13624 Federal Register / Vol. 60, No. 49 / Tuesday, March 14, 1995 / Rules and Regulations

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

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

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–06–01 Boeing: Amendment 39–9171.

Docket 94–NM–147–AD.

Applicability: Model 747–200 and –300

series airplanes equipped with General

Electric CF6–80C2 series engines with Power

Management Control (PMC) engine controls,

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (e) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To ensure the integrity of the fail safe

features of the thrust reverser system,

accomplish the following:

(a) Within 90 days after the effective date

of this AD, perform tests of the position

switch module and the cone brake of the

center drive unit (CDU) on each thrust

reverser, and perform an inspection to detect

damage to the bullnose seal on the translating

sleeve on each thrust reverser, in accordance

with paragraphs III.A. through III.C. of the

Accomplishment Instructions of Boeing

Service Bulletin 747–78A2130, dated May

26, 1994. Repeat the tests and inspection

thereafter at intervals not to exceed 1,000

hours time-in-service.

(b) Within 9 months after the effective date

of this AD, perform inspections and

functional tests of the thrust reverser control

and indication system in accordance with

paragraphs III.D. through III.F., III.H., and

III.I. of the Accomplishment Instructions of

Boeing Service Bulletin 747–78A2130, dated

May 26, 1994. Repeat these inspections and

functional tests thereafter at intervals not to

exceed 18 months.

(c) If any of the inspections and/or

functional tests required by this AD cannot

be successfully performed, or if any

discrepancy is found during those

inspections and/or functional tests,

accomplish either paragraph (c)(1) or (c)(2) of

this AD.

(1) Prior to further flight, correct the

discrepancy found, in accordance with

Boeing Alert Service Bulletin 747–78A2130,

dated May 26, 1994. Or

(2) The airplane may be operated in

accordance with the provisions and

limitations specified in an operator’s FAAapproved Minimum Equipment List (MEL),

provided that no more than one thrust

reverser on the airplane is inoperative.

(d) Within 10 days after performing each

initial inspection and test required by this

AD, submit a report of the inspection and/or

test results, both positive and negative, to the

FAA, Seattle Aircraft Certification Office

(ACO), ANM–100S, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056; fax (206)

227–1181. Information collection

requirements contained in this regulation

have been approved by the Office of

Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

(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, 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.

(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 inspections, corrections of

discrepancies, and tests shall be done in

accordance with Boeing Alert Service

Bulletin 747–78A2130, dated May 26, 1994.

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.

(h) This amendment becomes effective on

April 13, 1995.

Issued in Renton, Washington, on March 3,

1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–5782 Filed 3–13–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–CE–05–AD; Amendment 39–

9173; AD 94–18–04 R1]

Airworthiness Directives; Univair

Aircraft Corporation Models Ercoupe

415–C, 415–CD, 415–D, 415–E, and

415–G, Forney F–1 and F–1A, Alon A–

2 and A–2A, and Mooney M10

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises

Airworthiness Directive (AD) 94–18–04,

which currently requires the following

on Univair Aircraft Corporation

(Univair) Models Ercoupe 415–C, 415–

CD, 415–D, 415–E, and 415–G, Forney

F–1 and F–1A, Alon A–2 and A–2A,

and Mooney M10 airplanes: installing

inspection openings in the outer wing

panels, inspecting (one-time) the wing

outer panel structural components for

corrosion, and repairing any corroded

wing outer panel structural component.

Several reports of corrosion in the outer

wing panels of the affected airplanes

prompted that AD. This action

incorporates a revision to the service

information to include procedures that

the Federal Aviation Administration

(FAA) has determined are necessary for

installing future outer wing panel

inspection openings. The actions
Federal Register / Vol. 60, No. 49 / Tuesday, March 14, 1995 / Rules and Regulations 13625

specified by this AD are intended to

prevent wing damage caused by a

corroded wing outer panel structural

component, which, if not detected and

corrected, could progress to the point of

structural failure.

DATES: Effective March 24, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 24,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

May 19, 1995.

