10234 Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules

the States, or on the distribution of

power and responsibilities among the

various levels of government. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this proposed regulation (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 copy of the draft

regulatory evaluation prepared for this

action 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Bombardier, Inc. (Formerly de Havilland,

Inc.): Docket 2000–NM–347–AD.

Applicability: Model DHC–8–100, –200,

and –300 series airplanes, certificated in any

category, having serial numbers 408, 413, 434

through 463 inclusive, 465 through 489

inclusive, 491 through 505 inclusive, and

507.

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 (b) 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 an increased risk of spreading

a fire, or failure of the cabin to pressurize

adequately if certain foam filters are

installed, accomplish the following:

Removal of Foam Filters

(a) Within 4 months after the effective date

of this AD, remove the foam filters from the

cabin ducting installation located below the

dado panels on the left- and right-hand sides

of the airplane (including verifying that the

foam filters are installed behind the grille

assemblies, inspecting the grille assemblies

on both the port and starboard sides and

along the entire length of the interior of the

airplane, removing all foam filters and

ensuring that no pieces remain, and

reinstalling the grille assemblies by locating

the fasteners and pressing each with a

quarter-turn), per Bombardier Aerospace

Repair Drawing RD8–21–23, Issue 2, dated

December 16, 1999.

Alternative Methods of Compliance

(b) 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, New York

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, New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(c) 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.

Note 3: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–25, dated August 28, 2000.

Issued in Renton, Washington, on February

7, 2001.

Dorenda D. Baker,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–3677 Filed 2–13–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–261–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and Model A300 B4–600, A300

B4–600R, and A300 F4–600R

(Collectively Called A300–600) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This amendment proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Model A310 and Model A300

B4–600, A300 B4–600R, and A300 F4–

600R (collectively called A300–600)

series airplanes. This proposal would

require replacement of the ejection jack

on the ram air turbine (RAT). This

action is necessary to prevent the

ejection jack on the RAT from failing

when the RAT is deployed at high

airspeeds, leading to a loss of ability to

properly restrain the movement of the

RAT, possibly resulting in damage to

the RAT itself and to other airplane

components. In the event of an

emergency, failure of the ejection jack

on the RAT could also result in a

reduction of hydraulic pressure or

electrical power on the airplane. This

action is intended to address the

identified unsafe condition.

DATES: Comments must be received by

April 2, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

261–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–nprmcomment@faa.gov.

Comments sent via fax or the Internet

must contain ‘‘Docket No. 2000–NM–

261–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.

Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules 10235

The service information referenced in

this AD may be obtained from Airbus

Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Dan

Rodina, Aerospace Engineer, FAA,

Transport Airplane Directorate, ANM–

116, 1601 Lind Ave., SW, Renton,

Washington 98055–4056; telephone

(425) 227–2125; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this action may be changed in light

of the comments received.

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 proposed 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 proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal 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 2000–NM–261–AD.’’

The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

2000–NM–261–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Generale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on certain Airbus

Model A310 and Model A300 B4–600,

A300 B4–600R, and A300 F4–600R

(collectively called A300–600) series

airplanes.

The DGAC advises that an anomaly of

the ejection jack of the ram air turbine

(RAT) was found in production. Followup analyses showed that the nut at the

end of the ejection jack piston rod has

insufficient thread engagement to absorb

impact loads when the RAT is deployed

at high speed. This condition, if not

corrected, could lead to a loss of ability

to properly restrain the movement of the

RAT, possibly resulting in damage to

the RAT itself and to other airplane

components. In the event of an

emergency, failure of the ejection jack

on the RAT could also result in a

reduction of hydraulic pressure or

electrical power on the airplane.

Explanation of Relevant Service

Information

Airbus has issued service bulletin

A300–29–6048, Revision 01 (for A300–

600 series airplanes) and service

bulletin A310–29–2086, Revision 01 (for

A310 series airplanes), both dated July

12, 2000. These service bulletins

describe procedures for replacing the

ejection jack in the RAT and testing the

modified RAT. Replacing the ejection

jack reduces impact loads by dampening

the deployment of the RAT.

