Federal Register / Vol. 76, No. 66 / Wednesday, April 6, 2011 / Rules and Regulations 18865 

Accordingly, 7 CFR part 253 is 

amended as follows: 

PART 253—ADMINISTRATION OF THE 

FOOD DISTRIBUTION PROGRAM FOR 

HOUSEHOLDS ON INDIAN 

RESERVATIONS 

■ 1. The authority citation for 7 CFR 

part 253 continues to read as follows: 

Authority: 91 Stat. 958 (7 U.S.C. 2011– 

2036). 

■ 2. In § 253.6: 

■ a. Revise paragraph (d)(2)(i); 

■ b. Redesignate paragraphs (d)(2)(ii) 

through (d)(2)(iv) as (d)(2)(iii) through 

(d)(2)(v), respectively; 

■ c. Add new paragraph (d)(2)(ii); 

■ d. Add new paragraph (d)(2)(vi); 

■ e. Revise the second sentence of 

paragraph (e)(1)(i); 

■ f. Add new paragraph (e)(3)(xi); and 

■ g. Remove the second sentence of 

paragraph (f)(2). 

The revisions and additions read as 

follows: 

§ 253.6 Eligibility of households. 

* * * * * 

(d) * * * 

(2) * * * 

(i) The cash value of life insurance 

policies and the first $1,500 of the 

equity value of one bona fide pre-paid 

funeral agreement per household 

member. The equity value of a pre-paid 

funeral agreement is the value that can 

be legally converted to cash by the 

household member. For example, an 

individual has a $1,200 pre-paid funeral 

agreement with a funeral home. The 

conditions of the agreement allow the 

household to cancel the agreement and 

receive a refund of the $1,200 minus a 

service fee of $50. The equity value of 

the pre-paid funeral agreement is 

$1,150. 

(ii) The value of funds held in 

retirement accounts described in 

sections 401(a), 403(a), 403(b), 408, 

408A, 457(b), and 501(c)(18) of the 

Internal Revenue Code of 1986; the 

value of funds held in a Federal Thrift 

Savings Plan account as described in 5 

U.S.C. 8439; and any other retirement 

program or account for which a resource 

exclusion is allowed under the 

Supplemental Nutrition Assistance 

Program (SNAP). 

* * * * * 

(vi) The value of funds held in a 

qualified education savings program 

described in section 529 of Internal 

Revenue Code of 1986 or in a Coverdell 

education savings account under section 

530 of that Code, and any other 

education savings program or account 

for which a resource exclusion is 

allowed under SNAP. 

* * * * * 

(e) * * * 

(1) * * * 

(i) * * * The income eligibility 

standards shall be the applicable SNAP 

net monthly income eligibility 

standards for the appropriate area, 

increased by the amount of the 

applicable SNAP standard deduction for 

that area. 

* * * * * 

(3) * * * 

(xi) Combat pay. Combat pay is 

defined as additional payment that is 

received by or from a member of the 

United States Armed Forces deployed to 

a combat zone, if the additional pay is 

the result of deployment to or service in 

a combat zone, and was not received 

immediately prior to serving in a 

combat zone. 

* * * * * 

Dated: April 1, 2011. 

Julia Paradis, 

Administrator Food and Nutrition Service. 

[FR Doc. 2011–8153 Filed 4–5–11; 8:45 am] 

BILLING CODE 3410–30–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0323; Directorate 

Identifier 2011–SW–005–AD; Amendment 

39–16651; AD 2011–08–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. Model 212 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing emergency airworthiness 

directive (EAD) for the Bell Helicopter 

Textron, Inc. (Bell) Model 212 

helicopters with a certain main rotor 

hub inboard strap fitting (fitting) 

installed. That EAD requires, before 

further flight, removing certain serialnumbered fittings and replacing them 

with airworthy fittings. It also requires 

performing a magnetic particle 

inspection (MPI) on fittings with certain 

serial numbers (S/Ns) to inspect for a 

crack. If a crack is found, the cracked 

fitting must be replaced with an 

airworthy fitting, and certain data must 

be reported to the FAA. This 

airworthiness directive (AD) retains the 

requirements of that EAD and expands 

the applicability to require performing 

an MPI for a crack on additional serialnumbered fittings. This AD is prompted 

by the determination that certain fittings 

were not manufactured in accordance 

with the approved manufacturing 

processes and controls. In total, eight 

fittings have been found that have 

cracks. We are issuing this AD to 

prevent failure of a fitting, loss of a main 

rotor blade, and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective April 21, 

2011. 

