16066 Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations

exceed 800 hours TIS, or 12 calendar months

since last dye penetrant inspection,

whichever occurs first.

(iii) If cracks are discovered that are not

within the rework limits described in Section

III of the ASB, prior to further flight remove

the propeller from service and replace with

a serviceable part.

(iv) If cracks are discovered that are within

the rework limits described in Section III of

the ASB, prior to further flight rework the

propeller in accordance with Section III of

the SB, and resume inspecting repetitively in

accordance with paragraph (a)(1)(ii) of this

AD.

(2) For propellers with less than 3,000

hours TIS on the effective date of this AD,

upon accumulating 3,000 hours TIS perform

the steps required by paragraph (a)(1)(i)

through (a)(1)(iv) of this AD.

(b) 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. The request

should be forwarded through an appropriate

FAA 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.

(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 aircraft to

a location where the inspection requirements

of this AD can be accomplished.

(d) The actions required by this AD shall

be accomplished in accordance with the

following McCauley Propeller Systems ASB:

Document No. Page Date

221B .............. 1–22 December 16, 1996.

Total Pages: 22.

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 McCauley Propeller Systems 3535

McCauley Drive, P.O. Drawer 5053, Vandalia,

OH 45377–5053; telephone (513) 890–5246,

fax (513) 890–6001. 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.

(e) This amendment supersedes priority

letter AD 95–21–01, issued September 29,

1995.

(f) This amendment becomes effective on

April 24, 1997.

Issued in Burlington, Massachusetts, on

March 11, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–7594 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–63; Amendment 39–

9957; AD 97–05–13]

RIN 2120–AA64

Airworthiness Directives; CFM

International CFM56–5 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to CFM International

CFM56–5 series turbofan engines, that

requires rework of the air turbine engine

starter. This amendment is prompted by

three reports of air turbine engine starter

failures. The actions specified by this

AD are intended to prevent an air

turbine engine starter failure, which

could result in damage to the engine

electrical harnesses.

DATES: Effective June 3, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 3,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from CFM International, Technical

Publications Department, One Neumann

Way, Cincinnati, OH 45215; telephone

(513) 552–2981, fax (513) 552–2816.

This information may be examined at

the Federal Aviation Administration

(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.

FOR FURTHER INFORMATION CONTACT:

Glorianne Messemer, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; telephone

(617) 238–7132; fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to CFM International

(CFMI) CFM56–5 series turbofan

engines was published in the Federal

Register on April 15, 1996 (61 FR

16420). That action proposed to require

rework of the air turbine engine starter.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Two commenters support the rule as

proposed.

Although no comments were received

regarding the compliance end-date

stated in the compliance section of the

proposed rule, the FAA has revised the

calendar end-date to July 31, 1997,

based upon the anticipated effective

date of this AD.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

The FAA estimates that 190 engines

installed on aircraft of U.S. registry will

be affected by this AD, that it will take

approximately 2 work hours per engine

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Required parts will cost

approximately $2,400 per engine. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $478,800.

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.

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)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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
Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations 16067

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:

97–05–13 CFM International: Amendment

39–9957. Docket 95–ANE–63.

Applicability: CFM International (CFMI)

CFM56–5 series turbofan engines, installed

with air turbine engine starter, Part Number

301–781–201–0, installed on but not limited

to Airbus A320 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 (b)

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 on or before July 31,

1997, unless accomplished previously.

To prevent an air turbine engine starter

failure, which could result in damage to the

engine electrical harnesses, accomplish the

following:

(a) For air turbine engine starters, Part

Number 301–781–201–0, that have not been

previously reworked in accordance with any

revision level of CFMI CFM56–5 Service

Bulletin (SB) No. 80–003, rework the air

turbine engine starter in accordance with the

Accomplishment Instructions of CFMI

CFM56–5 SB No. 80–003, Revision 5, dated

October 25, 1994.

(b) 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. The request should be

forwarded 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.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(d) The actions required by this AD shall

be done in accordance with the following

CFMI SB:

Document

No.

Pages Revision Date

CFM56–

5 SB

No.

80–

003.

1–3 5 ........ October 25,

1994.

4–13 Original.July 16, 1991.

Total Pages: 13.

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 CFM International,

Technical Publications Department, One

Neumann Way, Cincinnati, OH 45215;

telephone (513)552–2981, fax (513)552–

2816. 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.

(e) This amendment becomes effective

on June 3, 1997.

Issued in Burlington, Massachusetts, on

February 24, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service. 

[FR Doc. 97–7977 Filed 4–3–97; 8:45 am]

[FR Doc. 97–7977 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–65; Amendment 39–

9958; AD 97–06–01]

RIN 2120–AA64

Airworthiness Directives; CFM

International CFM56–5, –5B, and –5C

Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to CFM International

CFM56–5, –5B, and –5C series turbofan

engines, that requires initial and

repetitive borescope inspections of the

stage 1 disk bore of certain high

pressure compressor rotor (HPCR) stage

1–2 spools for rubs and scratches, and

replacement, if found rubbed or

scratched, with a serviceable part. This

AD also requires removal and

replacement of certain stationary

number 3 bearing aft air/oil seals as

terminating action to the inspection

program. This amendment is prompted

by a report of an engine found with a

rub on the forward corner of the HPCR

stage 1 disk bore due to contact with the

stationary number 3 bearing aft air/oil

seal. The actions specified by this AD

are intended to prevent a failure of the

stage 1 disk of the HPCR stage 1–2

spool, which could result in an

uncontained engine failure and damage

to the aircraft.

DATES: Effective June 3, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 3,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from CFM International, Technical

Publications Department, One Neumann

Way, Cincinnati, OH 45215; telephone

(513) 552–2981, fax (513) 552–2816.

This information may be examined at

the Federal Aviation Administration

(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.

FOR FURTHER INFORMATION CONTACT:

Robert J. Ganley, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7138;

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to CFM International

(CFMI) CFM56–5, –5B, and –5C series

turbofan engines was published in the

Federal Register on June 4, 1996 (61 FR

28112). That action proposed to require

initial and repetitive borescope

inspections of the stage 1 disk bore of

certain high pressure compressor rotor

(HPCR) stage 1–2 spools for rubs and

scratches, and replacement, if found

rubbed or scratched, with a serviceable

part. That action also proposed to

require removal and replacement of

certain stationary number 3 bearing aft

air/oil seals as terminating action to the

inspection program.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.