Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations 16473

(d) Other Federal Regional

Commissions are those authorized

under Title V of the Public Works and

Economic Development Act of 1965.

Grants by these commissions are

handled in accordance with a separate

Project Management Agreement

between the respective Regional

Commission and RHS for each

Commission grant administered by RHS

(guide 1 of part 1942, subpart G). The

agreement should be prepared by the

RHS State Director and the appropriate

Commission official when the State

Director receives a notice from the

Commission of the amount of the grant

to be made.

(e) When the Agency has funds in the

project, no charge will be made for

administering grant funds.

(f) When RHS has no loan or grant

funds in the project, an administrative

charge will be made pursuant to the

Economy Act of 1932, as amended (31

U.S.C. 1535). A fee of 5 percent of the

first $50,000 and 1 percent of any

amount over $50,000 will be paid RHS

by the commission.

§§ 3570.94–3570.99 [Reserved]

§ 3570.100 OMB control number.

According to the Paperwork

Reduction Act of 1995, no persons are

required to respond to a collection of

information unless it displays a valid

OMB control number. The valid OMB

control number for this information

collection is 0575–0173.

Dated: March 28, 1997.

Inga Smulkstys,

Deputy Under Secretary, Operations and

Management, Rural Development.

Dated: March 28, 1997.

Dallas R. Smith,

Acting Under Secretary, Farm and Foreign

Agricultural Service.

[FR Doc. 97–8743 Filed 4–4–97; 8:45 am]

BILLING CODE 3410–XV–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–105–AD; Amendment

39–9988; AD 97–07–14]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320 series airplanes, that requires

modification of an area on the front spar

of the wing center section by installing

shims and new fasteners to reinforce

pressure floor fittings. This amendment

is prompted by a report from the

manufacturer indicating that full-scale

fatigue testing on the test model

revealed fatigue cracking in this area.

The actions specified by this AD are

intended to prevent fatigue cracking in

this area, which can reduce the

structural integrity of fuselage frame 36

and the wing center section.

DATES: Effective May 12, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 12,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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 Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Tim Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

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 Airbus

Model A320 series airplanes was

published in the Federal Register on

January 21, 1997 (62 FR 2982). That

action proposed to require modification

of an area on the front spar of the wing

center section by installing shims and

new fasteners to reinforce pressure floor

fittings.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

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.

Cost Impact

The FAA estimates that 5 Airbus

Model A320 series airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 13 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$576 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $6,780,

or $1,356 per airplane.

The 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.

Regulatory Impact

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)

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:
16474 Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations

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

adding the following new airworthiness

directive:

97–07–14 Airbus Industrie: Amendment

39–9988. Docket 96–NM–105–AD.

Applicability: Model A320 series airplanes

as listed in Airbus Service Bulletin A320–57–

1013, Revision 1, dated September 29, 1992;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 request approval for an

alternative method of compliance in

accordance with paragraph (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking in the rib

flange of the front spar side of the wing

center section, and consequent reduced

structural integrity of fuselage frame 36 and

the wing center section, accomplish the

following:

(a) Prior to the accumulation of 16,000 total

landings, or within 3 months after the

effective date of this AD, whichever occurs

later, modify the rib flange on the front spar

of the wing center section by installing shims

and new fasteners to reinforce pressure floor

fittings, in accordance with Airbus Service

Bulletin A320–57–1013, Revision 1, dated

September 29, 1992.

Note 2: Modification of the rib flange

accomplished prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A320–57–1013, dated April 12,

1989, is considered acceptable for

compliance with the modification required

by this AD.

(b) 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,

standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(c) Special flight permits may be issued in

accordance with §§ 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.

(d) The modification shall be done in

accordance with Airbus Service Bulletin

A320–57–1013, Revision 1, dated September

29, 1992, which contains the following list of

effective pages:

Page No. Revision level shown on page Date shown on page

1–3 ........................................................................................ 1 ............................................................................................ September 29, 1992.

4–11 ...................................................................................... Original ................................................................................. April 12, 1989.

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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

May 12, 1997.

Issued in Renton, Washington, on March

27, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8422 Filed 4–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–127–AD; Amendment

39–9987; AD 97–07–13]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model CN–235 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain CASA Model CN–

235 series airplanes, that requires

replacement of the center wing

attachment rods with new rods. This

amendment is prompted by a report

from the manufacturer indicating that

these rods failed during a full-scale

fatigue test. The actions specified by

this AD are intended to prevent fatigue

failure of these rods, which

consequently could reduce the

structural integrity of the wing-tofuselage attachment.

DATES: Effective May 12, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 12,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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 Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Greg

Dunn, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2799; fax (206) 227–1149.

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 CASA

Model CN–235 series airplanes was

published in the Federal Register on

January 27, 1997 (62 FR 3834). That

action proposed to require replacement

of the center wing attachment rods with

new rods.