We must receive any comments on 

this AD by June 6, 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. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Bell Helicopter 

Textron, Inc., P.O. Box 482, Fort Worth, 

TX 76101, telephone (817) 280–3391, 

fax (817) 280–6466, or at http:// 

www.bellcustomer.com/files/. 

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 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: 

Michael Kohner, Aerospace Engineer, 

Rotorcraft Directorate, Rotorcraft 

Certification Office, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, phone: (817) 222–5170; fax: 

(817) 222–5783; e-mail: 

mike.kohner@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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18866 Federal Register / Vol. 76, No. 66 / Wednesday, April 6, 2011 / Rules and Regulations 

Discussion 

This AD supersedes EAD 2010–25–51, 

issued November 24, 2010 (EAD 2010– 

25–51), which superseded EAD 2010– 

24–52, issued November 19, 2010 (EAD 

2010–24–52). EAD 2010–24–52 

superseded EAD 2010–24–51, issued 

November 12, 2010 (EAD 2010–24–51). 

EAD 2010–24–51, EAD 2010–24–52, 

and EAD 2010–25–51 were all issued for 

the Bell Model 212 helicopters with a 

certain fitting installed. 

EAD 2010–24–51, the initial EAD, 

was issued for all Bell Model 212 

helicopters with a fitting, part number 

(P/N) 212–010–103–007, S/Ns 9956 

through 10005 with a prefix of ‘‘A’’. That 

EAD required, before further flight, 

removing any affected fitting and 

replacing it with an airworthy fitting. 

That EAD also prohibited installing any 

affected fitting on any helicopter. That 

EAD was prompted by an accident that 

resulted in several fatalities. During the 

investigation of the accident, a crack 

was found on a fitting. Subsequently, 

four additional fittings from the same 

manufacturing lot were inspected, and 

two were found to exhibit the same type 

of cracking. We issued EAD 2010–24–51 

to remove this lot from service to 

prevent failure of a fitting, loss of a main 

rotor blade, and subsequent loss of 

control of the helicopter. 

After we issued EAD 2010–24–51, 

additional fittings from a different 

manufacturing lot were found to have 

the same type of crack as that found on 

the fitting involved in the accident. 

Therefore, we issued superseding EAD 

2010–24–52 to require the same actions 

as EAD 2010–24–51, and to expand the 

applicability to include additional 

fittings. In addition to S/Ns 9956 

through 10005 with a prefix of ‘‘A’’, EAD 

2010–24–52 added S/Ns 52, 54, 55, 57 

through 65, 67, 69, 70, 71, 73, 103, 112, 

113, 137, and 139 with a prefix of ‘‘SH’’ 

to the applicability. EADs 2010–24–51 

and 2010–24–52 were issued as interim 

actions to address a known unsafe 

condition, and Bell continued to 

investigate the cause of the cracking. 

Because the root cause of the cracking 

had not been determined, and due to the 

severity of a fitting failure, we issued 

superseding EAD 2010–25–51 to require 

the same action as EAD 2010–24–52 and 

to also require performing an MPI on 

fittings with S/Ns 9911 through 9955, 

10006 through 10049, 10075 through 

10174, 10455 through 10460, 10581 

through 10655, 10742 through 10791, 

and 10862 through 10946 with a prefix 

of ‘‘A’’ to detect a crack on those fittings. 

If you find a crack, you are required to 

replace the cracked fitting with an 

airworthy fitting, and within 24 hours, 

report the information specified in 

Appendix 1 of the EAD to the Manager, 

Rotorcraft Certification Office. If you do 

not find a crack, you are required to 

reidentify and refinish the fitting in 

accordance with the specified portion of 

Alert Service Bulletin (ASB) 212–10– 

142, dated November 24, 2010 (ASB 

212–10–142). 

Actions Since AD Was Issued 

Since we issued EAD 2010–25–51, 

additional fittings with cracks were 

found using the MPI process. In 

response to these findings, Bell issued 

ASB 212–10–142, Revision A, dated 

March 21, 2011, that specifies 

performing an MPI for a crack on all 

serial-numbered fittings with the same 

part number in stock or in service. We 

have determined that certain fittings 

were not manufactured in accordance 

with the approved manufacturing 

processes and controls. Due to the 

severity of a fitting failure, this 

superseding AD is being issued to 

continue to require replacing certain 

serial-numbered fittings, and to expand 

the applicability to require performing 

an MPI for a crack on the remaining 

serial numbers of the fittings with the 

same part number. Serial-numbered 

fittings affected by this superseding AD 

are listed in Table 1 of the Applicability 

section of this AD. This superseding AD 

is being issued to prevent failure of a 

fitting, loss of a main rotor blade, and 

subsequent loss of control of the 

helicopter. 

