Crash of a Cessna 208B Grand Caravan off Pelée Island: 10 killed

Date & Time: Jan 17, 2004 at 1638 LT
Type of aircraft:
Operator:
Registration:
C-FAGA
Flight Phase:
Survivors:
No
Schedule:
Pelée Island – Windsor
MSN:
208B-0658
YOM:
1998
Flight number:
GGN125
Country:
Crew on board:
1
Crew fatalities:
Pax on board:
9
Pax fatalities:
Other fatalities:
Total fatalities:
10
Captain / Total flying hours:
3465
Captain / Total hours on type:
957.00
Aircraft flight hours:
7809
Circumstances:
On 17 January 2004, the occurrence pilot started his workday in Toronto, Ontario, reporting for duty at 0445 eastern standard time. In the morning, he completed flights in the Cessna 208B Caravan from Toronto to Windsor, Ontario, Windsor to Pelee Island, Ontario, and then Pelee Island to Windsor where the aircraft landed at 0916. At approximately 1500, the pilot received local weather and passenger information by telephone from the Pelee Island office personnel. The 1430 weather was reported as follows: ceiling 500 feet obscured, visibility two miles. There were eight male passengers for pick up at Pelee Island. One additional passenger was travelling with the pilot. There was no discussion concerning the amount of cargo to be carried or the passenger weights. At 1508, the pilot received a faxed weather package that he had requested from the Flight Information Centre (FIC) in London, Ontario. At 1523, the aircraft was refuelled in preparation for the scheduled 1600 departure to Pelee Island. The passengers were loaded earlier than usual to allow time for aircraft de-icing, as wet snow had accumulated on the fuselage and wings since the previous flight. At 1555, the aircraft was de-iced with Type 1 de-icing fluid, and it departed for Pelee Island at 1605 on an instrument flight rules (IFR) flight plan as Flight GGN125. At 1615, the pilot advised the Cleveland Control Centre, Ohio, United States, that he had Pelee Island in sight, was cancelling IFR, and was descending out of 5000 feet. The pilot also advised Cleveland that he would be departing IFR out of Pelee Island in about 20 minutes as GGN126 and asked if a transponder code could be issued. The Cleveland controller issued a transponder code and requested a call when GGN126 became airborne. The pilot advised that the flight would depart on Runway 27 then turn north. These were the last recorded transmissions from the aircraft. The aircraft landed at 1620. While on the ramp, two individuals voiced concern to the pilot that there was ice on the wing. Freezing precipitation was falling. The pilot was observed to visually check the leading edge of the wing; however, he did not voice any concern and proceeded with loading the passengers and cargo. At approximately 1638, GGN126 departed Pelee Island for Windsor. After using most of the runway length for take-off, the aircraft climbed out at a very shallow angle. No one on the ground observed the aircraft once it turned toward the north; however, witnesses who were not at the airport reported that they heard the sound of a crash, then no engine noise. A normal flight from Pelee Island to Windsor in the Cessna Caravan takes 15 to 20 minutes. Shortly after the aircraft departed, the ticket agent in Windsor received a call from Pelee Island reporting that a crash had been heard. At 1705, when the aircraft had not arrived, the ticket agent called Windsor tower. The pilot had not made contact with any air traffic services (ATS) facility immediately before or after departure, so there was nothing in the ATS system to indicate that the aircraft had taken off. It was, therefore, unaccounted for. There was no signal heard from the emergency locator transmitter (ELT). At 1710, the Windsor tower controller contacted the Rescue Coordination Centre in Trenton, Ontario, and a search was initiated. At 1908, the aircraft empennage and debris were spotted by a United States Coast Guard (USCG) helicopter on the frozen surface of the lake, about 1.6 nautical miles (nm) from the departure end of the runway. There were no survivors. The empennage sank beneath the surface some four hours later. The wreckage recovery was not fully completed until 13 days later.
Probable cause:
Findings as to Causes and Contributing Factors:
1. At take-off, the weight of the aircraft exceeded the maximum allowable gross take-off weight by at least 15 per cent, and the aircraft was contaminated with ice. Therefore, the aircraft was being flown significantly outside the limitations under which it was certified for safe flight.
2. The aircraft stalled, most likely when the flaps were retracted, at an altitude or under flight conditions that precluded recovery before it struck the ice surface of the lake.
3. On this flight, the pilotís lack of appreciation for the known hazards associated with the overweight condition of the aircraft, ice contamination, and the weather conditions was inconsistent with his previous practices. His decision to take off was likely adversely affected by some combination of stress and fatigue.
Findings as to Risk:
1. Despite the abbreviated nature of the September 2001 audit, the next audit of Georgian Express Ltd. was not scheduled until September 2004, at the end of the 36-month window.
2. The internal communications at Transport Canada did not ensure that the principal operations inspector responsible for the air operator was aware of the Pelee Island operation.
3. The standard passenger weights available in the Aeronautical Information Publication at the time of the accident did not reflect the increased average weight of passengers and carry-on baggage resulting from changes in societal-wide lifestyles and in travelling trends.
4. The use of standard passenger weights presents greater risks for aircraft under 12 500 pounds than for larger aircraft due to the smaller sample size (nine passengers or less) and the greater percentage of overall aircraft weight represented by the passengers. The use of standard passenger weights could result in an overweight condition that adversely affects the safety of flight.
5. The Cessna Caravan de-icing boot covers up to a maximum of 5% of the wing chord. Research on this wing has shown that ice accumulation beyond 5% of the chord can result in degradation of aircraft performance.
6. At the Pelee Island Airport, the air operator did not provide the equipment that would allow an adequate inspection of the aircraft for ice during the pre-flight inspection and did not provide adequate equipment for aircraft de-icing.
7. Repetitive charter operators are not considered to be scheduled air operators under current Transport Canada regulations, and, therefore, even though the charter air operator may provide a service with many of the same features as a scheduled service, Transport Canada does not provide the same degree of oversight as it does for a scheduled air operator.
8. A review of the Canadian Aviation Regulations regarding simulator training requirements indicates that there is no requirement to conduct recurrent simulator training if currency and/or pilot proficiency checks do not lapse.
9. Commercial Air Service Standard 723.91(2) does not clearly indicate whether there is a requirement for simulator training following expiration of a pilot proficiency check.
10. Incorrect information on the passenger door placards, an incomplete safety features card, and the fact that the operating mechanisms and operating instructions for the emergency exits were not visible in darkness could have compromised passenger egress in the event of a survivable accident.
11. The dogs being carried on the aircraft were not restrained, creating a hazard for the flight and its occupants.
Final Report:

