EASA AD No.: 2014-0255

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0255

Date: 25 November 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption].


### Design Approval Holder’s Name: SAAB AB, AERONAUTICS Type/Model designation(s): 2000 aeroplanes

TCDS Number: EASA A.069

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2013-0172R1 dated 06 September 2013.



### ATA 38 Water / Waste – Potable Water System / In-line Heat er – Inspection / Modification

Manufacturer(s): Saab AB, Aeronautics (formerly Saa b Aerosystems)

Applicability: Model 2000 aeroplanes, serial number s (s/n) 004 through 016 inclusive, s/n 018, 022, 023, 024, 026, 029, 031, 032 and 033, s/n 035 through 039 inclusive, s/n 041 through 044 inclusive, s/n 046, 047, 048 an d 051, and s/n 053 through 063 inclusive.

Reason: One occurrence of rudder pedal restriction was repo rted on a SAAB 2000 aeroplane. Subsequent investigation showed that thi s was the result of water leakage at the inlet tubing for the in-line heater (25HY) in the lower part of the forward fuselage (Zone 116). The in-line heater att achment was found ruptured, which resulted in water spraying in the area. Froze n water on the rudder control mechanism in Zone 116 then led to the rudder pedal restriction. Analysis after the reported event indicated that th e pitch control mechanism (including pitch disconnect/spring unit) may also b e frozen as a result of water spray, which would prevent disconnection and normal pitch control. This condition, if not corrected, could result in f urther occurrences of reduced control of an aeroplane. To address this potential unsafe condition, SAAB is sued Service Bulletin (SB) 2000-38-10 to provide instructions to deactivate th e Potable Water System. Consequently, EASA issued Emergency AD 2013-0172-E, to require that action. That Emergency AD was revised and republish ed as EASA AD 2013-0172R1, introducing a temporary alternative pr ocedure for filling, which would allow reactivation and operation of the Potab le Water System.EASA AD No.: 2014-0255

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Since that AD was issued, SAAB developed an in-line heater spray shield and a water line shrink tube to eliminate the consequen ces of a water spray leak in case of rupture of the in-line heater. SAAB also is sued a SB 2000-38-011, providing instructions for inspection of the in-lin e heater and installation of a shrink tube and a spray shield. For reasons described above, this AD retains the re quirements of EASA AD 2013-0172R1, which is superseded, and requires insp ection of the in-line heater and installation of shrink tube and spray sh ield.

Effective Date: 09 December 2014

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: Re-statement of requirements of EASA AD 2013-0172R1 : (1) Within 30 days after 01 August 2013 [the effect ive date of the original issue of EASA AD 2013-0172], deactivate the potable water system in accordance with the instructions of SAAB SB 2000-38 -010. (2) As an alternative, or subsequent, to the action required by paragraph (1) of this AD, during each filling of the Potable Water S ystem after 06 September 2013 [the effective date of EASA AD 2013- 0172R1], accomplish the filling procedure in accordance with instructions of SAAB Service News Letter (SNL) 2000-1304, which allows r eactivation of the Potable Water System. New requirements of this AD : (3) Within the compliance time, as specified in Tab le 1 of this AD, depending on the aeroplane configuration, accomplish concurre ntly the actions specified in paragraphs (3.1) and (3.2) of this AD in accordance with the instructions of SAAB SB 2000-38-011. (3.1) Inspect the in-line heater, and (3.2) Install a water line shrink tube and in-line heater spray shield.

Table 1 Spray Shield Installation
Aeroplane configuration Compliance time
Potable Water System reactivated and operated using the alternative filling procedure as specified by paragraph (2) of this AD Within 6 month after the effective date of this AD

Potable Water System deactivated as required by paragraph (1) of this AD Before next flight after reactivation of the Potable Water System
(4) If, during the inspection as required by paragr aph (3.1) of this AD, any discrepancy is detected, before accomplishment of t he modification as required by paragraph (3.2) of this AD, accomplish all applicable corrective actions in accordance with the instructions of SAAB SB 2000-38-011. (5) Modification of an aeroplane as required by par agraph (3) of this AD, allows reactivation of the potable water system.

Ref. Publications: SAAB SB 2000-38-010 original iss ue, dated 12 July 2013. SAAB SNL 2000-1304 original issue, dated 30 August 2013. SAAB SB 2000-38-011 original issue, dated 22 Octobe r 2014. The use of later approved revisions is acceptable f or compliance with theEASA AD No.: 2014-0255

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 27 October 2014 as PAD 14- 157 for consultation until 10 November 2014. The Comment Response Docume nt can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: SAAB AB, Support and Services, SE-581 88 Linköping, Sweden, Fax: +46 13 184874. E-mail: saab2000.techsupport@saabgroup.com

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