EASA 

EASAAD No.: 2015-0203 

AIRWORTHINESS DIRECTIVE 

AD No.: 2015..0203 

Date: 07 October 2015 

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 Artlde 66 of that 

Regulation. 

This AD is issued in accordance with EU 748/2012, Part 21A3B. In accordance with EU 132112014 Annex I, Part M.A301 , 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 [EU 

1321/2014 Annex I, Part MA303] or agreed with the Authority of the State of Registry [EC 216/2008, Artide 14(4) exemption], 

Design Approval Holder's Name: Type/Model designation(s): 

SOCATA 

TCDS Number: 

Foreign AD: 

Supersedure: 

ATA32 

Manufacturer(s): 

Applicability: 

Reason: 

MS 880, MS 890 and RALL YE aeroplanes 

EASA.A.377 and EASA.A.379 

Not Applicable 

This AD supersedes OGAC France AD 91 -163(A)R2 dated 30 March 1994. 

Landing Gear- Nose Wheel Axle and Attachment Screws -

Inspection I Replacement 

Societe de Construction d'Avions de Tourisme et d'Affaires "S.O.C.A.T.A."-

Groupe AEROSPATIALE, Societe d'Exploitation des Etablissements 

MORANE-SAULNIER, Societe MORANE-SAULNIER) 

MS 880 B, MS 880 B-D, MS 881, MS 883, MS 884, MS 885, MS 886, MS 887, 

MS 890 A. MS 890 B. MS 892 A.150, MS 892 B.150, MS 892 E.150, 

MS 892 E-D.150, MS 893 A, MS 893 B, MS 893 E, MS 893 E-D, MS 894 A, 

MS 894 E. RALLYE 100 S, RALLYE 100 S-D, RALLYE 100 ST, 

RALLYE 100 ST-D, RALLYE 110 ST, RALLYE 150 ST. RALLYE 150 ST-D. 

RALLYE 150 T, RALLYE 150 T-D, RALLYE 150 SV, RALLYE 150 SVS, 

RALLYE 180 T, RALL YE 180 TS, RALLYE 180 T-D, RALLYE 235 A, 

RALLYE 235 F, RALL YE 235 E and RALL YE 235 E-D aeroplanes. all 

manufacturer serial numbers. 

A nose landing gear (NLG) wheel axle rupture occurred in service. The results 

of the technical investigations revealed that this failure was due to premature 

wear. 

This condition, if not detected and corrected, could lead to cracks in the axle 

and detachment of axle and wheel, possibly resulting in failure of the NLG with 

consequent damage to the aeroplane and injury to occupants. 

To address this potential unsafe condition, DGAC France issued AD 91-163(A) 

(later revised twice) to require repetitive detailed inspections (DET) of the NLG 

wheel axle and replacement of the NLG wheel axle attachment screws in 

accordance with the instructions of SOCATA Service Bulletin (SB) 150-32. 

Since DGAC France AD 91-163 A R2 was issued, new findin sled to an 

TE.CAP.00110·004 ©European Aviation Safety Agency. All rights reserved. 1/3 

Proprietary document. Copies are not controlled. Confirm reviSion status through the EASA-Intemet/lntranet. 
Effective Date: 

Required Action(s) 

and Compliance 

Time(s): 

Ref. Publications: 

EASAAD No.: 201 5-0203 

adjustment of the inspection interval. Consequently, SOCATA issued SB 

150-32, now at Revision 3. 

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

DGAC France AD 91 -163(A)R2, which is superseded, but requires these 

actions to be accomplished within reduced intervals. 

21 October 2015 

Required as indicated, unless accomplished previously: 

(1) Within the compliance time defined in Table 1 of this AD, as applicable, 

and, thereafter, at intervals not to exceed 200 FH, accomplish a DET of 

NLG wheel axle and attachment screws in accordance with the 

instructions of SOCA T A SB 150-32, Revision 3. 

Table 1 -Initial DET 

Compliance Time (whichever occurs later, A or B) 

Before exceeding 200 flight hours (FH) since aeroplane first flight 

A or since last inspection in accordance with SO CAT A SB 150-32 at 

Revision 2, as applicable. 

Within 50 FH after the effective date of this AD, or within 500 FH 

B since last inspection in accordance with SOCA T A SB 150-32 at 

Revision 2, whichever occurs first. 

(2) If, during any DET as required by paragraph (1) of this AD, any 

discrepancy, as defined in SOCATA SB 150-32 at Revision 3, is detected, 

before next flight, accomplish the applicable corrective action(s) in 

accordance with the instructions of SOCAT A SB 150-32 at Revision 3. 

(3) Within the compliance time defined in Table 2 of this AD, as applicable, 

and, thereafter, at intervals not to exceed 2 000 FH, replace the NLG 

wheel axle attachment screws with new ones in accordance with the 

instructions of SOCATA SB 150-32 at Revision 3. 

c 

0 

Table 2 -Initial Attachment Screws Replacement 

Compliance Time (whichever occurs later, C or D) 

Before exceeding 2 000 FH since aeroplane first flight, or since last 

attachment screws replacement with new ones as applicable. 

Within 50 FH after the 09 April 1994 [the effective date of DGAC 

France AD 91 -163(A)R2]. 

(4) From the effective date of this AD, installation of a used replacement NLG 

or used replacement NLG wheel axle is allowed, provided that, prior to 

installation, the NLG wheel axle passes an inspection in accordance with 

the instructions of SOCATA SB 150-32 at Revision 3 (see Note), and the 

NLG wheel axle attachment screws are replaced with new ones. 

Note: In showing compliance with the inspection requirement of paragraph (4) 

of this AD, credit may be taken from an inspection of a NLG wheel axle 

performed in accordance with SOCAT A SB 150-32 at Revision 2 or later, within 

200 FH before the installation. 

SOCATA SB 150-32 Revision 2 dated January 1994, or Revision 3 dated 

September 2015. 

The use of later approved revisions of this document is acceptable for 

TE.CAP.OOU0-004 ©European Aviation Safety Agency. All rights reserved. 2/ 3 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. 
EASA AD No.: 2015-0203 

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 04 September 2015 as PAD 15-116 for consultation 

until 02 October 2015. The Comment Response Document can be found at 

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

3. Enquiries regarding this AD should be referred to the Safety Information 

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: 

SOCATA, Direction des services, 65921 Tarbes Cedex 9, France 

Telephone +33 (0) 5 62 41 73 00, Fax+ 33 (0) 5 62 41 76 54. 

or for the U.S.A.: 

SOCATA NORTH AMERICA, 601 NE 10 Street, Pompano Beach, 

Florida 33060, United States of America 

Telephone +1 (954) -366-3331 . 

TE.CAP.OOU0-004 © European Aviation Safety Agency. All rights reserved. 

Proprietary document. Copies are not controlled. Confirm 

3/3 revision status through the EASA-Internet/Intranet.