AD/PHZL/86 Propeller Hub Cracks (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (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 - Hartzell

AD/PHZL/86 Propeller Hub Cracks 12/2006

Applicability:

Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) series propellers with non-suffix serial number (SN) propeller hubs installed on Lycoming O-, IO-, LO-, and AEIO-360 series reciprocating engines.

Note 1:  A list of aeroplanes these propellers may be fitted to, but not limited to is included in FAA AD 2006-18-15.

Note 2:  The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter(s) that varies the basic propeller model.  This AD still applies regardless of whether these letters are present or absent in the propeller model designation.

Propellers Not Affected by This AD

Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) series propellers installed on the following aircraft are not affected by this AD, but are affected by AD/PHZL/74 Amdt 1 which addresses the same unsafe condition:

a.    Piper PA-32 series aircraft with Lycoming 540 series engines that are rated at 300HP or higher; or

b.    Pilatus Britten Norman or Britten Norman BN-2 series aircraft (also known as Islander or Trislander) with Lycoming 540 series engines; or

c.    Any aircraft certificated in the aerobatic category; or

d.    Any aircraft routinely exposed to aerobatic manoeuvres; or

e.    Any aircraft that has been used for agricultural operations whilst the applicable propeller was installed.

Requirement:

1.    Perform an initial Eddy Current Inspection (ECI) of the front cylinder half of the propeller hub for cracks in accordance with paragraphs 3.A. through 3.A.(4)(g) of the Accomplishment Instructions of Hartzell Propeller Inc. Service Bulletin (SB) HC-SB-61-269, dated 18 April 2005.

2.    If any cracks are found, remove the propeller hub from service.

3.    If no cracks are found, mark the propeller using paragraph 3.A.(6)(a) of the Accomplishment Instructions of Hartzell Propeller Inc. Service Bulletin (SB) HC-SB-61-269, to indicate compliance with Hartzell Propeller Inc. SB
HC-SB-61-269.

4.    Perform repetitive ECIs of the front cylinder half of the propeller hub for cracks.

5.    If any cracks are found, remove the propeller hub from service.

Optional Terminating Action

As an optional terminating action to the repetitive ECIs required by this AD:

(1)   Replace the non-suffix SN propeller hub with a propeller hub identified by an "A" or "B" suffix letter in the propeller hub SN; except

(2)   Do not install a suffix "A" propeller hub that was previously installed on an aircraft affected by the original issue or later revision of Hartzell Propeller Inc. SB HC-SB-61-227.

(3)   Replacement propeller hub part numbers can be found in paragraph 2.A., Material Information, of Hartzell Propeller Inc. SB HC-SB-61-269.

Note 3:  FAA AD 2006-18-15 Amdt 39-14754 dated 30 August 2006 refers.

Compliance:

1.    Within 50 operating hours time-in-service (TIS) after the effective date of this AD.

2.    Before further flight after the effective date of this AD.

3.    Before returning the propeller to service following completion of Requirement 1 of this AD.

4.    Within every 100 operating hours TIS after the last propeller hub ECI inspection, or at every annual inspection, whichever occurs first.

5.    Before further flight after the effective date of this AD.

This Airworthiness Directive becomes effective on 23 November 2006.

Background: This AD results from a report of a propeller blade separating from a propeller hub.  The actions detailed in this AD are intended to prevent failure of the propeller hub causing blade separation and subsequent loss of aeroplane control.

James Coyne
Delegate of the Civil Aviation Safety Authority

12 October 2006