Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes, 40888-40891 [E6-11333]

Download as PDF 40888 Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations Actions Compliance (ii) The upper and lower wing skins for damage; and (iii) The inboard fuel tank area to determine if the inboard fuel tank ventilating system is installed. (2) If any crack damage is found: (i) Correct the crack damage designated as repairable in the service bulletin. (ii) For other crack damage, obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD and incorporate this repair scheme. (3) If wing distortion is found, obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD and incorporate this repair scheme. (4) If the inboard fuel tank ventilating system is not installed, install the inboard fuel tank ventilating system. (B) For Group 2 Airplanes: Within the next 90 days or 100 hours TIS, whichever occurs first, after August 23, 2006 (the effective date of this AD), unless already done. Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; facsimile: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 2003–13–04 are approved for this AD. mstockstill on PROD1PC68 with RULES Related Information (h) Swiss AD Numbers HB 2003–092, dated February 17, 2003, and HB 2005–289, effective date August 23, 2005, also address the subject of this AD. Material Incorporated by Reference (i) You must do the actions required by this AD following the instructions in Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57– 002, dated November 27, 2002, and Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 118, dated December 1972. (1) As of August 15, 2003 (68 FR 37394, June 24, 2003), the Director of the Federal Register previously approved the incorporation by reference of Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27, 2002; and Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 118, dated December 1972, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) To get a copy of this service information, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., VerDate Aug<31>2005 16:10 Jul 18, 2006 Jkt 208001 Procedures Before further flight after the inspections required in paragraph (e)(1) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27, 2002. Before further flight after the inspections required in paragraph (e)(1) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 57–002, dated November 27, 2002. Before further flight after the inspections required in paragraph (e)(1) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 118, dated December 1972. Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http:// dms.dot.gov. The docket number is FAA– 2006–24093; Directorate Identifier 2006–CE– 19–AD. Issued in Kansas City, Missouri, on July 11, 2006. Steven W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–11339 Filed 7–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24092; Directorate Identifier 2006–CE–18–AD; Amendment 39– 14682; AD 2006–15–02] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC– 6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1–H2 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) that supersedes AD 2003–09–01, which applies to certain Pilatus Aircraft Ltd (Pilatus) Model PC–6 airplanes. AD 2003–09–01 currently requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. Since we issued AD 2003–09–01, the FAA PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 determined the action should also apply to all the models of the PC–6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15 that were produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 2003–09–01 was to apply to all the affected serial numbers of the airplane models listed in TC No. 7A15. This AD retains all the actions of AD 2003–09–01, adds those Fairchild Republic Company airplanes to the applicability of this AD, and lists the individual specific airplane models. We are issuing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flightcontrol system. Such failure could lead to problems in controlling flight. DATES: This AD becomes effective on August 23, 2006. As of June 17, 2003 (68 FR 22582, April 29, 2003), the Director of the Federal Register previously approved the incorporation by reference of Pilatus Service Bulletin No. 27–001, dated June 5, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. ADDRESSES: To get the service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– E:\FR\FM\19JYR1.SGM 19JYR1 Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations 001 or on the Internet at http:// dms.dot.gov. The docket number is FAA–2006–24092; Directorate Identifier 2006–CE–18–AD. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion On May 3, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all the models of the PC–6 airplanes listed in the type certificate data sheet of TC No. 7A15 that were produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation) airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on May 9, 2006 (71 FR 26891). The NPRM proposed to supersede AD 2003–09–01 (68 FR 22582, April 29, 2003), add those Fairchild Republic Company airplanes to the applicability of this proposed AD, and would list the individual specific airplane models. The NPRM proposed to retain all of the actions of AD 2003– 09–01 for inspecting and correcting, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. Comments We provided the public the opportunity to participate in developing this AD. We received one comment in favor of the proposed AD. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 49 airplanes in the U.S. registry. We estimate the following costs to do the inspection and modifications: Labor cost Parts cost Total cost per airplane 7 work-hours × $80 per hour = $560 ....................................................................... $300 $860 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this AD. mstockstill on PROD1PC68 with RULES Regulatory Findings 15:11 Jul 18, 2006 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; VerDate Aug<31>2005 2. Is not a ‘‘significant rule’’ under the 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. We prepared a summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2006–24092; Directorate Identifier 2006–CE–18–AD’’ in your request. Jkt 208001 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I PO 00000 Authority: 49 U.S.C. 106(g), 40113, 44701. Frm 00015 Fmt 4700 Sfmt 4700 40889 § 39.13 Total cost on U.S. operators $860 × 49 = $42,140. [Amended] 2. FAA amends § 39.13 by removing Airworthiness Directive (AD) 2003–09– 01, Amendment 39–13130 (68 FR 22582, April 29, 2003), and by adding the following new AD: I 2006–15–02 Pilatus Aircraft Ltd.: Amendment 39–14682; Docket No. FAA– 2006–24092; Directorate Identifier 2006– CE–18–AD. Effective Date (a) This AD becomes effective on August 23, 2006. Affected ADs (b) This AD supersedes AD 2003–09–01, Amendment 39–13130. Applicability (c) This AD affects the following Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/ 350–H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, PC– 6/B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC– 6/C1–H2 airplanes that are certificated in any category: (1) Group 1 (maintains the actions from AD 2003–09–01): All manufacturer serial numbers (MSN) up to and including 939. (2) Group 2: MSN 2001 through 2092. Note: These airplanes are also identified as Fairchild Republic Company PC–6 airplanes, Fairchild Industries PC–6 airplanes, Fairchild Heli Porter PC–6 airplanes, or Fairchild-Hiller Corporation PC–6 airplanes. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland that requires retaining the E:\FR\FM\19JYR1.SGM 19JYR1 40890 Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations actions of AD 2003–09–01 and adding MSN 2001 through 2092 for all the models of the PC–6 airplanes listed in the type certificate data sheet of Type Certificate No. 7A15. We are issuing this AD to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight. Compliance (e) To address this problem, you must do the following: Compliance Procedures (1) Inspect, before removal of the wing bellcrank assemblies, part numbers (P/N) 6132.0071.51 and 6132.0071.52, for installed circlips, P/N N237. (i) If circlips are installed, do the actions required in paragraphs (e)(5) and (e)(6) of this AD. (ii) If circlips are not installed, perform all actions required by paragraphs (e)(3), (e)(4), (e)(5), (e)(6), and (e)(7) of this AD. (2) Inspect, before removal of the fuselage bellcrank assembly, P/N 6232.0118.00, for the circlip installed on the housing to prevent axial movement of the bellcrank on its bearing and the flange of the housing to the rear. If the fuselage bellcrank assembly has either no circlip and/or it is not installed as required, perform the actions in paragraphs (e)(8) and (e)(9) of this AD. (3) Remove the wing bellcrank assemblies, P/ Ns 6132.0071.51 and 6132.0071.52, and inspect for worn or damaged bearings. Replace worn or damaged bearings. (4) Stake and lock the bearing in the housing of the wing bellcranks, P/Ns 6132.0071.51 and 6132.0071.52. (5) Inspect the wing bellcranks control-cable attachment bolts for correct type and for signs of rub damage on the heads. Replace bolts that are damaged and/or have a total length (including head) of more than 21.5 mm (0.85 in.). (6) Inspect the wing bellcranks support plate for signs of rub damage caused by the bolts. If damage is found: (i) Obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme. (7) Reinstall wing bellcrank assemblies ............. mstockstill on PROD1PC68 with RULES Actions (A) For Group 1 Airplanes: Within the next 100 hours time-in-service (TIS) after June 17, 2003 (the effective date of AD 2003– 09–01), unless already done. (B) For Group 2 Airplanes: Within the next 100 hours TIS after August 23, 2006 (the effective date of this AD), unless already done. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspection required in paragraph (e)(1) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD, as applicable. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD. Before further flight after the inspections required in paragraphs (e)(1) and (e)(2) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Before further flight after the inspections required in paragraphs (e)(1), (e)(2), and (e)(8) of this AD. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. (8) Remove the fuselage bellcrank assembly, P/N 6232.0118.00, and inspect the housing for wear, damage, and signs of axial movement of the bearing in the housing. Replace worn or damaged bearings. If any signs of axial movement of a bearing are found: (i) Obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (f) of this AD. (ii) Incorporate this repair scheme. (9) Reinstall the fuselage bellcrank assembly. Ensure that the fuselage bellcrank assembly is installed so that the surface of the bellcrank with the flange of the housing is installed to the rear. The effect of this is to lock the bellcrank on the bearing tube and thus prevent movement. (10) Do not install any bellcrank assemblies, P/ Ns 6132.0071.51, 6132,0071.52, and 6232.0118.00 (or FAA-approved equivalent part numbers), unless the aileron assembly has been inspected, modified, and installed. VerDate Aug<31>2005 15:11 Jul 18, 2006 Jkt 208001 Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. Follow Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27–001, dated June 5, 2002. (A) For Group 1 Airplanes: As of June 17, Follow Pilatus Aircraft Ltd. PC–6 Service Bul2003 (the effective date of AD 2003–09–01). letin No. 27–001, dated June 5, 2002. (B) For Group 2 Airplanes: As of August 23, 2006 (the effective date of this AD), unless already done. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 E:\FR\FM\19JYR1.SGM 19JYR1 Federal Register / Vol. 71, No. 138 / Wednesday, July 19, 2006 / Rules and Regulations (f) Axial movement of serviceable bearings in the housings of the wing bellcranks is permitted provided no wear or damage to the bearing is found. (g) Any sign of axial movement of a bearing in the housing of the fuselage bellcrank assembly requires that you obtain a repair scheme from the manufacturer through FAA at the address specified in paragraph (i) of this AD and incorporate the repair scheme. (h) 14 CFR 21.303 allows for replacement parts through parts manufacturer approval (PMA). The phrase ‘‘or FAA-approved equivalent part number’’ in this AD is intended to signify those parts that are PMA approved through identicality to the design of the part under the type certificate and replacement parts to correct the unsafe condition under PMA (other than identicality). If parts are installed that are identical to the unsafe parts, then the corrective actions of the AD affect these parts also. In addition, equivalent replacement parts to correct the unsafe condition under PMA (other than identicality) may also be installed provided they meet current airworthiness standards, which include those actions cited in this AD. Alternative Methods of Compliance (AMOCs) (i) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; facsimile: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (j) AMOCs approved for AD 2003–09–01 are approved for this AD. mstockstill on PROD1PC68 with RULES Related Information (k) Swiss AD Number HB 2005–289, effective date August 23, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must do the actions required by this AD following the instructions in Pilatus Aircraft Ltd. PC–6 Service Bulletin No. 27– 001, dated June 5, 2002. (1) As of June 17, 2003 (68 FR 22582, April 29, 2003), the Director of the Federal Register previously approved the incorporation by reference of Pilatus Service Bulletin No. 27– 001, dated June 5, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) To get a copy of this service information, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http:// dms.dot.gov. The