Federal Register / Vol. 61, No. 114 / Wednesday, June 12, 1996 / Rules and Regulations 29641

records sought by a government

authority in connection with a lawful

proceeding, investigation, examination,

or inspection directed at the financial

institution in possession of such

records, or at an entity that is not a

customer as defined in § 219.2 of this

part.

(j) General Accounting Office

requests. Financial records sought by

the General Accounting Office pursuant

to an authorized proceeding,

investigation, examination, or audit

directed at a government authority.

(k) Federal Housing Finance Board

requests. Financial records or

information sought by the Federal

Housing Finance Board (FHFB) or any

of the Federal home loan banks in the

exercise of the FHFB’s authority to

extend credit to financial institutions or

others.

(l) Department of Veterans Affairs.

The disclosure of the name and address

of any customer to the Department of

Veterans Affairs where such disclosure

is necessary to, and used solely for, the

proper administration of benefits

programs under laws administered by

that Department.

§ 219.5 Conditions for payment.

(a) Direct costs. Payment shall be

made only for costs that are both

directly incurred and reasonably

necessary to provide requested material.

Search and processing, reproduction,

and transportation costs shall be

considered separately when

determining whether the costs are

reasonably necessary.

(b) Compliance with legal process,

request, or authorization. No payment

may be made to a financial institution

until it satisfactorily complies with the

legal process, the formal written request,

or the customer authorization. When the

legal process or formal written request

is withdrawn, or the customer

authorization is revoked, or where the

customer successfully challenges

disclosure to a grand jury or government

authority, the financial institution shall

be reimbursed for the reasonably

necessary costs incurred in assembling

the requested financial records prior to

the time the financial institution is

notified of such event.

(c) Itemized bill or invoice. No

reimbursement is required unless a

financial institution submits an

itemized bill or invoice specifically

detailing its search and processing,

reproduction, and transportation costs.

Search and processing time should be

billed in 15-minute increments.

§ 219.6 Payment procedures.

(a) Notice to submit invoice. Promptly

following a service of legal process or

request, the court or government

authority shall notify the financial

institution that it must submit an

itemized bill or invoice in order to

obtain payment and shall furnish an

address for this purpose.

(b) Special notice. If a grand jury or

government authority withdraws the

legal process or formal written request,

or if the customer revokes the

authorization, or if the legal process or

request has been successfully

challenged by the customer, the grand

jury or government authority shall

promptly notify the financial institution

of these facts, and shall also notify the

financial institution that it must submit

an itemized bill or invoice in order to

obtain payment of costs incurred prior

to the time of the notice to the financial

institution receives this notice.

§ 219.7 [Removed]

3. Section 219.7 is removed.

By order of the Board of Governors of the

Federal Reserve System, June 5, 1996.

William W. Wiles,

Secretary of the Board.

[FR Doc. 96–14688 Filed 6–11–96; 8:45 am]

BILLING CODE 6210–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–ANE–30; Amendment 39–

9646; AD 96–12–04]

RIN 2120–AA64

Airworthiness Directives; Superior Air

Parts, Inc. Pistons Installed on

Teledyne Continental Motors O–470

Series Reciprocating Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Superior Air Parts,

Inc. Parts Manufacturer Approval (PMA)

pistons installed on Teledyne

Continental Motors O–470 series

reciprocating engines, that requires

removal from service of certain pistons.

This amendment is prompted by piston

failures. The actions specified by this

AD are intended to prevent piston

failure, which can result in engine

power loss, engine failure and loss of

the aircraft.

DATES: Effective August 12, 1996.

FOR FURTHER INFORMATION CONTACT:

Richard Karanian, Aerospace Engineer,

Special Certification Office, FAA,

Rotorcraft Directorate, 2601 Meacham

Blvd., Fort Worth, TX 76137–4298;

telephone (817) 222–5195, fax (817)

222–5959.