Relevant Service Information 

We reviewed Bell Alert Service 

bulletin (ASB) No. 212–10–141, dated 

November 11, 2010 (ASB–212–10–141), 

which specified the immediate removal 

of the affected fittings, S/Ns A–9956 

through A–10005, from service. We also 

reviewed ASB No. 212–10–141, 

Revision A, dated November 18, 2010 

(ASB 212–10–141 Rev. A), which 

incorporates additional S/Ns of the 

affected fittings and specifies removing 

the affected serial-numbered fittings 

from service. In ASB 212–10–141, Bell 

states that they have determined that the 

fittings may not have been 

manufactured in accordance with the 

engineering design requirements and 

may fracture as a result of the 

nonconformance. 

We have also reviewed Bell ASB 212– 

10–142, initial release, dated November 

24, 2010 (ASB 212–10–142) which 

specifies performing an MPI on fittings 

with certain S/Ns to detect a crack on 

those fittings. 

Finally, we have reviewed Bell ASB 

212–10–142, Revision A, dated March 

21, 2011 (ASB 212–10–142 Rev. A), 

which includes all serial-numbered 

fittings except those already inspected 

and marked with ‘‘FM’’. ASB 212–10– 

142 Rev. A specifies 1) within 25 hours 

time-in-service (TIS) or 15 days, 

whichever comes first, for all fittings 

with less than 400 hours TIS; or 2) 

within 100 hours TIS or 30 days, 

whichever comes first, for all fittings 

with 400 or more hours but less than 

800 hours TIS; or 3) at the next main 

rotor teardown inspection or next 

tension-torsion strap replacement, 

whichever comes first, for all fittings 

with more than 800 hours TIS, 

performing a one-time MPI of the fitting, 

P/N 212–010–103–007, with all S/Ns in 

stock or in service. Finally, ASB 212– 

10–142 Rev. A states that all fittings, S/ 

Ns A–11021 and subsequent, SH–053, 

SH–066, SH–072, SH–074 through SH– 

102, SH–104 through SH–111, SH–114 

through SH–136, SH–138, and SH–140 

and subsequent are not affected by ASB 

212–10–142 Rev. A. Bell states that a 

one-time MPI of the affected fittings is 

required to ensure continued 

airworthiness of the fittings. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other helicopters of this 

same type design. 

AD Requirements 

This AD supersedes EAD 2010–25–51 

and requires the following: 

• Before further flight, for any 

helicopter with a fitting, S/N 9956 

through 10005, with a prefix of ‘‘A’’, and 

S/N 52, 54, 55, 57 through 65, 67, 69, 

70, 71, 73, 103, 112, 113, 137, and 139 

with a prefix of ‘‘SH’’, replace the fitting 

with an airworthy fitting. Any fitting 

with a S/N identified in this paragraph 

is no longer eligible for installation on 

any helicopter. 

• Before further flight, for any 

helicopter with a fitting, S/N 9911 

through 9955, 10006 through 10049, 

10075 through 10174, 10455 through 

10460, 10581 through 10655, 10742 

through 10791, and 10862 through 

10946, with a prefix of ‘‘A’’, perform an 

MPI of each fitting for a crack. If the 

fitting is cracked, replace it with an 

airworthy fitting. If the fitting is not 

cracked, reidentify and refinish the 

fitting. 

• For any fitting with a serial number 

identified in paragraph (h) in the 

Compliance section of this AD, perform 

an MPI of each fitting for a crack: 

Æ For any fitting with 400 or less 

hours TIS, perform an MPI within 25 


erowe on DSK5CLS3C1PROD with RULES
Federal Register / Vol. 76, No. 66 / Wednesday, April 6, 2011 / Rules and Regulations 18867 

hours TIS or 15 days, whichever comes 

first. 

Æ For any fitting with more than 400 

hours but less than 800 hours TIS, 

perform an MPI within 100 hours TIS or 

30 days, whichever comes first. 

Æ For fittings with 800 hours or more 

TIS, perfrom an MPI at the next main 

rotor hub teardown inspection or 

tension-torsion strap replacement, 

whichever comes first. 

