34132 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Proposed Rules

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:

Boeing: Docket 2000–NM–334–AD.

Applicability: Model 777–200 series

airplanes, line numbers 001 through 093

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 (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 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 find and fix cracking of the web of the

horizontal and sloping pressure decks, which

could result in rapid in-flight decompression

of the airplane, accomplish the following:

Initial Inspections

(a) Do the inspections in paragraphs (a)(1),

(a)(2), and (a)(3) of this AD at the compliance

times specified in those paragraphs. Do the

inspections according to the

Accomplishment Instructions of Boeing

Special Attention Service Bulletin 777–53–

0004, dated May 11, 2000.

(1) Area 1: Prior to the accumulation of

16,000 total flight cycles, do an internal high

frequency eddy current (HFEC) inspection or

an external low frequency eddy current

(LFEC) inspection of the horizontal pressure

deck web in Inspection Area 1, as defined in

the service bulletin.

(2) Area 2: Prior to the accumulation of

31,000 total flight cycles, do an internal

HFEC inspection or an external LFEC

inspection of the horizontal pressure deck

web, an internal HFEC inspection of the

sloping pressure deck, and a detailed visual

inspection of the stiffener end fittings at body

station (BS) 1245 and the stiffener splice

angles at BS 1287, in Inspection Area 2, as

defined in the service bulletin.

Note 2: 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.’’

(3) Area 3: Prior to the accumulation of

46,000 total flight cycles, do an internal

HFEC inspection or an external LFEC

inspection of the horizontal pressure deck

web, and an internal HFEC inspection of the

sloping pressure deck, in Inspection Area 3,

as defined in the service bulletin.

Repetitive Inspections

(b) Repeat the inspections in paragraph (a)

of this AD at least every 2,500 flight cycles

for areas inspected using the HFEC or

detailed visual inspection method, or at least

every 1,000 flight cycles for areas inspected

using the LFEC inspection method, until

paragraph (d) of this AD is done.

Corrective Actions

(c) If any cracking is found during any

inspection required by paragraph (a) or (b) of

this AD: Before further flight, repair the

affected area according to Boeing Special

Attention Service Bulletin 777–53–0004,

dated May 11, 2000; except, where the

service bulletin says to contact Boeing for

repairs, repair per a method approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA; or per data meeting the type

certification basis of the airplane approved

by a Boeing Company Designated

Engineering Representative who has been

authorized by the Manager, Seattle ACO, to

make such findings. For a repair method to

be approved by the Manager, Seattle ACO, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD. Repair according to this paragraph

ends the repetitive inspections required by

paragraph (b) of this AD for the repaired area.

Optional Preventative Modification

(d) Modification of Inspection Areas 1, 2,

and 3, according to Boeing Special Attention

Service Bulletin 777–53–0004, dated May 11,

2000, ends the repetitive inspections

required by paragraph (b) of this AD for the

modified area.

Alternative Methods of Compliance

(e) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(f) Special flight permits may be issued in

accordance with §§ 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 June 20,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–16054 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–23–AD]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 1000, 2000, 3000, and

4000 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

Fokker Model F.28 Mark 1000, 2000,

3000, and 4000 series airplanes. This

proposal would require a one-time eddy

current inspection for cracks of the

fuselage butt joint which is forward of

the emergency exits on the left- and

right-hand sides of the airplane at the

level of stringers 27/48. This proposal

would also require repair of any cracks

detected. This action is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

airworthiness authority. This action is

necessary to detect and correct cracks in

the area of the emergency escape

hatches, which, if undetected, could

Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Proposed Rules 34133

result in depressurization during flight,

possibly leading to structural failure of

the airplane. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

July 27, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket Number 2001–

NM–23–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 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. 2001–NM–23–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

Fokker Services B.V., P.O. Box 231,

2150 AE Nieuw-Vennep, the

Netherlands. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tom

Rodriguez, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–1137;

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 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 2001–NM–23–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

Number 2001–NM–23–AD, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056.

Discussion

The Rijksluchtvaartdienst (RLD),

which is the airworthiness authority for

the Netherlands, notified the FAA that

a crack was found in the fuselage skin

in a bonded doubler at stringer 48

during regular maintenance of a Model

F.28 Mark 1000 series airplane. The

airplane had accumulated 56,000 total

flight cycles when the crack was

discovered. Subsequent investigation

revealed that the crack began at a

scratch, which may have occurred

during production, on the bonded

doubler at the edge of the bonded lower

skin. This condition, if not corrected,

could result in depressurization during

flight, possibly leading to structural

failure of the airplane.

