37084 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Proposed Rules

6A service facility is defined as a place where

shares are accepted for members’ accounts, loan

applications are accepted, and loans are disbursed. 7A federal credit union’s service area is the area

that can reasonably be served by the service facility

accessible to the groups within the field of

membership. It will most often coincide with that

geographic area primarily served by the service

facility.

(If the group is an association, include a copy

of the association’s Charter/Bylaws or other

equivalent organizational documentation.)

3. Provide the proposed field of membership

wording. Use the example wording found in

NCUA’s Chartering and Field of Membership

Manual, Chapter 2:

b Section II.A for single occupational

common bond groups;

b Section III.A for single associational

common bond groups; or

b Section IV.A for multiple common bond

fields of membership.

4. How many primary potential members

(excluding immediate family and household

members) are in the group: llllllll

5. (a) For multiple common bond expansions,

what is the distance between the group’s

location and your credit union’s nearest

service facility 6 to which the group has

access (Reference Chapter 2, Section IV.A.1):

lllllllllllllllllllll

lllllllllllllllllllll

(b) What is the address of this service facility:

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

(c) Describe the service area 7 primarily

served by the above service facility:

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

6. Is the group in the field of membership of

any other credit union? Yesll Noll If

yes, and the overlapped credit union is not

a community credit union or a non-federally

insured credit union, please address the

following:

b Provide the name and location of the

other servicing credit union:

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

b Include a letter from the overlapped

credit union indicating whether it concurs or

objects to the overlap. If the overlapped

credit union objects or fails to respond,

document attempts to resolve the issue:

lllllllllllllllllllll

lllllllllllllllllllll

b Explain how the expansion’s beneficial

effect in meeting the convenience and needs

of the members of the group clearly

outweighs any adverse effect on the

overlapped credit union:

lllllllllllllllllllll

lllllllllllllllllllll

7. Attach a letter, on letterhead stationery if

possible, from the group requesting credit

union service. This letter must indicate:

b How the group shares the occupational

or associational common bond (for single

common bond additions only);

b That the group wants to be added to the

federal credit union’s field of membership;

b Whether the group presently has other

credit union service available;

b The number of persons currently

included within the group to be added and

the group’s location(s);

b The group’s proximity to the credit

union’s nearest service facility (for multiple

common bond additions only); and

b Why the formation of a separate credit

union for the group is not practical or

consistent with safety and soundness

standards (for multiple common bond

additions only). The formation of a separate

credit union may not be practical if the group

lacks sufficient volunteers or resources to

support the operation of a credit union or

does not meet the economic advisability

criteria outlined in Chapter 1 of NCUA’s

Chartering and Field of Membership Manual.

8. Other comments:

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

lllllllllllllllllllll

Name and title of credit union boardauthorized representative (e.g., President/

CEO):

lllllllllllllllllllll

(Typed/Printed Name)

lllllllllllllllllllll

(Signature)

lllllllllllllllllllll

(Date)

[FR Doc. 00–14782 Filed 6–12–00; 8:45 am]

BILLING CODE 7535–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–96–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 and A300–600 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 Airbus Model A300 and A300–

600 series airplanes. This proposal

would require repetitive inspections to

detect chafing and the existence of

repairs of the harness of the high-level

sensor of the fuel surge tanks, and to

detect chafe marks on the support

canisters of the magnetic level

indicators; and follow-on corrective

actions, if necessary. This proposal also

would require modification of the

harness for the high-level sensor of the

outer wing fuel tanks, which would

terminate certain repetitive inspections.

This proposal is prompted by issuance

of mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to prevent chafing of the

harness of the high-level sensor, which

could result in a short circuit and

consequent fuel ignition source inside

the outer wing fuel tanks.

DATES: Comments must be received by

July 13, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

96–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.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

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,

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.

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

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Proposed Rules 37085

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–96–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–96–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on certain Airbus

Model A300 and A300–600 series

airplanes. The DGAC advises that

maintenance personnel found a chafed

harness (cable) in the outer wing fuel

tank. The harness is routed to the surge

tank high-level sensor. Investigation

revealed that clipping and routing of the

cable (wiring) coupled with excessive

slack of the cable between the ‘‘P’’ clips

allows the cable to chafe against the

support canister for the magnetic level

indicator. Such chafing, if not corrected,

could result in a short circuit and

consequent fuel ignition source inside

the outer wing fuel tank.

Explanation of Relevant Service

Information

The manufacturer has issued Airbus

Service Bulletins A300–28–0077 (for

Model A300 series airplanes), and

A300–28–6062 (for Model A300–600

series airplanes), each dated July 19,

1999. These service bulletins describe

procedures for repetitive inspections to

detect chafing and the existence of

repairs of the harness of the high-level

sensor of the fuel surge tanks, and to

detect chafe marks on the support

canisters of the magnetic level

indicators; and follow-on corrective

actions, if necessary. The follow-on

corrective actions involve removing

original repairs, if necessary, and

accomplishing a splice repair and

installing sleeves to the inner and outer

cable coverings. The service bulletins

categorize the repairs as either

temporary or permanent depending

upon the location of the repair and

whether certain previous repairs were

accomplished. In addition, the followon corrective actions include a

repetitive visual inspection of the

harness to ensure the integrity of the

repair. This inspection would be

performed if certain conditions (e.g.,

any temporary repairs) exist.

