22482 Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Proposed Rules

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:

Fokker Services B.V.: Docket 99–NM–220–

AD.

Applicability: Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes; serial

numbers 11003 through 11091 inclusive,

11094 through 11171 inclusive, 11991, and

11992; 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 (f) 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 detect and correct cracks in the upper

girder of the main landing gear (MLG)

bracket, which could progress into the

vertical stiffeners of the MLG bracket and

result in reduced structural integrity of the

landing gear, accomplish the following:

Repetitive Inspections and Corrective

Actions

(a) Within 12 months after the effective

date of this AD, perform an eddy current

inspection of the upper girder of the MLG

brackets on the left and right sides of the

airplane for cracks, in accordance with the

Accomplishment Instructions of Fokker

Service Bulletin F28/57–90, Revision 1,

dated August 28, 2000.

(1) If no cracks are found, repeat the

inspection at least every 18 months, until

accomplishment of paragraph (d) of this AD.

(2) Except as provided by paragraph (c) of

this AD, if any crack is found, prior to further

flight, repair as specified in paragraph C.(1)

of the Accomplishment Instructions of the

service bulletin, in accordance with the

service bulletin. Thereafter, repeat the eddy

current inspection at intervals not to exceed

18 months, until accomplishment of

paragraph (d) of this AD.

Note 2: Inspections accomplished before

the effective date of this AD in accordance

with Fokker Service Bulletin F28/57–90,

dated March 1, 1999, are considered

acceptable for compliance with paragraph (a)

of this AD.

Reporting Requirement

(b) Within 10 days after accomplishing

each inspection required by paragraph (a) of

this AD, submit a report of the inspection

results to: Fokker Services B.V., Technical

Services, Attn: Manager Airline Support, P.O.

Box 231, 2150 AE Nieuw-Vennep, the

Netherlands. Information collection

requirements contained in this regulation

have been approved by the Office of

Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

Replacement

(c) For airplanes on which a crack greater

than 0.591 inch (15 mm) in length is found:

Except as provided by paragraph (e) of this

AD, prior to further flight, replace the

cracked MLG bracket with a new, improved

bracket (including measuring the position of

the existing MLG bracket, removing the

existing bracket and attachment fittings,

checking alignment of the fastener holes,

measuring gaps, installing a shim, and

aligning the new bracket); in accordance with

Fokker Proforma Service Bulletin F28/57–92,

dated July 1, 1999. Such replacement

constitutes terminating action for the

repetitive inspections required by paragraph

(a) of this AD.

Optional Terminating Action

(d) Except as provided by paragraph (e) of

this AD, replacement of the MLG bracket

with a new, improved bracket (including

measuring the position of the existing MLG

bracket, removing the existing bracket and

attachment fittings, checking alignment of

the fastener holes, measuring gaps, installing

a shim, and aligning the new bracket), in

accordance with Fokker Proforma Service

Bulletin F28/57–92, dated July 1, 1999;

constitutes terminating action for the

repetitive inspections specified in paragraph

(a) of this AD for the replaced bracket.

(e) If any discrepancy is detected during

accomplishment of the replacement

procedures, and the service bulletin or any

appendix to the service bulletin specifies to

contact Fokker for appropriate action: Prior

to further flight, repair in accordance with a

method approved by either the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Rijksluchtvaartdienst (or its delegated agent).

Alternative Methods of Compliance

(f) 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, FAA,

Transport Airplane Directorate. 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

(g) 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 4: The subject of this AD is addressed

in Dutch airworthiness directive 1999–045/2,

dated October 31, 2000.

Issued in Renton, Washington, on April 30,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–11227 Filed 5–3–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–274–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model Hawker 800XP Series Airplanes

and Model Hawker 800 (U–125A

Military) 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 Raytheon Model Hawker 800XP

series airplanes and certain Model

Hawker 800 (U–125A military)

airplanes. This proposal would require

a one-time inspection of an attachment

bolt in the main landing gear (MLG)

door system to determine whether the

bolt’s protruding threads have been

peened; and corrective action, if

Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Proposed Rules 22483

necessary. This action is necessary to

prevent the disconnection of the

retaining hook (which holds the MLG

door up and locked) from its means of

actuation, which could result in a gearup landing and possible injury to

passengers and crew. This action is

intended to address the identified

unsafe condition.

DATES: Comments must be received by

June 18, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

274–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–274–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,

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 2000–NM–274–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

2000–NM–274–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received results of a

routine production-line inspection that

identified an unsafe condition on

certain Raytheon Model Hawker 800XP

series airplanes and certain Model

Hawker 800 (U–125A military)

airplanes. The inspection concerned

attachment bolts on the retaining hooks

of the main landing gear (MLG) doors.

The bolts are located at the interface

between the retaining hooks on the right

and left MLG doors and the uplock

spring struts. On all of the airplanes

inspected, the threads of the attachment

bolts had not been peened, as required

by the airplanes’ type design. Peening is

the only positive means specified in the

design for retaining the nuts on the

attachment bolts. This condition, if not

corrected, could result in a gear-up

landing and possible injury to

passengers and crew.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Raytheon Service Bulletin SB 32–3386,

dated June 2000. The service bulletin

describes procedures for inspecting an

attachment bolt of the retaining hook of

the MLG door, at the interface between

the retaining hook and the uplock

spring strut, to determine whether the

bolt’s protruding threads next to the nut

have been peened. Corrective actions

described in the service bulletin include

peening the threads of any unpeened

bolt. Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require accomplishment of the actions

specified in the service bulletin

described previously.

Cost Impact

There are approximately 167

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

115 airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 1 work hour

per airplane to accomplish the proposed

inspection, 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 $6,900, or $60 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 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

22484 Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Proposed Rules

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–274–AD.

Applicability: Model Hawker 800XP series

airplanes, and Model Hawker 800 (U–125A

military) airplanes; certificated in any

category; as listed in Raytheon Service

Bulletin SB 32–3386, dated June 2000.

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 a main landing gear (MLG)

gear-up landing and possible injury to

passengers and crew, accomplish the

following:

Inspection

(a) Within 100 flight hours after the

effective date of this AD: Perform a general

visual inspection of the MLG attachment bolt

at the interface between the right and left

MLG door retaining hooks and the uplock

spring struts to determine whether the bolt’s

protruding threads next to the nuts have been

peened, in accordance with Raytheon Service

Bulletin SB 32–3386, dated June 2000. If the

threads have not been peened, prior to

further flight, peen the threads in accordance

with the service bulletin.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

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, 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

(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.

Issued in Renton, Washington, on April 30,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–11226 Filed 5–3–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–339–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–300 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 Dornier Model 328–300 series

airplanes. This proposal would require

replacing the brake assemblies with

modified brake assemblies. This action

is necessary to prevent overheating of

the brakes, which could result in

cracked pistons and consequent leakage

and burning of the hydraulic fluid. This

action is intended to address the

identified unsafe condition.

DATES: Comments must be received by

June 4, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

339–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–339–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

Fairchild Dornier, Dornier Luftfahrt

GmbH, P.O. Box 1103, D–82230

Wessling, Germany. 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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, 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