53-07-01: Elevator Hinge Attachment

53-07-01\tde HAVILLAND: Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 483 Inclusive. \n\n\tCompliance required as indicated. \n\n\tThere have been instances of the elevator outboard hinge becoming loose in its attachments to the horizontal stabilizer rib. Rivet holes have becomes enlarged permitting the fitting to "work". The de Havilland Aircraft of Canada, Ltd., in agreement with the Canadian Department of Transport, issued the following mandatory instructions in which the FAA concurs: \n\n\tInspection intervals: 50 hours, pending incorporation of the repair scheme described below. \n\n\tRepair scheme: The repair scheme described herein is not mandatory until a defect appears. (See Fig. 1.) \n\n\n\n\n\n\tThe following parts are required: \n\n\nC2-TP-179ND\nHinge plate\n2 required\n\nC2-TP-181ND\nAngle\n2 required\n1 each \nCR 162-6-8\nCherry rivet\n10 required\nend of\nCR 162-6-10\nCherry rivet\n12 required\nT/P.\nCR 163-6-8\nCherry rivet\n6 required\n\n\n\tProcedure.1.\tRemove tailcone. \n\t2.\tRemove elevator. \n\t3.\tLocate extreme outboard elevator hinges on tailplane. \n\t4.\tDrill out 4 rivets retaining hinge plates. \n\n\tImportant: Do not drill out rivet at point A until angle C2-TP-181ND has been riveted. (See Fig. 1.) \n\n\t5.\tRemove small tab at outboard ends of rear spar on tailplane. \n\t6.\tDrill out 3 rivets at point B securing angle C2-TP-139. (Angle must still remain in position secured by 1 rivet at point A.) \n\t7.\tLocate new angle C2-TP-181ND on spar rear face and flush with outer skin of end rib. \n\t8.\tRivet angles C2-TP-139 and -181ND to spar as shown at point B. \n\t9.\tDrill out rivet at point A. \n\t10.\tMake or secure new hinge plate C2-TP-179ND and assemble as shown. \n\t11.\tAssemble studs to new hinge plates. \n\t12.\tReplace elevator and tailcone. \n\n\t(de Havilland Technical News Sheet Series B, No. 60, dated February 10, 1953, Subject "Tailplane - Elevator Outboard Hinge - Mod. 2/901" covers this same subject.)