The manufacturer also has issued

Airbus Service Bulletins A300–28–0058,

Revision 02 (for Model A300 series

airplanes), and A300–28–6020, Revision

01 (for Model A300–600 series

airplanes), each dated September 28,

1999. These service bulletins describe

procedures for modification of the

harness for the high-level sensor in the

outer wing fuel tanks. The modification

involves re-routing the cables and

installing longer cleats and reversing the

‘‘P’’ clips that support the cables. This

modification will prevent the cables

from sagging and ensure adequate

clearance between the cables and the

support canisters of the magnetic level

indicators. Accomplishment of the

modification eliminates the need for

certain repetitive inspections of the

harness of the high-level sensor of the

fuel surge tanks. However, the

modification does not eliminate the

need for the 10,000-flight-hour detailed

visual inspections specified in the

follow-on corrective actions, following

the accomplishment of any temporary

repairs.

The DGAC classified Airbus Service

Bulletins A300–28–0077 and A300–28–

6062 as mandatory and issued French

airworthiness directive 1999–404–

293(B), dated October 6, 1999, in order

to assure the continued airworthiness of

these airplanes in France.

FAA’s Conclusions

These airplane models are

manufactured in France 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 DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, 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

repetitive inspections to detect chafing

and the existence of repairs of the wire

harnesses of the high-level sensors; and

to detect chafe marks on the support

canisters of the magnetic level

indicators; and follow-on corrective

actions, if necessary. This proposal also

would require modification of the

harness for the high-level sensor of the

outer wing fuel tanks, which would

terminate certain repetitive inspections.

The actions would be required to be

accomplished in accordance with the

service bulletins described previously,

except as discussed below.

Difference Between Proposed AD and

Related Service Information

Operators should note that this AD

proposes to mandate, within 18 months,

the modification of the harness of the

high-level sensor of the outer wing fuel

tanks described in Airbus Service

Bulletin A300–28–0058, Revision 02, or

A300–28–6020, as terminating action for

certain repetitive inspections.

[Incorporation of the terminating action

is optional in French airworthiness

directive 1999–404–293(B).]

The FAA has determined that longterm continued operational safety will

be better assured by design changes to

remove the source of the problem, rather

than by repetitive inspections. Longterm inspections may not provide the

degree of safety assurance necessary for

the transport airplane fleet. This,

coupled with a better understanding of

the human factors associated with

numerous continual inspections, has led

the FAA to consider placing less

emphasis on inspections and more

emphasis on design improvements. The

proposed modification requirement is

consistent with these conditions.

Cost Impact

The FAA estimates that 37 series

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

repetitive detailed visual inspections,

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 $2,220, or

$60 per airplane, per inspection cycle.

It would take approximately 1 work

hour per airplane to accomplish the

proposed modification, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $2,220, or $60 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

37086 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Proposed Rules

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

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:

Airbus Industrie: Docket 2000–NM–96–AD.

Applicability: Model A300 and A300–600

series airplanes, certificated in any category;

except those airplanes on which Airbus

Modification 04489 has been installed during

production.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 chafing of the wire harnesses of

the high-level sensors, which could result in

a short circuit and consequent fuel ignition

source inside the outer wing fuel tanks,

accomplish the following:

Detailed Visual Inspection

(a) Within 500 flight hours after the

effective date of this AD, perform a detailed

visual inspection to detect chafing and the

existence of repairs of the harness (cable) of

the high-level sensor of the fuel surge tanks,

and to detect chafe marks on the support

canisters of the magnetic level indicators; in

accordance with Airbus Service Bulletin

A300–28–0077 (for Model A300 series

airplanes), or A300–28–6062 (for Model

A300–600 series airplanes), each dated July

19, 1999, as applicable.

(1) For airplanes on which modification of

the harness in accordance the Airbus Service

Bulletin A300–28–0058 (for Model A300

series airplanes), or A300–28–6020 (for

Model A300–600 series airplanes), as

applicable; has NOT been accomplished:

Accomplish the requirements of paragraphs

(a)(1)(i) and (a)(1)(ii) of this AD.

(i) Repeat the detailed visual inspection

thereafter at intervals not to exceed 500 flight

hours until the requirements of paragraph

(a)(1)(ii) of this AD are accomplished. If any

wire chafing, chafe mark, or existing repair

is detected during any inspection, prior to

further flight, determine the appropriate

repair and/or condition of repair as specified

in Inspection Table 1 of the Accomplishment

Instructions of Airbus Service Bulletin A300–

28–0077 or A300–28–6062, as applicable. At

the times specified in Inspection Table I,

accomplish corrective actions (e.g.,

temporary or permanent repairs and followon inspections and repairs), in accordance

with the applicable service bulletin. If any

discrepancy is found during any follow-on

inspection, prior to further flight, repair the

discrepancy in accordance with the

applicable service bulletin.

