This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

64898

Vol. 65, No. 211

Tuesday, October 31, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–142–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B19 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Bombardier Model CL–600–2B19 series

airplanes, that currently requires, among

other actions, certain revisions to the

Airplane Flight Manual (AFM); and

removal of all elevator flutter dampers.

That AD also requires installation of

new elevator flutter dampers, and

replacement of shear pins and shear

links with new improved shear pins and

shear links. This action would add

airplanes to the applicability of the

existing AD; and would require

replacing certain shear pins with new,

improved shear pins; and, for certain

airplanes, inspecting of the maintenance

records to determine replacement status

of the shear pins; and corrective actions,

if necessary. This proposal is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent premature

failure of the shear pins of the elevator

damper, which may increase the

likelihood of jamming or restricting

movement of the elevator and the

resultant adverse effect on

controllability of the airplane.

DATES: Comments must be received by

November 30, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

142–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-anmnprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–142–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

the proposed rule may be obtained from

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087 Station A,

Montreal, Quebec H3C 3G9, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; and at the FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York.

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer,

ANE–171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7512; 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 notice 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–142–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–142–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On February 12, 1998, the FAA issued

AD 98–04–45, amendment 39–10356 (63

FR 9928, February 27, 1998), applicable

to certain Bombardier Model CL–600–

2B19 series airplanes, to require

revisions to the Airplane Flight Manual

(AFM) to advise the flight crew of the

need to perform daily checks to verify

proper operation of the elevator control

system, and to restrict altitude and

airspeed operations under certain

conditions.

That AD also requires removal of all

elevator flutter dampers. That AD also

requires inspections of certain airplanes

to detect deformation or discrepancies

of the flutter damper hinge fittings and

lug of the horizontal stabilizer, the

elevator hinge/damper fitting, and the

shear pin lugs; and replacement of

discrepant parts with serviceable parts.

That AD also requires installation of

new elevator flutter dampers, and

replacement of shear pins and shear

links with new, improved pins and

links. That action was prompted by

reports that the installation of certain

Federal Register / Vol. 65, No. 211 / Tuesday, October 31, 2000 / Proposed Rules 64899

shear pins may jam or restrict

movement of the elevator. The

requirements of that AD are intended to

prevent such jamming or restricting

movement of the elevator and the

resultant adverse effect on the

controllability of the airplane.

Actions Since Issuance of Previous Rule

Transport Canada Civil Aviation

(TCCA), which is the airworthiness

authority for Canada, has advised the

FAA that, in several cases, the new

shear pins of the elevator flutter

dampers have failed. These improved

shear pins were installed, as required by

AD 98–04–45, and were intended to

have a safe life limit of 20,000 flight

cycles. However, in three cases, the

failed shear pins had all been in service

between 5,000 and 6,000 flight cycles.

Investigation revealed that the failed

shear pins did not meet the design

specifications due to a quality control

problem (improper hardness of the

pins).

Explanation of Relevant Service

Information

The manufacturer has issued Canadair

Regional Jet Service Bulletin S.B. 601R–

27–100, Revision ‘A,’ dated March 10,

2000, which describes procedures for

the following:

• Part A of the Accomplishment

Instructions: For certain airplanes,

replacement of shear pins of the elevator

flutter dampers with new, improved

shear pins.

• Parts B and C of the

Accomplishment Instructions: For

certain other airplanes, inspection of the

maintenance records to determine the

replacement status of the shear pins of

the elevator flutter dampers, and

replacement of certain shear pins with

new, improved shear pins.

The manufacturer also has issued

Canadair Regional Jet Temporary

Revision RJ/68–1, dated February 15,

2000, to the AFM. The temporary

revision describes procedures for reintroducing additional first-flight-of-theday checks of the elevator control

system. These checks apply to certain

airplanes on which the previously

described service bulletin has not been

accomplished.

TCCA classified the service bulletin

as mandatory and issued Canadian

airworthiness directive CF–2000–10,

dated March 23, 2000, in order to assure

the continued airworthiness of these

airplanes in Canada.