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 Superior Air Parts,

Inc. Parts Manufacturer Approval (PMA)

pistons installed on Teledyne

Continental Motors O–470 series

reciprocating engines was published in

the Federal Register on February 22,

1995 (60 FR 9800). That action proposed

to require removal from service of

Superior Air Parts, Inc. pistons, Part

Number (P/N) SA626992, at the next

access to the piston, top overhaul, or

major overhaul. The affected pistons can

be identified by either a stamped-in P/

N on the piston dome (SA626992 or

SA626992P15) or, by a raised casting

number (SA632932) along one of the

piston pin bosses on the underside of

the piston.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The manufacturer has informed the

FAA that 5,585 pistons were shipped

between December 1976 and June 1981

and will be affected by this AD. The

FAA estimates that it will take

approximately 2 work hours per piston

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Required parts will cost

approximately $156 per piston. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $1,541,460.

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
29642 Federal Register / Vol. 61, No. 114 / Wednesday, June 12, 1996 / Rules and Regulations

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, 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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–12–04 Superior Air Parts, Inc.:

Amendment 39–9646. Docket 94–ANE–

30.

Applicability: Superior Air Parts, Inc. Parts

Manufacturer Approval (PMA) pistons, Part

Numbers (P/N’s) SA626992 and

SA626992P15, installed on Teledyne

Continental Motors Model O–470–K, –L, –R

reciprocating engines. These engines are

installed on but not limited to Cessna 182

series aircraft.

Note: This airworthiness directive (AD)

applies to each piston 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 pistons 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 Federal Aviation

Administration (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 piston from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent piston failure, which can result

in engine power loss, engine failure and loss

of the aircraft, accomplish the following:

(a) At the next access to the piston, top

overhaul, or major overhaul after the effective

date of this AD, whichever occurs first,

remove pistons, P/N SA626992, from service

and replace with a serviceable part.

Note: The affected pistons can be identified

by either a stamped-in P/N on the piston

dome (SA626992 or SA626992P15) or, by a

raised casting number (SA632932) along one

of the piston pin bosses on the underside of

the piston.

(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, Fort Worth

Special Certification Office. The request

should be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Fort Worth Special Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Fort Worth

Special Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(d) This amendment becomes effective on

August 12, 1996.

Issued in Burlington, Massachusetts, on

May 29, 1996.

Robert E. Guyotte,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 96–14870 Filed 6–11–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–104–AD; Amendment

39–9667; AD 96–12–24]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to all Lockheed Model L–

1011–385 series airplanes. This action

requires inspections to detect cracking

and other discrepancies of certain webto-cap fasteners of the rear spar between

inner wing stations (IWS) 310 and 343,

and of the web area around those

fasteners; and various follow-on actions.

This AD also provides for an optional

modification which, if accomplished,

will defer the initiation of the

inspections for a certain period of time.

This amendment is prompted by a

report of fatigue cracking in the web of

the rear spar of the wing. The actions

specified in this AD are intended to

prevent such fatigue cracking, which

could result in failure of the rear spar of

the wing and consequent fuel spillage.

DATES: Effective June 27, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 27,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

August 12, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

104–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Lockheed

Aeronautical Systems Support

Company, Field Support Department,

Dept. 693, Zone 0755, 2251 Lake Park

Drive, Smyrna, Georgia 30080. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Atlanta

Aircraft Certification Office, Small

Airplane Directorate, 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.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Branch, ACE–116A, FAA, Atlanta

Aircraft Certification Office, Small

Airplane Directorate, Campus Building,

1701 Columbia Avenue, Suite 2–160,

College Park, Georgia 30337–2748;

telephone (404) 305–7367; fax (404)

305–7348.

SUPPLEMENTARY INFORMATION: The FAA

received a report indicating that fatigue

cracking was found on the web of the

rear spar of the wing on a Lockheed

Model L–1011–385 series airplane that

had accumulated approximately 18,900

total landings. The crack, which was 24

inches long, grew rapidly in a

downward direction at a 45-degree

angle and stopped behind the trunnion

fitting of the main landing gear.

Consequently, the airplane began

leaking fuel during final taxi.

Fatigue cracking in the web of the rear

spar of the wing can originate in the

fasteners common to the web and the

vertical leg of the upper cap. Such

cracking can grow and remain

undetected for a significant period of