(ii) Within 18 months after the effective

date of this AD, modify the harness of the

high-level sensor in the outer wing fuel

tanks, in accordance with Airbus Service

Bulletin A300–28–0058, Revision 02 (for

Model A300 series airplanes), or A300–28–

6020, Revision 01 (for Model A300–600

series airplanes); each dated September 28,

1999. Accomplishment of the modification

terminates the 500-flight-hour repetitive

inspection required by paragraph (a)(1) of

this AD. However, if a temporary repair is

installed, the 10,000-flight-hour detailed

visual inspection specified in the follow-on

corrective actions of Table 1 continues to be

required by this AD.

(2) For airplanes on which modification of

the harness in accordance with Airbus

Service Bulletin A300–28–0058 (for Model

A300 series airplanes), or A300–28–6020 (for

Model A300–600 series airplanes); as

applicable; HAS been accomplished:

Accomplish the requirements of paragraph

(a)(2)(i) or (a)(2)(ii), as applicable.

(i) If no wire chafing, chafe marks, or

existing repairs are detected, no further

action is required by this AD.

(ii) If any wire chafing, chafe mark, or

existing repair is detected, prior to further

flight, determine the appropriate repair and/

or condition of repair as specified in

Inspection Table 2 of the Accomplishment

Instructions of Airbus Service Bulletin A300–

28–0077 or A300–28–6062, as applicable. At

the times specified in Inspection Table 2,

accomplish corrective actions (e.g.,

temporary or permanent repairs and followon inspections), in accordance with the

applicable service bulletin. If any

discrepancy is found during any follow-on

inspection, prior to further flight, repair the

discrepancy in accordance with the

applicable 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

mirrors, magnifying lenses, etc., may be used.

Surface cleaning and elaborate access

procedures may be required.’’

Note 3: Modification accomplished prior to

the effective date of this AD, in accordance

with Airbus Service Bulletin A300–28–0058,

dated December 15, 1988, Revision 01, dated

October 1, 1991 (for Model A300 series

airplanes), or A300–28–6020, dated

December 15, 1988 (for Model A300–600

series airplanes), is considered acceptable for

compliance with the action specified in

paragraph (a)(1)(ii) of this AD.

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,

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 4: 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

(c) 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.

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Proposed Rules 37087

Note 5: The subject of this AD is addressed

in French airworthiness directive 1999–404–

293(B), dated October 6, 1999.

Issued in Renton, Washington, on June 7,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14884 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–354–AD]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 340B and SAAB 2000 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to certain Saab Model

SAAB 340B and SAAB 2000 series

airplanes, that would have superseded

an existing AD. That AD currently

requires various inspections of

fluorescent lamps and lampholders in

the cabin area for discrepancies;

corrections, if necessary; and

reinspection of the lamps to ensure

correct installation after replacement or

reinstallation of the lamps or

lampholders. The proposed AD would

have added a requirement for

replacement of the electronic light

ballasts with improved ballasts, which

would terminate the reinspections, and

would have expanded the applicability

of the existing AD. That proposal was

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

This new action revises the proposed

rule to require a certain modification in

accordance with revised procedures.

The actions specified by this new

proposed AD are intended to prevent

electrical arcing between the fluorescent

tube pins and the lampholders, which

could burn the surrounding area and

lead to smoke and fumes in the

passenger compartment or lavatory area.

DATES: Comments must be received by

July 10, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

354–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 also

be sent via the Internet using the

following address: 9-anmnprmcomment@faa.gov. Comments sent

via the Internet must contain ‘‘Docket

No. 99–NM–354–AD’’ in the subject line

and need not be submitted in triplicate.

The service information referenced in

the proposed rule may be obtained from

SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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–354–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–354–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to certain

Saab Model SAAB 340B and SAAB

2000 series airplanes, was published as

a notice of proposed rulemaking

(NPRM) in the Federal Register on

March 27, 2000 (65 FR 16154). That

NPRM proposed to supersede AD 97–

13–06, amendment 39–10052 (62 FR

33545, June 20, 1997), which is

applicable to certain Saab Model SAAB

340B and SAAB 2000 series airplanes.

That NPRM would have continued to

require the actions specified in AD 97–

13–06. That NPRM would have added a

requirement for replacement of the

electronic light ballasts with improved

ballasts, which would terminate the

requirement for reinspections of the

lamps. That NPRM would also have

expanded the applicability of the

existing AD to include additional Model

SAAB 340B and SAAB 2000 series

airplanes that are also subject to the

identified unsafe condition. That NPRM

was prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority,

advising that a terminating modification

is available, and that additional

airplanes may be subject to fluorescent

lampholder charring due to the

incorrect installation of the lamps in

their holders. That condition, if not

corrected, could burn the surrounding

area and lead to smoke and fumes in the

passenger compartment or lavatory area.

Actions Since Issuance of Previous

Proposal

Since the issuance of that NPRM, the

FAA has been advised that Saab has

issued Service Bulletin 340–33–049,

Revision 01, dated November 15, 1999,

and Revision 02, dated February 2,

2000. The original issue of this service