Crash of a Boeing 737-3Q8 off Sharm el-Sheikh: 148 killed

Date & Time: Jan 3, 2004 at 0445 LT
Type of aircraft:
Operator:
Registration:
SU-ZCF
Flight Phase:
Survivors:
No
Schedule:
Sharm el-Sheikh - Cairo - Paris
MSN:
26283
YOM:
1992
Flight number:
FSH604
Country:
Region:
Crew on board:
13
Crew fatalities:
Pax on board:
135
Pax fatalities:
Other fatalities:
Total fatalities:
148
Captain / Total flying hours:
7443
Captain / Total hours on type:
474.00
Copilot / Total flying hours:
788
Copilot / Total hours on type:
242
Aircraft flight hours:
25603
Aircraft flight cycles:
17976
Circumstances:
Following a night takeoff from runway 22R at Sharm el Sheikh-Ophira Airport, the plane climbed and maneuvered for a procedural left turn to intercept the 306 radial from the Sharm el Sheikh VOR station. When the autopilot was engaged the captain made an exclamation and the autopilot was immediately switched off again. The captain then requested Heading Select to be engaged. The plane then began to bank to the right. The copilot then warned the captain a few times about the fact that the bank angle was increasing. At a bank angle of 40° to the right the captain stated "OK come out". The ailerons returned briefly to neutral before additional aileron movements commanded an increase in the right bank. The aircraft had reached a maximum altitude of 5,460 feet with a 50° bank when the copilot stated 'overbank'. Repeating himself as the bank angle kept increasing. The maximum bank angle recorded was 111° right. Pitch attitude at that time was 43° nose down and altitude was 3,470 feet. The observer on the flight deck, a trainee copilot, called 'retard power, retard power, retard power'. Both throttles were moved to idle and the airplane gently seemed to recover from the nose-down, right bank attitude. Speed however increased, causing an overspeed warning. At 04:45 the airplane struck the surface of the water in a 24° right bank, 24° nose-down, at a speed of 416 kts and with a 3,9 G load. The aircraft disintegrated on impact and debris sank by a depth of 900 metres. All 148 occupants were killed, among them 133 French citizens, one Moroccan, one Japanese and 13 Egyptian (all crew members, among them six who should disembark at Cairo). Weather at the time of accident was good with excellent visibility, outside temperature of 17° C and light wind. On January 17, the FDR was found at a depth of 1,020 metres and the CVR was found a day later at a depth of 1,050 metres.
Probable cause:
No conclusive evidence could be found from the findings gathered through this investigation to determine the probable cause. However, based on the work done, it could be concluded that any combination of these findings could have caused or contributed to the accident. Although the crew at the last stage of this accident attempted to correctly recover, the gravity upset condition with regards to attitude, altitude and speed made this attempt insufficient to achieve a successful recovery.
Possible causes:
- Trim/Feel Unit Fault (Aileron Trim Runaway),
- Temporarily, Spoiler wing cable jam (Spoiler offset of the neutral position),
- Temporarily, F/O wheel jam (Spoilers offset of the neutral position),
- Autopilot Actuator Hardover Fault.
Possible contributing factors:
- A distraction developing to Spatial Disorientation (SD) until the time the F/O announced 'A/C turning right' with acknowledgment of the captain,
- Technical log copies were kept on board with no copy left at departure station,
- Operator write up of defects was not accurately performed and resulting in unclear knowledge of actual technical status,
- There are conflicting signals which make unclear whether the captain remained in SD or was the crew unable to perceive the cause that was creating an upset condition until the time when the F/O announced that there was no A/P in action,
- After the time then the F/O announced 'no A/P commander' the crew behavior suggests the recovery attempt was consistent with expected crew reaction, evidences show that the corrective action was initiated in full, however the gravity of the upset condition with regards to attitude, altitude and speed made this attempt insufficient to achieve a successful recovery.
Additional findings:
- The ECAA authorization for RAM B737 simulator was issued at a date later than the date of training for the accident crew although the inspection and acceptance test were carried out at an earlier date.
- Several recorded FDR parameters were unreliable and could not be used for the investigation.
Final Report:

Crash of a PAC 750XL in the Pacific Ocean: 1 killed

Date & Time: Dec 26, 2003 at 0601 LT
Operator:
Registration:
ZK-UAC
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Hamilton – Pago Pago – Christmas Island – Kiribati – Hilo – Oakland
MSN:
103
YOM:
2003
Country:
Region:
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
16564
Captain / Total hours on type:
180.00
Aircraft flight hours:
65
Circumstances:
The pilot was ferrying the aircraft from Hamilton, New Zealand to Davis, California, via Pago Pago, American Samoa; Christmas Island, Kiribati; and Hilo, Hawaii. On the final leg, following a position report 858 nm from San Francisco, he reported a problem with his fuel system, indicating a probable ditching. Under the observation of a US Coast Guard HC-130 crew, the pilot ditched the aircraft at 1701 UTC, 341 nm from San Francisco, the aircraft nosing over on to its back as it touched down. The pilot did not emerge as expected and was later found by rescue swimmers, deceased, still in the cockpit. His body could not be recovered and was lost with the aircraft.
Probable cause:
The following findings were reported:
- The pilot was appropriately licensed, rated and experienced for the series of flights undertaken.
- The aeroplane had a valid airworthiness certificate and had been released to service.
- There was nothing (other than the item in 3.5) to suggest that the aeroplane was operating abnormally on the final flight.
- The aeroplane was being operated at 14 000 feet pressure altitude without supplementary oxygen as required by CAR 91.209 and 91.533.
- The left front fuel filler orifice was observed to be leaking fuel before departure.
- There was no attempt made to further investigate or correct this fuel leak and the pilot stated that it would stop once he departed.
- On most other aircraft this would be true, once the fuel level dropped away from the filler orifice and was no longer affected by aerodynamic suction.
- On the 750XL, the fuel system design was such that the front tanks were continuously topped up.
- The fuel loss would continue until all fuel in the rear tanks and the ferry system was consumed.
- The front fuel caps are thus critical items to be checked before flight.
- The fuel quantity uplifted at Hilo indicated that the problem had existed on the previous leg with a loss rate of up to 125 litres (33.2 US gallons) per hour.
- A comparison of the uplift figure with the expected consumption on the previous leg should have provided sufficient warning to the pilot that a problem existed.
- The existence of the problem could have been detected on the final flight by the shortened top-up intervals and by comparing fuel used by the engine with fuel remaining.
- Cumulative delays, especially including the longer than normal final refuelling time, probably influenced the pilot’s decision to depart without further checking the reason for the fuel leak or the apparent discrepancy between fuel figures.
- Cumulative fatigue, circadian rhythm and hypoxia were probably significant factors in the pilot’s failure to detect the fuel problem in flight, in time to make a safe return.
- By the time the pilot announced that he had a fuel problem, the only course of action open to him was ditching the aeroplane.
- The search and rescue facilities were activated appropriately, and had the potential to effect a successful rescue.
- The water entry impact on ditching was reasonably severe and probably incapacitated the pilot before he could vacate the cockpit.
Final Report:

Crash of a De Havilland DHC-3 Otter in Jellicoe: 2 killed

Date & Time: Dec 16, 2003 at 1200 LT
Type of aircraft:
Operator:
Registration:
C-GOFF
Flight Phase:
Survivors:
Yes
MSN:
65
YOM:
1954
Country:
Crew on board:
1
Crew fatalities:
Pax on board:
2
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
5016
Captain / Total hours on type:
540.00
Circumstances:
At approximately 0900 eastern standard time (EST), the pilot arrived at the airstrip and prepared the ski-equipped de Havilland DHC–3 (Otter) aircraft (registration C–GOFF, serial number 65) for the morning flight. This Otter was equipped with a turbine engine. Two passengers, with enough supplies for an extended period of time, including a snowmobile and camping gear, were to be flown to a remote location. The pilot loaded the aircraft and waited for the weather to improve. At approximately 1200 EST, the pilot and passengers boarded the aircraft and took off in an easterly direction. The aircraft got airborne near the departure end of the airstrip, and, shortly after take-off, the right wing struck a number of small bushes and the top of a birch tree. The aircraft descended and struck the frozen lake surface, approximately 70 feet below the airfield elevation in a steep, nose-down, right-wing-low attitude. When it came to rest, the aircraft was inverted and partially submerged, with only the aft section of the fuselage remaining above the ice. All of the occupants were wearing lap belts. The pilot and front seat passenger received fatal injuries. The rear seat passenger survived the impact and evacuated the aircraft with some difficulty due to leg injuries. The following morning, about 22 hours after the accident, a local air operator searching for the missing aircraft located and rescued the surviving passenger.
Probable cause:
Findings as to Causes and Contributing Factors:
1. The pilot attempted to take off from an airstrip that was covered with approximately 18 inches of snow, and the aircraft did not accelerate to take-off speed because of the drag; the aircraft was forced into the air and was unable to climb out of ground effect and clear the obstacles.
2. The pilot did not abort the take-off when it became apparent that the aircraft was not accelerating normally and before the aircraft became airborne.
Findings as to Risk:
1. Unidirectional G switches, which are found on many types of ELTs, do not always activate the unit when impact forces are not aligned with the usual direction of flight.
Other Findings:
1. The validity of the aircraft’s certificate of airworthiness was affected while it flew more flights than allowed by the ferry permit issued by Transport Canada.
2. The rear passenger seat was found to be installed incorrectly, contrary to de Havilland Alert Service Bulletin A3/49, dated 19 July 1991.
Final Report:

