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

Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations 33169

Aircraft Certification Office, 10 Fifth

Street, Third Floor, Valley Stream, New

York; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7512; fax

(516) 568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 2001–03–04,

amendment 39–12107 (66 FR 10187,

February 14, 2001), which is applicable

to certain Bombardier Model CL–600–

2B19 series airplanes, was published in

the Federal Register on March 29, 2001

(66 FR 17094). The action proposed to

continue to require repetitive ultrasonic

inspection to detect damage of the

actuator lugs of the flight spoiler center

hinge; and corrective action, if

necessary. The action also proposed to

mandate the previously optional

terminating action by requiring

replacement of the flight spoilers with

new improved spoilers.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 195

Bombardier Model CL–600–2B19 series

airplanes of U.S. registry that will be

affected by this AD.

The inspections that are currently

required by AD 2001–03–04, and

retained in this new AD, take

approximately 2 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

currently required actions on U.S.

operators is estimated to be $23,400, or

$120 per airplane, per inspection cycle.

The new replacement that is required

by this AD will take approximately 4

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. The required parts will be

provided by the manufacturer at no cost

to the operators. Based on these figures,

the cost impact of the new replacement

required by this AD on U.S. operators is

estimated to be $46,800, or $240 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the requirements of this AD, and that no

operator would accomplish those

actions in the future if this AD were not

adopted. The cost impact figures

discussed in AD rulemaking actions

represent only the time necessary to

perform the specific actions actually

required by the AD. These figures

typically do not include incidental

costs, such as the time required to gain

access and close up, planning time, or

time necessitated by other

administrative actions.

Regulatory Impact

The regulations adopted herein will

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. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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

removing amendment 39–12107 (66 FR

10187, February 14, 2001), and by

adding a new airworthiness directive

(AD), amendment 39–12280, to read as

follows:

2001–12–24 Bombardier, Inc. (Formerly

Canadair): Amendment 39–12280.

Docket 2001–NM–33–AD. Supersedes

AD 2001–03–04, Amendment 39–12107.

Applicability: Model CL–600–2B19 series

airplanes, 7003 though 7340 inclusive;

certificated in any category.

Note 1: This AD applies to each airplane

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

airplanes 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 (e) 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 uncommanded deployment of a

flight spoiler, which could result in reduced

controllability of the airplane, accomplish

the following:

Restatement of Requirements of AD 2001–

03–04

Inspections

(a) Prior to the accumulation of 3,000 total

flight cycles or within 30 days after March 1,

2001 (the effective date of AD 2001–03–04,

amendment 39–12107): Perform

nondestructive evaluation procedure NDE

UT–35 (ultrasonic inspections) to detect

damage (e.g., cracking) of the actuator lugs on

both of the center hinge fittings of flight

spoilers part numbers (P/N) 600–10602–1001

and –1002, at spoiler stations 195.36 and

204.36; in accordance with Section 2,

Accomplishment Instructions, Part A of

Bombardier Alert Service Bulletin A601R–

57–027, Revision C, dated May 30, 2000. If

no damage is detected, repeat the inspection

at intervals not to exceed 500 flight cycles

until the requirements of paragraph (c) of this

AD have been accomplished.

Note 2: Accomplishment of the

nondestructive evaluation procedure in

accordance with Bombardier Alert Service

Bulletin A601R–57–027, dated April 19,

1999; Revision A, dated July 23, 1999; or

Revision B, dated December 8, 1999; is

acceptable for compliance with the

requirements of paragraph (a) of this AD.

Corrective Actions

(b) If any damage (e.g., cracking) is

detected during the inspection required by

paragraph (a) of this AD: Prior to further

flight, remove the damaged flight spoiler and

33170 Federal Register / Vol. 66, No. 120 / Thursday, June 21, 2001 / Rules and Regulations

perform nondestructive evaluation procedure

NDE ET–27 of the lug, per Section 2 of the

Accomplishment Instructions of Part B of

Bombardier Alert Service Bulletin A601R–

57–027, Revision C, dated May 30, 2000.

(1) If no damage is detected, repeat the

inspection required by paragraph (a) of this

AD at intervals not to exceed 500 flight

cycles until the requirements of paragraph (c)

of this AD have been accomplished.

