EASA AD No : 2011-0065 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0065 

Date: 07 April 2011 

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]. 

Type Approval Holder’s Name : 

BAE SYSTEMS (OPERATIONS) LTD 

Type/Model designation(s) : 

BAe 146 and AVRO 146-RJ aeroplanes 

TCDS Number: EASA.A.182 

Foreign AD: Not applicable 

Supersedure: None 

ATA 26 Fire Protection - Baggage Bay Fire Bottles Wiring Looms – 

Inspection / Modification 

Manufacturer(s): BAE Systems (Operations) Ltd, British Aerospace plc, British Aerospace 

(Commercial Aircraft) Ltd, British Aerospace (Operations) Ltd, British 

Aerospace Regional Aircraft Ltd, British Aerospace Regional Aircraft trading 

as Avro International Aerospace. 

Applicability: BAe 146 and AVRO 146-RJ aeroplanes, all models, all serial numbers if 

they embody modifications HCM30480A, HCM30480B, HCM30480C, 

HCM30480D, HCM30480E or HCM30480F. 

Reason: The baggage bay fire bottles of certain BAe 146 and AVRO 146-RJ 

aeroplanes can be misassembled such that two squib electrical connectors 

can be cross-connected. This has been caused by an error in the baggage 

bay fire bottle Component Manufacturer Manual (CMM) and by excessive 

wiring loom length. 

This condition, if not corrected and in conjunction with a fire in one of the 

baggage bays, could result in the fire extinguishant to be discharged into a 

wrong compartment and consequent potential damage to the aircraft and 

injury to its occupants. 

In addition to the CMM revision, to address this unsafe condition, BAE 

Systems developed modifications to reroute the baggage bay fire bottle 

wiring looms and prevent crossed electrical connections. 

For the reasons described above, this AD requires the implementation of 

modifications HCM36250A and HCM36250B to affected aeroplanes. 
EASA AD No : 2011-0065 

EASA Form 110 Page 2/3 

Effective Date: 21 April 2011 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Note: 

If the instructions of BAE Systems (Operations) Ltd MSB 26-077-36250A at 

original issue or revision1 have been carried out before the effective date of 

this AD, refer to paragraph (11) of this AD. 

Within 3 months after the effective date of this AD, accomplish the following 

actions concurrently: 

(1) Inspect the baggage bay fire bottle WB8 Part Number (P/N) 473997-1 

for correct connection of the followings squib connectors in 

accordance with the accomplishment instructions of paragraph 

2.C.(3) of BAE Systems (Operations) Ltd Modification Service Bulletin 

(MSB) 26-077-36250A.B Revision 2: 

- Squib connectors WB8P1 (S1446-004A) and cartridge P/N 

446307, and 

- Squib connector and WB8P2 (S1446-004D) and squib P/N 

446290. 

(2) If, during the inspection required by paragraph (1) of this AD, any 

items are improperly connected, reconnect the squib connectors 

properly in accordance with the accomplishment instructions of 

paragraph 2.C.(3) of BAE Systems (Operations) Ltd MSB 26-077-

36250A.B Revision 2. 

(3) Inspect the length of wiring loom at the squib connector WB8P2 for 

any excessive length that could cause the connector to become cross 

connected with squib connector WB8P1 in accordance with the 

accomplishment instructions of paragraph 2.C.(4) of BAE Systems 

(Operations) Ltd MSB 26-077-36250A.B Revision 2. 

(4) If, during the inspection required by paragraph (3) of this AD, 

excessive length is found, modify the loom in accordance with the 

accomplishment instructions of paragraph 2.C.(4) of BAE Systems 

(Operations) Ltd MSB 26-077-36250A.B Revision 2. 

(5) Inspect the baggage bay fire bottle WB7 (P/N 473996-1) for correct 

connection of the followings squib connectors in accordance with the 

accomplishment instructions of paragraph 2.C.(5) of BAE Systems 

(Operations) Ltd MSB 26-077-36250A.B Revision 2: 

- Squib connectors WB7P1 (S1446-004A) and cartridge P/N 

446307, and 

- Squib connectors WB7P2 (S1446-004D) and squib P/N 446290. 

(6) If, during the inspection required by paragraph (5) of this AD, any 

items are improperly connected, reconnect the squibs connectors 

properly in accordance with the accomplishment instructions of 

paragraph 2.C.(5) of BAE Systems (Operations) Ltd MSB 26-077-

36250A.B Revision 2. 

(7) Modify the wiring loom to squib connector WB7P2 in accordance with 

the accomplishment instructions of paragraphs 2.C.(6) (a) and (c) of 

BAE Systems (Operations) Ltd MSB 26-077-36250A.B Revision 2. 

(8) Modify the wiring loom to squib connector WB7P1 in accordance with 

the accomplishment instructions of paragraph 2.C.(6)(b) of BAE 

Systems (Operations) Ltd MSB 26-077-36250A.B Revision 2. 
EASA AD No : 2011-0065 

EASA Form 110 Page 3/3 

(9) Install modification HCM36250B in accordance with the 

accomplishment instructions of paragraph 2.C.(7) of BAE Systems 

(Operations) Ltd MSB 26-077-36250A.B Revision 2. 

(10) Test and close up in accordance with paragraphs 2.D.and 2.E of BAE 

Systems (Operations) Ltd MSB 26-077-36250A.B Revision 2. 

(11) If modification HCM36250A has been embodied before the effective 

date of this AD through accomplishment of BAE Systems 

(Operations) Ltd MSB 26-077-36250A at original issue or at revision 

1, compliance with instructions of paragraph 2.C. Part 1 of BAE 

Systems (Operations) Limited MSB 26-077-36250A.B at Revision 2 is 

demonstrated and existing spiral wrap binding at the connectors must 

be removed concurrently with the accomplishment instructions of Part 

2 of BAE Systems (Operations) Limited MSB 26-077-36250A.B 

Revision 2 paragraph 2.F. Close up in accordance with 

accomplishment instructions of paragraph 2.G. of BAE Systems 

(Operations) Ltd MSB 26-077-36250A.B Revision 2. 

Ref. Publications: 

BAE Systems (Operations) Limited Modification Service Bulletin SB.26-077-

36250A.B Revision 2 dated 14 October 2010. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

Note: 

During the consultation period of this AD as Proposed AD (PAD) 

11-026, BAE Systems (Operations) Ltd informed that Revisions 3 and 4 of 

Modification Service Bulletin SB.26-077-36250A.B introduced corrections 

related to a misquoted adhesive material specification number. Contact BAe 

Systems (Operations) Ltd to request the latest revision of the Modification 

Service Bulletin. 

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

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 01 March 2011 as PAD 11-026 for consultation 

until 29 March 2011. No comments were received during the 

consultation period. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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.