Wise Masts A

WISE Main Adopted Solutions and Tips A320 Family

July 2014

Fleet performance

© AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.

WISE Main Adopted Solutions and Tips

• WISE Main Adopted Solutions and Tips was a standalone application

providing you with recommendations to improve your aircraft reliability and

reduce your operation costs. This application is now integrated into Next

Generation WISE.

• During the migration period, this PDF file is made available to you in order

to ensure continuity of the information delivered.

Disclaimer

• The values and information provided in this service are supplied in good faith and are based on in-service

experience feedback obtained from operators of the concerned aircraft fleets. The recommendations based on

said values and information do not constitute a contractual commitment, warranty or guarantee whatsoever

but are for information and convenience only.


Table of content

• AEVC upgrade to standard V06 amendment E

• FCV 1303 reliability improvement

• Outflow valve reliability improvement

• Skin Air Inlet Valve Overhaul

• Skin Air Outlet Valve Overhaul

• FAP improvement

• Handset improvement

• Recent Solution: Introduce new latch and keeper for OHSC

• Improved SDCU Power Supply card

• Improved smoke detectors for avionics zone

• Recent Solution: Introduce new smoke detectors for SDCU-based SDS

• Yaw damper servo control standard upgrade

• Improved SEC reliability


Table of content

• Modify position of ventillation holes on ELAC racks

• Preventive replacement of the radio PTT switch

• Recent Solution: Introduce roller bearing on rod end rudder servocontrol

• Recent Solution: Introduce roller bearing on rod end elevator servocontrol

• New fuse for moisture ingress protection

• Improved check-valve in HP/PTU manifold

• Modified elbow union

• Preventive replacement of Y PTU manifold

• Preventive replacement of Y HP manifold

• Upgrade of Eaton EDP

• Alleviate fluid leak from manifold

• Power Transfer Unit leakage reduction

• Modification of automatic brake selector valve


Table of content

• Preventive replacement of MLG door actuator hose

• MLG Lock Stay Actuator Hose Upgrade

• LED Navigation lights

• Recent solution: Sealing of drain hole to prevent liquid contamination

• Introduce the optional alignement improvement function on ADIRU

• Introduce PTFE seals to avoid air leak

• Forward and AFT cargo door proximity switches upgrade

• Introduce improved cockpit door locking control unit

• Install deflectors on IAE V2500 AFT Pylon Fairing

• Cockpit window preventive maintenance

• Install saddle clamp on CFM56-5B hydraulic line

• Recent Solution: Introduction of New HPTACC Valve 329695-5


AEVC upgrade to standard V06 amendment E

RECO-SA-21-01

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: MSN < 2700

Engine: ALL ATA 4D: 2126 & 2615 System: AEVC

Affected P/N: 87292325-04, 87292325-05, 87292325-06 Supplier: THALES AVIONICS

Impact: A/C Availability,Maintenance economics,Operations

Economic interest: Payback period < 2y l

Background: Some operators have encountered cases of avionics ventilation system issues (VENT AVNCS SYSTEM FAULT, VENT SKIN VALVE FAULT ECAM warning), leading to flight delays, cancellations but also to some aborted take-off or in-flight interruptions (due to the impossibility to pressurize cabin). The AEVC (PN 87292325-0X) is one of the main root cause for such warnings. Furthermore, AEVC may also be at the origin of spurious "AVIONICS SMOKE" warning, due to vibrations at RAM level, which is responsible for some in-flight interruptions (LAND ASAP cases).

Airbus recommendation: Operators are recommended to upgrade AEVC units to standard V06 amendment E (as a minimum) and so to embody, according to current AEVC standard, one or several of the following Thalès VSB: - VSB 87292325-21-008 to improve AEVC robustness with regards to electrical transient (for V04 units) - VSB 87292325-21-011 (covered by SB 21-1147) as a final fix towards the spurious "avionics" smoke warnings (for V05 units) - VSB 87292325-21-012 to improve the interface robustness between the AEVC and the Skin Air Valves (for V06 units, pre-amendment E) AEVC V06 amendment E has been introduced in production for MSN > 2700 and VSB 87592325-21-012, issued in 2006, has already been embodied on about 900 in-service aircraft with positive feedback. Notes: - The amount of the corresponding benefit mainly depends on the pre-mod AEVC standard. In other words, the reliability improvement will be more important (in term of MTBUR increase for example) with -04 pre-mod AEVC standard than with -05 or -06 (pre-amendment E). Yet in all cases, due to different kit price and manpower, the payback period is globally the same. The "cost / benefit analysis" presented here is relative to -05 pre-mod AEVC standard. - The cost/benefit analysis presented here does not include the cost corresponding to AEVC test after VSB embodiment

Back to table of content

Last update: 27 Feb 2009



Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events linked to Avionics Ventilation system issues 2) Reduction of the number of unscheduled and unjustified removals of AEVC (higher MTBUR and lower NFF rate) and so globally reduction of associated maintenance costs 3) Reduction of the number of unscheduled and unjustified removals of the Skin Air Valve (higher MTBUR and lower NFF rate) and so reduction of associated maintenance costs (not taken into account for the cost/benefit analysis)

General assumptions: Economic conditions: 2008 Labour rate on-A/C: 60 $ per MH Labour rate off-A/C: 60 $ per MH Annual aircraft utilisation: 3210 FH Average flight duration 1.8 FH Fleet size: 20 A/C

Maintenance economics assumptions: Spare price: 12570 $ Repair costs: N/C Test cost: N/C Typical NFF rate: 50%

Investment for recommendation: Labour on-A/C: 2.5 MH per A/C Labour off-A/C: 2 MH per A/C Number of kits: 1 Kit per A/C Kit price: 160 $ per Kit Other investment: None

Associated documentation:

TFU 21.26.00.020, SB 21-1147, TFU 21.26.00.019, VSB 87292325-21-011


RECO-SA-21-01 Last update: 27 Feb 2009



OI Rate reduction: 40% MTBUR increase: 20% Weight impact: 0 kg




FCV 1303 reliability improvement

RECO-SA-21-02

Program: A320 Family Applicability A/C Type: A319,A320,A321 Applicability msn: 0882 < MSN < 2532

Engine: ALL ATA 4D: 2151 & 2152 System: Flow Control Valve

Affected P/N: 1303A0000-02 Amdt B, 1303A0000-03 Amdt AB Supplier: LIEBHERR AEROSPACE TOULOUSE


Economic interest: 2y < Payback period < 4y l

Background: Some operators have encountered cases of AIR PACK 1(2) FAULT ECAM warning, or one PACK set to default HI FLOW. Such events, generally due to FCV failure, lead to aircraft delays (to secure that FCV is in closed position for example) and cancellations (ETOPS flight for example) but also to some cases of ground turn back and in-flight interruptions. Investigations have allowed to identify the valve position microswitch (FCV sub-component) as the main root cause for FCV 1303A0000-02 & 1303A0000-03 failures.

Airbus recommendation: VSB 1303-21-06 introduces a new FCV standard (PN 1303A0000-04), equipped with a different microswitch. This microswitch, made by Le Crouzet, is already embodied on FCV 751 series (A320 family, MSN < 1000) and FCV 964 series (A340 family) with very low failure rate. This new FCV has been introduced in production for MSN > 2500 and VSB 1303-21-06, issued in 2005, has already been embodied on more than 1000 aircraft with positive feedback. Note: this economic assessment has been considered on attrition as specified within the vendor technical documentation (ref. VSB 1303-21-06).


Last update: 08 Jul 2012



Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events linked to Pack System failure 2) Improvement of FCV reliability (higher MTBUR and MTBF) and so reduction of associated maintenance costs


Maintenance economics assumptions: Spare price: 24409 $ Repair costs: 3224 $ Test cost: 692 $ Typical NFF rate: 17%

Investment for recommendation: Labour on-A/C: None (on attrition) Labour off-A/C: 3.5 MH per FCV Number of kits: 1 Kit per FCV Kit price: 1100 $ per Kit Other investment: None


TFU 21.51.51.009, VSB 1303-21-06


RECO-SA-21-02 Last update: 08 Jul 2012


Outflow valve reliability improvement

RECO-SA-21-03

Program: A320 Family Applicability A/C Type: A319,A320,A321 Applicability msn: MSN < 1800

Engine: ALL ATA 4D: 2131 System: Outflow valve

Affected P/N: 20790-01AA, 20790-02AB Supplier: NORD-MICRO



Background: Some operators have encountered cases of CAB PR SYS 1(2) FAULT ECAM, CAB EXCESS CAB ALT ECAM warning or Cabin altitude oscillations, leading generally to aircraft delays and cancellations but also to some cases of ground turn-back or in-flight interruptions. Majority of these issues were observed after introduction of CPC-10, which performs a more sensitive monitoring of the outflow valve (Fault Code 81). Such events were generally solved through outflow valve removal and replacement.

