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,
17130 Federal Register / Vol. 62, No. 68 / Wednesday, April 9, 1997 / Proposed Rules

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2796; 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–113–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–113–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfahrt-Bundesamt (LBA),

which is the airworthiness authority for

Germany, recently notified the FAA that

an unsafe condition may exist on certain

Dornier Model 328–100 series airplanes.

The LBA advises that it received reports

of cracking of the support beam of the

main landing gear (MLG) fairing on

these airplanes. The cracking was found

during maintenance of the airplanes.

This cracking occurs at design-critical

locations; the design is not adequate due

to severe bending of materials at these

locations. Cracking of the support beam

of the MLG fairing, if not corrected,

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.

Explanation of Relevant Service

Information

Dornier has issued Alert Service

Bulletin ASB–328–53–010, dated

October 13, 1995, which describes

procedures for repetitive visual

inspections to detect cracking of the

lower attachment flanges in the area of

the bend radii of the forward and aft

support beams of the MLG. The alert

service bulletin also describes

procedures for a temporary repair (for

cracking within specified limits) and a

permanent repair (for cracking outside

specified limits). The temporary repair

entails stop drilling the crack, and

performing subsequent visual

inspections until the permanent repair

is accomplished, or until results of the

visual inspections reveal that the length

of the crack has increased to more than

50 mm. Among other things, the

permanent repair involves wet installing

and sealing the angle, protecting

reworked surfaces, and reworking the

existing flange. Accomplishment of the

permanent repair eliminates the need

for the repetitive inspections. The LBA

classified this alert service bulletin as

mandatory and issued German

airworthiness directive 95–413, dated

November 2, 1995, in order to assure the

continued airworthiness of these

airplanes in Germany.

FAA’s Conclusions

This airplane model is manufactured

in Germany 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 LBA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LBA,

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, the proposed AD would

require repetitive visual inspections to

detect cracking of the lower attachment

flanges in the area of the bend radii of

the forward and aft support beams of the

MLG, and permanent repair of any

cracking found. The actions would be

required to be accomplished in

accordance with the alert service

bulletin described previously.

Differences Between Alert Service

Bulletin and This Proposed AD

Operators should note that, while the

alert service bulletin recommends

accomplishment of a temporary repair

for cracking within specified limits, and

a permanent repair for cracking outside

those limits, this proposed AD would

require that the permanent repair be

accomplished for airplanes on which

cracking of any length is found. The

FAA has determined that, due to the

safety implications and consequences

associated with such cracking, the

permanent repair must be accomplished

prior to further flight on all beams that

are found to be cracked.

Cost Impact

The FAA estimates that 27 Dornier

Model 328–100 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 actions, 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 $1,620, or

$60 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.
Federal Register / Vol. 62, No. 68 / Wednesday, April 9, 1997 / Proposed Rules 17131

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:

Dornier: Docket 96–NM–113–AD.

Applicability: Model 328–100 series

airplanes, excluding serial numbers 3006,

3007, and 3010; 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 reduced structural integrity of

the lower part of the MLG fairing, and

subsequent separation of part of the fairing

from the airplane, accomplish the following:

(a) Within 300 hours time-in-service after

the effective date of this AD, perform a visual

inspection to detect cracking of the lower

attachment flanges in the area of the bend

radii of the forward and aft support beams of

the main landing gear (MLG), in accordance

with Dornier Alert Service Bulletin ASB–

328–53–010, dated October 13,

1995.

(1) If no cracking is found, repeat the

inspection thereafter at intervals not to

exceed 300 hours time-in-service.

(2) If any cracking is found, prior to further

flight, accomplish the permanent repair in

accordance with the alert service bulletin.

(b) Accomplishment of the permanent

repair in accordance with Dornier Alert

Service Bulletin ASB–328–53–010, dated

October 13, 1995, constitutes terminating

action for the repetitive inspections required

by this AD.

(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,

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

Issued in Renton, Washington, on April 2,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–9015 Filed 4–8–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–41–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 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 all Airbus

Model A310 and A300–600 series

airplanes, that currently requires a

revision to the Airplane Flight Manual

(AFM) that warns the flight crew of

certain consequences associated with

overriding the autopilot when it is in

the pitch control axis. That AD also

requires modification of certain flight

control computers (FCC). That AD was

prompted by the results of an FAA

review of the requirements of an earlier

AD. This proposed action would require

a modification to the autopilot that

would enable the flight crew to

manually disconnect the autopilot,

regardless of its mode and the altitude

of the airplane; accomplishment of that

modification would terminate the

current requirement to revise the AFM.

This proposed action also would require

repetitive operational testing of the

modified autopilot to determine if the

disconnect function operates properly,

and repair, if necessary. The actions

specified by the proposed AD are

intended to prevent an out-of-trim

condition between the trimmable

horizontal stabilizer and the elevator,

which could severely reduce

controllability of 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. 97–NM–

41–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:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2589; 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