docket number is FAA– VerDate Aug<31>2005 15:11 Jul 18, 2006 Jkt 208001 2006–24092; Directorate Identifier 2006–CE– 18–AD. Issued in Kansas City, Missouri, on July 10, 2006. Steven W. Thompson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–11333 Filed 7–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION National Highway Traffic Safety Administration 23 CFR Part 1350 [Docket No. NHTSA–2006–23700] RIN 2127–AJ86 Motorcyclist Safety Grant Program National Highway Traffic Safety Administration (NHTSA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: This final rule implements the Motorcyclist Safety grant program authorized under section 2010 of the Safe, Accountable, Flexible, Efficient Transportation Equity Act: A Legacy for Users (SAFETEA–LU) for fiscal years 2006 through 2009. Eligibility for the section 2010 grants is based on six statutorily-specified grant criteria. To receive an initial section 2010 grant, a State must demonstrate compliance with at least one of the six grant criteria. To receive a grant in subsequent fiscal years, a State must demonstrate compliance with at least two of the six grant criteria. This final rule establishes the requirements a State must meet and the procedures it must follow to receive a section 2010 Motorcyclist Safety grant, beginning in fiscal year 2006. DATES: This final rule becomes effective on July 19, 2006. FOR FURTHER INFORMATION CONTACT: For program issues: Marti Miller, Regional Operations and Program Delivery, National Highway Traffic Safety Administration, 400 Seventh Street, SW., Washington, DC 20590; Telephone: (202) 366–2121. For legal issues: Allison Rusnak, Office of the Chief Counsel, National Highway Traffic Safety Administration, 400 Seventh Street, SW., Washington, DC 20590; Telephone: (202) 366–1834. SUPPLEMENTARY INFORMATION: SUMMARY: Table of Contents I. Background II. Section 2010 Statutory Requirements III. Section 2010 Administrative Requirements PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 40891 IV. Notice of Proposed Rulemaking V. Comments A. In General B. Comments Regarding Programmatic Criteria 1. Motorcycle Rider Training Courses 2. Motorcyclists Awareness Program 3. Reduction of Fatalities and Crashes Involving Motorcycles and Reduction of Fatalities and Accidents Involving Impaired Motorcyclists 4. Impaired Driving Program C. Comments Regarding Administrative Issues VI. Statutory Basis for This Action VII. Regulatory Analyses and Notices A. Executive Order 12866 and DOT Regulatory Policies and Procedures B. Regulatory Flexibility Act C. Executive Order 13132 (Federalism) D. Executive Order 12988 (Civil Justice Reform) E. Paperwork Reduction Act F. Unfunded Mandates Reform Act G. National Environmental Policy Act H. Executive Order 13175 (Consultation and Coordination With Indian Tribes) I. Regulatory Identifier Number (RIN) J. Privacy Act I. Background An estimated 128,000 motorcyclists have died in traffic crashes since the enactment of the Highway Safety Act of 1966. There are nearly 6 million motorcycles 1 registered in the United States. Motorcycles made up more than 2 percent of all registered vehicles in the United States in 2004 and accounted for an estimated 0.3 percent of all vehicle miles traveled. Per vehicle mile traveled in 2004, motorcyclists were about 34 times more likely to die and 8 times more likely to be injured in a motor vehicle traffic crash than passenger car occupants. Motorcycle rider fatalities reached a high of 5,144 in 1980. After dropping to a low of 2,116 in 1997, motorcycle rider fatalities have increased for 7 consecutive years, reaching a total of 4,008 in 2004, the last full year for which data are available— an increase of 89 percent. Preliminary 2005 Fatality Analysis Reporting System (FARS) data show a projected increase of 7.7% in motorcycle fatalities. Impaired motorcycle operation contributes considerably to motorcycle fatalities and injuries. In fatal crashes in 2004, a higher percentage of motorcycle operators than any other type of motor vehicle operator had blood alcohol concentration (BAC) levels of .08 grams 1 For the purposes of the section 2010 grants, NHTSA proposed in the NPRM that the term ‘‘motorcycle’’ would have the same meaning as in 49 CFR 571.3, ‘‘a motor vehicle with motive power having a seat or saddle for the use of the rider and designed to travel on not more than three wheels in contact with the ground.’’ NHTSA received no comments on the meaning of the term ‘‘motorcycle.’’ Therefore, we retain the definition without change in this final rule. E:\FR\FM\19JYR1.SGM 19JYR1

Agencies

[Federal Register Volume 71, Number 138 (Wednesday, July 19, 2006)]
[Rules and Regulations]
[Pages 40888-40891]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11333]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD; 
Amendment 39-14682; AD 2006-15-02]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC-
6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, 
PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, 
and PC-6/C1-H2 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) that 
supersedes AD 2003-09-01, which applies to certain Pilatus Aircraft Ltd 
(Pilatus) Model PC-6 airplanes. AD 2003-09-01 currently requires you to 
inspect and correct, as necessary, the aileron control bellcrank 
assemblies at the wing and fuselage locations. Since we issued AD 2003-
09-01, the FAA determined the action should also apply to all the 
models of the PC-6 airplanes listed in the type certificate data sheet 
of Type Certificate (TC) No. 7A15 that were produced in the United 
States through a licensing agreement between Pilatus and Fairchild 
Republic Company (also identified as Fairchild Industries, Fairchild 
Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent 
of the applicability of AD 2003-09-01 was to apply to all the affected 
serial numbers of the airplane models listed in TC No. 7A15. This AD 
retains all the actions of AD 2003-09-01, adds those Fairchild Republic 
Company airplanes to the applicability of this AD, and lists the 
individual specific airplane models. We are issuing this AD to detect 
and correct increased friction in the aileron control bellcrank 
assemblies, which could result in failure of the aileron flight-control 
system. Such failure could lead to problems in controlling flight.

DATES: This AD becomes effective on August 23, 2006.
    As of June 17, 2003 (68 FR 22582, April 29, 2003), the Director of 
the Federal Register previously approved the incorporation by reference 
of Pilatus Service Bulletin No. 27-001, dated June 5, 2002, in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

ADDRESSES: To get the service information identified in this AD, 
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224.
    To view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-

[[Page 40889]]

001 or on the Internet at http://dms.dot.gov. The docket number is FAA-
2006-24092; Directorate Identifier 2006-CE-18-AD.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Discussion

    On May 3, 2006, we issued a proposal to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) to include an AD that 
would apply to all the models of the PC-6 airplanes listed in the type 
certificate data sheet of TC No. 7A15 that were produced in the United 
States through a licensing agreement between Pilatus and Fairchild 
Republic Company (also identified as Fairchild Industries, Fairchild 
Heli Porter, or Fairchild-Hiller Corporation) airplanes. This proposal 
was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on May 9, 2006 (71 FR 26891). The NPRM proposed to 
supersede AD 2003-09-01 (68 FR 22582, April 29, 2003), add those 
Fairchild Republic Company airplanes to the applicability of this 
proposed AD, and would list the individual specific airplane models. 
The NPRM proposed to retain all of the actions of AD 2003-09-01 for 
inspecting and correcting, as necessary, the aileron control bellcrank 
assemblies at the wing and fuselage locations.

Comments

    We provided the public the opportunity to participate in developing 
this AD. We received one comment in favor of the proposed AD.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
except for minor editorial corrections. We have determined that these 
minor corrections:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD affects 49 airplanes in the U.S. registry.
    We estimate the following costs to do the inspection and 
modifications:

----------------------------------------------------------------------------------------------------------------
                                                        Total cost per
             Labor cost                  Parts cost        airplane           Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
7 work-hours x $80 per hour = $560..            $300             $860   $860 x 49 = $42,140.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106 describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this AD.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2003-09-01, Amendment 39-13130 (68 FR 22582, April 29, 2003), and by 
adding the following new AD:

2006-15-02 Pilatus Aircraft Ltd.: Amendment 39-14682; Docket No. 
FAA-2006-24092; Directorate Identifier 2006-CE-18-AD.

Effective Date

    (a) This AD becomes effective on August 23, 2006.

Affected ADs

    (b) This AD supersedes AD 2003-09-01, Amendment 39-13130.

Applicability

    (c) This AD affects the following Models PC-6, PC-6-H1, PC-6-H2, 
PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, 
PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/
C1-H2 airplanes that are certificated in any category:
    (1) Group 1 (maintains the actions from AD 2003-09-01): All 
manufacturer serial numbers (MSN) up to and including 939.
    (2) Group 2: MSN 2001 through 2092.

    Note: These airplanes are also identified as Fairchild Republic 
Company PC-6 airplanes, Fairchild Industries PC-6 airplanes, 
Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller 
Corporation PC-6 airplanes.

