54376 Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations

it is determined that this final rule does

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)

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 final evaluation has

been prepared for this action and it is

contained in the rules docket. A copy of

it may be obtained from the rules docket

at the location provided under the

caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

97–21–15 British Aerospace Regional

Aircraft (Formerly British Aerospace

Regional Aircraft Limited, Avro

International Aerospace Division; British

Aerospace, PLC; British Aerospace

Commercial Aircraft Limited):

Amendment 39–10168. Docket 97–NM–

05–AD.

Applicability: All Model Avro 146–RJ

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 (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 possible overheating of the

electrical generator feeder cables and

consequent damage, which could lead to

possible fire or loss of essential electrical

systems, accomplish the following:

(a) Prior to the accumulation of 500 flight

cycles after the effective date of this AD,

modify the electrical system in the electrical

equipment bay in accordance with British

Aerospace Service Bulletin SB.24–113–

01532A, dated March 12, 1996, or British

Aerospace Service Bulletin SB.24–113–

01532A, Revision 1, dated June 18, 1996.

(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 to 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.

(d) The modification shall be done in

accordance with British Aerospace Service

Bulletin SB.24–113–01532A, dated March 12,

1996; or British Aerospace Service Bulletin

SB.24–113–01532A, Revision 1, dated June

18, 1996, which contains the following list of

effective pages:

Page No.

Revision level

shown on

page

Date shown

on page

1, 2 ............... 1 ................... June 18,

1996.

3–15 ............. Original ........ March 12,

1996.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia 20171.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in British airworthiness directive 006–03–96,

dated March 12, 1996.

(e) This amendment becomes effective on

November 24, 1997.

Issued in Renton, Washington, on October

10, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27576 Filed 10–17–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–120–AD; Amendment

39–10167; AD 97–21–14]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model C–212 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all CASA Model C–212

series airplanes, that requires an initial

inspection of the restrictor pistons on

the shock absorbers of the left and right

main landing gear (MLG) to determine

the number and condition of threaded

screw pins that are installed;

replacement of any discrepant pin; and

repetitive inspections of certain pistons.

Modification of certain pistons by the

installation of two additional pins

terminates these inspections. This

amendment is prompted by reports

indicating that the threaded screw pin

that holds the restrictor piston on the

slide tube of the shock absorber has

been found to have loosened on some

airplanes. The actions specified by this

AD are intended to prevent the loss of

hydraulic damping in the MLG, due to

failure of the screw pins that hold the

restrictor pistons on the slide tubes of

the shock absorbers, and consequent

structural damage to the airplane.

DATES: Effective November 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. This information

may be examined at the Federal

Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.
Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations 54377

FOR FURTHER INFORMATION CONTACT:

Gregory Dunn, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2799; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all CASA Model C–

212 series airplanes was published in

the Federal Register on March 7, 1997

(62 FR 10488). That action proposed to

require an initial inspection of the

restrictor pistons on the shock absorbers

of the left and right main landing gear

(MLG) to determine the number and

condition of threaded screw pins that

are installed; replacement of any

discrepant pin; and repetitive

inspections of certain pistons. Pistons

on which one pin is installed are

required to be modified by drilling two

new holes and unsealing two previously

drilled holes, and installing two

additional pins. This modification

terminates these repetitive inspection

requirements.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 41 CASA

Model C–212 series airplanes of U.S.

registry will be affected by this AD.

It will take approximately 20 work

hours per airplane to accomplish the

required actions, at an average labor rate

of $60 per work hour. Required parts

will cost approximately $11 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $49,651, or $1,211 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein will

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 final rule does

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)

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 final evaluation has

been prepared for this action and it is

contained in the rules docket. A copy of

it may be obtained from the rules docket

at the location provided under the

caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

97–21–14 Construcciones Aeronauticas, S.A.

(CASA): Amendment 39–10167. Docket

96–NM–120–AD.

