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.
16068 Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations

The commenter supports the rule as

proposed.

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 as proposed.

There are approximately 131 engines

of the affected design in the worldwide

fleet. The manufacturer has advised the

FAA that there are no engines installed

on U.S. registered aircraft that would be

affected by this AD. Therefore, there is

no associated cost impact on U.S.

operators as a result of this AD.

However, should an affected engine be

imported on an aircraft and placed on

the U.S. registry in the future, it will

take approximately 402 work hours to

accomplish the required actions, and

the average labor rate is $60 per work

hour. Required parts will cost

approximately $87,700 per engine.

Based on these figures, the cost impact

of the AD is estimated to be $111,820

per engine.

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

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:

97–06–01 CFM International: Amendment

39–9958. Docket 95–ANE–63.

Applicability: CFM International (CFMI)

CFM56–5, –5B, and –5C series turbofan

engines, installed on but not limited to

Airbus A320, A321, and A340 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 (h)

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 a failure of the stage 1 disk of

the high pressure compressor rotor (HPCR)

stage 1–2 spool, which could result in an

uncontained engine failure and damage to

the aircraft, accomplish the following:

(a) For CFM56–5, –5B, and –5C engines

that have a stationary number 3 bearing aft

air/oil seal, Part Number (P/N) 1364M71G02,

installed, inspect the stage 1 disk of the

HPCR stage 1–2 spool in accordance with the

Accomplishment Instructions of CFM56–5

Service Bulletin (SB) No. 72–440, CFM56–5B

SB No. 72–064, or CFM56–5C SB No. 72–229,

all Revision 2, dated June 23, 1995, as

applicable, as follows:

(1) If the disk has not been previously

inspected prior to the effective date of this

AD, inspect prior to accumulating 2,200

cycles since new (CSN).

(2) If the disk has been previously

inspected prior to the effective date of this

AD, and the disk was found not to be rubbed

or scratched, reinspect prior to accumulating

2,200 cycles since last inspection (CSLI).

(b) Thereafter, for disks that have been

inspected in accordance with paragraph

(a)(1) or (a)(2) of this AD, inspect in

accordance with the Accomplishment

Instructions of CFM56–5 SB No. 72–440,

CFM56–5B SB No. 72–064, or CFM56–5C SB

No. 72–229, all Revision 2, dated June 23,

1995, as applicable, at intervals not to exceed

2,200 CSLI.

(c) Remove from service HPCR stage 1–2

spools with rubbed or scratched stage 1 disks

and replace with a serviceable part, as

follows:

(1) For spools with less than 2,200 CSN on

the effective date of this AD, at the next

engine shop visit after the effective date of

this AD, or prior to accumulating 2,200 CSN,

whichever occurs first.

(2) For spools with 2,200 CSN or more on

the effective date of this AD, at the next

engine shop visit after the effective date of

this AD, or prior to accumulating 2,200 CSLI,

whichever occurs first.

(d) Remove from service stationary number

3 aft air/oil seals, P/N 1364M71G02, at the

next engine shop visit after the effective date

of this AD, and replace with a serviceable

part. Compliance with this paragraph

constitutes terminating action to the

inspection requirements of paragraphs (a)(1),

(a)(2), and (b) of this AD.

(e) For the purpose of this AD, a

serviceable HPCR stage 1–2 spool is defined

as a spool without a rub or scratch indication

on the stage 1 disk, a P/N 1834M55G01

spool, or a spool that has accomplished the

stage 1 disk rework in accordance with any

revision level of CFM56–5 SB No. 72–442,

CFM56–5B SB No. 72–066, or CFM56–5C SB

No. 72–230, as applicable.

(f) For the purpose of this AD, a serviceable

stationary number 3 bearing aft air/oil seal is

defined as any seal other than a P/N

1364M71G02 seal.

(g) For the purpose of this AD, an engine

shop visit is defined as the induction of an

engine into the shop for any reason.

(h) 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.

(i) 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.

(j) The actions required by this AD

shall be done in accordance with the

following CFMI SBs:

Document

No. Pages Revision Date

CFM56–5

SB No.

72–440.

1–9 2 June 23,

1995.

