EASA AD No.: 2012-0127R1 

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0127R1 

Date: 10 September 2012 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of 

the European third countries that participate in the activities of EASA under Article 66 of that 

Regulation. 

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Design Approval Holder’s Name : 

BAE SYSTEMS (OPERATIONS) LTD 

Type/Model designation(s) : 

ATP aeroplanes

TCDS Number: EASA.A.192 

Foreign AD: Not applicable 

Revision: This AD revises EASA AD 2012-0127 dated 10 July 2012. 

ATA 26 Fire Protection – Engine and Auxiliary Power Unit Automatic Fire 

Extinguishers – Inspection/Overhaul 

Manufacturer(s): British Aerospace plc, British Aerospace (Commercial Aircraft) Ltd 

Applicability: ATP aeroplanes, all serial numbers 

Reason: A fire handle on a BAe 146 aeroplane was operated on the ground as a 

precautionary measure after the throttle cable on the affected engine failed, 

due to corrosion. The extinguisher failed to discharge. 

Investigation results revealed that excess solder, which had been 

deposited during overhaul on the frangible plug of the extinguisher, 

prevented the release of the extinguishant. Prompted by this report, Kidde 

Graviner, the fire extinguisher manufacturer, identified four further 

extinguishers of similar design that had the same issue. The ATP 

aeroplane extinguisher is one of those of a similar design. 

This condition, if not detected and corrected, could result in the failure of a 

fire bottle to discharge, which reduces the ability of the fire protection 

system to extinguish fires in the engine or Auxiliary Power Unit (APU) fire 

zones, possibly resulting in damage to the aeroplane and injury to the 

occupants. 

For the reasons described above, EASA issued AD 2012-0127 to require a 

one-time inspection of the affected Part Number (P/N) 57183 engine and APU 

fire extinguishers. In addition, this AD prohibited installation of a fire 

extinguisher, unless it has passed the inspection as required by AD 2012-

0127. 

Revision 1 of this AD is issued to clarify that new extinguishers P/N 57183 
EASA AD No.: 2012-0127R1 

CAP.00110-001 © European Aviation Safety Agency. All rights reserved. 2/2 

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may be fitted with no additional inspection required by this AD. 

Effective Date: 

Revision 1: 17 September 2012 

Original issue: 24 July 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) For aeroplanes equipped with fire extinguishers manufactured by Kidde 

Graviner P/N 57183 (all dash numbers), within 12 months after the 

effective date of this AD, remove and inspect each affected fire 

extinguisher in accordance with the instructions of paragraph 2.A of BAE 

Systems (Operations) Ltd Service Bulletin (SB) ATP-26-016, which 

references Kidde Graviner SB 26-080 Revision 1. 

(2) Aeroplanes, which are equipped with P/N 57183 (all dash numbers) fire 

extinguishers that have been overhauled by Kidde Graviner or Hugen, or 

have been overhauled in accordance with the instructions of Kidde 

Graviner Service Information Letter (SIL) 01-10, or have been overhauled 

in accordance with Kidde Graviner Component Maintenance Manual 

(CMM) 26-21-52 at Revision 13 or later revision, are compliant with 

requirements of paragraph (1) of this AD. 

(3) From the effective date of this AD, do not install a Kidde Graviner P/N 

57183 (all dash numbers) fire extinguisher on any aeroplane, unless it is 

new, or has passed the inspection in accordance with the instructions of 

Kidde Graviner SB No. 26-080 Revision 1, or it has been overhauled by 

Kidde Graviner or Hugen, or it has been overhauled in accordance with 

the instructions of Kidde Graviner SIL 01-10, or it has been overhauled in 

accordance with Kidde Graviner CMM 26-21-52 at Revision 13 or later 

revision. 

Note: For the purpose of this AD, an overhaul is considered to include the 

replacement of the operating head. Replacement of the pressure relief 

plug assembly only is not considered an overhaul. 

Ref. Publications: BAE Systems (Operations) Limited SB ATP-26-016 Original Issue dated 4 

October 2011. 

Kidde Graviner SB 26-080 Revision 1 dated 27 July 2011. 

Kidde Graviner SIL 01-10 dated 29 July 2010. 

Kidde Graviner CMM 26-21-52 at Revision 13. 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 

Remarks : 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 30 May 2012 as PAD 12-049R1 for consultation 

until 27 June 2012. No comments were received during the consultation 

period. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements in 

this AD, please contact: 

BAE Systems (Operations) Ltd, Customer Information Department, 

Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United 

Kingdom; Telephone +44 1292 675207, Facsimile +44 1292 675704; 

E-mail: RApublications@baesystems.com.