21278 Federal Register / Vol. 66, No. 83 / Monday, April 30, 2001 / Rules and Regulations

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Incorporation by Reference

(e) The actions must be done in accordance

with Dornier Alert Service Bulletin ASB

328J–28–007, dated September 20, 2000. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from

Fairchild Dornier, Dornier Luftfahrt GmbH,

P.O. Box 1103, D–82230 Wessling, Germany.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 4: The subject of this AD is addressed

in German airworthiness directive 2001–058,

dated March 8, 2001.

Effective Date

(f) This amendment becomes effective on

May 15, 2001.

Issued in Renton, Washington, on April 23,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10592 Filed 4–27–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–75–AD; Amendment

39–12211; AD 2001–09–06]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Models 206H and

T206H Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Cessna Aircraft

Company (Cessna) Models 206H and

T206H airplanes. This AD requires you

to visually inspect the horizontal

stabilizer attachment reinforcement

brackets for the existence of seam welds

and replace any reinforcement bracket

found without seam welds. This AD is

the result of a report that these parts

were manufactured without seam welds.

The actions specified by this AD are

intended to detect and replace

structurally deficient horizontal

stabilizer attachment brackets.

Continued use of such brackets could

result in structural failure of the

horizontal stabilizer with reduced or

loss of control of the airplane.

DATES: This AD becomes effective on

May 18, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulation as of May 18, 2001.

The Federal Aviation Administration

(FAA) must receive any comments on

this rule on or before June 15, 2001.

ADDRESSES: Submit comments in

triplicate to FAA, Central Region, Office

of the Regional Counsel, Attention:

Rules Docket No. 2000–CE–75–AD, 901

Locust, Room 506, Kansas City,

Missouri 64106.

You may get the service information

referenced in this AD from Cessna

Aircraft Company, Product Support,

P.O. Box 7706, Wichita, Kansas 67277;

telephone: (316) 517–5800; facsimile:

(316) 942–9006. You may examine this

information at FAA, Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

75–AD, 901 Locust, Room 506, Kansas

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Eual

Conditt, Aerospace Engineer, Wichita

Aircraft Certification Office, FAA, 1801

Airport Road, Mid-Continent Airport,

Wichita, Kansas 67209; telephone: (316)

946–4128; facsimile: (316) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

Cessna recently notified FAA of a defect

in the manufacturing of the horizontal

stabilizer attachment reinforcement

brackets. Cessna manufactured certain

reinforcement brackets without seam

welds. The seam welds help provide the

required structural integrity for the

horizontal stabilizer attachment bracket.

What are the consequences if the

condition is not corrected? This

condition, if not corrected, could result

in structural failure of the horizontal

stabilizer with reduced or loss of control

of the airplane.

Is there service information that

applies to this subject? Cessna has

issued Service Bulletin SB00–55–03,

dated August 28, 2000. This service

bulletin includes procedures for:

—visually inspecting the right and left

horizontal stabilizer attachment

reinforcement brackets for the existence

of seam welds along the lower inboard

and outboard wall/flange; and

—removing and replacing the

horizontal stabilizer assemblies with

new parts.

The FAA’s Determination and an

Explanation of the Provisions of This

AD

What has FAA decided? The FAA has

reviewed all available information,

including the service information

referenced above; and determined that:

—The unsafe condition referenced in

this document likely exists on Cessna

Models 206H and T206H airplanes

within the listed serial number range;

—The actions specified in the

previously-referenced service

information (as specified in this AD)

should be accomplished on the affected

airplanes; and

—AD action should be taken in order

to correct this unsafe condition.

What does this AD require? This AD

requires you to accomplish the actions

previously specified in accordance with

Cessna Service Bulletin SB00–55–03,

dated August 28, 2000.

Will I have the opportunity to

comment prior to the issuance of the

rule? Because the unsafe condition

described in this document could result

in structural failure of the horizontal

stabilizer with possible reduced or loss

of control of the airplane, FAA finds

that notice and opportunity for public

prior comment are impracticable.

Therefore, good cause exists for making

this amendment effective in less than 30

days.

Comments Invited

How do I comment on this AD?

Although this action is in the form of a

final rule and was not preceded by

notice and opportunity for public

comment, we invite your comments on

the 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.

We will consider all comments received

on or before the closing date specified

above. We may amend this rule in light

of comments received. Factual

information that supports your ideas

and suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether we

need to take additional rulemaking

action.

