D-1 de HAVILLAND 53-7-1 de Havilland Applies to Model 10. Make or secure new hinge plate C2-TP- DHC-2 (Beaver) Aircraft, Serial Numbers 179ND and assemble as shown. 1 to 483 Inclusive. 11. Assemble studs to new hinge plates. Compliance required as indicated. 12. Replace elevator and tailcone. There have been instances of the elevator (de Havilland Technical News Sheet Series outboard hinge becoming loose in its attach• B, No, 60, dated February 10, 1953, Subject ments to the horizontal stabilizer rib. Rivet "Tailplane—Elevator Outboard Hinge—Mod. holes have become enlarged permitting the 2/901" covers this same subject.) fitting to "work". The de Havilland Aircraft 53-9-2 de Havilland Applies to All Model of Canada, Ltd., in agreement with the Cana• DHC-2 Beaver Aircraft. dian Department of Transport, issued the fol• Compliance required as indicated. lowing mandatory instructions in which the Inspect as soon as practical but not later than FAA concurs: the next 100-hour flying time and at 100-hour Inspection intervals: 50 hours, pending in• intervals thereafter for skin cracks on the fuse• corporation of the repair scheme described lage side panel at front door step. (See Fig• below. ure 2 for typical cracks and methods of repair• Repair scheme: The repair scheme described ing.) Any cracks found should be stop drilled herein is not mandatory until a defect appears. at each end and repaired in accordance with (See Fig. 1.) directions in sketch. 100-hour inspection may be discontinued upon incorporation of recom• The following parts are required: mended repair. 0.74 C2-TP-179ND Hinge plate— 2 required C2-TP-181ND Angle- _ 2 required— 1 each CR162-6-8— Cherry rivet- 10 required— end of OR 162-6-10— Cherry rivet- 12 required— T/P. CR 163-6-8 Cherry rivet— 6 required— Detail of Angle C2-TP. fr*lNS.1 -Make From Extruded Angle (Alcoa Die No. 78 - C ) Procedure. or Dural Bar 2*ST. Finiah -Anoiiae Exieting Angle 1. Remove tailcone. 2. Remove elevator. 3. Locate extreme outboard elevator hinges on tailplane. Skin (Ref.l 4. Drill out 4 rivets retaining hinge plates. Plate-Hinge 2 -°" 15 Dural or Alclad Important: Do not drill out rivet at point Sheet Spec.24ST. or 24St. Al Anodite Riveta Point A A until angle C2-TP-181ND has been riveted. t Aeiemble With 10 -Off 12-Off Retain Thi. Exjtting Duralac 0.30R "Rivet Until Final (See Fig. 1.) Aaa'y 5. Remove small tab at outboard ends of rear .50R. spar on tailplane. 6. Drill out 3 rivets at point B securing angle C2-TP-139. (Angle must still remain in position secured by 1 rivet at point A.) 7. Locate new angle C2-TP-181ND on spar rear face and flush with outer skin of end rib. Drill No 8. Rivet angles C2-TP-139 and -181ND to Hole! CSK Mf\ 0.06 Deep spar as shown at point B. VIEW ON L, HI OUTBOKD HINGE -TAILPLANE 9. Drill out rivet at point A. FIGURE 1 D-2 DB HAVILLAND Drill Out Theae 6 ftiveta 53-11-2 de Havilland Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 445 Inclusive. Compliance required as indicated. Cases have been reported of chafing of the engine oil sump by section assemblies. (P/N C2-E-105ND) and (P/N C2-E-107ND) of accessory firewall. An enlarged flange clear• ance is required to be incorporated as soon as possible but not later than the next 100 hours. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet, Series B, No. 64 dated March 23, 1953, available from de Havilland Aircraft of Canada, Ltd., Toronto, Ontario, Canada, covers this same subject and describes method of repair.) 53-12-2 de Havilland Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 451 Inclusive. Compliance required as indicated. VIEW ON FUSELAGE SIDE PANEL AT FRONT DOOR STEP SHOWING TYPICAL METHOD OF REPAIRING SKIN CRACKS Cases have been reported of loss of seals in FIGURE 2 the flap hydraulic hand pump No. 430EDH. To prevent the above condition a modification (de Havilland Technical News Sheet, Series (No. 2/926) was incorporated on production B, No. 59—Issue 2, dated January 15, 1953, aircraft and should be incorporated on aircraft covers this same subject.) in service as soon as possible but not later than the next 100 hours. 53-10-2 de Havilland Applies to Model The FAA concurs in this mandatory action DHC-2 (Beaver) Aircraft, Serial Numbers by the Canadian Department of Transport. 