62728 Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules

Regulatory Impact

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Boeing: Docket 97–NM–138–AD.

Applicability: Model 747–400 series

airplanes; as listed in Boeing Alert

Service Bulletin 747–24A2214, dated

June 19, 1997; 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 the auxiliary power unit (APU)

from overheat and heat damage due to an

improperly installed/maintained APU battery

ground, accomplish the following:

(a) Within 6 months after the effective date

of this AD, reconfigure the APU battery

grounds to a dual-direct ground, single-lug

configuration, in accordance with Boeing

Alert Service Bulletin 747–24A2214, dated

June 19, 1997.

(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 2: 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.

Issued in Renton, Washington, on

November 18, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–30868 Filed 11–24–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–11–AD]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to all

Lockheed Model L–1011–385 series

airplanes, that currently requires

inspections to detect cracking and other

discrepancies of certain web-to-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. That AD also

provides for an optional modification,

which, if accomplished, would defer the

initiation of the inspections for a certain

period of time. This action would

require accomplishment of the

previously optional modification. This

proposal is prompted by an FAA

determination that the optional

terminating modification specified in

the existing AD must be accomplished

within a specified period of time to

ensure an acceptable level of safety of

the affected fleet. The actions specified

by the proposed AD are intended to

prevent fatigue cracking in the web of

the rear spar of the wing, which could

result in failure of the rear spar of the

wing and consequent fuel spillage.

DATES: Comments must be received by

January 5, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

11–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Lockheed Aeronautical Systems

Support Company (LASSC), 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, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia

30337–2748; telephone (770) 703–6063;

fax (770) 703–6097.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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
Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules 62729

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–11–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

97–NM–11–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On June 5, 1996, the FAA issued AD

96–12–24, amendment 39–9667 (61 FR

29642, June 12, 1996), applicable to all

Lockheed Model L–1011–385 series

airplanes, to require repetitive visual

inspections to detect cracking and other

discrepancies of certain web-to-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. That action

also provides for an optional

modification, which, if accomplished,

would allow the initiation of the visual

inspections to be deferred for a certain

period of time. That action was

prompted by a report of fatigue cracking

in the web of the rear spar of the wing.

The requirements of that AD are

intended to prevent such fatigue

cracking, which could result in failure

of the rear spar of the wing and

consequent fuel spillage.

Actions Since Issuance of Previous Rule

Since the issuance of AD 96–12–24,

the FAA has determined that the

optional terminating modification

specified in the existing AD must be

required to be accomplished within a

specified period of time to reduce the

possibility of fatigue cracking remaining

undetected and to ensure an acceptable

level of safety of the affected fleet.

Lockheed Service Bulletin 093–57–

218, which is referenced in the existing

AD as the appropriate source of service

information, does not recommend a

limit on the number of inspections to be

accomplished prior to installation of the

modification. Table I of the service

bulletin recommends that the

inspections be accomplished at short

repetitive intervals, which range from

60 to 180 landings.

The FAA finds that the possibility of

maintenance errors during inspection

could result in a net degradation in

airplane safety if the inspections are

performed in accordance with the

schedule set forth in the service

bulletin. The FAA considers that

accomplishment of continuous

inspections at the short inspection

intervals specified in the service

bulletin increases the risk that fatigue

cracking could remain undetected.

Consequently, the FAA has determined

that the previously optional

modification must be accomplished to

ensure an acceptable level of safety.

Following accomplishment of the

modification, inspection must resume

after the accumulation of no more than

5,000 landings.

Explanation of Relevant Service

Information

Since the issuance of AD 96–12–24,

the FAA has reviewed and approved

Lockheed Service Bulletin 093–57–218,

Revision 1, dated September 9, 1996.

This service bulletin revision describes

procedures for inspections to detect

cracking and other discrepancies of

certain web-to-cap fasteners of the rear

spar, and for modification of the web-tocap fastener holes, in an expanded area

of the IWS (i.e., IWS 299 through IWS

343). In all other respects, Revision 1 of

the service bulletin is essentially the

same as the original issue.

