Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 23625 

replacement part, unless it has been 

inspected and, as applicable, repaired in 

accordance with the instructions of Airbus 

Mandatory Service Bulletin A330–55–3037, 

dated October 11, 2007, or Airbus Mandatory 

Service Bulletin A340–55–4033, dated 

October 11, 2007; and Airbus Mandatory 

Service Bulletin A330–55–3038, dated 

November 7, 2007, or Airbus Mandatory 

Service Bulletin A340–55–4034, dated 

November 7, 2007. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, 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: 

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. 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. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0012, dated January 14, 2008; and the service 

bulletins listed in Table 1 of this AD; for 

related information. 

TABLE 1—SERVICE BULLETINS

Airbus Mandatory Service Bulletin— Dated— 

A330–55–3037 ......................................................................................................................................................................... October 11, 2007. 

A330–55–3038 ......................................................................................................................................................................... November 7, 2007. 

A340–55–4033 ......................................................................................................................................................................... October 11, 2007. 

A340–55–4034 ......................................................................................................................................................................... November 7, 2007. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax +33 5 61 

93 45 80, e-mail airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information that is incorporated by reference 

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 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. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Date 

Airbus Mandatory Service Bulletin A330–55–3037, excluding Appendix 01 .......................................................................... October 11, 2007. 

Airbus Mandatory Service Bulletin A330–55–3038, including Appendix 01 ........................................................................... November 7, 2007. 

Airbus Mandatory Service Bulletin A340–55–4033, excluding Appendix 01 .......................................................................... October 11, 2007. 

Airbus Mandatory Service Bulletin A340–55–4034, including Appendix 01 ........................................................................... November 7, 2007. 

Issued in Renton, Washington, on May 6, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–11283 Filed 5–19–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0114; Directorate 

Identifier 2009–NE–03–AD; Amendment 39– 

15910; AD 2009–10–14] 

RIN 2120–AA64 

Airworthiness Directives; Hartzell 

Propeller Inc. Steel Hub Turbine 

Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Hartzell 

Propeller Inc. steel hub turbine 

propellers, with any counterweight slug 

attachment bolts, part number (P/N) B– 

3386–14H, LFC manufacturing lot 224, 

installed. This AD requires identifying 

and removing all counterweight slug 

attachment bolts, P/N B–3386–14H, LFC 

manufacturing lot 224, from service and 

installing serviceable bolts. This AD 

results from two reports of failure of the 

bolts that attach the propeller blade 

counterweight slug, and separation of 

the counterweight slug which led to 

propeller vibration and damage to the 

propeller spinner. We are issuing this 

AD to prevent separation of the 

23626 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 

propeller blade counterweight slug, 

which could lead to injury and damage 

to the airplane. 

DATES: This AD becomes effective June 

4, 2009. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of June 4, 2009. 

We must receive any comments on 

this AD by July 20, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Docket Management 

Facility, Department of Transportation, 

1200 New Jersey Avenue, SE., West 

Building Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

FOR FURTHER INFORMATION CONTACT: Tim 

Smyth, Senior Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, Small Airplane Directorate, 2300 

East Devon Avenue, Des Plaines, IL 

60018–4696; e-mail: 

timothy.smyth@faa.gov; telephone (847) 

294–8110; fax (847) 294–7132. 

SUPPLEMENTARY INFORMATION: In October 

2008, we became aware of two reports 

of failure of the bolts that attach the 

propeller blade counterweight slug, and 

separation of the counterweight slug 

which led to propeller vibration and 

damage to the propeller spinner. 

Investigation by Hartzell Propeller Inc. 

revealed that the bolts failed due to a 

bolt manufacturing defect. Hartzell 

Propeller Inc. determined that the bolts 

in LFC manufacturing lot 224, are 

suspect for having this defect. This 

condition, if not corrected, could result 

in separation of the propeller blade 

counterweight slug, which could lead to 

injury and damage to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Hartzell Propeller 

Inc. Alert Service Bulletin (ASB) No. 

