33166 Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations

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.

Special Flight Permits

(i) 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.

Documents That Have Been Incorporated by

Reference

(j) The inspection shall be done in

accordance with the following Turbomeca

service bulletins (SBs):

Document No. Pages Revision Date

SB Artouste II SB 223 72 0070; Total pages: 16 ........................................ All .................................. Original ......................... Jan. 21, 1999.

SB Artouste III SB 218 80 0093; Total pages: 18 ....................................... All .................................. 2 .................................... Jan. 14, 1999.

SB Artouste III SB 218 80 0098; Total pages: 10 ....................................... All .................................. Original ......................... Jan. 14, 1999.

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 Turbomeca S.A., 40220 Tarnos, France;

telephone 33 05 59 64 40 00, fax 33 05 59

64 60 80. 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.

Note 3: The subject of this AD is addressed

in Direction Generale de L’Aviation Civile

(DGAC) Airworthiness Directive (AD) 1999–

005(A), dated January 13, 1999, and AD

1999–090(A), dated February 24, 1999.

Effective Date

(k) This amendment becomes effective on

July 26, 2001.

Issued in Burlington, Massachusetts, on

June 11, 2001.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 01–15392 Filed 6–20–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–30–AD; Amendment

39–12276; AD 2001–12–20]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company (GE) CF6–50

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to General Electric Company

(GE) CF6–50 turbofan engines. This

amendment requires removal of old

high pressure compressor (HPC) air

ducts and mating hardware and

replacement with newly designed air

ducts and reworked mating hardware.

This amendment also requires the

repetitive inspection of certain

reworked mating hardware. This

amendment is prompted by reports of

an uncontained low pressure turbine

(LPT) disk failure that resulted from an

air duct failure that caused a fan mid

shaft (FMS) separation. The actions

specified by this AD are intended to

prevent HPC air duct failures that could

result in FMS failures, that in turn could

result in rejected takeoffs or

uncontained LPT events, and to prevent

HPC rear shaft failures that could result

in uncontained engine failures.

DATES: Effective date July 26, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of July 26, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from General Electric Company via

Lockheed Martin Technology Services,

10525 Chester Road, Suite C, Cincinnati,

Ohio 45215, telephone: (513) 672–8400;

fax: (513) 672–8422. You may examine

the AD docket (including any comments

and service information) at the FAA,

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA

between 8:00 a.m. and 4:30 p.m.,

Monday through Friday, except Federal

holidays. You may also examine the

service information at the Office of the

Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Karen Curtis, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington MA

01803–5299; telephone: (781) 238–7192;

fax: (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that is applicable to GE

CF6–50 turbofan engines was published

in the Federal Register on November 24,

2000 (65 FR 70533). That action

proposed to require removal of old high

pressure compressor (HPC) air ducts

and mating hardware and replacement

with newly designed air ducts and

reworked mating hardware in

accordance with GE Aircraft Engines

(GEAE) Service Bulletin (SB) CF6–50

72–1200, dated May 8, 2000; GEAE

Alert Service Bulletin (ASB) CF6–50

72–A1200, Revision 1, dated July 20,

2000; or GEAE ASB CF6–50 72–A1200,

Revision 2, dated November 2,

2000.Those bulletins describe

procedures for removal of the HPC air

duct assembly, part numbers (P/N’s):

9128M36G03 / G04 / G05 / G06 / G08

/ G20 / G21 or 1644M16G03 and mating

hardware (rear shaft or stage 11–14

spool shaft) and replacement with the

new design air duct and reworked

mating hardware.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Typographical Error

One commenter notes that there is a

typographical error in paragraph (a) of

the proposed rule. The error is in the

P/N for the air duct assembly. There is

no P/N 99128M36G03. The FAA agrees,

and has changed the P/N reference from

99128M36G03 to 9128M36G03.

Cost of 3–9 Spool Inspections

One commenter requests that the cost

of the stage 3–9 spool inspections

required by other AD’s be included in

the cost analysis for this rule as well.

The FAA does not agree. The costs of

the stage 3–9 spool inspections required

by other AD’s were accounted for in the

rule making process for those rules. This

AD does not require additional stage 3–

9 spool inspections.

Shop Visit Definition

Two commenters request that the

definition of shop visit for this rule be

modified or clarified because they

believe that the shop visit definition in

the proposed rule will force

Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations 33167

incorporation of newly designed air

ducts and modification of the mating

hardware sooner than intended. The

FAA agrees. The definition in the

proposed rule would have required

incorporation of the redesigned air duct

at any time the HPC stage 2 disk flange

was disassembled or the HPC stage 1

disk was removed, for any reason. As

the commenters note, this occurs during

routine maintenance and tying the

replacement of the HPC air duct to that

triggering event would have an

unintended acceleration of the HPC air

duct replacement program. Therefore,

the FAA has changed the definition of

HPC rotor exposure. The requirements

of this AD are triggered on removal of

the stage 3–9 spool from the HPC rotor

structure, regardless of whether any

blades, locking lugs, bolts or balance

weights remain assembled to the spool.

