EASA AD No.: 2009-0215 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0215 

Date: 07 October 2009 

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 : This AD supersedes EASA AD 2009-0020 dated 05 February 2009. 

ATA 05 Time Limits / Maintenance Checks – Airworthiness Limitations – 

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 

Chapters 05-10 “Time Limits”, 05-15 “Critical Design Configuration Control 

Limitations (CDCCL) - Fuel System Description and Operation” and 05-20 

“Scheduled Maintenance Checks”, some sub-chapters of which have been 

identified as requirements for continued airworthiness and EASA AD 2009-

0020 was issued to require operators to comply with those instructions. 

Since the issuance of that AD, BAE Systems (Operations) Limited has 

amended the AMM to introduce life limitations on additional main landing gear 

shock absorber inner and outer cylinder and bolt part numbers in sub-chapter 

05-10-15. In addition BAE Systems has updated and clarified the text in subchapters 05-00-00, 05-10-01, 05-20-00, 05-20-01 and 05-20-10 and changed 

the modification effectivity status in sub-chapters 05-10-05, 05-10-10 and 05-

20-10. Finally BAE Systems has introduced a new sub-chapter, 05-20-05, to 

define the maintenance for aeroplanes in the Life Extension Programme (LEP) 

which have had their landings life extended. 

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

EASA AD 2009-0020, which is superseded, and requires the implementation 

of the instructions, limitations, inspections and corrective measures as 

specified in the defined parts of Chapter 05 of the AMM at Revision 96.
EASA AD No.: 2009-0215 

EASA Form 110 Page 2/3 

Effective Date: 21 October 2009 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the next 3 months after the effective date of this AD, amend the 

approved aircraft maintenance schedule to incorporate the instructions of 

the sub-chapters of BAe 146 / AVRO 146-RJ AMM Chapter 05 at AMM 

Revision 96, as indicated in Table 1 of this AD. 

 Within sub-chapter 05-20-00, the relevant issues of the supporting 

documents are as follows: 

 - CPCP Document No. CPCP-146-01, Revision 3 dated 15 July 2008, 

plus Temporary Revision TR 2.1 dated October 2008. 

- SSID Document No. SSID-146-01, Revision 1 dated 15 June 2009. 

 Within sub-chapter 05-20-01, the relevant issue of the supporting 

document is as follows: 

 - MRBR Document No. MRB 146-01, Issue 2 Revision 15 dated May 2009 

(incorporating Temporary Revision TR 6.8 dated 27 October 2008). 

Table 1 

Subchapter 

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 Critical Design Configuration Control Limitations (CDCCL) - 

Fuel System Description and Operation 

05-20-00 Scheduled Maintenance, paragraphs 5 and 6 only, on the 

Corrosion Prevention and Control Programme (CPCP) and the 

Supplemental Structural Inspection Document (SSID) 

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 

05-20-10 

** 

Airframe Scheduled Maintenance, Life Extension Programme 

Calendar Life Extended 

05-20-15 Aircraft Equipment Scheduled Maintenance 

* Applicable only to aircraft post-modification HCM20011A or HCM20012A 

or HCM20013A. 

** Applicable only to aircraft post-modification HCM20010A. 

(2) Thereafter, within the thresholds and intervals indicated in that document, 

accomplish the tasks described in the above referenced parts of the AMM, 

except: 

- The initial accomplishment for the CPCP TR 2.1 task must be done 
EASA AD No.: 2009-0215 

EASA Form 110 Page 3/3 

within 2 years after 19 February 2009 [the effective date of AD 2009-0020] 

and 

- The initial accomplishment for the MRBR TR 6.8 task must be done 

within 2 years after 19 February 2009 [the effective date of AD 2009-

0020]. 

Note: When a Temporary Revision is superseded by the inclusion of the 

information in a permanent update of the applicable document, the 

requirements of this AD still apply. 

(3) For AVRO 146-RJ85 aeroplanes with Messier-Dowty Main Landing Gear 

(MLG) units installed that have been modified in accordance with the 

instructions of Messier-Dowty Service Bulletin (SB) 146-32-171, the life 

limit for the MLG main fittings may be extended from 32 000 landings to 

50 000 landings. It is expected that these revised life limits will be 

incorporated into the BAE Systems (Operations) Limited BAe 146/AVRO 

146-RJ AMM at a next revision. 

Ref. Publications: 

BAE Systems (Operations) Limited BAe 146/AVRO 146-RJ AMM Chapters 

05-10, 05-15 and 05-20 at Revision 96, dated 15 May 2009. 

Messier-Dowty SB 146-32-171 dated 11 August 2009. 

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 27 August 2009 as PAD 09-105 for consultation 

until 24 September 2009. The Comment Response Document can be 

found at http://ad.easa.europa.eu. 

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.