82-16-08 HELIO: Amendment 39-4427. Applies to all models H-250, H-295, HT-295, H-391, H-391B, H-395 and H-395A airplanes certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished. \n\n\tTo ensure the integrity of the wing spar carry-thru assembly, accomplish the following: \n\n\tA)\tOn all models H-250, H-295 (except S/N 1436, 1443 thru 1479), H-391, H- 391B, H-395, and H-395A airplanes that have the 391-030-401 wing spar carry-thru assembly, and not modified in accordance with STC SA1590CE within the next 10 hours' time in service, on all land planes with 3000 or more hours' time in service, or upon accumulation of 3000 hours' time in service; and on all seaplanes with 1500 or more hours' time in service, or on airplanes operated in both landplane and seaplane configurations with 3000 or more equivalent landplane hours' time in service or upon accumulation of 3000 equivalent landplane hours' time in service, * and thereafter, at intervals not to exceed 100 hours time-in-service, gamma ray inspect both the lower left and right, main spar, steel carry-thru fitting, P/N 391-030-4072, for cracks or corrosion in accordance with Helio Aircraft Company Service Bulletin No. 36. \n\n\t*NOTE (1):\tTo obtain equivalent landplane time in service, multiply seaplane time by two. \n\n\tNOTE (2):\tThe 295-030-401 wing carry-thru assembly has plates welded to the lower tube as detailed in figure 2. The 391-030-401 wing carry-thru assembly does not have these plates. \n\n\t\t1.\tIf indications of cracks or corrosion are found during any of the gamma ray inspections required herein, prior to further flight, install the kit detailed in STC SA159OCE. \n\n\tB)\tOn all models HT-295 airplanes, model H-295 (S/N's 1436, 1443 thru 1479) airplanes and those model H-250, H-295, H-391, H-391B, H-395 and H-395A airplanes on which the P/N 391-030-401 wing spar carry-thru assembly was replaced with the P/N 295-030-401 assembly, and not modified in accordance with STC SA1728CE within the next 10 hours time-in- service after the effective date of this AD, and at intervals not to exceed 100 hours time-in- service thereafter, perform a dye penetrant inspection on each end of the lower horizontal tube around the welds and the adjacent area on the inboard end of the four 1.25 x 4.56 x .188 pads (2 each side) as follows: \n\n\t\t1.\tInspect each side of the wing spar carry-thru assembly using Figures 1 and 2 to identify the areas to be inspected. On the side being inspected, jack up the wing at the wing tie-down ring. The wheel must clear the ground. On airplanes equipped with floats, jack the wing so that it is displaced upward 4.75 to 5.0 inches at the tie down ring. Access to the wing carry-thru assembly is gained by opening the head liner and removing the P/N 295-030-3047 guard assembly (if installed). Conduct the inspection in accordance with the instructions accompanying the dye penetrant inspection equipment. \n\n\tNOTE: Jacking of the wing is necessary to put a tension load on the lower horizontal tube of the wing spar carry-thru assembly to assist in exposing fatigue-type cracks that could exist in this component. \n\t\n\t\t2.\tThoroughly clean and remove the paint from all surfaces to be inspected before the required inspections. \n\n\t\t3.\tRemove all evidence of corrosion and renew the protective coatings after the inspection. Corrosion may be removed from the horizontal tube to a maximum depth of .005 inches. If indications of cracks or evidence of corrosion beyond the .005 inch maximum depth are found during the inspections required herein, prior to further flight, install the kit described in STC SA1728CE. \n\n\t\t4.\tClean and apply zinc chromate primer to all surfaces which were cleaned for the required inspections. \n\n\tC)\tOn or before August 1, 1984, install wing carry-thru assembly reinforcement on all P/N 295-030-401 wing carry-thru assemblies in accordance with STC SA1728CE and on all 391-030-401 wing carry-thru assemblies in accordance with STC SA1590CE. \n\n\tD)\tOn airplanes having wing carry-thru assembly reinforcements installed per STC's SA1590CE or SA1728CE accomplish the following inspection on or before 1500 hours time in service after installation of this reinforcement and each 1500 hours time in service thereafter: \n\n\t\t1.\tConduct a dye penetrant inspection in accordance with the instructions accompanying the dye penetrant inspection equipment. The critical areas to be inspected include the surfaces where the weld bead would be and around the three bolt holes. Use Figures 1 and 2 to identify these areas. On the side being inspected, jack up the wing at the wing tie-down ring in accordance with the instructions in Paragraph B)1. \n\n\t\t2.\tThoroughly clean and remove the paint from all surfaces to be inspected before the required inspections. \n\n\t\t3.\tRemove all evidence of corrosion and renew the protective coatings. Corrosion may be removed from the horizontal tube to a maximum depth of .005 inches. If indications of cracks or evidence of corrosion beyond the .005 inch maximum depth are found during the inspections required herein, prior to further flight, replace the carry-thru assembly with an airworthy part. \n\n\t\t4.\tClean and apply zinc chromate primer to all surfaces which were cleaned for the required inspections. \n\n\tE)\tAll non-destructive inspections required in this AD must be performed by an appropriately rated FAA repair station using technicians with recency of experience in performing dye penetrant and gamma ray inspections. \n\n\tF)\tAn equivalent method of compliance with this AD if used must be approved by Chief, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone number (316) 269-7005. \n\n\tThis AD supersedes ADs 71-21-11 and 81-26-07. \n\n\tThis amendment becomes effective on August 3, 1982.