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Regulatory Impact evaluation prepared for this action is 2002–22 01 Moravan A.S.: Amendment contained in the Rules Docket. A copy 39–12925; Docket No. 99–CE–71-AD. Does This AD Impact Various Entities? of it may be obtained by contacting the (a) What airplanes are affected by this AD? The regulations adopted herein will Rules Docket at the location provided This AD affects the following airplane not have a substantial direct effect on under the caption ADDRESSES. models and serial numbers that are the States, on the relationship between certificated in any category: the national government and the States, List of Subjects in 14 CFR Part 39 or on the distribution of power and Air transportation, Aircraft, Aviation Model Serial Nos. responsibilities among the various safety, Incorporation by reference, levels of government. Therefore, it is Safety. Z–143L .... All serial numbers up to and in- determined that this final rule does not cluding 0029, except 0025 have federalism implications under Adoption of the Amendment and 0027. Executive Order 13132. Z–242L .... All serial numbers up to and in- Accordingly, under the authority cluding 0733. Does This AD Involve a Significant Rule delegated to me by the Administrator, or Regulatory Action? the Federal Aviation Administration (b) Who must comply with this AD? amends part 39 of the Federal Aviation Anyone who wishes to operate any of the For the reasons discussed above, I Regulations (14 CFR part 39) as follows: certify that this action (1) is not a airplanes identified in paragraph (a) of this AD must comply with this AD. ‘‘significant regulatory action’’ under PART 39—AIRWORTHINESS (c) What problem does this AD address? Executive Order 12866; (2) is not a DIRECTIVES The actions specified by this AD are intended ‘‘significant rule’’ under DOT to prevent the engine crankcase ventilation Regulatory Policies and Procedures (44 1. The authority citation for part 39 continues to read as follows: lines from freezing during flight in cold FR 11034, February 26, 1979); and (3) weather (winter) conditions, which could will not have a significant economic Authority: 49 U.S.C. 106(g), 40113, 44701. result in oil leaking from the engine. Such a impact, positive or negative, on a condition could lead to engine failure. § 39.13 [Amended] substantial number of small entities (d) What actions must I accomplish to under the criteria of the Regulatory 2. FAA amends § 39.13 by adding a address this problem? To address this Flexibility Act. A copy of the final new AD to read as follows: problem, you must accomplish the following:

Actions Compliance Procedures

Modify the engine vent lines ...... Within the next 100 hours time-in-service after In accordance with Moravan Mandatory Serv- December 13, 2002 (the effective date of ice Bulletin Z 242L/19a—Rev. 3, Z 143L/ this AD). 20a, dated April 30, 1999.

