Misaligned take-off involving Bombardier DHC-8-315, VH-TQM, Mildura Airport, Victoria, on 25 February 2025

Final report

Report release date: 12/05/2026

Investigation summary

What happened

On 25 February 2025, a QantasLink DHC-8-315 aircraft, registered VH-TQM, was being operated on a scheduled passenger transport flight from Mildura to Melbourne Airport, Victoria. The flight crew commenced taxiing the aircraft prior to first light. The aircraft was backtracked on runway 09 and taxied past the threshold into the starter extension bypass pad to turn around and line up. The flight crew inadvertently lined up the aircraft with the right runway edge lights and commenced taking off from this position. 

During the take-off roll, the nose landing gear contacted and damaged 5 runway edge lights. Although the flight crew heard some external noises, neither recognised this as contact with the runway edge lights. The captain, however, identified that the aircraft was not on the centreline and manoeuvred towards the centreline and continued the take-off. During the initial climb, the flight crew realised that the aircraft had contacted the runway edge lights.

The flight crew conducted a low pass at Melbourne to facilitate a visual inspection of the landing gear by air traffic control. This did not identify any issues and the aircraft landed without incident. An inspection of the aircraft found minor damage to the nose landing gear, fuselage and right propeller blade.

What the ATSB found

The ATSB found that the incident took place in dark ambient conditions and that the taxi guidance line markings were not followed for the turn to line up. Instead, the aircraft was turned tighter, which positioned it closer to the right edge of the runway. Also, the flight crew’s attention was focused on conducting checks during the turn and on completion of the turn. However, as the flight crew believed they were correctly aligned with the runway centreline, they commenced the take-off roll.  

It was also established that, when conducting the low pass of the Melbourne air traffic control tower, the aircraft was not maintained at the briefed height of 200 ft above ground level and descended to 134 ft for a short period. It was noted that the flight crew did not seek advice on the low pass nor did the operator provide supporting procedures for this. 

Further, during post‑incident drug and alcohol testing, the captain tested positive for a non-prescribed medication. However, impairment was not expected given the reported dosage and time elapsed since taken.

What has been done as a result

QantasLink advised that human factors and non-technical skills training on the threat awareness of factors that have contributed to misaligned take-offs was included for wider flight crew recurrent training. Supporting documentation for Mildura Airport was updated to include information on the runway 09 starter extension for increased awareness along with education material being distributed regarding flight crew briefings and identifying relevant threats.

A safety alert was issued to prohibit the conduct of checks during runway end turns. This was incorporated into the Flight Crew Operating Manual. QantasLink also introduced policy aligned with Qantas Group operators regarding the risks associated with air traffic control tower fly pasts. 

Safety message

A number of factors known to influence misaligned take-off occurrences were identified in this investigation. Dark ambient conditions have been consistently identified in similar occurrences and can reduce the visual cues available. This may limit the ability of flight crew to identify their position when lining up. 

Although the completion of checks are a necessary part of a flight, they may result in a diversion of attention towards the checks at the expense of another task such as lining up. Pilots must consider the timing for conducting checks in situations where monitoring their external environment is important.

The incident further highlighted that, in non-normal situations for which there is no documented procedure, pilots should consult all available sources including their operator for assistance. Lastly, pilots should exercise caution when taking any medications and should be discouraged from taking prescription medications without medical supervision. Many prescription (and non-prescription) medications are not safe for use while conducting aviation activities and are therefore not permitted for use.

 

The investigation

The ATSB scopes its investigations based on many factors, including the level of safety benefit likely to be obtained from an investigation and the associated resources required. For this occurrence, the ATSB conducted a limited-scope investigation in order to produce a short investigation report, and allow for greater industry awareness of findings that affect safety and potential learning opportunities.

The occurrence

Flight schedule

On 24–25 February 2025, a QantasLink DHC-8-315 (Dash 8) aircraft, registered VH‑TQM, was operated on scheduled passenger transport flights over the 2 days, which consisted of 5 sectors on the first day and 3 sectors the following morning.1 The crew consisted of 2 flight crew and 2 cabin crew.

On 24 February, the flight crew signed on at 1040 local time in Melbourne, Victoria, and completed 2 return flights to Devonport, Tasmania, and Wagga Wagga, New South Wales. For the final sector to Mildura, Victoria, the aircraft departed Melbourne at about 1922 and arrived at 2045. The crew signed off from duty at 2100 and arrived at their accommodation about 15 minutes later.

On 25 February, at about 0545, the crew departed their accommodation and signed on for duty at 0600 for a 0630 scheduled departure from Mildura to Melbourne. The captain was the pilot flying (PF) and the first officer (FO) was the pilot monitoring2 for this sector. There were 50 passengers on board.

Taxi to runway 09

The captain commenced taxiing the aircraft before first light at about 0631. Closed-circuit television (CCTV) footage showed the aircraft taxi light was on, illuminating a portion of the tarmac ahead of the aircraft. The captain reported that they had also selected the approach lights to ‘on’ to provide greater illumination of the runway surface during the taxi. CCTV footage also showed that the taxiway, runway and starter extension bypass pad3 lighting was active.

After entering the runway, the aircraft was backtracked along the centreline. CCTV footage showed that, when the aircraft approached the runway 09 threshold, the approach lights were selected on. The aircraft was taxied past the threshold and into the runway starter extension bypass pad to turn the aircraft around and line up. The captain reported that the starter extension was not required for performance, but their preference was to use the full runway length where possible. They also stated that the wider extension area would provide more room for the turn around.

The recorded flight data4 showed that the aircraft path followed the taxi guideline marking into the starter extension but was turned right, prior to the end, and away from the guideline, which led to the extended centreline. The captain explained that their initial intent was to use the complete starter extension. However, once established in the extension, they chose not to do so to avoid inadvertently exiting the pavement in the dark conditions. The FO reported that this was not communicated to them at the time nor were they aware that the aircraft had been turned earlier. The aircraft path during the turn remained to the right of the extended centreline, resulting in it being positioned close to the right edge of the runway (Figure 1).

During the turn, the flight crew conducted the ‘ready checks’ and the associated checklist, during which time they both reported being focused within the flight deck on the conduct of the checks. The captain also reported being distracted by either smoke or mist outside the left window. On completion of the turn, the captain stated they were drawn to the white right runway edge lights, believing them to be runway centreline lights. The captain also indicated that the flight director and heading bug confirmed that the aircraft was aligned with the runway direction. The FO reported that they observed the runway 09 threshold markings, which they equated as the aircraft being in the correct position to line up. They did not recall noticing any lights ahead of their position. Once lined up, both flight crew believed they were aligned on the centreline of runway 09.

Take-off on runway 09

The captain recalled that, when they commenced the take-off roll, they advanced the power levers as close to the required power setting as possible, then called ‘set power’. At this point, the FO checked the power setting and adjusted the levers to ensure the exact power required was set. The FO reported their attention was predominantly focused inside the flight deck from this time. The captain identified that the take-off roll was ‘rough’, explaining that this was not unusual for an early morning first flight of the day for that aircraft type. 

The captain recalled that, about the time the FO called ‘70 kt’, the sounds and sensations became more intense and identified that the aircraft was on the runway edge (Figure 1). They then manoeuvred the aircraft to its correct position along the centreline. 

The FO reported hearing ‘1 or 2 thuds’ at about the time that they called ‘70 kt’. The FO also explained becoming momentarily distracted with the storm light5 on their side of the flight deck, which had unexpectedly turned on. The FO continued their scan between airspeed and ahead of the aircraft and shortly after made the calls ‘V1’ and ‘rotate’.6 

The FO stated that they had not become aware of the misaligned take-off until after the captain had already begun manoeuvring the aircraft toward the runway centreline.

The captain continued the take-off, recalling that the aircraft had operated normally, and that the abnormal sounds and sensations had ceased. Once airborne, the ‘after take-off’ procedures were completed, as required. 

Figure 1: Flight tracking data for the take-off with the starter extension inset

The figure is a satellite image of runway 09 with flight tracking data overlaid. An inset shows a closer view of the starter extension.

The aircraft track (within the inset) at the end of the starter extension shows a sharply clipped turn, which is due to the fidelity of the data. Source: Google Earth, with aircraft flight data overlaid and annotated by the ATSB

During the initial climb, the flight crew realised that they may have contacted the runway edge lights. The FO contacted the Mildura Airport aerodrome reporting officer and advised them of this. They requested the area be inspected and for them to report back on any debris located. The flight crew were subsequently advised that there was damage to 5 lights on the right edge of runway 09 (Figure 2). No aircraft debris was identified.

Figure 2: Damaged runway edge lights (inset) on runway 09

The figure shows the locations of the damaged runway lights with individual pictures of each damaged light.

Source: Google Earth and Mildura Airport, annotated by the ATSB

After take-off inspections

The flight crew reported that following discussion about what had occurred, they considered the possibility that the landing gear had not been damaged as the remainder of the take-off roll occurred normally and the landing gear retracted without fault. They consulted the Quick Reference Handbook, however, there was no procedure to assist them with assessing the landing gear status. They then discussed and assessed the potential risks for landing with potential damage to the aircraft, and that a visual inspection of the landing gear would be required. 

The captain explained that after the landing gear was extended, the main gear would become visible from the passenger cabin. The captain had briefed a cabin crew member that the landing gear would be extended earlier than normal for them to inspect. The captain asked them to check for any signs of fluid or tyre damage and whether the gear had deployed correctly. The cabin crew were to use the cabin ready button to signal if the landing gear appeared okay, otherwise they were to call the captain if they had concerns. Although the cabin crew were able to inspect the main landing gear, they could not view the nose landing gear. QantasLink advised that, during this time there was no contact for assistance between the flight crew and its operations centre.

The FO contacted Melbourne Centre air traffic control (ATC) and requested to conduct a low pass on their arrival at Melbourne Airport to facilitate a visual inspection of the landing gear. ATC was requested to focus their inspection on the nose landing gear. On advice from ATC, the flight crew briefed to complete the pass at approximately 200 ft above ground level (AGL), which would place the aircraft at an equivalent level to the controller who was in the control tower. The captain set the radar altimeter to 150 ft AGL to assist them in maintaining the aircraft at 200 ft AGL. As the landing gear and flaps would be extended, the captain planned to fly the aircraft at 120–130 kt. During the low pass, the captain reported that the height was adjusted to enable ATC to inspect the landing gear and that they received a minimums audio alert, signifying that the aircraft had descended below 150 ft AGL. The flight data identified the aircraft had descended at its lowest to a height of 134 ft AGL at which point the speed was 122 kt.   

The inspection of the main landing gear was completed by a cabin crew member and they pushed the cabin ready button to advise the flight crew that the gear appeared satisfactory. Similarly, ATC did not observe any anomalies of the landing gear, advising the flight crew that the gear appeared correctly aligned and the tyres appeared in satisfactory condition. Following the low pass, the landing gear was raised and a missed approach conducted. The flight crew completed another approach, and the aircraft was landed without further incident.

Context

Flight crew information

Qualifications and experience

The captain held an Air Transport Pilot Licence (Aeroplane) and a valid class 1 aviation medical certificate. They had a total of 19,000 hours flying experience of which 935 hours were on the Dash 8. The captain had flown 107 hours on the Dash 8 in the previous 90 days. 

The FO held a Commercial Pilot Licence (Aeroplane) and a valid class 1 aviation medical certificate. They had a total of 3,386 hours flying experience of which 773 hours were on the Dash 8. The FO had flown 45 hours on the Dash 8 in the previous 90 days. 

The captain’s logbook identified they had operated at Mildura on numerous occasions in the previous few months. None of those flights were at night or before first light. The FO reported they last operated in similar light conditions at Mildura in September 2024.

Flight crew fatigue assessment

The captain reported going to bed at around 2230 after arriving in Mildura and waking at around 0500 the next morning. The noise from the hotel had interrupted their sleep and they recalled feeling ‘a little tired, less than fresh’, to, ‘moderately tired’7 at the time of the incident. In total, the captain reported obtaining around 6 hours sleep in the previous 24 hours and around 13 hours in the previous 48 hours.

The FO reported they went to sleep at around 2200, woke around 0500, and obtained a ‘good’ sleep. During interview, the FO described that they did not feel ‘match fit’, as they had not operated a 5-sector overnight duty for some time. They also reported feeling ‘okay, somewhat fresh’7 at the time of the incident. In total, the FO reported obtaining around 7 hours sleep in the previous 24 hours and around 14.5 hours in the previous 48 hours.

Aside from the usual workload associated with a take-off in the dark, neither of the flight crew reported any additional fatigue‑related factors on the incident flight.

The ATSB assessed the flight crew’s sleep opportunity, actual sleep obtained, and quality of sleep leading up to the flight as well as other fatigue‑related factors. A number of factors were present that could have increased the risk of fatigue, including a minimum rest period that was provided after a 5-sector day, and a slight reduction of sleep hours and poor-quality sleep in the previous 24 hours (for the captain). However, given the total hours of sleep obtained, time awake, time on duty, and time of the incident, it was unlikely the flight crew was experiencing a level of fatigue known to have an adverse effect on performance. 

Drug and alcohol test results

In accordance with the QantasLink drug and alcohol management plan, the flight crew underwent a post-incident alcohol breath test and urine drug test. The FO returned a negative result, however, the captain’s drug test was non-negative. When the test was administered the captain declared that on consecutive days during the prior weekend they had taken a prescription medication that was not prescribed to them.

As there was a non-negative result, a second test of the sample was conducted at a laboratory. The presence of a testable substance above the cut-off level was confirmed. 

QantasLink confirmed that the captain had returned a positive test result and that they had been stood down pending further assessment in accordance with company policy. Their medical review officer explained that, while the test result confirmed the presence of a testable substance above the cut-off level, the testing could not indicate when or what dosage was taken, nor could it indicate if there were any effects. They further explained that the medication was not currently permitted for use by pilots, it had an effective period of about 10 hours, and there would be no lingering effects expected unless there was an adverse reaction.

The captain reported to the ATSB they did not experience any effect from the medication at the time it was taken, nor did they experience any side effects. The FO and cabin crew members reported not noticing anything of concern regarding the captain nor their fitness for duty on that morning.

The ATSB engaged a forensic pharmacologist to review the test results. They stated that the concentration detected was consistent with the reported dosage self-administered by the captain on the weekend prior to the incident flight.

The pharmacologist noted numerous potential adverse effects of the medication that included: insomnia, loss of appetite, restlessness, euphoria, dizziness, dyskinesia (involuntary, repetitive and or jerky movements), tremor, dysphoria and with higher doses personality changes, irritability, hyperactivity and psychosis. It may produce peripheral effects such as increasing blood pressure and heart rate, palpitations, increased sweating and hyperthermia (increased temperature). The manufacturer’s consumer medication information stated that the medication should not be taken by persons with known cardiovascular disease. Additionally, the information advised consumers to not drive or operate machinery until they know how the medication affects them. The pharmacologist advised it was possible that the non-therapeutic use of the medication could result in some impairment and potentially, in some cardiovascularly susceptible persons, serious harm. 

The pharmacologist further noted it was not possible to determine the likelihood of impairment from a urine sample. There were no studies that have established any relationship between urine concentration of the medication and psychomotor skills performance. For a person using a non-prescribed medication and who has not developed a tolerance, they indicated that impairment could not be excluded as being possible. However, based on the reported dosage, the specialist assessed that impairment would not have been expected on the day of the incident.

Aircraft information

General

The aircraft was a Bombardier DHC-8-315 (Dash 8) twin turbo-propeller regional aircraft capable of carrying 50 passengers and normally crewed by 2 flight crew and 2 cabin crew. It was manufactured in 2004 (serial number 604) and first registered in Australia in 2004.

Post‑incident maintenance

Following the incident, the operator conducted a towing assessment and general visual inspection of the aircraft, with particular attention paid to the landing gear, engines, propellers and fuselage. More detailed inspections of the nose and right main landing gear also took place. In addition, the aircraft manufacturer requested an unscheduled engine inspection.

Damage was identified to the nose landing gear, including both tyres, the cover for the weight on wheels sensor, and the trailing arm (Figure 3). The lower fuselage skin sustained minor impact damage (to 17 areas) and there was minor impact damage to the leading edge sheath of a right propeller blade. Both tyres, the weight on wheels sensor cover and the nose landing gear trailing arm were replaced. The remaining damage was assessed to be within the limits in accordance with manufacturer guidance.

Figure 3: Nose landing gear damage

The figure depicts the damage to the nose landing gear.

From left to right: trailing arm impact damage, tread cuts and chunking, tyre impact damage, tyre sidewall slice. Source: QantasLink

Meteorological information

The captain described the weather as good with no fog or rain, although it was dark at the time as their departure was before first light. They specifically noted that the conditions were very dark and the area was poorly lit when conducting the turn to line up. Similarly, the FO reported that it was clear but very dark. 

Data from the Bureau of Meteorology showed that the weather at Mildura was fine and clear of any cloud or significant phenomena that may have reduced visibility. The aerodrome weather information service recorded visibility in excess of 10 km at the time of the incident. The wind was generally from 170° (southerly) around 5 kt in the 10 minutes prior.

Information from Geoscience Australia identified that the incident was 14 minutes prior to first light and 40 minutes prior to sunrise.8 CCTV footage showed that the conditions were dark and the sun had not yet risen.

Airport information

Mildura Airport was a certified, non-controlled aerodrome and had 2 sealed runways, aligned 09/27 and 18/36. Runway 09/27 was 45 m wide and included a starter extension bypass pad at the western end of the runway. The starter extension bypass pad provided an additional surface of 117 m in length available for take-off from runway 09. It also provided an additional 23 m in width to turn an aircraft around.

The extension included taxi guideline markings with turn guidance to realign the aircraft with the centreline. It also had arrows aligned with the runway centreline and pointing to the runway threshold (Figure 4).

Figure 4: Runway 09 starter extension bypass pad

The figure depicts the runway 09 starter extension bypass pad, annotated to highlight key line markings.

Source: Google Earth, annotated by the ATSB

The airport was equipped with airfield lighting, which included elevated white omni‑directional runway edge lights, inset green and red bi-directional runway threshold lights9 and elevated blue omni-directional taxiway edge lights on taxiways C and D only. The starter extension also had elevated blue edge lights. Runway 09/27 did not have, nor was it required to have, runway centreline lighting. Runway 09 also included precision approach path indicator10 lighting on both sides of the runway. CCTV footage obtained from Mildura Airport confirmed that the airfield lighting was active at the time of the incident. Although the foreground was not illuminated by an aircraft taxi light, Figure 5 is indicative of the view that was likely available to the flight crew after lining up on the right edge of runway 09. 

Figure 5: View of the runway 09 lighting that was available to the flight crew when lined up with the right edge of the runway

The figure shows the view of the runway 09 lighting that was available to the flight crew when they lined up.

Source: Mildura Airport, annotated by the ATSB 

Operational information

Runway alignment

The Operations Manual OM 1 section 6.13.1.2 Navigation and monitoring of taxi routes stated that: 

During taxi, the PM is to monitor aircraft location and provide proactive guidance to the PF on the taxi route.

