Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21081

2001–08–28 Boeing: Amendment 39–12205.

Docket 97–NM–276–AD.

Applicability: Model 767–200 and -300

series airplanes having line numbers 1

through 669 inclusive, certificated in any

category.

Note 1: Boeing Model 767–300F freighter

airplanes are not affected by this AD.

Note 2: This AD requires revisions to

certain operator maintenance documents to

include new inspections. Compliance with

these inspections is required by 14 CFR part

91.403(c). For airplanes that have been

previously modified, altered, or repaired in

the areas addressed by these inspections, the

operator may not be able to accomplish the

inspections described in the revisions. In this

situation, to comply with 14 CFR part

91.403(c), the operator must request approval

for an alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include a description of

changes to the required inspections that will

ensure the continued damage tolerance of the

affected structure. The FAA has provided

guidance for this determination in Advisory

Circular (AC) 25–1529.

Compliance: Required as indicated, unless

accomplished previously.

To ensure continued structural integrity of

these airplanes, accomplish the following:

Revise Section 9 of the Boeing 767

Maintenance Planning Data (MPD)

(a) Within 3 years after the effective date

of this AD, revise Section 9 of the Boeing 767

Maintenance Planning Data (MPD) Document

entitled ‘‘Airworthiness Limitations and

Certification Maintenance Requirements

(CMR’s)’’ to incorporate Subsection B of

Boeing Document D622T001–9, Revision

‘‘June 1997.’’

Note 3: The referenced Subsection B

contains a requirement that cracks found

during the specified inspections be reported

to the Seattle Aircraft Certification Office

(ACO), FAA. Information collection

requirements contained in this regulation

have been approved by the Office of

Management and Budget under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501, et seq.) and have been

assigned OMB Control Number 2120–0056.

Note 4: For the purposes of this AD, the

terms Principal Structural Elements (PSE’s)

as used in this AD, and Structural Significant

Items (SSI’s) as used in Section 9 of Model

767 MPD Document, are considered to be

interchangeable.

Alternative Inspections and Inspection

Intervals

(b) Except as provided in paragraph (c) of

this AD: After the actions required by

paragraph (a) of this AD have been

accomplished, no alternative inspections or

inspection intervals shall be approved for the

SSI’s contained in Boeing 767 MPD

Document D622T001–9, Revision ‘‘June

1997.’’

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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

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 shall be done in accordance

with Subsection B of Boeing 767

Maintenance Planning Data Document

D622T001–9, Revision ‘‘June 1997’’, which

contains the following list of effective pages:

Page No.

Revision date

shown on

page

List of Effective Pages, Page

9.0–5.

June 1997.

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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. Copies may be inspected 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.

Effective Date

(f) This amendment becomes effective on

June 1, 2001.

Issued in Renton, Washington, on April 19,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10337 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–82–AD; Amendment

39–12204; AD 2001–08–27]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011 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 Lockheed Model

L–1011 series airplanes. This action

requires inspection of the windshield

heat wire bundle for chafing or damage,

and inspection of the harness clamps of

the wire bundle for damage; and

corrective actions, if necessary. For

certain airplanes, this action also

requires rerouting of the windshield

heat wire bundle. This action is

necessary to prevent chafing or damage

of the windshield heat wire bundle,

which could cause arcing and result in

smoke and fire in the cockpit. 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–

82–AD, 1601 Linda 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–82-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 Lockheed

Martin & Logistics Center, 120 Orion

Street, Greenville, South Carolina

29605. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30349; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom

Peters, Program Manager, Program

21082 Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations

Management Support Branch, ACE–

116A, FAA, Atlanta Aircraft

Certification Office, One Crown Center,

1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia 30349; telephone (770)

703–6063; fax (770) 703–6097.

SUPPLEMENTARY INFORMATION: The FAA

has received a report indicating that an

in-flight electrical arcing occurred to the

windshield heat wire bundle located

above the First Officer’s side window in

a Lockheed Model L–1011–385 series

airplane. The wires were smoldering

and flames were observed by the

flightcrew. After the flightcrew donned

smoke goggles and masks, two

windshield heat circuit breakers

opened, and the flightcrew opened the

remaining circuit breakers, which

removed power from the arcing wire

bundle. Investigation of the cockpit

revealed that the windshield and

window heat wire harness C–38 was

arcing in the proximity of a wire harness

clamp installed just above the First

Officer’s chart light mounting bracket.

Approximately 20 wires sustained

various degrees of damage. The

investigation also revealed that the

clamp, which had been directly over the

section of burned wire, was broken into

two pieces and the rubber insulation

appeared carbonized. The metal of the

clamp also appeared to have been

exposed to an electrical discharge. This

condition, if not corrected, could result

in chafing and damage to the C–38 wire

bundle, which could cause arcing and

result in smoke and fire in the cockpit.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Lockheed Service Bulletin 093–30–060,

dated March 6, 2001, which describes

procedures for a detailed visual

inspection of the C–38 wire harness for

any chafing or damage (e.g., shavings,

moisture, deterioration, etc.). The

service bulletin also describes

procedures for repair and replacement

of any damaged wiring. The FAA also

reviewed and approved Lockheed

Service Bulletin 093–30–057, dated

April 27, 1984. That service bulletin

describes procedures for rerouting the

C–38 windshield heat wire harness for

certain airplanes that have a First

Officer’s chart light installation that was

accomplished during production or after

delivery. Accomplishment of the actions

specified in the service bulletins is

intended to adequately address the

identified unsafe condition.

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

prevent damage to the C–38 wire

bundle, which can cause arcing and

result in smoke and fire in the cockpit.

This AD requires accomplishment of the

applicable actions specified in the

service bulletins described previously.

Determination of Rule’s Effective Date

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 shall 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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2001–NM–82–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it 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:

2001–08–27 Lockheed: Amendment 39–

12204. Docket 2001–NM–82–AD.

Applicability: Model L–1011 series

airplanes, as listed in Lockheed Service

Bulletin 093–30–060, dated March 6, 2001,

and Lockheed Service Bulletin 093–30–057,

Federal Register / Vol. 66, No. 82 / Friday, April 27, 2001 / Rules and Regulations 21083

dated April 27, 1984; certificated in any

category.

Note 1: This AD applies to each airplane

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

airplanes 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 prevent damage to the windshield heat

wire bundle, which could cause arcing and

result in smoke and fire in the cockpit;

accomplish the following:

Inspection of Wiring and Clamps, and

Corrective Actions

(a) For airplanes listed in Lockheed Service

Bulletin 093–30–060, dated March 6, 2001:

Within 60 days after the effective date of this

AD, perform the detailed visual inspections

and repair or replacements specified in

paragraph (a)(1) and (a)(2) of this AD, per

Lockheed Service Bulletin 093–30–060,

dated March 6, 2001.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(1) Remove the C–38 wire harness clamps

and perform a detailed visual inspection of

the clamps and the conforming cushions for

any sign of deterioration, damage, or slippage

on the metal band of the clamp. Before

further flight, replace any clamp that does

not meet the specified criteria in the service

bulletin with a new or serviceable clamp, per

the service bulletin.

(2) Perform a detailed visual inspection of

the C–38 wire harness for any damage from

chafing or contamination (e.g., shavings,

moisture, deterioration, etc.). Before further

flight, repair, or replace any chafed or

damaged wiring per the service bulletin.

Rerouting the C–38 Harness

(b) For airplanes listed in Lockheed Service

Bulletin 093–30–057, dated April 27, 1984:

Within 60 days after the effective date of this

AD, reroute the C–38 harness and add one

additional clamp to secure the harness away

from the mounting brackets of the Flight

Officer’s chart light assembly, per the service

bulletin.

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, Atlanta

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, Atlanta ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

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 shall be done in accordance

with Lockheed Service Bulletin 093–30–060,

dated March 6, 2001; and Lockheed Service

Bulletin 093–30–057, dated April 27, 1984,

as applicable. 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 Lockheed Martin & Logistics

Center, 120 Orion Street, Greenville, South

Carolina 29605. Copies may be inspected at

the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia 30349;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

Effective Date

(f) This amendment becomes effective on

May 14, 2001.

Issued in Renton, Washington, on April 19,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10339 Filed 4–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NE–09–AD; Amendment

39–12212; AD 2001–09–07]

RIN 2120–AA64

Airworthiness Directives; Pratt and

Whitney PW4000 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule, request for

comments.

SUMMARY: This amendment supersedes

an emergency airworthiness directive

(AD) 2001–08–52 that was sent

previously to all known U.S. owners

and operators of Pratt and Whitney (PW)

model PW4050, PW4052, PW4056,

PW4060, PW4060A, PW4060C,

PW4062, PW4152, PW4156, PW4156A,

PW4158, PW4160, PW4460, PW4462,

and PW4650 turbofan engines by

individual letters. That emergency AD

requires limiting the number of PW4000

engines, listed by serial number (SN) in

that AD, with potentially reduced

stability to no more than one engine on

each airplane; removal of certain

PW4000 engines, listed by SN in this

AD, before exceeding cyclic limits that

are determined by airplane model;

removal of certain PW4000 engines,

listed by SN in this AD, that have a high

pressure compressor with 1,500 or more

cycles-since-overhaul (CSO) greater than

the high pressure turbine (HPT) CSO;

and requires a minimum rebuild

standard for engines that are returned to

service. This amendment supersedes

emergency AD 2001–08–52 to provide

clarifications and additions to the

compliance and applicability of certain

paragraphs of AD 2001–08–52. This AD

is prompted by a report of a dual-engine

surge event during take-off on an Airbus

Industrie A300 airplane. The actions

specified by this AD are intended to

prevent multiple-engine power losses

due to high pressure compressor (HPC)

surge at a critical phase of flight such as

takeoff or climb.

DATES: Effective 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. 2001–NE–

09–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.

FOR FURTHER INFORMATION CONTACT:

Peter White, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7128;

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: On April

13, 2001, the Federal Aviation

Administration (FAA) issued emergency