AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/A320/116 and issues the following AD under subregulation 39.1 (1) of CAR 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.
Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/116
Amdt 1
Wing Fuel Boost Pump Wiring 6/2002
Applicability: All Model A319/A320/A321 aeroplanes without both Airbus Industrie modifications 30861 and 31612 embodied or Airbus Industrie Service Bulletin (SB) A320-28-1093 incorporated.
Requirement: 1. If not previously accomplished, revise the Limitations Section of the Aeroplane Flight Manual (AFM) by inserting the following:
FUEL SYSTEM
In case any wing fuel tank fuel pump circuit breaker 1QA, 2QA, 7QA or 8QA is tripped, do not re-engage.
This may be accomplished by inserting a copy of this Directive or the revised Temporary Revision 2.04.00/31 into the AFM.
2. If wing fuel tank pump circuit breaker 1QA, 2QA, 7QA or 8QA trips, either:
- remove the applicable fuel pump fairing and perform visual inspections of the following to detect any damage caused by electrical arcing and, if necessary, carry out the rectification specified in sub-paragraphs 2.a.(i), 2.a.(ii) or 2.a.(iii).
(i) Electrical wiring - If any damage to the wiring is detected replace the wire with new wire or repair it in accordance with the Aircraft Wiring Manual (AWM), Electrical Standard Practices Manual (ESPM), Chapter 20.
(ii) Fairing - If any damage to the fairing is detected replace the fairing with a new serviceable fairing using the appropriate installation and sealing procedures.
(iii) Wing skin within the fairing area - If any damage to the wing structure is detected repair the damaged structure in accordance with the aircraft Structural Repair Manual (SRM) or another approved method.
Caution: When replacing the fairing following the inspection, ensure that fuel boost pump wiring is not pinched or otherwise damaged. Incorrect replacement of the fairing could cause damage to the wiring.
or,
b. ensure that the applicable circuit breaker cannot be reset by collaring the circuit breaker(ie secure the circuit breaker in the open position by a positive means).
Note 1: If the Requirement 2.b. option is adopted, the aircraft may be dispatched in accordance with an approved MEL (based on associated DGAC MMEL 28-21).
3. If a circuit breaker is collared opened in accordance with Requirement 2.b. carry out the Requirement 2.a. inspection.
4. If any damage is detected during the Requirement 2.a. inspections submit a report to Airbus Industrie including the following details:
- description of the damage found,
- aeroplane serial number,
- total number of landings,
- total time in service (hours), and
- details of the last maintenance actions performed on the fuel boost pump and/or fairing.
- Modify the engine feed pump electrical harness and underwing fairings in accordance with SB A320-28-1093 and remove the AFM amendment introduced by Requirement 1.
Note 2: DGAC AD 2002-221(B) refers.
Compliance: For Requirement 1 - Remains unchanged as ‘Within ten days after the effective date of the original issue of this Directive’.
For Requirement 2 - Before further flight unless SB A320-28-1093 has been incorporated in accordance with Requirement 5.
For Requirement 3 - Within ten days of the circuit breaker being collared open in accordance with Requirement 2.b.
For Requirement 4 - Within ten days after accomplishing the Requirement 2.a. inspection.
For Requirement 5 - Before 30 April 2004.
This Amendment becomes effective on 13 June 2002.
Background: The original issue of this Directive superseded AD/A320/111, clarified the inspection requirements and allowed despatch of the aircraft with wing fuel tank pumps rendered inoperable. AD/A320/111 was issued to limit the risk of electrical arcing between the wing fuel tank boost pump wiring and the wing structural skin by the introduction of an AFM limitation.
This Amendment introduces terminating action for Requirements 1 and 2.
The original issue of this Airworthiness Directive became effective on 28 February 2001.
James Coyne
Delegate of the Civil Aviation Safety Authority 3 May 2002
The above AD is notified in the Commonwealth of Australia Gazette on 22 May 2002.
Overview
The Civil Aviation Safety Authority Act 1998, enacted by the Australian Parliament, was introduced to establish the Civil Aviation Safety Authority (CASA) and to provide for its functions and powers. This Act ensures the safe operation of civil aviation in Australia by setting safety standards and regulations. One of its key policy objectives is to ensure that airworthiness directives, which are regulatory measures aimed at correcting unsafe conditions, are effectively implemented. The Airworthiness Directive (AD) AD/A320/116 Amendment 1, issued under the authority of CASA, addresses the specific issue of electrical arcing in Airbus A319, A320, and A321 series aeroplanes, ensuring that appropriate measures are taken to prevent unsafe conditions related to wing fuel boost pump wiring. This AD requires operators to revise their Aeroplane Flight Manual and conduct inspections or implement corrective actions if certain circuit breakers are tripped, ensuring ongoing compliance with safety standards.
Scope and Application
The Airworthiness Directive (AD) AD/A320/116Amdt 1 pertains to the Airbus Industrie A319, A320, and A321 series aeroplanes, specifically those that do not have both Airbus Industrie modifications 30861 and 31612 embodied or Airbus Industrie Service Bulletin (SB) A320-28-1093 incorporated. This AD is issued under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 by a delegate of the Civil Aviation Safety Authority (CASA), whose signature appears on the directive. The directive requires certain actions to be taken to correct an unsafe condition, with specific requirements outlined in the directive that must be followed to ensure compliance. The AD was revoked and reissued to clarify the inspection requirements and to allow for the dispatch of the aircraft with wing fuel tank pumps rendered inoperable, addressing the risk of electrical arcing between the wing fuel tank boost pump wiring and the wing structural skin. The AD applies across the Commonwealth of Australia and is notified in the Commonwealth of Australia Gazette.
Key Provisions
This legislative instrument pertains to an Airworthiness Directive (AD) issued under the Civil Aviation Regulations 1998, specifically revoking AD AD/A320/116 and introducing a new AD (AD/A320/116 Amdt 1) for the Airbus Industrie A319, A320, and A321 series aeroplanes. This new directive mandates specific actions to address unsafe conditions identified with the wing fuel boost pump wiring, particularly focusing on preventing electrical arcing. The AD applies to all Model A319/A320/A321 aeroplanes unless they have implemented both Airbus Industrie modifications 30861 and 31612, or incorporated Airbus Industrie Service Bulletin (SB) A320-28-1093.
The requirements of the directive are quite detailed. Firstly, operators must revise the Limitations Section of the Aeroplane Flight Manual (AFM) by adding a specific limitation regarding the wing fuel tank fuel pump circuit breakers 1QA, 2QA, 7QA, and 8QA. This mandates that if any of these circuit breakers are tripped, they should not be re-engaged. Secondly, if any of these circuit breakers trip, operators must either remove the applicable fuel pump fairing and conduct a visual inspection of the electrical wiring, fairing, and wing skin within the fairing area to detect any damage caused by electrical arcing, and perform necessary repairs or replacements, or secure the circuit breaker in the open position by a positive means. The directive also stipulates reporting requirements if damage is detected during inspections. Furthermore, operators must modify the engine feed pump electrical harness and underwing fairings in accordance with SB A320-28-1093 and remove a specific amendment to the AFM introduced by the directive.
The AD imposes several obligations on the parties governed by it. Operators must comply with the timeframes specified for each requirement. For instance, the AFM limitation must be updated within ten days of the directive's effective date. If a circuit breaker is secured in the open position, the required inspection must be performed within ten days of the circuit breaker being collared. Any damage detected during inspections must be reported to Airbus Industrie within ten days. Modifications to the engine feed pump electrical harness and underwing fairings must be completed before 30 April 2004. Additionally, the directive requires operators to ensure that the aircraft is not flown unless specific conditions are met, particularly if the SB A320-28-1093 has been incorporated.
Failure to comply with the AD's requirements can result in significant consequences. While the specific penalties for non-compliance are not explicitly stated in the text, non-compliance with airworthiness directives generally carries severe penalties under aviation law. These may include fines, suspension or revocation of airworthiness certificates, and other enforcement actions. Such non-compliance can also lead to safety risks, grounding of aircraft, and potential legal liabilities for operators.