Airworthiness Directives; Hartzell Propeller Inc. Propellers, 53543-53547 [05-17667]

Download as PDF Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations done before further flight. Repeat the detailed inspection thereafter at intervals not to exceed 60 flight cycles or 3 months, whichever is first, until the actions required by paragraph (i) of this AD are accomplished. Note 1: When a statement identical to that in paragraph (f)(1) of this AD has been included in the general revision of the AFM, the general revision may be inserted into the AFM, and the copy of this AD may be removed from the AFM. ‘‘After each flight in which the slat anti-ice system is activated, inform maintenance.’’ The AFM revision may be done by inserting a copy of this AD into the AFM. Note 3: When a statement identical to that in paragraph (j)(1) of this AD has been included in the general revision of the AFM, the general revision may be inserted into the AFM, and the copy of this AD may be removed from the AFM. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ (g) For airplanes on which the actions described in paragraph (f)(1) of this AD are performed, doing the actions described in paragraph (f)(2) of this AD is terminating action for the requirements of paragraph (f)(1) of this AD. Once the initial detailed inspection specified in paragraph (f)(2) of this AD is performed, the AFM limitation and placard required by paragraph (f)(1) of this AD may be removed. Optional Replacement New Requirements of This AD New Inspections and Intervals (h) For airplanes not operated under the limitation in paragraph (f)(1) of this AD, before the next 10 flight cycles in which the slat anti-icing system is activated after the effective date of this AD: Do a boroscope inspection of each flexible hose installed in the slat anti-icing system. Do all the inspections and any applicable corrective action (including replacing the hose with a new hose having P/N FAL1005D), by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Dassault Alert Service Bulletin F10–A312, Revision 1, dated June 27, 2005. Any corrective action must be done before further flight. Repeat the inspection thereafter at intervals not to exceed 10 flight cycles in which the slat anti-icing system is activated. Doing this inspection terminates the repetitive inspection requirements of paragraph (f)(2) of this AD. (i) For airplanes on which the actions described in paragraph (f)(1) of this AD are performed, doing the actions described in paragraph (h) of this AD is terminating action for the requirements of paragraph (f)(1) of this AD. Once the initial boroscope inspection specified in paragraph (h) of this AD is performed, the AFM limitation and placard required by paragraph (f)(1) of this AD may be removed. AFM Revision (j) For airplanes not operated under the limitation in paragraph (f)(1) of this AD, before further flight after the effective date of this AD: Revise the Limitations section of the Dassault Aviation Falcon 10 AFM, to include the following information. VerDate Aug<18>2005 15:11 Sep 08, 2005 Jkt 205001 (k) For airplanes not operated under the limitation in paragraph (f)(1) of this AD: Replacing the flexible hose installed in the slat anti-icing system with a new hose having P/N FAL1007, in accordance with the Accomplishment Instructions of Dassault Service Bulletin F10–313, dated August 10, 2005, terminates the repetitive inspection intervals of paragraph (h) and (f)(2) of this AD. Repeat the replacement thereafter at intervals not to exceed 90 flight cycles in which the slat anti-icing system is activated. Reporting Requirement (l) At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD: After performing any inspection required by this AD, submit a report of the findings (positive and negative) of the inspection to: Dassault Falcon Jet, Attn: Service Engineering/Falcon 10, fax: (201) 541–4700. The report must include the airplane serial number, the location of the hose (inboard or outboard), the number of flight hours since hose installation, the number of cycles in icing conditions, and the manufacturing date and batch number of the hose. Submission of the Service Bulletins Compliance card, which is attached to Dassault Alert Service Bulletin F10–A312, is an acceptable method of complying with this requirement. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection is done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Actions Accomplished in Accordance With Previous Issue of Service Bulletin (m) Actions accomplished before the effective date of this AD in accordance with the Accomplishment Instructions of Dassault Alert Service Bulletin F10–A312, dated February 25, 2005, are acceptable for compliance with the corresponding action in this AD. Alternative Methods of Compliance (AMOCs) (n) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 53543 Related Information (o) French emergency airworthiness directive EASA.A.AD.01001, dated June 29, 2005, also addresses the subject of this AD. Material Incorporated by Reference (p) You must use Dassault Alert Service Bulletin F10–A312, dated February 25, 2005, including the Service Bulletins Compliance Card; and Dassault Alert Service Bulletin F10–A312, Revision 1, dated June 27, 2005, including the Service Bulletins Compliance Card; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. If accomplished, you must used Dassault Service Bulletin F10– 313, dated August 10, 2005, to perform the optional replacement specified by this AD. (1) The Director of the Federal Register approved the incorporation by reference of Dassault Alert Service Bulletin F10-A312, Revision 1, dated June 27, 2005, including the Service Bulletins Compliance Card; and Dassault Service Bulletin F10–313, dated August 10, 2005; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On April 26, 2005 (70 FR 18282, April 11, 2005), the Director of the Federal Register approved the incorporation by reference of Dassault Alert Service Bulletin F10–A312, dated