Federal Register / Vol. 62, No. 235 / Monday, December 8, 1997 / Rules and Regulations 64517

(ii) Disks with less than 6,000 CSN on the

effective date of this AD, inspect prior to

accumulating 8,000 CSN.

(2) Disks that have been fluorescent

penetrant inspected since introduction into

service, perform an FPI for cracks in all 30

tie bolt holes, prior to accumulating 8,000

CIS since last FPI, or within 250 CIS after the

effective date of this AD, whichever occurs

later, in accordance with PW Turbojet Engine

Standard Practices Manual, P/N 585005,

Chapter/Section 70–33, SPOP 70.

(3) Thereafter, perform FPI for cracks in all

30 tie bolt holes at intervals not to exceed

8,000 CIS since last FPI, in accordance with

PW Turbojet Engine Standard Practices

Manual, P/N 585005, Chapter/Section 70–33,

SPOP 70.

(4) Prior to further flight, remove from

service cracked disks, and replace with

serviceable parts.

(c) Report findings of cracked turbine disks

within 48 hours after inspection to Tara

Goodman, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–5299;

telephone (781) 238–7130, fax (781) 238–

7199, Internet: ‘‘Tara.Goodman@faa.dot.gov’’.

Reporting requirements have been approved

by the Office of Management and Budget and

assigned OMB control number 2120–0056.

(d) 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 requests 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 method of

compliance with this AD, if any, may be

obtained from the Engine Certification Office.

(e) 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 requirements of this AD

can be accomplished.

(f) This amendment becomes effective on

January 12, 1998.

Issued in Burlington, Massachusetts, on

November 28, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–31965 Filed 12–5–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–31–AD; Amendment

39–10233; AD 97–25–09]

RIN 2120–AA64

Airworthiness Directives; Allison

Engine Company Model 250–C40B

Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Allison Engine Company

Model 250–C40B turboshaft engines.

This action requires installation of a

placard requiring pilots to record torque

level and time in service operating

above 86% engine torque until the

defective parts have been replaced, no

later than December 31, 2000, or when

certain maintenance actions are

accomplished, or when certain

operational restrictions are exceeded,

whichever occurs earliest. This

amendment is prompted by a report

from Allison Engine Company of a

manufacturing defect in certain helical

power takeoff gearshaft assemblies,

identified by serial numbers. The

actions specified in this AD are

intended to prevent fatigue failure of the

helical power takeoff gearshaft

assembly, which could result in a loss

of engine power and inflight engine

shutdown.

DATES: Effective December 23, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

23, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

February 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–ANE–

31–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.

The service information referenced in

this AD 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; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: John

Tallarovic, Aerospace Engineer, Chicago

Aircraft Certification Office, FAA, Small

Airplane Directorate, ACE–118C, 2300

East Devon Avenue, Des Plaines, IL

60018; telephone (847) 294–8180, fax

(847) 294–7834.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

received a report from Allison Engine

Company of a manufacturing defect

discovered in certain helical power

takeoff gearshaft assemblies, part

number (P/N) 23056617, installed on

Model 250–C40B turboshaft engines.

The manufacturing defect was

discovered while measuring the depth

of the case hardening of the gear. The

manufacturing defect was caused by

excessive removal of case hardened

material from the gear during

manufacturing. This condition, if not

corrected, could result in fatigue failure

of the helical power takeoff gearshaft

assembly, which could result in a loss

of engine power and inflight engine

shutdown.

The FAA has reviewed and approved

the technical contents of Allison Alert

Commercial Engine Bulletin (CEB) No.

A–72–5009, dated May 21, 1997, that

lists by serial number (S/N) 49 affected

engines, gearboxes, and gears. This CEB

also describes procedures for

replacement of affected helical power

takeoff gearshaft assemblies with

serviceable parts.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design, this AD is being issued to

prevent a loss of engine power and

inflight engine shutdown. This AD

requires installation of a placard

requiring pilots to record torque and

time in service operating above 86%

engine torque until replacement of

defective helical power takeoff gearshaft

assemblies with serviceable parts, and

then the placard can be removed. The

compliance times were determined

based upon an analysis of the effect of

gearbox assembly torque loading on

component life. The actions are required

to be accomplished in accordance with

the CEB described previously.

The operational limitations imposed

by this AD have been coordinated with

the Rotorcraft Directorate.
64518 Federal Register / Vol. 62, No. 235 / Monday, December 8, 1997 / Rules and Regulations

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 AD

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 97–ANE–31–AD.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the

Rules Docket at the location provided

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

97–25–09 Allison Engine Company:

Amendment 39–10233. Docket 97–ANE–

31–AD.

Applicability: Allison Engine Company

Model 250–C40B turboshaft engines, with

engines, gearboxes, and gears identified by

serial number (S/N) in Allison Alert

Commercial Engine Bulletin (CEB) No. A–

72–5009, dated May 21, 1997. The 250–C40B

engine is installed on and limited to the

twin-engine Bell Helicopter Textron 430

series helicopters.

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 (g)

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 fatigue failure of the helical

power takeoff gearshaft assembly, which

could result in a loss of engine power and

inflight engine shutdown, accomplish the

following for part number (P/N) 23056617,

identified by S/N in Allison Alert CEB No.

A–72–5009, dated May 21, 1997:

(a) Prior to further flight, install the

following placard on the instrument panel in

clear view of the pilot, ‘‘RECORD TORQUE

AND TIME ABOVE 86% ENGINE TORQUE.’’

The placard shall be manufactured of a

material that cannot be easily defaced or

erased, and the lettering shall be block-style

and at least 1⁄8 inches in height. Additionally,

the color and lettering must contrast with the

background (color of placard material) such

that it is legible.