Accomplishment of the actions

specified in the service bulletins is

intended to adequately address the

identified unsafe condition. The DGAC

classified these service bulletins as

mandatory and issued French

airworthiness directive 2000–284–

317(B), dated July 12, 2000, to assure

the continued airworthiness of these

airplanes in France.

Explanation of Secondary Service

Information

The Airbus service bulletins refer to

Hamilton Sundstrand Service Bulletin

No. ERPS03/04EJ–29–1 as an additional

source of service information for

accomplishment of the modification of

the RAT and testing of the modified

RAT.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.19) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

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.

Explanation of 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 registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletins described

previously.

Cost Impact

The FAA estimates that 117 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 6 work hours per

airplane to accomplish the proposed

modification, and that the average labor

rate is $60 per work hour. There would

be no charge for required parts. Based

on these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $42,120, or $360 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this proposed 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 proposal would not

10236 Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this proposed regulation (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) 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 copy of the draft

regulatory evaluation prepared for this

action 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, Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Airbus Industrie: Docket 2000–NM–261–

AD.

Applicability: Model A310 and Model

A300 B4–600, A300 B4–600R, and A300 F4–

600R (collectively called A300–600) series

airplanes; certificated in any category, except

for airplanes on which Airbus Modification

12259 has been embodied.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 per

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 the ejection jack on the ram air

turbine (RAT) from failing when the RAT is

deployed at high airspeeds, leading to a loss

of ability to properly restrain the movement

of the RAT, possibly resulting in damage to

the RAT itself and to other airplane

components and in reduced hydraulic

pressure or electrical power, if such failure

occurs during an emergency, accomplish the

following:

Modification

(a) Within 34 months after the effective

date of this AD: Modify the RAT per Airbus

Service Bulletin A310–29–2086, Revision 01

(for Model A310 series airplanes) or A300–

29–6048, Revision 01 (for Model A300–600

series airplanes), both dated July 12, 2000, as

applicable.

(b) As of the effective date of this AD, no

person shall install on any airplane an

ejection jack, part number 730820, unless it

has been modified per paragraph (a) of this

AD.

Note 2: The Airbus service bulletins refer

to Hamilton Sundstrand Service Bulletin No.

ERPS03/04EJ–29–1, as an additional source

of service information for accomplishment of

the modification of the RAT and testing of

the modified RAT.

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,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(d) Special flight permits may be issued per

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.

Note 4: The subject of this AD is addressed

in French airworthiness directive 2000–284–

317(B), dated July 12, 2000.

Issued in Renton, Washington, on February

7, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–3676 Filed 2–13–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–212–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model BAe.125 Series 800A (C–29A

and U–125 Military), 1000A, and 1000B

Airplanes; Hawker 800 (U–125A

Military) Airplanes; and Hawker 800XP

and 1000 Series Airplanes.

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to certain Raytheon

Model BAe.125, Hawker 800 (U–125A

military) and Hawker 800XP series

airplanes that would have required

removal of existing clamps, bedding

tapes, and rubber connecting sleeves at

the ends of the turbine air discharge

duct and the water separator, and

replacement of the clamps and rubber

connecting sleeves with new, improved

components. This new action revises

the proposed rule by adding airplanes to

the applicability; and, for certain

airplanes, adding a new requirement to

remove aluminum bedding strips that

are installed under the existing clamps.

The actions specified by this new

proposed AD are intended to prevent

the turbine air discharge duct or water

separator outlet duct from disconnecting

from the cold air unit turbine or from

the water separator, resulting in the loss

of air supply to maintain adequate cabin

pressure. Loss of adequate cabin

pressure at high altitude would require

emergency procedures, such as use of

oxygen, auxiliary pressurization, or

emergency descent.

DATES: Comments must be received by

March 12, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

212–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-nprmcomment@faa.gov. Comments