Visually inspect the auxiliary wing spar near the location where the main landing gear trunnion is mounted, for cracks; in accordance with Cessna Service Bulletin MEB08-8 original issue, or later FAA approved revision. Now check the horizontal for level fore and aft. Reply. NOTE: The access and inspection provisions for the airplane are typically shown in the applicable maintenance/service manual. Measure the rib spacing on the plans and mark the rib locations on your spars and trailing edge. Location: Australia. The area is the lower fuselage stub wing carry-through section, at the lower main spar wing attach area. A failed main spar means that your wings may fall off. If any crack is detected during any inspection that is 0.5-inch or more, before further flight, replace the cracked part(s). Forward-swept wing of Sukhoi Su-47. Join Date: Jul 2001. I use measurements from the old spars as a guide, holes in the leading and trailing edges, and ultimately my square and clearances to position the ribs laterally. Yield Strength, б y = 378N/mm 2. The decision on the number and location of any as-needed inspection holes/covers is at the discretion of the inspector in order to adequately inspect the entire surface of both wing spars. RC – Remove wing inspection panels and fairings, as required, to gain visual access to the main wing spar. 2. IF you can and all else is OK then consider changing the spacer under the front spar of the horizontal to correct it. Wood wing spars are fabricated in various designs. Good luck getting the wing spar replaced for only $12-13K. The forward-swept configuration has a number of characteristics which increase as the angle of sweep increases. A forward-swept wing is an aircraft wing configuration in which the quarter-chord line of the wing has a forward sweep. Note the alignment to the marks. Gain access to the upper and lower surfaces of the wing carry through forging. This was always around 26000 hours on a Chieftain. Attach the trailing edge first, but don’t attach the root rib yet. Check that the rods are straight and your ribs are square, then spread the ribs out to the proper spacing. 3.2.1 Location of Spars in wing construction Earlier wings were designed with three or more spars because use of several spars format a reduction in rib stresses and majorly used because of space requirement for housing of fuel tank and landing gears. Characteristics. I have heard that the modification and inspection process for the initial wing spar retirement is not much of a drama. And I kept coming back to the reasons behind the proposed AD. This is the wing root/rear spar modification to strengthen the wing root rib and rear spar attachment due to torsional failures of the rear spar attachment when at high G-loads. This DOES NOT include the 2-inch flange of the W-407B or W-407D parts. MAIN WING SPAR LOWER WING BOLT REPLACEMENT AND TENSION CABLE PER T-34 SPAR CORP. AMOC TO AD 2004-25-51 READ ALL OF THESE INSTRUCTIONS BEFORE UNPACKING ANY OF THE COMPONENTS ! The first wing spar is now complete so that just leaves the other one to do next week. Wing spar location Thread starter pegus; Start date Feb 2, 2014; Feb 2, 2014 #1 pegus. The only relief from the AD for a new spar replacement that I see is "If a main wing spar has been replaced with a new (zero hours TIS) main wing spar, count the number of 100-hour inspections from the time of installation of the new main wing spar." are six pre-molded spars installed; two in each wing (outbd main in front and outbd aft), and the center main and center aft. C dated December 2, 2003, Wings- Inspection and Repair of T-34 Wing Spar Structure Addendum 1, March 18, 2004 to T-34 Spar … 9 0. Upper cap stability (column, lateral-torsional, etc.) Cosmetic considerations are not reflected. Panels had to be manufactured by other firms (which was inconvenient) and then moved to the Leonardo plants to be mounted on the main structure. 27 WING TIP INSPECTION SUBJECT: VISUAL INSPECTION OF WING TIP AREA FOR EVIDENCE OF CRACKS. Inspect the whole wing carry-through forging for any indications of corrosion. Cosmetic considerations are not reflected. Joined: Nov 28, 2016 Messages: 6,194 Location: KFAR Display Name: … Two Piece Wing - The nominal way to do a two-piece is with the same pin locations as for a one-piece wing, but now you have two separate wings with two spars that overlap each other through the fuselage and both engage both pins, so the spars have to be slightly different for port and starboard wings. Wing Main Spar Carry-Through Section 10/90 Applicability: All models. RyanB Administrator Management Council Member PoA Supporter. Outer Spars Construction of the outer spars is similar to the center spars, except that you need to taper the spar caps front to rear before you laminate them to plywood. The rear wing spar root is the inboard edge of the spar web. In a fixed-wing aircraft, the spar is often the main structural member of the wing, running spanwise at right angles (or thereabouts depending on wing sweep) to the fuselage. MODELS AFFECTED: All … The decision on the number and location of any as-needed inspection holes/covers is at the discretion of the inspector in order to adequately inspect the entire surface of both wing spars. Location of the wing spar lower cap outer bolts 4. The wing fillets will hide the extra spar material. 