HC–ASB–61–313, Revision 2, dated 

March 27, 2009. That ASB lists the 

affected Hartzell Propeller Inc. steel hub 

turbine propeller models and describes 

procedures for identifying and removing 

all counterweight slug attachment bolts, 

P/N B–3386–14H, LFC manufacturing 

lot 224, from service, and installing 

serviceable bolts. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other Hartzell Propeller Inc. steel 

hub turbine propellers of the same type 

design. For that reason, we are issuing 

this AD to prevent separation of the 

propeller blade counterweight slug, 

which could lead to injury and damage 

to the airplane. This AD requires 

identifying and removing all 

counterweight slug attachment bolts, 

P/N B–3386–14H, LFC manufacturing 

lot 224, from service, within the next 50 

flight hours after the effective date of the 

AD, and installing serviceable bolts. 

You must use the service information 

described previously to perform the 

actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, 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 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2009–0114; Directorate Identifier 

2009–NE–03–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 the 

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 23627 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration amends part 39 

of the Federal Aviation Regulations (14 

CFR part 39) as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2009–10–14 Hartzell Propeller Inc.: 

Amendment 39–15910. Docket No. 

FAA–2009–0114; Directorate Identifier 

2009–NE–03–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 4, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Hartzell 

Propeller Inc. steel hub turbine propellers 

listed in Table 1 of this AD, with any 

counterweight slug attachment bolts, part 

number (P/N) B–3386–14H, LFC 

manufacturing lot 224, installed. These 

propellers are installed on, but not limited to, 

the airplanes listed in Table 1 of this AD. 

TABLE 1—PROPELLER MODELS APPLICABILITY

Propeller model Airplane manufacturer Airplane model 

HC–B3TN–5K ...................... AERO COMMANDER ..................................................... 680T, 680V, 681. 

HC–B3TN–5DL, –5FL, –5NL AERO COMMANDER ..................................................... 690(A, B, C), 695A. 

HC–A3MVF–7B .................... AEROSPACE TECHNOLOGIES .................................... N22B, N24A, N22S, N22C. 

HC–A3VF–7, –7B ................ AEROSPACE TECHNOLOGIES .................................... N22B, N24A, N22S, N22C. 

HC–B5MP–3A, –3C ............. AIR TRACTOR ................................................................ AT–502A. 

HC–B5MP–3C ...................... AIR TRACTOR ................................................................ AT–503, 602. 

HC–B5MA–3D(T) ................. AIR TRACTOR ................................................................ AT–802. 

HC–B5MP–3F ...................... AIR TRACTOR ................................................................ AT–802. 

HC–B5MA–5A ...................... ANTONOV ....................................................................... AN–38. 

HC–B3TN–5V ...................... AYRES ............................................................................ S–2R. 

HC–B4TN–5NL, –5PL .......... AYRES ............................................................................ S–2R(–1340), –G(5, 6, 10), –R3S, –R1820, –T(6, 11, 

15, 34, 45, 65). 

HC–B5MP–3C ...................... AYRES ............................................................................ S–2R(HG)–T65. 

HC–B3TN–3AE .................... AYRES ............................................................................ S–2R–T( ). 

HC–B3TN–5K ...................... BAE (JETSTREAM) ........................................................ 137. 

HC–B4MP–3A ...................... BEECH ............................................................................ 1900C. 

HC–B4MP–3B ...................... BEECH ............................................................................ 300, 300LW. 

HC–B3TF–7A ....................... BEECH ............................................................................ A36, A36TC. 

HC–B4MP–3C ...................... BEECH ............................................................................ B300, B300C. 

HC–B4MN–5AL .................... CASA ............................................................................... C–212–CC, –CF. 

HC–B3TF–7A ....................... CESSNA .......................................................................... 206. 

HC–B3TF–7 ......................... CESSNA .......................................................................... 402. 

HC–B3MN–3 ........................ CESSNA .......................................................................... 208, 208A, 208B. 

HC–B3TN–3AEY, –3AF ....... CESSNA .......................................................................... 208, 208A, 208B. 

HC–B3TF–7A ....................... CESSNA .......................................................................... P210N. 

HC–B3TN–3AEY .................. DE HAVILLAND CANADA .............................................. DHC–3. 

HC–B4TN–5NL .................... DE HAVILLAND CANADA .............................................. DHC–3. 

