Boeing Co 747-338, VH-EBT

Summary

The Boeing 747 departed Cairns with a load sheet showing its take-off weight as 316,500 kg and its landing weight at Narita as 241,500 kg. During descent, company staff at Narita advised the crew to amend the aircraft's landing weight to 243,200 kg, the difference being due to 1,850 kg of cargo stowed in position 11 that had been recorded incorrectly.

Company staff identified a unit load device (ULD) weighing 950 kg, which had been packed in Sydney and transported to Cairns. At Cairns, the weight of the ULD was wrongly recorded as 1,850 kg. The reason for the error was not established, but it was possible that loading staff at Cairns may have pulled an old weight tag from the ULD tag pouch and noted the weight written on it.

The incorrect weight of 1,850 kg was then transcribed as 185 kg onto a `deadweight statement' (baggage and cargo weight) which was sent to Load Control three hours before scheduled departure. Coincidentally, 185 kg was the weight of an empty ULD. The load controller used 185 kg as the ULD weight in preparing the Load Instruction Report (LIR) for the Cairns loading staff, but they did not detect the discrepancy between the ULD tag weight (1,850 kg) and the LIR weight (185 kg). As the load controller had used 185 kg in the load calculations, both the Provisional Load sheet and the Final Load sheet understated the aircraft gross weight.

While the aircraft was in transit, company staff at Narita queried the ULD weight with the load controller, who then contacted the Cairns freight staff. Three hours before the aircraft was due to land, the freight staff sent a revised deadweight statement to the load controller, showing the ULD weight as 1,850 kg. The load controller then recalculated the load weight and passed this to the company staff at Narita, who in turn advised the crew to increase the aircraft landing weight by 1,700 kg. As the actual weight of the ULD was 950 kg, the revised landing weight overstated the true landing weight by 750 kg.

Since the occurrence, the company Freight Branch has issued a reminder to freight terminal staff to remove old weight tags from ULDs and has asked the Cairns freight staff to take action to prevent incorrect completion of deadweight statement forms. In addition, the Ramp Training and Safety Co-ordinator at Cairns has issued a notice to loading staff to check all weights on ULD tags against the weights stated on the LIR.

Occurrence summary

Investigation number 200002693
Occurrence date 11/06/2000
Location Cairns, Aero.
State Queensland
Report release date 01/08/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Loading related
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer The Boeing Company
Model 747
Registration VH-EBT
Serial number 23222
Sector Jet
Operation type Air Transport High Capacity
Departure point Cairns, QLD
Destination Narita, JAPAN
Damage Nil

Cessna A185F, VH-TLO

Summary

The Cessna 185 (C185) aircraft had returned and landed at the departure aerodrome after completing a charter flight of approximately 90 minutes duration. The pilot reported that following a normal landing and after the tail wheel had been lowered to the runway, the aircraft nose commenced to yaw to the right. The pilot estimated that the aircraft was travelling at about 20 kts and despite applying full rudder and the use of differential braking it was not possible to regain directional control and the aircraft ground-looped. The left main gear-leg collapsed and the outboard portion of the left wing was substantially damaged when it struck the surface of the runway. The propeller also was damaged on contact with the runway. The pilot and three passengers were not injured and vacated the aircraft without assistance.

The pilot had been endorsed on the aircraft approximately one week before the accident. Although he had significant experience operating other tail-wheel equipped aircraft, he had logged only 18 hours on the C185. The majority of that experience had been accumulated while ferrying the aircraft from Moorabbin to Broome.

Following the accident, archived data from the Broome automatic weather station was retrieved from the Bureau of Meteorology. The data indicated that at the time of the accident a southerly wind was blowing with wind gusts recorded up to 11 kts. Analysis of the data indicated that the pilot could have encountered a right crosswind of up to 10 kts during the landing. That was within the aircraft manufacturer's demonstrated crosswind limit of 15 kts.

The aircraft centre of gravity was calculated to have been within published limits. However, it was close to the aft limit, thereby making directional control more difficult in the gusting crosswind conditions.

The weather conditions prevailing at the time of the accident would have made the aircraft more difficult to control, especially during the later stages of the landing roll as the aircraft slowed down and the rudder became less effective. Directional control at lower speeds becomes increasingly dependent on tail-wheel steering and the use of differential braking. The directional instability would have been further exacerbated with any sudden increase in crosswind component due to the gusty crosswind conditions.

Occurrence summary

Investigation number 200002700
Occurrence date 27/06/2000
Location Broome, Aero.
State Western Australia
Report release date 27/09/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Loss of control
Occurrence class Accident
Highest injury level None

Aircraft details

Manufacturer Cessna Aircraft Company
Model 185
Registration VH-TLO
Serial number 18503658
Sector Piston
Operation type Charter
Departure point Broome, WA
Destination Broome, WA
Damage Substantial

Saab SF-340A, VH-KEQ

Safety Action

Local safety action

The operator reported that following the incident, they reviewed their SF340 simulator training procedures highlighting the requirement for closer monitoring of propeller RPM indications. Changes were also made to their SF340 Flight Crew Operations Manual, and the incident was featured in the company's Safety Promotion Newsletter.

Summary

The SAAB SF 340's departure from Wagga airport had been delayed for 4.5 hours due to ground fog. As the aircraft taxied for departure, the crew completed the pre-flight checks. Incorporated within these checks was the requirement for a "first flight of day" propeller governor overspeed test. As it was the aircraft's first flight for the day, the check was carried out.

Following take-off, and shortly after landing gear retraction, with the Constant Torque On Take-off system engaged, the crew noted that the right engine propeller RPM was low; at approximately 1,100 RPM. The left propeller was within the normal operating range at an indicated 1,378 RPM.

As a return to Wagga was unavailable, due to ground fog, the crew contacted air traffic control indicating their intention to divert to Albury Airport. An Alert Phase was declared and Albury Emergency Services were on stand-by for the aircraft's arrival.

The crew then carried out the appropriate abnormal checklist actions for a propeller underspeed, shutting down the right engine just prior to the top of descent. During that time, the crew briefed the cabin attendant on the engine problem, before informing the passengers of the situation via the aircraft's public address system. Following an uneventful single engine approach and landing, the Alert Phase was cancelled.