Additionally, the FAA has reviewed

and approved several other Lockheed

service bulletins, listed below, which

provide options for accomplishment of

certain modifications in lieu of that

specified in Lockheed Service Bulletin

093–57–218. If accomplished, these

modifications would allow the

repetitive inspections to be deferred for

specified periods of time.

For Lockheed Model L–1011–385–3

series airplanes:

• Lockheed Service Bulletin 093–57–

203, Revision 3, dated October 28, 1991;

as amended by Change Notifications

093–57–203, R3–CN1, dated June 22,

1992; 093–57–203, R3–CN2, dated

February 15, 1993; and 093–57–203,

R3–CN3, dated September 15, 1994.

• Lockheed Service Bulletin 093–57–

215, dated April 11, 1996. For Lockheed

Model L–1011–385–1 series airplanes:

• Lockheed Service Bulletin 093–57–

184, Revision 6, dated October 28, 1991,

as amended by Change Notifications

093–57–184, R6–CN1, dated June 22,

1992, and 093–57–184, R6–CN2, dated

December 14, 1992.

• Lockheed Service Bulletin 093–57–

184, Revision 7, dated December 6,

1994, as amended by Change

Notifications 093–57–184, R7–CN1,

dated August 22, 1995, 093–57–184,

R7–CN2, dated February 20, 1996, and

093–57–184, R7–CN3, dated April 4,

1996; and Lockheed Service Bulletin

093–57–212, dated November 14, 1994,

as amended by Change Notification

093–57–212, CN1, dated September 27,

1995.

• Lockheed Service Bulletin 093–57–

196, Revision 5, dated October 28, 1991,

as amended by Change Notification

093–57–196, R5–CN1, dated June 22,

1992; and Lockheed Service Bulletin

093–57–212, dated November 14, 1994,

as amended by Change Notification

093–57–212, CN1, dated September 27,

1995.

• Lockheed Service Bulletin 093–57–

196, Revision 6, dated December 6,

1994, as amended by Change

Notification 093–57–196, R6–CN1,

dated August 22, 1995, 093–57–196,

R6–CN2, dated February 20, 1996, and

093–57–196, R6–CN3, dated May 21,

1996.

A description of each service bulletin

follows:

• Lockheed Service Bulletin 093–57–

203. This service bulletin describes

procedures for modification of the

upper and lower caps of the rear spar

between IWS 228 and IWS 346. The

modification involves removal of

fasteners, reaming of fastener holes,

performing an eddy current inspection,

removing crack indications, cold

working the holes, installing oversize

fasteners, adding angle reinforcements

to the upper caps, and adding doublers

at the rear spar and main landing gear

fitting joint.

• Lockheed Service Bulletin 093–57–

215: This service bulletin describes

procedures for modification of the left

and right wing rear spars. The

modification entails cold working the

fasteners, installing new oversized

fasteners (if necessary), adding structure

reinforcements to the lower caps, and

adding new upper caps and webs at the

rear spar and main landing gear fitting

joint.

• Lockheed Service Bulletins 093–

57–184 and 093–57–212. These service
62730 Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules

bulletins describe procedures for

modification of the inboard and

outboard rear spars, respectively.

Modification of the inboard spar web

entails removing the entire web inboard

to IWS 228.774 and replacing it with a

new web portion; adding new upper

caps and stiffeners in both wings, cold

working certain fastener holes, and

removing certain existing fasteners for

eddy current hole inspection.

Modification of the outboard spar web

involves performing an eddy current

inspection of the fastener holes, cold

working specific fastener holes (if no

cracking is found), repairing any crack

found, and installing a new outboard

web section.

• Lockheed Service Bulletin 093–57–

196. This service bulletin describes

procedures for modification of the

inboard rear spar, which includes

removing the entire web inboard to IWS

228.774 and replacing it with a new web

portion; adding new upper caps and

stiffeners in both wings, cold working

certain fastener holes, and removing

certain existing fasteners for eddy

current hole inspection.

Accomplishment of the actions

specified in the service bulletins is

intended to adequately address the

identified unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

supersede AD 96–12–24 to continue to

require inspections to detect cracking

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

IWS 310 and IWS 343, and of the web

area around those fasteners; and various

follow-on actions. This proposed AD

would require accomplishment of the

previously optional modification,

which, when accomplished, will defer

the initiation of the inspections for a

certain period of time. The proposed AD

also provides for additional options for

accomplishment of the previously

optional modification, which also defer

the inspections for certain specified

periods of time. The actions would be

required to be accomplished in

accordance with the service bulletin

described previously.