Airbus recommendation: SB 21-1136 / VSB 20790-21-002 introduces a new outflow valve standard (PN 20790-02AC), with new electronic box software and potentiometer, to reduce the risk of Fault Code 81 occurrences . This outflow valve standard has been introduced in production for MSN > 1800 and SB 21-1136, issued in 2002, has already been embodied on more than 400 aircraft, with positive feedback.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events due to cabin pressure issues 2) Reduction of the number of unscheduled removals of the Outflow Valve (higher MTBUR) and so reduction of associated maintenance costs





SB 21-1136, VSB 20790-21-002, TFU 21.31.51.015, SB 21-1132




Skin Air Inlet Valve Overhaul

RECO-SA-21-04

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: ALL

Engine: ALL ATA 4D: 2126 System: Avionics Equipment Ventilation

Affected P/N: VFT210A2, VFT210A2 Amdt A, VFT210B00, VFT210B00 Amdt A Supplier: TECHNOFAN


Background: Operators have reported a repetitive "VENT AVNCS SYS FAULT" ECAM warning associated during takeoffs with "VENT SKIN VALVE FAULT" indicating that the Skin Air valve (FIN 15HQ) is not fully closed.

Airbus recommendation: Airbus recommends to apply at regular interval an overhaul of the Skin Air Inlet Valve and the Skin Air Outlet Valve at the same time. Present analysis considers a 18 000 FH interval between overhauls for the only Skin Air Inlet valves (decorrelated from the Skin Air Outlet valves, which overhaul is assessed through a separate analysis).





Benefit of the recommendation: This overhaul will decrease the possible malfunction of the Skin Air Inlet Valve which can result in costly delays, Aborted Take-off or In-Flight Turn Back events occurence. In the mean time, costly Skin Air Inlet Valve removals reported to Airbus also decrease significantly (the schedule maintenance interval being shorter than the component reliability itself - MTBUR).



Investment for recommendation: Labour on-A/C: 1 MH per A/C Labour off-A/C: 12 MH per A/C Number of kits: 1 kit per A/C Kit price: 3730 $ Other investment: None


SIL 210A2-21-520, SIL 210B00-21-520





OI Rate reduction: 75% MTBUR increase: 300% Weight impact: N/A




Skin Air Outlet Valve Overhaul

RECO-SA-21-05


Engine: ALL ATA 4D: 2126 System: Avionics Equipment Ventilation

Affected P/N: VFT300B00, VFT300B00 Amdt A Supplier: TECHNOFAN


Background: Operators have reported a repetitive "VENT AVNCS SYS FAULT" ECAM warning associated during takeoffs with "VENT SKIN VALVE FAULT" indicating that the Skin Air valve (FIN 22HQ) is not fully closed.

Airbus recommendation: Airbus recommends to apply at regular interval an overhaul of the Skin Air Inlet Valve and the Skin Air Outlet Valve at the same time. Present analysis considers a 18 000 FH interval between overhauls for the only Skin Air Outlet valves (decorrelated from the Skin Air Inlet valves, which overhaul is assessed through a separate analysis).





Benefit of the recommendation: This overhaul will decrease the possible malfunction of the Skin Air Outlet Valve which can result in costly delays, Aborted Take-off or In-Flight Turn Back events occurence. In the mean time, costly Skin Air Outlet Valve removals reported to Airbus also decrease significantly (the schedule maintenance interval being shorter than the component reliability itself - MTBUR).



Investment for recommendation: Labour on-A/C: 1 MH per A/C Labour off-A/C: 11 MH per A/C Number of kits: 1 kit per A/C Kit price: 3190 $ Other investment: None


SIL 300B00-21-520




FAP improvement

RECO-SA-23-01


Engine: ALL ATA 4D: 2373 System: CIDS

Affected P/N: Z130H0XXX110 Supplier: Kid Système

Impact: A/C Availability,Maintenance economics Economic interest: 2y < Payback period < 4y l

Background: Operational experience has shown that Forward Attendant Panels (FAPs) with the P/N Z130H0XXX110 may freeze after a short power interruption. A faulty FAP is not a "NO GO ITEM". In case of FAP freezing, the cabin crew cannot control the cabin lighting anymore. The lighting setting will either stay as selected or will be switched automatically to 50% if the FAP loses communication with the CIDS director.

Airbus recommendation: SB 23-1259 consists in performing a check of the FAP P/N and S/N to assess the applicability of the modification. When FAP P/N and S/N meet the SB requirements, the modification is then FOC. The present economic analysis applies to FAP which couple (P/N, S/N) is out of the SB range. Meaning that is considered the charged implementation of Kid-Systeme's VSB Z130H-23-037.




FAP improvement

Benefit of the recommendation: Implementation of Kid-Systeme's VSB Z130H-23-037 fixes the FAP freeze issue. 1) Improvement of the FAP MTBUR 2) Reduction of the number of Operational Interruptions



Investment for recommendation: Labour on-A/C: 5 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 1 Kit per A/C Kit price: 1265 $ per Kit Other investment: None


SB 23-1259, VSB Z130H-23-037




FAP improvement





Handset improvement

RECO-SA-23-02

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: All MSN

Engine: ALL ATA 4D: 2373 System: Handset

Affected P/N: 89-01-07000, 89-01-07122, ST3100-33-10, ST3100-23-10 Supplier: Holmberg or Becker



Background: Some operators report low reliability of Holmberg & Becker Handsets. The reliability issues reported are as follows: 1) Handset brackets do not hold the handset enough securely and handset falls down. 2) Handset housings are not robust enough and break when they fall down on the Non Textile Floor. 3) The Holmberg handset cable D-Sub connector/pins attachment are unreliable and cable leads are often found damaged. 4) Holmberg general reliability issues: microphone, reed contact fail.

Airbus recommendation: Upgrade handsets series: 89-01-07000 (with support bracket 98-01-07900) 89-01-07122 (with support bracket 98-01-07902) ST3100-33-10 (with support bracket HC3100-33-10) ST3100-23-10 (with support bracket HC3100-23-10) with N40-1B series. Note: The cost/benefit analysis presented here corresponds to the replacement of the handset on attrition basis.


Last update: 26 Mar 2012


Handset improvement

Benefit of the recommendation: 1) Operational reliability improvement 2) Component reliability improvement 3) The new standard is less expensive than the pre mod one (either becker or holmberg handset)



Investment for recommendation: Labour on-A/C: 2.5 MH per Handset Labour off-A/C: 0 MH per A/C Number of kits: N/A Kit price: N/A Other investment: None


TFU 23.73.00.089, SIL 23-030:VSIL 7301-23-09, SB 25-1906, VSB 89-23-15


RECO-SA-23-02 Last update: 26 Mar 2012


Handset improvement





Recent Solution: Introduce new latch and keeper for OHSC

RECO-SA-25-01


Engine: ALL ATA 4D: 2524 System: Overhead stowage compartments

Affected P/N: FA259-50600-000, FA259-51000-000 Supplier: AIRBUS OPERATIONS SAS

Impact: A/C Availability,Maintenance economics,Operations,Airline image


Background: Some operators have reported a high rate of overhead stowage bin latches becoming unserviceable. The cause is a deflection of the overhead bottom panel when the overhead stowage compartment is heavily loaded. This leads to difficulty in opening or closing the OHSC. This results in several different types of damage to the keeper, latch hooks, handles or the edge protection.

Airbus recommendation: Airbus recommends to install an improved latch and keeper for the OHSC. Note: this economic assessment has been considered on a retrofit basis on A319. Similar results are observed on A320/A321.


Last update: 02 Aug 2012



Benefit of the recommendation: Accomplishment of this Service Bulletin with the revised latch and keeper geometry will improve the operation of the latch mechanism on the OHSC. The improved latch places the hook into a deeper position and allows better closing of the OHSC.


