Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Proposed Rules 72409 

bulletin has been included in general 

revisions of the AFM, the general revisions 

may be inserted into the AFM and the 

advance amendment bulletin may be 

removed, provided the relevant information 

in the general revision is identical to that in 

the advance amendment bulletin. 

TABLE 1.—AFM REVISIONS

Airplane model AFM documents to be 

revised 

SD3–30 .............. SBH.3.2, SBH.3.3, 

SBH.3.6, SBH.3.7, 

SBH.3.8, and SBH.3.9. 

SD3–60 .............. SB.4.3, SB.4.6, and 

SB.4.8. 

TABLE 1.—AFM REVISIONS—

Continued 

Airplane model AFM documents to be 

revised 

SD3–60 SHERPA.SB.5.2. 

SD3–SHERPA ... SB.6.2. 

Revision of Airworthiness Limitation (AWL) 

Section 

(g) Within 180 days after the effective date 

of this AD: Revise the AWL section of the 

Instructions for Continued Airworthiness by 

incorporating airplane maintenance manual 

sections 5–20–01 and 5–20–02 as introduced 

by the Shorts temporary revisions (TR) 

specified in Table 1 of this AD into the AWL 

section of the AMMs for the airplane models 

specified in Table 1. Thereafter, except as 

provided by paragraph (i) of this AD, no 

alternative structural inspection intervals 

may be approved for the longitudinal skin 

joints in the fuselage pressure shell. 

Note 3: The requirements of paragraph (g) 

of this AD may be done by inserting a copy 

of the applicable TR into the applicable 

AMM. When the TR has been included in 

general revisions of the AMM, the general 

revisions may be inserted in the AMM and 

the TR may be removed, provided the 

relevant information in the general revision 

is identical to that in the TR. 

TABLE 2.—AMM TEMPORARY REVISIONS

Airplane model Temporary revision Dated To AMM 

SD3–30 .......................................................... TR330–AMM–14 ............................................ June 21, 2004 ........ SD3–30 AMM. 

SD3–60 .......................................................... TR360–AMM–33 ............................................ July 27, 2004 ......... SD3–60 AMM. 

SD3–60 SHERPA .......................................... TRSD360S–AMM–14 .................................... July 29, 2004 ......... SD3–60 SHERPA AMM. 

SD3–SHERPA ............................................... TRSD3S–AMM–15 ........................................ July 28, 2004 ......... SD3–SHERPA AMM. 

Resistance Check, Inspection, and Jumper 

Installation 

(h) Within 180 days after the effective date 

of this AD: Perform the insulation resistance 

check, general visual inspections, and 

bonding jumper wire installations; in 

accordance with Shorts Service Bulletin 

SD330–28–37, SD360–28–23, SD360 

SHERPA–28–3, or SD3 SHERPA–28–2; all 

dated June 2004; as applicable. If any defects 

or damage are discovered during any 

inspection or check required by this AD, 

before further flight, repair the defects or 

damage using a method approved by either 

the Manager, International Branch, ANM–

116, Transport Airplane Directorate, FAA; or 

the Civil Aviation Authority (CAA) (or its 

delegated agent). 

Note 4: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(j) British airworthiness directive G–2004–

0021, dated August 25, 2004, also addresses 

the subject of this AD. 

Issued in Renton, Washington, on 

November 25, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–23600 Filed 12–2–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23159; Directorate 

Identifier 2005–SW–10–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model SA–365N, SA–365N1, 

AS–365N2, and SA–366G1 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

superseding an existing airworthiness 

directive (AD) that currently applies to 

Eurocopter France (ECF) Model SA 

365N, N1, and AS 365N2 helicopters. 

That AD currently requires inspecting 

the main gearbox (MGB) suspension 

diagonal cross-member (diagonal crossmember) for cracks and replacing it with 

an airworthy part if any crack is found. 

This action proposes to require more 

frequent inspections of the diagonal 

cross-member and adding the Model 

SA–366G1 helicopters to the 

applicability. This proposal is prompted 

by several reports of cracks in the 

diagonal cross-member. The actions 

specified by the proposed AD are 

intended to prevent failure of the 

diagonal cross-member, pivoting of the 

MGB, severe vibrations, and a 

subsequent forced landing. 

