Federal Register / Vol. 61, No. 83 / Monday, April 29, 1996 / Proposed Rules 18707

series airplanes (2 slides per airplane) of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour per slide to

accomplish the proposed actions, and

that the average labor rate is $60 per

work hour. Required parts would cost

approximately $84 per slide. Based on

these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $21,600, or $144 per

slide.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

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

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Boeing: Docket 95–NM–218–AD.

Applicability: Model 747–400 series

airplanes equipped with BFGoodrich

Evacuation Slide/Rafts at door 5; having

slide/raft assembly part number

7A1469–1, –2, –3, –4, –7, –8, –9, –10,

–11, or –12 (all unit 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

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 failure of the door 5 evacuation

slide/raft to deploy properly, which could

contribute to injury of passengers on the slide

and could delay or impede the evacuation of

passengers during an emergency, accomplish

the following:

(a) Within 36 months after the effective

date of this AD, modify the door 5 evacuation

slide/raft in accordance with BFGoodrich

Service Bulletin 7A1469–25–283, dated

November 6, 1995.

Note 2: Modification previous to the

effective date of this AD in accordance with

Boeing Alert Service Bulletin 747–25A3096,

which references BFGoodrich Service

Bulletin 7A1469–25–283, dated November 6,

1995, is considered acceptable for

compliance with the modification

requirements of paragraph (a) of this AD.

(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 3: 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.

Issued in Renton, Washington, on April 23,

1996.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–10506 Filed 4–26–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–NM–49–AD]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Jetstream Model 4101 airplanes, that

currently requires inspection to

determine the number of hours time-inservice on the landing gear control unit,

and modification of the cable (electrical

wiring circuit) of the landing gear

control unit. That AD was prompted by

a report of failure of a micro-switch in

the landing gear control unit. This

action would require installation of a

new landing gear control unit. This

action also would expand the

applicability of the existing AD to

include additional airplanes. The

actions specified by the proposed AD

are intended to prevent uncommanded

retraction of a landing gear, which could

adversely affect airplane controllability.

DATES: Comments must be received by

June 10, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

49–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Jetstream Aircraft, Inc., P.O. Box 16029,

Dulles International Airport,

Washington, DC 20041–6029. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,
18708 Federal Register / Vol. 61, No. 83 / Monday, April 29, 1996 / Proposed Rules

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

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, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal 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 Number 96–NM–49–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

96–NM–49–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On May 18, 1995, the FAA issued AD

95–09–03, amendment 39–9241 (60 FR

28035, May 30, 1995), applicable to

certain Jetstream Model 4101 airplanes,

to require inspection to determine the

number of hours time-in-service on the

landing gear control unit, and

modification of the cable (electrical

wiring circuit) of the landing gear

control unit. That action was prompted

by a report of failure of a micro-switch

in the landing gear control unit. The

requirements of that AD are intended to

prevent uncommanded retraction of a

landing gear, which could adversely

affect airplane controllability.

In the preamble to AD 95–09–03, the

FAA indicated that modification

(Jetstream Modification JM41490) of the

cable (electrical wiring circuit) of the

landing gear control unit was

considered ‘‘interim action’’ and that

further rulemaking action was being

considered. As a follow-on action from

that determination, the FAA is now

proposing additional, final action.

Explanation of Relevant Service

Information

Since the issuance of AD 95–09–03,

Jetstream has issued Service Bulletin

J41–32–044, dated September 22, 1995,

which describes procedures for

installation of a new improved landing

gear control unit, identified as

Modification JM41501. The procedures

involve installing a new landing gear

control unit that has revised switching.

The new switching will prevent

uncommanded landing gear retractions

caused by spurious signals from single

switch failures.

The installation also involves revising

certain wiring, which includes

removing cables installed in accordance

with Jetstream Modification JM41490.

Additionally, the installation involves

reallocating a spare pin in the airplane

connector to prevent the operation of

the old landing gear control unit in the

event that one is inadvertently installed.

Accomplishment of Modification

JM41501 will positively address the

unsafe condition identified as

uncommanded retraction of a main

landing gear.

In addition, the effectivity listing of

this service bulletin includes additional

airplanes that were not previously

affected by AD 95–09–03, and removes

certain others.

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, classified this

service bulletin as mandatory in order to

assure the continued airworthiness of

these airplanes in the United Kingdom.

