EASA AD No.: 2010-0214 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0214 

Date: 02 November 2010 

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 : 

AIRBUS

Type/Model designation(s) : 

A340-500/-600 aeroplanes 

TCDS Number : EASA.A.015 

Foreign AD : Not applicable 

Supersedure : None 

ATA 32 Landing Gear – Nose Landing Gear (NLG) – Drag Stay Lower 

Arm Assembly – Inspection / Replacement 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A340 aeroplanes, models -541 and -642, Weight Variant (WV) 000, 

WV001, WV002, WV003 and WV004, all manufacturer serial numbers. 

Reason: Several NLG drag stay lower arms on A340-500/-600 aeroplanes have 

exhibited corrosion and rust traces in the lugs and on the bearing outer 

surface, discovered visually during scheduled maintenance checks or 

aeroplane walk around. 

Investigation has revealed that this corrosion of the drag stay lower arm can 

be due to: 

- the damage to the sealant applied on the external interface between the 

lug bore and the bearing race, 

- the ingress of contaminants and moisture between the lug bore and 

bearing race, 

- the degradation of the Cadmium plating by chemical phenomena, 

- the degradation of the Cadmium plating by mechanical phenomena. 

The failure of the drag stay lower arm may result in NLG collapse, which 

would constitute an unsafe condition during the take off phase. 

For the above described reasons, this AD requires : 

- repetitive inspections of the NLG drag stay lower arm assembly 

part number (P/N) 30-1018002-01 at the interface between the arm and 
EASA AD No.: 2010-0214 

EASA Form 110 Page 2/3 

the spherical bearing races, for identification of corrosion traces, and 

replacement of the NLG drag stay lower arm assembly in case of 

findings, and 

- Replacement of the affected NLG drag stay lower arm assembly by a 

new or modified part with an improved corrosion protection, as a 

terminating action of the requirements of this AD. 

Effective Date: 16 November 2010 

Required 

action(s) and 

Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) At the time indicated in Table 1 of this AD, accumulated by the NLG 

drag stay lower arm assembly since first installation on an aeroplane, or 

since the last overhaul, as applicable, within the compliance time 

indicated in Table 1 of this AD do a general visual inspection of the NLG 

drag stay lower arm assembly P/N 30-1018002-01 at the interface 

between the arm and the spherical bearing races for identification of 

corrosion traces, in accordance with the instructions of Airbus Service 

Bulletin (SB) A340-32-5099: 

 Table 1 

Calendar time (in 

months)

Compliance Time (in months), whichever 

occurs first:

Less than 36 Before accumulating 45 

Between 36 and 45 Before accumulating 52, or within 9 months 

after the effective date of this AD 

Between 45 and 60 Before accumulating 65, or within 7 months 

after the effective date of this AD 

Between 60 and 72 Before accumulating 75, or within 5 months 

after the effective date of this AD 

Between 72 and 84 Before accumulating 85, or within 3 months 

after the effective date of this AD 

More than 84 Within 1 month after the effective date of this 

AD 

(2) If no corrosion traces are found, repeat the inspection required by 

paragraph (1) of this AD, at intervals not to exceed 6 months from the 

last inspection. 

(3) If corrosion traces are found during the initial or repetitive inspection 

required by paragraph (1) or (2) of this AD, within the compliance time 

defined in Table 2 of this AD replace the NLG drag stay lower arm 

assembly in accordance with the instructions of Airbus SB 

A340-32-5099: 

Table 2 

For NLG drag stay lower arm assembly having 

accumulated (at the date of the inspection 

accomplishment) since its first installation on an 

aeroplane or from the last NLG overhaul or part 

replacement: 

Replace 

within: 

More than 85 months AND which has not been 

inspected in the last 6 months 

5 Flight 

Cycles 

Between 65 and 85 months AND which has not been 

inspected in the last 6 months 1 Month 

More than 64 months AND which has been 

inspected in the last 6 months 3 Months 

Less than 65 months 3 Months 
EASA AD No.: 2010-0214 

EASA Form 110 Page 3/3 

(4) At each replacement of the NLG drag stay lower arm assembly as 

required by paragraph (3) of this AD: 

No later than 45 months after the replacement, perform the initial 

inspection required by paragraph (1) of this AD and thereafter the 

repetitive inspections required by paragraph (2) of this AD, and do the 

applicable corrective actions defined in paragraph (3) of this AD. 

(5) Within 90 days after accomplishment of the initial or repetitive 

inspection required by paragraph (1) or (2) of this AD, report the 

inspection results, including nil finding, to Airbus. 

(6) Within 10 years after the effective date of this AD, replace the NLG 

drag stay lower arm assembly with a serviceable part having improved 

corrosion protection, in accordance with the instructions of Airbus SB 

A340-32-5101. 

(7) Replacement of the NLG drag stay lower arm assembly on an 

aeroplane as required by paragraph (6) of this AD cancels the 

requirements of this AD. 

Ref. Publications: Airbus Service Bulletin A340-32-5099 Original issue dated 

23 September 2010. 

Airbus Service Bulletin A340-32-5101 Original issue dated 

20 October 2010. 

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 required actions and the risk allowance have granted the issuance 

of a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

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 questions concerning the technical content of the requirements 

in this AD, please contact: 

Airbus – Airworthiness Office – EAL; 

E-mail: airworthiness.A330-A340@airbus.com.