1 to 401 Inclusive. (de Havilland Technical News Sheet, Series Compliance required as indicated. B, No. 63 dated March 19, 1953, available After the aircraft has acquired 500 hours of from de Havilland Aircraft of Canada, Ltd., flying time and pending the incorporation of Toronto, Ontario, Canada, covers this same the recommended repair, the wings should be subject and describes method of repair.) inspected for cracks in lower wing skin at ends 53-21-1 de Havilland Applies to All Model of the short stringers at the root end station DHC-2 (Beaver) Aircraft. of the whig leading edges at 50-hour intervals. Compliance required as indicated. If no cracks are evident reinforcements should Several cases have been reported where be installed on the bottom surface of the wing mechanics in the field upon assembling DHC-2 as a preventive measure. The FAA concurs in wings to fuselage have installed extra washers, this mandatory action by the Canadian Depart• packing, etc., to the rear spar wing bolt in ment of Transport. order to take out any end play. It should be (de Havilland Technical News Sheet Series pointed out that a clearance is purposely pro• B, No. 59—Issue 2 dated January 15, 1953, vided in this fitting as the rear wing attach• available from de Havilland Aircraft of Can• ment is not designed to take drag loads. ada, Ltd., Toronto, Ontario, Canada, covers All Beaver aircraft should be inspected as this same subject and describes method of soon as possible but not later than December 1, reinforcement.) 1953, to see that no washers, bushings, etc., DE HAVILLAND all threaded terminals at turnbuckles should (de Havilland Technical News Sheet CT be inspected at the following locations: (104) No. 65 dated August 4, 1955, covers this same subject.) Control Number cable Location of turn- 55-25-2 de Havilland Applies to All Model circuit buckles 104 "Dove" Aircraft. Ailerons 1. Base of control column. 2 2. Outboard wing Inspection 4 Compliance required as indicated. panels. Cases have occurred recently where cracks Elevators 3. Hatch on underside of rear 2 have been found in the left-hand front fin fuselage. attachment brackets, P/N 4FS.1749 (Pre. Dove Rudder 4. Bear fuselage interior. 2 Model 7, "Individual fin attachment and Damaged or defective cables must be rudder control pulley bracket"), and P/N replaced. 4FS.6781 (Dove Mod. 7, "To introduce single casting for front fin attachments and control If any evidence of defects is found, de Havil- pulley brackets"). The cracks generally ema• land will supply replacement cables. nate from the top rivet hole in the left row and The FAA concurs in this mandatory action pass through the flange. by the Canadian Department of Transport. The de Havilland Service strongly recom• (de Havilland Technical News Sheet Series mends inspection of the fin attachment brackets B, No. 76 dated June 23, 1954, available from at an early date with which the FAA concurs de Havilland Aircraft of Canada, Limited, and considers mandatory. Postal Station "L," Toronto, Canada, covers Inspect both front fin attachment brackets this same subject.) for cracks, using a magnifying glass after removing the paint, as soon as practical, but 55-20-1 de Havilland Applies to All Model not later than the next 25 hours operation 104 "Dove" Aircraft. unless already accomplished, and thereafter at Compliance required prior to original cer• each check II (approximately 100-hour pe• tification or by next airworthiness certificate riods). Access can be made by entering renewal unless already accomplished. through bulkhead No. 5. Attention of operators of the Dove aircraft Should any cracks be found, install new is drawn to the manufacturer's recommenda• front fin attachment and pulley brackets, P/N tion for periodic inspection of the alclad engine 4FS.9165 L. H. and 4FS.9166 R. H. (Ref. mount pickup fittings, P/N 4W1137 and Dove Modification 903) and secure to bulkhead 4W1141. Several cases of fitting failures have No. 6 using 2BA bolts and nuts or equivalent been reported. Unless this failure is detected in the top six holes. Rivets are used in the at an early stage, the bottom flange of the front other positions. false spar may be subjected to excessive loads Repetitive inspection may be discontinued and may crack as a result. Accordingly, the when the new front fin attachment and pulley de Havilland Aircraft Co., in agreement with brackets per Modification 903 are installed. the British Registration Board, issued the fol• (de Havilland Technical News Sheet CT lowing mandatory modification and informa• (104) No. 112, Issue 2, dated September 1, tion in which the FAA concurs. 1954, covers this same subject.) 1. To prevent fractures and to give increased 55-25-3 de Havilland Applies to All Model strength, Modification No. 524 has been de• 104 "Dove" Aircraft. vised to change the fittings from aluminum Compliance required as soon as practical but alloy to steel and at the same time to reduce not later than February 15,1956, unless already the limits from 0.0009 inch to 0.0003 inch and accomplished.