Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Proposed Rules 63553

Action Compliance time Procedures

(2) You may not install,on any affected airplane, a nose landing gear unit that does not

incorporate a modified steering actuator piston rod, as required by paragraph (d)(1) of

this AD.

As of the effective date of this AD ................... Not Applicable.

(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 airplane

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 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 (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, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Mr. S.M. Nagarajan,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

City, Missouri 64106; telephone: (816) 329–

4145; facsimile: (816) 329–4090.

(g) What if I need to fly the airplane 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 airplane 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 obtain copies

of the documents referenced in this AD from

British Aerospace Regional Aircraft,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland. You may examine 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 British AD 004–05–2000.

Issued in Kansas City, Missouri, on

October 17, 2000.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 00–27223 Filed 10–23–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–CE–83–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace HP137 Mk1, Jetstream

Series 200, and Jetstream Models 3101

and 3201 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain British

Aerospace HP137 Mk1, Jetstream series

200, and Jetstream Models 3101 and

3201 airplanes that are equipped with

certain nose landing gear units. The

proposed AD would require you to

inspect the steering jack assembly to

assure proper clearance between the

bush heads on the steering plates and

the shim on the steering jack trunnions

and to assure that there is adequate

lubrication at both trunnions and the

eye end fitting. The proposed AD would

also require you to adjust the clearance

and provide adequate lubrication, as

necessary. The proposed AD is the

result of mandatory continuing

airworthiness information (MCAI)

issued by the airworthiness authority for

the United Kingdom. The actions

specified by the proposed AD are

intended to prevent cracked steering

jack piston rods caused by inadequate

clearance or inadequate lubrication of

the steering jack pivot points. The

condition could result in failure of the

nose wheel steering system with

consequent loss of airplane control.

DATES: The Federal Aviation

Administration (FAA) must receive any

comments on this proposed rule on or

before November 22, 2000.

ADDRESSES: Submit comments in

triplicate to FAA, Central Region, Office

of the Regional Counsel, Attention:

Rules Docket No. 99–CE–83–AD, 901

Locust, Room 506, Kansas City,

Missouri 64106. Comments may be

inspected at this location between 8

a.m. and 4 p.m., Monday through

Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

British Aerospace Regional Aircraft,

Prestwick International Airport,

Ayrshire, KA9 2RW, Scotland;

telephone: (01292) 479888; facsimile:

(01292) 479703. This information also

may be examined at the Rules Docket at

the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

S.M. Nagarajan, Aerospace Engineer,

FAA, Small Airplane Directorate, 901

Locust, Room 301, Kansas City,

Missouri 64106; telephone: (816) 329–

4145; facsimile: (816) 329–4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

How do I comment on the proposed

AD? The FAA invites comments on this

proposed rule. You may submit

whatever written data, views, or

arguments you choose. You need to

include the rule’s docket number and

submit your comments in triplicate to

the address specified under the caption

ADDRESSES. The FAA will consider all

comments received on or before the

closing date. We may amend the

proposed rule in light of comments

received. Factual information that

supports your ideas and suggestions is

extremely helpful in evaluating the

effectiveness of the proposed AD action

and determining whether we need to

take additional rulemaking action.

Are there any specific portions of the

proposed AD I should pay attention to?

The FAA specifically invites comments

on the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule that might suggest a

need to modify the rule. You may

examine all comments we receive before

and after the closing date of the rule in

the Rules Docket. We will file a report

in the Rules Docket that summarizes

each FAA contact with the public that

63554 Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Proposed Rules

concerns the substantive parts of the

proposed AD.

We are re-examining the writing style

we currently use in regulatory

documents, in response to the

Presidential memorandum of June 1,

1998. That memorandum requires

Federal agencies to communicate more

clearly with the public. We are

interested in your comments on whether

the style of this document is clearer, and

any other suggestions you might have to

improve the clarity of FAA

communications that affect you. You

can get more information about the

Presidential memorandum and the plain

language initiative at http://

www.plainlanguage.gov. 

How can I be sure FAA receives my

comment? If you want us to

acknowledge the receipt of your

comments, you must include a selfaddressed, stamped postcard. On the

postcard, write ‘‘Comments to Docket

No. 99–CE–83–AD.’’ We will date stamp

and mail the postcard back to you.

