Supplier Support Management
NFF NF F No Fault Found policy A320 Family and A330 / A340 Family
Customer Services
This is the fourth issue of the
NFF No Fault Found policy A320 Family and A330/A340 Family
Airbus No Fault Found (NFF) Policy Since the policy introduction in 1994, Airbus has worked closely with the major avionic suppliers to further promote data exchange on this subject. In our analysis of the NFF cases, the major concern remains that the aircraft operators do not always report the reasons for removal of units. The NFF rate will be significantly reduced by application of the policy by ensuring that the requested removal substantiation data is provided. Airbus is proud of the fact that this policy is the only NFF reduction procedure in use in the aerospace industry today. This policy is also issued as part of the Suppliers Product Support Agreement as defined in the GCP2000 (General Conditions of Purchase).
Supplier Support Management
Ref. AI/SP/921.0320/03 - Nov 2003
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No Fault Found policy Aims and benefits to be achieved from implementing this policy
The policy applies to Line Replaceable Units (LRUs) returned to the supplier or to a suppliers authorised repair station. G
Reduction of No Fault Found costs for the Airline.
G
A better understanding of the Centralised Fault Display System (CFDS) and Centralised Maintenance System (CMS). Reduced system interrogation times as experience is gained. This is in conjunction with the revised A320 Trouble Shooting Manual (TSM), which is in the same format as the A330/A340 document.
G
A better understanding between all parties and quicker resolutions of NFF issues will ensue. The suppliers authorised repair station will contact the operator to ensure that reasons for removal are understood and to obtain historic data on the units. Airbus Supplier Support Management may be involved to make sure all causes are documented and to facilitate any interface issues with regard to the application of the NFF policy.
G
Reduction of unjustified removals will result in optimum utilisation of spares.
G
Improvement of the TSM procedures through correlation of common NFF removals.
G
Time to identify rogue LRUs will be reduced through analysis of historic records.
G
This policy is based on the minimum supporting data required to substantiate an unscheduled removal. In developing the policy Airbus has given careful consideration to operational restrictions.
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No Fault Found policy The success of the policy is dependent on each party fulfilling the specific requirements in terms of reporting and tracking the relevant information as defined below.
Suppliers responsibility The supplier is responsible for keeping historic data by serial number of all units. These files should not only contain data on a LRU warranty aspects but also on the total repair history, reasons for removal, testing, NFF, modification standard and all the work performed on the LRU. In taking the leadership of the removal analysis, the supplier or suppliers authorised repair station will contact the operator to obtain any information associated with the LRU removal required to complete the LRU history.
Operators responsibility The application of the policy along with an adequate operator involvement in trouble shooting will significantly lower the number of NFF cases. The operator will provide the minimum data for removal substantiation. The removal data are: G
The initiating Pilot Report (PIREP) and/or Maintenance Report (MAREP) and Post Flight Report (PFR) and
G
The BITE/Trouble Shooting Data (TSD) printout as applicable or The failure results of the return to service test procedure (as per CMM) and historic data of all NFF occurrences at operators facility (for LRU history files)
G
This policy presupposes that the Airbus operational - Flight Crew Operating Manual (FCOM) including Operation Engineering bulletins (OEBs) and maintenance recommendations are followed. The operator is requested to include a technical contact on the paperwork.
3
No Fault Found policy NFF charges
Tests resulting in NFF may be charged whenever: G G G
No supporting data is supplied with the unit The supporting data does not substantiate the removal Operator chooses not to provide the substantiating data after the request of the suppliers repair station.
When no LRU defect is found to be the origin of a fault message, the cause will be clarified between the supplier and Airbus. The supplier will open a specific file for these cases. Airbus and the suppliers will not support NFF cases where clear TSM procedures, in relation to a PFR warning message, provide for correct system trouble shooting.
Automatic Test Equipment (ATE) at operators facility
The operator shall not be deemed responsible where it is shown that the LRU test specification is incomplete or incorrect. The LRU supplier takes responsibility to verify test specifications. The ATE manufacturer is responsible for translation of test specifications. Where the LRU test specification published in the CMM is shown to be correct, the operators selected ATE manufacturer is responsible to clarify NFF resulting from incorrect implementation. If necessary, Airbus Supplier Support Management will facilitate for such issues.