Maintenance economics assumptions: Spare price: 329 $ Repair costs: N/A Test cost: N/A Typical NFF rate: N/A

Investment for recommendation: Labour on-A/C: 1 MH per OHSC Labour off-A/C: 0 MH per A/C Number of kits: A319: 40 latch & keeper A320: 46 latch & keeper A321: 60 latch & keeper Kit price: 125 $ per OHSC door until 31st of March 2013 Other investment: None


SB 25-1786, TFU 25.24.00.010, SIL 25-158


RECO-SA-25-01 Last update: 02 Aug 2012


Improved SDCU Power Supply card

RECO-SA-26-02


Engine: ALL ATA 4D: 2616 & 2617 System: SDCU

Affected P/N: RAI2800M0706 Supplier: THALES AVIONICS



Background: Some operators have encountered cases of SMOKE LAV + CRG DET FAULT ECAM warning (with no access to SDCU menu via MCDU), leading generally to aircraft delays and cancellations but also to some in-flight interruptions. Majority of these warnings are spurious ones, that can be cleared by an SDCU reset on ground. Yet, in certain cases, smoke detector or SDCU is removed and replaced, giving an unconfirmed fault in shop (high NFF rate for SDCU and Smoke detectors). The heating of SDCU power supply card is one of the main root cause for such spurious warning. Note: Refer to RECO-SA-26-001 if access to SDCU menu is possible

Airbus recommendation: VSB RAI2800-26-015 improves the design of SDCU Power Supply card in order to decrease its heating, which can be at the origin of spurious warning occurrences. This VSB, issued in 2004, has not been introduced in production, as recent aircraft are no more equipped with SDCU, but has been embodied on more than 300 in-service aircraft with positive feedback.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events linked to smoke detection system failure 2) Reduction of the number of unscheduled and unjustified SDCU removals (higher MTBUR, lower NFF rate), and thus reduction of the associated maintenance costs 3) Reduction of the number of unscheduled and unjustified Smoke Detector removals (higher MTBUR, lower NFF rate), and thus reduction of the associated maintenance costs (not taken into account for the cost/benefit analysis) 4) Easier trouble-shooting and so reduction of delay duration when smoke detection system failure








Improved smoke detectors for avionics zone

RECO-SA-26-03


Engine: ALL ATA 4D: 2615 & 2126 System: Smoke detectors

Affected P/N: CG7G0 Supplier: SIEMENS



Background: Some operators have encountered cases of AVNCS SMOKE ECAM warning. These warning have mainly been reported on ground, leading generally to aircraft delays or cancellations. However some warning have also been generated in flight, shortly after take-off, leading to in-flight-interruptions (LAND ASAP). Majority of these warnings are spurious ones. The ionic smoke detectors (PN CG7G0), which are sensitive to high humidity and high temperature conditions, is one of the main root causes for such spurious warning.

Airbus recommendation: SB 26-1052 allows the installation of Optical Smoke Detectors (PN CGDU2000-00) instead of Ionic Smoke Detector in avionics compartment. These improved smoke detectors have been introduced in production for MSN > 1500 and SB 26-1052, issued in 2000, has already been embodied on about 400 in-service aircraft, with positive feedback.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events linked to avionics smoke warning 2) Improvement of smoke detectors reliability (higher MTBF) and so reduction of associated maintenance costs 3) Easier trouble-shooting and reduction of delay duration when avionics smoke 4) Cancellation of MPD task 261500-04-1 associated with ionic smoke detectors cleaning and thus maintenance cost savings





SB 26-1052, TFU 26.15.15.001

A318_A319_A320_A321 MPD 26-15-00-04-1




Recent Solution: Introduce new smoke detectors for SDCU-based SDS

RECO-SA-26-04


Engine: ALL ATA 4D: 2615 & 2616 & 2617 System: Smoke detectors

Affected P/N: PPA2100-00, PPA1102-00, PPA1203-00, GPA1102-00, GPA1101-00, PPA1202-00, PPA1201-00, GPA1202-00 Supplier: SIEMENS



Background: Smoke detection issues on Long Range (LR) aircraft have been reported. Subsequent laboratory tests have shown that, under certain circumstances, conducted Electro Magnetic Interferences (EMI) could lead to the disconnection of the Smoke Detectors (SD). On Single Aisle (SA) aircraft, the disconnection of one or more SDs could lead to the ECAM warning SMOKE / SMOKE LAV / CRG DET FAULT associated with class 1 maintenance message SMOKE DET LOOP. New SD P/Ns have been introduced on LR aircraft to reduce disconnection occurrences in case of conducted EMI. In addition, due to the obsolescence of the old P/Ns and the commonality of P/Ns between the LR and SA programs, the old P/Ns will be no longer available for the SA program.

Airbus recommendation: This Service Bulletin is published to advise all operators of A319, A320 and A321 aircraft of the issue of SIEMENS Service Bulletin No. PPAGPA-26-004, which replaces the existing SDs with modified units. This increases the robustness of the smoke detectors against EMI to reduce the smoke detection disconnection occurences. Note: - The cost/benefit analysis presented here corresponds to the modification implementation by retrofit mean. - Last date to place a purchase order at the price mentionned in the Cost/Benefit analysis: end of October 2014 - The payback period takes into account OI rate and MTBUR improvement for both Smoke Detector and SDCU


Last update: 10 Sept 2013



Benefit of the recommendation: Accomplishment of the modification will bring following benefits: 1) Reduction of the number of Operational Interruptions events linked to the ECAM warning SMOKE / SMOKE LAV / CRG DET FAULT associated with class 1 maintenance message SMOKE DET LOOP. 2) Improvement of Smoke Detectors and Smoke Detection Control Unit reliability (higher MTBUR) and so reduction of associated maintenance costs


Maintenance economics assumptions: Spare price: 5000 $ Repair costs: 1000 $ Test cost: N/A Typical NFF rate: N/A

Investment for recommendation: Labour on-A/C: 10 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 10 smoke detectors in average per aircraft Kit price: 829 $ per detector Other investment: None


SB 26-1081, VSB PPAGPA-26-004


RECO-SA-26-04 Last update: 10 Sept 2013



OI Rate reduction: 95% MTBUR increase: 250% Weight impact: 0 Kg




Yaw damper servo control standard upgrade

RECO-SA-27-01


Engine: ALL ATA 4D: 2726 System: Yaw Damper

Affected P/N: SC4700-3, SC4700-4 Supplier: GOODRICH ACTUATION SYSTEMS



Background: Some operators have encountered hydraulic leaks at yaw damper level (and more precisely at piston rod sealing level of the yaw damper servo control) with servo control PN SC4700-3 or SC4700-4. Such events generate long delays, flight cancellations or even in-flight interruptions and may lead to the loss of the hydraulic system (green or yellow). Note that one yaw damper system may be inoperative according to MMEL 22.63.01, but with operational restrictions for landing (CAT 3 Single only).

Airbus recommendation: SB 27-1147 allows the installation of SC-4700-5 standard yaw damper servo control. This actuator has been introduced in production for MSN > 2000 and SB 27-1147, issued in 2003, has already been embodied on around 1000 in-service aircraft, with positive feedback. Notes: - the cost/benefit analysis presented here is based on SC4700-3 pre-mod standard hypothesis (kit price, MTBUR...) - the kit to upgrade units from SC4700-4 to SC4700-5 is Free Of Charge (FOC)





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events due to hydraulic leak at yaw damper level and so reduction of associated costs 2) Reduction of the probability to loose the hydraulic system and so reduction of associated costs (filling of the hydraulic system with new fluid, EDP replacement if the operational check of the pump has failed, aircraft towing if the lost hydraulic system is the green one) 3) Improvement of yaw damper servo control reliability (MTBF) and so reduction of associated (unscheduled) maintenance costs 4) Cancellation of MPD task 272651-01-1 associated to yaw damper actuator inspection and thus maintenance costs saving



Investment for recommendation: Labour on-A/C: 8.5 MH per A/C Labour off-A/C: 22 MH per A/C Number of kits: 2 Kits per A/C Kit price: 6200 $ per Kit Other investment: 400 $ per Fleet


TFU 27.26.00.010, TFU 27.26.51.001, SB 27-1139, SB 27-1147, VSB SC4700-27-26-02, VSB SC4700-27-04

A318_A319_A320_A321 MPD 272651-01-1

A318_A319_A320_A321 MMEL 22-63-01




Improved SEC reliability

RECO-SA-27-02

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: 1800 < MSN < 3900 (Power Boost) / 2500 < MSN < 3400 (S-RAM issue)

Engine: ALL ATA 4D: 2794 System: SEC

Affected P/N: B372BAM04#, B372BAM05# Supplier: THALES AVIONICS



Background: Some operators have encountered cases of F/CTL SEC 1(2/3) FAULT warning, mainly on ground during electrical transients (engine start), leading generally to aircraft delays or ground turn back. Investigations led with Thalès have allowed identifying two main root causes at SEC computer level: - Power Boost Fucntion - S-RAM (S-RAM failure may appear in any flight phase and lead to F/CTL Spoiler fault) These two issues, considered as quality issues, affect a certain batch of SEC computers: - Power Boost Function: 1800 < MSN < 3900, SEC SN between Q00136009440 and Q00136016499 - S-RAM: 2500 < MSN < 3400, SEC SN between Q00136012084 and Q00136015015

