### 6855 Federal Register / Vol. 67, No. 31 / Thursday, February 14, 2002 / Rules and Regulations 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. Does This AD Involve a Significant Rule or Regulatory Action?

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 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, under 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. FAA amends § 39.13 by adding a new AD to read as follows: 2002
– 03
– 03 Socata

— Groupe Aerospatiale: Amendment 39

– 12644; Docket No. 2001

– CE

– 10

–AD. (a) What airplanes are affected by this AD? This AD affects Model TBM 700 airplanes, serial numbers 1 through 164, that are certificated in any category.

(b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraph (a) of this AD must comply with this AD.

(c) What problem does this AD address? The actions specified by this AD are intended to prevent water from accumulating in the fuselage, then freezing and interfering with or causing the elevator controls to seize. This could result in loss of elevator control with consequent loss of airplane control.

(d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following: Actions Compliance Procedures Incorporate Kit No. OPT70 K072

– 53 ................. Within the next 3 months after March 29, 2002 (the effective date of this AD), unless already accomplished. In accordance with the Technical Instructions supplied with Kit No. OPT70 K072

– 53, as specified in Socata Service Bulletin SB 70

– 082 53, dated June 2000.
(e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if:

(1) Your alternative method of compliance provides an equivalent level of safety; and

(2) The Manager, Standards Office, Small Airplane Directorate, approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standards Office, Small Airplane Directorate.

Note 1: This AD applies to each airplane identified in paragraph (a) of this AD, 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 you have not eliminated the unsafe condition, specific actions you propose to address it.

(f) Where can I get information about any already-approved alternative methods of compliance? Contact Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329

– 4146; facsimile: (816) 329

–4090.

(g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD.

(h) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with the Technical Instructions supplied with Kit No. OPT70 K072

– 53, as specified in Socata Service Bulletin SB 70

– 082 53, dated June 2000. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You can get copies from SOCATA

— Groupe AEROSPATIALE, Customer Support, Aerodrome Tarbes-Ossun-Lourdes, BP 930

— F65009 Tarbes Cedex, France; or the Product Support Manager, SOCATA

— Groupe AEROSPATIALE, North Perry Airport, 7501 Pembroke Road, Pembroke Pines, Florida 33023. You can look at copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

Note 2: The subject of this AD is addressed in French AD 2000

– 373(A), dated October 18, 2000.

(i) When does this amendment become effective? This amendment becomes effective on March 29, 2002.

Issued in Kansas City, Missouri, on February 4, 2002. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 02

– 3167 Filed 2

– 13

– 02; 8:45 am] BILLING CODE 4910
– 13 – U DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2000 – NM –266 –AD; Amendment 39 – 12651; AD 2002 – 03 – 10] RIN 2120 –AA64 Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 Series Airplanes and Model Avro 146 – RJ Series Airplanes AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. SUMMARY : This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146

–RJ series airplanes, that requires repetitive inspections to detect cracking of the oleo strut of the nose landing gear (NLG), and corrective actions if necessary. This AD also provides for optional terminating action for the repetitive inspections. This action is necessary to detect and correct fatigue cracking of the oleo strut of the NLG, which could result in failure of the NLG. This action is intended to address the identified unsafe condition. DATES : Effective March 21, 2002.

The incorporation by reference of certain publications listed in the


### 6856 Federal Register / Vol. 67, No. 31 / Thursday, February 14, 2002 / Rules and Regulations regulations is approved by the Director of the Federal Register as of March 21, 2002. ADDRESSES : The service information referenced in this AD may be obtained from British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. 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, International Branch, 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 BAE Systems (Operations) Limited Model BAe 146 and Avro 146

–RJ series airplanes was published in the Federal Register on November 23, 2001 (66 FR 58678). That action proposed to require repetitive inspections to detect cracking of the oleo strut of the nose landing gear, and corrective actions if necessary. That action also proposed to provide for optional terminating action for the repetitive inspections. 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 60 Model BAe 146 series airplanes and Model Avro 146

–RJ series airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required inspection, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the requirements of this AD on U.S. operators is estimated to be $3,600, or $60 per airplane, per inspection cycle.

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: 2002
– 03
– 10 BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Amendment 39

– 12651. Docket 2000

–NM

– 266

–AD. Applicability: Model BAe 146 series airplanes and Model Avro 146

–RJ series airplanes, certificated in any category, as listed in BAE Systems (Operations) Limited Service Bulletin SB.32

– 158, dated June 2, 2000, except those on which Messier-Dowty Modification AC12248 has been installed.

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 (d) 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 oleo strut of the nose landing gear (NLG), which could result in failure of the NLG, accomplish the following: Inspection

(a) Perform an ultrasonic inspection to detect cracking of the oleo strut of the NLG, in accordance with BAE Systems (Operations) Limited Service Bulletin SB.32

– 158, dated June 2, 2000, according to the applicable time schedule specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD. Thereafter, repeat the inspection at least every 2,500 landings, until the actions specified by paragraph (c) of this AD have been performed.

(1) For NLGs identified in paragraph D.(3) of BAE Systems (Operations) Limited Service Bulletin SB.32

– 158, dated June 2, 2000: Inspect before the NLG accumulates 2,500 landings after accomplishment of the initial inspection specified by Messier-Dowty Service Bulletin 146

– 32

– 149, or within 30 days after the effective date of this AD, whichever occurs later.

(2) For NLGs having part number 201138002, serial numbers M

–DG

– 0158 to M

–DG

– 0168 inclusive, as identified in paragraph D.(4) of BAE Systems (Operations) Limited Service Bulletin SB. 32

– 158, dated June 2, 2000: Inspect before the NLG accumulates 20,000 total landings, or within 500 landings after the effective date of this AD, whichever occurs later.

(3) For NLGs other than those identified in paragraph (a)(1) or (a)(2) of this AD: Inspect before the NLG accumulates 8,000 total landings, or within 500 landings after the effective date of this AD, whichever occurs later. Corrective Actions

(b) If any crack is found during any inspection required by this AD: Before further flight, replace the oleo strut of the


### 6857 Federal Register / Vol. 67, No. 31 / Thursday, February 14, 2002 / Rules and Regulations
NLG with a new or serviceable strut in accordance with BAE Systems (Operations) Limited Service Bulletin SB.32

– 158, dated June 2, 2000. Optional Terminating Action

(c) Modification of the NLG in accordance with BAE Systems (Operations) Limited Service Bulletin SB.32

– 159

– 70668ABC, dated June 14, 2000, terminates the repetitive inspections required by this AD. Alternative Methods of Compliance

(d) 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

(e) 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

(f) The inspections and replacement, as applicable, shall be done in accordance with BAE Systems (Operations) Limited Service Bulletin SB.32

– 158, dated June 2, 2000. The terminating action, if accomplished, shall be done in accordance with BAE Systems (Operations) Limited Service Bulletin SB.32

– 159

– 70668ABC, dated June 14, 2000. (Only the first page of these documents is dated; no other page of these documents contains this information.) 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 British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. 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 British airworthiness directive 002

– 06

– 2000. Effective Date

(g) This amendment becomes effective on March 21, 2002.

Issued in Renton, Washington, on February 6, 2002. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 02

– 3309 Filed 2

– 13

– 02; 8:45 am] BILLING CODE 4910
– 13 – U DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2000 – NE –34 –AD; Amendment 39 – 12642; AD 2002 – 03 – 01] RIN 2120 –AA64 Airworthiness Directives; Honeywell International, Inc., (Formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, T53 – L– 11, T53 – L– 11A, T53 – L – 11B, T53 – L– 11C, T53
– L– 11D, T53 – L– 11A S/SA, T53
– L– 13B, T53 – L – 13B S/SA, T53
– L– 13B S/SB, and T53 – L–703 Turboshaft Engines AGENCY : Federal Aviation Administration, DOT. ACTION : Final rule. SUMMARY : This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former military T53

– L

– 11, T53

– L

– 11A, T53

– L

– 11B, T53

– L

– 11C, T53

– L

– 11D, T53

– L

– 11A S/SA, T53

– L

– 13B, T53

– L

– 13B S/ SA, T53

– L

– 13B S/SB, and T53

– L

– 703 series turboshaft engines. This amendment requires initial and repetitive special vibration tests of the engine, and if necessary replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This amendment is prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. The actions specified in this AD are intended to prevent excessive vibrations produced by the reduction gearbox assembly that could cause failure of the tachometer drive spur gear. DATES : Effective date March 21, 2002. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 21, 2002. ADDRESSES : The service information referenced in this AD may be obtained from Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming), Attn: Data Distribution, M/S 64

– 3/2101

– 201, P.O. Box 29003, Phoenix, AZ 85038

– 9003; telephone: (602) 365

– 2493; fax: (602) 365

– 5577. This information may be examined, by appointment, at the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT : Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712

– 4137; telephone: (562) 627

– 5245; fax: (562) 627

– 5210. SUPPLEMENTARY INFORMATION : A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former military T53

– L

– 11, T53

– L

– 11A, T53

– L

– 11B, T53

– L

– 11C, T53

– L

– 11D, T53

– L

– 11A S/ SA, T53

– L

– 13B, T53

– L

– 13B S/SA, T53

– L

– 13B S/SB, and T53

– L

– 703 series turboshaft engines was published in the Federal Register on June 15, 2001 (66 FR 32591). That action proposed to require initial and repetitive special vibration tests of the engine, and if necessary replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight, in accordance with AlliedSignal, Inc., Service Bulletin (SB) No. ’’ s T5311A/B

– 0100, dated January 20, 2000; T5313B/17

– 0100, dated November 19, 1999; T53

– L

– 11

– 0100, dated January 20, 2000; T53

– L

– 13B

– 0100, Revision 2, dated May 11, 1999; and T53

– L

– 703

– 0100, Revision 2, dated May 11, 1999. Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the one comment received.

The commenter stated that further investigation into the root problem causing the spur gear failures needs to be addressed. The problem may be a manufacturing problem from one U.S. Government contract supplier.

The FAA does not agree. The commenter did not supply sufficient evidence substantiating a design nonconformity.

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. Economic Analysis

There are about 4,500 engines of the affected design in the worldwide fleet. The FAA estimates that 300 engines