328 Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Rules and Regulations

been added to this final rule to clarify

this requirement. The FAA has

determined that this addition will

neither increase the economic burden

on any operator nor increase the scope

of the AD.–

The FAA has recently reviewed the

figures it has used over the past several

years in calculating the economic

impact of AD activity. In order to

account for various inflationary costs in

the airline industry, the FAA has

determined that it is necessary to

increase the labor rate used in these

calculations from $55 per work hour to

$60 per work hour. The economic

impact information, below, has been

revised to reflect this increase in the

specified hourly labor rate.

There are approximately 20 Lockheed

Model 382 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that it will will take

approximately 4 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

$4,800, or $240 per airplane.

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)

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:

94–26–15 Lockheed Aeronautical Systems

Company: Amendment 39–9110. Docket

94–NM–88–AD.–

Applicability: Model 382, 382B, 382E,

382F, and 382G series airplanes, as listed in

Hercules Service Bulletin 382–57–74 (82–

688), dated January 31, 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 (b) 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 structural failure of the outer

wing assembly, accomplish the following: –

(a) Within 30 days after the effective date

of this AD, or prior to the accumulation of

18,000 total flight hours, whichever occurs

later, perform an ultrasonic inspection to

determine the distance between the edge of

each of the six most outboard fasteners on

kingpin riser number 18 and the edge of the

riser, in accordance with Appendix A of

Hercules Service Bulletin 382–57–74 (82–

688), dated January 31, 1994.

(1) If all six of these fasteners are

positioned 0.31 inch or more from the

kingpin riser edge: No further action is

required by this AD.–

(2) If any of the six most outboard fasteners

is positioned less than 0.31 inch from the

edge of the kingpin riser: Prior to the

applicable threshold specified in Table 1 of

Hercules Service Bulletin 382–57–74 (82–

688), or prior to further flight if that

threshold has been exceeded as of the

effective date of this AD, perform an

ultrasonic inspection to detect cracks in the

kingpin riser, in accordance with Inspection

Procedure SP–265 (Appendix B) of the

service bulletin.

Note 2: For airplanes on which an outer

wing replacement is installed, the total flight

hours threshold is counted from the time of

outer wing replacement.

(i) If no crack is found, repeat this

inspection, thereafter, at intervals not to

exceed 7,400 flight hours.

(ii) If any cracked kingpin riser is found,

prior to further flight, repair in accordance

with a method approved by the Manager,

Atlanta Aircraft Certification Office (ACO),

FAA, Small Airplane Directorate. Repeat this

inspection, thereafter, at intervals not to

exceed 7,400 flight hours.–

(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, Atlanta

ACO, FAA, Small 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, Atlanta ACO.–

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.–

(c) 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. –

(d) The inspections shall be done in

accordance with Hercules Service Bulletin

382–57–74 (82–688), dated January 31, 1994

(includes Attachment 1, and Appendices A

and B). 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 Lockheed Aeronautical Systems

Support Company, Field Support

Department, Department 693, Zone 0755,

2251 Lake Park Drive, Smyrna, Georgia

30080. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

FAA, Small Airplane Directorate, Atlanta

Certification Office, Campus Building, 1701

Columbia Avenue, Suite 2–160, College Park,

Georgia; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.–

(e) This amendment becomes effective on

February 3, 1995.

Issued in Renton, Washington, on

December 21, 1994.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–48 Filed 1–3–95; 8:45 am]

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