Federal Register / Vol. 62, No. 186 / Thursday, September 25, 1997 / Rules and Regulations 50251

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:

97–20–06 Saab Aircraft AB: Amendment

39–10144. Docket 96–NM–213–AD.

Applicability: Model SAAB 2000 series

airplanes, serial numbers –004 through –039

inclusive, on which Saab Modification No.

5780, as specified in Saab Service Bulletin

2000–53–020, Revision 02, dated October 18,

1996, has not been accomplished; certificated

in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent short circuiting between the

floormat heater and the floor panel, which

could cause overheating of the floormat

heater and lead to smoke or fire in the

airplane cabin, accomplish the following:

(a) Within 14 days after the effective date

of the AD, deactivate the flight attendant’s

floormat heater by either disconnecting

electrical cable HW71–20 between the

floormat heater and the floor panel, or by

removing fuse 17HW (1) on panel 306VU, in

accordance with Saab Service Bulletin 2000–

A25–022, Revision 01, dated January 23,

1996.

(b) Installation of a floormat heater, floor

covering, and a new floor panel made of nonconductive material, in accordance with Saab

Service Bulletin 2000–53–020, Revision 02,

dated October 18, 1996, constitutes

terminating action for the deactivation

required by paragraph (a) of this AD.

(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 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.

(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 modification shall be done in

accordance with Saab Service Bulletin 2000–

A25–022, Revision 01, dated January 23,

1996. 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 SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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

October 30, 1997.

Issued in Renton, Washington, on

September 17, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–25166 Filed 9–24–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–170–AD; Amendment

39–10145; AD 97–20–07]

RIN 2120–AA64

Airworthiness Directives; Airbus 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

A300–600 series airplanes, that requires

repetitive inspections to detect fatigue

cracking in the left and right wings in

the area where the top skin attaches to

the center spar; and repair or

modification of this area, if necessary.

This amendment is prompted by a

report from the manufacturer indicating

that, during full-scale fatigue testing of

the airframe, fatigue cracking was

detected in this area. The actions

specified by this AD are intended to

detect and correct this cracking, which

could reduce the residual strength of the

top skin of the wings, and consequently

affect the structural integrity of the

airframe.

DATES: Effective October 30, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of October 30,

1997.

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:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2589; 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 Airbus

Model A300–600 series airplanes was

published in the Federal Register on
50252 Federal Register / Vol. 62, No. 186 / Thursday, September 25, 1997 / Rules and Regulations

May 1, 1997 (62 FR 23697). That action

proposed to require repetitive

inspections to detect fatigue cracking in

the left and right wings in the area

where the top skin attaches to the center

spar between ribs 1 and 7; and repair or

modification of this area, if necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment 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 35 Airbus

Model A300–600 series airplanes of U.S.

registry will be affected by this AD.

For airplanes on which Airbus

Modification 10089 has not been

installed, it will take approximately 2

work hours to accomplish each detailed

visual inspection or 3 work hours to

accomplish each high frequency eddy

current (HFEC) inspection. The average

labor rate is $60 per work hour. Based

on these figures, the cost impact of each

inspection on U.S. operators is

estimated to be either $120 or $180 per

airplane, depending on the type of

inspection conducted.

For airplanes on which Airbus

Modification 10089 has been installed,

it will take approximately 3 work hours

to accomplish each low frequency eddy

current inspection. The average labor

rate is $60 per work hour. Based on

these figures, the cost impact of the each

inspection on U.S. operators is

estimated to be $180 per airplane.

The cost impact figures discussed

above are 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:

97–20–07 Airbus: Amendment 39–10145.

Docket 96–NM–170–AD.

Applicability: Model A300–600 series

airplanes on which Airbus Modification

10160 has not been installed during

production; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct fatigue cracking in

the left and right wings in the area where the

top skin attaches to the center spar, which

could reduce the residual strength of this

skin, and consequently affect the structural

integrity of the airframe, accomplish the

following:

(a) For airplanes on which Airbus

Modification 10089 has not been installed:

Prior to the accumulation of 18,000 total

landings, or within 1,500 landings after the

effective date of this AD, whichever occurs

later, conduct either a detailed visual

inspection or a high frequency eddy current

(HFEC) inspection to detect fatigue cracking

in the left and right wings in the area where

the top skin attaches to the center spar

between ribs 1 and 7, in accordance with

Airbus Service Bulletin A300–57–6044,

Revision 2, dated September 6, 1995,

including Appendix 1.

(1) If no cracking is detected, conduct

repetitive inspections thereafter at the

following intervals:

(i) If the immediately preceding inspection

was conducted using detailed visual

techniques, conduct the next inspection

within 5,000 landings.

(ii) If the immediately preceding inspection

was conducted using HFEC techniques,

conduct the next inspection within 9,500

landings.

(2) If any cracking is detected or suspected

during any detailed visual inspection

required by paragraph (a), (a)(1), or (a)(3)(i)

of this AD, prior to further flight, confirm this

finding and the length of this cracking by

conducting a HFEC inspection, in accordance

with the service bulletin. If no cracking is

confirmed during the HFEC inspection,

accomplish the repetitive inspection required

by paragraph (a)(1)(ii) of this AD at the time

specified in that paragraph.

(3) If any cracking is detected or confirmed

during any HFEC inspection required by

paragraph (a), (a)(1), or (a)(2) of this AD:

(i) If the cracking is 75 mm or less per rib

bay, prior to further flight, repair in

accordance with the service bulletin.

Thereafter, conduct repetitive detailed visual

inspections of the repaired area at intervals

not to exceed 50 landings, in accordance

with the service bulletin.

(ii) If the cracking exceeds 75 mm per rib

bay, prior to further flight, install Airbus

Modification 10089, in accordance with the

service bulletin. Thereafter, conduct a low

frequency eddy current inspection in

accordance with the requirements of

paragraph (b) of this AD.

Note 2: The Airbus service bulletin

references Airbus Service Bulletin A300–57–

6041, Revision 4, dated November 16, 1995,

as an additional source of service information

for installing Airbus Modification 10089.

(b) For airplanes on which Airbus

Modification 10089 has been installed: Prior

to the accumulation of 22,000 total landings

after this modification has been installed, or

within 1,500 landings after the effective date

of this AD, whichever occurs later, conduct

a low frequency eddy current inspection to

detect fatigue cracking in the inboard and

rear edges of the top skin reinforcing plates,

in accordance with Airbus Service Bulletin

A300–57–6044, Revision 2, dated September

6, 1995, including Appendix 1.

(1) If no cracking is detected, repeat this

inspection thereafter at intervals not to

exceed 11,000 landings.
Federal Register / Vol. 62, No. 186 / Thursday, September 25, 1997 / Rules and Regulations 50253

(2) If any cracking is detected, prior to

further flight, repair in accordance with a

method approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Thereafter,

repeat this inspection at intervals not to

exceed 11,000 landings.

(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, 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 3: 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 inspections and installation shall

be done in accordance with Airbus Service

Bulletin A300–57–6044, Revision 2, dated

September 6, 1995, including Appendix 1,

which contains the specified effective pages:

Page number

shown on

page

Revision

level

shown on

page

Date shown on

page

1–8 ............... 2 .............. Sept. 6, 1995.

9, 10 ............. Original .... Mar. 1, 1993.

Appendix 1

1 ................... 1 .............. Nov. 25, 1994.

2–6 ............... Original .... Mar. 1, 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

October 30, 1997.

Issued in Renton, Washington, on

September 17, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–25164 Filed 9–24–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Coast Guard

33 CFR Part 117

[CGD13–97–026]

Drawbridge Operation Regulations;

Columbia River, OR

AGENCY: Coast Guard, DOT.

ACTION: Notice of temporary deviation.

SUMMARY: Notice is hereby given that

the Coast Guard has issued a temporary

deviation to the regulations governing

the operation of the twin, Interstate 5,

drawbridges across the Columbia River,

mile 105.6, between Vancouver,

Washington and Portland, Oregon. The

draws of the two bridges need not open

for the passage of vessels from midnight,

September 15 through midnight,

October 7, 1997, to accommodate the

replacement of a defective part in the

lift machinery.

EFFECTIVE DATES: The period of

deviation begins at midnight September

15 and ends at midnight October 7,

1997.

FOR FURTHER INFORMATION CONTACT: Mr.

John E. Mikesell, Chief, Plans and

Programs Section, Thirteenth Coast

Guard District. Telephone number (206)

220–7270.

SUPPLEMENTARY INFORMATION: A recent

survey of the operating machinery of the

twin Interstate 5 Bridges across the

Columbia River revealed serious defects

in the trunion shafts of the lift

mechanism. The shafts require

immediate replacement to insure the

continued safe operation of the lift

spans. During the closure period, low

water conditions will allow for the

passage of most commercial navigation

through an alternate high level fixed

span at midriver.

The District Commander has

authorized a temporary deviation from

the operation regulations from

midnight, September 15, through

midnight, October 7, 1997, during

which the draws of the twin Interstate

5 bridges across the Columbia River

need not open for the passage of vessels,

while repairs are being made to the

draw machinery. A concurrent action by

the Coast Guard Captain of The Port

establishes an Exclusionary Zone which

restricts the entry of vessels into the

area around the drawspans.

This deviation from normal operating

regulations (33 CFR 117.869) is

authorized in accordance with the

provisions of Title 33 of the Code of

Federal Regulations, § 117.35.

Dated: September 9, 1997.

J. David Spade,

Rear Admiral, U.S. Coast Guard, Commander,

13th Coast Guard District.

[FR Doc. 97–25371 Filed 9–24–97; 8:45 am]

BILLING CODE 4910–14–M

LIBRARY OF CONGRESS

36 CFR Part 703

[Docket No. LOC 97–2]

Availability of Library of Congress

Records

AGENCY: Library of Congress.

ACTION: Final regulation.

SUMMARY: The Library of Congress

issues this final regulation to revise

Library of Congress Regulation 1917–3

(see 36 CFR 703.1 et seq.). The revised

regulation will reflect the renaming and

organizational restructuring of the

responsible division from Central

Services to Office Systems Services, an

increase in the number of disclosure

exemptions, a new definitional section

for the types of records covered under

the Regulation, and increased fees and

charges for processing record requests.

Access to Library records, including

those in the LC Archives and exclusive

of materials in the collections, must be

made through the Chief, Office Systems

Services.

EFFECTIVE DATE: September 25, 1997.

FOR FURTHER INFORMATION CONTACT:

Lana Kay Jones, Acting General

Counsel, Office of the General Counsel,

Library of Congress, Washington, D.C.

20540–1050. Telephone No. (202) 707–

6316.

SUPPLEMENTARY INFORMATION: This

Regulation implements the policy of the

Library with respect to the public

availability of Library of Congress

records. Although the Library is not

subject to the Freedom of Information

Act, as amended (5 U.S.C. § 552), this

Regulation follows the spirit of that Act

consistent with the Library’s duties,

functions, and responsibilities to the

Congress. The application of that Act to

the Library is not to be inferred, nor

should this Regulation be considered as

conferring on any member of the public

a right under that Act of access to or

information from the records of the

Library. Nothing in this Regulation

modifies current instructions and

practices in the Library with respect to

handling Congressional correspondence.

The Copyright Office, although a

service unit of the Library, is by law (17

U.S.C. § 701) subject to the provisions of

the Freedom of Information Act, as