54372 Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations

Issued in Renton, Washington, on October

8, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27221 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–126–AD; Amendment

39–10165; AD 97–21–12]

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 a onetime inspection to detect fatigue

cracking in the area of the center wingto-fuselage attachment fitting, and

repair, if necessary. This amendment

also would require installation of a

reinforcing plate in the attachment area

of that fitting. This amendment is

prompted by a report from the

manufacturer indicating that, during

full-scale fatigue testing, fatigue cracks

were detected in this area. The actions

specified by this AD are intended to

prevent fatigue cracking, which

consequently could reduce the

structural integrity of this area.

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.

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

(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 certain CASA

Model CN–235 series airplanes was

published in the Federal Register on

March 3, 1997 (62 FR 9388). That action

proposed to require a one-time

inspection to detect fatigue cracking in

the area where the center wing-tofuselage attachment fitting is located,

and repair, if necessary. In addition, that

action proposed the installation of a

reinforcing plate in the attachment area

of the center wing-to-fuselage

attachment fitting, after inspection and

any necessary repairs have been

accomplished.

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 2 CASA

Model CN–235 series airplanes of U.S.

registry will be affected by this AD.

It will take approximately 25 work

hours per airplane to accomplish the

required actions, at an average labor rate

of $60 per work hour. Required parts

will cost approximately $645 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $4,290, or $2,145 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:

97–21–12 Construcciones Aeronauticas, S.A.

CASA: Amendment 39–10165.Docket

96–NM–126–AD.

Applicability: Model CN–235 series

airplanes, as listed in CASA Service Bulletin

SB–235–53–20, Revision 2, dated June 9,

1994 (for non-military airplanes); and Service

Bulletin SB–235–53–20M, Revision 1, dated

November 27, 1995 (for military 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.
Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations 54373

To prevent fatigue cracking in the area of

the center wing-to-fuselage attachment

fitting, which consequently could reduce the

structural integrity of this area, accomplish

the following:

(a) For non-military airplanes: Prior to the

accumulation of 17,000 total landings,

accomplish the actions specified in

paragraphs (a)(1), (a)(2), and (a)(3) of this AD:

(1) Remove all parts and other items in the

area of the center wing-to-fuselage

attachment fitting, in accordance with

Paragraph 2.B. (‘‘Removal’’) of the

Accomplishment Instructions of CASA

Service Bulletin SB–235–53–20, Revision 2,

dated June 9, 1994.

(2) After all parts and other items have

been removed in accordance with paragraph

(a)(1) of this AD, conduct a visual inspection,

using a magnifier of at least 10x magnitude,

to detect fatigue cracking in this area (ref:

Figure 1, Sheet 1, of the service bulletin). If

any cracking is detected, prior to further

flight and prior to installing the reinforcing

plate in accordance with paragraph (a)(3) of

this AD, repair in a manner approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate.

(3) Install a reinforcing plate having CASA

part number (P/N) 35–25010–0101 in the

attachment area of the center wing-tofuselage attachment fitting, in accordance

with the service bulletin.

(b) For military airplanes: Prior to the

accumulation of 15,000 total landings,

accomplish the actions specified in

paragraphs (b)(1), (b)(2), and (b)(3) of this AD:

(1) Remove all parts and other items in the

area of the center wing-to-fuselage

attachment fitting, in accordance with

Paragraph 2.B. (‘‘Removal’’) of the

Accomplishment Instructions of CASA

Service Bulletin SB–235–53–20M, Revision

1, dated November 27, 1995.

(2) After all parts and other items have

been removed in accordance with paragraph

(b)(1) of this AD, conduct a visual inspection,

using a magnifier of at least 10x magnitude,

to detect fatigue cracking in this area (ref:

Figure 1, Sheet 1, of the service bulletin). If

any cracking is detected, prior to further

flight and prior to installing the reinforcing

plate in accordance with paragraph (b)(3) of

this AD, repair in a manner approved by the

Manager, Standardization Branch, ANM–113,

FAA.

(3) Install a reinforcing plate having CASA

part number (P/N) 35–25010–0101 in the

attachment area of the center wing-tofuselage attachment fitting, in accordance

with the service bulletin.

(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.

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.

(e) Certain actions shall be done in

accordance with CASA Service Bulletin SB–

235–53–20M, Revision 1, dated November

27, 1995 (for military airplanes); and CASA

Service Bulletin SB–235–53–20, Revision 2,

dated June 9, 1994 (for non-military

airplanes), which contains the following list

of effective pages:

Page No.

Revision

level shown

on page

Date shown on

page

1 ................ 1 ................ April 13, 1994.

2 ................ 2 ................ June 9, 1994.

3–11 .......... Original ...... July 29, 1993.

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.

Note 3: The subject of this AD is addressed

in Spanish airworthiness directive 03/94,

dated August 1994.

(f) This amendment becomes effective on

November 24, 1997.

Issued in Renton, Washington, on October

9, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27354 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–ANE–18–AD; Amendment

39–10161; AD 97–21–08]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CT58 Series

Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to General Electric Company

CT58 series turboshaft engines, that

requires removal from service of certain

stage 1 and 2 forward cooling plates,

and stage 2 aft cooling plates, and

replacement with serviceable parts. This

amendment is prompted by reports of

certain cooling plates forged with

contaminated alloy that could reduce

the lives of the parts. The actions

specified by this AD are intended to

prevent cooling plate fracture, which

could result in a contained engine

failure, and an inflight engine

shutdown.

DATES: Effective December 19, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

19, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from General Electric Company (GE),

1000 Western Ave., Lynn, MA 01909;

telephone (781) 594–9894, fax (781)

594–1527. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Diane Cook, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7133, fax

(781) 238–7199.

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 General Electric

Company (GE) Models CT58–110–1,

–110–2, –140–1, –140–2, and T58–GE–

3/–5/–8F/–10/–100 turboshaft engines

was published in the Federal Register

on June 9, 1997 (62 FR 31370). That

action proposed to require removal from

service of certain stage 1 and 2 forward

cooling plates, and stage 2 aft cooling

plates, and replacement with

serviceable parts.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public.

Since publication of the proposed

rule, GE Aircraft Engines has issued GE

Aircraft Engines CT58 Service Bulletin

(SB) No. 72–188 (CEB–293), Revision 1,

dated July 15, 1997. This final rule

references this current revision.

The FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously.