10232 Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules

Actions Compliance Procedures

(1) Inspect the airbrake levers in the wing for

lower end corrosion and for play in flight direction when fully extended, and retracting

under load.

Within the next 30 calendar days after the effective date of this AD, and thereafter at

every three calendar years.

Do these actions following the applicable

Rolladen Schneider Technical Bulletin:

Model LS 3: No. 3051, dated September 14,

1999;

Model LS 4: No. 4043, dated September 14,

1999; or

Model LS 6c: No. 6037, dated September 14,

1999.

(2) Replace the bearings if there is jamming

under the load.

Before further flight after the inspection required by this AD.Do this action following the applicable

Rolladen Schneider Technical Bulletin:

Model LS 3: No. 3051, dated September 14,

1999;

Model LS 4: No. 4043, dated September 14,

1999; or

Model LS 6c: No. 6037, dated September 14,

1999.

(3) If corrosion of the bearings is found, but no

jamming, replace the bearings.

Within 6 calendar months after the inspection

required by this AD.

Do this action following the applicable

Rolladen Schneider Technical Bulletin:

Model LS 3: No. 3051, dated September 14,

1999;

Model LS 4: No. 4043, dated September 14,

1999; or

Model LS 6c: No. 6037, dated September 14,

1999.

(4) For only the Model LS 3, adjust the lower

lever member.

Within the next 30 calendar days after the effective date of this AD.Do this action following the procedures contained in Rolladen Schneider Technical Bulletin No. 3051, dated September 14, 1999.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

Note 1: This AD applies to each sailplane

identified in paragraph (a) of this AD,

regardless of whether it has been modified,

altered, or repaired in the area subject to the

requirements of this AD. For sailplanes 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 (e)

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 you have not

eliminated the unsafe condition, specify

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Mike Kiesov, Aerospace

Engineer, Small Airplane Directorate, 901

Locust, Room 301, Kansas City, Missouri

64106; telephone: (816) 329–4121; facsimile:

(816) 329–4091.

(g) What if I need to fly the sailplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your sailplane to a location

where you can accomplish the requirements

of this AD.

(h) How do I get copies of the documents

referenced in this AD? You may get copies of

the documents referenced in this AD from

Rolladen-Schneider Flugzeugbau GmbH,

Muhlstrasse 10, D–63329 Egelsbach,

Germany. You may read these documents at

FAA, Central Region, Office of the Regional

Counsel, 901 Locust, Room 506, Kansas City,

Missouri 64106.

Note 2: The subject of this AD is addressed

in these German AD’s dated March 9, 2000:

—2000–076;

—2000–082; and

—2000–085.

Issued in Kansas City, Missouri, on January

22, 2001.

David R. Showers,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3678 Filed 2–13–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–347–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–100, –200, and –300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Bombardier Model DHC–8–100,

–200, and –300 series airplanes. This

proposal would require removing

certain foam filters from the cabin

ducting installation located below the

dado panels on the left- and right-hand

sides of the airplane. This action is

necessary to prevent an increased risk of

spreading a fire or failure of the cabin

to pressurize adequately if certain foam

filters are installed. This action is

intended to address the identified

unsafe condition.

DATES: Comments must be received by

March 16, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

347–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–347–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 10233

The service information referenced in

the proposed rule may be obtained from

Bombardier, Inc., Bombardier Regional

Aircraft Division, 123 Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York.

FOR FURTHER INFORMATION CONTACT: Dan

Parrillo, Aerospace Engineer, Systems

and Flight Test Branch, ANE–172, FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York 11581; telephone

(516) 256–7505; fax (516) 568–2716.

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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–347–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–347–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Transport Canada Civil Aviation

(TCCA), which is the airworthiness

authority for Canada, notified the FAA

that an unsafe condition may exist on

certain Bombardier Model DHC–8–100,

–200, and –300 series airplanes. TCCA

advises that certain foam filters for the

cabin exhaust system were incorporated

erroneously on production airplanes.

(There is no requirement that these

filters be installed.) These filters failed

to pass the flammability tests specified

in Appendix F of part 25 of the Federal

Aviation Regulations (14 CFR part 25).

This condition, if not corrected, could

increase the risk of spreading a fire on

the airplane.

In addition, pressurization tests are

required by § 25.843(b) of the Federal

Aviation Regulations [14 CFR

25.843(b)]; however, these tests were

conducted without foam filters installed

in the cabin exhaust system of the

airplane. The impact on pressurization

of the airplane to proper levels is

unknown for airplanes on which these

filters are installed; therefore,

pressurization tests would have to be

reaccomplished on any airplane having

the filters. Installation of these filters

could result in failure of the cabin to

pressurize adequately.

Explanation of Relevant Service

Information

The manufacturer has issued

Bombardier Repair Drawing RD8–21–23,

Issue 2, dated December 16, 1999,

which describes procedures for

removing certain foam filters from the

cabin ducting installation located below

the dado panels on the left- and righthand sides of the airplane. These

procedures include: verifying that

certain 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. Accomplishment of the

actions specified in the repair drawing

is intended to adequately address the

identified unsafe condition. TCCA

classified this repair drawing as

mandatory and issued Canadian

airworthiness directive CF–2000–25,

dated August 28, 2000, in order to

assure the continued airworthiness of

these airplanes in Canada.

FAA’s Conclusions

These airplane models are

manufactured in Canada and are type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

TCCA has kept the FAA informed of the

situation described above. The FAA has

examined the findings of TCCA,

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

Proposed 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 repair drawing described

previously.

Cost Impact

The FAA estimates that 38

Bombardier Model DHC–8–100, –200,

and –300 series airplanes of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 8 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$18,240, or $480 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 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 proposed herein

would not have a substantial direct

effect on the States, on the relationship

between the national Government and

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.