22498 Federal Register / Vol. 60, No. 88 / Monday, May 8, 1995 / Rules and Regulations

Replacement in the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995.

(2) Accomplish the installation test

contained in paragraph 3. Installation Test

Procedure in the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995. Accomplish the appropriate valve test

thereafter at intervals not to exceed 600 hours

TIS.

(d) If any fuel valve replacement is

necessary and the replacement parts are not

available, accomplish the following provided

the parts have been ordered from the

manufacturer and are installed within 25

hours TIS after availability:

(1) Incorporate the following into the

Limitations Section of the Pilots Operating

Handbook (POH) and FAA-approved

Airplane Flight Manual (AFM):

(i) For the Model T303 airplanes: Unusable

Fuel: Indicated fuel quantity below 36

pounds (6 gallons) in each main tank is

unusable.

(ii) For the Models 402C, 404, 414A, and

421C airplanes: Unusable Fuel: Indicated fuel

quantity below 90 pounds (15 gallons) in

each main tank is unusable.

(iii) For the Model 404 airplanes: Fuel

Quantity: Minimum indicated fuel quantity

for takeoff is 228 pounds (38 gallons) in each

main tank.

(iv) For the Models 402C, 414A, and 421C

airplanes: Fuel Quantity: Minimum indicated

fuel quantity for takeoff is 210 pounds (35

gallons) in each main tank.

(2) Fabricate placards, as applicable, with

the following words in letters at least 0.10-

inch in height and install these placards

within the pilot’s clear view on the

instrument panel in close proximity to the

fuel quantity gage:

(i) For Models 402C, 404, 414A, and 421C

airplanes: ‘‘UNUSABLE FUEL—INDICATED

FUEL QUANTITY BELOW 90 POUNDS (15

GALLONS) IN EACH MAIN TANK IS

UNUSABLE’’.

(ii) For Model T303 airplanes:

‘‘UNUSABLE FUEL—INDICATED FUEL

QUANTITY BELOW 36 POUNDS (6

GALLONS) IN EACH MAIN TANK IS

UNUSABLE’’.

(3) For the Model 404 airplanes, fabricate

four placards with the following in letters at

least 0.10- inch in height: ‘‘157 GAL’’. Install

these placards covering the four existing

‘‘172 GAL’’ markings on the existing placard

around the engine fuel selector handles.

(4) For the Models 402C, 414A, and 421C

airplanes, fabricate four placards with the

following in letters at least 0.10-inch in

height: ‘‘88 GAL’’. Install these placards

covering the four existing ‘‘103 GAL’’

markings on the existing placard around the

engine fuel selector handles.

(5) For the Model T303 airplanes, fabricate

the following placards in letters at least 0.10-

inch in height:

(i) ‘‘423 LBS’’ (2 placards). Install these

placards covering the two existing ‘‘459 LBS’’

markings on the existing placard around the

engine fuel selector handles.

(ii) ‘‘363 LBS’’ (1 placard). Install this

placard covering the existing ‘‘399 LBS’’

marking on the existing placard around the

engine fuel selector handles.

(6) For all affected Model airplanes,

fabricate a placard with the following words

in letters at least 0.10-inch in height and

install this placard within the pilot’s clear

view on the instrument panel: ‘‘ROLLING,

TURNING TAKEOFFS ARE PROHIBITED.’’

Note 3: The placard requirements may

already be accomplished in accordance with

either superseded AD 92–27–20 or AD 93–

05–03 (superseded by this action). These

placard requirements are eliminated upon

installation of the improved fuel valves as

required by this AD.

Note 4: The repetitive functional or

installation test is not required if parts are

not available and the requirements of

paragraph (d) of this AD (including all

subparagraphs) are complied with.

(e) Special flight permits may be issued in

accordance with §§ 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.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Manager, Wichita ACO, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas 67209. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(g) The installation, replacement, and tests

required by this AD shall be done in

accordance with the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995. 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 the Cessna Aircraft Company, P.O. Box

7704, Wichita, Kansas 67277. Copies may be

inspected at the FAA, Central Region, Office

of the Assistant Chief 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.

(h) This amendment (39–9217) supersedes

AD 93–05–03, Amendment 39–8508.

(i) This amendment (39–9217) becomes

effective on June 14, 1995.