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No Fault Found policy Procedure - NFF Policy flow chart e c i v r e s o t n r u t e R
r e s i l a r t e a o p p d f u m o E d r s c e y T e u o I b b g B c o e s U r p r i e n s y R e o l a L K i n f a
y r o t m e e s m e r E e T I r o B f e p b m u D
e a l t b a a i e d l t a v u g t i i n a t s t r n o D o p S C p T u o s n f i
r o n t o i a r t a e t p s o r t i a c a p t e n R o c
s e a i l t a p d p u g s i n r t o r t o a r p e p p u s S O
O N
e l b t a s e e r T g a h c
E Y
S S A P
L I A F
t s e t
r o
E T A
t f a r c r i A
o n t o i t t a n t e s s i r t i a n p U e r
O N
g n d i t r t a e o a d u p d l c S p n E u i S Y
S S A P t s e T
r i a p e R
L I A F
s e t a g i t l n n a i t a v r t o s o p b m p u e u s r S a t a d
S E Y
t h u t i E o i w t T t t n I n n u B i r e p s
k o o b y r t n e g o L
S E Y
R F P N A M R I A
O N
F F N
S E Y y i t t l i s e b t a r p o t a c a r h e c p n O e b
O N
t s a r o p r t i o a a h p r e e p s R o
M S T
d e r i u q M e r S t T s y e b t E T I B
d e m r E i f T n I o B c y t l b u a F
d l e a l v u o d m e h e r c t i s n n U u
O N e v e D i r S t e T R
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t h u t i t D o w i n t S t n n u T i r e p s
e l b t a s e e r T g a h c
t d s e e T g r a o h N c
No Fault Found policy Explanation of the flow chart :
Procedure on aircraft Action is initiated by a cockpit effect or repetitive CFDS fault. A cockpit effect can be in the form of an ECAM warning or aural call out, or crew observation leading to log book entry.
Log Book entry All entries are made by the flight crew (PIREP) or maintenance personnel (MAREP) into the aircraft log.
Post Flight Report (PFR) A summary of ECAM warning messages. These are identified and cross referenced at the time of message occurrence and ATA chapter reference of the equipment involved. A print is made of the PFR on the on-board printer OR the PRF is printed from the ‘on-ground maintenance aid software’ - AIRMAN.
BITE test Interrogation of CFDS/CMS to confirm equipment fault in reference to the PFR warning or log book entry.
Fault confirmed by BITE test When the fault is confirmed by CFDS the unscheduled removal is supported. A print is made of the BITE test results and returned with the removed LRU. The LRU is removed in accordance with TSM procedures and dispatched to suppliers authorised repair station with supporting data.
In this case the supporting data is the PFR (coming from the aircraft or from AIRMAN) and/or the logbook and the BITE test results (where applicable). Fault not confirmed by BITE test In the case of intermittent faults, the decision to remove the LRU may be delayed until time allows deeper trouble shooting. Prior to the LRU removal the Trouble Shooting Data should be retrieved.
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No Fault Found policy
Trouble Shooting Data (TSD) Snapshot of system at time of ECAM warning (creation of PFR message). This allows an analysis of the system and to correctly attribute the failure. A print is made of the TSD and returned with the removed LRU. The LRU is removed in accordance with the TSM and dispatched to the suppliers authorised repair station with the supportive data. In this case the supporting data is the PFR and TSD.
Procedure in operator shop Fail Test at Test Bench If the LRU fails test then it is sent for repair. If the LRU passes the test it is returned to service.
Unscheduled removal supported by ATE results The LRU is returned to supplier repair station together with the ATE failure report. In this case the supporting data is the PFR and the ATE report.
CFDS/CMS print included with LRU If the PFR plus the BITE Test Results or TSD as applicable or the ATE failure results are included and demonstrate (in conjunction with TSM) that the removal is justified, then no testing charges will apply in case of NFF. If the above data confirm aircraft system fault and if no Airbus Operational or Maintenance procedure exists to prevent LRU removal, Airbus will warrant that the aircraft system responsible party supports test charges.
Removals not supported by CFDS/CMS data The LRU is considered as an unsupported unscheduled removal. The operator is charged for testing in case of NFF.
