31138 Federal Register / Vol. 63, No. 109 / Monday, June 8, 1998 / Proposed Rules

adverse changes in handling characteristics,

use of the autopilot is prohibited when any

of the visual cues specified above exist, or

when unusual lateral trim requirements or

autopilot trim warnings are encountered

while the airplane is in icing conditions.

• All wing icing inspection lights must be

operative prior to flight into known or

forecast icing conditions at night. [NOTE:

This supersedes any relief provided by the

Master Minimum Equipment List (MMEL).]’’

(2) Revise the FAA-approved AFM by

incorporating the following into the Normal

Procedures Section of the AFM. This may be

accomplished by inserting a copy of this AD

in the AFM.

‘‘THE FOLLOWING WEATHER

CONDITIONS MAY BE CONDUCIVE TO

SEVERE IN-FLIGHT ICING

• Visible rain at temperatures below 0

degrees Celsius ambient air temperature.

• Droplets that splash or splatter on impact

at temperatures below 0 degrees Celsius

ambient air temperature.

PROCEDURES FOR EXITING THE SEVERE

ICING ENVIRONMENT

These procedures are applicable to all

flight phases from takeoff to landing. Monitor

the ambient air temperature. While severe

icing may form at temperatures as cold as

¥18 degrees Celsius, increased vigilance is

warranted at temperatures around freezing

with visible moisture present. If the visual

cues specified in the Limitations Section of

the AFM for identifying severe icing

conditions are observed, accomplish the

following:

• Immediately request priority handling

from Air Traffic Control to facilitate a route

or an altitude change to exit the severe icing

conditions in order to avoid extended

exposure to flight conditions more severe

than those for which the airplane has been

certificated.

• Avoid abrupt and excessive

maneuvering that may exacerbate control

difficulties.

• Do not engage the autopilot.

• If the autopilot is engaged, hold the

control wheel firmly and disengage the

autopilot.

• If an unusual roll response or

uncommanded roll control movement is

observed, reduce the angle-of-attack.

• Do not extend flaps when holding in

icing conditions. Operation with flaps

extended can result in a reduced wing angleof-attack, with the possibility of ice forming

on the lower surface further aft on the wing

than normal, possibly aft of the protected

area.

• If the flaps are extended, do not retract

them until the airframe is clear of ice.

• Report these weather conditions to Air

Traffic Control.’’

(b) Incorporating the AFM revisions, as

required by this AD, may be performed by

the owner/operator holding at least a private

pilot certificate as authorized by section 43.7

of the Federal Aviation Regulations (14 CFR

43.7), and must be entered into the aircraft

records showing compliance with this AD in

accordance with section 43.11 of the Federal

Aviation Regulations (14 CFR 43.11).

(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.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(e) All persons affected by this directive

may examine information related to this AD

at the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on May

29, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–15081 Filed 6–5–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–23–AD]

RIN 2120–AA64

Airworthiness Directives; Allison

Engine Company 250–B and 250–C

Series Turboshaft 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 Allison Engine Company 250–B

and 250–C series turboshaft engines.

This proposal would require replacing

existing beryllium copper main fuel

control (MFC) bellows assemblies with

Inconel 718 stainless steel welded MFC

bellows assemblies. This proposal is

prompted by reports of leaking MFC

bellows assemblies resulting in an

uncommanded minimum fuel flow

condition, loss of engine fuel flow

control and subsequent forced landing.

The actions specified by the proposed

AD are intended to prevent MFC

bellows assembly leakage, which can

result in an uncommanded minimum

fuel flow condition and subsequent loss

of engine fuel flow control.

DATES: Comments must be received by

August 7, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–ANE–

23–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Allison Engine Company, P.O. Box 420,

Speed Code U–15, Indianapolis, IN

46206–0420, telephone (317) 230–6674.

This information may be examined at

the FAA, New England Region, Office of

the Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: John

Tallarovic, Aerospace Engineer, Chicago

Aircraft Certification Office, FAA, Small

Airplane Directorate, 2350 E. Devon

Avenue, Room 323, Des Plaines, IL

60018; telephone (847) 294–8180, fax

(847) 294–7834.

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

should 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
Federal Register / Vol. 63, No. 109 / Monday, June 8, 1998 / Proposed Rules 31139

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–ANE–23–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, New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 98–ANE–23–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has received reports of inflight

engine shutdowns due to main fuel

control (MFC) beryllium copper bellows

assembly leakage on Allison Engine

Company engines. This same design is

used on Allison Engine Company 250–

B15, 250–B17, 250–B17F, 250–C18,

250–C20, 250–C20R, 250–C28, and 250–

C30 series turboshaft engines. The

investigation revealed that the MFC

bellows assemblies leaked due to

corrosion. This AD requires the

replacement of existing beryllium

copper MFC bellows assemblies with

Inconel 718 stainless steel welded MFC

bellows assemblies, a material that is

less susceptible to corrosion. The

compliance schedule balanced the need

to remove the highest risk bellows

assemblies first with the ability to

manufacture replacement parts at the

required rate. This condition, if not

corrected, could result in MFC bellows

assembly leakage, which can result in

an uncommanded minimum fuel flow

condition and subsequent loss of engine

fuel flow control.

The FAA has reviewed and approved

the technical contents of Allison

Commercial Engine Bulletins (CEBs) No.

CEB–A–282 (250–C18 series), No. CEB–

A–1329 (250–C20 series), No. CEB–A–

73–2053 (250–C28 series), No. CEB–A–

73–3068 (250–C30 series), No. CEB–A–

73–4029 (250–C20R series), No. TP

CEB–A–158 (250–B15G series), No. TP

CEB–A–1286 (250–B17 series), and TP

CEB–A–73–2014 (250–B17F series), all

Revision 2, all dated April 15, 1998, that

describe procedures for replacing

existing beryllium copper MFC bellows

assemblies with Inconel 718 stainless

steel welded MFC bellows assemblies.

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 replacing the existing beryllium

copper MFC bellows assemblies at the

next repair or overhaul of the MFC

bellows assembly, or, since corrosion

was a factor, by the calendar end-dates

specified, whichever occurs first. The

actions would be required to be

accomplished in accordance with the

CEBs described previously.

The FAA estimates that 2,500 engines

installed on aircraft of U.S. registry

would be affected by this proposed AD,

that it would take no additional work

hours per engine to accomplish the

proposed actions at regularly scheduled

overhaul, and required parts would cost

approximately $1,495 per engine. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $3,737,500.

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:

Allison Engine Company: Docket No. 98–

ANE–23–AD.

Applicability: Allison Engine Company

250–B15, 250–B17, 250–B17F, 250–C18,

250–C20, 250–C20R, 250–C28, and 250–C30

series turboshaft engines, installed on but not

limited to Bell Models 206, 230, 406;

Enstrom Model TH28/480; and Boeing

Models 500, 520N, 530F rotorcraft.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 main fuel control (MFC)

bellows assembly leakage, which can result

in an uncommanded minimum fuel flow

condition and subsequent loss of engine fuel

flow control, accomplish the following:

(a) Replace existing beryllium copper MFC

bellows assemblies, part numbers (P/Ns)

2523722, 2539647, 2540539, 2540767, and

2542526, with Inconel 718 stainless steel

welded MFC bellows assemblies, P/N

2543598, in accordance with the applicable

Allison Commercial Engine Bulletins (CEBs)

referenced in paragraph (b) of this AD, at the

earlier of the following:

(1) The next time after the effective date of

this AD the MFC is being repaired or

overhauled; or

(2) The following populations of MFCs, as

applicable

(i) All MFCs listed by P/Ns in Tables 1 and

2 of the Allison CEBs referenced in paragraph

(b) of this AD by March 31, 1999; or

(ii) All MFCs listed by P/Ns in Table 3 of

the Allison CEBs referenced in paragraph (b)

of this AD by August 31, 1999.

(iii) All MFCs listed by P/Ns in Tables 4

and 5 of the Allison CEBs referenced in

paragraph (b) of this AD by October 31, 1999.

(b) Perform the replacement of MFC

bellows assemblies required by paragraph (a)

of this AD in accordance with the applicable

Allison CEB from among the following:

(1) CEB–A–282 Revision 2, dated April 15,

1998 (250–C18 series), or

(2) CEB–A–1329 Revision 2, dated April

15, 1998(250–C20 series), or

(3) CEB–A–73–2053 Revision 2, dated

April 15, 1998(250–C28 series), or

(4) CEB–A–73–3068 Revision 2, dated

April 15, 1998(250–C30 series), or,

(5) CEB–A–73–4029 Revision 2, dated

April 15, 1998(250–C20R series), or
31140 Federal Register / Vol. 63, No. 109 / Monday, June 8, 1998 / Proposed Rules

(6) TP (Turboprop) CEB–A–158 Revision 2,

dated April 15, 1998 (250–B15G series), or

(7) TP CEB–A–1286 Revision 2, dated

April 15, 1998 (250–B17 series), or

(8) TP CEB–A–73–2014 Revision 2, dated

April 15, 1998 (250–B17F series).

(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, Chicago

Aircraft Certification Office. Operators shall

submit their request through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Chicago Aircraft Certification

Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

Aircraft Certification Office.

(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 aircraft to a

location where the requirements of this AD

can be accomplished.

Issued in Burlington, Massachusetts, on

May 29, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–15087 Filed 6–5–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–134–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B19 (Regional Jet

Series 100) 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 Bombardier Model CL–600–

2B19 (Regional Jet Series 100) airplanes.

This proposal would require repetitive

inspections of the inboard and outboard

flap actuators to measure the rotational

freedom of the actuator ball screw

adjacent to the actuator housing, and

replacement of the flap actuators with

new or serviceable actuators, if

necessary. This 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 premature wear

of the internal gears on the flap

actuators, which could result in

complete disconnection of the actuator

gear set and a mechanical jam of the flap

system. This condition could cause

structural damage and/or significant

twist of a flap panel, which could lead

to reduced controllability of the

airplane.

DATES: Comments must be received by

July 8, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

134–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

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9,

Canada. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Engine and Propeller

Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York.

FOR FURTHER INFORMATION CONTACT:

Anthony E. Gallo, Aerospace Engineer,

Systems and Flight Test Branch, ANE–

172, FAA, Engine and Propeller

Directorate, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7510; fax

(516) 568–2716.

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–134–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–134–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Transport Canada Aviation (TCA),

which is the airworthiness authority for

Canada, notified the FAA that an unsafe

condition may exist on certain

Bombardier Model CL–600–2B19

(Regional Jet Series 100) airplanes. TCA

advises that there have been several inservice reports of premature wear of the

internal gears on the inboard and

outboard flap actuators on airplanes

returned from service. Such

deterioration could result in complete

disconnection of the actuator gear set

and a mechanical jam of the flap system,

which could cause structural damage

and/or significant twist of a flap panel,

and result in reduced controllability of

the airplane.

Explanation of Relevant Service

Information

EEMCO has issued Service Bulletin

852D100–27–03, Revision A, dated

February 27, 1997, including

Appendices 1 and 2. This service

bulletin describes procedures for

repetitive inspections of the inboard and

outboard flap actuators to measure the

rotational freedom of the actuator ball

screw adjacent to the actuator housing

to determine the allowable intervals for

backlash measurement; and replacement

of the flap actuators with new or

serviceable actuators, if necessary.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. TCA

classified this service bulletin as

mandatory and issued Canadian

airworthiness directive CF–97–05, dated

May 5, 1997, in order to assure the

continued airworthiness of these

airplanes in Canada.