Crash of a Cessna 208B Super Cargomaster in Cody: 1 killed

Date & Time: Oct 29, 2003 at 0854 LT
Type of aircraft:
Operator:
Registration:
N791FE
Flight Type:
Survivors:
No
Schedule:
Casper – Cody
MSN:
208B-0289
YOM:
1991
Flight number:
FDX8773
Location:
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
11094
Captain / Total hours on type:
5821.00
Aircraft flight hours:
6885
Aircraft flight cycles:
6599
Circumstances:
ARTCC asked the pilot of Airspur 8773 if he would be able to execute the VOR instrument approach. The pilot said he could, but he wanted to "hold for a while to see if [the weather] gets a little better" [according to the METAR, visibility was 1.75 statute miles and there was a 200-foot overcast ceiling]. He was cleared to hold north of the VOR at 12,000 feet msl. While holding, the pilot filed the following PIREP indicating light rime icing. Shortly thereafter, he was cleared for the approach. Three witnesses saw the airplane on the downwind leg, just past midfield, at an estimated altitude of 500 feet. Shortly thereafter, one of them heard the engine "spool up to high power...[like reversing] the pitch of the propeller to slow down," and he thought the airplane had landed. Five witnesses said the airplane emerged from the overcast and banked "sharply to the left, then back to the right, then back to the left, then took a hard bank to the right," rolled inverted and struck the highway just south of the airport perimeter. The airplane slid down the embankment and out into a lake, becoming partially submerged. Witnesses said it was "snowing hard" and the highway was covered with 1 to 2 inches of slush. Wreckage examination revealed the flaps were down 30 degrees, the wing deice boots were "ribbed," and the inertial separator was open. According to the toxicological report, chlorpheniramine, desmethylsertraline, sertraline, and pseudoephedrine were detected in blood. In addition, chlorpheniramine, sertraline, phenylpropanolamine, and pseudoephedrine were detected in the urine. The urine also contained acetaminophen. Sertraline (trade name Zoloft) is a prescription antidepressant medication. According to the Guide for Aviation Medical Examiners, "The use of a psychotropic medication is considered disqualifying. This includes all... antidepressant drugs..." Chlorpheniramine is an over-the-counter sedating antihistamine used primarily for the treatment of allergies. Pseudophedrine (trade name Sudafed) is a decongestant. Acetaminophen (trade name Tylenol) is an over-the-counter pain reliever and fever-reducer. According to Dr. Stanley R. Mohler's "Medication and Flying: A Pilot's Guide," the adverse side effects of chlorpheniramine include drowsiness, dizziness, and lessened coordination. The side effects of pseudophedrine are usually mild and infrequent, but may include sleepiness, dizziness, restlessness, headache, and perhaps some loss of coordination and alertness or confusion.
Probable cause:
The pilot's failure to maintain aircraft control. Contributing factors include the pilot's failure to divert to an alternate airport, an inadvertent stall, and the snow and icing conditions.
Final Report:

Crash of a Socata TBM-700 in Dundee

Date & Time: Oct 24, 2003 at 1742 LT
Type of aircraft:
Operator:
Registration:
N700VA
Flight Type:
Survivors:
Yes
Schedule:
Edinburgh – Dundee
MSN:
233
YOM:
2002
Region:
Crew on board:
1
Crew fatalities:
Pax on board:
3
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
3170
Captain / Total hours on type:
65.00
Circumstances:
After an uneventful flight from Edinburgh the pilot made a visual approach to Runway 28 (landing distance available 1,400 metres) at Dundee. The pilot reported that the aircraft floated down the runway in the flare and bounced lightly on touchdown. During the bounce the aircraft initially yawed left and then rolled left in a normal pitch attitude with no stall warning. Full right rudder was applied but this was unable to correct the yaw. Power was applied to initiate a go-around, whilst maintaining full right rudder, but the pilot was unable to prevent the left wing from hitting the ground. This caused the aircraft to yaw rapidly to the left bringing one of its wheels into contact with a low wall. The pilot then reduced power and ditched in the River Tay, approximately 10 metres from the shore. The air traffic controllers on duty reported that the aircraft achieved a high nose attitude during the go-around before the left wing dropped and the aircraft veered to the left. The aircraft came to rest with the top of the fuselage out of the water and the pilot and passengers were able to evacuate though the main door and stand on the wing to await rescue by the airport's hovercraft. The hovercraft could only carry two passengers at a time thus the process was delayed resulting in the pilot and passengers suffering from mild hypothermia.
Final Report:

Crash of a PZL-Mielec AN-2TP in Urimán: 1 killed

Date & Time: Oct 11, 2003 at 1600 LT
Type of aircraft:
Operator:
Registration:
YV-1128C
Flight Phase:
Flight Type:
Survivors:
Yes
MSN:
1G238-12
YOM:
1990
Country:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Circumstances:
Shortly after takeoff from Urimán Airport, while in initial climb, the single engine aircraft stalled and crashed in the Caroni River. The captain was killed and the copilot was injured. The aircraft was destroyed. Possible engine failure.

