AD/HS 125/159 - Wiring Inspections

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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 


British Aerospace BAe 125 Series Aeroplanes

 

AD/HS 125/159 Wiring Inspections  1/2000 DM

Applicability: Model Hawker 1000 series aeroplanes serial numbers 258151, 258159 and 259003

through 259052 inclusive.

 

Requirement: 1. Perform a detailed visual inspection of the PS wire bundle coming from the bung ‘DF’ for chafing against the front ventral tank transfer/crossfeed actuator, in accordance with Raytheon Aircraft Service Bulletin SB 24-3201 dated October 1998.

 

Note 1: For the purposes of this Airworthiness Directive, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required."

 

2.    Perform the applicable action when the following conditions are found during the Requirement 1 inspection:

 

  1. No chafing - Ensure a minimum 0.25-inch clearance exists between the PS wire bundle and valve actuator; and install spiral wrap, as necessary, in accordance with the service bulletin.

 

b.    Chafing on a 22, 20, 16, or 14 gauge (non-shielded) wire - Repair chafed wire by splicing the damaged section using MIL-S-81824/1 splices. Ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary, in accordance with the service bulletin.

 

c.    Chafing on a 10 gauge wire - Replace the entire wire with a new 10 gauge wire. Ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary, in accordance with the service bulletin.

 

3.    Perform a detailed visual inspection of the shielded wires going to the fuel probe ‘G’ for chafing against the wing transfer valve actuator and mounting screws, in accordance with Raytheon Aircraft Service Bulletin SB 24-3201 dated October 1998.

 

4.    Perform the applicable action when the following conditions are found during the Requirement 3 inspection:

 

  1. No chafing - Ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary, in accordance with the service bulletin.

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 

b.    Chafing - Replace the entire shielded wire with a new shielded wire. Ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary, in accordance with the service bulletin.

 

5.    Perform a borescope inspection of the entire forward wing spar/forward ventral tank area for chafing of any other wire or wire bundle; and install spiral wrap, as necessary; in accordance with Raytheon Aircraft Service Bulletin SB 24-3201 dated October 1998.

 

6.    Perform the applicable action when the following conditions are found during the Requirement 5 inspection:

 

  1. No chafing - No further action is required by this Airworthiness Directive.

 

b.    Chafed wire or wire bundle - Repair in accordance with a method approved by the Head, Certification Standards Branch, Standards Division, CASA. For a repair method to be approved by the Head, Certification Standards Branch, as required by this paragraph, the approval letter must specifically reference this Airworthiness Directive.

 

Note 2: FAA AD 99-23-10 Amdt 39-11406 refers.

 

Compliance: 1. Within 50 hours time in service after 17 December 1999.

 

2.    Prior to further flight.

 

3.    Within 50 hours time in service after 17 December 1999.

 

4.    Prior to further flight.

 

5.    Within 50 hours time in service after 17 December 1999.

 

6.    Prior to further flight.

 

This Airworthiness Directive becomes effective on 17 December 1999.

 

Background:  Raytheon has received a report of wire bundle chafing against the forward tank transfer/crossfeed valve which caused an electrical short and resulted in the failure of a landing light. This directive is intended to prevent a short circuit caused by wire chafing, which can cause a fire in the ventral fuel tank area.

Overview

The Civil Aviation Regulations 1998, amended by the Civil Aviation Amendment (Enhancing Aviation Infrastructure) Regulations 2006, establish the framework for ensuring the safety and airworthiness of aircraft operating in Australia. This legislation was enacted to address the need for stringent regulatory oversight in the civil aviation sector, ensuring that all aircraft meet the required safety standards to protect passengers, crew, and the general public. The policy objective of these regulations is to mitigate risks associated with air travel by imposing rigorous safety standards and mandatory compliance checks. The Civil Aviation Safety Authority (CASA) is the enforcing body responsible for the implementation and oversight of these regulations, ensuring that aircraft operators adhere to the stipulated safety directives and maintenance protocols.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority Schedule of Airworthiness Directives, mandates specific wiring inspections for certain Hawker 1000 series aeroplanes to ensure airworthiness and prevent potential fire hazards. This directive applies to aeroplanes with serial numbers 258151, 258159, and 259003 through 259052 inclusive. The inspections are designed to detect and address chafing of the PS wire bundle and shielded wires against various components, with specific actions required depending on the severity of the chafing found during the inspection. Compliance with this directive must occur within 50 hours of service after 17 December 1999, and before further flight, ensuring that any necessary repairs or replacements are made to maintain the safety standards set forth by the Civil Aviation Safety Authority. This directive is a crucial measure to mitigate the risk of electrical shorts leading to potential fires within the aircraft's fuel tank area.

Key Provisions

The Civil Aviation Regulations 1998, as amended, include specific airworthiness directives (AD) for maintaining the safety of aircraft. One such directive, AD/HS 125/159 1/2000, focuses on the inspection and maintenance of wiring for the British Aerospace BAe 125 Series aeroplanes, specifically the Hawker 1000 series aeroplanes with serial numbers between 258151 and 259052 inclusive. The directive mandates several detailed inspections and corrective actions to prevent chafing of wiring, which could lead to electrical shorts and potential fires. Section 1 requires a detailed visual inspection of the PS wire bundle from the bung ‘DF’ to ensure there is no chafing against the front ventral tank transfer/crossfeed actuator, and to take corrective action if any chafing is found. Similarly, section 3 demands a detailed visual inspection of the shielded wires leading to the fuel probe ‘G’ to ensure they are not chafed against the wing transfer valve actuator and mounting screws. Additionally, section 5 involves a borescope inspection of the entire forward wing spar/forward ventral tank area to detect any chafing of wires or wire bundles. Entities governed by these regulations, such as aircraft operators and maintenance service providers, must comply with the outlined inspections and corrective actions within specific timeframes. These requirements include conducting the inspections within 50 hours of time in service after the directive's effective date of 17 December 1999 and ensuring all corrective actions are completed prior to further flight. Failure to comply with these airworthiness directives can result in serious consequences. Section 8 of the Civil Aviation Act 1988 provides that any person who contravenes a direction made under the Act is liable to a penalty, which can include fines and imprisonment. The specific penalties can vary but may include fines up to $21,600 for individuals and significantly higher amounts for corporations, along with potential imprisonment terms. Furthermore, failure to adhere to these directives can result in the aircraft being deemed unairworthy, leading to grounding and potential legal action from regulatory authorities.

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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.