Section 6.13.5.1 Takeoff also required that: 

Prior to commencing the takeoff the Pilot in Command and the First Officer shall check the aircraft position is on the runway centreline and either at the correct runway threshold or other designated takeoff position (e.g. intersection).

Similarly, section 2.8 Takeoff of the Flight Crew Operating Manual 300 (FCOM) also indicated that the captain shall align the aircraft with the runway centreline prior to take‑off.

‘Ready’ and take-off procedures

The FCOM included a ‘Ready and Line Up’ procedure. Although it directed flight crew to conduct the associated checks at an appropriate time, the FCOM did not provide detail as to when was appropriate. However, the captain reported that they would not normally conduct the ready checks during a turn to line up, explaining that some runways they operated on were 30 m wide and the tight turn required was not compatible with the conduct of the ready checks. They further explained that runway 09 at Mildura was 45 m wide, with an even wider starter extension, and they felt comfortable that this would allow them the appropriate time and area to conduct the checks concurrent with the turn.

The FCOM also included a rejected take-off procedure in section 3.4.1. The procedure stated that the take-off should be rejected for a critical malfunction (for example, a master warning, engine failure or directional control issue) when between 70 kt and V1. At and after V1, the take-off must be continued. Neither the captain nor FO reported anything meeting the rejected take-off criteria. The captain did, however, discuss in hindsight that they possibly should have rejected the take-off.

Low flying

Section 4.4.4 Low Flying Operations in the Operations Manual OM 1 stated:

A company aircraft shall not be flown below 500’ AGL in day VMC [visual meteorological conditions],11 below LSALT [lowest safe altitude] at night or in IMC [instrument meteorological conditions],12 or below 1000’ over a built up area, unless it is:

• An emergency,

• To takeoff or land,

• Part of a published instrument approach,

• In accordance with ATC instructions, or

• Specifically authorised.

There was no guidance provided on conducting a low pass for the purposes of an external visual inspection of the aircraft.  

Airport guidance

Qantaslink provided additional operational guidance for Mildura Airport, which included: 

The standard position for RWY [runway] 09 take-off is on the threshold lines. An alternate start position is available which includes the runway starter extension.

However, guidance on how or when flight crew could use the starter extension for runway 09 was not included.

Misaligned take-offs 

Previous research 

When pilots taxi and take-off during daylight conditions, they normally have a wide range of visual cues by which they can navigate and verify their location. At night, however, the amount of visual information available is markedly reduced. Pilots rely more on the taxiway and runway lighting patterns presented to them and what can be seen in the field of the aircraft’s taxi and landing lights.

The ATSB research report Factors influencing misaligned take-off occurrences at night (AR-2009-033) was published in 2010 following the review of 24 misaligned take-offs that occurred at night in Australia and overseas. The report identified 8 common and recurring factors that contributed to misaligned take-offs at night, as presented below (Figure 6).

Figure 6: Factors contributing to misaligned take-off occurrences

The figure shows a graph of the factors contributing to misaligned take-off occurrences.

Source: ATSB

Environmental factors were the predominant contributors, which included physical features such as the runway layout, line markings and lighting. Weather and visibility were also considerations. The report identified that confusing runway entry, lighting or taxiway layout/lighting were the most frequent factors and that additional areas of pavement around taxiway entry and runway threshold areas could provide erroneous cues for pilots at night. 

Human factors were the next most common contributor, in particular, flight crew distraction, divided attention, workload and fatigue. Flight crew distraction upon entering, or just prior to entering the runway was frequently identified as a factor. The report described distraction as the drawing away or diverting attention, or an action that divided attention. This was reported to have occurred for numerous reasons including the performance of checklists, setting power or checking instruments.

The report explained that: 

…distraction comes about when multiple stimuli or tasks make simultaneous demands for attention. Generally, distraction results from one of these competing stimuli or tasks interfering with or diverting attention from the original task or focus of an individual.

Part of the problem with distraction is the resulting divided attention of the flight crew, with a focus on tasks inside the cockpit being at the expense of accurately assessing the external environment. This often occurs during taxi, when flight crew need to be ‘eyes inside’ the cockpit for significant periods of time. That is, instead of maintaining a visual look out from when they enter the runway, their attention is drawn inside for some reason such as checking instruments, confirming aircraft configuration or performing checklist items. While multi-crew operations partially mitigate this risk by articulating and dividing aircraft handling and monitoring roles between the pilots, there are still times when both crew members may not be processing the external environmental cues accurately. This divided attention is often a necessary part of lining up or beginning the take-off roll, but occasionally the attention of the flight crew will be diverted for longer than normal in response to an unusual event or problem. It is often attention to this non-standard action or item that contributes to line-up error events.

Operational factors were also identified such as air traffic control clearances and intersection departures were examples and in some cases they either contributed to, precipitated and/or exacerbated the environmental and human factors that were present.

Related occurrences

A review of the ATSB occurrence database identified a previous QantasLink misaligned take-off, which was investigated by the ATSB in 2009. ATSB investigation AO-2023-027 detailed 3 misaligned take-offs at Perth Airport in 2023 and 2024, and a number of other related occurrences were discussed in that report.

ATSB investigation AO-2009-007

On 11 February 2009, at about 1922 local time, a Bombardier DHC-8-315 aircraft, commenced the take-off roll on runway 01 at Townsville Airport for Cairns, Queensland. During the take-off, the captain realised that the aircraft was aligned with the left runway edge. The aircraft was manoeuvred to the centre of the runway and the take-off rejected. It was later determined that the aircraft’s left mainwheel had damaged a runway edge light. There were no injuries to the 34 passengers or 5 crew members and no damage to the aircraft.

The investigation found a number of factors that may have led to the captain not aligning the aircraft on the runway centreline for the take-off. Those factors included misinterpreting the normal runway cues, time pressure to depart, the weather conditions at Townsville Airport and the associated delays during the aircraft’s arrival, landing and departure.

ATSB investigation AO-2023-027

Between June 2023 and April 2024, 3 misaligned take-offs occurred at Perth Airport, Western Australia. Each occurred before first light and in all 3 incidents, when entering runway 06 from taxiway V, the pilots taxied past the turn onto the centreline and lined the aircraft up along the runway edge lighting on the far side of the runway to where they entered. The investigation found that, in each incident, the pilots believed they had correctly aligned the aircraft with the runway centreline, prior to taking off.  Several factors known to increase the risk of a misaligned take-off in the dark were identified from the investigation: 

  • In terms of the runway environment, there was an unlit and unmarked extended pavement area on each side of runway 06, which made the runway appear wider. 
  • In relation to the available airport lighting, the lead-on lights from the taxiway continued across the taxiway to the other side, meaning there was limited guidance when taxiing to the runway’s centreline. 
  • Recessed edge lights at the start of runway 06 could be mistaken for centreline lighting. 
  • There was limited ambient airport lighting around taxiway V and runway 06 to enhance visibility. 
  • The taxi lighting on one of the aircraft was reported by the pilots as being of limited benefit. 
  • The required runway markings were reported by 2 of the incident pilots to be difficult to see at night.

In one of the incidents, the flight crew’s attention was diverted to completing pre-take-off tasks and their take-off clearance while lining up on the runway. This divided their attention between the flight deck and the monitoring of the external environment.

Safety analysis

Diverted attention

The starter extension included a taxi guideline that curved around towards the extended centreline. The guideline was likely visible to the crew as the flight data showed that the aircraft was taxied along the line from the time it entered the starter extension bypass pad until the time it commenced the right turn to line up on runway 09. The captain reported that, although their intention was to use the full length of the extension, it was not required and due to the dark, ambient conditions, they did not want to continue that plan and risk exiting the pavement. As such, they turned the aircraft early. 

The flight crew reported that the ready checks were conducted while turning the aircraft to line up for departure. The Flight Crew Operating Manual stated that ready checks could be conducted at a time appropriate for the anticipated take-off. However, the manual did not provide any guidance as to when an appropriate time was during this process. Therefore, the decision was at crew discretion and dependent on the circumstances at the time. 

The FO and captain had predominantly focused their attention inside the flight deck while conducting the ready checks. The captain also reported becoming momentarily distracted looking out the side window. This was at a time when they would also be required to monitor the aircraft’s taxi path. The data showed that the aircraft was turned tightly to the right of the extended centreline and was no longer following the line markings for guidance.

Barshi and others (2009) discuss that it was easy for attention to become absorbed in one or more tasks, allowing another task to drop from awareness. Therefore, it can be concluded that, during the turn to line up, the flight crew's attention was diverted to completing the ready checks, likely reducing their monitoring of the aircraft position within the starter extension, and resulted in it being close to the edge of runway 09. This was consistent with the ATSB research report (2010), which discussed flight crews becoming focused on other tasks upon entering the runway or just prior to entering the runway, and that this was a frequently cited factor in misaligned take-off occurrences.

Misaligned take-off

Although not required for performance, using the starter extension allowed for additional take-off distance and a wider turn than was normally available at airports where the aircraft was mostly operated. However, as identified through ATSB research (2010) and related investigations, additional pavement on one or both sides of the runway has been known to provide erroneous visual cues for pilots. This potentially gives the impression that the additional pavement is part of the runway and that the runway is wider than it is.   

Then, following completion of the ready checks and when the aircraft neared completion of the turn to line up, the captain reported being drawn to a row of white lights, believing them to be centreline lights, even though such lights were not fitted to runway 09. With reduced visual cues available due to the dark conditions, a distinct visual indicator such as the white runway edge lights was likely to have been an influence in their belief that it was the runway centreline. Such dark ambient conditions have been consistently cited in the research and similar occurrences. The FO reported looking up but also believed the aircraft was correctly lined up, having associated their observation of the runway threshold markings as being in the correct position to line up.

However, imagery of runway 09 in similar conditions to the incident flight did show that the runway threshold lights, edge lights and right side precision approach path indicator lights would have been visible to the crew from their line‑up position. Confirmation bias is the tendency for people to seek information and cues that confirm their tentatively held hypothesis or belief (Wickens et al, 2022). As the flight crew believed they were correctly aligned with the runway centreline, they commenced the take-off roll.

Low pass

The flight crew noted no indications of a landing gear malfunction or failure, and the gear was retracted without issue following the misaligned take-off. They also received advice from the Mildura Airport aerodrome reporting officer that no aircraft parts or debris were identified along the runway. As the aircraft documentation did not provide guidance for such an incident, and to further assess the condition of the landing gear, the flight crew decided that a visual inspection via a low pass of the Melbourne Airport ATC tower was necessary. 

The flight crew did not contact QantasLink operations for assistance regarding the landing gear or the conduct of the low pass. This prevented QantasLink from providing input into the decision-making process. Further, while a visual inspection (using binoculars) by ATC from the tower may give a general assessment of the landing gear, it was not likely to have identified specific damage that would have otherwise been visible at close proximity during a ground inspection.

A flight at low altitude, and at a low speed with the landing gear and flaps extended may introduce a number of risks. Notably, the low pass was conducted lower than the briefed low pass height. As this was not a procedure within the operations manuals, there was no assurance that all potential risks had been identified and mitigated. 

Unauthorised/unsupervised use of prescription medication

Post‑incident drug and alcohol screening of the flight crew detected the presence of a medication, which the captain reported was not prescribed to them. The medication had been taken in the days prior to the incident flight, and although the substance was above the permitted threshold for detection, the results could not be used to assess any level of impairment. Independent analysis by a forensic pharmacologist indicated any effects from the medication could not be completely ruled out, however, impairment was not expected given the reported dosage and time elapsed.

The medication taken could only be dispensed with a prescription, and its consumer medicine information sheet highlighted this requirement and several cautions and potential side effects. Although it was a strictly controlled, commercially produced medication, the absence of medical supervision meant there was no assurance that the captain would not experience any adverse effects or impairment that may have impacted their ability to safely operate the aircraft.

Findings

ATSB investigation report findings focus on safety factors (that is, events and conditions that increase risk). Safety factors include ‘contributing factors’ and ‘other factors that increased risk’ (that is, factors that did not meet the definition of a contributing factor for this occurrence but were still considered important to include in the report for the purpose of increasing awareness and enhancing safety). In addition ‘other findings’ may be included to provide important information about topics other than safety factors. 

These findings should not be read as apportioning blame or liability to any particular organisation or individual.

From the evidence available, the following findings are made with respect to the misaligned take-off involving Bombardier DHC-8-315, VH-TQM, at Mildura Airport, Victoria, on 25 February 2025. 

Contributing factors

  • During line‑up, the aircraft was taxied off the starter extension guidance line and the flight crew’s attention was diverted to completing the ready checks. This likely reduced their monitoring of the aircraft's position within the starter extension and resulted in it being positioned close to the right edge of runway 09.
  • The flight crew commenced the take-off from a misaligned position resulting in damage to the aircraft and runway edge lights.

Other factors that increased risk

  • The flight crew conducted a low pass to facilitate a visual inspection of the landing gear by air traffic control. There were no supporting procedures for the low pass or visual inspection, nor did the flight crew contact the operator to seek assistance.
  • The presence of a prescription medication was detected in the captain's post‑incident drug and alcohol test that was not prescribed for them. While they were unlikely to have been impaired by the medication, there was no assurance that the captain would not experience any adverse effects or impairment that may have impacted their ability to safely operate the aircraft.

Safety actions

Whether or not the ATSB identifies safety issues in the course of an investigation, relevant organisations may proactively initiate safety action in order to reduce their safety risk. All of the directly involved parties are invited to provide submissions to this draft report. As part of that process, each organisation is asked to communicate what safety actions, if any, they have carried out to reduce the risk associated with this type of occurrences in the future. The ATSB has so far been advised of the following proactive safety action in response to this occurrence. 

Safety action by QantasLink

QantasLink advised the ATSB of the following safety actions:

  • Targeted human factors/non-technical skills training on the threat awareness of factors that have contributed to misaligned take-offs has been included in wider flight crew recurrent training.
  • Further information and a diagram was added to QantasLink operational documentation for Mildura Airport, specifically for the runway 09 starter extension to improve flight crew familiarity and situation awareness. 
  • Educational material regarding departure briefings and identifying relevant threats was included in various mediums available to flight crew.
  • A safety alert was issued to flight crew soon after the incident with a new policy that prohibits ‘ready checks’ being completed during runway end turns. This was incorporated permanently in the Flight Crew Operating Manual to ensure that during runway turns the flight crew’s attention was not divided externally between aircraft manoeuvring and internally on checklist completion.
  • A policy was introduced to outline the risks associated with an ATC tower fly past published in the operations manual and aligned with other operators in the Qantas Group.
  • A risk review was conducted on reduced sleep opportunity during overnights, fatigue reporting trends, risk controls and mitigators currently used in fatigue risk management.                                                                          

Sources and submissions

Sources of information

The sources of information during the investigation included:

  • the flight crew
  • the cabin crew
  • QantasLink
  • Civil Aviation Safety Authority
  • Airservices Australia
  • Bureau of Meteorology
  • Mildura Airport
  • recorded data from the aircraft
  • the consultant forensic pharmacologist. 

References

Australian Transport Safety Bureau. (2010). Factors influencing misaligned take-off occurrences at night, Australian Transport Safety Bureau, Australian Government.

Civil Aviation Safety Authority. (2024). Civil Aviation Safety Regulations 1998 Part 99- Drug and alcohol management plans and testing, Civil Aviation Safety Authority, Australian Government.

Civil Aviation Safety Authority. (2019). Part 139 Manual of Standards for Aerodromes, Civil Aviation Safety Authority, Australian Government.

Dawson, D., Sprajcer, M., & Thomas, M. (2021). How much sleep do you need? A comprehensive review of fatigue related impairment and the capacity to work or drive safely. Accident Analysis & Prevention, 151, 105955. doi: 10.1016/j.aap.2020.105955.

Goode J.H. (2003). Are pilots at risk of accidents due to fatigue?’ Journal of Safety Research, 34(3), 309–313. doi: 10.1016/s0022-4375(03)00033-1.

Dawson, D., Sprajcer, M., & Thomas, M. (2021). How much sleep do you need? A comprehensive review of fatigue related impairment and the capacity to work or drive safely. Accident Analysis & Prevention, 151, 105955. doi: 10.1016/j.aap.2020.105955.

Loukopoulos, L. D., Dismukes, R. K., & Barshi, I. (2009). The multitasking myth: Handling complexity in real-world operations. Routledge.

Submissions

Under section 26 of the Transport Safety Investigation Act 2003, the ATSB may provide a draft report, on a confidential basis, to any person whom the ATSB considers appropriate. That section allows a person receiving a draft report to make submissions to the ATSB about the draft report. 

A draft of this report was provided to the following directly involved parties:

  • flight crew
  • cabin crew
  • QantasLink
  • Civil Aviation Safety Authority
  • consultant forensic pharmacologist.

Submissions were received from:

  • the flight crew
  • QantasLink.

The submissions were reviewed and, where considered appropriate, the text of the report was amended accordingly.

Purpose of safety investigations

The objective of a safety investigation is to enhance transport safety. This is done through: 

  • identifying safety issues and facilitating safety action to address those issues
  • providing information about occurrences and their associated safety factors to facilitate learning within the transport industry.

It is not a function of the ATSB to apportion blame or provide a means for determining liability. At the same time, an investigation report must include factual material of sufficient weight to support the analysis and findings. At all times the ATSB endeavours to balance the use of material that could imply adverse comment with the need to properly explain what happened, and why, in a fair and unbiased manner. The ATSB does not investigate for the purpose of taking administrative, regulatory or criminal action.

About ATSB reports

ATSB investigation reports are organised with regard to international standards or instruments, as applicable, and with ATSB procedures and guidelines.

Reports must include factual material of sufficient weight to support the analysis and findings. At all times the ATSB endeavours to balance the use of material that could imply adverse comment with the need to properly explain what happened, and why, in a fair and unbiased manner.

An explanation of terminology used in ATSB investigation reports is available here. This includes terms such as occurrence, contributing factor, other factor that increased risk, and safety issue.

