67550 Federal Register / Vol. 62, No. 248 / Monday, December 29, 1997 / Rules and Regulations

PART 725—NATIONAL CREDIT UNION

ADMINISTRATION CENTRAL

LIQUIDITY FACILITY

1. The authority citation for part 725

continues to read as follows:

Authority: Secs. 301–307 Federal Credit

Union Act, 92 Stat. 3719–3722 (12 U.S.C.

1795–1795f).

2. Section 725.19 is revised to read as

follows:

§ 725.19 Collateral requirements.

(a) Each Facility advance and each

Agent loan shall be secured by a first

priority security interest in collateral of

the credit union with a net book value

at least equal to 110% of all amounts

due under the applicable Facility

advance or Agent loan, or by guarantee

of the National Credit Union Share

Insurance Fund.

(b) The Facility may accept as

collateral for each Facility advance to a

Regular member, a security interest in

all assets of the Regular member;

provided however, that the value of any

assets in which any third party has a

perfected security interest that is

superior to the security interest of the

Facility shall be excluded for purposes

of complying with the requirements of

paragraph (a) of this section.

(c) The Facility may accept as

collateral for each Facility advance to an

Agent member, a security interest in the

Agent loans for which the Facility

advance was made; provided however,

that the collateral for such Agent loan

meets the requirements of paragraph (a)

of this section.

[FR Doc. 97–33750 Filed 12–24–97; 8:45 am]

BILLING CODE 7535–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–294–AD; Amendment

39–10264; AD 97–26–21]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100, 747–200, 747–300,

747SR, and 747SP 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 certain Boeing Model 747–

100, 747–200, 747–300, 747SR, and

747SP series airplanes. This action

requires a one-time inspection to detect

cracking of the longeron splice fittings

at stringer 11, on the left and right sides

at body station 2598, and replacement of

any cracked fitting with a new fitting.

This amendment is prompted by reports

that fatigue cracking was found on

longeron splice fittings. The actions

specified in this AD are intended to

detect and correct such fatigue cracking,

which could result in reduced

controllability of the horizontal

stabilizer.

DATES: Effective January 13, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 13,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

February 27, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

294–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Bob

Breneman, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington; telephone (425) 227–2776;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received three reports indicating

that fatigue cracking was found on the

longeron splice fittings at stringer 11 on

Boeing Model 747SR and 747–200 series

airplanes. The most recent cracking was

detected on an airplane that had

accumulated 62,783 total flight hours

and 16,867 total flight cycles. Such

fatigue cracking, if not detected and

corrected in a timely manner, could

result in reduced controllability of the

horizontal stabilizer.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

53A2410, Revision 2, dated October 30,

1997, including Addendum, which

describes procedures for repetitive

detailed inspections to detect cracking

of the longeron splice fittings at stringer

11, on the left and right sides at body

station 2598, and replacement of any

cracked fitting with a new fitting. The

alert service bulletin specifies various

compliance times for groups of

airplanes having different flight hour

and flight cycle thresholds.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other Boeing Model 747–

100, 747–200, 747–300, 747SR, and

747SP series airplanes of the same type

design, this AD requires a one-time

detailed inspection to detect cracking of

the longeron splice fittings at stringer

11, on the left and right sides at body

station 2598, and replacement of any

cracked fitting with a new fitting. The

actions are required to be accomplished

in accordance with the alert service

bulletin described previously.

Differences Between the AD and the

Alert Service Bulletin

The AD differs from the previously

described alert service bulletin in that

the AD requires a one-time inspection

and shortened compliance time, rather

than the repetitive inspections and

multiple compliance times specified in

the referenced alert service bulletin. The

recent report of cracking detected on a

Boeing Model 747–200 series airplane at

a relatively low threshold has indicated

the need for interim action requiring

inspection at an early date, directed to

those airplanes that have accumulated

the highest number of flight hours or

flight cycles (i.e., 78,000 total flight

hours or 22,000 total flight cycles).

In addition, the AD differs from the

alert service bulletin by providing a

compliance period in terms of calendar

time, rather than flight cycles/hours, for

those airplanes that have exceeded the

threshold. Due to the limited

availability of replacement fittings, a 90-

day compliance period is provided by

this AD. This compliance period will

allow the operators of affected airplanes

an opportunity to schedule the

inspection and have necessary

replacement fittings available if cracks

are found during the inspection.

Interim Action

This AD is considered to be interim

action. The FAA is considering separate

rulemaking action that would propose

similar inspections at repetitive

intervals for all airplanes affected by the

previously described alert service

bulletin.
Federal Register / Vol. 62, No. 248 / Monday, December 29, 1997 / Rules and Regulations 67551

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications shall identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–294–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–26–21 Boeing: Amendment 39–10264.

Docket 97–NM–294–AD.

Applicability: Model 747–100, 747–200,

747–300, 747SR, and 747SP series airplanes

having line positions 201 through 886

inclusive; 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 detect and correct fatigue cracking of

the longeron splice fittings at stringer 11,

which could result in reduced controllability

of the horizontal stabilizer, accomplish the

following:

(a) Perform a one-time detailed visual

inspection to detect cracking of the longeron

fittings at stringer 11, on the left and right

sides at body station 2598, at the later of the

times specified in paragraphs (a)(1) and (a)(2)

of this AD, in accordance with the

Accomplishment Instructions of Boeing Alert

Service Bulletin 747–53A2410, Revision 2,

dated October 30, 1997, including

Addendum. If any crack is detected, prior to

further flight, replace the cracked fitting with

a new fitting, in accordance with the alert

service bulletin.

(1) Inspect prior to the accumulation of

22,000 total flight cycles or 78,000 total flight

hours, whichever occurs first; or

(2) Inspect within 90 days after the

effective date of this AD.

Note 2: Where there are differences

between the AD and the alert service

bulletin, the AD prevails.

(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, Seattle

Aircraft Certification Office (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, Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle 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 actions shall be done in accordance

with Boeing Alert Service Bulletin 747–

53A2410, Revision 2, dated October 30, 1997,

including Addendum. 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 Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle, Washington

98124–2207. 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

January 13, 1998.

Issued in Renton, Washington, on

December 19, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–33668 Filed 12–24–97; 8:45 am]

BILLING CODE 4910–13–U