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

75882 Federal Register / Vol. 65, No. 234 / Tuesday, December 5, 2000 / Proposed Rules

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–275–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.

2000–NM–275–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA received a report indicating

an in-flight engine fire occurred on a

Model 747–400 series airplane powered

by General Electric CF6–80C2 series

engines. The fire was caused by a fuel

leak in the Integrated Drive Generator

fuel/oil heat exchanger and was ignited

by fuel vapors coming in contact with

the hot turbine case. The fire was

located directly under the core cowls

and caused significant damage to the

cowls, which weakened the aluminum

structure supporting the steel latches

that hold the core cowls closed.

Opening of the core cowls during an

engine fire breaches the engine fire

containment design features and could

allow the engine fire to spread to the

strut and wing. (Model 767 series

airplanes powered by General Electric

CF6–80C2 series engines have a similar

design.) Such conditions, if not

corrected, could result in separation of

an engine core cowl and its strut fire

barrier from the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletins 747–71–2285

(for Model 747–400 series airplanes)

and 767–71–0088 (for Model 767 series

airplanes), both dated October 8, 1998,

which describe procedures for

modification of the left- and right-hand

core cowl assemblies of the engines. The

modification includes, but is not limited

to, replacement of the aluminum

forward and extension frames located

between the forward hinge and the latch

in each core cowl with inconel frames

that provide fireproof reinforcement to

the core cowl latches. The Boeing

service bulletins reference ROHR

Service Bulletin TBC/80C2–NAC–71–

028, dated August 1, 1998, as an

additional source of service information

for accomplishment of the modification.

Accomplishment of the actions

specified in the service bulletins is

intended to adequately address the

identified unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require accomplishment of the actions

specified in the service bulletins

described previously, except as

discussed below.

Difference Between Service Bulletins

and This Proposed AD

Operators should note that this

proposed AD would require

modification of the core cowl

assemblies of the engines to be

accomplished within 24 months after

the effective date of this AD. The service

bulletins recommend that this

modification should be accomplished

‘‘as soon as manpower and facilities are

available.’’ But in developing an

appropriate compliance time for the

proposed modification, the FAA

considered not only the manufacturer’s

recommendation and the degree of

urgency associated with addressing the

subject unsafe condition, but also the

average utilization of the affected fleet

and the time necessary to perform the

modification. The FAA has determined

that 24 months represents an

appropriate interval of time allowable

wherein the modification can be

accomplished during scheduled

airplane maintenance and an ample

number of required parts will be

available for modification of the U.S.

fleet within the proposed compliance

period. The FAA also finds that such a

compliance time will not adversely

affect the safety of the affected

airplanes.

Cost Impact

There are approximately 563

airplanes of the affected design in the

worldwide fleet.

The FAA estimates that 14 Model

747–400 series airplanes of U.S. registry

would be affected by this proposed AD,

that it would take approximately 168

work hours (42 per engine) per airplane

to accomplish the proposed

modification, and that the average labor

rate is $60 per work hour. Required

parts would cost approximately $84,732

($21,183 per engine) per airplane. Based

on these figures, the cost impact of the

modification proposed by this AD on

U.S. operators is estimated to be

$1,327,368, or $94,812 per airplane.

The FAA estimates that 64 Model 767

series airplanes of U.S. registry would

be affected by this proposed AD, that it

would take approximately 84 work

hours (42 per engine) per airplane to

accomplish the proposed modification,

and that the average labor rate is $60 per

work hour. Required parts would cost

approximately $42,366 ($21,183 per

engine) per airplane. Based on these

figures, the cost impact of the

modification proposed by this AD on

U.S. operators is estimated to be

$3,033,984 or $47,406 per airplane.

The cost impact figures discussed

above are 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 proposed 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 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

Federal Register / Vol. 65, No. 234 / Tuesday, December 5, 2000 / Proposed Rules 75883

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

adding the following new airworthiness

directive:

Boeing: Docket 2000–NM–275–AD.

Applicability: Model 747–400 and 767

series airplanes equipped with General

Electric CF6–80C2 series engines, certificated

in any category; as listed in Boeing Service

Bulletins 747–71–2285 or 767–71–0088, both

dated October 8, 1998.

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 per

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 core cowl latches

during an engine fire, and consequent inflight separation of an engine core cowl and

its strut fire barrier from the airplane,

accomplish the following:

Modification

(a) Within 24 months after the effective

date of this AD: Modify the left- and righthand core cowl assemblies of the engines per

the Accomplishment Instructions of Boeing

Service Bulletin 747–71–2285 (for Model

747–400 series airplanes) or 767–71–0088

(for Model 767 series airplanes), both dated

October 8, 1998.

Note 2: The Boeing service bulletins

reference ROHR Service Bulletin TBC/80C2–

NAC–71–028, dated August 1, 1998, as an

additional source of service information for

accomplishment of the modification.

Spares

(b) As of 6 months after the effective date

of this AD, no one may install an aluminum

core cowl assembly, part number 224–2301–

513 (left-hand) or 224–2302–539 (right-hand),

on any airplane.

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, Seattle

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Operations

Inspector or Principal Maintenance

Inspector, as applicable, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permit

(d) Special flight permits may be issued per

§§ 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

November 29, 2000.

Ali Bahrami,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30949 Filed 12–4–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–28–AD]

RIN 2120–AA64

Airworthiness Directives; Fairchild

Aircraft, Inc. Models SA226 and SA227

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking (NPRM);

Reopening of the comment period.

SUMMARY: This document proposes to

revise an earlier proposed airworthiness

directive (AD) that would apply to

certain Fairchild Aircraft SA226 and

SA227 series airplanes. The earlier

NPRM would have required you to

replace the brake shuttle valves with

parts of improved design and install a

shield over the hydraulic lines. The

earlier NPRM resulted from a report of

a wheel brake system malfunction

caused by a faulty brake shuttle valve on

an affected airplane. Evaluation of the

public comments on the NPRM reveals

the need to also include airplanes that

have an anti-skid system in the

Applicability of the proposed AD. In

addition, we are proposing a

requirement of replacing the rubber fuel

hose with a metal device for the SA226

series airplanes. Since these actions

impose an additional burden over that

proposed in the NPRM, we are

reopening the comment period to allow

the public the chance to comment on

these additional actions.

DATES: The Federal Aviation

Administration (FAA) must receive

comments on or before January 11,

2001.

ADDRESSES: Submit comments in

triplicate to FAA, Central Region, Office

of the Regional Counsel, Attention:

Rules Docket No. 2000–CE–28–AD, 901

Locust, Room 506, Kansas City,

Missouri 64106. Comments may be

inspected at this location between 8

a.m. and 4 p.m., Monday through

Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Fairchild Aircraft, Inc., P.O. Box

790490, San Antonio, Texas 78279–

0490; telephone: (210) 824–9421;

facsimile: (210) 820–8609. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT:

Werner Koch, Aerospace Engineer,

FAA, Airplane Certification Office, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150; telephone: (817) 222–5133;

facsimile: (817) 222–5960.

SUPPLEMENTARY INFORMATION:

Comments Invited

How Do I Comment on the Proposed

AD?

The FAA invites comments on this

proposed rule. You may submit

whatever written data, views, or

arguments you choose. You need to

include the rule’s docket number and

submit your comments in triplicate to

the address specified under the caption

ADDRESSES. The FAA will consider all

comments received on or before the

closing date. We may amend the

proposed rule in light of comments

received. Factual information that

supports your ideas and suggestions is

extremely helpful in evaluating the

effectiveness of the proposed AD action

and determining whether we need to

take additional rulemaking action.

Are There Any Specific Portions of the

Proposed AD I Should Pay Attention to?

The FAA specifically invites

comments on the overall regulatory,

economic, environmental, and energy

aspects of the proposed rule that might

suggest a need to modify the rule. You

may examine all comments we receive

before and after the closing date of the

rule in the Rules Docket. We will file a

report in the Rules Docket that

summarizes each FAA contact with the

public that concerns the substantive

parts of the proposed AD.

We are re-examining the writing style

we currently use in regulatory