This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

61555 

Vol. 76, No. 193 

Wednesday, October 5, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0570; Directorate 

Identifier 2011–NM–014–AD; Amendment 

39–16822; AD 2011–20–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 series airplanes; 

Model A310 series airplanes; and Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model C4–605R 

Variant F airplanes (collectively called 

A300–600 series airplanes). This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

* * * * * 

A recent analysis conducted by the 

manufacturer showed a particular risk for 

explosive failure of the * * * hydraulic 

accumulator. 

This condition, if not detected and 

corrected, might, for some aeroplane 

installations, lead to damage to all three 

hydraulic circuits, possibly resulting in loss 

of control of the aeroplane or could, for 

certain other aeroplane installations, lead to 

an undetected fire in the wheel bay. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 9, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 22, 2011 (76 FR 36387). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Since 1984, the design of the hydraulic 

accumulator installed on all the affected 

Airbus types has changed. The Part Number 

(P/N) remained the same, but the 

manufacturer did not record the serial 

number of the part that was the first to be 

manufactured to the changed design 

specification. 

The new design hydraulic accumulator is 

manufactured with 2 pieces unit welded, 

instead of 4 pieces unit with 3 welds (old 

design) as pictured in Appendix 1 of this 

[EASA] AD. The welding process of the new 

design hydraulic accumulator provides a 

higher strength shell material and more 

reliability. 

A recent analysis conducted by the 

manufacturer showed a particular risk for 

explosive failure of the old design hydraulic 

accumulator. 

This condition, if not detected and 

corrected, might, for some aeroplane 

installations, lead to damage to all three 

hydraulic circuits, possibly resulting in loss 

of control of the aeroplane or could, for 

certain other aeroplane installations, lead to 

an undetected fire in the wheel bay. 

For the reasons explained above, this 

[EASA] AD requires a one time detailed 

visual inspection to identify the old designed 

accumulators installed on certain hydraulic 

systems, the replacement of those 

accumulators by new designed accumulators 

and, irrespective of findings, the installation 

of warning placards to avoid installation of 

old designed accumulators on the affected 

hydraulic systems. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 36387, June 22, 2011) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 184 products of U.S. registry. We 

also estimate that it will take about 7 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $197 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $145,728, or 

$792 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 5 work-hours and require parts 

costing $10,700, for a cost of $11,125 

per product. We have no way of 


jlentini on DSK4TPTVN1PROD with RULES
61556 Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Rules and Regulations 

determining the number of products 

that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator.‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ’’significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ’’significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (76 FR 36387, June 

22, 2011), the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

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 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–20–09 Airbus: Amendment 39–16822. 

Docket No. FAA–2011–0570; Directorate 

Identifier 2011–NM–014–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the products 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

all manufacturer serial numbers. 

(1) Model A300 B2–1A, B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes. 

(3) Model A300 B4–601, B4–603, B4–620, 

and B4–622 airplanes; A300 B4–605R and 

B4–622R airplanes; A300 F4–605R and F4– 

622R airplanes; and A300 C4–605R Variant F 

airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * * * 

A recent analysis conducted by the 

manufacturer showed a particular risk for 

explosive failure of the * * * hydraulic 

accumulator. 

This condition, if not detected and 

corrected, might, for some aeroplane 

installations, lead to damage to all three 

hydraulic circuits, possibly resulting in loss 

of control of the aeroplane or could, for 

certain other aeroplane installations, lead to 

an undetected fire in the wheel bay. 

* * * * * 

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. 

Inspection, Replacement, and Placard 

Installation 

(g) Within 30 months or 6,000 flight hours 

after the effective date of this AD, whichever 

occurs first: Do a detailed inspection of each 

type 5 hydraulic accumulator, part number 

(P/N) 3059103–1, P/N 3059103–2, P/N 

3059103–8, and P/N 3059103–9, to determine 

if an old design accumulator (i.e., pre-1984) 

is installed on any affected hydraulic circuit 

indicated in table 1 of this AD, as applicable, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus 

mandatory service bulletin identified in table 

2 of this AD. 

TABLE 1—APPLICABLE HYDRAULIC CIRCUITS

Airbus model Hydraulic circuit 

A300 airplanes pre-modification 02447 ........................................................................................................................................ Blue and Green. 

A300 airplanes post-modification 02447 ....................................................................................................................................... Blue. 

A300–600 airplanes ...................................................................................................................................................................... Blue. 

A310 airplanes .............................................................................................................................................................................. Green. 

TABLE 2—APPLICABLE SERVICE INFORMATION

Airbus Mandatory Service Bulletin— Revision— Dated— 

A300–29–0126 (for Model A300 airplanes) ............................................................................................................ 01 October 12, 2010. 

A300–29–6063 (for Model A300–600 airplanes) .................................................................................................... .................. August 12, 2010. 


jlentini on DSK4TPTVN1PROD with RULES
Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Rules and Regulations 61557 

TABLE 2—APPLICABLE SERVICE INFORMATION—Continued 

Airbus Mandatory Service Bulletin— Revision— Dated— 

A310–29–2099 (for Model A310 airplanes) ............................................................................................................ .................. August 12, 2010. 

(h) If, during any detailed inspection 

required by paragraph (g) of this AD, an old 

design hydraulic accumulator (i.e., pre-1984) 

is found installed on any affected hydraulic 

circuit as indicated in table 1 of this AD, as 

applicable to airplane model, before further 

flight replace each affected old design 

accumulator with a new design accumulator, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus 

mandatory service bulletin identified in table 

2 of this AD. 

