Federal Register / Vol. 65, No. 234 / Tuesday, December 5, 2000 / Proposed Rules 75879

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Note 3: An inspection per Airbus Service

Bulletin A330–29A3073, dated January 18,

2000 (for Model A330 series airplanes), or

A340–29A4058, dated January 20, 2000 (for

Model A340 series airplanes), is acceptable

for compliance with the requirements of

paragraph (a) of this AD.

Note 4: The Airbus service bulletins refer

to Le Bozec Filtration & Systems Service

Bulletin 4020Q8–29–03, dated December 17,

1999, as an additional source of service

information for accomplishment of the

actions specified by this AD.

Spares

(b) As of the effective date of this AD, you

may not install any air pressurization unit

having P/N 4020 Q8–3 on any airplane,

unless all actions have been accomplished

for that part in accordance with the

requirements of this AD.

Alternative Methods of Compliance

(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, Manager,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(d) 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.

Note 6: The subject of this AD is addressed

in French airworthiness directives 2000–

138–118(B) and 2000–139–143(B), both dated

March 22, 2000.

Issued in Renton, Washington, on

November 29, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30951 Filed 12–4–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–224–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (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 all British

Aerospace (Jetstream) Model 4101

airplanes, that currently requires

repetitive inspections to detect loose or

migrated levers of the elevator cable

tension regulators, and replacement of

the regulator assembly with a new

assembly, if necessary. This action

would require modification of the

elevator cable tension regulator lever

assembly, terminating the repetitive

inspections. The proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent the elevator

cable tension regulator from becoming

detached from the splined shaft of the

assembly, which could result in

difficulty adjusting the elevators,

leading to reduced controllability of the

airplane.

DATES: Comments must be received by

January 4, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

224–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. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-nprmcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–224–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

the proposed AD may be obtained from

British Aerospace Regional Aircraft

American Support, 13850 Mclearen

Road, Herndon, Virginia 20171. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT: Dan

Rodina, Aerospace Engineer, ANM–116,

FAA, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2125; fax (425) 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 action may be changed in light

of the comments received.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–224–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–114, Attention: Rules Docket No.

75880 Federal Register / Vol. 65, No. 234 / Tuesday, December 5, 2000 / Proposed Rules

2000–NM–224–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On December 17, 1999, the FAA

issued AD 99–26–18, amendment 39–

11478 (64 FR 72531, December 28,

1999) applicable to all British Aerospace

(Jetstream) Model 4101 airplanes, to

require repetitive inspections to detect

loose or migrated levers of the elevator

cable tension regulators, and

replacement of the regulator assembly

with a new assembly, if necessary. That

action was prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The

requirements of that AD are intended to

detect and correct loose or migrated

regulator levers of the elevator cable

tension regulators, which could result in

reduced controllability of the airplane.

Actions Since Issuance of Previous Rule

In the preamble to AD 99–26–18, the

FAA indicated that the action required

by that AD was considered ‘‘interim

action’’ until final action was identified,

at which time further rulemaking might

be considered. Since the issuance of AD

99–26–18, British Aerospace has issued

Jetstream Service Bulletin J41–27–059,

dated May 31, 2000, which describes

procedures for modification of the

elevator cable tension regulator

assembly, which eliminates the need for

repetitive inspections of the regulator

assembly. The modification involves

removing the existing bolt, nut, cotter

pin, and washers and installing a new

locking clip, sleeves, bolt, nut, cotter

pin, and washers. Accomplishment of

the actions specified in the service

bulletin is intended to adequately

address the identified unsafe condition.

Jetstream Service Bulletin J41–27–059

refers to Pacific Scientific Service

Bulletin 25–1128, dated April 15, 2000,

as an additional source of service

information for accomplishment of the

modification of the elevator cable

tension regulators. Pacific Scientific

Company has designed a secondary

locking clip, which, when installed

under the bolt, will prevent the elevator

cable tension regulator from becoming

detached from the splined shaft of the

regulator assembly.

