Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations 54369

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:

97–21–05 Raytheon Aircraft Company

(Formerly Beech, Raytheon Corporate

Jets, British Aerospace, Hawker

Siddeley, et al.): Amendment 39–10158.

Docket 96–NM–274–AD.

Applicability: All Model DH.125–400A,

BH.125–400A and –600A, HS.125–600A and

–700A, and BAe 125–800A series airplanes;

and Model Hawker 800 and Hawker 800 XP

series airplanes (including Military Variants

C29A, U125, and U125A airplanes); having

serial numbers 1 through 258294 inclusive;

on which Modification 252036 has been

installed with a high pressure oxygen hose

assembly having part number WKA 34609;

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.

Note 2: Raytheon (Beech) Model DH.125–

400B, BH.125–400B and –600B, HS. 125–

600B and –700B, and BAe 125–800B series

airplanes are similar in design to the

airplanes that are subject to the requirements

of this AD, and therefore, also may be subject

to the unsafe condition addressed by this AD.

However, as of the effective date of this AD,

those models are not type certificated for

operation in the United States. Airworthiness

authorities of countries in which those

models are approved for operation should

consider adopting corrective action,

applicable to these models, that is similar to

the corrective action required by this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent leaks in high pressure oxygen

hose assemblies, which could result in

insufficient oxygen quantity available to the

passengers or crew if the cabin pressure

altitude should rise to a level requiring

emergency oxygen, accomplish the following:

(a) Within 90 days after the effective date

of this AD, perform a one-time inspection to

determine whether any high pressure oxygen

hose assembly having a discrepant part

number WKA 34609 is installed, in

accordance with Raytheon Service Bulletin

SB.35–46, dated September 30, 1996. If no

discrepant part number is detected, no

further action is required by this AD. If any

hose assembly having discrepant part

number WKA 34609 is installed, prior to

further flight, replace the hose assembly with

a hose assembly having part number 58179–

101, in accordance with the service bulletin.

(b) As of the effective date of this AD, no

person shall install a high pressure oxygen

hose having part number WKA 34609 on any

airplane.

(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, Wichita

Aircraft Certification Office (ACO), FAA,

Small 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, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(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) The actions shall be done in accordance

with Raytheon Service Bulletin SB.35–46,

dated September 30, 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

Raytheon Aircraft Company, Manager Service

Engineering, Hawker Customer Support

Department, P.O. Box 85, Wichita, Kansas

67201–0085. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

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

the FAA, Small Airplane Directorate, Wichita

Aircraft Certification Office, 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(f) This amendment becomes effective on

November 24, 1997.

Issued in Renton, Washington, on October

8, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27223 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–64–AD; Amendment

39–10157; AD 97–21–04]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

Equipped With Pratt & Whitney

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A310 and A300–600 series airplanes,

that requires flow checks of the

hydraulic pump drain system to ensure

that the system is not clogged, and

correction of any discrepancy.

Additionally, this amendment requires

replacement of the existing seal of the

accessory gearbox with a new, improved

seal assembly; this replacement

terminates the requirement for repetitive
54370 Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations

flow checks. This amendment is

prompted by reports indicating that

hydraulic fluid had contaminated the

engine oil system as a result of failure

of the seal of the hydraulic pump shaft.

The actions specified by this AD are

intended to prevent clogging of the

hydraulic pump drain system, which

could cause failure of the seal of the

hydraulic pump shaft and subsequent

contamination of the engine accessory

gearbox oil; this condition could result

in an in-flight engine shutdown.

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 Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

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: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2797; 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 Airbus

Model A310 and A300–600 series

airplanes was published in the Federal

Register on February 18, 1997 (62 FR

7184). That action proposed to require

repetitive flow checks of the hydraulic

pump drain system to ensure that the

system is not clogged, and correction of

any discrepancy. Additionally, the

action proposed to require replacement

of the existing seal of the accessory

gearbox with a new, improved seal

assembly. This replacement, when

accomplished, would provide

terminating action for the repetitive

flow checks.

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.

References to Service Bulletin Change

Notices

Since the issuance of the proposal,

Airbus has issued Service Bulletin

Change Notice No. O.A., dated June 17,

1993, for Airbus Service Bulletin A300–

72–6018 (for Model A300–600 series

airplanes equipped with Pratt &

Whitney JT9D–7R4 engines). This

change notice revises the service

bulletin by specifying the latest French

airworthiness directive: 92–231–

136(B)R1, dated March 27, 1993.

Airbus also has issued Service

Bulletin Change Notice No. O.A., dated

June 17, 993, for Airbus Service Bulletin

A300–72–6019 (for Model A300–600

series airplanes equipped with Pratt &

Whitney PW 4000 engines). This change

notice also revises the service bulletin

by referencing the French airworthiness

directive specified previously.

Additionally, the change notice revises

the service bulletin effectivity by

specifying the operators of airplanes

having certain manufacturer’s serial

numbers.

The FAA has revised the final rule to

include references to these service

bulletin change notices.

Conclusion

After careful review of the available

data, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 3 Airbus

Model A300–600 and A310 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 3 work hours per

airplane to accomplish the required onetime inspection, and that the average

labor rate is $60 per work hour. It will

take approximately 10 work hours per

airplane to accomplish the required

terminating modification, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$1,500 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $6,840,

or $2,280 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:

97–21–04 Airbus: Amendment 39–10157.

Docket 96-NM–64-AD.

Applicability: Model A300B4–620, –622,

–622R, and A300C4–620; and Model

A310–221, –222, –322, –324, and –325

series airplanes; equipped with Pratt &

Whitney turbofan engines; on which

Airbus Modification 10399 or 10400 has

not been accomplished; 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
Federal Register / Vol. 62, No. 202 / Monday, October 20, 1997 / Rules and Regulations 54371

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.

To prevent clogging of the hydraulic pump

drain system, which could cause failure of

the seal of the hydraulic pump shaft and

subsequent contamination of the engine

accessory gearbox oil, and could result in an

in-flight engine shutdown, accomplish the

following:

(a) Within 30 days after the effective date

of this AD, perform a flow check of the

hydraulic pump drain system to ensure that

it is not clogged and, prior to further flight,

correct any discrepancies, in accordance with

either paragraph (a)(1) or (a)(2) of this AD, as

applicable. Repeat the flow check, thereafter,

at intervals not to exceed 500 flight hours

until the modification required by paragraph

(b) of this AD is accomplished.

(1) For Model A310 series airplanes:

Perform the flow checks and correct

discrepancies in accordance with Airbus

Service Bulletin A310–72–2022, dated

February 16, 1993 (for airplanes on which

Pratt & Whitney JT9D–7R4D1 and –7R4E1

engines are installed); or Airbus Service

Bulletin A310–72–2023, Revision 1, dated

December 22, 1993 (for airplanes on which

Pratt & Whitney PW4152 and PW4156A

engines are installed); as applicable.

Note 2: Flow checks accomplished prior to

the effective date of this AD in accordance

with the original issuance of Airbus Service

Bulletin A310–72–2023 are considered

acceptable for compliance with the

applicable action specified in this AD.

(2) For Model A300–600 series airplanes:

Perform the flow checks and correct

discrepancies in accordance with Airbus

Service Bulletin A300–72–6018, Revision 1,

dated December 22, 1993, as revised by

Service Bulletin Change Notice No. O.A.,

dated June 17, 1993 (for airplanes on which

Pratt & Whitney JT9D–7R4H1 engines are

installed); or Airbus Service Bulletin A300–

72–6019, Revision 1, dated December 22,

1993, as revised by Service Bulletin Change

Notice No. O.A., dated June 17, 1993 (for

airplanes on which Pratt & Whitney PW4158

engines are installed); as applicable.

Note 3: Flow checks accomplished prior to

the effective date of this AD in accordance

with the original issuance of Airbus Service

Bulletin A300–72–6018 or Airbus Service

Bulletin A300–72–6019 are considered

acceptable for compliance with the

applicable action specified in this AD.

(b) Within 12 months after the effective

date of this AD, replace (on both engines) the

existing seal of the green hydraulic system

gearbox with a new, improved seal assembly

in accordance with either paragraph (b)(1) or

(b)( 2) of this AD, as applicable.

Accomplishment of this replacement

terminates the repetitive flow check

requirements for this AD.

(1) For Model A310 series airplanes:

Accomplish the replacement in accordance

with Airbus Service Bulletin A310–72–2018,

Revision 2, dated December 22, 1993 (for

airplanes on which Pratt & Whitney PW

JT9D–7R4D1 and -7R4E1 engines are

installed); or Airbus Service Bulletin A310–

72–2019, Revision 2, dated December 22,

1993 (for airplanes on which Pratt & Whitney

PW4152 and PW4156A engines are

installed); as applicable.

Note 4: Replacement of the existing seal on

the green hydraulic system gearbox with a

new, improved seal assembly accomplished

prior to the effective date of this AD, in

accordance with the original issuance or

Revision 1 of Airbus Service Bulletin A310–

72–2019, or with the original issuance or

Revision 1 of Airbus Service A310–72–2018,

is considered acceptable for compliance with

the applicable action specified in this AD.

(2) Model A300–600 series airplanes:

Accomplish the replacement in accordance

with Airbus Service Bulletin A300–72–6014,

dated March 15, 1993 (for airplanes on which

Pratt & Whitney PW JT9D–7R4H1 engines are

installed); or Airbus Service Bulletin A300–

72–6015, dated March 15, 1993 (for airplanes

on which Pratt & Whitney PW4158 engines

are installed); as applicable.

(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, 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 5: 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) The actions shall be done in

accordance with the following Airbus

service bulletins, as applicable, which

include the specified effective pages:

Service bulletin No. Page No.

Revision

level

shown on

page

Date shown on page

A310–72–2022, February 16, 1993 ............................................................................................. 1–7 .......... Original .... February 16, 1993.

A310–72–2023, Revision 1, December 22, 1993 ........................................................................ 1, 2, 4–6 .. 1 .............. December 22, 1993

3, 7 .......... Original .... February 16, 1993.

A300–72–6018, Revision 1, December 22, 1993 ........................................................................ 1, 2, 4 ...... 1 .............. December 22, 1993.

3, 5–7 ...... Original .... February 16, 1993.

A300–72–6018, Service Bulletin Change Notice No. O.A., June 17, 1993 ................................ 1 .............. Original .... June 17, 1993.

A300–72–6019, Revision 1, December 22, 1993 ........................................................................ 1–6 .......... 1 .............. December 22, 1993.

7 .............. Original .... February 16, 1993.

A300–72–6019, Service Bulletin Change Notice No. O.A., June 17, 1993 ................................ 1–2 .......... Original .... June 17, 1993.

A310–72–2018, Revision 2, December 22, 1993 ........................................................................ 1–3, 5–7 .. 2 .............. December 22, 1993.

4, 9 .......... Original .... March 15, 1993.

8 .............. 1 .............. August 6, 1993.

A310–72–2019, Revision 2, December 22, 1993 ........................................................................ 1–3, 5–7 .. 2 .............. December 22, 1993.

4, 9 .......... Original .... March 15, 1993.

8 .............. 1 .............. August 6, 1993.

A300–72–6014, March 15, 1993 .................................................................................................. 1–7 .......... Original .... March 15, 1993.

A300–72–6015, March 15, 1993 .................................................................................................. 1–9 .......... Original .... March 15, 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 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.

(f) This amendment becomes effective on

November 24, 1997.
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.