This change will achieve the intended

rate of compliance for the redesigned air

duct incorporation while maintaining

an acceptable level of safety.

Revision of Economic Impact

Two commenters believe that the cost

analysis of the AD should be revised to

reflect a higher cost due to additional

maintenance or inspections that will be

needed once the HPC is disassembled to

piece-part level for the rework and

installation of the new air duct. The

FAA does not agree. The costs cited in

the proposal reflect the costs for

complying with this AD. Other potential

costs that may be incurred for other

reasons (i.e. normal maintenance or

other AD required inspections) are not

included in the cost analysis for the

actions required by this AD.

Inspection of Certain Reworked Rear

Shafts

In addition, a comment was received

to Docket No. 90–ANE–25–AD in

response to a Notice of Proposed

Rulemaking (NPRM) published on

October 12, 2000 (65 FR 60597) that

proposed to revise AD 91–10–03 R1.

That proposed revision was to add

reworked rear shaft part numbers to the

list of affected parts in AD 91–10–03 R1

to ensure that the necessary inspections

were continued following rework and

reidentification of the parts. The rework

is required in order to use these rear

shafts with the redesigned air duct, and

does not address the bolt hole condition

that prompted the inspection

requirements of 91–10–03 R1. The

commenter believed that the new

effective date of the proposed revision

to AD 91–10–03 R1 could be

misconstrued and result in parts

continuing in service without the

required inspections for longer than

intended by AD 91–10–03 R1.

The FAA agrees that the new

effectivity date of the proposed revision

to AD 91–10–03 R1 could reduce the

intended level of safety. Therefore, the

NPRM Docket No. 90–ANE–25–AD is

being withdrawn, and the requirement

to inspect the reworked shafts that was

proposed by that proposed rule has

instead been incorporated into this final

rule. Incorporation of the air duct

required by this rule also requires that

the existing rear shafts be reworked and

reidentified in order to be used with the

new air duct design. The rework

procedure requires that the rear shaft be

inspected at the time of the rework,

regardless of any prior inspection

history. Part of that inspection includes

the same fluorescent penetrant

inspection required by AD 91–10–03 R1.

If the part has not already received an

initial inspection in accordance with

AD 91–10–03 R1, it will receive the

necessary inspection as part of the

rework procedure. Therefore, the

repetitive inspection interval of 6,000

CSLI will be added to this AD for

reworked and reidentified rear shafts.

The additional cost for this inspection

has been added to the cost analysis for

this AD.

Finally, the applicability for this AD

now also reflects the reidentified rear

shafts. The total number of engines

affected by this AD, however, remains

the same because the incorporation of

the new air duct also requires

modification of the rear shaft.

Service Bulletin update

The FAA has added to paragraph (a)

a reference to GE Aircraft Engines Alert

Service Bulletin CF6–50 72–A1200,

Revision 3, dated May 30, 2001, as an

option by which to perform the required

air duct replacement and rework of the

mating hardware.

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 changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Economic Impact

There are about 1,730 engines of the

affected design in the worldwide fleet.

The FAA estimates that 469 engines

installed on aircraft of U.S. registry

would be affected by this AD, that it

would take about 70 work hours per

engine to disassemble and reassemble

the HPC module, that it would take 19

hours to rework the mating hardware,

that the repetitive inspection of each

reworked rear shaft would take two

hours, and that the average labor rate is

$60 per work hour. Each new air duct

assembly will cost $32,985. Based on

these figures, the total AD cost impact

on U.S. operators is estimated to be

$18,030,705.

Regulatory Impact

This final rule does not have

federalism implications, as defined in

Executive Order 13132, because it

would not have a substantial direct

effect 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.

Accordingly, the FAA has not consulted

with state authorities prior to

publication of this final rule.

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 the 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 final evaluation has

been prepared for this action and it is

contained 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, 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 a new airworthiness directive to

read as follows:

2001–12–20 General Electric Company

(GE) CF6–50 turbofan engines:

Amendment 39–12276. Docket 2000–

NE–30–AD.

