Federal Register / Vol. 62, No. 216 / Friday, November 7, 1997 / Proposed Rules 60191

regulatory evaluation prepared for this

action has been placed 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 a new airworthiness directive

(AD) to read as follows:

SOCATA—Groupe Aerospatiale: Docket No.

97–CE–77–AD.

Applicability: Models TB9, TB10, TB20,

TB21, and TB200 airplanes, serial numbers 1

through 1701; 1707 to 1750; 1758 to 1763;

1767, 1768, and 1769, certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (e) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated in the

body of this AD, unless already

accomplished.

To prevent failure of the upper seat belt

attachment caused by excessive loads on the

upper attachment of the belt, which could

result in bodily injury to the occupants

during landing, accomplish the following:

(a) Within the next 50 hours time-inservice (TIS) after the effective date of this

AD, inspect the bolts and spacers of the

upper attachments of the front belts for

cracks, dents, etc. (damage), in accordance

with the ACCOMPLISHMENT

INSTRUCTIONS section of one of the

following service bulletins, as applicable:

(1) Socata Service Bulletin No. SB 10–103,

dated June 1996, which applies to Socata

Models TB10, TB20, TB21, and TB200

airplanes, and Model TB9 airplanes equipped

with upholstering on the upper duct posts.

(2) Socata Service Bulletin No. SB 10–104,

dated June 1996, which applies to Socata

Model TB9 airplanes not equipped with

upholstering on the upper duct posts.

(b) Prior to further flight, replace any

damaged bolts or spacers found during the

inspection required by paragraph (a) of this

AD.

(c) Within the next 50 hours TIS after the

effective date of this AD, incorporate either

front belts upper attachment reinforcement

kit No. OPT10 921000 or OPT10 920900 and

recondition the belts in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of the applicable service bulletin

referenced in paragraph (a)(1) or (a)(2) of this

AD.

(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.

(e) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(f) All persons affected by this directive

may obtain copies of the documents referred

to herein upon request to SOCATA—Groupe

AEROSPATIALE, Socata Product Support,

Aeroport Tarbes-Ossun-Lourdes, B P 930,

65009 Tarbes Cedex, France; or Perry

Airport, 7501 Pembroke Road, Pembroke

Pines, Florida 33023. These documents may

also be examined at the FAA, Central Region,

Office of the Regional Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Note 3: The subject of this AD is addressed

in French AD 96–142(A) and French AD 96–

143(A), both dated July 17, 1996.

Issued in Kansas City, Missouri, on

October 31, 1997.

James E. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–29422 Filed 11–6–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–236–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 inspections to

detect discrepancies of the support

straps of the flaps and adjacent areas,

and corrective action, if necessary; it

would also require replacement of the

support straps with new straps made of

steel. This proposal is prompted by the

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent fatigue cracking

of the support straps of the flaps, which

could result in further damage to the

flap structure, and consequently lead to

reduced controllability of the airplane.

DATES: Comments must be received by

December 8, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

236–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.
60192 Federal Register / Vol. 62, No. 216 / Friday, November 7, 1997 / Proposed Rules

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–236–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–236–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 it

received a report indicating that, during

a scheduled inspection, fatigue cracks

were found in flap support straps. Such

fatigue cracking, if not detected and

corrected in a timely manner, could

result in damage to the flap structure,

and consequently lead to reduced

controllability of the airplane.

Explanation of Relevant Service

Information

Saab has issued Service Bulletin 340–

57–033, dated May 29, 1997, Revision 1,

dated August 18, 1997, which describes

procedures for visual and detailed

inspections to detect discrepancies of

the flap support straps and adjacent

areas, and corrective action, if

necessary. The service bulletin also

describes procedures for replacement of

the support straps of the flaps with new

straps made of steel. 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. 1–117,

dated June 9, 1997, in order to assure

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 Revision 1 of the service bulletin

described previously, except as

specified below.

Differences Between the Proposed AD

and the Related Service Information

This proposed AD would differ from

Saab Service Bulletin 340–57–033,

Revision 1, dated August 18, 1997, in

that the service bulletin recommends

that any crack detected during an

inspection be repaired in accordance

with instructions that would be

provided by the manufacturer. However,

the FAA has determined that the repair

of any crack would be required to be

accomplished in accordance with a

method approved by the FAA.

Cost Impact

The FAA estimates that 252 Saab

Model SAAB SF340A and SAAB 340B

series airplanes of U.S. registry would

be affected by this proposed AD.

It would take approximately 30 work

hours per airplane to accomplish the

proposed visual inspection, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the visual inspection proposed by

this AD on U.S. operators is estimated

to be a total of $1,800 per airplane.

It would take approximately 180 work

hours per airplane to accomplish the

proposed detailed visual inspection and

concurrent replacement, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $4,580 per airplane.

Based on these figures, the cost impact

of the detailed visual inspection and

replacement proposed by this AD on

U.S. operators is estimated to be

$3,875,760, or $15,380 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 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
Federal Register / Vol. 62, No. 216 / Friday, November 7, 1997 / Proposed Rules 60193

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–236–AD.

Applicability: Model SAAB SF340A and

SAAB 340B series airplanes, as listed in Saab

Service Bulletin 340–57–033, Revision 1,

dated August 18, 1997; 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 (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 fatigue cracking of the flap

support straps, which could result in further

damage to the flap structure and reduced

controllability of the airplane, accomplish

the following:

(a) Except as provided by paragraph (b) of

this AD: Prior to the accumulation of 16,000

total flight cycles, or within 1,500 flight

cycles after the effective date of this AD,

whichever occurs later, perform a visual

inspection to detect discrepancies (i.e.,

cracking and/or damage) of the support

straps of the left-and right-hand flaps and

adjacent areas, in accordance with Saab

Service Bulletin 340–57–033, Revision 1,

dated August 18, 1997. If any discrepancy is

detected, prior to further flight, repair it in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(b) At the next scheduled structural

inspection of the flaps, but not later than the

accumulation of 3,000 flight cycles after the

effective date of this AD, accomplish

paragraphs (b)(1) and (b)(2) of this AD, in

accordance with Saab Service Bulletin 340–

57–033, Revision 1, dated August 18, 1997.

Accomplishment of the inspection and

replacement specified in paragraphs (b)(1)

and (b)(2) of this AD constitutes terminating

action for the requirements of paragraph (a)

of this AD.

(1) Perform a detailed inspection to detect

discrepancies (i.e., cracking and/or damage)

of the support straps of the left-and righthand flaps and adjacent areas, in accordance

with the service bulletin. If any discrepancy

is detected, prior to further flight, repair it in

accordance with a method approved by the

Manager, International Branch, ANM–116.

And,

(2) Replace the support straps of the leftand right-hand flaps with new straps made

of steel, in accordance with the service

bulletin.

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

person shall install a flap assembly having

part number 7257800–501 through –508

inclusive, –571, –572, or –851 through –858

inclusive, on any airplane, unless that flap

assembly has been modified in accordance

with Saab Service Bulletin 340–57–033,

Revision 1, dated August 18, 1997.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, 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.

(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 3: The subject of this AD is addressed

in Swedish airworthiness directive SAD No.

1–117, dated June 9, 1997.

Issued in Renton, Washington, on October

31, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–29421 Filed 11–6–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–179–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 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 A320 series

airplanes. This proposal would require

replacement of a capacitor of the main

landing gear (MLG) circuitry with a new

electrolytic capacitor having a tantalum

casing. This proposal is prompted by

the issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended to prevent the failure of the

landing gear to retract properly as a

result of failure of a capacitor in the

MLG circuitry and subsequent power

interruption.

DATES: Comments must be received by

December 8, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

179–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

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:

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