16990 Federal Register / Vol. 72, No. 66 / Friday, April 6, 2007 / Rules and Regulations 

4. Projected reporting, recordkeeping, 

and other compliance requirements. 

There are no reporting, recordkeeping, 

or other compliance requirements 

associated with the revised 

Interpretation. 

5. Minimizing significant economic 

impact of the revised Interpretation on 

small entities. There were no public 

comments that suggested a significant 

alternative that would minimize the 

impact of the proposal on small entities. 

There are eleven bankers’ banks 

qualifying as ‘‘small entities’’ under 

RFA. The revised Interpretation 

provides all bankers’ banks with the 

ability to maintain their exemption from 

reserve requirements, if any, while 

undertaking certain additional bankers’

bank activities or customers as 

authorized by their chartering 

authorities. No bankers’ bank is required 

to seek a determination under the 

revised Interpretation. The revised 

Interpretation imposes no economic 

burdens on bankers’ banks, and instead 

only offers the opportunity to bankers’

banks that are exempt from reserve 

requirements to maintain the economic 

benefits of that exemption under the 

specified circumstances. Accordingly, 

the Board believes that the revised 

Interpretation will not have a significant 

impact on a substantial number of small 

entities. 

B. Paperwork Reduction Act 

In accordance with the Paperwork 

Reduction Act (PRA) of 1995 (44 U.S.C. 

3506; 5 CFR part 1320 Appendix A.10), 

the Board reviewed the proposal under 

the authority delegated to the Board by 

the Office of Management and Budget 

(OMB). The proposal contains no 

requirements subject to the PRA. 

VI. Plain Language 

The Board received one comment on 

whether the proposal was in plain 

language. This commenter stated that 

the Board’s failure to propose standards 

for its exercise of authority under the 

proposal amounted to a failure to 

comply with the ‘‘Plain Language’’

provisions of the Gramm-Leach-Bliley 

act. This commenter stated that the 

Board should instead say that it 

proposes to do whatever it wants given 

its view of the purposes of the Act. For 

the reasons stated above, the Board 

believes that the revised Interpretation 

is stated in plain language to the greatest 

extent possible at this point in time. As 

also stated above, the Board expects to 

publish further guidance and standards 

as it obtains additional experience in 

the future with requests for 

determinations under the revised 

Interpretation. Accordingly, the Board 

believes that the revised Interpretation 

complies with applicable plain language 

requirements. 

List of Subjects in 12 CFR Part 204 

Banks, banking, Reporting and 

recordkeeping requirements. 

■ For the reasons set forth in the 

preamble, the Board is amending 12 

CFR part 204 as follows: 

PART 204—RESERVE 

REQUIREMENTS OF DEPOSITORY 

INSTITUTIONS (REGULATION D) 

■ 1. The authority citation for part 204 

continues to read as follows: 

Authority: 12 U.S.C. 248(a), 248(c), 371a, 

461, 601, 611, and 3105. 

■ 2. The second sentence of paragraph 

(a)(2)(iii) of § 204.121 is revised to read 

as follows: 

§ 204.121 Bankers’ banks. 

(a) * * * 

(2) * * * 

(iii) * * * First, the range of 

customers with which the institution 

does business must be limited to 

depository institutions, including 

subsidiaries or organizations owned by 

depository institutions; directors, 

officers or employees of the same or 

other depository institutions; 

individuals whose accounts are 

acquired at the request of the 

institution’s supervisory authority due 

to the actual or impending failure of 

another depository institution; share 

insurance funds; depository institution 

trade associations; and such others as 

the Board may determine on a case-bycase basis consistent with the purposes 

of the Act and the bankers’ bank 

exemption. * * * 

* * * * * 

By order of the Board of Governors of the 

Federal Reserve System, April 3, 2007. 

Jennifer J. Johnson, 

Secretary of the Board. 

