94-17-13 Amendment 39-9008. Docket No. 94-ANE-19. Supersedes ...

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94-17-13 Amendment 39-9008. Docket No. 94-ANE-19. Supersedes AD 93-16-14, Amendment 39-8704. Applicability: Hartzell Propeller Inc. HC-( )3Y( )-( ) series three-bladed propellers with model designa- tions and serial number ranges listed as follows: Propeller Basic Hub Model Propeller Serial Number Range PHC-C3YF-1R( ) EE1 through EE1461 PHC-J3YF-1R( ) FP1 through FP37 PHC-L3YF-1R( ) FD1 through FD7 HC-C3YF-1R( ) EC1 through EC1020 HC-C3YK-1R( ) or HC-C3YR-1R( ) DY1 through DY1897 HC-C3YK-1( ) CT1 through CT101 HC-C3YK-2( ) or HC-C3YR-2( ) CK1 through CK3510 HC-C3YK-4( ) or HC-C3YR-4( ) EL1 through EL67 HC-E3YK-1( ) or HC-E3YR-1( ) FM1 through FM487 HC-E3YK-2( ) or HC-E3YR-2( ) DF1 through DF79 HC-E3YK-2A( ) or HC-E3YR-2A( ) DJ1 through DJ7787 HC-F3YK-2( ) or HC-F3YR-2( ) DA1 through DA1586 HC-F3YK-1( ) or HC-F3YR-1( ) DB1 through DB137 HC-I3YK-2( ) or HC-I3YR-2( ) FS1 through FS32 This airworthiness directive (AD) applies to the above affected propellers when installed on any agricultural aircraft with any engine, or installed on any aircraft utilizing Textron Lycoming TIO-540 or LTIO-540 series reciprocating engines, or IO-540 series reciprocating engines that have a turbo- charger added by the airframe manufacturer or have been modified by a Supplemental Type Certifi- cate (STC) to incorporate a turbocharger, or a turbocharger retrofitted to an IO-540 engine by any other means. The known affected propellers are generally installed on, but not limited to the follow- ing aircraft: AGRICULTURAL AIRCRAFT: Fletcher FU24-950 Cessna A188 Agwagon modified by STC SA895SO Piper PA-36-285 and PA-36-300 (three-bladed propellers only) Piper PA-36-375 Piper PA-36 Pawnee modified by STC SA3952WE Transavia Airtruk Models and PL-12/T-300 Skyfarmer AIRCRAFT WITH TEXTRON LYCOMING TIO-540, LTIO-540, and TURBOCHARGED IO-540 SERIES ENGINES: Cessna 310 and 320 modified by Riley STC SA2082WE Gulfstream 700 (formerly Rockwell 700, Fuji FA-300-12) Helio H-700 Piper PA-23-250 and PA-E23-250 (with TIO-540 only) Piper PA-31 Navajo (with TIO-540 only) Piper PA-31-325 Navajo C/R Piper PA-31-350 Navajo “Chieftain” Piper PA-31P-350 Mohave Piper T-1020 (same as PA-31-350) Piper PA-32(R)-301T Turbo Saratoga Aerostar PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P. Propellers with model designations and serial number ranges listed above and installed on non- agricultural aircraft, which do NOT utilize Textron Lycoming TIO-540, LTIO-540, or turbocharged IO-540 series engines are exempt from this AD. Propellers with new post-1983 hub configurations, i.e., which have the relocated grease fitting holes near the hub parting line as shown in Figure 1, page 9, of Hartzell Propeller, Inc., Service Bulletin (SB) No. 165E, dated January 21, 1994, even though the propeller model and serial number are listed above, are exempt from this AD. Compliance: Required as indicated, unless accomplished previously. To prevent possible propeller hub failure due to cracks that originate in the grease fitting holes on the side of he hub, which could result in propeller blade separation and loss of the aircraft, accom- plish the following: (a) or propellers installed on Textron Lycoming TIO-540 or LTIO-540 series reciprocating engines or turbocharged IO-540 series reciprocating engines which are installed on Piper PA-31-325 Navajo C/R, PA-31-350 Navajo “Chieftain,” T-1020 (same as PA-31-350), PA- 60-700P, Aerostar 700P aircraft, or propellers installed on any agricultural aircraft with any engine, accomplish the following: (1) Within 10 hours time in service (TIS) after the effective date of this AD, but not to exceed 25 hours TIS since the last inspection, whichever occurs first, and thereafter at intervals of 10 hours TIS, perform a visual inspection for presence of grease on the propeller and determine the source of this grease leakage prior to further flight. Following the visual inspection, perform an eddy current inspection (ECI) or fluores- cent penetrant inspection (FPI) for cracks in accordance with Hartzell Propeller Inc. SB No. 165E, dated January 21, 1994. NOTE: Use of a black light to inspect the suspect area can aid in determining the source of grease leakage because authorized grease contains fluorescent properties. i) If grease is leaking from the hub arm or wall, replace the propeller with a serviceable propeller prior to further flight. ii) If grease is determined to be leaking from other causes, take the appropriate corrective maintenance action and record in appropriate maintenance records. (2) If a crack is found in a propeller hub during the inspections required in paragraph (a)(1) of this AD, replace the propeller hub prior to further flight with a new post-1983 configuration propeller hub, or with a serviceable 1983 or earlier hub that has been inspected in accordance with Hartzell Propeller Inc. SB No. 165E, dated January 21, 1994. Thereafter, perform a visual inspection, and ECI or FPI, for cracks in accor- dance with Hartzell Propeller Inc. SB No. 165E, dated January 21, 1994, at intervals not to exceed 10 hours TIS since the last inspection, unless a new post-1983 later style propeller hub is installed, per paragraph (d) of this AD. (b) For propellers installed on all other aircraft models, except for the four non-agricultural models listed in paragraph (a) of this AD, and that utilize Textron Lycoming TIO-540, LTIO- 540, or turbocharged IO-540 series reciprocating engines accomplish the following: (1) Within 50 hours TIS after the effective date of this AD, but not to exceed 50 hours TIS since the last inspection, and thereafter at intervals of 50 hours TIS, perform a visual inspection for presence of grease on the propeller and determine the source of this grease leakage prior to further flight. Following the visual inspection, perform an ECI or FPI for cracks in accordance with Hartzell Propeller Inc. SB No. 165E, dated January 21, 1994.