Mon, May 02, 2005
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.
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