An investigation by the aircraft's operator, included analysis of the aircraft's flight data recorder readout. The analysis indicated that during taxi the right propeller RPM had reduced from 1,040 to 990. That RPM drop was consistent with the crew carrying out the propeller governor overspeed test. However, unlike the left propeller, the right propeller RPM had not fully recovered at the completion of the check.

Both crew members reported that on completion of the propeller overspeed governor checks, once they had observed the propeller indications returning towards normal, their attention was diverted towards other checks. The crew also indicated that during the take-off they did not normally check the propeller RPM indications, instead monitoring the engine parameters of "torque and inter-turbine temperature". Consequently, the low right-propeller RPM had not been initially detected.

During the take-off roll the crew noted that the right engine torque had lagged behind the left. That was considered to be due to not having the right power lever pushed far enough forward, as the Constant Torque On Take-off system only engages after advancing the power lever past 64 degrees. The crew had then pushed the right power lever further forward in order to equalise both engine torque indications.

After the flight, the operator completed a thorough maintenance check of the right engine and propeller systems. No unserviceabilities were found during that check. Following consultation with the aircraft's engine manufacturer the aircraft was returned to service. The problem did not re-occur.

The operator attempted to replicate the problem in their SAAB 340 flight simulator. That attempt was observed by a representative from the Civil Aviation Safety Authority. After thorough investigation, the operator was unable to repeat the occurrence.

Occurrence summary

Investigation number 200002644
Occurrence date 10/06/2000
Location Wagga Wagga, Aero.
State New South Wales
Report release date 20/12/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Propeller/rotor malfunction
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer Saab Aircraft Co.
Model 340
Registration VH-KEQ
Serial number 340A-011
Sector Turboprop
Operation type Air Transport Low Capacity
Departure point Wagga Wagga, NSW
Destination Melbourne, VIC
Damage Nil

British Aerospace Plc BAe 146-200A, VH-JJX

Safety Action

The operator replaced both right wing aileron trim cables and chains on the aircraft. As a result of this incident the operator carried out an aileron trim cable inspection of its fleet of twelve BAe146 aircraft. Notable corrosion in the rib 14 pulley area was found in both wings of another aircraft. All aileron trim (wing loop) cables of that aircraft were subsequently replaced.

On 27 July 2000 the operator issued an Engineering Release (ER) that required a more thorough inspection of aileron trim cables for corrosion at each C check. The inspection aimed to ensure that any hidden corrosion at pulley locations did not pass through major checks undetected. Inspection highlighted the need to operate flight controls over their complete range of movement allowing inspection of cable obscured by pulleys. The ER also called for cleaning and lubrication of cables, paying particular attention to the lengths of cable passing through the pulley bank.

Summary

During climb-out from Darwin, passengers on the British Aerospace Bae146 advised the cabin manager that about 3 metres of cable was trailing from the trailing edge of the right wing. After the first officer had conducted a visual inspection, the crew advised Darwin ATC that they had a problem and required a return for landing. Fuel was burnt off to achieve maximum landing weight. Controllability checks found no handling problems with the aircraft, which was landed safely.

An inspection identified the trailing cable as an aileron trim cable (upper). Failure of the cable had occurred at the outboard pulley located at wing rib 14. The cable was found to have failed as a result of significant corrosion between the pulley bank and the wing rear spar. Corrosion was also present on the failed cable coinciding with the location of the inboard pulley at wing rib 14. No corrosion was found on the left-wing aileron trim cables. Previous inspection of the area was reportedly carried out during a 6C check in May 1999, 3,495 flight hours earlier.

The aileron trim cable material was zinc coated carbon steel (MIL-W-83420, Type 1, Composition A). Stainless steel trim cables were not available from the aircraft manufacturer.

No other reported failures of BAe146 aileron trim cables were found in a search of the Civil Aviation Safety Authority major defect and ATSB incident databases. The operator advised that corroded cables and seized pulleys at that location had been recorded on various BAe146 aircraft since 1992. The aircraft maintenance manual required special attention for corrosion during inspection of cable sections in contact with pulleys.

Occurrence summary

Investigation number 200002622
Occurrence date 22/06/2000
Location 28 km E Darwin, Aero.
State Northern Territory
Report release date 25/05/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Flight control systems
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer British Aerospace
Model BAe 146
Registration VH-JJX
Serial number E2127
Sector Jet
Operation type Air Transport High Capacity
Departure point Darwin, NT
Destination Gove, NT
Damage Minor

Fairchild SA227-DC, VH-ANY

Safety Action

Local safety action

The Darwin Australian Defence Air Traffic System software was upgraded on 14 June 2000 to allow a "second look" access to controllers at each console.

Significant Factors

  1. The Brisbane sector controller did not ensure separation between two aircraft that were on his radio frequency and in airspace that was under his jurisdiction.
  2. The Brisbane sector controller did not provide a "no restrictions" hand-off to the Darwin controller.
  3. The Darwin approach trainee authorised a level change without ensuring separation.
  4. The introduction of a software change that would have enabled the Darwin trainee to view the relative positions of the aircraft, was scheduled for implementation the day after the occurrence.

Factual Information

History of the flights

A Metroliner had departed Darwin on a flight to Dili, East Timor. The crew had climbed to flight level (FL) 180 and were maintaining that altitude. They had been under the control of Darwin Air Traffic Control for the first 60 NM and had transferred to Brisbane Control in accordance with normal procedures. They had established two-way radio communication with Brisbane sector control.

The Airbus A330 (A330) was on a flight from Kuala Lumpur, Malaysia to Darwin and the crew had commenced descent to FL210 in accordance with instructions from Brisbane Control.

When the A330 was approximately 97 NM from Darwin, the crew requested further descent. The Brisbane controller immediately activated the intercom line to Darwin Approach and informed the Darwin controller of the position of the A330. The Metroliner was 81 NM from Darwin at that time.

The Darwin controller, who was under training, only had access to a 60 NM radius display screen. He had already handed off the outbound Metroliner to the Brisbane controller and authorised descent to FL 120 for the A330 in the belief that the Brisbane controller would separate the two aircraft. The trainee was not immediately aware of the relative positions of the aircraft as the conflict was not shown on his display.

The training officer immediately realised that separation had not been assured by the coordination interaction and looked to one side where he had set up a second screen display on an adjacent console. He had selected a greater range scale on the console, that showed the position of the two aircraft. As he was briefing the trainee on urgent action to remedy the situation, the crew of the A330 reported on the Darwin Approach radio frequency that they were on descent to FL120. While that radio exchange was occurring, the trainee had selected the longer range scale on his console and the display had now appeared on his screen. It showed that the aircraft were approximately 9 NM apart in a nose-to-nose conflict. He immediately issued an amended instruction to the crew of the A330 to maintain FL190. The crew was able to carry out that instruction before the vertical separation standard of 1,000 ft was infringed.

A few moments later the captain of the Metroliner saw the A330 pass immediately overhead. He reported that there was insufficient time to draw the co-pilots attention to the aircraft before it passed. He was of the opinion that there would have been insufficient time to initiate an evasive manoeuvre if it had been required.

The A330 crew saw the Metroliner but took no action as the aircraft were obviously going to miss. The traffic alert and collision-avoidance system was serviceable but did not activate.

Radar analysis indicated that the aircraft passed with approximately 1,300 ft vertical separation but with no horizontal difference.

At the Brisbane sector console, the short term conflict alert activated approximately 20 seconds prior to the time of passing. The controller immediately checked the radar display and found that a separation standard was being applied by Darwin approach control and took no further action.

Darwin approach control

The Darwin approach unit controlled airspace to 60 NM, in the north-west quadrant, up to and including FL200. At the time of the coordination from Brisbane sector, both aircraft were outside those parameters and, therefore, not subject to direct control by Darwin.

Local procedures required that arriving aircraft be assigned no lower than FL210 by Brisbane Control. Therefore Darwin Control was required to approve any further descent despite the aircraft being in Brisbane's airspace. When the Brisbane controller coordinated the position of the A330, the trainee read into the tone of the voice that a request was being made for further descent even though the actual words used did not state that intent. The trainee was not immediately aware of the confliction because it was outside his area of jurisdiction and not within the range of his selected display. The trainee also had the impression that, as the aircraft were in Brisbane's airspace, he was only approving descent in Darwin's airspace and that the Brisbane controller was still responsible for the separation of the aircraft.

Radar hand-off was the subject of a specific instruction in the Manual of Air Traffic Services Supplement (MATS Supp) which stated: "Aircraft handed off by radar between Darwin ATC and Brisbane/Tindall Sectors shall be subject to `no restrictions' unless otherwise advised."

The adjacent console was not in use and had been positioned so that the controllers could view the display screen, albeit at a distance of 2 - 3 m. The range was selected at a longer distance than the 60 NM in use at their primary screen. That selection meant that the position of the aircraft could be seen but the details in the information blocks could not be read. A software change was scheduled for introduction the next day that would have allowed the trainee to view the longer range (second look) on his own console rather than having to look across to the second screen.

When the trainee had approved descent for the A330, the Brisbane controller de-selected the intercom line before the training officer could intervene to cancel the approval. The training officer immediately briefed the trainee to maintain the A330 at FL190 because he expected the crew to change frequency quickly as, in his experience, they normally did. The training officer was prepared to go back to Brisbane via the intercom line, but the broadcast by the crew of the A330 made that option redundant.

Brisbane sector control

The controller coordinated the position of the A330 with Darwin Control and expected an instruction from Darwin regarding descent. When they issued approval for FL120 he assumed that they were separating the aircraft, even though he thought that he may not have looked at his display at the time of carrying out the coordination and may have, momentarily, overlooked the actual position of the Metroliner. He then issued the descent instruction and told the crew to change radio frequency to Darwin Approach.

Shortly after, the short term conflict alert activated and the controller immediately checked the display. He saw that there was no infringement of separation standards and took no further action.

The controller had been rated on The Australian Advanced Air Traffic System (TAAATS) for 4 months but had just returned from a month's leave. He received 2 days familiarisation and had performed 4 active shifts prior to the occurrence. He stated that he was well rested and that the workload was moderate. However, he said that he was a bit `rusty' and that the 2 days familiarisation was a bare minimum for adequacy.

Short term conflict alert

The activation of the alert was to warn the controller that the aircraft were predicted to pass within 600 ft and 4.1 NM. Analysis of the performance of the alert indicates that it operated in accordance with the parameters and provided approximately 20 seconds warning of the conflict.

Analysis

Airspace management

The general control technique to ensure separation on this route was for Darwin to assign FL200 (or below) for departures and for Brisbane to only assign FL210 for descent; therefore ensuring the 1,000ft separation standard.

In accordance with MATS Supp, when an aircraft was handed off from one controller to the other, that aircraft shall be subject to "no restrictions" unless otherwise stated. In the case of the A330, the Brisbane controller had not mentioned any restrictions for its descent and had, therefore, incorrectly coordinated the aircraft with Darwin. Darwin Control had correctly coordinated the Metroliner with Brisbane Control and had transferred the crew to the Brisbane controller's radio frequency before that aircraft had left their area of responsibility. As the Metroliner had passed outside 60 NM from Darwin, it was under the control of the Brisbane controller. Had the crew of the A330 been slow with their radio frequency transfer, neither controller would have been able to prevent the A330 descending through the level of the Metroliner.

Darwin approach control

The trainee controller made a decision to allow the A330 further descent based on a belief that the Brisbane controller would separate the aircraft that were in that controller's airspace. However reasonable that belief may have been, the approval left open a possibility for an infringement in separation standards. Phraseologies to ensure separation were available and would have clarified that the descent was subject to the Brisbane controller's separation of the aircraft.

The intended action of the training officer was appropriate and timely, but the broadcast from the crew of the A330 made his plans redundant.

Had the software change that was to be implemented the next day been available at the time, the trainee would have had a better opportunity to see the relative positions of the aircraft and, therefore, observe the developing air traffic situation and take more appropriate action.

