适航指令AIRWORTHINESS DIRECTIVE Nose Landing Gear Steering

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COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105
CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Page 1 of 4
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes
Airworthiness Directive (AD) AD/A320/187 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in
the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product
mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the
requirement section; and (c) at the time mentioned in the compliance section.
Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/187
Amdt 1
Nose Landing Gear Steering 4/2007
Applicability: AIRBUS A318, A319, A320 and A321 aircraft that are equipped with an EMM
Braking and Steering Control Unit (BSCU) part number (PN) E21327001 (Standard
L4.1, AIRBUS Modification 26965 - Service Bulletin A320-32-1912) or PN
E21327003 (Standard L4.5, AIRBUS Modification 33376 - Service Bulletin
A320-32-1261).
This Airworthiness Directive (AD) is not applicable to aircraft that have been
delivered and equipped with BSCU standard L4.8 from production incorporating
modification 35216( installation of EMM BSCU PN E21327004) or non EM BSCU.
Requirement: 1. The following operational procedure is only for those aircraft that have not
incorporated AIRBUS modification 31152 in production (i.e. applicable only to
aircraft with the steering powered by the green hydraulic system).
Incorporate the following 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 into the Aircraft Operations Manual as well as the
Aircraft Flight Manual.
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-centering and
steering recovery.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105
CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/187 Amdt 1 (continued)
Page 2 of 4
- 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 centered.
- During landing, delay nose wheel touchdown for as long as
possible.
- Refer to the ECAM STATUS

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
2. Check the NLG strut inflation pressure, weight off and weight on wheels, in
accordance with AIRBUS Aircraft Maintenance Manual (AMM) 12-14-32 and
its associated TR issued on 13 November 2005; and
Perform a one time boroscopic inspection of the NLG upper support (backplate)
to detect anti-rotation lugs ruptured (completely broken), in accordance with
AIRBUS Technical Note 957.1901/05, dated 18 October 2005; and
Report the results of all inspections to AIRBUS.
3. If any upper support anti-rotation lugs are found ruptured (completely broken),
carry out all necessary actions to get a serviceable NLG.
4. Perform a boroscopic inspection of the NLG upper support lugs and carry out any
rectification as required. Rectification is detailed in SB A320-32-1310.
Terminating Action.
Installation of a NLG with new upper support anti-rotation lugs and new cylinder
lugs;
or
Installation of a NLG for which it can be demonstrated that is was never driven by
EMM BSCU L4.1 or L4.5;
Together with the installation of an EMM BSCU standard L4.8 or non EMM BSCU
provides terminating action to the requirements of this AD.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105
CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/187 Amdt 1 (continued)
Page 3 of 4
Note: EASA AD 2006-0174 dated 21 June 2006 refers. This AD supersedes DGAC
AD F-2005-191.
Compliance: 1. Remains unchanged as from 5 December 2005 (the effective date of the original
issue of this AD).
2. Within 100 flight cycles following an ECAM caution ‘L/G SHOCK ABSORBER
FAULT’ associated with at least one of the following 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’.
3. Before further flight.
4. For aircraft that are equipped with EMM BSCU standard L4.1 or L4.5:
Prior to the accumulation of 20 months or 6000 flight hours or 4500 flight cycles
since first flight of the aircraft, whichever occurs first; or
Within 6 months, or 1800 flight hours or 1350 flight cycles following the
effective date of this AD, whichever occurs first.
Thereafter repeat the inspection at intervals not to exceed 6 months or 1800 flight
hours or 1350 flight cycles whichever occurs first.
For aircraft that are equipped with EMM USCU standard L4.8 or a non
EMM BSCU:
Prior to the accumulation of 20 months or 6000 flight hours or 4500 flight cycles
since first flight of the aircraft, whichever occurs first; or
Within 6 months, or 1800 flight hours or 1350 flight cycles following the
effective date of this AD.
Thereafter repeat the inspection at intervals not to exceed 20 months or 6000
flight hours or 4500 flight cycles whichever occurs first.
This Amendment becomes effective on 12 April 2007.
Background: An event where an A320 landed with the Nose Landing Gear (NLG) wheels rotated at
90 degrees to the aircraft centreline was recently reported.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105
CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/187 Amdt 1 (continued)
Page 4 of 4
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 lose their
centered position reference normally ensured by the shock-absorber cams. The
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 proceed
with the re-centering of the wheels.
To prevent reoccurrence of landings with the NLG turned 90 degrees, this AD
introduces operational procedures and maintenance actions.
This amendment changes the applicability, introduces an additional boroscopic
inspection and provides a terminating action to the AD through modifications.
The original issue of this AD became effective on 5 December 2005.
David Punshon
Delegate of the Civil Aviation Safety Authority
16 February 2007