77776 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Mike Kiesov, Aerospace

Engineer, FAA, Small Airplane Directorate,

901 Locust, Room 301, Kansas City, Missouri

64106; telephone: (816) 329–4144; facsimile:

(816) 329–4090.

(g) What if I need to fly the glider to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your glider to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

S.N. CENTRAIR Service Bulletin No. 201–16,

Revision 1, dated December 12, 1999, and

S.N Centrair Process Sheet for Fitment of the

Release Unit for the Rear Canopy Strap on

Glider Centrair 201 ‘‘Marianne’’, dated March

17, 1999 (including photo 1A added to page

3 or November 8, 1999). The instructions

provided with the modification kit also

include these procedures. The Director of the

Federal Register approved this incorporation

by reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from S.N.

CENTRAIR, Aerodome 36300 Le Blanc,

France; telephone: 02.54.37.07.96; facsimile:

02.54.37.48.64. You can look at copies at the

FAA, Central Region, Office of the Regional

Counsel, 901 Locust, Room 506, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW, suite

700, Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on January 27, 2001.

Note 2: The subject of this AD is addressed

in French AD 1999–055(A)R1, dated

February 5, 2000.

Issued in Kansas City, Missouri, on

November 28, 2000.

William J. Timberlake,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–30903 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–37–AD; Amendment

39–12031; AD 2000–24–24]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

plc RB211 Trent 768–60, Trent 772–60,

and Trent 772B–60 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Rolls-Royce plc RB211

Trent 768–60, Trent 772–60, and Trent

772B–60 series turbofan engines having

common nozzle assembly part number

(P/N) FK16544 or FK16558. This action

requires initial and repetitive visual

inspections of the inner and outer skins

of the common nozzle assembly and

specifies allowable limits for cracks,

loose rivets, and missing rivets. This

action also requires repair if the

common nozzle assembly damage

exceeds allowable limits. This

amendment is prompted by two reports

of in-flight inner skin detachment. The

actions specified in this AD are

intended to detect cracks, loose rivets,

and missing rivets, which could result

in inner skin detachment, release of

common nozzle assembly debris from

the engine, and possible damage to the

airplane control surfaces.

DATES: Effective January 12, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of January 12, 2001.

Comments for inclusion in the Rules

Docket must be received on or before

February 12, 2001.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2000–NE–37–AD, 12 New

England Executive Park, Burlington, MA

01803–5299. Comments may also be

sent via the Internet using the following

address: ‘‘9-ane-adcomment@faa.gov’’.

Comments sent via the Internet must

contain the docket number in the

subject line.

The service information referenced in

this AD may be obtained from RollsRoyce 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. This

information may be examined 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.

FOR FURTHER INFORMATION CONTACT:

Keith Mead, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone: 781–238–7744;

fax: 781–238–7199.

SUPPLEMENTARY INFORMATION: The Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom (UK), recently notified the

Federal Aviation Administration (FAA)

that an unsafe condition may exist on

Rolls-Royce plc (RR) RB211 Trent 768–

60, Trent 772–60, and Trent 772B–60

series turbofan engines having common

nozzle assembly P/N FK16544 or

FK16558. The CAA received reports of

cracking and rivet loss on the outer and

inner skin of the common nozzle

assembly, with two reports of inner skin

detachment. Rolls-Royce has

determined that cracks and detachment

of inner skin, and cracks of outer skin

occurred due to a combination of

missing rivets, loose rivets, and high

stress levels on common nozzle

assemblies with a high number of flight

cycles. This condition, if not corrected,

could result in inner skin detachment,

release of common nozzle assembly

debris from the engine, and possible

damage to the airplane control surfaces.

The compliance times specified in this

AD are based on Rolls-Royce service

bulletin criteria and CAA

recommendations.

Manufacturer’s Service Information

RR has issued Mandatory Service

Bulletin (MSB) No. RB.211–78–C931,

Revision 1, dated June 13, 2000, that

specifies procedures for initial visual

inspections of inner and outer skin,

including allowable limits, for cracks,

missing rivets, and loose rivets. The

MSB also specifies repair for common

nozzle assemblies that are out of limits.

The MSB also specifies on common

nozzle assemblies with more than 1,500

cycles-since-new, initial visual

inspections for cracks in inner and outer

skins, missing rivets, loose rivets not

later than 500 flight hours after release

of AD, and repetitive inspections within

500 flight hours since the last

inspection. The CAA classified this

MSB as mandatory and issued

airworthiness directive (AD) 005–06–

Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations 77777

2000 in order to ensure the

airworthiness of these engines in the

UK.

Bilateral Airworthiness Agreement

This engine model is manufactured in

the UK and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. As required by

this bilateral airworthiness agreement,

the CAA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for engines of this type design that

could be used on airplanes certificated

for operation in the United States.

Required Actions

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design that could be used on

airplanes registered in the United States,

this AD requires initial and repetitive

in-service visual inspections of the

common nozzle assembly to detect

cracks, missing rivets, and loose rivets,

including allowable acceptance limits.

This AD also requires repair for

common nozzle assemblies that are out

of limits. The actions must be done in

accordance with the MSB described

previously.

Immediate Adoption

A situation exists that allows the

immediate adoption of this regulation.

Since there are currently no domestic

operators of this engine model, notice

and opportunity for prior public

comment are unnecessary.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

to the address specified under the

caption ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NE–37–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

This proposal does not have

federalism implications, as defined in

Executive Order (EO) 13132, because it

would not have 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 proposal.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under EO 12866. It has been

determined further that this action

involves an emergency regulation under

DOT Regulatory Policies and Procedures

(44 FR 11034, February 26, 1979). If it

is determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

2000–24–24 Rolls-Royce plc: Amendment

39–12031. Docket 2000–NE–37–AD.

Applicability: This airworthiness directive

(AD) is applicable to Rolls-Royce plc (RR)

RB211 Trent 768–60, Trent 772–60, and

Trent 772B–60 series turbofan engines having

common nozzle assembly part number (P/N)

FK16544 or FK16558 installed. These

engines are installed on but not limited to

Airbus A330–341 and A330–342 series

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 (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 detect cracking, loose rivets, and

missing rivets on common nozzle assembly

P/N FK16544 or FK16558, which could result

in inner skin detachment, release of exit

nozzle debris from the engine, and possible

damage to the airplane control surfaces, do

the following:

Initial Inspection

(a) Visually inspect all common nozzle

assemblies for cracks, missing rivets, and

loose rivets, within 500 flight hours after the

effective date of this AD, and disposition in

accordance with Accomplishment

Instructions, Paragraph 3A of RR Mandatory

Service Bulletin (MSB) No. RB.211–78–C931,

Revision 1, dated June 13, 2000.

Repetitive Inspections

(b) Thereafter, on common nozzle

assemblies that have greater than 1,500

cycles-since-new, do repetitive visual

inspection for cracks, loose rivets, and

missing rivets, within 500 flight hours since

the last inspection, and disposition in

accordance with Accomplishment

Instructions, Paragraph 3A of RR MSB No.

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

2000.

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.