63914 Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Proposed Rules

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

Eurocopter France (Formerly Aerospatiale,

Society Nationale Industrielle, Sud

Aviation): Docket No. 96–SW–22–AD.

Applicability: Model SA–365N, SA–365N1,

AS–365N2, and SA–366G1 helicopters,

certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To detect cracks that reduce the strength of

the main gearbox strut attachment and could

result in failure of the main gearbox

mounting, and subsequent loss of control of

the helicopter, accomplish the following:

(a) For Model SA–365N, SA–365N1, and

SA–366G1 helicopters, on or before attaining

4,000 hours time-in-service (TIS), or within

50 hours TIS after the effective date of this

AD, whichever occurs later; and for Model

SA–365N2 helicopters, on or before attaining

2,000 hour TIS, or within 50 hours TIS after

the effective date of this AD, whichever

occurs later; perform the following:

(1) Inspect the transmission deck for cracks

using a dye-penetrant inspection method, in

accordance with paragraph BB of Eurocopter

France Telex Service No. 10011, dated

February 24, 1995. If a crack is found in the

transmission deck, repair prior to further

flight.

Note 2: A FAA-approved repair solution

can be initiated by contacting the American

Eurocopter Technical Support Department,

ATTN: Manager, telephone: 972–641–3460,

fax: 972–641–3527.

(2) Replace the currently installed

transmission deck support beams, part

numbers (P/N) 365A21–3365–49 and

365A21–3365–CY, with reinforced

transmission deck support beams, P/N

365A21–3365–JE–01 and 365A21–3365–JF–

01, in accordance with the Accomplishment

Instructions in Eurocopter France Service

Bulletin No. 05.00.36, Rev. 1, dated

December 16, 1996.

(b) After completion of paragraphs (a)(1)

and (a)(2) of this AD, clean, prime and paint

the affected areas of the transmission deck

and the reinforced support beams in

accordance with paragraph BB 2A of

Eurocopter France Telex Service No. 10011,

dated February 24, 1995.

(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, Rotorcraft

Standards Staff, FAA, Rotorcraft Directorate.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Rotorcraft Certification

Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft 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 helicopter

to a location where the requirements of this

AD can be accomplished.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 95–068–017(B) and AD 95–067–

038(B), both dated April 12, 1995.

Issued in Fort Worth, Texas, on November

24, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–31614 Filed 12–2–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–72–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Models B200,

B200C, and B200T 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

Raytheon Aircraft Company (Raytheon)

Models B200, B200C, and B200T

airplanes (formerly referred to as Beech

Models B200, B200C, and B200T

airplanes). The proposed AD would

require replacing the wiring for the

engine fire detector system with fire

resistant wiring. The proposed AD is the

result of the discovery during aircraft

production of the potential for the

existing engine fire detector system

wiring on the affected airplanes to fail

because of high heat and/or fire. The

actions specified by the proposed AD

are intended to prevent failure of the

engine fire detector system if high heat

and/or fire stopped an electrical signal

between the engine fire detectors and

the engine fire warning annunciator

lights located in the cockpit, which

could result in passenger injury in the

event of an airplane fire.

DATES: Comments must be received on

or before February 4, 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–72–

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 the

Raytheon Aircraft Company, P.O. Box

85, Wichita, Kansas 67201–0085. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Randy Griffith, Aerospace Engineer,

Wichita Aircraft Certification Office,

FAA, 1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4145; facsimile

(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

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
Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Proposed Rules 63915

statement is made: ‘‘Comments to

Docket No. 97–CE–72–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–72–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Discussion

Raytheon recently advised the FAA

that an unsafe condition could exist on

certain Raytheon Models B200, B200C,

and B200T airplanes. Raytheon reports

that the current wiring on a certain

engine fire protection system could fail

under certain conditions. When the

engine fire detector system was changed

from an optical system to a heat sensing

system, the engine fire detector wiring

was not furnished with the engine fire

detector. The wiring for these new

systems consisted of four wires that

were routed from the engine firewall

connector to the engine fire detector

connector as part of each engine’s wire

harness assembly.

In May 1997, Raytheon issued

Engineering Change Record 9896 and

Engine Fire Detector Harness Kit, part

number 101–3208–1, which specifies

the design and provides the procedures

for replacing the existing engine fire

protector system wiring with fire

resistant wiring.

Aircraft equipped with the heat

sensing fire protector system before this

change order and modification were

developed utilize non-fire resistant

wiring. This condition, if not corrected,

could result in failure of the engine fire

detector system if high heat and/or fire

stopped an electrical signal between the

engine fire detectors and the engine fire

warning annunciator lights located in

the cockpit, which could result in

passenger injury in the event of an

airplane fire.

Relevant Service Information

Raytheon has issued Mandatory

Service Bulletin No. 2701, Issued: May,

1997, which specifies the incorporation

of Engine Fire Detector Harness Kit, part

number 101–3208–1. This kit consists of

the parts and instructions to replace the

wiring for the engine fire detector

system with fire resistant wiring.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

including the service information

previously referenced, the FAA has

determined that AD action should be

taken to prevent failure of the engine

fire detector system if high heat and/or

fire stopped an electrical signal between

the engine fire detectors and the engine

fire warning annunciator lights located

in the cockpit, which could result in

passenger injury in the event of an

airplane fire.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Raytheon Models

B200, B200C, and B200T airplanes

(formerly referred to as Beech Models

B200, B200C, and B200T airplanes) of

the same type design, the FAA is

proposing an AD. The proposed AD

would require replacing the wiring for

the engine fire detector system with fire

resistant wiring by incorporating Engine

Fire Detector Harness Kit, part number

101–3208–1. Accomplishment of the

proposed modifications would be

required in accordance with the service

information previously referenced.

Cost Impact

The FAA estimates that 77 airplanes

in the U.S. registry would be affected by

the proposed AD, that it would take

approximately 4 workhours per airplane

to accomplish the proposed

modification, and that the average labor

rate is approximately $60 an hour. Parts

will be provided by the manufacturer at

no cost to the owners/operators of the

affected airplanes. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $18,480, or $240 per

airplane. These figures are based on the

presumption that no owner/operator of

the affected airplanes has incorporated

the proposed modification.

Raytheon has informed the FAA that

approximately 40 kits have been

shipped from the Raytheon Aircraft

Authorized Service Center. Presuming

that each of the 40 kits is incorporated

on an affected airplane, this would

reduce the cost impact of the proposed

AD by $9,600 from $18,480 to $8,880.

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.

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:

Raytheon Aircraft Company: Docket No. 97–

CE–72–AD.

Applicability: The following model and

serial number airplanes, certificated in any

category:

Model Serial Nos.

B200 ................. BB–1439, BB–1444

through BB–1447, BB–

1449, BB–1450, B–1452,

BB–1453, BB–1455, BB–

1456, and BB–1458

through BB–1512;

B200C .............. BL–139 and BL–140;

B200C (C–12R) BW–1 through BW–5; and

B200T ............... BT–35 through BT–38.

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
63916 Federal Register / Vol. 62, No. 232 / Wednesday, December 3, 1997 / Proposed Rules

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 within the next 200

hours time-in-service after the effective date

of this AD, unless already accomplished.

To prevent failure of the engine fire

detector system if high heat and/or fire

stopped an electrical signal between the

engine fire detectors and the engine fire

warning annunciator lights located in the

cockpit, which could result in passenger

injury in the event of an airplane fire,

accomplish the following:

(a) Replace the existing engine fire

protection system wiring with fire resistant

wiring by incorporating Engine Fire Detector

Harness Kit, part number 101–3208–1.

