11390 Federal Register / Vol. 62, No. 48 / Wednesday, March 12, 1997 / Proposed Rules

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (f) 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 fuselage, restricted operation of the main

landing gear (MLG) free-fall system, and,

consequently, reduced ability to use the MLG

during an emergency, accomplish the

following:

(a) Prior to the accumulation of 12,000 total

landings, or within 6 months after August 23,

1993 (the effective date of AD 93–14–04,

amendment 39–8628), whichever occurs

later, accomplish the requirements of

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

accordance with Airbus Industrie Service

Bulletin A320–53–1024, dated September 23,

1992, or Revision 1, dated March 31, 1994.

As of the effective date of this new AD, only

Revision 1 of this service bulletin shall be

used.

(1) Conduct an eddy current inspection to

detect cracking around the fastener/bolt holes

at the top horizontal flange of the floor beams

and side box-beams, at the two sides of the

pressure floor, and at the vertical integral

stiffener of the side box-beams; and

(2) Conduct a detailed visual inspection to

detect cracking around the fastener/bolt holes

at the fillet radius and riveted area of the top

outboard flange of the side box-beam, and at

the flange-corner radius of the slanted

inboard flange of the side box-beam and

fittings.

(b) If any crack is detected during the

inspections required by paragraph (a) of this

AD, prior to further flight, repair the crack in

accordance with a method approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate.

(c) For airplanes on which the modification

specified in Airbus Service Bulletin A320–

53–1023, dated September 23, 1992, as

amended by Service Bulletin Change Notice

0A, dated January 20, 1993; Revision 1, dated

March 23, 1993; Revision 2, dated October

22, 1993; Revision 3, dated March 18, 1994;

Revision 4, dated September 30, 1994;

Revision 5, dated February 28, 1995; or

Revision 6, dated September 4, 1995; has

been accomplished: Accomplish paragraphs

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

(1) Prior to the accumulation of 1,000

landings after the effective date of this AD,

perform a one-time inspection to verify

proper clearance between the fasteners of the

reinforcement bracket and the bellcrank of

the free-fall extension system of the MLG and

its associated tie rod attachment nut, in

accordance with Airbus All Operators Telex

(AOT) 53–08, Revision 01, dated January 15,

1996.

(i) If the minimum clearance is greater than

3 mm (0.118 inch) and no evidence of

interference is detected, within 60 months

following accomplishment of the inspection

required by paragraph (c)(1) of this AD,

reinstall the reinforcement bracket fasteners

in accordance with Airbus Service Bulletin

A320–53–1023, Revision 7, dated November

3, 1995.

(ii) If the minimum clearance is 3 mm

(0.118 inch) or less, and no evidence of

interference is detected, within 18 months

following accomplishment of the inspection

required by paragraph (c)(1) of this AD,

reinstall the reinforcement bracket fasteners

in accordance with Airbus Service Bulletin

A320–53–1023, Revision 7, dated November

3, 1995.

(iii) If any interference is detected, prior to

further flight, accomplish either paragraph

(c)(1)(iii)(A) or (c)(1)(iii)(B) of this AD.

(A) Reinstall the reinforcement bracket

fasteners in accordance with Airbus Service

Bulletin A320–53–1023, Revision 7, dated

November 3, 1995; or

(B) Rework the bellcrank lever and

fasteners in accordance with Airbus AOT 53–

08, Revision 01, dated January 15, 1996.

Within 60 months following accomplishment

of the rework, reinstall the reinforcement

bracket fasteners in accordance with Airbus

Service Bulletin A320–53–1023, Revision 7,

dated November 3, 1995.

(2) Prior to the accumulation of 24,000

total landings, or 6 months after the effective

date of this AD, whichever occurs later,

modify the pressure floor at section 15 of the

fuselage in accordance with Airbus Service

Bulletin A320–53–1023, Revision 7, dated

November 3, 1995. Accomplishment of the

modification terminates the requirements of

this AD.

(d) For airplanes on which the

modification specified in Airbus Service

Bulletin A320–53–1023, dated September 23,

1992, as amended by Service Bulletin Change

Notice 0A, dated January 20, 1993; Revision

1, dated March 23, 1993; Revision 2, dated

October 22, 1993; Revision 3, dated March

18, 1994; Revision 4, dated September 30,

1994; Revision 5, dated February 28, 1995; or

Revision 6, dated September 4, 1995; has not

been accomplished: Prior to the

accumulation of 18,000 total landings, or

within 6 months after the effective date of

this AD, whichever occurs later, modify the

pressure floor at section 15 of the fuselage in

accordance with Airbus Service Bulletin

A320–53–1023, Revision 7, dated November

3, 1995. Accomplishment of the modification

terminates the requirements of this AD.

