28736 Federal Register / Vol. 61, No. 110 / Thursday, June 6, 1996 / Rules and Regulations

Service Bulletin 215–389, dated November

15, 1988, prior to the effective date of this

AD, is considered acceptable for compliance

with this paragraph.

(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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York 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 shall be done in

accordance with Canadair Alert Service

Bulletin 215–A363, dated March 16, 1987.

The modification shall be done in accordance

with Canadair Service Bulletin 215–389,

Revision 1, dated September 30, 1991. 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

Bombardier, Inc., Canadair Aerospace Group,

P.O. Box 6087, Station Centre-ville, Quebec

H3C 3G9, Canada. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, New York

Aircraft Certification Office, Engine and

Propeller Directorate, 10 Fifth Street, Third

Floor, Valley Stream, New York; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(h) This amendment becomes effective on

June 21, 1996.

Issued in Renton, Washington, on May 30,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14036 Filed 6–5–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 92–ANE–08; Amendment 39–

8781; AD 93–25–17]

Airworthiness Directives; General

Electric CT7 Series Turboprop and

Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document makes a

correction to Airworthiness Directive

(AD) 93–25–17 applicable to General

Electric (GE) CT7 series turboprop and

turboshaft engines that was published in

the Federal Register on January 3, 1994

(59 FR 3). The docket number in the

header to the applicability section is

incorrect. This document corrects the

docket number. In all other respects, the

original document remains the same.

EFFECTIVE DATE: June 6, 1996.

FOR FURTHER INFORMATION CONTACT:

Dave Keenan, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7139,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A final

rule airworthiness directive applicable

to General Electric (GE) CT7 series

turboprop and turboshaft engines, was

published in the Federal Register on

January 3, 1994 (59 FR 3). The following

correction is needed:

§ 39.13 [Corrected]

On page 4, in the first column, in the

heading above the Applicability Section

of AD 93–25–17, in the second line,

‘‘Docket No. 93–ANE–08’’ is corrected

to read ‘‘Docket No. 92–ANE–08’’.

Issued in Burlington, Massachusetts, on

May 16, 1996.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 96–13888 Filed 6–5–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–56–AD; Amendment

39–9652; AD 96–12–10]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 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 McDonnell

Douglas Model MD–11 series airplanes.

This action requires either the

application of a vapor sealant on the

back of the receptacle of the auxiliary

power unit (APU) power feeder cable; or

a visual inspection for gold-plating and

evidence of damage of the connector

contacts of the power feeder cable of the

APU generator, and various follow-on

actions. This amendment is prompted

by reports of burning and arcing of these

connector contacts. The actions

specified in this AD are intended to

reduce the potential for a fire hazard as

a result of such burning or arcing.

DATES: Effective June 21, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 21,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

August 5, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

56–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from

McDonnell Douglas Corporation, 3855

Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Department C1–L51 (2–60). This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Transport

Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (310) 627–5347; fax (310)

627–5210.

SUPPLEMENTARY INFORMATION: The FAA

has received several reports of burning

and arcing of the connector contacts

(pins/sockets) of the power feeder cable

of the auxiliary power unit (APU)

generator on Model MD–11 series

airplanes. This condition was indicated

by the inability to electrically power the

airplane using APU generator power. In

all cases, the connector and receptacle

were heat-damaged beyond repair. The

associated power feeder cables also

sustained heat damage. Investigation

revealed that the connector contacts had

been nickel plated during production.

These connector contacts must be gold

plated to be able to withstand the loads

applied. Burning and arcing of the

connector contacts of the power feeder

cable of the APU generator, if not

corrected, could result in potential fire

hazard.