ADDRESSES: Submit comments in

triplicate to the FAA, Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket 94–CE–05–AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Service information that applies to

this AD may be obtained from the

Univair Aircraft Corporation, 2500

Himalaya Road, Aurora, Colorado

80011; telephone (303) 375–8882;

facsimile (303) 375–8888. This

information may also be examined at

the FAA, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 94–CE–05–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106; or at the Office of the

Federal Register, 800 North Capitol

Street NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Roger P. Chudy, Aerospace Engineer,

FAA, Denver Aircraft Certification

Office, 5440 Roslyn Street, suite 133,

Denver, Colorado 80216; telephone

(303) 286–5684; facsimile (303) 286–

5689.

SUPPLEMENTARY INFORMATION: AD 94–

18–04, Amendment 39–9017 (59 FR

43727, September 25, 1994), currently

requires the following on Univair

Models Ercoupe 415–C, 415–CD, 415–D,

415–E, and 415–G, Forney F–1 and F–

1A, Alon A–2 and A–2A, and Mooney

M10 airplanes: installing inspection

openings in the outer wing panels,

inspecting (one-time) the wing outer

panel structural components for

corrosion, and repairing any corroded

wing outer panel structural component.

Accomplishment of these actions is in

accordance with Univair Service

Bulletin (SB) No. 29, Revision A, dated

June 7, 1994.

Since the FAA issued AD 94–18–04,

Univair has revised SB No. 29 to the

Revision B level. This SB revision

changes the dimension of one of the

openings to position it symmetrically

between two ribs; and clarifies the

dimensioning system utilized in

placement of the inspection openings.

Univair SB No. 29, Revision B, also

presents a further discussion of the

service difficulties encountered on the

referenced subject and clarifies the

intent of the preliminary inspection

procedure that may be accomplished

prior to the installation of the inspection

openings.

After examining the circumstances

and reviewing all available information

related to the incidents described above,

the FAA has determined that (1) the

procedures presented in Univair SB No.

29, Revision B, dated January 2, 1995,

should be mandatory for future

inspection opening installations; and (2)

AD action should be taken in order to

prevent wing damage caused by a

corroded wing outer panel structural

component, which, if not detected and

corrected, could progress to the point of

structural failure.

Since an unsafe condition has been

identified that is likely to exist or

develop in other Univair Models

Ercoupe 415–C, 415–CD, 415–D, 415–E,

and 415–G, Forney F–1 and F–1A, Alon

A–2 and A–2A, and Mooney M10

airplanes of the same type design, this

AD revises AD 94–18–04, Amendment

39–9017, to require installing inspection

openings in the outer wing panels,

inspecting (one-time) the wing outer

panel structural components for

corrosion, and repairing any corroded

wing outer panel structural component.

The actions are required to be

accomplished in accordance with the

instructions in Univair SB No. 29,

Revision B, dated January 2, 1995. No

further action will be required by

owners/operators who have successfully

accomplished these actions in

accordance with either Univair SB No.

29, dated January 27, 1994, or Univair

SB No. 29, Revision A, dated June 7,

1994.

Since a situation exists (the

possibility of damaging the wing

structure because of improper

positioning of the inspection openings)

that requires the immediate adoption of

this regulation, it is found that notice

and opportunity for public prior

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 immediate flight safety and,

thus, was not preceded by notice and

opportunity to 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 should identify the

Rules Docket number and be submitted

in triplicate to the address specified

above. 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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 94–CE–05–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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 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

(otherwise, an evaluation is not

required). A copy of it, if filed, may be

obtained from the Rules Docket.
13626 Federal Register / Vol. 60, No. 49 / Tuesday, March 14, 1995 / 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing AD 94–18–04, Amendment

39–9017 (59 FR 43727, September 25,

1994), and by adding a new

airworthiness directive to read as

follows:

94–18–04 R1 Univair Aircraft Corporation:

Amendment 39–9173; Docket No. 94–

CE–05–AD. Revises AD 94–18–04,

Amendment 39–9017.

