EASA AD No.: 2011-0023-E 

EASA Form 111 Page 1/3

EASA EMERGENCY AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0023-E 

[Corrected: 10 February 2011] 

Date: 09 February 2011 

Note: This Emergency 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 : 

Turboméca 

Type/Model designation(s) : 

ARRIEL 1 series turboshaft engines 

TCDS Number : EASA.E.073 

Foreign AD : Not applicable 

Supersedure : None 

ATA 73 Engine Fuel & Control – Low Pressure Fuel System / Ejector 

Assembly – Inspection / Replacement 

Manufacturer(s): Turboméca S.A. 

Applicability: Arriel 1E2, 1S and 1S1 turboshaft engines, all serial numbers, on which 

Turbomeca Internal Consign (IC) No. 298468 or Turbomeca Service Bulletin 

(SB) No. 292 73 0826 version A has been accomplished. 

These engines are known to be installed on, but not limited to, the following 

helicopters: 

Eurocopter Deutschland MBB BK117-C2 and BK117-C1, Sikorsky S-76A 

series and C series. 

Reason: In October 2009, Turbomeca issued Turbomeca SB No.292 73 0826 version A 

that instructed operators to check the effectiveness of the bonding of the 

ejector jet installed on the low pressure fuel system between the tank and the 

high pressure fuel pump. 

So far, TURBOMECA have been informed of three discrepancies with the 

reassembly of the ejector following a maintenance procedure performed during 

accomplishment of Turbomeca SB No. 292 73 0826 version A. 

In all three cases, the discrepancies led to a “one-off” abnormal evolution of 

gas generator (NG) rating during engine starting. In one of these cases, this 

resulted in an uncommanded in-flight engine shut-down, during a cruising 

phase at 8 000 feet. 

In all three cases, the ejector was incorrectly positioned in the ejector assembly 

body. 
EASA AD No.: 2011-0023-E 

EASA Form 111 Page 2/3

This condition, if not detected and corrected, could affect the ejector 

performance and lead to an increase in fuel system internal leakages that may 

cause fluctuations of NG and fuel flow disruptions. 

Over a given amplitude, fluctuations in fuel flow can result in an uncommanded 

in-flight engine shut-down of one of the engines. In addition, if the ejectors of 

both engines are incorrectly reassembled, this could result in an 

uncommanded in-flight engine shut-down of both engines which, on a twinengine helicopter, could ultimately lead to an emergency autorotation landing. 

To address this unsafe condition, for engines on which Turbomeca SB No. 

292 73 0826 version A or Turbomeca IC No. 298468 has been accomplished, 

Turboméca have developed Turbomeca Mandatory Service Bulletin (MSB) No. 

A292 73 0834 version B. 

For the reasons described above, this AD requires inspection for proper 

installation of the fuel ejector and, in case of discrepancy, replacement of the 

part with a serviceable part. 

This AD is republished to correct a typographical error with the related 

Turbomeca SBs & MSB reference number. 

Effective Date: 11 February 2011 

Required 

Action(s) and 

Compliance 

Time(s): 

Required as indicated, unless accomplished previously:

(1) Within the compliance time indicated in Table 1 of this AD, inspect the fuel 

ejector in the body of the fuel ejector assembly for proper installation in 

accordance with Paragraph 2.B of Turboméca MSB No. A292 73 0834 

version B. 

Table 1: 

Engine and aircraft configuration: Compliance time:

SB No. 292 73 0826 version A (*) or IC No. 

298468 has been accomplished to the two 

engines of the same aircraft AND Starting difficulties (**) have been 

encountered in at least one of the two 

engines 

5 Flight Hours (FH) 

or 3 days after the 

effective date of 

this AD, whichever 

occurs first 

SB No. 292 73 0826 version A (*) or IC No. 

298468 has been accomplished to only one 

AND of the two engines of the same aircraft 

Starting difficulties (**) have been 

encountered on the related engine 

20 FH or 30 days 

after the effective 

date of this AD, 

whichever occurs 

first 

SB No. 292 73 0826 version A (*) or IC No. 

298468 has been accomplished to one or 

both engines of the same aircraft AND Starting difficulties (**) have not been 

encountered 

100 FH or 90 days 

after the effective 

date of this AD, 

whichever occurs 

first 

Notes for Table 1 of this AD: 

(*): In the engine log book, this might be recorded “SB No. 292 73 0826” 

or “SB No. 292 73 0826 version A”. 

(**): Starting difficulties is when N1 stagnation or variation has been 

encountered. Applicable guidance can be found in Paragraph 1.A.(1) of 

Turboméca MSB No. A292 73 0834 version B. 

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

injector is found to be improperly installed, before next flight, replace the 

ejector assembly with a serviceable unit. 

(3) As an alternative to the actions required by paragraphs (1) and (2) of this 

AD, accomplishment of Turbomeca SB No. 292 73 0826 version B is 
EASA AD No.: 2011-0023-E 

EASA Form 111 Page 3/3

acceptable to comply with all the requirements of this AD, provided that 

the actions are taken within the same compliance time of this AD, as 

applicable. 

(4) After the effective date of this AD, do not install on a helicopter an engine 

on which Turbomeca IC No. 298468 or Turbomeca SB No. 292 73 0826 

version A has been accomplished, unless in compliance with the 

requirements of this AD. 

(5) Inspections / replacements accomplished before the effective date of this 

AD, in accordance with the instructions of Turbomeca SB No. 

A292 73 0834 version A, are acceptable to comply with the requirements 

of this AD. 

Ref. 

Publications: 

Turbomeca Mandatory Service Bulletin No. A292 73 0834 version B dated 

08 February 2011. 

Turbomeca Service Bulletin A292 73 0826 version B dated 4 February 2011. 

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. The safety assessment has requested not to implement the full 

consultation process and an immediate publication and notification. 

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: 

Turboméca, S.A., ARRIEL 1 Customer Support, 40220 TARNOS, 

FRANCE. Fax: +33 5 59 74 45 15 or contact your nearest technical 

representative at www.turbomeca-support.com