3276 Federal Register / Vol. 63, No. 14 /Thursday, January 22, 1998 / Proposed Rules

fleet. The FAA estimates that 100

engines on aircraft of U.S. registry

would be affected by the proposed AD,

that it would take approximately 300

work hours per engine to accomplish

the proposed actions, and that the

average labor rate is $60 per work hour.

Replacement parts, if required, would

cost approximately $86,000 per engine.

Based on these figures, and assuming

that 16 of the inspected HPTR disks will

require replacement, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $3,176,000.

The manufacturer has advised the FAA

that certain costs incurred from the

inspection and replacement of parts

affected by this AD may be borne by the

manufacturer, therefore, the total cost

impact of this AD to U.S. operators may

be less than estimated by the FAA.

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), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

CFM International: Docket No. 97–ANE–

46–AD.

Applicability: CFM International (CFMI)

CFM56–2, –2A, –2B, –3, –3B, and –3C series

turbofan engines installed on, but not limited

to McDonnell Douglas DC–8 series, Boeing

737 series, as well as Boeing E–3, E–6, and

KC–135 (military) series aircraft.

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 the potential for an

uncontained failure of the high pressure

turbine rotor (HPTR) disk, which could result

in an inflight engine shutdown, aborted

takeoff, or damage to the aircraft, accomplish

the following:

(a) Eddy current inspect for cracks or

gouges in HPTR disks, Part Numbers

1475M29P01, 1475M29P02, 9514M69P01,

9514M69P04, 9514M69P05, 9514M69P06,

and 9514M69P09, with Serial Numbers listed

in Table 1 of the applicable Service Bulletin

(SB), as follows:

(1) For CFM56–2 engines, in accordance

with CFM56–2 SB No. 72–817, dated January

14, 1997, prior to June 30, 1998.

(2) For CFM56–2A engines, in accordance

with CFM56–2A SB No. 72–419, Revision 1,

dated January 31, 1997, within 500 cycles in

service (CIS) after the effective date of this

AD, or by December 31, 1999, whichever

occurs first.

(3) For CFM56–2B engines, in accordance

with CFM56–2B SB No. 72–561, Revision 1,

dated January 31, 1997, within 500 CIS after

the effective date of this AD, or by December

31, 1999, whichever occurs first.

(4) For CFM56–3, –3B, and –3C engines, in

accordance with CFM56–3/–3B/–3C SB No.

72–843, dated January 14, 1997, prior to June

30, 1998.

(b) Remove from service HPTR disks found

cracked or gouged, and replace with

serviceable parts.

(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, Engine

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, Engine 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 Engine

Certification Office.

(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 aircraft to

a location where the inspection requirements

of this AD can be accomplished.

Issued in Burlington, Massachusetts, on

January 8, 1998.

James C. Jones,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 98–1484 Filed 1–21–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–119–AD]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Models PC–12 and PC–12/

45 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain Pilatus

Aircraft Ltd. (Pilatus) Models PC–12 and

PC–12/45 airplanes. The proposed AD

would require replacing certain

propeller de-icing controllers with ones

that are not susceptible to

electromagnetic interference (EMI). The

proposed AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for Switzerland. The actions

specified by the proposed AD are

intended to prevent improper operation

of the propeller de-icing controller

caused by EMI, which could result in

ice build-up on the propeller with

possible airplane controllability

problems.

DATES: Comments must be received on

or before February 27, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–

119–AD, Room 1558, 601 E. 12th Street,
Federal Register / Vol. 63, No. 14 /Thursday, January 22, 1998 / Proposed Rules 3277

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

Pilatus Aircraft Ltd., Marketing Support

Department, CH–6370 Stans,

Switzerland; telephone: +41 41–6196

233; facsimile: +41 41–6103 351. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Roman T. Gabrys, Aerospace Engineer,

Small Airplane Directorate, Airplane

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone: (816) 426–6932;

facsimile: (816) 426–2169.

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 that

summarizes 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–CE–119–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, Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–CE–119–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Discussion

The Federal Office for Civil Aviation

(FOCA), which is the airworthiness

authority for Switzerland, notified the

FAA that an unsafe condition may exist

on certain Pilatus Models PC–12 and

PC–12/45 airplanes. The FOCA of

Switzerland reports that part number (P/

N) 968.29.13.223 (BFG 4E3163–1)

propeller de-icing controllers are

susceptible to electromagnetic

interference (EMI). This condition was

identified during component

qualification testing at the factory.

This condition, if not corrected in a

timely manner, could result in improper

operation of the de-icing controller,

leading to ice-buildup on the propeller

with possible airplane controllability

problems.

Relevant Service Information

Pilatus has issued Service Bulletin

No. 30–002, dated August 19, 1996,

which specifies procedures for

identifying an affected propeller deicing controller, P/N 968.29.13.223 (BFG

4E3163–1); serial number U999 or lower

that does not have ‘‘SB30–1’’ marked on

it, and replacing this controller with one

that is not susceptible to EMI.

The FOCA of Switzerland classified

this service bulletin as mandatory and

issued Swiss AD HB 96–416, dated

September 30, 1996, in order to assure

the continued airworthiness of these

airplanes in Switzerland.

The FAA’s Determination

This airplane model is manufactured

in Switzerland 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 FOCA of Switzerland has kept the

FAA informed of the situation described

above.

