Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules 54405 

Comments Due Date 

(a) We must receive comments by October 

17, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to PIAGGIO AERO 

INDUSTRIES S.p.A Model PIAGGIO P–180 

airplanes, all serial numbers, that are: 

(1) Certificated in any category; and 

(2) have installed any of the following 

main landing gear (MLG) actuators: 

(i) Messier-Dowty Part Number (P/N) 

114346003 (left hand side): with serial 

number (S/N) SA0706275, SA0706276, 

SA0706726, SA0706727, SA0706728, 

SA0706729, SA0706738, 

SA0706739,SA0707243, SA0707864, or 

SA0708072; or 

(ii) Messier-Dowty P/N 114346004 (right 

hand side): with S/N SA0703800, 

SA0703801, SA0705520, SA0706219, 

SA0706960, or SA0706961. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Some lock sleeves (part number (P/N) 

114146681), which were installed in some 

Main Landing Gear (MLG) actuators, had 

been incorrectly manufactured. 

If left uncorrected, this condition could 

lead to failure to lock the MLG actuator or 

to its unlock from the correct position, with 

subsequent possible damage to the aeroplane 

and injuries to occupants during landing. 

This AD requires replacing defective MLG 

actuators with serviceable ones. 

Defective actuators can be repaired by the 

manufacturer and identified with the ‘‘P180– 

32–29’’ marking on the name plate. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 25 hours time-in-service (TIS) 

after the effective date of this AD, inspect 

both installed MLG actuators to determine if 

an affected P/N and S/N actuator is installed. 

(2) If any affected P/N and S/N actuator is 

identified with the ‘‘P180–32–29’’ marking 

on the name plate, no further action is 

required by this AD on that actuator. 

(3) If one or both affected MLG actuators 

are not identified with the ‘‘P180–32–29’’ 

marking on the name plate, before reaching 

a total of 3,000 hours TIS on the actuator or 

within the next 150 hours TIS after the 

effective date of this AD, whichever occurs 

later, replace the affected actuator(s) with 

serviceable parts following Part B of the 

Accomplishment Instructions of Piaggio Aero 

Industries S.p.A. Mandatory Service Bulletin 

No. 80–0304, dated July 9, 2010. 

(4) After the effective date of this AD, do 

not install any MLG actuator having an 

affected P/N and S/N, unless it is identified 

with the ‘‘P180–32–29’’ marking on the name 

plate. 

Note 1: There is a warranty expiration date 

for the replacement of the actuators. The 

FAA recommends owners/operators that 

have affected main landing gear actuators 

contact the manufacturer immediately and 

replace the actuators under warranty. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: The 

compliance times of the MCAI are presented 

in flight cycles (landings). When doing the 

conversion for these airplanes from flight 

cycles to hours TIS, the FAA has estimated 

that 1 flight cycle is equal to 1 hour TIS 

based on the utility of this class of airplane. 

Since operators of aircraft of U.S. registry are 

required to keep track of hours TIS, the 

compliance time of this AD is in hours TIS. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090; e-mail: mike.kiesov@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No.: 2011–0133, 

dated July 12, 2011; and Piaggio Aero 

Industries S.p.A. Mandatory Service Bulletin 

No. 80–0304, dated July 9, 2010, for related 

information. For service information related 

to this AD, contact Piaggio Aero Industries 

S.p.A Airworthiness Office; Via Luigi 

Cibrario, 4–16154 Genova–Italy; telephone: 

+39 010 6481353; fax: +39 010 6481881; 

E-mail: airworthiness@piaggioaero.it. 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. 

Issued in Kansas City, Missouri, on August 

26, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–22387 Filed 8–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0915; Directorate 

Identifier 2011–NM–020–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require repetitive general 

visual inspections for broken or missing 

latch pins of the lower sills of the 

forward and aft lower lobe cargo doors; 

repetitive detailed inspections for 

cracking of the latch pins; and 

corrective actions if necessary. This 

proposed AD was prompted by reports 

of fractured latch pins found in service; 

investigation revealed that the cracking 

and subsequent fracture were initiated 

by fatigue and propagated by a 

combination of fatigue and stress 

corrosion. We are proposing this AD to 

detect and correct fractured or broken 

latch pins, which could result in a 

forward or aft lower lobe cargo door 

opening and detaching during flight, 

and consequent rapid decompression of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by October 17, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
54406 Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules 

• 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

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 proposed 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6428; fax: (425) 917–6590; e-mail: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–0915; Directorate Identifier 2011– 

NM–020–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

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 we receive 

about this proposed AD. 

