Bogotá-El Dorado

The following findings were identified:
- Inadequate flight planning by the operator of the aircraft, and by the crew, by failure to properly perform dispatch procedures, takeoff performance calculations and verification of limitations imposed by operational conditions of the aerodrome according to the configuration of the aircraft.
- Wrong crew decision making by not considering a key aspect affecting aircraft performance, such as the prevailing tailwind at takeoff.
- Erroneous selection of takeoff speeds V1/VR and V2, by the crew, corresponding to an aircraft without modification in its flap system, which led to rotate the aircraft with five more knots of speed, increasing the takeoff run.
- Erroneous rotation technique applied by the Pilot, delayed maneuver that extended the long takeoff run even more.
- Loss of components (landing gear, trailing inboard flap right) and damage to functional systems (loss of engine power n°3 and hydraulic system) necessary to control the aircraft in flight.
- Loss of control in flight generated by asymmetries of lift, power and emptying of the main hydraulic systems that exceeded the capacity of the crew and made it impossible to maintain adequate directional control and stability of the aircraft.
Contributing Factors:
- Non-compliance with the Aeronautical Regulations by the operating company of the aircraft, operating to an aerodrome unsuitable for the operation of B727-200 equipment, which, in addition, was not authorized for that type of aircraft in the company's Operating Specifications, approved by the Aeronautical Authority.
- Lack of standardization and supervision of the operating company of the aircraft, allowing the operation of the B727-200 equipment, to which a modification had been applied to the flap system, with the reference tables of speeds corresponding to the aircraft without modification.
- Execution of take-off with a weight that exceeded the maximum value established in the aircraft performance charts for the conditions prevailing at the Germán Olano airport.
- Omission of the crew by not activating the Standby hydraulic system, which might have allowed emergency hydraulic pressure, to regain control of the aircraft.
- Lack of supervision by the Aeronautical Authority, which allowed for several years the operation of equipment B727-200 of the company operating the aircraft at the Germán Olano aerodrome in Puerto Carreño, when the characteristics of the aerodrome did not allow it and without the operator being authorized to operate equipment B727-200 in that aerodrome.

The pilot lost control of the airplane following a loss of power on the left engine during initial climb. Investigations were unable to determine the exact cause of this loss of power. The aircraft's speed dropped to 107 knots and the pilot likely did not have time to identify the problem. Operation from a high density altitude airport contributed to the accident.

The following factors were identified:
- The lack of technical knowledge published in the POH for the execution of the pertinent actions during the failure of the engine in flight, together with the unwise decisions made by the crew in that situation.
- The haste of the crew members to land caused them to act in an uncoordinated manner and without the assertiveness required for the execution of the procedures contemplated by the manufacturer, the navigation charts and the published approach procedures.
- The omissions, reactions and deviations inappropriate to conduct the flight safely to the runway.
- The turning to the runway on the same side of the inoperative (critical) engine and maximum power on the operational engine during the unstabilized approach to the runway threshold which led to loss of control of the aircraft in low altitude flight.

Execution of the flight below the angle of approach, due to a misjudgment of the crew, believing to be much higher, leading the aircraft to fly a typical trajectory of a 'black hole' illusion, which was experienced during the night-time approach to a runway with low contrast surrounded in bright focused lights, aggravated by bad weather of heavy rain.

The inability of the accident aircraft to maintain flight after the loss of power of two engines.
The following contributing factors were identified:
A non-recoverable surge on the engine n°4 during the rotation, resulting in a loss of engine power. Contributing to the surge were the combined effects of the inefficient high pressure turbine, excessive blade-tip clearance, reduced cord of the fan blades and of the leading edges and the effects of high altitude. An undetermined anomaly in the engine n°1, which manifested itself during the extra power, resulted in loss of engine power. Contributing to the loss of engine power was inadequate n°1 operation to maintain the proper speed during the ascent of the aircraft, resulting in extra power use and, in turn, exposing the anomaly of the engine.

Carrying out a landing with an unresolved issue on the left engine, causing the aircraft to be unable to stop within the remaining distance available. The failure to correct the maintenance reports in a satisfactory manner and the failure to properly follow-up on repetitive entries were considered as contributing factors.

The exact cause of the accident could not be determined.

Following a flight under IFR mode, the crew decided to continue the approach by night and limited visibility under VFR mode, without meeting the minimum requirements for this type of operation. This decision led the aircraft descending at an unsafe altitude until it collided with a television antenna and crashed. The following contributing factors were identified:
- Poor approach planning,
- Poor judgment,
- Violation of IFR procedures,
- The crew's inability to circumvent the obstacle on the ground by encountering unforeseen circumstances beyond their capacity.

Failure of the right main gear during taxi due to the presence of corrosion in the trunnion.