AD 75-22-09

75-22-09 ROCKWELL: Amendment 39-2396. Applies to Model 112, S/N 3 through 380, certificated in all categories.

Compliance required as indicated:

(a) Before further flight and prior to each flight thereafter until complete inspection and modifications are accomplished, visually inspect the airplane structure at all aileron hinge positions. If visual inspection reveals distortion of the aileron skin or readily visible cracks in hinge doublers, comply with subparagraph (b)(3) below:

(b) Within 10 hours' time in service, after the effective date of this AD, accomplish the following:

(1) Replace all outboard aileron doublers in accordance with Rockwell International Service Bulletin No. SB-112-35 dated October 1, 1975, or later approved revision or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas.

(2) Inspect all inboard aileron doublers for cracks, proper doubler thickness (.040 inches), and preloading of hinge doublers in accordance with Rockwell International Service Bulletin No. SB-112-35 dated October 1, 1975, or later approved revision, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas.

(3) If cracks, improper thickness, or preloading are found, replace doublers in accordance with Rockwell International Service Bulletin No. SB-112-35 dated October 1, 1975, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas, before further flight.

This amendment becomes effective November 4, 1975.