United States Government Publishing Office publisher pbl distributor dst United States National Archives and Records Administration Office of the Federal Register author aut Government Organization text government publication eng FR Regulatory Information 1996_register executive 2010-09-24 article Rules and Regulations D09002ee1be04ccd4 D09002ee1be04d170 United States Department of Transportation originator org United States Government Agency or Subagency This amendment supersedes an existing airworthiness directive (AD), applicable to 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, that currently requires that all blades of applicable Hamilton Standard propellers be calibrated for ultrasonic transmissibility before conducting the ultrasonic shear wave inspection. In addition, that AD decreases the repetitive inspection interval for the Hamilton Standard Models 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 propellers from 1,250 flight cycles to 500 flight cycles. That AD also establishes a new ultrasonic shear wave inspection interval of 1,000 flight cycles for the Hamilton Standard Model 14RF-19, and 2,500 flight cycles for the Hamilton Standard Model 14RF-21 and Hamilton Standard/British Aerospace Model 6/5500/F. Also, that AD removes Hamilton Standard Model 14SFL11 propellers from service. This amendment requires a blade repair that constitutes terminating action to the repetitive ultrasonic taper bore inspections. Repetitive ultrasonic taper bore inspections are required until the blade is repaired in accordance with this AD. This amendment is prompted by the development of a taper bore repair process that removes the damaged material and returns the blade to a condition that does not require repetitive ultrasonic taper bore inspections. The actions specified by this AD are intended to prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of aircraft control. 61 FR 18052 https://www.govinfo.gov/app/details/FR-1996-04-24/96-9806 96-9806 fr24ap96-4 4910-13-U Docket No. 96-ANE-05 Amendment 39-9568 AD 96-08-02 https://www.govinfo.gov/app/details/FR-1996-04-24/96-9806 https://www.govinfo.gov/content/pkg/FR-1996-04-24/html/96-9806.htm https://www.govinfo.gov/content/pkg/FR-1996-04-24/pdf/96-9806.pdf 7 p. 18052 18058 61 FR 18052 Title 14 Part 39 14 CFR Part 39 Airworthiness Directives; 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; Federal Register Vol. 61, Issue RULE 96-9806 DEPARTMENT OF TRANSPORTATION 1996-05-09 Docket No. 96-ANE-05 Amendment 39-9568 AD 96-08-02 4910-13-U 96-9806 Final rule; request for comments.

This amendment supersedes an existing airworthiness directive (AD), applicable to 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, that currently requires that all blades of applicable Hamilton Standard propellers be calibrated for ultrasonic transmissibility before conducting the ultrasonic shear wave inspection. In addition, that AD decreases the repetitive inspection interval for the Hamilton Standard Models 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 propellers from 1,250 flight cycles to 500 flight cycles. That AD also establishes a new ultrasonic shear wave inspection interval of 1,000 flight cycles for the Hamilton Standard Model 14RF-19, and 2,500 flight cycles for the Hamilton Standard Model 14RF-21 and Hamilton Standard/British Aerospace Model 6/5500/F. Also, that AD removes Hamilton Standard Model 14SFL11 propellers from service. This amendment requires a blade repair that constitutes terminating action to the repetitive ultrasonic taper bore inspections. Repetitive ultrasonic taper bore inspections are required until the blade is repaired in accordance with this AD. This amendment is prompted by the development of a taper bore repair process that removes the damaged material and returns the blade to a condition that does not require repetitive ultrasonic taper bore inspections. The actions specified by this AD are intended to prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of aircraft control.

Effective May 9, 1996. Frank Walsh, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (617) 238-7152, fax (617) 238-7199. Vol. 61, no. 80 Office of the Federal Register, National Archives and Records Administration 1996-04-24 continuing daily deposited born digital 190 p. Table of Contents: AE 2.7: GS 4.107: AE 2.106: KF70.A2 https://www.govinfo.gov/app/details/FR-1996-04-24 P0b002ee180a2dbba 0097-6326 0042-1219 0364-1406 769-004-00000-9 000582072 f:fr24ap96 https://www.govinfo.gov/app/details/FR-1996-04-24 https://www.govinfo.gov/content/pkg/FR-1996-04-24/pdf/FR-1996-04-24.pdf fdlp 18047 18227 DGPO 2010-09-24 2023-05-06 FR-1996-04-24 machine generated eng FR FR-1996-04-24 61 80