Publishing information

Released in accordance with section 25 of the Transport Safety Investigation Act 2003

Published by: Australian Transport Safety Bureau

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Footnotes

1Although the crew was scheduled for 3 sectors the following morning, the captain was only rostered to fly the first sector back to Melbourne.
2Pilot flying (PF) and pilot monitoring (PM): procedurally assigned roles with specifically assigned duties at specific stages of a flight. The PF does most of the flying, except in defined circumstances, such as planning for descent, approach and landing. The PM carries out support duties and monitors the PF’s actions and the aircraft’s flight path.
3Starter extension bypass pad: a runway starter extension may be established where additional take-off distance, take‑off run or accelerate-stop distance is required (Civil Aviation Safety Authority advisory circular AC 139.C-09 v1.0). It may also incorporate a bypass pad, which resembles a runway turn pad except that it is part of the runway starter extension and allows an aircraft to go around the declared end of the runway and runway end lights before turning around 180° to use the runway in a reciprocal direction.
4The flight data for the incident was downloaded by the operator and provided to the ATSB for analysis. The cockpit voice recorder was removed from the aircraft and downloaded by the ATSB. However, a combination of the 1 hour and 45-minute flight time and delays in the isolation of the recorder resulted in the incident flight being overwritten.
5The storm light is part of the flight deck lighting, which will illuminate the instrument panel when on.
6The 70 kt and V1 calls were procedural calls that served as a confirmation of the indicated airspeed (70 kt) and as a decision point for the flight crew. Below 70 kt, the take-off was to be rejected for any failure, malfunction or caution/warning light. Between 70 kt and V1, the take-off was to be rejected for a critical malfunction or malfunction that was deemed to make the aircraft not flyable. Above V1, the take-off was to be continued.
7Responses based on the Samn-Perelli 7-point scale which asks people to rate their fatigue at a point in time: 1 = fully alert, wide awake; 2 = very lively, responsive, but not at peak; 3 = okay, somewhat fresh; 4 = a little tired, less than fresh; 5 = moderately tired, let down; 6 = extremely tired, very difficult to concentrate; 7 = completely exhausted, unable to function effectively.
8Morning civil twilight or first light is defined as the instant in the morning when the centre of the Sun is at a depression angle of 6° below an ideal horizon. At this time in the absence of moonlight, artificial lighting or adverse atmospheric conditions, the illumination is such that large objects may be seen but no detail is discernible. The brightest stars and planets can be seen and for navigation purposes at sea, the sea horizon is clearly defined. Sunrise is defined as the instant in the morning under ideal meteorological conditions, with standard refraction of the Sun's rays, when the upper edge of the Sun's disk is coincident with an ideal horizon.
9Runway threshold lights: When viewed approaching the start of a runway, the threshold lights will be green, with red showing at the end of the runway.
10Precision approach path indicator: a ground based system that uses a system of coloured lights used by pilots to identify the correct glide path to the runway when conducting a visual approach.
11Visual meteorological conditions (VMC): an aviation flight category in which visual flight rules flight is permitted – that is, conditions in which pilots have sufficient visibility to fly the aircraft while maintaining visual separation from terrain and other aircraft.
12Instrument meteorological conditions (IMC): weather conditions that require pilots to fly primarily by reference to instruments, and therefore under instrument flight rules, rather than by outside visual reference. Typically, this means flying in cloud or limited visibility.

 

Occurrence summary

Investigation number AO-2025-008
Occurrence date 25/02/2025
Occurrence time and timezone 0636 EDT
Location Mildura Airport
State Victoria
Report release date 12/05/2026
Report status Final
Investigation level Short
Investigation type Occurrence Investigation
Investigation phase Final report: Dissemination
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Collision with terrain, Runway excursion
Occurrence class Serious Incident
Highest injury level None

Aircraft details

Manufacturer Bombardier Inc
Model DHC-8-315
Registration VH-TQM
Serial number 604
Aircraft operator Eastern Australia Airlines Pty Ltd operating as QantasLink
Sector Turboprop
Operation type Part 121 Air transport operations - larger aeroplanes
Activity Commercial air transport-Scheduled-Domestic
Departure point Mildura Airport, Victoria
Destination Melbourne Airport, Victoria
Injuries None
Damage Minor

Seat falling from helicopter involving a Bell 206L-1, 15 km west of Mitchell Plateau, Western Australia, on 27 August 2024

Occurrence Briefs are concise reports that detail the facts surrounding a transport safety occurrence, as received in the initial notification and any follow-up enquiries. They provide an opportunity to share safety messages in the absence of an investigation. Because occurrence briefs are not investigations under the Transport Safety Investigation Act 2003, the information in them is de-identified. 

What happened

On 27 August 2024, a Bell 206L-1 LongRanger helicopter with a single pilot on board was conducting a ferry flight with the doors removed, from Mitchell Falls campground to a coastal landing site on Nat Beach, Western Australia. 

The helicopter departed at 0615 local time and climbed to an altitude of 1,800 feet AMSL. During the flight, the seat located in the rear row on the right side fell out of the helicopter. The pilot was unaware that the seat had fallen out until after the helicopter landed at Nat Beach and the pilot was preparing to pick up the passengers for the next flight.

The seat did not impact the tail rotor or stabilisers and there was no damage to the helicopter.

The helicopter had finished a 100 hourly maintenance inspection the day prior to the incident flight. It then conducted a ferry flight to Mitchell Falls with the doors on. The doors were removed at Mitchell Falls campground and the seat base was lost on the next flight (Figure 1).

Figure 1: Missing seat after landing at Nat Beach

Figure 1: Missing seat after landing at Nat beach

Source: Operator  

The operator’s internal investigation revealed that the seat had been incorrectly installed prior to release from the 100 hourly inspection. During installation, the brackets on the seat were most likely not installed fully onto the locating pins before the securing pin was installed (Figure 2), or the brackets missed the securing pin (Figure 3). 

Figure 2: Incorrect installation – seat brackets not installed on locating pins

Figure 2: Incorrect installation – seat brackets not installed on locating pins

Source: Operator, annotated by the ATSB  

Figure 3: Incorrect installation – securing pin not fully engaged

Figure 3: Incorrect installation – securing pin not fully engaged

Source: Operator, annotated by the ATSB  

Safety action

The Head of maintenance briefed the engineer who completed the 100 hourly inspection and reiterated to all engineering staff during a toolbox meeting the necessity of ensuring proper seat installation. The helicopter was inspected by the maintenance team and no damage was found. The Fleet Service Manager raised an alert relative to this occurrence to remind both pilots and engineers on the seat installation instructions.

Safety message

The Bell 206L rear seats are not standardised and have several different ways that they may be secured. Personnel installing seats need to be vigilant in understanding and double‑checking that seats are installed correctly, which usually requires a close visual inspection and a pull on the seat to check security, as seemingly minor tasks in nature can have a substantial impact. 

Pilots accepting aircraft from maintenance should conduct a particularly thorough pre-flight inspection. Errors in maintenance can and do occur, and that first pre-flight inspection is a critical part in capturing those errors.

About this report

Decisions regarding whether to conduct an investigation, and the scope of an investigation, are based on many factors, including the level of safety benefit likely to be obtained from an investigation. For this occurrence, no investigation has been conducted and the ATSB did not verify the accuracy of the information. A brief description has been written using information supplied in the notification and any follow-up information in order to produce a short summary report, and allow for greater industry awareness of potential safety issues and possible safety actions.

Occurrence summary

Mode of transport Aviation
Occurrence ID AB-2024-037
Occurrence date 27/08/2024
Location 15 km west of Mitchell Plateau
State Western Australia
Occurrence class Serious Incident
Aviation occurrence category Objects falling from aircraft
Highest injury level None
Brief release date 26/02/2025

Aircraft details

Manufacturer Bell Helicopter Co
Model 206L-1
Sector Helicopter
Operation type Part 133 Air transport operations - rotorcraft
Departure point Mitchell Falls, WA
Destination Nat Beach, WA
Damage Nil

Ferry flight ditching inevitable after engine failure

The ditching of a twin-engine Cessna 53 km off the coast of Queensland after one of its engines failed was inevitable due to the weight of the aircraft and the failed engine’s propeller not being able to be feathered, an ATSB investigation report details.

The twin piston-engine Cessna 421C, with two pilots on board, had departed Sunshine Coast Airport on the first leg of a transpacific ferry flight to the United States early on the morning of 10 November 2023. The aircraft had been fitted with additional fuel tanks to extend its endurance, including a large (1,134 litre) bladder tank in the main cabin, and a smaller (132 litre) tank in the nose locker.  A special permit had been issued to allow the aircraft to conduct the ferry flight exceeding its certified maximum take-off weight.

When about 250 km offshore and climbing through 12,000 ft the pilots heard a muffled bang as the left engine failed. Oil was observed streaming from the engine and a large bulge had developed in the cowling. 

Due to the nature of the engine failure the propeller would not fully feather, meaning it windmilled, creating excessive drag.

After turning back, the pilots identified that the aircraft could not maintain altitude and they calculated based on their rate of descent that they would be unable to reach the Sunshine Coast. 

“The drag from the propeller combined with the weight of the fuel onboard meant a ditching was unavoidable as the aircraft was unable to maintain altitude on one engine,” explained ATSB Director Transport Safety Dr Stuart Godley. 

The pilots notified air traffic control of their intention to ditch, with ATC in turn alerting the Joint Rescue Coordination Centre (operated by the Australian Maritime Safety Agency), which immediately began coordinating a search and rescue response.

“The pilots’ chances of surviving the ditching were enhanced by their early liaison with air traffic control and their preparation of the aircraft during its descent,” Dr Godley noted.

The aircraft was ditched in the open ocean about 53 km off the coast, with the pilots configuring the aircraft to avoid a nose down attitude on touchdown and allowing their airspeed to slow before the aircraft contacted the water.

“The pilots reported the aircraft initially skimmed the crest of a wave before it rapidly decelerated when the nose pitched into the water,” Dr Godley said.

The pilots deployed a life raft from the rear cabin before exiting the aircraft. The first of two inbound rescue helicopters arrived overhead shortly after, and winched them to safety. The aircraft sank and was not recovered.

“Impact forces during the ditching were minimised by the pilots ensuring the descent and airspeeds were managed prior to their contact with the water.”

The investigation also found that the pilots did not hold the required licence ratings and approvals to conduct the flight, and that the aircraft was not compliant with the special ferry flight permit conditions. 

“However, while these factors did remove important safety defences, they did not contribute to the engine failure and the need to conduct the ditching,” Dr Godley noted.

“Nonetheless, operating outside of aviation regulations removes built-in safety defences, increasing the likelihood that undetected problems can emerge.” 

Read the final report: Ditching involving Cessna 421C, VH-VPY, 53 km east of Sunshine Coast Airport, Queensland, on 10 November 2023

Metro hangar collision

Following an in-flight hydraulics failure a Metro aircraft had a low-speed collision with a hangar at Perth Airport after the captain elected to taxi to the apron after mistakenly assessing that the brakes were functioning.

An ATSB investigation report details that on the morning of 12 August 2024, the Skippers Aviation Fairchild Metro 23 twin-turboprop was being operated on a charter flight from Forrestania, in Western Australia’s Wheatbelt region, to Perth, with two flight crew and four passengers on board.

The first officer was completing supervised line flying and was pilot flying. The captain was pilot monitoring.

Near the top of the planned descent into Perth, the aircraft sustained a complete loss of hydraulic system pressure.

The crew entered a holding pattern to determine the appropriate speed and extra distance required to conduct a flapless landing at Perth, and for the captain to instruct the first officer on how to conduct a manual extension of the landing gear using the hand pump.

“The captain advised air traffic control that a tow vehicle would be required to get the aircraft from the runway to the apron,” ATSB Director Transport Safety Dr Stuart Godley noted.

The captain then took over as pilot flying due to the first officer’s limited experience, and conducted an uneventful flapless landing on Perth’s runway 24.

“After landing, the captain could not see or establish direct communication with the requested tow vehicle,” Dr Godley explained. “Finding some brake pressure evident, the captain opted to taxi to the apron.”

As the aircraft approached the hangar, its speed increased due to a slight downhill gradient, and braking was ineffective.

“Aiming to avoid a collision, the captain momentarily used reverse thrust, but then shut down the engines and feathered the propellers before the aircraft’s right wingtip, and then propeller, collided with the hangar at a low speed,” Dr Godley said.

The aircraft came to a rest and all occupants then disembarked safely.

The investigation report notes that the first officer was a cadet in training with 325 hours total flying experience, and about 34 hours on type.

“Consistent with this minimal experience, the first officer’s ability to contribute to the in-flight emergency management was limited,” Dr Godley explained.

“This meant the captain was required to manage the emergency, effectively taking on both the pilot flying and pilot monitoring roles, and reducing their ability to manage the emergency effectively.”

After stopping on the taxiway after landing, the captain mistakenly assumed the brakes were functioning, after noting some braking pressure was evident.

“Unable to locate or contact the tow tug, and influenced by self-imposed time pressure, the captain chose to taxi to the apron, and the minimal available braking capacity meant the crew was unable to stop the aircraft.”

The investigation found the hydraulic failure occurred when a crack in a hydraulic line led to a hydraulic fluid leak.

Dr Godley noted that the investigation highlights the necessity for accurately assessing system functionality following an in-flight failure and the need to follow standard operating procedures. 

“Vigilance when assessing aircraft performance and an objective assessment of system status are vital to minimise opportunities for error and avoid relying on potentially misleading indicators,” he said. 

“This incident highlights the importance of prioritising procedural compliance in uncertain circumstances, especially when experiencing perceived pressure in non-normal situations.”

Read the final report: Hydraulics system failure involving Fairchild SA227-DC, VH-WAJ, at Perth Airport, Western Australia, on 12 August 2024

Ground proximity alerts involving Sikorsky S-92A, VH-IPE, 71 km north-north-west of Exmouth Aerodrome, Western Australia, on 1 February 2025

Final report

Report release date: 04/02/2026

Investigation summary

What happened

On 1 February 2025, a Sikorsky S‑92A helicopter operated by PHI International Australia, departed Exmouth Aerodrome, Western Australia, to conduct night recency flights, including landings and take-offs, at an off-shore drill rig for the 3 crew on board. They departed for the Transocean Endurance drill rig, about 71 km north-north-west of Exmouth Aerodrome.

During the cruise, the copilot was rushed to complete the calculations of the helicopter’s take-off safety speed, a requirement to complete the approach briefing. Unsure of the accuracy of the calculation the crew agreed to use an estimated take-off safety speed and commenced the descent.

At about 1,500 ft, the copilot set the radar altitude hold mode to the circuit height of 660 ft to allow the helicopter’s automation to descend to, and level at, the preset circuit height.

Assuming the helicopter had levelled at the preset circuit height of 660 ft, the captain requested the copilot to check the accuracy of their earlier take-off safety speed estimate, which required the copilot to use the electronic flight bag. At about the same time, the captain elected to activate the helicopter’s moveable searchlight and shifted their focus outside to adjust the position of the searchlight beam. 

Unnoticed by the crew, the helicopter continued to descend and, at about 220 ft above the ocean surface, the enhanced ground proximity warning system indicated a terrain caution alert, followed about 4 seconds later by a terrain warning as the aircraft descended through 181 ft. The crew responded to the warning and initiated a climb, the helicopter descended to its lowest point of 152 ft above the water, before climbing away. 

What the ATSB found

Both flight crew members had limited experience on the helicopter type at night. The combination of this limited experience and a shorter than normal sector, which reduced the time to plan the approach, resulted in them experiencing a higher than normal workload.

As the helicopter descended through about 1,200 ft, the captain inadvertently mis‑selected the vertical speed mode while attempting to select the helicopter’s autopilot heading hold mode. The mode selection error was not recognised by either flight crew member. The selection cancelled an automation mode that would have levelled the helicopter at a preset circuit height, and instead activated a mode that set up a continuous 500 ft per minute descent until the crew reacted to the EGPWS alerts.

The flight crew had been unable to accurately determine the take-off safety speed prior to their descent for landing. While in the circuit area, the captain requested the copilot calculate the speed, which increased workload and focused them away from their monitoring duties.

While in the circuit area, both flight crew members were preoccupied with additional tasks and therefore not monitoring the helicopter’s altitude as it continued to descend below the preset circuit height until the flight crew reacted to the automated terrain alert.

The operator’s pre-flight operational risk assessment completed by the flight crew did not capture the risks of the flight crew’s limited experience on type at night.

What has been done as a result

PHI International Australia advised that procedural improvements have been implemented, including:

  • All initial approaches during night flights to be conducted as an instrument approach, which ensures a more structured process with procedural barriers.
  • Night recency flights not to be conducted on a first flight back following any pilots’ period of leave.
  • Radar altimeter alert to be set at 500 ft.

PHI International Australia also increased the risk loading on its operational risk assessment for pilots with less than 500 hours on type. Night flights with both pilots with less than 500 hours on type at night now require discussion with the senior base pilot regarding the additional risks relating to inexperience on type.

Learnings from this occurrence have been shared and promoted both internally and externally. These efforts included an internal safety alert and a ‘learning from occurrence’ video detailing what happened and why to the international community through industry body HeliOffshore.

The S‑92A cockpit lighting environment was reviewed by the operator with subject matter experts to consider if an engineered improvement was practicable. A procedural change was implemented by PHI International Australia that required the use of small lights that are worn on the pilot’s fingers to improve visibility of the cockpit environment (such as switches, buttons, and controls) during S‑92A night flights.

Operational procedures regarding multi-crew cooperation, automation mode changes/awareness, and EGPWS alerts were highlighted to all flight crews through internal communications. These points were also highlighted within the training and competency teams as focus areas during both simulator and line training sessions.

Safety message

The incident highlights the importance of disciplined and effective multi-crew cooperation. A deviation by flight crew from operational processes may lead to unrecognised errors and undesired aircraft states. Flight crew are reminded of the risks associated with divided attention in the cockpit and the potential serious consequences of an unmonitored aircraft. Operators are advised to review their guidance on flight crew preoccupation.

All operators of Sikorsky S‑92A helicopters are advised of the potential hazard that exists with differing display versions of the automatic flight control system mode select panel. Due to the lighting design of the panel, distinguishing between hard and soft keys is more difficult at night. More recent versions of the mode select panel include a tactile white finger barrier installed between the rows of hard and soft keys which reduce but do not eliminate the risk of a mode selection error.

 

The occurrence

On the evening of 1 February 2025, a Sikorsky S‑92A helicopter operated by PHI International Australia and registered VH-IPE, departed Exmouth Aerodrome, Western Australia, to drilling rig Transocean Endurance, located about 38 NM (71 km) to the north‑north-west of Exmouth Aerodrome. On board were 3 crew conducting a night recency flight, the captain was the pilot flying (PF), in the right seat and the copilot was the pilot monitoring (PM)[1] in the left seat. The third pilot was seated in a passenger seat in the main cabin of the helicopter.[2]

The helicopter departed Exmouth at about 1918 local time, with last light occurring at 1933. The purpose of the flight was for each pilot to conduct 3 take-offs and landings so the crew would remain current in case of a night medical emergency evacuation from an offshore drilling rig. The operator routinely used offshore rigs for night recency flights so pilots remained familiar with night helideck landings. 

Cruise

On board flight data indicated that following the departure from Exmouth, the helicopter reached the top of climb height of 4,000 ft at 1924 and maintained the cruise altitude for about 9 minutes. During that time the PM completed flight administration tasks that included:

  • communication with Melbourne Centre air traffic control (ATC)
  • conduct of the cruise checklist
  • entering the flight log details with ETA to the rig
  • calculation of top of descent
  • communication with the drill rig to confirm weather and deck status
  • conduct of the descent checklist.

