49430 Federal Register / Vol. 62, No. 183 / Monday, September 22, 1997 / Rules and Regulations

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:

97–20–03 de Havilland: Amendment 39–

10141. Docket 97–NM–36–AD.

Applicability: All Model DHC–7 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

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 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, accomplish the

following:

(a) Within 30 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) to include the following statements.

This action may be accomplished by

inserting a copy of this AD into the AFM.

‘‘Positioning of power levers below the

flight idle stop while the airplane is in flight

is prohibited. Such positioning may lead to

loss of airplane control or may result in an

overspeed condition and consequent loss of

engine power.’’

(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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Maintenance Operations

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(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) This amendment becomes effective on

October 27, 1997.

Issued in Renton, Washington, on

September 16, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–25054 Filed 9–19–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–07–AD; Amendment

39–10140; AD 97–20–02]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–188A and L–188C Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to all Lockheed Model L–

188A and L–188C series airplanes. This

amendment requires revising the

Airplane Flight Manual (AFM) to

prohibit the positioning of the power

levers below the flight idle stop during

flight, and to provide a statement of the

consequences of positioning the power

levers below flight idle stop. This

amendment is prompted by incidents

and accidents involving airplanes

equipped with turboprop engines where

the propeller ground 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 October 27, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of October 27,

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. 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, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia;

or at the Office of the Federal Register,

800 North Capitol Street, NW., suite

700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

1895 Phoenix Boulevard, Suite 450,

Atlanta,-Georgia 30349; telephone (770)

703–7367; fax (770) 703–7348.

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

L–188A and L–188C series airplanes

was published in the Federal Register

on April 22, 1997 (62 FR 19526). 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 during flight, and to

provide a statement of the consequences

of positioning the power levers below

flight idle stop.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule, but remarks that, if an

inherent design problem exists on the

affected airplanes to allow flightcrews to

select the power levers below the flight

idle stop while in flight, the FAA

should consider the addition of a

mechanical means to preclude such

selection. The FAA acknowledges the

commenter’s concern, and may consider

additional rulemaking to address that

concern in the future on certain

airplanes. However, until such final

action is identified, the FAA considers

it appropriate to proceed with issuance

of this final rule. No change to the final

rule is required.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 75 Lockheed

Model L–188A and L–188C series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

32 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
Federal Register / Vol. 62, No. 183 / Monday, September 22, 1997 / Rules and Regulations 49431

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 $1,920, 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 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:

97–20–02 Lockheed: Amendment 39–10140.

Docket 97-NM–07-AD.

Applicability: All Model L–188A and L–

188C 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

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 loss of airplane controllability

or engine overspeed with consequent loss of

engine power caused by the power levers

being positioned below the flight idle stop

while the airplane is in flight, accomplish the

following:

(a) Within 30 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) to include the following statements.

This action may be accomplished by

inserting either a copy of this AD into the

AFM or the revision to the Limitations

Section of the FAA-approved Electra 188A or

188C AFM, both dated October 17, 1996, as

applicable.

Positioning of power levers below the

flight idle stop while the airplane is in flight

is prohibited. Such positioning may lead to

loss of airplane control or may result in an

overspeed condition and consequent loss of

engine power.

(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, Atlanta

Aircraft Certification Office (ACO), FAA,

Small Airplane Directorate. Operators shall

submit their requests through an appropriate

FAA Principal Operations Inspector, who

may add comments and then send it to the

Manager, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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 AFM revision shall be done in

accordance with Electra 188A Airplane

Flight Manual, dated October 17, 1996; or

Electra 188C Airplane Flight Manual, dated

October 17, 1996; as applicable. 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

Lockheed Aeronautical Systems Support

Company (LASSC), Field Support

Department, Dept. 693, Zone 0755, 2251 Lake

Park Drive, Smyrna, Georgia. Copies may be

inspected at the Federal Aviation

Administration (FAA), Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small Airplane

Directorate, Atlanta Aircraft Certification

Office, Campus Building, 1701 Columbia

Avenue, Suite 2–160, College Park, Georgia;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(e) This amendment becomes effective on

October 27, 1997.

Issued in Renton, Washington, on

September 16, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–25055 Filed 9–19–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–237–AD; Amendment

39–10139; AD 97–20–01]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Boeing Model 747

series airplanes. This action requires

repetitive inspections to detect cracks,

corrosion, or damage of the lower spar

fitting body and lug, and corrective

actions, if necessary. This AD also

provides for optional terminating action

for the repetitive inspection

requirements. This amendment is

prompted by reports that fatigue

cracking was found in the lower spar

fitting lug on the number 3 pylon and

in the lower spar fitting body. The

actions specified in this AD are

intended to detect and correct such

fatigue cracking, which could result in

failure of the strut and separation of the

engine from the airplane.

DATES: Effective October 7, 1997.

The incorporation by reference of

Boeing Service Bulletin 747–54–2062,