Brisbane sector control

When the response from Darwin Control was for descent to FL120, the controller accepted the level and issued descent to that level to the crew of the A330 when the aircraft were approximately 16 NM apart and with a closing speed of approximately 12 NM per minute. Irrespective of the response from Darwin, the Brisbane controller still had responsibility for separation of the aircraft outside the 60 NM arc and the aircraft were obviously going to pass in that controller's airspace. The controller also had both aircraft on his radio frequency and the instruction to the crew of the A330 gave away both separation and radio contact. However, the crew of the A330 made a timely and successful change of frequency to the Darwin controller. Had this transfer taken longer to take place, the only solution would have been for the Brisbane controller to issue emergency instructions to the crew of the Metroliner. As the controller had considered that Darwin were separating the aircraft at the time of issuing the A330 descent, it is unlikely that such action would have been taken in time.

Summary

A Metroliner had departed Darwin on a flight to Dili, East Timor. The crew had climbed to flight level (FL) 180 and were maintaining that altitude. They had been under the control of Darwin Air Traffic Control for the first 60 NM and had transferred to Brisbane Control in accordance with normal procedures. They had established two-way radio communication with Brisbane sector control.

Occurrence summary

Investigation number 200002485
Occurrence date 13/06/2000
Location 167 km NW Darwin, Aero.
State International
Report release date 02/11/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer Fairchild Industries Inc
Model SA227
Registration VH-ANY
Serial number DC-840B
Sector Turboprop
Operation type Air Transport Low Capacity
Departure point Darwin, NT
Destination Dili, East Timor
Damage Nil

Aircraft details

Manufacturer Airbus
Model A330
Registration 9M-MKC
Sector Jet
Operation type Air Transport High Capacity
Departure point Kuala Lumpur, Malaysia
Destination Darwin, NT
Damage Nil

Cessna 172P, VH-THO

Summary

The privately operated Cessna 172 was being used to muster cattle on a station near Halls Creek in Western Australia. One of the station workers said that the pilot reported by radio that he had found some cattle in timber country that he could not move. The worker, who was not aviation qualified, advised the pilot to "bomb them". He meant the pilot should fly low and scare the cattle. About 2 minutes later, he heard a bang and saw a cloud of dust about 500 m to the east, but did not see the accident. The pilot was fatally injured. The ATSB did not conduct an on-site investigation into the accident.

The wreckage trail extended about 22 m from where the aircraft had hit a tree and just 12 m from where it first hit the ground. An inspection of the wreckage revealed no pre-existing mechanical fault that may have contributed to the accident.

The pilot was inexperienced; having a total of just over 400 flying hours, acquired over about 10 years. He had about 330 flying hours in aeroplanes, of which about 125 hours were in command or in command under supervision. Although the pilot finished training for the mustering qualification about 1 month before the accident, at that time he had insufficient in-command flying hours to apply for an approval from the Civil Aviation Safety Authority (CASA). Subsequently, the pilot conducted several flights with the station manager, who was a qualified mustering pilot, to gain sufficient flying hours for the approval. He applied for a mustering approval 8 days before the accident, but the CASA representative advised the pilot that there would be a delay in processing the paperwork and issuing the approval. The CASA representative reported that she also advised him not to conduct mustering until the approval was issued. The station manager reported that the pilot did not tell him of the CASA advice.

According to the station manager, the pilot began flying mustering operations as the pilot in command the day after the documentation was submitted to CASA. The station manager also said he thought that the pilot had received sufficient guidance and training to operate in the conditions on the day without supervision.

The approved pilot who trained the pilot to conduct mustering operations reported that the pilot was an excellent student who seemed eager to please. He also reported that during training, the pilot appeared to be overly concerned about achieving required standards within a certain amount of time. The station manager also reported that the pilot appeared to be very eager, with an unquestioning approach to learning the job.

The weather report indicated that wind conditions at the time were fresh and gusty from the east with a significant wind shear in the lower levels. The wind speed at 2,000 ft above sea level was 22 kts, and at 3,000 ft was 46 kts. The surface wind at the time of the accident was reported to be about 15 kts, but had become blustery and gusting to about 35 kts within about an hour of the accident. Consequently, it is likely that the wind strength and direction were variable and unpredictable at the heights at which the pilot was operating.

In the absence of any associated aircraft mechanical fault, the evidence was consistent with the pilot losing control of the aircraft while manoeuvring at low level in adverse wind conditions. The pilot's eagerness and lack of experience may have influenced him to operate the aircraft in a manner inappropriate for the weather conditions at the time.

Occurrence summary

Investigation number 200002383
Occurrence date 14/06/2000
Location 100 km E Halls Creek, Aero
State Western Australia
Report release date 08/12/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Collision with terrain
Occurrence class Accident
Highest injury level Fatal

Aircraft details

Manufacturer Cessna Aircraft Company
Model 172
Registration VH-THO
Serial number 17275223
Sector Piston
Operation type Private
Departure point Flora Valley Station, WA
Destination Flora Valley Station, WA
Damage Destroyed

British Aerospace Plc BAe 146-300 , VH-NJL

Summary

The co-pilot reported that during the BAe 146 handover, the previous crew stated that the aircraft had an air-conditioning contamination problem and that it appeared to emanate from the No. 2 air-conditioning pack. On entering the aircraft the co-pilot noted that only the No. 2 pack was operating and the ambient air was contaminated. The crew switched off the No. 2 pack until the engines were started and the aircraft had taxied to the runway holding point.

After take-off, the co-pilot reported that he began to feel nauseous and had developed a headache. After discussing the problem with the aircraft captain, he donned an oxygen mask and gradually felt better. During the flight, a flight attendant entered the cockpit and reported a soreness of the head, and that she felt nauseous.

On the return flight, the crew left the No. 2 pack switched off. They reported that the contamination was far less noticeable than the previous flight.

Inspection by the company maintenance personnel did not initially find any evidence of contamination. However, the co-pilot reported that subsequent replacement of the aircraft auxiliary power unit appeared to have rectified the air contamination problem.

Occurrence summary

Investigation number 200002431
Occurrence date 30/04/2000
Location 56 km N Perth, Aero.
State Western Australia
Report release date 20/11/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Air/pressurisation
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer British Aerospace
Model BAe 146
Registration VH-NJL
Serial number E3213
Sector Jet
Operation type Air Transport High Capacity
Departure point Perth, WA
Destination Paraburdoo, WA
Damage Nil

Airbus A320-211, VH-HYX

Safety Action

R20000285

As a result of the investigation the Australian Transport Safety Bureau recommends that Airservices Australia develop risk management protocols that improve its ability to recognise and track controllers' fitness for operational duty.

