33530 Federal Register / Vol. 63, No. 118 / Friday, June 19, 1998 /Rules and Regulations

incorporated by reference in Type

Certificate No. E00054EN are 21.29 and

part 33, effective February 1, 1965, as

amended by Amendments 33–1 through

33–14, and Special Conditions SC–33–

ANE–05, Docket No. 95–ANE–46,

published on April 15, 1996 (61 FR

16375).

The Administrator finds that the

applicable airworthiness regulations in

part 33, as amended, do not contain

adequate or appropriate safety standards

for the additional new engine rating for

the Model Arriel 2S1 turboshaft engine

because it is a novel or unusual engine

rating feature, special conditions are

prescribed under the provision of 14

CFR 21.16.

Special conditions, as appropriate, are

issued in accordance with 14 CFR 11.49

after public notice, as required by

§§ 11.28 and 11.29(b), and become part

of the type certification basis in

accordance with 14 CFR 21.101(b)(2).

Novel or Unusual Design Features

The Turbomeca S.A., Model Arriel

2S1 turboshaft engine will incorporate

the following novel or unusual design

features: Rated 30-minute power. The

power available for rotorcraft hovering

to perform maritime search and rescue

missions is currently limited to the

maximum continuous rating power

under current part 33. The proposed

‘‘30-minute power’’ rating would

provide higher power level than

currently available for use up to 30

minutes at any time between takeoff and

landing in one flight. This new rating

will enhance rotorcraft safety through

the availability of increased power for

hovering operations calling for greater

than maximum continuous power.

Discussion of Comments

Interested persons have been afforded

the opportunity to participate in the

making of these special conditions. No

comments were received on the special

conditions as proposed. After careful

review of the available data, the FAA

has determined that air safety and the

public interest require the adoption of

the special conditions without change.

Applicability

As discussed above, these special

conditions are applicable to the

Turbomeca S.A., Model Arriel 2S1

turboshaft engine. Should Turbomeca

S.A., of Bordes, France, apply at a later

date for a change to the type certificate

to include another model incorporating

the same or novel or unusual design

feature, the special conditions would

apply to that model as well under the

provisions of 14 CFR 21.101(a)(1).

These special conditions provide

necessary increased hover time to

enable operators to better perform

critical, life-saving search and rescue

missions, particularly in overwater

situations. For this reason and because

a delay would not be in the public

interest, the FAA has determined that

good cause exists for adopting these

special conditions immediately upon

publication.

Conclusion

This action affects only certain novel

or unusual design features on one model

of engines. It is not a rule of general

applicability and it affects only the

applicant who applied to the FAA for

approval of these features on the engine.

List of Subjects in 14 CFR Part 33

Air transportation, Aircraft, Aviation

safety, Safety.

The authority citations for these

special conditions is as follows:

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

44702, 44704.

The Special Conditions

Accordingly, the Federal Aviation

Administration (FAA) proposes the

following special conditions as part of

the type certification basis for the

Turbomeca S.A., Model Arriel 2S1

turboshaft engine:

Section 33.4, Instructions for Continued

Airworthiness

(a) In addition to the requirements of

§ 33.4, the procedures must:

(1) Ensure that the engine

deterioration in service will not exceed

the level shown in certification using

the rated 30-minute rating.

(2) Be included in the airworthiness

limitations section of the Instructions

for Continued Airworthiness.

Section 33.7, Engine Ratings and

Operating Limitations

(a) In addition to the ratings provided

in § 33.7, a ‘‘Rated 30-minute power’’

rating is available, which shall be

defined as the approved brake

horsepower developed under static

conditions at specified altitudes and

temperatures within the operating

limitations established under part 33 of

this chapter, and limited in use to

periods of not over 30 minutes each.

Section 33.87, Endurance Test

(a) Unless already accomplished

under § 33.87(d), in addition to the

requirements of § 33.87, the following

test must be conducted:

Rated 30-minute power. Thirty

minutes at rated 30-minute power

during the twenty-five 6-hour

endurance test cycles.

Issued in Burlington, Massachusetts on

June 12, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–16359 Filed 6–18–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–46–AD; Amendment

39–10585; AD 98–12–32]

RIN 2120–AA64

Airworthiness Directives; CFM

International CFM56–2, –2A, –2B, –3,

–3B, and –3C Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to CFM International (CFMI)

CFM56–2, –2A, –2B, –3, –3B, and –3C

series turbofan engines, that requires a

one-time eddy current inspection (ECI)

for cracks or gouges in certain high

pressure turbine rotor (HPTR) disks.

This amendment is prompted by a

report of a HPTR disk found to have a

crack in a rim bolt hole during a routine

shop manual ECI. The actions specified

by this AD are intended to prevent the

potential for an uncontained failure of

the HPTR disk, which could result in an

inflight engine shutdown, aborted

takeoff, or damage to the aircraft.

