18970 Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules 

Proposed AD Requirements 

This proposed AD would require, for 

S–76C model helicopters with serial 

numbers 760506 and 760607 through 

760812, within 6 months after the 

effective date of the proposed AD, 

installing an improved throttle stop and 

a wider trigger on each ECL as specified 

in the ASB. 

Differences Between This Proposed AD 

and the Service Information 

The Sikorsky ASB requires 

installation of the modifications on or 

before March 7, 2012. The proposed AD 

requires installation within 6 months 

after the effective date of the AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 52 helicopters of U.S. 

Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. To replace the engine 

control lever stop and trigger assemblies 

will require 2 work-hours at an average 

labor cost of $85 per hour. Required 

parts will cost about $939. Based upon 

these costs, we estimate a total cost of 

$1,109 per helicopter and a total cost of 

$57,668 for the entire U.S. operator 

fleet. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

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); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 (AD): 

Sikorsky Aircraft Corporation: Docket No. 

FAA–2012–0340; Directorate Identifier 

2011–SW–073–AD. 

(a) Applicability 

This AD applies to Sikorsky Aircraft 

Corporation (Sikorsky) Model S–76C 

helicopters, serial numbers 760506 and 

760607 through 760812, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

unintended movement of the engine control 

levers due to an external force to the 

windshield or canopy. This condition could 

result in significantly reduced engine power, 

unrecoverable loss of main rotor speed, and 

subsequent loss of control of the helicopter. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(d) Required Action 

Within 6 months, replace the throttle stop 

and trigger assembly on each engine control 

lever and perform a throttle position check as 

specified in the Accomplishment 

Instructions, Sections 3.A and 3.B, of 

Sikorsky Alert Service Bulletin No. 76–76– 

6A Revision A, dated May 18, 2011. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Kirk Gustafson, Aerospace Engineer, FAA, 

Boston Aircraft Certification Office, Engine 

and Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7190; email 

kirk.gustafson@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under Part 91, 

Subpart K, we suggest that you notify your 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate holding 

district office before operating any aircraft 

complying with this AD through an AMOC. 

(f) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7600: Engine Controls. 

Issued in Fort Worth, Texas, on March 20, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–7541 Filed 3–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0337; Directorate 

Identifier 2010–SW–090–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the Bell 

Helicopter Textron Canada Limited 

(BHTC) Model 407 helicopters. This 

proposed AD is prompted by a review 

of the tailboom-attachment installation, 

which revealed that the torque value of 

the bolts specified in the BHTC Model 

407 Maintenance Manual and applied 

during manufacturing was incorrect and 

exceeded the torque range 

recommended for the bolts. This 

proposed AD would require you to 

replace tailboom-attachment hardware 

(attachment hardware), and perform 

initial and recurring determinations of 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules 18971 

the torque on the nuts of the tailboomattachment bolts (bolts) at all four 

attachment locations. The actions 

required by this proposed AD are 

intended to prevent an over-torque of a 

bolt, bolt failure, loss of the tailboom, 

and subsequent loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by May 29, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

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 proposed 

AD, the economic 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. 

For service information identified in 

this proposed AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272, or 

at http://www.bellcustomer.com/files/. 

You may review copies of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aerospace Engineer, 

FAA, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; fax: 

(817) 222–5961; email: sharon.y.miles@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

Transport Canada, which is the 

aviation authority for Canada, has 

issued AD No. CF–2010–33, dated 

September 30, 2010 (AD CF–2010–33), 

to correct an unsafe condition for the 

BHTC Model 407 helicopter, serial 

numbers (S/Ns) 53000 through 53990. 

Transport Canada advises that a review 

of the tailboom-attachment installation 

determined that the torque value of the 

bolts specified in the BHTC Model 407 

Maintenance Manual and applied 

during manufacturing exceeded the 

torque range recommended for the bolts. 

Transport Canada states that this 

situation, if not corrected, could lead to 

a bolt failure, detachment of the 

tailboom, and subsequent loss of control 

of the helicopter. 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, Transport 

Canada, its technical representative, has 

notified us of the unsafe condition 

described in its AD. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Related Service Information 

BHTC has issued Alert Service 

Bulletin No. 407–10–93, Revision A, 

dated August 30, 2010 (ASB), which 

specifies installing new attachment 

hardware with a reduced torque value. 

This ASB specifies performing a torque 

check of the newly installed bolts and 

nuts every one to five flight hours until 

torque stabilizes at all locations, and 

thereafter at intervals not to exceed 300 

flight hours. Transport Canada classified 

this ASB as mandatory and issued AD 

CF–2010–33 to ensure the continued 

airworthiness of these helicopters. 

Proposed AD Requirements 

This proposed AD would require for 

helicopters with 7000 hours or less 

time-in-service (TIS), at the next 600 

hours scheduled inspection, or 90 days, 

whichever comes first; and for 

helicopters with more than 7000 hours 

TIS, within 150 hours TIS or 90 days, 

whichever comes first, the following 

actions: 

• Remove the left upper bolt, 

washers, and nut. Install a new bolt, 

part number (P/N) NAS627–30; 

washers, P/N 140–007–29S25E6 and 

P/N NAS1149G0732P; and new nut, 

P/N 42FLW–720. Repeat this action for 

the opposite right upper attachment 

hardware. 

• Remove the left lower bolt, washers, 

and nut. Install a new bolt, P/N 

NAS626–26; washer, P/N 140–007– 

25S22E6, washer(s), P/N 

NAS1149G0663P; and new nut, P/N 

42FLW–624. Repeat this action for the 

opposite right lower attachment 

hardware. 

• After installation of the new 

attachment hardware, at intervals of not 

less than 1 hour TIS but not exceeding 

5 hours TIS, determine the torque of 

each nut until torque stabilizes at each 

attachment location. Thereafter, 

determine the torque of each nut at 

recurring intervals not to exceed 300 

hours TIS. If the proper torque has not 

been retained since the last torquing, 

remove and inspect the tailboom 

assembly for damage, corrosion, 

improper assembly, and condition. If 

the tailboom assembly is airworthy, 

replace the attachment hardware and 

determine that the torque has stabilized 

at each attachment location. Replace 

any unairworthy tailboom assembly 

with an airworthy tailboom assembly 

before further flight. 

Differences Between This Proposed AD 

and the Transport Canada AD 

The differences between this 

proposed AD and the Transport Canada 

AD are as follows: 

• This proposed AD uses the term 

‘‘hours time-in-service’’ to describe 

compliance times, and the Transport 

Canada AD uses the term ‘‘air time’’; 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

18972 Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules 

• For helicopters with 7000 hours or 

less TIS, the Transport Canada AD 

requires accomplishing the actions in 

the AD at the next scheduled 600-hour 

inspection or by December 31, 2010, 

whichever occurs first. This proposed 

AD requires accomplishing the actions 

at the next scheduled 600-hour 

inspection or 90 days, whichever occurs 

first. 

• This proposed AD uses the term 

‘‘determine the torque’’ when referring 

to the torque on a nut, and the Transport 

Canada AD uses the term ‘‘perform a 

torque check.’’ 

Costs of Compliance 

We estimate that this proposed AD 

would affect 552 helicopters of U.S. 

registry. We estimate it would take 

about 2.0 work-hours per helicopter to 

replace the hardware and 1.0 work-hour 

per helicopter to determine the 

recurring torque value at an average 

labor rate of $85 per work hour. 

Required parts would cost about $498 

per helicopter. Based on these figures, 

we estimate for the first year the total 

cost per helicopter to be $923, and the 

total cost impact on U.S. operators to be 

$509,496. This estimated total cost 

assumes attachment hardware will be 

replaced on all affected helicopters, the 

torque will be considered stabilized 

after determining the torque value once, 

and the 300-hour TIS recurring torque 

determination will be accomplished 

twice a year. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

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); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 (AD): 

Bell Helicopter Textron Canada (BHTC): 

Docket No. FAA–2012–0337; Directorate 

Identifier 2010–SW–090–AD. 

(a) Applicability 

BHTC Model 407 helicopters, serial 

numbers 53000 through 53990, certificated in 

any category. 

(b) Unsafe Condition 

This proposed AD defines the unsafe 

condition as an incorrect torque value of the 

tailboom attachment bolt (bolt) specified in 

the BHTC Model 407 Maintenance Manual 

and applied during manufacturing, which 

exceeds the torque range recommended for 

the bolts. This condition could result in an 

over-torque of the bolt, bolt failure, loss of 

the tailboom, and subsequent loss of control 

of the helicopter. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(d) Required Actions 

(1) For helicopters with 7000 hours or less 

time-in-service (TIS), at the next 600 hours 

scheduled inspection, or 90 days, whichever 

comes first; and for helicopters with more 

than 7000 hours TIS, within 150 hours TIS 

or 90 days, whichever comes first, replace the 

tailboom-attachment hardware (attachment 

hardware) as follows: 

(i) Remove the left upper bolt, washers, 

and nut. 