Æ If a fitting is cracked, replace it 

with an airworthy fitting. If a fitting is 

not cracked, reidentify and refinish the 

fitting. 

• If a crack is found on any fitting, 

within 24 hours, report the information 

requested in Appendix 1 of this AD to 

the Manager, Rotorcraft Certification 

Office, FAA, 2601 Meacham Blvd, Fort 

Worth, Texas 76137, or e-mail 7–AVS– 

ASW–170@faa.gov. 

Differences Between the AD and the 

Service Information 

This AD differs from ASB 212–10–142 

Rev. A as follows: 

• We do not require returning parts to 

Bell. 

• We require performing an MPI 

before further flight on certain S/N 

fittings included in the initial release of 

ASB 212–10–142. 

• We require sending information to 

the Rotorcraft Certification Office and 

not to Bell. 

• Bell uses the term ‘‘total time-inservice’’ to describe compliance times, 

and we use the term ‘‘time-in-service.’’ 

• We specify S/Ns in our AD, and 

Bell does not specify S/Ns in ASB 212– 

10–142 Rev. A. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA finds that the risk to the 

flying public justifies waiving notice 

and comment prior to adoption of this 

rule because we evaluated all the 

available information and determined 

the unsafe condition described is likely 

to exist or develop in other helicopters 

of this same type design. Therefore, we 

find that notice and opportunity for 

prior public comment are impracticable 

because of the short compliance times, 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the Docket Number 

FAA–2011–0323 and ‘‘Directorate 

Identifier 2011–SW–005–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to 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 AD. 

Costs of Compliance 

We estimate that this AD affects 84 

helicopters of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

helicopter 

Cost on U.S. 

operators 

(a) For any fitting, S/N 9956 through 10005 and a prefix of 

‘‘A’’; or a S/N of 52, 54, 55, 57 through 65, 67, 69, 70, 71, 

73, 103, 112, 113, 137, 139 with a prefix of ‘‘SH’’; replace 

the fitting with an airworthy fitting (assumes action affects 

72 fittings).

40 work-hours × $85 per hour 

= $3,400.

$2,367 $5,767 $415,224 

(c) For any fitting affected by this AD with a S/N not identified in paragraph (a) of this table, perform an MPI on 

each fitting for a crack unless documentation exists of any 

previous MPI performed during regularly scheduled maintenance (assumes action affects 12 fittings).

40 work-hours × $85 per hour 

= $3,400.

0 3,400 40,800 

We estimate a total cost of $456,024 

to do the actions required by this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, 

(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. 


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18868 Federal Register / Vol. 76, No. 66 / Wednesday, April 6, 2011 / Rules and Regulations 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends Part 39 of the Federal 

Aviation Regulations (14 CFR part 39) as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–08–01 Bell Helicopter Textron, Inc. 

(Bell): Amendment 39–16651; Docket 

No. FAA–2011–0323; Directorate 

Identifier 2011–SW–005–AD. 

Effective Date 

(a) This AD is effective on April 21, 2011. 

Other Affected ADs 

(b) This AD supersedes Emergency AD 

2010–25–51, issued on November 24, 2010, 

Directorate Identifier 2010–SW–096–AD. 

Applicability 

(c) This AD applies to Model 212 

helicopters certificated in any category, with 

a main rotor hub inboard strap fitting 

(fitting), part number (P/N) 212–010–103– 

007, installed, with the serial numbers (S/Ns) 

listed in the following Table 1: 

TABLE 1 

Serial numbers with a prefix of: 

‘‘A’’ or ‘‘A–FS’’: 7 through 10946. 

‘‘A1’’: 430 through 7606. 

‘‘DI’’: 22296 through 22681. 

‘‘EA’’: 333 through 381. 

‘‘LK’’: 4619 through 4631. 

‘‘MB’’: 11908 through 11916. 

‘‘SH’’: 52, 54, 55, 57 through 65, 67, 69, 70, 

71, 73, 103, 112, 113, 137, and 139. 

‘‘WR’’: 275 through 319. 

Unsafe Condition 

(d) This AD is prompted by a recent 

accident that resulted in several fatalities. 

During the investigation of the accident, a 

crack was found on a fitting. We have 

determined that certain fittings were not 

manufactured in accordance with approved 

manufacturing processes and controls. Due to 

the severity of a fitting failure, we are 

requiring replacing certain serial-numbered 

fittings, and we are expanding the 

applicability to require performing a 

magnetic particle inspection (MPI) for a crack 

on the remaining serial numbers of the 

fittings with the same part number. The 

actions specified by this AD are intended to 

prevent failure of a fitting, loss of a main 

rotor blade, and subsequent loss of control of 

the helicopter. 

