14304 Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations

(2) Ensure that there is a sealant bead (1)

around the edge of each blade cuff. If no

sealant bead exists or if a sealant bead shows

excessive wear, before further flight, apply a

sealant bead in accordance with paragraph

2.2 of the Accomplishment Instructions of

Eurocopter France SB 65.137 R1, dated

November 17, 1993.

(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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Regulations Group.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(c) Special flight permits will not be

issued.

(d) The modification shall be done in

accordance with paragraph 2.2 of the

Accomplishment Instructions of Eurocopter

France SB 65.137 R1, dated November 17,

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 American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972)

641–3527. Copies may be inspected at the

FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas; or at the Office

of the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

(e) This amendment becomes effective on

April 16, 2001.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 1998–171–039(A)R2 and 1998–

170–056(A)R2, both dated January 12, 2000.

Issued in Fort Worth, Texas, on February

20, 2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–5164 Filed 3–9–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–CE–89–AD; Amendment 39–

12137; AD 2001–05–01]

RIN 2120–AA64

Airworthiness Directives; DG

Flugzeugbau GmbH Model DG–500MB

Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain DG Flugzeugbau

GmbH (DG Flugzeugbau) Model DG–

500MB sailplanes equipped with a

SOLO 2625 02 engine. This AD requires

you to install additional access holes in

the propeller mount and modify the

engine. This AD also requires you to do

a ground test run and replace the digital

engine indicator circuit breaker. This

AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for the Federal Republic of

Germany. The actions specified by this

AD are intended to correct an

inadequate circuit breaker and

unsatisfactory drive belt tension that

could cause damage to the engine

crankshaft. Such damage could lead to

engine failure and loss of control of the

sailplane.

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

DG Flugzeugbau GmbH, Postbox 41 20,

D–76646 Bruchsal, Federal Republic of

Germany; telephone: +49 7257–890;

facsimile: +49 7257–8922. You may

examine this information at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 99–CE–89–

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:

Mike Kiesov, Aerospace Engineer, FAA,

Small Airplane Directorate, 901 Locust,

Room 301, Kansas City, Missouri 64106;

telephone: (816) 329–4144; facsimile:

(816) 329–4090.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The Luftfahrt-Bundesamt (LBA), which

is the airworthiness authority for the

Federal Republic of Germany, notified

FAA that an unsafe condition may exist

on all DG Flugzeugbau Model DG–

500MB sailplanes equipped with a

SOLO 2625 02 engine. The LBA reports

that the service history for the SOLO

2625 02 engine shows a need to modify

the front crank shaft bearing.

Additionally, the digital engine

indicator circuit breaker amperage is too

low for use and needs replacement.

What are the consequences if the

condition is not corrected? The actions

specified by this AD are intended to

correct an inadequate circuit breaker

and unsatisfactory drive belt tension

that could cause damage to the engine

crankshaft. Such damage could lead to

engine failure and loss of control of the

sailplane.

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 DG

Flugzeugbau Model DG–500MB

sailplanes equipped with a SOLO 2625

02 engine. This proposal was published

in the Federal Register as a notice of

proposed rulemaking (NPRM) on

December 27, 2000 (65 FR 81782). The

NPRM proposed to require you install

additional access holes in the propeller

mount and modify the engine. The

NPRM also proposed to require you to

do a ground test run and replace the

digital engine indicator circuit breaker.

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 sailplanes does this AD

impact? We estimate that this AD affects

1 sailplane in the U.S. registry.

What is the cost impact of this AD on

owners/operators of the affected

sailplanes? We estimate the following

costs to accomplish the modification:

Federal Register / Vol. 66, No. 48 / Monday, March 12, 2001 / Rules and Regulations 14305

Labor cost Parts cost Total cost per

sailplane

Total cost on U.S.

operators

12 workhours × $60 per hour =

$720.

The manufacturer will do the engine modification and provide the

new circuit breaker under warranty.

$720 $720 × 1 = $720

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:

2001–05–01 DG Flugzeugbau GMBH:

Amendment 39–12137; Docket No. 99–

CE–89–AD.

(a) What sailplanes are affected by this

AD? This AD affects Model DG–500MB

sailplanes, all serial numbers equipped with

a SOLO 2625 02 engine, that are certificated

in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above sailplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to correct an inadequate circuit breaker and

unsatisfactory drive belt tension that could

cause damage to the engine crankshaft. Such

damage could lead to engine failure and loss

of control of the sailplane.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance Procedures

(1) Remove the engine from the propeller

mount.

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

after April 27, 2001 (the effective date of

this AD).

In accordance with the maintenance manual.

Ship engine to the engine manufacturer,

SOLO, or a licensed repair station, for

modification according to the SOLO Technical Note (TN) 4600–1.

(2) Install additional access holes in the propeller mount.Before further flight after removing the engine

and before installing the modified engine to

the propeller mount.

In accordance with drawing 5M102 of DG

Flugzeugbau Technical Note 843/13, dated

November 3, 1999.

(3) Install the modified engine to the propeller

mount.

Before further flight after rermoving the engine

and after the engine modification.

In accordance with the maintenance manual.

(4) Do a gound test run ...................................... Before further flight after the previous action .. In accordance with DG Flugzeugbau Technical Note 843/13, dated November 3,

1999.

(5) Replace the digital engine indicator (DEI)

circuit breaker with a new 5 ampere Klixon

7277–2–5A circuit breaker (or FAA-approved

equivalent part number).

Before further flight after the previous actions In accordance with DG Flugzeugbau Technical Note 843/13, dated November 3,

1999.

(6) Do not install any engine that has not been

modified following SOLO TN 4600–1.

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

AD).

Not Applicable.

(7) Do not install any DEI circuit breaker that is

not a 5 ampere Klixon 7277–2–5A circuit

breaker (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 sailplane

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 sailplanes 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

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: