21134 Federal Register / Vol. 65, No. 77 / Thursday, April 20, 2000 / Rules and Regulations

F28 Mark 1000–4000

Lockheed

L–1011 TriStar

L–188 Electra

CASA

CN–235

Dassault Aviation

Mystere Falcon 50

Mystere Falcon 900

Mystere Falcon 200

Fan Jet Falcon Series G

Boeing (MDC)

DC–10–30

DC–10–40

DC–9

DC–9–81

DC–9–82

DC–9–83

DC–9–87

Boeing 707

Boeing 727

Boeing 737

Boeing 747

Bombardier

CL–215–1A10

CL–215–6B11

CL–600–1A11

CL–600–2A12

CL–600–2B16

Gulfstream

G1159 (G–II)

G–1159A (G–III)

G–IV

Mode ‘‘C’’ Transponder Part Numbers

Rockwell Collins

622–2224–001

622–2224–003

522–2703–001

522–2703–011

787–6211–001

787–6211–002

Bendix

066–1056–00

066–1056–01

066–1123–00

2041599–6508

Wilcox

97637–201

97637–301

IFF

APX–100

APX–101

This rescission is effective April 20, 2000.

Issued in Renton, Washington, on April 7,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–9247 Filed 4–19–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–97–AD; Amendment

39–11689; AD 2000–08–03]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 series airplanes,

that currently requires the deactivation

of the forward and center cargo control

units (CCU). That amendment was

prompted by a report of failure of a

CCU, which produced overheating of

the electrical pins inside the CCU; the

subsequent release of hot gases and

flames ignited an adjacent insulation

blanket. This amendment expands the

applicability of the existing AD to

include additional airplanes. The

actions specified in this AD are

intended to prevent overheating of the

electrical pins inside the CCU’s and

subsequent release of hot gases and

flames, which could result in smoke and

fire in the cargo compartment.

DATES: Effective May 5, 2000. Comments

for inclusion in the Rules Docket must

be received on or before June 19, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

97–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Information pertaining to this

amendment may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Transport

Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California.

FOR FURTHER INFORMATION CONTACT:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5350;

fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: On

February 28, 2000, the FAA issued AD

2000–05–01, amendment 39–11610 (65

FR 11459, March 3, 2000), applicable to

certain McDonnell Douglas Model MD–

11 series airplanes, to require the

deactivation of the forward and center

cargo control units (CCU). That action

was prompted by a report of failure of

a CCU, which produced overheating of

the electrical pins inside the CCU; the

subsequent release of hot gases and

flames ignited an adjacent insulation

blanket. The actions required by that AD

are intended to prevent such conditions,

which could result in smoke and fire in

the cargo compartment.

The incident that prompted AD 2000–

05–01 is not considered to be related to

an accident that occurred off the coast

of Nova Scotia involving a McDonnell

Douglas Model MD–11 series airplane.

The cause of that accident is still under

investigation.

Other Related Rulemaking

The FAA, in conjunction with Boeing

and operators of Model MD–11 series

airplanes, is continuing to review all

aspects of the service history of those

airplanes to identify potential unsafe

conditions and to take appropriate

corrective actions. This AD is one of a

series of actions identified during that

process. The process is continuing and

the FAA may consider additional

rulemaking actions as further results of

the review become available.

Actions Since Issuance of Previous Rule

The applicability statement of AD

2000–05–01 lists the serial numbers of

the affected airplanes, which were

provided by the airplane manufacturer.

Since the issuance of that AD, the

airplane manufacturer has informed the

FAA that it inadvertently provided two

incorrect airplane serial numbers (i.e.,

48679 and 58563); those serial numbers

do not exist. The correct serial numbers

of those two airplanes are 48769 and

48563. The FAA has determined that

affected airplanes having serial numbers

48769 and 48563 also are subject to the

identified unsafe condition.

Explanation of Requirements of Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of this same

type design, this AD supersedes AD

2000–05–01 to continue to require the

deactivation of the forward and center

CCU’s. This AD also expands the

applicability of the existing AD to

include additional airplanes.

Federal Register / Vol. 65, No. 77 / Thursday, April 20, 2000 / Rules and Regulations 21135

Interim Action

This is considered to be interim

action. The FAA is currently

considering requiring a modification of

the CCU assembly would constitute

terminating action for the requirements

of this AD. However, the planned

compliance time for the installation of

the modification is sufficiently long so

that notice and opportunity for prior

public comment will be practicable.

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.

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 2000–NM–97–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, 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 39–11610 (65 FR

11459, March 3, 2000), and by adding a

new airworthiness directive (AD),

amendment 39–11689, to read as

follows:

2000–08–03 McDonnell Douglas:

Amendment 39–11689. Docket 2000–

NM–97–AD. Supersedes AD 2000–05–

01, Amendment 39–11610.

Applicability: Model MD–11 series

airplanes, certificated in any category,

having the serial numbers listed below.

Group 1 Airplanes:

48565 48566 48533 48549 48470 48406

48504 48602 48603 48571 48439 48605

48572 48471 48573 48600 48601 48633

48513 48574 48575 48542 48543 48576

48415 48631 48544 48632 48577 48545

48578 48546 48743 48744 48747 48748

48745 48746 48749 48579 48766 48768

48767 48769 48754 48623 48770 48753

48773 48774 48755 48758 48775–48779

inclusive

48624 48756 48780 48532

Group 2 Airplanes:

48555 48556 48581 48630 48557 48539

48558 48559 48616 48560 48617 48618

48561 48629 48562 48563 48757 48540

48564 48634 48541 48798 48781–48792

inclusive

48794 48799 48801 48800 48802–48806

inclusive

21136 Federal Register / Vol. 65, No. 77 / Thursday, April 20, 2000 / Rules and Regulations

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 (d) 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 overheating of the

electrical pins inside the cargo control

units (CCU) and subsequent release of

hot gases and flames, which could result

in smoke and fire in the cargo

compartment, accomplish the following:

Restatement of Requirements of AD

2000–05–01:

Deactivation

(a) For Group 1 airplanes having serial

numbers other than that identified in

paragraph (c) of this AD: Within 15 days

after March 20, 2000 (the effective date

of AD 2000–05–01, amendment 39–

11610), deactivate the forward and

center CCU’s in accordance with the

following procedures:

(1) Remove the access panel to the

forward cargo compartment CCU circuit

breaker panel located at fuselage station

1009.300 (right side looking aft). Pull

and collar the following circuit breakers:

B1–506

B1–485

B1–500

B1–489

B1–480

B1–495

B1–488

B1–481

B1–499

B1–487

B1–498

B1–490

B1–486

B1–482

(2) Remove the access panel to the

center cargo compartment CCU circuit

breaker panel located at fuselage station

1701.000 (right side looking aft). Pull

and collar the following circuit breakers:

B1–552

B1–758

B1–753

B1–762

B1–518

B1–764

B1–761

B1–519

B1–752

B1–760

B1–751

B1–763

B1–759

B1–520

(b) For Group 2 airplanes having

serial numbers other than that identified

in paragraph (c) of this AD: Within 15

days after March 20, 2000, deactivate

the forward and center CCU’s in

accordance with the following

procedures:

(1) Remove the access panel to the

forward cargo compartment CCU circuit

breaker panel located at fuselage station

1009.300 (right side looking aft). Pull

and collar the following circuit breakers:

B1–506

B1–485

B1–500

B1–489

B1–480

B1–495

B1–488

B1–481

B1–499

B1–487

B1–498

B1–490

B1–486

B1–482

(2) Remove the access panel to the

center cargo compartment CCU circuit

breaker panel located at fuselage station

1701.000 (right side looking aft). Pull

and collar the following circuit breakers:

B1–552

B1–758

B1–753

B1–762

B1–518

B1–764

B1–761

B1–519

B1–752

B1–760

B1–751

B1–759

B1–520

New Requirements of this AD:

(c) For Group 1 airplane, serial

number 48769, and for Group 2

airplane, serial number 48563: Within

15 days after the effective date of this

AD, accomplish the actions specified in

either paragraph (a) or (b) of this AD, as

applicable.

Alternative Methods of Compliance

(d)(1) 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, Los

Angeles Aircraft Certification Office

(ACO), FAA, Transport Airplane

Directorate. Operators shall submit their

requests through an appropriate FAA

Principal Maintenance Inspector, who

may add comments and then send it to

the Manager, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(2) Alternative methods of

compliance, approved previously in

accordance with AD 2000–05–01,

amendment 39–11610, are approved as

alternative methods of compliance with

paragraph (a) or (b) of this AD, as

applicable.

Special Flight Permits

(e) 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.

(f) This amendment becomes effective

on May 5, 2000.

Issued in Renton, Washington, on April 12,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–9674 Filed 4–19–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–69–AD; Amendment

39–11695; AD 2000–08–09]

RIN 2120–AA64

Airworthiness Directives; Robinson

Helicopter Company Model R22

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Robinson Helicopter

Company (RHC) Model R22 helicopters.

This action requires replacing certain

serial number sprag clutches with an

airworthy sprag clutch as specified in

this AD. This amendment is prompted

by several reports of clutch assemblies

with cracked or fractured sprag ends.

The actions specified by this AD are

intended to prevent a sprag clutch

failure, loss of main rotor RPM during

autorotation, and subsequent loss of

control of the helicopter.