AD/PHZL/60 Amdt 4 - Three Bladed Y Shank Aluminium Hubs

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B06220 In force Legislative Instrument

Legislation content

 


Propellers - Variable Pitch - Hartzell

 

AD/PHZL/60

Amdt 4


Three Bladed ‘Y’ Shank Aluminium Hubs 13/94

 

Applicability: All HC-( )3Y( )-( ) propellers with the model designations and serial number range with pre 1983 hubs listed below installed on any agricultural aircraft with any engine, or installed on any aircraft fitted with Textron Lycoming TIO-540 or LTIO-540 series engines, or IO-540 series engines that have a turbocharger.

Hub Model Serial Number Range

 

PHC-C3YF-1R( ) EE1 through EE1461

 

PHC-J3YF-1R( ) FP1 through FP37

 

PHC-L3YF-1R( ) FD1 through FD7

 

HC-C3YF-1R( ) EC1 through EC1020

 

HC-C3YK-1( ) CT1 through CT101

 

HC-C3YK-1R( ) or HC-C3YR-1R( ) DY1 through DY1897

 

HC-C3YK-2( ) or HC-C3YR-2( ) CK1 through CK3510

 

HC-C3YK-4( ) or HC-C3YR-4( ) EL1 through EL67

 

HC-E3YK-1( ) or HC-E3YR-1( ) FM1 through FM487

 

HC-E3YK-2( ) or HC-E3YR-2( ) DF1 through DF79

 

HC-E3YK-2A( ) or HC-E3YR-2A( ) DJ1 through DJ7787

 

HC-F3YK-2( ) or HC-F3YR-2( ) DA1 through DA1586

 

HC-F3YK-1( ) or HC-F3YR-1( ) DB1 through DB137

 

HC-I3YK-2( ) or HC-I3YR-2( ) FD1 through FS32

 

The known affected propellers are generally installed on but not limited to the following aircraft.

 

Agricultural Aircraft

 

Fletcher FU24-950

 

Cessna A188 Agwagon modified by STC SA895SO

 

Piper PA-36-285 and PA-36-300 (three bladed propellers only) PA-36-375

PA-36 Pawnee modified by STC SA3952WE Transavia Airtruk model PL-12/T-300 Skyfarmer

Aircraft with Textron Lycoming (L)TIO-540 and Turbocharged IO-540 series engines

 

Cessna 310 and 320 modified by Riley STC SA2082WE Gulfstream 700 (formerly Rockwell 700, Fuji FA-300-12) Helio H-700

Piper PA-23-250, PA-E23-250 (with TIO-540 only)

 

Piper PA-31 Navajo (with TIO-540 only)

 

Piper PA-31-325 Navajo C/R

 

Piper PA-31-350 Navajo “Chieftain” Piper PA-31P-350 Mohave

Piper T-1020 (same as PA-31-350) Piper A-32(R)-301T Turbo Saratoga

Aerostar PA-60-600, PA-60-601, PA-60-601P PA-60-602P, and PA-60-700P

 

Requirement: 1. Carry out a visual inspection of the hub using a 10X glass looking for signs of cracking or grease leakage. Replace any hub found cracked prior to further flight. Perform an eddy current or dye penetrant inspection in accordance with the procedures specified in Hartzell SB 165E on any of the above specified model and S/N propellers installed on any agricultural aircraft or Piper PA-31-325 Navajo C/R, Piper PA-31-350 Navajo “Chieftain”, Piper T-1020 (same as PA-31-350), PA-60-700P or Aerostar 700P aircraft.

 

2.    For all other aircraft types listed in this Directive carry out a visual inspection of the hub using a 10X glass looking for signs of cracking or grease leakage. Replace any hub found cracked prior to further flight. Perform an eddy current or dye penetrant inspection IAW the procedures specified in Hartzell SB 165E.

 

3.    For propellers installed on agricultural aircraft or Piper PA-31-325 Navajo C/R, Piper PA-31-350 Navajo “Chieftain”, Piper T-1020 (same as PA-31-350), PA-60- 700P or Aerostar 700P aircraft, replace pre 1983 style hubs with post 1983 hubs. If during overhaul, post 1983 style hubs are not available and the hub passes overhaul requirements then, the pre 1983 hub chamfer modification in accordance with Procedure 2 of Hartzell SB 165E may be incorporated. Hubs so modified are exempt from Requirements 1 and 2 of this Directive.

4.    For all other aircraft types listed in this directive, replace pre 1983 style hubs with post 1983 hubs. If during overhaul post 1983 style hubs are not available, and the hub meets overhaul requirements then, the pre 1983 hub chamfer modification in accordance with Procedure 2 of Hartzell SB 165E may be incorporated in a serviceable pre 1983 hub. Modified hubs are exempt from Requirements 1 and 2 of this Directive.

 

Note. FAA AD 94-17-13 which supersedes FAA AD 93-16-14 amdt 39-8704, refers.

 

Compliance: 1. Visual inspection - within 10 hours time in service after 8 December 1994, and thereafter, at intervals not exceeding 10 hours time in service until a post 1983 style hub has been fitted. Any removed hub shall be permanently retired from service.

 

Eddy Current or Dye Penetrant Inspection - within 25 hours time in service after 8 December 1994 and thereafter at intervals not exceeding 25 hours time in service until post 1983 style hub has been fitted. Any removed hub shall be permanently retired from service.

 

2.    Within 50 hours time in service after 8 December 1994 and thereafter at intervals not exceeding 50 hours time in service until post 1983 style hub has been fitted. Any removed hub shall be permanently retired from service.

 

3.    For Piper PA-31-325 Navajo C/R, Piper PA-31-350 Navajo “Chieftain”, Piper T- 1020, PA-60-700P, Aerostar PA-60-700P and all agricultural aircraft, any time a hub is fully dismantled for repair or overhaul of the propeller after 8 December 1994 or by 30 June 1995, whichever occurs first. Modified hubs may be retained in service for a further 400 hours or 36 calendar months, whichever occurs first. Any removed hub shall be permanently retired from service.

 

4.    For all other aircraft types, at the next propeller overhaul after 8 December 1994. Modified hubs may be retained in service provided an internal inspection of the hub in accordance with Hartzell SB 165 E is carried out at intervals not exceeding 400 hours or 36 calendar months, whichever occurs first. Any removed hub shall be permanently retired from service.

 

 

Background:  There have been incidents of hub cracks in Hartzell three blade “compact” aluminium hub propellers. Cracks have originated in the threads of a grease fitting hole on the side of the hub and have also originated in the fillet radius area. The cracks are believed to be observable with careful visual examination using a 10X magnifying glass.

 

As the cracks propagate around the blade arm of the hub their progression accelerates and results in failure of one hub half which can then, potentially, progress to blade separation. Replacement with the later style hubs, post 83, provides terminating action for this Directive. The previous amendment reduces the repetitive inspection interval while this amendment, in line with the manufacturer’s SB, further reduces the inspection intervals, introduces an eddy current or fluorescent penetrant inspection requirement, allows chamfer modifications of the hub and for specific aircraft types mandates replacement of pre 83 hubs within a certain time frame.

Overview

The Propellers – Variable Pitch – Hartzell AD/PHZL/60Amdt 4 was enacted to address the problem of hub cracks in Hartzell three bladed “compact” aluminium hub propellers, which have been observed to originate in the threads of a grease fitting hole or in the fillet radius area. These cracks can propagate around the blade arm of the hub, leading to potential blade separation. The Civil Aviation Safety Authority (CASA) introduced this Airworthiness Directive to mitigate these risks. The policy objective of the amendment is to further reduce inspection intervals, introduce an eddy current or fluorescent penetrant inspection requirement, allow for chamfer modifications of the hub, and mandate the replacement of pre 1983 hubs within a certain time frame for specific aircraft types. Compliance with the directive is required for propellers installed on affected aircraft types, with visual inspections and hub replacements to be carried out at specified intervals to ensure continued airworthiness.

Scope and Application

The Propellers – Variable Pitch – Hartzell AD/PHZL/60Amdt 4 pertains to specific propeller models installed on particular aircraft, namely those fitted with Hartzell propellers having three-bladed ‘Y’ shank aluminium hubs. This legislative instrument applies to certain propellers with designated model numbers and serial number ranges that were manufactured before 1983 and are installed on agricultural aircraft, as well as aircraft equipped with Textron Lycoming TIO-540, LTIO-540 series engines, or IO-540 series engines that have a turbocharger. The geographic and jurisdictional scope of this legislation is not explicitly defined in the text, but it presumably applies under the relevant Australian aviation regulatory framework. The Act does not mention any exclusions, exemptions, or thresholds. Compliance with this Act may be extended or restricted through subordinate instruments, but such details are not provided in the text. The primary requirement of this legislation is to ensure the safety of the affected propellers by mandating specific inspections and modifications to address known issues with the hubs.

Key Provisions

The legislative instrument F2006B06220, Propellers - Variable Pitch - Hartzell AD/PHZL/60Amdt 4, mandates specific inspection, modification, and replacement requirements for certain Hartzell propellers installed on various agricultural and other aircraft. The affected propellers include three-bladed 'Y' shank aluminium hubs with model designations and serial number ranges specified, particularly those with pre-1983 hubs installed on agricultural aircraft or aircraft with specific Textron Lycoming engines (sections 1 and 2). The primary requirement is a visual inspection using a 10X magnifying glass for signs of cracking or grease leakage. Any cracked hubs must be replaced before further flight (section 1). For specified aircraft types, an eddy current or dye penetrant inspection in accordance with Hartzell SB 165E must also be performed (sections 1 and 2). Additionally, pre-1983 hubs must be replaced with post-1983 hubs. If post-1983 hubs are unavailable during overhaul and the hub passes overhaul requirements, a pre-1983 hub chamfer modification can be performed, exempting the hub from further inspection requirements (sections 3 and 4). Compliance with these provisions involves specific inspection intervals. For agricultural aircraft and certain Piper and Aerostar models, a visual inspection must be conducted within 10 hours of service after 8 December 1994 and at intervals not exceeding 10 hours of service until a post-1983 hub is fitted (section 1). An eddy current or dye penetrant inspection must be performed within 25 hours of service after 8 December 1994 and at intervals not exceeding 25 hours of service until a post-1983 hub is fitted (section 1). For all other aircraft types, a visual inspection must be conducted within 50 hours of service after 8 December 1994 and at intervals not exceeding 50 hours of service until a post-1983 hub is fitted (section 2). Hubs must be permanently retired from service once removed. Failure to comply with the requirements outlined in this legislative instrument may result in severe operational risks due to potential hub failure. While the specific penalties for non-compliance are not detailed in the text, the implications of not adhering to these safety directives could lead to significant safety hazards, including potential aircraft accidents. The seriousness of the potential consequences underscores the importance of strict compliance with the specified inspection and modification protocols.

Legal classification tags

Instrument
Legislative Instrument
Concepts
Definitions & Interpretation
Reporting & Disclosure Obligations
Compliance Obligations
Prohibited Conduct
Catchwords
Hub Replacement
Visual Inspection

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.