Discussion

What events have caused this

proposed AD? The Civil Aviation

Authority (CAA), which is the

airworthiness authority for the United

Kingdom, recently notified the FAA that

an unsafe condition may exist on certain

British Aerospace HP137 Mk1, Jetstream

series 200, and Jetstream Models 3101

and 3201 airplanes. The CAA reports

incidents where cracking has occurred

at the base of the thread in the steering

jack piston rod, part number 618212, in

the nose landing gear unit. The

condition could occur on the referenced

airplanes that are equipped with nose

landing gear unit 1873, B00A702852A,

B00A703064A, or B00A703056A. ]

Inadequate clearance or inadequate

lubrication of the steering jack pivot

points can result in unusually high

operational loads. These loads could

result in such cracks in the steering jack

piston rod.

What are the consequences if the

condition is not corrected? A cracked

steering jack piston rod could result in

failure of the nose wheel steering system

with consequent loss of airplane

control.

Is there service information that

applies to this subject? British

Aerospace has issued Mandatory

Service Bulletin 32-JA 981043, dated

March 5, 1999. This service bulletin:

• Specifies inspecting the steering

jack assembly to assure proper clearance

between the bush heads on the steering

plates and the shim on the steering jack

trunnions and to assure that there is

adequate lubrication at both trunnions

and the eye end fitting;

• Specifies adjusting the clearance

and providing adequate lubrication, as

necessary; and

• References APPH Ltd. Service

Newsletter, Issue 2, Jetstream 31

Steering Jack Part Number 618200. The

procedures to accomplish the abovereferenced actions are included in this

service newsletter.

What action did the CAA take? The

CAA classified this service bulletin as

mandatory and issued British AD

Number 012–03–99, in order to assure

the continued airworthiness of these

airplanes in the United Kingdom.

Was this in accordance with the

bilateral airworthiness agreement?

These airplane models are

manufactured in the United Kingdom

and are type certificated for operation in

the United States under the provisions

of section 21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement.

Pursuant to this bilateral

airworthiness agreement, the CAA has

kept FAA informed of the situation

described above.

The FAA’s Determination and an

Explanation of the Provisions of the

Proposed AD

What has FAA decided? The FAA has

examined the findings of the CAA;

reviewed all available information,

including the service information

referenced above; and determined that:

• The unsafe condition referenced in

this document exists or could develop

on other British Aerospace HP137 Mk1,

Jetstream series 200, and Jetstream

Models 3101 and 3201 airplanes of the

same type design;

• The actions specified in the

referenced service information should

be accomplished on the affected

airplanes; and

• AD action should be taken in order

to correct this unsafe condition.

What would the proposed AD require?

This proposed AD would require you to

inspect the steering jack assembly to

assure proper clearance between the

bush heads on the steering plates and

the shim on the steering jack trunnions

and to assure that there is adequate

lubrication at both trunnions and the

eye end fitting. The proposed AD would

also require you to adjust the clearance

and provide adequate lubrication, as

necessary.

Accomplishment of the proposed

action would be in accordance with

APPH Ltd. Service Newsletter, Issue 2,

Jetstream 31 Steering Jack Part Number

618200, as referenced in British

Aerospace Mandatory Service Bulletin

32-JA 981043, dated March 5, 1999.

Cost Impact

How many airplanes would the

proposed AD impact? We estimate that

the proposed AD would affect 300

airplanes in the U.S. registry.

What would be the cost impact of the

proposed AD on owners/operators of the

affected airplanes? We estimate the

following costs to accomplish the

proposed inspection:

Labor cost Parts cost Total cost per

airplane

Total cost on

U.S. airplane

operators

1 workhour × $60 per hour ........................................... No parts required to accomplish the inspection .......... $60 ................. $18,000

We estimate the following costs to

accomplish any necessary adjustments

that would be required based on the

results of the proposed inspections. We

have no way of determining the number

of airplanes that may need such

adjustments:

Labor cost Parts cost Total cost per

airplane.

1 workhour × $60 per hour ......................................................... No parts necessary for adjustment ............................................ $60

Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Proposed Rules 63555

Regulatory Impact

Would this proposed AD impact

various entities? 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 proposed rule

would not have federalism implications

under Executive Order 13132.

Would this proposed AD involve a

significant rule or regulatory action? For

the reasons discussed above, I certify

that this proposed action (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 has been placed 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, under 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. FAA amends Section 39.13 by

adding a new airworthiness directive

(AD) to read as follows:

British Aerospace:—Docket No. 99–CE–83–

AD

(a) What airplanes are affected by this AD?

This AD affects Models HP137 Mk1,

Jetstream series 200, and Jetstream Models

3101 and 3201 airplanes, all serial numbers,

that are:

(1) equipped with a nose landing gear unit

1873, B00A702852A, B00A703064A, or

B00A703056A; and

(2) certificated in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes on the U.S. Register must

comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to prevent cracked steering jack piston rods

caused by inadequate clearance or

inadequate lubrication of the steering jack

pivot points. The condition could result in

failure of the nose wheel steering system

with consequent loss of airplane control.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Action Compliance time Procedures

(1) Inspect the steering jack assembly to

assure proper clearance between the

bush heads on the steering plates and

the shim on the steering jack trunnions

and to assure that there is adequate lubrication at both trunnions and the eye

end fitting.