(ii) Install a new bolt, part number 

(P/N) NAS627–30; washer, P/N 140–007– 

29S25E6; washer(s), P/N NAS1149G0732P; 

and new nut, P/N 42FLW–720 in accordance 

with paragraphs 2.a) through paragraph 3.e) 

of the ‘‘Accomplishment Instructions: 

Replacement of tailboom attachment bolts 

and nuts’’ section and Figure 2 in the BHTC 

Alert Service Bulletin No. 407–10–93, 

Revision A, dated August 30, 2010 (ASB). 

(iii) Remove the opposite right upper bolt, 

washers, and nut, and accomplish the 

requirements in paragraph (d)(1)(ii) of this 

AD. 

(iv) Remove the left lower bolt, washers, 

and nut. 

(v) Install a new bolt, (P/N) NAS626–26; 

washer, P/N 140–007–25S22E6; washer(s), 

P/N NAS1149G0663P; and new nut, P/N 

42FLW–624 in accordance with paragraphs 

6.a) through 7.e) of the ‘‘Accomplishment 

Instructions: Replacement of tailboom 

attachment bolts and nuts’’ section and 

Figure 2 in the ASB. 

(vi) Remove the right lower bolt, washers, 

and nut, and accomplish the requirements in 

paragraph (d)(1)(v) of this AD. 

(2) After installation of the new attachment 

hardware, at intervals of not less than 1 hour 

TIS but not exceeding 5 hours TIS, determine 

the torque of each nut until the torque 

stabilizes at each attachment location, 

referring to Figure 2 of the ASB. Apply the 

minimum specified torque of the range, plus 

the minimum acceptable tare torque of 14 

inch/lbs (1.58 Nm) for the upper nuts, and 

9.5 inch/lbs (1.07 Nm) for the lower nuts. 

(3) At intervals not to exceed 300 hours 

TIS, determine the torque of each of the four 

attachment nuts, referring to Figure 2 of the 

ASB. Apply the minimum specified torque of 

the range plus the minimum acceptable tare 

torque of 14 inch/lbs (1.58 Nm) for the upper 

nuts, and 9.5 inch/lbs (1.07 Nm) for the lower 

nuts. If the proper torque has not been 

retained since the last torque determination, 

remove and inspect the tailboom assembly 

for damage, corrosion, improper assembly, 

and condition. If the tailboom assembly is 

airworthy, replace the attachment hardware 

in accordance with the requirements in 

paragraphs (d)(1)(i) through (d)(1)(vi) and 

determine that the torque has stabilized in 

accordance with paragraph (2) of this AD. 

Replace any unairworthy tailboom assembly 

with an airworthy tailboom assembly. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 61 / Thursday, March 29, 2012 / Proposed Rules 18973 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; fax: 817– 

222–5961; email: sharon.y.miles@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under Part 91, 

Subpart K, we suggest that you notify your 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate holding 

district office before operating any aircraft 

complying with this AD through an AMOC. 

(f) Additional Information 

The subject of this AD is addressed in the 

Transport Canada Civil Aviation (TCCA) AD 

CF–2010–33, dated September 30, 2010. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302, Rotorcraft tailboom. 

Issued in Fort Worth, Texas, on March 21, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–7542 Filed 3–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Occupational Safety and Health 

Administration 

29 CFR Parts 1910, 1915, 1917, 1926, 

and 1928 

[Docket Nos. OSHA–2010–0058, OSHA– 

2010–0059] 

RIN 1218–AC51 

Reinforced Concrete in Construction, 

and Preventing Backover Injuries and 

Fatalities 

AGENCY: Occupational Safety and Health 

Administration (OSHA), Labor. 

ACTION: Request for information (RFI). 

SUMMARY: OSHA is aware of employee 

safety risks in two areas, reinforcing 

operations in concrete work 

(construction only) and fatal backovers 

by vehicles and equipment (all 

industries), and is requesting 

information from the public on these 

risks. This RFI requests information that 

will assist the Agency in determining 

what steps, if any, it can take to prevent 

injuries and fatalities in these two areas. 

DATES: Submit comments and other 

information by June 27, 2012. All 

submissions must bear a postmark or 

provide other evidence of the 

submission date. 

ADDRESSES: Submit comments and 

additional materials using any of the 

following methods (submissions relating 

to Reinforced Concrete in Construction 

to Docket No. OSHA–2010–0058, and 

submissions relating to Preventing 

Backover Injuries and Fatalities to 

Docket No. OSHA–2010–0059): 

Electronically. Submit comments and 

attachments electronically at http:// 

www.regulations.gov, which is the 

Federal eRulemaking Portal. Follow the 

instructions online for making 

electronic submissions. 