February 25, 2005, including the Service Bulletins Compliance Card. (3) Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–17598 Filed 9–8–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19955; Directorate Identifier 2004–NE–17–AD; Amendment 39– 14252; AD 2005–18–12] RIN 2120–AA64 Airworthiness Directives; Hartzell Propeller Inc. Propellers Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: E:\FR\FM\09SER1.SGM 09SER1 53544 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Hartzell Propeller Inc. propellers. This AD requires inspecting the propeller blades and other critical propeller parts for corrosion and mechanical damage. This AD results from two events where a ‘‘Z-shank’’ blade failed and separated and the results of teardown inspections that detected corrosion in the blade bore. We are issuing this AD to detect corrosion and mechanical damage that can cause failure of a propeller, which could result in loss of control of the airplane. This AD becomes effective October 14, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of October 14, 2005. DATES: You can get the service information identified in this AD from Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778–4200; fax (937) 778–4391. You may examine the AD docket on the Internet at http://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. ADDRESSES: Tim Smyth, Aerospace Engineer, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; telephone (847) 294–7132; fax (847) 294–7834. FOR FURTHER INFORMATION CONTACT: The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to certain Hartzell Propeller Inc. propellers. We published the proposed AD in the Federal Register on December 29, 2004 (69 FR 77961). That action proposed to require inspecting the propeller blades and other critical propeller parts for corrosion and mechanical damage. SUPPLEMENTARY INFORMATION: Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management System Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. VerDate Aug<18>2005 15:11 Sep 08, 2005 Jkt 205001 Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Recommendation To Modify the AD To Exclude Certain Propellers One commenter recommends that this AD be modified to exclude propellers that have been examined in connection with AD 95–11–08 within the last five years. The commenter feels his propeller has been adequately inspected and he does not want to remove the propeller at this time. Doing so could introduce potential oil leaks that are difficult and expensive to seal. We do not agree. AD 95–11–08 corrects an unsafe condition in blade clamp screws and on the outside surface of the blade shank. The requirements of that AD are not equivalent to the actions mandated by this AD. This AD mandates inspections of the entire propeller assembly, especially the inside surface area of the blade balance hole. Requests To Provide More Clarity in the Compliance Section One commenter requests that we clarify the compliance section. We agree, and reworded it. We changed the title for Table 1 to ‘‘List of Applicable Propeller Assemblies by Hub Model Series’’. The same commenter suggests we should be more specific in detailing the inspection method in Table 3 if we intend a more thorough inspection. We agree. We have changed (b) in Table 3 to state ‘‘Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance hole.’’ The same commenter states that if the FAA intends to detect small or light cracks in the hub or blade clamps, we should consider adding the following text to Table 3, under the ‘‘Then:’’ column, under (c): ‘‘Perform a magneticparticle-inspection of the hub and blade clamps for cracks’’. However, if the FAA intends to detect gross corrosion only, then the added wording in (c) is not needed. The commenter further states that although they support the need for a blade dimensional inspection, they suggest the FAA review the justification for this inspection. The commenter believes the FAA may find this inspection requirement not supportable by service events. We do not agree that (c) should be changed. Appropriate clarifying changes PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 to Table 3, paragraph (b), as noted earlier, achieve the proper inspection. The same commenter suggests that the text to Table 3, under the ‘‘Then:’’ column, under (d) which reads ‘‘Repair and replace with serviceable parts, as necessary’’ be changed to ‘‘If any of these conditions are present, perform additional inspections, including magnetic particle or fluorescentpenetrant inspections as appropriate to determine the serviceability of the part’’. The commenter states that these inspections be specifically required when corrosion or other damage has been visually identified since cracks are more likely to start from these conditions, and the cracks are likely to be small and only detectable by magnetic particle or fluorescentpenetrant inspection. We do not agree that (d) should be changed. Appropriate clarifying changes to Table 3, paragraph (b), as noted earlier, achieve the proper inspection. Request for Repetitive Inspections One commenter, the National Transportation Safety Board (NTSB), states that it generally supports the proposed AD. However, the NTSB notes that the proposed AD only proposes a onetime inspection rather than a repetitive inspection. The commenter further states that although the proposed AD also includes a requirement to report inspection findings and indicates that we will use this information to determine whether repetitive inspections are in order, the NTSB continues to believe that repetitive inspections best reflect the manufacturer’s inspection recommendations. These recommendations have been established in consideration of product design and service requirements. Therefore, the NTSB again urges us to require that these propellers be subject to repetitive inspections. We do not agree. Our review of the service history for the specified propellers supports the need for a onetime action, especially in