This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

66657

Vol. 65, No. 216

Tuesday, November 7, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–102–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC—8—100, -200, and —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 Bombardier Model DHC–8–100,

–200, and –300 series airplanes. This

proposal would require inspection to

determine the orientation of the Wiggins

fuel couplers of the fuel tank vent line

and scavenge line in the right wing at

station 249, and follow-on corrective

actions. This action is necessary to

prevent contact between the nuts of the

Wiggins fuel couplers and the stiffener

on the access panel of the upper surface

of the right wing, which could

compromise the lightning protection of

the fuel tank of the right wing in the

event of a lightning strike, and could

result in possible fuel tank explosion.

This action is intended to address the

identified unsafe condition.

DATES: Comments must be received by

December 7, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

102–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–102–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

Bombardier, Inc., Bombardier Regional

Aircraft Division, 123 Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York.

FOR FURTHER INFORMATION CONTACT:

Serge Napoleon, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7512; fax

(516) 568–2716.

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 2000–NM–102–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–102–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Transport Canada Civil Aviation

(TCCA), which is the airworthiness

authority for Canada, notified the FAA

that an unsafe condition may exist on

certain Bombardier Model DHC–8–100,

–200, and –300 series airplanes. TCAA

advises that it received a report

indicating that a Wiggins fuel coupler

had come in contact with the stiffener

of the wing access panel at wing station

249.

Investigation revealed that the

Wiggins fuel couplers in the right wing

of both the fuel tank vent line and

scavenge line had been installed

incorrectly, with the nut of each coupler

facing the outboard side of the wing,

rather than the inboard side. This

incorrect installation allowed contact

between one nut of the coupler and the

stiffener on the access panel of the

upper surface of the right wing. Such

contact could compromise the lightning

protection of the fuel tank of the right

wing in the event of a lightning strike,

and could result in possible fuel tank

explosion.

Explanation of Relevant Service

Information

The manufacturer has issued

Bombardier Alert Service Bulletin A8–

28–32, dated January 14, 2000, which

describes procedures for a one-time

general visual or x-ray inspection to

determine the orientation of the Wiggins

fuel couplers of the fuel tank vent line

66658 Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Proposed Rules

and scavenge line in the right wing at

station 249. For airplanes on which the

couplers are oriented correctly, the alert

service bulletin describes procedures for

rework of the stiffener on the access

panel of the upper surface of the right

wing. For airplanes on which any

incorrectly oriented coupler is found,

the alert service bulletin describes

procedures for removal of the coupler

and a one-time detailed visual

inspection to detect damage of that

coupler.

For airplanes on which no damaged

coupler is found, the alert service

bulletin describes procedures for

reinstallation of the coupler in the

correct orientation and rework of the

stiffener on the access panel of the

upper surface of the right wing.

However, for airplanes on which any

damaged coupler is found, the alert

service bulletin describes procedures for

blending out the damage and

performing a detailed visual inspection

of the fuel coupler for cracks; and

reinstallation of the coupler in the

correct orientation and rework of the

stiffener on the access panel of the

upper surface of the right wing, or

replacement of the coupler with a new

or serviceable coupler in the correct

orientation and rework the stiffener on

the access panel of the upper surface of

the right wing, if necessary.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. TCAA

classified this alert service bulletin as

mandatory and issued Canadian

airworthiness directive CF–2000–05,

dated February 28, 2000, in order to

assure the continued airworthiness of

these airplanes in Canada.

FAA’s Conclusions

This airplane model is manufactured

in Canada and is 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,

TCAA has kept the FAA informed of the

situation described above. The FAA has

examined the findings of TCAA,

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 alert service bulletin described

previously, except as discussed below.

Differences Between This Proposed AD

and Relevant Service Information

Operators should note that certain

compliance times specified in this

proposed AD differ from those specified

in the alert service bulletin:

• For airplanes having correctly

oriented fuel couplers, the alert service

bulletin recommends reworking the

stiffener within 5,000 flight hours after

the initial inspection. The Canadian

airworthiness directive requires the

rework ‘‘at the next convenient

maintenance opportunity but not later

than the next ‘C’ check or 5,000 hours

flight time after the effective date of this

directive, whichever occurs first.’’

However, this proposed AD would

require the rework for these airplanes

within 5,000 flight hours after the

effective date of the AD.

• For airplanes having incorrectly

oriented fuel couplers, the alert service

bulletin also recommends reworking the

stiffener within 5,000 flight hours of the

initial inspection. However, this

proposed AD requires the rework for

these airplanes prior to further flight

after detecting the incorrect orientation.

In developing the compliance times

for this proposed AD, the FAA

considered not only the manufacturer’s

recommendation, but the degree of

urgency associated with addressing the

subject unsafe condition, and the

compliance times specified in the

Canadian airworthiness directive. In

light of these factors, the FAA finds that

its proposed compliance times for the

rework represent the appropriate

intervals of time allowable for affected

airplanes to continue to operate without

compromising safety.

Cost Impact

The FAA estimates that 195 airplanes

of U.S. registry would be affected by this

proposed AD.

It would take approximately 1 work

hour per airplane to accomplish the

actions (inspection) specified in Part A

of the alert service bulletin, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of these proposed actions on U.S.

operators is estimated to be $11,700, or

$60 per airplane.

It would take approximately 2 work

hours per airplane to accomplish the

actions (rework) specified in Part B of

the alert service bulletin, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of these

proposed actions on U.S. operators is

estimated to be $23,400, 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 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.

Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Proposed Rules 66659

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Bombardier, Inc. (Formerly de Havilland,

Inc.): Docket 2000–NM–102–AD.

Applicability: Model DHC–8–100, –200,

and –300 series airplanes having serial

numbers 003 through 540 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 (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 contact between the nuts of the

Wiggins fuel couplers and the stiffener on the

access panel of the upper surface of the right

wing, which could compromise the lightning

protection of the fuel tank of the right wing

in the event of a lightning strike, and could

result in possible fuel tank explosion,

accomplish the following:

General Visual or X-ray Inspection

(a) Within 90 days after the effective date

of this AD: Perform a one-time general visual

or x-ray inspection to determine the

orientation of the Wiggins fuel couplers of

the fuel tank vent line and scavenge line in

the right wing at station 249, in accordance

with Part A of the Accomplishment

Instructions of Bombardier Alert Service

Bulletin A8–28–32, dated January 14, 2000.

Action for Airplanes Having Correctly

Oriented Fuel Couplers

(b) For airplanes on which the orientation

of all Wiggins fuel couplers is found to be

correct, as specified in Bombardier Alert

Service Bulletin A8–28–32, dated January 14,

2000: Within 5,000 flight hours after the

effective date of this AD, rework the stiffener

on the access panel of the upper surface of

the right wing in accordance with Part B of

the Accomplishment Instructions of the alert

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.’’

Actions for Airplanes Having an Incorrectly

Oriented Fuel Coupler

(c) For airplanes on which the orientation

of any Wiggins fuel coupler is incorrect, as

specified in Bombardier Alert Service

Bulletin A8–28–32, dated January 14, 2000:

Prior to further flight, remove the incorrectly

oriented Wiggins fuel coupler, and perform a

one-time detailed visual inspection to detect

damage of the fuel coupler, in accordance

with Part A of the Accomplishment

Instructions of the alert service bulletin.

Note 3: 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.’’

(1) If no damage is found: Prior to further

flight, reinstall the Wiggins fuel coupler in

the correct orientation, as specified in the

alert service bulletin, and rework the stiffener

on the access panel of the upper surface of

the right wing, in accordance with Part B of

the Accomplishment Instructions of the alert

service bulletin. No further action is required

by this AD.

(2) If any damage is found, prior to further

flight, blend out the damage and perform a

detailed visual inspection of the fuel coupler

for cracks, in accordance with the alert

service bulletin.

(i) If no crack is found, and blending CAN

be accomplished to meet the limits specified

in the Accomplishment Instructions of the

alert service bulletin: Prior to further flight,

reinstall the Wiggins fuel coupler in the

correct orientation, as specified in the alert

service bulletin, and rework the stiffener on

the access panel of the upper surface of the

right wing, in accordance with Part B of the

Accomplishment Instructions of the alert

service bulletin. No further action is required

by this AD.

(ii) If any crack is found, or if blending

CANNOT be accomplished to meet the limits

specified in the Accomplishment

Instructions of the alert service bulletin: Prior

to further flight, replace the Wiggins fuel

coupler with a new or serviceable coupler in

the correct orientation, as specified in the

alert service bulletin, and rework the stiffener

on the access panel of the upper surface of

the right wing, in accordance with Part B of

the Accomplishment Instructions of the alert

service bulletin. No further action is required

by 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, New York

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, New York ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York 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.

Note 5: The subject of this AD is addressed

in Canadian airworthiness directive CF–

2000–05, dated February 28, 2000.

Issued in Renton, Washington, on

November 1, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28481 Filed 11–06–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF COMMERCE

National Institute of Standards and

Technology

14 CFR Part 285

[Docket No. 000831249–0249–01]

RIN 0693–ZA39

National Voluntary Laboratory

Accreditation Program; Operating

Procedures

AGENCY: National Institute of Standards

and Technology, Commerce.

ACTION: Notice of proposed rulemaking:

request for comments.

SUMMARY: The Director of the National

Institute of Standards and Technology

(NIST), United States Department of

Commerce, requests comments on

proposed amendments to regulations

pertaining to the operation of the

National Voluntary Laboratory

Accreditation Program (NVLAP). NIST

proposes to revise the NVLAP

procedures to ensure continued

consistency with international

standards and guidelines currently set

forth in the International Organization

for Standardization (ISO)/International

Electrotechnical Commission (IEC)

17025:1999, General requirements for

the competence of testing and

calibration laboratories, and ISO/IEC

Guide 58:1993, Calibration and testing

laboratory accreditation systems—

General requirements for operation and

recognition, thereby facilitating and

promoting acceptance of test and

calibration results between countries to

avoid barriers to trade. Provisions in

this regard will facilitate cooperation

between laboratories and other bodies,

assist in the exchange of information