Federal Register / Vol. 62, No. 190 / Wednesday, October 1, 1997 / Proposed Rules 51385

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–140–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model Hawker 1000 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 Raytheon Model Hawker 1000

series airplanes. This proposal would

require modifying the aft core cowl

nozzles of the engine nacelles. This

proposal is prompted by a report

indicating that the sealant on the core

cowl nozzles may extend higher than

the forward flange of the core cowl

nozzles, which could result in contact

between the cowl sealant surface and

the lever of the engine mechanical overspeed control system. The actions

specified by the proposed AD are

intended to prevent such contact, which

could cause result in the over-speed

system to function improperly and

consequent engine structural failure.

DATES: Comments must be received by

October 27, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

140–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

Raytheon Aircraft Company, Manager,

Service Engineering, Hawker Customer

Support Department, P.O. Box 85,

Wichita, Kansas 67201–0085. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW, Renton,

Washington; or at the FAA, Small

Airplane Directorate, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT:

Randy Griffith, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas

67209; telephone (316) 946–4145; fax

(316) 946–4407.

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 No. 97–NM–140–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.

97–NM–140–AD, 1601 Lind Avenue

SW, Renton, Washington 98055–4056.

Discussion

The FAA received a report indicating

that sealant, which is applied on a

portion of the aft core cowl nozzle of the

engine nacelle to provide fluid drainage,

may extend higher than the forward

flange of the core cowl nozzle. This may

allow the lever of the mechanical engine

over-speed system to contact the cowl

sealant surface. This condition, if not

corrected, could cause the over-speed

system to function improperly and

consequent engine structural failure.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Raytheon Service Bulletin SB.71–48–

25F021B, dated May 20, 1997, which

describes procedures for modification of

the aft core cowl nozzles of the left- and

right-hand engine nacelles. (The service

bulletin references Nordam Hawker

1000 Service Bulletin PW300 71–9,

dated April 29, 1995, as the appropriate

source of service information for

accomplishment of the modification.)

The modification involves replacing the

sealant on the aft core cowl nozzle with

a filler made from aluminum.

Accomplishment of the modification

will prevent contact between the surface

of the core cowl sealant and the lever of

the engine mechanical over-speed

control system.

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 modification of the aft core cowl

nozzles of the left- and right-hand

engine nacelles. The actions would be

required to be accomplished in

accordance with the service bulletin

described previously.

Cost Impact

There are approximately 52 Model

Hawker 1000 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 14 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 4 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would be provided by the manufacturer

at no cost to operators. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$3,360, or $240 per airplane.

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.
51386 Federal Register / Vol. 62, No. 190 / Wednesday, October 1, 1997 / Proposed Rules

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

adding the following new airworthiness

directive:

Raytheon Aircraft Company (Formerly

Raytheon Aircraft Corporation; Beech

Aircraft Corporation; Raytheon Corporate

Jets, Inc.; British Aerospace, PLC;

deHavilland; Hawker Siddeley): Docket

97–NM–140–AD.

Applicability: Model Hawker 1000 series

airplanes, serial numbers 258151, 258159,

and 259003 through 259052 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 (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 contact between the cowl

sealant surface and the lever of the engine

mechanical over-speed control system, which

could cause the over-speed system to

function improperly and consequent engine

structural failure, accomplish the following:

(a) Within 150 flight hours or 3 months

after the effective date of this AD, whichever

occurs first, modify the aft core cowl nozzles

of the left-and right-hand engine nacelles in

accordance with Raytheon Service Bulletin

SB.71–48–25F021B, dated May 20, 1997.

Note 2: The Raytheon service bulletin

references Nordam Hawker 1000 Service

Bulletin PW300 71–9, dated April 29, 1995,

as the appropriate source of service

information for accomplishment of the

modification.

(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, Wichita

Aircraft Certification Office (ACO), FAA,

Small 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, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita 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

September 25, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–25975 Filed 9–30–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–146–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

adoption of a new airworthiness

directive (AD) that is applicable to

certain British Aerospace (Jetstream)

Model 4101 airplanes. This proposal

would require a one-time inspection of

the tailplane (horizontal stabilizer)

leading edges and surrounding area for

discrepancies, and corrective action, if

necessary. This proposal is prompted by

the issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent separation of the

horizontal stabilizer from the fin, which

could lead to reduced controllability of

the airplane.

DATES: Comments must be received by

October 27, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

146–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

AI(R) American Support, Inc., 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:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2148; 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 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.