FAA’s Conclusions

This airplane model is manufactured

in Canada and is type certificated for

operation in the United States under the

provisions of section 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

supersede AD 98–04–45 to continue to

require:

• Revisions to the AFM to advise the

flight crew of the need to perform daily

checks to verify proper operation of the

elevator control system, and to restrict

altitude and airspeed operations under

certain conditions;

• Removal of all elevator flutter

dampers;

• Inspections of certain airplanes to

detect deformation or discrepancies of

the flutter damper hinge fittings and lug

of the horizontal stabilizer, the elevator

hinge/damper fitting, and the shear pin

lugs;

• Replacement of discrepant parts

with serviceable parts; and

• Installation of new elevator flutter

dampers.

This new action would require adding

airplanes to the applicability of the

existing AD; replacing certain shear pins

with new, improved shear pins; and, for

certain airplanes, inspecting the

maintenance records to determine

replacement status of the shear pins,

and corrective actions, if necessary. The

actions would be required to be

accomplished in accordance with the

service bulletin described previously.

Cost Impact

There are approximately 214

Bombardier Model CL–600–2B19 series

airplanes of U.S. registry that would be

affected by this proposed AD.

The removal of the elevator dampers

and the AFM revision that are currently

required by AD 98–04–45, and retained

in this AD, take approximately 6 hours

per airplane to accomplish, at an

average rate of $60 per work hour. The

FAA estimates that all affected U.S.

operators have previously accomplished

these requirements, therefore, the future

cost impact of these requirements is

minimal.

The inspections that are currently

required by AD 98–04–45, and retained

in this AD, take approximately 26 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the inspection requirements of AD

98–04–05 is estimated to be $1,560 per

airplane.

The installation of flutter dampers

that is currently required by AD 98–04–

45 takes approximately 12 work hours

per airplane to accomplish, at an

average labor rate of $60 per work hour.

Required parts would be provided at no

cost to the operators by the

manufacturer. Based on these figures the

cost impact of the installation currently

required AD 98–04–45 is estimated to be

$720 per airplane.

The new actions (i.e., replacement of

the shear pins, check of maintainence

records, and AFM revision) that are

proposed in this AD action would take

approximately 21 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts are estimated to cost

$801. Based on these figures, the cost

impact of these proposed requirements

of this AD on U.S. operators is estimated

to be $441,054, or $2,061 per airplane.

The cost impact figures discussed

above are 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

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,

64900 Federal Register / Vol. 65, No. 211 / Tuesday, October 31, 2000 / Proposed Rules

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

removing amendment 39–10356 (63 FR

9928, February 27, 1998), and by adding

a new airworthiness directive (AD), to

read as follows:

Bombardier, Inc. (Formerly Canadair):

Docket 2000–NM–142–AD. Supersedes

AD 98–04–45, Amendment 39–10356.

Applicability: Model CL–600–2B19 series

airplanes, having serial numbers 7003

through 7357 inclusive, 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 (i) 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 premature failure of the shear

pins of the elevator damper, which may

increase the likelihood of jamming or

restricting movement of the elevator and the

resultant adverse effect on controllability of

the airplane; accomplish the following:

Restatement of AFM Required by AD

98–04–45

(a) For airplanes having serial numbers

7003 through 7054 inclusive: Within 30 days

after January 26, 1994 (the effective date of

AD 94–01–09, amendment 39–8791), revise

the Limitations Section of the FAA-approved

Airplane Flight Manual (AFM) to include the

following restrictions of altitude and airspeed

operations under conditions of single or

double hydraulic system failure; and advise

the flight crew of these revised limits.

Revision of the AFM may be accomplished

by inserting a copy of this AD or AFM

Revision 34, dated June 12, 1995, in the

AFM. Restrictions of altitude and airspeed

operations under conditions of single or

double hydraulic system failure are listed in

the following tables.

