AD 2004-12-10 Airworthiness Directives; Hamilton Sundstrand Corporation (Formerly Hamilton Standard Division) Model 568F Propellers

This AD applies to Hamilton Sundstrand Corporation (formerly Hamilton Standard Division) 568F propellers with propeller blades, part numbers (P/Ns) R815505-3 and R815505-4, serial numbers (SNs) FR1699 through FR2625 inclusive (877 blades), and SNs FR20010610 through FR20021010 inclusive (713 blades), installed. These composite propeller blades are installed on, but not limited to, Aerospatiale ATR42-400, ATR42-500, ATR72-212, and ATR72-500 airplanes.

You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Removal From Service of Affected Propeller Blades (f) Remove propeller blades, P/Ns R815505-3 and R815505-4 from service as follows: (1) Blades listed by SN in the following Table 1 of this AD must be removed no later than the date listed in Table 1 of this AD. See Table 2 of this AD for blade SNs that are excluded from the compliance times specified in Table 1 of this AD. (2) Remove the blades that are listed by SN in Table 2 of this AD no later than December 31, 2007. (3) In some instances, an “RT” reference immediately follows the numeric portion of the serial number on the blade. For purposes of this AD, the “RT” reference has been omitted when specifying affected serial numbers. Table 1.—Propeller Blade Removal Schedule For propeller blades SNs: Remove propeller blades from service for rework, no later than: FR1699 through FR1765 December 31, 2003. FR1766 through FR1776 March 31, 2004. FR1777 through FR1855 June 30, 2004. FR1856 through FR1956 September 30, 2004. FR1957 through FR2132 December 31, 2004. FR2133 through FR2230 March 31, 2005. FR2231 through FR2315 June 30, 2005. FR2316 through FR2390 September 30, 2005. FR2391 through FR2433 December 31, 2005. FR2434 through FR2553 March 31, 2006. FR2554 through FR2625 June 30, 2006. FR20010610 through FR20010729 June 30, 2006 FR20010730 through FR20011018 September 30, 2006. FR20011019 through FR20011218 December 31, 2006. FR20011219 through FR20020511 March 31, 2007. FR20020512 through FR20020757 June 30, 2007. FR20020758 through FR20020842 September 30, 2007. FR20020843 through FR20021010 December 31, 2007. Table 2.—Blade SNs Excluded From Table 1         FR1720 FR1887 FR1962 FR2163 FR1740 FR1888 FR1963 FR2164 FR1742 FR1889 FR2013 FR2165 FR1752 FR1892 FR2022 FR2166 FR1777 FR1893 FR2032 FR2167 FR1791 FR1927 FR2037 FR2168 FR1796 FR1928 FR2038 FR2173 FR1841 FR1929 FR2039 FR2177 FR1843 FR1930 FR2047 FR2179 FR1858 FR1931 FR2058 FR2180 FR1860 FR1932 FR2059 FR2183 FR1865 FR1933 FR2060 FR2204 FR1869 FR1934 FR2063 FR2205 FR1871 FR1935 FR2064 FR2206 FR1872 FR1936 FR2067 FR2207 FR1873 FR1937 FR2068 FR2208 FR1874 FR1938 FR2099 FR2233 FR1875 FR1942 FR2108 FR2234 FR1877 FR1943 FR2134 FR2467 FR1878 FR1957 FR2135 FR20010626 FR1879 FR1960 FR2136 FR20010936 FR1880 FR1961 FR2137 FR20011218 Installation of Propeller Blades that have a SN Listed in Table 1 or Table 2 of this AD (g) After the effective date of this AD, do not install any blade that has P/N R815505-3 or R815505-4 and SN listed in Table 1 or Table 2 of this AD, and that has exceeded the date for replacement. Alternative Methods of Compliance (AMOCs) (h) The Manager, Boston 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. Material Incorporated by Reference (i) None. Related Information (j) Hamilton Sundstrand Service Bulletin No. 568F-61-A45, Revision 1, dated October 7, 2003, provides information to rework and remark the affected blades for return to service. Issued in Burlington, Massachusetts, on June 1, 2004. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 04-13145 Filed 6-10-04; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of propeller blades found at inspection, with random areas of missing adhesive under the compression wrap, which exposed the steel tulip part of the blade. We are issuing this AD to prevent propeller blade failure due to corrosion-induced fatigue, which could result in blade separation and possible loss of airplane control.