Federal Register / Vol. 73, No. 89 / Wednesday, May 7, 2008 / Proposed Rules 25597 

(c) Statement of disagreement. (1) If 

we deny your appeal regarding a request 

for amendment, you may file a concise 

statement of disagreement with the 

denial. We will maintain your statement 

with the record you sought to amend, 

and any disclosure of the record will 

include a copy of your statement of 

disagreement. 

(2) When practicable and appropriate, 

we will provide a copy of the statement 

of disagreement to any prior recipients 

of the record. 

Subpart C—Disclosure of Records 

§ 261a.11 Restrictions on disclosure. 

We will not disclose any record about 

you contained in a system of records to 

any person or agency without your prior 

written consent unless the disclosure is 

authorized by 5 U.S.C. 552a(b). 

§ 261a.12 Exempt Records. 

(a) Information compiled for civil 

action. This regulation does not permit 

you to have access to any information 

compiled in reasonable anticipation of a 

civil action or proceeding. 

(b) Law enforcement information. 

Pursuant to 5 U.S.C. 552a(k)(2), we have 

determined that it is necessary to 

exempt the systems of records listed 

below from the requirements of the 

Privacy Act concerning access to 

records, accountings of disclosures of 

records, maintenance of only relevant 

and necessary information in files, and 

certain publication provisions, 

respectively, 5 U.S.C. 552a(c)(3), (d), 

(e)(1), (e)(4)(G), (H) and (I), and (f), and 

§§ 261a.5, 261a.7, and 261a.8 of this 

part. The exemption applies only to the 

extent that a system of records contains 

investigatory materials compiled for law 

enforcement purposes. 

(1) BGFRS-1 Recruiting and 

Placement Records. 

(2) BGFRS 2 Personnel Security 

Systems. 

(3) BGFRS 4 General Personnel 

Records. 

(4) BGFRS 5 EEO Discrimination 

Complaint File. 

(5) BGFRS 18 Consumer Complaint 

Information. 

(6) BGFRS 21 Supervisory 

Enforcement Actions and Special 

Examinations Tracking System. 

(7) BGFRS 31 Protective 

Information System. 

(8) BGFRS 32 Visitor Registration 

System. 

(9) BGFRS 36 Federal Reserve 

Application Name Check System. 

(10) BGFRS/OIG 1 OIG 

Investigative Records. 

(c) Confidential references. Pursuant 

to 5 U.S.C. 552a(k)(5), we have 

determined that it is necessary to 

exempt the systems of records listed 

below from the requirements of the 

Privacy Act concerning access to 

records, accountings of disclosures of 

records, maintenance of only relevant 

and necessary information in files, and 

certain publication provisions, 

respectively, 5 U.S.C. 552a(c)(3), (d), 

(e)(1), (e)(4)(G), (H) and (I), and (f), and 

§§ 261a.5, 261a.7, and 261a.8 of this 

part. The exemption applies only to the 

extent that a system of records contains 

investigatory material compiled to 

determine an individual’s suitability, 

eligibility, and qualifications for Board 

employment or access to classified 

information, and the disclosure of such 

material would reveal the identity of a 

source who furnished information to the 

Board under a promise of 

confidentiality. 

(1) BGFRS-1 Recruiting and 

Placement Records. 

(2) BGFRS-2 Personnel Security 

Systems. 

(3) BGFRS-4 General Personnel 

Records. 

(4) BGFRS-10 General Files on 

Board Members. 

(5) BGFRS-11 Official General 

Files. 

(6) BGFRS-13 Federal Reserve 

System Bank Supervision Staff 

Qualifications. 

(7) BGFRS-14 General File on 

Federal Reserve Bank and Branch 

Directors. 

(8) BGFRS-25 Multi-Rater 

Feedback Records. 

(9) BGFRS/OIG-1 OIG Investigative 

Records. 

(10) BGFRS/OIG-2 OIG Personnel 

Records. 

(d) Criminal law enforcement 

information. Pursuant to 5 saU.S.C. 

552a(j)(2), we have determined that the 

OIG Investigative Records (BGFRS/OIG–

1) are exempt from the Privacy Act, 

except the provisions regarding 

disclosure, the requirement to keep an 

accounting, certain publication 

requirements, certain requirements 

regarding the proper maintenance of 

systems of records, and the criminal 

penalties for violation of the Privacy 

Act, respectively, 5 U.S.C. 552a(b), 

(c)(1), and (2), (e)(4)(A) through (F), 

(e)(6), (e)(7), (e)(9), (e)(10), (e)(11) and 

(i). 

By order of the Board of Governors of the 

Federal Reserve System, April 30, 2008. 

Jennifer J. Johnson, 

Secretary of the Board. 

[FR Doc. E8–9927 Filed 5–6–08; 8:45 am] 

BILLING CODE 6210–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0174; Directorate 

Identifier 2008–NE–03–AD] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. CFM56–5B1/P; –5B2/ 

P; –5B3/P; –5B3/P1; –5B4/P; –5B4/P1; 

–5B5/P; –5B6/P; –5B7/P; –5B8/P; and 

–5B9/P Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

CFM International, S.A. CFM56–5B1/P; 

–5B2/P; –5B3/P; –5B3/P1; –5B4/P; 

–5B4/P1; –5B5/P; –5B6/P; –5B7/P; 

–5B8/P; and –5B9/P turbofan engines. 

This proposed AD would require initial 

and repetitive eddy current inspections 

(ECIs) of certain part number (P/N) lowpressure (LP) turbine rear frames. This 

proposed AD results from a refined 

lifing analysis by the engine 

manufacturer that shows the need to 

identify initial and repetitive inspection 

thresholds for inspecting certain LP 

turbine rear frames. We are proposing 

this AD to detect low-cycle-fatigue 

cracks in the LP turbine rear frame, 

which could result in engine separation 

from the airplane, possibly leading to 

loss of control of the airplane. 

DATES: We must receive any comments 

on this proposed AD by July 7, 2008. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

You can get the service information 

identified in this proposed AD from 

CFM International, Technical 

Publications Department, 1 Neumann 

Way, Cincinnati, OH 45215; telephone 

(513) 552–2800; fax (513) 552–2816. 

FOR FURTHER INFORMATION CONTACT: 

Stephen Sheely, Aerospace Engineer, 


rwilkins on PROD1PC63 with PROPOSALS
25598 Federal Register / Vol. 73, No. 89 / Wednesday, May 7, 2008 / Proposed Rules 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: 

stephen.k.sheely@faa.gov; telephone 

(781) 238–7750; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2008–0174; Directorate Identifier 2008–

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

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the 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:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

Discussion 

CFM International, S.A. performed a 

refined lifing analysis that shows the 

need to identify initial and repetitive 

inspection thresholds for inspecting LP 

turbine rear frames, P/Ns 338–171–703–

0; 338–171–704–0; 338–171–705–0; and 

338–171–706–0. These parts are 

installed in CFM56–5B1/P; –5B2/P; 

–5B3/P; –5B3/P1; –5B4/P; –5B4/P1; 

–5B5/P; –5B6/P; –5B7/P; –5B8/P; and 

–5B9/P turbofan engines. This proposed 

AD would require initial and repetitive 

ECIs of these LP turbine rear frames. 

This condition, if not corrected, could 

result in low-cycle-fatigue cracks in the 

LP turbine rear frame, engine separation 

from the airplane, possibly leading to 

loss of control of the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of CFM International, 

S.A. Service Bulletin No. CFM56–5B S/ 

B 72–0620, Revision 1, dated December 

20, 2007, that describes procedures for 

performing ECIs of the LP turbine rear 

frame. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would require initial and 

repetitive ECIs of the affected P/N LP 

turbine rear frames. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 426 CFM56–5B series 

turbofan engines installed on airplanes 

of U.S. registry. We estimate that it 

would take about 3 work-hours to 

perform an eddy current inspection of 

an LP turbine rear frame. The average 

labor rate is $80 per work-hour. A 

replacement LP turbine rear frame costs 

about $102,240. If all 426 LP turbine 

rear frames needed replacement, we 

estimate the total cost of the proposed 

AD to U.S. operators to be $43,656,480. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

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 that the proposed AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

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

3. Would 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 regulatory evaluation 

of the estimated costs to comply with 

this proposed AD. You may get a copy 

of this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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: 

CFM International, S.A.: Docket No. FAA–

2008–0174; Directorate Identifier 2008–

NE–03–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by July 7, 

2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to CFM International, 

S.A. CFM56–5B1/P; –5B2/P; –5B3/P; –5B3/ 

P1; –5B4/P; –5B4/P1; –5B5/P; –5B6/P; –5B7/ 

P; –5B8/P; and –5B9/P turbofan engines with 


rwilkins on PROD1PC63 with PROPOSALS
Federal Register / Vol. 73, No. 89 / Wednesday, May 7, 2008 / Proposed Rules 25599 

low-pressure (LP) turbine rear frames, part 

numbers 338–171–703–0; 338–171–704–0; 

338–171–705–0; and 338–171–706–0, 

installed. These engines are installed on, but 

not limited to, Airbus A318, A319, A320, and 

A321 series airplanes. 