(e) Can I comply with this AD in any other §§21.197 and 21.199 of the Federal Aviation DEPARTMENT OF TRANSPORTATION way? You may use an alternative method of Regulations (14 CFR 21.197 and 21.199) to compliance or adjust the compliance time if: operate your airplane to a location where you Federal Aviation Administration (1) Your alternative method of compliance can accomplish the requirements of this AD. provides an equivalent level of safety; and (h) Are any service bulletins incorporated 14 CFR Part 39 (2) The Manager, Small Airplane into this AD by reference? Actions required Directorate, approves your alternative. by this AD must be done in accordance with [Docket No. 2002–CE–28–AD; Amendment Submit your request through an FAA Moravan Inc. Mandatory Service Bulletin Z 39–12927; AD 2002–22–03] Principal Maintenance Inspector, who may 242L/19a—Rev. 3, Z 143L/20a, dated April add comments and then send it to the RIN 2120–AA64 30, 1999. The Director of the Federal Register Manager, Small Airplane Directorate. approved this incorporation by reference Airworthiness Directives; PILATUS Note 1: This AD applies to each airplane under 5 U.S.C. 552(a) and 1 CFR part 51. You identified in paragraph (a) of this AD, Aircraft Ltd. Model PC–7 Airplanes may get copies from Moravan, Inc., 765 81 regardless of whether it has been modified, Otrokovice, Czech Republic; telephone: +420 altered, or repaired in the area subject to the AGENCY: Federal Aviation requirements of this AD. For airplanes that 67 767 3940; facsimile: +420 67 792 2103. Administration, DOT. You may view copies at the FAA, Central have been modified, altered, or repaired so ACTION: Final rule. that the performance of the requirements of Region, Office of the Regional Counsel, 901 this AD is affected, the owner/operator must Locust, Room 506, Kansas City, Missouri, or SUMMARY: This amendment adopts a request approval for an alternative method of at the Office of the Federal Register, 800 new airworthiness directive (AD) that compliance in accordance with paragraph (e) North Capitol Street, NW., suite 700, applies to certain PILATUS Aircraft Ltd. Washington, DC. of this AD. The request should include an (Pilatus) Model PC–7 airplanes. This AD assessment of the effect of the modification, Note 2: The subject of this AD is addressed requires you to repetitively inspect the alteration, or repair on the unsafe condition in Czech Republic AD Number CAA–AD– main landing gear front attachment addressed by this AD; and, if you have not 042/1999, August 18, 1999. eliminated the unsafe condition, specific brackets for cracks, and, if cracks are (i) When does this amendment become actions you propose to address it. found, install improved-design brackets. effective? This amendment becomes effective (f) Where can I get information about any on December 13, 2002. Installing the improved-design brackets already-approved alternative methods of terminates the required inspections. compliance? Contact Doug Rudolph, Issued in Kansas City, Missouri, on This AD is the result of mandatory Aerospace Engineer, FAA, Small Airplane October 18, 2002. continuing airworthiness information Directorate, 901 Locust, Room 301, Kansas Michael Gallagher, (MCAI) issued by the airworthiness City, Missouri 64106; telephone: (816) 329– Manager, Small Airplane Directorate, Aircraft 4059; facsimile: (816) 329–4090. authority for Switzerland. The actions Certification Service. (g) What if I need to fly the airplane to specified by this AD are intended to another location to comply with this AD? The [FR Doc. 02–27201 Filed 10–31–02; 8:45 am] detect and correct cracks in the main FAA can issue a special flight permit under BILLING CODE 4910–13–P landing gear front attachment brackets,