On receiving the updated weather information from the rig, the PM intended to calculate the take-off safety speed (Vtoss) for landing. Vtoss is used by the operator as a minimum target speed in the event that one engine became inoperable during the approach to land. The target airspeed is set on the airspeed indicator with a marker bug for the crew to use as a reference, and is required to be set as part of the approach briefing (see Take‑off safety speed (Vtoss)).

The PM recalled that while trying to obtain the predicted gross landing weight from the onboard flight management system, they had difficulty obtaining an accurate figure. This delayed the input of the weight into the Sikorsky performance application. The PM later reported the process was rushed, and as a result was unsure of the accuracy of the calculated Vtoss for landing prior to the top of descent. 

To allow the crew to complete the descent checklist, the PM later reported that the crew agreed to use 45 kt, based on their previous experience in the S‑92A, with the intention of recalculating the speed when time permitted.

Descent

At about 1933 and 11 NM (20 km) south-east of the drill rig and now in darkness (see Meteorological information), the helicopter began a descent to the lowest safe altitude of 1,500 ft (Figure 1). At 1937, the PF requested the PM to engage the radar altimeter (RADALT) hold mode and lower the target altitude capture height to the 660 ft circuit height. This was confirmed by the PM and the helicopter commenced a further descent to the drill rig circuit height. Both flight crew later recalled completing the before landing checklist during the descent.

Figure 1: VH-IPE flight track 

VH-IPE flight track from Exmouth to drill rig Transocean Endurance

Source: Google Earth, annotated by the ATSB

At 1938:21 and about 1,235 ft, during the descent for a visual approach to the rig (Figure 2), the PF attempted to select the heading mode on the automatic flight control system (AFCS) mode select panel to adjust the heading and avoid flying directly over the rig. 

While attempting to press the heading mode button, the PF inadvertently and unknowingly selected the vertical speed button which was directly below it.

The inadvertent selection of the vertical speed hold mode captured the helicopter’s 500 ft per minute rate of descent, and cancelled the RADALT hold mode that would have levelled the helicopter at a preset circuit height of 660 ft above sea level. 

The PF noticed the heading button on the AFCS panel was not lit, indicating it was not engaged and presumed the original selection had not registered on the first attempt and reselected the heading mode key. Heading hold mode was engaged at 1938:24, at about 1,200 ft. The PF later recalled confirming the selection with the PM.

During interviews conducted with the ATSB following the occurrence, both flight crew reported they believed their total time and time at night flying the S‑92A likely affected their familiarity with the cockpit and efficiency completing administrative tasks. 

Figure 2: VH-IPE flight track from 1,500 ft

VH-IPE flight track showing the descent from 1,500 ft

Source: Google Earth, annotated by the ATSB

Circuit

At 1939:00, the helicopter joined a crosswind leg to conduct a right circuit to the rig. This was so the PF could keep the rig visible from their side of the helicopter. While on the crosswind leg, the PM’s radio was keyed several times (see Recorded information). During this time, both crew were unaware that the helicopter had continued descent through the preset circuit height of 660 ft.

At 1939:46 and about 500 ft, the PF commenced a turn onto the downwind leg of the circuit and later stated they were certain the helicopter had levelled at the circuit height. The PF then requested the PM to check the Vtoss for landing, later stating that they thought the estimated speed was too high. This required the PM to use the electronic flight bag (EFB). During an interview the PF recalled at this point they also began to manoeuvre the helicopter searchlight which required them to visually identify that the beam was in the desired direction. The PF later reported they had difficulty finding the searchlight beam due to reflection on the water from the well-lit rig, and therefore setting the beam in the right position took longer than expected.

At 1940:17 and 221 ft, the crew received an EGPWS terrain caution alert and at 1940:21 and 181 ft, this was followed by a terrain warning alert. The crew reacted to the alerts and initiated an emergency climb to the minimum safe altitude of 1,500 ft. At 1940:25, recorded data showed the helicopter had descended as low as 152 ft above the ocean before increasing altitude. 

Debrief and continued operations

When the helicopter had reached the minimum safe altitude, the crew discussed the incident and believed that they had identified that the unintended descent was a result of the PF accidently adjusting the RADALT target height as the trim switch is located in close proximity to the searchlight slew toggle on the collective[3] control lever.

The crew agreed they were comfortable to continue with the planned night recency flights and the helicopter landed on the helideck of the rig at 1949.

The 3 crew each completed the 3 required night take-offs and landings from the rig and then returned to Exmouth without incident, landing at 2208.

Context

Personnel information

Captain

The captain held an Air Transport Pilot Licence (Helicopter), issued on 23 June 1995 and a class 1 aviation medical that was valid until 20 June 2025. They had accumulated about 10,240 hours total aeronautical experience, of which 1,100 hours were at night and about 3,530 total hours in multi-engine helicopters. The captain also held an instrument rating valid until 31 May 2026.

The captain joined PHI International Australia (previously Helicopters New Zealand) in 2014 and had operated from its Karratha, Western Australia base, flying AW 109 helicopters for marine pilot transfer operations.

The captain completed crew resource management (CRM) training as part of their operator conversion course for the S‑92A on 31 December 2023 and the CRM command training on 22 August 2024.

The captain had held a command position on the S‑92A with the operator since 8 October 2024 and had accumulated 77 command hours on type. They had previously flown the S‑92A as copilot and were checked to line in that position on 19 July 2024. At the time of the incident, the captain had accumulated 299 hours on type of which 13 hours were at night. The captain’s night hours were a combination of simulator assessments and their initial 5‑night helideck landings which was a minimum requirement for newly type rated flight crew.  

The captain had last flown at night during an operational proficiency check flight in a simulator on 8 November 2024 and had completed their initial 5-night helideck landings as required by the operator to be rostered for night standby duty on 2 November 2024 while under supervision.

The captain had been rostered on night standby 5 times during their previous roster period, however had not been required to fly. 

The occurrence flight was the captain’s first flight following 4 weeks off duty.

Copilot

The copilot held a commercial pilot licence (helicopter), issued on 20 August 2010 and a class 1 aviation medical valid until 6 June, 2025. The copilot’s total aeronautical experience was about 5,360 hours of which 1,240 were at night and about 2,390 total hours in multi-engine helicopters. The copilot held an instrument rating valid to 31 August 2025.

The copilot joined PHI International Australia in 2023 and had initially flown for the operator from their Karratha, Western Australia base flying the AW 109 for marine pilot transfer operations.

They had completed CRM training as part of their operator conversion course for the S‑92A on 11 November 2024. They were checked to line on the S‑92A on 29 November 2024 and had accumulated a total of 224 hours as copilot, of which 9 hours were at night at the time of the incident.

The copilot had last flown at night on 14 December 2024 during their initial night helideck landings under supervision.

The copilot was rostered for standby night duty 7 times during their previous roster period and also had not been required to fly at night before the occurrence flight.

The copilot began their rostered-on period on 17 January 2025 and had flown 3.6 hours the day prior to the occurrence flight.

Fatigue

The captain recently completed 4 weeks off duty and had travelled from their home in New Zealand to Perth 2 days prior to the occurrence and from Perth to Exmouth the day prior to the occurrence. The captain began their duty period at about 1715 on the afternoon of the occurrence and reported they felt well rested prior to the flight.

The captain reported that they had slept about 9 hours in the last 24 hours and had been awake for 13 hours but reported feeling lively and responsive at the time of the occurrence.

The copilot had commenced an online training course between 0800 and 1430 that day from their accommodation. They stated that they took the opportunity for a lay down to rest for an hour and eat following the course before commencing the second duty period at 1715 and stated they felt fine before the flight.

The copilot reported they had about 8 hours sleep in the last 24 hours and reported feeling okay and somewhat fresh at the time of the occurrence.

The ATSB considered that fatigue was not likely at a level that adversely affected the performance of either pilot.

Aircraft information

General information

The Sikorsky S‑92A is a 2 crew, twin-engine helicopter with a maximum take-off weight of 12,020 kg. With a capacity of 19 passengers it is commonly used for offshore oil and gas industry passenger transport. The S‑92A is powered by twin General Electric CT7‑8A turboshaft engines, producing 1,737 kW during maximum continuous power. The engines power a fully articulated 4-bladed main rotor system. 

VH-IPE was manufactured in the United States in 2006 as serial number 920038 and was first registered in Australia in April 2017 by PHI International Australia (then Helicopters New Zealand).

Automation

The rotorcraft flight manual for the S‑92A provided a description of the automatic flight control system:

The Automatic Flight Control System (AFCS) electronically enhances basic aircraft handling qualities through a trim system, Stability Augmentation System (SAS), Attitude Hold (ATT) features, and Coupled Flight Director (CFD). The AFCS is dual redundant in all features except trim actuators. It is controlled via a single AFCS control panel located on the center console and two mode select panels located on each side of the instrument panel. Cyclic and collective switches plus main flight display bezel keys are also used to control the AFCS. The core of the AFCS consists of two separate and identical Flight Control Computers (FCC) which receive data from various aircraft sensors. AFCS control inputs are enabled via electrically powered trim actuators and hydraulically powered SAS servos.

Coupled flight director

The CFD utilised trim actuators to maintain the helicopter on a pilot selected flight path. The following features (Table 1) are available through the CFD.

Table 1: CFD features

  • airspeed hold
  • VOR navigation
  • altitude hold
  • VOR approach 
  • heading hold
  • FMS navigation 
  • radar altitude hold 
  • FMS approach 
  • vertical speed
  • ILS approach 
  • altitude preselect
  • localiser back course approach
  • go around
  • pseudo ILS approach
Mode select panel

Two AFCS mode select panels were located on the lower middle section of the helicopter instrument panel (Figure 3). The rotorcraft flight manual described the mode select panel (MSP) functions: 

Coupled modes are selected by pressing the appropriate keys on the active MSP. There are four hard keys on top of each MSP. These hard keys allow the pilot to select or deselect the three basic autopilot modes of airspeed, altitude and heading hold. The function of these hard keys does not change. When any of these hard keys are pressed on the active MSP the aircraft will immediately couple the selected parameter and the hard key will light. The standby hard key on the active MSP and the standby button on either cyclic stick will always deselect all flight director functions and decouple the aircraft. Hard keys along the bottom of the MSP allow the pilot to choose CRUISE, APPROACH or TEST menus. The centre display area of the MSP is surrounded by soft keys whose function will change depending on the menu selected. Once a soft key is pressed the mode goes to ARM, CAPTURE or ON. ARM is displayed in white signifying that control inputs are not being made based on this mode. CAPTURE or ON is displayed in green signifying that the mode is now controlling that portion of the CFD.

Figure 3: Sikorsky S‑92A cockpit

Sikorsky S92A cockpit showing the Captain and copilots PFDs and AFCS mode select panel

Source: Vertical, annotated by the ATSB (occurrence aircraft not depicted)

The manufacturer advised that from aircraft serial number 920057 (built after VH-IPE), the mode select panel was upgraded to incorporate 2 white coloured finger barriers above and below the display screen between the rows of hard and soft keys (Figure 4). The barrier protruded higher than the height of both the soft and hard keys and gave pilots tactile feedback on finger position in relation to the rows of hard and soft keys. The manufacturer advised that the design change was likely due to customer feedback regarding the panel.

Figure 4: Sikorsky S‑92A mode select panels

Image showing the original and revised mode select panels highlighting the raised white finger barrier on the revised mode select panel.

Source: Lockheed Martin, annotated by the ATSB

VH-IPE featured an MSP without the white finger barriers on the left copilot side of the cockpit but with the revised MSP with the finger barriers on the captain’s right side. In this occurrence, the mis-selection of button below the finger barrier was done by the captain as the pilot flying.

The maintenance manual for the S‑92A advised that it was acceptable to mix versions of the mode select panel within the same helicopter, stating:

It is acceptable to mix and match mode select panels dashes 92900‑01812‑104, 92900‑01812‑105, 92900‑01812‑106, 92900‑01812‑110

Mode select panels 92900-01812-112 can be installed as a replacement unit but is not interchangeable with any other mode select panel part number. The mode select panel 92902‑01812‑112 must be installed in pairs with another 92900‑01812‑112

Mode select panel lighting and display

The top row of hard keys, which included the heading key, were not back lit when the relevant modes were not engaged (Figure 5). The manufacturer identified that the lower row of hard keys featured a lit border on the individual key as those keys were menu keys and changed the function of the lower row of soft keys. The white finger barrier (when installed) separating the hard and soft keys did not illuminate.

Figure 5: Sikorsky S‑92A mode select panel at night

Image shows the mode select panel at night

Source: PHI International Australia, annotated by the ATSB

Automation modes controlled by the top row of soft keys were displayed with an ‘ON’ symbol on the MSP display screen below the relevant key. There was no change in colour or lighting to the soft key itself when selected. Active automation modes captured on the AFCS MSP were also displayed on the flight crew’s primary flight display (PFD) (Figure 6).

Figure 6: Sikorsky S‑92A primary flight display

Primary flight display showing the pitch, roll and collective indication and with the same modes engaged on the mode select panel

Source: Lockheed Martin, amended and annotated by the ATSB

Primary flight display indications

The letters P (Pitch), R (Roll), and C (Collective) are displayed at the top of each PFD. These letters correspond to the autopilot axis controlling each CFD mode. 

  • if the helicopter is coupled so that the pitch axis is controlling altitude, ALT is displayed next to the P
  • if the helicopter is coupled so that the pitch axis is controlling airspeed and the collective axis is controlling altitude, IAS is displayed next to the P and ALT is displayed next to the C.

Modes that are captured ‘ON’, are displayed on the PFD in green letters signifying that the mode is now controlling that portion of the CFD. Modes that are armed, but not yet captured, are displayed in white letters signifying that control inputs are not being made based on this mode.

The system does not provide audible tones or display alerts when a mode is changed or immediately captured.

The PM stated that the PFD was used to confirm that the correct automation modes had been engaged.

Radar altitude hold

The RADALT hold is engaged using the corresponding soft key on the AFCS MSP. 

The RADALT will capture the reference radar altitude height which is displayed on the PFD. The S‑92A rotorcraft flight manual states that a pilot can adjust the reference height using the following methods:

Depress and hold the collective trim release, manually fly the aircraft to the desired altitude and release the trim button, or

Use the collective trim beeper to beep to the selected altitude. When increasing radar altitude with the collective beep switch, the aircraft will climb at a maximum of 500 fpm. When decreasing radar altitude with the collective beep switch, aircraft descent rate is predicated on the current radar altitude. When above 500 feet AGL, the aircraft will descend at a maximum of 500 fpm. As the aircraft descends below 500 feet, the descent rate will decrease linearly so that the maximum descent rate at 200 feet AGL and below is 200 fpm.

RADALT mode was engaged to descend the helicopter from 1,500 ft and the PM adjusted the target altitude to the circuit height of 660 ft. The flight crew confirmed the target altitude and the helicopter commenced a descent.

Vertical speed mode

The engagement of the vertical speed (VS) mode will capture the aircraft’s current rate of climb or descent. When the VS mode is engaged, the MSP display will indicate a green ‘ON’ symbol below the VS display. The collective axis display on the PFD would display ‘VS’ to indicate vertical speed mode is now controlling the collective axis and the rate of climb or descent will be displayed on the vertical speed indicator on the PFD.

Heading mode

The heading mode is engaged by selecting the heading button on the AFCS MSP and will immediately turn the helicopter to the reference heading. When engaged the reference heading is adjusted by turning the heading knob on the remote instrument controller or by the lateral beeper switch located on the cyclic control to adjust the heading left or right from the helicopter’s current track.

As the helicopter approached the drill rig using a lateral navigation mode, the captain reported that they engaged the heading mode to cancel the navigation and then adjusted the helicopter track so to avoid flying directly over the top of the rig.

EGPWS

The Honeywell MKII enhanced ground proximity warning system (EGPWS) was installed on the S‑92A helicopter.

The EGPWS purpose is to provide an audio and visual alert to crew when terrain or obstacle clearance is not assured. 

The S‑92A rotorcraft flight manual contained the following system description:

The EGPWS computer receives inputs from aircraft sensors to include radar altitude, barometric altitude, airspeed, vertical speed, pitch and roll attitude, magnetic heading, temperature, navigational radios, and FMS GPS. These inputs are combined with internal terrain and obstacle databases to predict when the aircraft will impact terrain or an obstacle. The system is designed to provide a warning to the pilot in sufficient time to take corrective action to prevent CFIT (controlled flight into terrain) while avoiding unnecessary false alarms.

The EGPWS had numerous modes for different stages of flight. The ‘look ahead’ mode used helicopter sensors to determine the helicopter flight path. It compared the helicopter predicted position to the terrain and obstacle database to look for conflicting terrain or obstacles. When the helicopter is approximately 30 seconds from impact with terrain or obstacles, a caution will be given. When the helicopter is approximately 20 seconds from impact, a warning will be given. The pilot will see and hear the caution or warning until the helicopter is manoeuvred away from the hazard (Figure 7).

Look ahead cautions: CAUTION TERRAIN, CAUTION TERRAIN or CAUTION OBSTACLE, CAUTION OBSTACLE aural alert every seven seconds

Look ahead warnings: WARNING TERRAIN or WARNING OBSTACLE continuous aural alert.

The flight crew received a terrain caution alert as the helicopter descended through about 220 ft followed by a terrain warning alert at about 180 ft AGL.

Figure 7: EGPWS look ahead mode

Image from the S92A rotorcraft flight manual illustrating the terrain caution and warning alerts

Source: Lockheed Martin, annotated by the ATSB

External lighting

Two 450-watt landing lights were located under the nose of the helicopter. The lights were controlled by the switches located on the exterior light control panel in the cockpit.

In addition to the landing lights, another 450-watt controllable searchlight was located under the right-side nose of the helicopter and was coupled with a directional searchlight control located on the collective controls. The searchlight ON/OFF/STOW switch on the collective moved the light from its stowed position to its operating position and turned the light on. The searchlight can be moved forward through a 120° arc from the stow position. The searchlight slew switch allowed rotation of the light through 360°.

The operator’s before landing checklist required the landing lights to be selected ‘On’, although there was no requirement for the use of the searchlight for landing in the operator’s checklists.

The PF reported that the use of the searchlight was, in the event of a water ditching, to assist the flight crew to visually identify the water’s surface and therefore time control inputs to assist in managing the ditching. 

Take‑off safety speed (Vtoss)

The pilot monitoring was required to calculate Vtoss using the Sikorsky performance application on the EFB. The calculation required the input of:

  • pressure altitude[4]
  • outside air temperature
  • gross weight of the helicopter for landing.

The operator’s flight crew operating manual stated that for normal landings:

The airspeed bug should be set at Vtoss/Vblss[5] for all landings. This is so that the crew have a reference speed to accelerate to, and remain above, in the event of engine failure.

Meteorological information 

Bureau of Meteorology

The aerodrome forecast (TAF)[6] for Learmonth, about 22 km south of Exmouth, was issued at 1317 and valid between 1400 on 1 February and 1400 on 2 February 2025. The forecast wind after 1700 was from 260° at about 14 kt with a slight directional change after 20000 to 240˚at about 10 kt with CAVOK[7] conditions. The temperature was forecast at 32˚ with a QNH[8] of 1003.

Transocean Endurance weather

A weather report obtained prior to departure for the Transocean Endurance, and valid at 1750, indicated:

  • wind 241°/ 07 kt
  • visibility 15,000 m
  • QNH 1001
  • temperature 30°C
  • dewpoint 30°C
  • cloud 0/8 okta[9]
  • present weather – fine.
Last light

Sunset was recorded as 1909 and last light at 1933, with the end of nautical twilight recorded at 2001 at Exmouth. 

The crew reported that some residual terrestrial light remained as they approached the rig and allowed them to see the ocean and recalled the wind conditions to be calm with no white caps.

Airport information

The drill rig Transocean Endurance is described as a harsh environment semi‑submersible vessel accommodating up to 130 people (Figure 8). The dimensions of the rig were 116 m x 97 m and had an obstacle height of 343 ft.

The helideck height was 109 ft above the ocean surface and approved to accommodate the S‑92A helicopter. 

The operator’s helideck approach guidance indicated a 1,500 ft height for minimum safe altitude above the rig and that the circuit height was 660 ft above mean sea level.

The rig was located 38 NM (71 km) north‑north-west of Exmouth Aerodrome and was being used for the night recency flight due to its proximity.

Figure 8: Drilling rig Transocean Endurance

Drilling rig Transocean Endurance

Source: PHI International Australia Pty Ltd

Recorded information

On board recorded data from the flight data monitoring system was obtained and analysed by the ATSB for the occurrence. 

Autopilot mode selection

Following the descent from 4,000 ft, the crew continued descent to the minimum safe altitude height of 1,500 ft in the vicinity of the rig.

  • At about 1937:25, while the helicopter maintained 1,500 ft, the PM selected the RADALT hold mode on
  • 55 seconds later the vertical speed mode was selected, simultaneously RADALT mode automatically disengaged.
Heading adjustments

During the descent from 1,500 ft: 

  • At 1938:24, 3.3 seconds after the engagement of vertical speed mode, the heading mode was shown to be engaged at about 1,170 ft (Figure 9).
  • At 1938:32, the helicopter heading was adjusted from 348° to 333°.
  • The flight track was adjusted to the left and the helicopter passed to the south-west of the drilling rig.
  • At 1939:46, as the helicopter descended through about 510 ft, the helicopter heading was again adjusted from 345° to 065° and the helicopter commenced a turn onto the downwind leg of a right circuit to the drilling rig helideck.

Figure 9: VH-IPE flight data

A graph of data recorded onboard the occurrence aircraft.

Source: ATSB

Pilot monitoring radio keying

At 1939:10, when the helicopter was recorded descending through about 810 ft on the crosswind leg[10] of the circuit the PM’s radio was keyed for a 6‑second period. At 1939:27, and about 675 ft, the PM’s radio was again keyed for a duration of 9 seconds and at 1939:43 a further 1‑second radio key when the helicopter descended through 526 ft.

EGPWS terrain alerts

At 1940:17 as the helicopter descended through 221 ft on the downwind leg[11] of the circuit the EGPWS terrain caution alert was triggered. The caution was followed by an EGPWS terrain warning at 1940:21 and 181 ft.

Cockpit voice recorder

VH-IPE was fitted with a 4‑channel cockpit voice recorder (CVR). The CVR recorded continuously for 120 minutes before being overwritten. Following the occurrence the crew continued with the night recency flights for each of the 3 flight crew. Therefore the CVR from the occurrence was overwritten prior to their return to Exmouth.

Operator information

PHI International Australia Pty Ltd is a global helicopter operator founded in the United States and commenced operations in Australia in 1980, operating from numerous bases on the coast of Western Australia. These operations support the offshore oil and gas industry as well as conducting marine pilot transfers and search and rescue operations.

PHI International Australia operates a fleet of about 20 helicopters that include the following types:

  • Augusta Westland AW189
  • Augusta Westland AW139
  • Augusta Westland AW109
  • Airbus H175
  • Sikorsky S‑92A.

PHI International Australia’s Exmouth base supports the offshore oil and gas industry, transferring employees to and from offshore fixed installations and mobile drilling rigs. Employee transfers arrive and depart from the Learmonth Airport located about 22 km south of Exmouth. Transfers are typically daytime only operations, however flight crews are rostered on standby each evening for immediate emergency medical evacuations if required. 

When flight crew are required to conduct night recency flights, nearby offshore rigs are used to ensure pilots are familiar with the helideck landings at night.

Operational policy and procedures
Multicrew cooperation

The Sikorsky S‑92A helicopter requires a 2-pilot configuration and duties of the crew are divided between the PF and PM. PHI International Australia’s flight operations manual part 2 (FOM 2) described the intention of a coordinated flight crew:

Operating procedures have been developed to achieve the optimum use of both pilots. Many duties may be carried out by either pilot, depending upon which one at the particular time has spare capacity. However, system handling by the PF should never interfere with their main task of flying the aircraft. Particular attention must be given to good crew co-ordination during all phases of flight. A crew briefing must be completed prior to every take-off, approach and landing. Normally the crew briefing will be given by the PF.

Normal checklists

The FOM 2 detailed the operator’s philosophy regarding checklists:

Crews should operate the aircraft, which includes changing the configuration and setting up systems, using the “next event” activity cycle, based around the priorities of "Aviate - Navigate - Communicate - Administrate". The NCL [normal checklist] should be used as the mechanism to confirm that the required actions have been completed and the aircraft is configured correctly for the task ahead. Crews should avoid flying the aircraft by checklist.

Prior to commencing the descent, the crew completed the descent checklist which required them to conduct an approach briefing. The briefing required the crew to confirm the navigation setup for the approach that included:

  • clearance
  • flight director, bugs, pointers, preview
  • navigation source
  • radio tuning unit and flight management system.

As the copilot was unable to determine the Vtoss for landing prior to the approach briefing, the crew discussed and bugged an estimated 45 kt Vtoss speed to the airspeed indicator and completed the approach brief and descent checklist.

Crew rostering policy

PHI International Australia’s rostering policy for flight crew minimum experience reflected the guidance of the International Association of Oil and Gas Producers for offshore helicopter operations, which stated: 

For ATO [air transport operations], co-pilots with less than 500 hours offshore multi engine and multi-crew should not be rostered with any commander who has less than 100 hours PIC since command appointment on the contracted type. 

The captain had less than the 100 hours in command of the S‑92A, however the copilot had significant experience in multi-engine helicopters in offshore operations including operations at night that exceeded the requirement to be paired with a captain with more experience on type (see Personnel information).

No additional rostering restrictions were identified in either the International Association of Oil and Gas Producers guidance or the operator’s policies for flight crews experience for pairing crew night.

Flight crew roles and responsibilities

The FOM 2 detailed that while conducting multi-crew operations and engaging automated flight modes, the PF was to monitor the helicopter’s flight path, anticipate any planned changes to that path and to make changes to flight references and automation modes, or instruct the PM to make the required changes. 

Other responsibilities of the PF also included:

  • cockpit management
  • control of the helicopter
  • responding to any immediate actions related to any emergencies
  • communicating with the PM in accordance with good CRM practice
  • interacting with the PM on checklist procedures
  • briefing the PM prior to undertaking any flight procedure or deviation to the planned flight.

The primary role of the PM was to monitor the helicopter’s flight path, the activities of the PF and any other activities designated in the operations manual including radio transmissions.

The FOM 2 further detailed night operations, stating:

During all operations, the priority role of the PM is to monitor the PF, especially below 1000', and not be distracted from the task. Reference to checklists, navigation logs or other manuals is not to be made during these critical flight phases. Essential drills, type specific, may be completed with due consideration for the monitoring tasks.

Crew communication and standard callouts

The FOM 2 provided the standard phraseology for the multi-crew environment and stated that the callouts were designed to promote situational awareness to ensure crew have an understanding of the helicopter system’s status.

These included standard calls for automation mode selection: 

It is important to ensure that the flight director modes have been selected, armed and captured correctly. Both crew members should be actively involved in this process.

When the PF performs the ‘action’, the PM is required to check and confirm the status of the actions (Figure 10).

Figure 10: Examples of PHI International Australia standard callouts

Table showing an example of the operator's standard callouts

Note: ALTP (altitude preselect), FD (flight director), VS (vertical speed), ALT (altitude). Source: PHI International Australia flight operations manual part 2

Following the selection of the heading mode the PF later stated that they confirmed the mode selection with the PM, however neither crew member recognised the unintended selection of the VS mode.

While the PM was communicating on the radio, the helicopter descended through the intended circuit height of 660 ft and no ‘Alt captured’ call was made by the PF or challenged by the PM.

Pilot monitoring and deviation calls

The FOM 2 detailed that standard crew calls were designed to stimulate early corrective behaviour in response to identified deviations from assigned or briefed flight references and that deviation from the reference should trigger a prompt. The FOM 2 stated that a 100 ft difference from cleared or briefed altitude was considered a deviation.

While in the circuit area and following the radio communication, the PM began using the EFB to calculate the landing Vtoss speed. No deviation call was made by either flight crew member and the helicopter descended below the intended circuit height.

Operational risk assessment

During pre-flight planning, flight crews were required to complete an operational risk assessment relevant to the flight. The operator used aviation management software that generated a risk level for the flight based on algorithms set by the operator. 

The risk assessment completed by the crew captured:

  • Human factors – illness, medication, stress, alcohol, fatigue and eating.
  • Personal recency – flown the helicopter type within the last 30 days, if operating from home base, and if flight crew had accumulated more than 500 hours on the helicopter type.
  • Operational factors – type of flight such as routine, training or medevac, planning time, client pressure or any additional factors.
  • Environmental factors – day or night, instrument flight rules weather conditions or if adverse weather was anticipated.
  • Helicopter factors – minimum equipment list items that may affect the flight. 

Operational risk level output categories were classed as:

  • Normal operations – Crews were required to complete normal pre-flight planning procedures and briefing.
  • Caution – Flight may proceed after the pilot in command and crew discuss the risk factors and record details of the discussion.
  • High caution – Flight may proceed after discussion with the senior base pilot.
  • Critical safety decision – Pilot in command required specific authorisation prior to flight from the Chief Pilot / Head of Flying Operations.

Both flight crew had not yet accumulated 500 hours on the helicopter type. The crew selected a routine flight type and also indicated that the flight would be conducted at night. The operational risk assessment did not capture the flight crew’s personal recency or experience on type at night.

The completed risk assessment indicated a ‘caution’ risk due to the crews’ experience on the aircraft type and flight at night. The crew recorded that they had discussed the risks involved with their inexperience and night flight during the sortie planning.

The captain also stated that as this was their first flight back following an off-duty period they took additional time to go through pre-flight checklists recalling they did not want to rush.

PHI International Australia advised it was able to customise the aviation management software parameters and could configure the operational risk assessment to assign individual risks and a unique risk score as it deemed suitable for its operation.

Regulatory requirements

The captain had conducted their last flight at night on 8 November 2024 and the purpose of the occurrence flight was so the crew could remain current at night.

Civil Aviation Safety Regulation (CASR) part 61.395 sub regulation (2) states that:

The holder of a pilot licence is authorised to pilot, during take‑off or landing, an aircraft of a particular category carrying a passenger at night only if the holder has, within the previous 90 days, in an aircraft of that category or an approved flight simulator for the purpose, conducted, at night:

 (a) at least 3 take‑offs; and

 (b) at least 3 landings;

while controlling the aircraft or flight simulator.

Human performance

Workload represents the level of mental and physical demand placed on an individual by the operational environment and the nature of the task. Excessive and insufficient workload can degrade performance. 

High workload may lead to errors when task demands exceed the available cognitive or physical resources. As task demand increases beyond certain limits, performance declines even though an individual’s effort may rise.

Slips occur when a person’s understanding of the situation is correct, and the wrong action is executed (Wickens, Helton, Hollands, & Banbury, 2022). Characteristics of this error also occur when people accept a close match for the proper object, something that looks similar, is in the expected location or does a similar job. Slips and lapses (forgetting to do an action) can be reduced through good design of the working interfaces, procedures and environments, however it is impossible to prevent them entirely.

Divided attention refers to the allocation of cognitive resources to several tasks at once. The ability for individuals to attend to multiple stimuli and do various tasks at a time has limits (Dismukes, Berman, & Loukopoulous, 2017). The efficiency of divided attention depends on the task’s complexity and familiarity. Simpler, well-practiced tasks require less cognitive effort and are more easily combined than complex or novel tasks. 

Expectations strongly influence where a person will search for information and what they will search for (Wickens & McCarley, 2008), and they also influence the perception of information (Wickens, Hollands, Banbury, & Parasuraman, 2013). For example, pilots frequently set the automation and in almost all situations, the helicopter will perform as the automation was intended.

Crew resource management 

Crew resource management (CRM) is the effective use of all available resources for flight crew personnel to assure a safe and effective operation, reducing error, avoiding stress and increasing efficiency. It encompasses a wide range of knowledge, skills and attitudes including communications, situational awareness, problem solving, decision‑making, and teamwork, along with the sub-disciplines which support these areas. CRM helps mitigate human limitations risks discussed above.

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On 6 September 2023 the pilot of a Boeing 737 inadvertently input full left rudder trim when they intended to activate the flight deck door switch, resulting in an in-flight upset and a cabin crew member sustaining a minor injury.

Unstable approach involving Embraer 190, VH-UZI, about 4 km north-east of Brisbane Airport, Queensland (AO-2024-030)

On 9 May 2024 following a request from the captain the first officer inadvertently pushed the flight path angle button – a ‘slip’ type error, which unintentionally disengaged the ILS approach mode. 

Surprised by the mode change, over the next 10 seconds the flight crew focused on resolving it, rather than conducting a go-around.

During this time, the pilots were not effectively monitoring the aircraft’s flight path, and it exceeded the glideslope limit requirement of the operator’s stabilised approach criteria.

Safety analysis

Introduction

On 1 February 2025 a Sikorsky S‑92A helicopter, registered VH-IPE and operated by PHI International Australia, was conducting a night recency flight to an offshore drilling rig north‑north-west of Exmouth, Western Australia. The captain was the pilot flying (PF) for the outbound flight to the rig and the copilot was the pilot monitoring (PM).

While on descent to the rig the PF intended to activate the heading hold mode on the automatic flight control system mode select panel to adjust the heading to avoid overflying the rig. An inadvertent and unrecognised selection resulted in the cancellation of an automation mode that would have levelled the helicopter at a preset circuit height. The helicopter continued descent below the circuit height until the crew received an enhanced ground proximity warning system (EGPWS) alert at about 220 ft.

This analysis will explore the operational considerations pertaining to flight crew experience, pre-occupation in the cockpit, decision‑making and flight crew coordination. 

Flight crew experience and workload

The flight crew were experienced pilots, however, both had limited flight time in the S‑92A at night. As the crew departed Exmouth and flew direct to the drill rig, this decreased the time at cruise altitude by about 5 minutes compared to normal passenger‑carrying flights the crew would usually conduct from Learmonth. This reduced the time available to complete the required cockpit administration and likely contributed to the PM being unable to complete the required tasks prior to top of descent.

Since their initial check to line on the S‑92A in November 2024, the PM had accumulated about 220 hours on the S‑92A, of which about 9 hours were at night. Their total experience on the helicopter type meant it was likely the PM was still becoming familiar with the onboard systems and administration requirements of the helicopter type, especially at night.

The combination of the shorter than usual flight time and the PM’s experience on the helicopter type, resulted in them being rushed to complete the take-off safety speed (Vtoss) calculation prior to the top of descent. 

The PF had accumulated about 300 hours flying the S‑92A of which 13 hours was night flying conducted during training and simulator sessions. The PF’s low familiarity with the helicopter type at night likely created an unfamiliar cockpit environment which was compounded by their lack of recency, following a 4-week period off duty. In a complex cockpit environment such as the S‑92A this increased the risk of a selection error.

Contributing factor

The flight crew had limited time on type and on type at night which increased risk and due to the short sector were experiencing a higher than normal workload.

Autopilot mode selection error

During the descent to the rig, it was the PF’s intention to engage the autopilot heading mode to adjust the helicopter track and avoid flying directly over the top of the rig. However, they mistakenly selected the vertical speed key before then reselecting the heading key. The inadvertent selection of the vertical speed mode went unrecognised by the crew.

Both the heading and vertical speed keys are physically close, located one above the other. Further, as the top row of hard keys were not backlit when the mode was not engaged, identification of the correct key is more difficult in a dark cockpit, especially for flight crew who had limited experience flying the S‑92A at night.

This inadvertent selection was consistent with an unintentional slip, which cancelled an automation mode the crew had engaged to level the helicopter when it reached circuit height. 

Following the inadvertent activation of the vertical speed mode, the PF confirmed with the PM that the engagement of the intended heading mode was correct as per the operator’s procedures. However, as the PF was unaware they had selected the vertical speed mode, the engagement was not announced to the PM, nor would the PM have any expectation that the vertical speed mode would be engaged at that point of the flight. 

The helicopter continued a 500 feet per minute rate of descent that was not recognised by the crew in the mostly dark conditions. The reduced visual reference when combined with the preoccupation of additional tasks resulted in the helicopter’s continued descent until the crew reacted to the EGPWS alert.

Contributing factor

During a night recency flight, an autopilot mode selection error was made which the flight crew did not recognise. This cancelled the helicopter levelling off at 660 feet and set up a continuous 500 feet per min rate of descent.

Captain’s request to calculate safety speed

Following the crew’s estimation of the Vtoss for landing, the PF became concerned that the reference speed was too high. With an expectation the helicopter had levelled in the circuit area, the PF requested the PM to again attempt to calculate the Vtoss for landing which required the PM to use Sikorsky’s performance application in the electronic flight bag. 

PHI International Australia flight operations manual detailed that, especially for flight at night and below 1,000 ft, the PM was not to be distracted from their monitoring duties. However, at the PF’s request the PM’s attention became focused on the electronic flight bag, this drew their attention away from their required monitoring duties while the helicopter was below 1,000 ft above ground level (AGL).

Contributing factor

Within the circuit area the captain requested the copilot to calculate Vtoss for landing, diverting the copilot’s attention away from their pilot monitoring duties.

Preoccupation in the circuit area

When focus is diverted to a secondary task, attention can narrow to that task, and so monitoring of other sources degrades (Dismukes, Berman, & Loukopoulous, 2017). This degradation of monitoring can occur without the flight crew realising. 

As the helicopter approached the circuit area, it continued to descend through 810 ft AGL as the PM communicated on the radio. At the completion of the radio transmissions, the helicopter was recorded at about 526 ft AGL and below the intended circuit height.

The operator’s standard calls for flight crew required the PF to announce the helicopter had captured the intended altitude and the announcement should then be crosschecked and confirmed by the pilot monitoring. However during this time the PM was communicating on the radio and an ‘altitude captured’ call was not made by the PF.

A short time after the completion of the PM’s radio transmissions, the PF commanded the aircraft to turn onto the downwind leg of the circuit. 

While the PF requested the PM to calculate the Vtoss for landing, they also diverted their own attention to activating and manipulating the searchlight beam outside the helicopter. 

Consequently, neither flight crew member was monitoring the helicopter’s altitude which contributed to the unidentified descent below the circuit height, triggering a ground proximity alert. 

Contributing factor

Both flight crew members became preoccupied with additional tasks. Neither crew were monitoring the altitude nor identified that the helicopter had not levelled at the circuit height and continued the descent.

Pre-flight operational risk assessment

Flight crews were required to complete the PHI International Australia pre-flight operational risk assessment prior to departure. The risk assessment captured the flight crew’s overall experience on the helicopter type and that the flight was being conducted at night, presenting the flight crew with a caution risk level that required a discussion of the elevated risk between themselves.

However, the risk assessment did not capture the flight crew’s experience on the helicopter type at night. Prior to the occurrence flight neither flight crew member had flown the S‑92A helicopter at night outside of their training and simulator sessions and both individually had less than 13 total hours flying the S‑92A at night. However, no additional risk was placed on their limited night experience on type.

The flight crew’s combined experience in the S‑92A at night was not formally risk assessed and no controls were in place to prevent the pairing of flight crew with limited night hours on type. This increased the likelihood of an event due to a lack of familiarity with the helicopter systems and was a missed opportunity to provide further risk controls for the intended night operations.

Contributing factor

PHI International Australia Pty Ltd’s operational risk assessment did not capture the risk of the crew’s limited experience on type at night. (Safety Issue)

Findings

ATSB investigation report findings focus on safety factors (that is, events and conditions that increase risk). Safety factors include ‘contributing factors’ and ‘other factors that increased risk’ (that is, factors that did not meet the definition of a contributing factor for this occurrence but were still considered important to include in the report for the purpose of increasing awareness and enhancing safety). In addition ‘other findings’ may be included to provide important information about topics other than safety factors. 

Safety issues are highlighted in bold to emphasise their importance. A safety issue is a safety factor that (a) can reasonably be regarded as having the potential to adversely affect the safety of future operations, and (b) is a characteristic of an organisation or a system, rather than a characteristic of a specific individual, or characteristic of an operating environment at a specific point in time.

These findings should not be read as apportioning blame or liability to any particular organisation or individual.

From the evidence available, the following findings are made with respect to the ground proximity alerts involving Sikorsky S‑92A VH-IPE, 71 km north‑north‑west of Exmouth Aerodrome on 1 February 2025. 

Contributing factors

  • The flight crew had limited time on type and on type at night which increased risk and due to the short sector were experiencing a higher than normal workload.
  • During a night recency flight, an autopilot mode selection error was made which the flight crew did not recognise. This cancelled the helicopter levelling off at 660 feet and set up a continuous 500 feet per min rate of descent.
  • Within the circuit area the captain requested the copilot to calculate Vtoss for landing, diverting the copilot’s attention away from their pilot monitoring duties.
  • Both flight crew members became preoccupied with additional tasks. Neither crew were monitoring the altitude nor identified that the helicopter had not levelled at the circuit height and continued the descent.
  • PHI International Australia Pty Ltd’s operational risk assessment did not capture the risk of the flight crew’s limited experience on type at night. (Safety Issue)

Safety issues and actions

Central to the ATSB’s investigation of transport safety matters is the early identification of safety issues. The ATSB expects relevant organisations will address all safety issues an investigation identifies. 

Depending on the level of risk of a safety issue, the extent of corrective action taken by the relevant organisation(s), or the desirability of directing a broad safety message to the Aviation industry, the ATSB may issue a formal safety recommendation or safety advisory notice as part of the final report.

All of the directly involved parties were provided with a draft report and invited to provide submissions. As part of that process, each organisation was asked to communicate what safety actions, if any, they had carried out or were planning to carry out in relation to each safety issue relevant to their organisation. 

Descriptions of each safety issue, and any associated safety recommendations, are detailed below. Click the link to read the full safety issue description, including the issue status and any safety action/s taken. Safety issues and actions are updated on this website when safety issue owners provide further information concerning the implementation of safety action.

Ineffective operational risk assessment

Safety issue number: AO-2025-005-SI-01

Safety issue description: PHI International Australia’s operational risk assessment did not capture the risk of the crew’s limited experience on type at night.

Safety action not associated with an identified safety issue

Whether or not the ATSB identifies safety issues in the course of an investigation, relevant organisations may proactively initiate safety action in order to reduce their safety risk. The ATSB has been advised of the following proactive safety action in response to this occurrence.

The S‑92A cockpit lighting environment was reviewed by the operator with subject matter experts to consider if an engineered improvement was practicable. A procedural change was implemented by PHI International Australia that required the use of small lights that are worn on the pilot’s fingers to improve visibility of the cockpit environment (such as switches, buttons, and controls) during S‑92A night flights.

PHI International Australia advised lessons from this occurrence have been shared and promoted both internally and externally. These efforts included an internal safety alert and a ‘learning from occurrence’ video detailing what happened and why to the international community through industry body HeliOffshore.

Operational procedures regarding multi-crew cooperation, automation mode changes/awareness, and EGPWS alerts were highlighted to all flight crews through internal communications. These points were also highlighted within the training and competency teams as focus areas during both simulator and line training sessions.

Glossary

AFCSAutopilot flight control system
AGLAbove ground level
ATPLAir transport pilot licence
ATSAir traffic services
CASACivil Aviation Safety Authority
CASRCivil Aviation Safety Regulations
EFBElectric flight bag
EGPWSEnhanced ground proximity warning system
FCOMFlight crew operations manual
IASIndicated airspeed
MSPMode select panel
NAVNavigation
PFPilot flying
PFDPrimary flight display
PMPilot monitoring
RADALTRadar altitude
VSVertical speed

Sources and submissions

Sources of information

The sources of information during the investigation included:

  • the pilot of the occurrence flight
  • the copilot of the occurrence flight
  • PHI International Australia Pty Ltd
  • Civil Aviation Safety Authority
  • Lockheed Martin
  • Bureau of Meteorology
  • recorded flight data
  • International Association of Oil and Gas Producers.

References

Dismukes, R. K., Berman, B. A., & Loukopoulous, L. (2017). The limits of expertise: Rethinking pilot error and the causes of airline accidents. Routledge.

Wickens, C. D., & McCarley, J. S. (2008). Applied attention theory. Boca Raton, FL: CRC Press.

Wickens, C. D., Helton, W. S., Hollands, J. G., & Banbury, S. (2022). Engineering Psychology and Human Performance 5th edition. New York: Routledge.

Wickens, C. D., Hollands, J. G., Banbury, S., & Parasuraman, R. (2013). Engineering Psychology and human performance, 4th edition. Boston, MA: Pearson.

Submissions

Under section 26 of the Transport Safety Investigation Act 2003, the ATSB may provide a draft report, on a confidential basis, to any person whom the ATSB considers appropriate. That section allows a person receiving a draft report to make submissions to the ATSB about the draft report. 

A draft of this report was provided to the following directly involved parties:

  • captain of the occurrence aircraft
  • copilot of the occurrence aircraft
  • PHI International Australia Pty Ltd
  • Lockheed Martin
  • Civil Aviation Safety Authority
  • Bureau of Meteorology.

Submissions were received from:

  • captain of the occurrence aircraft
  • copilot of the occurrence aircraft
  • PHI International Australia Pty Ltd
  • Lockheed Martin.

The submissions were reviewed and, where considered appropriate, the text of the report was amended accordingly.

Purpose of safety investigations

The objective of a safety investigation is to enhance transport safety. This is done through: 

  • identifying safety issues and facilitating safety action to address those issues
  • providing information about occurrences and their associated safety factors to facilitate learning within the transport industry.

It is not a function of the ATSB to apportion blame or provide a means for determining liability. At the same time, an investigation report must include factual material of sufficient weight to support the analysis and findings. At all times the ATSB endeavours to balance the use of material that could imply adverse comment with the need to properly explain what happened, and why, in a fair and unbiased manner. The ATSB does not investigate for the purpose of taking administrative, regulatory or criminal action.

About ATSB reports

ATSB investigation reports are organised with regard to international standards or instruments, as applicable, and with ATSB procedures and guidelines.

Reports must include factual material of sufficient weight to support the analysis and findings. At all times the ATSB endeavours to balance the use of material that could imply adverse comment with the need to properly explain what happened, and why, in a fair and unbiased manner.

An explanation of terminology used in ATSB investigation reports is available here. This includes terms such as occurrence, contributing factor, other factor that increased risk, and safety issue.

Publishing information

Released in accordance with section 25 of the Transport Safety Investigation Act 2003

Published by: Australian Transport Safety Bureau

© Commonwealth of Australia 2025

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Copyright in material obtained from other agencies, private individuals or organisations, belongs to those agencies, individuals or organisations. Where you wish to use their material, you will need to contact them directly.

[1]     Pilot flying (PF) and pilot monitoring (PM): procedurally assigned roles with specifically assigned duties at specific stages of a flight. The PF does most of the flying, except in defined circumstances, such as planning for descent, approach and landing. The PM carries out support duties and monitors the PF’s actions and the aircraft’s flight path.

[2]     The third pilot, seated in the passenger seat could hear and communicate with both crew, however their view of the cockpit and instrumentation was obstructed.

[3]     Collective: a primary helicopter flight control that simultaneously affects the pitch of all blades of a lifting rotor. Collective input is the main control for vertical velocity. 

[4]     Pressure altitude: altitude adjusted for air pressure.

[5]     Vblss: baulked landing safety speed.

[6]     TAF: aerodrome forecast: a statement of meteorological conditions expected in the airspace within a radius of 8 kilometres of the aerodrome reference point.

[7]     Ceiling and visibility okay (CAVOK): visibility, cloud and present weather are better than prescribed conditions. For an aerodrome weather report, those conditions are visibility 10 km or more, no significant cloud below 5,000 ft, no cumulonimbus cloud and no other significant weather.

[8]     QNH: the altimeter barometric pressure subscale setting used to indicate the height above mean seal level.

[9]     Okta: an okta is a unit of measurement used to describe the extent of cloud cover (1‍–‍8).

[10]    The crosswind leg is flown perpendicular to the runway.

[11]    The downwind leg is the segment when the aircraft is flying parallel to the runway but in the opposite direction of landing.

Occurrence summary

Investigation number AO-2025-005
Occurrence date 01/02/2025
Location 71 km north-north-west of Exmouth Airport
State Western Australia
Report release date 04/02/2026
Report status Final
Investigation level Defined
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Aircraft preparation, E/GPWS warning
Occurrence class Serious Incident
Highest injury level None

Aircraft details

Manufacturer Sikorsky Aircraft
Model S-92A
Registration VH-IPE
Serial number 920038
Aircraft operator PHI International Australia Pty Ltd
Sector Helicopter
Operation type Part 91 General operating and flight rules
Departure point Exmouth Aerodrome, Western Australia
Destination Transocean Endurance, Western Australia
Damage Nil

Airframe overspeed involving Diamond DA40, VH-EQF, 63 km east of Kingaroy Airport, Queensland, on 12 February 2025

Final report

Report release date: 06/06/2025

Investigation summary

What happened

At 1520 on 12 February 2025, an instructor and student departed from Brisbane West Wellcamp Airport, Queensland for a training flight in a Diamond DA40 aircraft, registered VH-EQF and operated by Flight Training Adelaide.

At 1649, as the instructor and student were conducting stall and upset recovery training at an altitude of about 6,300 ft above mean sea level, the instructor took control of the aircraft. Acting on impulse and without providing a briefing to the student, the instructor attempted a wingover.

During the attempted wingover, the bank angle quickly exceeded the aircraft’s 60° bank angle limitation before continuing beyond inverted and the aircraft’s pitch became steeply nose down. During the recovery, the speed increased beyond the aircraft’s never exceed airspeed (VNE). The flight was completed without further incident and the aircraft landed at Wellcamp at 1726.

What the ATSB found

The ATSB found that the instructor attempted a wingover manoeuvre for which they had not been trained. During the manoeuvre, the aircraft was rolled through 360°, exceeding the aircraft's 60° bank angle limit and the aircraft exceeded VNE by 20 knots.

What has been done as a result

Following the incident, Flight Training Adelaide issued an internal notice to instructors and students restricting the conduct of non-training syllabus manoeuvres. The notice advised that prior to such manoeuvres being conducted, prior permission must be obtained from the Head of Operations or Deputy Head of Operations.

A presentation was also provided to instructors on the importance of personal limitations and effective decision‑making to ensure safe operations.

Safety message

This incident underlines that pilots should not attempt unfamiliar manoeuvres without first receiving appropriate training. Effective training reduces the likelihood of mishandling and also prepares a pilot to respond appropriately should a manoeuvre deviate from the intended flightpath.

While the aircraft was not damaged during this incident, it is important that all exceeded limitations are entered onto the maintenance release and reported quickly to ensure the aircraft is inspected before further flight. This will ensure that other pilots are not exposed to the risk of operating a damaged aircraft.

 

The investigation

Decisions regarding the scope of an investigation are based on many factors, including the level of safety benefit likely to be obtained from an investigation and the associated resources required. For this occurrence, a limited-scope investigation was conducted in order to produce a short investigation report, and allow for greater industry awareness of findings that affect safety and potential learning opportunities.

The occurrence

At 1520 local time on 12 February 2025, an instructor and student departed from Brisbane West Wellcamp Airport, Queensland for a training flight in a Diamond DA40 aircraft, registered VH-EQF and operated by Flight Training Adelaide. The flight intended to track via Gatton and Sunshine Coast Airport before conducting stall and upset recovery training near Jimna and then returning to Brisbane West Wellcamp Airport (Figure 1).

Figure 1: Overview of flight

A satellite image of the area of the flight overlaid with the recorded flightpath. The turning points for the flight are annotated.

Source: Google Earth, annotated by the ATSB 

At 1649, as the instructor and student were conducting the stall and upset recovery training at an altitude of about 6,300 ft above mean sea level (AMSL), the instructor took control of the aircraft. Acting on impulse, and without providing a briefing to the student, the instructor attempted a wingover manoeuvre (see the section titled Wingover). The instructor pitched the aircraft down to increase speed before pitching the aircraft up and beginning a rapid left roll at 120 kt indicated airspeed. At the same time, the instructor began reducing engine power.

The roll quickly exceeded the aircraft’s 60° bank angle limitation (see the section titled Aircraft details) and the instructor continued applying a roll input. As the roll angle exceeded 90°, the pitch angle dropped below the level attitude and the airspeed began increasing. The aircraft then rolled beyond inverted, the aircraft’s pitch became steeply nose down, and the instructor reduced power to idle to begin recovery from the dive. 

The instructor was aware of the risk of exceeding the aircraft’s maximum G[1] limitation and so slowly increased the pitch attitude as speed continued increasing. At 1649:56, the speed increased beyond the never exceed speed[2] of 178 kt, and 3 seconds later reached a maximum of 198 kt. The instructor continued the recovery from the dive and at 1650:02, the aircraft reached a minimum recorded altitude of 4,159 ft AMSL before a climb was commenced. At 1650:04, the speed reduced below 178 kt.

The instructor then climbed the aircraft back up to an altitude of about 5,000 ft and the student advised the instructor of the speed exceeding 178 kt. The instructor then conducted an inspection of the airframe visible from the cabin and did not identify any defects. They then handed control of the aircraft back to the student to continue the flight. About 3 minutes after the incident, another stall recovery training manoeuvre was completed. The rest of the flight was conducted normally, with the student flying the aircraft. At 1726 the aircraft landed at Wellcamp.

The instructor reported that, after landing, they thought about the attempted wingover, but also had to focus on preparation for another flight. The instructor confirmed that no bookings were scheduled for the aircraft that evening, however they did not mark the aircraft as unavailable or endorse its maintenance release at that time. The instructor then completed an evening of night flying in another aircraft. Later at home they recognised that the incident needed to be reported to the operator and intended to do so the next morning.

Early the next morning, the instructor marked the aircraft as unserviceable in the operator’s booking system. The instructor also contacted the operator’s training manager and had the aircraft’s maintenance release endorsed to prevent further flights.

Context

Instructor and student details

The instructor held a commercial pilot licence (aeroplane) and class 1 aviation medical certificate. The instructor had 930 hours of flying experience, of which 900 hours were in the DA40, with 120 hours accrued in the previous 90 days. 

The instructor had completed spin recovery training but had not completed any other aerobatics training and did not hold an aerobatics endorsement. The instructor had previously been in a DA40 where a wingover had been demonstrated, but the instructor had not received training in conduct of the manoeuvre.

The student held a student pilot licence (aeroplane) and class 1 aviation medical certificate and had about 125 hours of flying experience.

The ATSB found no indicators that the instructor or student were experiencing a level of fatigue known to adversely affect performance.

Aircraft details

The Diamond Aircraft Industries DA40 is a 4-seat, low-wing, fixed-tricycle-undercarriage aircraft with a single reciprocating engine driving a variable pitch 2-bladed propeller (Figure 2). The never exceed speed (VNE) of 178 kt was not to be exceeded for any operation in the aircraft.

Figure 2: VH-EQF

Figure 2: VH-EQF

Source: Mitch Coad, modified by ATSB

The DA40 was certified to operate in the normal and utility categories and was not certified for aerobatics. The utility category had a maximum weight limit of 980 kg. For all operations above that weight, the aircraft could be operated in the normal category only. At the time of the incident, the aircraft weighed 1,111 kg. 

The aircraft’s airplane flight manual stated that when operated in the normal category, the maximum positive load factor was 3.8 G and approved manoeuvres were limited to:

1) All normal flight manoeuvres;

2) Stalling (with the exception of dynamic stalling); and

3) Lazy Eights, Chandelles, as well as steep turns and similar manoeuvres, in which an angle of bank of not more than 60° is attained.

The manual also cautioned that aerobatics, spinning, and flight manoeuvres with more than 60° of bank were not permitted when operating in the normal category. When operating the aircraft in the utility category, the bank angle limitation was 90°. All other manoeuvre limitations were unchanged.

Wingover

The wingover manoeuvre involves a combination of pitching up and banking of the aircraft to effect a change in heading. It can be conducted at varying angles of bank and pitch to turn through different angles of heading change. For a typical 180° heading change wingover, the aircraft is descended slightly to accelerate before the aircraft is pitched up to commence a climb, followed by a left or right turn. During the turn, the pitch is reduced below level to commence descending. The angle of bank is then reduced to exit the manoeuvre in the opposite direction, at the same altitude as commencement and with wings level.

A lazy eight is a pair of wingovers of 180° heading change made in succession and in opposite directions. The resulting flightpath resembles a horizontal figure of 8 (Figure 3).

Figure 3: Lazy eight manoeuvre

A pictorial representation of the lazy 8 manoeuvre.

