26426 Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required within the next 3

calendar months after the effective date of

this AD, unless already accomplished.

To prevent the operator from using

inaccurate weight and balance information

provided in the sailplane flight manual

(SFM), which could lead to hazardous flight

conditions, accomplish the following:

(a) Replace page 2 (dated May 16, 1984)

and page 13 (dated February 16, 1984) from

the Alexander Schleicher Model ASK 21

SFM with new pages 2 and 13, both dated

June 4, 1984, in accordance with Alexander

Schleicher ASK 21 Technical Note No. 13 a,

dated June 4, 1984.

(b) Incorporating the SFM revisions, as

required by this AD, may be performed by

the owner/operator holding at least a private

pilot certificate as authorized by section 43.7

of the Federal Aviation Regulations (14 CFR

43.7), and must be entered into the aircraft

records showing compliance with this AD in

accordance with section 43.9 of the Federal

Aviation Regulations (14 CFR 43.9).

(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 sailplane

to a location where the requirements of this

AD can be accomplished.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, Aircraft Certification Service,

1201 Walnut, suite 900, Kansas City,

Missouri 64106. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(e) Questions or technical information

related to Alexander Schleicher ASK 21

Technical Note No. 13 a, dated June 4, 1984,

should be directed to Alexander Schleicher,

Segelflugzeugbau, 6416 Poppenhausen,

Wasserkuppe, Federal Republic of Germany;

telephone: 49.6658.890 or 49.6658.8920;

facsimile: 49.6658.8923 or 49.6658.8940.

This service information may be examined at

the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

(f) The replacement required by this AD

shall be done in accordance with Alexander

Schleicher ASK 21 Technical Note No. 13 a,

dated June 4, 1984. 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 Alexander Schleicher,

Segelflugzeugbau, 6416 Poppenhausen,

Wasserkuppe, Federal Republic of Germany.

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.

Note 3: The subject of this AD is addressed

in German AD No. 84–32/2 Schleicher, dated

June 12, 1984.

(g) This amendment becomes effective on

June 26, 998. Issued in Kansas City, Missouri,

on April 30, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–12380 Filed 5–12–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–297–AD; Amendment

39–10519; AD 98–10–08]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model C–212 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain CASA Model C–

212 series airplanes, that requires a onetime inspection of the lower shaft and

support structure of the rudder for

corrosion, repair of any discrepancy

found, and modification of the

structure. This amendment is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent corrosion from

developing in the lower shaft and

support structure of the rudder, which

could result in the failure of the rudder

lower shaft and consequent reduced

controllability of the airplane.

DATES: Effective June 17, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 17,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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:

Norman B. Martenson, Manager,

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 CASA

Model C–212 series airplanes was

published in the Federal Register on

March 10, 1998 (63 FR 11631). That

action proposed to require a one-time

inspection of the lower shaft and

support structure of the rudder for

corrosion, repair of any discrepancy

found, and modification of the

structure.

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 38 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 7

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$400 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$31,160, or $820 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
Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations 26427

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:

98–10–08 Construcciones Aeronauticas,

S.A. (CASA): Amendment 39–10519.

Docket 97–NM–297–AD.

Applicability: Model C–212 series

airplanes, as listed in CASA Service Bulletin

SB–212–27–34, dated November 22, 1993,

certificated in any category.

Note 1: 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 (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 prevent corrosion from developing in

the lower shaft and support structure of the

rudder, which could result in the failure of

the rudder lower shaft and consequent

reduced controllability of the airplane,

accomplish the following:

(a) Within 7 months after the effective date

of this AD, accomplish paragraphs (a)(1) and

(a)(2) of this AD, in accordance with CASA

Service Bulletin SB–212–27–34, dated

November 22, 1993.

(1) Inspect the rudder lower shaft and

support structure for corrosion; and, prior to

further flight, repair any discrepancy found.

And

(2) Modify the rudder lower shaft and

support structure to prevent the entry and

accumulation of water.

(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, FAA,

Transport Airplane Directorate. 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 CASA Service Bulletin SB–212–27–34,

dated November 22, 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 Construcciones

Aeronauticas, S.A., Getafe, Madrid, Spain.

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 Spanish airworthiness directive 06/96,

dated May 21, 1996.

(e) This amendment becomes effective on

June 17, 1998.

Issued in Renton, Washington, on May 5,

1998.

D. L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–12519 Filed 5–12–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–24–AD; Amendment 39–

10517; AD 98–10–06]

RIN 2120–AA64

Airworthiness Directives; Burkhart

Grob Luft-und Raumfahrt Models

G115C, G115C2, G115D, and G115D2

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 96–19–07,

which currently requires the following

on Burkhart Grob Luft-und Raumfahrt

(Grob) Models G115C, G115C2, G115D,

and G115D2 airplanes: installing a

placard that restricts the never exceed

speed (Vne) of the affected airplane

models from 184 knots to 160 knots;

installing on the airspeed indicator glass

a red line at 296 km/h (160 knots);

installing a placard that prohibits

aerobatic maneuvers; and placing a copy

of the AD in the Limitations Section of

the airplane flight manual. This AD will

temporarily retain the flight restrictions

that are currently required by AD 96–

19–07; and will eventually require

accomplishing certain inspections and

modifications, as terminating action for

these flight restrictions. This AD is the

result of mandatory continuing

airworthiness information (MCAI)

issued by the airworthiness authority for

Germany. The actions specified by this

AD are intended to prevent loss of

control of the airplane caused by

excessive speed or aerobatic maneuvers.

DATES: Effective June 28, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 28,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Burkhart Grob Luft-und Raumfahrt, D–

8939 Mattsies, Germany. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 98–CE–24–AD, Room 1558,

601 E. 12th Street, 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: Mr.

Karl M. Schletzbaum, Aerospace

Engineer, FAA, Small Airplane