Federal Register / Vol. 65, No. 128 / Monday, July 3, 2000 / Rules and Regulations 40983

(2) For all other stage 1 turbine wheel SNs

with P/Ns 23065891 and 23062373, replace

before accumulating 13,100 engine CSN.

(b) Remove stage 2 turbine wheels, P/Ns

23065892 and 23063462, and replace with

new or serviceable parts as follows:

(1) For stage 2 turbine wheels with SNs

listed in Table 6 of Rolls-Royce ASB AE

3007A–A–72–105 and AE 3007C–A–72–105,

dated January 29, 1999, replace before

accumulating 7,800 engine CSN.

(2) For all other stage 2 turbine wheel SNs

with P/Ns 23065892 and 23063462, replace

before accumulating 8,400 engine CSN.

Alternative Life Limits

(c) This AD establishes new cyclic life

limits for the turbine wheels identified in

paragraphs (a) and (b) of this AD. Except in

accordance with paragraph (d) of this AD, no

alternative life limits may be approved for

the turbine wheels identified in paragraphs

(a) and (b) of this AD.

Alternative Method 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, Chicago

Aircraft Certification Office. Operators shall

submit their request through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Chicago Aircraft Certification

Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

Aircraft Certification Office.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the aircraft to a

location where the requirements of this AD

can be accomplished.

Documents Incorporated by Reference

(f) This AD references Rolls-Royce Alert

Service Bulletin AE 3007A–A–72–105/AE

3007C–A–72–105, dated January 29, 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 Rolls-Royce Allison, P.O. Box 420,

Indianapolis, IN 46206–0420; telephone:

(888) 255–4766. 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

(g) This amendment becomes effective on

September 1, 2000.

Issued in Burlington, Massachusetts, on

June 19, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–16232 Filed 6–30–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–05–AD; Amendment

39–11804; AD 2000–13–05–AD]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

plc. RB211 Trent 768–60, Trent 772–60,

and Trent 772B–60 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. (RR)

RB211 Trent 768–60, Trent 772–60, and

Trent 772B–60 turbofan engines. This

action requires initial and repetitive

ultrasonic inspections for cracks in fan

blade dovetail roots, and if necessary,

replacement with serviceable parts. This

amendment is prompted by reports of

fan blade failures due to dovetail root

cracks. The actions specified in this AD

are intended to prevent possible

multiple fan blade failures, which could

result in an uncontained engine failure

and damage to the airplane.

DATES: Effective August 2, 2000. The

incorporation by reference of certain

publications listed in the rule is

approved by the Director of the Federal

Register as of August 2, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

September 1, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2000–NE–

05–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@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: 011–44–1332–249428; fax

011–44–1332–249223. 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:

James Lawrence, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone 781–238–7176;

fax 781–238–7199.

SUPPLEMENTARY INFORMATION: The Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom (U.K.), recently notified the

FAA that an unsafe condition may exist

on Rolls-Royce plc. (RR) RB211 Trent

768–60, Trent 772–60, and Trent 772B–

60 turbofan engines with fan blade part

numbers (P/N’s) FK22580, FK23411,

FK25441, and FK25968 installed. The

CAA received a report of multiple fan

blade root cracks in a factory engine. A

recent inspection of a set of fan blades

from a factory fleet leader test engine

has identified small cracks in the blade

roots on the convex root flank. To date,

this is the only engine that has exhibited

the blade root cracks. This condition, if

not corrected, could result in possible

multiple fan blade failures, which could

result in an uncontained engine failure

and damage to the airplane.

Manufacturer’s Service Information

Rolls-Royce plc (RR) has issued

service bulletin (SB) No. RB.211–72–

C878, Revision 1, dated December 10,

1999, that specifies procedures for

ultrasonic inspections for cracks in fan

blade dovetail roots. The CAA classified

this SB as mandatory and issued

airworthiness directive (AD) 003–11–99

in order to assure the airworthiness of

these engines in the U.K.

Differences Between This AD and the

Manufacturer’s Service Information

This AD applies only to those engines

with fan blades having four specific part

numbers. The manufacturer’s service

bulletin is not limited in that fashion.

The FAA expects that future changes in

the design of the affected fan blades will

eliminate the need for the required

inspections and that those newer fan

blades will have different part numbers.

The installation of the newer part

number will therefore have the effect of

removing the engine from the

applicability of this AD.

Bilateral Airworthiness Agreement

This engine model is manufactured in

the U.K. 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. Pursuant to

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

40984 Federal Register / Vol. 65, No. 128 / Monday, July 3, 2000 / Rules and Regulations

for products of this type design that are

certificated for operation in the United

States.

Requirements of This AD

Although none of these affected

engine models are used on any airplanes

that are registered in the United States,

the possibility exists that the engine

models could be used on airplanes that

are registered in the United States in the

future. Because an unsafe condition has

been identified that is likely to exist or

develop on other RR RB211 Trent 768–

60, Trent 772–60, and Trent 772B–60

series turbofan engines of the same type

design, with fan blade P/N’s FK22580,

FK23411, FK25441, and FK25968

installed, this AD requires:

• Initial ultrasonic inspections within

200 cycles after the effective date of this

AD, or within 200 cycles of achieving

2,800 cycles since new, whichever is

later; and

• Repetitive ultrasonic inspection of

the fan blade root within 340 cycles

since the last inspection.

The actions are required to be

completed in accordance with the

service bulletin described previously.

Immediate Adoption

Since there are currently no domestic

operators of this engine model, notice

and opportunity for prior public

comment are unnecessary. Therefore, a

situation exists that allows the

immediate adoption of this regulation.

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

in triplicate 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–05–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

This proposed 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 proposed rule.

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 Executive Order 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:

2000–13–05 Rolls-Royce plc: Amendment

39–11804. Docket 2000–NE–05–AD.

Applicability

This AD is applicable to Rolls-Royce plc.

(RR) RB211 Trent 768–60, Trent 772–60, and

Trent 772B–60 turbofan engines with fan

blade part numbers (P/N’s) FK22580,

FK23411, FK25441, and FK25968 installed.

These engines are installed on but not

limited to Airbus A330–341 and A330–342

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

Compliance with this AD is required as

indicated below, unless already completed.

To prevent possible multiple fan blade

failures, which could result in an

uncontained engine failure and damage to

the airplane, do the following:

Ultrasonic Inspections

(a) Ultrasonically inspect the dovetail roots

of all fan blade P/N’s FK22580, FK23411,

FK25441, and FK25968 with more than 2800

cycles since new (CSN), for cracks as follows:

Initial Inspection

(1) Initially inspect the fan blade in

accordance with paragraph 3.A.(1) or

paragraph 3.B.(1) through paragraph 3.B.(8)

of RR service bulletin (SB) No. RB.211–72–

C878, revision 1, dated December 10, 1999,

at the later of the following:

(i) Within 200 fan blade cycles in service

(CIS) after the effective date of this AD; or

(ii) Within 200 fan blade CIS of achieving

2800 CSN.

Repetitive Inspections

(2) Thereafter, inspect at intervals not to

exceed 340 CIS, since last inspection, in

accordance with paragraph 3.A.(1) or

paragraph 3.B.(1) through paragraph 3.B.(8)

of RR SB No. RB.211–72–C878, revision 1,

dated December 10, 1999.

Alternative Methods 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

Federal Register / Vol. 65, No. 128 / Monday, July 3, 2000 / Rules and Regulations 40985

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 airworthiness directive,

if any, may be obtained from the ECO.

Special Flight Permits

(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 requirements of this AD

can be accomplished.

Incorporation by Reference Material

(d) The actions required by this AD shall

be performed in accordance with the

following service documents:

Document No. Pages Revision Date

RB.211–72–C878 ................................................................................. 1–2 ............................. 1 ................................. December 10, 1999

3–4 ............................. Original ....................... November 19, 1999

Appendix .................... Original ....................... November 19, 1999

Total pages: 7.

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: 011–44–1332–249428;

fax: 011–44–1332–249223. 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

(e) This amendment becomes effective on

August 2, 2000.

Issued in Burlington, Massachusetts, on

June 21, 2000.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–16231 Filed 6–30–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–196–AD; Amendment

39–11806; AD 2000–13–07]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes. This

AD requires repetitive detailed visual

and ultrasonic inspections of the main

landing gear (MLG) to detect fatigue

cracks, and repair if necessary;

replacement of certain nose landing gear

(NLG) handwheel controllers and

certain placards with new placards;

installation of steering angle recording

software; and corrective action for

exceeding certain steering angles. This

AD also requires an AFM revision to

limit the nose wheel steering angle for

pushback and towing and to limit the

nose wheel steering for powered turns.

This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent MLG failure due to

fatigue cracking, which could result in

reduced structural capability of the

airplane and collapse of the MLG.

DATES: Effective August 7, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 7,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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 Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Airbus Model

A330 and A340 series airplanes was

published in the Federal Register on

January 12, 2000 (65 FR 1833). That

action proposed to require repetitive

detailed visual and ultrasonic

inspections of the main landing gear

(MLG) to detect fatigue cracks, and

repair if necessary; replacement of

certain nose landing gear (NLG)

handwheel controllers and certain

placards with new placards; installation

of steering angle recording software;

corrective action for exceeding certain

steering angles; and an AFM revision to

limit the nose wheel steering angle for

pushback and towing and to limit the

nose wheel steering for powered turns.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received.

Request To Exclude Certain Airplanes

From Proposed Actions

The commenter (an operator) requests

that certain airplanes be excluded from

the actions specified in the proposed

AD. (Although the proposed rule

identifies no affected U.S.-registered

airplanes, the commenter has since

taken delivery of several Model A330

series airplanes.) Subsequent to

issuance of the proposed rule, the

manufacturer developed the following

production modifications for Model

A330 and A340 series airplanes (all of

which have been installed on the

commenter’s airplanes):

Modification 47487: Introduces scallop

on the growth main fitting of the main

landing gear (MLG)

Modification 47500: Introduces brake

steering and control unit (BSCU) S8D

for the MLG

Modification 47701: Provides for

application of markings for maximum

turning angle (±65 degrees) for towing

and pushback of the nose landing gear

doors

Modification 47787: Introduces ACMS

software to record nose wheel steering

angles exceeding 67 degrees during

towing and pushback

FAA Response

The FAA concurs with the request.

The Direction Ge ́ne ́rale de l’Aviation