Landing (descent or approach)

Flight Type:

Cargo

Survivors:

Shabeellaha Hoose (شبيلي السفلى)

Site:

Plain, Valley

Schedule:

Oostend – Cairo – Mogadishu

MSN:

129

YOM:

1980

Flight number:

TSY810

Location:

Afgooye

Country:

Somalia

Region:

Africa

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Circumstances:

The crew was performing a cargo flight from Ostend to Mogadishu with an intermediate stop in Cairo with perishable goods on board on behalf of the AMISOM, the African Mission in Somalia. The final approach to Mogadishu-Aden Abdulle International Airport was performed by night. As the crew was unable to localize the runway, he abandoned the approach and initiated a go-around procedure. A second attempt was also interrupted and the crew initiated a new go-around then continued towards the north of the capital city. Eventually, the captain decided to attempt an emergency belly landing near Afgooye, about 25 km northwest of Mogadishu. Upon landing, the aircraft lost its both engines and came to rest in the bush. Two crew members were taken to hospital while four others were uninjured. The aircraft was damaged beyond repair. According to Somalian Authorities, the International Airport of Mogadishu is open to traffic from 0600LT till 1800LT. For undetermined reason, the crew started the descent while the airport was already closed to all traffic (sunset at 1747LT). Also, an emergency landing was unavoidable, probably due to a fuel exhaustion. It is unknown why the crew did not divert to the alternate airport.

Probable cause:

When the controller received the estimated time of arrival for TSY810 from the Flight Information Center (FIC) Nairobi he advised FIC Nairobi (Kenya) that Mogadishu Airport was closed at the estimated time of arrival and advised the crew should divert to their alternate aerodrome but received no feedback. At 14:45Z the tower received first communication from the crew advising they would be overhead the aerodrome at 15:02Z, the controller advised again that the aerodrome would already be closed by then, the crew insisted however that they would land. Tower provided the necessary landing information like weather and active runway. At 15:02Z there was no sight of the aircraft, tower queried with the crew who reported still being 54nm out and revised their estimated time of arrival. At 15:27Z the aircraft turned final for runway 05, tower advised the crew to land at own discretion as tower's "instructions were only advisory and not clearance". The controller added that the approach was aborted and all subsequent approaches were unsuccessful too. "At one point the pilot mistook street parallel to the runway lighted by flood lights with intention of landing but was alerted the runway was on his right and the approach was discontinued. The crew has been warned numerous times that Mogadishu Airport closed at 1800LT (1500Z) and there is no adequate runway lights as the airport is not prepared to receive flights during night time hours. Thus, the pilot has intentionally tried to land at the airport while the visibility was limited to few metres due to darkness.

Final Report:

Crash of a BAe 146-300 in Tamale

Date & Time: Oct 6, 2015 at 0831 LT

Type of aircraft:

BAe 146

Operator:

Registration:

9G-SBB

Flight Phase:

Flight Type:

Scheduled Revenue Flight

Survivors:

Site:

De Havilland DHC-6 Twin Otter

Schedule:

Accra – Tamale

MSN:

E.3123

YOM:

1989

Flight number:

IKM110

Location:

Country:

Region:

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Circumstances:

After landing on runway 23 at Tamale Airport, the four engine aircraft failed to stop within the remaining distance. It went through a fence that was delimiting a work area as the runway was subject to an extension. Upon impact, the nose gear was torn off and the aircraft slid for few dozen metres before coming to rest. All 76 occupants escaped uninjured but the aircraft was damaged beyond repair. It was specified in a NOTAM that the runway 23 length was reduced to 1,860 meters and that works were in progress to extend runway 23, with the presence of men and equipment. So, caution was advised during landing and takeoff procedures.

Crash of a De Havilland DHC-6 Twin Otter 200 in Dubai

Date & Time: Oct 2, 2015

Type of aircraft:

Operator:

Registration:

DU-SD4

Flight Phase:

Flight Type:

Skydiving / Paratroopers

Survivors:

Site:

Schedule:

Dubai - Dubai

MSN:

132

YOM:

1968

Location:

Country:

Region:

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Circumstances:

Following an uneventful skydiving mission over the Dubai Drop Zone, the pilot was returning to his base. Upon landing on runway 06, the twin engine aircraft went out of control, veered off runway to the left, struck an embankment and came to rest with the right wing torn off. The pilot was uninjured and the aircraft was damaged beyond repair.