Significant Factors

  1. The crews were not using the same air traffic control frequency at the same time.
  2. An assessment of the controller's fitness for duty did not include due consideration of the cumulative effects of stress.
  3. The controller was probably unaware of the harmful effect of stress on individual performance.
  4. The management of staff by a number of different managers did not aid Airservices Australia to readily identify the controller's fitness for duty.
  5. The operation of traffic alert and collision avoidance systems and aircraft secondary surveillance radar transponders by the crews were valuable defences for the aviation system.

Analysis

There were opportunities for both crews to be alerted that they were assigned the same level. However, these were missed because:

- the B767 crew had been instructed to monitor the Woomera sector frequency and did not hear the controller approve the A320 crew to climb to FL280,
- the controller's transmission about the A320 interrupted the B767 crew's on-frequency report that would have included their level,
- the controller did not include the assigned level for the opposite direction aircraft in the sighting and passing report transmission to both crews, and
- the presentation of system data reinforced the controller's view that vertical separation had been applied between the aircraft.

High levels of stress can increase the likelihood of individuals failing to complete actions or recognise a situation. For example, stress promotes slips and lapses by narrowing the focus of attention. Slips most often occur when an individual is performing an automated task in familiar surroundings, but is distracted by external events or internal thoughts. A preoccupation with personal problems can divert attentional resources, particularly at times of low workload. Such conditions are ideal for inducing a slip.

The controller's inability to appreciate the use of the wrong level and its relationship with his traffic management plan, and the indicators available to him from the air traffic system was consistent with him being preoccupied. An increased state of stress was probably the prime reason for the lack of concentration or preoccupation by the controller. This then led him to instructing the A320 crew to climb to the wrong level and causing the separation standard to be infringed. This was consistent with the controller's stressful state while under a low workload.

Research literature on occupational stress strongly supports giving priority to person-job fit issues as a strategy to prevent work stress. Also, a change to the work environment has the potential to cause health problems if not managed well. Airservices Australia had not been able to address the controller's concerns about occupational opportunities. Nor were they able to either understand or reduce the controller's increasing reaction to these stressors. The result was an organisational climate that contributed to the controller's stress levels. Concurrently, the controller had significant difficulty adjusting to the changes in vocational circumstances. These organisational and personal factors combined to produce increased stress in the controller.

The impact of stress on the controller's performance was one that needed consideration and action as advised in the CATSOAM. Airservices knew the controller had personal and vocational problems but seemed unable to reduce the individual's occupational discontent. It is probable the change in management staff during the TAAATS transition limited the organisation's ability to recognise the extent of the controller's stress and consequent potential effect on safety. This lack of organisational understanding and the use of various managers, in addressing the issues, may have limited the centre manager's ability to decide on the controller's fitness for duty. Without a full understanding of the controller's situation and current susceptibility to stress related conditions the manager had to assess whether the controller was able to work. The ability to readily access a controller's complete history or the use of a protocol, that ensured vocational and personal details were considered with any commensurate safety risk, would have enabled the manager to make a more informed decision. As it was, the centre manager tried to mitigate the situation by briefing the flight information region manager and the team leader. However, the flight information region manager and the team leader lacked a full understanding of the situation and were less able than the centre manager to assess the controller's fitness for duty.

Had either a more encompassing risk protocol or a better system of monitoring a controller's career been in place it is likely the cumulative stress from the controller's job discontent, the two recent unfavourable briefings and his family problem would have been recognised. If there had been a better understanding of either the controller's situation or the potential risk to safety, the centre manager would have probably removed the controller from duty until a formal evaluation of fitness for duty was done.

Accurate work and rest times were not available to assess the level of fatigue for the controller but it is likely the controller was tired before the occurrence. The controller's overall heightened stress, preoccupation and fatigue made him unlikely to be capable of making a coherent and rational decision about his fitness for operational tasks.

Radio facilities to enable crews under the jurisdiction of the Alice Springs sector to maintain continuous radio communications with that controller would reduce the possibility for similar events.

Summary

A Boeing 767 (B767) was en route from Sydney to Jakarta, Indonesia, on the two-way air route A576 and was estimating overhead Alice Springs at 1255 Central Standard Time at flight level (FL) 280. The crew of an Airbus Industrie A320 (A320) taxiing at Alice Springs had also flight planned via A576, in the opposite direction to the B767, for Sydney. The A320 crew had planned the flight at FL370 but the Alice Springs sector controller, operating from the Melbourne air traffic control centre, intended to issue a clearance of FL270 to the crew. This would have provided the required 1,000 ft vertical separation standard between the A320 and the B767. The A320 departed at 1218 on climb initially to FL200 and the crew contacted the controller at 1225. The controller entered FL270 in the air traffic system but told the crew to climb to FL280. The crew correctly read back FL280.

The estimated time of passing of the two aircraft was 1237. The controller told both crews the opposite direction aircraft was 1,000 ft above or below them respectively and to report sighting the other aircraft. At 1236 the A320 crew reported to the controller that they were descending because of a traffic alert and collision avoidance system resolution advisory. The controller acknowledged the report and then queried the B767 crew about the traffic alert and collision avoidance system event. The B767 crew confirmed that their aircraft's systems had received a traffic alert and collision avoidance system resolution advisory to climb.

Later analysis of aircraft data showed that both aircraft had been maintaining FL280 on reciprocal tracks. The combined closing groundspeed of the aircraft was 920 kts and they were about 9 NM apart when the traffic alert and collision avoidance system activated. As the crews complied with the resolution advisory the A320 crew saw the B767 pass above them when the vertical spacing and lateral distance between the aircraft was 900 ft and 0.5 NM respectively. There was an infringement of separation standards.

Controller background

The controller had over 10 years experience in en route and five years in tower control. Following a staff rationalisation exercise the controller reluctantly moved from Moorabbin to the Melbourne centre in mid-1998. Since that time, he had experienced increasing levels of stress because of:

- dissatisfaction with career opportunities,
- problems with undertaking night duty,
- personal problems with supervisory staff,
- unsuccessful applications for positions in the tower, and
- a recent diagnosis of the critical illness of a family member.