HC–B5MA–3M ..................... DE HAVILLAND CANADA .............................................. DHC–4. 

HC–B4TN–5ML .................... DORNIER ........................................................................ DO228–100, –101, –200, –201, –202, –212. 

HC–B4TN–5L ....................... DORNIER ........................................................................ DO228–200, –201, –202, –212. 

HC–B5MA–3(J, M, C) .......... DOUGLAS ....................................................................... DC–3C. 

HC–B5MA–2 ........................ EMBRAER ....................................................................... EMB–314. 

HC–B4TN–5EL, –5HL, –5KL FAIRCHILD AIRCRAFT .................................................. SA–226T(B). 

HC–B3TF–7, –7A ................. FLUG & FAHRZEUGWERKE AG ................................... AS202/32TP. 

HC–B3TF–7A ....................... FUJI ................................................................................. KM–2D (T–5). 

HC–B5MP–5 ........................ GRUMMAN ..................................................................... S–2. 

HC–B5MA–5H ...................... GRUMMAN ..................................................................... S–2F3AT. 

HC–3BTF–7A ....................... MAULE ............................................................................ M–7–420, MX(T)–7–420. 

HC–B4TN–5DL, –5GL, –5JL MITSUBISHI .................................................................... MU–2B–25A, –26A, –30, –35A, –36A, –40 (MU–2P), 

–60 (MU–2N). 

HC–B5MP–3(A) ................... NORD .............................................................................. 262 FRAKES. 

HC–B5MP–3C ...................... NORMAN AEROPLANE ................................................. NAC 6–65. 

HC–B5MP–3D ...................... POLISH AVIATION (MIELEC) ........................................ M–28, –28B. 

HC–B5MP–3G ..................... POLISH AVIATION (MIELEC) ........................................ M–28B. 

HC–B3TN–5U ...................... PZL MIELEC ................................................................... M18. 

HC–B4TN–5NL .................... PZL MIELEC ................................................................... M18. 

HC–B5MP–5BL .................... PZL MIELEC ................................................................... M18. 

HC–B5MP–3C ...................... PZL MIELEC ................................................................... M18, M18A, M18B. 

HC–B4MN–5B ...................... ROCKWELL .................................................................... OV–10 (LEFT SIDE). 

HC–B4MN–5BL .................... ROCKWELL .................................................................... OV–10 (RIGHT SIDE). 

HC–B5MP–3A ...................... SHORT BROTHERS ....................................................... SD3–30. 

HC–B5MP–3C ...................... SHORT BROTHERS ....................................................... SD3–60–200, SD3–SHERPA–200. 

HC–B3TF–7A ....................... SIAI MARCHETTI (AERMACCHI) .................................. F.260C, D. 

HC–B3TF–7A ....................... SIAI MARCHETTI (AERMACCHI) .................................. SM–1019. 

HC–B3TF–7A ....................... SIAI MARCHETTI (VULCANAIR) ................................... SF600 CANGURO. 

23628 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 

TABLE 1—PROPELLER MODELS APPLICABILITY—Continued 

Propeller model Airplane manufacturer Airplane model 

HC–B5MP–3(F) .................... THRUSH AIRCRAFT ...................................................... S–2R–T660. 

HC–B3TN–5FL, –5NL .......... TWIN COMMANDER ...................................................... 690A, 690B, 690C. 

HC–B3TF–7A ....................... VALMET .......................................................................... L–90TP. 

HC–B3TF–7A ....................... VULCANAIR (PARTENAVIA) ......................................... AP68TP–300, –600. 

Unsafe Condition 

(d) This AD results from two reports of 

failure of the bolts that attach the propeller 

blade counterweight slug, and separation of 

the counterweight slug which led to 

propeller vibration and damage to the 

propeller spinner. Investigation by Hartzell 

Propeller Inc. revealed that the bolts failed 

due to a bolt manufacturing defect. We are 

issuing this AD to prevent separation of the 

propeller blade counterweight slug, which 

could lead to injury and damage to the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

50 flight hours after the effective date of this 

AD, unless the actions have already been 

done. 