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which could result in failure of the Discussion Was the Public Invited To Comment? brackets. Such failure could lead to the What Events Have Caused This AD? main landing gear leg detaching from The FAA encouraged interested the wing main spar. The Federal Office for Civil Aviation persons to participate in the making of (FOCA), which is the airworthiness this amendment. We did not receive any DATES: This AD becomes effective on authority for Switzerland, recently comments on the proposed rule or on December 20, 2002. notified FAA that an unsafe condition our determination of the cost to the The Director of the Federal Register may exist on certain Pilatus Model PC– public. 7 airplanes. The FOCA reports that an approved the incorporation by reference FAA’s Determination of certain publications listed in the operator of a similar aircraft type design, regulations as of December 20, 2002. which uses identical main landing gear What Is FAA’s Final Determination on support brackets, reported a single crack This Issue? ADDRESSES: You may get the service in one bracket. A fleet inspection of the information referenced in this AD from operator’s aircraft revealed stress After careful review of all available Pilatus Aircraft Ltd., Customer Liaison corrosion cracking in more than 20 information related to the subject Manager, CH–6371 Stans, Switzerland; aircraft. presented above, we have determined telephone: +41 41 619 63 19; facsimile: that air safety and the public interest What Is the Potential Impact if FAA require the adoption of the rule as +41 41 619 6224; or from Pilatus Took No Action? Business Aircraft Ltd., Product Support proposed except for minor editorial Cracks in the main landing gear front Department, 11755 Airport Way, corrections. We have determined that attachment brackets could result in these minor corrections: Broomfield, Colorado 80021; telephone: failure of the brackets. Such failure (303) 465–9099; facsimile: (303) 465– —Provide the intent that was proposed could lead to the main landing gear leg in the NPRM for correcting the unsafe 6040. You may view this information at detaching from the wing main spar. the Federal Aviation Administration condition; and (FAA), Central Region, Office of the Has FAA Taken Any Action to This —Do not add any additional burden Regional Counsel, Attention: Rules Point? upon the public than was already Docket No. 2002–CE–28–AD, 901 We issued a proposal to amend part proposed in the NPRM. Locust, Room 506, Kansas City, 39 of the Federal Aviation Regulations Cost Impact Missouri 64106; or at the Office of the (14 CFR part 39) to include an AD that Federal Register, 800 North Capitol would apply to certain Pilatus Model How Many Airplanes Does This AD Street, NW., Suite 700, Washington, DC. PC–7 airplanes. This proposal was Impact? published in the Federal Register as a FOR FURTHER INFORMATION CONTACT: notice of proposed rulemaking (NPRM) We estimate that this AD affects 14 Doug Rudolph, Aerospace Engineer, on August 9, 2002 (67 FR 51794). The airplanes in the U.S. registry. FAA, Small Airplane Directorate, 901 NPRM proposed to repetitively inspect What Is the Cost Impact of This AD on Locust, Room 301, Kansas City, the main landing gear front attachment Owners/Operators of the Affected Missouri 64106; telephone: (816) 329– brackets for cracks, and, if cracks are Airplanes? 4059; facsimile: (816) 329–4090. found, install improved-design brackets. Installing the improved-design brackets We estimate the following costs to SUPPLEMENTARY INFORMATION: terminates the required inspections. accomplish the inspection:

Total cost per Total cost on Labor cost Parts cost airplane U.S. operator

4 workhours × $60 = $240 ...... No parts required ...... $240 $240 × 14 = $3,360.

The FAA has no method of airplanes so the cost impact is based on results of the inspection. We have no determining the number of repetitive the initial inspection. way of determining the number of inspections each owner/operator would We estimate the following costs to airplanes that may need such incur over the life of each of the affected accomplish any necessary replacements replacement: that would be required based on the

Labor cost Parts cost Total cost per airplane

80 workhours × $60 = $4,800 per side ...... $2,500 per side ...... $4,800 + $2,500 = $7,300 per side.

Regulatory Impact determined that this final rule does not ‘‘significant rule’’ under DOT have federalism implications under Regulatory Policies and Procedures (44 Does This AD Impact Various Entities? Executive Order 13132. FR 11034, February 26, 1979); and (3) will not have a significant economic The regulations adopted herein will Does This AD Involve a Significant Rule impact, positive or negative, on a not have a substantial direct effect on or Regulatory Action? the States, on the relationship between substantial number of small entities the national government and the States, For the reasons discussed above, I under the criteria of the Regulatory or on the distribution of power and certify that this action (1) is not a Flexibility Act. A copy of the final responsibilities among the various ‘‘significant regulatory action’’ under evaluation prepared for this action is levels of government. Therefore, it is Executive Order 12866; (2) is not a contained in the Rules Docket. A copy

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of it may be obtained by contacting the PART 39—AIRWORTHINESS numbers 101 through 618, that are Rules Docket at the location provided DIRECTIVES certificated in any category. under the caption ADDRESSES. (b) Who must comply with this AD? 1. The authority citation for part 39 Anyone who wishes to operate any of the List of Subjects in 14 CFR Part 39 continues to read as follows: airplanes identified in paragraph (a) of this Air transportation, Aircraft, Aviation Authority: 49 U.S.C. 106(g), 40113, 44701. AD must comply with this AD. safety, Incorporation by reference, (c) What problem does this AD address? Safety. § 39.13 [Amended] The actions specified by this AD are intended to detect and correct cracks in the main 2. FAA amends § 39.13 by adding a Adoption of the Amendment landing gear front attachment brackets, new AD to read as follows: which could result in failure of the brackets. Accordingly, under the authority 2002–22–03 Pilatus Aircraft LTD.: Such failure could lead to the main landing delegated to me by the Administrator, Amendment 39–12927; Docket No. gear leg detaching from the wing main spar. the Federal Aviation Administration 2002–CE–28–AD. (d) What actions must I accomplish to amends part 39 of the Federal Aviation (a) What airplanes are affected by this AD? address this problem? To address this Regulations (14 CFR part 39) as follows: This AD affects Model PC–7 airplanes, serial problem, you must accomplish the following:

Compliance Actions Procedures

(1) Initial Inspection: At whichever of the fol- Inspect, using the Impedance-Plane Eddy- In accordance with the ACCOMPLISHMENT lowing occurs later, unless already accom- Current Inspection, both main landing gear INSTRUCTIONS section of Pilatus PC–7 plished: (i) Upon the accumulation of 3,000 front attachment brackets, part number (P/ Service Bulletin No. 57–004, Revision No. hours time-in-service (TIS) on the attachment N) 111.34.07.105 and P/N 111.34.07.106 1, dated June 17, 2002; the ACCOMPLISH- brackets or 10 years after installation of the for cracks. MENT INSTRUCTIONS section of Pilatus brackets, whichever occurs first; or (ii) within PC–7 Service Bulletin No. 57–005, dated 90 days after December 20, 2002 (the effec- September 10, 2001; and Pilatus PC–7 tive date of this AD). Maintenance Manual, Temporary Revision No. 05–10, dated September 10, 2001.

(2) Repetitive Inspections: Within 12 calendar Inspection, using the Impedance-Plane Eddy- In accordance with the ACCOMPLISHMENT months after the initial inspection required in Current Inspection, both main landing gear INSTRUCTIONS section of Pilatus PC–7 paragraph (d)(1) of this AD and thereafter at front attachment brackets, P/N Service Bulletin No. 57–004, Revision No. intervals not to exceed 12 calendar months. 111.34.07.105 and P/N 111.34.07.106 for 1, dated June 17, 2002; the ACCOMPLISH- cracks. MENT INSTRUCTIONS section of Pilatus PC–7 Service Bulletin No. 57–005, dated September 10, 2001; and Pilatus PC–7 Maintenance Manual, Temporary Revision No. 05–10, dated September 10, 2001.

(3) Prior to further flight after the inspection in If a crack is found in any main landing gear In accordance with the ACCOMPLISHMENT which the damage was found. front attachment bracket during any inspec- INSTRUCTIONS section of Pilatus PC–7 tion required in this AD, replace with an im- Service Bulletin No. 57–005, dated Sep- proved bracket, P/N 557.10.09.045, P/N tember 10, 2001. 557.10.09.046, or FAA-approved equivalent P/N. Repetitive inspections are still required on any P/N 111.34.07.105 and P/N 111.34.07.106 for cracks.

(4) At any time as terminating action for the re- You may terminate the inspections required in In accordance with the ACCOMPLISHMENT petitive inspections. However, you must re- paragraphs (d)(1) and (d)(2) of this AD INSTRUCTIONS section of Pilatus PC–7 place prior to further flight if you find cracks when improved design main landing gear Service Bulletin No. 57–005, dated Sep- during any inspections required by this AD. front attachment brackets, P/N tember 10, 2001. 557.10.09.045, P/N 557.10.09.046, or FAA- approved equivalent P/Ns, are installed on both sides of the airplane.

(5) As of December 20, 2002 (the effective date Only install main landing gear brackets that Not Applicable. of this AD). are P/N 557.10.09.045, P/N 557.10.09.046, or FAA-approved equivalent P/Ns.

