Federal Register / Vol. 67, No. 31 / Thursday, February 14, 2002 / Rules and Regulations 6855

or on the distribution of power and

responsibilities among the various

levels of government. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

Does This AD Involve a Significant Rule

or Regulatory Action?

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, under 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. FAA amends § 39.13 by adding a

new AD to read as follows:

2002–03–03 Socata—Groupe Aerospatiale:

Amendment 39–12644; Docket No.

2001–CE–10–AD.

(a) What airplanes are affected by this AD?

This AD affects Model TBM 700 airplanes,

serial numbers 1 through 164, that are

certificated in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

airplanes identified in paragraph (a) of this

AD must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to prevent water from accumulating in the

fuselage, then freezing and interfering with or

causing the elevator controls to seize. This

could result in loss of elevator control with

consequent loss of airplane control.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance Procedures

Incorporate Kit No. OPT70 K072–53 ................. Within the next 3 months after March 29,

2002 (the effective date of this AD), unless

already accomplished.

In accordance with the Technical Instructions

supplied with Kit No. OPT70 K072–53, as

specified in Socata Service Bulletin SB 70–

082 53, dated June 2000.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Standards Office, Small

Airplane Directorate, approves your

alternative. Submit your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Standards Office, Small Airplane

Directorate.

Note 1: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 modification,

alteration, or repair on the unsafe condition

addressed by this AD; and, if you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Karl Schletzbaum,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

City, Missouri 64106; telephone: (816) 329–

4146; facsimile: (816) 329–4090.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

the Technical Instructions supplied with Kit

No. OPT70 K072–53, as specified in Socata

Service Bulletin SB 70–082 53, dated June

2000. The Director of the Federal Register

approved this incorporation by reference

under 5 U.S.C. 552(a) and 1 CFR part 51. You

can get copies from SOCATA—Groupe

AEROSPATIALE, Customer Support,

Aerodrome Tarbes-Ossun-Lourdes, BP 930—

F65009 Tarbes Cedex, France; or the Product

Support Manager, SOCATA—Groupe

AEROSPATIALE, North Perry Airport, 7501

Pembroke Road, Pembroke Pines, Florida

33023. You can look at copies at the FAA,

Central Region, Office of the Regional

Counsel, 901 Locust, Room 506, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW, suite

700, Washington, DC.

Note 2: The subject of this AD is addressed

in French AD 2000–373(A), dated October

18, 2000.

(i) When does this amendment become

effective? This amendment becomes effective

on March 29, 2002.

Issued in Kansas City, Missouri, on

February 4, 2002.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 02–3167 Filed 2–13–02; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–266–AD; Amendment

39–12651; AD 2002–03–10]

RIN 2120–AA64

Airworthiness Directives; BAE

Systems (Operations) Limited Model

BAe 146 Series Airplanes and Model

Avro 146–RJ Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain BAE Systems

(Operations) Limited Model BAe 146

and Avro 146–RJ series airplanes, that

requires repetitive inspections to detect

cracking of the oleo strut of the nose

landing gear (NLG), and corrective

actions if necessary. This AD also

provides for optional terminating action

for the repetitive inspections. This

action is necessary to detect and correct

fatigue cracking of the oleo strut of the

NLG, which could result in failure of

the NLG. This action is intended to

address the identified unsafe condition.

DATES: Effective March 21, 2002.

The incorporation by reference of

certain publications listed in the

6856 Federal Register / Vol. 67, No. 31 / Thursday, February 14, 2002 / Rules and Regulations

regulations is approved by the Director

of the Federal Register as of March 21,

2002.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Regional

Aircraft American Support, 13850

Mclearen Road, Herndon, Virginia

20171. 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: Dan

Rodina, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2125;

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 BAE

Systems (Operations) Limited Model

BAe 146 and Avro 146–RJ series

airplanes was published in the Federal

Register on November 23, 2001 (66 FR

58678). That action proposed to require

repetitive inspections to detect cracking

of the oleo strut of the nose landing

gear, and corrective actions if necessary.

