Federal Register / Vol. 62, No. 68 / Wednesday, April 9, 1997 / Proposed Rules 17127

Compliance: Required within the next 100

hours time-in-service after the effective date

of this AD or within the next 6 calendar

months after the effective date of this AD,

whichever occurs first, unless already

accomplished.

To prevent failure of the MLG to extend

because of corroded MLG inboard locking

hinges, which could result in loss of control

of the airplane during landing operations,

accomplish the following:

(a) Remove the MLG inboard doors and the

door locking control mechanism (MOD 70–

065–32) in accordance with the Technical

Instruction of Modification OPT70 KO59–32,

dated December 1995, as referenced in Socata

SB Socata 70–073, Amdt. 1, dated June 1996.

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

person may remove MOD 70–065–32 on any

affected airplane, by reinstalling the MLG

inboard doors and the door locking control

mechanism.

(c) 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.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Brussels Aircraft

Certification Division, FAA, Europe, Africa,

and Middle East Office, c/o American

Embassy, B–1000 Brussels, Belgium. The

request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Brussels Aircraft Certification

Division.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels Aircraft

Certification Division.

(e) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to the SOCATA

Groupe AEROSPATIALE, Socata Product

Support, Aeroport Tarbes-Ossun-Lourdes, B

P 930, 65009 Tarbes Cedex, France; or the

Product Support Manager, U.S.

AEROSPATIALE, 2701 Forum Drive, Grand

Prairie, Texas 75053; or may examine this

document at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Issued in Kansas City, Missouri, on April

2, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–8995 Filed 4–8–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–130–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

supersedure of an existing airworthiness

directive (AD), applicable to certain

Saab Model SAAB SF340A and SAAB

340B series airplanes, that currently

requires inspections to detect improper

connections of the wire harness

installation to the cartridges of the fire

extinguishers in the engine nacelles,

correction of any discrepancy, and

modification of the wiring. This action

would add a revised modification of

that wiring, which, if accomplished,

would terminate the inspections

currently required by the existing AD.

This proposal is prompted by reports

indicating that, due to the removal of a

certain clamp during maintenance,

these fire extinguisher cartridges still

could be connected incorrectly after the

modification required by the existing

AD has been accomplished. The actions

specified by the proposed AD are

intended to prevent incorrect wiring of

these cartridges, which would result in

inability of the fire extinguishers to

jointly discharge extinguishing agent

into a nacelle in the event of an engine

fire.

DATES: Comments must be received by

May 19, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

130–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:

Ruth Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1721; fax (206) 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 96–NM–130–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.

96–NM–130–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On January 26, 1994, the FAA issued

AD 94–03–06, amendment 39–8813 (59

FR 4575, February 1, 1994), applicable

to certain Saab Model SAAB SF340A

and SAAB 340B series airplanes, to

require repetitive inspections to detect

improper connections of the harness

installation to the cartridges of the fire

extinguishers in the engine nacelles. If

an improper connection is found, the

AD requires that it be corrected. This

inspection is to be accomplished on all

airplanes immediately after any

maintenance action that requires
17128 Federal Register / Vol. 62, No. 68 / Wednesday, April 9, 1997 / Proposed Rules

disconnection of the electrical

connectors to the cartridges of either fire

extinguisher. In addition, if the wiring

to one of the electrical connectors

exceeds a certain length, it is to be

shortened by making a loop in the

wiring and securing the loop with wax

string.

That action was prompted by a report

of improperly routed control wiring to

the nacelle fire extinguisher cartridges

on a Model SAAB 340B series airplane.

An investigation revealed that certain

wiring of the electrical connectors to

these extinguisher cartridges on some

airplanes is excessively long; this

contributes to the possibility of

incorrectly connecting these cartridges.

There is one fire extinguisher in each

nacelle, and each extinguisher has a

forward and aft cartridge. When the

electrical connectors to the forward and

aft cartridges of both extinguishers are

connected correctly, extinguishing agent

from both extinguishers can be

discharged on a fire in either nacelle.

Should these connectors be reversed,

however, the fire extinguishers cannot

jointly discharge extinguishing agent

into a nacelle in the event of an engine

fire.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

FAA has received reports indicating that

the wiring of some of these electrical

connectors still could be connected

incorrectly to the fire extinguisher

cartridges, in spite of accomplishment

of the modification mandated by that

AD. This can occur when the clamp on

the modified wiring is removed during

maintenance. Should an incorrect

connection occur, extinguishing agent

from only one extinguisher, instead of

both extinguishers, can be discharged

into a nacelle in the event of a fire.

Explanation of Relevant Service

Information

Saab has issued Service Bulletin

SAAB 340–26–015, Revision 1, dated

December 8, 1995, which describes

procedures for conducting an inspection

of the wiring of the electrical connectors

to the cartridges of each fire

extinguisher to detect if they are

incorrectly connected; and correction of

any discrepancy. (The inspection

procedures differ slightly from the

procedures for inspection specified in

Saab Service Bulletin SAAB 340–26–

012, Revision 1, dated October 5, 1993.

That service bulletin is referenced as the

appropriate source of service

information in AD 94–03–06.)

This service bulletin also describes

procedures for a modification that is

revised from the modification required

by the existing AD. This revised

modification entails cutting the wiring

to one of the connectors when it exceeds

a certain length. This revised

modification prevents this wiring from

being connected to the wrong cartridge

of the fire extinguisher, and eliminates

the need for repetitive inspections of

this wiring.