(b) Remove from service affected helical

power takeoff gearshaft assemblies, P/N

23056617, and replace with serviceable parts,

in accordance with Allison Alert CEB No. A–

72–5009, dated May 21, 1997, when the first

of the following conditions exists:

(1) At the time of turbine overhaul; or

(2) During gearbox disassembly for any

reason; or

(3) If any of the operational restrictions

listed in paragraph (c) of this AD are

exceeded; or

(4) No later than December 31, 2000.

(c) After the effective date of this AD,

observe the following operational restrictions

at all times, until paragraph (b) of this AD is

complied with by installing serviceable

helical power takeoff gearshaft assemblies:

(1) Total operational time accumulated on

the suspect helical power takeoff gearshaft

assemblies may not exceed 1,750 hours time

in service (TIS). Engines are to be operated

in the torque sharing mode only.

(2) Operation of the engine at power

between 86% torque and 93% torque is

limited to one hour prior to reaching 1,750

hours TIS.

(3) Operation of the engine above 93%

torque will require replacement of the helical

power takeoff gearshaft assemblies. Any

previously recorded time (Electronic Control

Unit (ECU)), Integrated Instrument Display

System ((IIDS) or Log Book) must be

accounted for. Operators will be allowed four

hours of operation at torque levels less than

86% torque to ferry the aircraft to a

maintenance facility for replacement of the

assembly unless any of the following have

been exceeded:

(i) Operation of the engine between 93%

torque and 105% torque for more than six

minutes requires replacement of the

assembly before further flight.

(ii) Operation of the engine between 105%

torque and 110% torque for more than ninety

seconds requires replacement of the assembly

before further flight.

(d) Revise the limitations section of the

FAA-approved Rotorcraft Flight Manual

(RFM) by inserting a copy of this AD.

Thereafter, except as provided in paragraph

(g) of this AD, no alternative limitations may

be approved for affected helical power

takeoff gearshaft assemblies, P/N 23056617.

(e) After replacing parts in accordance with

paragraph (b) of this AD, remove the placard
Federal Register / Vol. 62, No. 235 / Monday, December 8, 1997 / Rules and Regulations 64519

and the AD required by paragraphs (a) and

(d) of this AD.

(f) For the purposes of this AD, a

serviceable helical power takeoff gearshaft

assembly is one not identified by S/N in

Allison Alert CEB No. A–72–5009, dated May

21, 1997.

(g) 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 requests 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.

(h) 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) and paragraph (c)(3) of

this AD to operate the aircraft to a location

where the requirements of this AD can be

accomplished.

(i) The actions required by this AD shall be

done in accordance with the following

Allison Alert CEB:

Document No. Pages Date

A–72–5009 ........... 1–5 May 21, 1997.

Total pages: 5.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Allison Engine Company, P.O. Box 420,

Speed Code U–15, Indianapolis, IN 46206–

0420; telephone: (317) 230–6674. Copies may

be inspected at the FAA, New England

Region, Office of the Assistant Chief Counsel,

12 New England Executive Park, Burlington,

MA; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(j) This amendment becomes effective on

December 23, 1997.

Issued in Burlington, Massachusetts, on

November 28, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–31966 Filed 12–5–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–286–AD; Amendment

39–10235; AD 97–25–11]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B16 Series Airplanes

Modified in Accordance With

Supplemental Type Certificate (STC)

SA6003NM

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Bombardier Model

CL–600–2B16 series airplanes. This

action requires disabling the remote

fuel/defuel panel in the cockpit. This

action also provides for an optional

modification of the remote fuel/defuel

panel, which would terminate the

requirement to disable the panel. This

amendment is prompted by reports of

in-flight failure of the panel that

resulted when a circuit breaker on a

battery bus opened due to insufficient

current flow capacity. The actions

specified in this AD are intended to

prevent the circuit breakers from

opening during flight, which could

result in irreversible loss of engine

indicating and fuel quantity systems in

the cockpit.

DATES: Effective December 23, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

23, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

January 7, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

286–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from

Bombardier Aviation Services, 1255

East Aeropark Boulevard, Tucson,

Arizona 85706. 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; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (562) 627–5350; fax (562)

627–5210.

SUPPLEMENTARY INFORMATION: The FAA

has received reports of three in-flight

occurrences of loss of all engine

indicating and fuel quantity systems in

the cockpit on certain Bombardier

Model CL–600–2B16 series airplanes. In

each case, the internal fuel/defuel panel

had been left in the ‘‘ON’’ position for

an extended period of time. When the

panel was switched off, all engine and

fuel quantity indications were lost;

subsequent attempts to cycle the panel

power back on were unsuccessful.

Investigation revealed an opened circuit

breaker. It was determined that, if power

to the remote fuel/defuel panel is left on

for up to approximately one hour, the

controlling circuit breaker on the battery

bus will have insufficient capacity to

hold the current flow and, as a result,

may open during flight. This condition,

if not corrected, could result in

irreversible loss of engine indicating

and fuel quantity systems in the cockpit.

Explanation of Relevant Service

Information

Bombardier has issued Service

Bulletin SB TUS–28–20–02–1, dated

November 13, 1997, which describes

procedures for disabling the remote

fuel/defuel panel in the cockpit.

Bombardier also has issued Service

Bulletin SB TUS–28–20–02, dated

November 13, 1997, which describes

procedures for modifying the remote

fuel/defuel panel; accomplishment of

this modification eliminates the need to

disable the panel. The modification

involves replacing certain circuit

breakers for the fuel/defuel power and

fuel quantity displays with new circuit

breakers, and adding three 4-pole relays

to allow switching of fuel quantity when

the internal fuel panel is selected.

U.S. Type Certification of the Airplane

This airplane model is manufactured

in Canada 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.