For example, on the day before the occurrence the controller was told that he had again been unsuccessful in a recent selection exercise for positions in the tower or terminal area streams. This was a source of stress to the controller.

Day of the occurrence

The controller reported that he did not have breakfast because of the early start and woke at 0400 after about 5 hours sleep. He began work at 0530. He later said he felt "somewhat tired" on the day of the incident and that he did not feel his limited period of sleep influenced his performance. Individuals suffering mild to moderate fatigue are generally unaware of decreasing levels of performance.

This was to be the controller's last working shift before starting leave. The controller had been approved to take 2 weeks leave to be able to be with his family because of the illness of the family member.

About 3 hours before the occurrence the controller was relieved at the position to enable him to meet with the centre manager. The centre manager advised that a claim of harassment by the controller had been investigated and was dismissed. This information distressed the controller. The centre manager told him to take time to compose himself before going back to the console or operations room. During this exchange the controller advised the centre manager of the strain he was under because of the recent diagnosis of a family member with a terminal illness. Before this meeting the centre manager was unaware of the illness in the controller's family. The centre manager told him that he didn't have to return to the console - it was his choice.

Airservices' Australia (Airservices) Civil ATS Operations Administration Manual (CATSOAM) provides guidance material on stress awareness for Airservices' staff. It states in part that "routine tasks with monotonous or minimum workload can cause some people to run over previous events or issues and, if they have been unpleasant or difficult, then concentration on the task being performed may deteriorate". It also warns that "stress is cumulative and can affect performance at work" and includes a caution that "professional guidance should be sought in case of doubts concerning mental state and fitness for work". With illness, injury or medication the manual places the onus on individuals to ensure that they are able to undertake rostered duties. It states, "a person having any doubt about their fitness to perform at the correct level for a full tour of duty must tell the appropriate supervisor. They should be stood down from operational duties until they feel fit to resume duty, or until the matter has been resolved by a medical practitioner".

The controller later reported that he had felt similarly distraught on other occasions and had performed satisfactorily and believed he would be able to do so again. Also, he felt that he had little choice but to return to the operator position. The controller spent 30 to 40 minutes recovering from the meeting and returned to the position after an absence of about 90 minutes.

The centre manager advised the flight information region manager in the operations room and the controller's team leader of the outcome of the meeting. The centre manager briefed the flight information region manager to stand the controller down from operational tasks should there be any doubt about that individual's ability to control. The flight information region manager saw the controller on two occasions during the 40 - 50 minute period following the return to the operating position. The flight information region manager's impression was the controller was managing the position and did not need relief.

Organisational issues

During the last decade, there has been an increased rate of organisational change within Airservices. This has led to increased changes in work practices and a tendency toward expanding many job roles through multiskilling.

Research shows that perceived major causes of stress in Australian workplaces include the rate of change and poor organisational communication. Similar factors were also reported during the investigation.

Despite the strong influence of organisational climate factors on employee stress levels, operational demands also contribute to psychological stress. Also, stress is more likely to be reported where morale is lower than normal.

During 1998 and 1999 the Melbourne Centre was undergoing significant change in preparation for and during the transition to The Australian Advanced Air Traffic Control System (TAAATS). Because of this change, during late 1999 and early 2000 the controller had five different managers. The management of the controller within the centre was such that operational, health and career management and other issues were handled by a number of different managers. This arrangement relied on a high level of coordination and communication between managers for each to maintain an understanding of the progress of staff specific issues. The investigation did not establish the degree to which the controller's issues had been passed on to the relevant individuals during the changeover in management staff.

Air traffic system

Alice Springs sector is a non-radar sector that uses procedural control methods to separate aircraft. Controllers use a combination of a presentation of aircraft positions on an air situation display and lists of electronic flight progress strips to manage and separate aircraft. The air traffic system updates aircraft positions based on limits, including aircraft performance data, meteorological data and the flight data record created for each flight from a flight plan. Controllers update aircraft flight data records after receiving position reports from flight crew.

The label for each aircraft depicted on the air situation display includes a field for operational data. After the controller had been told the A320 had left Alice Springs he annotated the operational data field to show the crew had planned at FL370 and that an amended level of FL270 was needed. When the A320 crew reported on frequency, the controller selected FL270 in the cleared flight level field of the label but told the crew to climb to FL280. When the crew read back FL280 the controller did not detect the error and accepted FL270 in the aircraft's flight data record. Shortly after, the controller deleted the amended FL270 note from the operational data field. Later analysis of the recorded data confirmed the controller had correctly entered FL270 into the system but had issued a wrong level, FL280, to the A320 crew.

The controller had a similar event with a Boeing 737 that left Alice Springs five minutes after the A320 on the same route. The crew of this aircraft also needed to be assigned FL270 to ensure separation from the B767. The controller initially assigned FL280 but corrected it to FL270 during the same radio transmission to the B737 crew. The B737 crew sought clarification of the assigned level from the controller and the controller confirmed the required level was FL270

Pilot - controller communication

Because of very high frequency (VHF) radio coverage limits, air traffic controllers needed to tell crews to change frequency at a position about 250 NM south-east of Alice Springs when operating below FL310. As the B767 was at FL280 the controller told the crew to transfer to 132.9 Mhz, which was a frequency, used by the adjacent Woomera sector. This was to ensure that the crew maintained VHF communications with Melbourne centre. Responsibility for the separation of the flight remained with the Alice Springs sector controller while the crew was monitoring the Woomera sector frequency. The Alice Springs sector controller could not monitor 132.9 Mhz. During the period the crew were monitoring the Woomera sector they did not hear the Alice Springs sector controller tell the A320 crew to climb to FL280. Shortly after, the B767 crew returned to the Alice Springs sector frequency.

The Manual of Air Traffic Services (MATS) states that a reply to a voice call shall consist of the identification of the calling unit, the identification of the called unit and the words "Go ahead" or "Standby" as appropriate. However, while "communications should normally start with a call and reply, when reasonably sure that the call will be received, the calling unit may go ahead without waiting for a reply". In a situation similar to this occurrence, the resulting report from a crew would include the altitude or level being maintained. However, following the B767 crew's on-frequency report the controller immediately told them to report sighting and passing the A320. The controller did not ask nor did the crew report the flight level being maintained.