Differences Between the Service

Bulletin and This Proposed AD

Operators should note that Revision 1

of Lockheed Service Bulletin 093–57–

218 expands the inspection area to

include IWS 299 through IWS 310.

However, the FAA has determined that

the various X-ray, eddy current, and

ultrasonic inspections of certain areas of

the rear spar caps, web, skin, and

fastener holes required by AD 96–07–13,

amendment 39–9563 (61 FR 16379,

April 15, 1996), adequately address

fatigue cracking in the expanded area

specified in Revision 1 of the service

bulletin. Therefore, this proposed AD

does not require inspection of that

expanded area. However, the FAA finds

that accomplishment of the proposed

modification in the expanded area, as

recommended in the service bulletin, is

necessary to ensure an acceptable level

of safety.

Cost Impact

There are approximately 235

Lockheed Model L–100–385 series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

117 airplanes of U.S. registry would be

affected by this proposed AD.

The actions that are currently

required by AD 96–12–24 take

approximately 13 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

currently required actions on U.S.

operators is estimated to be $91,260, or

$780 per airplane.

The new actions that are proposed in

this AD action would take

approximately 100 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

proposed requirements of this AD on

U.S. operators is estimated to be

$702,000, or $6,000 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or proposed 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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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

removing amendment 39–9667 (61 FR

29642, June 12, 1996), and by adding a

new airworthiness directive (AD), to

read as follows:

Lockheed: Docket 97–NM–11–AD.

Supersedes AD 96–12–24, Amendment

39–9667.

Applicability: All Model L–1011–385

series airplanes, 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 (h)(1) 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 on the web of

the rear spar of the wing, which could result

in failure of the rear spar of the wing and

consequent fuel spillage, accomplish the

following:

Restatement of Requirements of AD

96–12–24

(a) Perform a visual inspection to detect

signs of cracking and other discrepancies

(i.e., corrosion, fastener looseness, nicks,
Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules 62731

scratches, or other surface damage) of the

web-to-cap fasteners of the rear spar between

inner wing stations (IWS) 310 and 343, as

specified in Figure 2 of Lockheed Service

Bulletin 093–57–218, dated April 11, 1996,

or Revision 1, dated September 9, 1996; and

of the web area around those fasteners; in

accordance with Part I of the

Accomplishment Instructions of that service

bulletin. Perform the inspection at the

applicable time specified in paragraph (a)(1)

or (a)(2) of this AD.

(1) Except as provided by paragraph (a)(2)

of this AD: Perform the initial inspection

prior to the accumulation of the number of

landings specified as the ‘‘inspection

threshold’’ in Table I of Lockheed Service

Bulletin 093–57–218, dated April 11, 1996,

or Revision 1, dated September 9, 1996, or

within 10 days after June 27, 1996 (the

effective date of AD 96–12–24), whichever

occurs later.

(2) For airplanes on which the wing rear

spar has been modified prior to June 27,

1996, in accordance with one of the

Lockheed service bulletins listed in

paragraph (a)(2)(ii) of this AD, accomplish

the inspection as follows:

(i) Perform the initial inspection prior to

the accumulation of the number of landings

specified as the ‘‘inspection threshold’’ in

Table I of Lockheed Service Bulletin 093–57–

218, dated April 11, 1996, or Revision 1,

dated September 9, 1996, calculated from the

time the wing rear spar was modified (rather

than from the date of manufacture of the

airplane), or within 10 days after June 27,

1996, whichever occurs later.

(ii) This paragraph applies to airplanes on

which the wing rear spar has been modified

in accordance with one of the following

service bulletins:

• Lockheed Service Bulletin 093–57–184,

Revision 6, dated October 28, 1991, or

Revision 7, dated December 6, 1994; or

• Lockheed Service Bulletin 093–57–196,

Revision 5, dated October 28, 1991, or

Revision 6, dated December 6, 1994; or

• Lockheed Service Bulletin 093–57–203,

Revision 3, dated October 28, 1991, or

Revision 4, dated March 27, 1995; or

• Lockheed Service Bulletin 093–57–215,

dated April 11, 1996.