DATES: Effective July 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 20,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from CFM International, Technical

Publications Department, 1 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 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:

Glorianne Messemer, Aerospace

Engineer, Engine Certification Office,
Federal Register / Vol. 63, No. 118 / Friday, June 19, 1998 /Rules and Regulations 33531

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; telephone

(781) 238–7132; fax (781) 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) CFM56–2, –2A, –2B, –3, –3B,

and –3C series turbofan engines was

published in the Federal Register on

January 22, 1998 (63 FR 3275). That

action proposed to require a one-time

eddy current inspection for cracks or

gouges in certain high pressure turbine

rotor (HPTR) disks in accordance with

CFM56–2 Service Bulletin (SB) No. 72–

817, dated January 14, 1997, CFM56–2A

SB No. 72–419, Revision 1, dated

January 31, 1997, CFM56–2B SB No.

72–561, Revision 1, dated January 31,

1997, and CFM56–3/–3B/–3C SB No.

72–843, dated January 14, 1997.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Three commenters support the rule as

proposed.

Since issuance of the proposed rule,

CFMI has revised CFM56–2 SB No. 72–

817, CFM56–2A SB No. 72–419, and

CFM56–3/–3B/–3C SB No. 72–843.

These revisions include an update of a

HPTR disk serial number identified in

Table 1. Therefore, since these SB

revisions do not alter the proposed

actions, this AD will include reference

to CFM56–2 SB No. 72–817, Revision 1,

dated November 25, 1997, CFM56–2A

SB No. 72–419, Revision 2, dated

November 14, 1997, and CFM56–3/–3B/

–3C SB No. 72–843, Revision 1, dated

November 25, 1997, for the

accomplishment of the HPTR disk

inspections.

In addition, this AD revises the

compliance date requirement for

CFM56–2, CFM56–3, –3B, and –3C

engines to 45 days after the 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 as proposed.

There are approximately 276 engines

of the affected design in the worldwide

fleet. The FAA estimates that 100

engines installed on aircraft of U.S.

registry will be affected by this AD, that

it will take approximately 300 work

hours per engine to accomplish the

required 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 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 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:

98–12–32 CFM International: Amendment

39–10585. Docket 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, Revision 1,

dated November 25, 1997, within 45 days

after the effective date of this AD.

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

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

dated November 14, 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, Revision 1, dated November 25,

1997, within 45 days after the effective date

of this AD.

(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
33532 Federal Register / Vol. 63, No. 118 / Friday, June 19, 1998 /Rules and Regulations

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.

(e) The actions required by this AD shall

be done in accordance with the following

CFMI SBs:

Document No. Pages Revision Date

CFM56–2 SB No. 72–817 ...................... 1–2 ......................................................... 1 ............................................................. November 25,

1997.

3–12 ....................................................... Original .................................................. January 14, 1997.

13 ........................................................... 1 ............................................................. November 25,

1997.

14–19 ..................................................... Original .................................................. January 14, 1997.

Total Pages: 19.

CFM56–2A SB No. 72–419 .................... 1–2 ......................................................... 2 ............................................................. November 14,

1997.

3–4 ......................................................... 1 ............................................................. January 31, 1997.

5–10 ....................................................... Original .................................................. January 14, 1997.

11–12 ..................................................... 2 ............................................................. November 14,

1997.

13–18 ..................................................... Original .................................................. January 14, 1997.

Total Pages: 18.

CFM56–2B SB No. 72–561 .................... 1 ............................................................. 1 ............................................................. January 31, 1997.

2 ............................................................. Original .................................................. January 14, 1997.

3–4 ......................................................... 1 ............................................................. January 31, 1997.

5–19 ....................................................... Original .................................................. January 14, 1997.

Total Pages: 19.

CFM56–3/–3B/–3C SB No. 72–843 ....... 1–2 ......................................................... 1 ............................................................. November 25,

1997.

3–11 ....................................................... Original .................................................. January 14, 1997.

12 ........................................................... 1 ............................................................. November 25,

1997.

13–18 ..................................................... Original .................................................. January 14, 1997.

Total Pages: 18.

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, 1

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 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.

(f) This amendment becomes effective

on July 20, 1998.

Issued in Burlington, Massachusetts, on

June 5, 1998.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 98–15785 Filed 6–18–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–CE–53–AD; Amendment 39–

10591; AD 98–13–03]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model H.P. 137 Mk1,

Jetstream Series 200, and Jetstream

Model 3101 Airplanes.

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 82–20–04

R1, which currently requires

repetitively inspecting the main landing

gear (MLG) hinge fitting, support angles,

and attachment bolts on British

Aerospace H.P. 137 Mk1 and Jetstream

series 200 airplanes, and repairing or

replacing any part that is cracked

beyond certain limits. This AD requires

installing improved design MLG fittings,

as terminating action for the repetitive

inspections that are currently required

by AD 82–20–04 R1, and will

incorporate the Jetstream Model 3101

airplanes into the Applicability of the

AD. The Federal Aviation

Administration’s policy on aging

commuter-class aircraft is to eliminate

or, in certain instances, reduce the

number of certain repetitive shortinterval inspections when improved

parts or modifications are available. The

actions specified by this AD are

intended to prevent structural failure of

the MLG caused by fatigue cracking,

which could result in loss of control of

the airplane during landing operations.

DATES: Effective August 3, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 3,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

British Aerospace Regional Aircraft,

Prestwick International Airport,

Ayrshire, KA9 2RW, Scotland;

telephone: (01292) 479888; facsimile:

(01292) 671715. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 95–CE–53–

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

Kansas City, Missouri 64106; or at the

Office of the Federal Register, 800 North