5752 Federal Register / Vol. 62, No. 26 / Friday, February 7, 1997 / Rules and Regulations

pump with a new or serviceable fuel pump.

Prior to further flight following

accomplishment of the replacement, repeat

the insulation resistance test.

(iii) If all resistance measurements are

greater than or equal to 5 megohms, repeat

the visual inspection and insulation

resistance test within 5,000 flight hours or 18

months, whichever occur first.

(2) If any discrepancy is detected, prior to

further flight, replace the fuel pump with a

new or serviceable fuel pump, in accordance

with the applicable service bulletin. Prior to

further flight following accomplishment of

the replacement, perform an insulation

resistance test of the fuel pump wiring, in

accordance with the Accomplishment

Instructions of the applicable service

bulletin.

(i) If any resistance measurement is less

than or equal to 1 megohms, prior to further

flight, replace the fuel pump with a new or

serviceable fuel pump, in accordance with

the applicable service bulletin. Prior to

further flight following accomplishment of

the replacement, repeat the insulation

resistance test.

(ii) If all resistance measurements are

greater than 1 megohm, but one or more are

less than 5 megohms: Repeat the visual

inspection and insulation resistance test

within 500 flight hours, or replace the fuel

pump with a new or serviceable fuel pump.

Prior to further flight following

accomplishment of the replacement, repeat

the insulation resistance test.

(iii) If all resistance measurements are

greater than or equal to 5 megohms, repeat

the visual inspection and insulation

resistance test within 5,000 flight hours or 18

months, whichever occur first.

(b) Within 30 days after accomplishing the

initial visual inspection required by

paragraph (a) of this AD, or within 30 days

after the effective date of this AD, whichever

is later, submit a report of the inspection

results (both positive and negative findings)

to the Manager, Seattle Aircraft Certification

Office (ACO), 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056; telephone

(206) 227–2180; 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.

(c) 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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(d) 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.

(e) Except as specified in NOTE 2 of this

AD, the actions shall be done in accordance

with Boeing Service Bulletin 747–28A2194,

Revision 1, dated January 18, 1996 (for Model

747 series airplanes); or Boeing Service

Bulletin 757–28A0043, Revision 1, dated

January 18, 1996 (for Model 757 series

airplanes); as applicable. 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.

(f) This amendment becomes effective on

March 14, 1997.

Issued in Renton, Washington, on January

30, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–2854 Filed 2–6–97; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–NM–124–AD; Amendment

39–9920; AD 97–03–15]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9 and Model DC–9–

80 Series Airplanes, Model MD–88

Airplanes, and C–9 (Military) Series

Airplanes Equipped With BFGoodrich

Evacuation Slides

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–9 and Model DC–9–

80 series airplanes, Model MD–88

airplanes, and C–9 (military) series

airplanes, that requires modification of

the girt and firing lanyard stowage. This

amendment is prompted by reports of

in-cabin inflation of certain evacuation

slides due to the impingement of the

galley service cart on the slide girt and

firing lanyard. The actions specified by

this AD are intended to prevent

inadvertent inflation of the evacuation

slides inside the cabin, which could

contribute to injury of passengers and/

or flightcrew in the passenger cabin.

DATES: Effective March 14, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 14,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from BFGoodrich Company, Aircraft

Evacuation Systems, Department 7916,

Phoenix, Arizona 85040. 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 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:

Tracy Ton, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (310) 627–5352; fax (310)

627–5210.

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 McDonnell

Douglas Model DC–9 and Model DC–9–

80 series airplanes, Model MD–88

airplanes, and C–9 (military) series

airplanes was published in the Federal

Register on November 5, 1996 (61 FR

56919). That action proposed to require

modification of the girt and firing

lanyard stowage.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Both commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments 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 300

BFGoodrich evacuation slides installed

on 100 McDonnell Douglas Model DC–

9 and Model DC–9–80 series airplanes,

Model MD–88 airplanes, and C–9

(military) series airplanes of the affected

design in the worldwide fleet.

The FAA estimates that 180

BFGoodrich evacuation slides installed

on 60 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 2 work hours per slide to

accomplish the required actions, and
Federal Register / Vol. 62, No. 26 / Friday, February 7, 1997 / Rules and Regulations 5753

that the average labor rate is $60 per

work hour. Required parts will cost

approximately $75 per forward slide

and $100 per aft slide. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $195

per forward slide and $220 per aft slide.

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.

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.

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:

97–03–15 McDonnell Douglas: Amendment

39–9920. Docket 96–NM–124–AD.

Applicability: Model DC–9–10, –20, –30,

–40, and –50 series airplanes; Model DC–9–

81 (MD–81), DC–9–82 (MD–82), DC–9–83

(MD–83), DC–9–87 (MD–87) series airplanes,

Model MD–88 airplanes; and C–9 (military)

series airplanes; equipped with BFGoodrich

Evacuation Slides, as listed in BFGoodrich

Service Bulletin 25–280, Revision 2, dated

August 15, 1996; 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 in-cabin inflation of the

evacuation slides, which could contribute to

injury of passengers and/or flightcrew in the

passenger cabin, accomplish the following:

(a) Within 36 months after the effective

date of this AD, modify the girt and firing

lanyard stowage in accordance with

BFGoodrich Service Bulletin 25–280,

Revision 2, dated August 15, 1996.

(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, Los

Angeles 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, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles 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.

(d) The modification shall be done in

accordance with BFGoodrich Service

Bulletin 25–280, Revision 2, dated August

15, 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 BFGoodrich Company, Aircraft

Evacuation Systems, Department 7916,

Phoenix, Arizona 85040. Copies may be

inspected 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.

(e) This amendment becomes effective on

March 14, 1997.

Issued in Renton, Washington, on January

30, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–2853 Filed 2–6–97; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–NM–218–AD; Amendment

39–9921; AD 96–03–16]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 and MD–11F

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 and MD–11F

series airplanes, that currently requires,

among other things, repetitive visual

inspections to detect discrepancies of

the fuel pipe of the fuel transfer system

of the tail tank and associated mounting

bracket located in the aft fuselage

compartment. That AD was prompted

by reports of cracking or bending of the

fuel pipe mounting support and/or

attaching bracket in the aft fuselage

compartment due to a fuel pressure

surge that caused repetitive loading of

this area. This amendment adds a

requirement to install a restraint on the

tail tank fuel pipe, which would

terminate the repetitive visual

inspections. The actions specified by

this AD are intended to prevent such

cracking/bending, which could expose

the fuel pipe coupling O-ring. An

exposed O-ring could lose its sealing

effect and could allow a fuel leak in the

aft fuselage compartment, which would

present a fire hazard.

DATES: Effective March 14, 1997.

The incorporation by reference of

McDonnell Douglas Alert Service

Bulletin MD11–28A082, dated May 14,

1996, as listed in the regulations, was

approved previously by the Director of

the Federal Register as of July 24, 1996

(61 FR 35946, July 9, 1996).