AD 95-05-03 Airworthiness Directives; Hamilton Standard 14RF Series, 14SF Series, and Hamilton Standard/British Aerospace Model 6/5500/F Propellers

Hamilton Standard Models 14RF-9, 14RF-19, 14RF- 21, and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propellers installed on but not limited to Embraer EMB-120 and EMB 120-RT; SAAB-SCANIA SF 340B; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72; DeHavilland DHC-8-100 series, DHC-8-300 Series; Construcciones Aeronauticas SA (CASA) CN-235 series and CN-235-100; Canadair CL-215T and CL-415; and British Aerospace ATP airplanes.

Required as indicated, unless accomplished previously. To prevent loss of a propeller blade due to cracks initiating in the blade taper bore, that can result in possible aircraft damage, and possible loss of aircraft control, accomplish the following: (a) For propeller blades that have accumulated 1,750 or more flight cycles since ultrasonic shear wave inspection in accordance with AD 94-09-06, perform either paragraph (a) or (d) of this AD within 100 flight cycles of the effective date of this AD: (1) Perform an ultrasonic shear wave inspection for cracks in the blade taper bore, in accordance with the procedures described in the following Hamilton Standard Alert Service Bulletins (ASB's), as applicable: No. 14RF-21-61-A53, dated April 18, 1994, and No. 14RF- 21-61-A55, Revision 1, dated October 5, 1994; No. 14SF-61-A73, dated April 18, 1994, and No. 14SF-61-A74, [[Page 12665]] Revision 1, dated October 5, 1994; No. 14RF-19-61-A34, dated April 18, 1994, and No. 14RF-19-61-A36, Revision 1, dated October 5, 1994; No. 14RF-9- 61-A66, dated April 18, 1994, and No. 14RF-9-61-A69, Revision 1, dated October 5, 1994; No. 6/5500/F-61-A27, dated April 18, 1994, and No. 6/5500/F-61-A29, dated August 29, 1994. Remove cracked propeller blades and replace with a serviceable blade prior to further flight. (2) Thereafter, perform repetitive ultrasonic shear wave inspections at intervals not to exceed 1,250 CIS since last inspection in accordance with the applicable Hamilton Standard ASB's listed in paragraph (a)(1) of this airworthiness directive (AD). Remove cracked propeller blades and replace with a serviceable blade prior to further flight. (3) No later than December 31, 1997, perform the visual and borescope inspection required by paragraph (d) of this AD. (b) For propeller blades that have accumulated less than 1,750 flight cycles since ultrasonic shear wave inspection in accordance with AD 94-09-06, perform either paragraph (a) or (d) of this AD before accumulating 1,850 flight cycles since ultrasonic shear wave inspection in accordance with AD 94-09-06. (c) For propeller blades that have not been inspected in accordance with AD 94-09-06, perform paragraphs (a)(1) or (d) of this AD prior to installing the blade in service and thereafter perform paragraph (a)(2) of this AD if applicable. (d) Prior to December 31, 1997, remove and scrap the propeller inner taper bore cork seal and visually inspect the inside surface of the taper bore for corrosion pits in accordance with the applicable Hamilton Standard Service Bulletins (SB's): No. 14RF-9- 61-70, dated August 26, 1994; No. 14RF-19-61-37, dated August 29, 1994; No. 14RF-21-61-56, dated August 29, 1994; No. 14SF-61-75, dated August 29, 1994; and No. 6/5500/F-61-30, dated August 29, 1994. (1) For propeller blades found with any corrosion pits, remove from service prior to further flight and send the propeller blades to an FAA-approved repair facility for disposition in accordance with Hamilton Standard ASB's No. 14SF-61-A74, Revision 1, dated October 5, 1994; No. 14RF-9-61-A69, Revision 1, dated October 5, 1994; No. 14RF-19-61-A36, Revision 1, dated October 5, 1994; No. 14RF-21-61-A55, Revision 1, dated October 5, 1994; and No. 6/5500/F- 61-A29, dated August 29, 1994; as applicable. (2) For propeller blades found with no corrosion pits, mark the blade and return it to service in accordance with the Hamilton Standard SB's listed in paragraph (d) of this AD. (3) Returning propeller blades to service in accordance with paragraph (d) of this AD constitutes terminating action to the repetitive ultrasonic shear wave inspections required by paragraph (a)(2) of this AD. (e) For the purpose of this AD, a flight cycle is defined as one takeoff and the next landing of an aircraft. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Boston Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. Note: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Boston Aircraft Certification Office. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (h) The requirements of this AD shall be done in accordance with the following Hamilton Standard ASB's and SB's: ------------------------------------------------------------------------ Document No. Pages Revision Date ------------------------------------------------------------------------ ASB No. 14SF-61- 1-7 1............... October 5, 1994. A74. Total pages: 7. ASB No. 14SF-61- 1-19 Original........ April 18, 1994. A73. Total pages: 19. SB No. 14SF-61-75. 1-17 Original........ August 29, 1994. Total pages: 17. ASB No. 14RF-9-61- 1-6 1............... October 5, 1994. A69. Total pages: 6. ASB No. 14RF-9-61- 1-19 Original........ April 18, 1994. A66. Total pages: 19. SB No. 14RF-9-61- 1-17 Original........ August 29, 1994. 70. Total pages: 17. ASB No. 14RF-19-61- 1-6 1............... October 5, 1994. A36. Total pages: 6. ASB No. 14RF-19-61- 1-19 Original........ April 18, 1994. A34. Total pages: 19. SB No. 14RF-19-61- 1-17 Original........ August 29, 1994. 37. Total pages: 17. ASB No. 14RF-21-61- 1-6 1............... October 5, 1994. A55. Total pages: 6. ASB No. 14RF-21-61- 1-19 Original........ April 18, 1994. A53. Total pages: 19. SB No. 14RF-21-61- 1-17 Original........ August 29, 1994. 56. Total pages: 17. ASB No. 6/5500/F- 1-5 Original........ August 29, 1994. 61-A29. Total pages: 5. ASB No. 6/5500/F- 1-19 Original........ April 18, 1994. 61-A27. Total pages: 19. SB No. 6/5500/F-61- 1-17 Original........ August 29, 1994. 30. Total pages: 17. ------------------------------------------------------------------------ The incorporation by reference of the following Hamilton Standard ASB's was approved by the Director of the Federal Register as of May 2, 1994: ASB's No. 14RF-9-61-A66, No. 14RF-19-61-A34, No. 14RF-21-61-A53, No. 14SF-61-A73, and No.P6/5500/F-61-A27, all dated April 18, 1994. The incorporation by reference of all other Hamilton Standard ASB's and SB's listed in this AD was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010; telephone (203) 654-3610. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on March 23, 1995. [[Page 12666]] Issued in Burlington, Massachusetts, on February 28, 1995. James C. Jones, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 95-5483 Filed 3-7-95; 8:45 am] BILLING CODE 4910-13-P