## 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 aircra ft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [ EU 132 1/20 14 Annex I, Part MA303] or agreed with the Authority of the State of Registry [EC 216/2008 , Artid e 14(4) exemption], 

### Des ign Approval Holder's Name : Type/Model designation(s) : SOCA TA 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 se rial 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 add re ss 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 throug h the EASA- Intemet/lntranet.Effec tive Date : Required Action(s) and Compliance Ti me(s) :

Ref. Publi cati ons: EASAAD No.: 201 5-0203 adjustment of the i nspection interval. Consequently, SOCATA issued SB 150-32, now at Revision 3. For the reaso ns described above , this new AD retains the requirements of DGAC Fra nce AD 91 - 163(A)R2 , which is su perseded, but requires these actions to be accomplished within red uced intervals. 21 October 2015 Requi red as indicated , unl ess accomplished previously: (1) With in the compliance time defined in Table 1 of this AD , as applicable, and, the reafte r , at intervals not to exceed 200 FH , accomp l ish a DET of NLG wheel axle and attach ment screws in accordance with t he instructions of SOCA TA SB 150-32, Revision 3. Table 1 -Ini tial DET Compliance Time (whichever occurs later, A or B) Before exceeding 2 00 flight hours (FH) since aeroplane first flight 

### A or since last in spection in accordance with SO CAT A SB 1 50-32 at Revis ion 2, as app licable. Wi thin 50 FH after the effective date of this AD , or w ith i n 500 F H 

### B s ince last in spection in accor dance with SOCA TA SB 150-32 at Revision 2, whichever occurs first. (2) If, during any DET as requ ired by paragraph (1) of this AD, any discrepancy, as defined in SOCATA SB 150-32 at Revis ion 3, is detec ted, before next flight , accomplish th e applicable co rrective action (s) in accordance w ith the instructions of SOCAT A SB 150-32 at Revision 3 . (3) Within the compl iance tim e defined in Table 2 of this AD , as applicable , and, thereafter, at intervals not to exceed 2 000 FH, replace the NLG whee l axle attachment screws with new ones in accordance with the instructions of SOCATA SB 150-32 at Revisio n 3.



# c 0 Table 2 -Initial Attachment Screws Replacement Compliance Time (whichever occu rs later, C or D) Before exceeding 2 000 FH since aeroplane first flig ht, or since last attachment screws replacem ent 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 N LG or used replacement N LG wheel axle is allowed , provided that , prior to installation, the NLG wheel axle passes an inspection in accordance with the instructions of SOCATA SB 150-3 2 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 p aragraph (4) of this AD , cred it may be taken from an inspection of a NLG w heel axle performed in accordance with SOCAT A SB 150-32 at Revision 2 or later, w it hin 200 FH before the installatio n . SOCATA SB 150-32 Revi s ion 2 dated January 1994 , or Revision 3 dated September 2015 . The use of later approved revisions of thi s document is acceptable for

TE.CAP .OOU0 -004 ©E urop ean Aviation Safety Agency
. All rights rese rved
. 2/ 3 Proprietary document. Cop ies 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.e u. 3 . Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@ easa .euro pa .e u . 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 4 1 73 00, Fax+ 33 (0) 5 62 41 76 54
. or for the U.S.A.: SOCATA NORT H AMERICA , 601 NE 10 Street , Pompano Beach , Florida 33060, United States of America Telephone +1 (954) -366-3331
.

TE .CAP. OOU 0 -004 © Euro pean A vi at io n Safety Agen c y. All rights rese rved. 3/3 Proprietary document
. Copies are not controlled. Confirm revision status through t he EASA-I nternet/I ntran et.