Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations 63005

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 Galaxy Aerospace Corporation,

One Galaxy Way, Fort Worth Alliance

Airport, Fort Worth, Texas 76177. 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.

Effective Date

(e) This amendment becomes effective on

November 24, 2000.

Issued in Renton, Washington, on October

12, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26708 Filed 10–19–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–91–AD; Amendment

39–11936; AD 2000–21–04]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767

series airplanes, that requires

installation of sleeving on the 90-minute

auxiliary power unit (APU) standby

power feeder cable at body station 1351.

This amendment is prompted by a

report of damage to the 90-minute APU

standby power feeder cable caused by

shifting of unrestrained cargo containers

during flight. The actions specified by

this AD are intended to prevent damage

to the 90-minute APU standby power

feeder cable, which could result in

arcing between the standby power

feeder cable and the shroud of the APU

fuel line, penetration of the fuel line

shroud, and a consequent fire in the

main deck floor above the aft cargo

compartment.

DATES: Effective November 24, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Dennis Kammers, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2956; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Boeing

Model 767 series airplanes was

published in the Federal Register on

May 12, 2000 (65 FR 30553). That action

proposed to require installation of

sleeving on the 90-minute auxiliary

power unit (APU) standby power feeder

cable at body station 1351.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

Revise Paragraph (a) of the Proposal

The commenter notes that paragraph

(a) of the proposal states, ‘‘Within 6

months after the effective date of this

AD, install sleeving on the 90-minute

APU standby power feeder cable at body

station 1351 on the left side of the

airplane * * *’’ The commenter also

reiterates a portion of the Discussion

section that reads, ‘‘The cargo

containers damaged the 90-minute APU

standby power feeder cable and the

cabin floor support beam at body station

1351, on the right side of the airplane.

Investigation revealed evidence of

arcing between the cable and the beam.’’

The commenter inquires as to why there

is no proposed requirement for sleeving

of the cable on the right-hand side of the

airplane. The commenter further states

that even though the fuel line is not on

the right-hand side of the airplane, any

cable arcing may still become a

potential hazard and should be

addressed. Therefore, the commenter

requests that paragraph (a) of the

proposal be revised to read, ‘‘* * * on

the left and right sides of the airplane

* * *’’

The FAA does not concur with the

commenter’s request. Accomplishment

of the corrective action of the APU

standby power feeder cable, as required

by paragraph (a) of the final rule, is to

reduce the fire hazard associated with

an unrestrained cargo container

impacting the cable. Damaging the cable

in the region specified could cause

arcing against the APU fuel line shroud,

which could penetrate the fuel line and

result in a cabin fire. The arcing damage

between the APU standby power feeder

cable and the cargo floor beam, which

was reported in the initial investigation,

although serious in nature, was not

deemed an unsafe condition or a threat

to continued safe operation of the

airplane. Further investigation

determined that no structural or fire

concerns resulted from the incident.

Therefore, sleeving of the standby

power feeder cable is necessary only in

areas where damage to the cable may

cause arcing to the APU fuel line. No

change to paragraph (a) of the final rule

is necessary in this regard.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 151

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

14 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 1 work hour per airplane

to accomplish the required action, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the AD on U.S. operators

is estimated to be $840, or $60 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

The regulations adopted herein will

not have a substantial direct effect on

the States, on the relationship between

the national Government and the States,

or on the distribution of power and

63006 Federal Register / Vol. 65, No. 204 / Friday, October 20, 2000 / Rules and Regulations

responsibilities among the various

levels of government. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–21–04 Boeing: Amendment 39–11936.

Docket 2000–NM–91–AD.

Applicability: Model 767 series airplanes;

as listed in Boeing Alert Service Bulletin

767–24A0126, dated February 24, 2000;

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 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 damage to the 90-minute

auxiliary power unit (APU) standby power

feeder cable, which could result in arcing

between the standby power feeder cable and

the shroud of the APU fuel line, penetration

of the fuel line shroud, and a consequent fire

in the main deck floor above the aft cargo

compartment, accomplish the following:

Installation of Sleeving

(a) Within 6 months after the effective date

of this AD, install sleeving on the 90-minute

APU standby power feeder cable at body

station 1351 on the left side of the airplane,

in accordance with Boeing Alert Service

Bulletin 767–24A0126, dated February 24,

2000.

Alternative Methods of Compliance

(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.

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.

Special Flight Permits

(c) Special flight permits may be issued in

accordance with §§ 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.

Incorporation by Reference

(d) The installation shall be done in

accordance with Boeing Alert Service

Bulletin 767–24A0126, dated February 24,

2000. 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.

Effective Date

(e) This amendment becomes effective on

November 24, 2000.

Issued in Renton, Washington, on October

12, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26707 Filed 10–19–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–98–AD; Amendment

39–11938; AD 2000–21–06]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes Equipped

with Pratt & Whitney (PW) JT9D–7Q

and JT9D–7Q3 Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747

series airplanes, that requires a detailed

visual inspection to detect evidence of

wear or contact between the precooler

support fitting and link assembly; and

rework and reidentification of the

fitting. This amendment is prompted by

a report of rupturing of a diffuser case

on a PW JT9D–7Q engine due to

cracking in the outer pressure wall in

the rear skirt area. The actions specified

by this AD are intended to prevent

contact between the precooler support

link and the precooler support fitting,

which could contribute to an

uncontained failure of the diffuser case

and damage to the airplane.

DATES: Effective November 24, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Dionne Krebs, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2250; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Boeing

Model 747 series airplanes was

published in the Federal Register on