EASA AD No.: 2011-0099 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0099 

Date: 26 May 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 21 Air Conditioning - Front and Rear Discharge Valves Fuselage Skin 

– Inspection / Repair 

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, except 

aeroplanes that have incorporated auto-pressurisation modification No. 

HCM50259A during production. 

Reason: An operator has reported the cracking and surface anomalies (bulges and/or 

dents) of the fuselage skin at the water trap/air drier unit of the forward 

discharge valve located between Frames 22 and 23 and between stringers 22 

and 23. 

Further investigation established that these surface anomalies (bulges and/or 

dents) were due to corrosion beneath the water trap/air drier unit that has 

resulted in cracking of the fuselage skin. A crack at the subject location could 

propagate towards the forward discharge valve outlet and result in the failure of 

the fuselage skin leading to a possible sudden loss of cabin pressure. 

For the reasons described above, this AD mandates an initial and repetitive 

inspections of the fuselage skin adjacent to the front and rear discharge valves, 

the accomplishment of the associated correctives actions if applicable and the 

application of an additional sealant in the affected area. 

Effective Date: 09 June 2011 
EASA AD No.: 2011-0099 

EASA Form 110 Page 2/3 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 12 months after the effective date of this AD and thereafter at 

intervals not exceeding 24 months, perform a Detailed Visual Inspection 

(DVI) of the external fuselage skin adjacent to the discharge valve outlets 

(one frame bay fore and aft, one stringer above and below) to check for 

bulging, surface anomalies and cracking in accordance with the 

accomplishment instructions of paragraph 2.C. of BAE Systems 

(Operations) Ltd. ISB 21-162 Revision 1. 

(2) If, during a DVI as required by paragraph (1) of this AD, any damage 

(bulging and/or surface anomalies and/or cracking) is found, before next 

flight, accomplish the associated corrective action defined in Table 1 of this 

AD: 

Table 1 

Damage found: Corrective action 

within the criteria as 

specified in Structural Repair 

Manual (SRM) 53-00-00 

Repair in accordance with the 

accomplishment instructions of 

paragraph 2.G. of BAE 

Systems (Operations) Ltd. ISB 

21-162 Revision 1. 

exceeds the criteria as 

specified in SRM 53-00-00 

Contact BAE Systems 

(Operations) Ltd. for approved 

repair instructions and 

accomplish those instructions 

accordingly. 

(3) At the next maintenance opportunity, or within 24 months after the 

effective date of this AD, whichever occurs first, unless a repair has 

already been accomplished as required by paragraph (2) of this AD, apply 

additional sealant in accordance with paragraph 2.C.(2) of BAE systems 

(Operations) Ltd. ISB 21-162 revision 1. Application of additional sealant 

does not constitute terminating actions for the repetitive DVI required by 

paragraph (1) of this AD. 

(4) Accomplishment of a repair as required by paragraph (2) of this AD 

terminates the repetitive inspection requirements of paragraph (1) of this 

AD. 

(5) Accomplishment of any DVI before the effective date of this AD, in 

accordance with BAE Systems (Operations) Ltd. ISB 21-162 at initial issue 

is acceptable to comply with the initial requirement of paragraph (1) of this 

AD. 

(6) Accomplishment of a repair before the effective date of this AD in 

accordance with the instructions of BAE Systems (Operations) Ltd. ISB 21-

162 at initial issue is acceptable to comply with the requirements of 

paragraphs (2) and (4) of this AD. 

Ref. Publications: BAE Systems (Operations) Limited Inspection Service Bulletin No. 21-162 

Revision 1 dated 16 September 2010. 

BAe 146 Series 100/200 and AVRO 146 Series RJ70/RJ85 Structural Repair 

Manual Revision 65 dated 15 September 2010. 

BAe 146-300 and AVRO 146-RJ100 Structural Repair Manual Revision 43 

dated 15 September 2010. 

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

compliance with the requirements of this AD. 
EASA AD No.: 2011-0099 

EASA Form 110 Page 3/3 

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

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 04 April 2011as PAD 11-035 for consultation until 

02 May 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.