Are there any specific portions of the

AD I should pay attention to? The FAA

specifically invites comments on the

overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

Federal Register / Vol. 66, No. 83 / Monday, April 30, 2001 / Rules and Regulations 21279

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 concerns

the substantive parts of this AD.

We are reviewing 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 clear, 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. 2000–CE–75–AD.’’ We will date

stamp and mail the postcard back to

you.

Regulatory Impact

Does this AD impact various entities?

These regulations will 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, FAA

has determined that this final rule does

not have federalism implications under

Executive Order 13132.

Does this AD involve a significant rule

or regulatory action? The FAA has

determined that this regulation is an

emergency regulation that must be

issued immediately to correct an unsafe

condition in aircraft, and is not a

significant regulatory action under

Executive Order 12866. It has been

determined further that this action

involves an emergency regulation under

DOT Regulatory Policies and Procedures

(44 FR 11034, February 26, 1979). If it

is determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket

(otherwise, an evaluation is not

required). A copy of it, if filed, may be

obtained from the Rules Docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, under the authority

delegated to me by the Administrator,

the Federal Aviation Administration

amends 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 § 39.13 by adding a

new airworthiness directive (AD) to

read as follows:

2001–09–06 Cessna Aircraft Company:

Amendment 39–12211; Docket No.

2000–CE–75–AD.

(a) What airplanes are affected by this AD?

This AD applies to the following airplane

models and serial numbers that are

certificated in any category:

Model Serial Numbers

206H ................. 20608001 through 20608053, 20608055 through 20608086, 20608088 and 20608089.

T206H ............... T20608001 through T20608093, T20608095 through T20608145, T20608147, T20608149, T20608150, T20608152,

T20608156, T20608157, and T20608160.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to detect and replace structurally deficient

horizontal stabilizer attachment brackets.

Continued use of such brackets could result

in structural failure of the horizontal

stabilizer with reduced or loss of control of

the airplane.

(d) What must I do to address this

problem? To address this problem, you must

accomplish the following actions:

Action Compliance time Procedures

(1) Visually inspect the right and left horizontal stabilizer

attachment reinforcement brackets, part number (P/N)

1232624–1, for the existence of seam welds along

both the lower inboard and outboard wall/flange..

Within the next 20 hours time-in-service

(TIS) after May 18, 2001 (the effective

date of this AD), unless already accomplished..

In accordance with the Accomplishment

Instructions in Cessna Service Bulletin

SB00–55–03, dated August 28, 2000,

and the applicable maintenance manual.

(2) If no seam weld is found along both the lower inboard and outboard wall/flange on the right and left

horizontal stabilizer attachment reinforcement bracket

during the inspection required in paragraph (d)(1) of

this AD, replace with a new or airworthy P/N

1232624–1 horizontal stabilizer attachment reinforcement bracket..

Accomplish any necessary replacements

prior to further flight after the inspection

required by this AD, unless already accomplished..

In accordance with the Accomplishment

Instructions in Cessna Service Bulletin

SB00–55–03, dated August 28, 2000,

and the applicable maintenance manual.

(3) If the right and left horizontal stabilizer attachment

reinforcement bracket has seam welds along both the

lower inboard and outboard wall/flange, no further action is required..

Not applicable. .......................................... Not applicable.

(4) Do not install any P/N 1232624–1 horizontal stabilizer attachment reinforcement bracket (or FAA-approved equivalent part) unless the bracket: (i) is inspected as required in paragraph (d)(1) of this AD;

and (ii) has seam welds along both the lower inboard

and outboard wall/flange..

Not applicable ........................................... Not applicable.

21280 Federal Register / Vol. 66, No. 83 / Monday, April 30, 2001 / Rules and Regulations

(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, Wichita Aircraft

Certification Office (ACO), approves your

alternative. Submit your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO.

Note: 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 Eual Conditt, Aerospace

Engineer, Wichita Aircraft Certification

Office, FAA, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209;

telephone: (316) 946–4128; facsimile: (316)

946–4407.

(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

§§ 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) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Cessna Service Bulletin SB00–55–03, dated

August 28, 2000. The Director of the Federal

Register approved this incorporation by

reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from Cessna

Aircraft Company, Product Support, P.O. Box

7706, Wichita, Kansas 67277. You can look

at copies at FAA, Central Region, Office of

the Regional Counsel, 901 Locust, Room 506,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on May 18, 2001.