Discussion 

We have received reports of fractured 

latch pins found in service; 

investigation revealed that the cracking 

and subsequent fracture were initiated 

by fatigue and propagated by a 

combination of fatigue and stress 

corrosion. One operator reported a 

fractured latch pin of the lower sill of 

the aft lower lobe cargo door; the 

fracture initiated from a crack on the 

pin’s internal diameter. Part of the pin 

was found on the ground during an 

airplane walk-around. The airplane had 

accumulated 75,495 total flight hours 

and 9,393 total flight cycles. A dye 

penetrant inspection of the remaining 

seven latch pins in the lower sill was 

done with no defects found. This 

condition, if not corrected, could result 

in a forward or aft lower lobe cargo door 

opening and detaching during flight, 

and consequent rapid decompression of 

the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–53A2835, original, dated 

October 28, 2010. The service 

information describes procedures for 

repetitive general visual inspections for 

broken or missing latch pins of the 

lower sills of the forward and aft lower 

lobe cargo doors; repetitive detailed 

inspections of the replaced latch pins 

for broken or missing latch pins; and 

corrective actions if necessary. 

For Groups 1 and 2 airplanes, 

Configurations 1 and 2; and for Group 

3 airplanes; the corrective actions 

include replacing any broken or missing 

latch pin, and the latch pins at the 

adjacent latch fitting locations, with 

new latch pins; and replacing any 

cracked latch pins with new latch pins. 

For Group 1 airplanes, Configurations 

3 and 4, there are two options for 

corrective actions: 

• Replacing any broken or missing 

latch pin, and the latch pins at the 

adjacent latch fitting locations, with 

new latch pins (with identical part 

numbers); and replacing any cracked 

latch pins with new latch pins (with 

identical part numbers). 

• Modifying or replacing the latch 

pins and bearing plates; replacing any 

broken or missing latch pin, and the 

latch pins at the adjacent latch fitting 

locations, with new latch pins (with 

alternative part numbers); and replacing 

any cracked latch pins with new latch 

pins (with alternative part numbers). 

For airplanes on which all latch pins 

are replaced, the first repetitive 

inspection interval is within 6,000 flight 

cycles after replacement. For airplanes 

on which not all of the latch pins are 

replaced, the first repetitive inspection 

interval is 1,600 flight cycles after 

inspecting. For all airplanes, the 

repetitive interval for subsequent 

inspections is 1,600 flight cycles. 

FAA’s Determination 

We are proposing 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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Interim Action 

We consider this proposed AD 

interim action. The manufacturer is 

currently developing a modification that 

will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, we might consider 

additional rulemaking. 

Costs of Compliance 

We estimate that this proposed AD 

affects 228 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ......... 3 work-hours × $85 per hour = 

$255 per inspection cycle.

$0 $255 per inspection cycle .............. $58,140 per inspection cycle. 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules 54407 

We estimate the following costs to do 

any necessary replacements/ 

modifications that would be required 

based on the results of the proposed 

inspection. We have no way of 

determining the number of aircraft that 

might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of latch pins ................................................ 8 work-hours × $85 per hour = $680 ............................... $0 $680 

Modification of latch fittings .............................................. 36 hours × $85 per work-hours = $3,060 ........................ 0 3,060 

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 above, 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, 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. 

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): 

The Boeing Company: Docket No. FAA– 

2011–0915; Directorate Identifier 2011– 

NM–020–AD. 

Comments Due Date 

(a) We must receive comments by October 

17, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes; 

certificated in any category. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD was prompted by reports of 

fractured latch pins found in service; 

investigation revealed that the cracking and 

subsequent fracture were initiated by fatigue 

and propagated by a combination of fatigue 

and stress corrosion. We are issuing this AD 

to detect and correct fractured or broken 

latch pins, which could result in a forward 

or aft lower lobe cargo door opening and 

detaching during flight, and consequent 

rapid decompression of the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections 

(g) Before the accumulation of 6,000 total 

flight cycles, or within 1,000 flight cycles 

after the effective date of this AD, whichever 

occurs later: Do a general visual inspection 

for broken or missing latch pins of the lower 

sills of the forward and aft lower lobe cargo 

doors, and a detailed inspection for cracking 

of the latch pins, in accordance with 

paragraph 3.B., ‘‘Work Instructions,’’ of 

Boeing Alert Service Bulletin 747–53A2835, 

original, dated October 28, 2010. Repeat the 

inspections thereafter at the applicable 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2835, original, dated 

October 28, 2010. Before further flight, do all 

applicable corrective actions, in accordance 

with paragraph 3.B., ‘‘Work Instructions,’’ of 

Boeing Alert Service Bulletin 747–53A2835, 

original, dated October 28, 2010. 

Special Flight Permits 

(h) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided the cabin is not pressurized. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office (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. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes ODA that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

Related Information 

(j) For more information about this AD, 

contact Nathan Weigand, Aerospace 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
54408 Federal Register / Vol. 76, No. 170 / Thursday, September 1, 2011 / Proposed Rules 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; phone: (425) 917–6428; fax: 

(425) 917–6590; e-mail: 

nathan.p.weigand@faa.gov. 

(k) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

e-mail me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You may 

review copies of the referenced 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. 

Issued in Renton, Washington, on August 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22371 Filed 8–31–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Office of the Secretary 

45 CFR Parts 46, 160, and 164 

Food and Drug Administration 

21 CFR Parts 50 and 56 

Human Subjects Research 

Protections: Enhancing Protections for 

Research Subjects and Reducing 

Burden, Delay, and Ambiguity for 

Investigators; Extension of Comment 

Period 

AGENCIES: The Office of the Secretary, 

HHS, and the Food and Drug 

Administration, HHS. 