Source: United States Federal Aviation Administration Airplane Flying Handbook

Aerobatics

The Civil Aviation Safety Authority defined aerobatics as:[3]

aerobatic manoeuvres, for an aircraft, means manoeuvres of the aircraft that involve:

 (a) bank angles that are greater than 60°; or

 (b) pitch angles that are greater than 45°, or are otherwise abnormal to the aircraft type; or

 (c) abrupt changes of speed, direction, angle of bank or angle of pitch.

Incident reporting and post-incident inspection

Following the flight, the instructor identified that the aircraft was not scheduled to be used further that evening. However, the aircraft’s maintenance release was not endorsed, and the aircraft was not made unavailable until early the following morning. 

Upon being advised of the exceedance, the aircraft manufacturer required that the aircraft undergo a minimum of a major structural inspection. This inspection found that the aircraft was not damaged during the incident. 

Meteorology and terrain

The incident manoeuvre was conducted in clear visual meteorological conditions. 

At 1700, 11 minutes after the incident, the Bureau of Meteorology (BoM) automatic weather station at Kingaroy Airport, 63 km west of the incident recorded the wind as 4 kt from 060° magnetic. There was no recorded cloud and visibility was greater than 10 km.

The ground level elevation beneath the aircraft during the incident was about 1,400 to 1,650 ft AMSL.

Recorded data

The aircraft was equipped with Garmin G1000 instrumentation that recorded the incident (Figure 4).

Figure 4: Recorded data from VH-EQF

Figure 4: Recorded data from VH-EQF

Altitudes are above mean sea level. Source: ATSB

The manoeuvre commenced at 1649:29 with a slight descent and acceleration from an altitude of 6,297 ft AMSL. The left roll then commenced at 1649:47 at an airspeed of 120 kt, a pitch angle of 11° nose up and the bank angle reached 79° left one second later. At the same time engine power began reducing. 

A second later, at 1649:49, the pitch attitude reduced below the level attitude and the bank angle reached 111° left before the aircraft rolled beyond inverted (180° roll) 2 seconds later. At that time, the pitch angle was 33° nose down and the engine power was reduced to idle as the aircraft accelerated through 122 kt.

At 1649:53, 6 seconds after the roll commenced, the aircraft had rolled through 271° and was now in a right 89° bank, and the pitch angle had reached 59° nose down, with the speed rapidly increasing past 149 kt. Three seconds later, the speed increased beyond the never exceed speed (VNE) of 178 kt and continued increasing. At 1649:56, with the nose still pitched down 19° and the wings now level, the speed reached a maximum of 198 kt. At the same time, the recorded G level increased to a maximum of 1.42 G. Speed then began to reduce and 3 seconds later, the aircraft reached a minimum recorded altitude of 4,159 ft AMSL, about 2,600 ft above the ground. Another 5 seconds later, at 1650:04, the speed reduced back below VNE.

Safety analysis

During stall and upset recovery training, the instructor took control of the aircraft and, without briefing the student, attempted a wingover. A wingover, being essentially half of a lazy eight, was a permitted manoeuvre in the aircraft provided the angle of bank did not exceed 60° (flight manual limitation) and the pitch angle remained less than 45° (aerobatic definition limitation). However, the instructor had not been trained in this manoeuvre and did not increase pitch sufficiently before applying a rapid roll input that quickly exceeded the aircraft’s bank angle limitation. As the aircraft rolled, it began pitching down rapidly and as the roll passed beyond inverted, the pitch angle became steeply nose down. 

The instructor responded to the nose down attitude by reducing power to idle but then prioritised minimising G load during the recovery from the dive. Although the instructor achieved this aim, with a maximum recorded G value of 1.42 G, well below the 3.8 G maximum, by not increasing pitch more positively, the aircraft’s speed increased rapidly and significantly exceeded the never exceed speed. Exceeding this limitation risked structural damage or failure.

The instructor then recovered from the incident and re-established normal flight before then conducting a visual inspection of the visible airframe. Control was then handed back to the student and a further stall recovery exercise was conducted. The continuation of the planned flight indicated that the risk associated with the incident and the potential for undetected damage and control issues was not fully recognised. However, the aircraft landed without further incident.

Findings

ATSB investigation report findings focus on safety factors (that is, events and conditions that increase risk). Safety factors include ‘contributing factors’ and ‘other factors that increased risk’ (that is, factors that did not meet the definition of a contributing factor for this occurrence but were still considered important to include in the report for the purpose of increasing awareness and enhancing safety). In addition ‘other findings’ may be included to provide important information about topics other than safety factors. 

These findings should not be read as apportioning blame or liability to any particular organisation or individual.

From the evidence available, the following findings are made with respect to the airframe overspeed involving Diamond DA 40, VH-EQF, 63 km east of Kingaroy Airport, Queensland on 12 February 2025.

Contributing factors

  • During a training flight, the instructor attempted a wingover manoeuvre for which they had not been trained.
  • During the manoeuvre, the aircraft pitched steeply nose down and was rolled through 360°, exceeding the aircraft's 60° bank angle limit. During the subsequent recovery, the aircraft exceeded its never exceed airspeed by 20 knots.

Safety actions

Whether or not the ATSB identifies safety issues in the course of an investigation, relevant organisations may proactively initiate safety action in order to reduce their safety risk. The ATSB has been advised of the following proactive safety action in response to this occurrence

Proactive safety action by Flight Training Adelaide

Action number:AO-2025-007-PSA-01
Action organisation:Flight Training Adelaide

Flight Training Adelaide issued an internal notice to instructors and students restricting the conduct of non-training syllabus manoeuvres. The notice advised that prior to such manoeuvres being conducted, prior permission must be obtained from the Head of Operations or Deputy Head of Operations.

A presentation was also provided to instructors on the importance of personal limitations and effective decision‑making to ensure safe operations.

 

Sources and submissions

Sources of information

The sources of information during the investigation included:

  • the instructor and student
  • Flight Training Adelaide
  • Civil Aviation Safety Authority
  • the aircraft manufacturer
  • recorded data from VH-EQF. 

References

United States Federal Aviation Administration (2021), Airplane Flying Handbook (FAA-H-8083-3C) Chapter 10 (p.10-6).

Submissions

Under section 26 of the Transport Safety Investigation Act 2003, the ATSB may provide a draft report, on a confidential basis, to any person whom the ATSB considers appropriate. That section allows a person receiving a draft report to make submissions to the ATSB about the draft report. 

A draft of this report was provided to the following directly involved parties:

  • Flight Training Adelaide
  • the instructor and student
  • Civil Aviation Safety Authority

Submissions were received from:

  • Flight Training Adelaide
  • the instructor and student

The submissions were reviewed and, where considered appropriate, the text of the report was amended accordingly.

Purpose of safety investigations

The objective of a safety investigation is to enhance transport safety. This is done through: 

  • identifying safety issues and facilitating safety action to address those issues
  • providing information about occurrences and their associated safety factors to facilitate learning within the transport industry.

It is not a function of the ATSB to apportion blame or provide a means for determining liability. At the same time, an investigation report must include factual material of sufficient weight to support the analysis and findings. At all times the ATSB endeavours to balance the use of material that could imply adverse comment with the need to properly explain what happened, and why, in a fair and unbiased manner. The ATSB does not investigate for the purpose of taking administrative, regulatory or criminal action.

Terminology

An explanation of terminology used in ATSB investigation reports is available here. This includes terms such as occurrence, contributing factor, other factor that increased risk, and safety issue.

Publishing information

Released in accordance with section 25 of the Transport Safety Investigation Act 2003

Published by: Australian Transport Safety Bureau

© Commonwealth of Australia 2025

Title: Creative Commons BY - Description: Creative Commons BY

Ownership of intellectual property rights in this publication

Unless otherwise noted, copyright (and any other intellectual property rights, if any) in this report publication is owned by the Commonwealth of Australia.

Creative Commons licence

With the exception of the Commonwealth Coat of Arms, ATSB logo, and photos and graphics in which a third party holds copyright, this report is licensed under a Creative Commons Attribution 4.0 International licence.

The CC BY 4.0 licence enables you to distribute, remix, adapt, and build upon our material in any medium or format, so long as attribution is given to the Australian Transport Safety Bureau. 

Copyright in material obtained from other agencies, private individuals or organisations, belongs to those agencies, individuals or organisations. Where you wish to use their material, you will need to contact them directly.

 

[1]      G load: the nominal value for acceleration. In flight, G load represents the combined effects of flight manoeuvring loads and turbulence and can have a positive or negative value.

[2]      VNE (Never Exceed Speed): the speed limit that may not be exceeded at any time. The calculation of this speed is driven by structural or aerodynamic limitations; however, control system flutter is typically one limitation that factors heavily into the calculation of VNE.

[3]      Civil Aviation Safety Regulations Part 91 – Dictionary, Part 1 - Definitions

Occurrence summary

Investigation number AO-2025-007
Occurrence date 12/02/2025
Location 63 km east of Kingaroy Airport
State Queensland
Report release date 06/06/2025
Report status Final
Investigation level Short
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Airframe overspeed, Loss of control
Occurrence class Serious Incident
Highest injury level None

Aircraft details

Manufacturer Diamond Aircraft Industries
Model DA40
Registration VH-EQF
Serial number 40.806
Aircraft operator Flight Training Adelaide Pty Ltd
Sector Piston
Operation type Part 142 Integrated and multi-crew pilot flight training
Departure point Brisbane West Wellcamp Airport, Queensland
Destination Brisbane West Wellcamp Airport, Queensland
Damage Nil

R44 spraying accident preliminary report

The ATSB has released a preliminary report from its ongoing investigation into a fatal accident involving a Robinson R44 helicopter that was conducting aerial spraying operations near Boorowa, New South Wales on 4 December 2024.

Prior to the accident, the pilot had completed 10 spraying runs to apply herbicide, each taking about 10 minutes.

When the helicopter did not return 15 minutes after beginning the eleventh run, and the pilot could not be contacted via radio, the base manager instigated a search.

The wreckage of the helicopter was located in a steep gully towards the southern end of the spray area. The pilot was seriously injured, and shortly after succumbed to their injuries.

“ATSB examination of the site identified a tree with broken branches prior to the first items in the debris trail, which included the helicopter’s stabiliser assembly and right side spray boom,” Director Transport Safety Kerri Hughes said.

“There were two ground scars, consistent with landing gear skids, with the majority of the wreckage coming to rest in a gully.”

ATSB transport safety investigators’ inspection of the wreckage so far has not identified any evidence of pre-impact structural or mechanical defects with the helicopter.

The helicopter’s fuel system was found to hold about 55 L of fuel, which was visibly clear of contaminants and tested negative to the presence of water, and external examination of the engine did not identify any defects.

“As the investigation progresses, ATSB investigators will review and examine witness accounts, recorded data, the wreckage, helicopter documentation, operational records, as well as the pilot’s medical records, qualifications and experience,” Ms Hughes said.

The ATSB will release a final report, which will detail the ATSB’s analysis and findings, at the conclusion of the investigation.

“However, should a critical safety issue be identified during the course of the investigation, the ATSB will immediately notify relevant parties so appropriate and timely safety action can be taken,” Ms Hughes concluded.

Read the preliminary report: Collision with terrain involving Robinson R44 II, VH-XIX, 50 km east of Young Airport, New South Wales, on 4 December 2024

Shielding, inaccurate relayed information

Shielding from buildings at Geraldton Airport and inaccurate relayed information contributed to the pilots of two charter aircraft commencing their take-off runs from runways with intersecting flight paths within seconds of each other.

An ATSB investigation report details that just after 8 am on 19 March 2024, a Fairchild Metroliner was lined up on the threshold of Geraldton’s runway 03 to take off to the north-east, while a Beechcraft Bonanza was lined up on runway 14, to take off to the south-east.

While the two runways do not cross each other, they form a ‘y’ shape in which aircraft departing runway 14 (and landing on the reciprocal runway 32) overfly runway 03 (and the reciprocal runway 21).

Geraldton Airport is a non-controlled aerodrome, where pilots are responsible for maintaining separation from other aircraft by monitoring and broadcasting radio calls on a common traffic advisory frequency, or CTAF.

After reaching their respective runway thresholds and preparing for take-off, each pilot had attempted to contact the other, but they could not hear or see one another.

The pilot of a third aircraft, from the same operator as the Bonanza, attempted to assist by passing along traffic information.

However, the aircraft began their take-off rolls within three seconds of one another, and the Metroliner crossed about 400 m in front of the Bonanza, with a vertical separation of about 250300 ft.

The ATSB investigation confirmed the position of airport buildings made it unlikely aircraft would be able to see one another when positioned at the thresholds of runway 03 and runway 14, which are over 2,100 m apart.

Further, the investigation found aircraft in these positions may not be able to reach one another on VHF radio due to potential shielding effects.

“Each aircraft was unable to verify the other’s location while lined up for take-off,” ATSB Director Transport Safety Kerri Hughes said.

“While the third aircraft pilot was attempting to assist, the details provided were inaccurate and incomplete, which inadvertently resulted in misinterpretation by the Metroliner and Bonanza pilots, influencing their almost simultaneous decisions to take off.”

After the incident, Geraldton Airport conducted radio checks which identified the potential for VHF shielding. The airport subsequently submitted an amendment to the En Route Supplement Australia to highlight this possibility.

“Operations at non-controlled aerodromes require pilots to monitor traffic and maintain separation through the use of VHF radio in conjunction with a vigilant lookout under the principles of alerted see-and-avoid,” Ms Hughes explained.

“As such, especially where communications and visibility are limited, it is critical for pilots to take all reasonable measures to verify the position and intentions of known traffic.”

CASAIR, the operator of the Metroliner, has since emphasised to its pilots to stop or slow down when communication difficulties are identified, until completely assured of the situation.

Similarly, Shine Aviation, the operator of the Bonanza, has highlighted to its pilots the importance of being completely certain of another aircraft’s position and intentions, and not to make assumptions.

Read the final report: Near collision involving Beechcraft A36, VH-CKX, and Fairchild SA226-TC, VH-KGX, at Geraldton Airport, Western Australia, on 19 March 2024

Wheel brake failure involving Sling Aircraft Sling LSA, VH-PPY, Moorabbin Airport, Victoria, on 14 February 2025

Final report

Report release date: 18/11/2025

Investigation summary

What happened

On 14 February 2025, an instructor and student pilot were conducting a training flight using a Sling Aircraft Sling LSA, registered VH‑PPY, operating from Moorabbin Airport in Victoria. After landing and as the aircraft was vacating the runway, there was a jolt and an unusual sound from the right side of the aircraft. After the instructor taxied the aircraft to the operator’s parking area and disembarked, the right main landing gear brake disc was found to have fractured through its entire circumference.

What the ATSB found

The ATSB found that the aircraft brake disc fractured during normal operation due to severe corrosion that compromised its structural integrity. This corrosion was not identified by those maintaining and operating the aircraft as having progressed to a point where failure of the brake disc was possible. 

The fractured brake disc fitted to the aircraft was an aftermarket part. Manufacture of the brake disc was consistent with the manufacturer’s specifications, however it had not been approved for fitment to the Sling LSA and therefore assurance that it was a suitable replacement had not been established.

What has been done as a result

The operator replaced all corroded brake discs fitted to its Sling LSA fleet with the correct Matco parts, and the aircraft are now moved onto the apron prior to boarding allowing easier access to inspect the landing gear. Additionally, the operator discussed the occurrence in a safety presentation to instructor pilots which included a description of the event, photos of the corroded brake, possible reasons for the corrosion, and a direction to ensure inspection of the brakes is carried out prior to flight.

Safety message

There are multiple opportunities for those operating aircraft to identify defects such as corrosion, and those maintaining the aircraft should take timely action to prevent its progression or replace that part before the serviceability of the aircraft is affected. Additionally, consideration should be given to the operating environment of the aircraft and whether additional maintenance activities could be employed to limit corrosion development. 

 

The investigation

The ATSB scopes its investigations based on many factors, including the level of safety benefit likely to be obtained from an investigation and the associated resources required. For this occurrence, the ATSB conducted a limited-scope investigation in order to produce a short investigation report, and allow for greater industry awareness of findings that affect safety and potential learning opportunities.

The occurrence

On 14 February 2025, an instructor and student pilot were conducting a training flight from Moorabbin Airport, Victoria, using a Sling LSA, manufactured by Sling Aircraft[1] and registered VH‑PPY. 

At about midday, the instructor landed the aircraft on runway 17R.[2] As the aircraft was vacating the runway onto taxiway A4, there was a jolt and an unusual sound from the right side of the aircraft. The instructor continued to taxi, and after noticing that the aircraft’s wheel brakes were less effective, brought the aircraft to a stop and conducted after-landing checks without noting anything significant.

The instructor re-commenced taxiing to the operator’s parking area, and after disembarkation saw that the right main landing gear brake disc had failed (Figure 1). The instructor noted the brake failure on the aircraft’s maintenance release, grounding the aircraft.

Figure 1: VH-PPY right brake disc post-flight

A close-up picture of the right main landing gear brake disc showing the failure area.

Source: Learn to Fly Australia and Sling Aircraft, annotated by the ATSB

Context

Aircraft information

General information

The Sling LSA is a low-wing, 2-seat aircraft, designed and manufactured in South Africa for private flying and flying training. The aircraft is constructed predominantly from aluminium alloy, has a fixed, tricycle landing gear and is powered by a Rotax 912 ULS2‑01 engine. 

VH‑PPY was manufactured in 2018 and was first registered in Australia in March 2019. The aircraft had been first registered by the current operator, Learn to Fly Australia, in October 2020. At the time of the occurrence, the aircraft had accumulated 2,951.2 hours total time in service.[3]

The nose and both main wheels were originally fitted with aerodynamic fairings, however the aircraft’s main wheel fairings were removed[4] from VH‑PPY when the aircraft entered service, for ongoing ease of inspection and tyre changes.

Main landing gear brakes
General information

The Sling LSA main landing gear wheels are fitted with disc brakes (Figure 2). Braking action is achieved by the pilot’s feet acting on the aircraft’s rudder pedals, directing hydraulic fluid to the brake caliper piston to move the lining (pad), which in turn acts on the friction area of the brake disc. 

Figure 2: Sling LSA main landing gear and Matco wheel brake assembly

A technical drawing showing the principal components for the aircraft main landing gear, wheels, and brakes.

Source: Sling Aircraft, annotated by the ATSB

Aircraft manufacturers prescribe specific approved parts for use on their aircraft. Parts that are not approved by the manufacturer are ineligible for fitment. The brake assemblies approved for fitment to the Sling LSA are manufactured by Matco Aircraft Landing Systems (Matco). They consist of a wheel rim, a brake disc, and a brake caliper assembly. Matco used zinc as the standard corrosion protection coating on the brake disc, however electroless nickel plating[5] is offered as an option. Matco indicated that the nickel plating offers better protection, longevity and high temperature tolerance. The aircraft manufacturer did not specify the type of coating on the Matco brakes fitted to the Sling LSA.

The brake disc fitted to VH‑PPY at the time of the occurrence was manufactured by Rapco (Figure 3). Rapco brake discs are manufactured from forged carbon steel and electroless nickel plated for corrosion prevention. Rapco brake discs are identified with a laser-etched part number and have 2 areas where the section thickness has been reduced, which is not a feature of the approved Matco part.

Figure 3: Brake disc as received at the ATSB’s technical facility

A close-up picture of the right main landing gear brake disc at the ATSB’s technical facility showing the failure area, the corrosion, and the zone that was sectioned for detailed analysis.

Source: ATSB

The aircraft manufacturer advised that there were no approved alternates to the Matco brake discs for fitment to the Sling LSA. The maintenance organisation reported that they were not aware that the disc fitted to VH‑PPY was an unapproved part and there was no record in the aircraft logbooks of fitment of the Rapco brake disc.

Inspection and maintenance 

The aircraft’s pilot operating handbook contained instructions for a pre-flight check to be carried out prior to the first flight of the day and after any maintenance activity. This check included an inspection of the right and left main wheels and brakes for fluid leaks, security, general condition, tyre condition, inflation and wear. The preamble for the pre‑flight check noted that:

The word “condition” in the instructions means a visual inspection of surface for damage deformations, scratching, chafing, corrosion or other damages, which may lead to flight safety degradation.

The operator of VH-PPY required its instructor pilots to carry out a daily inspection prior to the first flight of the day, which encompassed the pre-flight requirements and other inspections such as checking the engine oil level and checking onboard fuel for the presence of water. Instructor pilots then carried out pre-flight inspections prior to every flight and supervised students in carrying out daily inspections prior to every flight they conduct.

VH‑PPY was being used for flying training and in the 2.5 months prior to the occurrence had flown about 140 flights. Periodic inspections and servicing were being carried out on VH-PPY every 100 flying hours, which would typically be accrued in about 2 months. The inspections were carried out in accordance with the Sling 2 and Sling LSA maintenance manual. This included an inspection of all components of the main landing gears for ‘poor condition’. The maintenance organisation, which had been carrying out periodic and other maintenance on the operator’s Sling LSA since 2023, was monitoring the condition of the brakes while it was sourcing replacement parts. It reported that while it was aware of the increasing corrosion on the brake disc, it had not reached a point where it considered it to be critical.

A section of the maintenance manual provided guidelines for corrosion prevention and noted that:

The information supplied here is as a general guideline only, and is by no means intended to be exhaustive, complete or authoritative. For more in depth information refer to an applicable and authoritative publication, such as the [Federal Aviation Administration] FAA Advisory Circular AC 43.13-1B: Acceptable Methods, Techniques and Practices - Aircraft Inspection and Repair.

It is highly advisable that expert advice be sought with regard to corrosion related issues. 

Included in the general guidance was that:

… If any trace of corrosion is detected it should be removed as soon as possible and the applicable part should be treated immediately to prevent further corrosion.

Treatment consists of mechanically removing as much as possible of any corrosion by-products, applying corrosion inhibitor and replacing any original finish.

Matco published inspection requirements for the approved brake assembly in a technical service bulletin. This document provided methods to remove corrosion from the area where the brake lining contacts the disc and prohibited removal of the plating from other areas of the brake disc. The minimum thickness[6] of the friction area was specified as 0.130 inches (3.303 mm).

Rapco, the manufacturer of the brake disc fitted to VH‑PPY, specified the minimum thickness of the friction area as 0.167 inches (4.242 mm).

Generic inspection and maintenance guidelines

The United States Federal Aviation Administration (FAA) advisory circular AC 43.13‑1B – Acceptable Methods, Techniques and Practices - Aircraft Inspection and Repair[7] provided guidelines for corrosion preventative maintenance, an inspection guide, and procedures for corrosion removal for specific material types such as ferrous alloys. The Civil Aviation Safety Authority (CASA) airworthiness bulletin AWB 02-045 permitted AC 43.13-1B to be used as approved maintenance data for minor repairs of aircraft that meet the eligibility requirements.

The FAA advisory circular AC 43.4B – Corrosion Control for Aircraft[8] also provided guidelines for the identification of corrosion on ferrous metals, information on how it propagates, guidelines for its removal and for the subsequent treatment of those areas. The advisory circular includes instructions for a corrosion prevention plan based on the location of the aircraft. As the Australian coastline is considered a ‘severe’ zone, cleaning, inspection, lubrication, and preservation was suggested to be carried out every 15 calendar days.

Examination of failed brake disc

The brake disc was examined at the ATSB’s technical facility in Canberra. 

The brake disc exhibited uniform corrosion[9] with associated material loss and thinning of the base metal. The disc was most severely corroded around the region of failure, which was adjacent to the friction (braking) area and associated with a reduction in part thickness. The measured maximum thickness of the brake disc friction area was 3.63 mm (0.143 inches), making it about 0.612 mm (0.024 inches) less than the minimum thickness specified by Rapco.

Elemental analysis of the disc materials was conducted using energy dispersive spectroscopy (EDS). The materials were consistent with a plain carbon steel base layer and electroless nickel surface coating. 

Electroless nickel plating is a barrier coating, meaning that it protects the substrate (in this case the brake disc) by sealing it off from the environment. This can be contrasted with zinc plating where zinc acts as a sacrificial material that corrodes in preference to the substrate, thereby protecting it.

To examine the remaining plating for continuity, a section was taken through the brake disc. The plating was measured to be about 10 µm (0.01 mm) thick and was broadly continuous around the hub but degraded closer to the region of failure. There were examples where cracking in the plating corresponded to sub-plating corrosion of the disc (Figure 4).

Figure 4: Sectioned view of damaged plating

A picture taken with an electron microscope showing the thickness of the nickel plating, external corrosion, and sub-plating corrosion corresponding to cracked areas of the plating.

Source: ATSB

Other aircraft

After the occurrence, the operator checked the brake discs fitted to the remaining 6 Sling LSA in its fleet. Those aircraft were first registered in Australia between 2017 and 2021. The disc part numbers were not confirmed, however images showed that most had the same changes in section thickness as the subject Rapco disc. All of the discs were observed to have advanced corrosion with resulting material loss. Additionally, a radial crack was found on the brake discs of 2 aircraft in the friction area. These brake discs were replaced immediately with the correct Matco parts and the remainder during scheduled maintenance.

Matco reported that it had seen corrosion on brake discs in service when there has been a loss of plating, but not to the extent seen on the brake disc from VH‑PPY. The aircraft manufacturer also was not aware of instances of corrosion to this extent.

Aircraft operating environment

The operator conducted flying training from its facility at Moorabbin Airport, which is situated about 3 km from Port Phillip Bay (a large saltwater bay) at its closest point.

The operator’s aircraft were parked outside on concrete pads, surrounded by gravel and grass (Figure 5). Rain reportedly pools on and around these pads.

Figure 5: Parking area for the operator’s aircraft

A picture of a Sling LSA parked on concrete pads, which are surrounded by gravel and grass.

Source: Learn to Fly Australia, annotated by the ATSB

Safety analysis

The right brake disc of VH‑PPY was severely corroded and its structural integrity had been compromised to the point where it failed during normal aircraft braking after landing. While there were no injuries or further aircraft damage from this occurrence, failure of the aircraft’s braking system could result in a more serious outcome such as a runway excursion or surface movement collision.

The Rapco brake disc fitted to VH-PPY was not approved by the aircraft manufacturer for fitment to the Sling LSA, so assurance that it was a suitable replacement had not been established. However, the materials used in the construction were similar to those offered by the original equipment manufacturer (Matco) and found to be consistent with Rapco specifications. 

Rapco employed an electroless nickel barrier coating to prevent corrosion. This meant that corrosion can initiate at any point the plating becomes discontinuous, which was the most likely initiator for the corrosion in this case. 

It was not determined when the brake disc had been replaced and, therefore, the time taken for the corrosion to develop was not established. However, VH‑PPY was being parked outside and operated in the vicinity of a saltwater environment, which would have contributed to the corrosion development. The effect of the environment was also demonstrated by the extent of corrosion observed on the brake disc assemblies of the other 6 aircraft in the operator's fleet. 

There were multiple opportunities to intervene ahead of the failure, given that the aircraft was being inspected daily by pilots, and typically every 2 months by a maintenance organisation. Importantly, the maintenance organisation was aware of the corrosion, but had not identified that it had progressed to a point where the structural integrity of the brake disc had been compromised, or taken any maintenance actions to limit its progression. There are authoritative publications that provide information for the prevention and maintenance of corrosion and, if needed, guidance can be sought from the aircraft or brake manufacturers. 

Findings

ATSB investigation report findings focus on safety factors (that is, events and conditions that increase risk). Safety factors include ‘contributing factors’ and ‘other factors that increased risk’ (that is, factors that did not meet the definition of a contributing factor for this occurrence but were still considered important to include in the report for the purpose of increasing awareness and enhancing safety). In addition ‘other findings’ may be included to provide important information about topics other than safety factors. 

These findings should not be read as apportioning blame or liability to any particular organisation or individual.

From the evidence available, the following findings are made with respect to the wheel brake failure involving Sling Aircraft Sling LSA, VH-PPY, at Moorabbin Airport, Victoria, on 14 February 2025. 

Contributing factors

  • The corrosion on the brake disc assembly of VH-PPY was not identified by those maintaining and operating the aircraft as having progressed to the point where the brake's structural integrity had been compromised. 

Other findings

  • The brake disc fitted to the aircraft was not approved for fitment to the Sling LSA and therefore assurance that it was a suitable replacement had not been established.

Safety actions

Whether or not the ATSB identifies safety issues in the course of an investigation, relevant organisations may proactively initiate safety action in order to reduce their safety risk. The ATSB has been advised of the following proactive safety action in response to this occurrence.

Safety action

The operator replaced all corroded brake discs fitted to its Sling LSA fleet with the correct Matco parts, and the aircraft are now moved onto the apron prior to boarding, allowing easier access to inspect the landing gear. Additionally, the operator discussed the occurrence in a safety presentation to instructor pilots which included a description of the event, photos of the corroded brake, possible reasons for the corrosion, and a direction to ensure inspection of the brakes is carried out prior to flight.

Sources and submissions

Sources of information

The sources of information during the investigation included:

  • the instructor pilot
  • the aircraft manufacturer
  • the brake disc manufacturer
  • Civil Aviation Safety Authority
  • Learn to Fly Australia
  • Westernport Aviation Services. 

References

ASM International Handbook Committee. (1982). ASM Handbook Volume 5 Surface Cleaning, Finishing, and Coating. Metals Handbook Ninth Edition.

ASM International Handbook Committee. (1987). ASM Handbook Volume 13 Corrosion.

The Airplane Factory, Sling 2 Pilot Operating Handbook, 10 June 2019.

The Airplane Factory, Sling 2 and Sling LSA Maintenance Manual, 26 November 2021.

U.S. Department of Transportation Federal Aviation Administration. (2018). AC 43.4B Corrosion Control for Aircraft. Washington DC: U.S. Department of Transportation Federal Aviation Administration.

U.S. Department of Transportation Federal Aviation Administration. (1998). AC 43.13-1B Acceptable Methods, Techniques and Practices - Aircraft Inspection and Repair. Washington DC: U.S. Department of Transportation Federal Aviation Administration.

Submissions

Under section 26 of the Transport Safety Investigation Act 2003, the ATSB may provide a draft report, on a confidential basis, to any person whom the ATSB considers appropriate. That section allows a person receiving a draft report to make submissions to the ATSB about the draft report. 

A draft of this report was provided to the following directly involved parties:

  • aircraft manufacturer
  • brake disc manufacturers
  • instructor pilot
  • Learn to Fly Australia
  • maintenance organisation
  • Civil Aviation Safety Authority
  • National Transportation Safety Board (United States)
  • South African Civil Aviation Authority.

The submissions were reviewed and, where considered appropriate, the text of the report was amended accordingly.

Purpose of safety investigations

The objective of a safety investigation is to enhance transport safety. This is done through: 

  • identifying safety issues and facilitating safety action to address those issues
  • providing information about occurrences and their associated safety factors to facilitate learning within the transport industry.

It is not a function of the ATSB to apportion blame or provide a means for determining liability. At the same time, an investigation report must include factual material of sufficient weight to support the analysis and findings. At all times the ATSB endeavours to balance the use of material that could imply adverse comment with the need to properly explain what happened, and why, in a fair and unbiased manner. The ATSB does not investigate for the purpose of taking administrative, regulatory or criminal action.

About ATSB reports

ATSB investigation reports are organised with regard to international standards or instruments, as applicable, and with ATSB procedures and guidelines.

Reports must include factual material of sufficient weight to support the analysis and findings. At all times the ATSB endeavours to balance the use of material that could imply adverse comment with the need to properly explain what happened, and why, in a fair and unbiased manner.

An explanation of terminology used in ATSB investigation reports is available here. This includes terms such as occurrence, contributing factor, other factor that increased risk, and safety issue.

Publishing information

Released in accordance with section 25 of the Transport Safety Investigation Act 2003

Published by: Australian Transport Safety Bureau

© Commonwealth of Australia 2025

Title: Creative Commons BY - Description: Creative Commons BY

Ownership of intellectual property rights in this publication

Unless otherwise noted, copyright (and any other intellectual property rights, if any) in this report publication is owned by the Commonwealth of Australia.

Creative Commons licence

With the exception of the Commonwealth Coat of Arms, ATSB logo, and photos and graphics in which a third party holds copyright, this report is licensed under a Creative Commons Attribution 4.0 International licence.

The CC BY 4.0 licence enables you to distribute, remix, adapt, and build upon our material in any medium or format, so long as attribution is given to the Australian Transport Safety Bureau. 

Copyright in material obtained from other agencies, private individuals or organisations, belongs to those agencies, individuals or organisations. Where you wish to use their material, you will need to contact them directly.

[1]     Called ‘The Airplane Factory’ at the time of manufacture.

[2]     Runway numbering: represents the magnetic heading closest to the runway orientation (for example, runway 17R is oriented 164º magnetic).

[3]     Total time in service (TTIS) for VH-PPY was measured by engine operating hours. 

[4]     The Sling LSA aircraft maintenance manual allowed the aircraft to be operated with the nose and main wheel fairings installed or removed in any combination.

[5]     Electroless nickel plating: a process where nickel is deposited onto the part surface without the use of an electric current.

[6]     Material will be lost from the friction area due to wear from the brake caliper action. When its thickness reduces to a point less than the specified minimum, the brake is no longer serviceable and must be replaced.

[9]     Uniform corrosion: all metals are affected by this form of attack in some environments; the rusting of steel and the tarnishing of silver are typical examples of uniform corrosion. In some metals, such as steel, uniform corrosion produces a somewhat rough surface by removing a substantial amount of metal, which either dissolves in the environment or reacts with it to produce a loosely adherent, porous coating of corrosion products.

Occurrence summary

Investigation number AO-2025-006
Occurrence date 14/02/2025
Location Moorabbin Airport
State Victoria
Report release date 18/11/2025
Report status Final
Investigation level Short
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Landing gear/indication
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer The Boeing Company
Model Sling LSA
Registration VH-PPY
Serial number 282
Aircraft operator Learn to Fly Australia Pty Ltd
Sector Piston
Operation type Part 141 Recreational, private and commercial pilot flight training
Departure point Moorabbin Airport, Victoria
Destination Moorabbin Airport, Victoria
Damage Minor

Fuel starvation event involving a Piper PA-28-180, Parafield Airport, South Australia, on 26 November 2024

Occurrence Briefs are concise reports that detail the facts surrounding a transport safety occurrence, as received in the initial notification and any follow-up enquiries. They provide an opportunity to share safety messages in the absence of an investigation. Because occurrence briefs are not investigations under the Transport Safety Investigation Act 2003, the information in them is de-identified. 

What happened

On 26 November 2024, an instructor was conducting training operations with a student pilot in a Piper PA-28-180 Cherokee aircraft. Activities involved general aircraft handling in the Parafield Airport training area, South Australia, before returning to the aerodrome for circuit operations on runway 26L.

Around 1345 local time, as the aircraft was descending through about 600 ft on final approach to the runway, the student advanced the throttle to correct the descent profile when the engine did not respond. The instructor assumed aircraft control and began troubleshooting actions while managing the descent. At about 300 ft, when it was evident that the engine would not respond, the instructor committed to an emergency landing on the grassed area to the east of runway 21L. The landing was uneventful, and the student and instructor evacuated the aircraft without injury. The aircraft was undamaged.

Examination of the aircraft’s systems after the landing found that the fuel selector was in the left tank position – being the tank that was selected before the flight commenced. On inspection, the left tank contained no usable fuel.

Aircraft information

The Piper PA-28-180 aircraft has two independent fuel tanks within the wings, which feed the engine via a ‘Left-Right-Off’ selector valve located on the cockpit left side. The quantity of fuel in each tank is indicated by dash-mounted gauges. A fuel pressure gauge is co-located with the quantity gauges.

The aircraft manufacturer’s Pilot’s Operating Handbook (POH) lists the following actions in the event of a loss of engine power in-flight:

  1. Fuel Selector – switch to another tank containing fuel
  2. Electric Fuel Pump – On
  3. Mixture – Rich
  4. Carburettor Heat – On
  5. Engine Gauges – check for an indication of the cause of Power Loss
  6. Primer – Check Locked
  7. If no fuel pressure is indicated, check tank selector position to be sure it is on a tank containing fuel.

Safety action

Following the occurrence, the operator’s Head of Operations reviewed the known details of the incident flight with all instructors, highlighting the absence of a ‘both tanks’ fuel selection on the PA-28 aircraft and reinforcing the requirement to use calculated fuel logs that are cross‑referenced against the aircraft gauges at periodic intervals during flight.

Safety message

All general aviation pilots must ensure they are fully familiar with the control and operation of the fuel system/s of the aircraft they are operating. This includes actions in the event of engine power loss at any phase of flight, where timely and appropriate responses to possible fuel flow interruptions can be critical to a safe outcome. Emergency checklists should be readily accessible and periodically reviewed to ensure pilots remain familiar with the appropriate actions in the event of fuel-related engine power loss.

About this report

Decisions regarding whether to conduct an investigation, and the scope of an investigation, are based on many factors, including the level of safety benefit likely to be obtained from an investigation. For this occurrence, no investigation has been conducted and the ATSB did not verify the accuracy of the information. A brief description has been written using information supplied in the notification and any follow-up information in order to produce a short summary report, and allow for greater industry awareness of potential safety issues and possible safety actions.

Occurrence summary

Mode of transport Aviation
Occurrence ID AB-2024-047
Occurrence date 26/11/2024
Location Parafield Airport
State South Australia
Aviation occurrence category Engine failure or malfunction, Forced/precautionary landing, Fuel starvation
Highest injury level None
Brief release date 18/02/2025

Aircraft details

Manufacturer Piper Aircraft Corp
Model PA-28-180 Cherokee
Sector Piston
Operation type Part 141 Recreational, private and commercial pilot flight training
Departure point Parafield Airport, South Australia
Destination Parafield Airport, South Australia
Damage Nil