(b) If no sign of cracking or other

discrepancy is found during the inspection

required by paragraph (a) of this AD, repeat

that inspection thereafter at intervals not to

exceed the number of landings specified as

the ‘‘repeat visual inspection interval’’ in

Table I of Lockheed Service Bulletin 093–57–

218, dated April 11, 1996, or Revision 1,

dated September 9, 1996.

(c) If any sign of cracking is found during

an inspection required by paragraph (a) or (b)

of this AD, prior to further flight, perform

either eddy current surface scan (ECSS)

inspections, or bolt hole eddy current (BHEC)

inspections, as appropriate, to confirm

cracking, in accordance with Lockheed

Service Bulletin 093–57–218, dated April 11,

1996, or Revision 1, dated September 9, 1996.

(1) If no cracking is confirmed, repeat the

inspection specified in paragraph (a) of this

AD at intervals not to exceed the number of

landings specified as the ‘‘repeat visual

inspection interval’’ in Table I of the service

bulletin.

(2) If any cracking is confirmed, prior to

further flight, repair it in accordance with the

service bulletin.

New Requirements of This AD

(d) Except as provided by paragraph (e) or

(f) of this AD, as applicable: Within 12

months after the effective date of this AD,

modify the web-to-cap fastener holes of the

rear spar between IWS 299 and IWS 343 in

accordance with Part II of the

Accomplishment Instructions of Lockheed

Service Bulletin 093–57–218, Revision 1,

dated September 9, 1996. Within 5,000

landings following accomplishment of the

modification, perform the visual inspection

required by paragraph (a) of this AD.

Thereafter, repeat that inspection at intervals

not to exceed the number of landings

specified as the ‘‘repeat visual inspection

interval’’ in Table I of Lockheed Service

Bulletin 093–57–218, Revision 1, dated

September 9, 1996.

(e) For Model L–1011–385–3 series

airplanes: Accomplishment of the

modifications specified in paragraph (e)(1) or

(e)(2) of this AD, within 12 months after the

effective date of this AD, constitutes an

acceptable alternative to the modification

specified in paragraph (d) of this AD.

(1) Modify the upper and lower caps of the

rear spar between IWS 228 and IWS 346 in

accordance with Part I of the

Accomplishment Instructions of Lockheed

Service Bulletin 093–57–203, Revision 3,

dated October 28, 1991. Within 5,000

landings following accomplishment of the

modification, perform the visual inspection

required by paragraph (a) of this AD.

Thereafter, repeat that inspection at intervals

not to exceed the number of landings

specified as the ‘‘repeat visual inspection

interval’’ in Table I of Lockheed Service

Bulletin 093–57–218, Revision 1, dated

September 9, 1996. Or

(2) Modify the left and right wing rear

spars in accordance with the

Accomplishment Instructions of Lockheed

Service Bulletin 093–57–215, dated April 11,

1996. Within the thresholds specified in

Table I of Lockheed Service Bulletin 093–57–

218, Revision 1, dated September 9, 1996

(calculated from the date of installation of

Lockheed Service Bulletin 093–57–215,

dated April 11, 1996), perform the visual

inspection required by paragraph (a) of this

AD. Thereafter, repeat that inspection at

intervals not to exceed the number of

landings specified as the ‘‘repeat visual

inspection interval’’ in Table I of Lockheed

Service Bulletin 093–57–218, Revision 1,

dated September 9, 1996.

(f) For Model L–1011–385–1 series

airplanes: Accomplishment of the

modifications specified in paragraph (f)(1) or

(f)(2) of this AD, within 12 months after the

effective date of this AD, constitutes an

acceptable alternative to the modification

specified in paragraph (d) of this AD.