Identification and Removal of All Propeller 

Blade Counterweight Slug Bolts, P/N B– 

3386–14H, LFC Manufacturing Lot 224, 

From Service, and Installation of 

Serviceable Bolts 

(f) Identify and remove all propeller blade 

counterweight slug bolts, P/N B–3386–14H, 

LFC manufacturing lot 224, from service, and 

install serviceable bolts. 

(g) Use paragraphs 3.A.(1) through 

3.A.(4)(b)5 of the Accomplishment 

Instructions of Hartzell Propeller Inc. ASB 

No. HC–ASB–61–313, Revision 2, dated 

March 27, 2009, to do the identification, 

removals from service, and installations. 

Definition 

(h) For the purpose of this AD, a 

serviceable propeller blade counterweight 

slug bolt is a P/N B–3386–14H bolt with an 

LFC manufacturing lot other than lot 224. 

Alternative Methods of Compliance 

(i) The Manager, Chicago 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. 

Related Information 

(j) Contact Tim Smyth, Senior Aerospace 

Engineer, Chicago Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

2300 East Devon Avenue, Des Plaines, IL 

60018–4696; e-mail: timothy.smyth@faa.gov; 

telephone (847) 294–8110; fax (847) 294– 

7132, for more information about this AD. 

Material Incorporated by Reference 

(k) You must use Hartzell Propeller Inc. 

ASB No. HC–ASB–61–313, Revision 2, dated 

March 27, 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 Hartzell Propeller Inc. 

Technical Publications Department, One 

Propeller Place, Piqua, OH 45356; telephone 

(937) 778–4200; fax (937) 778–4391, 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: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

May 8, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–11518 Filed 5–19–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[USCG–2009–0228] 

Drawbridge Operating Regulations; 

Back Bay of Biloxi, Biloxi, MS 

AGENCY: Coast Guard, DHS. 

ACTION: Notice canceling temporary 

deviation from regulations. 

SUMMARY: The Coast Guard is canceling 

the temporary deviation concerning the 

operation of the I–110 bascule span 

bridge across the Back Bay of Biloxi, 

mile 3.0, in Biloxi, Harrison County, 

Mississippi. The deviation allowed the 

bridge to remain closed to navigation for 

two (2) two-hour periods daily to 

facilitate the movement of vehicular 

traffic. 

DATES: The temporary deviation 

published on April 13, 2009 (74 FR 

16781) is cancelled as of May 20, 2009. 

ADDRESSES: The docket for this 

cancelled deviation is available for 

inspection or copying at the Docket 

Management Facility (M–30), U.S. 

Department of Transportation, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. You may also 

find this docket on the Internet by going 

to http://www.regulations.gov, selecting 

the Advanced Docket Search option on 

the right side of the screen, inserting 

USCG–2009–0228 in the Docket ID box, 

pressing Enter, and then clicking on the 

item in the Docket ID column. 

FOR FURTHER INFORMATION CONTACT: 

David Frank, Bridge Administration 

Branch, telephone (504) 671–2128. 

Background and Purpose 

On April 13, 2009, we published a 

temporary deviation entitled 

‘‘Drawbridge Operating Regulations; 

Back Bay of Biloxi, Biloxi, Mississippi’’ 

in the Federal Register (74 FR 16781). 

The temporary deviation concerned 

allowing the I–110 bridge across the 

Back Bay of Biloxi, mile 3.0, in Biloxi, 

Harrison County, Mississippi to remain 

closed to navigation for two (2) twohour periods daily to facilitate the 

movement of vehicular traffic. This 

deviation from the operating regulations 

was authorized under 33 CFR 117.35. 

Cancellation 

The deviation was established to 

facilitate the flow of increased vehicular 

traffic on the I–110 bridge caused by the 

allision to the Popps Ferry Rd. bridge. 

The Popps Ferry Rd. bridge was 

damaged in an allision on March 20, 

2009 when two sections of the roadway 

were destroyed. The bridge was 

returned to service on April 25, 2009, 

thus reducing the vehicular traffic on 

the I–110 bridge during the morning and 

afternoon rush hours. 

Dated: April 29, 2009. 

David M. Frank, 

Bridge Administrator. 

[FR Doc. E9–11689 Filed 5–19–09; 8:45 am] 

BILLING CODE 4910–15–P