Airbus recommendation: VSB B372BAM-27-028 and B372BAM-27-030 improve drastically the reliability of the SEC through two hardware modifications (respectively replacement of S-RAM and transistors). These VSB, issued respectively in 2008 / 2009, have been introduced in production on MSN > 3400 / 3900, have been embodied on around 200 / 500 in-service SEC with positive feedback. Note: different strategies are possible to emboby these VSB (on attrition vs. retrofit). Yet Airbus recommends operators to speed up the embodiment progress through a retrofit campaign. The cost/benefit analysis presented here corresponds to this option, which means that the SEC units is sent specifically to the shop to implement these two modifications (it is supposed that the SEC unit is in the batch of SEC units affected by both issues: S-RAM & Power Boost). That also implies that a Return To Service test is to be done once VSB have been embodied, note that the corresponding cost has been taken into account in the analysis.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events linked to SEC failure 2) Improvement of SEC MTBUR / MTBF and thus reduction of the associated maintenance costs



Investment for recommendation: Labour on-A/C: 1.5 MH per A/C Labour off-A/C: 5 MH per A/C Number of kits: 1 global Kit per A/C Kit price: 500 $ per Kit Other investment: 1232 $ per SEC (RTS)


VSB B372BAM-27-028, VSB B372BAM-27-030, TFU 27.94.00.022




Modify position of ventillation holes on ELAC racks

RECO-SA-27-03


Engine: ALL ATA 4D: 2793 System: ELAC

Affected P/N: 3945128# Supplier: THALES AVIONICS

Impact: Maintenance economics Economic interest: 2y < Payback period < 4y l

Background: Several operators reported recurrent fault messages "ELACx-COM (or MON) OR WIRING FROM ACCLRM y" // "ELACx OR WIRING FROM B (or Y or G) HYD PRESS XMTR y" in PFR. The fault is not systematically reproduced during fault confirmation test "BITE test of the EFCS". Also the fault is usually cleared by ELAC replacement. Very few cases of aircraft pitch up tendency in manual mode have also been reported.

Airbus recommendation: Root cause is identified as pollution inside ELAC back assembly connectors. This pollution originates from aircraft environment. The SB 27-1209 recommends to modify the position of ventilation holes of ELAC racks to decrease air flow around ELAC back assembly.





Benefit of the recommendation: This Service Bulletin will prevent or delay the pollution creation inside ELAC back assembly connectors.


Maintenance economics assumptions: Spare price: 122680 $ Repair costs: 3700 $ Test cost: N/A Typical NFF rate: N/A

Investment for recommendation: Labour on-A/C: 4 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: None Kit price: None Other investment: None


SB 27-1209





OI Rate reduction: N/A MTBUR increase: 10% Weight impact: N/A




Preventive replacement of the radio PTT switch

RECO-SA-27-04

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: All MSN

Engine: ALL ATA 4D: 2792 System: PTT switch

Affected P/N: D27310099# Supplier: AIRBUS OPERATIONS SAS


Background: Some airlines have reported an increase of radio Push To Talk (PTT) switch removals.

Airbus recommendation: Airbus recommends a preventive replacement of the radio PTT switch at 8,000 FC through AMM tasks 27-92-41-000-010-A01 / AMM 27-92-41-400-010-A01. This given interval may have to be adapted by operators according to their own experience. The replacement of the radio PTT switch can be made using the original or alternate procedure. The alternate procedure allows to remove the radio PTT switch without removal of the side stick control-handle. This alternative procedure uses splices. A saving of around 3 MH (1 MH instead of 4 MH) is expected when comparing original and alternate AMM tasks. The cost analysis is computed for alternate procedure usage. For information the saving with the original procedure is 7%.


Last update: 06 Jan 2014



Benefit of the recommendation: High reduction of the number of Operational Interruptions events linked to Ecam Warnings "VHF emitting" and/or PTT switch failure/replacement.



Investment for recommendation: Labour on-A/C: 2 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 2 kit per A/C Kit price: 300 $ per Kit Other investment: None


TFU 27.92.00.002

A318_A319_A320_A321 AMM 27-92-41-000-010-A, AMM 27-92-41-400-010-A, AMM 27-92-41-000-010-A01, AMM 27-92-41-400-010-A01


RECO-SA-27-04 Last update: 06 Jan 2014



OI Rate reduction: 90% MTBUR increase: N/A Weight impact: N/A




Recent Solution: Introduce roller bearing on rod end rudder servocontrol

RECO-SA-27-05

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: 0029 < MSN < 5831

Engine: ALL ATA 4D: 2724 System: Flight Controls - Rudder hydraulic actuation

Affected P/N: 810A0000-03, 810A0000-04, 810A0000-05, 810A0000-06 Supplier: LIEBHERR-AEROSPACE LINDENBERG GmbH



Background: Cases of rudder vibration reports have been received from customers. Rudder vibrations are caused by play developing at rudder and rudder Single Chime (SC) attachment levels. Rudder servocontrol bearings are one of the contributors to this play. In-service experiences demonstrated that rudder servocontrol rod end bearing (surface side) is more subject to wear. Introduction of roller bearing (re-greaseable) on rudder servocontrol rod end has been decided in order to increase bearing wear robustness, to reduce its wear and thus to prevent rudder vibration occurrences.

Airbus recommendation: This Service Bulletin is published to advise all operators of A318/A319/A320/A321 aircraft of the issue of LIEBHERR-AEROSPACE Service Bulletin No. 810A-27-06. It recommends replacing the current rod end fitted with self lubricating spherical bearing (Teflon coated bearing) by a new rod end fitted with a roller bearing (FINs 1025 GM, 2025 GM and 3025 GM). Note: The cost/benefit analysis presented here corresponds to the modification implementation by retrofit mean on A/C





Benefit of the recommendation: Accomplishment of this Service Bulletin will increase wear robustness of rudder servocontrol rod end bearing. Note: this new type of rod end fitted with roller bearing requires a period servicing (re-greasing); this will be reflected as required in the Maintenance Planning Document (MPD). Additional benefits: 1) Reduction of the number of Operational Interruptions events linked to vibrations 2) Improvement of the Servocontrol-Rudder reliability (higher MTBUR) and so reduction of associated maintenance costs


Maintenance economics assumptions: Spare price: 28943 $ Repair costs: 6926 $ Test cost: 925 $ Typical NFF rate: 0.11

Investment for recommendation: Labour on-A/C: 7.5 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 3 roller bearing Kit price: 2715 $ per roller Other investment: None


SB 27-1224, TFU 27.24.51.004, VSB 810A-27-06





OI Rate reduction: 80% MTBUR increase: 80% Weight impact: -0.360 kg




Recent Solution: Introduce roller bearing on rod end elevator servocontrol

RECO-SA-27-06


Engine: ALL ATA 4D: 2734 System: Flight Controls - Elevator and hydraulic actuation

Affected P/N: 341203-# Supplier: UTC Aerospace Systems



Background: On elevator servo control, one case of rod end rupture and several rod ends cracks have been reported. Investigations have shown that rod end cracks and rupture are caused by a particular bending effect.

Airbus recommendation: Install new rods end with an integrated roller bearing replacing the old rods end fitted with a self-lubricating spherical bearing (Teflon coated bearing) (FINs 34CE1, 34CE2, 34CE3 and 34CE4). Note: SB to be accomplished on-wing to save shop recertification cost at VSB embodiment.


Last update: 27 Mar 2014



Benefit of the recommendation: Accomplishment of Service Bulletin 27-1223 cancels the inspection requirements of Inspection Service Bulletin No. 27-1186 (AD 2010-0046: final fix to crack & rupture) and will solve the in-service issue of elevator rod end cracks. Introduction of roller bearing will also have a positive effect on the bearing wear rate (reduction), and thus prevents elevator vibration occurrences, avoiding in some circumstances: - Operational Interruptions - Servo control Elevator removals and associated costs (maintenance, recertification).