DATES: Comments must be received on 

or before February 3, 2006. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically; 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically; 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590; 

• Fax: 202–493–2251; or 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this proposed AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 

72410 Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Proposed Rules 

75053–4005, telephone (972) 641–3460, 

fax (972) 641–3527. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http://dms.dot.gov. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Guidance Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5130, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any written 

data, views, or arguments regarding this 

proposed AD. Send your comments to 

the address listed under the caption 

ADDRESSES. Include the docket number 

‘‘FAA–2005–23159, Directorate 

Identifier 2005–SW–10–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed 

rulemaking. Using the search function 

of our docket Web site, you can find and 

read the comments to any of our 

dockets, including the name of the 

individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78) or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Management 

System (DMS) Docket Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone 1–800–647–

5227) is located at the plaza level of the 

Department of Transportation NASSIF 

Building in Room PL–401 at 400 

Seventh Street, SW., Washington, DC. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Discussion 

On April 3, 1998, we issued AD 98–

08–14, Amendment 39–10463 (63 FR 

17676, April 10, 1998), to require 

inspecting each diagonal cross-member 

for cracks and replacing it with an 

airworthy diagonal cross-member if any 

crack is found. That action was 

prompted by several reports of cracks in 

diagonal cross-members. The 

requirements of that AD are intended to 

prevent failure of the diagonal crossmember, which could cause the MGB to 

pivot resulting in severe vibrations and 

a subsequent forced landing. 

Since issuing that AD, we have 

determined the Model SA–366G1 

helicopter should be added to the 

applicability because this model may 

contain an affected diagonal crossmember, part number (P/N) 365A38–

3023–22, –23 or –24. Also, we have 

determined after further study and 

additional reports of failed diagonal 

cross-members that more frequent 

inspections of the diagonal crossmember are necessary. 

The Direction Generale De L’Aviation 

Civile (DGAC), the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

ECF Model AS–365N, N1, N2, and SA 

366 G1 helicopters. The DGAC advises 

of the discovery of a crack in a diagonal 

cross-member of the ECF Model SA 366 

G1 helicopter. 

ECF has issued Service Bulletin (SB) 

No. 05.00.37, dated May 29, 1997, for 

Model AS–365N, N1, and N2 

helicopters. The SB specifies a periodic 

inspection for a crack or failure of a 

central branch of the MGB suspension 

strut pre-MOD 0763B80. ECF has also 

issued Alert Service Bulletin (ASB) No. 

05.25, dated June 19, 2002. The ASB 

specifies checking the center portion of 

the MGB suspension cross-bar for Model 

AS–366G1 helicopters, with a crossbar, 

P/N 365A38–3023–22, –23, or –24, 

installed. The DGAC classified these 

service bulletins as mandatory and 

issued ADs 2003–241(A) and 1997–093–

041(A) R2, both dated June 25, 2003, to 

ensure the continued airworthiness of 

these helicopters in France. 

These helicopter models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement, the DGAC has kept 

the FAA informed of the situation 

described above. The FAA has 

examined the findings of the DGAC, 

reviewed all available information, and 

determined that AD action is necessary 

for products of these type designs that 

are certificated for operation in the 

United States. 

This previously described unsafe 

condition is likely to exist or develop on 

other helicopters of the same type 

designs. Therefore, the proposed AD 

would supersede AD 98–08–14 to 

require the following: 

• For Model SA–365N and SA–365N1 

helicopters, before accumulating 15,000 

operating cycles; and for Model AS–

365N2 and SA–366G1 helicopters, 

before accumulating 11,000 operating 

cycles: 

• Inspect the diagonal cross-member 

for a crack in the area of the center 

borehole. Use a borescope with a 90- 

degree drive, a video assembly with 

optical fiber illumination, or any other 

appropriate device that makes it 

possible to visually inspect the center 

area of the part. 

• Repeat the previous inspections at 

intervals not to exceed 250 operating 

cycles or 50 hours time-in-service, 

whichever occurs first. 

• If a crack is found, before further 

flight, replace the diagonal crossmember with an airworthy diagonal 

cross-member. 

We estimate that this proposed AD 

would affect 133 helicopters of U.S. 

registry, and would: 

• Take about 1 work hour to inspect 

the diagonal cross-member, 

• Take about 10 work hours to 

replace the diagonal cross-member, if 

necessary, at an average labor rate of $65 

per work hour, and 

• Cost about $6,600 to replace the 

part. 

Based on these figures, we estimate 

the total cost impact of the proposed AD 

on U.S. operators to be $139,990, 

assuming 12 inspections per year per 

helicopter, and assuming 5 helicopters 

require replacing the diagonal crossmember. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, 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 that the 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); 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 draft economic 

evaluation of the estimated costs to 

comply with this proposed AD. See the 

Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Proposed Rules 72411 

DMS to examine the draft economic 

evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend 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. Section 39.13 is amended by 

removing Amendment 39–10463 (63 FR 

17676, April 10, 1998), and by adding 

a new airworthiness directive (AD), to 

read as follows: 

Eurocopter France: Docket No. FAA–2005–

23159; Directorate Identifier 2005–SW–

10–AD. Supersedes AD 98–08–14, 

Amendment 39–10463, Docket No. 97–

SW–21–AD. 

