7378 Federal Register / Vol. 62, No. 33 / Wednesday, February 19, 1997 / Proposed Rules

$23,280 for the U.S. fleet. The FAA has

no way of determining how many

owners/operators of these affected

airplanes have accomplished this

action.

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 action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under 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 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 14

CFR part 39 of the Federal Aviation

Regulations as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Airworthiness Directive (AD)

95–20–06, Amendment 39–9384, and by

adding a new AD to read as follows:

Air Tractor Incorporated: Docket No. 96–

CE–47–′AD; Supersedes AD 95–20–06,

Amendment 39–9384.

Applicability: The following airplane

models and serial numbers that have not

accomplished the modification in Snow

Engineering Company Report No. 138,

dated July 29, 1995, which is referenced

in superseded AD 95–20–06, certificated

in any category:

Note 1: The modification in Snow

Engineering Company Report No. 138, dated

July 29, 1995 and AD 95–20–06 required the

airplanes to replace 3/16-inch thick fin front

spar attach fittings with 1/4-inch thick fin

front spar attach fittings.

Models Serial Nos.

AT–301 and

AT–401.

301–0261 through 301–0736,

and 401–0662 through

401–0736 that have been

converted to turbine powerplants and equipped with

the all metal rudder, part

number (P/N) 30456–1.

AT–302 ........ All aircraft equipped with the

all metal rudder, P/N

30456–1.

AT–400 and

AT–400A.

All aircraft equipped with the

all metal rudder, P/N

30456–1.

AT–402 ........ 402–0694 and 402–0695

through 402–0736.

AT–501 ........ 501–0002 through 501–0030

that have been converted to

turbine powerplants and

equipped with the all metal

rudder, P/N 30456–1.

AT–502 ........ 502–0002 through 502–0030.

Note 2: 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 (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 initially within the

next 25 hours time-in-service (TIS) after the

effective date of this AD, unless already

accomplished, and thereafter as indicated in

the body of this AD.

To prevent in-flight vertical fin structural

failure of the front spar attachments and

eventually the rear spar attachment, which,

if not detected and corrected, could result in

loss of directional control and loss of control

of the airplane, accomplish the following:

(a) Inspect the fin front spar attachment

fittings for fatigue cracks in accordance with

the INSTRUCTIONS section of the Snow

Engineering Report (SER) number (No.) 138,

Revised August 7, 1996.

(b) If no cracks are found during the initial

inspection, repeat the inspection required by

paragraph (a) of this AD at intervals not to

exceed 25 hours TIS thereafter in accordance

with the INSTRUCTIONS section of the SER

No. 138, Revised August 7, 1996.

(c) If cracks are found during any

inspections required by this AD, prior to

further flight, modify the fin front spar

attachment fittings in accordance with the

INSTRUCTIONS section of the SER No. 138,

Revised August 7, 1996.

(d) Incorporating the modification

specified in paragraph (c) of this AD is

considered terminating action for the

repetitive inspection requirements of this

AD.

(e) Special flight permits may be issued in

accordance with 14 CFR 21.197 and 21.199

to operate the airplane to a location where

the requirements of this AD can be

accomplished.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Fort Worth Airplane Certification

Office, 2601 Meacham Boulevard, Fort

Worth, Texas 76193–0150. The request shall

be forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Fort Worth Airplane Certification Office.

Alternative methods of compliance approved

in accordance with AD 95–20–06 are

considered approved as alternative methods

of compliance for this AD.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth Aircraft

Certification Office.

(g) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to Air Tractor

Incorporated, P. O. Box 485, Olney, Texas

76374; 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.

(h) This amendment supersedes AD 95–

20–06, Amendment 39–9384. Issued in

Kansas City, Missouri, on February 10, 1997.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–3958 Filed 2–18–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–144–AD]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model CN–235 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 CASA Model CN–235 series

airplanes. This proposal would require

disabling the brake control valve of the
Federal Register / Vol. 62, No. 33 / Wednesday, February 19, 1997 / Proposed Rules 7379

propeller. This proposal also would

require that, prior to restoring propeller

brake operation, the propeller brake

control unit be replaced with a certain

new propeller brake control unit. This

proposal is prompted by reports of

uncommanded activation of the

propeller brake system on in-service

airplanes during flight, due to the

existing design of the brake control

valve. The actions specified by the

proposed AD are intended to prevent inflight uncommanded activation of the

propeller brake system, which could

result in in-flight shutdown of the

engine.