5. Density = 2800kg/mm3 2. the location of the aileron bay inboard wing rib is established. Rib locations are specified as percentages of span length. Main spar location. Earlier aircraft utilised a tension bolt in this location, characterised by the “bathtub” type fitting. At the factory, all the ribs were located and attached with the aid of a spacing jig. Among the different components that were present in the wing box, the main spars (both front and rear) proved the most interesting to monitor and also the most challenging locations for insertion of the sensor networks. WannFly Final Approach. dmspilot, Jun 8, 2020 #8. Many aircraft wing spars are intermediate diagonal tension beams, so a full analysis (per NACA TN 2661 or similar) needs to be performed. Hi, I wonder where is the best location for a wing spar thorugh its cord. I am not sure I would’ve been happy flying the airplane for many more hours knowing the potential consequences of wing spar corrosion. is the lower fuselage stub wing carry-through section, at the lower main spar wing attach area. Wish I could get my plane serviced at the FAA's estimated labor rates! The wing box, the part of the wing that carries the loads, consists of top and bottom covers (each cover is composed of a skin and stringers that stiffen the skin and run lengthwise), spars that create the sides of the wing box and run lengthwise (some of the larger airplanes may have three spars) and ribs; the covers take the bending loads. UNIVAIR AIRCRAFT CORPORATION OCTOBER 12, 1987 SERVICE BULLETIN NO. It will be interesting to see how CASA rewords this into Australian terms. This is known as the RV-3 "A" (aerobatic) designation and is done as a CN-1-1 for type 1 spars or CN-1-2 for type 2 spars (there are differences in the mod for each per Vans drawings). Repairs to the wing carry- through forging shall be in accordance with Schemes approved by the Authority. both the left and right wings, at a location that provides direct visual access to the inspection area. This Amendment becomes effective on 20 November 2008. Recommended method to repair either a solid or laminated rectangle spar; The use of a scarf joint to repair a spar or any other component of an aircraft; Wood wing spars repair procedure; A longitudinal crack in a solid spar may be repaired. Up to where I know it is on the Aerodynamic center (approximately 1/4 of the chord from the leading edge) because is the point on the chord where the lift acts. The spar carries flight loads and the weight of the wings whilst on the ground. Over time, the tension loads have caused cracking to occur, primarily radiating from the various fastener holes. Typically, the leading edge also sweeps forward. LOADS ON THE WING FUSELAGE LUG ATTACHMENT BRACKET I used the jig shown above to taper my spar caps. Spar and stringer locations are specified as percentages of chord length. Recommendations CASA recommends if meeting the criteria in Section 1 Effectivity, to review the airplane maintenance records to determine the factored service hours in accordance with the formula in the proposed FAA AD paragraph (h)(2). Over time, the tension loads have caused cracking to occur, primarily radiating from the various fastener holes. All aircraft utilise tension type fittings on the forward spar upper attachment and the upper and lower rear spar attachments. 2. Piper PA30/39 Wing Spar Cap Corrosion AWB 51-4 Issue 1, 27 September 2002 Applicability All Piper PA-30 and PA-39 Twin Comanche aircraft. Make sure the ribs are square and attach the spar, but don’t glue the root rib yet. However once the second spar life and therefore the airframe life limit kicks in its a different matter. Clamp the wing spar in the new location, put Van’s block of wood under the level, and raise the tail of the fuselage until the bubble centers. I am using a 17in chord S1223 airfoil. The two spar wing construction usually consists of front and rear spar. Doublers extend the minimum distance beyond the crack. NordicDave, Jan 15, 2021 #5. Requirement: 1. At this location a wing attach fitting is bolted into the carry-through structure with multiple attach bolts. Spars are modelled as shear webs only with the skins taking up the bending loads. Therefore it follows quite simply that if the flexural centre and centre of pressure do not coincide, the wing must twist and bend at the same time. Poison's Ratio, μ = 0.3 4. 1. The undamaged portion of the spar need not be removed from the wing in making the repair. Proceed to Step 2. The three main and the center aft spars all have aluminum inserts bonded within their shear webs at strategic locations depending on the particular spar … At this location a wing attach fitting is bolted into the carry-through structure with multiple attach bolts. Reference Documents : T-34 Spar Corp. AMOC-1, Rev. November is also a good time of year to get work done on an aircraft in Oregon—it’s not flying season. Issue an airworthiness directive to require an immediate inspection of the main wing spars and upper wing skin at the wing root of Piper PA-28 airplane with over a specified number of service hours for evidence of cracking. Ultimate Strength, б u = 485N/mm 2 4. Rivets and instructions for installation are supplied with the assembly. Very likely you can’t measure the change from its original position. 2nd Feb 2012, 06:02 #4 LeadSled . These estimates might work IF an owner found a shop already seasoned with this procedure and in a low labor rate location. The more spar cap material here, the better. The centre of pressure for most wing profiles is in fact just behind the front spar, in the vicinity of the quarter-chord position, that is 25% of the chord length behind the leading edge. The material considered for the I section wing spar and rivets joint of the wing structure is aluminum alloy-2024T351. In addition, an end cap can be added which closes the wing box and acts as a rib at the tip location. must be verified. Thereafter, after each annual inspection and 100-hour TIS inspection, recalculate the factored service hours for each main wing spar until the main wing spar has accumulated 5,000 or more factored service hours. The 0 wing root location is located at 17.0 inches out from the wing root (when measured along the lower surface of the wing spar). Young’s Modulus, E = 70000N/mm2 3.