Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 68767

(3) The issuance of the order 

amending the Northeast and other 

orders is favored by at least two-thirds 

of the producers who were engaged in 

the production of milk for sale in the 

marketing area. 

Specifically, this final rule 

permanently adopts classification of 

milk use provisions that reclassify milk 

used to produce evaporated or 

sweetened condensed milk products in 

consumer type-packages from Class III 

to Class IV.

List of Subjects in 7 CFR Parts 1000, 

1001, 1005, 1006, 1007, 1030, 1032, 

1033, 1124, 1126, and 1131

Milk marketing orders.

Order Relative to Handling

■ It is therefore ordered, that on and after 

the effective date hereof, the handling of 

milk in the Northeast and other 

marketing areas shall be in conformity to 

and in compliance with the terms and 

conditions of the orders, as amended, 

and as hereby further amended, as 

follows:

■ Parts 1000, 1001, 1005, 1006, 1007, 

1030, 1032, 1033, 1124, 1126, and 

1131—General Provisions and Milk in 

the Northeast and other Milk Marketing 

Areas.

■ The interim final rule amending 7 CFR 

parts 1000, 1001, 1005, 1006, 1007, 1030, 

1032, 1033, 1124, 1126, and 1131 which 

was published at 69 FR 21950 on April 

23, 2004, is adopted as a final rule 

without change.

Dated: November 19, 2004. 

A.J. Yates, 

Administrator, Agricultural Marketing 

Serivce.

[FR Doc. 04–26123 Filed 11–24–04; 8:45 am] 

BILLING CODE 3410–02–U

FARM CREDIT ADMINISTRATION

12 CFR Parts 613, 614, and 618

RIN 3052–AC06

Eligibility and Scope of Financing; 

Loan Policies and Operations; General 

Provisions; Credit and Related 

Services; Effective Date

AGENCY: Farm Credit Administration.

ACTION: Notice of effective date.

SUMMARY: The Farm Credit 

Administration (FCA) published a final 

rule under parts 613, 614, and 618 on 

July 21, 2004 (69 FR 43511). This final 

rule amends regulations governing 

domestic and international lending, 

certain intra-Farm Credit System 

consent requirements concerning 

similar entity participation transactions, 

provisions of general financing 

agreements, and related services. In 

accordance with 12 U.S.C. 2252, the 

effective date of the final rule is 30 days 

from the date of publication in the 

Federal Register during which either or 

both Houses of Congress are in session. 

Based on the records of the sessions of 

Congress, the effective date of the 

regulations is November 19, 2004.

DATES: The regulation amending 12 CFR 

parts 613, 614, and 618 published on 

July 21, 2004 (69 FR 43511), is effective 

November 19, 2004.

FOR FURTHER INFORMATION CONTACT: Dale 

Aultman, Policy Analyst, Office of 

Policy and Analysis, Farm Credit 

Administration, McLean, VA 22102–

5090, (703) 883–4498, TTY (703) 883–

4434; or James Morris, Senior Counsel, 

Office of General Counsel, Farm Credit 

Administration, McLean, VA 22102–

5090, (703) 883–4020, TTY (703) 883–

2020.

(12 U.S.C. 2252(a)(9) and (10))

Dated: November 19, 2004. 

Jeanette C. Brinkley, 

Secretary, Farm Credit Administration Board.

[FR Doc. 04–26131 Filed 11–24–04; 8:45 am] 

BILLING CODE 6705–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NE–61–AD; Amendment 

39–13879 AD 2004–24–03] 

RIN 2120–AA64

Airworthiness Directives; Hamilton 

Sundstrand Power Systems T–62T 

Series Auxiliary Power Units (APUs)

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Hamilton Sundstrand Power Systems 

Models T–62T–46C12 and T–62T–

40C14 (APS 500R) APUs with fuel filter 

housing assembly, part number (P/N) 

4951627, 4951960, or 4952039, 

installed. This AD requires installation 

of a bracket to prevent a failed bypass 

button from protruding beyond the 

internal o-ring seal. This AD results 

from reports of leaks caused by cracked 

bypass buttons that protruded beyond 

the o-ring seal. We are issuing this AD 

to prevent a fire or explosion caused by 

a fuel leak from a failed bypass button 

on the fuel filter housing.

DATES: This AD becomes effective 

January 3, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of January 3, 2005.

ADDRESSES: You can get the service 

information identified in this AD from 

Hamilton Sundstrand Technical 

Publications Department, P.O. Box 

7002, Rockford, IL 61125–7002, U.S.A. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA; or at 

the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT:

Roger Pesuit, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; telephone (562) 627–5251, 

fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed airworthiness directive (AD). 

The proposed AD applies to Hamilton 

Sundstrand Power Systems Models T–

62T–46C12 and T–62T–40C14 (APS 

500R) APUs with fuel filter housing 

assembly, P/N 4951627, 4951960, or 

4952039 installed. We published the 

proposed AD in the Federal Register on 

May 7, 2004 (69 FR 25525). That action 

proposed to require installation of a 

bracket to prevent a failed bypass button 

from protruding beyond the internal oring seal. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request To Add Alert Service Bulletin 

Reference 

Two commenters request that for 

APUs Model T–62T–40C14 (APS 500R),

68768 Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 

we add EMBRAER Alert Service 

Bulletin (ASB) No. 145–49–A027, dated 

January 6, 2004, as another means of 

complying with the AD. We do not 

agree. That ASB does not contain 

instructions for installing the bracket, 

but only instructs the operator to use 

Hamilton Sundstrand ASB No. ASB–

4504112–49–22, for installing the 

bracket. Because of this, we have not 

incorporated by reference that ASB. 

Request To Reference the Latest ASB 

Revision 

One commenter requests that we 

reference the latest revision of Hamilton 

Sundstrand ASB No. ASB–4504112–49–

22, which is Revision 1, dated January 

5, 2004. The commenter states that the 

original ASB specified a gap dimension 

of 0.32 inch-to-0.65 inch, which is 

incorrect and unachievable. ASB 

Revision 1 corrects the gap dimension to 

the proper value of 0.50 inch, plus or 

minus 0.015 inch. Also, ASB Revision 1 

increases the recommended compliance 

threshold from within 400 hours timein-service (TIS) to within 500 hours TIS. 

We agree that the latest ASB Revision 

should be referenced, which is Revision 

2, dated October 4, 2004. The 500 hours 

TIS threshold is consistent with 

EMBRAER ASB No. 145–49–A027, 

dated January 6, 2004. ASB Revision 2 

requires, as does this AD, that brackets 

installed using Hamilton Sundstrand 

ASB No. ASB–4504112–49–22, Original 

issue, be inspected one time for proper 

gap and adjusted if necessary. ASB 

Revision 2 also introduces as an 

alternative, the installation of a different 

part number fuel filter assembly for 

APU Model T–62–T–40C14, that is 

designed to prevent bypass button 

failure. We have added that alternative 

as optional terminating action for APU 

Model T–62–T–40C14. 

We are allowing previous credit for 

brackets installed using Hamilton 

Sundstrand ASB No. ASB–4504112–49–

22, Original, dated December 2, 2003, or 

Revision 1, dated January 5, 2004, 

before the effective date of this AD. We 

have incorporated the changes 

described previously in this AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

There are about 552 Hamilton 

Sundstrand APUs of the affected design 

in the worldwide fleet. We estimate that 

448 APUs installed on airplanes of U.S. 

registry will be affected by this AD. We 

also estimate that it would take about 1 

work hour per APU to perform the 

actions, and that the average labor rate 

is $65 per work hour. Required parts 

will cost about $517 per APU. The 

manufacturer indicated that they might 

provide the parts at no cost. Based on 

these figures, we estimate the total cost 

of the AD to U.S. operators to be 

$260,736. 

Regulatory Findings 

We have determined that 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); 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES.

Include ‘‘AD Docket No. 2003–NE–61–

AD’’ in your request.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 14 CFR part 39 as follows:

PART 39—AIRWORTHINESS 

DIRECTIVES

■ 1. The authority citation for part 39 

continues to read as follows:

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

§ 39.13 [Amended]

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

2004–24–03 Hamilton Sundstrand Power 

Systems: Amendment 39–13879. Docket 

No. 2003–NE–61–AD. 

Effective Date 

(a) This AD becomes effective January 3, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Hamilton 

Sundstrand Power Systems Models T–62T–

46C12 and T–62T–40C14 (APS 500R) 

auxiliary power units (APUs) with fuel filter 

housing assemblies, part numbers (P/Ns) 

4951627, 4951960, or 4952039, installed. 

These APUs are installed on, but not limited 

to, Bombardier DHC–8–400 airplanes and 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER) EMB–135 and –145 series 

airplanes. 

Unsafe Condition 

(d) This AD results from reports of leaks 

caused by cracked bypass buttons that 

protruded beyond the o-ring seal. We are 

issuing this AD to prevent a fire or explosion 

caused by a fuel leak from a failed bypass 

button on the fuel filter. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

500 hours time-in-service or 6 months after 

the effective date of this AD, whichever 

occurs earlier, unless the actions have 

already been done. 

Installation of Bracket on APU Model T–

62T–46C12

(f) Install a bracket onto the fuel filter 

housing assembly on APU Model T–62T–

46C12. Use 2.A through 2.D of the 

Accomplishment Instructions of Hamilton 

Sundstrand Alert Service Bulletin (ASB) No. 

ASB–4503067–49–9, dated December 2, 

2003, to install the bracket. 

Installation of Bracket on APU Model T–

62T–40C14 (APS 500R) 

(g) Install a bracket onto the fuel filter 

housing assembly on APU Model T–62T–

40C14 (APS 500R). Use 2.B. and 2.D.(1) of the 

Accomplishment Instructions of Hamilton 

Sundstrand ASB No. ASB–4504112–49–22, 

Revision 2, dated October 4, 2004, to install 

the bracket. 

Previous Credit 

(h) Previous credit is allowed for brackets 

installed using Hamilton Sundstrand ASB 

No. ASB–4503067–49–9, dated December 2, 

2003, Hamilton Sundstrand ASB No. ASB–

4504112–49–22, Original, dated December 2, 

2003, or Revision 1, dated January 5, 2004, 

before the effective date of this AD. 

One-Time Inspection for Proper Gap 

(i) For brackets previously installed using 

Hamilton Sundstrand ASB No. ASB–

4504112–49–22, Original, dated December 2, 

2003, perform a one-time inspection for 

proper gap and if necessary, adjust the gap 

between the bracket and bypass button. Use 

2.B. and 2.D.(1) of the Accomplishment

Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 68769

Instructions of Hamilton Sundstrand ASB 

No. ASB–4504112–49–22, Revision 2, dated 

October 4, 2004 to inspect and adjust the gap. 

Optional Terminating Action for APU Model 

T–62T–40C14 (APS 500R) 

(j) For APU Model T–62T–40C14 (APS 

500R), installation of a part number fuel filter 

assembly that is not listed in this AD 

constitutes optional terminating action to the 

requirements of this AD. 

Alternative Methods of Compliance 

(k) The Manager, Los Angeles Aircraft 

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. 

Material Incorporated by Reference 

(l) You must use the Alert Service Bulletins 

listed in Table 1 of this AD to perform the 

bracket installations required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of the documents 

listed in Table 1 of this AD in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. You 

can get a copy from Hamilton Sundstrand 

Technical Publications Department, P.O. Box 

7002, Rockford, IL 61125–7002, U.S.A. You 

can review copies at the FAA, New England 

Region, Office of the Regional Counsel, 12 

New England Executive Park, Burlington, 

MA; or at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html. Table 1 follows:

TABLE 1.—INCORPORATION BY REFERENCE

Alert service bulletin No. Page number(s) shown on the 

page 

Revision level 

shown on the 

page 

Date shown on the 

page 

Hamilton Sundstrand ASB–4503067–49–9 ........................................ All ................................................. Original ......... December 2, 2003.

Hamilton Sundstrand ASB–4504112–49–22 ...................................... All ................................................. 2 ................... October 4, 2004. 

Related Information 

(m) None.

Issued in Burlington, Massachusetts, on 

November 15, 2004. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25792 Filed 11–24–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NE–23–AD; Amendment 

39–13880; AD 2004–24–04] 

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce 

Corporation (Formerly Allison Engine 

Company, Allison Gas Turbine 

Division, and Detroit Diesel Allison) 

(RRC) Models 250–C30R/3, –C30R/3M, 

–C47B, and –C47M Turboshaft Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

RRC models 250–C30R/3, –C30R/3M, 

–C47B, and –C47M turboshaft engines. 

That AD currently requires initial and 

repetitive electrical signal inspections of 

the hydromechanical unit (HMU) Power 

Lever Angle (PLA) potentiometer. This 

ad continues to require those 

inspections and adds replacement of the 

existing HMU with a new design HMU 

as a mandatory terminating action to the 

repetitive inspection requirements. This 

AD results from the manufacturer 

releasing a redesigned HMU that has a 

dual-element potentiometer. We are 

issuing this AD to prevent 

uncommanded and sudden changes in 

engine power.

DATES: This AD becomes effective 

January 3, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of January 3, 2005.

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce Corporation, P.O. Box 420, 

Indianapolis, IN 46206–0420; telephone 

(317) 230–6400; fax (317) 230–4243. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA; or at 

the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, 

or go to: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT:

Khailaa Hosny, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, 2300 East Devon Avenue, Des 

Plaines, IL 60018–4696; telephone (847) 

294–7134; fax (847) 294–7834.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to RRC models 250–C30R/3, 

–C30R/3M, –C47B, and –C47M 

turboshaft engines. We published the 

proposed AD in the Federal Register on 

June 9, 2004 (69 FR 32287). That action 

proposed to require initial and 

repetitive electrical signal inspections of 

the HMU PLA potentiometer and 

replacement of the existing HMU with 

a new design HMU as a mandatory 

terminating action to the repetitive 

inspection requirements. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See 

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the proposal or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

We estimate that 700 engines installed 

on helicopters of U.S. registry will be 

affected by this AD. We estimate that it 

will take about 4 work hours per engine 

to replace a single-element HMU with a 

dual-element HMU. We also estimate 

that 12 percent of the single-element 

HMUs will fail the required inspection 

and require replacing the HMU. The 

average labor rate is $65 per work hour. 

Required parts cost about $615 per 

engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $686,000.