light of the aging of the specified propeller fleet. As stated in the proposed AD, we will review the need for a repetitive inspection only if new reports submitted per the AD requirements, document the need to mandate a repetitive inspection. We encourage the public to comply with manufacturer’s maintenance recommendations, but the public is only required to maintain their aircraft in accordance with 14 CFR part 91 requirements. E:\FR\FM\09SER1.SGM 09SER1 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 1,700 Hartzell propeller assemblies of the affected design in the worldwide fleet. We estimate that 1,200 propeller assemblies installed on airplanes of U.S. registry will be affected by this AD. We also estimate that it will take about 20 work hours per propeller assembly to perform the actions, and that the average labor rate is $65 per work hour. Required parts will cost about $450 per propeller assembly. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $2,100,000. 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 rulemaking action. 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 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 placed it in the AD Docket. You may get a copy of this summary at the address listed under 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 14 CFR part 39 as follows: I 53545 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2005–18–12 Hartzell Propeller Inc. Propellers: Amendment 39–14252. Docket No. FAA–2004–19955; Directorate Identifier. 2004–NE–17–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 14, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Hartzell propeller assemblies with hub model series specified in Table 1 of this AD. These propellers are installed on, but not limited to, the aircraft listed in Table 2 of this AD. TABLE 1.—LIST OF APPLICABLE PROPELLER ASSEMBLIES BY HUB MODEL SERIES HC–92W Hub Model Series BHC–92W Hub Model Series HC–92Z Hub Model Series BHC–92Z Hub Model Series HC–B3P Hub Model Series HC–B3R Hub Model Series HC–B3W Hub Model Series BHC–B3W Hub Model Series HA–B3Z Hub Model Series HC–B3Z Hub Model Series TABLE 2.—LIST OF AIRPLANES THAT MIGHT USE AN AFFECTED PROPELLER ASSEMBLY Aircraft manufacturer Aircraft model AERMACCHI (AERONAUTICA MACCHI) ............................................... AERO COMMANDER .............................................................................. AEROSPATIALE (MORANE SAULNIER) ................................................ AEROSTAR AIRCRAFT CORP. .............................................................. AEROTEK II, INC. (CALLAIR) ................................................................. AIR & SPACE ........................................................................................... BEECH ..................................................................................................... AM–3C 560–F680, 680E, 680F, 680FL, 680FLP, 720 733 360 B1A (CALLAIR) 18, 18A 18 SERIES C45 35 SERIES A65, 65, 65–80, 65–A80, 65–B80, 65–88 95, B95, B95A, D95A, E95 70 C18S [(C–45(A, F), UC–45(B, F), AT–7 (A, B, C), JRB–(1, 2, 3, 4), SNB–2(C)] C18S, AT–11 C–45G,C–45H; TC–45G, H, J; RC–45J D18S,E18S, G18S, H18; 3N, 3NM, 3TM E50, F50, G50, H50, J50 BUSHMASTER 2000 172 175, 175A BUSHMASTER AIRCRAFT CORP .......................................................... CESSNA ................................................................................................... VerDate Aug<18>2005 15:11 Sep 08, 2005 Jkt 205001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\09SER1.SGM 09SER1 53546 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations TABLE 2.—LIST OF AIRPLANES THAT MIGHT USE AN AFFECTED PROPELLER ASSEMBLY—Continued Aircraft manufacturer Aircraft model CESSNA ................................................................................................... DE HAVILLAND CANADA ....................................................................... DORNIER ................................................................................................. FOUND BROTHERS ................................................................................ FOUND BROTHERS ................................................................................ GOODYEAR (LOCKHEED MARTIN) ....................................................... GRUMMAN (GULFSTREAM AERO.) ...................................................... GRUMMAN (MCKINNON) ........................................................................ HELIO ....................................................................................................... ICA (ROMANIA) ....................................................................................... JOBMASTER ............................................................................................ KWAD ....................................................................................................... LAKE (REVO) ........................................................................................... LOCKHEED .............................................................................................. MESSERSCHMITT ................................................................................... MOONEY .................................................................................................. NAVY ........................................................................................................ NORD ....................................................................................................... PACIFIC AEROSPACE (FLETCHER) ..................................................... PIAGGIO ................................................................................................... PILATUS ................................................................................................... PIPER ....................................................................................................... PROCAER ................................................................................................ REVO (COLONIAL) .................................................................................. SAAB ........................................................................................................ SCHWEIZER (GRUMMAN) ...................................................................... SIMMERING GRAZ PAUKER A.G .......................................................... SPARTON ................................................................................................ UTVA ........................................................................................................ WDL AVIATION (formerly WDL FLUGDIENST) ...................................... WEATHERLY ........................................................................................... 