(i) Before further flight after accomplishing 

the inspection required by paragraph (g) of 

this AD: Install a placard at the designated 

location of any affected hydraulic circuit 

indicated in table 1 of this AD, as applicable 

to airplane model, in accordance with the 

Accomplishment Instructions of the 

applicable Airbus mandatory service bulletin 

identified in table 3 of this AD. 

TABLE 3—OTHER APPLICABLE SERVICE INFORMATION

Airbus Mandatory Service Bulletin— Revision— Dated— 

A300–29–0127 (for Model A300 airplanes) ............................................................................................................. .................. August 12, 2010. 

A300–29–6064 (for Model A300–600 airplanes) ..................................................................................................... .................. August 12, 2010. 

A310–29–2100 (for Model A310 airplanes) ............................................................................................................. .................. August 12, 2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to Attn: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be e-mailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2011–0006, dated January 17, 2011; 

and the Airbus mandatory service bulletins 

identified in table 4 of this AD; for related 

information. 

TABLE 4—RELATED SERVICE INFORMATION

Airbus Mandatory Service Bulletin— Revision— Dated— 

A300–29–0126 ...................................................................................................................................................... 01 October 12, 2010. 

A300–29–0127 ...................................................................................................................................................... .................... August 12, 2010. 

A300–29–6063 ...................................................................................................................................................... .................... August 12, 2010. 

A300–29–6064 ...................................................................................................................................................... .................... August 12, 2010. 

A310–29–2099 ...................................................................................................................................................... .................... August 12, 2010. 

A310–29–2100 ...................................................................................................................................................... .................... August 12, 2010. 

Material Incorporated by Reference 

(l) 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 the date 

specified: 

(1) Airbus Mandatory Service Bulletin 

A300–29–0126, excluding Appendices 01 

and 02, Revision 01, dated October 12, 2010, 

approved for IBR November 9, 2011. 

(2) Airbus Mandatory Service Bulletin 

A300–29–0127, excluding Appendix 01, 

dated August 12, 2010, approved for IBR 

November 9, 2011. 

(3) Airbus Mandatory Service Bulletin 

A300–29–6063, dated August 12, 2010, 

approved for IBR November 9, 2011. 

(4) Airbus Mandatory Service Bulletin 

A300–29–6064, dated August 12, 2010, 

approved for IBR November 9, 2011. 

(5) Airbus Mandatory Service Bulletin 

A310–29–2099, excluding Appendix 01, 

dated August 12, 2010, approved for IBR 

November 9, 2011. 

(6) Airbus Mandatory Service Bulletin 

A310–29–2100, dated August 12, 2010, 

approved for IBR November 9, 2011. 

(7) 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 http:// 

www.airbus.com. 

(8) 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. 

(9) 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: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 


jlentini on DSK4TPTVN1PROD with RULES
61558 Federal Register / Vol. 76, No. 193 / Wednesday, October 5, 2011 / Rules and Regulations 

Issued in Renton, Washington, on 

September 22, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25308 Filed 10–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0735; Directorate 

Identifier 2011–NE–01–AD; Amendment 39– 

16807; AD 2011–19–02] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Type R212/4–30–4/22 and 

R251/4–30–4/49 Propeller Assemblies 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Reports have been received from a small 

number of HS.748 operators of finding cracks 

in the propeller hub port buttress threads of 

R212 and R251 propellers. The affected hubs 

had accumulated in excess of 6,000 flight 

hours. This condition, if not detected and 

corrected, could lead to propeller blade 

separation, possibly resulting in damage to 

the aeroplane and/or injury to persons on the 

ground. 

We are issuing this AD to prevent 

propeller hub failure due to cracks in 

the hub, which could result in damage 

to the airplane. 

DATES: This AD becomes effective 

November 9, 2011. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

November 9, 2011. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax: 781–238–7170; e-mail: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on May 11, 2011 (76 FR 27281). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

Reports have been received from a small 

number of HS.748 operators of finding cracks 

in the propeller hub port buttress threads of 

R212 and R251 propellers. The affected hubs 

had accumulated in excess of 6,000 flight 

hours. This condition, if not detected and 

corrected, could lead to propeller blade 

separation, possibly resulting in damage to 

the aeroplane and/or injury to persons on the 

ground. 

The cracks originating from the root of 

the buttress threads in the blade ports 

are caused by high-cycle fatigue. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM 

published in the Federal Register on 

May 11, 2011 (76 FR 27281) or on the 

determination of the cost to the public. 

Since we published the NPRM in the 

Federal Register on May 11, 2011 (76 

FR 27281), we changed the AD Docket 

No. from FAA–2011–0033, to FAA– 

2011–0735. The original number was 

inadvertently used both by the FAA 

Engine & Propeller Directorate, and the 

FAA Transport Airplane Directorate. 

Also since we published the NPRM in 

the Federal Register on May 11, 2011 

(76 FR 27281), we became aware that 

Dowty Propellers made minor changes 

to Alert Service Bulletin (ASB) No. 61– 

1043, Revision 6, and issued Revision 7, 

dated March 1, 2011. Revision 6 of the 

ASB had an incorrect Non-Destructive 

Testing (NDT) reference in Effectivity 

paragraph 1.D. We do not reference that 

paragraph in this AD, however, we 

changed the AD to reference the most 

current ASB, which is Revision 7. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

2 propellers installed on one airplane of 

U.S. registry. We also estimate that it 

will take about 1 work-hour per 

propeller to comply with this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $20,000 

per propeller. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $40,170. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 


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