[FR Doc. E7–6473 Filed 4–5–07; 8:45 am] 

BILLING CODE 6210–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25105; Directorate 

Identifier 2006–CE–33–AD; Amendment 39–

15016; AD 2007–06–01 R1] 

RIN 2120–AA64 

Airworthiness Directives; Raytheon 

Aircraft Company Beech Models 45 

(YT–34), A45 (T–34A, B–45), and D45 

(T–34B) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: We are clarifying information 

contained in Airworthiness Directive 

(AD) 2007–06–01, which supersedes AD 

62–24–01 and applies to all Raytheon 

Aircraft Company (RAC) Beech Models 

45 (YT–34), A45 (T–34A, B45), and D45 

(T–34B) airplanes. AD 2007–06–01 

currently requires you to repetitively 

inspect, using the eddy current method, 

the front and rear horizontal stabilizer 

spars for cracks and replace any cracked 

stabilizer. We inadvertently left out the 

language in this AD that required 

replacement of any horizontal stabilizer 

spar found cracked prior to further flight 

although the procedures in the 

appendix made reference to corrective 

action. The replacement information 

was contained in the notice of proposed 

rulemaking (NPRM). This document 

adds this information already proposed 

back into the AD. We are issuing this 

AD to prevent failure of the front and/ 

or rear horizontal stabilizer spars caused 

by fatigue cracks. This failure could 

result in stabilizer separation and loss of 

control of the airplane. 

DATES: This AD becomes effective on 

April 16, 2007. 

ADDRESSES: To view the AD docket, go 

to the Docket Management Facility, U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2006–25105; Directorate Identifier 

2006–CE–33–AD. 

FOR FURTHER INFORMATION CONTACT: T.N. 

Baktha, Aerospace Engineer, FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Mid-Continent 

Airport, Wichita, Kansas 67209; 

telephone: (316) 946–4155; fax: (316) 

946–4107. 

SUPPLEMENTARY INFORMATION: 


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Discussion 

On March 5, 2007, we issued AD 

2007–06–01, Amendment 39–14982 (72 

FR 10909, March 12, 2007), to supersede 

AD 62–24–01. AD 2007–06–01 retained 

inspections of the front and rear 

horizontal stabilizer spars for cracks, but 

changed the inspection method from the 

dye penetrant method to the surface 

eddy current method. 

We inadvertently left out the language 

in AD 2007–06–01 that required 

replacement of any horizontal stabilizer 

spar found cracked prior to further flight 

although the procedures in the 

appendix made reference to corrective 

action. The replacement information 

was contained in the NPRM. 

Consequently, the FAA sees a need to 

clarify AD 2007–06–01 to assure that 

any cracked horizontal stabilizer spar is 

replaced prior to further flight. 

Correction of Publication 

This document clarifies AD 2007–06–

01 by incorporating the replacement 

language that was proposed in the 

NPRM and adds the amendment to 

section 39.13 of the Federal Aviation 

Regulations (14 CFR 39.13). 

Since this action only clarifies the 

intent of what was originally proposed 

in the NPRM, it has no adverse 

economic impact and imposes no 

additional burden on any person than 

was already proposed. Therefore, the 

FAA has determined that prior notice 

and opportunity for public comment are 

unnecessary. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

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 

removing Airworthiness Directive (AD) 

2007–06–01, Amendment 39–14982 (72 

FR 10909, March 12, 2007), and adding 

the following new AD: 

2007–06–01 R1 Raytheon Aircraft 

Company: Amendment 39–15016; 

Docket No. FAA–2006–25105; 

Directorate Identifier 2006–CE–33–AD. 

Effective Date 

(a) This AD becomes effective on April 16, 

2007. 

Affected ADs 

(b) This AD revises AD 2007–06–01, 

Amendment 39–14982, which superseded 

AD 62–24–01, Amendment 39–508. 

Applicability 

(c) This AD affects the following airplane 

models and serial numbers that are 

certificated in any category: 

Model Serial 

Nos. 

Beech 45 (YT–34) ........................... All. 

Beech A45 (T34A, B–45) ................ All. 

Beech D45 (T–34B) ........................ All. 

Unsafe Condition 

(d) This AD is intended to prevent failure 

of the front and/or rear horizontal stabilizer 

spars caused by fatigue cracks by changing 

the inspection method from dye penetrant to 

surface eddy current. This failure could 

result in stabilizer separation and loss of 

control of the airplane. 

Compliance 

(e) Using the surface eddy current 

inspection procedures outlined in the 

appendix of this AD, inspect the front and 

rear horizontal stabilizer spars between the 

butt rib and the inboard end for cracks, 

unless already done, as presented below. If 

any crack is found in either spar or the 

reinforcing doubler during any inspection 

required by this AD, prior to further flight, 

replace the stabilizer and continue to 

repetitively inspect at intervals not to exceed 

500 hours time-in-service (TIS). 

(1) If the last inspection of the front and 

rear horizontal stabilizer spars was done 

using the surface eddy current method (or 

FAA-approved equivalent method) to show 

compliance with AD 62–24–01 and/or to 

show compliance with the alternative method 

of compliance (AMOC) to AD 2004–25–51: 

Repetitively inspect thereafter at intervals not 

to exceed 500 hours TIS. 

(2) If the last inspection of the front and 

rear horizontal stabilizer spars required by 

AD 62–24–01 was done using the dye 

penetrant method: Inspect initially as 

presented in the table below and repetitively 

thereafter at intervals not to exceed 500 hours 

TIS: 

If Then 

(i) Less than 200 hours TIS have passed since 

the last inspection required by AD 62–24–01: 

Inspect at whichever of the following occurs later: 

(A) Upon accumulating 200 hours TIS since the last inspection required by AD 62–24–01; 

or 

(B) Within the next 6 months after April 16, 2007 (the effective date of this AD). 

(ii) 200 hours TIS or more have passed since 

the last inspection required by AD 62–24–01: 

Inspect at whichever of the following occurs first, unless paragraph (e)(2)(iii) of this AD applies, as specified below: 

(A) At the next repetitive inspection required by AD 62–24–01; or 

(B) Within the next 6 months after April 16, 2007 (the effective date of this AD). 

(iii) Paragraph (e)(2)(ii) results in the initial surface eddy current inspection becoming mandatory within 30 days after the effective date 

of this AD: 

Inspect within the next 30 days after April 16, 2007 (the effective date of this AD). 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office, FAA, ATTN: T.N. 

Baktha, Aerospace Engineer, 1801 Airport 

Road, Mid-Continent Airport, Wichita, 

Kansas 67209; telephone: (316) 946–4155; 

fax: (316) 946–4107, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

(g) AMOCs approved for AD 62–24–01 are 

approved for this AD. 

Appendix to AD 2007–06–01 R1— 

Surface Eddy Current Inspection 

Procedure 

Note: This surface eddy current inspection 

procedure is based on T–34 Spar Corporation 

TSC 3506, Rev C, dated May 10, 2005. The 

T–34 Spar Corporation is allowing the use of 

this procedure to be included in this 

Airworthiness Directive. Alternative methods 

of compliance procedures will be allowed, if 

approved by the Wichita Aircraft 

Certification Office and requested using the 

procedures found in 14 CFR 39.19. 

Purpose 

This procedure is to be used to detect 

cracks in the inner and outer spars of the 

front and rear spar assemblies of Raytheon 

Aircraft Company Beech Models 45 (YT–34), 

A45 (T–34A, B–45), and D45 (T–34B) 

airplane stabilizers outside of the steel 

bushings in the attach holes. 


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Area To Be Inspected 

To access the area of inspection, remove 

the stabilizer from the airplane. The areas to 

be inspected include the forward and aft 

surfaces of the inner and outer front and rear 

spars of the horizontal stabilizers in the areas 

surrounding each of the attach holes. 

Preparing the Area for Inspection 

Thoroughly clean area to be inspected with 

solvent (acetone or equivalent) as required 

until no signs of dirt, grime, or oil remain on 

the front and rear spars from the closeout 

former inboard on the forward and aft 

surfaces of the spars. 

Surfaces to be inspected should be smooth 

and corrosion-free. Any loss of thickness due 

to corrosion below material thickness 

tolerance is cause for rejection of the 

structure. An ultrasonic tester may be used 

to determine if material thickness has been 

compromised. 

Equipment Requirements 

Nortec Stavely 2000D Eddy Current Tester 

or equivalent. 

Probe: 50–500 KHz, shielded, absolute, 

0.071′′ diameter (0.090 max. diameter), right 

angle, pencil style, surface probe, 5′′ long, 

drop or equivalent. Use 0.025′ notch (beyond 

head) for calibration. 

Personal Requirements 

Technicians with Eddy Current, Level II or 

Level III per one of the following 

specifications: ATA specification 105, SNT–

TC–1A, or NAS–410 (MIL-std 410E). 

Methods 

Typical Set-up Parameters: 

Frequency ¥350 KHz, Gain Vertical ¥75 

dB, Horizontal ¥69 dB, Drive-Mid, Filters-Lo 

Pass-30, Hi Pass-0, Lift off-Horizontal to the 

left, adjust as required. The most reliable 

indication (minimum of 1⁄2 to 2 graticules) of 

the smallest observable flaw in the coupon 

(see the attached Figures) occurs from the 

notch extending 0.025′′ past the edge of the 

nominal fastener head (total notch length of 

0.100′′ from the edge of the nominal hole). 

Install appropriate aluminum guide pin into 

bushing such that the edge of the guide pin 

is flush with the edge of the bushing. Using 

the pin (see the attached Figures) as a guide, 

circle the area surrounding the steel bushing 

with the probe and adjacent area 

(approximately 1⁄4′′) to inspect for cracks. 

Inspect forward and aft surfaces surrounding 

bushings of each spar. 

Note: T–34 Spar Corporation, 2800 Airport 

Road, Hanger A, Ada, Oklahoma 74820 is a 

source for these coupons and pin. 

Accept/Reject Criteria 

Any repeatable flaw indication is cause for 

rejection in accordance with the procedure. 

In the event that any crack is detected, 

describe the flaw in detail providing sketch 

as needed and send the information to the 

Wichita ACO. 

Documentation Requirements 

Record inspection findings in the aircraft 

logbook. 


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16998 Federal Register / Vol. 72, No. 66 / Friday, April 6, 2007 / Rules and Regulations 

Issued in Kansas City, Missouri, on March 

30, 2007. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 07–1715 Filed 4–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27687; Directorate 

Identifier 2000–NE–42–AD; Amendment 39–

15012; AD 2007–07–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF34–1A, –3A, –3A1, 

–3A2, –3B, and –3B1 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

General Electric Company (GE) CF34–

1A, –3A, –3A1, –3A2, –3B, and –3B1 

turbofan engines. That AD requires a 

onetime inspection of certain fan disks 

for electrical arc-out indications, 

replacing fan disks with electrical arcout indications, and reducing the life 

limit of certain fan disks. This AD 

requires the same reduced life limit of 

certain fan disks, but requires on-wing 

inspection of certain fan disks installed 

on regional jets within 500 flight hours 

after the effective date of this AD. This 

AD also requires more enhanced shoplevel inspections of all fan disks for 

electrical arc-out defects. This AD 

results from a report that in January 

2007, a CF34–3B1 turbofan engine 

experienced an uncontained fan disk 

failure during flight operation. We are 

issuing this AD to prevent an 

uncontained fan disk failure and 

airplane damage. 

DATES: Effective April 23, 2007. The 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of April 23, 2007. 

We must receive any comments on 

this AD by June 5, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this 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–

0001. 

• Fax: (202) 493–2251. 

• 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. 

