80-14-09 EAGLE BALLOONS LTD. (SEMCO): Amendment 39-3825. Applies to Semco Hot Air Balloon, Model TC-4A, S/N SEM 81 and subsequent; Model T, S/N SEM 78 and subsequent Challenger, S/N SEM 25 and subsequent, equipped with tubular aluminum gondolas covered with chair duck canvas. \n\n\tCompliance required as indicated below after the effective date of this AD. \n\n\tTo preclude failure of the gondola structural fittings and to alter the gondola chair duck canvas, accomplish the following: \n\n\t1.\tBefore next flight, and each flight thereafter: \n\n\t\ta.\tVisually check all Diamond aluminum fittings for cracks, in the tongue radius area, on the following models: \n\n\n\nModel No.\n\nFitting \n\nDash No.\nPart\nQty. \n\n11\nNo. 150\n4 \n\n14\nNo. 156\n8 \n\n28\nNo. 115\n4 \nModel TC-4A Dug. No. 1\n4\nNo. 103\n8 \n\n4\nNo. 150\n4 \n\n5\nNo. 156\n8 \n\n3\nNo. 115\n4 \nModel T Dug. No. 1\n6\nNo. 103\n8 \n\n3\nNo. 150\n4 \n\n6\nNo. 156\n8 \n\n9\nNo. 115\n4 \nChallenger Dug. No. 1\n11\nNo. 1038\n\n\t\tb.\tReplace cracked parts with new parts before next flight. \n\n\t2.\tSecure the gondola chair duck canvas siding to the gondola floor using grommets in the lower portion of the canvas. Extend the existing canvas using a 3/8" french fell seam per Advisory Circular 43.13-1A, Chapter 3, Page 85. Hem the bottom of the canvas and install grommets as noted in sketch below. \n\nAD 80-14-09 \n\n\n\n\nRework existing plywood floor as shown below. \n\n\nAD 80-14-09 \n\n\nLace canvas to plywood floor using 1/4" diameter braided nylon line as shown. \n\n\nAD 80-14-09 \n\n\n\t3.\tWithin the next 100 hours or next annual inspection, whichever occurs first, accomplish the following: \n\n\t\ta.\tRemove Diamond aluminum slip-on fittings noted in paragraph 1.a. \n\n\t\tb.\tClean surfaces as necessary and visually inspect for cracks by dye penetrant with a glass of at least 10 power, or equivalent, particularly in the tongue radius area. \n\n\t\tc.\tIf no cracks are found, the Diamond aluminum slip-on fittings may be returned to service. \n\n\t\td.\tReplace cracked parts with unused parts prior to next flight. \n\n\t4.\tThe repetitive inspection in paragraph (3) is to be accomplished at intervals not to exceed 100 hours in service or annually thereafter, whichever occurs first. \n\n\t5.\tEquivalent inspections, alterations and replacement parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. \n\n\t6.\tUpon submission of substantiating data by an owner, or operator through an FAA Maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance times specified in this AD. \n\n\tThis amendment is effective July 7, 1980. \n\nAD 80-14-09