Crash of a Curtiss C-46A-45-CU Commando in Déline

Date & Time: Sep 25, 2015 at 1203 LT

Type of aircraft:

Curtiss C-46 Commando

Operator:

Registration:

C-GTXW

Flight Phase:

Flight Type:

Cargo

Survivors:

Site:

Schedule:

Yellowknife – Norman Wells

MSN:

30386

YOM:

1944

Flight number:

BFL525

Location:

Déline

Northwest Territories

Country:

Canada

Region:

Rockwell Grand Commander 680

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Circumstances:

The Buffalo Airways Curtiss C-46A (C-GTXW) was operating as flight 525 from Yellowknife, NT (YZF) to Norman Wells, NT (YVQ). While en route, approximately 140 nautical miles southeast of Norman Wells at 6500 feet above sea level, the crew noticed a drop in the right engine oil quantity indicator in conjunction with a propeller overspeed. The propeller pitch was adjusted to control the overspeed however, oil quantity indication continued to drop rapidly. A visual confirmation of the right engine nacelle confirmed that oil was escaping via the engine breather vent at an abnormally high rate. The right propeller speed became uncontrollable and the crew completed the "Prop overspeed drill". However, the propeller did not feather as selected. Several additional attempts were made to feather the propeller before it eventually feathered. The engine was secured and the shutdown checklist completed. The crew elected to divert to Tulita, NT (ZFN), but quickly determined that the descent rate would not permit that as an option. The only other option for diversion was Déline, NT (YWJ) where weather was reported at half a mile visibility and 300 feet ceiling. An emergency was declared with Déline radio. BFL525 was able to land at Déline however, the landing gear was not selected down to prevent further loss of airspeed resulting in a belly landing approximately midpoint of runway 08. The aircraft continued off the end of the runway coming to a stop approximately 700 feet beyond the threshold. The crew evacuated the aircraft sustaining no injuries however, the aircraft was destroyed.

Probable cause:

Buffalo Airways’ initial investigation revealed the engine oil scavenge pump had failed. No TSB-BST investigation was conducted on the event.

Crash of a Rockwell Grand Commander 680E in Boise

Date & Time: Sep 21, 2015 at 1620 LT

Type of aircraft:

Operator:

James R. Metzger

Registration:

N222JS

Flight Phase:

Flight Type:

Private

Survivors:

Site:

Schedule:

Weiser - Boise

MSN:

680E-721-28

YOM:

1959

Location:

Boise

Idaho

Country:

United States of America

Region:

De Havilland DHC-6 Twin Otter

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Captain / Total flying hours:

18000

Captain / Total hours on type:

2500.00

Aircraft flight hours:

7500

Circumstances:

The commercial pilot was conducting a personal flight. He reported that he did not recall what happened the day of the accident. One witness, who was former pilot, reported that he saw the airplane fly over his house and that the engines sounded as if they were "out of sync." A second witness, who lived about 5 miles away from the airport, reported that she saw the airplane flying unusually low. She added that the engines sounded terrible and that they were "popping and banging." A third witness, who was holding short of the runway waiting to take off, reported that he saw the airplane approaching the runway about 75 ft above ground level (agl). He then saw the airplane descend to about 50 ft agl and then climb back to about 75 ft agl, at which point the airplane made a hard, right turn and then impacted terrain. Although a postaccident examination of both engines revealed no evidence of a mechanical failure or malfunction that would have precluded normal operation, the witnesses' described what appeared to be an engine problem. It is likely that one or both of the engines was experiencing some kind of problem and that the pilot subsequently lost airplane control. The pilot reported in a written statement several months after the accident that, when he moved the left rudder pedal back and forth multiple times after the accident, neither the torque tubes nor the rudder would move, that he found several of the rivets sheared from the left pedal, and that he believed the rudder had failed. However, postaccident examination of the fractured rivets showed that they exhibited deformation patterns consistent with overstress shearing that occurred during the accident sequence. No preimpact anomalies with the rudder were found.

Probable cause:

The pilot's failure to maintain airplane control following an engine problem for reasons that could not be determined because postaccident examination of both engines and the rudder revealed no malfunctions or anomalies that would have precluded normal operation.

Final Report:

Crash of a De Havilland DHC-6 Twin Otter 200 in Louisburg

Date & Time: Sep 6, 2015 at 1540 LT

Type of aircraft:

Operator:

Registration:

N181CS

Flight Phase:

Survey / Patrol / Reconnaissance

Flight Type:

Survivors:

Site:

Schedule:

Washington - Louisburg

MSN:

181

YOM:

1968

Location:

Louisburg-North Raleigh

North Carolina

Country:

United States of America

Region:

Cessna 550 Citation Bravo

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Captain / Total flying hours:

7337

Captain / Total hours on type:

1058.00

Copilot / Total flying hours:

3187

Copilot / Total hours on type:

1180

Aircraft flight hours:

26915

Circumstances:

