28524 Federal Register / Vol. 60, No. 105 / Thursday, June 1, 1995 / Rules and Regulations

equal to 85 percent of the comparable

percentage of parity at which shorn

wool is supported for the 1995

marketing year.

List of Subjects in 7 CFR Part 1468

Assistance grant programs—

agriculture, Livestock, Mohair,

Reporting and recordkeeping

requirements, Wool.

Accordingly, 7 CFR part 1468 is

amended as follows:

PART 1468—WOOL AND MOHAIR

1. The authority citation for 7 CFR

part 1468 continues to read as follows:

Authority: 7 U.S.C. 1781–1787; 15 U.S.C.

714b and 714c.

2. Section 1468.4 is amended by

adding paragraphs (b)(1)(ii)(E), (b)(2)(v),

and (b)(3)(v) to read as follows:

§ 1468.4 Eligibility for payments.

* * * * *

(b)(1) * * *

(ii) * * *

(E) 1995—$2.12 per pound.

(2) * * *

(v) 1995—an amount equal to 80

percent of the difference between the

national average price received by

producers for shorn wool for the 1995

marketing year and the 1995 shorn wool

support price, multiplied by 5.

(3) * * *

(v) 1995—$4.657 per pound.

* * * * *

Signed at Washington, DC, on May 24,

1995.

Bruce R. Weber,

Acting Executive Vice President, Commodity

Credit Corporation.

[FR Doc. 95–13383 Filed 5–31–95; 8:45 am]

BILLING CODE 3410–05–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–NM–176–AD; Amendment

39–9244; AD 95–11–11]

Airworthiness Directives; McDonnell

Douglas Model DC–10–10, –15, –30,

–40, and KC–10 (Military) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas DC–10 and KC–10 series

airplanes, that requires repetitive eddy

current inspections to detect fatigue

cracking of the pylon aft bulkhead

flange, upper pylon box web, fitting

radius, and adjacent tangent areas; and

repair, if necessary. This amendment is

prompted by fatigue cracking found in

the wing pylon aft bulkheads on two

airplanes. The actions specified by this

AD are intended to prevent failure of the

wing pylon aft bulkhead due to fatigue

cracking, which could lead to separation

of the engine and pylon from the

airplane.

DATES: Effective July 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 3, 1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from McDonnell Douglas Corporation,

3855 Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). This information

may be examined at the Federal

Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office,

Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Maureen Moreland, Aerospace

Engineer, Airframe Branch, ANM–120L,

Los Angeles Aircraft Certification

Office, FAA, Transport Airplane

Directorate, 3960 Paramount Boulevard,

Lakewood, California 90712; telephone

(310) 627–5238; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain McDonnell

Douglas DC–10 and KC–10 series

airplanes was published in the Federal

Register on January 18, 1995 (60 FR

3590). That action proposed to require

repetitive eddy current inspections to

detect fatigue cracking of the pylon aft

bulkhead flange, upper pylon box web,

fitting radius, and adjacent tangent

areas; and repair, if necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter supports the

proposal.

Another commenter expresses

concern that enough spare parts may not

be available to affected operators to

comply with the proposed rule. This

commenter requests that the FAA

require the McDonnell Douglas

Corporation to stock enough spare aft

bulkheads and attachment hardware

prior to release of the final rule in order

to accommodate operators that may

need to replace cracked parts. The FAA

does not concur with this request. The

FAA has received no indication that a

problem exists with regard to the

availability of parts associated with the

requirements of this AD action. This AD

mandates inspections to detect cracks in

various items, and repair of any items

that are found to be cracked. Such repair

would be required in order to keep the

airplane airworthy, regardless of

whether or not this AD is issued. If the

availability of repair parts should

become a problem, paragraph (d) of this

final rule provides operators with the

opportunity to request use of an

alternative method of compliance with

the AD until parts can be located.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

There are approximately 436 Model

DC–10 and KC–10 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 269 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 8 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $129,120, or $480 per airplane, per

inspection cycle.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

The regulations adopted herein will

not have substantial direct effects 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. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (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)
Federal Register / Vol. 60, No. 105 / Thursday, June 1, 1995 / Rules and Regulations 28525

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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–11–11 McDonnell Douglas: Amendment

39–9244. Docket 94–NM–176–AD.

Applicability: Model DC–10–10, –15, –30,

–40, and KC–10 (military) series airplanes; as

listed in McDonnell Douglas Alert Service

Bulletin A54–106, Revision 2, dated

November 3, 1994; certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (d) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the wing pylon aft

bulkhead due to fatigue cracking, which

could lead to separation of the engine and

pylon from the airplane, accomplish the

following:

(a) Prior to the accumulation of 1,800

landings after the effective date of this AD,

conduct an eddy current inspection to detect

fatigue cracks in the pylon aft bulkhead

flange, upper pylon box web, fitting radius,

and adjacent tangent areas, in accordance

with McDonnell Douglas Alert Service

Bulletin A54–106, Revision 2, dated

November 3, 1994. Repeat this inspection

thereafter at intervals not to exceed 1,800

landings.

(b) If any crack(s) is found during any

inspection required by paragraph (a) of this

AD, prior to further flight, repair in

accordance with a method approved by the

Manager, Los Angeles Aircraft Certification

Office (ACO), FAA, Transport Airplane

Directorate.

(c) Accomplishment of the gap inspection

and necessary shimming in accordance with

‘‘Phase III,’’ as specified in McDonnell

Douglas Alert Service Bulletin A54–106,

Revision 2, dated November 3, 1994,

constitutes terminating action for the

inspections required by paragraph (a) of this

AD.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles ACO, FAA, Transport Airplane

Directorate. Operators shall submit their

requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(f) The inspection shall be done in

accordance with McDonnell Douglas Alert

Service Bulletin A54–106, Revision 2, dated

November 3, 1994. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from McDonnell Douglas

Corporation, 3855 Lakewood Boulevard,

Long Beach, California 90846, Attention:

Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office,

Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

July 3, 1995.

Issued in Renton, Washington, on May 19,

1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–12826 Filed 5–31–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–194–AD; Amendment

39–9245; AD 95–11–12]

Airworthiness Directives; McDonnell

Douglas Model DC–9, DC–9–80, and C–

9 (Military) Series Airplanes, and Model

MD–88 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–9, DC–9–80, and C–

9 (military) series airplanes, and Model

MD–88 airplanes, that requires

repetitive replacement of the emergency

power switch in the overhead switch

panel with a new switch. This

amendment is prompted by a report of

heavy smoke in the cockpit coming from

the overhead switch panel on a Model

DC–9–81 series airplane. The actions

specified by this AD are intended to

ensure replacement of the emergency

power switch when it has reached its

maximum life limit; an emergency

power switch that is not replaced could

fail and lead to a short in the electrical

circuit, which could result in a fire in

the overhead switch panel and smoke in

the cockpit.

DATES: Effective July 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 3, 1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from McDonnell Douglas Corporation,

3855 Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Department C1–L51 (2–60). This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office,

Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Elvin Wheeler, Aerospace Engineer,