190, 195, A, B 421, 421A A185E, A185F (SEAPLANES ONLY) T50 DHC–2 MKI DO28D, DO28D–1 100 FBA–2C GZ20, GZ20A G44, G44A G21A H–250 H–295, HT–295 (U–10D) H–395 (L–28A, U–10B) H–500 IAR–831 DGA–15P SUPER–V LA–4 12A 207 M20A N3N–3 3400, 3402 FU–24, FU–24A P–166B, C PC–6/350; PC–6/350–H1, –H2 PA–23 PA–24 PA–25 F15/B C–2 91D SAFIR G–164 SGP222 7W 66 An Airship 201B, 201C, 620, 620A, 620C Unsafe Condition Aircraft With Experimental Type Certificates (d) This AD results from two events where a ‘‘Z-shank’’ blade failed and separated and the results of teardown inspections that detected corrosion in the blade bore. We are issuing this AD to detect corrosion and mechanical damage that can cause failure of a propeller, which could result in loss of control of the airplane. (f) We recommend that you comply with the inspection requirements of this AD, if you have an aircraft with an experimental type certificate, and you have a propeller hub model listed in this AD installed on that aircraft. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. VerDate Aug<18>2005 15:11 Sep 08, 2005 Jkt 205001 Inspection of the Propeller (g) If the time-since-overhaul (TSO) of the propeller is 10 years or fewer on the effective date of this AD, no further action is required. (h) If the propeller assembly was inspected using Hartzell Service Bulletin (SB) No. HC– SB–61–136, Revision I, dated April 25, 2003; SB No. 136, Revision H, dated March 12, 1993; or SB No. 136, Revision G, dated PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 November 15, 1991; no further action is required. (i) If the TSO of the propeller assembly is more than 10 years on the effective date of this AD, or if the TSO is unknown, or if the propeller has not complied with Hartzell SB No. HC–SB–61–136, Revision I, dated April 25, 2003; or SB No. 136, Revision H, dated March 12, 1993; or SB No. 136, Revision G, dated November 15, 1991; perform the actions specified in Table 3 of this AD. Use the compliance times specified in Table 3 of this AD. Information on inspecting the propeller assembly for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance bore can be found in the applicable Hartzell maintenance manuals. E:\FR\FM\09SER1.SGM 09SER1 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 53547 TABLE 3.—COMPLIANCE TIMES FOR ONETIME INSPECTION If the TSO of the propeller assembly on the effective date of this AD is . . . (1) More 25 years or the TSO is not known. (2) Twenty-one to 25 years ............. (3) Sixteen to 20 years ................... (4) Eleven to 15 years .................... Then . . . Perform the the inspection . . . (a) Disassemble and clean the propeller assembly .............................. (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test. (a) Disassemble and clean the propeller assembly .............................. (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test. (a) Disassemble and clean the propeller assembly .............................. (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test. (a) Disassemble and clean the propeller assembly .............................. (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test. Within 12 months after the effective date of this AD. Related Information Propeller Overhaul (j) Performing an overhaul of the propeller assembly after the effective date of this AD constitutes compliance with the requirements specified in this AD. The latest applicable Maintenance Manuals issued by Hartzell Propeller Inc. contain information on overhauling a propeller assembly. (k) The time-since-overhaul only changes if you overhaul the propeller assembly while performing the requirements specified in this AD. Reporting Requirements (l) Report inspection results to the Manager, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Ave, Des Plaines, IL 60018, within 15 working days of the inspection. The Office of Management and Budget (OMB) approved the reporting requirements and assigned OMB control number 2120–0056. Alternative Methods of Compliance (m) The Manager, Chicago Aircraft Certification Office has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. VerDate Aug<18>2005 15:11 Sep 08, 2005 Jkt 205001 (n) None. Material Incorporated by Reference (o) You must use Hartzell Service Bulletin No. HC–SB–61–136, Revision I, dated April 25, 2003, to perform the inspections and rework required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778–4200; fax (937) 778–4391, for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–0001, on the internet at http://dms.dot.gov, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Within 18 months after the effective date of this AD. Within 24 months after the effective date of this AD. Within 36 months after the effective date of this AD. Issued in Burlington, Massachusetts, on August 29, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–17667 Filed 9–8–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22252; Directorate Identifier 2005–NM–182–AD; Amendment 39–14260; AD 2005–18–51] RIN 2120–AA64 Airworthiness Directives; Boeing Model 777 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: E:\FR\FM\09SER1.SGM 09SER1

