Federal Register / Vol. 62, No. 238 / Thursday, December 11, 1997 / Proposed Rules 65231

FAA’s Conclusions

This airplane model is manufactured

in France and is 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

accomplishment of the actions specified

in the service bulletin described

previously.

Cost Impact

The FAA estimates that 155 Dassault

Model Mystere-Falcon 50 series

airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 6 work hours

per airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $355 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators is estimated to be $110,825, or

$715 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 substantial direct effects

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,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

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:

Dassault Aviation: Docket 97–NM–190–AD.

Applicability: All Model Mystere-Falcon 50

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

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 interference between the wiring

harnesses and adjacent equipment, support

brackets, and structural elements, which

could cause an electrical short circuit

resulting in fire, and consequent loss of

electrical power to essential flight systems;

accomplish the following:

(a) Within 6 months or 300 flight hours

after the effective date of this AD, whichever

occurs first, accomplish the requirements of

paragraphs (a)(1), (a)(2), and (a)(3) of this AD

in accordance with Dassault Service Bulletin

F50–256 (F50–20–5), Revision 1, dated

December 22, 1996.

(1) Perform a one-time inspection of the

clearances between the wiring harnesses and

the adjacent equipment, support brackets,

and structural elements. If any clearance is

outside the limits specified in the service

bulletin, prior to further flight, readjust the

clearances in accordance with the service

bulletin.

(2) Install Teflon protective strips on the

wiring harnesses in the vicinity of the

equipment supports.

(3) Install rubber protective strips to the

rear edges of the equipment supports.

(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 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.

(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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 96–094–

017(B)R1, dated December 18, 1996.

Issued in Renton, Washington, on

December 5, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–32423 Filed 12–10–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–145–AD]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 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 2000 series

airplanes. This proposal would require

repetitive visual inspections to detect

discrepancies of the bushing installation
65232 Federal Register / Vol. 62, No. 238 / Thursday, December 11, 1997 / Proposed Rules

of the aileron actuation fitting, and

eventual installation of staked bushings

in the fitting. Accomplishment of such

installation terminates the repetitive

inspections. This proposal also provides

for an optional temporary preventive

action, which, if accomplished, would

allow the repetitive inspection intervals

to be extended until the terminating

action is accomplished. 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

fitting lugs due to vibration caused by

loose bushings in the fittings, and

consequent reduced controllability of

the airplane.

DATES: Comments must be received by

January 12, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

145–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:

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.

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 97–NM–145–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–103, Attention: Rules Docket No.

97–NM–145–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 2000 series airplanes. The

LFV advises that, during vibration

damping tests, it has been discovered

that the bushings in the aileron

actuation fittings can become loose and

cause vibration. Such vibration, if not

corrected, could lead to failure of the

fitting lugs, and consequent reduced

controllability of the airplane.

Explanation of Relevant Service

Information

Saab has issued Service Bulletin

SAAB 2000–57–014, Revision 02, dated

February 11, 1997, which describes

procedures for repetitive visual

inspections to detect discrepancies of

the bushing installations. In addition,

the service bulletin describes

procedures for eventual installation of

new staked bushings in the aileron

actuation fitting, which, when

accomplished, eliminates the need for

the repetitive inspections. The service

bulletin also describes procedures for an

optional temporary preventive action,

which entails various corrective actions

and installation of washers on the

bushings of the aileron actuation

fittings. 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 (SAD)

No. 1–102R1, dated November 8, 1996,

in order to assure the continued

airworthiness of these airplanes in

Sweden.

FAA’s Conclusions

This airplane model is manufactured

in Sweden and is 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 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

Service Bulletin

Operators should note that, although

the service bulletin specifies that the

manufacturer may be contacted for

disposition of a certain repair condition,

this proposal would require the repair of

that condition to be accomplished in

accordance with a method approved by

the FAA.

Cost Impact

The FAA estimates that 1 airplane of

U.S. registry would be affected by this

proposed AD.

The FAA estimates that it would take

approximately 1 work hour to

accomplish the proposed inspection,

and that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the proposed inspection

on the single U.S. operator is estimated

to be $60 per airplane, per inspection

cycle.

The FAA estimates that it would take

approximately 4 work hours to

accomplish the proposed installation,

and that the average labor rate is $60 per

work hour. Required parts would be

provided by the manufacturer at no cost

to the operator. Based on these figures,

the cost impact of the proposed

installation on the single U.S. operator

is estimated to be $240 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of
Federal Register / Vol. 62, No. 238 / Thursday, December 11, 1997 / Proposed Rules 65233

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Should an operator elect to

accomplish the optional temporary

preventive action that would be

provided by this AD action, it would

take approximately 1 work hour to

accomplish it, at an average labor rate of

$60 per work hour. Required parts

would be provided by the manufacturer

at no cost to the operator. Based on

these figures, the cost impact of the

optional temporary preventive action

would be $60 per airplane.

Regulatory Impact

The regulations proposed herein

would not have substantial direct effects

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,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

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:

SAAB Aircraft AB: Docket 97–NM–145–AD.

Applicability: Model SAAB 2000 series

airplanes having serial numbers –002

through -023 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

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 (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 prevent failure of the fitting lugs, due

to vibration caused by loose bushings in the

aileron actuation fittings, which could result

in reduced controllability of the airplane;

accomplish the following:

(a) Within 100 flight hours after the

effective date of this AD, inspect the bushing

installations of the left-hand and right-hand

aileron actuation fittings to detect any

discrepancies, in accordance with Saab

Service Bulletin 2000–57–014, Revision 02,

dated February 11, 1997.

(1) If no discrepancy is found, repeat the

inspection thereafter at intervals not to

exceed 300 flight hours until the

requirements of paragraph (b) of this AD have

been accomplished. Accomplishment of the

temporary preventive action specified in

paragraph 2.E. of the Accomplishment

Instructions of the service bulletin allows the

repetitive inspections to be accomplished at

intervals of 600 flight hours until the

requirements of paragraph (b) of this AD have

been accomplished.

(2) If any discrepancy is found, prior to

further flight, accomplish the requirements of

either paragraph (a)(2)(i) or (a)(2)(ii) of this

AD in accordance with the service bulletin.

(i) Except as specified in paragraph (c),

accomplish the installation required by

paragraph (b) of this AD. Accomplishment of

this installation constitutes terminating

action for the requirements of this AD. Or

(ii) Accomplish the temporary preventive

action specified in paragraph 2.E. of the

Accomplishment Instructions of the service

bulletin. Thereafter, repeat the inspection

required by paragraph (a) of this AD at

intervals not to exceed 600 flight hours until

the requirements of paragraph (b) of this AD

have been accomplished.

(b) Except as specified in paragraph (c) of

this AD, within 3,000 flight hours after the

effective date of this AD, install the new

staked bushings in the aileron actuation

fitting in accordance with Saab Service

Bulletin 2000–57–014, Revision 02, dated

February 11, 1997. Accomplishment of this

installation terminates the requirements of

this AD.

(c) If, during the accomplishment of the

installation required by paragraph (a)(2)(i) or

paragraph (b) of this AD, the diameter of the

small hole of the fitting lug is found to be

outside the limits specified in Saab Service

Bulletin 2000–57–014, Revision 02, dated

February 11, 1997, repair it in accordance

with a method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(d) As of the effective date of this AD, no

person shall install on any airplane an

aileron having part number, 7357995–843

(left-hand) or 7357995–844 (right-hand),

unless it has been modified in accordance

with paragraph (b) of this AD.

(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,

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.

(f) 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 3: The subject of this AD is addressed

in Swedish airworthiness directive (SAD) 1–

102R1, dated November 8, 1996.

Issued in Renton, Washington, on

December 5, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–32424 Filed 12–10–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–47–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Boeing Model 747 series airplanes, that