Accomplish this replacement in accordance

with the instructions included with the

above kit, as referenced in Raytheon

Mandatory Service Bulletin No. 2701, Issued:

May, 1997.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas 67209. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(d) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to the Raytheon

Aircraft Company, P.O. Box 85, Wichita,

Kansas 67201–0085; or may examine this

document at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on

November 26, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–31681 Filed 12–2–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–ACE–14]

Proposed Revocation of Class E

Airspace; Minneapolis, KS

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This action proposes to

remove the Class E airspace area at

Minneapolis City County Airport,

Minneapolis, KS. The VHF

Omnidirectional Range/Distance

Measuring Equipment (VOR/DME)

Standard Instrument Approach

Procedure (SIAP) to Runway (RWY) 34

was canceled on August 14, 1997. This

was the only SIAP to Minneapolis City

County Airport and was canceled due to

lack of evidence as to the need by the

community and absence of utilization

by other users in the local area. In

addition, there is not an Airport Layout

Plan (ALP) or an engineer’s drawing

available. The Director, Division of

Aviation for Kansas, concurred with

canceling the SIAP. The intended effect

of this rule is to remove Class E airspace

extending upward from 700 feet above

the surface for Minneapolis City County

Airport, Minneapolis, KS.

DATES: Comments must be received on

or before January 15, 1998.

ADDRESSES: Send comments on the

proposal in triplicate to: Manager,

Airspace Branch, ACE–520, Federal

Aviation Administration, Airspace

Docket No. 97–ACE–14, 601 East 12th

Street, Kansas City, MO 64106.

The official docket may be examined

in the Office of the Regional Counsel for

the Central Region at the same address

between 9:00 a.m. and 3:30 p.m.,

Monday through Friday, except Federal

holidays.

An informal docket may also be

examined during normal business hours

in the office of the Manager, Airspace

Branch, Air Traffic Division, at the

address listed above.

FOR FURTHER INFORMATION CONTACT:

Kathy Randolph, Air Traffic Division,

Airspace Branch, ACE–520C, Federal

Aviation Administration, 601 East 12th

Street, Kansas City, Missouri 64106;

telephone (816) 426–3408.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested parties are invited to

participate in this proposed rulemaking

by submitting such written data, views,

or arguments as they may desire.

Comments that provide the factual basis

supporting the views and suggestions

presented are particularly helpful in

developing reasoned regulatory

decisions on the proposal. Comments

are specifically invited on the overall

regulatory, economic, environmental,

and energy-related aspects of the

proposal. Communications should

identify the airspace docket number and

be submitted in triplicate to the address

listed above. Commenters wishing the

FAA to acknowledge receipt of their

comments on this notice must submit

with those comments a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Airspace Docket No. 97–

ACE–14.’’ The postcard will be date/

time stamped and returned to the

commenter. All communications

received on or before the closing date

for comments will be considered before

taking action on the proposed rule. The

proposal contained in this notice may

be changed in light of comments

received. All comments submitted will

be available for examination in the

Rules Docket both before and after the

closing date for comments. A report

summarizing each substantive public

contact with FAA personnel concerned

with this rulemaking will be filed in the

docket.

Availability of NPRMs

Any person may obtain a copy of this

Notice of Proposed Rulemaking (NRPM)

by submitting a request to the Federal

Aviation Administration, Office of

Public Affairs, Attention: Public Inquiry

Center, APA–230, 800 Independence

Avenue, SW, Washington, DC 20591, or

by calling (202) 267–3484.

Communications must identify the

notice number of this NPRM. Persons

interested in being placed on a mailing

list for future NPRMs should also

request a copy of Advisory Circular No.

11–2A, which describes the procedures.

The Proposal

The FAA proposes to amend 14 CFR

part 71 (part 71) to remove the Class E

airspace extending upward from 700

feet above the surface at the

Minneapolis City County Airport,

Minneapolis, KS. The area will be

removed from appropriate aeronautical

charts. Class E airspace designations for

airspace areas extending upward from

700 feet or more above the surface of the

earth are published in paragraph 6005 of

FAA Order 7400.9E, dated September

16, 1997, and effective September 17,

1997, which is incorporated by

reference in 14 CFR 71.1. The Class E

airspace designation listed in this