That action also proposed to provide for

optional terminating action for the

repetitive inspections.

Comments

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 60 Model BAe

146 series airplanes and Model Avro

146–RJ series airplanes of U.S. registry

will be affected by this AD, that it will

take approximately 1 work hour per

airplane to accomplish the required

inspection, and that the average labor

rate is $60 per work hour. Based on

these figures, the cost impact of the

requirements of this AD on U.S.

operators is estimated to be $3,600, or

$60 per airplane, per inspection cycle.

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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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:

2002–03–10 BAE Systems (Operations)

Limited (Formerly British Aerospace

Regional Aircraft): Amendment 39–

12651. Docket 2000–NM–266–AD.

Applicability: Model BAe 146 series

airplanes and Model Avro 146–RJ series

airplanes, certificated in any category, as

listed in BAE Systems (Operations) Limited

Service Bulletin SB.32–158, dated June 2,

2000, except those on which Messier-Dowty

Modification AC12248 has been installed.

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 (d) 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 fatigue cracking of

the oleo strut of the nose landing gear (NLG),

which could result in failure of the NLG,

accomplish the following:

Inspection

(a) Perform an ultrasonic inspection to

detect cracking of the oleo strut of the NLG,

in accordance with BAE Systems

(Operations) Limited Service Bulletin SB.32–

158, dated June 2, 2000, according to the

applicable time schedule specified in

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

Thereafter, repeat the inspection at least

every 2,500 landings, until the actions

specified by paragraph (c) of this AD have

been performed.

(1) For NLGs identified in paragraph D.(3)

of BAE Systems (Operations) Limited Service

Bulletin SB.32–158, dated June 2, 2000:

Inspect before the NLG accumulates 2,500

landings after accomplishment of the initial

inspection specified by Messier-Dowty

Service Bulletin 146–32–149, or within 30

days after the effective date of this AD,

whichever occurs later.

(2) For NLGs having part number

201138002, serial numbers M–DG–0158 to

M–DG–0168 inclusive, as identified in

paragraph D.(4) of BAE Systems (Operations)

Limited Service Bulletin SB. 32–158, dated

June 2, 2000: Inspect before the NLG

accumulates 20,000 total landings, or within

500 landings after the effective date of this

AD, whichever occurs later.

(3) For NLGs other than those identified in

paragraph (a)(1) or (a)(2) of this AD: Inspect

before the NLG accumulates 8,000 total

landings, or within 500 landings after the

effective date of this AD, whichever occurs

later.

Corrective Actions

(b) If any crack is found during any

inspection required by this AD: Before

further flight, replace the oleo strut of the

Federal Register / Vol. 67, No. 31 / Thursday, February 14, 2002 / Rules and Regulations 6857

NLG with a new or serviceable strut in

accordance with BAE Systems (Operations)

Limited Service Bulletin SB.32–158, dated

June 2, 2000.

Optional Terminating Action

(c) Modification of the NLG in accordance

with BAE Systems (Operations) Limited

Service Bulletin SB.32–159–70668ABC,

dated June 14, 2000, terminates the repetitive

inspections required by this AD.

Alternative Methods of Compliance

(d) 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, Transport

Airplane Directorate, FAA. 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.

Special Flight Permits

(e) 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.

Incorporation by Reference

(f) The inspections and replacement, as

applicable, shall be done in accordance with

BAE Systems (Operations) Limited Service

Bulletin SB.32–158, dated June 2, 2000. The

terminating action, if accomplished, shall be

done in accordance with BAE Systems

(Operations) Limited Service Bulletin SB.32–

159–70668ABC, dated June 14, 2000. (Only

the first page of these documents is dated; no

other page of these documents contains this

information.) 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 British Aerospace Regional Aircraft

American Support, 13850 Mclearen Road,

Herndon, Virginia 20171. 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 British airworthiness directive 002–06–

2000.

Effective Date

(g) This amendment becomes effective on

March 21, 2002.

Issued in Renton, Washington, on February

6, 2002.

Ali Bahrami,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 02–3309 Filed 2–13–02; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–34–AD; Amendment

39–12642; AD 2002–03–01]

RIN 2120–AA64

Airworthiness Directives; Honeywell

International, Inc., (Formerly

AlliedSignal, Inc., and Textron

Lycoming) T5311A, T5311B, T5313B,

T5317A, T5317B, T53–L–11, T53–L–

11A, T53–L–11B, T53–L–11C, T53–L–

11D, T53–L–11A S/SA, T53–L–13B,

T53–L–13B S/SA, T53–L–13B S/SB, and

T53–L–703 Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD), that is

applicable to Honeywell International,

Inc., (formerly AlliedSignal, Inc., and

Textron Lycoming) T5311A, T5311B,

T5313B, T5317A, T5317B, and former

military T53–L–11, T53–L–11A, T53–L–

11B, T53–L–11C, T53–L–11D, T53–L–

11A S/SA, T53–L–13B, T53–L–13B S/

SA, T53–L–13B S/SB, and T53–L–703

series turboshaft engines. This

amendment requires initial and

repetitive special vibration tests of the

engine, and if necessary replacement

with a serviceable reduction gearbox

assembly, or a serviceable engine before

further flight. This amendment is

prompted by reports of tachometer drive

spur gear failure, resulting in potential

engine overspeed, loss of power turbine

speed (N2) instrument panel indication,

and hard landings. The actions specified

in this AD are intended to prevent

excessive vibrations produced by the

reduction gearbox assembly that could

cause failure of the tachometer drive

spur gear.

DATES: Effective date March 21, 2002.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 21,

2002.

ADDRESSES: The service information

referenced in this AD may be obtained

from Honeywell International, Inc.,

(formerly AlliedSignal, Inc., and

Textron Lycoming), Attn: Data

Distribution, M/S 64–3/2101–201, P.O.

Box 29003, Phoenix, AZ 85038–9003;

telephone: (602) 365–2493; fax: (602)

365–5577. This information may be

examined, by appointment, at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional 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:

Robert Baitoo, Aerospace Engineer, Los

Angeles Aircraft Certification Office,

FAA, Transport Airplane Directorate,

3960 Paramount Blvd., Lakewood, CA

90712–4137; telephone: (562) 627–5245;

fax: (562) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that is applicable to

Honeywell International, Inc., (formerly

AlliedSignal, Inc., and Textron

Lycoming) T5311A, T5311B, T5313B,

T5317A, T5317B, and former military

T53–L–11, T53–L–11A, T53–L–11B,

T53–L–11C, T53–L–11D, T53–L–11A S/

SA, T53–L–13B, T53–L–13B S/SA, T53–

L–13B S/SB, and T53–L–703 series

turboshaft engines was published in the

Federal Register on June 15, 2001 (66

FR 32591). That action proposed to

require initial and repetitive special

vibration tests of the engine, and if

necessary replacement with a

serviceable reduction gearbox assembly,

or a serviceable engine before further

flight, in accordance with AlliedSignal,

Inc., Service Bulletin (SB) No.’’s

T5311A/B–0100, dated January 20,

2000; T5313B/17–0100, dated

November 19, 1999; T53–L–11–0100,

dated January 20, 2000; T53–L–13B–

0100, Revision 2, dated May 11, 1999;

and T53–L–703–0100, Revision 2, dated

May 11, 1999.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the one

comment received.

The commenter stated that further

investigation into the root problem

causing the spur gear failures needs to

be addressed. The problem may be a

manufacturing problem from one U.S.

Government contract supplier.

The FAA does not agree. The

commenter did not supply sufficient

evidence substantiating a design

nonconformity.

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.

Economic Analysis

There are about 4,500 engines of the

affected design in the worldwide fleet.

The FAA estimates that 300 engines