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
Federal Register / Vol. 61, No. 114 / Wednesday, June 12, 1996 / Rules and Regulations 29643

time because the crack can propagate on

the interior (fuel side) of the web before

it breaches the aft side (flap side) of the

web. Such fatigue cracking, if not

detected and corrected in a timely

manner, could result in failure of the

rear spar of the wing and consequent

fuel spillage.

Other Relevant Rules

The FAA previously issued AD 96–

07–13, amendment 39–9563 (61 FR

16379, April 15, 1996), which requires

various X-ray, eddy current, and

ultrasonic inspections to detect fatigue

cracking of certain areas of the rear spar

caps, web, skin, and certain fastener

holes; and repair or modification, if

necessary. The inspections are required

to be repeated at intervals of 2,000 flight

cycles. That AD was prompted by

reports of fatigue cracks in the caps,

web, and skin of the wing rear spar

inboard of inner wing station 346. The

actions specified by that AD are

intended to prevent rupture of the rear

spar, which could result in extensive

damage to the wing and fuel spillage.

The fatigue cracking that was the

subject of the recent in-service incident,

described above, indicates that fatigue

cracking in the area of the web of the

rear spar of the wing apparently can

occur and propagate at a faster rate and

at a reduced threshold than previously

realized. In light of this, the FAA is

considering revising AD 96–07–13 to

reduce the repetitive inspection

intervals to ensure that fatigue cracking

can be found in a more timely manner.

(The FAA indicated this in the preamble

to that AD.)

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Lockheed L–1011 Service Bulletin 093–

57–218, dated April 11, 1996. Part I of

the service bulletin describes

procedures for repetitive visual

inspections to detect fatigue cracking

and other discrepancies (i.e., corrosion,

fastener looseness, nicks, scratches, or

other surface damage) of certain web-tocap 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.

The follow-on actions include repetitive

visual inspections, eddy current surface

scan (ECSS) inspections, bolt hole eddy

current (BHEC) inspections, and repair.

Part II of the service bulletin describes

procedures for an optional modification

that will allow the initiation of the

visual inspections to be deferred for a

period of time. The modification

involves removing certain web-to-cap

fasteners, verifying that the subject

fastener holes are free of cracks, cold

working the fastener holes, and

replacing the fasteners with oversize

fasteners.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other Model L–1011–385

series airplanes of the same type design,

this AD is being issued 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. This AD

requires repetitive visual inspections to

detect cracking and other discrepancies

of certain web-to-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 AD also provides for an optional

modification which, if accomplished,

will allow the initiation of the visual

inspections to be deferred for a certain

period of time. The actions are required

to be accomplished in accordance with

the Lockheed service bulletin described

previously.

The inspections that are required by

this AD are in addition to—not in lieu

of—those currently required by AD 96–

07–13, amendment 39–9563.

Differences between the Rule and the

Referenced Service Information

Operators should note that, although

the Lockheed service bulletin specifies

that the manufacturer must be contacted

for disposition of certain conditions,

this AD requires that the repair of those

conditions be accomplished in

accordance with a method approved by

the Manager, Atlanta Aircraft

Certification Office (ACO), FAA, Small

Airplane Directorate.

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 96–NM–104–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.
29644 Federal Register / Vol. 61, No. 114 / Wednesday, June 12, 1996 / Rules and Regulations

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:

96–12–24 Lockheed: Amendment 39–9667.

Docket 96–NM–104–AD.

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 (e) 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:

(a) Perform a visual inspection to detect

signs of cracking and other discrepancies

(i.e., corrosion, fastener looseness, nicks,

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;

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 within 10 days after the effective date of

this AD, whichever occurs later.

(2) For airplanes on which the wing rear

spar has been modified prior to the effective

date of this AD 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, 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 the

effective date of this AD, 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.

(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.

(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 1 of the service bulletin.

(2) If any cracking is confirmed, prior

to further flight, repair it in accordance

with the service bulletin.

(d) Accomplishment of the

modification specified in Part II of the

Accomplishment Instructions of

Lockheed Service Bulletin 093–57–218,

dated April 11, 1996, and in accordance

with that service bulletin, allows the

visual inspections required by

paragraph (a) of this AD to be deferred

for the period specified in paragraph

(d)(2) of this AD.

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

fasteners per stiffener bay, or cracking)

is identified during the accomplishment

of the modification that 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.

(2) 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 the service

bulletin.

(e) 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, 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.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(f) 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.

(g) The actions shall be done in

accordance with Lockheed L–1011

Service Bulletin 093–57–218, dated

April 11, 1996. 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,

Dept. 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, 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.

(h) This amendment becomes

effective on June 27, 1996.
Federal Register / Vol. 61, No. 114 / Wednesday, June 12, 1996 / Rules and Regulations 29645

Issued in Renton, Washington, on June 5,

1996.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14692 Filed 6–11–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 96–ANM–001]

Amendment of Class E Airspace;

Baker, Montana

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action modifies the

Baker, Montana, Class E airspace to

provide additional controlled airspace

necessary to accommodate a revised

Global Positioning System (GPS)

standard instrument approach

procedure (SIAP) to the Baker

Municipal Airport.

EFFECTIVE DATE: 0901 UTC, August 15,

1996.

FOR FURTHER INFORMATION CONTACT:

James C. Frala, Operations Branch,

ANM–532.4, Federal Aviation

Administration, Docket No. 96–ANM–

001, 1601 Lind Avenue SW., Renton,

Washington 98055–4056; telephone

number: (206) 227–2535.

SUPPLEMENTARY INFORMATION:

History

On April 22, 1996, the FAA proposed

to amend part 71 of the Federal Aviation

Regulations (14 CFR part 71) to amend

Class E airspace at Baker, Montana, to

accommodate a revised GPS SIAP to the

Baker Municipal Airport (61 FR 17607).

Interested parties were invited to

participate in the rulemaking

proceeding by submitting written

comments on the proposal. No

comments were received.

The coordinates for this airspace

docket are based on North American

Datum 83. Class E airspace areas

extending upward from 700 feet or more

above the surface of the earth are

published in paragraph 6005 of FAA

Order 7400.9C dated August 17, 1995,

and effective September 16, 1995, which

is incorporated by reference in 14 CFR

71.1. The Class E airspace listed in this

document will be published

subsequently in the Order.

The Rule

This amendment to part 71 of Federal

Aviation Regulations amends Class E

airspace at Baker, Montana. The FAA

has determined that this regulation only

involves an established body of

technical regulations for which frequent

and routine amendments are necessary

to keep them operationally current. It,

therefore, (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) does not warrant

preparation of a regulatory evaluation as

the anticipated impact is so minimal.

Since this is a routine matter that will

only affect air traffic procedures and air

navigation, it is certified that this rule

will not have a significant economic

impact on a substantial number of small

entities under the criteria of the

Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

FAA amends 14 CFR part 71 as follows:

PART 71—[AMENDED]

1. The authority citation for 14 CFR

part 71 continues to read as follows:

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

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

1963 Comp., p. 389; 14 CFR 11.69.

§ 71.1 [Amended]

2. The incorporation by reference in

14 CFR 71.1 of the Federal Aviation

Administration Order 7400.9C, Airspace

Designations and Reporting Points,

dated August 17, 1995, and effective

September 16, 1995, is amended as

follows:

Paragraph 6005 Class E airspace areas

extending upward from 700 feet or more

above the surface of the earth.

* * * * *

ANM MT E5 Baker, MT [Revised]

Baker Municipal Airport, MT

lat. 46°20′52′′ N, long. 104°15′34′′ W)

That airspace extending upward from 700

feet above the surface within a 8.9-mile

radius of the Baker Municipal Airport; that

airspace extending upward from 1,200 feet

above the surface bounded by a line

beginning at lat. 46°20′00′′ N,

long.104°45′00′′ W; to lat. 46°30′30′′ N, long.

104°31′00′′ W; to lat. 46°37′00′′N, long.

104°31′00′′W; to lat. 46°37′00′′N, long.

103°59′40′′W; to lat. 46°37′55′′N, long.

103°53′45′′W; to lat. 46°25′45′′N, long.

103°37′30′′W; to lat. 46°17′30′′N, long.

103°48′15′′W; to lat. 45°40′00′′N, long.

103°00′50′′W; to lat. 45°35′30′′N, long.

103°01′45′′W; to lat. 45°55′20′′N, long.

103°53′15′′W; to lat. 46°00′00′′N, long.

104°13′00′′W; to lat. 46°04′20′′N, long.

104°10′45′′W; to the point of beginning;

excluding that portion within the Bowman

Municipal Airport, ND, 1,200-foot Class E

airspace area.

* * * * *

Issued in Seattle, Washington, on May 28,

1996.

Richard E. Prang,

Acting Assistant Manager, Air Traffic

Division, Northwest Mountain Region.

[FR Doc. 96–14878 Filed 6–11–96; 8:45 am]

BILLING CODE 4910–13–M

Office of the Secretary

14 CFR Part 399

RIN 2105–AC43

Editorial Changes to Policies Relating

to Accounts and Reports

AGENCY: Office of the Secretary, DOT.

ACTION: Final rule.

SUMMARY: The Department of

Transportation amends its regulations in

order to remove redundant provisions.

This rule makes no substantive changes

to current regulations. This action is

taken in response to the President’s

Regulatory Reinvention Initiative.

EFFECTIVE DATE: This rule is effective on

July 12, 1996.

FOR FURTHER INFORMATION CONTACT:

Bernie Stankus, Regulations Division,

Office of Airline Information, K–25, U.S.

Department of Transportation, 400

Seventh Street SW., Washington, DC

20590, (202) 366–4387, or M. Clay

Moritz, (202) 366–4385.

SUPPLEMENTARY INFORMATION:

Background and Purpose

Subpart D of 14 CFR Part 399 is being

removed as superfluous. Section 399.50

is redundant to section 241.22(c);

section 399.51 is redundant to section

241.22(b)(3); and section 399.52 is

redundant to section 241.2–4(d). The

policies regarding extensions of time for

filing reports, confidential treatment of

unaudited preliminary year-end reports,

and retroactive adjustments of expenses

remain unchanged.

Notice and Opportunity for Public

Comment Unnecessary

Since this change relates to

departmental management,

organization, procedure, and practice,

notice and comment are unnecessary.

The changes made in this document are

ministerial, removing redundant

material.

Regulatory Evaluation

This rule is not a significant

regulatory action under section 3(f) of

Executive Order 12866. It has not been