Compliance 

(e) Required as indicated, unless 

accomplished previously. 

(f) Before further flight, for any helicopter 

with a fitting, serial number (S/N) 9956 

through 10005 with a prefix of ‘‘A’’, and S/ 

N 52, 54, 55, 57 through 65, 67, 69, 70, 71, 

73, 103, 112, 113, 137, and 139 with a prefix 

of ‘‘SH’’ installed, replace the fitting with an 

airworthy fitting. Any fitting with a S/N 

identified in this paragraph is no longer 

eligible for installation on any helicopter. 

(g) Before further flight, for any helicopter 

with a fitting, S/N 9911 through 9955, 10006 

through 10049, 10075 through 10174, 10455 

through 10460, 10581 through 10655, 10742 

through 10791, and 10862 through 10946 

with a prefix of ‘‘A’’, perform an MPI of each 

fitting for a crack. If a fitting is cracked, 

replace it with an airworthy fitting. If a fitting 

is not cracked, reidentify and refinish the 

fitting using a vibrating stylus (not to exceed 

0.005 inch depth nor to extend within 0.10 

inch of part edge) by adding ‘‘FM’’ at the end 

of the P/N. Touch up the reworked area with 

brush cadmium plating or zinc chromate 

primer. Reidentify the historical service 

records with ‘‘FM’’ at the end of the P/N. 

Note 1: The Bell Model 212 Component, 

Repair, and Overhaul Manual, which is not 

incorporated by reference, contains 

additional information about MPI 

procedures. 

(h) For any fitting with a S/N identified in 

Table 1 of the Applicability section of this 

AD, and not identified in paragraph (f) or (g) 

of this AD, perform an MPI of each fitting for 

a crack as follows: 

(1) For a fitting with 400 or less hours timein-service (TIS), perform an MPI within 25 

hours TIS or 15 days, whichever comes first. 

(2) For a fitting with more than 400 but less 

than 800 hours TIS, perform an MPI within 

100 hours TIS or 30 days, whichever comes 

first. 

(3) For a fitting with 800 or more hours 

TIS, perform an MPI at the next main rotor 

hub teardown inspection or tension-torsion 

strap replacement, whichever comes first. 

(4) If a fitting is cracked, replace it with an 

airworthy fitting. 

(5) If a fitting is not cracked, reidentify and 

refinish the fitting in accordance with the 

instructions in paragraph (g) of this AD. 

(i) Within 24 hours after finding any 

cracked fitting, report the information 

requested in Appendix 1 of this AD to the 

Manager, Rotorcraft Certification Office, to 

the address, fax number, or email specified 

in the Appendix. 

Paperwork Reduction Act Burden Statement 

(j) 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 Office of 

Management and Budget (OMB) Control 

Number. Under the provisions of the 

Paperwork Reduction Act (44 U.S.C. 3501 et 

seq.), the OMB has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

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. 

Subject 

(k) The Joint Aircraft System Component/ 

Air Transport Association of America Code is 

6220: Main rotor hub. 

Alternative Methods of Compliance 

(AMOCs) 

(l) The Manager, Rotorcraft Certification 

Office, 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 

‘‘Additional Information’’ section of this AD. 

Note 2: Before using any approved AMOC, 

we request that you notify your appropriate 

principal inspector, or if you have no 

principal inspector, your local Flight 

Standards District Office. 

Additional Information 

(m)(1) For service information identified in 

this AD, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, TX 76101, 

telephone (817) 280–3391, fax (817) 280– 

6466, or at http://www.bellcustomer.com/ 

files/. 

(2) You may review copies of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas. 

(3) Bell Helicopter Alert Service Bulletin 

No. 212–10–141, Revision A, dated 

November 18, 2010, and Alert Service 

Bulletin No. 212–10–142, Revision A, dated 

March 21, 2011, contain additional guidance 

pertaining to the subject of this AD but are 

not incorporated by reference. A picture of a 

crack indication on an actual fitting is shown 

in Figure 1 of Bell Alert Service Bulletin 

212–10–142, Rev. A. 

Appendix 1 to AD 2011–08–01 

AD Compliance Inspection Report (Sample 

Format) 

Provide the following information and 

mail, fax, or e-mail report to: Manager, 

Rotorcraft Certification Office, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137, fax 

(817) 222–5783, e-mail 7–AVS–ASW– 

170@faa.gov. 