FAA’s Conclusions

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the CAA has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of the Requirements of the

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would

supersede AD 95–09–03. For those

airplanes subject to AD 95–09–03, it

would continue to require an inspection

to determine the number of hours timein-service on the landing gear control

unit, and modification of the cable

(electrical wiring circuit) of the landing

gear control unit. For those airplanes

and certain others, it would require

installation of a new improved landing

gear control unit. The actions would be

required to be accomplished in

accordance with the Jetstream service

bulletin described previously.

The applicability of the proposed AD

would include additional airplanes that

have been identified to be subject to the

same unsafe condition (an included in

the effectivity listing of the Jetstream

service bulletin).

Cost Impact

There are approximately 44 Jetstream

Model 4101 airplanes of U.S. registry

that would be affected by this proposed

AD.

The actions that are currently

required by AD 95–09–03, and retained

in this proposed AD, take approximately

7 work hours per airplane to

accomplish, at an average labor rate of

$60 per work hour. The required parts

are provided by the manufacturer at no

cost to the operator. Based on these

figures, the cost impact on U.S.

operators of the actions currently

required is estimated to be $18,480, or

$420 per airplane. The FAA has been

advised that all affected U.S. operators

have accomplished these requirements;

therefore, there is no future cost impact

of these requirements on current U.S.

operators of these airplanes.

The new installation that would be

required by this proposed AD would

take approximately 6 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would be provided at no

cost to the operator. Based on these

figures, the cost impact on U.S.

operators of the proposed requirements

of this AD is estimated to be $15,840, or

$360 per airplane. This cost impact

figure is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.
Federal Register / Vol. 61, No. 83 / Monday, April 29, 1996 / Proposed Rules 18709

Regulatory Impact

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

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

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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

removing amendment 39–9241 (60 FR

28035, May 30, 1995), and by adding a

new airworthiness directive (AD), to

read as follows:

Jetstream Aircraft Limited: Docket 96–NM–

49–AD. Supersedes AD 95–09–03,

Amendment 39–9241.

Applicability: Model 4101 airplanes,

constructor numbers 41001 through 41073

inclusive; 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 (d) 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 uncommanded retraction of the

landing gear, which can adversely affect

airplane controllability, accomplish the

following:

(a) For airplanes having constructor

numbers 41001 through 41046 inclusive, and

41048 through 41052 inclusive; equipped

with either landing gear control unit part

number 717701–1 or 717701–1 Mod A:

Within 8 hours time-in-service after June 14,

1995 (the effective date of AD 95–09–03,

amendment 39–9241), perform an inspection

to determine the number of hours time-inservice on the landing gear control unit, in

accordance with Jetstream Alert Service

Bulletin J41–A32–042, dated April 13, 1995.

(1) For those airplanes on which the

control unit has accumulated less than 200

hours time-in-service: Prior to further flight,

modify the cable (electrical wiring circuit) of

the landing gear control unit in accordance

with the alert service bulletin.

(2) For those airplanes on which the

control unit has accumulated 200 hours or

more time-in-service: Within 50 hours timein-service or within 7 days after June 14,

1995 (the effective date of AD 95–09–03,

amendment 39–9241), whichever occurs

earlier, modify the cable (electrical wiring

circuit) of the landing gear control unit in

accordance with the alert service bulletin.

(b) For airplanes having constructor

numbers 41001 through 41073 inclusive:

Within 6 months after the effective date of

this AD, install a new improved landing gear

control unit and modify the wiring, in

accordance with Jetstream Service Bulletin

J41–32–044, dated September 22, 1995.

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

person shall install a landing gear control

unit having part number 717701–1 or

717701–1 Mod A, on any airplane.

(d) 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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Manager, Standardization

Branch, ANM–113.

(e) 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.

Issued in Renton, Washington, on April 23,

1996.

S. R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–10505 Filed 4–26–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–237–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Airbus Model A320 series

airplanes. This proposal would require

an inspection to detect damage to the

electrical wiring of the fuel tank of the

wings and to verify if the proper P-clip

is installed in the electrical wiring. The

proposed AD would also require refitting any proper P-clip, replacing any

improper P-clip with a new P-clip, and

repairing damaged electrical wiring.

This proposal is prompted by a report

that incorrect P-clips were found

installed in the electrical wiring of the

fuel system on these airplanes. The

actions specified by the proposed AD

are intended to ensure that the proper

P-clips are installed. Improper P-clips

could fail to adequately safeguard the

fuel tank of the wing against a lightning

strike, which could result in electrical

arcing and resultant fire.

DATES: Comments must be received by

June 10, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

237–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Charles Huber, Aerospace Engineer,