16474 Federal Register / Vol. 62, No. 66 / Monday, April 7, 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:

97–07–14 Airbus Industrie: Amendment

39–9988. Docket 96–NM–105–AD.

Applicability: Model A320 series airplanes

as listed in Airbus Service Bulletin A320–57–

1013, Revision 1, dated September 29, 1992;

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 fatigue cracking in the rib

flange of the front spar side of the wing

center section, and consequent reduced

structural integrity of fuselage frame 36 and

the wing center section, accomplish the

following:

(a) Prior to the accumulation of 16,000 total

landings, or within 3 months after the

effective date of this AD, whichever occurs

later, modify the rib flange on the front spar

of the wing center section by installing shims

and new fasteners to reinforce pressure floor

fittings, in accordance with Airbus Service

Bulletin A320–57–1013, Revision 1, dated

September 29, 1992.

Note 2: Modification of the rib flange

accomplished prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A320–57–1013, dated April 12,

1989, is considered acceptable for

compliance with the modification required

by this AD.

(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 3: 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 §§ 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 Airbus Service Bulletin

A320–57–1013, Revision 1, dated September

29, 1992, which contains the following list of

effective pages:

Page No. Revision level shown on page Date shown on page

1–3 ........................................................................................ 1 ............................................................................................ September 29, 1992.

4–11 ...................................................................................... Original ................................................................................. April 12, 1989.

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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, 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.

(e) This amendment becomes effective on

May 12, 1997.

Issued in Renton, Washington, on March

27, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8422 Filed 4–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–127–AD; Amendment

39–9987; AD 97–07–13]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model CN–235 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain CASA Model CN–

235 series airplanes, that requires

replacement of the center wing

attachment rods with new rods. This

amendment is prompted by a report

from the manufacturer indicating that

these rods failed during a full-scale

fatigue test. The actions specified by

this AD are intended to prevent fatigue

failure of these rods, which

consequently could reduce the

structural integrity of the wing-tofuselage attachment.

DATES: Effective May 12, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 12,

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.

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: 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 CASA

Model CN–235 series airplanes was

published in the Federal Register on

January 27, 1997 (62 FR 3834). That

action proposed to require replacement

of the center wing attachment rods with

new rods.
Federal Register / Vol. 62, No. 66 / Monday, April 7, 1997 / Rules and Regulations 16475

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 1 CASA

Model CN–235 series airplane of U.S.

registry will be affected by this AD, that

it will take approximately 12 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$1,485 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $2,205

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:

97–07–13 Construcciones Aeronauticas,

S.A. (CASA): Amendment 39–9987.

Docket 96-NM–127-AD.

Applicability: Model CN–235 series

airplanes; as listed in CASA Service Bulletin

SB–235–53–21M, Revision 1, dated

November 21, 1994 (military airplanes), and

CASA Service Bulletin SB–235–53–21,

Revision 3, dated November 30, 1994 (nonmilitary 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 fatigue from causing the center

wing attachment rods to fail, which

consequently could reduce the structural

integrity of the wing-to-fuselage attachment,

accomplish the following:

(a) Prior to the accumulation of 16,000 total

landings, replace center wing attachment

rods having CASA part number (P/N) 35–

22058–0003 or 35–22067–0001 with new

rods having CASA P/N 35–22067–0003, in

accordance with CASA Service Bulletin SB–

235–53–21M, Revision 1, dated November

21, 1994 (for military airplanes); or CASA

Service Bulletin SB–235–53–21, Revision 3,

dated November 30, 1994 (for non-military

airplanes); as applicable.

(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 replacement shall be done in

accordance with CASA Service Bulletin SB–

235–53–21M, Revision 1, dated November

21, 1994; or CASA Service Bulletin SB–235–

53–21, Revision 3, dated November 30, 1994;

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 Construcciones Aeronauticas,

S.A., Getafe, Madrid, Spain. 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.

(e) This amendment becomes effective on

May 12, 1997.

Issued in Renton, Washington, on March

27, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8423 Filed 4–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–ANE–56; Amendment 39–

9978; AD 97–07–04]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

plc RB.211–524 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Rolls-Royce plc RB.211–

524 series turbofan engines, that

requires initial and repetitive borescope

inspections of the head section and

meterpanel assembly of the combustion

liner, and replacement, if necessary,

with serviceable parts. In addition, this

AD allows an optional installation of a

front combustion liner with a

strengthened head section as a

terminating action to the inspection