33168 Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations

Applicability

This airworthiness directive (AD) is

applicable to General Electric Company (GE)

CF6–50 turbofan engines with high pressure

compressor (HPC) rotor air duct assemblies,

part numbers (P/N’s): 9128M36G03 / G04 /

G05 / G06 / G08 / G20 / G21, or 1644M16G03

installed. This AD is also applicable to CF6–

50 turbofan engines with HPC rear shaft P/

N’s: 1999M25P01 / P02 / P03 / P04 / P05 /

P06 / or P07 installed. These engines are

installed on but not limited to Boeing 747,

Airbus A300, and McDonnell Douglas DC10

airplanes.

Note 1: This 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 (d) 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

Compliance with the requirements of this

AD is required as indicated, unless already

done.

To prevent HPC air duct failures that could

result in fan mid shaft (FMS) failures and

uncontained low pressure turbine (LPT)

events, and to prevent HPC rear shaft failures

that could result in uncontained engine

failures, do the following:

(a) At next HPC rotor exposure, remove the

HPC air duct assembly P/N’s: 9128M36G03 /

G04 / G05 / G06 / G08 / G20 / G21 or

1644M16G03 and mating hardware (rear

shaft or stage 11–14 spool shaft) and replace

with the new design air duct and reworked

mating hardware in accordance with the

accomplishment instructions of GE Aircraft

Engines (GEAE) Service Bulletin (SB) CF6–50

72–1200, dated May 8, 2000; GEAE Alert

Service Bulletin (ASB) CF6–50 72–A1200,

Revision 1, dated July 20, 2000; GEAE ASB

CF6–50 72–A1200, Revision 2, dated

November 2, 2000; or GEAE ASB CF6–50 72–

A1200, Revision 3, dated May 30, 2001.

(b) Inspect rear shaft P/N’s: 1999M25P01 /

P02 / P03 / P04 / P05 / P06 / or P07 in

accordance with the Accomplishment

Instructions of GEAE ASB CF6–50 72–A0958,

Revision 3, dated May 25, 2001, at intervals

not to exceed 6,000 cycles since last

inspection.

(c) For the purposes of this AD, HPC rotor

exposure is defined as disassembly and

removal of the stage 3–9 spool from the HPC

rotor structure, regardless of whether any

blades, locking lugs, bolts or balance weights

remain assembled to the spool.

Alternative Methods of Compliance

(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 (ECO). Operators shall

submit their request through an appropriate

Federal Aviation Administration (FAA)

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Documents That Have Been Incorporated by

Reference

(e) The actions shall be done in accordance

with the following GE Aircraft Engines

service bulletin (SB) and alert service

bulletins (ASB’s):

Document No. Pages Revision Date

SB CF6–50 72–1200 .......................................................... All ......................................... Original ................................ May 8, 2000.

Total pages: 17

ASB CF6–50 72–A1200 ...................................................... All ......................................... 1 ........................................... July 20, 2000.

Total pages: 18

ASB CF6–50 72–A1200 ...................................................... All ......................................... 2 ........................................... November 2, 2000.

Total pages: 19

ASB CF6–50 72–A1200 ...................................................... All ......................................... 3 ........................................... May 30, 2001.

Total pages: 21

ASB CF6–50 72–A0958 ...................................................... All ......................................... 3 ........................................... May 25, 2001.

Total pages: 6

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 General Electric Company via Lockheed

Martin Technology Services, 10525 Chester

Road, Suite C, Cincinnati, Ohio 45215,

telephone: (513) 672–8400; fax: (513) 672–

8422. 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.

Effective Date

(f) This amendment becomes effective on

July 26, 2001.

Issued in Burlington, Massachusetts, on

June 13, 2001.

Wayne E. Gaulzetti,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–15446 Filed 6–20–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–33–AD; Amendment

39–12280; AD 2001–12–24]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B19 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Bombardier Model

CL–600–2B19 series airplanes, that

currently requires repetitive ultrasonic

inspection to detect damage of the

actuator lugs of the flight spoiler center

hinge; and corrective action, if

necessary. This amendment mandates

the previously optional terminating

action by requiring replacement of the

flight spoilers with new improved

spoilers. The actions specified by this

AD are intended to prevent

uncommanded deployment of a flight

spoiler, which could result in reduced

controllability of the airplane. This

action is intended to address the

identified unsafe condition.

DATES: Effective July 26, 2001.

The incorporation by reference of

certain publications, as listed in the

regulations, was approved previously by

the Director of the Federal Register as of

March 1, 2001 (66 FR 10187).

ADDRESSES: The service information

referenced in this AD may be obtained

from Bombardier, Inc., Canadair,

Aerospace Group, P.O. Box 6087,

Station Centreville, Montreal, Quebec

H3C 3G9, Canada. 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 FAA, New York