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, has classified the

Jetstream service bulletin as mandatory

and issued British airworthiness

directive 006–05–2000 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 Requirements of

Proposed AD

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 99–26–18 to continue to

require inspection of the elevator cable

tension regulator lever assembly and to

require modification of the elevator

cable tension regulators. The

modification would be required to be

accomplished in accordance with

Jetstream Service Bulletin J41–27–059.

Cost Impact

There are approximately 57 airplanes

of U.S. registry that would be affected

by this proposed AD. The repetitive

inspection that is currently required by

AD 99–26–18 takes approximately 2

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the currently required actions

on U.S. operators is estimated to be

$120 per airplane, per inspection cycle.

The modification that is proposed in

this AD would take approximately 6

work hours per airplane to accomplish

at an average labor rate of $60 per work

hour. There would be no charge for

required parts. Based on these figures,

the cost impact of the proposed

requirements of this AD on U.S.

operators is estimated to be $20,520, or

$360 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished 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 proposed herein

would 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 responsibilities among the

various levels of government. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

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 39–11478 (64 FR

72531, December 28, 1999), and by

adding a new airworthiness directive

(AD), to read as follows:

British Aerospace Regional Aircraft

[Formerly Jetstream Aircraft Limited

British Aerospace (Commercial Aircraft)

Limited]: Docket 2000–NM–224–AD.

Supersedes AD 99–26–18, Amendment

39–11478.

Applicability: All Model Jetstream 4101

airplanes, 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 (e) of this AD.

Federal Register / Vol. 65, No. 234 / Tuesday, December 5, 2000 / Proposed Rules 75881

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 the elevator cable tension

regulators from becoming detached from the

splined shaft of the assembly, which could

result in difficulty adjusting the elevators,

leading to reduced controllability of the

airplane, accomplish the following:

Restatement of Certain Actions Required by

AD 99–26–18

Inspection

(a) Within 7 weeks after February 1, 2000

(the effective date of AD 99–26–18,

amendment 39–11478), perform a detailed

visual inspection of the elevator cable

tension regulator lever assembly to detect

discrepancies (including looseness and

migration along the splines of the elevator

cable tension regulator assembly), in

accordance with Jetstream Alert Service

Bulletin J41–A–27–053, dated September 14,

1999. Repeat the inspection thereafter at

intervals not to exceed 1,500 flight hours

until accomplishment of paragraph (c) of this

AD.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

New Actions Required by This AD

Modification

(b) If any discrepancy is detected during

any inspection required by paragraph (a) of

this AD: Prior to further flight, perform the

requirements of paragraph (c) of this AD.

(c) Except as required by paragraph (b) of

this AD: Within 12 months after the effective

date of this AD, modify the elevator cable

tension regulators in accordance with

Jetstream Service Bulletin J41–27–059, dated

May 31, 2000.

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

person shall install any elevator cable tension

regulator lever assembly, unless that

assembly has been modified in accordance

with the requirements of paragraph (c) of this

AD.

Alternative Methods of Compliance

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(f) 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.

Note 4: The subject of this AD is addressed

in British airworthiness directive 006–05–

2000.

Issued in Renton, Washington, on

November 29, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30950 Filed 12–4–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–275–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 and 767 Series

Airplanes Equipped With General

Electric CF6–80C2 Series Engines

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 Boeing Model 747–400 and 767

series airplanes. This proposal would

require modification of the core cowl

assemblies of the engines. This action is

necessary to prevent failure of the core

cowl latches during an engine fire, and

consequent in-flight separation of an

engine core cowl and its strut fire

barrier from the airplane. This action is

intended to address the identified

unsafe condition.

DATES: Comments must be received by

January 19, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

275–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. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-nprmcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–275–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

the proposed rule may be obtained from

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Sulmo Mariano, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2686; fax (425) 227–1181.

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 action may be changed in light

of the comments received.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

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