AIRWORTHINESS DIRECTIVE Landing Gear Nose landing gear Wheels at 90 degrees

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EASA AIRWORTHINESS DIRECTIVE
AD No.: 2006 - 0174
Date: 21 June 2006
No person may operate an aircraft to which an Airworthiness Directive applies, except in accordance with the
requirements of that Airworthiness Directive unless otherwise agreed with the Authority of the State of Registry.
Type Approval Holder’s Name :
AIRBUS
Type/Model designations:
A318, A319, A320 and A321 aircraft
TCDS Number : EASA.A.064
Foreign AD : None
Supersedure: DGAC AD F-2005-191, EASA approval No. 2005-6411
ATA 32 Landing Gear - Nose landing gear – Wheels at 90 degrees
Manufacturers: AIRBUS (formerly AIRBUS INDUSTRIE)
Applicability: AIRBUS A318, A319, A320 and A321 aircraft, all certified models and all
serial numbers that are equipped with or have ever been equipped with a
EMM Breaking/Steering Control Unit (BSCU) part number (PN):
- PN E21327001 (standard L4.1) installed by AIRBUS Modification
26965 or by AIRBUS Service Bulletin (SB) A320-32-1912
Or
- PN E21327003 (standard L4.5) installed by AIRBUS Modification
33376 or SB A320-32-1261.
Aircraft on which the BSCU has always been standard L4.8 ( modification
35216 : installation of EMM BSCU PN E21327004) or non EMM BSCU are
not affected by the requirements of this Airworthiness Directive (AD).
Reason: An event where an A320 landed with the Nose Landing Gear (NLG)
wheels rotated at 90 degrees to the aircraft centreline was recently
reported.
Investigation showed that the upper support of the NLG shock absorber
was damaged and the anti-rotation lugs were ruptured. This led the nose
wheels to loose their centred position reference normally ensured by the
shock-absorber cams. The Braking and Steering Control Unit (BSCU) had
logged a steering system fault, because hydraulic power was not available
at the time of steering system checks, therefore the BSCU was not able to
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proceed with the re-centring of the wheels.
To prevent reoccurrence of landings with NLG turned 90 degrees, AD F-
2005-191 that dealt with the same subject, rendered mandatory an
operational procedure and maintenance actions.
This AD supersedes AD F-2005-191 and is issued to extend the
applicability and to introduce a repetitive boroscopic inspection of the NLG
upper support lugs and cylinder lugs.
Effective Date: 05 July 2006
Compliance: 1. Operational procedure only applicable to aircraft listed in the
applicability paragraph that have not received AIRBUS modification
31152 in production (i.e. applicable only to aircraft with the steering
powered by the green hydraulic system).
From the effective date of this AD , the following operational procedure is
mandatory for all flights:
The ECAM message, in case of a nose wheel steering failure, will be worded
as follows:
- “WHEEL N/W STRG FAULT” for aircraft with FWC software post E3P
- “WHEEL N.W STEER FAULT” for aircraft with FWC software pre E3P
􀂾 If the L/G SHOCK ABSORBER FAULT ECAM caution is triggered at any
time in flight, and the WHEEL N/W STRG FAULT ECAM caution is
triggered after the landing gear extension:
􀁹 When all landing gear doors are indicated closed on ECAM WHEEL
page, reset the BSCU:
- A/SKID&N/W STRG---------------------------- OFF THEN ON
􀁹 If the WHEEL N/W STRG FAULT ECAM caution is no longer displayed,
this indicates a successful nose wheel re-centring and steering
recovery.
- Rearm the AUTO BRAKE, if necessary.
􀁹 If the WHEEL N/W STRG FAULT ECAM caution remains displayed,
this indicates that the nose wheel steering remains lost, and that the
nose wheels are not centred.
- During landing, delay nose wheel touchdown for as long as
possible.
- Refer to the ECAM STATUS
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􀂾 If the WHEEL N/W STRG FAULT ECAM caution appears, without the L/G
SHOCK ABSORBER FAULT ECAM caution:
- No specific crew action is requested by the WHEEL N/W STRG FAULT
ECAM caution procedure.
- Refer to the ECAM STATUS
Incorporation of this AD or AFM TR 4.02.00/33 for aircraft without FWC
H2E3P or H1E3P or subsequent standard, or TR 4.02.00/34 for aircraft with
FWC H2E3P or H1E3P or subsequent standard in the Aircraft Operations
Manual as well as in the Aircraft Flight Manual and strict adherence by the
crew allows complying with paragraph compliance 1 of this AD.