Issued in Kansas City, Missouri, on April

26, 1995.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–10833 Filed 5–5–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–CE–17–AD; Amendment 39–

9215; AD 95–09–11]

Airworthiness Directives; SchemppHirth Cirrus and Cirrus VTC Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Schempp-Hirth Cirrus and

Cirrus VTC sailplanes. This action

requires modifying the airbrake

actuating lever and replacing the

airbrake system coupling balls. Reports

of the coupling balls on the airbrake

actuating lever breaking at the threaded

end on several of the affected sailplanes

prompted this action. The actions

specified by this AD are intended to

prevent airbrake system failure caused

by the above condition, which, if not

detected and corrected, could result in

sailplane controllability problems.

DATES: Effective June 9, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 9,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

Schempp-Hirth Flugzeubau GmbH,

Krebenstr. 25, D–7312 Kirchheim/Teck,

Germany. This information may also be

examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

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.

Herman C. Belderok, Project Officer,

Sailplanes, Small Airplane Directorate,

Airplane Certification Service, FAA,

1201 Walnut, suite 900, Kansas City,

Missouri 64106; telephone (816) 426–

6932; facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to

Schempp-Hirth Cirrus and Cirrus VTC

sailplanes was published in the Federal

Register on December 20, 1994 (59 FR

65520). The action proposed modifying

the airbrake actuating lever and

replacing the airbrake system coupling

balls. Accomplishment of the proposed

actions would be in accordance with

Schempp-Hirth Technical Note 265–10,

dated November 5, 1992.

Interested persons have been afforded

an opportunity to participate in the
Federal Register / Vol. 60, No. 88 / Monday, May 8, 1995 / Rules and Regulations 22499

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

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.

The FAA estimates that 21 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

1 workhour per sailplane to accomplish

the required action, and that the average

labor rate is approximately $60 an hour.

Parts cost approximately $25 per

sailplane. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $1,785. This

figure is based on the assumption that

no affected sailplane owner/operator

has accomplished the required

modification. The FAA believes that

several of the 21 affected sailplane

owners/operators have already

accomplished the required

modification, thereby reducing the cost

impact upon the public.

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

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, 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new AD to read as follows:

95–09–11 Schempp-Hirth: Amendment 39–

9215; Docket No. 94–CE–17–AD.

Applicability: Cirrus and Cirrus VTC

Sailplanes, all serial numbers, certificated in

any category.

Note 1: This AD applies to each sailplane

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

sailplanes that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any sailplane from the

applicability of this AD.

Compliance: Required upon the

accumulation of 500 hours time-in-service

(TIS) or within the next 20 hours TIS after

the effective date of this AD, whichever

occurs later, unless already accomplished.

To prevent airbrake system failure caused

by broken coupling balls on the airbrake

actuating lever, which, if not detected and

corrected, could result in sailplane

controllability problems, accomplish the

following:

(a) Modify the airbrake actuating lever and

replace the airbrake system coupling balls

(located on the actuating lever) in accordance

with the instructions in Schempp-Hirth

Technical Note No. 265–10, dated November

5, 1992.

(b) Special flight permits may be issued in

accordance with §§ 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.

(c) 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,

FAA, 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.

(d) The modification required by this AD

shall be done in accordance with SchemppHirth Technical Note No. 265–10, dated

November 5, 1992. 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 Schempp-Hirth Flugzeubau

GmbH, Krebenstr. 25, D–7312 Kirchheim/

Teck, Germany. Copies may be inspected at

the FAA, Central Region, Office of the

Assistant Chief 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.

(e) This amendment (39–9215) becomes

effective on June 9, 1995.

Issued in Kansas City, Missouri, on April

26, 1995.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–10830 Filed 5–5–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 91–CE–40–AD; Amendment 39–

9216; AD 95–09–12]

Airworthiness Directives; Alexander

Schleicher Models ASW–12, ASW–15,

ASW–15B, and ASW–17 Gliders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 88–11–05,

which currently requires repetitively

inspecting the wing spar of Alexander

Schleicher Models ASW–15 and ASW–

15B gliders for wood rot, and replacing

any wing spar where wood rot is found.

Alexander Schleicher Models ASW–12

and ASW–17 gliders are of a similar

type design to Models ASW–15 and

ASW–15B gliders, and the Federal

Aviation Administration (FAA), in

working with the Civil Aviation

Authority of Germany, has decided that

the actions referenced in AD 88–11–05

should also apply to Models ASW–12

and ASW–17 gliders. The actions

specified by this AD are intended to

prevent failure of the wing spar caused