Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 / Proposed Rules 30155

• provide the flight crew with

recognition cues for, and procedures for

exiting from, severe icing conditions.

In addition to the proposed rule

described previously, in September

1997, the FAA issued 24 other similar

proposals that address the subject

unsafe condition on various airplane

models. These 24 proposals also were

published in the Federal Register on

September 16, 1997. Numerous

comments were received on all 24

proposed actions.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received for this AD. The

comment received is from the

manufacturer and directly relates to the

I.A.M. Model Piaggio P–180 airplane.

The manufacturer states that the I.A.M.

Model Piaggio P–180 does not meet the

criteria of the proposed action. This

airplane has a bleed air and electrothermal wing anti-icing system, not a

pneumatic system. The FAA concurs

and has decided to withdraw the NPRM.

Withdrawal of this NPRM constitutes

only such action, and does not preclude

the agency from issuing future

rulemaking on this issue, nor does it

commit the agency to any course of

action in the future.

Since this action only withdraws an

NPRM, it is neither a proposed nor a

final rule and therefore, is not covered

under Executive Order 12866, the

Regulatory Flexibility Act, or DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979).

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

Safety, Safety.

The Withdrawal

Accordingly, the notice of proposed

rulemaking, Docket No. 97–CE–52–AD,

published in the Federal Register on

September 16, 1997 (62 FR 48502), is

withdrawn.

Issued in Kansas City, Missouri, on May

22, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–14616 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–142–AD]

RIN 2120–AA64

Airworthiness Directives; Honeywell

IC–600 Integrated Avionics Computers,

as Installed in, but not Limited to,

Learjet Model 45 and EMBRAER Model

EMB–145 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 Honeywell IC–600 integrated

avionics computers. This proposal

would require modification of the

integrated avionics computers. This

proposal is prompted by a report of

integrated avionics computer failures,

which caused a ‘‘random reset’’

condition of the electronic flight

instrument system. The actions

specified by the proposed AD are

intended to prevent such ‘‘random

reset’’ conditions, which could affect

the pilot’s ability to control the airplane.

DATES: Comments must be received by

July 20, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

142–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

Honeywell Inc., Business and

Commuter Aviation Systems, Box

29000, Phoenix, Arizona 85038. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Transport

Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California.

FOR FURTHER INFORMATION CONTACT: J.

Kirk Baker, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5345;

fax (562) 627–5210.

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 98–NM–142–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.

98–NM–142–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received a report

indicating that, during several test

flights of a Cessna Model XL series

airplane, the screen of the electronic

flight instrument system (EFIS) turned

blank. Investigation has revealed that

the Honeywell IC–600 integrated

avionics computer failed, which

resulted in a ‘‘random reset’’ condition

of the EFIS. During such a ‘‘random

reset’’ condition, the following events

may occur: the primary flight displays

may turn blank, or display a red ‘‘X,’’

and take 10 to 15 seconds to reboot; the

flight director mode may drop; the EFIS

may reset to its default state; and the

autopilot and/or the yaw damper, if

engaged, may disconnect. This ‘‘random

reset’’ condition of the EFIS, if not
30156 Federal Register / Vol. 63, No. 106 /Wednesday, June 3, 1998 / Proposed Rules

corrected, could affect the pilot’s ability

to control the airplane.

The affected computers are

Honeywell IC–600 integrated avionics

computers, which may be installed in,

but not limited to, Learjet Model 45 and

EMBRAER Model EMB–145 series

airplanes.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Honeywell Service Bulletin 7017000–

22–43, dated March 24, 1998, which

describes procedures for modification of

the integrated avionics computers. This

modification involves replacing

programmable array logic devices U6,

U32, and U33 with new modified parts;

adding two resistors; replacing resistor

R7 with a new value; adding two

capacitors; and adding bus wires.

Accomplishment of the actions

specified in the service bulletin 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 bulletin

described previously.

Cost Impact

There are approximately 38 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 20

airplanes of U.S. registry would be

affected by this proposed AD. It would

take approximately 2 work hours per

airplane to accomplish the proposed

modification at an average labor rate of

$60 per work hour. Required parts

would be supplied 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

$2,400, or $120 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.

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:

Honeywell. Docket 98–NM–142–AD.

Applicability: Honeywell IC–600 integrated

avionics computers having part numbers

7017000–82201, –82202, –82203, –82204,

–82351, –82352, –82401, –82402, –82403,

–83351, –83352, –83401, –83402, and

–83403, as installed in, but not limited to,

Learjet Model 45 and EMBRAER Model

EMB–145 series airplanes.

Note 1: This AD applies to Honeywell IC–

600 integrated avionics computers having

part numbers 7017000–82201, –82202,

–82203, –82204, –82351, –82352, –82401,

–82402, –82403, –83351, –83352, –83401,

–83402, and –83403, as installed in any

airplane, regardless of whether the airplane

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 (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 a ‘‘random reset’’ condition of

the electronic flight instrument system,

which could affect the pilot’s ability to

control the airplane, accomplish the

following:

(a) Within 6 months after the effective date

of this AD, modify the IC–600 integrated

avionics computer, in accordance with

Honeywell Service Bulletin 7017000–22–43,

dated March 24, 1998.

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

person shall install a Honeywell IC–600

integrated avionics computer having part

number 7017000–82201, –82202, –82203,

–82204, –82351, –82352, –82401, –82402,

–82403, –83351, –83352, –83401, –83402, or

–83403 on any airplane, unless it has been

modified in accordance with Honeywell

Service Bulletin 7017000–22–43, dated

March 24, 1998.

(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, 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles 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.

Issued in Renton, Washington, on May 27,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14612 Filed 6–2–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 98–AGL–36]

Proposed Removal of Class D

Airspace and Class E Airspace;

Willoughby, OH

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This notice proposes to

remove Class D airspace and Class E