Federal Register / Vol. 61, No. 109 / Wednesday, June 5, 1996 / Rules and Regulations 28497

Dated at Rockville, MD, this 29th day of

May, 1996.

For the Nuclear Regulatory Commission.

John C. Hoyle,

Secretary of the Commission.

[FR Doc. 96–13874 Filed 6–4–96; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–161–AD; Amendment

39–9644; AD 96–12–02]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2 and B4 Series Airplanes,

Excluding Model 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

A300 B2 and B4 series airplanes, that

requires measurements of the thickness

of the inner skin of the longitudinal lap

joint from the inside of the fuselage at

certain stringers. This amendment also

requires inspections to detect stress

corrosion cracking in the subject area,

and repair, if necessary. This

amendment is prompted by reports of

stress corrosion cracking found in the

skin at the longitudinal lap joint at

certain stringers of the fuselage, which

was caused by the increased stress level

in the subject area when it was

reworked beyond certain limits. The

actions specified by this AD are

intended to prevent such stress

corrosion cracking which, if not

detected and corrected in a timely

manner, could result in rapid

depressurization of the airplane.

DATES: Effective July 10, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 10,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; 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 A300 B2 and B4 series airplanes

was published in the Federal Register

on February 28, 1996 (61 FR 7444). That

action proposed to require

measurements of the thickness of the

inner skin of the longitudinal lap joint

from the inside of the fuselage at certain

stringers using the ultrasonic thickness

measurement method. That action also

proposed to require high frequency

eddy current (HFEC) inspections to

detect cracking in the subject area, and

repair, if necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Support for the Proposal

Both commenters support the

proposed rule.

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 17 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 32

work hours 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 $32,640, or $1,920 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:

96–12–02 Airbus Industrie: Amendment 39–

9644. Docket 95–NM–161–AD.

Applicability: Model A300 B2 and B4

series airplanes, manufacturer serial numbers

003 through 156 inclusive; on which Airbus

Modification 2611 has not been installed;

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 (c) 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
28498 Federal Register / Vol. 61, No. 109 / Wednesday, June 5, 1996 / Rules and Regulations

been eliminated, the request should include

specific proposed actions to address it.

Note 2: Model A300–600 series airplanes

are not subject to the requirements of this

AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent stress corrosion cracking in the

longitudinal lap joints of the fuselage, which

could result in rapid depressurization of the

airplane, accomplish the following:

Note 3: Any of the inspections and

measurements required by this AD that were

performed before the effective date of this AD

in accordance with Airbus All Operator

Telex (AOT) 53–05 (original issue), dated

August 16, 1995, are considered acceptable

for compliance with the applicable

requirements of this AD.

(a) Within 60 days after the effective date

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

(a)(2) of this AD in accordance with Airbus

All Operator Telex (AOT) 53–05, Revision 1,

dated August 16, 1993.

(1) Measure the thickness of the inner skin

of the longitudinal lap joint from the inside

of the fuselage at stringer 57 between frames

65 and 72 using the ultrasonic thickness

measurement method, in accordance with the

AOT. If the thickness is less than or equal to

the limits specified in the AOT, prior to

further flight, repair the longitudinal lap joint

in accordance with a method approved by

the Manager, Standardization Branch, ANM–

113, FAA, Transport Airplane Directorate.

(2) Perform a high frequency eddy current

(HFEC) inspection to detect cracking of the

longitudinal lap joint at stringer 57 between

frames 65 and 72, in accordance with the

AOT. If any cracking is detected, prior to

further flight, repair the longitudinal lap joint

in accordance with a method approved by

the Manager, Standardization Branch, ANM–

113.

(b) Within 6 months after the effective date

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

(b)(2) of this AD in accordance with Airbus

AOT 53–05, Revision 1, dated August 16,

1993.

(1) Measure the thickness of the inner skin

of the longitudinal lap joint from the inside

of the fuselage at stringer 52 (left-and righthand) between frames 58 and 65 using the

ultrasonic thickness measurement method, in

accordance with the AOT. If the thickness is

less than or equal to the limits specified in

the AOT, prior to further flight, repair the

longitudinal lap joint in accordance with a

method approved by the Manager,

Standardization Branch, ANM–113.

(2) Perform a HFEC inspection to detect

cracking of the longitudinal lap joint at

stringer 52 (left- and right-hand) between

frames 58 and 65, in accordance with the

AOT. If any cracking is detected, prior to

further flight, repair the longitudinal lap joint

in accordance with a method approved by

the Manager, Standardization Branch, ANM–

113.

(c) 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.

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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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) The measurements and inspections

shall be done in accordance with Airbus All

Operator Telex (AOT) 53–05, Revision 1,

dated August 16, 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 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.

(f) This amendment becomes effective on

July 10, 1996.

Issued in Renton, Washington, on May 28,

1996.

Bill R. Boxwell,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–13798 Filed 6–4–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–133–AD; Amendment

39–9643; AD 96–12–01]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Jetstream Model

4101 airplanes, that requires

replacement of the flexible cables of the

power and condition controls of the

engines with new flexible cables. This

amendment also requires installation of

protective tape on the outside case of

these flexible cables, and

reidentification of the cables. This

amendment is prompted by reports of

stiff operation of the power and

condition controls of the engines due to

heat damage to and moisture

contamination of the flexible cable. The

actions specified by this AD are

intended to prevent heat damage and

moisture contamination to the flexible

cable, which could result in stiff

operation of the power and condition

controls and subsequent reduced engine

control.

DATES: Effective July 10, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 10,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Jetstream Aircraft, Inc., P.O. Box

16029, Dulles International Airport,

Washington, DC 20041–6029. 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:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; 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 Jetstream

Model 4101 airplanes was published in

the Federal Register on December 19,

1995 (60 FR 65258). That action

proposed to require replacement of the

flexible cables of power and condition

controls of the engines with new

flexible cables. The action also proposed

to require installation of protective tape

on the outside case of the new flexible

cables of the power and condition

controls of the engines, and

reidentification of the assembly number

of the cable.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Request to Provide Additional

Terminating Action

One commenter requests that the FAA

revise the proposal to require the

accomplishment of the actions

described in Jetstream Service Bulletin

J41–76–013 () (Modification JM41485A),

as interim action only. The commenter

states that the flexible cables associated

with the proposed action have a life

limit of 6,000 hours time-in-service, and

have not demonstrated reliability

warranting an escalation of this limit.

Instead, the commenter requests that the

proposal be revised to include a