Federal Register / Vol. 60, No. 237 / Monday, December 11, 1995 / Rules and Regulations 63411

the rules governing the assessment of

institutions insured by the FDIC; and

Whereas, paragraph 327.9(c)(1) of title

12 of the C.F.R. prescribes the

assessment rate schedule applicable to

members insured by the SAIF; and

Whereas, based upon its semiannual

review of the SAIF capitalization

schedule and assessment rates for SAIFinsured institutions, the Board finds

that it is appropriate to retain the

existing assessment rate schedule

applicable to members of the SAIF with

the result that the SAIF assessment rates

to be paid by depository institutions

whose deposits are subject to

assessment by the SAIF will continue to

range from 23 cents per $100 of

assessable deposits to 31 cents per $100

of assessable deposits, depending on

risk classification.

Now, therefore, be it resolved, that the

existing assessment rate schedule

applicable to members of the SAIF shall

be retained for the first semiannual

assessment period of 1996 from January

1, 1996, through June 30, 1996.

Be it further resolved, that the Board

hereby directs the Executive Secretary,

or his designee, to cause the

aforementioned Federal Register notice

document to be published in the

Federal Register in a form and manner

satisfactory to the Executive Secretary,

or his designee, and the General

Counsel, or his designee.

By the order of the Board of Directors.

Dated at Washington, D.C., this 14th day of

November, 1995.

Federal Deposit Insurance Corporation.

Robert E. Feldman,

Deputy Executive Secretary.

[FR Doc. 95–28720 Filed 12–8–95; 8:45 am]

BILLING CODE 6714–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–CE–26–AD; Amendment 39–

9442; AD 95–24–12]

Airworthiness Directives; Jetstream

Aircraft Limited Model 3201 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Jetstream Aircraft Limited

(JAL) Model 3201 airplanes. This action

requires repetitively inspecting the main

landing gear (MLG) bay forward lower

edge wing skin structure for cracks,

replacing any cracked doubler with a

joggled doubler of improved design to

reinforce the area and prevent future

cracking, and eventually incorporating

these doublers on all affected airplanes.

Cracking found at the MLG bay forward

lower edge wing skin structure during

fatigue testing of the JAL Model 3201

prompted this action. The actions

specified by this AD are intended to

prevent the MLG bay forward lower

edge wing skin structure from cracking,

which, if not detected and corrected,

could cause failure of the wing structure

and loss of control of the airplane.

DATES: Effective January 17, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 17,

1996.

ADDRESSES: Service information that

applies to this AD may be obtained from

Jetstream Aircraft Limited, Prestwick

International Airport, Ayrshire, KA9

2RW, Scotland, telephone (44–292)

79888; facsimile (44–292) 79703; or

Jetstream Aircraft Inc., Librarian, P.O.

Box 16029, Dulles International Airport,

Washington DC 20041–6029; telephone

(703) 406–1161; facsimile (703) 406–

1469. This information may also be

examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket 95–CE–26–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: Ms.

Dorenda Baker, Program Officer,

Brussels Aircraft Certification Office,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322)

508.2715; facsimile (322) 230.6899; or

Mr. Sam Lovell, Project Officer, 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

Jetstream Aircraft Limited (JAL) Model

3201 airplanes was published in the

Federal Register on August 14, 1995 (60

FR 41868). The action proposed to

require repetitively inspecting the main

landing gear (MLG) bay forward lower

edge wing skin structure for cracks,

replacing any cracked doubler with a

joggled doubler of improved design to

reinforce the area and prevent future

cracking, and eventually incorporating

these doublers on all affected airplanes.

Accomplishment of the proposed action

would be in accordance with Jetstream

Service Bulletin (SB) 57–A–JA920540;

Original Issue September 1, 1992.

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.

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 134 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

35 workhours per airplane to

accomplish the required action, and that

the average labor rate is approximately

$60 an hour. Parts will be provided by

the manufacturer at no cost to the

owners/operators. Based on these

figures, the total cost impact of this AD

on U.S. operators is estimated to be

$281,400. This figure is based on the

assumption that all of the affected

airplanes do not have the new joggled

doublers installed and that none of the

owners/operators of the affected

airplanes have replaced the doublers.

The FAA has no way of determining the

number of repetitive inspections an

owner/operator may incur.

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
63412 Federal Register / Vol. 60, No. 237 / Monday, December 11, 1995 / Rules and Regulations

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. 106(g), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

AD No. 95–24–12. Jetstream Aircraft

Limited: Amendment 39–9442; Docket

No. 95–CE–26–AD.

Applicability: Model 3201 Airplanes (all

serial numbers), 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 (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 the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated in the

body of this AD, unless already

accomplished.

To prevent the main landing gear (MLG)

bay forward lower edge wing skin structure

from cracking, which, if not detected and

corrected, could cause failure of the wing

structure and loss of control of the airplane,

accomplish the following:

(a) Upon accumulating 4,000 hours timein-service (TIS) or within the next 200 hours

TIS after the effective date of this AD,

whichever occurs later, inspect the MLG bay

forward lower edge wing skin structure

adjacent to the main spar for cracks in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Jetstream Service

Bulletin (SB) 57–A–JA920540, Original Issue

September 1, 1992.

(1) If cracks are found, prior to further

flight, replace the existing doublers with

joggled doublers of improved design in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Jetstream SB 57–

A–JA920540, Original Issue September 1,

1992.

(2) If no cracks are found, re-inspect the

MLG bay forward lower edge wing skin

structure at intervals not to exceed 600 hours

TIS until modified as specified in paragraph

(b) of this AD.

(b) Upon accumulating 9,000 hours TIS or

within the next 200 hours TIS after the

effective date of this AD, whichever occurs

later, unless already accomplished as

specified in paragraph (a)(1) of this AD,

replace the existing doublers with joggled

doublers of improved design in accordance

with the ACCOMPLISHMENT

INSTRUCTIONS section of Jetstream SB 57–

A–JA920540.

(c) Replacing the joggled doublers as

required by paragraph (a)(1) or (b) of this AD

eliminates the repetitive inspection

requirements of this AD.

(d) 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.

(e) 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, Brussels Aircraft Certification

Office, FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Brussels Aircraft Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels Aircraft

Certification Office.

(f) The inspection and modification

required by this AD shall be done in

accordance with SB 57–A–JA920540,

Original Issue September 1, 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

Jetstream Aircraft Limited, Prestwick

International Airport, Ayrshire, KA9 2RW,

Scotland; or Jetstream Aircraft Inc., Librarian,

P.O. Box 16029, Dulles International Airport,

Washington DC 20041–6029. 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., 7th Floor, suite

700, Washington, DC.

(g) This amendment (39–9442) becomes

effective on January 9, 1996.

Issued in Kansas City, Missouri, on

November 17, 1995.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–30133 Filed 12–8–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–145–AD; Amendment

39–9455; AD 95–25–09]

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A310 and A300–600 series airplanes,

that requires that certain flight control

computers be modified so that the

autopilot will disengage when the

airplane is in the ‘‘go-around’’ mode

under certain conditions. This

amendment is prompted by an accident

in which the flight crew may have

initiated an inadvertent go-around

which, following several subsequent

actions by the crew and automated

system, placed the airplane in a severe

out-of-trim condition. The actions

specified by this AD are intended to

prevent an out-of-trim condition

between the trimmable horizontal

stabilizer and the elevator, which may

severely reduce controllability of the

airplane.

EFFECTIVE DATE: Effective January 10,

1996.

ADDRESSES: Information concerning this

AD may be obtained from or examined

at the Federal Aviation Administration

(FAA), Transport Airplane Directorate,

Rules Docket, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

FOR FURTHER INFORMATION CONTACT:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2589; fax (206) 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 Airbus

Model A310 and A300–600 series

airplanes was published in the Federal

Register on October 17, 1994 (59 FR

52273). That action proposed to require

modification of flight control computers

(FCC’s) having part numbers (P/N’s)

B216ABM6, B350AAM1, B350AAM2,

and B350AAM3 (for Model A310 series

airplanes); and P/N’s B297AAM3,

B297AAM4, and B297AAM5 (for Model

A300–600 series airplanes).

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due