Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21067

137’’ and add in their place the words

‘‘parts 63, 121, 125, 135, and 137’’.

PART 145—REPAIR STATIONS

28. The authority citation for part 145

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701–

44702, 44707, 44717.

§ 145.2 Performance of maintenance,

preventive maintenance, alterations and

required inspections for an air carrier or

commercial operator under the continuous

airworthiness requirements of parts 121

and 127, and for airplanes under the

inspection program required by part 125.

29. Amend § 145.2 as follows:

a. In the section heading remove the

words ‘‘parts 121 and 127’’ and add in

their place the words ‘‘part 121’’.

b. In paragraph (a) remove the words

‘‘or part 127’’; and remove the words ‘‘or

subpart I of part 127 (except §§ 127.131,

127.134, 127.136, and 127.140)’’.

§ 145.63 Reports to defects or unairworthy

conditions.

30. Amend § 145.63(c) by removing

the words ‘‘part 121, 127, or 135’’ and

adding in their place the words ‘‘part

121 or 135’’; and by removing the words

‘‘under § 21.3, § 37.17, § 121.703,

§ 127.313, or § 135.57’’ and adding in

their place the words ‘‘under § 21.3,

§ 37.17, § 121.703, or § 135.57’’.

PART 161—NOTICE AND APPROVAL

OF AIRPORT NOISE AND ACCESS

RESTRICTIONS

31. The authority citation for part 161

continues to read as follows:

Authority: 49 U.S.C. 106(g), 47523–47527,

47533.

§ 161.5 Definitions.

32. Amend § 161.5 by removing the

words ‘‘under parts 127 and 135’’ from

the definition for Aviation user class

and adding in their place the words

‘‘under part 135’’.

PART 170—ESTABLISHMENT AND

DISCONTINUANCE CRITERIA FOR AIR

TRAFFIC CONTROL SERVICES AND

NAVIGATIONAL FACILITIES

33. The authority citation for part 170

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40103–40107,

40113, 44502, 44701–44702, 44708–44709,

44719, 44721–44722, 46308.

§ 170.3 Definitions

34. Amend § 170.3 by removing the

words ‘‘parts 121, 127, and 135’’ from

the definition for Scheduled commercial

service and adding in their place the

words ‘‘parts 121 and 135’’.

Issued in Washington, DC on April 19,

2001.

Donald P. Byrne,

Assistant Chief Counsel for Regulations.

[FR Doc. 01–10239 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–29–AD; Amendment

39–12192; AD 2001–08–15]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

Corporation (Formerly Allison Engine

Company) AE 3007 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 Corporation

(formerly Allison Engine Company) AE

3007A, AE 3007A1/1, AE 3007A1/2, AE

3007A1, AE 3007A1/3, AE 3007A1P,

and AE 3007A3 turbofan engines. This

action requires initial and repetitive

inspections for bearing material

contamination of the engine oil system.

This amendment is prompted by reports

of rapid failures of the No. 1 bearing.

The actions specified in this AD are

intended to detect the rapid failure of

the No. 1 bearing, which could result in

smoke in the cabin and an

uncommanded in-flight engine

shutdown.

DATES: Effective May 14, 2001. The

incorporation by reference of certain

publications listed in the rule is

approved by the Director of the Federal

Register as of May 14, 2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 26, 2001.

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–

29–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. 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 Allison

Engine Company, Inc., P.O. Box 420,

Indianapolis, IN 46206 USA, Phone:

(317) 230–6400; Fax: (317) 230–4243.

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: Kyri

Zaroyiannis, Aerospace Engineer,

Chicago Aircraft Certification Office,

FAA, Small Airplane Directorate, 2300

East Devon Avenue, Des Plaines, IL

60018; telephone: (847) 294–7836; fax:

(847) 294–7834.

SUPPLEMENTARY INFORMATION: The RollsRoyce Corporation (RR) (formerly

Allison Engine Company) has notified

the FAA that there is a design problem

with the No. 1 bearing installed on the

AE 3007A, AE 3007A1/1, AE 3007A1/2,

AE 3007A1, AE 3007A1/3, AE 3007A1P,

and AE 3007A3 turbofan engines. This

can lead to an event involving smoke in

cabin, followed by an uncommanded inflight engine shutdown. RR has

determined that this problem is the

result of the rapid failure of the number

1 bearing installed on the AE 3007A, AE

3007A1/1, AE 3007A1/2, AE 3007A1,

AE 3007A1/3, AE 3007A1P and AE

3007A3 turbofan engines. This

condition, if not corrected, could result

in the rapid failure of the number 1

bearing, which could result in smoke in

the cabin and an uncommanded inflight engine shutdown.

RR is developing a number of design

modifications for affected models

which, if installed, may reduce the rate

of No. 1 bearing distress. The FAA may

take additional mandatory action to

incorporate these modifications and to

eliminate the need for the inspections

mandated by this AD. The compliance

time of this AD was chosen based on the

failure sequence of the number 1

bearing.

Manufacturer’s Service Information

The FAA has reviewed and approved

the technical contents of Rolls-Royce

Alert Service Bulletin (ASB) AE 3007A–

A–79–027, dated August 17, 2000, that

provides procedures for inspecting for

bearing material contamination of the

engine oil system.

Determination of an Unsafe Condition

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design, this AD is being issued to

require initial and repetitive inspections

for bearing material contamination of

the engine oil system, to prevent events

caused by the rapid failure of the

21068 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

number 1 bearing. The actions are

required to be accomplished in

accordance with the ASB described

previously.

Immediate Adoption of This AD

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

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–29-AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

This final rule does not have

federalism implications, as defined in

Executive Order No. 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.

