This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

67477

Vol. 66, No. 250

Monday, December 31, 2001

OFFICE OF PERSONNEL

MANAGEMENT

5 CFR Part 550

Pay Administration (General)

AGENCY: Office of Personnel

Management.

ACTION: Technical amendment.

SUMMARY: This document contains a

technical amendment to the final

regulation that was published in the

Federal Register on January 9, 1981.

This amendment removes a reference to

the CFR that is no longer available.

DATES: This amendment is effective on

December 31, 2001.

FOR FURTHER INFORMATION CONTACT:

Jacquline D. Carter, (202) 606–1973.

SUPPLEMENTARY INFORMATION: On Friday,

December 10, 1999, (64 FR 69176) the

Office of Personnel Management

published a Final rule removing

§ 550.342 from 5 CFR Part 550. This

amendment removes the reference

‘‘§ 550.342’’ from subpart C,

§ 550.311(a)(3).

Regulatory Flexibility Act

I certify that these changes will not

have a significant economic impact on

a substantial number of small entities

because the regulations pertain only to

Federal employees and agencies.

List of Subjects in 5 CFR Part 550

Administrative practice and

procedure, Claims, Government

employees, Wages.

Office of Personnel Management.

Jacquline D. Carter,

Federal Register Liaison Officer.

Accordingly, OPM is amending 5 CFR

part 550 as follows:

PART 550—PAY ADMINISTRATION

(GENERAL)

1. The authority citation for subpart C

of part 550 continues to read as follows:

Authority: 5 U.S.C. 5527, E.O. 10982, 3

CFR 1959–1963 Comp., p. 502.

§ 550.311 [Amended]

2. In § 550.311 paragraph (a) (3),

remove the first ‘‘§ ’’, and the phrase

‘‘and 550.342’’.

[FR Doc. 01–31903 Filed 12–28–01; 8:45 am]

BILLING CODE 6325–39–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–33–AD; Amendment

39–12575; AD 2001–26–11]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce,

plc RB211 Trent 800 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that is applicable to Rolls-Royce, plc

RB211 Trent 800 series turbofan

engines. That AD currently requires

initial and repetitive ultrasonic

inspections of low pressure compressor

(LPC) fan blade roots for cracks, and

replacement, if necessary, with

serviceable parts. This amendment

requires initial inspections at modified

thresholds and repetitive inspections at

reduced intervals from the current AD

using new LPC fan blade inspection

criteria, and requires renewal of dry film

lubricant on removed blades. This

amendment is prompted by reports that

an in-service engine experienced LPC

fan blade root cracking at a lower life

than previously forecast, and, the

manufacturer’s further investigation that

has led to a better understanding of the

causes of fan blade root cracking. The

actions specified in this AD are

intended to prevent LPC fan blade

failure due to cracking, which could

result in multiple fan blade release,

uncontained engine failure, and

possible damage to the airplane.

DATES: Effective January 30, 2002. The

incorporation by reference of certain

publications listed in the rule is

approved by the Director of the Federal

Register as of January 30, 2002.

Comments for inclusion in the Rules

Docket must be received on or before

March 1, 2002.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–ANE–

33–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may be inspected at this location, by

appointment, between 8 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays. Comments may also

be sent via the Internet using the

following address: ‘‘9-aneadcomment@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 Rolls-Royce plc,

Technical Publications Department, PO

Box 31, Derby, England DE248BJ;

telephone 44 1332 242424, fax, 1332

249936. This information may be

examined, by appointment, 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: On

November 30, 2000, the Federal

Aviation Administration (FAA) issued

airworthiness directive (AD) 2000–24–

26, Amendment 39–12033 (65 FR

77778, December 13, 2000), applicable

to Rolls-Royce, plc RB211 Trent 875,

RB211 Trent 877, RB211 Trent 884,

RB211 Trent 892, and RB211 Trent 892B

series turbofan engines, to require initial

and repetitive ultrasonic inspections of

low pressure compressor (LPC) fan

blade roots for cracks, and replacement,

if necessary, with serviceable parts. This

AD requires initial inspections at

modified thresholds and repetitive

67478 Federal Register / Vol. 66, No. 250 / Monday, December 31, 2001 / Rules and Regulations

inspections at reduced intervals from

the current AD using new LPC fan blade

inspection criteria, and requires renewal

of dry film lubricant on removed blades.

Since AD 2000–24–26 was issued, the

Civil Aviation Authority (CAA), which

is the airworthiness authority for the

United Kingdom (UK), advises that an

in-service engine experienced LPC fan

blade root cracking at a lower life than

previously forecast. The manufacturer’s

analysis of this new event has produced

an improved understanding of the

relationship between engine climb and

takeoff speeds, and their effect on the

crack initiation mechanism. These

changes are the result of an improved

understanding of the crack propagation

mechanism and the latest service

operational data.

Manufacturer’s Service Information

Rolls-Royce, plc has issued Service

Bulletin (SB) No. RB.211–72-C445,

Revision 7, dated May 10, 2001, that

specifies initial inspections at modified

thresholds and repetitive inspections at

reduced intervals from the current AD

using new LPC fan blade inspection

criteria, and requires renewal of dry film

lubricant on removed blades. The CAA

classified this service bulletin as

mandatory and issued AD 003–04–98,

dated May 10, 2001, in order to assure

the airworthiness of these Rolls-Royce,

plc 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. 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

for products of this type design that are

certificated for operation in the United

States.

FAA’s Determination of an Unsafe

Condition and Required Actions

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. Since an unsafe condition has

been identified that is likely to exist or

develop on other Rolls-Royce, plc

RB211 Trent 875, RB211 Trent 877,

RB211 Trent 884, RB211 Trent 892, and

RB211 Trent 892B series turbofan

engines of the same type design, this AD

is being issued to prevent LPC fan blade

failure, which could result in multiple

fan blade release, uncontained engine

failure, and possible damage to the

airplane. This AD requires initial

inspections at modified thresholds and

repetitive inspections at reduced

intervals from the current AD using new

LPC fan blade inspection criteria, and

requires renewal of dry film lubricant

on removed blades. The actions are

required to be done in accordance with

the service bulletin described

previously.

Immediate Adoption of This AD

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

appointment, by interested persons. A

report that summarizes each FAApublic 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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–ANE–33–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Analysis

This final 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 final rule.

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 the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 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, 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 39–12033 (65 FR

77778 December 13, 2000) and by

adding a new airworthiness directive,

Amendment 39–12575, to read as

follows:

2001–26–11 Rolls-Royce, plc: Amendment

39–12575. Docket No. 98–ANE–33–AD.

Supersedes AD 2000–24–26,

Amendment 39–12033.

Applicability

This airworthiness directive (AD) is

applicable to Rolls-Royce plc (RR) RB211

Trent 875, RB211 Trent 877, RB211 Trent

Federal Register / Vol. 66, No. 250 / Monday, December 31, 2001 / Rules and Regulations 67479

884, RB211 Trent 892, and RB211 Trent 892B

series turbofan engines, with low pressure

compressor (LPC) fan blades, part numbers

(P/N’s) FK23750, FK25975, FK25548, or

FK26757 installed. These engines are

installed on, but not limited to Boeing 777

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 (i) 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, unless already done.

To prevent LPC fan blade failure due to

cracking, which could result in multiple fan

blade release, uncontained engine failure,

and possible damage to the airplane, do the

following:

Initial Inspection

(a) Ultrasonically inspect the dovetail roots

of LPC fan blades for cracks, in accordance

with Appendix 1 (Method A) of RR Service

Bulletin (SB) RB.211–72–C445, Revision 7,

dated May 10, 2001, at the Initial Inspection

Threshold cyclic times listed in the following

Table 1 of this AD:

TABLE 1.—INSPECTION SCHEDULE

Engine model (rating)

Initial

inspection

threshold,

cycles-sincenew (CSN)

Inspection

intervals,

cycles-sincelast inspection

(CSLI)

Part life

threshold,

CSN

(1) Trent 875 ................................................................................................................................ 3,000 400 4,200

(2) Trent 877 ................................................................................................................................ 2,000 350 3,050

(3) Trent 884 ................................................................................................................................ 1,500 350 2,200

(4) Trent 892 and Trent 892B ..................................................................................................... 900 200 1,300

Dry Film Lubricant Renewal

(b) Apply an approved dry film lubricant

to LPC fan blade roots of blades inspected by

Method A. Procedures for renewing the dry

film lubricant on the blade roots are specified

in the AMM task 72–31–11–300–801–R00

(Repair Scheme FRS A031 by air spray

method only) or engine manual 72–31–11–

R001 (Repair Scheme FRS A028). For

purposes of this AD, approved lubricants are

Dow Corning 321R (Rolls-Royce (RR) Omat

item 4/52), Rocol Dry Moly Spray (RR Omat

item 4/52), Molydag 709 (RR Omat item 444),

or PL.237/R1 (RR Omat item 4/43).

Repetitive Inspections

(c) Except for the first inspection after

exceeding the Part Life Threshold listed in

Table 1 of this AD, ultrasonically inspect the

dovetail roots of LPC fan blades for cracks

and renew dry film lubricant when specified

in accordance with Appendix 1 (Method A)

or Appendix 2 (Method B) of RR SB RB.211–

72–C445, Revision 7, dated May 10, 2001,

and the Inspection Intervals listed Table 1 of

this AD.

First Inspection After Exceeding Part Life

Threshold

(d) For the first inspection after exceeding

the Part Life Threshold listed in Table 1 of

this AD, ultrasonically inspect the dovetail

roots of LPC fan blades for cracks in

accordance with Appendix 1 (Method A) of

RR SB RB.211–72–C445, Revision 7, dated

May 10, 2001. Thereafter, the repetitive

inspections may be done using either

Appendix 1 (Method A) or Appendix 2

(Method B), as specified in paragraph (c) of

this AD.

Fan Blades Exceeding Initial Inspection

Threshold

(e) For blades that have, on the effective

date of the AD, more cycles since installation

than the initial compliance criteria in Table

1, inspect blades within 100 cycles in service

after the effective date of this AD.

Engine Rating Changes

(f) For an engine that has changed its

rating, inspect fan blades at the correct cycle

time as follows:

(1) From higher rating to lower rating,

inspect fan blades before further flight, as

specified in this AD and reinspect at the

interval applicable to the lower rating.

(2) From lower rating to higher rating,

inspect fan blades at intervals applicable to

the higher rating.

Method A Acceptance Criteria

(g) For Method A, replace blades that do

not meet the acceptance criteria in Appendix

1 of RR SB RB.211–72–C445, Revision 7,

dated May 10, 2001.

Method B Acceptance Criteria

(h) For Method B, for blades that do not

meet the acceptance criteria in Appendix 2

of RR SB RB.211–72–C445, Revision 7, dated

May 10, 2001, remove blades and

ultrasonically inspect the dovetail roots for

cracks in accordance with Appendix 1

(Method A) of RR SB RB.211–72–C445,

Revision 7, dated May 10, 2001.

Alternative Methods of Compliance

(i) 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 must

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

(j) 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 airplane to a

location where the requirements of this AD

can be done.

Documents That Have Been Incorporated by

Reference

(k) The inspection must be done in

accordance with Rolls-Royce plc Service

Bulletin(SB) No. RB.211–72–C445, Revision

7, dated May 10, 2001. 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, Technical

Publications Department, PO Box 31, Derby,

England DE248BJ; telephone 44 1332 242424,

fax, 1332 249936. Copies may be inspected,

by appointment, 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.

Note 3: The subject of this AD is addressed

in Civil Aviation Authority airworthiness

directive AD 003–04–98, issued on May 10,

2001.

Effective Date

(l) This amendment becomes effective on

January 30, 2002.

Issued in Burlington, Massachusetts, on

December 17, 2001.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 01–31699 Filed 12–28–01; 8:45 am]

BILLING CODE 4910–13–P