2. For all aircraft listed in the applicability paragraph:
Within 100 flight cycles following an ECAM caution 'L/G SHOCK
ABSORBER FAULT' associated with at least one of the below Centralised
Fault Display System (CFDS) messages:
'N L/G EXT PROX SNSR 24GA TGT POS',
'N L/G EXT PROX SNSR 25GA TGT POS',
'N L/G SHOCK ABSORBER FAULT 2526GM'.
2.1. Check the NLG strut inflation pressure, weight off and weight on
wheels, in accordance with AIRBUS Aircraft Maintenance Manual
AMM 12-14-32 revised by TR No 12-001. Adjust/correct as applicable.
Note: the instructions for the NLG pressure check are also given in SB
A320-32-1310 at original issue.
2.2. Perform a boroscopic inspection of the NLG upper support antirotation
lugs and the cylinder lugs, in accordance with AIRBUS
Technical Note 957.1901/05, dated October 18, 2005.
If any upper support anti-rotation lugs are found broken or cracked or if
the cylinder lugs are found to be missing: before next flight, apply all
necessary actions to get a serviceable NLG (contact AIRBUS Fax: 33 5
61 93 32 73).
All inspection results should be reported to AIRBUS.
Note: the instructions for the boroscopic inspection are also given in
SB A320-32-1310 at original issue.
3. For aircraft listed in the applicability paragraph that are equipped
with EMM BSCU standard L4.1 or L4.5:
3.1. At the latest of these two dates:
- Prior to the accumulation of 20 months, or 6000 flight hours, or 4500
flight cycles, since the aircraft first flight, whichever occurs first,
or
- Within the 6 months, or 1800 flight hours, or 1350 flight cycles,
following the effective date of this AD, whichever occurs first,
Perform a boroscopic inspection of the NLG upper support lugs and
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cylinder lugs and apply corrective actions, if necessary, in accordance
with SB A320-32-1310 at original issue.
3.2. Repeat the inspection defined in above paragraph compliance 3.1
at intervals not exceeding 6 months or 1800 flight hours or 1350 flight
cycles, whichever occurs first and apply corrective actions, if
necessary, in accordance with SB A320-32-1310 at original issue.
- Installation of a NLG with new upper support anti-rotation lugs and new
cylinders lugs
Or
- Installation of a NLG for which it can be demonstrated that it was never
driven by a EMM BSCU L4.1 or L4.5
together with the installation of a EMM BSCU standard L4.8 or a non EMM
BSCU render void the requirements of this AD. No further action is
required by this AD.
4. For aircraft listed in the applicability paragraph that are equipped
with EMM BSCU standard L4.8 or a non EMM BSCU:
4.1. At the latest of these two dates:
- Prior to the accumulation of 20 months, or 6000 flight hours, or 4500
flight cycles, since the aircraft first flight, whichever occurs first,
or
- Within the 6 months, or 1800 flight hours, or 1350 flight cycles,
following the effective date of this AD, whichever occurs first,
Perform a boroscopic inspection of the NLG upper support lugs and
cylinder lugs and apply corrective actions, if necessary, in accordance
with SB A320-32-1310 at original issue.
4.2. Repeat the inspection defined in above paragraph compliance 4.1 at
intervals not exceeding 20 months or 6000 flight hours or 4500 flight
cycles, whichever occurs first and apply corrective actions, if
necessary, in accordance with SB A320-32-1310 at original issue.
- Installation of a NLG with new upper support anti-rotation lugs and new
cylinders lugs
Or
- Installation of a NLG for which it can be demonstrated that it was never
driven by EMM BSCU L4.1 or L4.5
renders void the requirements of this AD. No further action is required by
this AD.
Ref. Publications: AIRBUS Aircraft Maintenance Manual TR No 12-001 based on the Nov
01/05 revision
AIRBUS Aircraft Maintenance Manual 12-14-32
AIRBUS Technical Note reference 957.1901/05 dated October 18, 2005
AIRBUS AFM TR 4.02.00/33
AIRBUS AFM TR 4.02.00/34
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AIRBUS Service Bulletin A320-32-1310 at original issue
or later approved revisions.
Remarks : 1. If requested and appropriately substantiated the responsible EASA
manager for the related product has the authority to accept Alternative
Method of Compliance (AMOCs) for this AD.
2. This AD was posted as PAD 06-071 for consultation on 22 March with a
comment period until 05 April 2006. The Comment Response Document
can be found at http://ad.easa.eu.int/ .
3. Enquiries regarding this AD should be addressed to Mr. M. Capaccio, AD
Focal Point, 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 AIRBUS - Fax 33 5 61 93 44 51