Facsimile. Commenters may fax 

submissions, including attachments, 

that are no longer than 10 pages in 

length to the OSHA Docket Office at 

(202) 693–1648; OSHA does not require 

hard copies of these documents. 

Commenters must submit lengthy 

attachments that supplement these 

documents (e.g., studies, journal 

articles) to the OSHA Docket Office, 

Technical Data Center, Room N–2625, 

U.S. Department of Labor, 200 

Constitution Ave., NW., Washington, 

DC 20210. These attachments must 

clearly identify the commenter’s name, 

date, subject, and docket number (i.e., 

for Reinforced Concrete in Construction, 

OSHA–2010–0058, and for Preventing 

Backover Injuries and Fatalities, OSHA– 

2010–0059) so the Agency can attach 

them to the appropriate comments. 

Regular mail, express delivery, hand 

(courier) delivery, or messenger service. 

Submit a copy of comments and any 

additional material (e.g., studies, journal 

articles) to the OSHA Docket Office, 

Docket No. OSHA–2010–0058 (for 

Reinforced Concrete in Construction), 

Technical Data Center, Room N–2625, 

U.S. Department of Labor, 200 

Constitution Avenue NW., Washington, 

DC 20210; telephone (202) 693–2350 

(TDY number: (877) 889–5627). For 

submissions relating to Preventing 

Backover Injuries and Fatalities, please 

identify the docket number as OSHA– 

2010–0059. Note that security 

procedures may result in significant 

delays in receiving comments and other 

written materials by regular mail. 

Contact the OSHA Docket Office for 

information about security procedures 

concerning delivery of materials by 

express delivery, hand delivery, or 

messenger service. The hours of 

operation for the OSHA Docket Office 

are 8:15 a.m.–4:45 p.m., e.t. 

Instructions. All submissions must 

include the Agency name and the OSHA 

docket number for this rulemaking; i.e., 

for Reinforced Concrete in Construction, 

Docket No. OSHA–2010–0058, and for 

Preventing Backover Injuries and 

Fatalities, Docket No. OSHA–2010– 

0059. The Agency places all 

submissions, including any personal 

information provided, in the public 

docket without change; this information 

will be available online at http:// 

www.regulations.gov. Therefore, the 

Agency cautions commenters about 

submitting information they do not 

want made available to the public, or 

submitting comments that contain 

personal information (either about 

themselves or others) such as Social 

Security numbers, birth dates, and 

medical data. 

Docket. To read or download 

submissions or other material in the 

docket, go to http:// 

www.regulations.gov, or to the OSHA 

Docket Office at the address above. 

While the Agency lists all documents in 

the docket in the http:// 

www.regulations.gov index, some 

information (e.g., copyrighted material) 

is not publicly available to read or 

download through this Web site. All 

submissions, including copyrighted 

material, are available for inspection 

and copying at the OSHA Docket Office. 

Contact the OSHA Docket Office for 

assistance in locating docket 

submissions. 

FOR FURTHER INFORMATION CONTACT: 

Information regarding this Request for 

Information is available from the 

following sources: 

Press inquiries. Contact Frank 

Meilinger, Director, OSHA Office of 

Communications, Room N–3647, U.S. 

Department of Labor, 200 Constitution 

Avenue NW., Washington, DC 20210; 

telephone: (202) 693–1999. 

General and technical information. 

Contact Blake Skogland, Office of 

Construction Standards and Guidance, 

OSHA Directorate of Construction, 

Room N–3468, U.S. Department of 

Labor, 200 Constitution Avenue NW., 

Washington, DC 20210; telephone: (202) 

693–2020; fax: (202) 693–1689. 

Copies of this Federal Register notice. 

Electronic copies are available at 

http://www.regulations.gov. This 

Federal Register notice, as well as news 

releases and other relevant information, 

also are available at OSHA’s Web page 

at http://www.osha.gov. 

Table of Contents of This RFI 

Exhibits Referenced in this RFI 

Reinforced Concrete in Construction, Docket 

No. OSHA–2010–0058 

Preventing Backover Injuries and Fatalities, 

Docket No. OSHA–2010–0059 

Authority and Signature 

SUPPLEMENTARY INFORMATION: 

Exhibits Referenced in This RFI 

Documents referenced by OSHA in 

this request for information, other than 

OSHA standards and Federal Register 

notices, are in Docket Nos. OSHA– 

2010–0058 (Reinforced Concrete in 

Construction) and OSHA–2010–0059 

(Preventing Backover Injuries and 

Fatalities). The dockets are available at 

http://www.regulations.gov, the Federal 

mstockstill on DSK4VPTVN1PROD with PROPOSALS