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

Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules 10237

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–212–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

Raytheon Aircraft Company, Manager,

Service Engineering, Product Support

Department (62), P.O. Box 85, Wichita,

Kansas 67201–0085. This information

may be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT: Paul

C. DeVore, Aerospace Engineer, Systems

and Propulsion Branch, ACE–116W,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas

67209; telephone (316) 946–4142; fax

(316) 946–4407.

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–212–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–212–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to certain

Raytheon Model BAe.125, Hawker 800

(U–125A), and Hawker 800XP series

airplanes, was published as a notice of

proposed rulemaking (NPRM) in the

Federal Register on August 14, 2000 (65

FR 49523). That NPRM 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.

Actions Since Issuance of Previous

Proposal

Since the issuance of that NPRM, the

FAA has received reports indicating that

aluminum bedding strips may inhibit

proper torquing of the clamp. Such

improper torquing of the clamp may

allow separation of the turbine air

discharge duct or water separator outlet

duct from the cold air unit turbine or

from the water separator, which could

result 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.

Issuance of a New Service Bulletin

The FAA has reviewed and approved

Raytheon Service Bulletin SB 21–3414,

Revision 1, dated July 2000, that

describes procedures for removing

certain aluminum bedding strips on the

air conditioning duct sleeves attached to

both ends of the turbine air discharge

duct and at the outlet end of the water

separator. That service bulletin also

specifies additional airplane models to

the effectivity specified in Raytheon

Service Bulletin SB 21–3377, Revision

1, dated July 2000, which was specified

as the appropriate service information

in the original NPRM.

Conclusion

Since this change expands the scope

of the originally proposed rule, the FAA

has determined that it is necessary to

reopen the comment period to provide

additional opportunity for public

comment.

Cost Impact

There are approximately 270 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 of the affected design in

the worldwide fleet.

The FAA estimates that 154 airplanes

of U.S. registry would be affected by

paragraph (a) of this proposed AD. We

estimate that the actions required by

paragraph (a) of this AD would take

approximately 8 work hours per

airplane to accomplish, and that the

average labor rate is $60 per work hour.

Required parts would cost

approximately $492 per airplane. Based

on these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $149,688, or $972 per

airplane.

The FAA estimates that an additional

36 airplanes of U.S. registry would be

affected by paragraph (b) of this

proposed AD. We estimate that the

actions required by paragraph (b) of this

AD would take approximately 2 hours

per airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. There is no cost

for required parts. Based on these

figures, the cost impact of paragraph (b)

of the proposed AD on U.S. operators is

estimated to be $4,320, or $120 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

10238 Federal Register / Vol. 66, No. 31 / Wednesday, February 14, 2001 / Proposed Rules

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,

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:

Raytheon Aircraft Company: Docket 2000–

NM–212–AD.

Applicability: Model BAe.125 series 800A

(C–29A and U–125 military), 1000A, and

1000B airplanes, Hawker 800 (U–125A

military) airplanes; up to and including serial

number 258406; and Hawker 800XP series

airplanes, up to and including serial number

258483 and 1000 series airplanes; 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 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, accomplish the following:

Replacement

(a) For Model BAe.125 series 800A (C–29A

and U–125 military) series airplanes, Hawker

800 (U–125A military) airplanes up to and

including serial number 258406, and Hawker

800XP series airplanes up to and including

serial number 258459: Remove the clamps,

bedding tapes, and rubber connecting sleeves

at the ends of the air turbine discharge duct

and the water separator, and replace the

clamps and rubber connecting sleeves with

new, improved components, in accordance

with the Accomplishment Instructions of

Raytheon Service Bulletin SB 21–3377,

Revision 1, dated July 2000, at the earliest of

the times specified in paragraphs (a)(1),

(a)(2), and (a)(3) of this AD.

(1) Prior to any extended over-water

operation.

(2) Within the next 300 hours time-inservice after the effective date of this AD.

(3) Within the next six months after the

effective date of this AD.

Note 2: An extended over-water operation

is defined in 14 CFR 1.1 as ‘‘ * * * an

operation over water at a horizontal distance

of more than 50 nautical miles from the

nearest shoreline. * * * ’’

(b) For Model Hawker 800XP series

airplanes having serial numbers 258460

through 258483, Model BAe.125 series

1000A/1000B airplanes, and Hawker 1000

series airplanes: Remove the aluminum

bedding strips from the air conditioning duct

sleeves attached to both ends of the turbine

air discharge duct and at the outlet end of the

water separator, in accordance with the

Accomplishment Instructions of Raytheon

Service Bulletin SB 21–3414, Revision 1,

dated July 2000, at the earliest of the times

specified in paragraphs (b)(1), (b)(2), and

(b)(3) of this AD.

(1) Prior to any extended over-water

operation.

(2) Within the next 300 hours time-inservice after the effective date of this AD.

(3) Within the next six months after the

effective date of this AD.

Actions Accomplished Previously and

Terminating Actions

(c) For certain airplanes, actions described

in the original issuance of Raytheon Service

Bulletin SB 21–3377, may have been

accomplished prior to the effective date of

this AD. On those airplanes, those actions are

not required to be repeated, as allowed by the

phrase, ‘‘unless accomplished previously.’’

However, any action described in Raytheon

Service Bulletin SB 21–3377, Revision 1,

dated July 2000, or Raytheon Service Bulletin

SB 21–3414, Revision 1, dated July 2000, that

has not been accomplished on those

airplanes must be accomplished in

accordance with this AD. Accomplishment of

the actions specified in both Raytheon

Service Bulletin SB 21–3377, Revision 1,

dated July 2000, and Raytheon Service

Bulletin SB 21–3414, Revision 1, dated July

2000, is considered to be terminating action

for the requirements of this AD.

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, Wichita

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, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita 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.

Issued in Renton, Washington, on February

7, 2001.

Donald L. Riggin,

Acting Manager,, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–3675 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–45–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–102, –103, –106, –201,

–202, –301, –311, –314, and –315 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 all

Bombardier Model DHC–8–102, –103,

–106, –201, –202, –301, –311, –314, and

–315 series airplanes. This proposal

would require revising the Bombardier

maintenance program to incorporate

repetitive inspections to detect fatigue

cracking in certain structures; and

corrective actions, if necessary. This

proposal is prompted by issuance of