applicable, either Cessna Aircraft
rudder stop bumpers, and attachment or within the next 12 months after Company Service Kit SK152-25B,
hardware with the new rudder stop December 11, 2009 (the effective dated March 22, 2011, or Cessna
modification kit P/N SK152-25B. date retained from AD 2009-10-09 Aircraft Company Service Kit SK152-
(ii) For airplanes with a sheet R1), whichever occurs first. 24B, dated March 22, 2011.
metal bulkhead, replace the rudder
stops, rudder stop bumpers, and
attachment hardware with the new
rudder stop modification kit P/N
SK152-24B.
(iii) Refer to Table 3 in paragraph
(g) of this AD for other applicable
kit P/Ns.
----------------------------------------------------------------------------------------------------------------
(h) Kit Part Number Applicability
Table 3 of this AD identifies when a kit P/N that has already
been ordered may be used to comply with this AD. All future orders
received by Cessna for kits P/Ns SK152-24, SK152-25, SK152-24A, and
SK 152-25A will automatically be filled with P/Ns SK152-24B and
SK152-25B, respectively.
Table 3--Kit Applicability
----------------------------------------------------------------------------------------------------------------
Can it be installed to
comply with this AD, or
Kit P/N Type of bulkhead will credit be given for
compliance with previous
revisions of this AD?
----------------------------------------------------------------------------------------------------------------
(1) SK152-24............................. sheet metal............................. NO.
(2) SK152-25............................. forged.................................. ONLY if washer P/N
NAS1149F0332P is used (and
this is recorded in the
maintenance log), AND full
rudder travel can be
verified.
(3) SK152-24A............................ sheet metal............................. ONLY if full rudder travel
can be verified.
(4) SK152-25A............................ forged.................................. ONLY if full rudder travel
can be verified.
(5) SK152-24B............................ sheet metal............................. YES.
(6) SK152-25B............................ forged.................................. YES.
----------------------------------------------------------------------------------------------------------------
(i) Credit for Actions Accomplished Using Previous Service Information
Credit will be given for the actions in paragraphs (g)(1) and
(g)(2) of this AD if already done and you were able to verify full
rudder travel before the effective date of this AD per AD 2009-10-09
R1, Amendment 39-16074 (74 FR 57408, November 6, 2009); Cessna
Aircraft Company Service Bulletin SEB01-1, dated January 22, 2001;
and, as applicable, either Cessna Aircraft Company Service Kit
SK152-25A, Revision A, dated February 9, 2001, or Cessna Aircraft
Company Service Kit SK152-24A, Revision A, dated March 9, 2001.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Wichita ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) AMOCs approved for AD 2009-10-09 (74 FR 22429, May 3, 2009)
and AD 2009-
[[Page 53312]]
10-09 R1 (74 FR 57408, November 6, 2009) are approved as AMOCs for
this AD.
(k) Related Information
For more information about this AD, contact Ann Johnson,
Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4105; fax: (316) 946-4107; e-mail: ann.johnson@faa.gov.
(l) Material Incorporated by Reference
(1) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the
following service information on September 12, 2011:
(i) Cessna Aircraft Company Service Bulletin SEB01-1, Revision
1, dated March 22, 2011;
(ii) Cessna Aircraft Company Service Kit SK152-25B, dated March
22, 2011; and
(iii) Cessna Aircraft Company Service Kit SK152-24B, dated March
22, 2011.
(2) For service information identified in this AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS
67277; telephone: (316) 517-5800; fax: (316) 517-7271; Internet:
https://www.cessna.com.
(3) You may review copies of the service information at the FAA,
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106.
For information on the availability of this material at the FAA,
call (816) 329-4148.
(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 an NARA facility, 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 August 11, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-21210 Filed 8-25-11; 8:45 am]
BILLING CODE 4910-13-P