Explanation of Relevant Service

Information

Fokker has issued Service Bulletin

SBF28/53–148, dated August 15, 2000,

which describes procedures for

conducting a one-time eddy current

inspection for cracks of the fuselage butt

joint forward of the emergency exits on

the left- and right-hand sides of the

airplane at the level of stringers 27/48

and reporting the findings to Fokker.

The RLD classified this service bulletin

as mandatory and issued Dutch

airworthiness directive 2000–151, dated

November 30, 2000, in order to assure

the continued airworthiness of these

airplanes in the Netherlands. If any

cracks are found as a result of the

inspection, repair is to be conducted in

a manner approved by the FAA or the

RLD.

FAA’s Conclusions

These airplane models are

manufactured in the Netherlands and

are type certificated for operation in the

United States under the provisions of

§ 21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the RLD has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RLD,

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 require

accomplishment of the actions specified

in the service bulletin described

previously, except as discussed below.

The proposed AD also would require

reporting of the results (positive or

negative) to the FAA.

Differences Between Proposed Rule and

Foreign Airworthiness Directive

Operators should note that, although

the Dutch airworthiness directive

specifies that the manufacturer may be

contacted for disposition of certain

repair conditions, this proposal would

require the repair of those conditions to

be accomplished per a method approved

by either the FAA or the RLD (or a

delegated agent of the RLD). In light of

the type of repair that would be required

to address the identified unsafe

condition, and in consonance with

existing bilateral airworthiness

agreements, the FAA has determined

that, for this proposed AD, a repair

approved by either the FAA or the RLD

would be acceptable for compliance

with this proposed AD.

Cost Impact

The FAA estimates that 23 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 2 work hours per

airplane to accomplish the proposed

34134 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Proposed Rules

eddy current 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 $2,760, or $120 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

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:

Fokker Services B.V.: Docket 2001–NM–23–

AD.

Applicability: All Model F.28 Mark 1000,

2000, 3000, and 4000 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 detect and correct cracks in the area of

the emergency escape hatches, which, if

undetected, could result in depressurization

during flight, possibly leading to structural

failure of the airplane, accomplish the

following:

Inspection

(a) Prior to the accumulation of 30,000 total

flight cycles, or within 12 months after the

effective date of this AD, whichever occurs

later: Perform a one-time eddy current

inspection to detect cracks of the fuselage

butt joint forward of the emergency hatches

on the left- and right-hand sides of the

airplane at the level of stringers 27/48, in

accordance with the Accomplishment

Instructions of Fokker Service Bulletin

SBF28/53–148, dated August 15, 2000.

Repair

(b) If any crack is found during the

inspection required by paragraph (a) of this

AD: Prior to further flight, repair the crack

per a method approved by either the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate; or the

Rijksluchtvaartdienst (or its delegated agent).

Reporting

(c) Submit a report of inspection findings

(both positive and negative) to Fokker

Services B.V., P.O. Box 231, 2150 AE NieuwVennep, the Netherlands; and to Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington 98055–

4056; fax (425) 227–1320. The report is to be

submitted at the applicable time specified in

paragraph (c)(1) or (c)(2) of this AD. The

report must include the inspections results,

a description of any discrepancies found, the

airplane serial number, and the number of

landings and flight hours on the airplane.

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.

(1) For airplanes on which the inspection

is accomplished after the effective date of

this AD: Submit a report of findings within

10 days after performing the inspection

required by paragraph (a) of this AD.

(2) For airplanes on which the inspection

was accomplished prior to the effective date

of this AD: Submit a report of findings within

10 days after the effective date 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,

International Branch, ANM–116. 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 2: 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

(e) Special flight permits may be issued in

accordance with §§ 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 June 20,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–16053 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–24–AD]

RIN 2120–AA64

Airworthiness Directive; Fokker Model

F27 Mark 100, 200, 300, 400, 500, 600,

and 700 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

Fokker Model F27 Mark 100, 200, 300,

400, 500, 600, and 700 series airplanes.

This proposal would require a one-time