Commonwealth legislation

AD/PHS/21 Amdt 1 - Blade Spar Taper Bore

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

AD/PHS/21 Amdt 1 requires ultrasonic shear‑wave inspections of specified Hamilton Standard blade-and-pin assemblies (serials <885718) fitted to listed aircraft and mandates those inspections be carried out by a qualified NDT Authority. It adds a blade repair option that, once performed, stops the need for repetitive taper-bore inspections. The Directive was prompted by fatigue cracking in the taper-bore area that caused a blade to separate in flight.

JSON API

Deep dive

Want the full deep dive?

Zoe can write the in-depth analysis on top of the summary above: how it works, who it affects and what each part actually does.

Current sections

Direct links to the current provisions in AD/PHS/21 Amdt 1 - Blade Spar Taper Bore.

AD/PHS/21 Amdt 1 - Blade Spar Taper Bore

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 107 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source
Propellers - Variable Pitch - Hamilton Standard

AD/PHS/21

Amdt 1

Blade Spar Taper Bore 8/96 DM

Applicability: All model 14RF, 14SF, and 6/5500/F Series propellers with blade and pin assemblies with manufacturing serial number less than 885718.

Note: These propellers are fitted to Embraer EMB-120, DHC-8-100 and 300, Aerospatiale ATR42, CASA CN-235, SAAB SF340, BAe ATP, and Canadair CL215T/CL415T Series aircraft.

Requirement: Action in accordance with the technical requirements of FAA AD 96-08-02 Amendment 39-9568. The ultrasonic shear wave inspections required by this Directive must be carried out by an appropriately qualified NDT Authority holder.

Note 1: FAA AD 96-08-02 Amdt 39-9568 supersedes FAA AD 96-01-01 Amdt 39- 9477 which superseded FAA Telegraphic AD T95-18-51 and FAA Priority Letter AD 95-18-06R1.

Note 2: Initial issue of this Directive cancelled AD/PHS/17 Amdt 2 and AD/PHS/19 Amdt 1.

Note 3: All blade and pin assemblies previously inspected in accordance with AD/PHS/17 Amdt 2, AD/PHS/19 Amdt 1 or AD/PHS/21 are required to be re- inspected in accordance with this Directive.

Compliance: Effective 29 May 1996; as detailed in the Requirement Document.

Background: A recent accident involving an Embraer EMB-120 aircraft has been attributed to fatigue cracking in the blade taper bore area which resulted in the liberation of a blade during flight. The initial Directive was issued to require an improved taper bore ultrasonic shear wave inspection and also to reduce various re-inspection intervals that are dependent on which aircraft propeller model is being inspected and provides an inspection to re-evaluate the serviceability of blade and pin assemblies previously rejected in accordance with AD/PHS/19 Amdt 1.

Amendment 1 requires a blade repair that constitutes terminating action for the repetitive taper bore ultrasonic inspection requirement.

The initial issue of this Airworthiness Directive became effective on 27 February 1996.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/PHS/21 Amdt 1 - Blade Spar Taper Bore

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 107 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Propellers - Variable Pitch - Hamilton Standard