Occurrence summary

Investigation number 200002379
Occurrence date 09/06/2000
Location 222 km SSE Alice Springs, (VOR)
Report release date 08/05/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Loss of separation
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer Airbus
Model A320
Registration VH-HYX
Serial number 288
Sector Jet
Operation type Air Transport High Capacity
Departure point Alice Springs, NT
Destination Sydney, NSW
Damage Nil

Aircraft details

Manufacturer The Boeing Company
Model 767
Registration VH-OGS
Serial number 28725
Sector Jet
Operation type Air Transport High Capacity
Departure point Sydney, NSW
Destination Jakarta, INDONESIA
Damage Nil

Boeing Co 767-238, VH-EAM

Summary

Prior to the top of the descent, the crew of the Boeing 767 monitored the Perth Airport automatic terminal information service, which indicated low mist patches in the airport area. The approach controller indicated to the crew that fog was rapidly obscuring both runways. However, a short time later, the tower controller indicated that the visibility on runway 21 was 800 metres. At the minimum descent altitude, the crew reported to the tower controller that they could see the runway. The crew later reported that during the landing roll, visibility reduced to less than 600 metres. The aircraft landed at 2156 WST on runway 21.

The Bureau of Meteorology issued a terminal area forecast at 1838 which forecast a 30% probability of fog from 0200-0800 the next morning. An amended terminal area forecast was issued at 2045 which forecast a 40% probability of fog from 0000-0900 the next morning. The current airport trend type forecast indicated periods of reduced visibility to 4,000 metres for 30 minutes or less. The onset of fog occurred 2.5 hours prior to the forecast time.

A report from the Bureau of Meteorology Perth office indicated that the assessment was that fog would be a possibility depending on how quickly the showers and cloud cleared, the wind speed decreased and stabilisation of the dewpoint occurred. At 2040 a pilot landing at Jandakot Airport, about 16 kilometres from the Perth Airport, advised that fog patches were forming at that airport. At 2050 the duty Senior Supervising Meteorologist conducted a `rooftop' observation from the Regional Forecasting Centre and noted that the Perth control tower, about 12 kilometres, and lights on the Darling escarpment, about 19 kilometres, were visible. The observed conditions confirmed that fog from 0000 seemed a reasonable possibility. The Bureau of Meteorology indicated that experience had shown that it was rare for fog to occur as early as it had. The early occurrence of fog at Perth always follows precipitation in the preceding daylight hours. The passage of a front in the afternoon, accompanied by precipitation is a good precursor of early fog at Perth. The frontal passage was in the early evening at 1930. While fog can form almost immediately after a frontal passage, as it did on this occasion, experience has shown that it is rare for this to happen. The number of fogs forming at 2200 or earlier, over a 26 year period at Perth Airport is approximately 20 out of a total of 340 or 5% of occasions. The forecasting team on duty that night were surprised by the onset of fog, earlier than expected, once the showers had cleared.

The Bureau of Meteorology advised that the soon to be implemented Bureau of Meteorology Research Centre Fog Project at Perth Airport will assist with the knowledge and the quality of aviation fog forecasting.

Occurrence summary

Investigation number 200002305
Occurrence date 31/05/2000
Location Perth, Aero.
State Western Australia
Report release date 01/08/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Navigation - Other
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer The Boeing Company
Model 767
Registration VH-EAM
Serial number 23309
Sector Jet
Operation type Air Transport High Capacity
Departure point Sydney, NSW
Destination Perth, WA
Damage Nil

Supplementary report: Collision with water, Piper PA-31-350, VH-MZK, on 31 May 2001

Executive summary

Report release date: 28/10/2003

Since the release by the ATSB on 19 December 2001 of Report 200002157 on the fatal accident involving Piper Chieftain VH-MZK in Spencer Gulf in South Australia on 31 May 2000, further events have taken place, and additional information has become available, regarding issues that were examined in ATSB Report 200002157. The ATSB formally re-opened its investigation in November 2002 under the provisions of Part 2A of the Air Navigation Act in order to test the significance of the new evidence.

From July 2002 until July 2003, the South Australian Coroner conducted a public inquest into the accident. The Coroner delivered his findings on 24 July 2003 and disagreed with the conclusions in ATSB Report 200002157 and was critical of the ATSB investigation. The Coroner concluded that the left and right engines had failed independently. He found that the right engine overheated and was damaged during the climb from Adelaide, and developed a hole in the No 6 piston 8 minutes into the cruise phase of the flight. He concluded that the left engine subsequently independently failed because of fatigue cracking initiated by a sub-surface manufacturing defect in the crankshaft.

Between 1 February and 16 September 2002 (after ATSB Report 200002157 was released), the engine manufacturer issued Mandatory Service Bulletins 550, 552, and 553 concerning potential crankshaft defects. The serial number of the MZK left engine crankshaft appeared in Service Bulletin 553. It has been reported that of the crankshafts that were subject to that service bulletin, almost 70 percent of those tested were not defective and were permitted to continue in service after testing.

As stated in ATSB Report 200002157, initial examination of the crankshaft by the ATSB indicated that it complied with the proprietary standards set by the engine manufacturer. Based on their examination of a sample that had been cut from the crankshaft by the ATSB and stored for 18 months, academics from a local university commissioned by the Coroner, along with a US firm acting for the plaintiffs in civil damages litigation, reported the existence of 'massive' high temperature oxide 'inclusions' in the crankshaft material. However, later examination by the same experts and destructive testing of the crankshaft in the vicinity of the fatigue crack origin did not reveal any evidence of massive inclusions. Nevertheless, the opinion of the US firm concluded that a manufacturing defect (rather than a thermal crack as suggested in ATSB Report 200002157) was responsible for initiating the fatigue crack. They stated that while no large foreign body manufacturing inclusion was found at the crack initiation site, it may have 'fallen out' as the crack propagated. Detailed examination of the crankshaft material and the fracture area, including both sides of the fracture surface by the ATSB (in the presence of independent observers) in March 2003 did not reveal any irregularity in the crankshaft steel that could have initiated the fatigue fracture under normal engine operating conditions. No evidence of any large inclusions or of any 'honeycomb feature' as suggested in material associated with the service bulletins was found. Without receiving expert advice, the Coroner in his findings stated that the ATSB's 50 page test report 'takes the matter no further' and chose to rely on earlier opinion and circumstantial evidence.

