Federal Register / Vol. 63, No. 82 /Wednesday, April 29, 1998 /Rules and Regulations 23381

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

June 3, 1998.

Issued in Renton, Washington, on April 21,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–11071 Filed 4–28–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–303–AD; Amendment

39–10503; AD 98–09–22]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model ATR42–200, –300, and –320

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Aerospatiale Model

ATR42–200, –300, and –320 series

airplanes, that requires an inspection to

detect fatigue cracking of the

windshield frame structure, and

modification of the windshield frame

structure. This amendment is prompted

by the issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent reduced structural

integrity of the airplane resulting from

fatigue cracking of the windshield frame

structure.

DATES: Effective June 3, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 3,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Aerospatiale, 316 Route de

Bayonne, 31060 Toulouse, Cedex 03,

France. 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.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

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 certain Aerospatiale

Model ATR42–200, –300, and –320

series airplanes was published in the

Federal Register on February 19, 1998

(63 FR 8373). That action proposed to

require an inspection to detect fatigue

cracking of the windshield frame

structure, and modification of the

windshield frame structure.

Comments

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.

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

The FAA estimates that 106 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 19 work

hours per airplane to accomplish the

required inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

inspection required by this AD on U.S.

operators is estimated to be $120,840, or

$1,140 per airplane.

It will take approximately 191 work

hours per airplane to accomplish the

required modification specified in

Aerospatiale Service Bulletin ATR42–

53–0093, Revision 1, dated February 19,

1996, at an average labor rate of $60 per

work hour. Required parts will be

provided by the manufacturer at no cost

to the operators. Based on these figures,

the cost impact of this modification on

U.S. operators is estimated to be $11,460

per airplane.

It will take approximately 281 work

hours per airplane to accomplish the

required modification specified in

Aerospatiale Service Bulletin ATR42–

53–0094, Revision 2, dated February 19,

1996, at an average labor rate of $60 per

work hour. Required parts will be

provided by the manufacturer at no cost

to the operators. Based on these figures,

the cost impact of this modification on

U.S. operators is estimated to be $16,860

per airplane.

The cost impact figures discussed

above are 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:

98–09–22 Aerospatiale: Amendment 39–

10503. Docket 97–NM–303–AD.

Applicability: Model ATR42–200, –300,

and –320 series airplanes, on which
23382 Federal Register / Vol. 63, No. 82 /Wednesday, April 29, 1998 /Rules and Regulations

Aerospatiale Modification 01392 has not

been installed, 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 reduced structural integrity of

the airplane resulting from fatigue cracking of

the windshield frame structure, accomplish

the following:

(a) Prior to the accumulation of 24,000 total

flight cycles, or within 60 days after the

effective date of this AD, whichever occurs

later: Inspect to detect cracking of the

windshield frame structure in accordance

with Operation Description (B—Inspection)

of the Accomplishment Instructions of

Aerospatiale Service Bulletin ATR42–53–

0093, Revision 1, or ATR42–53–0094,

Revision 2, both dated February 19, 1996.

(1) If the inspection reveals no crack, or

reveals cracking that does not exceed the

specifications listed in Figure 6, Sheet 1, of

Service Bulletin ATR42–53–0093, Revision 1,

dated February 19, 1996: Prior to further

flight, modify the windshield frame structure

in accordance with either service bulletin.

(2) If the inspection reveals any crack that

exceeds the specifications in Figure 6, Sheet

1, of Service Bulletin ATR42–53–0093,

Revision 1, dated February 19, 1996, but does

not exceed the cut-out areas specified in

Figure 7, Sheet 1, of Service Bulletin ATR42–

53–0094, Revision 2, dated February 19,

1996: Prior to further flight, modify the

windshield frame structure in accordance

with Service Bulletin 42–53–0094, Revision

2, dated February 19, 1996.

(3) If the inspection reveals any crack that

exceeds the cut-out areas specified in Figure

7, Sheet 1, of Service Bulletin ATR42–53–

0094, Revision 2, dated February 19, 1996:

Prior to further flight, modify the windshield

frame structure in accordance with a method

approved by the Manager, International

Branch, ANM–116, FAA, Transport Airplane

Directorate.

Note 2: Accomplishment of the

modifications specified in ATR Service

Bulletin ATR42–53–0093, Revision 1, or

ATR42–53–0094, Revision 2, both dated

February 19, 1996, is not equivalent to

accomplishment of Aerospatiale

Modification 01392. Therefore the ATR42

Time Limits Document inspection items with

‘‘PRE MOD 1392’’ effectivity are still

applicable for airplanes modified by either of

the previously described service bulletins.

(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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 the following Aerospatiale Service

Bulletins, which contain the specified

effective pages:

Service bulletin referenced and date Page number shown on page

Revision

level

shown on

page

Date shown on page

ATR42–53–0093, Revision 1, February 19, 1996 ..... 1–4, 13 ....................................................................... 1 .............. February 19, 1996.

5–12, 14–41 ............................................................... Original .... April 26, 1995.

ATR42–53–0094, Revision 2, February 19, 1996 ..... 1, 2, 8, 9, 16, 18, 39, 40, 48, 53, 54 ......................... 2 .............. February 19, 1996.

3, 4, 7, 10–15, 17, 19–24, 26, 27, 29–32, 34–38,

47, 55, 56.

1 .............. May 29, 1995.

5, 6, 25, 28, 33, 41–46, 49–52 .................................. Original .... April 24, 1995

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 Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, France. 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 4: The subject of this AD is addressed

in French airworthiness directive 95–126–

061(B), dated June 21, 1995.

(e) This amendment becomes effective on

June 3, 1998.

Issued in Renton, Washington, on April 21,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–11068 Filed 4–28–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–59–AD; Amendment

39–10504; AD 98–09–23]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011 Series Airplanes

Equipped With Rolls Royce Model

RB211–22B Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Lockheed Model

L–1011 series airplanes, that currently

requires various modifications and

corrective actions to prevent a potential

fire hazard caused by heat damage to the

flex fuel feed line from an undetected

gearbox fire. In lieu of the various

modifications and corrective actions,

that AD also provides for an optional

terminating action (i.e., installation of a

vent air tube in the gear compartment

and thickened gearbox housings) for

another existing AD. For airplanes on

which that optional terminating action

has been accomplished, this amendment

requires accomplishment of the various

modifications and corrective actions.

This amendment is prompted by a

report indicating that, due to bearing

failure, an in-flight fire occurred on an

airplane on which a thickened gearbox

housing was installed. The actions

specified by this AD are intended to

detect and correct bearing failure, which

could lead to a fire in the gearbox.

DATES: Effective June 3, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 3,

1998.