The Luftfartsverket (LFV), which is

the airworthiness authority for Sweden,

classified this service bulletin as

mandatory and issued Swedish

airworthiness directive SAD No. 1–079,

dated November 24, 1995, 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 § 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

supersede AD 94–03–06 to continue to

require repetitive inspections to detect

improper connections of the wire

harness installation to the cartridges of

the fire extinguishers in the engine

nacelles, and correction of any

discrepancies.

The proposed AD also would require

a revised modification of the wiring to

one of the electrical connectors if it

exceeds a certain length.

Accomplishment of this modification

would terminate the repetitive

inspections of the wiring currently

required by AD 94–03–06.

The actions would be required to be

accomplished in accordance with the

service bulletin described previously.

Cost Impact

There are approximately 235 Saab

Model SAAB SF340A and SAAB 340B

series airplanes of U.S. registry that

would be affected by this proposed AD.

The actions that are currently

required by AD 94–03–06 take

approximately 6 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. The

cost for required parts would be

minimal. Based on these figures, the

cost impact on U.S. operators of the

actions currently required is estimated

to be $77,760, or $360 per airplane. (At

the time AD 94–03–06 went into effect,

it was estimated that 216 airplanes

would be affected.)

The new actions that are proposed in

this AD action would take

approximately 6 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would be provided at no

cost to operators. Based on these figures,

the cost impact on U.S. operators of the

proposed requirements of this AD is

estimated to be $84,600, or $360 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or 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
Federal Register / Vol. 62, No. 68 / Wednesday, April 9, 1997 / Proposed Rules 17129

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

removing amendment 39–8813 (59 FR

4575, February 1, 1994), and by adding

a new airworthiness directive (AD), to

read as follows:

SAAB Aircraft AB: Docket 96–NM–130–AD.

Supersedes AD 94–03–06, Amendment

39–8813.

Applicability: Model SAAB SF340A series

airplanes having serial numbers 004 through

159 inclusive; and Model SAAB 340B series

airplanes having serial numbers 160 through

345 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 (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 the incorrect wiring of the wire

harness installation to the fire extinguisher

cartridges in the engine nacelles, which

would result in the inability of the fire

extinguishers to jointly discharge agent into

a nacelle in the event of a fire:

(a) Within 25 days after February 16, 1994

(the effective date of AD 94–03–06,

amendment 39–8813), perform an inspection

to ensure proper connections of the wire

harness installation to the engine nacelle fire

extinguisher, in accordance with Saab

Service Bulletin SAAB 340–26–012, Revision

1, dated October 5, 1993, or Saab Service

Bulletin SAAB 340–26–015, Revision 1,

dated December 8, 1995. Prior to further

flight, correct any discrepancy found and

modify the wiring, in accordance with the

service bulletin. After the effective date of

this AD, perform this inspection and correct

any discrepancy found, in accordance with

Saab Service Bulletin SAAB 340–26–015,

Revision 1, dated December 8, 1995.

(b) Repeat the inspection specified in

paragraph (a) of this AD immediately

following any maintenance action during

which both electric connectors to either of

the fire extinguishers in the nacelle electrical

bays are disconnected.

(c) Prior to the accumulation of 4,000 hours

time-in-service after the effective date of this

AD, or at the next scheduled maintenance

inspection after the effective date of this AD,

whichever occurs earlier:

(1) Conduct an inspection to ensure proper

connection of the wire harness installation to

the fire extinguisher cartridges in both engine

nacelles, in accordance with Saab Service

Bulletin SAAB 340–26–015, Revision 1,

dated December 8, 1995. If any discrepancy

is detected, prior to further flight, correct this

discrepancy in accordance with the service

bulletin.

(2) After the inspection required by

paragraph (c)(1) of this AD has been

accomplished, measure the total length of the

wiring harness from the clamp to connector

9WB–P2/10WB–P2, in accordance with Saab

Service Bulletin SAAB 340–26–015, Revision

1, dated December 8, 1995. If the wiring

harness has been modified with a loop in

accordance with the requirements of

paragraph (a) of this AD, or in accordance

with Saab Service Bulletin SAAB 340–26–

012, Revision 1, dated October 5, 1993,

before measuring, remove the loop in the

wire harness in accordance with Saab Service

Bulletin SAAB 340–26–015, Revision 1,

dated December 8, 1995.

(i) If the total length is 7 inches (180mm)

or less, no further action is required by this

AD.

(ii) If the total length exceeds 7 inches

(180mm), modify this wiring in accordance

with Saab Service Bulletin SAAB 340–26–

015, Revision 1, dated December 8, 1995.

Accomplishment of this modification

constitutes terminating action for the

repetitive inspections required by paragraph

(b) of this AD, and no further action is

required by this AD.

Note 2: Accomplishment of this

modification in accordance with Saab

Service Bulletin SAAB 340–26–015, dated

November 23, 1995, prior to the effective date

of this AD, is considered acceptable for

compliance with the requirements of

paragraph (c)(2)(ii) of this AD.

(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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

Issued in Renton, Washington, on April 2,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–9012 Filed 4–8–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–113–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 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 Dornier Model 328–100 series

airplanes. This proposal would require

repetitive inspections to detect cracking

of the support beam of the main landing

gear (MLG) fairing, and permanent

repair of any cracking found.

Accomplishment of the permanent

repair terminates the repetitive

inspections. This proposal is prompted

by reports of cracking of the support

beam of the MLG fairing. The actions

specified by the proposed AD are

intended to prevent such cracking,

which could result in reduced structural

integrity of the lower part of the MLG

fairing, and subsequent separation of

part of the fairing from the airplane.

DATES: Comments must be received by

May 19, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

113–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

Dornier Luftfahrt GmbH, P.O. Box 1103,

D–82230 Wessling, Germany. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

Connie Beane, Aerospace Engineer,