(e) Accomplishment of the modification of

the pressure floor at section 15 of the fuselage

in accordance with Airbus Service Bulletin

A320–53–1023, Revision 7, dated November

3, 1995, constitutes terminating action for the

requirements of this AD.

(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,

Standardization Branch, ANM–113.

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.

(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 March 5,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–6085 Filed 3–11–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–219–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

modifying the main landing gear (MLG)

bay areas by installing additional slush

protection covers in those areas. This

proposal is prompted by the

identification of a problem during flight

test analysis, which indicated that slush

can accumulate in the MLG bay areas.

The actions specified by the proposed

AD are intended to prevent the

accumulation of slush in the MLG bay

areas, which could freeze and interfere

with the landing gear or render it

inoperative.

DATES: Comments must be received by

April 21, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

219-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,
Federal Register / Vol. 62, No. 48 / Wednesday, March 12, 1997 / Proposed Rules 11391

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–219–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–219–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 flight test analysis

has revealed that slush can accumulate

in the main landing gear (MLG) bay

areas when the airplane operates on

taxiways and runways with more than

5 mm (0.2 inches) of slush. If this

occurs, the slush could freeze and

interfere with the extension or retraction

of the landing gear and cause it to

become inoperative.

Explanation of Relevant Service

Information

Dornier has issued Service Bulletin

SB–328–30–132, dated October 11,

1995, which describes procedures for

modifying the left and right MLG bay

areas by installing additional slush

protection covers in the MLG bay areas.

This modification to the MLG bay areas

will preclude the accumulation of slush

in those areas, and will allow the

airplane to operate in slush conditions

up to 15 mm (0.6 inch).

The LBA classified this service

bulletin as mandatory and issued

German airworthiness directive 95–412,

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 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 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 registered in the United

States, the proposed AD would require

modifying the left and right MLG bay

areas by installing additional slush

protection covers in those areas. The

actions would be required to be

accomplished in accordance with the

service bulletin described previously.

Cost Impact

The FAA estimates that 40 Dornier

Model 328–100 series airplanes of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 8 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. The cost of

required parts would be negligible.

Based on these figures, the cost impact

of the proposed AD on U.S. operators is

estimated to be $19,200, or $480 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:

Dornier: Docket 96-NM–219-AD.

Applicability: Dornier Model 328–100

series airplanes, serial numbers 3005

through 3063 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
11392 Federal Register / Vol. 62, No. 48 / Wednesday, March 12, 1997 / Proposed Rules

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 the accumulation of slush in

the main landing gear (MLG) bay areas that

could freeze and interfere with the landing

gear and result in it becoming inoperative,

accomplish the following:

(a) Within 90 days after the effective date

of this AD, modify the MLG bay areas by

installing additional slush protection covers

in those areas in accordance with Dornier

Service Bulletin SB–328–30–132, dated

October 11, 1995.

(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,

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.

(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.

Issued in Renton, Washington, on March 5,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–6084 Filed 3–11–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–177–AD]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 340B and 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 340B and

Model SAAB 2000 series airplanes. This

proposal would require a one-time

inspection to determine if certain

switches are installed on the fire handle

panel of the fire handle assembly; and

replacement of the fire handle panel

with a new fire handle panel, if

necessary. This proposal is prompted by

a report indicating that, during

manufacture, a batch of defective

switches were installed on certain fire

handle panels on these airplanes. The

actions specified by the proposed AD

are intended to ensure the proper

switches are installed in the fire handle

assembly. A defective switch in the fire

handle assembly could prematurely fail

and, consequently, prevent the proper

operation of the engine fire protection

system in the event of a fire.

DATES: Comments must be received by

April 21, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

177–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–177–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–177–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfartsverket (LFV), which is

the airworthiness authority for Sweden,

recently notified the FAA that an unsafe

condition may exist on certain Saab

Model SAAB 340B and Model SAAB

2000 series airplanes. The LFV advises

it has received a report indicating that,

during manufacture, a batch of defective

switches was installed in the fire handle

assemblies on Model SAAB 340 series

airplanes and Model SAAB 2000 series

airplanes. A defective switch in the fire

handle assembly could prematurely fail

and, consequently, prevent the proper

operation of the engine fire protection

system in the event of a fire.

Explanation of Relevant Service

Information

Saab has issued Service Bulletin 340–

26–016, dated November 9, 1995 (for

Model SAAB 340 series airplanes), and

Service Bulletin SAAB 2000–26–006,

dated November 9, 1995 (for Model

SAAB 2000 series airplanes). These

service bulletins describe procedures for

performing a one-time inspection to

determine the color of the switches

installed on the fire handle panel of the

fire handle assembly. For cases where a

blue switch is installed, the service

bulletin also describes procedures for

performing a one-time inspection to

determine the serial number of the fire

handle assembly; and replacement of

the fire handle panel with a new fire

handle panel, if necessary. The LFV

classified these service bulletins as