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No Fault Found policy Definition of terms
AIRCRAFT MALFUNCTION
UNSCHEDULED REMOVAL Known or suspected malfunction
UNJUSTIFIED REMOVAL
JUSTIFIED REMOVAL
No defect of failure found
Failure found whether or not the failure substantiates the reason for removal
UNCONFIRMED REMOVAL
CONFIRMED REMOVAL
No failure which substantiates the reason for removal even though another failure may be found
Failure found substantiating the reason for removal
Applicability Equipment such as proximity switches, pressure transducers, circuit breakers, hydraulic, mechanical and engine system parts are not included in the NFF policy. Such cases may be reviewed with the aim of improving maintenance practices - including Trouble Shooting Manual (TSM) quality but the decision to remove a part will remain with the operator. It has been found that such cases are impossible to adjudicate as far as assessing the responsibility within the standard maintenance practices. The NFF Policy is intended for application with avionic components. A list is enclosed and updated periodically for clarity. 8
No Fault Found policy Equipment list The revised policy applies to the following equipment:
A320 Family ACP ACARS ADF ADIRU
Audio Control Panel A/C Comm. & Reporting System Mngt. Unit Automatic Direction Finder Air Data Inertial Reference Unit
AEVC ALTU AMU AOA SNSR ATC ATSU
Avionic Equipment Ventilation Computer Annunciator Light Test Unit Audio Management Unit Angle of Attack Sensor Air Traffic Control Unit Air Traffic Servicing Unit
Team Honeywell Thales Avionics Honeywell/ Northrop Grumman Thales Avionics Airbus Avionics Team Thales Avionics Thales Avionics Airbus Avionics
BCL BMC BSCU BTMU
Battery Charge Limiter Bleed Air Monitor Computer Brake System Control Unit Brake Temperature Monitoring Unit
Thales Avionics Intertechnique Messier-Bugatti Thales Avionics
CAL CFDIU CHC CIDS CPC CVR
Cockpit Amplifier Loudspeaker Centralised Fault Display Interface Unit Cargo Heat Controller Cabin Intercommunication Data System Cabin Pressure Controller Cockpit Voice Recorder
Airbus Avionics Thales Avionics BAT KID Systeme Nord Micro Honeywell
DMC
Display Management Computer
DMU DME
Data Management Unit Distance Measuring Equipment
Thales Avionics/ DIEHL Avionik Hamilton Sundstrand Thales Avionics
ECB ECP EIU ELAC EVMU FAC
Electronic Control Box, APU ECAM Control Panel Engine Interface Unit Elevator Aileron Computer Engine Vibration Monitoring Unit Flight Augmentation Computer
Honeywell Airbus Avionics Thales Avionics Thales Avionics Vibrometer Thales Avionics 9
No Fault Found policy FCD FCDC FCU FDU FDIU FLSCU FMGC FQIC FWC
Full Colour Display or DU Flight Control Data Concentrator Flight Control Unit Fire Detection Unit Flight Data Interface Unit Fuel Level Sensing Control Unit Flight Mngt. and Guidance Computer Fuel Quantity Indication Computer Flight Warning Computer
Thales Avionics Litef Thales Avionics L’Hotellier SFIM BFG Fuel Thales Avionics Smiths/BFG Fuel Airbus Avionics
GCU GPCU GPWC
Generator Control Unit Ground Power Control Unit Ground Proximity Warning Computer
Hamilton Sundstrand Hamilton Sundstrand Honeywell
HF
High Frequency Receiver
Rockwell Collins/ Honeywell
ILS
Instrument Landing System
Rockwell Collins/ Honeywell
LGCIU
Landing Gear Control/Interface Unit
Ultra Electronics
MCDU
Multi-Purpose Display Unit
Thales Avionics
PC PHC Prntr
Pack Controller Temperature Probe Heat Computer Printer
Liebherr Thales Avionics Honeywell
RMP RALTU RADAR
Radio Management Panel Reprogrammable Annunciator Light Test Weather Radar
Thales Avionics Thales Avionics Rockwell Collins/ Honeywell
SDAC SDCU
System Data Acquisition Concentrator Smoke Detection Control Unit
SEC SFCC SSFDR
Secondary/Flight Control Computer Slat/Flap Control Computer Solid State Flight Data Recorder
Airbus Avionics Thales Avionics/ Cerberus Thales Avionics GEC Marconi SFIM/Honeywell
TCAS
Traffic Collision Avoidance System Comp.