(1) Modify the inboard and outboard rear

spars in accordance with the

Accomplishment Instructions of Lockheed

Service Bulletin 093–57–184, Revision 6,

dated October 28, 1991, or Revision 7, dated

December 6, 1994; and Lockheed Service

Bulletin 093–57–212, dated November 14,

1994, as amended by Change Notification

CN1, dated September 27, 1995. Within the

thresholds specified in Table I of Lockheed

Service Bulletin 093–57–218, Revision 1,

dated September 9, 1996 (calculated from the

date of installation of Lockheed Service

Bulletin 093–57–184, Revision 6, dated

October 28, 1991, or Revision 7, dated

December 6, 1994; and Lockheed Service

Bulletin 093–57–212, dated November 14,

1994, as amended by Change Notification

CN1, dated September 27, 1995), perform the

visual inspection required by paragraph (a) of

this AD. Thereafter, repeat that inspection at

intervals not to exceed the number of

landings specified as the ‘‘repeat visual

inspection interval’’ in Table I of Lockheed

Service Bulletin 093–57–218, Revision 1,

dated September 9, 1996. Or

(2) Modify the inboard and outboard rear

spars in accordance with the

Accomplishment Instructions of Lockheed

Service Bulletin 093–57–196, Revision 5,

dated October 28, 1991, or Revision 6, dated

December 6, 1994; and Lockheed Service

Bulletin 093–57–212, dated November 14,

1994, as amended by Change Notification

CN1, dated September 27, 1995. Within the

thresholds specified in Table I of Lockheed

Service Bulletin 093–57–218, Revision 1,

dated September 9, 1996 (calculated from the

date of installation of Lockheed Service

Bulletin 093–57–196, Revision 5, dated

October 28, 1991, or Revision 6, dated

December 6, 1994; and Lockheed Service

Bulletin 093–57–212, dated November 14,

1994, as amended by Change Notification

CN1, dated September 27, 1995), perform the

visual inspection required by paragraph (a) of

this AD. Thereafter, repeat that inspection at

intervals not to exceed the number of

landings specified as the ‘‘repeat visual

inspection interval’’ in Table I of Lockheed

Service Bulletin 093–57–218, Revision 1,

dated September 9, 1996.

(g) If any condition (i.e., number of

fasteners per stiffener bay, or cracking) is

identified during the accomplishment of the

modification specified in Lockheed Service

Bulletin 093–57–218, Revision 1, dated

September 9, 1996, and that condition

exceeds the limits specified in paragraph

B.(3) of Part II of the Accomplishment

Instructions of the service bulletin, prior to

further flight, repair in accordance with a

method approved by the Manager, Atlanta

Aircraft Certification Office (ACO), FAA,

Small Airplane Directorate.

(h)(1) 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. 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.

(2) Alternative methods of compliance,

approved previously in accordance with AD

96–12–24, amendment 39–9667, are

approved as alternative methods of

compliance with paragraph (d) of this AD.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.
62732 Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules

1 17 CFR 240.14a–8.

2 17 CFR 240.14a–4.

3 17 CFR 240.14a–5.

4 17 CFR 240.14a–2.

5 17 CFR 240.13d–5.

(i) 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.

Issued in Renton, Washington, on

November 18, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–30857 Filed 11–24–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 94–AWP–2]

Proposed Relocation of the Kahului

(OGG) VORTAC and Realignment of

VOR Federal Airways; Hawaii

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Proposed rule; withdrawal.

SUMMARY: This action withdraws the

notice of proposed rulemaking (NPRM)

published in the Federal Register on

March 18, 1994. The NPRM proposed to

relocate the Kahului Very High

Frequency Omnidirectional Range/

Tactical Air Navigation (VORTAC) and

realign seven Federal airways. The FAA

has determined that withdrawal of the

proposal is warranted due to an in-flight

aeronautical evaluation (flight check)

that revealed the airways would not

meet FAA designed criteria.

DATES: The proposed rule is withdrawn

as of November 25, 1997.

FOR FURTHER INFORMATION CONTACT:

William C. Nelson, Airspace and Rules

Division, (ATA–400), Office of Air

Traffic Airspace Management, Federal

Aviation Administration, 800

Independence Avenue, SW.,

Washington, DC 20591; telephone: (202)

267–8783.

SUPPLEMENTARY INFORMATION: On March

18, 1994, an NPRM was published in

the Federal Register to amend 14 CFR

part 71 to relocate the Kahului VORTAC

and realign seven Federal airways that

would be affected by this Kahului

VORTAC relocation. No comments were

received on the proposal.