Issued in Kansas City, Missouri, on April

20, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–10590 Filed 4–27–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–AAL–20]

Revision of Class E Airspace; Bethel,

AK

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action revises Class E

airspace at Bethel, AK, in two ways: The

FAA will cancel the Bethel Very High

Frequency (VHF) Omnidirectional

Range (VOR) instrument approach to

runway (RWY) 36 at Bethel, AK, and

simultaneously reduce the Class E

(surface area extension) airspace at

Bethel, AK; the FAA will correct an

administrative error by revising the

Class E (surface area) airspace with an

exclusion area for Hanger Lake seaplane

base operations. This rule will

accomplish two actions: Allow for the

Napakiak airport to be outside of the

Bethel Class E (surface area extension)

airspace and reduce the required

controlled airspace for aircraft flying

Instrument Flight Rules (IFR) operations

at Bethel, AK; and fix an administrative

oversight by adding the Hanger Lake

exclusion area to the Class E airspace

description at Bethel, AK.

EFFECTIVE DATE: 0901 UTC, July 12,

2001.

FOR FURTHER INFORMATION CONTACT:

Robert Durand, Operations Branch,

Federal Aviation Administration, 222

West 7th Avenue, Box 14, Anchorage,

AK 99513–7587; telephone number

(907) 271–5898; fax: (907) 271–2850;

email: Bob.Durand@faa.gov. Internet

address: http://www.alaska.faa.gov/at or

at address http://162.58.28.41/at.

SUPPLEMENTARY INFORMATION:

History

On February 20, 2001, a proposal to

amend part 71 of the Federal Aviation

Regulations (14 CFR part 71) to revise

the Class E airspace at Bethel, AK, was

published in the Federal Register (66

FR 10861). This proposal was necessary

to accomplish two actions: (1) Allow for

the Napakiak airport to be outside of the

Bethel Class E (surface area extension)

airspace and reduce the required

controlled airspace for aircraft flying

Instrument Flight Rules (IFR) operations

at Bethel, AK; and (2) fix an

administrative oversight by adding the

Hanger Lake exclusion area to the Class

E airspace description at Bethel, AK.

On November 11, 2000, the FAA

initiated Airspace Study Number 00–

AAL–077NR, Notice of Proposed

Revocation of the VOR RWY 36

Approach Procedure at Bethel, Alaska.

Comments during several meetings over

the last year with airspace users in the

Bethel area indicated that they would

like to have Napakiak Airport (WNA)

excluded from the Class E (surface area

extension) airspace at Bethel, AK. The

Bethel Airport has four approaches to

RWY 36: (1) Localizer (LOC)/Distance

Measuring Equipment (DME) Back

Course (BC) RWY 36, (2) VOR/DME

RWY 36, (3) Global Positioning System

(GPS) RWY 36, and (4) the VOR RWY

36. The Bethel VOR RWY 36 instrument

approach, with a procedure turn at

1,600 feet, allows aircraft to descend to

700 feet after the procedure turn is

completed. The FAA protects airspace

from the point an aircraft may legally

descend below 1,000 feet with Class E

(surface area) airspace. For aircraft going

to Bethel Airport, the Napakiak Airport,

located 7.1 nautical miles on a 200° true

bearing from Bethel VORTAC, is an

alternate place to land and wait for

weather to improve when the Bethel

surface area is restricted due to weather.

The FAA received favorable

comments from Craig Air Incorporated,

US Coast Guard District 17, Kusko

Aviation Incorporated, Alaska Airlines,

and the US Fish and Wildlife Service—

Bethel. With the adoption of this

proposal, the FAA intends to

simultaneously cancel the VOR RWY 36

instrument approach and shorten the

Class E airspace to the southwest of

Bethel. There would be three remaining

instrument approaches to the Bethel

RWY 36: (1) LOC/DME BC RWY 36, (2)

VOR/DME RWY 36, and (3) GPS RWY

36. This proposal would allow Visual

Flight Rules (VFR) operations to

continue at Napakiak Airport during

Special VFR operations at Bethel

Airport, AK.

Additionally, this proposal would fix

an administrative oversight by including

an exclusion area for the Hanger Lake

seaplane base operations to the Class E

(surface area) airspace description.

Changes to the Bethel airspace would

incorporate an exclusion below 1,100

feet MSL between the 061° radial and

the 081° radial from 2.9 nautical miles

northeast of the Bethel VORTAC.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No public comments to the proposal

were received, thus the rule is adopted

as written.

The area will be depicted on

aeronautical charts for pilot reference.

The coordinates for this airspace docket

are based on North American Datum 83.