Unsafe Condition 

(d) This AD results from a refined lifing 

analysis by the engine manufacturer that 

shows the need to identify initial and 

repetitive inspection thresholds for 

inspecting certain LP turbine rear frames. We 

are issuing this AD to detect low-cyclefatigue cracks in the LP turbine rear frame, 

which could result in engine separation from 

the airplane, possibly leading to loss of 

control of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Initial Inspection 

(f) Perform an initial eddy current 

inspection (ECI) of the LP turbine rear frame 

using paragraphs 3.A. through 3.A.(7)(d) of 

the Accomplishment Instructions of CFM 

International, S.A. Service Bulletin (SB) No. 

CFM56–5B S/B 72–0620, Revision 1, dated 

December 20, 2007, at the following 

compliance times: 

(1) For commercial engine applications, 

within 25,000 cycles-since-new (CSN) on the 

LP turbine rear frame. 

(2) For corporate engine applications, 

within 19,000 CSN on the LP turbine rear 

frame. 

(3) For engines with unknown LP turbine 

rear frame CSN, within 300 cycles from the 

effective date of this AD. 

Repetitive Inspections 

(g) Perform repetitive ECIs of the LP 

turbine rear frame using paragraphs 3.A. 

through 3.A.(7)(d) of the Accomplishment 

Instructions of CFM International, S.A. SB 

No. CFM56–5B S/B 72–0620, Revision 1, 

dated December 20, 2007. Use the inspection 

intervals in paragraph 3.A.(8) of the 

Accomplishment Instructions of CFM 

International, S.A. SB No. CFM56–5B S/B 

72–0620, Revision 1, dated December 20, 

2007. 

LP Turbine Rear Frame Removal Criteria 

(h) Remove LP turbine rear frames from 

service that have a single crack length of 2.56 

inches (65 mm) or longer, or multiple cracks 

with accumulated crack length of 2.56 inches 

(65 mm) or longer. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) European Aviation Safety Agency AD 

2007–0221, dated August 13, 2007, also 

addresses the subject of this AD. 

(k) Contact Stephen Sheely, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: stephen.k.sheely@faa.gov; 

telephone (781) 238–7750; fax (781) 238–

7199, for more information about this AD. 

Issued in Burlington, Massachusetts, on 

April 29, 2008. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–10050 Filed 5–6–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0520; Directorate 

Identifier 2008–NM–018–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777–200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Boeing Model 777–200 series airplanes. 

This proposed AD would require 

repetitive inspections for any wrinkle in 

certain external skin panels, and for 

cracking at the fuselage bulkhead shear 

tie end fastener locations at certain 

stations of section 48 of the fuselage; 

and doing related investigative and 

corrective actions if necessary. This 

proposed AD results from a report of 

cracks found in the external skin on the 

left and right sides of the Section 48 

panel of the fuselage on two airplanes 

with skin wrinkles found at two of the 

external crack locations. We are 

proposing this AD to detect and correct 

wrinkles and cracks in certain external 

skin panels of Section 48, which could 

join together and result in reduced 

structural integrity of support structure 

for the vertical and horizontal stabilizers 

and inability of the airplane to sustain 

limit loads. 

DATES: We must receive comments on 

this proposed AD by June 23, 2008. 

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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Duong Tran, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6452; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2008–0520; Directorate Identifier 

2008–NM–018–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 a report of cracks 

found in the external skin on the left 

and right sides of the section 48 panel 

of the fuselage on two airplanes. There 

were ten external skin cracks on one 

airplane with 22,732 total flight hours 

and 20,286 total flight cycles; the cracks 

were 0.20 to 0.50 inch in length at 


rwilkins on PROD1PC63 with PROPOSALS