Crash of a Convair CV-580F off Paraparaumu: 2 killed

Date & Time: Oct 3, 2003 at 2125 LT
Type of aircraft:
Operator:
Registration:
ZK-KFU
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Christchurch – Palmerston North
MSN:
17
YOM:
1952
Flight number:
AFZ642
Country:
Region:
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
16928
Captain / Total hours on type:
3286.00
Copilot / Total flying hours:
20148
Copilot / Total hours on type:
194
Aircraft flight hours:
66660
Aircraft flight cycles:
98774
Circumstances:
On Friday 3 October 2003, Convair 580 ZK-KFU was scheduled for 2 regular return night freight flights from Christchurch to Palmerston North. The 2-pilot crew arrived at the operatorís base on Christchurch Aerodrome at about 1915 and together they checked load details, weather and notices for the flight. The flight, using the call sign Air Freight 642 (AF642), was to follow a standard route from Christchurch to Palmerston North via Cape Campbell non-directional beacon (NDB), Titahi Bay NDB, Paraparaumu NDB and Foxton reporting point. The pilots completed a pre-flight inspection of ZK-KFU and at 2017 the co-pilot (refer paragraph 1.10.4) called Christchurch Ground requesting a start clearance. The ground controller approved engine start and cleared AF 642 to Palmerston North at flight level 210 (FL 210) and issued a transponder code of 5331. The engines were started and the aircraft taxied for take-off on runway 20. At 2032 AF 642 started its take-off on schedule and tracked initially south towards Burnham NDB before turning right for Cape Campbell NDB, climbing to FL210. The flight progressed normally until crossing Cook Strait. After crossing Cape Campbell NDB, the crew changed to the Wellington Control frequency and at 2108 advised Wellington Control that AF 642 was at FL210, and requested to fly directly to Paraparaumu NDB. The change in routing was common industry practice and offered a shorter distance and flight time with no safety penalty. The Wellington controller approved the request and AF 642 tracked directly to Paraparaumu NDB. At 2113 the Wellington controller cleared AF 642 to descend initially to FL130 (13 000 feet (ft)). The co-pilot acknowledged the clearance. At 2122 the Wellington controller cleared AF 642 for further descent to 11 000 ft, and at 2125 instructed the crew to change to the Ohakea Control frequency. At 2125:14, after crossing Paraparaumu NDB, the co-pilot reported to Ohakea Control that AF 642 was in descent to 11 000 ft. The Ohakea controller responded 'Air Freight 642 Ohakea good evening, descend to 7000 ft. Leave Foxton heading 010, vectors [to] final VOR/DME 076 circling for 25. Palmerston weather Alfa, [QNH] 987.' At 2125:34 the co-pilot replied ìRoger down to 7000 and leaving Foxton heading 010 for 07 approach circling 25 and listening for Alfa. Air Freight 642. At 2125:44 the Ohakea controller replied 'Affirm, the Ohakea QNH 987.' The crew did not respond to this transmission. A short time later the controller saw the radar signature for AF 642 turn left and disappear from the screen. At 2126:17 the Ohakea controller attempted to contact AF 642 but there was no response from the crew. The controller telephoned Police and a search for AF 642 was started. Within an hour of the aircraft disappearing from the radar, some debris, later identified as coming from AF 642, was found washed ashore along Paraparaumu Beach. Later in the evening an aerial search by a Royal New Zealand Air Force helicopter using night vision devices and a sea search by local Coastguard vessels located further debris offshore. After an extensive underwater search lasting nearly a week, aircraft wreckage identified as being from ZK-KFU was located in an area about 4 km offshore from Peka Peka Beach, or about 10 km north of Paraparaumu. Police divers recovered the bodies of the 2 pilots on 11 October and 15 October.
Probable cause:
The following findings were identified:
Findings are listed in order of development and not in order of priority.
- The crew was appropriately licensed and fit to conduct the flight.
- The captain was an experienced company line-training captain, familiar with the aircraft and route.
- The co-pilot while new to the Convair 580 was, nevertheless, an experienced pilot and had flown the route earlier in the week.
- The aircraft had a valid Certificate of Airworthiness and was recorded as being serviceable for the flight.
- The estimated aircraft weight and balance were within limits at the time of the accident.
- With a serviceable weather radar the weather was suitable for the flight to proceed.
- The captain was the flying pilot for the flight from Christchurch to Palmerston North.
- The flight proceeded normally until the aircraft levelled after passing Paraparaumu NDB.
- Why the aircraft was levelled at about 14 400 ft was not determined, but could have been because of increasing or expected turbulence.
- The weather conditions at around the time of the accident were extreme.
- The aircraft descended through an area of forecast severe icing, which was probably beyond the capabilities of the aircraft anti-icing system to prevent ice build-up on the wings and tailplane.
- The crew was probably aware of the presence of icing but might not have been aware of the likely speed and the extent of ice accretion.
- The rate of ice accretion might have left insufficient time for the crew to react and prevent the aircraft stalling.
- The transponder transmissions were impaired probably due to ice build-up on the aerials.
- The aircraft probably stalled because of a rapid build-up of ice, pitching the aircraft nose down and probably disorientating the crew. This could have resulted from a tailplane stall.
- Although the aircraft controls were probably still functional in the descent, a very steep nose down attitude, high speed and a potentially stalled tailplane, made recovery very unlikely.
- Under a combination of high airspeed and G loading, the aircraft started to break-up in midair, probably at about 7000 ft.
- Although there was no evidence to support the possibility of a mechanical failure or other catastrophic event contributing to the accident, given the level of destruction to ZK-KFU and that some sections of the aircraft were not recovered, these possibilities cannot be fully ruled out.
- The crew of AF 642 not being advised of the presence of a new SIGMET concerning severe icing should not have affected the pilotsí general awareness of the conditions being encountered.
- Had the crew been aware of the new SIGMET it might have caused them to be more alert to icing.
- Pilots awareness of the presence of potentially hazardous conditions would be increased if other pilots commonly sent AIREPs when such conditions were encountered.
- Operatorsí manuals, especially for IFR operators, might contain inadequate and misleading information for flight in adverse weather conditions.
- The search for the aircraft and pilots was competently handled in adverse conditions.
- The regular mandatory checks of the CVR failed to show that it was not recording on all channels.
- The lack of any intra cockpit voice recordings hampered and prolonged the investigation.
- The DFDR data and available CVR recordings provided limited but valuable information for the investigation.
- Had more modern and capable recorders been installed on ZK-KFU, significantly more factual information would have be available for the investigation, thus enhancing the investigation and increasing the likelihood of finding a confirmed accident cause, rather than a probable one.
- Had suitable ULB tracking equipment been available, the finding of the wreckage and recovery of the recorders would have been completed more promptly.
- The lack of tracking equipment could have resulted in the recorders not being found, and possibly even the wreckage not being found had it been in deeper water.
Final Report:

