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

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, floorcovering, 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.

### 50253 Federal Register / Vol. 62, No. 186 / Thursday, September 25, 1997 / Rules and Regulations

(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