Federal Register / Vol. 62, No. 69 / Thursday, April 10, 1997 / Rules and Regulations 17537

operations, since other additional fire

extinguishing features of the system can

address problems that occur within a

typical flight range (or 60 minutes).

Conclusion

After careful review of the available

data, including the comments noted

above, 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 48 Airbus

Model A310 and A300–600 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 1 work hour per airplane

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the AD on U.S. operators

is estimated to be $2,880, or $60 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

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:

97–08–03 Airbus Industrie: Amendment

39–9991. Docket 94–NM–196–AD.

Applicability: Model A310 and A300–600

series airplanes on which Airbus

Modification 6403 (reference Airbus Service

Bulletin A310–26–2010 or A300–600–26–

6011) has been installed; certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it otherwise

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 use the authority

provided in paragraph (b) 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 airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To ensure that a faulty pressure reducing

valve in the cargo fire extinguishing system

is not installed, which could result in

reduced fire protection of the cargo

compartment of the airplane from 260

minutes to 60 minutes, accomplish the

following:

(a) Prior to the accumulation of 600 total

flight hours after the effective date of this AD,

perform a functional flow test and leak test

to verify if the pressure reducing valve in the

cargo fire extinguishing system is in a

serviceable condition, in accordance with

paragraph 4.2., Description, of Airbus All

Operators Telex AOT 26–13, dated June 28,

1994. If a faulty pressure reducing valve is

installed, prior to extended range twinengine operations (ETOPS), replace it with a

new valve, in accordance with the aircraft

maintenance manual, reference 26–23–14,

Page block 401.

(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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 tests shall be done in accordance

with Airbus All Operators Telex AOT 26–13,

dated June 28, 1994. 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 Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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.

(e) This amendment becomes effective on

May 15, 1997.

Issued in Renton, Washington, on April 2,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–9011 Filed 4–9–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 92–CE–41–AD; Amendment 39–

9994; AD 97–08–06]

RIN 2120–AA64

Airworthiness Directives; Louis

L’Hotellier, S.A., Ball and Swivel Joint

Quick Connectors

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Louis L’Hotellier S.A.

(L’Hotellier) ball and swivel joint quick

connectors installed on gliders and

sailplanes that are not equipped with a

‘‘Uerling’’ sleeve or an LS-safety sleeve.

These connectors allow the operator of

the gliders and sailplanes to quickly

connect and disconnect the control
17538 Federal Register / Vol. 62, No. 69 / Thursday, April 10, 1997 / Rules and Regulations

systems during assembly and

disassembly for storage purposes. This

action requires enlarging the safety pin

guide hole diameter, and fabricating and

installing a placard that specifies a

check of the security of the connectors

prior to each flight. Several in-flight

accidents involving inadvertent

disconnection of these connectors that

are installed on certain gliders and

sailplanes prompted this action. The

actions specified by this AD are

intended to prevent the connectors from

becoming inadvertently disconnected,

which could result in loss of control of

the sailplane or glider.

DATES: Effective June 2, 1997.

ADDRESSES: This AD may be examined

at the Federal Aviation Administration

(FAA), Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket 92–CE–41–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.

J. Mike Kiesov, Project Officer,

Sailplanes/Gliders, Small Airplane

Directorate, Aircraft Certification

Service, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106; telephone

(816) 426–6932; facsimile (816) 426–

2169.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply Louis L’Hotellier S.A.

(L’Hotellier) ball and swivel joint quick

connectors was published in the

Federal Register on November 21, 1996

(61 FR 59203). The action proposed to

require the following actions for gliders

and sailplanes utilizing the L’Hotellier

ball and swivel joint quick connectors,

and that are not equipped with a

‘‘Uerling’’ sleeve or an LS-Safety sleeve:

—Enlarge the safety pin guide hole

diameter to a minimum of 1.2 mm

(0.05 in.) to accommodate a safety

wire or pin, as applicable.

—Fabricate a placard (using 1⁄8 inch

letters) with the following words:

‘‘All L’Hotellier control system

connectors must be secured with

safety wire, pins, or safety sleeves,

as applicable, prior to operation.’’

—Install this placard in the glider or

sailplane within the pilot’s clear view.

Interested persons have been 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.

The FAA’s Determination

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.

Cost Impact

The FAA estimates that 1,100

sailplanes and gliders, with an average

of 4 connectors per sailplane, in the U.S.

registry would be affected by this AD,

that it would take less than 4 workhours

per sailplane or glider to accomplish the

action (less than 1 workhour per

connector), and that the average labor

rate is approximately $60 an hour.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be $264,000. This cost is

figured for the estimated time it would

take for an authorized mechanic to

enlarge the safety pin guide hole

diameter. An owner/operator who holds

a private pilot’s certificate, as

authorized by sections 43.7 and 43.11 of

the Federal Aviation Regulations (14

CFR 43.7 and 43.11), can fabricate and

install the placard. This $264,000 figure

is based on the assumption that all of

the affected owners/operators of the

affected sailplanes and gliders do not

have the guide pin hole already

enlarged, a safety sleeve installed, or the

placard installed.

Compliance Time

The compliance time of this AD is in

calendar time instead of hours time-inservice (TIS). The average monthly

usage of the affected sailplanes and

gliders ranges throughout the fleet. For

example, one owner may operate the

sailplane or glider 25 hours in one

week, while another operator may

operate the sailplane or glider 25 hours

in one year. For this reason, the FAA

has determined that, in order to ensure

that all of the owners/operators of the

affected sailplanes and gliders

incorporate the required actions within

a reasonable amount of time, a calendar

compliance time is required.

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

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, 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 a new airworthiness directive

(AD) to read as follows:

97–08–06 Louis L’Hotellier, S.A. Ball and

Swivel Joint Quick Connectors:

Amendment 39–9994; Docket No. 92–

CE–41–AD.

Applicability: All quick connectors

installed in, but not limited to, the following

gliders and sailplanes that are not equipped

with a ‘‘Uerling’’ sleeve or an LS-Safety

sleeve:
Federal Register / Vol. 62, No. 69 / Thursday, April 10, 1997 / Rules and Regulations 17539

Manufacturer Models

Alexander Schleicher .......... ASK21, ASK23, ASW12, ASW15, ASW15B, ASW17, ASW19, ASW19B, ASW24, ASW24B, AS12, AS–K13, AS–

K13, Ka 6, Ka 6 B, Ka 6 BR, Ka 6 C, Ka 6 CR, Ka 6 CR–Pe, Ka 6 E, K7, Ka2B, K 8, K 8 B, and Rhonlerche II.

Centrair, S.N ....................... 101, 101A, 101P, 101AP, and 201B.

Eiravion ............................... PIK 20, PIK 20B, and PIK 20D.

Glaser Dirks ........................ DG100, DG400, and DG–500M.

Burkhart Grob ..................... G102 Astir CS, G102 Club Astir III, G102 Club Astir IIIb, G102 Standard Astir III, G102, G103 Twin Astir, G103

Twin II, G103A Twin II Acro, G103C Twin III Acro, G103C Twin III SL, G109, and G109B.

Intreprinderea ICA (Lark) .... IS–28B2 and IS–29D2.

Rolladen Schneider ............ LS1–f and LS3–a.

Schempp-Hirth .................... Cirrus, Std Cirrus, Nimbus 2, Nimbus 2B, Mini-Nimbus HS–7, Mini-Nimbus B, Janus, Discus a, Duo-Discus, Standard Austria-S, Standard Austria-SH, Standard Austria-SH1, Ventus, Ventus-a, and Ventus-a/16.6.

Schweizer ........................... 2–33 and 1–26.

Note 1: This AD applies to the product

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

the product that has 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 (d) 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 within the next 30

calendar days after the effective date of this

AD, or upon installation of the quick

connectors, whichever occurs later, unless

already accomplished.

To prevent the quick connectors from

becoming inadvertently disconnected, which

could result in loss of control of the sailplane

or glider, accomplish the following:

(a) For quick connectors that have a safety

pin guide hole, enlarge the hole in the lock

plate to a minimum diameter of 1.2 mm (0.05

in.) to accommodate a safety wire or pin.

(b) Fabricate and install a placard (using 1/

8 inch letters) in the glider or sailplane,

within the pilot’s clear view, with the

following words: ‘‘All L’Hotellier control

system connectors must be secured with

safety wire, pins, or safety sleeves, as

applicable, prior to operation.’’

(c) Fabricating and installing the placard as

required by paragraph (b) of 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 sailplane’s or glider’s records

showing compliance with this AD in

accordance with section 43.9 of the Federal

Aviation Regulations.

(d) An alternative method of compliance or

adjustment of the compliance times 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 Small Airplane Directorate.

(e) Copies of this AD 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.

(f) This amendment (39–9994) becomes

effective on June 2, 1997.

Issued in Kansas City, Missouri, on April

2, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–9164 Filed 4–9–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 97

[Docket No. 28882; Amdt. No. 1792]

RIN 2120–AA65

Standard Instrument Approach

Procedures; Miscellaneous

Amendments

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment establishes,

amends, suspends, or revokes Standard

Instrument Approach Procedures

(SIAPs) for operations at certain

airports. These regulatory actions are

needed because of the adoption of new

or revised criteria, or because of changes

occurring in the National Airspace

System, such as the commissioning of

new navigational facilities, addition of

new obstacles, or changes in air traffic

requirements. These changes are

designed to provide safe and efficient

use of the navigable airspace and to

promote safe flight operations under

instrument flight rules at the affected

airports.

DATES: An effective date for each SIAP

is specified in the amendatory

provisions.

Incorporation by reference-approved

by the Director of the Federal Register

on December 31, 1980, and reapproved

as of January 1, 1982.

ADDRESSES: Availability of matters

incorporated by reference in the

amendment is as follows:

For Examination

1. FAA Rules Docket, FAA

Headquarters Building, 800

Independence Avenue, SW.,

Washington, DC 20591;

2. The FAA Regional Office of the

region in which the affected airport is

located; or

3. The Flight Inspection Area Office

which originated the SIAP.

For Purchase

Individual SIAP copies may be

obtained from:

1. FAA Public Inquiry Center (APA–

200), FAA Headquarters Building, 800

Independence Avenue, SW.,

Washington, DC 20591; or

2. The FAA Regional Office of the

region in which the affected airport is

located.

By Subscription

Copies of all SIAPs, mailed once

every 2 weeks, are for sale by the

Superintendent of Documents, U.S.

Government Printing Office,

Washington, DC 20402.

FOR FURTHER INFORMATION CONTACT:

Paul J. Best, Flight Procedures

Standards Branch (AFS–420), Technical

Programs Division, Flight Standards

Service, Federal Aviation

Administration, 800 Independence

Avenue, SW., Washington, DC 20591;

telephone (202) 267–8277.

SUPPLEMENTARY INFORMATION: This

amendment to part 97 of the Federal

Aviation Regulations (14 CFR part 97)

establishes, amends, suspends, or

revokes Standard Instrument Approach

Procedures (SIAPs). The complete