Propellers - Variable Pitch - Hamilton Standard
AD/PHS/18  Amdt 2  Hub Cracking 6/2005

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 EMB-120 series, CASA CN-235 series and SAAB SF-340 series aircraft.

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 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(d) 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 of this Directive, within 30 days from the effective date of this Directive.
(b) Before further flight.
(c) Unless previously accomplished in accordance with the original issue or amendment 1 of this Directive, within 30 days from the effective date of this Directive.
(d) Before further flight.
(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 85 flight hours.
(b) Before further flight.
This Amendment becomes effective on 9 June 2005.

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 corrects 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 1 of this Directive became effective 27 November 2003. The original issue of this Directive became effective 4 May 1994.

FMI: www.casa.gov.au/airworth/airwd/ADfiles/equip/phs/PHS-018.pdf