Maintenance economics assumptions: Spare price: 66790 $ Repair costs: N/C Test cost: N/C Typical NFF rate: N/C



SB 27-1223, TFU 27.34.00.017, SIL 27-164:AOT:27A1186, VSB 31075-27-22

A318_A319_A320_A321 AMM 27-34-51-000-009-A, AMM 27-34-51-400-006-A





OI Rate reduction: 50% MTBUR increase: 100% Weight impact: +0,080 kg




New fuse for moisture ingress protection

RECO-SA-28-01


Engine: ALL ATA 4D: 2842 System: FQI Fuse

Affected P/N: F561626PZ922Y Supplier: DEUTSCH Ltd



Background: Some operators have encountered cases of degraded Fuel Quantity Indication (FQI) for LH(RH) inner and outer tank, and as a consequence degraded Fuel On Board (FOB) indication. Such events generally lead to flight delays or cancellations but also to some in-flight interruptions. Malfunction of the fused connector (PN F561626PZ922Y) has been identified as the root cause of this issue. Note: Departure is authorized in such scenario, as per MMEL 28-40-06, but loss of accuracy needs to be taken into account for the fuel planning, as indicated in FCOM 3.04.28.

Airbus recommendation: SB 28-1143 introduces a new fused plug connector and a new fuse, in order to obtain an improved insulation resistance and resistance to moisture ingress. This modification has been introduced in production for MSN > 2550 and SB 28-1143, issued in 2005, has already been embodied on about 250 in-service aircraft with positive feedback.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events due to degraded fuel quantity indication 2) Reduction of the number of unscheduled and unjustified removals of FQIC (not taken into account for the cost/benefit analysis)


Maintenance economics assumptions: Spare price: N/A Repair costs: N/A Test cost: N/A Typical NFF rate: N/A



SB 28-1143, TFU 28.42.00.039

A318_A319_A320_A321 TSM 28.42.00.810.873

A318_A319_A320_A321 MMEL 28-40-06, FCOM 3.04.28





OI Rate reduction: 90% MTBUR increase: N/A Weight impact: 0 kg




Improved check-valve in HP/PTU manifold

RECO-SA-29-01


Engine: ALL ATA 4D: 2911 & 2913 & 2923 & 2924 System: HP/PTU Check Valve

Affected P/N: ZCV66, ZCV67 Supplier: CIRCOR



Background: Some operators have reported cases of hydraulic leakage at check valves of the PTU manifold / HP main manifold with PN ZCV66 and ZCV67. Such leaks may potentially lead to HYD G(Y/B) RSVR LO LVL or HYD G(Y/B) RSVR LO AIR PR or HYD G(Y) RSVR OVHT ECAM warning and to hydraulic system loss (green or yellow). Investigations have shown that these leakages were caused by a missing retainer ring, leading to a loosening of the check valve cap and a damage of the O-ring seal subsequently.

Airbus recommendation: SB 29-1107 introduces improved check valves PN ZCV66-1 and PN ZCV67-1 with a new cap. These check valves have been introduced in production for MSN > 1000 and SB 29-1107, issued in 2003, has already been embodied on 160 aircraft with positive feedback.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events due to hydraulic leaks at HP / PTU manifold level and so reduction of associated costs 2) Reduction of the probability to loose the hydraulic system and so reduction of associated costs (filling of the hydraulic system with new fluid, EDP replacement if the operational check of the pump has failed, aircraft towing if the lost hydraulic system is the green one) 3) Improvement of the reliability of check valves and so maintenance cost saving (not taken into account for the cost/benefit analysis)



Investment for recommendation: Labour on-A/C: 15 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 5 Kits per A/C Kit price: 100 $ per Kit Other investment: None


SB 29-1107, SB 29-1109




Modified elbow union

RECO-SA-29-02


Engine: ALL ATA 4D: 2911 & 2913 System: Elbow union

Affected P/N: MS21907D10 Supplier: AIRBUS OPERATIONS SAS



Background: Some operators have reported cases of hydraulic leakage in tail area, close to bulkhead. These leakages, caused by cracked elbow union in the green and yellow return lines, are generally found on ground during aircraft check, leading to long delays or cancellations.

Airbus recommendation: SB 29-1110 replaces the aluminium elbow union by a reinforced elbow union made out of steel. Based on in-service reported events, the majority of the hydraulic leakages have been experienced on aircraft with MSN higher than MSN 1100, so that Airbus does not consider elbow replacements as necessary on aircraft below MSN 1100. This modification has been introduced in production for MSN > 1950 and SB 29-1110, issued in 2004, has already been embodied on about 280 in-service aircraft with positive feedback.





Benefit of the recommendation: Reduction of the number of Operational Interruptions events due to hydraulic leaks in section 19 and so reduction of associated costs





SB 29-1110, TFU 29.00.00.033, SIL 29-063




Preventive replacement of Y PTU manifold

RECO-SA-29-03


Engine: ALL ATA 4D: 2913 System: Yellow PTU Manifold

Affected P/N: D290701790# Supplier: AIRBUS


Background: Some operators have reported cases of heavy hydraulic leakage from the Yellow Power Transfer Unit (PTU) Manifold, generally resulting in long delays or cancellations. These events are due to a fatigue crack of the PTU Manifold housing, that typically occurs after 15000 FC. This reliability issue is known to be one of the top drivers of hydraulic leakage for aircraft having a MSN < 972. The Yellow PTU Manifold is more impacted by this fatigue phenomenon because it is subject to additional cycles due to the operation of the cargo doors.

Airbus recommendation: Airbus recommends operators still equipped with PTU Manifold P/N D2907019, to perform a preventive replacement of the Yellow PTU Manifold - FIN 3013 GM - (by the same P/N) before 15000 FC. This preventive maintenance strategy has already been applied by several operators with good results. Alternatively, operators may choose to embody SB 29-1113, which requires the installation of an improved PTU Manifold P/N 1556A9900-01 (post-mod. 27490) with enhanced fatigue endurance properties.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions caused by hydraulic leakage of the Yellow PTU Manifold 2) Reduction of the probability of the Yellow Hydraulic System loss and associated costs of restoration 3) Savings estimated around 22% in terms of Yellow PTU Manifold associated global costs. The preventive maintenance strategy introduces Scheduled Maintenance associated costs, but significantly decreases the costs associated with Unscheduled Maintenance, Operational Interruptions and Yellow Hydraulic System loss.



Investment for recommendation: Labour on-A/C: 10 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 1 Y PTU Manifold per A/C Kit price: 2400 $ per PTU Manifold Other investment: None


SB 29-1113, SIL 29-080, SIL 29-063




Preventive replacement of Y HP manifold

RECO-SA-29-04


Engine: ALL ATA 4D: 2913 System: Yellow HP Manifold

Affected P/N: D29070185# Supplier: AIRBUS


Background: Some operators have reported cases of heavy hydraulic leakage from the Yellow High Pressure (HP) Manifold, generally resulting in long delays or cancellations. These events are due to a fatigue crack of the HP Manifold housing, that typically occurs after 20000 FC. This reliability issue is known to be one of the top drivers of hydraulic leakage for aircraft having a MSN < 972. The Yellow HP Manifold is more impacted by this fatigue phenomenon because it is subject to additional cycles due to the operation of the cargo doors.

Airbus recommendation: Airbus recommends operators still equipped with HP Manifold P/N D29070185 series, to perform a preventive replacement of the Yellow HP Manifold - FIN 3011 GM - (by the same P/N) before 20000 FC. This preventive maintenance strategy has already been applied by several operators with good results. Alternatively, operators may choose to install manifold P/N 1553A0000-01 (post-mod. 27490) with enhanced fatigue endurance properties.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions caused by hydraulic leakage of the Yellow HP Manifold 2) Reduction of the probability of the Yellow Hydraulic System loss and associated costs of restoration 3) Savings estimated around 15% in terms of Yellow HP Manifold associated global costs. The preventive maintenance strategy introduces Scheduled Maintenance associated costs, but significantly decreases the costs associated with Unscheduled Maintenance, Operational Interruptions and Yellow Hydraulic System loss.



Investment for recommendation: Labour on-A/C: 7.5 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 1 Y HP Manifold per A/C Kit price: 5450 $ per HP Manifold Other investment: None


SIL 29-080, SIL 29-063




Upgrade of Eaton EDP

RECO-SA-29-05


Engine: ALL ATA 4D: 2911 & 2913 System: Engine Driven Pump (EDP)

Affected P/N: 887673 Supplier: VICKERS



Background: Some operators, equipped with Eaton EDP, have reported cases of hydraulic leakages at EDP level, and more precisely at the parting line interface between the adapter and the housing of the hydraulic pump. Such reliability issue is known to be one of the top drivers of hydraulic leak at fleet level. These EDP leaks are generally discovered on ground during aircraft check (leading to long delays or cancellations), but can also be detected in flight, through ECAM warning and loss of the hydraulic system (yellow or green).