The FAA has examined the findings

of the FOCA of Switzerland; reviewed

all available information, including the

service information referenced above;

and determined that AD action is

necessary for products of this type

design that are certificated for operation

in the United States.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Pilatus Models PC–12

and PC–12/45 airplanes of the same

type design registered in the United

States, the proposed AD would require

replacing certain propeller de-icing

controllers with ones that are not

susceptible to EMI. Accomplishment of

the proposed installation would be in

accordance with the service information

previously referenced.

Cost Impact

The FAA estimates that 53 airplanes

in the U.S. registry would be affected by

the proposed AD, that it would take

approximately 2 workhours per airplane

to accomplish the proposed

replacement, and that the average labor

rate is approximately $60 an hour. Parts

will be provided by the manufacturer

free of charge. Based on these figures,

the total cost impact of the proposed AD

on U.S. operators is estimated to be

$6,360.

Compliance Time of the Proposed AD

While the condition described in this

proposed AD is unsafe while the

airplane is in operation, it is not a direct

result of airplane operation. For

example, the unsafe condition exists or

could develop on an airplane with 500

hours time-in-service (TIS) the same as

one with 10 hours TIS. For this reason,

the FAA has determined that a

compliance based on calendar time

should be utilized in the proposed AD

in order to assure that the unsafe

condition is addressed on all airplanes

in a reasonable time period.

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 action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under 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 has been placed in the Rules

Docket. A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.
3278 Federal Register / Vol. 63, No. 14 /Thursday, January 22, 1998 / Proposed Rules

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 a new airworthiness directive

(AD) to read as follows:

Pilatus Aircraft Ltd: Docket No. 97–CE–119–

AD.

Applicability: Models PC–12 and PC–12/45

airplanes, serial numbers MSN 101 through

MSN 153, 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 (d) 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 in the

body of this AD, unless already

accomplished.

To prevent improper operation of the

propeller de-icing controller caused by

electromagnetic interference (EMI), which

could result in ice build-up on the propeller

with possible airplane controllability

problems, accomplish the following:

(a) Within the next 9 calendar months after

the effective date of this AD, accomplish the

following in accordance with the instructions

in Pilatus Service Bulletin No. 30–002, dated

August 19, 1996:

(1) Identify the serial number of the

affected propeller de-icing controller, part

number (P/N) 968.29.13.223 (BFG 4E3163–1)

(or FAA-approved equivalent part number);

(2) For those airplanes with a propeller deicing controller, P/N 968.29.13.223 (BFG

4E3163–1) (or FAA-approved equivalent part

number), with a serial number of U999 or

lower that does not have ‘‘SB30–1’’ marked

on it, replace it with a P/N 500.50.1.109 (BFG

SB4E3163–1–30–1) (or FAA-approved

equivalent part number) propeller de-icing

controller.

Note 2: The airplanes affected by this AD

could have propeller de-icing controllers

installed that have Parts Manufacturer

Approval (PMA). For those airplanes having

PMA parts that are equivalent (PMA by

equivalency) to those referenced in this AD,

the phrase ‘‘or FAA-approved equivalent part

number’’ means that this AD applies to

airplanes with PMA by equivalency propeller

de-icing controllers installed.

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

person may install, on any affected airplane,

a propeller de-icing controller, P/N

968.29.13.223 (BFG 4E3163–1) (or FAAapproved equivalent part number), with a

serial number of U999 or lower that does not

have ‘‘SB30–1’’ marked on it.

(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, 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) Questions or technical information

related to Pilatus Service Bulletin No. 30–002

dated August 19, 1996, should be directed to

Pilatus Aircraft Ltd., Marketing Support

Department, CH–6370 Stans, Switzerland;

telephone: +41 41–6196 233; facsimile: +41

41–6103 351. This service information may

be examined at the FAA, Central Region,

Office of the Regional Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Note 4: The subject of this AD is addressed

in Swiss AD HB–96–416, dated September

30, 1996.

Issued in Kansas City, Missouri, on January

14, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–1463 Filed 1–21–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–68–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Model 1900D

Airplane (Formerly Known as Beech

Aircraft Corporation Model 1900D

Airplane)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to Raytheon

Aircraft Company (Raytheon) Models

1900D airplanes (formerly known as

Beech Aircraft Corporation Models

1900D airplanes). The proposed action

would require inspecting and repairing

the radio switching panel relay printed

circuit board (PCB) and the nose

avionics wire harnesses, and replacing

the existing A017 component PCB with

a new A017 component PCB that has

internal overcurrent protection fuses.

Several reported incidents of lost pilot/

co-pilot intercom ability, VHF

communication ability, and public

address system ability while in flight

prompted the proposed action. The

actions specified by the proposed AD

are intended to prevent the loss of the

pilot and co-pilot intercom, VHF

communications, and passenger address

system, which could result in loss of all

communication during critical phases of

flight.

DATES: Comments must be received on

or before March 14, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–68–

AD, Room 1558, 601 E. 12th Street,

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

Raytheon Aircraft Company, P. O. Box

85, Wichita, Kansas 67201–0085;

telephone (800) 625–7043. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Harvey Nero, Aerospace Engineer,

Wichita Aircraft Certification Office,

Room 100, 1801 Airport Rd., Wichita,