Applicability: Model SA–365N, SA–365N1, 

AS–365N2, and SA–366G1 helicopters with 

a main gearbox (MGB) suspension diagonal 

cross-member (diagonal cross-member) part 

number (P/N) 365A38–3023–20, –21, –22, 

–23, or –24 installed, certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the diagonal crossmember, pivoting of the MGB, severe 

vibrations, and subsequent forced landing, do 

the following: 

(a) For Model SA–365N and SA–365N1 

helicopters, before accumulating 15,000 

operating cycles; and for Model AS–365N2 

and SA–366G1 helicopters, before 

accumulating 11,000 operating cycles: 

(1) Inspect the diagonal cross-member for 

a crack in the area of the center borehole. Use 

a borescope with a 90-degree drive, a video 

assembly with optical fiber illumination, or 

any other appropriate device that allows you 

to visually inspect the center area of the part. 

(2) Repeat the inspection required by 

paragraph (a)(1) of this AD at intervals not to 

exceed 250 operating cycles or 50 hours timein-service, whichever occurs first. 

Note 1: ‘‘Operating cycles’’ are defined in 

the Airworthiness Limitations Section of the 

Master Servicing Recommendations. 

(b) If a crack is found as a result of the 

inspections required by this AD, before 

further flight, replace the diagonal crossmember with an airworthy diagonal crossmember. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Safety Management Group, 

Rotorcraft Directorate, FAA, for information 

about previously approved alternative 

methods of compliance. 

Note 2: The subject of this AD is addressed 

in Direction Generale De L’Aviation Civile 

(France) AD 1997–093–041(A) R2, dated June 

25, 2003, and 2003–241(A), dated June 25, 

2003. 

Issued in Fort Worth, Texas, on November 

23, 2005. 

Carl F. Mittag, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–23602 Filed 12–2–05; 8:45 am] 

BILLING CODE 4910–13–P 

SOCIAL SECURITY ADMINISTRATION 

20 CFR Parts 404 and 416 

[Regulation Nos. 4 and 16] 

RIN 0960–AG12 

Nonpayment of Benefits to Fugitive 

Felons and Probation or Parole 

Violators 

AGENCY: Social Security Administration. 

ACTION: Proposed rules. 

SUMMARY: To implement section 203 of 

the Social Security Protection Act of 

2004 (SSPA), we propose to revise our 

regulations on the payment of Social 

Security and Supplemental Security 

Income benefits under titles II and XVI 

of the Social Security Act (the Act). 

Section 203 requires that title II benefits 

will not be paid to a person who is a 

fugitive felon or probation or parole 

violator, unless good cause is shown as 

specified in this new law. Section 203 

also added a good cause exception to 

the title XVI fugitive felon ineligibility 

provision. In addition, we propose to 

make other changes in our regulations, 

required by this legislation, such as 

removing the reference to high 

misdemeanors in the state of New 

Jersey. Finally, we propose to clarify our 

interpretation of the statutory language 

‘‘fleeing to avoid’’ for the purposes of 

the title II and title XVI provisions. 

DATES: To be sure that we consider your 

comments, we must receive them by 

February 3, 2006. 

ADDRESSES: You may give us your 

comments by: Using our Internet site 

facility (i.e., Social Security Online) at 

http://policy.ssa.gov/erm/rules.nsf/ 

Rules+Open+To+Comment or the 

Federal eRulemaking Portal at http:// 

www.regulations.gov; e-mail to 

regulations@ssa.gov; telefax to (410) 

966–2830; or letter to the Commissioner 

of Social Security, P.O. Box 17703, 

Baltimore, MD 21235–7703. You may 

also deliver them to the Office of 

Regulations, Social Security 

Administration, 100 Altmeyer Building, 

6401 Security Boulevard, Baltimore, MD 

21235–6401, between 8 a.m. and 4:30 

p.m. on regular business days. 

Comments are posted on our Internet 

site, or you may inspect them physically 

on regular business days by making 

arrangements with the contact person 

shown in this preamble. 

Electronic Version 

The electronic file of this document is 

available on the date of publication in 

the Federal Register at http:// 

www.gpoaccess.gov/fr/index.html. 

FOR FURTHER INFORMATION CONTACT: 

Richard Bresnick, Social Insurance 

Specialist, Office of Regulations, Social 

Security Administration, 100 Altmeyer 

Building, 6401 Security Boulevard, 

Baltimore, MD 21235–6401, (410) 965–

1758 or TTY (410) 966–5609. For 

information on eligibility or filing for 

benefits, call our national toll-free 

number, 1–800–772–1213 or TTY 1–

800–325–0778, or visit our Internet site, 

Social Security Online, at http:// 

www.socialsecurity.gov. 

SUPPLEMENTARY INFORMATION: The 

Personal Responsibility and Work 

Opportunity Reconciliation Act 

(PRWORA) of 1996 (Pub. L. 104–193) 

provided in section 1611(e)(4) of the Act 

that a person is ineligible for payments 

under title XVI for any month he or she 

is avoiding prosecution for a felony, is 

avoiding confinement for conviction of 

a felony, or is violating a condition of 

probation or parole. Prior to the 

enactment of the SSPA (Pub. L. 108–

203) on March 2, 2004, section 

1611(e)(4) of the Act also provided that