Altitude limit

(maximum)

Airspeed limit

(maximum)

Single Hydraulic System Failure

31,000 feet ................ 0.55 Mach (199

KIAS).

30,000 feet ................ 0.55 Mach (204

KIAS).

28,000 feet ................ 0.55 Mach (213

KIAS).

26,000 feet ................ 0.55 Mach (222

KIAS).

24,000 feet ................ 0.55 Mach (232

KIAS).

22,000 feet ................ 0.55 Mach (241

KIAS).

20,000 feet and

below.

252 KIAS.

Double Hydraulic System Failure

10,000 feet ................ 200 KIAS.

Note 2: The restrictions described in the

AFM Temporary Revision (TR) RJ/30, dated

December 16, 1993, meet the requirements of

this paragraph. Therefore, inserting a copy of

TR RJ/30 in lieu of this AD in the AFM is

considered an acceptable means of

compliance with this paragraph.

Restatement of AFM Revision Required by

AD 98–04–45

(b) Within 7 days after December 14, 1994

(the effective date of AD 94–24–02,

amendment 39–9075), accomplish the

requirements of paragraph (b)(1) and (b)(2) of

this AD.

(1) Remove the elevator dampers in

accordance with Canadair Regional Jet Alert

Service Bulletin S.B. A601R–27–041, dated

October 28, 1994.

(2) Revise the Limitations Section of the

FAA-approved AFM to include the

following, which advises the flight crew of

daily checks to verify proper operation of the

elevator control system. Revision of the AFM

may be accomplished by inserting a copy of

this AD or AFM Revision 32, dated March 30,

1995, in the AFM.

Note 3: The daily check described in the

AFM TR RJ/40, dated October 28, 1994,

meets the requirements of this paragraph.

Therefore, inserting a copy of TR RJ/40 into

the AFM in lieu of this AD is considered an

acceptable means of compliance with this

paragraph.

‘‘Elevator, Before Engine Start (First Flight of Day)

(1) Elevator ........... Check .... Travel range (to

approximately

1⁄2 travel) using

each hydraulic

system in turn,

with the other

hydraulic systems depressurized.’’

Restatement of Inspections Required by AD

98–04–45

(c) For airplanes having serial numbers

7003 through 7049 inclusive: Within 12

months after April 3, 1998 (the effective date

of AD 98–04–45, amendment 39–10356),

perform the actions required in paragraphs

(c)(1), (c)(2), and (c)(3) of this AD, as

applicable, in accordance with Section 2.B.,

Part A, of Canadair Regional Jet Service

Bulletin S.B. 601R–27–040, Revision ‘B,’

dated September 11, 1995.

(1) Remove the shear pins and shear links

of the flutter dampers and perform a visual

inspection to detect any deformation or

discrepancy of the flutter damper hinge

fitting and lug of the horizontal stabilizer.

Prior to further flight, replace any deformed

or discrepant part with a serviceable part in

accordance with the service bulletin.

(2) Perform a visual inspection to detect

any deformation or discrepancy of the

elevator hinge/damper fitting and shear pin

lugs. Prior to further flight, replace any

discrepant part with a serviceable part in

accordance with the service bulletin.

(3) Perform a fluorescent penetrant

inspection and a dimensional inspection to

detect any deformation or discrepancy of the

shear pin lugs. If any deformation or

discrepancy is found on the lugs, prior to

further flight, replace the elevator with a new

or serviceable elevator in accordance with

the service bulletin.

Note 4: 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.’’

(d) For airplanes having serial numbers

7003 through 7054: Within 12 months after

April 3, 1998 (the effective date of AD 98–

04–45, amendment 39–10356), install new

elevator flutter dampers (P/N 601R75142–7)

in accordance with Section 2.B., Part B, of

Canadair Regional Jet Service Bulletin S.B.

601R–27–040, Revision ‘B,’ dated September

11, 1995.