Airbus recommendation: SB 29-1123 / VSB 887673-29-06 introduces a modified hydraulic pump with the new PN 3031863-001 (also called PV3-240-10D). This modification has been introduced in production for MSN > 3000 and SB 29-1123, issued in 2005, has already been embodied on more than 1000 in-service aircraft with positive feedback. Note: the cost/benefit analysis presented here corresponds to the EMP upgraded on attrition. The additionnal cost of this upgrade is the difference between the repair price including the embodiment of this SB and the typical repair price.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions events due to hydraulic leaks at EDP level 2) Reduction of the probability to loose the hydraulic system and so reduction of associated costs (filling of the hydraulic system with new fluid, aircraft towing if the lost hydraulic system is the green one...) 3) Improvement of the reliability of the EDP (higher MTBUR and MTBF)


Maintenance economics assumptions: Spare price: 31417 $ Repair costs: N/A Test cost: N/A Typical NFF rate: 5%

Investment for recommendation: Labour on-A/C: 14.5 MH per A/C Labour off-A/C: N/A Number of kits: 2 Kits per A/C Kit price: N/A Other investment: 2666 $ per A/C


SB 29-1123, TFU 29.10.00.026, VSB 887673-29-06




Alleviate fluid leak from manifold

RECO-SA-29-06


Engine: ALL ATA 4D: 2913 System: Plug for alternate brake manifold

Affected P/N: AN814-6JL Supplier: AIRBUS



Background: Some operators have reported that a hydraulic leak from a blanking plug and bleeder on a hydraulic manifold assembly at the Over Wing Panel (OWP) has been detected. Continual loss of hydraulic fluid from the blanking plug and bleeder could lead to a total loss of Yellow System Hydraulics.

Airbus recommendation: This Service Bulletin details instructions to install a new manifold blanking plug and bleeder and fixing bolt with holes for wire locking for aircraft that are post modification No 26925P4576. Accomplishment of this Service Bulletin will alleviate potential hydraulic fluid leakage from the manifold of the Yellow System Hydraulics.


Last update: 17 Oct 2011



Benefit of the recommendation: 1) No more Operational Interruptions linked to the blanking plug and bleeder of the hydraulic manifold assembly at the Over Wing Panel (OWP). 2) Yellow hydraulic liquid savings



Investment for recommendation: Labour on-A/C: 6 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 2 Kits per A/C Kit price: 82.2 $ per Kit Other investment: None


SB 29-1142


RECO-SA-29-06 Last update: 17 Oct 2011



OI Rate reduction: 100% MTBUR increase: infinite Weight impact: 0 kg




Power Transfer Unit leakage reduction

RECO-SA-29-07

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: MSN with MOD 22489 or MOD 30627

Engine: ALL ATA 4D: 2913 System: PTU

Affected P/N: 4101002-9, 4101002-11 Supplier: TRIUMPH GROUP INC



Background: For both the 4101002-9 and -11 configuration PTU's, the seal assemblies installed on the inlet transfer tubes between the variable port housing and manifold valve housing have experienced fretting damage, which creates an external leak path. Existing inlet transfer tube seal assemblies have experienced elastomer nibbling. The existing aluminum grounding lug could be easily damaged during handling. For the -11 configuration PTU only, some control piston guides have lost torque during operation, allowing for the extrusion of the seal assembly. The resulting internal leak path prevents proper compensator control leading to unstable system pressures.

Airbus recommendation: Airbus recommends operators still equipped with Power Transfer Units 4101002-9 series 6 or 7, or with Power Transfer Units -11 series 2 or 3 to perform Triumph Actuation Systems SB 4101002-29-00038 on worn units. Indeed, reliability improvements (leakage reduction) were noted on upgraded Power Transfer Units In Service. Note: - SB applicable to PTU -9 series 6 & 7 OR PTU -9 serie 5 with SB 4101002-29-00037 concurrent requirement - SB applicable to PTU -11 series 2 & 3 OR PTU -11 serie 1 with SB 4101002-29-00037 concurrent requirement - this economic assessment has been considered on attrition.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions linked to the Power Transfer Unit hydraulic leaks 2) Improvement of PTU reliability (higher MTBUR and MTBF) and so reduction of associated maintenance costs



Investment for recommendation: Labour on-A/C: None (on attrition) Labour off-A/C: None (on attrition) Number of kits: No kit Kit price: 10000 $ Other investment: None


VSB 4101002-29-00038





OI Rate reduction: 65% MTBUR increase: 65% Weight impact: +0.154 kg




Modification of automatic brake selector valve

RECO-SA-32-01


Engine: ALL ATA 4D: 3242 System: Automatic brake selector valve

Affected P/N: A25461-10#, D2907017021200 Supplier: AIRBUS OPERATIONS SAS



Background: Some operators have experienced cases of hydraulic leak from a connection piece (port E) of the automatic brake selector valve (FIN 2576GM). In fact, such leak are caused by difficulties during assembly and maintenance of this valve, leading to possible damage of the union. Such leaks are generally found on ground during aircraft check, leading to long delays or cancellations, but can also occur in flight with potential loss of the yellow hydraulic system and IFTB / Diversions. This issue affects 790 < MSN < 1900 as: - aircraft with MSN < 790 (pre mod 26409) were equipped with a different type of system - automatic brake selector valve was suppressed on MSN > 1900

Airbus recommendation: SB 29-1102 replaces the hydraulic connection (port E) of the automatic brake selector valve by a new unit with an enlarged hexagon, in order to facilitate assembly and maintenance. This modification has already been embodied on more than 700 aircraft with good feedback. Note that a 15% discount (taken into account in presented cost/benefit analysis) is offered by Airbus on kit price until end of 2012





Benefit of the recommendation: 1) Facilitation of the assembly and maintenance of the parking brake selector valve 2) Reduction of the number of Operational Interruptions events due to hydraulic leaks at parking brake selector valve level and so reduction of associated maintenance costs 3) Reduction of the probability to loose the yellow hydraulic system and so reduction of associated costs (aircraft cleaning, filling of the hydraulic system with new fluid, EDP replacement if the operational check of the pump has failed)





SB 29-1102




Preventive replacement of MLG door actuator hose

RECO-SA-32-02


Engine: ALL ATA 4D: 3231 System: MLG door actuator hose

Affected P/N: AE2463921G0097 Supplier: EATON


Background: Some operators have reported cases of hydraulic leakage of the Green Hydraulic System due to the rupture of the Main Landing Gear (MLG) door actuator hoses post mod. 32954 standard. These hoses were introduced in service via Airbus SB 32-1260. This issue has significant operational impact in terms of delays and cancellations; a few cases of in-flight turn back have also been reported following the loss of the Green Hydraulic System during flight. Investigations have revealed that the leakage of the MLG hoses is caused by a fatigue fracture of the metallic hose braid which in turn leads to damage of the hose's Teflon tube. It has been observed from in-service experience that leakage may occur starting at 6000 FC, and with an average for the reported events of 8500 FC.

Airbus recommendation: Airbus recommends operators still equipped with MLG Hose configuration post. mod 32954 or having embodied Airbus SB 32-1260 to perform a preventive replacement of the hoses FIN 2765GM, 2766GM, 2767GM, 2768GM GM at 6000 FC. This preventive maintenance strategy requires a relatively low investment, both in terms of labour and material costs, and has already been applied by several operators with good results. Alternatively operators may choose to embody SB 32-1371 which introduces an improved MLG door actuator hose installation with increased fatigue resistance.





Benefit of the recommendation: 1) Reduction of the number of Operational Interruptions caused by MLG door actuator hoses hydraulic leakage 2) Reduction of the probability of the Green Hydraulic System Loss and associated costs of restoration 3) Savings estimated at around 55% in terms of MLG door actuator hoses and associated global costs. The preventive maintenance strategy introduces Scheduled Maintenance associated costs, but significantly decreases the costs associated with Unscheduled Maintenance, Operational Interruptions and Green Hydraulic System loss.