Unsafe Condition

    (d) This AD results from mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Switzerland that requires retaining the

[[Page 40890]]

actions of AD 2003-09-01 and adding MSN 2001 through 2092 for all 
the models of the PC-6 airplanes listed in the type certificate data 
sheet of Type Certificate No. 7A15. We are issuing this AD to detect 
and correct increased friction in the aileron control bellcrank 
assemblies, which could result in failure of the aileron flight-
control system. Such failure could lead to problems in controlling 
flight.

Compliance

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect, before removal   (A) For Group 1       Follow Pilatus
 of the wing bellcrank         Airplanes: Within     Aircraft Ltd. PC-6
 assemblies, part numbers (P/  the next 100 hours    Service Bulletin
 N) 6132.0071.51 and           time-in-service       No. 27-001, dated
 6132.0071.52, for installed   (TIS) after June      June 5, 2002.
 circlips, P/N N237.           17, 2003 (the
(i) If circlips are            effective date of
 installed, do the actions     AD 2003-09-01),
 required in paragraphs        unless already done.
 (e)(5) and (e)(6) of this    (B) For Group 2
 AD.                           Airplanes: Within
(ii) If circlips are not       the next 100 hours
 installed, perform all        TIS after August
 actions required by           23, 2006 (the
 paragraphs (e)(3), (e)(4),    effective date of
 (e)(5), (e)(6), and (e)(7)    this AD), unless
 of this AD.                   already done.
(2) Inspect, before removal   Before further        Follow Pilatus
 of the fuselage bellcrank     flight after the      Aircraft Ltd. PC-6
 assembly, P/N 6232.0118.00,   inspection required   Service Bulletin
 for the circlip installed     in paragraph (e)(1)   No. 27-001, dated
 on the housing to prevent     of this AD.           June 5, 2002.
 axial movement of the
 bellcrank on its bearing
 and the flange of the
 housing to the rear. If the
 fuselage bellcrank assembly
 has either no circlip and/
 or it is not installed as
 required, perform the
 actions in paragraphs
 (e)(8) and (e)(9) of this
 AD.
(3) Remove the wing           Before further        Follow Pilatus
 bellcrank assemblies, P/Ns    flight after the      Aircraft Ltd. PC-6
 6132.0071.51 and              inspections           Service Bulletin
 6132.0071.52, and inspect     required in           No. 27-001, dated
 for worn or damaged           paragraphs (e)(1)     June 5, 2002.
 bearings. Replace worn or     and (e)(2) of this
 damaged bearings.             AD, as applicable.
(4) Stake and lock the        Before further        Follow Pilatus
 bearing in the housing of     flight after the      Aircraft Ltd. PC-6
 the wing bellcranks, P/Ns     inspections           Service Bulletin
 6132.0071.51 and              required in           No. 27-001, dated
 6132.0071.52.                 paragraphs (e)(1)     June 5, 2002.
                               and (e)(2) of this
                               AD, as applicable.
(5) Inspect the wing          Before further        Follow Pilatus
 bellcranks control-cable      flight after the      Aircraft Ltd. PC-6
 attachment bolts for          inspections           Service Bulletin
 correct type and for signs    required in           No. 27-001, dated
 of rub damage on the heads.   paragraphs (e)(1)     June 5, 2002.
 Replace bolts that are        and (e)(2) of this
 damaged and/or have a total   AD, as applicable.
 length (including head) of
 more than 21.5 mm (0.85
 in.).
(6) Inspect the wing          Before further        Follow Pilatus
 bellcranks support plate      flight after the      Aircraft Ltd. PC-6
 for signs of rub damage       inspections           Service Bulletin
 caused by the bolts. If       required in           No. 27-001, dated
 damage is found:              paragraphs (e)(1)     June 5, 2002.
(i) Obtain a repair scheme     and (e)(2) of this
 from the manufacturer         AD.
 through FAA at the address
 specified in paragraph (f)
 of this AD.
(ii) Incorporate this repair
 scheme..
(7) Reinstall wing bellcrank  Before further        Follow Pilatus
 assemblies.                   flight after the      Aircraft Ltd. PC-6
                               inspections           Service Bulletin
                               required in           No. 27-001, dated
                               paragraphs (e)(1)     June 5, 2002.
                               and (e)(2) of this
                               AD.
(8) Remove the fuselage       Before further        Follow Pilatus
 bellcrank assembly, P/N       flight after the      Aircraft Ltd. PC-6
 6232.0118.00, and inspect     inspections           Service Bulletin
 the housing for wear,         required in           No. 27-001, dated
 damage, and signs of axial    paragraphs (e)(1)     June 5, 2002.
 movement of the bearing in    and (e)(2) of this
 the housing. Replace worn     AD.
 or damaged bearings. If any
 signs of axial movement of
 a bearing are found:
(i) Obtain a repair scheme
 from the manufacturer
 through FAA at the address
 specified in paragraph (f)
 of this AD.
(ii) Incorporate this repair
 scheme..
(9) Reinstall the fuselage    Before further        Follow Pilatus
 bellcrank assembly. Ensure    flight after the      Aircraft Ltd. PC-6
 that the fuselage bellcrank   inspections           Service Bulletin
 assembly is installed so      required in           No. 27-001, dated
 that the surface of the       paragraphs (e)(1),    June 5, 2002.
 bellcrank with the flange     (e)(2), and (e)(8)
 of the housing is installed   of this AD.
 to the rear. The effect of
 this is to lock the
 bellcrank on the bearing
 tube and thus prevent
 movement.
(10) Do not install any       (A) For Group 1       Follow Pilatus
 bellcrank assemblies, P/Ns    Airplanes: As of      Aircraft Ltd. PC-6
 6132.0071.51, 6132,0071.52,   June 17, 2003 (the    Service Bulletin
 and 6232.0118.00 (or FAA-     effective date of     No. 27-001, dated
 approved equivalent part      AD 2003-09-01).       June 5, 2002.
 numbers), unless the         (B) For Group 2
 aileron assembly has been     Airplanes: As of
 inspected, modified, and      August 23, 2006
 installed.                    (the effective date
                               of this AD), unless
                               already done.
------------------------------------------------------------------------


[[Page 40891]]

    (f) Axial movement of serviceable bearings in the housings of 
the wing bellcranks is permitted provided no wear or damage to the 
bearing is found.
    (g) Any sign of axial movement of a bearing in the housing of 
the fuselage bellcrank assembly requires that you obtain a repair 
scheme from the manufacturer through FAA at the address specified in 
paragraph (i) of this AD and incorporate the repair scheme.
    (h) 14 CFR 21.303 allows for replacement parts through parts 
manufacturer approval (PMA). The phrase ``or FAA-approved equivalent 
part number'' in this AD is intended to signify those parts that are 
PMA approved through identicality to the design of the part under 
the type certificate and replacement parts to correct the unsafe 
condition under PMA (other than identicality). If parts are 
installed that are identical to the unsafe parts, then the 
corrective actions of the AD affect these parts also. In addition, 
equivalent replacement parts to correct the unsafe condition under 
PMA (other than identicality) may also be installed provided they 
meet current airworthiness standards, which include those actions 
cited in this AD.

Alternative Methods of Compliance (AMOCs)

    (i) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.
    (j) AMOCs approved for AD 2003-09-01 are approved for this AD.

Related Information

    (k) Swiss AD Number HB 2005-289, effective date August 23, 2005, 
also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must do the actions required by this AD following the 
instructions in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 27-
001, dated June 5, 2002.
    (1) As of June 17, 2003 (68 FR 22582, April 29, 2003), the 
Director of the Federal Register previously approved the 
incorporation by reference of Pilatus Service Bulletin No. 27-001, 
dated June 5, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) To get a copy of this service information, contact Pilatus 
Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; 
telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. To review 
copies of this service information, go to the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, go to: http://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_locations.html or call 
(202) 741-6030. To view the AD docket, go to the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on 
the Internet at http://dms.dot.gov. The docket number is FAA-2006-
24092; Directorate Identifier 2006-CE-18-AD.

    Issued in Kansas City, Missouri, on July 10, 2006.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-11333 Filed 7-18-06; 8:45 am]
BILLING CODE 4910-13-P