59708 Federal Register / Vol. 65, No. 195 / Friday, October 6, 2000 / Rules and Regulations

and that certain actions are to be

accomplished in accordance with a

method approved by the FAA, rather

than a specific service bulletin.

Therefore, consistent with the FAA’s

intent in the supplemental NPRM, this

correction is necessary to require

operators of specific airplanes to replace

certain ground block screws with new

screws and to reterminate the circuit

ground wires of the EPCU to separate

grounding points.

These actions shall be done in

accordance with McDonnell Douglas

Alert Service Bulletin MD90–24A060,

Revision 01, dated September 2, 1999;

and McDonnell Douglas Service

Bulletin MD90–24–062, dated February

3, 2000; as applicable. The FAA

inadventently omitted McDonnell

Douglas Service Bulletin MD90–24–062

from the incorporation by reference

paragraph and is incorporating by

reference that service bulletin in this

final rule.

Correction of Publication

Action is taken herein to correct these

inadvertent errors in AD 2000–16–01

and to correctly add this AD as an

amendment to section 39.13 of the

Federal Aviation Regulations (14 CFR

39.13). The AD is reprinted in its

entirety for the convenience of affected

operators.

Since this action only corrects current

requirements, it has no adverse

economic impact and imposes no

additional burden on any person.

Therefore, the FAA has determined that

notice and public procedures are

unnecessary.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Correction

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 39–11855 (65 FR

49728, August 15, 2000), and by adding

a new airworthiness directive (AD),

amendment 39-, to read as follows:

2000–20–04 McDonnell Douglas:

Amendment 39–11915. Docket 99–NM–329–

AD. Supersedes AD 2000–16–01,

Amendment 39–11855.

Applicability: Model MD–90–30 series

airplanes, as listed in McDonnell Douglas

Alert Service Bulletin MD90–24A060,

Revision 01, dated September 2, 1999, and

McDonnell Douglas Service Bulletin MD90–

24–062, dated February 3, 2000; 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 a loose electrical ground block

of the circuit ground wires of the electrical

power control unit (EPCU), accomplish the

following:

Replacement

(a) For airplanes listed in McDonnell

Douglas Alert Service Bulletin MD90–

24A060, Revision 01, dated September 2,

1999: Within 30 days after the effective of

this AD, replace the electrical ground block

screws with new screws in accordance with

McDonnell Douglas Alert Service Bulletin

MD90–24A060, Revision 01, dated

September 2, 1999.

Note 2: Accomplishment of the

replacement of electrical ground block

screws prior to the effective date of this AD

in accordance with McDonnell Douglas Alert

Service Bulletin MD90–24A060, dated July

28, 1999, is acceptable for compliance with

the requirements of paragraph (a) of this AD.

Modification of the Electrical Power Control

Unit

(b) For airplanes listed in McDonnell

Douglas Service Bulletin MD90–24–062,

dated February 3, 2000: Within 12 months

after the effective date of this AD, reterminate

the circuit ground wires of the EPCU to

separate grounding points to ensure that a

single point failure does not occur, in

accordance with McDonnell Douglas Service

Bulletin MD90–24–062, dated February 3,

2000.

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, Los

Angeles Aircraft Certification Office (ACO),

FAA. 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Incorporation by Reference

(d) The actions shall be done in accordance

with McDonnell Douglas Alert Service

Bulletin MD90–24A060, Revision 01, dated

September 2, 1999; and McDonnell Douglas

Service Bulletin MD90–24–062, dated

February 3, 2000; as applicable.

(1) The incorporation by reference of

McDonnell Douglas Service Bulletin MD90–

24–062, dated February 3, 2000, is approved

by the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51.

(2) The incorporation by reference of

McDonnell Douglas Alert Service Bulletin

MD90–24A060, Revision 01, dated

September 2, 1999, was approved previously

by the Director of the Federal Register as of

September 19, 2000 (65 FR 49728, August 15,

2000).

(3) Copies may be obtained from Boeing

Commercial Aircraft Group, Long Beach

Division, 3855 Lakewood Boulevard, Long

Beach, California 90846, Attention: Technical

Publications Business Administration, Dept.

C1–L51 (2–60). Copies may be inspected at

the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Los Angeles

ACO, 3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(e) This amendment becomes effective on

November 13, 2000.

Issued in Renton, Washington, on

September 26, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–25149 Filed 10–5–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–356–AD; Amendment

39–11916; AD 2000–20–05]

RIN 2120–AA64

Airworthiness Directives; Empresa

Brasileira de Aeronautica S.A.

(EMBRAER) Model EMB–120 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

Federal Register / Vol. 65, No. 195 / Friday, October 6, 2000 / Rules and Regulations 59709

applicable to certain EMBRAER Model

EMB–120 series airplanes, that requires

revising the Airplane Flight Manual

(AFM), and either installing hydraulic

tube assemblies incorporating a check

valve, or visually inspecting the check

valve if already installed and corrective

action, if necessary. 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 the landing gear

doors from becoming blocked from

opening during application of

emergency procedures in the event of a

loss of hydraulics.

DATES: Effective November 13, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

13, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Empresa Brasileira de Aeronautica

S.A. (EMBRAER), P.O. Box 343—CEP

12.225, Sao Jose dos Campos—SP,

Brazil. 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 FAA, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia; or at the Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Robert Capezzuto, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Atlanta Aircraft

Certification Office, One Crown Center,

1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia 30349; telephone (770)

703–6071; fax (770) 703–6097.

