77774 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

comments may be submitted to the

Rules and Directives Branch, Office of

Administration, U.S. Nuclear Regulatory

Commission, Washington DC 20555.

FOR FURTHER INFORMATION CONTACT: E.

M. McKenna, Office of Nuclear Reactor

Regulation, U.S. Nuclear Regulatory

Commission, Washington DC 20555;

telephone (301) 415–2189; email

EMM@NRC.GOV.

SUPPLEMENTARY INFORMATION:

Background

The Nuclear Regulatory Commission

amended its rule, 10 CFR 50.59,

‘‘Changes, Tests, and Experiments’’ on

October 4, 1999 (64 FR 53582). This

amendment clarified the rule

requirements, and also provided

licensees greater flexibility to make

certain changes without NRC approval

that involve only minimal increases in

likelihood or consequences of events.

The implementation date of this

amendment was made dependent upon

guidance being issued to nuclear reactor

licensees on implementing the revised

requirements.

Regulatory Guide 1.187 endorses a

document prepared by the Nuclear

Energy Institute (NEI), NEI 96–07,

Revision 1, dated November 2000.

Regulatory Guide 1.187 was published

for public comment (65 FR 24231) as

DG–1095, ‘‘Guidance for

Implementation of 10 CFR 50.59,

Changes, Tests, and Experiments’’. The

comments submitted by licensees and

other commenters were addressed by

revisions made by NEI to NEI 96–07,

Revision 1, as submitted in November

2000; the NRC staff concurs in these

revisions.

Therefore, the effective date of the

October 4, 1999, amendment to 10 CFR

50.59 is March 13, 2001.

Dated at Rockville, Maryland, this 6th day

of December 2000.

For the Nuclear Regulatory Commission.

Annette Vietti-Cook,

Secretary of the Commission.

[FR Doc. 00–31735 Filed 12–12–00; 8:45 am]

BILLING CODE 7590–01–P 1

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–48–AD; Amendment

39–12029; AD 2000–24–22]

RIN 2120–AA64

Airworthiness Directives; S.N.

CENTRAIR Model 201B Gliders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all S.N. CENTRAIR Model

201B gliders. This AD requires you to

modify the rear canopy emergency

release system. This AD is the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for France. The

actions specified in this AD are

intended to prevent the rear canopy

retaining strap from not releasing

properly during the emergency egress

procedure because of the current design

of the rear canopy emergency release

system. This condition, if not corrected,

will not allow the rear canopy to

completely separate from the glider and

could result in potential injury to the

pilot during an emergency egress.

DATES: This AD becomes effective on

January 27, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of January 27, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

S.N. CENTRAIR, Aerodome—36300 Le

Blanc, France; telephone:

02.54.37.07.96; facsimile:

02.54.37.48.64. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

48–AD, 901 Locust, Room 506, Kansas

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION 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.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on all S.N.

CENTRAIR Model 201B gliders. The

DGAC reports an incident where a

Model 201B rear canopy strap did not

properly release during an actual

emergency egress.

The DGAC advises that the problem is

related to the unreliability of the rear

canopy in completely separating from

the glider during an emergency egress

procedure.

What are the consequences if the

condition is not corrected? If the rear

canopy retaining strap does not release

properly during the emergency egress

procedure, the rear canopy will not

completely separate from the glider.

This could result in potential injury to

the pilot during an emergency egress.

Has FAA taken any action to this

point? We issued a proposal to amend

part 39 of the Federal Aviation

Regulations (14 CFR part 39) to include

an AD that would apply to all S.N.

CENTRAIR Model 201B gliders. This

proposal was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on September 29,

2000 (65 FR 58495). The NPRM

proposed to require you to install a

mechanism that automatically releases

the rear canopy strap when the

emergency canopy lever is actuated.

Was the public invited to comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. No comments were

received on the proposed rule or the

FAA’s determination of the cost to the

public.

The FAA’s Determination

What is FAA’s Final Determination on

this Issue? After careful review of all

available information related to the

subject presented above, we have

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. We determined

that these minor corrections:

—will not change the meaning of the

AD; and

—will not add any additional burden

upon the public than was already

proposed.

Compliance Time of this AD

What is the compliance time of this

AD? The compliance time of this AD is

‘‘within the next 3 months after the

effective date of this AD.’’

Why is the compliance time presented

in calendar time instead of hours timein-service (TIS)? Although the rear

canopy retaining strap not releasing

properly during the emergency egress

Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations 77775

procedure occurs during flight, the

condition is not a direct result of glider

operation. The chance of this situation

occurring is the same for a glider with

10 hours TIS as it would be for a glider

with 500 hours TIS. A calendar time for

compliance will assure that the unsafe

condition is addressed on all gliders in

a reasonable time period.

What are the differences between the

French AD and this AD?

The French AD requires installation

of a mechanism that automatically

releases the rear canopy strap when the

emergency canopy lever is actuated. The

French AD also requires a visual

inspection to ensure that the

modification is incorporated correctly.

The FAA does not require this

inspection because we believe that the

procedures are adequate to allow the

maintenance personnel to accomplish

the action correctly.

Cost Impact

How many gliders does this AD

impact? We estimate that this AD affects

41 gliders in the U.S. registry.

What is the cost impact of this AD on

owners/operators of the affected gliders?

We estimate the following costs to

accomplish the modification:

Labor cost Parts cost Total cost per glider

Total cost

on U.S.

Operators

4 workhours × $60 per hour = $240 ......... $150 per glider .......................................... $390 per glider .......................................... $15,990

Regulatory Impact

Does this AD impact various entities?

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.

Does this AD involve a significant rule

or regulatory action? 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 copy of the final

evaluation prepared for this action 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, under 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. FAA amends § 39.13 by adding a

new AD to read as follows:

2000–24–22 S.N. Centrair: Amendment 39–

12029; Docket No. 2000–CE–48–AD.

(a) What gliders are affected by this AD?

This AD affects Model 201B gliders, all serial

numbers, certificated in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above gliders must comply with this AD.

(c) What problem does this AD address?

The actions specified in this AD are intended

to prevent the rear canopy retaining strap

from not releasing properly during the

emergency egress procedure because of the

current design of the rear canopy emergency

release system. This condition, if not

corrected, will not allow the rear canopy to

completely separate from the glider and

could result in potential injury to the pilot

during an emergency egress.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance times Procedures

(1) Install a mechanism that automatically releases the rear canopy strap when the emergency canopy lever is actuated.Within the next 3 months after January 27,

2001 (the effective date of AD).

Follow the procedures in 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 (or the instructions provided with the

modification kit). The document specified

above is referenced in S.N. CENTRAIR

Service Bulletin No. 201–16, Revision 1,

dated December 12, 1999. The inspection

referenced in the service bulletin is not required by this AD.

(2) Do not install a rear canopy emergency release system without incorporating the modification referenced in paragraph (d)(1) of this

AD.

As of January 27, 2001 (the effective date of

this AD).

Not Applicable.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

Note 1: This AD applies to each glider

identified in paragraph (a) of this AD,

regardless of whether it has been modified,

altered, or repaired in the area subject to the

requirements of this AD. For gliders 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)

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–