AFS-640

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AFS-640 ( afs-640 )

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9/8/98 AC 43.13-1B (c) Step 3. Determine percent reduc- tion in width (∆w%) from figure 8-27. (d) Step 4. Calculate the blade width repair allowable (∆w) ∆w =(∆w%) x (w) x(0.01) = (2.5) x (1.88) x (0.01) = 0.05 in. (e) Step 5. Calculate the minimum blade width limit (w1) at the repair location w1 =w-∆w=1.88-0.05=1.83in. (2) Example 2. Determine the blade thickness repair allowable (∆t) and minimum blade thickness limit (t1) for a blade having a diameter (d) of 10 ft. 6 in. The repair location (r1) is 43 in. from the shank and the original, as manufactured, blade thickness (t) at the re- pair location is 0.07 in. (a) Step 1. Calculate the blade radius (r) r = d/2 = (10 ft 6 in)/2 = 126/2 = 63 in. (b) Step 2. Calculate percent of blade radius to repair (r%) r% = r/r x 100 = (43/63) x 100 = 68 (c) Step 3. Determine percent reduc- tion in thickness (∆t%) from figure 8-28. (d) Step 4. Calculate the blade thickness repair allowable (∆t) ∆t = (∆t%) x (t) (0.01) = (4.0) x (0.07) x (0.01) = 0.003 in. (e) Step 5. Calculate the minimum blade thickness limit (t1) at the repair location t1 =t-∆t=0.07-0.003=0.067in. Par 8-74 8-75. STEEL HUBS AND HUB PARTS. Repairs to steel hubs and parts must be ac- complished only in accordance with the manu- facturer’s recommendations. Welding and remachining is permissible only when covered by manufacturer’s service bulletins (SB). 8-76. PROPELLER HUB AND FLANGE REPAIR. When the fixed-pitch propeller bolt holes in a hub or crankshaft become damaged or oversized, it is permissible to make repairs by using methods (A) or (B) in figure 8-29, or by use of aircraft standard bolts 1/16-inch larger than the original bolts. Make the repairs in accordance with the recommendations of the propeller metal hub manufacturer or the engine manufacturer, as applicable. Obtain from the engine or propeller hub manufacturer suitable flange bushings with threaded or smooth bores, as illustrated in methods (A) or (B) of figure 8-29. Drill the flange and insert the bushings as recommended by the propeller to accommodate the bushings, and protect the holes with 2 coats of aluminum paint or other high moisture-resistant coating. Use bolts of the same size as those originally used. Any of the following combinations may be used: (1) drilled head bolt and castellated nut, (2) drilled head bolt and threaded bushing, or (3) undrilled bolt and self-locking nut. Where it is desirable to use oversized bolts, obtain suitable aircraft-standard bolts 1/16-inch larger than the original bolts. Enlarge the crankshaft propeller flange holes and the propeller hub holes sufficiently to accommodate the new bolts without more than 0.005-inch clearance. Such reboring will be permitted only once. Further repairs of bolt holes may be in accor- dance with the methods listed in (A) or (B) of figure 8-29. NOTE: Method (A) or (B) is pre- ferred over the oversized bolt method, because a propeller hub flange re- drilled in accordance with this latter Page 8-33

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