On April 4, 1994, at 1815 Pacific daylight time, Skywest Airlines Flight 5435, a Fairchild SA-227AC, N174SW, experienced rapid decompression resulting from the loss of the pilot's side windscreen. The aircraft was owned and operated by Skywest Airlines Inc., and was on a scheduled commuter flight under 14 CFR Part 135 of Federal Aviation Regulations. Visual meteorological conditions prevailed at the time and an IFR flight plan had been filed for the operation. The aircraft sustained minor damage. The captain, a certificated airline transport pilot, sustained minor injuries. Neither the first officer nor any of the remaining ten passengers were injured. The flight originated from Los Angeles, California, at 1750 on the day of the mishap as a nonstop flight to Yuma, Arizona. Use your browsers 'back' function to return to synopsisReturn to Query Page
The captain stated the aircraft had been cleared to climb from 17,500 feet to flight level 210 and was climbing at 1,000 feet per minute. The cabin altitude controller had been set for a cruise altitude of 23,000 feet. As the aircraft reached 19,800 feet, he heard a loud "bang" and felt himself being sucked suddenly and violently through the broken left side window. As a result, the captain's head, arms, and upper chest were forced through the opening. In the process, he struck his left side on the windscreen lower frame. After about 2 to 4 seconds, he was able to pull himself back into the aircraft, unassisted. He stated that, although he was wearing his seat belt, he was not wearing his shoulder harness at the time of the incident.
The captain declared an emergency and landed the aircraft at Ontario airport without further incident. A postincident inspection of the aircraft revealed several cuts on the left propeller deicing boots.
A review of the maintenance records revealed that an applicable Airworthiness Directive AD 93-19-06 requiring an inspection of the windscreen had been complied with within the last 143.8 flight hours. The AD incorporates Fairchild Aircraft Service Bulletin 227-56-002 for inspection procedures to be utilized.
The Fairchild Service Bulletin provides two methods in order to comply with the inspection requirements. The first requires the removal of the outer retainer which permits a direct visual examination of the windscreen surface.
The second method requires that an oiled 90-degree face of a prism be placed on the window surface so that a constant film extends across the contacting prism face and windscreen surface. The inspector then looks into the 90-degree prism surface which is perpendicular to the face placed against window. The image of the hole area covered by the retainer frame then appears in the prism.
Under the second method, the image of an unfractured hole appears as a frosty cylinder. If the hole is countersunk, the cylinder will appear to have a cone on one end. The image of a hole with a crack extending from the hole to the surface of the window will appear as a frosty or reflective projection extending from the hole. The image of a crack which has progressed from one hole to another will appear as a frosty or reflective irregular surface which may, in some cases, completely bypass adjacent holes to progress into yet another hole once or twice removed from the hole of origin. Cracks which exceed 4.3 inches require the removal and replacement of the windscreen with a serviceable replacement or placing a restriction on the aircraft prohibiting pressurized flight.
According to the operator, the method chosen to comply with the AD was the prism seated with mineral oil procedure.
The aircraft was examined on April 5, 1994, by a Federal Aviation Administration (FAA) airworthiness inspector and a technical representative from Fairchild Aircraft. The technical representative stated that an inspection of the remaining fragments of the windscreen showed evidence that a crack had originated in the upper forward corner and then had propagated aft, migrating from screw hole to screw hole across the top of the windscreen. According to the representative, the initial cracking was wholly within the frame and, as such, would not have been visible to a casual observer.
Fairchild Aircraft Service Bulletin 227-56-002 is more restrictive than the AD in that it requires the windscreen be removed and replaced if a crack from a single screw hole exceeds 0.30 inches. The maximum combined length of multiple cracks between two adjacent screw holes shall not exceed 0.30 inches before replacement is required. Finally, if a maximum of three screw holes exhibit cracking in excess of 0.299 inches, replacement is also required. Any cracks that are detected which are less than 0.30 inches require that the windscreen be inspected every 25 flight hours.
It was the Fairchild representative's opinion that this crack had originated prior to the inspection and had propagated slowly, which he based on residue found on the forward 6.5 inch portion of the crack surface and the prior history windscreen cracking on this aircraft make and model. He offered an explanation for why the crack was not detected during the inspection. He stated that the maintenance personnel may have failed to detect the extent of the crack, due to the indirect prism/mineral oil viewing procedure employed.