DATES: Comments must be received by

March 31, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96-NM–

144-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

Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. This information

may be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Greg

Dunn, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2799; 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–144–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–144–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direccio ́n General de Aviacio ́n

(DGAC), which is the airworthiness

authority for Spain, recently notified the

FAA that an unsafe condition may exist

on certain CASA Model CN–235, CN–

235–100, and CN–235–200 series

airplanes. The DGAC advises that it has

received reports of uncommanded

activation of the propeller brake system

on CASA Model CN–235 series

airplanes during flight. Investigation

revealed that the existing design of the

brake control valve of the propeller can

cause such a malfunction, including

failure of the low pressure warning

system during ground operation. This

condition, if not corrected, could result

in the in-flight shutdown of an engine.

Explanation of Relevant Service

Information

CASA has issued Communication

COM 235–82, Revision 3, dated January

31, 1995, which describes procedures

for disabling the brake control valve of

the propeller.

CASA also has issued Service Bulletin

SB–235–61–01, dated October 11, 1994,

and Service Bulletin SB–235–61–01M,

Revision 2, dated January 25, 1996 (for

military airplanes). These service

bulletins describe procedures for

replacement of the propeller brake

control unit, having part number (P/N)

HP1410100–5 or HP1410100–7, with a

new propeller brake control unit, having

P/N HP1410100–9. This installation is

to be performed prior to restoring

propeller brake operation.

The DGAC classified these service

bulletins as mandatory and issued

Spanish airworthiness directive 01/94

R1, dated July 1995, in order to assure

the continued airworthiness of these

airplanes in Spain.

FAA’s Conclusions

This airplane model is manufactured

in Spain 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 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,

first, disabling the brake control valve of

the propeller. Then, prior to restoring

propeller brake operation, the proposed

AD would require replacement of

certain propeller brake control units

with certain new propeller brake control

units. The actions would be required to

be accomplished in accordance with the

service bulletins described previously.

Cost Impact

The FAA estimates that 2 CASA

Model CN–235 series airplanes of U.S.

registry would be affected by this

proposed AD.

It would take approximately 3 work

hours per airplane to accomplish the

proposed disabling of the brake control

valve, at an average labor rate of $60 per

work hour. Based on these figures, the

cost impact of this proposed action on

U.S. operators is estimated to be $360,

or $180 per airplane.

It would take approximately 8 work

hours per airplane to accomplish the

proposed replacement, at an average

labor rate of $60 per work hour.

Required parts would be supplied by

the manufacturer at no cost to the

operators. Based on these figures, the

cost impact of this proposed action on

U.S. operators is estimated to be $960,

or $480 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
7380 Federal Register / Vol. 62, No. 33 / Wednesday, February 19, 1997 / Proposed Rules

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:

Construcciones Aeronauticas, S.A., CASA:

Docket 96–NM–144–AD.

Applicability: All Model CN–235, CN–235–

100, and CN–235–200 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 (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 in-flight uncommanded

activation of the propeller brake system,

which could result in in-flight shutdown of

the engine, accomplish the following:

(a) Within 10 days after the effective date

of this AD, disable the brake control valve of

the propeller in accordance with Annex 1 of

CASA Communication COM 235–82,

Revision 3, dated January 31, 1995.

(b) Prior to restoring propeller brake

operation, replace the propeller brake control

unit having part number (P/N) HP1410100–

5 or HP1410100–7, with a new propeller

brake control unit having P/N HP1410100–9,

in accordance with CASA Service Bulletin

SB–235–61–01, dated October 11, 1994; or

CASA Service Bulletin SB–235–61–01M,

Revision 2 (for military airplanes), dated

January 25, 1996; as applicable.

Accomplishment of this replacement

constitutes terminating action for the

requirements of paragraph (a) of 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 February

11, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3966 Filed 2–18–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–155–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A310, and A300–600 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 all

Airbus Model A300, A310, and A300–

600 series airplanes. This proposal

would require performing a ram air

turbine (RAT) extension test; removing

and disassembling the RAT lever

assembly; performing an inspection to

detect corrosion of the RAT lever

assembly, and replacement with a new

assembly, if necessary; and cleaning all

the parts of the RAT control shaft and

its bearing component parts. This

proposal is prompted by reports

indicating that the RAT did not extend

during ground testing, due to corrosion

in the uplock pin/shaft and the needle

bearing of the RAT. The actions

specified by the proposed AD are

intended to detect and correct such

corrosion of the RAT, which could

result in failure of the RAT to deploy

and subsequent loss of emergency

hydraulic power to the flight controls in

the event that power is lost in both

engines.

DATES: Comments must be received by

March 31, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

155–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