ACTION: Advance notice of proposed 

rulemaking; extension of comment 

period. 

SUMMARY: The Office of the Secretary of 

the Department of Health and Human 

Services (HHS) in coordination with the 

Office of Science and Technology Policy 

(OSTP) is extending the comment 

period for an advance notice of 

proposed rulemaking (ANPRM) 

requesting comment on how current 

regulations for protecting human 

subjects who participate in research 

might be modernized and revised to be 

more effective. That ANPRM was 

published in the Federal Register on 

July 26, 2011. 

DATES: The comment period for the 

proposed rule published July 26, 2011, 

at 76 FR 44512 is extended. Comments 

will be received through October 26, 

2011. 

ADDRESSES: You may submit comments, 

identified by docket ID number HHS– 

OPHS–2011–0005, by one of the 

following methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Enter the above 

docket ID number in the ‘‘Enter 

Keyword or ID’’ field and click on 

‘‘Search.’’ On the next web page, click 

on ‘‘Submit a Comment’’ action and 

follow the instructions. 

• Mail/Hand delivery/Courier [For 

paper, disk, or CD–ROM submissions] 

to: Jerry Menikoff, M.D., J.D., OHRP, 

1101 Wootton Parkway, Suite 200, 

Rockville, MD 20852. 

Comments received, including any 

personal information, will be posted 

without change to http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: Jerry 

Menikoff, M.D., J.D., Office for Human 

Research Protections (OHRP), 

Department of Health and Human 

Services, 1101 Wootton Parkway, Suite 

200, Rockville, MD 20852; telephone: 

240–453–6900 or 1–866–447–4777; 

facsimile: 301–402–2071; e-mail: 

jerry.menikoff@hhs.gov. 

SUPPLEMENTARY INFORMATION: The 

ANPRM was published in the Federal 

Register on July 26, 2011 (Volume 76, 

Number 143, page 44512) with a 

deadline for comments of September 26, 

2011. The ANPRM requests comments 

on how current regulations for 

protecting human subjects who 

participate in research might be 

modernized and revised to be more 

effective and how to better protect 

human subjects who are involved in 

research, while facilitating valuable 

research and reducing burden, delay, 

and ambiguity for investigators. Since 

the ANPRM was published the 

Department has received requests to 

extend the comment period to allow 

sufficient time for a full review of the 

ANPRM. HHS and OSTP are committed 

to affording the public a meaningful 

opportunity to comment on the ANPRM 

and welcome comments. 

Dated: August 26, 2011. 

Kathleen Sebelius, 

Secretary. 

[FR Doc. 2011–22341 Filed 8–31–11; 8:45 am] 

BILLING CODE 4150–28–P 

DEPARTMENT OF THE INTERIOR 

National Indian Gaming Commission 

25 CFR Chapter III 

Regulatory Review Schedule 

AGENCY: National Indian Gaming 

Commission. 

ACTION: Notice of cancellation of 

consultation meeting. 

SUMMARY: The purpose of this document 

is to cancel ten tribal consultations 

scheduled during November 2011, 

December 2011, January 2012, and 

February 2012 and to modify the dates 

for six tribal consultations scheduled 

during September 2011, October 2011 

and November 2011. 

DATES: See SUPPLEMENTARY INFORMATION

below for dates and locations of 

cancelled consultations. 

FOR FURTHER INFORMATION CONTACT: Lael 

Echo-Hawk, National Indian Gaming 

Commission, 1441 L Street, NW., Suite 

9100, Washington, DC 20005. 

Telephone: 202–632–7003; e-mail: 

reg.review@nigc.gov. 

SUPPLEMENTARY INFORMATION: On 

November 18, 2010, the National Indian 

Gaming Commission (NIGC) issued a 

Notice of Inquiry and Notice of 

Consultation advising the public that it 

was conducting a review of its 

regulations promulgated to implement 

25 U.S.C. 2701–2721 of the Indian 

Gaming Regulatory Act (IGRA) and 

requesting public comment on the 

process for conducting the regulatory 

review. On April 4, 2011, after holding 

eight consultations and reviewing all 

comments, NIGC published a Notice of 

Regulatory Review Schedule in the 

Federal Register setting out 

consultation schedules and review 

processes. (76 FR 18457, April 4, 2011). 

The Commission’s regulatory review 

process established a tribal consultation 

schedule with a description of the 

regulation groups to be covered during 

consultation. 

Group 1 included a review of: 

(a) A Buy Indian Act regulation; 

(b) Part 523—Review and Approval of 

Existing Ordinances or Resolutions; 

(c) Part 514—Fees; 

(d) Part 559—Facility License 

Notifications, Renewals, and 

Submissions; and 

(e) Part 542—Minimum Internal 

Control Standards. 

Group 2 included a review of: 

(a) Part 573—Enforcement; and 

(b) Regulations concerning 

proceedings before the Commission, 

including: Parts 519—Service, Part 

524—Appeals, Part 539—Appeals, and 


emcdonald on DSK2BSOYB1PROD with PROPOSALS