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Federal Register / Vol. 76, No. 66 / Wednesday, April 6, 2011 / Rules and Regulations 18869 

Aircraft Registration No. 

Helicopter Serial No. 

Helicopter Owner/Operator. 

Contact Phone No. 

Fitting Part Number. 

Fitting Serial Number. 

Hours Time-in-Service on Fitting at Time of Inspection. 

Description of Findings. 

Who Performed the Inspection? 

Date and Location the Inspection was Performed. 

Describe the crack size, location, orientation (provide a sketch or pictures with the fitting part and serial numbers). 

Provide any other comments. 

Issued in Fort Worth, Texas, on March 29, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–8133 Filed 4–5–11; 8:45 am] 

BILLING CODE 4910–13–P 

PENSION BENEFIT GUARANTY 

CORPORATION 

29 CFR Part 4044 

Allocation of Assets in SingleEmployer Plans 

CFR Correction 

In Title 29 of the Code of Federal 

Regulations, Part 1927 to End, revised as 

of July 1, 2010, on page 1007, in the 

table in Appendix B, in the entry for 

July 1994, the fourth column is 

corrected to read ‘‘.0525’’. 

[FR Doc. 2011–8325 Filed 4–5–11; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[Docket No. USCG–2011–0166] 

RIN 1625–AA00 

Safety Zone; Chicago Harbor, Navy 

Pier East, Chicago, IL 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of enforcement of 

regulation. 

SUMMARY: The Coast Guard will enforce 

the Navy Pier East Safety Zone in 

Chicago Harbor from 9:20 p.m. through 

9:40 p.m. on May 7, 2011. This action 

is necessary and intended to ensure 

safety of life on the navigable waters of 

the United States immediately prior to, 

during, and immediately after fireworks 

events. This rule will establish 

restrictions upon and control movement 

of vessels in a specified area 

immediately prior to, during, and 

immediately after fireworks events. 

During the enforcement period, no 

person or vessel may enter the safety 

zone without the permission of the 

Captain of the Port, Sector Lake 

Michigan. 

DATES: The regulations in 33 CFR 

165.933 will be enforced from 9:20 p.m. 

through 9:40 p.m. on May 7, 2011. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this notice, call 

or e-mail BM1 Adam Kraft, Prevention 

Department, Coast Guard Sector Lake 

Michigan, Milwaukee, WI at 414–747– 

7154, e-mail Adam.D.Kraft@uscg.mil. 

SUPPLEMENTARY INFORMATION: The Coast 

Guard will enforce the safety zone; 33 

CFR 165.933–Chicago Harbor, Navy Pier 

East, Chicago, IL for the following event: 

(1) Alexian Brothers Foundation 

Fireworks; on May 7, 2011 from 9:20 

p.m. through 9:40 p.m. 

All vessels must obtain permission 

from the Captain of the Port, Sector Lake 

Michigan, or his or her on-scene 

representative to enter, move within or 

exit the safety zone. Vessels and persons 

granted permission to enter the safety 

zone shall obey all lawful orders or 

directions of the Captain of the Port, 

Sector Lake Michigan, or his or her onscene representative. While within a 

safety zone, all vessels shall operate at 

the minimum speed necessary to 

maintain a safe course. 

This notice is issued under authority 

of 33 CFR 165.933 Safety Zone, Chicago 

Harbor, Navy Pier East, Chicago IL and 

5 U.S.C. 552 (a). In addition to this 

notice in the Federal Register, the Coast 

Guard will provide the maritime 

community with advance notification of 

these enforcement periods via broadcast 

Notice to Mariners or Local Notice to 

Mariners. The Captain of the Port, 

Sector Lake Michigan, will issue a 

Broadcast Notice to Mariners notifying 

the public when enforcement of the 

safety zone established by this section is 

suspended. If the Captain of the Port, 

Sector Lake Michigan, determines that 

the safety zone need not be enforced for 

the full duration stated in this notice, he 

or she may use a Broadcast Notice to 

Mariners to grant general permission to 

enter the safety zone. The Captain of the 

Port, Sector Lake Michigan, or his or her 

on-scene representative may be 

contacted via VHF Channel 16. 

Dated: March 24, 2011. 

L. Barndt, 

Captain, U.S. Coast Guard, Captain of the 

Port, Sector Lake Michigan. 

[FR Doc. 2011–8214 Filed 4–5–11; 8:45 am] 

BILLING CODE 9110–04–P 


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