Note 1: If you find cracks on one side only, (2) The Standards Office Manager, Small this AD is affected, the owner/operator must you are only required to replace the damaged Airplane Directorate, approves your request approval for an alternative method of side with the new improved-design bracket alternative. Submit your request through an compliance in accordance with paragraph (e) and continue the repetitive inspections FAA Principal Maintenance Inspector, who of this AD. The request should include an required by paragraph (d)(2) of this AD. may add comments and then send it to the assessment of the effect of the modification, Repetitive inspections are still required on Standards Office Manager. alteration, or repair on the unsafe condition any installed bracket with either P/N Note 2: This AD applies to each airplane addressed by this AD; and, if you have not 111.34.07.105 or P/N 111.34.07.106. identified in paragraph (a) of this AD, eliminated the unsafe condition, specific (e) Can I comply with this AD in any other regardless of whether it has been modified, actions you propose to address it. way? You may use an alternative method of altered, or repaired in the area subject to the (f) Where can I get information about any compliance or adjust the compliance time if: requirements of this AD. For airplanes that already-approved alternative methods of (1) Your alternative method of compliance have been modified, altered, or repaired so compliance? Contact Doug Rudolph, provides an equivalent level of safety; and that the performance of the requirements of Aerospace Engineer, FAA, Small Airplane

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Directorate, 901 Locust, Room 301, Kansas Limited (Pilatus Britten-Norman) BN–2, What Is the Potential Impact if FAA City, Missouri 64106; telephone: (816) 329– BN–2A, BN–2B, BN–2T, and BN2A MK. Took No Action? 4059; facsimile: (816) 329–4090. III series airplanes. This AD requires This condition, if not detected and (g) What if I need to fly the airplane to you to repetitively inspect the bottom another location to comply with this AD? The corrected, could result in failure of the FAA can issue a special flight permit under corner of the engine mount bracket for engine mount. Such failure could result §§ 21.197 and 21.199 of the Federal Aviation cracks and replace any cracked bracket in the engine separating from the Regulations (14 CFR 21.197 and 21.199) to with a new one. This AD is the result airplane and lead to loss of control of operate your airplane to a location where you of mandatory continuing airworthiness the airplane. can accomplish the requirements of this AD. information (MCAI) issued by the (h) Are any service bulletins incorporated airworthiness authority for the United Has FAA Taken Any Action to This into this AD by reference? Actions required Kingdom. The actions specified by this Point? by this AD must be done in accordance with AD are intended to detect and correct We issued a proposal to amend part Pilatus PC–7 Service Bulletin No. 57–004, cracks in the engine mount bracket. 39 of the Federal Aviation Regulations Revision No. 1, dated June 17, 2002; Pilatus PC–7 Service Bulletin No. 57–005, dated Such a condition could cause the engine (14 CFR part 39) to include an AD that September 10, 2001; and Pilatus PC–7 mount assembly to fail, which could would apply to all Pilatus Britten- Maintenance Manual, Temporary Revision result in the engine separating from the Norman BN–2, BN–2A, BN–2B, BN–2T, No. 05–10, dated September 10, 2001. The airplane and lead to loss of control of and BN2A MK. III series airplanes. This Director of the Federal Register approved this the airplane. proposal was published in the Federal incorporation by reference under 5 U.S.C. DATES: This AD becomes effective on Register as a notice of proposed 552(a) and 1 CFR part 51. You may get copies December 20, 2002. rulemaking (NPRM) on August 22, 2002 from Pilatus Aircraft Ltd., Customer Liaison (67 FR 54384). The NPRM proposed to Manager, CH–6371 Stans, Switzerland; The Director of the Federal Register require you to repetitively inspect the telephone: +41 41 619 63 19; facsimile: +41 approved the incorporation by reference bottom corner of the engine mount 41 619 6224; or from Pilatus Business of certain publications listed in the bracket for cracks, replace any cracked Aircraft Ltd., Product Support Department, regulations as of December 20, 2002. 11755 Airport Way, Broomfield, Colorado bracket, return the removed bracket(s) to 80021; telephone: (303) 465–9099; facsimile: ADDRESSES: You may get the service Pilatus Britten-Norman, and report the (303) 465–6040. You may view copies at the information referenced in this AD from return to FAA. FAA, Central Region, Office of the Regional B–N Group Limited, Bembridge, Isle of Are There Differences Between This AD, Counsel, 901 Locust, Room 506, Kansas City, Wight, United Kingdom PO35 5PR; the Service Information, and the CAA Missouri, or at the Office of the Federal telephone: +44 (0) 1983 872511; AD? Register, 800 North Capitol Street, NW, suite facsimile: +44 (0) 1983 873246. You 700, Washington, DC. may view this information at the The CAA AD and the service Note 3: The subject of this AD is addressed Federal Aviation Administration (FAA), information allow continued flight if in Swiss AD HB 2002–270, dated June 24, Central Region, Office of the Regional cracks are found in the engine mount 2002. Counsel, Attention: Rules Docket No. bracket that do not exceed certain (i) When does this amendment become 2002–CE–21–AD, 901 Locust, Room limits. The applicable service bulletin effective ? This amendment becomes effective 506, Kansas City, Missouri 64106; or at specifies replacement of the engine on December 20, 2002. the Office of the Federal Register, 800 mount bracket only if cracks are found Issued in Kansas City, Missouri, on North Capitol Street, NW., suite 700, exceeding this limit, as does CAA AD October 22, 2002. Washington, DC. 005–11–2001. This AD does not allow continued flight if any crack is found. David R. Showers, FOR FURTHER INFORMATION CONTACT: FAA policy is to disallow airplane Acting Manager, Small Airplane Directorate, Doug Rudolph, Aerospace Engineer, Aircraft Certification Service. operation when known cracks exist in FAA, Small Airplane Directorate, 901 primary structure, unless the ability to [FR Doc. 02–27418 Filed 10–31–02; 8:45 am] Locust, Room 301, Kansas City, sustain ultimate load with these cracks BILLING CODE 4910–13–P Missouri 64106; telephone: (816) 329– is proven. The engine mount bracket is 4059; facsimile: (816) 329–4090. considered primary structure, and the SUPPLEMENTARY INFORMATION: DEPARTMENT OF TRANSPORTATION FAA has not received any analysis to Discussion prove that ultimate load can be Federal Aviation Administration sustained with cracks in this area. What Events Have Caused This AD? Is There a Modification I Can 14 CFR Part 39 The Civil Aviation Authority (CAA), Incorporate Instead of Repetitively [Docket No. 2002–CE–21–AD; Amendment which is the airworthiness authority for Inspecting the Engine Mount Brackets? 39–12926; AD 2002–22–02] the United Kingdom, recently notified The FAA has determined that long- FAA that an unsafe condition may exist term continued operational safety will RIN 2120–AA64 on all Pilatus Britten-Norman BN–2, be better assured by design changes that BN–2A, BN–2B, BN–2T, and BN2A remove the source of the problem rather Airworthiness Directives; Pilatus MK. III series airplanes. The CAA Britten-Norman Limited BN–2, BN–2A, than by performing repetitive reports two occurrences of extensive inspections. With this in mind, we will BN–2B, BN–2T, and BN2A MK. III cracks being found on the bottom corner Series Airplanes continue to work with Pilatus Britten- of the engine mount bracket between the Norman in collecting information to AGENCY: Federal Aviation attachment flange and the main bracket. determine whether a future design Administration, DOT. The cracks were found during regular change may be necessary. scheduled maintenance. ACTION: Final rule. The manufacturer has determined that Was the Public Invited To Comment? SUMMARY: This amendment adopts a this condition is a result of the The FAA encouraged interested new airworthiness directive (AD) that reinforcing doubler being too close to persons to participate in the making of applies to all Pilatus Britten-Norman the flange. this amendment. We did not receive any

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