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Bleed Air Leaks
|Category:||Fire Smoke and Fumes|
An aircraft Bleed Air Leak refers to the uncontrolled loss of bleed air from any part of the aircraft pneumatic system or from the services which utilize bleed air.
Bleed Air Systems
Bleed air, in the context of a turbine engine, refers to compressed air which is taken from within the engine. The point at which the air is bled from the engine varies by engine type but is always tapped from the compressor, at an intermediate stage or just after the last stage, but before the combustors. The use of bleed air is common in jet engine powered aircraft inclusive of turbojet, turbofan and turboprop installations. Bleed air is useful in an aircraft because of two properties: high temperature (typically 200 – 250 degrees C.) and moderate pressure (regulated to approximately 40 PSI exiting the engine pylon). This hot, compressed air can be used in many different ways. Typical uses include engine start, air conditioning and pressurization, engine and airframe de/anti-icing, pressurization of water reservoirs, hydraulic reservoirs and pneumatically powered actuators and, in some cases, it is used as the motive power for pneumatically driven hydraulic pumps.
The uncontrolled loss of bleed air from the pneumatic system or from any of the pneumatically powered services has the potential to cause:
- damage to aircraft wiring
- components to overheat
- damage to aircraft structures
- inflight fire.
Even after the the bleed air leak has been secured using the appropriate ECAM, QRH or AFM procedure, secondary effects of the original fault may occur. Isolating part of the bleed air system will inevitably lead to some degradation in the operation of other aircraft systems such as:
- pneumatically operated control surfaces
- air driven hydraulic pumps
- air conditioning/presurisation systems
- anti-icing systems.
Managing the remainder of the flight with the loss of some or all of these systems will require careful thought and planning. Having a comprehensive knowledge of the pneumatic systems in the aircraft will help in the decision making process. It is essential that the pilots understand what is working and what is not as well as the consequent limitations to the operation.
Some combination of gauges and warning systems is incorporated into the bleed air system to allow the pilots to monitor the normal function of the system and to provide audio and/or visual warning in the event of an overhear or failure. Valves are incorporated into the system to provide the means to automatically or manually isolate parts of the bleed air manifold or individual components in the event of a failure. Some of these defenses include:
- Cockpit Gauges - allow the pilots to monitor bleed air manifold temperature and pressure.
- Overheat Detectors - located in close proximity to bleed air ducts. In the event of a bleed air leak from a ruptured duct, the overheat detector will cause a warning to be generated on the flight deck.
- Bleed Air Shut-off Valves - located at various points in the pneumatic system. In the event of a failure, the shut-off valves can be used to isolate the failed portion of the system.
- Bleed Air Monitoring Systems - detect the loss of pressure caused by a duct failure and generate a warning on the flight deck.
- Fire Wall Bleed Air Shut-off Valves - allow the bleed air from an engine to be isolated from the rest of the aircraft. It is typically closed when the Engine Fire checklist is actioned. Closing the fire wall bleed air valve prevents contamination of the bleed air system by the failed engine and, if the fire warning was caused by a ruptured bleed air duct within the engine, prevents the bleed air system from perpetuating the warning.
The electronic and mechanical defenses, as listed above, are essential to the timely detection and successful containment of a bleed air leak. However, many emergency or abnormal checklists for bleed air faults require some post action analysis to assess whether the action taken has been successful. A critical part of that analysis is a sound understanding, by the pilots, of the pneumatic system and all of its associated functions and components. If the isolation has not been successful, diversion should be initiated and an appropriate balance struck between the time spent on analysis and the need to get the aircraft on the ground as quickly as possible. Even when the isolation is successful, the pilots need to consider how the failure will affect the remainder of the flight. The impact of the loss of all or part of the bleed air system as it affects their particular aircraft type must be examined. Depending upon aircraft type, the analysis might consider items such as:
- Icing - are anti-icing systems affected by the failure? Are there specific AFM limitation to be considered?
- Pressurisation - can the planned altitude be maintained?
- Approach, Landing, Go-Around - does the failure in any way impact upon extension or retraction of landing gear, high lift or deceleration devices?
- A bleed air modulating valve in the right wing anti-ice system fails in the fully open position causing the anti-ice system to overheat. A flight deck warning is generated and the wing anti-ice system is turned off. The aircraft is descended to warmer air where icing is no longer a factor.
- The main pneumatic duct in the left wing suffers a catastrophic failure. The overheat detectors in proximity to the duct generate a warning on the flight deck. Checklist action is followed to close the fire wall bleed air shut-off valve on the left engine and the bleed air shut-off valve for the left wing isolating the leak. The notes and cautions associated with the checklist procedure advise that "icing conditions must be avoided". Moderate mixed icing has been reported by aircraft in descent at the planned destination. The crew elects to divert to their alternate where there is some cloud cover but no icing is forecast or has been reported.
Aircraft wiring is often routed in proximity to pneumatic ducts. A bleed air leak from a compromised duct can melt the insulation of these wires causing short circuits and potentially result in the generation of a number of false warnings. These multiple warnings may mask the actual failure. If the bleed air leak is allowed to persist, heat damage to the airframe structure or a fire is possible.