Agencies

[Federal Register Volume 70, Number 174 (Friday, September 9, 2005)]
[Rules and Regulations]
[Pages 53543-53547]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-17667]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19955; Directorate Identifier 2004-NE-17-AD; 
Amendment 39-14252; AD 2005-18-12]
RIN 2120-AA64


Airworthiness Directives; Hartzell Propeller Inc. Propellers

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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[[Page 53544]]

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Hartzell Propeller Inc. propellers. This AD requires inspecting 
the propeller blades and other critical propeller parts for corrosion 
and mechanical damage. This AD results from two events where a ``Z-
shank'' blade failed and separated and the results of teardown 
inspections that detected corrosion in the blade bore. We are issuing 
this AD to detect corrosion and mechanical damage that can cause 
failure of a propeller, which could result in loss of control of the 
airplane.

DATES: This AD becomes effective October 14, 2005. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of October 14, 2005.

ADDRESSES: You can get the service information identified in this AD 
from Hartzell Propeller Inc. Technical Publications Department, One 
Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 
778-4391.
    You may examine the AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim Smyth, Aerospace Engineer, Chicago 
Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 
East Devon Avenue, Des Plaines, IL 60018-4696; telephone (847) 294-
7132; fax (847) 294-7834.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to certain Hartzell Propeller Inc. propellers. We published the 
proposed AD in the Federal Register on December 29, 2004 (69 FR 77961). 
That action proposed to require inspecting the propeller blades and 
other critical propeller parts for corrosion and mechanical damage.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
System Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5227) 
is located on the plaza level of the Department of Transportation 
Nassif Building at the street address stated in ADDRESSES. Comments 
will be available in the AD docket shortly after the DMS receives them.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Recommendation To Modify the AD To Exclude Certain Propellers

    One commenter recommends that this AD be modified to exclude 
propellers that have been examined in connection with AD 95-11-08 
within the last five years. The commenter feels his propeller has been 
adequately inspected and he does not want to remove the propeller at 
this time. Doing so could introduce potential oil leaks that are 
difficult and expensive to seal.
    We do not agree. AD 95-11-08 corrects an unsafe condition in blade 
clamp screws and on the outside surface of the blade shank. The 
requirements of that AD are not equivalent to the actions mandated by 
this AD. This AD mandates inspections of the entire propeller assembly, 
especially the inside surface area of the blade balance hole.

Requests To Provide More Clarity in the Compliance Section

    One commenter requests that we clarify the compliance section. We 
agree, and reworded it. We changed the title for Table 1 to ``List of 
Applicable Propeller Assemblies by Hub Model Series''.
    The same commenter suggests we should be more specific in detailing 
the inspection method in Table 3 if we intend a more thorough 
inspection. We agree. We have changed (b) in Table 3 to state ``Perform 
visual and nondestructive inspections of propeller components for 
cracks, corrosion or pits, nicks, scratches, wear, blade minimum 
dimensions, and damage in the blade balance hole.''
    The same commenter states that if the FAA intends to detect small 
or light cracks in the hub or blade clamps, we should consider adding 
the following text to Table 3, under the ``Then:'' column, under (c): 
``Perform a magnetic-particle-inspection of the hub and blade clamps 
for cracks''. However, if the FAA intends to detect gross corrosion 
only, then the added wording in (c) is not needed. The commenter 
further states that although they support the need for a blade 
dimensional inspection, they suggest the FAA review the justification 
for this inspection. The commenter believes the FAA may find this 
inspection requirement not supportable by service events.
    We do not agree that (c) should be changed. Appropriate clarifying 
changes to Table 3, paragraph (b), as noted earlier, achieve the proper 
inspection.
    The same commenter suggests that the text to Table 3, under the 
``Then:'' column, under (d) which reads ``Repair and replace with 
serviceable parts, as necessary'' be changed to ``If any of these 
conditions are present, perform additional inspections, including 
magnetic particle or fluorescent-penetrant inspections as appropriate 
to determine the serviceability of the part''. The commenter states 
that these inspections be specifically required when corrosion or other 
damage has been visually identified since cracks are more likely to 
start from these conditions, and the cracks are likely to be small and 
only detectable by magnetic particle or fluorescent-penetrant 
inspection.
    We do not agree that (d) should be changed. Appropriate clarifying 
changes to Table 3, paragraph (b), as noted earlier, achieve the proper 
inspection.