Maintenance economics assumptions: Spare price: 90 $ Repair costs: N/A Test cost: N/A Typical NFF rate: 0%

Investment for recommendation: Labour on-A/C: 10 MH per A/C Labour off-A/C: 1 MH per A/C Number of kits: 4 hoses per A/C Kit price: 90 $ per hose Other investment: None


SB 32-1371, TFU 32.31.35.003




MLG Lock Stay Actuator Hose Upgrade

RECO-SA-32-03


Engine: ALL ATA 4D: 3211 System: Landing Gear

Affected P/N: 201042010, 201042011, 201042029, 201042030, 201042091, 201042092, 201042093, 201042094, 201655144, 201655145, 201655146, 201655147, 201655181, 201655183, 201655184 Supplier: Messier-Dowty

Impact: A/C Availability,Maintenance economics Economic interest: 4y < Payback period < 5y l

Background: Some operators have reported several swivel joint ruptures, due to stress corrosion, of the lock stay actuator-hoses on the Main Landing Gear (MLG). It may lead to the loss of the green hydraulic system. The EATON hoses have a swivel joint manufactured from 440C stainless steel. This material has been identified as having a low resistance to stress corrosion.

Airbus recommendation: Airbus recommends the emodiment of the SB A320-32-1364 and VSB 200-32-300 for A318, A319 and A320 aircrafts and VSB 201-32-52 for A321 aircrafts. It introduces a new flexible hose to help prevent the loss of the green hydraulic system.


Last update: 20 May 2011



Benefit of the recommendation: The new flexible hose from Parker/Stratoflex is manufactured from 15-5PH stainless steel that has a superior resistance to stress corrosion than the EATON flexible hose. Accomplishment of this Service Bulletin will increase the resistance of the swivel joint to stress corrosion and thus reduce the risk of rupture of the swivel joint and subsequent green hydraulic system loss.


Maintenance economics assumptions: Spare price: 1477 $ Repair costs: N/C Test cost: N/A Typical NFF rate: N/A



SB 32-1364, VSB 200-32-300, VSB 201-32-52

A318_A319_A320_A321 AMM 20-21-12, AMM 32-11-22


RECO-SA-32-03 Last update: 20 May 2011


LED Navigation lights

RECO-SA-33-01


Engine: ALL ATA 4D: 3341 System: Exterior lights

Affected P/N: 528-20, 528-30, 528-70, 528-80 Supplier: Honeywell

Impact: A/C Availability,Maintenance economics Economic interest: Payback period < 2y l

Background: Introduction of new LED technology.

Airbus recommendation: In order to achieve a significant lifetime improvement, it was decided to introduce the new Light Emitting Diode (LED) technology for the wingtip Navigation (NAV) lights on A320 aircraft instead of halogen filament lamps. The new LED lights are compatible with A/C fitted with any of the dual or single nav light system.


Last update: 19 May 2011



Benefit of the recommendation: 1) This modification improves reliability and performances from 500 Operating Hours to 20,000 OH (Honeywell specification data), reduces the weight, electrical consumption and operators’ maintenance costs without any changes to the way the navigation lights are operating. 2) The new LED navigation light includes the Near End Of Life (NEOL) indication function (flashing blue LED) that indicates that the LED light module is within the last 950 OH of its useful life ending. Note that instead of MTBUR reliability figure, the service life is considered in this particular case for the economic assessment (pre-mod of 500 OH to 20 000 OH post-mod).



Investment for recommendation: Labour on-A/C: 2.25 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 2 Kits per A/C Kit price: 4560 $ per Kit Other investment: None


SB 33-1062





OI Rate reduction: N/A MTBUR increase: N/A Weight impact: -0.366 kg




Recent solution: Sealing of drain hole to prevent liquid contamination

RECO-SA-33-02

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: MSN > 475

Engine: ALL ATA 4D: 3340 System: RTO Lights

Affected P/N: 4236534, 8000281Y00, 8000306Y00 Supplier: TELEFLEX INC



Background: Some operator have reported, especially during cold weather operations, damage on the transformer and the connector pins of the equipment. It is due to liquid ingress into the runway turn off light.

Airbus recommendation: Airbus recommends operators equipped with Zodiac Runway Turnoff lights to perform the sealing of drain hole to prevent liquid contamination. Note: this economic assessment has been considered on a retrofit basis.





Benefit of the recommendation: The accomplishment of this Service Bulletin will reduce the number of Operational Interruptions linked to the Runway Turnoff lights contamination.



Investment for recommendation: Labour on-A/C: 2 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 6 seals per A/C Kit price: 240 $ per A/C Other investment: None


VSB 4236534-33-003, VSB 8000281-33-002, VSB 8000306-33-002, SIL 33-049, SIL 33-030




Introduce the optional alignement improvement function on ADIRU

RECO-SA-34-01

Program: A320 Family Applicability A/C Type: A318,A319,A320,A321 Applicability msn: MSN having embodied SB 34-1350 or 34-1332

Engine: ALL ATA 4D: 3414 System: ADIRU

Affected P/N: HG2030A#, 465020-0303031# Supplier: Airbus SAS

Impact: Operations Economic interest: Payback period < 2y l

Background: This SB has been issued further to an operator's request. Some In Service Operational events have been reported to Airbus (delays mostly and a few cancellations). Technical data from the fleet In Service shows that the optional alignement improvement function on ADIRUs able to be fitted with is extremely efficient.

Airbus recommendation: Airbus recommends to perform SB 34-1346 which proposes to activate the ADIRU optional improved alignment function on ADIRUs able to receive the kit with no extra costs. This modification has been introduced in production (> MSN 2277) with a proven operational reliability performance. In Service Aircraft performing this SB will as a consequence reach MOD33240 performance. Note: This economic assessment considers Retrofit policy and SB 34-1350 or 34-1332 already implemented.


Last update: 30 Jan 2013



Benefit of the recommendation: Accomplishment of this Service Bulletin will introduce: 1) Shortened alignment time 2) Automatic position initialization 3) Pilot manual initialization checked automatically by the GPS (avoiding erroneous position risk) 4) In Service operational Reliability performance improvement



Investment for recommendation: Labour on-A/C: 3 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 1 kit per A/C Kit price: 227 $ per kit Other investment: None


SB 34-1346




Introduce PTFE seals to avoid air leak

RECO-SA-36-01


Engine: ALL ATA 4D: 3611 & 3622 & 2152 System: Seals for Bleed Air System

Affected P/N: 600#, 630#, 460DC#, 9093A000#, NSA8206#, ABS0737-72, ABS06#, NSA0854-72# Supplier: LIEBHERR AEROSPACE GMBH



Background: Some operators have reported cases of air leak with the following ECAM warnings: - AIR R (L) WING LEAK - AIR ENG 1 (2) BLEED LEAK - AIR APU BLEED LEAK leading to long (as trouble-shooting is known to be complex) delays, cancellations and even few in-flight interruptions. Experience has shown that the seals made of silicon could lose their sealing qualities after some time in service, which could explain air leakages in various areas of the aircraft (e.g. pipe between ACM and heat exchanger, pipe in the pylon, pipe in the leading edge...).

Airbus recommendation: SB 21-1165 (for several ATA 21/36 sub-systems), 21-1153 (for pack system), 36-1043 (for bleed system except wing area) and 36-1050 (for wing area of the bleed system) allow to replace silicon seals by PTFE seals (PN ABS1040; ABS5800), which have no life limit. These modifications has been introduced in production. Note that, as the number of man-hours to change the seal is relatively important (around 100 Man-Hours per aircraft for the four SB), it is recommended to embody these modifications at next MPD opportunity (Tasks 215200-07-1 & 361100-05-1 to replace seals). Present analysis considers this embodiment assumption. Note: Airbus recommends also operators to consult SIL 36-036 revision 8 which provides a synthesis about recommended bleed duct seals and target replacement locations.





Benefit of the recommendation: Accomplishment of those Service Bulletins will lead to: 1) Reduction of the risk of air leakage, thanks to better reliability of the seals 2) Cancellation (as PTFE seals have no life-limit) of MPD tasks 215200-07-1, 361100-05-1 (and leak checks 361100-06-1, 361100-07-1) corresponding to the removal and replacement of seals for air conditioning and bleed air systems and thus maintenance cost savings



Investment for recommendation: Labour on-A/C: 35 MH per A/C (kit 361050B02R00; rest on attrition) Labour off-A/C: 0 MH per A/C Number of kits: 1 global Kit per A/C Kit price: 1370 $ (kit 361050B02R00; rest on attrition) Other investment: None


TFU 36.22.00.009, SB 21-1153, VSB 1802A-21-03, SB 21-1165, SB 36-1043, SB 36-1050, SIL 21-039, SIL 36-036, SIL 36-047

A318_A319_A320_A321 TSM 36-22-00-810-8XX, MPD 21-52-00-07, MPD 36-11-00-05-1, MPD 36-11-00-06-1, MPD 36-11-00-07-1





OI Rate reduction: 80% MTBUR increase: N/A Weight impact: +0.29 kg




Forward and AFT cargo door proximity switches upgrade

RECO-SA-52-01


Engine: ALL ATA 4D: 5230 System: Cargo Door Proximity Sensor

Affected P/N: 8-484-01 Supplier: CRANE AEROSPACE & ELECTRONICS



Background: Several cases of in-flight cargo door warnings have been reported to Airbus. Most of these events led to operational interruption such as aborted take-off or in-flight turn back. The warnings affect both forward and aft cargo doors.

