87-13-05 R1 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5651 as amended by Amendment 39-5927. Applies to Aerospatiale Model AS 355 series helicopters, certificated in any category which are equipped with main gearbox suspension bars with Part Numbers 355A-38-0040-02, -03, -04, -05. \n\n\tCompliance is required as indicated (unless already accomplished). \n\n\tTo detect possible unbonding of main gearbox suspension bar end fittings and to prevent failure of the bars, accomplish the following: \n\n\t(a)\tWithin the next 10 hours time in service after the effective date of this AD: \n\n\t\t(1)\tVisually inspect the ends of each suspension bar for displacement of the spherical bearings relative to the tube and for cracking or protrusion of the PR compound as shown in figure No. 1. If this inspection is conducted without disassembly, use a light and inspection mirror as needed to inspect both ends of each bar. \n\n\t\t(2)\tIf no bearing displacement or PR compound discrepancies are found, affix an adhesive tape such as POLYPENCO A 2007 around each end of each bar. Locate the edge of the tape nearest the end of the bar so that it is in line with (and tangent to) the surface of the anchoring lug as shown in figure No. 2. This will provide an aid for use in repetitive checks. \n\n\t(b)\tAfter the initial inspection of paragraph (a)(1) and modification of paragraph (a)(2), conduct a visual check of the marking tapes on the suspension bars thereafter at intervals not to exceed 10 hours time in service: \n\n\t\t(1)\tCheck that the edge of the tape is in line with the anchoring lug surface as shown in Figure No. 2. This check may be conducted by the pilot. The person performing this check shall make appropriate entries of the results of the check in the aircraft records. \n\n\t\t(2)\tIf the tape edge is no longer in line with the anchoring lug surface, remove the bar for a closer inspection for bearing displacement or PR compound protrusion as shown in figure No. 1.(c)\tReplace all bars found to be faulty with serviceable parts. \n\n\t(d)\tAn alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Department of Transportation, Federal Aviation Administration, Fort Worth, Texas 76193-5100, or by the Manager, Brussels Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. \n\n\t(e)\tIn accordance with FAR 21.197 and 21.199, flight is permitted to a base where the inspections required by this AD may be accomplished. \n\n\t(f)\tAerospatiale Service Bulletin No. 05.16 pertains to the inspections and checks of this AD. \n\n\tThis amendment, 39-5927, amends Amendment 39-5651 (52 FR 24142; June 29, 1987), AD 87-13-05. \n\tThis amendment, 39-5927, becomes effective June 8, 1988. \n\n\n\nAD 87-13-05 R1 \n\n\n\t\tFIGURE NO. 1 BASIC CHECK FOR END FITTING DISPLACEMENT \n\n\n\nAD 87-13-05 R1 \n\n\n\n\n\nUNSATISFACTORY \n(Tape displaced relative to lug fitting) \n\nFIGURE NO. 2 TAPE LOCATION CHECK FOR END FITTING DISPLACEMENT