Boeing 767-338ER, VH-OGN

Safety Action

LOCAL SAFETY ACTION

Following this and other similar occurrences, Airservices Australia has changed the TAAATS system to reduce the possibility of similar false radar couplings. This change consisted of adding an additional longitudinal check that limits the size of the Coupling Corridor to within a defined Variable System Parameter (minutes) ahead and behind the estimated position of the aircraft based on FDP time estimates. Initially this parameter was set to 12 minutes. This additional longitudinal check was only to be applied for Flight plans that were "Active" or "Inhibited".

The software carrying this fix was installed in the ML FIR on the night of January 17th, 2001, and in the BN FIR on the night of May 10th, 2001.

Analysis

In the TAAATS Eurocat Radar Data Processor, coupling between Radar tracks and Flight Plans was limited to a corridor around the flight plan route - ahead of the last overflown position. This significantly restricted the chances of false coupling to aircraft squawking incorrect SSR codes.

In geographically small systems with relatively saturated radar coverage, this was very effective and anomalies are usually easily determined and rectified. However, with the geographical extent of TAAATS en-route system, and the reliance in TAAATS on Flight Plan tracks for separation purposes, the possibility and ramifications of false couplings assumes greater significance.

A solution was to longitudinally restrict the coupling corridor to a time/distance ahead and behind the estimated position of the aircraft based on Flight Data Processor (FDP) time estimates.

Unless the non-radar controller observed the flight plan track and jurisdiction strip deletion, no cues other than the controllers memory or scratch pad notes existed of the presence of the flight and the controllers situational awareness was severely compromised.

The radar controllers in Sydney may not have noticed the newly coupled radar track and if they did, it may have been disregarded as a false coupling.

Summary

The flight plan track, which was an on-screen indication showing the location of the Boeing 767 (B767) aircraft while outside radar coverage, disappeared from the air situation display while the crew was receiving an air traffic control service. This loss of display resulted in the controller loosing situational awareness and no separation or SAR alerting service being provided to the aircraft.

The controller observed the aircraft's flight plan track overhead Oodnadatta at 1727 Central Summer Time. At 1736 the crew reported their position overhead AGAGO, the controller had no on-screen indication of the B767 as the flight data record for the aircraft no longer existed. All indications of the aircraft had been removed from the controller's screen.

An investigation carried out by Airservices Australia revealed that the crew of an aircraft close to Sydney was cycling through SSR codes on its transponder and momentarily squawked the code that was assigned to the flight data record of the aircraft near Oodnadatta. The received transponder return was a valid code within the coupling corridor associated with that aircraft's track. That scenario caused a false radar coupling that resulted in The Australian Advanced Air Traffic System (TAAATS) automatically modifying the flight data record, which resulted in the deletion of the flight plan track and the controller's jurisdiction strip. That sequence of events displayed a coupled radar track for 10 seconds. However, the track was outside of the controllers displayed range.

A flight data record may couple on either the Previous SSR code (PSSR) or Assigned SSR code (ASSR), there was no indication to the controller on which of these codes the flight data record had coupled unless the controller selected "SSR ALL" to determine the squawked code. The PSSR is the code assigned by the previous control authority, in the receiving control authority TAAATS attempts to retain this code. The aircraft PSSR was the code assigned by the Singapore Control Authority and was retained by Brisbane and Melbourne TAAATS. This code was one normally used for code allocations to Visual Flight Rules flight data records.

Occurrence summary

Investigation number 200000520
Occurrence date 09/02/2000
Location AGAGO, (IFR)
Report release date 05/09/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer The Boeing Company
Model 767
Registration VH-OGN
Serial number 25576
Sector Jet
Operation type Air Transport High Capacity
Departure point SINGAPORE
Destination Sydney, NSW
Damage Nil

Piper PA-38-112, VH-ZWG

Summary

The Piper Tomahawk aircraft was being used to conduct a series of touch-and-go landings during a dual instructional flight. During the climb after the second take-off, and when the aircraft was at a height of about 200 ft, the engine failed without warning. The instructor manoeuvred the aircraft to avoid landing in a lake located just beyond the end of the runway and landed in an adjacent paddock. Although the aircraft hit some low bushes during the landing roll, the pilots were not injured, and the aircraft was not damaged.

The aircraft was moved to a maintenance facility and, prior to conducting any maintenance or inspections, the engine was started and ground-run without any obvious problems. The maintenance inspection revealed a contact mark had been worn through the Teflon coating of the wear area of the carburettor float needle. When the carburettor was reassembled and tested, it was found that the carburettor float needle would stick in the valve seat and prevent fuel flowing into the carburettor bowl. The float needle and seat were replaced, and the aircraft test-flown without further incident.

Occurrence summary

Investigation number 200000313
Occurrence date 31/01/2000
Location Point Cook, Aero.
State Victoria
Report release date 01/08/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Fuel starvation
Occurrence class Incident
Highest injury level None

Aircraft details

Manufacturer Piper Aircraft Corp
Model PA-38
Registration VH-ZWG
Serial number 38-78A0234
Sector Piston
Operation type Flying Training
Departure point Essendon, VIC
Destination Essendon, VIC
Damage Nil

Cessna 182Q, VH-LMH

Summary

The pilot reported that while in cruise flight over water, the C182 aircraft was subjected to a strong downdraft. The pilot immediately reduced engine power to slow the aircraft in anticipation of further turbulence. Having established the desired airspeed, the pilot attempted to re-apply power but the engine did not respond. He selected carburettor heat and attempted several times to start the engine.

As there was no suitable landing area on nearby Huon Island, the pilot ditched the aircraft 1 km from the mainland shore. Three of the four occupants exited the aircraft unassisted; the fourth had to be pulled free by the pilot. All then made their way to the shoreline.

Subsequent salvage attempts were unable to locate the wreckage. Consequently, to assess the airworthiness of the aircraft, the investigation could examine only the aircraft documentation. No deficiencies that might have contributed to the accident were identified.

Information provided by the Bureau of Meteorology indicated that atmospheric conditions at the time of the engine failure were conducive to the formation of moderate to severe carburettor icing. The formation of ice in the carburettor venturi can result in partial or complete loss of power. Contamination of the fuel system was also considered. However, the aircraft operator said that the aircraft had not been fuelled from known contaminated batches.

The investigation could not determine why the engine failed. However, it is possible that carburettor icing formed after the pilot reduced power in response to the turbulent conditions.

Occurrence summary

Investigation number 200000190
Occurrence date 21/01/2000
Location 1 km S Verona Sands
State Tasmania
Report release date 01/08/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Ditching
Occurrence class Incident
Highest injury level Minor

Aircraft details

Manufacturer Cessna Aircraft Company
Model 182
Registration VH-LMH
Serial number 18266830
Sector Piston
Operation type Charter
Departure point Cambridge, TAS
Destination Melaleuca, TAS
Damage Destroyed

British Aerospace Plc BAe 146-300, VH-NJL

Summary

While en route from Darwin to Gove, the master warning system of the BAe 146 chimed and the crew noticed that the engine vibration indication for the number four engine was fluctuating between 0.6 and 2.0 inches per second. All other engine indications appeared normal. The pilot in command switched off the thrust management system, retarded the number four engine power lever to idle and switched off the associated bleed air. At the same time, a loud series of thuds were heard and the master warning system again chimed, alerting the crew to low oil pressure indications for this engine. The pilot in command and the first officer then noticed smoke in the cabin when they looked back through the flight deck door. The crew donned oxygen masks and completed the "smoke or fire in cabin" and "engine fire or severe damage" checklists. ATC was notified and a return to Darwin requested. With the diversion approved and a distress phase declared, the subsequent return and one-engine-inoperative landing were uneventful. Company maintenance inspection found the number four-engine could not be rotated and had incurred severe internal damage.

The manufacturer inspected the engine and found that the number 1 bearing pack had failed. The pinion gear retention nut backed off, and had misaligned the gears, causing metal contamination in the oil supply from the improperly meshed gear teeth. The failure of the bearing pack in turn caused major internal damage to other parts of the engine as the high-pressure compressor shaft was allowed to orbit within the engine. The reason the pinion gear nut lost tension could not be determined.

The manufacturer indicated that the incidence of failure of the pinion gear retention nut is very low, with a mean time between failure of 2.9 million fleet hours. As a result, the ATSB does not believe further safety action is necessary.

The company investigation also identified several other issues associated with this occurrence that are being addressed:

  1. The quality of communications between cabin crew and cockpit crew using the dedicated emergency-in-cabin (EIC) call facility;
  2. The clarity of audio when the crew were wearing oxygen masks; and
  3. Formalising procedures for medical examinations and counselling after the event.

The operator will advise the ATSB if any safety action is taken.

The cabin crew reported minor and temporary eye irritation and sinus discomfort from the smoke during the incident. The medical examinations the following week did not find anything notable. The pilot in command and first officer did not seek medical attention after the incident.

Occurrence summary

Investigation number 200000176
Occurrence date 21/01/2000
Location 241 km E Darwin, (NDB)
State Northern Territory
Report release date 30/04/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Abnormal engine indications
Occurrence class Incident
Highest injury level None

Aircraft details

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

Cessna 210M, VH-NOK

Summary

On the morning of the accident, the pilot woke at 0530 Central Summer Time (CSuT) and started duty at 0630. The pilot had undertaken an Instrument Flight Rules (IFR) Regular Public Transport (RPT) check flight in a Cessna 402 for 2.3 hours during the mid-morning on the day of the occurrence. The pilot's performance during the check flight was considered above average. The pilot was then tasked by the company for a Visual Flight Rules (VFR) charter flight in a Cessna 210. Towards the end of this substantial tour of duty, the pilot entered the Croker Island circuit for an approach to runway 31 at about 1806. During final approach, the pilot did not recall any auditory landing gear warnings, nor did he recall the status of the landing gear indicator lights. The pilot proceeded to land the aircraft with the landing gear retracted. This event occurred at approximately 1813 (CSuT). The pilot and five passengers were unharmed and evacuated the aircraft.

The pilot reported that he was fatigued during the flight and that the landing gear pump circuit breaker had popped on the final leg to Croker Island. The pilot recycled the landing gear pump circuit breaker and realised that the electric motor was still running. The pilot subsequently elected to pull the circuit breaker to prevent damage to the electric motor. This procedure was executed in accordance with the Cessna 210 Information Manual recommendation that when the hydraulic pump continues to run after gear cycle completion (up or down), the gear pump circuit breaker should be pulled out to shut off the hydraulic pump motor, thereby preventing damage to the pump and motor. The circuit breaker must be re-engaged prior to landing so that the landing gear can been extended (sections 3-20 & 7-12 of Cessna 210 Information Manual). On approach to Croker Island, the pilot selected the landing gear down but forgot to re-engage the landing gear pump circuit breaker. Consequently, the wheels did not deploy.

The pilot reported that the aircraft had sustained damage to the propeller and the underside of the aircraft. An initial engineering inspection revealed no apparent damage to the engine crankshaft or other engine components. A maintenance engineer from the company's contracted maintenance organisation found the landing gear handle in the fully extended position and the landing gear pump circuit breaker disengaged.

The pilot had accrued 2286.9 hours of flight time, of which 785.0 hours were on the Cessna 210. The pilot was considered as above average and very capable by both the chief pilot and the check-and-training officer. The pilot had flown five aircraft types in the week preceding the occurrence.

The maintenance release indicated no problems with the landing gear. The pilot reported that the Cessna 210 was well maintained and serviceable prior to flight.

The company did not have a documented procedure for the actions required when the landing gear hydraulic pump continues to run when the landing gear has been retracted. The Cessna 210 Information Manual recommends that when the hydraulic pump continues to run after gear cycle completion (up or down), the gear pump circuit breaker should be pulled out to shut off the hydraulic pump motor, thereby preventing damage to the pump and motor. The circuit breaker must be re-engaged prior to landing so that the landing gear can been extended (sections 3-20 & 7-12 of Cessna 210 Information Manual). The pilot reported that he was familiar with this procedure as annotated in the Cessna 210 Information Manual. The pilot also reported that the landing gear warning systems were tested and found to be fully functional prior to flight. These systems include the landing gear intermittent warning tone and gear indicator lights.

The pilot did not recall hearing any audio warning indicating that the gear had not extended until the aircraft was on the ground. In addition, the pilot did not recall the status of the landing gear indicator lights prior to landing. Finally, the pilot did not visually confirm the extension of the landing gear.

The pilot reported that he was very tired on the day of the occurrence and that he had been tired for some time leading up to the accident. The pilot's work/rest history for the 14 weeks before the accident was examined using a computerised fatigue algorithm developed by the Centre for Sleep Research, University of South Australia. The results indicated that the pilot was probably not suffering severely from cumulative fatigue on the day of the accident. On the day of the occurrence, however, the pilot reported feeling tired and he had been on duty for almost 12 hours before the accident. Moreover, he had been awake for almost 14 hours before the accident.

The pilot probably suffered from a transient fatigue related memory lapse where he forgot to re-engage the landing gear pump circuit breaker before landing and failed to visually check that the landing gear was down and locked.

Occurrence summary

Investigation number 200000148
Occurrence date 17/01/2000
Location Croker Island, Aero.
State Northern Territory
Report release date 09/08/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Wheels up landing
Occurrence class Accident
Highest injury level None

Aircraft details

Manufacturer Cessna Aircraft Company
Model 210
Registration VH-NOK
Serial number 210-62063
Sector Piston
Operation type Charter
Departure point Smith Point, NT
Destination Croker Island, NT
Damage Substantial

Robinson R22 Beta, VH-JHZ

Summary

The helicopter was being used to conduct basic helicopter training at Jandakot. There was an accumulation of raindrops on the helicopter's canopy due to showers that had recently passed through the area. The instructor reported that both he and the student were getting hot from prolonged hovering and that he decided that a short flight was needed to cool the cockpit. The instructor took control of the helicopter from the student and transitioned into forward flight, climbing at about 35 kts to approximately 50 ft before commencing a continuous left turn to return to the hover. The instructor reported that while he was looking out to his left at the area where he intended arriving, he realised that the helicopter was too low to the ground. The helicopter's left skid hit the ground then the helicopter rolled right and the main rotor blades hit the ground. The helicopter then cartwheeled two or three times before skidding and coming to rest on its right side. The fuel tanks ruptured and the helicopter caught fire. Just after both pilots escaped through the front of the shattered canopy, the wreckage exploded. The student sustained minor injuries while the instructor suffered burns to his right arm and head. The pilots were not wearing helmets. The pilots reported that the helicopter was operating normally before it hit the ground. The investigation could not determine if the raindrops that had accumulated on the canopy had affected the instructor's visual perception.

Occurrence summary

Investigation number 200000125
Occurrence date 17/01/2000
Location Jandakot, Aero.
State Western Australia
Report release date 08/08/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Aviation
Aviation occurrence category Collision with terrain
Occurrence class Accident
Highest injury level Serious

Aircraft details

Manufacturer Robinson Helicopter Co
Model R22
Registration VH-JHZ
Sector Helicopter
Operation type Flying Training
Departure point Jandakot, WA
Destination Jandakot, WA
Damage Destroyed

Steering gear failure on the Australian flag motor Warden Point

Final report

Summary

On 9 November 1999, the Australian flag bulk carrier Warden Point was southbound off the north coast of New South Wales, en route to Melbourne, with a cargo of fly ash. At about 0230, the weather changed due to an intense low-pressure system approximately 300 nautical miles to the south. By 0800 the vessel was experiencing near gale force winds from the south. The vessel was pitching heavily in large seas submerging the lower poop deck, at times, under 2-3 m of water.

At 1400, the duty engineer reported that the rope locker hatch lid, on the lower poop deck, was leaking and that water had entered the rope locker and adjoining steering flat. The crew subsequently managed to reseal the hatch lid after some problems due to waves that were periodically sweeping the deck and running over the hatch.

At 2330, Australian Eastern Standard Time (EST), the second mate came on the bridge to take the watch. After the watch was handed over, he instructed the 12-4 integrated rating (IR) to go through the accommodation and advance the clocks 1 hour, he also instructed the IR to check the rope locker and steering flat. The IR rang back a short time later to report that the rope locker and steering flat were awash and that the water was running over the steering motors. The second mate started the stand-by steering motor and called the duty engineer. Just as he put the phone down one steering motor failed, followed by the other motor about 10 seconds later. The second mate stopped the ship and called the master. The time was 0115, Australian Eastern Summer Time (EDT), 10 November 1999, with the vessel east of Sugarloaf Point, north of Newcastle. Once the vessel lost headway it became beam-on to the large sea and rolled heavily.

All the engineers and integrated ratings were called to the engine room to work on restoring the steering and pumping the steering flat and rope locker dry. Both steering motors were dismantled and found to be damaged beyond repair. There was no spare motor so the lower rated stand-by main engine jacket cooling water pump motor was used to make an emergency repair. While the crew were completing the emergency repairs to the steering the cargo shifted, causing a port list of 2-3° and a noticeable trim by the head.

At 0852 on 10 November 1999, with the steering finally restored, the vessel headed for Newcastle, the nearest port of refuge, to effect permanent repairs. However, Newcastle Port closed at 1526 on 10 November 1999, due to the bad weather, and the decision was made to divert Warden Point to Port Kembla.

Warden Point arrived at the Port Kembla pilot boarding ground at 1000 on 11 November 1999 by which time the list had increased to over 5°. The steering was limited to a maximum of 15° helm and the vessel was berthed using two tugs. At 1236, the vessel was finally made fast alongside no.1 coal berth. The ships engineers and shore contractors worked into the night on the steering gear and rope locker hatch lid. The cargo was inspected and found to have moved in both holds. The list was corrected by re-trimming the cargo in no.1 hold.

Warden Point departed Port Kembla at 0830 on 12 November 1999 and completed the voyage to Melbourne without further incident.

Conclusions

These conclusions identify the different factors contributing to the incident and should not be read as apportioning blame or liability to any particular organisation or individual.

On 9,10, 11 November 1999 Warden Point experienced a series of events in which the ship suffered significant damage and which endangered the vessel and crew.

1. The initial failure of Warden Point's steering gear was a result of the steering pump motors failing after contact with seawater.

2. The seawater gained access to the steering gear flat via the two lowest penetrations in the bulkhead between the steering flat and the adjacent rope locker, which had been flooded as a result of its leaking hatch lid.

3. The rope locker hatch lid leaked as a result of seawater over the lower poop deck, and the poor seal between the hatch lid and the hatch coaming. The rope locker hatch lid had not been maintained in a watertight condition in that the worn dogs and wedges were not exerting sufficient clamping pressure to secure the hatch lid given the recent fitment of soft new sealing rubber.

4. The seawater contamination of the fuel service tanks was a result of poorly maintained breather vents and the weight of seawater over the vents in the poor weather conditions.

5. The vessel's initial list to port was a result of the fly ash cargo shifting. The shift of cargo was the direct result of the movement of the vessel when lying starboard beam-on to the large sea.

Although not contributing factors, it is further considered that:

6. The initial stability conditions for the vessel should have been calculated after completion of loading at Gladstone. Some assessment of the vessel's stability should also have been made after the cargo had shifted.

7. Safety harnesses and lifelines would have minimized the risk of crew members being swept overboard when working on resealing the rope locker hatch while the lower poop deck was being regularly swamped by waves.

8. The absence of a bilge alarm fitted in either the rope locker or steering flat prevented the crew being alerted to the water ingress in sufficient time to avert the failure of the steering motors.

9. The knowledge of the transportation properties of the Gladstone power station fly ash is insufficient; an accurate stowage factor needs to be ascertained and the 'cohesive' categorisation of the cargo reviewed. Adequate measures also need to be prescribed to minimise the risk of cargo shifting in adverse conditions.

10. The decision to divert the vessel to Port Kembla, rather than a closer port of refuge, may have unnecessarily endangered the vessel and crew with the continued movement of the cargo.

11. The efforts of the crew on the days of 9,10, 11 November, in resealing the rope locker hatch, restoring the steering and navigating Warden Point safely to port in such adverse conditions, were commendable.

Occurrence summary

Investigation number 152
Occurrence date 10/11/1999
Location Off east coast, Australia
State New South Wales
Report release date 04/06/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Marine
Marine occurrence category Equipment
Occurrence class Incident
Highest injury level None

Ship details

Name Warden Point (formerly Red Sea)
IMO number 7636822
Ship type Bulk carrier
Flag Australia
Departure point Port Kembla, NSW
Destination Melbourne, Vic

Collision involving Craig The Pioneer and FV May Bell II

Final report

Summary

At 0155 on 9 October 1999, the prawn trawler May Bell II was about 50 miles east of Newcastle, NSW, heading slowly west. The skipper and the deckhand were recovering their nets when the deckhand heard the sound of a ship's wash just forward of the trawler. He ran to the wheelhouse where he put the engine full astern but, a few seconds later, the two vessels came into contact.

The deckhand sounded the trawler's horn, leaving it on, but there was no answering signal from the ship. He was unable to make out a stern light or the ship's name on the stern as the ship continued on towards the northeast.

The bow of the trawler was holed by the impact, but there was no ingress of water. The skipper called Sydney Radio on VHF (very high frequency radio) to say that the trawler had been struck by a ship, informing the station of the position and time of the collision and adding that he was returning to Sydney.

The trawler returned to Sydney that afternoon, whereupon the Australian Transport Safety Bureau (ATSB) interviewed the crew and obtained samples of paint deposited, as a result of the collision, on the stem of the trawler.

AusSAR, the Australian search and rescue organisation, provided the ATSB with a surface picture (surpic) of ships in the area at the time of the collision. Positions were obtained from certain ships on the surpic and a woodchip carrier, Craig The Pioneer, was close enough to the position of the collision to warrant further investigation.

When Craig The Pioneer arrived at Bell Bay in Tasmania in November 1999, interviews were conducted with the master, deck officers and the AB (able-bodied seaman) who had been on watch with the 2nd mate. The 2nd mate and AB, who had been on the navigation watch at the time, denied all knowledge of the incident stating that they had not seen the trawler either visually or by radar.

The ATSB also obtained paint samples from the ship. Paint samples from both vessels were analysed by the Scientific Unit, Forensic Services, of the Australian Federal Police at Canberra, the report concluding that there was strong evidence that the ship and fishing vessel had come into contact.

Conclusions

These conclusions identify the different factors contributing to the incident and should not be read as apportioning blame or liability to any particular organisation or individual.

  • On the basis of the positions of both vessels and the analysis of paint samples from the fishing vessel and the ship, the Inspector is satisfied that Craig The Pioneer collided with May Bell II.
  • Those on watch on the bridge of Craig The Pioneer did not maintain a proper lookout either by sight or by radar. Under the conditions of optimum visibility at the time of the incident, the lookout being maintained on board the ship would have to be considered seriously deficient to miss seeing the trawler prior to the collision.
  • The skipper and deckhand of the trawler were on deck, concentrating on retrieving nets, when the collision occurred and were not keeping a proper lookout.
  • The vision of both the skipper and deckhand of the trawler was significantly impaired from working under bright lights.

It is also considered that the fitting of a radar reflector or similar device to the fishing vessel to enhance its radar returns would have increased the likelihood of it being detected by a ship.

Occurrence summary

Investigation number 151
Occurrence date 09/10/1999
Location Off Port Stephens
State New South Wales
Report release date 28/02/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Marine
Marine occurrence category Collision
Occurrence class Incident
Highest injury level None

Ship details

Name Craig The Pioneer
IMO number 8519370
Ship type Woodchip carrier
Flag Liberia
Departure point Newcastle
Destination Bell Bay, Tasmania

Ship details

Name May Bell II, LFB 11725
IMO number N/A
Ship type Fishing vessel
Flag Australia
Departure point 50 miles east of Newcastle

Shift of cargo aboard the general cargo vessel Sun Breeze

Final report

Summary

The Panamanian flag general cargo vessel Sun Breeze berthed at the West Australian port of Bunbury on 16 August 1999 to load a cargo of sawn timber.

The vessel loaded packs of timber of various sizes, most of which had no weights marked on them. During loading, the master estimated weights of cargo loaded in each of the vessel's two hatches by draught survey. When the hatches were full, the weight of cargo loaded on the hatch tops and deck was limited by the master's requirement to maintain a minimum metacentric height (GM) of 50 cm.

After loading was completed on 21 August, the vessel's GM, after allowing for free surface effects in certain tanks, was calculated to be 47 cm.

After lashing of the deck cargo was completed, Sun Breeze sailed at 1800 the same day for China. The vessel was upright when the harbour master piloted it from the port. After the harbour master disembarked, the engine revolutions were increased to sea speed at 1830.

When the master left the bridge, the 3rd mate changed the steering from manual to autopilot, at which time the ship started turning to starboard on its own accord. He changed back to manual steering, ordering helm to bring the vessel back on course. The vessel then seemed to him to list initially to port before listing to starboard.

The master returned to the bridge, by which time the list was about 15° or 20° to starboard. He stopped the engine and the list increased before settling at about 25°. The vessel lost some packs of timber from no. 1 hatch top over the side at this time. A distress message was sent out at about 1848 before the master anchored the vessel at 1900. The harbour master went out to the ship and non-essential crewmembers were disembarked by a tug.

The master corrected the list by ballasting side tanks. He advised the owner of the ship of the situation and obtained permission from the harbour master to re-enter the port after a surveyor had verified the vessel's stability.

The vessel berthed at Bunbury once more at 1310 on the 22nd August. The cargo was restowed and secured and the amount of deck cargo was reduced, after which the vessel sailed for the discharge port in China, where it arrived safely on 10 September 1999.

Conclusions

These conclusions identify the different factors contributing to the incident and should not be read as apportioning blame or liability to any particular organisation or individual.

Based on all the evidence available, the following factors are considered to have contributed to the incident:

  1. All fuel, diesel, fresh water and some ballast tanks were slack, reducing the vessel's stability.
  2. The cargo in the holds and tween decks was not secured to prevent movement in a seaway in accordance with the approved cargo securing manual.
  3. The ship's stability was based on an inclining experiment that did not meet IMO approved standards. As a result, the position of the lightship centre of gravity is in question.
  4. The stability information supplied to the ship contained incorrect data on free surface moments.
  5. Packages of timber were not marked with their weights and the master had to estimate weights in each compartment by draught survey.
  6. The lashings at hatch no. 1 were incorrectly set up, opening to permit the cargo to be lost overboard after the vessel listed.
  7. The voyage instructions mentioned lashings for the deck cargo. It made no mention of securing arrangements for cargo in the hatches.
  8. The master did not have a copy of the charter party, neither was he informed of correct stowage factors or weights of the type of cargo to load. He did not have sufficient information with which to prepare a proper loading plan and exercise proper oversight of loading.
  9. The owner, master and the vessel's agent did not inform the Australian Maritime Safety Authority that the vessel would be loading timber deck cargo.
  10. The master did not have a copy of the code of safe practice for the carriage of timber deck cargoes, neither did the ship's approved cargo securing manual include timber deck cargoes.
  11. The stability calculations did not allow for absorption of water by the deck cargo or for consumption of fuel from low tanks once the vessel was at sea.

In addition, the Inspector considers that the master would have been justified in delaying loading of the cargo until he was given all information necessary to ensure the ship's safety.

Occurrence summary

Investigation number 150
Occurrence date 21/08/1999
Location Bunbury
State Western Australia
Report release date 07/06/2001
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Marine
Marine occurrence category Cargo shift
Occurrence class Incident
Highest injury level None

Ship details

Name Sun Breeze
IMO number 9197179
Ship type General cargo
Flag Panama
Departure point Bunbury, WA
Destination China

Release of oil from the Italian flag motor tanker Laura D'amato

Final report

Summary

The Italian flag tanker Laura D'Amato berthed at the Shell Terminal Gore Bay Sydney, at 1224 on 3 August 1999, with about 90,957 tonnes of Murban Crude Oil. The loading arms were connected to the ship, the tank ullages measured and the quantity of oil on board checked. The mate and the Shell shore officer conferred and signed the 'Ship/Shore Safety' checklist. The checklist was also counter signed by a Sydney Ports inspector.

At 1412, the ship commenced discharging using no. 2 cargo pump. Initially, the water bottoms were removed at a slow rate of pumping. At 1430, all the cargo tanks were opened to lower their levels and the discharge rate was increased to 1000 m/h. At 1650, some cargo tanks were shut, the rate was further increased to 1500 m/h, and the suction valves for the two slop tanks (six wings port and starboard) opened.

By about 1815, the mate decided the level of the slop tanks was falling too slowly. To draw more directly from these two tanks and to increase the rate of discharge, the mate decided to open no. 3 cargo line to no. 2 pump by opening two 'crossover' valves on the main sea line in the pumproom. At about 1820, he ordered the cadet to open the two valves.

At 1825, the Shell wharf watchkeeper was returning from a routine check of the loading arms and moorings, when he suddenly smelled a strong odour of hydrogen sulphide. He immediately contacted the shore officer reporting the smell and asking whether the ship was venting its tanks for any reason. It was established that this was not the case.

The wharf watchkeeper went back to the shore manifold but detected no sign of a leak. The smell of hydrogen sulphide was still strong and, as he checked the water between the ship and the shore, he detected a slick of oil, which he traced to the ship's port side. He reported to the shore officer, who immediately ordered the ship to stop pumping.

The ship's pumps were stopped at 1836. The Shell emergency plan was implemented immediately.

The mate, who had already ordered the cadet to close the two valves that he had just opened, then ordered the 3rd mate to stop the cargo pump. He went ashore to see if he could locate the source of the oil spill. The wharf watchkeeper showed him the position on the port side, of the vessel, where oil was seen to be welling to the surface of the water. The mate and the pumpman then went to the pumproom and checked all the valves. They found the two sea-chest valves on the sea suction line were fully open.

When the two men attempted to close the sea-chest valves, they found the large, manual, butterfly valves 'back-seated' open. To close the valves, both men had to use a large wheel key to break the seat. In closing the valves, any security seals placed between the two adjacent valve handles were broken.

At this point, the flow of Murban crude oil from Laura D'Amato into Gore Bay ceased.

Conclusions

These conclusions identify the different factors contributing to the incident and should not be read as apportioning blame or liability to any particular organisation or individual.

The factors which lead to the escape of crude oil cargo from Laura D'Amato into Sydney Harbour include but are not limited to:

  1. The sea-chest valves on the sea suction line adjacent to the port sea chest in the vessel's cargo pumproom were open.
  2. The use of the sea suction line as a cargo pump suction crossover line led to cargo filling the line and escaping through the open sea-chest valves overboard.
  3. The ship's cargo system did not provide for a separate designated cargo pump suction crossover line or some means of isolating the cargo system from direct connection to the sea chest.
  4. The presence, at various times, of seals placed between the sea-chest valves lead to a false assumption on the part of the ship's staff that the sea-chest valves must therefore be shut.
  5. The false assumption contributed to the fact that the ship's staff did not properly check the sea-chest valves, as required by the ISM Code procedure, the ISGOTT Guide and normal tanker operations, before loading in Jebel Dhanna and discharging in Sydney.
  6. There was no remote monitoring, on the cargo control console, of the positioning of the two sea-chest valves.
  7. The vessel's Safety Management System did not adequately detail the pressure test procedures to be carried out on the sea-chest valves each time they were to be checked for tightness.
  8. The independent cargo surveyor in Jebel Dhanna did not recognise that the sea-chest valves were, in fact, open.
  9. The Ship/Shore Checklist procedures, in Jebel Dhanna and Sydney, did not physically check and identify that the sea-chest valves were in a closed position.
  10. The probability is that the sea-chest valves were opened some time after leaving Zhanjiang and before arriving at Jebel Dhanna. There was no operational reason for opening these valves.

Occurrence summary

Investigation number 149
Occurrence date 04/08/1999
Location Sydney Harbour
State New South Wales
Report release date 24/02/2000
Report status Final
Investigation type Occurrence Investigation
Investigation status Completed
Mode of transport Marine
Marine occurrence category Pollution
Occurrence class Incident
Highest injury level None

Ship details

Name Laura D'Amato
IMO number 8907539
Ship type Tanker
Flag Italy
Departure point Zhanjiang
Destination Sydney, NSW