Request for Repetitive Inspections

    One commenter, the National Transportation Safety Board (NTSB), 
states that it generally supports the proposed AD. However, the NTSB 
notes that the proposed AD only proposes a onetime inspection rather 
than a repetitive inspection. The commenter further states that 
although the proposed AD also includes a requirement to report 
inspection findings and indicates that we will use this information to 
determine whether repetitive inspections are in order, the NTSB 
continues to believe that repetitive inspections best reflect the 
manufacturer's inspection recommendations. These recommendations have 
been established in consideration of product design and service 
requirements. Therefore, the NTSB again urges us to require that these 
propellers be subject to repetitive inspections.
    We do not agree. Our review of the service history for the 
specified propellers supports the need for a onetime action, especially 
in light of the aging of the specified propeller fleet. As stated in 
the proposed AD, we will review the need for a repetitive inspection 
only if new reports submitted per the AD requirements, document the 
need to mandate a repetitive inspection. We encourage the public to 
comply with manufacturer's maintenance recommendations, but the public 
is only required to maintain their aircraft in accordance with 14 CFR 
part 91 requirements.

[[Page 53545]]

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 1,700 Hartzell propeller assemblies of the affected 
design in the worldwide fleet. We estimate that 1,200 propeller 
assemblies installed on airplanes of U.S. registry will be affected by 
this AD. We also estimate that it will take about 20 work hours per 
propeller assembly to perform the actions, and that the average labor 
rate is $65 per work hour. Required parts will cost about $450 per 
propeller assembly. Based on these figures, we estimate the total cost 
of the AD to U.S. operators to be $2,100,000.

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 
rulemaking action.

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 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 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

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 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2005-18-12 Hartzell Propeller Inc. Propellers: Amendment 39-14252. 
Docket No. FAA-2004-19955; Directorate Identifier. 2004-NE-17-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
14, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Hartzell propeller assemblies with hub 
model series specified in Table 1 of this AD. These propellers are 
installed on, but not limited to, the aircraft listed in Table 2 of 
this AD.

  Table 1.--List of Applicable Propeller Assemblies by Hub Model Series
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
HC-92W Hub Model Series
BHC-92W Hub Model Series
HC-92Z Hub Model Series
BHC-92Z Hub Model Series
HC-B3P Hub Model Series
HC-B3R Hub Model Series
HC-B3W Hub Model Series
BHC-B3W Hub Model Series
HA-B3Z Hub Model Series
HC-B3Z Hub Model Series
------------------------------------------------------------------------


    Table 2.--List of Airplanes That Might Use An Affected Propeller
                                Assembly
------------------------------------------------------------------------
         Aircraft manufacturer                    Aircraft model
------------------------------------------------------------------------
AERMACCHI (AERONAUTICA MACCHI).........  AM-3C
AERO COMMANDER.........................  560-F680, 680E, 680F, 680FL,
                                          680FLP, 720
AEROSPATIALE (MORANE SAULNIER).........  733
AEROSTAR AIRCRAFT CORP.................  360
AEROTEK II, INC. (CALLAIR).............  B1A (CALLAIR)
AIR & SPACE............................  18, 18A
BEECH..................................  18 SERIES
                                         C45
                                         35 SERIES
                                         A65, 65, 65-80, 65-A80, 65-B80,
                                          65-88
                                         95, B95, B95A, D95A, E95
                                         70
                                         C18S [(C-45(A, F), UC-45(B, F),
                                          AT-7 (A, B, C), JRB-(1, 2, 3,
                                          4), SNB-2(C)]
                                         C18S, AT-11
                                         C-45G,C-45H; TC-45G, H, J; RC-
                                          45J
                                         D18S,E18S, G18S, H18; 3N, 3NM,
                                          3TM
                                         E50, F50, G50, H50, J50
BUSHMASTER AIRCRAFT CORP...............  BUSHMASTER 2000
CESSNA.................................  172
                                         175, 175A

[[Page 53546]]

 
                                         190, 195, A, B
                                         421, 421A
                                         A185E, A185F (SEAPLANES ONLY)
CESSNA.................................  T50
DE HAVILLAND CANADA....................  DHC-2 MKI
DORNIER................................  DO28D, DO28D-1
FOUND BROTHERS.........................  100
FOUND BROTHERS.........................  FBA-2C
GOODYEAR (LOCKHEED MARTIN).............  GZ20, GZ20A
GRUMMAN (GULFSTREAM AERO.).............  G44, G44A
GRUMMAN (MCKINNON).....................  G21A
HELIO..................................  H-250
                                         H-295, HT-295 (U-10D)
                                         H-395 (L-28A, U-10B)
                                         H-500
ICA (ROMANIA)..........................  IAR-831
JOBMASTER..............................  ...............................
                                         DGA-15P
KWAD...................................  SUPER-V
LAKE (REVO)............................  LA-4
LOCKHEED...............................  12A
MESSERSCHMITT..........................  207
MOONEY.................................  M20A
NAVY...................................  N3N-3
NORD...................................  3400, 3402
PACIFIC AEROSPACE (FLETCHER)...........  FU-24, FU-24A
PIAGGIO................................  P-166B, C
PILATUS................................  PC-6/350; PC-6/350-H1, -H2
PIPER..................................  PA-23
                                         PA-24
                                         PA-25
PROCAER................................  F15/B
REVO (COLONIAL)........................  C-2
SAAB...................................  91D SAFIR
SCHWEIZER (GRUMMAN)....................  G-164
SIMMERING GRAZ PAUKER A.G..............  SGP222
SPARTON................................  7W
UTVA...................................  66
WDL AVIATION (formerly WDL FLUGDIENST).  An Airship
WEATHERLY..............................  201B, 201C, 620, 620A, 620C
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from two events where a ``Z-shank'' blade 
failed and separated and the results of teardown inspections that 
detected corrosion in the blade bore. We are issuing this AD to 
detect corrosion and mechanical damage that can cause failure of a 
propeller, which could result in loss of control of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Aircraft With Experimental Type Certificates

    (f) We recommend that you comply with the inspection 
requirements of this AD, if you have an aircraft with an 
experimental type certificate, and you have a propeller hub model 
listed in this AD installed on that aircraft.

Inspection of the Propeller

    (g) If the time-since-overhaul (TSO) of the propeller is 10 
years or fewer on the effective date of this AD, no further action 
is required.
    (h) If the propeller assembly was inspected using Hartzell 
Service Bulletin (SB) No. HC-SB-61-136, Revision I, dated April 25, 
2003; SB No. 136, Revision H, dated March 12, 1993; or SB No. 136, 
Revision G, dated November 15, 1991; no further action is required.
    (i) If the TSO of the propeller assembly is more than 10 years 
on the effective date of this AD, or if the TSO is unknown, or if 
the propeller has not complied with Hartzell SB No. HC-SB-61-136, 
Revision I, dated April 25, 2003; or SB No. 136, Revision H, dated 
March 12, 1993; or SB No. 136, Revision G, dated November 15, 1991; 
perform the actions specified in Table 3 of this AD. Use the 
compliance times specified in Table 3 of this AD. Information on 
inspecting the propeller assembly for cracks, corrosion or pits, 
nicks, scratches, wear, blade minimum dimensions, and damage in the 
blade balance bore can be found in the applicable Hartzell 
maintenance manuals.

[[Page 53547]]



            Table 3.--Compliance Times for Onetime Inspection
------------------------------------------------------------------------
  If the TSO of the propeller
assembly on the effective date        Then . . .         Perform the the
      of this AD is . . .                               inspection . . .
------------------------------------------------------------------------
(1) More 25 years or the TSO    (a) Disassemble and     Within 12 months
 is not known.                   clean the propeller     after the
                                 assembly.               effective date
                                (b) Perform visual and   of this AD.
                                 nondestructive
                                 inspections of
                                 propeller components
                                 for cracks, corrosion
                                 or pits, nicks,
                                 scratches, wear,
                                 blade minimum
                                 dimensions, and
                                 damage in the blade
                                 balance hole.
                                (c) Inspect and rework
                                 the propeller blade
                                 bore. Use 3.A. of the
                                 Accomplishment
                                 instructions of
                                 Hartzell SB No. HC-SB-
                                 61-136, Revision I,
                                 dated April 26, 2003.
                                (d) Repair and replace
                                 with serviceable
                                 parts, as necessary..
                                (e) Reassemble and
                                 test..
(2) Twenty-one to 25 years....  (a) Disassemble and     Within 18 months
                                 clean the propeller     after the
                                 assembly.               effective date
                                (b) Perform visual and   of this AD.
                                 nondestructive
                                 inspections of
                                 propeller components
                                 for cracks, corrosion
                                 or pits, nicks,
                                 scratches, wear,
                                 blade minimum
                                 dimensions, and
                                 damage in the blade
                                 balance hole.
                                (c) Inspect and rework
                                 the propeller blade
                                 bore. Use 3.A. of the
                                 Accomplishment
                                 instructions of
                                 Hartzell SB No. HC-SB-
                                 61-136, Revision I,
                                 dated April 26, 2003.
                                (d) Repair and replace
                                 with serviceable
                                 parts, as necessary..
                                (e) Reassemble and
                                 test..
(3) Sixteen to 20 years.......  (a) Disassemble and     Within 24 months
                                 clean the propeller     after the
                                 assembly.               effective date
                                (b) Perform visual and   of this AD.
                                 nondestructive
                                 inspections of
                                 propeller components
                                 for cracks, corrosion
                                 or pits, nicks,
                                 scratches, wear,
                                 blade minimum
                                 dimensions, and
                                 damage in the blade
                                 balance hole.
                                (c) Inspect and rework
                                 the propeller blade
                                 bore. Use 3.A. of the
                                 Accomplishment
                                 instructions of
                                 Hartzell SB No. HC-SB-
                                 61-136, Revision I,
                                 dated April 26, 2003.
                                (d) Repair and replace
                                 with serviceable
                                 parts, as necessary..
                                (e) Reassemble and
                                 test..
(4) Eleven to 15 years........  (a) Disassemble and     Within 36 months
                                 clean the propeller     after the
                                 assembly.               effective date
                                (b) Perform visual and   of this AD.
                                 nondestructive
                                 inspections of
                                 propeller components
                                 for cracks, corrosion
                                 or pits, nicks,
                                 scratches, wear,
                                 blade minimum
                                 dimensions, and
                                 damage in the blade
                                 balance hole.
                                (c) Inspect and rework
                                 the propeller blade
                                 bore. Use 3.A. of the
                                 Accomplishment
                                 instructions of
                                 Hartzell SB No. HC-SB-
                                 61-136, Revision I,
                                 dated April 26, 2003.
                                (d) Repair and replace
                                 with serviceable
                                 parts, as necessary..
                                (e) Reassemble and
                                 test..
------------------------------------------------------------------------

Propeller Overhaul

    (j) Performing an overhaul of the propeller assembly after the 
effective date of this AD constitutes compliance with the 
requirements specified in this AD. The latest applicable Maintenance 
Manuals issued by Hartzell Propeller Inc. contain information on 
overhauling a propeller assembly.
    (k) The time-since-overhaul only changes if you overhaul the 
propeller assembly while performing the requirements specified in 
this AD.

Reporting Requirements

    (l) Report inspection results to the Manager, Chicago Aircraft 
Certification Office, FAA, Small Airplane Directorate, 2300 East 
Devon Ave, Des Plaines, IL 60018, within 15 working days of the 
inspection. The Office of Management and Budget (OMB) approved the 
reporting requirements and assigned OMB control number 2120-0056.

Alternative Methods of Compliance

    (m) The Manager, Chicago Aircraft Certification Office has the 
authority to approve alternative methods of compliance for this AD 
if requested using the procedures found in 14 CFR 39.19.

Related Information

    (n) None.

Material Incorporated by Reference

    (o) You must use Hartzell Service Bulletin No. HC-SB-61-136, 
Revision I, dated April 25, 2003, to perform the inspections and 
rework required by this AD. The Director of the Federal Register 
approved the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hartzell 
Propeller Inc. Technical Publications Department, One Propeller 
Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 778-
4391, for a copy of this service information. You may review copies 
at the Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-0001, on the internet at http://
dms.dot.gov, or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on August 29, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-17667 Filed 9-8-05; 8:45 am]
BILLING CODE 4910-13-P