### 33014 Federal Register / Vol. 66, No. 119 / Wednesday, June 20, 2001 / Rules and Regulations

Conclusion

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact

There are approximately 124 Model Hawker 800XP series airplanes of the affected design in the worldwide fleet. The FAA estimates that 87 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 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 $10,440, or $120 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. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. Regulatory Impact

The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.

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: 2001–12–17 Raytheon Aircraft Company: Amendment 39

– 12273. Docket 2000

– NM

– 176

–AD. Applicability: Model Hawker 800XP series airplanes, certificated in any category, having the following serial numbers 258266, and 258277 through 258399 inclusive.

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 (b) 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 of the fuselage skin, and consequent loss of cabin pressurization, accomplish the following: Inspection and Corrective Action

(a) Within 600 flight hours or 12 months after the effective date of this AD, whichever occurs first: Do a one-time detailed visual inspection to confirm the installation of rivets at fuselage stations 251.975, 262.35, 272.725, and 283.10. Do the inspection per the Accomplishment Instructions of Raytheon Service Bulletin 51

– 3336, Revision 1, dated January 2001. If any rivet is missing, before further flight, install a new rivet per the Accomplishment Instructions of the service bulletin.

Note 2: Accomplishment of the actions in accordance with Raytheon Service Bulletin 51

– 3336, dated May 2000, is acceptable for compliance with the requirements of paragraph (a) of this AD.
Alternative Methods of Compliance

(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, Wichita Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.

Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO.
Special Flight Permits

(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. Incorporation by Reference

(d) The actions shall be done in accordance with Raytheon Service Bulletin 51

– 3336, Revision 1, dated January 2001. 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 Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 67201

– 0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Effective Date

(e) This amendment becomes effective on July 25, 2001.

Issued in Renton, Washington, on June 11, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01

– 15211 Filed 6

– 19

– 01; 8:45 am]

BILLING CODE 4910

– 13

– P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39
[Docket No. 2000

– NM

–262

–AD; Amendment 39

– 12274; AD 2001

– 12

– 18]

RIN 2120

–AA64
Airworthiness Directives; Construcciones Aeronauticas, S.A. (CASA), Model CN

–235 Series Airplanes

AGENCY : Federal Aviation Administration, DOT.

ACTION : Final rule.

SUMMARY : This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN

–


### 33015 Federal Register / Vol. 66, No. 119 / Wednesday, June 20, 2001 / Rules and Regulations

235 series airplanes, that requires modification of the rigging of the engine control cable assembly and replacement of either the entire engine control cable assembly or a segment of the control cables. This amendment is prompted by issuance of mandatory continuing airworthiness information issued by a foreign airworthiness authority. The actions specified by this AD are intended to prevent fatigue of the engine control cables, leading to breakage of the cables, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.

DATES : Effective July 25, 2001.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 25, 2001.

ADDRESSES : The service information referenced in this AD may be obtained from Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. 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 : Dan Rodina, Aerospace Engineer, ANM

– 116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055

– 4056; telephone (425) 227

– 2125; 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 CASA Model CN

– 235 series airplanes was published in the Federal Register on March 19, 2001 (66 FR 15363). That action proposed to require modification of the rigging of the engine control cable assembly and replacement of either the entire engine control cable assembly or a segment of the control cables.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA ’ s determination of the cost to the public.

Conclusion

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 2 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per airplane to accomplish the required modification, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the required modification on U.S. operators is estimated to be $960, or $480 per airplane.

The FAA estimates that it will take approximately 47 work hours per airplane to accomplish the required replacement of either the engine control cable assembly or a segment of the control cables, and that the average labor rate is $60 per work hour. Required parts will cost approximately $1,444 per airplane. Based on these figures, the cost impact of the required modification on U.S. operators is estimated to be $8,528, or $4,264 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. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. Regulatory Impact

The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.

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:

2001

– 12

– 18 Construcciones Aeronauticas, S.A. (CASA): Amendment 39

– 12274. Docket 2000

–NM

– 262

–AD. Applicability: Model CN

– 235 series airplanes, serial numbers C001 to C074, 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 been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue of the engine control cables, leading to breakage of the engine control cables, which could result in reduced controllability of the airplane, accomplish the following:
Modification

(a) Within 15 days after the effective date of this AD: Rig the power lever and condition lever control stops, in accordance with CASA COM 235

– 140, Revision 01, dated March 21, 2000. Replacement

(b) Prior to the accumulation of 12,000 total flight cycles or within 6 months after the effective date of this AD, whichever occurs later: Replace either the entire engine control cable assembly (part number 7

– 44728

– 12) with a new assembly or replace a segment of the control cable (part number


### 33016 Federal Register / Vol. 66, No. 119 / Wednesday, June 20, 2001 / Rules and Regulations

72830

– 20) with a new segment, in accordance with CASA COM 235

– 140, Revision 01, dated March 21, 2000. Alternative Methods of Compliance

(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, International Branch, ANM

– 116, Transport Airplane Directorate, FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM

– 116.

Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM

– 116. Special Flight Permits

(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. Incorporation by Reference

(e) The actions shall be done in accordance with CASA COM 235

– 140, Revision 01, dated March 21, 2000. 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. 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.

Note 3: The subject of this AD is addressed in Spanish airworthiness directive 03/00, dated March 2000.

Effective Date

(f) This amendment becomes effective on July 25, 2001.

Issued in Renton, Washington, on June 11, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01

– 15210 Filed 6

– 19

– 01; 8:45 am]

BILLING CODE 4910

– 13

– P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39
[Docket No. 2000

– NM

– 320

–AD; Amendment 39

– 12269; AD 2001

– 12

– 14]

RIN 2120

–AA64
Airworthiness Directives; Boeing Model 747

– 400 Series Airplanes

AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule.

SUMMARY : This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747

– 400 series airplanes, that requires an inspection to detect miswiring of diodes in the heating system of the pitot static probes, and corrective action, if necessary. The actions specified by this AD are intended to prevent reduced power to the heating system of the pitot static probes, leading to ice accumulation on the pitot static probes, which could result in erroneous airspeed or altitude indications to the flight crew, and consequent reduced operational safety in all phases of flight. This action is intended to address the identified unsafe condition.
DATES : Effective July 25, 2001.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 25, 2001.

ADDRESSES : The service information referenced in this AD may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124

– 2207. 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 : Don Eiford, Aerospace Engineer, Systems and Equipment Branch, ANM

– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055

– 4056; telephone (425) 227

– 2788; fax (425) 227

– 1181.
SUPPLEMENTARY INFORMATION : A Notice of Proposed Rulemaking (NPRM) to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) applicable to certain Boeing Model 747

– 400 series airplanes was published in the Federal Register on February 21, 2001 (66 FR 10972). That action proposed to require an inspection to detect miswiring of diodes in the heating system of the pitot static probes, and corrective action, if necessary. Editorial Change

The compliance time for rewiring of any miswiring, detected during the special detailed inspection required by paragraph (a) of this AD, was inadvertently omitted. Paragraph (a) of this AD has been changed to require rewiring of any miswiring prior to further flight. Comments 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 with the change described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of this AD. Cost Impact

There are approximately 497 Model 747

– 400 series airplanes of the affected design in the worldwide fleet. The FAA estimates that 69 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 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 $8,280, or $120 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. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. Regulatory Impact

The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.

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)