Total

pages:

9.

CFM56–5B

SB No.

72–064.

1–9 2 June 23,

1995.

Total

pages:

9.

CFM56–5C

SB No.

72–229.

1–9 2 June 23,

1995.
Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations 16069

Document

No. Pages Revision Date

Total

Pages:

9.

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.

(k) This amendment becomes effective

on June 3, 1997.

Issued in Burlington, Massachusetts, on

February 27, 1997.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–7979 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–131–AD; Amendment

39–9982; AD 97–07–08]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Jetstream Model

4101 airplanes, that requires the

replacement of weight limitation

placards in the aft main baggage bay and

in the aft right stowage compartment

with new placards indicating lower

maximum weight limits. It also requires

a revision of the Airplane Flight Manual

to delete references to the current higher

weight limits for these areas. This

amendment is prompted by a report

indicating that existing weight

limitations could result in failure of the

front bulkhead of the aft main baggage

bay and doors of the aft right stowage

compartment during emergency

dynamic landing conditions. The

actions specified by this AD are

intended to prevent such failure, which

consequently could result in injury to

passengers and flight crew, and hinder

evacuation of the airplane through the

exit adjacent to this bulkhead.

DATES: Effective May 9, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Jetstream Aircraft, Inc., P.O. Box

16029, Dulles International Airport,

Washington, DC 20041–6029. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., Suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1149.

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 certain Jetstream

Model 4101 airplanes was published in

the Federal Register on December 6,

1996 (61 FR 64643). That action

proposed to require removal of the

weight limitation placards in the aft

main baggage bay and aft right stowage

compartment, and replacement with

new placards that establish lower

maximum weight limits in these areas.

It also proposed to require a revision to

the AFM for certain airplanes that

would remove references to higher

weight limits in effect before the new

placards are installed.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter supports the

proposed AD.

Request to Withdraw Proposal

One commenter requests that the

proposal be withdrawn since there

would be no U.S. airplanes subject to it.

The commenter points out that the

applicability statement of the proposal

indicates that airplanes listed in

Jetstream Service Bulletin J41–11–004

would be subject to the AD. However,

that service bulletin states that it does

not affect any airplanes on which the

procedures specified in Jetstream

Service Bulletin J41–53–006 have been

accomplished. The commenter states

that only 18 U.S. airplanes would be

applicable to the proposed AD, and all

of those airplanes are owned by one

U.S. operator (the commenter). All of

these airplanes have been modified in

accordance with Jetstream Service

Bulletin J41–53–006. In light of this, the

proposal would not be applicable to any

U.S. airplane and, therefore, should be

withdrawn.

The FAA does not concur with the

commenter’s request to withdraw the

proposal, for the following reasons:

First, the FAA acknowledges that the

Cost Impact section of the preamble to

the notice erroneously indicated that 44

airplanes would be affected by the

proposed AD; although this number was

in error, the correct number of airplanes

affected is 25, not 18, as stated by the

commenter. (The referenced Jetstream

Service Bulletin J41–11–014 also lists a

total of 25 possibly affected airplanes.)

Accordingly, the Cost Impact

information, below, has been corrected

to show that 25 airplanes are affected by

the requirements of the AD.

Second, the FAA has no evidence to

prove that all 25 affected airplanes have

been modified in accordance with

Jetstream Service Bulletin J41–53–006,

and thus would not be subject to the

AD.

Third, even if all affected airplanes

have been modified in accordance with

Jetstream Service Bulletin J41–53–006,

the issuance of this AD is still necessary

to make it mandatory that the correct

placards are installed and the AFM

revision is accomplished on all affected

airplanes on the U.S. register. This AD

is also required to ensure that, if the

modification described in Service

Bulletin J41–53–006 is removed from a

modified airplane at a later date, the

placards and AFM revision required by

this AD are implemented.

Conclusion

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 as proposed.

Cost Impact

The FAA estimates that 25 Jetstream

Model 4101 airplanes of U.S. registry

will be affected by this AD, that it will

take approximately 1 work hour per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will be provided by the manufacturer at

no cost to operators. Based on these

figures, the cost impact of the AD on