Question

In terms of the Aloha Airlines maintenance program, what were the major shortcomings that contributed to the incident in flight 243? Include a discussion on the relevant ageing aircraft issues such as suitability of the maintenance program at addressing the highly corrosive operating environment and the high cycle to flight hour ratio. Compare to contemporary requirements and practices.

Answer 1

Aloha Airline was damaged after repair and was in place. Additional damage to the aircraft included damaged and contiguous horizontal stabilizers, both of which were hit by flying debris. Some metal debris also attacked the vertical stabilizer of the aircraft, causing minor damage. The leading edge of both wings and both caps also has permanent damage.

The wreckage of the plane that was detonated by the plane was not found. An investigation by the US National Transportation Safety Board (NTSB) concluded that the accident was caused by metal fatigue, exacerbated by the cracking of the crack. The plane was 19 years old and operating in a coastal environment exposed to salt and moisture.

In an interview, a passenger, Gail Yamamoto, told investigators she noticed cracks in the plane when boarding but did not notify anyone.

For the manufacture of aircraft number 292 and after having an additional layer of skin or double coat on the joint. In this aircraft construction, this double sheet was not used in addition to any other parts to attach the parts. In the case of Product Line 292 and above, this double sheet provides an additional 0.91 mm thickness in the thighs of the ramp. In Flight 243, a cold connection with the connector used to maintain the internal contact of the joint was previously used, which allows electrically connecting the load to the joint. This cooler welding uses a sponge clamp cloth to join the 0.9m thick skin pad. These sponge towels react at room temperature, so they are stored at dry ice temperatures while used in production. Solid connection at room temperature after installation. Cold welding processes reduce weight and total production costs. The load on the body cavity (the load on the skin due to cabin pressure) is desired to be transferred through the joint and not through the rivets, which allows for the use of lighter skin panels on the chassis without Let life deteriorate.
Extra-layer construction improves joints by:

    Elimination of details for fatigue on the edge of the knife as a result of inaccuracy of the rivet pad for scrubbing in the upper skin, which breaks down;
    Eliminate the fear of rust associated with the scraper cloth, which can remove moisture in the thighs.

The investigation found that the quality of monitoring and maintenance programs was insufficient. Because aircraft inspections are scheduled at night, it is difficult to adequately monitor the exterior skin of the aircraft.

Also, the destruction of the chassis was initiated in the buffer column along the S-10; The failure mechanism is the result of repeated fatigue of the skin, next to the rivets, for the rivets along the upper rivet, the joint part of the thigh, and the tearing of the strap, denying the safety features of the chassis. Finally, fatigue cracking began with the edge of the knife, which was in contact with the ribs on the lap of the car. The edge of the stress concentrator knife is transferred through the rivets due to the breaking of the knee joint.

The NTSB finished its latest accident report 73-74

    The National Transportation Safety Board determined that the probable cause of the accident was the inability of Aloha's maintenance program to detect significant damage and fatigue, which ultimately led to the failure of The attachment of S-1L and the division of the upper part of the chassis. Contributing to the accident was the failure of the Alo Airlines to properly manage its maintenance forces. FA's Failure to Require Airworthiness Inspection 87-22-08 Checks All School Circuits Proposed by Brent Notice Notice S 737-53A1039. And a complete lack of complete activity following the detection of initial production difficulties in the B-737 circuits of the circuit, leading to low durability of connections, corrosion, and rapid fatigue cracking.