EASA AD No.: 2014-0071

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2014-0071 

Date: 19 March 2014 

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 EU 748/2012, Part 21.A.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): 

BAe 146 and AVRO 146-RJ aeroplanes 

TCDS Number: EASA.A.182 

Foreign AD: Not applicable 

Supersedure: This AD supersedes EASA AD 2012-0004 dated 12 January 2012. 

ATA 05 Time Limits / Maintenance Checks - Airworthiness Limitations - 

Amendment / Implementation 

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. 

Reason: The BAe 146 / AVRO 146-RJ Aircraft Maintenance Manual (AMM) includes the 

Chapters as listed in Appendix 1 of this AD. Compliance with these chapters 

has been identified as a mandatory action for continued airworthiness and 

EASA AD 2012-0004 was issued to require operators to comply with those 

instructions. 

Since that AD was issued, BAE Systems (Operations) Ltd revised the AMM 

(Revision 107), introducing a new defined life limit for the Fire Bottle Cartridge 

Firing Unit into Chapter 05-10-15. Subsequently, Revision 108 of the AMM 

introduced in Chapter 05-20-00 inspection tasks for repairs applied to fatigue 

critical structures and also introduced a new Chapter 05-20-07 to provide 

Structural Repair Manual (SRM) references for these tasks, applicable to 

repairs accomplished after the publication of AMM Revision 108. Finally, AMM 

Revision 111 introduced safe life limitations into Chapter 05-10-15 for rollers of 

main landing gear and door up-locks. 

Furthermore, Section 6 of the Maintenance Review Board Report (MRBR) 

Document MRB 146-01, Issue 2, Revision 18 was published (as referenced 

in Chapter 05-20-01 of the AMM) to correct discrepancies in inspection tasks 

for a number of Structurally Important Items (SIIs). Grace periods for these 
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revised inspection tasks are included in BAE Systems (Operations) Ltd 

Inspection Service Bulletin (ISB) ISB.53-237. 

Failure to comply with the new and more restrictive tasks and limitations 

referenced above could result in an unsafe condition. 

For the reasons described above, this AD retains the requirements of EASA 

AD 2012-0004, which is superseded, and requires implementation of the 

maintenance tasks and/or airworthiness limitations as specified in the 

defined parts of Chapter 05 of the AMM at Revision 112. 

Effective Date: 02 April 2014 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) From the effective date of this AD, accomplish the following actions, in 

accordance with the instructions as specified (or included by reference) in 

the chapters of BAE Systems (Operations) Limited BAe 146 / Avro 

146-RJ AMM at Revision 112, as listed in Appendix 1 of this AD. 

(1.1) Replace each component before exceeding the applicable life limit. 

(1.2) Within the thresholds and intervals, accomplish all applicable 

maintenance tasks. 

(1.3) Ensure the continuing airworthiness of the aeroplane by 

compliance with each Critical Design Configuration Control 

Limitations (CDCCL) – Fuel System item. 

(2) Compliance with the requirements of paragraph (1) of this AD can be 

demonstrated by: 

(2.1) Revising as follows the approved Aircraft Maintenance Programme 

(AMP) on the basis of which the operator or the owner ensures the 

continuing airworthiness of each operated aeroplane: 

 Incorporate all applicable maintenance tasks, airworthiness 

limitations and CDCCL – Fuel System items as specified (or 

included by reference) in the chapters of BAE Systems 

(Operations) Limited AMM at Revision 112, as listed in Appendix 1 

of this AD, 

 and 

(2.2) Complying with the approved AMP described in paragraph (2.1) of 

this AD. 

Ref. Publications: BAE Systems (Operations) Limited documents: 

BAe 146/AVRO 146-RJ AMM, at Revision 112 dated 15 October 2013. 

Corrosion Prevention Control Program (CPCP) Document No. CPCP-146-01, 

Revision 4 dated 15 September 2010. 

Supplemental Structural Inspections Document (SSID) Document No. SSID146-01, Revision 2 dated 15 August 2012. 

MRBR Document No. MRB 146-01, Issue 2 Revision 19 dated August 2012. 

ISB ISB.53-237 Revision 1 dated 2 April 2013. 

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 13 February 2014 as PAD 14-037 for consultation 

until 13 March 2014. No comments were received during the consultation 
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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. 

 
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Appendix 1 

Chapter Subject 

05-10-01 Airframe Airworthiness Limitations before Life Extension Programme 

05-10-05 * Airframe Airworthiness Limitations, Life Extension Programme - 

Landings Life Extended 

05-10-10 ** Airframe Airworthiness Limitations, Life Extension Programme - 

Calendar Life Extended 

05-10-15 Aircraft Equipment - Airworthiness Limitations 

05-10-17 Power Plant - Airworthiness Limitations 

05-15-00 CDCCL - Fuel System Description and Operation 

05-20-00 Scheduled Maintenance, paragraphs 6, 7 and 8 only, on the CPCP, the 

SSID and the SRM detail inspection tasks for published repairs to 

fatigue critical structure as defined in the AMM Chapter 05-20-07. 

05-20-01 Airframe Scheduled Maintenance – Before Life Extension Programme 

(MRBR Section 6) 

05-20-05 * Airframe Scheduled Maintenance, Life Extension Programme Landings 

Life Extended 

05-20-07 Airframe Scheduled Maintenance – Published Repairs 

05-20-10 ** Airframe Scheduled Maintenance, Life Extension Programme Calendar 

Life Extended 

05-20-15 Aircraft Equipment Scheduled Maintenance 

* Applicable only to aeroplanes post-modification HCM20011A or HCM20012A or HCM20013A. 

** Applicable only to aeroplanes post-modification HCM20010A. 

Note 1: Within Chapter 05-20-00, the current relevant issues of the supporting documents are: 

 - CPCP Document No. CPCP-146-01, Revision 4 dated 15 September 2010. 

- SSID Document No. SSID-146-01, Revision 2 dated 15 August 2012. 

Note 2: Within Chapter 05-20-01, the current relevant issue of the supporting document is MRBR 

Document No. MRB 146-01, Issue 2 Revision 19 dated August 2012. 

Note 3: ISB.53-237 Revision 1 allows grace periods for the implementation of some of the SIIs in 

Section 6 of the MRBR.