AD/PHS/18 Amdt 3 Hub Cracking (Cth)
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/PHS/18 Amdt 2 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Propellers - Variable Pitch - Hamilton Standard
| AD/PHS/18 Amdt 3 | Hub Cracking | 12/2007 |
Applicability: | All model 14RF-9, 14RF-19 and 14RF-21 propellers. Note 1: These propellers may be installed on but are not limited to Embraer |
Requirement: | 1. (a) Perform a torque check of the propeller hub retaining nuts, in accordance with the applicable Hamilton Sundstrand Maintenance Manual (MM). (b) Remove from service propellers where the hub retaining nuts are found not to meet the acceptance criteria outlined in the applicable Hamilton Sundstrand MM. (c) Inspect for cracks in accordance with the applicable Hamilton Sundstrand MM. (d) Remove from service propeller hubs with cracks. (e) If the propeller hub retaining nut torque check is acceptable in accordance with the applicable Hamilton Sundstrand MM, support the propeller with an appropriate lifting fixture and loosen the propeller hub retaining nuts. Tighten the propeller hub retaining nuts as detailed in the applicable Hamilton Sundstrand MM. (f) Make an entry in the propeller maintenance records to record: (i) that the initial torque check was performed; (ii) the propeller hub retaining nuts were loosened and tightened in accordance with Requirement 1(e) of this Directive; and (iii) the torque values. 2. Repeat requirement 1(a) up to and including 1(d) of this Directive. |
| 3. Install all propellers using the propeller hub retaining nut tightening procedure defined in the applicable Hamilton Sundstrand MM. Record the torque values in accordance with Requirement 1(f) (iii) of this Directive. 4. (a) Visually inspect for and investigate all external propeller oil leakage. (b) If the leakage is found to be caused by other than a leak in the blade seal, the pressure relief valve, or actuator assembly, remove the propeller from service. Note 2: FAA AD 94-06-05 Amdt 39-8853 refers. | |
Compliance: | 1 (a) Unless previously accomplished in accordance with the original issue or amendment 1 or 2 of this Directive, within 30 days from the effective date of this Directive. (b) Before further flight after the effective date of this Directive. (c) Unless previously accomplished in accordance with the original issue or amendment 1 or 2 of this Directive, within 30 days from the effective date of this Directive. (d) Before further flight after the effective date of this Directive. (e) Following requirement 1(a) of this Directive and prior to further flight. (f) Following completion of Requirement 1(a) and 1(e) of this Directive. 2. At intervals not to exceed 500 flight hours. 3. From the effective date of this Directive. 4. (a) At intervals not to exceed 70 flight hours. (b) Before further flight after the effective date of this Directive. |
| This Amendment becomes effective on 22 November 2007. | |
Background: | The original issue of this Directive addressed manufacturer’s torqueing procedures for the propeller hub retaining nuts, which was insufficient to prevent fretting during normal propeller operation. If allowed to continue, cracking of the propeller hub may occur. This amendment clarifies the loosening of the propeller hub retaining nuts and recording of the torque values in the propeller maintenance records (which only has to be done initially and when a propeller is installed to the aircraft) and brings the oil leakage inspection interval in line with FAA AD 94-06-05. |
| Amendment 2 corrected errors in Amendment 1 of the Directive with no change to the intent of the Directive. Amendment 1 removed references to manufacturer’s temporary revision and instead refers to the manufacturers publications that incorporate the correct values and procedures for torqueing the propeller hub retaining nuts. Amendment 2 of this Directive became effective 9 June 2005. Amendment 1 of this Directive became effective 27 November 2003. The original issue of this Directive became effective 4 May 1994. |
David Punshon
Delegate of the Civil Aviation Safety Authority
12 October 2007
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