26088 Federal Register / Vol. 61, No. 102 / Friday, May 24, 1996 / Rules and Regulations

[FR Doc. 96–12884 Filed 5–23–96; 8:45 am]

BILLING CODE 6714–01–C
Federal Register / Vol. 61, No. 102 / Friday, May 24, 1996 / Rules and Regulations 26089

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–110–AD; Amendment

39–9631; AD 96–11–06]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–7 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain de Havilland

Model DHC–7 series airplanes, that

requires modification of the emergency

lights circuitry. This amendment is

prompted by reports of the emergency

lights turning on inadvertently due to

voltage spikes from other equipment;

and reports that the existing emergency

light switch arrangement allows the

flight compartment and flight

attendant’s panel switches to override

each other. The actions specified by this

AD are intended to prevent such failures

of the emergency light systems, which

could prevent the use of the emergency

lights in the event of an emergency.

DATES: Effective June 28, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 28,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Bombardier

Regional Aircraft Division, Garratt

Boulevard, Downsview, Ontario M3K

1Y5, Canada. 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, Engine and

Propeller Directorate, New York Aircraft

Certification Office, 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.

FOR FURTHER INFORMATION CONTACT:

Wing Chan, Aerospace Engineer,

Systems and Flight Test Branch, ANE–

172, FAA, Engine and Propeller

Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7511; fax

(516) 568–2716.

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 de

Havilland Model DHC–7 series

airplanes was published in the Federal

Register on January 9, 1996 (61 FR 636).

That action proposed to require

modification of the emergency lights

circuitry.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

Two commenters support the

proposed rule.

Request To Include an Additional

Modification Requirement

One commenter requests that

proposed rule be revised to include a

requirement to install Modification 7/

2622. This modification is described in

de Havilland Service Bulletin 7–33–23

and also affects the emergency lighting

system. The commenter mentions that

this modification is mandated by

Canadian airworthiness directive CF

95–03. The commenter states that, by

including a requirement in the proposal

to install Modification 7/2622, safety

would be enhanced and unnecessary

requests for alternate means of

compliance would be avoided.

The FAA does not concur with the

commenter’s request to revise this AD

action to require installation of

Modification 7/2622. The FAA finds

that, although the unsafe condition that

prompted the Transport Canada

airworthiness action to mandate that

modification concerns the failure of the

emergency lighting systems, the cause of

that failure is different from the causes

of failure addressed in this AD.

Additionally, the modification affects

some airplanes other than those

identified in the applicability of this

AD.

However, the FAA is considering

separate rulemaking action to address

the installation of Modification 7/2622

on applicable airplanes.

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

The FAA estimates that 14 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 8

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will be provided at no

cost to the operators. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $6,720,

or $480 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.

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.
26090 Federal Register / Vol. 61, No. 102 / Friday, May 24, 1996 / Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–11–06 De Havilland, Inc.: Amendment

39–9631. Docket 95–NM–110–AD.

Applicability: Model DHC–7 series

airplanes, serial numbers 3 through 27

inclusive, on which de Havilland

Modification No. 7/1697 has not been

installed; 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 (c) 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 failure of the emergency

lighting system due to voltage spikes from

other equipment or due to inadvertent

override of the emergency lighting switches,

accomplish the following:

(a) Within 6 months after the effective date

of this AD, modify the emergency lights

circuitry by accomplishing de Havilland

Modification No. 7/1697 (Emergency LightsRevised Switching Logic), in accordance with

the Accomplishment Instructions of de

Havilland Service Bulletin No. 7–33–7, dated

October 17, 1980.

(b) As of the effective date of this AD, no

person shall install an emergency light

switch, part number MS24659–21A, on any

airplane subject to this AD.

(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, 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York 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) The modification shall be done in

accordance with de Havilland Service

Bulletin No. 7–33–7, dated October 17, 1980.

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., Bombardier Regional

Aircraft Division, Garratt Boulevard,

Downsview, Ontario M3K 1Y5, 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 11581; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(f) This amendment becomes effective on

June 28, 1996.

Issued in Renton, Washington, on May 15,

1996.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–12729 Filed 5–23–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–197–AD; Amendment

39–9632; AD 96–11–07]

RIN 2120–AA64

Airworthiness Directives; Learjet

Model 31 and 35A Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Learjet Model 31

and 35A airplanes, that requires

replacement of two segments of 16

American Wire Gauge (AWG) wire with

8 AWG wire at the connector that is

connected to the auxiliary cabin heater

relay box. This amendment is prompted

by a report that two segments of the 16

AWG wire in the auxiliary cabin heater

that were spliced during production do

not provide adequate current-carrying

capacity. The actions specified by this

AD are intended to prevent electrical

arcing and a subsequent fire hazard that

could result from wiring with

inadequate current-carrying capacity.

DATES: Effective June 28, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 28,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Learjet, Inc., One Learjet Way,

Wichita, Kansas 67209–2942. 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,

Wichita Aircraft Certification Office,

Small Airplane Directorate, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dale

Bleakney, Aerospace Engineer, Flight

Test Branch, ACE–117W, FAA, Small

Airplane Directorate, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas; telephone (316) 946–

4135; fax (316) 946–4407.

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 Learjet

Model 31 and 35A airplanes was

published in the Federal Register on

March 7, 1996 (61 FR 9119). That action

proposed to require replacement of two

segments of 16 AWG wire with 8 AWG

wire at the P190 connector that is

connected to the E33 auxiliary cabin

heater relay box.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 52 Learjet

Model 31 and 35A airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 44 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 4 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will be supplied by the

manufacturer at no cost to the operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $10,560, or $240 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.

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