66500 Federal Register / Vol. 62, No. 244 / Friday, December 19, 1997 / Rules and Regulations

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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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 a new airworthiness directive

(AD) to read as follows:

97–26–15 Raytheon Aircraft Company:

Amendment 39–10258; Docket No. 97–

CE–13–AD.

Applicability: The following model and

serial number airplanes, certificated in any

category, that are equipped with at least one

part number (P/N) 114–380041–11 (or FAAapproved equivalent part number) main

landing gear actuator:

Model Serial numbers

1900 ......... UA–2 and UA–3.

1900C ...... UB–1 through UB–74, and UC–1

through UC–174.

1900C (C–

12J).

UD–1 through UD–6.

1900D ...... UE–1 through UE–249 and UE–

252.

Note 1: The airplanes affected by this AD

could have main landing gear actuators

installed that have Parts Manufacturer

Approval (PMA). For those airplanes having

PMA parts that are equivalent (PMA by

equivalency) to those referenced in this AD,

the phrase ‘‘or FAA-approved equivalent part

number’’ means that this AD applies to

airplanes with PMA by equivalency main

landing gear actuators installed.

Note 2: 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 (e) of this AD.

The request should include an assessment of

the effect of the installation, 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 in the

body of this AD, unless already

accomplished.

To prevent actuator rod end failure caused

by excessive friction in the rod end bearing,

which could result in the inability to lower

the main landing gear or result in landing

gear collapse during landing, accomplish the

following:

(a) Upon accumulating 1,200 hours timein-service (TIS) on each P/N 114–380041–11

(or FAA-approved equivalent part number)

main landing gear actuator or within the next

100 hours TIS after the effective date of this

AD, whichever occurs later, lubricate the

actuator rod ends in accordance with

Raytheon Safety Communique ́ 1900–128,

dated October 25, 1996.

(1) Installation of P/N M81935/1–8K (or

FAA-approved equivalent part number) main

landing gear actuator rod ends constitutes

terminating action to the lubricating

requirements of paragraph (a) of this AD.

(2) Installing the P/N M81935/1–8K (or

FAA-approved equivalent part number) main

landing gear actuator rod ends may be

accomplished at any time prior to the next

600 hours TIS, at which time they must be

installed (see paragraph (b) of this AD).

(b) Within the next 600 hours TIS after the

effective date of this AD, install Teflon-lined

main landing gear actuator rod ends, P/N

M81935/1–8K (or FAA-approved equivalent

part number), in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Raytheon Mandatory Service

Bulletin No. 2730, Issued: November, 1996.

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

person may install a P/N 114–380041–11 (or

FAA-approved equivalent part number) main

landing gear actuator without replacing the

rod ends with P/N M81935/1–8K (or FAAapproved equivalent part number). Installing

these Teflon-lined rod ends re-identifies the

main landing gear actuator as P/N 114–

380041–13.

(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) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas 67209. The request shall be

forwarded through an appropriate FAA

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.

(f) The lubrication required by this AD

shall be done in accordance with Raytheon

Safety Communique ́ 1900–128, dated

October 25, 1996. The installation required

by this AD shall be done in accordance with

Raytheon Mandatory Service Bulletin No.

2730, Issued: November, 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 the

Raytheon Aircraft Company, P.O. Box 85,

Wichita, Kansas 67201–0085. Copies may be

inspected at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri, or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(g) This amendment (39–10258) becomes

effective on January 25, 1998.

Issued in Kansas City, Missouri, on

December 10, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–32994 Filed 12–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–140–AD; Amendment

39–10254; AD 97–26–11]

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 corrosion of the rear spars of the

wings, and corrective actions, if

necessary. This amendment is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are
Federal Register / Vol. 62, No. 244 / Friday, December 19, 1997 / Rules and Regulations 66501

intended to detect and correct possible

corrosion on the rear spars of the wings,

which could result in reduced structural

integrity of the wings.

DATES: Effective January 23, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 23,

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:

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, –320 series

airplanes was published in the Federal

Register on October 01, 1997 (62 FR

51388). That action proposed to require

an inspection to detect corrosion of the

rear spars of the wings, and corrective

actions, if necessary.

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.

Request to Withdraw the Proposal

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC) has no technical

objection to the proposal, but requests

that the FAA withdraw it because

French airworthiness directive 95–127–

062(B) was issued against a target set of

airplanes, and was intended to evaluate

and quantify the problems with

corrosion in the area of the wing spars.

The results of the inspection enabled

the manufacturer to define long term

actions and revise the airplane

maintenance program (known as the

Maintenance Review Board or MRB), to

include the necessary inspections and

corrective actions. The commenter

further states that the revised MRB has

been implemented by U.S. operators,

and that an AD mandating these same

actions is not required.

The FAA does not concur with the

commenter’s request to withdraw the

proposal. The MRB document

referenced by the commenter is not

mandatory for U.S. operators. Therefore,

the issuance of this AD is the only

means available to the FAA to require

changes in the maintenance of the

airplane which are related to an unsafe

condition. The ‘‘Compliance’’ provision

of this AD states that compliance is

required as indicated, ‘‘unless

accomplished previously.’’ Therefore, if

an operator has adopted and complied

with MRB provisions that describe the

inspection required by this AD, it may

take credit for prior accomplishment of

those actions.