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:

2001–08–15 Rolls-Royce Corporation:

Amendment 39–12192. Docket 2000–

NE–29–AD.

Applicability: This airworthiness directive

(AD) is applicable to Rolls-Royce Corporation

(formerly Allison Engine Company) AE

3007A, AE 3007A1/1, AE 3007A1/2, AE

3007A1, AE 3007A1/3, AE 3007A1P, and AE

3007A3 turbofan engines. These engines are

installed on, but not limited to, Embraer

Model EMB–145, EMB–145ER, EMB–145MR,

EMB–145LR, EMB–135ER and EMB–135LR

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: Compliance with this AD is

required as indicated, unless already done.

Compliance

Compliance with this AD is required as

indicated, unless already done.

To detect the rapid failure of the No. 1

bearing, which could result in smoke in the

cabin and an uncommanded in-flight engine

shutdown, do the following:

Inspection for Bearing Material

Contamination of the Oil System

(a) Inspect for bearing material

contamination of the oil system in

accordance with 2.A.(1) through 2.A.(2) of

the Accomplishment Instructions of RollsRoyce alert service bulletin (ASB) No. AE

3007A–A–79–027, dated August 17, 2000, as

follows:

(1) Do an initial inspection within 30 flight

hours, or three flight days after the effective

date of this AD, whichever occurs first.

(2) Thereafter, inspect for every 30 flight

hours, or every three flight days, whichever

occurs first.

Terminating Action

(b) Incorporation of Embraer Service

Bulletin 145–79–0001, dated April 24, 1998,

is considered terminating action for the

inspections required by paragraphs (a)(1) and

(a)(2) of this AD.

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, Chicago

Aircraft Certification Office (ACO). Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Chicago ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

ACO.

Special Flight Permits

(d) 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.

(e) The inspection shall be done in

accordance with Rolls-Royce alert service

bulletin No. AE 3007A–A–79–027, dated

August 17, 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 Allison Engine Company, Inc., P.O. Box

420, Indianapolis, IN 46206 USA, Phone:

Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21069

317–230–6400; Fax: 317–230–4243. 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.

(f) This amendment becomes effective on

May 14, 2001.

Issued in Burlington, Massachusetts, on

April 16, 2001.

Francis A. Favara,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–10022 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–87–AD; Amendment

39–12200; AD 2001–08–23]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767–200 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Boeing Model 767–

200 series airplanes. This action

requires repetitive inspections for

cracking of the outboard pitch load

fittings of the wing front spar, and

corrective action, if necessary. This

action also provides a terminating

action for the repetitive inspections,

which is optional for uncracked pitch

load fittings. This action is necessary to

find and fix cracking of the outboard

pitch load fittings of the wing front spar,

which could lead to loss of the upper

link load path and result in separation

of the strut and engine from the

airplane. This action is intended to

address the identified unsafe condition.

DATES: Effective May 14, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 14,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 26, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

87–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2001–NM–87–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined at

the FAA, Transport Airplane

Directorate, 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: John

Craycraft, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2782;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received reports that fatigue

cracking of the outboard pitch load

fittings on the wing front spar has been

found on certain Boeing Model 767–200

series airplanes. Recently, the FAA has

received new reports that such fatigue

cracking was found on four out of seven

inspected airplanes. The outboard pitch

load fittings on the wing front spar are

part of the upper link load path. Such

cracking, if not corrected, could lead to

loss of the upper link load path and

result in separation of the strut and

engine from the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 767–57A0070,

Revision 1, dated November 16, 2000,

which describes procedures for

repetitive high frequency eddy current

(HFEC) inspections for cracking of the

outboard pitch load fitting of the wing

front spar on the left and right sides of

the airplane, and corrective action, if

necessary. The corrective action

involves rework or replacement of

cracked parts. The service bulletin also

describes procedures for replacement of

the outboard pitch load fittings with

new fittings of improved design. These

procedures include an HFEC inspection

for damage of fastener holes, and repair

of damaged fastener holes (if necessary).

Installation of new, improved fittings

eliminates the need for the repetitive

inspections described in the service

bulletin.

Boeing Service Bulletin 767–

57A0070, Revision 1, refers to Boeing

Service Bulletin 767–57–0053 as an

additional source of service information

for accomplishment of the replacement

of the outboard pitch load fitting on

Model 767–200 series airplanes.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

find and fix cracking of the outboard

pitch load fittings of the wing front spar,

which could lead to loss of the upper

link load path and result in separation

of the strut and engine from the

airplane. This AD requires

accomplishment of the actions specified

in Boeing Service Bulletin 767–

57A0070, Revision 1, described

previously, except as discussed below.

Differences Between This AD and

Service Bulletin

This AD differs from Boeing Service

Bulletin 767–57A0070, Revision 1, in

the following ways:

• The service bulletin instructs that

the manufacturer should be contacted

for rework instructions. However, this

AD requires such rework to be

accomplished per a method approved

by the FAA, or per data meeting the

type certification basis of the airplane

approved by a Boeing Company

Designated Engineering Representative

who has been authorized by the

Manager of the Seattle Aircraft

Certification Office, to make such

findings.

• The service bulletin specifies a

compliance time of 180 days after

receipt of the service bulletin for

accomplishment of the initial inspection

per that service bulletin. However, this

AD requires accomplishment of the

initial inspection within 30 days after

the effective date of this AD. In

developing an appropriate compliance

time for this AD, the FAA considered

not only the manufacturer’s

recommendation, but the degree of

urgency associated with addressing the

subject unsafe condition, and, in

particular, the recent reports indicating

that cracked pitch load fittings were

found on four of seven inspected

airplanes. In light of all of these factors,

the FAA finds a 30-day compliance time

for completing the required inspection

to be warranted, in that it represents an