Applicability: All Model C–212 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 (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 loss of hydraulic damping

in the main landing gear, due to failure of the

screw pins that hold the restrictor pistons on

the slide tubes of the shock absorbers, and

consequent structural damage to the airplane,

accomplish the following:

(a) Prior to the accumulation of 600 hours

time-in-service after the effective date of this

AD, conduct an inspection of each restrictor

piston to detect the number and condition of

installed threaded screw pins; in accordance

with CASA Service Bulletin SB–212–32–38,

dated June 16, 1994. Prior to further flight,

replace any loose pin, in accordance with the

service bulletin and accomplish the

following, as applicable:

(1) For any piston on which three threaded

screw pins are installed: No further action is

required by this AD for this piston.

(2) For any piston on which one pin is

installed and two holes are sealed with

epoxy: Remove the epoxy, and install two

additional threaded screw pins, in

accordance with the service bulletin.

Thereafter, no further action is required by

this AD for this piston.

(3) For any piston on which one pin is

installed and no other holes exist:

(i) Repeat the inspection required by

paragraph (a) of this AD at intervals not to

exceed 600 hours time-in-service until the

modification required by paragraph (a)(3)(ii)

of this AD is accomplished.

(ii) Prior to the accumulation of 1,800

hours time-in-service after the effective date

of this AD, or within 3 years after the

effective date of this AD, whichever occurs

later, modify this piston in accordance with

the service bulletin. Accomplishment of this

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a)(3)(i) of this AD. Thereafter, no

further action is required by this AD with

regard to that piston.

(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.

(d) The actions shall be done in accordance

with CASA Service Bulletin SB–212–32–38,

dated June 16, 1994. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Construcciones Aeronauticas,

S.A., Getafe, Madrid, Spain. Copies may be
54378 Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 3: The subject of this AD is addressed

in Spanish airworthiness directive 07/94,

dated October 1994.

(e) This amendment becomes effective on

November 24, 1997.

Issued in Renton, Washington, on October

10, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27581 Filed 10–17–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–08–AD; Amendment

39–10166; AD 97–21–13]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model 382 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Lockheed Model 382

series airplanes, that requires revising

the Airplane Flight Manual (AFM) to

prohibit the positioning of the power

levers below the flight idle stop, and to

provide a statement of the consequences

of positioning the power levers below

the flight idle stop. This amendment is

prompted by incidents and accidents

involving airplanes equipped with

turboprop engines in which the

propeller beta was used improperly

during flight. The actions specified by

this AD are intended to prevent loss of

airplane controllability, or engine

overspeed and consequent loss of

engine power caused by the power

levers being positioned below the flight

idle stop while the airplane is in flight.

DATES: Effective November 24, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

24, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Lockheed Aeronautical Systems

Support Company (LASSC), Field

Support Department, Dept. 693, Zone

0755, 2251 Lake Park Drive, Smyrna,

Georgia 30080. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small

Airplane Directorate, Atlanta Aircraft

Certification Office, One Crown Center,

1895 Phoenix Boulevard, Suite 450,

Atlanta, Georgia.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia

30349; telephone (707) 703–6063; fax

(707) 703–6097.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Lockheed Model

382 series airplanes was published in

the Federal Register on March 26, 1997

(62 FR 14369). That action proposed to

require revising the Limitations Section

of the Airplane Flight Manual (AFM) to

prohibit the positioning of the power

levers below the flight idle stop, and to

provide a statement of consequences of

positioning the power levers below the

flight idle stop.

Interim Action

This is considered interim action

until final action is identified, at which

time the FAA may consider further

rulemaking.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 18 Lockheed

Model 382 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 18 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 1 work

hour per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

AD on U.S. operators is estimated to be

$1,080, or $60 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein will

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 final rule does

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)

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 final evaluation has

been prepared for this action and it is

contained in the rules docket. A copy of

it may be obtained from the rules docket

at the location provided under the

caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

97–21–13 Lockheed Aeronautical Systems

Company: Amendment 39–10166.

Docket 97–NM–08–AD.

Applicability: All Model 382 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

modified, altered, or repaired in the area

subject to the requirements of this AD. For