The ATSB does not agree with the Coroner's findings and is strongly of the view that the engine failure mechanisms and the sequence of events contained in ATSB Report 200002157 remain the most likely explanation of the circumstances of the accident, based on the limited factual information that was available. This Supplementary Aviation Safety Investigation Report includes the ATSB's detailed response to the Coroner's findings. The report also includes further explanation of the main issues addressed in ATSB Report 200002157, as well as matters of major interest that arose during the inquest, including:

  • The possibility that the failure of the VH-MZK left engine crankshaft was linked to a manufacturing defect,
  • The possibility of an engine failure sequence that differed from that advanced in Report 200002157,
  • The extent and timing of the left engine No 6 connecting rod big end bearing 'failure',
  • The operation of the turbocharger on the Textron Lycoming TIO-540 engine,
  • The maximum single engine speed the aircraft could achieve.

In summary, the ATSB explanation for the initiation of the fatigue crack in the left engine crankshaft about 50 flights before the accident was a thermal crack caused by localised surface heating when a bearing insert failed to operate as designed and a bearing edge interfered with the crankshaft surface. This resulted from some combination of excessive engine pressures probably caused by preignition from incandescent lead oxybromide deposits (linked to fuel leaning, eg in the climb but within the aircraft manufacturer's guidelines) and bearing slippage assisted by an anti-galling lubricant. In addition to MZK, this was based on the ATSB's observations of damage in a number of engines (now more than a dozen) including two from another engine manufacturer. The ATSB concluded that the holing of the right engine No. 6 piston was the result of detonation in response to the left engine failure (the right engine damage was therefore a dependent failure). As the ATSB stated when releasing Report 200002157 on 19 December 2001, it is not appropriate to 'blame' the young pilot in this scenario given the paucity of evidence and the ATSB did not do so.

The ATSB does not agree with the Coroner that MZK's pilot was likely to have allowed, ahead of any stressful situation, his right engine to overheat to a point 8 minutes into the cruise of melting a hole in a piston (especially as the temperature probe is atop the melted No. 6 piston cylinder) and then be unlucky enough that a deep-seated long-term progressive fatigue crack problem in the left engine crankshaft would have suddenly caused that engine to independently fail.

Following the release of ATSB Report 200002157, the ATSB received responses from the US FAA concerning Recommendations R20010254 and R20010255 that dealt with combustion chamber deposits and anti-galling compounds. The FAA advised that it would review the effect of anti-galling compounds on bearing insert retention, and that it was conducting an extensive evaluation of the detonation characteristics of high performance reciprocating engines and would include an examination of deposit formation as part of that evaluation.

In July 2002, the ATSB issued Safety Recommendation R200220149 for CASA to examine the potential safety benefits of devices that monitor aircraft fuel and engine system operation and whether those systems should be fitted to general aviation aircraft engaged in air transport operations. CASA advised that it did not consider the safety benefits of those devices warranted their fitment being made mandatory. However, CASA did not have any concern with operators voluntarily fitting such equipment.

While maintaining that the engine failure mechanisms and the sequence of events contained in ATSB Report 200002157 remain the most likely scenario, the Bureau examined carefully a range of scenarios. In particular, an assessment was made of any safety action that might be required if an accident as a result of a less likely scenario was to be prevented in the future.

The Coroner included five recommendations in his findings:

  1. As suggested in the ATSB's submissions, the Coroner sought clarification of engine operating procedures between different versions of pilot operating handbooks and flight manuals for piper Chieftain aircraft to ensure that engine detonation limits are not exceeded. The ATSB has written to CASA supporting the Coroner's recommendation and requesting that CASA seek clarification of detonation limits from the US FAA, and examine how engine operating procedures for operators of more than one model of a particular aircraft type take proper account of differences in versions of operating manuals and handbooks.
  2. The Coroner sought improved lines of communication between international aviation regulation and safety investigation agencies, even where litigation might be threatened. The ATSB already enjoys close working international relationships, but agrees that the flow of information could be improved in some instances. However, there are practical limitations that apply in other countries and through multilateral agencies over which the ATSB has no control.
  3. The Coroner sought that CASA mandate the fitment of on-board recorders in aircraft carrying fare-paying passengers. The ATSB considers that its Safety Recommendation R200220149, referred to above, addressed that issue.
  4. The Coroner sought the carriage of life jackets and/or life rafts in fare-paying passenger operations over water, which is supportive of earlier ATSB recommendations. ATSB Report 200002157, Section 4.4, detailed Safety Recommendations R20000248 and R20000249 concerning the carriage of life jackets and emergency and life saving equipment. R20000248 was accepted by CASA and Civil Aviation Order 20.11 amended to require life jackets to be carried on all passenger flights over water. As regards R20000249, CASA has advised that it was considering a number of issues regarding emergency and life saving equipment in twin engine aeroplanes in the context of the proposed CASR Part 121B, Air Transport Operations - Small Aeroplanes. The draft regulations included in a Notice of Proposed Rule Making (NPRM) released by CASA in July 2003 for this Part includes various requirements for emergency cabin lighting and carriage of items such as of life jackets and other flotation devices, life rafts, ELTs (Emergency Locator Transmitters) or EPIRBs (Electronic Position Indicating Radio Beacons) and other survival equipment, including provisions.
  5. The Coroner proposed a research program concerning self-deploying ELT units. The ATSB's recommendation to CASA R20000249 encompasses enhanced emergency and life saving equipment such as ELTs and the Bureau believes that CASA, AusSAR (AMSA) and Defence are best placed to progress the issue.

Occurrence summary

Investigation number 200002157A
Occurrence date 31/05/2000
Location 28 km SE Whyalla Airport
State South Australia
Report release date 28/10/2003
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Occurrence class Accident
Highest injury level Fatal

Aircraft details

Model PA-31-350
Registration VH-MZK
Serial number 31-8152180
Sector Piston
Departure point Adelaide, SA
Destination Whyalla, SA
Damage Destroyed