The FAA has decided to withdraw the

proposal at this time due to flight check

results.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

The Withdrawal

In consideration of the foregoing, the

Notice of proposed rulemaking,

Airspace Docket No. 94–AWP–2, as

published in the Federal Register on

March 18, 1994 (59 FR 12875), is hereby

withdrawn.

Authority: 49 U.S.C. 106(g), 40103, 40113,

40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959–

1963 Comp., p. 389.

Issued in Washington, DC, on November

13, 1997.

Nancy B. Kalinowski,

Acting Program Director for Air Traffic

Airspace Management.

[FR Doc. 97–30773 Filed 11–24–97; 8:45 am]

BILLING CODE 4910–13–M

SECURITIES AND EXCHANGE

COMMISSION

17 CFR Part 240

[Release No. 34–39336; IC–22896; File No.

S7–25–97]

RIN 3235–AH20

Amendments to Rules on Shareholder

Proposals

AGENCY: Securities and Exchange

Commission.

ACTION: Proposed rule; Extension of

comment period.

SUMMARY: The Securities and Exchange

Commission (‘‘we’’ or ‘‘Commission’’) is

extending the comment period for its

proposals to amend rule 14a–8, and

related rules, set forth in Securities

Exchange Act Release No. 39093 (9/18/

97), 62 FR 50682 (9/26/97) (the

‘‘Release’’). The original deadline

established by the Release was

November 25, 1997. The new deadline

is January 2, 1998.

DATES: Public comments are due on or

before January 2, 1998.

ADDRESSES: Please send three copies of

the comment letter to Jonathan G. Katz,

Secretary, U.S. Securities and Exchange

Commission, 450 Fifth Street, N.W.,

Washington, D.C. 20549. Comment

letters can be sent electronically to the

following e-mail address: rulecomments@sec.gov. The comment letter

should refer to File No. S7–25–97; if email is used please include the file

number in the subject line. Anyone can

inspect and copy the comment letters in

the SEC’s Public Reference Room, 450

Fifth Street, N.W., Washington, D.C.

20549. We will post comment letters

submitted electronically on our Internet

site (http://www.sec.gov).

FOR FURTHER INFORMATION CONTACT:

Frank G. Zarb, Jr., Special Counsel,

Office of Chief Counsel, Division of

Corporation Finance, at (202) 942–2900,

or Doretha M. VanSlyke, Division of

Investment Management, at (202) 942–

0721, Securities and Exchange

Commission, 450 Fifth Street N.W.,

Washington, D.C. 20549.

SUPPLEMENTARY INFORMATION: On

September 18, 1997, the Commission

issued the Release, proposing

amendments to rule 14a–8,1 the

shareholder proposal rule, and related

amendments to rules 14a–4,2 14a–5,3

14a–2,4 and 13d–5.5 The deadline for

submitting public comments established

by the Release was November 25, 1997.

The Commission has received requests

to extend the deadline. We are therefore

extending the comment period to

January 2, 1998, so that commenters are

ensured of adequate time to fully

address the issues raised by the Release.

Dated: November 19, 1997.

By the Commission.

Margaret H. McFarland,

Deputy Secretary.

[FR Doc. 97–30922 Filed 11–24–97; 8:45 am]

BILLING CODE 8010–01–M

DEPARTMENT OF LABOR

Mine Safety and Health Administration

30 CFR Part 75

Self-Rescue Devices; Use and

Location Requirements

AGENCY: Mine Safety and Health

Administration, (MSHA) Labor.

ACTION: Extension of comment period.

SUMMARY: MSHA is extending the

comment period on its proposed policy

letter (PPL) relating to the approval

guidelines for storage plans for SelfContained Self-Rescue (SCSR) Devices

in underground coal mines.

DATES: Submit all comments on or

before February 23, 1998.

ADDRESSES: Comments may be

transmitted by electronic mail, fax or

mail. Comments by electronic mail must

be clearly identified as such and sent to

this e-mail address: psilvey@msha.gov.

Comments by fax must be clearly

identified as such and sent to: Mine

Safety and Health Administration,

Office of Standards, Regulations and

Variances, 703–235–5551. Send mail

comments to: Mine Safety and Health

Administration, Office of Standards,