Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Proposed Rules 21677

(1) Prior to the accumulation of 8 years

since date of manufacture or 8,000 total flight

cycles, whichever occurs first.

(2) Within 6 months after the effective date

of this AD.

Attach Fittings That Have Been Overhauled

or Replaced

(b) For attach fittings on the outboard flaps

that have been overhauled in accordance

with Boeing 747 OHM 57–52–55, dated June

1, 1997, prior to the effective date of this AD,

or replaced with a new fitting; and for attach

fittings on the inboard actuators that have

been replaced with a new fitting: Accomplish

the actions of paragraph (c) of this AD at the

later of the times specified in paragraphs

(b)(1) and (b)(2) of this AD.

(1) Within 8 years or 8,000 total flight

cycles after the attach fitting was overhauled

or replaced, whichever occurs first.

(2) Within 6 months after the effective date

of this AD.

Inspections and Corrective Action

(c) Perform a detailed visual inspection to

detect corrosion around the lower bearing

journal on the actuator attach fittings on the

inboard and outboard flaps, and perform an

ultrasonic inspection to detect cracks around

the lower bearing journal of the attach fittings

of the outboard flaps, in accordance with

Boeing Service Bulletin 747–57A2310,

Revision 1, dated November 23, 1999.

Note 2: For the purposes of this AD, a

detailed 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: Inspections and replacements

accomplished in accordance with Boeing

Alert Service Bulletin 747–57A2310, dated

June 17, 1999, are acceptable for compliance

with the requirements of paragraph (c) of this

AD.

(1) If no corrosion or cracks are detected,

repeat the inspections required by paragraph

(c) of this AD at intervals not to exceed 18

months. Within 5 years after the initial

inspections required by paragraph (c) of this

AD, accomplish the actions specified in

paragraph (d) or (e) of this AD.

(2) If any corrosion is detected, prior to

further flight, remove the corrosion by

accomplishing the actions of either paragraph

(c)(2)(i) or (c)(2)(ii) of this AD.

(i) If corrosion is within the limits of the

Boeing 747 Overhaul Manual, prior to further

flight, accomplish the actions specified in

paragraph (d) or (e) of this AD.

(ii) If corrosion is not within the limits of

the Boeing 747 Overhaul Manual, prior to

further flight, accomplish the actions

specified in paragraph (e) of this AD.

(3) If any crack is detected, prior to further

flight, accomplish the actions specified in

paragraph (e) of this AD.

Overhaul

(d) Overhaul the actuator attach fittings on

the outboard flaps in accordance with Boeing

OHM 57–52–55, Temporary Revision 57–7,

dated June 1, 1999. Repeat the overhaul of

actuators on the outboard flaps as specified

in Part 2 of the Work Instructions of the

service bulletin thereafter at intervals not to

exceed 8 years or 8,000 flight cycles,

whichever occurs first. Accomplishment of

the overhaul of the attach fittings on the

outboard flaps constitutes terminating action

for the repetitive inspection requirements of

paragraph (c)(1) of this AD. Overhaul the

attach fittings on the inboard flaps in

accordance with Boeing OHM 57–52–35,

Temporary Revision 57–8, dated June 10,

1999. Accomplishment of the overhaul of the

actuators on the inboard flaps constitutes

terminating action for the requirements of

this AD for the inboard flap attach fittings.

Replacement

(e) Replace the attach fittings on the

inboard and outboard flap actuators with

new attach fittings in accordance with Boeing

Service Bulletin 747–57A2310, Revision 1,

dated November 23, 1999. Accomplishment

of the replacement constitutes terminating

action for the repetitive inspection and

overhaul requirements of paragraphs (c)(1),

(c)(2), and (c)(3) of this AD. Within 8 years

or 8,000 flight cycles following

accomplishment of the replacement,

whichever occurs first, repeat the

replacement or accomplish the overhaul

specified in paragraph (d) of this AD.

Note 4: Replacement of the attach fitting on

the inboard flaps with fittings that have been

overhauled in accordance with Boeing OHM

57–52–35, Temporary Revision 57–8, dated

June 10, 1999, constitutes terminating action

for the requirements of this AD for the

inboard flap attach fittings.

Alternative Methods of Compliance

(f) 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

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 5: 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

(g) 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.

Issued in Renton, Washington, on April 18,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–10162 Filed 4–21–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–25–AD]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B 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 Saab Model SAAB SF340A and

SAAB 340B series airplanes. This

proposal would require a one-time

inspection to detect chafing of the wires

and harnesses in the cabin compartment

ceiling; repair, if necessary; and

installation of protective sleeving. 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 false warnings of a

hot engine exhaust tailpipe and

intermittent signal failure, which could

result in the consequent execution of

unnecessary procedures by the

flightcrew.