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 16 Model

ATR42–200, –300, and –320 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 24 work hours per

airplane to accomplish the required

actions, and 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

$23,040, or $1,440 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:

97–26–11 Aerospatiale: Amendment 39–

10254. Docket 95–NM–140–AD.

Applicability: Model ATR42–200, -300,

and -320 series airplanes, as listed in

Aerospatiale Service Bulletin ATR42–57–

0044, dated May 30, 1995, or Revision 1,

dated June 28, 1995; 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 detect and correct corrosion on the rear

spars of the wings, which could result in

reduced structural integrity of the wing,

accomplish the following:

(a) Within 60 days after the effective date

of this AD, perform a one-time detailed

visual inspection to detect corrosion of the

rear spars of the wings, in accordance with

Aerospatiale Service Bulletin ATR42–57–

0044, dated May 30, 1995, or Revision 1,

dated June 28, 1995.
66502 Federal Register / Vol. 62, No. 244 / Friday, December 19, 1997 / Rules and Regulations

(1) If no corrosion is detected, prior to

further flight, apply a protective compound

to the areas specified in the service bulletin,

in accordance with the service bulletin.

(2) If any corrosion is detected, prior to

further flight, repair it in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(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 2: 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 Aerospatiale Service Bulletin ATR42–

57–0044, dated May 30, 1995; or Aerospatiale

Service Bulletin ATR42–57–0044, Revision 1,

dated June 28, 1995; which contain the

specified effective pages.

Service bulletin referenced and date Page No. Revision level

shown on page

Date shown on

page

ATR42–57–0044, May 30, 1995 ....................................................................... 1–17 ................................... Original ............. May 30, 1995.

ATR42–57–0044, Revision 1, June 28, 1995 ................................................... 1, 4, 6–8, 15–16 ................. 1 ....................... June 28, 1995.

2, 3, 5, 9–14, 17 ................. Original ............. May 30, 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 3: The subject of this AD is addressed

in French airworthiness directive 95–127–

063(B), dated August 2, 1995.

(e) This amendment becomes effective on

January 23, 1998.

Issued in Renton, Washington, on

December 11, 1997.

Gilbert L. Thompson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–32999 Filed 12–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93–ANE–08; Amendment 39–

10260; AD 97–26–17]

RIN 2120–AA64

Airworthiness Directives; Teledyne

Continental Motors IO–360, TSIO–360,

LTSIO–360, IO–520, LIO–520, TSIO–

520, LTSIO–520 Series, and RollsRoyce plc IO–360 and TSIO–360 Series

Reciprocating Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Teledyne

Continental Motors (TCM) IO–520 and

TSIO–520 series reciprocating engines,

that currently requires ultrasonic

inspection for subsurface fatigue cracks

in crankshafts installed in TCM IO–520

and TSIO–520 series engines and

replacement of the crankshaft if a crack

is found. This amendment adds a

requirement to remove crankshafts

manufactured using the airmelt process

and replace them with crankshafts

manufactured using the vacuum arc

remelt (VAR) process, incorporates new

ultrasonic inspection criteria in the AD,

adds engine series TCM IO–360, TSIO–

360, LTSIO–360, IO–520, LIO–520,

TSIO–520, LTSIO–520 and Rolls-Royce,

plc IO–360 and TSIO–360 to the

applicability, and revises the economic

impact analysis. This amendment is

prompted by reports of crankshaft

failures due to subsurface fatigue

cracking on engines that had been

inspected in accordance with the

current AD. The actions specified by

this AD are intended to prevent

crankshaft failure and subsequent

engine failure.

DATES: Effective January 23, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 23,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Teledyne Continental Motors, P.O.

Box 90, Mobile, AL 36601; telephone

(334) 438–3411. 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 01803–5299; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jerry

Robinette, Aerospace Engineer, Atlanta

Aircraft Certification Office, FAA, Small

Airplane Directorate, Campus Building,

1701 Columbia Ave., Suite 2–160,

College Park, GA 30337–2748;

telephone (404) 305–7371, fax (404)

305–7348.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

add an airworthiness directive (AD),

applicable to certain Teledyne

Continental Motors (TCM) IO–360,

TSIO–360, LTSIO–360, IO–520 and

TSIO–520 series reciprocating engines

was published as a supplemental notice

of proposed rulemaking (SNPRM) in the

Federal Register on August 24, 1995 (60

FR 43995). That proposal would have

superseded AD 87–23–08, Amendment

39–5735 (52 FR 41937, October 30,

1987), which currently requires

ultrasonic inspection of TCM IO–520

and TSIO–520 series engines for subsurface fatigue cracks in the crankshaft

and replacement of the crankshaft, if a

crack is found. The proposed AD would

have retained the ultrasonic inspection,

but would have required the removal of

crankshafts manufactured using the

airmelt process and required

replacement with crankshafts that were

manufactured using the vacuum arc

remelt (VAR) process. The proposed AD

would have also expanded the affected

population of engines to add the TCM

IO–360, TSIO–360 and LTSIO–360

series engines to the IO–520 and TSIO–

520 series engines affected by AD 87–

23–08. That proposal was prompted by

reports of crankshaft failures due to

subsurface fatigue cracking on engines

that had been inspected in accordance

with AD 87–23–08. That condition, if