Applicability: Models Ercoupe 415–C, 415–

CD, 415–D, 415–E, and 415–G, Forney F–1

and F–1A, Alon A–2 and A–2A, and Mooney

M10 airplanes (all serial numbers),

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (d) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any aircraft from the

applicability of this AD.

Compliance: Required within the next 12

calendar months after the effective date of

this AD, unless already accomplished (See

Note 2).

To prevent wing damage caused by a

corroded wing outer panel structural

component, which, if not detected and

corrected, could progress to the point of

structural failure, accomplish the following:

(a) Install inspection openings in the outer

wing panels and inspect the wing outer panel

internal structural components for corrosion

in accordance with the PROCEDURE section

of Univair Service Bulletin (SB) No. 29,

Revision B, dated January 2, 1995. Prior to

further flight, repair any corroded wing outer

panel internal structural component in

accordance with the instructions contained

in the above-referenced service information.

Note 2: Complying with the original

version of Univair SB No. 29, dated January

27, 1994, or Univair SB No. 29, Revision A,

dated June 7, 1994, is considered equivalent

to the requirements of paragraph (a) of this

AD, and is considered ‘‘unless already

accomplished’’ for that portion of the AD.

(b) Send the results of the inspection

required by paragraph (a) of this AD to the

Manager, Denver Aircraft Certification Office

(ACO), 5440 Roslyn Street, suite 133, Denver,

Colorado 80216. State whether corrosion was

found, the location and extent of any

corrosion found, and the total hours time-inservice of the component at the time the

corrosion was found. (Reporting approved by

the Office of Management and Budget under

OMB no. 2120–0056.)

(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) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Denver ACO, 5440

Roslyn Street, suite 133, Denver, Colorado

80216. The request shall be forwarded

through an appropriate FAA Maintenance

Inspector, who may add comments and then

send it to the Manager, Denver ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Denver ACO.

(e) The inspection and installation required

by this AD shall be done in accordance with

Univair Service Bulletin No. 29, Revision B,

dated January 2, 1995. 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 the Univair Aircraft

Corporation, 2500 Himalaya Road, Aurora,

Colorado 80011. Copies may be inspected at

the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri, or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment (39–9173) revises AD

94–18–04, Amendment 39–9017.

(g) This amendment (39–9173) becomes

effective on March 24, 1995.

Issued in Kansas City, Missouri, on March

6, 1995.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–6058 Filed 3–13–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 94–ASO–25]

Establishment of Class E Airspace;

Hampton, GA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment establishes

Class E airspace at Hampton, GA. A GPS

RWY 24 Standard Instrument Approach

Procedure (SIAP) has been developed

for Clayton County-Tara Field.

Controlled airspace extending upward

from 700 feet above the surface (AGL) is

needed to accommodate this SIAP and

for instrument flight rules (IFR)

operations at the airport. The operating

status of the airport will change from

VFR to include IFR operations

concurrent with publication of the

SIAP.

EFFECTIVE DATE: 0901 UTC, May 25,

1995.

FOR FURTHER INFORMATION CONTACT:

Michael J. Powderly, System

Management Branch, Air Traffic

Division, Federal Aviation

Administration, P.O. Box 20636,

Atlanta, Georgia 30320; telephone (404)

305–5570.

SUPPLEMENTARY INFORMATION:

History

On January 4, 1995, the FAA

proposed to amend part 71 of the

Federal Aviation Regulations (14 CFR

part 71) by establishing Class E airspace

at Hampton GA (60 FR 396). This action

would provide adequate Class E

airspace for IFR operations at Clayton

County-Tara Field.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments objecting to the proposal

were received. Designations for Class E

airspace extending upward from 700

feet or more above the surface are

published in Paragraph 6005 of FAA

Order 7400.9B dated July 18, 1994, and

effective September 16, 1994. The Class

E airspace designation listed in this

document will be published

subsequently in the Order.

The Rule

This amendment to part 71 of the

Federal Aviation Regulations (14 CFR

part 71) establishes Class E airspace at

Hampton, GA, to accommodate a GPS

RWY 24 SIAP and contain IFR

operations at Clayton County-Tara

Field. The operating status of the airport

will be changed from VFR to include