Accidents and Incidents
The following events involved problems with the bleed air system and/or bleed air leaks:
- A319, en-route, Free State Province South Africa, 2008 (On 7 September 2008 a South African Airways Airbus A319 en route from Cape Town to Johannesburg at FL370 received an ECAM warning of the failure of the No 1 engine bleed system. The crew then closed the No. 1 engine bleed with the applicable press button on the overhead panel. The cabin altitude started to increase dramatically and the cockpit crew advised ATC of the pressurisation problem and requested an emergency descent to a lower level. During the emergency descent to 11000 ft amsl, the cabin altitude warning sounded at 33000ft and the flight crew activated the cabin oxygen masks. The APU was started and pressurisation was re-established at 15000ft amsl. The crew completed the flight to the planned destination without any further event. The crew and passengers sustained no injuries and no damage was caused to the aircraft.)
- A320, en-route, north of Öland Sweden, 2011 (On 5 March 2011, a Finnair Airbus A320 was westbound in the cruise in southern Swedish airspace after despatch with Engine 1 bleed air system inoperative when the Engine 2 bleed air system failed and an emergency descent was necessary. The Investigation found that the Engine 2 system had shut down due to overheating and that access to proactive and reactive procedures related to operations with only a single bleed air system available were deficient. The crew failure to make use of APU air to help sustain cabin pressurisation during flight completion was noted.)
- A332, Karachi Pakistan, 2014 (On 4 October 2014, the fracture of a hydraulic hose during an A330-200 pushback at night at Karachi was followed by dense fumes in the form of hydraulic fluid mist filling the aircraft cabin and flight deck. After some delay, during which a delay in isolating the APU air bleed exacerbated the ingress of fumes, the aircraft was towed back onto stand and an emergency evacuation completed. During the return to stand, a PBE unit malfunctioned and caught fire when one of the cabin crew attempted to use it which prevented use of the exit adjacent to it for evacuation.)
- A332, vicinity Perth Australia, 2014 (On 9 June 2014, a 'burning odour' of undetermined origin became evident in the rear galley of an Airbus A330 as soon as the aircraft powered up for take off. Initially, it was dismissed as not uncommon and likely to soon dissipate, but it continued and affected cabin crew were unable to continue their normal duties and received oxygen to assist recovery. En route diversion was considered but flight completion chosen. It was found that the rear pressure bulkhead insulation had not been correctly refitted following maintenance and had collapsed into and came into contact with APU bleed air duct.)
- A333, en-route, south of Moscow Russia, 2010 (On 22 December 2010, a Finnair Airbus A330-300 inbound to Helsinki and cruising in very cold air at an altitude of 11,600 metres lost cabin pressurisation in cruise flight and completed an emergency descent before continuing the originally intended flight at a lower level. The subsequent Investigation was carried out together with that into a similar occurrence to another Finnair A330 which had occurred 11 days earlier. It was found that in both incidents, both engine bleed air systems had failed to function normally because of a design fault which had allowed water within their pressure transducers to freeze.)
- B735, en-route, SE of Kushimoto Wakayama Japan, 2006 (On 5 July 2006, during daytime, a Boeing 737-500, operated by Air Nippon Co., Ltd. took off from Fukuoka Airport as All Nippon Airways scheduled flight 2142. At about 08:10, while flying at 37,000 ft approximately 60 nm southeast of Kushimoto VORTAC, a cabin depressurization warning was displayed and the oxygen masks in the cabin were automatically deployed. The aircraft made an emergency descent and, at 09:09, landed on Chubu International Airport.)
- B737 en-route, Glen Innes NSW Australia, 2007 (On 17 November 2007 a Boeing 737-700 made an emergency descent after the air conditioning and pressurisation system failed in the climb out of Coolangatta at FL318 due to loss of all bleed air. A diversion to Brisbane followed. The Investigation found that the first bleed supply had failed at low speed on take off but that continued take off had been continued contrary to SOP. It was also found that the actions taken by the crew in response to the fault after completing the take off had also been also contrary to those prescribed.)
- B738, Glasgow UK, 2012 (On 19 October 2012, a Jet2-operated Boeing 737-800 departing Glasgow made a high speed rejected take off when a strange smell became apparent in the flight deck and the senior cabin crew reported what appeared to be smoke in the cabin. The subsequent emergency evacuation resulted in one serious passenger injury. The Investigation was unable to conclusively identify a cause of the smoke and the also- detected burning smells but excess moisture in the air conditioning system was considered likely to have been a factor and the Operator subsequently made changes to its maintenance procedures.)
- B752, en-route, North Sea, 2006 (On 22 October 2006 a blue haze was observed in the passenger cabin of a Boeing 757-200, operated by Thomsonfly, shortly after reaching cruise altitude on a scheduled passenger flight from Newcastle to Larnaca. A precautionary diversion was made to London Stansted, where an emergency evacuation was carried out successfully.)
- An analysis of fumes and smoke events in Australian aviation ATSB (Australia), 2014