14306 Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations

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 Mike Kiesov, Aerospace

Engineer, FAA, Small Airplane Directorate,

901 Locust, Room 301, Kansas City, Missouri

64106; telephone: (816) 329–4144; facsimile:

(816) 329–4090.

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

DG Flugzeugbau GmbH Technical Note No.

843/13, dated November 3, 1999. 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 DG Flugzeugbau GmbH, Postbox 41 20,

D–76646 Bruchsal, Federal Republic of

Germany. 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 German AD Number 1999–383, dated

December 1, 1999.

Issued in Kansas City, Missouri, on

February 26, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–5276 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–46–AD; Amendment

39–12138; AD 2001–05–02]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Model PC–7 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 98–08–22,

which currently requires inspecting the

elevator and rudder attachment brackets

for cracks and corrosion on certain

Pilatus Aircraft Ltd. (Pilatus) Model PC–

7 airplanes and replacing any cracked or

corrosion-damaged parts. Since the

issuance of AD 98–08–22, Pilatus has

redesigned the brackets. Installation of

these brackets should inhibit corrosion,

which resulted in cracks or corrosion

damage. This AD requires you to replace

the elevator and rudder attachment

brackets with parts of improved design.

This AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for Switzerland. The actions

specified by this AD are intended to

prevent failure of the elevator and

rudder attachment brackets because of

cracks or corrosion damage. Such failure

could result in the elevator or rudder

separating from the airplane with

consequent loss of airplane control.

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

Pilatus Aircraft Ltd., Customer Liaison

Manager, CH–6371 Stans, Switzerland;

telephone: +41 41 619 6509; facsimile:

+41 41 610 3351. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

46–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:

Roman Gabrys, Aerospace Engineer,

FAA, Small Airplane Directorate, 901

Locust, Room 301, Kansas City,

Missouri 64106; telephone: (816) 329–

4141; facsimile: (816) 329–4090.

SUPPLEMENTARY INFORMATION:

Discussion

Has FAA taken any action to this

point? Reports received from the

Federal Office for Civil Aviation

(FOCA), which is the airworthiness

authority for Switzerland, revealed

instances of corrosion and cracking in

the elevator and rudder attachment

brackets on Pilatus Model PC–7

airplanes that have been operated in

areas of high humidity or salt content.

This caused FAA to issue AD 98–08–22,

Amendment 39–10471 (63 FR 19175,

April 17, 1998). That AD requires you

to inspect the elevator and rudder

attachment brackets for cracks and/or

corrosion, and replace any cracked or

corrosion-damaged parts, as applicable.

What has happened since AD 98–08–

22 to initiate this action? The FOCA

recently notified FAA of the need to

change AD 98–08–22. The FOCA reports

that Pilatus has redesigned the elevator

and rudder attachment brackets.

Installation of these brackets should

inhibit the cause of corrosion, which

resulted in cracks or corrosion damage.

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

Pilatus Model PC–7 airplanes. This

proposal was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on January 2, 2001

(66 FR 57). The NPRM proposed to

supersede AD 98-08–22. AD 98–08–22

currently requires inspecting the

elevator and rudder attachment brackets

for cracks and corrosion, and replacing

any cracked or corrosion-damaged parts.

Since the issuance of AD 98–08–22,

Pilatus has redesigned the brackets.

Installation of these brackets should

inhibit corrosion, which resulted in

cracks or corrosion damage. The NPRM

also proposed to require you to replace

the elevator and rudder attachment

brackets with parts of improved design.

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.

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 minor

editorial corrections. We determined

that 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

8 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:

Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations 14307

Labor cost Parts cost Total cost per

airplane

Total cost on U.S.

operators

8 workhours × $60 per hour =

$480.

Parts will be provided by the manufacturer free of charge ................. $480 $480 × 8 = $3,840

Why is the compliance in hours timein-service (TIS) and calendar time? The

affected airplanes are used in general

aviation operations. Some operators

may accumulate 100 hours TIS on the

airplane in less than 6 months. We have

determined that the dual compliance

time:

—Gives all owners/operators of the

affected airplanes adequate time to

schedule and do the actions in this

AD; and

—Ensures that the unsafe condition

referenced in this AD will be

corrected within a reasonable time

period without inadvertently

grounding any of the affected

airplanes.

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 removing

Airworthiness Directive (AD) 98–08–22,

Amendment 39–10471 (63 FR 19175,

April 17, 1998), and by adding a new

AD to read as follows:

2001–05–02 Pilatus Aircraft LTD:

Amendment 39–12138; Docket No. 2000–

CE–46–AD; Supersedes AD 98–08–22,

Amendment 39–10471.

(a) What airplanes are affected by this AD?

This AD affects Model PC–7 airplanes, serial

numbers MSN 001 through MSN 612, 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 failure of the elevator and rudder

attachment brackets because of cracks or

corrosion damage, which could result in the

elevator or rudder separating from the

airplane 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

(1) Replace the horizontal stabilizer brackets

with new parts using replacement kit No.

500.50.07.132 and replace the vertical stabilizer bracket with new parts using replacement kit No. 500.50.07.133.

Within the next 100 hours time-in-service

(TIS) or 6 months after April 27, 2001 (the

effective date of this AD), whichever occurs

first, unless already accomplished.

In accordance with the Accomplishment Instructions of Pilatus Service Bulletin No.

55–005, dated March 23, 2000, the aircraft

maintenance manuals, and illustrated parts

catalogs.

(2) Do not install any parts identified as old

parts in replacement kit No. 500.50.07.132

(or FAA-approved equivalent part numbers)

or 500.50.07.133 (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?

(1) You may use an alternative method of

compliance or adjust the compliance time if:

(i) Your alternative method of compliance

provides an equivalent level of safety; and

(ii) 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.

(2) Alternative methods of compliance

approved under AD 98–08–22, which is

superseded by this AD, are not approved as

alternative methods of compliance with this

AD.

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 Roman Gabrys,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

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

4141; 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

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