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 certain EMBRAER

Model EMB–120 series airplanes was

published in the Federal Register on

April 17, 2000 (65 FR 20388). That

action proposed to require revising the

Airplane Flight Manual (AFM), and

either installing hydraulic tube

assemblies incorporating a check valve,

or visually inspecting the check valve if

already installed and corrective action,

if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Change Made to the Final Rule

Since the issuance of the proposed

AD, the FAA has determined that the

installation required by paragraph (c)

must be accomplished only in

accordance with EMBRAER Service

Bulletin 120–32–0077, Change 02, dated

December 23, 1997, after the effective

date of this AD. (EMBRAER Service

Bulletin 120–32–0077, Change 01, dated

September 25, 1997; and EMBRAER

Service Bulletin 120–32–0077, Change

02, dated December 23, 1997, were cited

as the appropriate sources of service

information in the proposed AD.) The

final rule has been changed accordingly,

and a new Note 2 has been added to

give credit for accomplishment of the

installation in paragraph (c) prior to the

effective date of this AD in accordance

with EMBRAER Service Bulletin 120–

32–0077, Change 01, dated September

25, 1997.

Conclusion

After careful review of the available

data, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 213 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 1 work

hour per airplane to incorporate the

applicable AFM revision, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AFM revision required by this Ad

on U.S. operators is estimated to be

$12,780, or $60 per airplane.

It will take approximately 1 work

hour per airplane to perform the visual

inspection of the check valve, and that

the average labor rate is $60 per work

hour. Based on these figures, the cost

impact of the inspection required by

this AD on U.S. operators is estimated

to be $60 per airplane.

It will take approximately 2 work

hours per airplane to install the

hydraulic tube assemblies incorporating

a check valve, and that the average labor

rate is $60 per work hour. Required

parts will cost approximately $2,021 per

airplane. Based on these figures, the cost

impact of the installation required by

this AD on U.S. operators is estimated

to be $2,141 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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.

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 DOT

Regulatory Policies and Procedures (44

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

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 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.

59710 Federal Register / Vol. 65, No. 195 / Friday, October 6, 2000 / Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–20–05 Empresa Brasileira de

Aeronautica S.A. (EMBRAER):

Amendment 39–11916. Docket 99–NM–

356–AD.

Applicability: Model EMB–120 series

airplanes as listed in EMBRAER Service

Bulletin 120–32–0077, Change 02, dated

December 23, 1997; 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 (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 the landing gear doors from

becoming blocked from opening during

application of emergency procedures in the

event of a loss of hydraulics, accomplish the

following:

Airplane Flight Manual (AFM) Revision

(a) Within 10 flight hours after the effective

date of this AD, revise the ‘‘Emergency

Procedures’’ and ‘‘Abnormal Procedures’’

sections of the FAA-approved AFM by

inserting into the AFM a copy of EMB–120

AFM 120/794, Revision 45, dated October 14,

1996.

(b) For airplanes on which the check valve

has been installed in accordance with

EMBRAER Service Bulletin 120–32–0077,

dated February 7, 1997: Within 100 hours

after the effective date of this AD, conduct a

visual inspection to detect the check valve

flow direction in accordance with Service

Bulletin 120–32–0077, Change 02, dated

December 23, 1997. If the check valve is

installed incorrectly, prior to further flight,

reinstall the check valve in the proper

position in accordance with Change 02 of the

service bulletin.

(c) For airplanes on which the check valve

has not been installed in accordance with

EMBRAER Service Bulletin 120–32–0077,

dated February 7, 1997; or Change 01, dated

September 25, 1997; or Change 02, dated

December 23, 1997: Within 2,000 flight hours

after the effective date of this AD, install

hydraulic tube assemblies incorporating a

check valve in accordance with Service

Bulletin 120–32–0077, Change 02, dated

December 23, 1997.

Note 2: Accomplishment of the installation

in accordance with EMBRAER Service

Bulletin 120–32–0077, Change 01, dated

September 25, 1997, prior to the effective

date of this AD, is acceptable for compliance

with this paragraph.

Alternative Methods 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, Atlanta

Aircraft Certification Office (ACO), FAA.

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

(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.

Incorporation by Reference

(f) Except as provided by paragraph (a) of

this AD, the actions shall be done in

accordance with EMBRAER Service Bulletin

120–32–0077, Change 02, dated December

23, 1997. EMBRAER Service Bulletin 120–

32–0077, Change 02, dated December 23,

1997 contains the following list of effective

pages:

Page No.

Revision

level

shown on

page

Date shown on page

1, 2, 11, 12 ............................................................................................................................................ 02 December 23, 1997.

3–10 ....................................................................................................................................................... 01 September 25, 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 Empresa Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225, Sao

Jose dos Campos—SP, Brazil. Copies may be

inspected 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; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in Brazilian airworthiness directive 97–05–

03R2, dated March 16, 1998.

Effective Date

(g) This amendment becomes effective

on November 13, 2000.

Issued in Renton, Washington, on

September 26, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–25150 Filed 10–5–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–26–AD; Amendment

39–11902; AD 2000–19–01]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–1A11 (CL–600) and CL–

600–2A12 (CL–601) Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document corrects a

typographical error that appeared in

airworthiness directive (AD) AD 2000–

19–01 that was published in the Federal

Register on September 20, 2000 (65 FR

56780). The typographical error resulted

in failure to reference an acceptable

method of compliance for a certain

requirement. This AD is applicable to

certain Bombardier Model CL–600–

1A11 (CL–600) and CL–600–2A12 (CL–

601) series airplanes. This AD requires

modification of the main landing gear

(MLG) brake units and inboard MLG

wheels; and a revision to the Airplane

Flight Manual (AFM) to include the

increased cooling times for the modified

brakes. This AD allows, for certain

cases, removal of the inboard and/or

outboard wheel discs by installation of

a placard to limit airplane operation on

the ground and a revision to the AFM

to include information for operating the

airplane with the wheel discs removed.

Additionally, this AD provides for an