(2) If any damage is detected, prior to

further flight, replace the damaged flight

spoiler with a new or serviceable flight

spoiler, per Bombardier Service Bulletin

601R–57–029, dated May 30, 2000.

(i) For a flight spoiler with no damage or

one that is replaced with a new or serviceable

flight spoiler: Repeat the inspection required

by paragraph (a) of this AD at intervals not

to exceed 500 flight cycles, until the

requirements of paragraph (c) of this AD have

been accomplished.

(ii) If both flight spoilers are replaced with

new improved spoilers, no further action is

required by this AD.

New Requirements of this AD

Replacement of Certain Flight Spoilers

(c) Within 36 months after the effective

date of this AD, replace any flight spoiler

having part number (P/N) 600–10602–1001

or 600–10602–1002 with a new improved

left-hand flight spoiler having P/N 600–

10602–73 or a new right-hand flight spoiler

having P/N 600–10602–74, as applicable; in

accordance with Bombardier Service Bulletin

601R–57–029, dated May 30, 2000. Such

replacement of both the left-hand and righthand flight spoilers constitutes terminating

action for the repetitive inspection

requirements of this AD.

Reporting Requirements

(d) Within 30 days of accomplishing the

inspection required by paragraph (a) of this

AD: Submit a report of any findings of

cracking to Bombardier, Inc., Canadair,

Aerospace Group, P.O. Box 6087, Station

Centre-ville, Montreal, Quebec H3C 3G9,

Canada. Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

Alternative Methods of Compliance

(e) 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, New York

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(f) 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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(g) The actions shall be done in accordance

with Bombardier Alert Service Bulletin

A601R–57–027, Revision C, dated May 30,

2000; and Bombardier Service Bulletin 601R–

57–029, dated May 30, 2000. The

incorporation by reference of these

documents was approved previously by the

Director of the Federal Register as of March

1, 2001 (66 FR 10187, February 14, 2001).

Copies may be obtained from Bombardier,

Inc., Canadair, Aerospace Group, P.O. Box

6087, Station Centre-ville, Montreal, Quebec

H3C 3G9, Canada. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, New York

Aircraft Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 4: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–15R1, dated February 22, 2001.

Effective Date

(h) This amendment becomes effective on

July 26, 2001.

Issued in Renton, Washington, on June 14,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–15573 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–NM–158–AD; Amendment

39–12277; AD 2001–12–21]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Boeing Model 747

series airplanes, that currently requires

revising the Airplane Flight Manual to

include procedures to prevent dry

operation of the center wing fuel tank

override/jettison pumps and, for certain

airplanes, to prohibit operation of the

horizontal stabilizer tank transfer

pumps in-flight. For certain airplanes,

this amendment requires installation of

improved fuel pumps, which terminates

the requirements of the existing AD.

This amendment is prompted by new

information received from the fuel

pump manufacturer. The actions

specified by this AD are intended to

prevent contact between the rotating

paddle wheel and the stationary end

plates within the center wing tank

override/jettison fuel pumps or

horizontal stabilizer tank transfer

pumps, which could cause sparks and/

or a hot surface condition and

consequent ignition of fuel vapor in the

center wing tank or horizontal stabilizer

tank during dry pump operation (no fuel

flowing).

DATES: Effective July 26, 2001.

ADDRESSES: Information pertaining to

this AD may be examined at the Federal

Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Sulmo Mariano, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2686; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–25–52,

amendment 39–10957 (63 FR 71214,

December 24, 1998), which is applicable

to all Boeing Model 747 series airplanes,

was published in the Federal Register

on November 20, 2000 (65 FR 69718).

The action proposed to require, for

certain airplanes, installation of

improved fuel pumps, which would

terminate the requirements of the

existing AD.

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.

Clarify Intent of Paragraph (b)

One commenter requests that the FAA

revise paragraph (b) of the proposed rule

to clarify that compliance with the

requirements of that paragraph

terminates the requirements of

paragraph (a) of the proposed rule. The

commenter points out that, while

paragraph (b) states that no further

action is required if it is determined that

the correct thrust washer is installed

under the guidelines in paragraphs

(b)(1), (b)(2), and (b)(3) of the proposed

rule, paragraph (b) does not state that

the operational limitations in paragraph

(a) are no longer necessary.