Rockwell Collins/ Honeywell/ Thales Avionics-ACSS
VHF
Very High Frequency Receiver
Rockwell Collins/ Honeywell
WHC
Window Heat Controller
SAT
ZC
Zone Controller 10
Liebherr
No Fault Found policy A330/A340 Family ACP ACARS ADIRU ADF AEVC AMU ATC ATSU
Audio Control Panel A/C Comm. & Reporting System Mngt. Unit Air Data Inertial Reference Unit Automatic Direction Finder Antenna Avionic Equipment Ventilation Computer Audio Management Unit Air Traffic Control Unit Air Traffic Servicing Unit
Team Teledyne/Honeywell Honeywell/ Northrop Grumman Thales Avionics Intertechnique Team Thales Avionics Airbus Avionics
BCL BMC BSCU BTMU
Battery Charge Limiter Bleed Monitoring Computer Brake System Control Unit Brake Temperature Monitoring Unit
Thales Avionics Intertechnique Messier-Bugatti Thales Avionics
CBMU CIDS CMC CPC CVR
Circuit Breaker Monitoring Unit Cabin Intercommunication Data System Central Maintenance Computer Cabin Pressure Control Unit Cockpit Voice Recorder
Intertechnique KID Systeme Airbus Avionics Nord Micro Honeywell
DDRMI DMC
Digital Distance & Radio Mngt. Indicator Display Management Computer
DME DMU
Distance Measuring Equipment Data Management Unit
Thales Avionics Thales Avionics/ DIELH Avionik Thales Avionics Honeywell
ECB ECP EIVMU
Electronic Control Box APU ECAM Control Panel Engine Indicating Vibration Monitoring Unit
Honeywell Airbus Avionics Vibrometer
FCD FCDC FCMC FCPC FCSC FDIU FDU
Full Colour Display or DU Flight Control Data Concentrator Fuel Control Monitoring Computer Flight Control Primary Computer Flight Control Secondary Computer Flight Data Interface Unit Fire Detection Unit
Thales Avionics Thales Avionics BFG Fuel Airbus Avionics Thales Avionics Honeywell/SFIM L’Hotellier
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No Fault Found policy FMGEC FWC
Flight Mngt. Guidance/Envelope Computer Fight Warning Computer
Thales Avionics Airbus Avionics
GCUE GPCU GPSSU
Generator Control Unit, Emergency Ground Power Control Unit Global Positioning System Unit
GPWC
Ground Proximity Warning Computer
Hamilton Sundstrand Hamilton Sundstrand Northrop Grumman/ Honeywell Honeywell
HF
HF Receiver
HSMU
Hydraulic System Monitoring Unit
ILS
Instrument Landing System
Rockwell Collins/ Honeywell
LGCIU
Landing Gear Control Interface Unit
Ultra Electronics
PC PHC PSCU
Pack. Controller Temperature Probe Heat Computer Proximity Switch Control Unit
Liebherr Intertechnique ELDEC
RA RMP
Radio Altimeter Transceiver Radio Management Panel
Rockwell Collins Thales Avionics
SDAC SDCU
System Data Acquisition Concentrator Smoke Detection Control Unit
SFCC SSFDR
Slat Flap Control Computer Solid State Flight Data Recorder
Airbus Avionics Thales Avionics/ Cerberus Honeywell SFIM/Honeywell
TCAS
Traffic Collision Avoidance Sys. Comp.
TPIC TR
Tire Pressure Indicating Computer Transformer Rectifier
VC VHF
Ventilation Controller Very High Frequency Receiver
VOR VSC WBC WHC WXR
ZC
Rockwell Collins/ Honeywell Intertechnique
Rockwell Collins/ Honeywell/ Thales Avionics-ACSS Labinal Artus BAT Rockwell Collins/ Honeywell Rockwell Collins/ Honeywell AOA
VHF Omnidirectional Range Vacuum System Controller Weight and Balance Computer Window Heat Controller Weather Radar Transceiver
DIEHL Avionik Intertechnique Rockwell Collins/ Honeywell
Zone Controller
Liebherr 12
AIRBUS S.A.S. 31707 BLAGNAC CEDEX, FRANCE CONCEPT DESIGN GDC REFERENCE GDCO S- S298/03 NOVEMBER 2003
PRINTED IN FRANCE © AIRBUS S.A.S. 2003 ALL RIGHTS RESERVED
AN EADS JOINT COMPANY WITH BAE SYSTEMS
The statements made herein do not constitut e an offer. They are based on the assumptions shown and are expressed in good faith. Where the supporting grounds for these statements are not shown, the Company will be pleased to explain the basis thereof. This document is the property of Airbus and is supplied on the express condition that it is to be treated as confidential. No use of reproduction may be made thereof other than that expressely authorised.