Airbus recommendation: The purpose of this SIL is to inform A319/A320/A321 operators about the possible identified causes for a cargo door warning and provide further recommendations regarding trouble-shooting and preventive actions. Of all the recommendations given, the most intresting from an economics perspective is an upgrade of the cargo door proximity switches (Aft and forward proximity switches: 28WV (34WV) / 30WV (32WV)). Therefore, in the frame of this WISE Main Adopted Solution and Tips, only this part of the SIL has been put forward for promotion.





Benefit of the recommendation: A strong reduction of the number of operational interruptions is the main benefit. The increase in MTBUR is also good although it's influence on economics is limited (because of an already good MTBUR).





SIL 52-055




Introduce improved cockpit door locking control unit

RECO-SA-52-02


Engine: ALL ATA 4D: 5251 System: Pessanger Compartment Fixed Interiior Doors

Affected P/N: AR4709-10, AR4709-103, AR4709-301, AR4709-303, AR4709-11 Supplier: ADAMS RITE AEROSPACE INC



Background: The electrical strikes with thermal protection based on Polymer Positive Temperature Coefficient (PPTC) for the electrical cockpit door locking system require updating to maintain reliability.

Airbus recommendation: Update the software of the respective Cockpit Door Locking Control Unit (CDLCU). FIN 24MQ (SB CONF2) and FIN 28MQ if a 2nd back-up unit is installed (SB CONF1). Note: This economic assessment considers Retrofit policy.





Benefit of the recommendation: The accomplishment of this Service Bulletin will reduce malfunctions and improve the reliability of the electrical cockpit door release system.



Investment for recommendation: Labour on-A/C: 3 MH per A/C Labour off-A/C: 5.75 MH per A/C Number of kits: 1 Kit per A/C Kit price: 1640 $ per Kit Other investment: None


SB 52-1146, VSB AR4709-25-06, TFU 52.51.00.003




Install deflectors on IAE V2500 AFT Pylon Fairing

RECO-SA-54-01


Engine: IAE-V2500 ATA 4D: 5400 System: AFT Pylon Fairing

Affected P/N: D5453030000000, D5453030000100, D5453030000400, D5453030000600 Supplier: AIRBUS



Background: Damaged surface protection and corrosion have been reported on the V2500 engine pylon aft fixed fairing skin panels.

Airbus recommendation: In the case of extensive corrosion, the replacement of the panel or the installation of a doubler may be required. This Service Bulletin details instructions to install deflectors Inconel 625 on the aft lower fairing in order to deviate the engine exhaust gas. Accomplishment of this Service Bulletin will prevent chemical degradation of the paint scheme and further corrosion.


Last update: 19 Apr 2014



Benefit of the recommendation: 1) Outboard aft fixed fairing panels are no longer corroded. 2) Inboard aft fixed fairing panels meet 90% of improvement regarding corrosion issue. An optional cleaning procedure at A-check could help in removing residual exhaust gaz deposit. 3) Scheduled Maintenance workload at C-check will decrease (200 man hours per A/C - estimation confirmed In-Service). Please note that a panel replacement is allowed only once within the aircraft life. As a consequence, if a new V2500 engine pylon aft fixed fairing skin panel needs to be replaced, it would be at great costs.



Investment for recommendation: Labour on-A/C: 14 MH per A/C Labour off-A/C: 0 MH per A/C Number of kits: 2 Kits per A/C Kit price: 1700 $ per Kit Other investment: N/A


SB 54-1020, SB IT 11-0004


RECO-SA-54-01 Last update: 19 Apr 2014



OI Rate reduction: N/A MTBUR increase: N/A Weight impact: 0,722 kg


RECO-SA-54-01 Last update: 19 Apr 2014


Cockpit window preventive maintenance

RECO-SA-56-01


Engine: ALL ATA 4D: 5610 System: Cockpit window

Affected P/N: All cockpit window Supplier: SAINT GOBAIN SULLY or PPG INDUSTRIES INC or GKN ATS


Background: Cockpit window event/issue can have an impact on aircraft dispatch reliability. There is no hard life limit for cockpit window installed on an aircraft. Nevertheless, Airbus would like to highlight that a cockpit window has to be replaced several times during the life of an aircraft. A damage on a cockpit window leading to a replacement can have many different origin: FOD (Foreign Object Damage), ageing, manufacturing defect, moisture ingress, delamination, overheating, electrical trouble, etc.

Airbus recommendation: One of the origins of the in-service issues can be linked with the non-respect of the scheduled maintenance. Airbus scheduled maintenance recommendations are reminded in SIL 56-022: - SIL 56-017: List of the scheduled maintenance given in the MPD. - AMM 56-10: Allowable damage limitations. - AMM 56-11: Distinction between heating film cracking/middle ply cracking/ outer ply cracking. - Vendor CMM: Weather seal condition. Present analysis determines the benefits of performing recommended maintenance against not performing this maintenance.





Benefit of the recommendation: Applying the recommended scheduled maintenance helps limiting the operational impact of cockpit window issue.



Investment for recommendation: Labour on-A/C: 0.3 MH every 3Mo, 0.3 MH every 20Mo, 0.1 MH every 48Mo Labour off-A/C: 0 MH per A/C Number of kits: None Kit price: None Other investment: None


SIL 56-022

A318_A319_A320_A321 AMM 56-10, MPD 561000-01-1, MPD 561000-02-1, MPD 561200-01-1

FOT SE 999.0044/11




Install saddle clamp on CFM56-5B hydraulic line

RECO-SA-70-01


Engine: CFM56-5B ATA 4D: 7000 System: Standard practice - Engine

Affected P/N: C10GT3-12 Supplier: ROHR INC Aerostructures

Impact: Maintenance economics Economic interest: Payback period < 2y l

Background: During check, hydraulic lines clamps failure might be detected.

Airbus recommendation: The Service Bulletin (SB 70-1001) recommends replacing the 9 o’clock "P" clamp (PN C10GT3-12) by 9 o’clock "saddle" clamp (PN NAS1716C12K). This new clamp requests a modification of the channel bracket to include an additional hole (9 o’clock: fan zone, left side). The SB is applicable to CFM56-5B A318/A319/A320/A321 Engine Build-Up Units (EBU) prior to S/N 9921001 (except EBU serial numbers 9915001, 9916001 and 9916002). It corresponds to MSN rank between 0434 and 4006. The economical analysis corresponds to the cost of the SB application and to the removal of the 9 o'clock "P" clamp replacement task during check.





Benefit of the recommendation: No more replacement of the 9 o'clock "P" clamp during check.





SB 70-1001, VSB RA32029-14





OI Rate reduction: N/A MTBUR increase: N/A Weight impact: 0 kg




Recent Solution: Introduction of New HPTACC Valve 329695-5

RECO-SA-75-01


Engine: CFM56-5B ATA 4D: 7521 System: ENGINE AIR - HPT Air Clearance Control Valve

Affected P/N: 329695-4 Supplier: CFM INTL



Background: Large overboard fuel leakage has been reported from HPTACC valves having accumulated between 3000 and 5000 hours. The primary and secondary seals from HPTACC valves on the actuator rod wear out, permiting the leakage into the overboard drain.

Airbus recommendation: CFM recommends to introduce the new improved HPTACC valve P/N 329695-5 when the old one is routed for repair. Note: this economic assessment has been considered on attrition basis.





Benefit of the recommendation: The PTFE slipper seal has fillers that increase resistance to wear.The entire seal is made larger to reduce the impact of tolerances on groove fill and load. The thicker seal provides for more wear capability.



Investment for recommendation: Labour on-A/C: 0 MH on AC Labour off-A/C: 8 MH per AC Number of kits: 2 seals per VLV Kit price: Free of charge Other investment: None


VSB 75-0041




© Airbus S.A.S. All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of AIRBUS. No intellectual property rights are granted by the delivery of this document or the disclosure of

its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS S.A.S. This document and its content shall not be used for any purpose other than that for which it is supplied. The statements

made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supporting grounds for these statements are not shown, AIRBUS S.A.S. will be pleased to explain the basis thereof.

AIRBUS, its logo, A300, A310, A318, A319, A320, A321, A330, A340, A350, A380, A400M are registered trademarks.

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