New Requirements of This AD: Installation

of Shear Pins

(e) For airplanes having serial numbers

7003 through 7142 inclusive, and 7144:

Within 12 months after the effective date

of this AD, install new shear pins [part

number (P/N) 601R24063–31/S] in

accordance with Part A of the

Accomplishment Instructions of Canadair

Regional Jet Service Bulletin S.B. 601R–27–

100, Revision ‘A,’ dated March 10, 2000.

Federal Register / Vol. 65, No. 211 / Tuesday, October 31, 2000 / Proposed Rules 64901

After accomplishment of the installation of

new shear pins, Canadair Regional Jet TR RJ/

68–1, dated February 15, 2000, may be

removed from the AFM.

Inspection of Maintenance Records Required

by This AD

(f) For airplanes having serial numbers

7143, and 7145 through 7357 inclusive:

Within 14 days after the effective date of this

AD, perform a one-time inspection of the

maintenance records to determine the

replacement status of the shear pins of the

elevator flutter dampers, in accordance with

Part B of the Accomplishment Instructions of

Canadair Regional Jet Service Bulletin S.B.

601R–27–100, Revision ‘A,’ dated March 10,

2000.

(1) If the maintenance records indicate that

all shear pins were NOT replaced after

delivery of the airplane, or if all shear pins

were replaced with shear pins having P/N

601R24063–31/S: No further action is

required by this AD.

(2) If the maintenance records indicate that

any shear pin was replaced after delivery of

the airplane with a shear pin having P/N

601R24063–31 or 601R24063–953, or if the

maintenance records do not verify that all

shear pins having P/N 601R24063–31/S are

installed: Accomplish the requirements of

paragraph (g) of this AD at the times

specified in that paragraph.

AFM Revision and Replacement Required by

This AD

(g) For airplanes on which any shear pin

of the elevator flutter dampers of the

elevators was replaced after delivery of the

airplane with a shear pin having P/N

601R24063–31 or 601R24063–953, or for

airplanes on which verification of shear pins

having P/N 601R24063–31/S is not possible:

Accomplish the requirements of paragraphs

(g)(1) and (g)(2) of this AD at the times

specified in those paragraphs.

(1) Within 30 days after the effective date

of this AD, revise the Normal Procedures

Section of the AFM by inserting Canadair

Regional Jet TR RJ/68–1, dated February 15,

2000 in the AFM, which advises the flight

crew of an additional first-flight-of-the-day

check of the elevator control system.

(2) Within 12 months after the effective

date of this AD, replace the shear pins with

new, improved shear pins having P/N

601R24063–31/S, in accordance with Part C

of the Accomplishment Instructions of

Canadair Regional Jet Service Bulletin S.B.

601R–27–100, Revision ‘A,’ dated March 10,

2000. After accomplishment of the

installation of new shear pins, the temporary

revision required by paragraph (g)(1) of this

AD may be removed from the AFM.

Spares

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

person shall install a shear pin of the elevator

flutter dampers having P/N 601R24063–31 or

601R24063–953 on any airplane.

Alternative Methods of Compliance

(i) 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 5: 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

(j) 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 6: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–10, dated March 23, 2000.

Issued in Renton, Washington, on October

25, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–27947 Filed 10–30–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–72–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2, A300 B4, A300 B4–600, A300

B4–600R, A300 F4–600R, and A310

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 Airbus Model A300 B2, A300

B4, A300 B4–600, A300 B4–600R, A300

F4–600R, and A310 series airplanes.

This proposal would require

modification of the escape slides. This

action is necessary to prevent deflation

of the escape slide after deployment,

which could result in a delay during an

emergency evacuation. This action is

intended to address the identified

unsafe condition.

DATES: Comments must be received by

November 30, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

72–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–

72–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

the proposed rule 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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2110; 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 notice may be changed in light

of the comments received.

Submit comments using the following

format:

• Organize comments by issue. For

example, discuss a request to change the

compliance time and a request to

change a service bulletin reference as

two separate issues.

• For each issue, state the specific

change to the proposed AD 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