Crash of a Beechcraft 200 Super King Air off Funchal: 10 killed

Date & Time: Sep 11, 2003 at 2156 LT
Registration:
N600BV
Flight Phase:
Survivors:
No
Schedule:
Funchal – Málaga
MSN:
BB-254
YOM:
1977
Location:
Country:
Region:
Crew on board:
1
Crew fatalities:
Pax on board:
9
Pax fatalities:
Other fatalities:
Total fatalities:
10
Captain / Total flying hours:
332
Captain / Total hours on type:
10.00
Circumstances:
The twin engine aircraft departed Funchal-Santa Cruz Madeira Airport runway 05 at 2154LT on a charter flight to Málaga, carrying one pilot and nine Spanish passengers, three men, three women and three children aged 2, 4 and 7. During initial climb by night, at an altitude of 2,200 feet, the aircraft entered a cloud then entered a left turn and an uncontrolled descent. Forty seconds later, it crashed in the sea less than one km offshore, northeast of Caniçal. The aircraft disintegrated on impact and all 10 occupants were killed.
Probable cause:
The exact cause of the accident could not be determined with certainty. However, it is believed that the pilot lost control of the aircraft following a spatial disorientation.
Final Report:

Crash of a Beechcraft 1900D off Hyannis: 2 killed

Date & Time: Aug 26, 2003 at 1540 LT
Type of aircraft:
Operator:
Registration:
N240CJ
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Hyannis - Albany
MSN:
UE-40
YOM:
1993
Flight number:
US9446
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
2
Captain / Total flying hours:
2891
Captain / Total hours on type:
1364.00
Copilot / Total flying hours:
2489
Copilot / Total hours on type:
689
Aircraft flight hours:
16503
Aircraft flight cycles:
24637
Circumstances:
The accident flight was the first flight after maintenance personnel replaced the forward elevator trim cable. When the flightcrew received the airplane, the captain did not address the recent cable change noted on his maintenance release. The captain also did not perform a first flight of the day checklist, which included an elevator trim check. Shortly after takeoff, the flightcrew reported a runway trim, and manually selected nose-up trim. However, the elevator trim then traveled to the full nose-down position. The control column forces subsequently increased to 250 pounds, and the flightcrew was unable to maintain control of the airplane. During the replacement of the cable, the maintenance personnel skipped a step in the manufacturer's airliner maintenance manual (AMM). They did not use a lead wire to assist with cable orientation. In addition, the AMM incorrectly depicted the elevator trim drum, and the depiction of the orientation of the cable around the drum was ambiguous. The maintenance personnel stated that they had completed an operational check of the airplane after maintenance. The Safety Board performed a mis-rigging demonstration on an exemplar airplane, which reversed the elevator trim system. An operational check on that airplane revealed that when the electric trim motor was activated in one direction, the elevator trim tabs moved in the correct direction, but the trim wheel moved opposite of the corresponding correct direction. When the manual trim wheel was moved in one direction, the elevator trim tabs moved opposite of the corresponding correct direction.
Probable cause:
The improper replacement of the forward elevator trim cable, and subsequent inadequate functional check of the maintenance performed, which resulted in a reversal of the elevator trim system and a loss of control in-flight. Factors were the flightcrew's failure to follow the checklist procedures, and the aircraft manufacturer's erroneous depiction of the elevator trim drum in the maintenance manual.
Final Report: