14308 Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations

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

Pilatus Service Bulletin No. 55–005, dated

March 23, 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 Pilatus

Aircraft Ltd., Customer Liaison Manager,

CH–6371 Stans, Switzerland. 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.

(i) Does this AD action affect any existing

AD actions? This amendment supersedes AD

98–08–22, Amendment 39–10471.

(j) When does this amendment become

effective? This amendment becomes effective

on April 27, 2001.

Note 2: The subject of this AD is addressed

in Swiss AD HB 2000–411, dated September

27, 2000.

Issued in Kansas City, Missouri, on

February 26, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–5275 Filed 3–9–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–61–AD; Amendment

39–12139; AD 2001–05–03]

RIN 2120–AA64

Airworthiness Directives; SOCATA—

Groupe AEROSPATIALE Model TBM

700 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain SOCATA—Groupe

AEROSPATIALE (Socata) Model TBM

700 airplanes. This AD requires you to

apply Loctite on attaching bolt/screw

threads of inboard, central, and

outboard carriages; increase tightening

torques of associated hardware; and

replace central carriage attaching bolts.

This AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for France. The actions

specified by this AD are intended to

prevent loose, or the loss of, flap

attaching bolts/screws, which could

cause rough or irregular control. Such

rough or irregular control could lead to

the loss of control of the airplane.

DATES: This AD becomes effective on

April 27, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of April 27, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

SOCATA Groupe AEROSPATIALE,

Customer Support, Aerodrome TarbesOssun-Lourdes, BP 930–F65009 Tarbes

Cedex, France; telephone: (33)

(0)5.62.41.73.00; facsimile: (33)

(0)5.62.41.76.54; or the Product Support

Manager, SOCATA—Groupe

AEROSPATIALE, North Perry Airport,

7501 Pembroke Road, Pembroke Pines,

Florida 33023; telephone: (954) 894–

1160; facsimile: (954) 964–4191. You

may examine this information at the

Federal Aviation Administration (FAA),

Central Region, Office of the Regional

Counsel, Attention: Rules Docket No.

2000–CE–61–AD, 901 Locust, Room

506, Kansas City, Missouri 64106; or at

the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

FOR FURTHER INFORMATION 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.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified FAA that an unsafe

condition may exist on certain Socata

Model TBM 700 airplanes. The DGAC

reports two occurrences on Socata

model TBM 700 airplanes where,

following a flight, a screw of a flap

attachment fitting was found partly

unscrewed and another was missing.

These occurrences are the result of flap

vibration.

What are the consequences if the

condition is not corrected? Loose or the

loss of flap attaching bolts/screws could

result in rough or irregular control. Such

rough or irregular control could lead to

loss of control of the airplane.

Has FAA taken any action to this

point? We issued a proposal to amend

part 39 of the Federal Aviation

Regulations (14 CFR part 39) to include

an AD that would apply to certain

Socata Model TBM 700 airplanes. This

proposal was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on January 2, 2001

(66 FR 64). The NPRM proposed to

require you to apply Loctite on

attaching bolt/screw threads of inboard,

central, and outboard carriages; increase

tightening torques of associated

hardware; and replace central carriage

attaching bolts.

Was the public invited to comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. No comments were

received on the proposed rule or the

FAA’s determination of the cost to the

public.

Socata has revised Service Bulletin

No. SB 70–087 57, dated September

2000 (Amendment 1, dated November

2000), to incorporate minor procedural

changes. This AD requires no further

action if the original service bulletin is

accomplished.

FAA’s Determination

What is FAA’s final determination on

this issue? After careful review of all

available information related to the

subject presented above, we have

determined that air safety and the

public interest require the adoption of

the rule as proposed except for the

addition of the revised service

information and minor editorial

corrections. We determined that this

addition and these minor corrections:

—Will not change the meaning of the

AD; and

—Will not add any additional burden

upon the public than was already

proposed.

Cost Impact

How many airplanes does this AD

impact? We estimate that this AD affects

75 airplanes in the U.S. registry.

What is the cost impact of this AD on

owners/operators of the affected

airplanes? We estimate the following

costs to accomplish the modification:

Labor cost Parts cost Total cost per airplane Total cost on U.S.

operators

6 workhours × $60 per hour = $360 ........................................................... $10 $360 + $10 = $370 $370 × 75 = $27,750

Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations 14309

Regulatory Impact

Does this AD impact various entities?

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.

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:

2001–05–03 Socata—Groupe Aerospatiale:

Amendment 39–12139; Docket No.

2000–CE–61–AD.

(a) What airplanes are affected by this AD?

This AD affects Model TBM 700 airplanes,

serial numbers 1 through 164, and 166

through 173, that are certificated in any

category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to prevent loose, or the loss of, flap attaching

bolts/screws, which could cause rough or

irregular control. Such rough or irregular

control could lead to the loss of control of the

airplane.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance Procedures

(1) Apply Loctite on attaching bolt/screw

threads of inboard, central, and outboard carriages; increase tightening torques of associated hardward; and replace central carriage

attaching bolts with new bolts, part number

Z00.N5109337315.

Within the next 25 hours time-in-service (TIS)

after April 27, 2001 (the effective date of

this AD), if not already done.

In accordance with the ACCOMPLISHMENT

INSTRUCTIONS in Socata Service Bulletin

SB 70–087, Amendment 1, dated November 2000, and applicable maintenance manual. No further action is required if accomplished in accordance with Socata Service

Bulletin SB 70–087, dated September 2000,

and the applicable maintenance manual.

(2) Do not install any central carriage attaching

bolts that are not part number

Z00.N5109337315 (or FAA-approved equivalent part number).

As of April 27, 2001 (the effective date of this

AD).

Not Applicable.

(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, 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, 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

Socata Service Bulletin No. SB 70–087 57,

Amendment 1, dated November 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-OssunLourdes, 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.

(i) When does this amendment become

effective? This amendment becomes effective

on April 27, 2001.

Note 2: The subject of this AD is addressed

in French AD 2000–375(A), dated September

20, 2000.

Issued in Kansas City, Missouri, on

February 26, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–5274 Filed 3–9–01; 8:45 am]

BILLING CODE 4910–13–P