Within the next 200 hours time-in-service

(TIS) after the effective date of this AD,

unless already accomplished.

Accomplish in accordance with the instructions in

APPH Ltd. Service Newsletter, Issue 2, Jetstream

31 Steering Jack Part Number 618200, as referenced in British Aerospace the Mandatory Service

Bulletin 32–JA 981043 dated March 5, 1999.

(2) Adjust the clearance and provide adequate lubrication, as necessary.Prior to further flight after the inspection

required by paragraph (d)(1) of this AD.

Accomplish in accordance with the instructions in

APPH Ltd. Service Newsletter, Issue 2, Jetstream

31 Steering Jack Part Number 618200, as referenced in British Aerospace Mandatory Service

Bulletin 32–JA 981043, dated March 5, 1999.

Note 1: The FAA is proposing other AD

action that would require installing a

modified nose landing gear steering actuator

piston rod. Incorporating this action does not

justify the need to inspect the piston rod for

cracks.

(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 2: This AD applies to each airplane

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 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 (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, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Mr. S.M. Nagarajan,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

City, Missouri 64106; telephone: (816) 329–

4145; facsimile: (816) 329–4090.

(g) What if I need to fly the airplane 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 airplane 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 obtain copies

of the documents referenced in this AD from

British Aerospace Regional Aircraft,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland. You may examine these

documents at FAA, Central Region, Office of

the Regional Counsel, 901 Locust, Room 506,

Kansas City, Missouri 64106.

Note 3: The subject of this AD is addressed

in British AD 012–03–99.

63556 Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Proposed Rules

Issued in Kansas City, Missouri, on

October 17, 2000.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 00–27295 Filed 10–23–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–249–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAe ATP 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

British Aerospace Model BAe ATP

airplanes. This proposal would require

revising the Airworthiness Limitations

Section of the Instructions for

Continued Airworthiness to incorporate

life limits for certain items and

inspections to detect fatigue cracking in

certain structures. This proposal is

prompted by issuance of a revision to

the airworthiness limitations of the

British Aerospace ATP Aircraft

Maintenance Manual, which specifies

new inspections and compliance times

for inspection and replacement action.

The actions specified by the proposed

AD are intended to ensure that fatigue

cracking of certain structural elements is

detected and corrected; such fatigue

cracking could adversely affect the

structural integrity of these airplanes.

DATES: Comments must be received by

November 24, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

249–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. 99–NM–249–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

British Aerospace Regional Aircraft

American Support, 13850 Mclearen

Road, Herndon, Virginia 20171. 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,

Transport Airplane Directorate, 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 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 99–NM–249–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.

99–NM–249–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, has notified the

FAA that a revision to Section 05–00–

00 of British Aerospace ATP Aircraft

Maintenance Manual (AMM) has been

issued. [The FAA refers to the

information included in that section of

the AMM as the Airworthiness

Limitations Section (ALS).] That

revision affects all British Aerospace

Model BAe ATP airplanes. The revision

provides mandatory replacement times

and structural inspection intervals

approved under section 25.571 of the

Joint Aviation Requirements and the

Federal Aviation Regulations (14 CFR

25.571). As airplanes gain service

experience, or as results of postcertification testing and evaluation are

obtained, it may become necessary to

add additional life limits or structural

inspections to ensure the continued

structural integrity of the airplane.

The CAA advises that analysis of

fatigue test data has revealed that

certain inspections must be performed

at specific intervals to preclude fatigue

cracking in certain areas of the airplane.

In addition, the CAA advises that

certain life limits must be imposed for

various components on these airplanes

to preclude the onset of fatigue cracking

in those components. Such fatigue

cracking, if not corrected, could

adversely affect the structural integrity

of these airplanes.

Explanation of Relevant Service

Information

British Aerospace has issued a

revision to Section 05–00–00, ‘‘General,

Airworthiness Limitations,’’ dated

August 15, 1999, of British Aerospace

ATP Aircraft Maintenance Manual

(AMM), which references additional

chapters. That revised section of the

AMM includes mandatory life

limitations for the airframe and power

plant/engine; structural inspections of

the fuselage, engine, horizontal

stabilizer, and wing bottom surface. The

revised section also describes new

inspections and compliance times for

inspection and replacement actions.

Accomplishment of those actions will

preclude the onset of fatigue cracking of