Contact General Electric Company via 

Lockheed Martin Technology Services, 

10525 Chester Road, Suite C, Cincinnati, 

Ohio 45215; telephone (513) 672–8400; 

fax (513) 672–8422, for the service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tara 

Chaidez, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: tara.chaidez@faa.gov; telephone 

(781) 238–7773; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: On 

February 24, 2006, the FAA issued AD 

2006–05–04, Amendment 39–14501 (71 

FR 10832; March 3, 2006). That AD 

requires a onetime inspection, and if 

necessary replacement of certain fan 

disks for electrical arc-out defects. That 

AD also reduces the life limit of certain 

fan disks. That AD was the result of a 

fan disk crack found during a visual 

inspection as part of routine engine 

maintenance. That condition, if not 

corrected, could result in an 

uncontained failure of the engine. 

Actions Since AD 2006–05–04 was 

Issued 

Since that AD was issued, a CF34–

3B1 turbofan engine experienced an 

uncontained fan disk failure during 

flight operation, in January 2007. An 

inspection of the recovered segments of 

the fan disk found an electrical arc-out 

defect at the fracture origin site. The fan 

disk was marked using the electrochemical etch marking (ECM) procedure 

during engine assembly. If the ECM 

procedure is performed incorrectly, an 

arc-out defect can occur. This arc-out 

defect, caused during part marking, 

resulted in the uncontained failure. 

The uncontained fan disk failure 

during flight operation in January 2007 

showed that the inspections in GE 

Service Bulletin No. CF34–BJ 72–

A0088, Revision 1, dated October 30, 

2000 and in GE Alert Service Bulletin 

(ASB) No. CF34–AL 72–A0103, dated 

August 4, 2000, mandated by AD 2006–

05–04, are not adequate to find all 

electrical arc-out defects. 

We issued emergency AD 2007–04–51 

on February 16, 2007, and its follow-up 

published version, AD 2007–05–16, on 

February 28, 2007, to perform an 

enhanced onetime inspection of a highrisk suspect population of 31 fan disks. 

While complying with those ADs, 

operators found indications of 

additional electrical arc-out defects. 

Because these additional indications 

of electrical arc-out defects validate our 

concern for the significant risk posed in 

the remaining suspect population of fan 

disks, we are issuing this final rule; 

request for comments AD. This AD 

requires an accelerated inspection 

schedule using the improved 

inspections of the three GE ASBs listed 

below. These ASBs include fluorescent 

penetrant inspection (FPI), tactile and 

enhanced visual (TEV) inspection, and 

eddy current inspection (ECI) for 

finding electrical arc-out defects. This 

condition, if not corrected, could result 

in an uncontained fan disk failure and 

airplane damage. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of GE ASBs No. 

CF34–BJ S/B 72–A0212, Revision 2, 

dated March 22, 2007, ASB No. CF34–

AL S/B 72–A0233, Revision 2, dated 

March 22, 2007, and ASB No. CF34–AL 

S/B 72–A0231, dated March 7, 2007. All 

three ASBs list the affected fan disks by 

serial number and part number. The 

first two ASBs describe procedures for 

performing FPI, a tactile and TEV 

inspection, and ECI for cracks and 

electrical arc-out defects. The third ASB 

describes procedures for performing an 

on-wing TEV inspection of fan disks for 

electrical arc-out defects. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other GE CF34–1A, –3A, –3A1, 

–3A2, –3B, and –3B1 turbofan engines 

of the same type design. We are issuing 

this AD to prevent an uncontained fan 

disk failure and airplane damage. This 

AD requires on-wing TEV inspection of 

fan disks for electrical arc-out defects on 

fan disks installed on regional jets 

within 500 flight hours after the 

effective date of this AD. This AD also 

requires for all affected fan disks shoplevel FPI, enhanced TEV, and ECI 

inspections for cracks and electrical arcout defects. This AD also carries 

forward from AD 2006–05–04 the 

reduced life limit for certain fan disks. 

You must use the service information 

described previously to perform the 

actions required by this AD. 


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