DATES: Comments must be received by

May 24, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

25–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.

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:

21678 Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Proposed Rules

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

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–25–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–25–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfartsverket (LFV), which is

the airworthiness authority for Sweden,

notified the FAA that an unsafe

condition may exist on certain Saab

Model SAAB SF340A and SAAB 340B

series airplanes. The LFV advises that

there has been one reported false

warning indicating the engine exhaust

tailpipe was hot. The warning was

caused by chafed wires located in the

cabin compartment ceiling. Those wires

are routed through the lightening holes

of the airframe. The chafing was found

between the wires and the edge (edge

string) of the lightening holes. The LFV

further advised of two additional

occurrences of similar chafing. Such

false warnings could result in

unnecessary procedures executed by the

flightcrew.

Explanation of Relevant Service

Information

Saab has issued Service Bulletin 340–

92–027, dated December 10, 1999,

which describes procedures for a onetime inspection to detect chafing of the

wires and harnesses in the cabin

compartment ceiling. The service

bulletin describes procedures for repair

of certain chafing. The service bulletin

further describes procedures for the

installation of protective sleeving on all

of the harnesses routed in the inspection

area. Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. The LFV

classified this service bulletin as

mandatory and issued Swedish

airworthiness directive 1–149, dated

December 10, 1999, in order to ensure

the continued airworthiness of these

airplanes in Sweden.

FAA’s Conclusions

These airplane models are

manufactured in Sweden and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the LFV has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the LFV,

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.

Differences Between Proposed Rule and

Relevant Service Information

Operators should note that, although

the service bulletin 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 in

accordance with a method approved by

either the FAA, or the LFV (or its

delegated agent). 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 LFV would be acceptable for

compliance with this proposed AD.

Cost Impact

The FAA estimates that 288 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 36 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts for

the sleeving installation would cost

approximately $358 per airplane. Based

on these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $725,184, or $2,518 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 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:

Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Proposed Rules 21679

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:

Saab Aircraft AB: Docket 2000–NM–25–AD.

Applicability: Model SAAB SF340A, serial

numbers –004 through –159 inclusive; and

SAAB 340B series airplanes, serial numbers

–160 through –459 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 (c) 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 false warning of a hot engine

exhaust tailpipe and intermittent signal

failure, the consequent execution of

unnecessary procedures by the flightcrew,

accomplish the following:

(a) Prior to the accumulation of 14,000 total

flight hours, or within 4,000 flight hours after

the effective date of this AD, whichever

occurs later: Perform a detailed visual

inspection to detect chafing of the wires and

harnesses in the cabin compartment ceiling,

and install protective sleeving on all of the

harnesses routed in the inspection area; in

accordance with Saab Service Bulletin 340–

92–027, dated December 10, 1999. Except as

provided by paragraph (b) of this AD, prior

to further flight, repair any chafing in

accordance with 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.’’

(b) For any chafing detected during the

inspection required by paragraph (a) of this

AD for which the service bulletin specifies to

contact Saab for appropriate action: Prior to

further flight, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Luftfartsverket (LFV) (or its delegated agent).

For a repair method to be approved by the

Manager, International Branch, ANM–116, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Alternative Methods of Compliance

(c) 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 3: 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

(d) 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 4: The subject of this AD is addressed

in Swedish airworthiness directive 1–149,

dated December 10, 1999.

Issued in Renton, Washington, on April 18,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–10163 Filed 4–21–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–56–AD]

RIN 2120–AA64

Airworthiness Directives; Dassault

Model Falcon 2000, Mystere-Falcon

900, Falcon 900EX, Fan Jet Falcon,

Mystere-Falcon 50, Mystere-Falcon 20,

Mystere-Falcon 200, and Falcon 10

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

Dassault Model Falcon 2000, MystereFalcon 900, Falcon 900EX, Fan Jet

Falcon, Mystere-Falcon 50, MystereFalcon 20, Mystere-Falcon 200, and

Falcon 10 series airplanes. This

proposal would require repetitive tests

and inspections to detect discrepancies

of the overwing emergency exit; and

corrective action, if necessary. 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 failure of the

overwing emergency exits to open, and

consequent injury to passengers or crew

members during an emergency

evacuation.

DATES: Comments must be received by

May 24, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

56–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.

Information pertaining to this

proposed rule 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.

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.