The airline transport pilot was conducting a cross-country aerial observation flight in the multiengine airplane. The pilot reported that the airplane was on the final leg of the traffic pattern when he reduced the power levers for landing and noticed that the right engine sounded like the propeller was moving toward the beta position. The pilot increased the engine power, and the sound stopped. As the airplane got closer to the runway, he decreased the engine power, and the sound returned. In addition, the airplane began to yaw right. The pilot applied left aileron and rudder inputs to remain above the runway centerline without success. While over the runway, the pilot reduced the engine power to idle, and the airplane continued to yaw right. The pilot applied full power in an attempt to perform a go-around; however, the airplane yawed about 30 degrees off the runway centerline, touched down in the grass, and impacted trees before coming to rest. The right wing, right engine, and right propeller assembly were impact-separated. The right engine propeller came to rest about 50 ft forward of the main wreckage, and it was found in the feathered position. A review of maintenance records revealed that the right propeller had been overhauled and reinstalled on the airplane 2 days before the accident and had operated 9 hours since that time. Subsequent testing of the right propeller governor revealed that it functioned without anomaly; however, the speed settings were improperly configured. Further, the testing revealed that the beta valve travel from the neutral position was out of tolerance. Although this could have let oil pressure port to one side of the spool or the other and, thus, changed the propeller blade angle, it could not be determined whether this occurred during the accident landing. Impact damage precluded examination of the right propeller governor control linkage; therefore, it could not be determined if it was inadequately installed or rigged, which could have resulted in the propeller moving into the beta position. The investigation could not determine why the right propeller moved toward the beta position as engine power was reduced, as reported the pilot.

Probable cause:

The propeller’s movement to the beta position during landing for reasons that could not be determined during postaccident examination and testing, which resulted in an attempted goaround and subsequent loss of airplane control.

Final Report:

Crash of a Cessna 550 Citation Bravo in Vienna

Date & Time: Sep 3, 2015 at 1227 LT

Type of aircraft:

Operator:

Registration:

OE-GLG

Flight Phase:

Charter/Taxi (Non Scheduled Revenue Flight)

Flight Type:

Survivors:

Site:

Schedule:

Salzburg - Vienna

MSN:

550-0977

YOM:

2001

Location:

Country:

Region:

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Captain / Total flying hours:

5000

Captain / Total hours on type:

1800.00

Copilot / Total flying hours:

1200

Copilot / Total hours on type:

350

Aircraft flight hours:

7525

Aircraft flight cycles:

5807

Circumstances:

Following an uneventful flight from Salzburg, the crew was cleared to descent to Vienna-Schwechat Airport. On approach to runway 34, the crew completed the checklist and lowered the landing gear when he realized the the left main gear remained stuck in its wheel well and that the green light failed to come on on the cockpit panel. The crew agreed to continue. After touchdown on runway 34, the aircraft deviated to the left, veered off runway and came to rest in a grassy area located near taxiway D and taxiway B5 and B6. All five occupants evacuated safely and the aircraft was damaged beyond repair.

Probable cause:

The accident was caused by a metallic foreign body between valve seat and ball of the spring loaded ball check valve in the undercarriage servo valve of the left main landing gear caused the check valve not to close as intended and hydraulic fluid was directed directly to the landing gear cylinder without moving the piston rod. Due to the fact that the piston rod of the undercarriage servo valve did not move as intended, the mechanical unlocking hook of the left undercarriage was also not controlled - the landing gear was therefore not deployed.
Contributing factors:
- The possibility to abort the approach, to Go Around and fly a holding to carry out troubleshooting, as described in the operations manual of the aviation company as well as in the "Emergency / Abnormal Procedures" manual of the aircraft manufacturer, was not used.
- The emergency extension system of the landing gear was not used.

Final Report:

Crash of a Boeing 737-3Q8 in Wamena

Date & Time: Aug 28, 2015 at 1547 LT

Type of aircraft:

Boeing 737-300

Operator:

Registration:

PK-BBY

Flight Phase:

Flight Type:

Cargo

Survivors:

Site:

Schedule:

Jayapura – Wamena

MSN:

23535/1301

YOM:

1986

Flight number:

8F189

Location:

Wamena

Special Region of Papua

Country:

Indonesia

Region:

Asia

Crew on board:

Crew fatalities:

Pax on board:

Pax fatalities:

Other fatalities:

Total fatalities:

Captain / Total flying hours:

13880

Captain / Total hours on type:

4877.00

Copilot / Total flying hours:

608

Copilot / Total hours on type:

342

Aircraft flight hours:

54254

Aircraft flight cycles:

38422

Circumstances:

On 28 August 2015 a Boeing 737-300 Freighter, registered PK-BBY was being operated by PT. Cardig Air on a scheduled cargo flight from Sentani Airport (WAJJ) Jayapura to Wamena Airport (WAVV) Papua, Indonesia. At 1234 LT (0334 UTC), the aircraft departed to Wamena and on board the aircraft were two pilots, and 14,610 kg of cargo. The Pilot in Command (PIC) acted as Pilot Flying (PF) while the Second in Command (SIC) who was under line training acted as Pilot Monitoring (PM). There was no reported or recorded aircraft system abnormality during the flight until the time of occurrence. At 0637 UTC, when the aircraft approaching PASS VALLEY, the Wamena Tower controller provided information that the runway in use was runway 15 and the wind was 150°/18 knots, QNH was 1,003 mbs and temperature was 23 °C. At 0639 UTC, the pilot reported position over PASS VALLEY, descended passing FL135. The Wamena Tower controller instructed the pilot to report position over JIWIKA. At 0645 UTC, the pilot reported position over JIWIKA and continued to final runway 15. At 0646 UTC, the pilot reported position on final runway 15 and Wamena Tower controller provided landing clearance with additional information of wind 150°/15 knots and QNH 1,003 mbs. At 0647 UTC, the aircraft touched down about 35 meter before the beginning runway 15 with vertical acceleration of 3.68 G. The left main landing gear collapsed and the left engine contacted to the runway surface. The aircraft stopped at about 1,500 meters from runway threshold. No one was injured on this occurrence.

Probable cause:

According to factual information during the investigation, the Komite Nasional Keselamatan Transportasi determines the findings of the investigation are listed as follows:
1. The pilots held valid licenses and medical certificates.
2. The aircraft had a valid Certificate of Airworthiness (C of A) and Certificate of Registration (C of R), and was operated within the weight and balance envelope.
3. There were no reports of aircraft system abnormalities during the flight.
4. After passed JIWIKA on altitude 10,000 feet, the FDR recorded the engines were on idle, the average rate of descend was approximately 2,000 feet per minute.
5. At altitude approximately 8,000 feet, the flap selected to 40 position and moved to 39.9° one minute 25 seconds later.
6. The BMKG weather report was wind 150°/14-19 knots and the Wamena Tower controller reported to the pilot that the wind was 150°/15 knots. The information of gust wind, which indicated the possibility of windshear, was not reported to the pilot.
7. The EGPWS “CAUTION WINDSHEAR” active on altitude of 5,520 feet.
8. 06:45:43 UTC, the engine power increased when the aircraft altitude was on 5,920 feet prior the EGPWS altitude call “ONE HUNDRED” heard.
9. Started from 06:45:45 UTC, the FDR recorded the CAS increased from 148 knots to 154 knots followed by N1 decreased gradually from 73% to 38%. Three seconds before touched down, the rate of descend was constant on value 1,320 feet per minute followed by EGPWS warning “SINK RATE”.
10. The aircraft touched down at about 35 meters before the beginning runway 15 with the vertical acceleration recorded of 3.68 G.
11. The trunnion link of the left Main Landing Gear (MLG) assembly was found broken and the left main landing gear collapsed.
12. The FDR data contained of 107 flight hours consisted of 170 flight sectors which recorded five times of the vertical acceleration more than 2 G during landing at Wamena. The accumulation of such value of vertical acceleration might lead to landing gear strength degradation.
13. The Visual Approach Slope Indicator (VASI) of runway 15 was not operated after the runway extension.
14. The investigation found several touchdown marks on the pavement before the runway 15.
15. Excessive rubber deposit was found on the surface of runway 15 at about 600 meter started from the runway threshold.
16. The absence of speed correction following the information of headwind of 15 knots and pilot crew briefing after activation of EGPWS caution windshear indicated that the pilot did not aware of the existing windshear, that might be contributed by the absence of gust wind information.
17. The large thrust reduction was not in accordance with the FCOM for windshear precaution and resulted in rapid descend.
18. The accident flight collapsed the landing gear, the FDR recorded the vertical acceleration was 3.683 G which was within the landing gear design limit. This indicated the degradation of landing gear strength.

Contributing Factor:
The large thrust reduction during the windshear resulted in rapid descend and the aircraft touched down with 3.683 G then collapsed the landing gear that had strength degradation.

Final Report:

Crash of a Beechcraft E90 King Air in Fayetteville

Date & Time: Aug 28, 2015 at 1400 LT

Type of aircraft:

Beechcraft 90 King Air

Operator:

Chopaire

Registration:

N891PC

Flight Phase:

Flight Type:

Private

Survivors:

Site:

Schedule:

Shelbyville – Huntsville

MSN:

LW-40

YOM:

1973

Location:

Fayetteville

Tennessee

Country:

United States of America

Region: