77778 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

Alternative Methods of Compliance

(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 (ECO). Operators shall

submit their requests through an appropriate

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 AD, if any, may be

obtained from the ECO.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The actions required by this AD must

be performed in accordance with the

Accomplishment Instructions of RR MSB No.

RB.211–78–C931, Revision 1, dated June 13,

2000. 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 Rolls-Royce plc, PO Box 31, Derby,

England; telephone: International Access

Code 011, Country Code 44, 1332–249428,

fax: International Access Code 011, Country

Code 44, 1332–249223. 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 of This AD

(f) This amendment becomes effective on

January 12, 2001.

Issued in Burlington, Massachusetts, on

November 28, 2000.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–31113 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–33–AD; Amendment

39–12033; AD 2000–24–26]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

plc RB211 Trent 800 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Rolls-Royce plc

RB211 Trent 800 series turbofan

engines, that currently requires initial

and repetitive ultrasonic inspections of

fan blade roots for cracks, and

replacement, if necessary, with

serviceable parts. This amendment

requires the reduction of the initial

cyclic compliance threshold and

repetitive inspection intervals. This

amendment also allows inspections to

be accomplished within 100 cycles-inservice if the initial or repetitive

thresholds are exceeded on the effective

date of this AD. This amendment is

prompted by an improved

understanding of the crack propagation

mechanism and the latest service

operational data. The actions specified

by this AD are intended to detect and

prevent fan blade failure, which could

result in multiple fan blade releases,

uncontained engine failure, and

possible damage to the airplane.

DATES: Effective February 12, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of February 12, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Rolls-Royce North America, Inc.,

2001 South Tibbs Ave., Indianapolis, IN

46241; telephone: (317) 230–3995, fax:

(317) 230–4743. 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 01803–5299; or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Richard Woldan, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone: (781) 238–7136,

fax: (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–19–21,

Amendment 39–10762 (63 FR 50484,

September 22, 1998, corrected by 63 FR

52961, October 2, 1998), applicable to

Rolls-Royce plc (RR) RB211 Trent 800

series turbofan engines, was published

in the Federal Register on December 3,

1999 (64 FR 67806). That action

proposed to require the reduction of

initial compliance thresholds and

repetitive cyclic inspection intervals.

The action also proposed the allowance

for inspections to be accomplished

within 100 cycles-in-service if the initial

or repetitive thresholds are exceeded on

the effective date of the AD.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the one

comment received.

Request To Revise Economic Analysis

The comment states that all RR Trent

800 series engines on the US registry

that will be affected by the AD have

already been modified to RR Service

Bulletin RB.211–72–C629. Therefore,

the estimate of the total cost impact of

the proposed action on US operators is

zero.

The FAA disagrees. Although some

Trent 800 series engines on US

registered airplanes may have already

been modified to RR Service Bulletin

RB.211–72–C629 and the actual cost

may be reduced, the original economic

analysis is retained.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Regulatory Impact

This rule does not have federalism

implications, as defined in Executive

Order (EO) 13132, because it does 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

rule.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under EO

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.

Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations 77779

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration (FAA) 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 39–10762 (63 FR

50484, September 22, 1998) and by

adding a new airworthiness directive,

Amendment 39–12033, to read as

follows:

AD 2000—24–26 Rolls-Royce plc.:

Amendment 39–12033. Docket 98–ANE–

33–AD. Supersedes AD 98–19–21,

Amendment 39–10762.

Applicability: Rolls-Royce plc (RR) RB211

Trent 875, RB211 Trent 877, RB211 Trent

884, RB211 Trent 892, and RB211 Trent 892B

series turbofan engines, except if the fan

blades described in RR Service Bulletin (SB)

RB.211–72–C629 were installed as complete

sets. These engines are installed on but not

limited to Boeing 777 series airplanes.

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 as indicated, unless

accomplished previously.

To prevent fan blade failure, which could

result in multiple fan blade releases,

uncontained engine failure, and possible

damage to the airplane, accomplish the

following:

Ultrasonic Inspections (Reduced Thresholds

and Repetitive Intervals)

(a) Perform initial and repetitive

inspections of fan blade roots for cracks, in

accordance with RR SB No. RB211–72–C445,

Revision 6, dated September 3, 1999, as

follows:

(1) For Trent 875 series engines, inspect as

follows:

(i) Initially, prior to accumulating 3,000

cycles-since-new (CSN).

(ii) Thereafter, at intervals not to exceed

400 cycles-in-service (CIS) since last

inspection.

(2) For Trent 877 series engines, inspect as

follows:

(i) Initially, prior to accumulating 2,000

CSN.

(ii) Thereafter, at intervals not to exceed

350 CIS since last inspection.

(3) For Trent 884 series engines, inspect as

follows:

(i) Initially, prior to accumulating 1,500

CSN.

(ii) Thereafter, at intervals not to exceed

350 CIS since last inspection.

(4) For Trent 892 and 892B series engines,

inspect as follows:

(i) Initially, prior to accumulating 900 CSN.

(ii) Thereafter, at intervals not to exceed

200 CIS since last inspection.

Engines Exceeding Thresholds and

Repetitive Intervals

(5) For engines that exceed the initial

inspection thresholds listed in paragraphs

(a)(1)(i), (a)(2)(i), (a)(3)(i), and (a)(4)(i) on the

effective date of this AD, conduct initial

inspection within 100 CIS after the effective

date of this AD.

(6) For engines that exceed the repetitive

inspection intervals listed in paragraphs

(a)(1)(ii), (a)(2)(ii), (a)(3)(ii), and (a)(4)(ii) on

the effective date of this AD, inspect within

100 CIS after the effective date of this AD.

Cracked Parts

(7) Prior to further flight, remove from

service cracked fan blades and replace with

serviceable parts.

Alternate Method of Compliance

(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 (ECO). Operators shall

submit their requests through an appropriate

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 AD, if any, may be

obtained from the ECO.

Ferry Flights

(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 airplane to

a location where the inspection requirements

of this AD can be accomplished.

Incorporation by Reference Material

(d) The actions required by this AD must

be done in accordance with the following

Rolls-Royce SB:

Document No. Pages Revision Date

RB.211–72–C445 ............................ 1–9 ............................................... 6 ................................................... September 3, 1999.

Appendix 1 ...................................... 1 ................................................... Original ......................................... February 13, 1998.

2 ................................................... 6 ................................................... September 3, 1999.

3–4 ............................................... Original ......................................... February 13, 1998.

Appendix 2 ...................................... 1 ................................................... Revision 4 .................................... November 6, 1998.

2–3 ............................................... Original ......................................... February 13, 1998.

77780 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

Total pages: 16.

The incorporations by reference were

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 Rolls-Royce North America, Inc., 2001

South Tibbs Ave., Indianapolis, IN 46241;

telephone: (317) 230–3995; fax: (317) 230–

4743. Copies may be inspected at the FAA,

New England Region, Office of the Regional

Counsel, 12 New England Executive Park,

Burlington, MA 01803–5299; or at the Office

of the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

Effective Date

(e) This amendment becomes effective on

February 12, 2001.

Issued in Burlington, Massachusetts, on

November 30, 2000.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–31066 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–49–AD; Amendment

39–12037; AD 2000–25–03]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron Inc. Model 205A–1,

205B, 212, 412, and 412CF Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Bell Helicopter Textron Inc. (BHTI)

Model 205A–1, 205B, 212, 412, and

412CF helicopters. This action requires

inspecting the locking washer on each

main rotor actuator (actuator) for

twisting or damage to the tab and

replacing any locking washer that has a

twisted or damaged tab. Replacing

certain locking washers, regardless of

condition, is also required within a

specified time period. Installing a

certain airworthy locking device on

each actuator constitutes terminating

action for the requirements of this AD.

This amendment is prompted by an

incident in which a damaged locking

washer allowed the rod end to detach

from the collective actuator, causing

loss of collective control of the main

rotor. The current locking washer is

subject to mechanical damage and

failure, which allows the actuator piston

to unthread itself from its rod end. This

condition, if not corrected, could cause

loss of control of the main rotor and

subsequent loss of control of the

helicopter.

DATES: Effective December 28, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

28, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

February 12, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2000–SW–

49–AD, 2601 Meacham Blvd., Room

663, Fort Worth, Texas 76137. You may

also send comments electronically to

the Rules Docket at the following

address: 9-asw-adcomments@faa.gov.

The service information referenced in

this AD may be obtained from HR

Textron, 25200 W. Rye Canyon Road,

Santa Clarita, California 91355–1265,

telephone (611) 702–5509, fax (661)

702–5970. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Alfred Boutin, Aviation Safety Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Certification Office, Fort Worth, Texas

76193–0170, telephone (817) 222–5157,

fax (817) 222–5783.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new AD for BHTI

Model 205A–1, 205B, 212, 412, and

412CF helicopters. This AD requires,

within 25 hours time-in-service (TIS),

inspecting the tab on the NAS513–6

locking washer on all actuators, part

number (P/N) 41105950, serial number

with an ‘‘HR’’ prefix up to and

including 490 and P/N 41000470, serial

numbers with a prefix of ‘‘HR’’ up to

and including 10010, for a twisted or

damaged tab. P/N’s 41105950 and

41000470 were assigned by the

manufacturer; the BHTI P/N’s are 205–

076-036 and 212–076–005. Replacing

any twisted or damaged locking washer

with an airworthy NAS1193K6C locking

device is required before further flight.

Replacing any NAS513–6 locking

washer with an airworthy NAS1193K6C

locking device, regardless of the

condition of the tab, is required within

100 hours TIS or at the next actuator

overhaul, whichever occurs first.

Installing an airworthy NAS 1193K6C

locking device on all actuators

constitutes terminating action for the

requirements of this AD. This AD is

prompted by the discovery of a damaged

locking washer. The damage to the

locking washer was discovered when an

operator experienced a problem with a

collective control while attempting to

take off. The collective control could not

be moved upward from the full down

position. Further inspection revealed

that the lower piston of the actuator had

unthreaded and separated from the

lower rod end, causing the piston to

make contact with the rod end support

assembly and lodge itself against the rod

end shank at an angle limiting any

movement of the collective control. The

collective servo cylinder assembly is

used to provide irreversible collective

control of the main rotor. Because the

actuator end locking washer failed, the

servo lower piston could rotate inside

the lower servo head assembly and

unthread itself from the rod end. This

condition, if not corrected, could cause

loss of control of the main rotor and

subsequent loss of control of the

helicopter.

The FAA has reviewed HR Textron

Alert Service Bulletin (ASB) No.

41000470–67A–05, Revision 1 and HR

Textron ASB No. 41105950–67A–01,

Basic Issue, both dated October 19,

2000, which describe procedures for

inspecting and replacing certain locking

washers. BHTI has issued ASB No.’s

205–00–79, 205B–00–33, 212–00–109,

412–00–105, and 412CF–00–12, all

dated October 19, 2000, which include

the applicable HR Textron Alert Service

Bulletins.

Since an unsafe condition has been

identified that is likely to exist or

develop on other BHTI Model 205A–1,

205B, 212, 412, and 412CF helicopters

of the same type designs, this AD is

being issued to prevent an actuator

piston from unthreading itself from its

rod end causing loss of collective

control and subsequent loss of control of

the helicopter. This AD requires

inspecting the locking washers on all

actuators for twisting or damage to the

tab and replacing any locking washer

that has a twisted or damaged tab.

Replacing certain locking washers,

regardless of condition, is also required

within 100 hours TIS or at the next

actuator overhaul, whichever occurs

first. Installing an airworthy

NAS1193K6C locking device on all

actuators constitutes terminating action

for the requirements of this AD. The

actions must be accomplished in

accordance with the HR Textron service

bulletins described previously. The

short compliance time involved is

required because the previously

described critical unsafe condition can