AD 99-05-14

This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters, that requires inspecting the main rotor blade cuff attachment fitting in the area of the main rotor blade (blade) attachment bolts for cracks, and removing and replacing the blade if a crack is found. This amendment is prompted by a report of a crack in a blade cuff attachment fitting/spar assembly that was discovered during fatigue testing by the manufacturer. The actions specified by this AD are intended to prevent failure of a blade cuff attachment fitting at a bolt hole location, loss of a blade, and subsequent loss of control of the helicopter.

Final rule

99-05-14 EUROCOPTER FRANCE: Amendment 39-11062. Docket No. 97-SW-14-AD. \n\tApplicability: Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters, with a main rotor blade, part number (P/N) 3160S.11.10.000, 3160S.11.30.000, 3160S.11.35.000, 3160S.11.40.000, 3160S.11.45.000, 3160S.11.50.000, or 3160S.11.55.000, installed, certificated in any category. \n\n\tNOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. \n\n\tCompliance: (1) For blades with less than 400 hours time-in-service (TIS), required prior to the accumulation of 400 hours TIS, unless accomplished previously, and thereafter at intervals not to exceed 400 hours TIS; or (2) for blades with 400 hours or more TIS, required within 50 hours TIS or 30 calendar days after the effective date of this AD, whichever occurs first, unless accomplished previously, and thereafter at intervals not to exceed 400 hours TIS: \n\n\tTo prevent failure of a main rotor blade (blade) cuff attachment fitting at a bolt hole location, loss of a blade, and subsequent loss of control of the helicopter, accomplish the following: \n\n\t(a)\tInspect both upper and lower blade surfaces of each blade cuff for cracks (see Figure 1) as follows: \n\n\t\t(1)\tUse a mild liquid detergent or equivalent to remove all dirt from the blade cuff. \n\n\t\t(2)\tInspect the blade cuff for cracks, paying particular attention to the area around the attaching bolts, using a 10-power or higher magnifying glass. \n\n\t\t(3)\tIf a crack is suspected, remove any paint and clean the area under inspection using a Naptha-type solvent or equivalent, and conduct a dye penetrant inspection. Completely isolate the area under inspection with self-adhesive aluminum tape to prevent solvent or penetrating dye seepage into the other areas of the blade. \n\n\t(b)\tIf a crack is detected, remove the blade and replace it with an airworthy blade. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through anFAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. \n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. \n\n\t(d)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. \n\n\tNOTE 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 96-081-036(B)R1, and AD 96-082-054(B)R1, both dated April 24, 1996. \n\n\t(e)\tThis amendment becomes effective on April 7, 1999.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters was published in the Federal Register on November 3, 1998 (63 FR 59252). That action proposed to require inspecting the blade cuff attachment fitting in the area of the blade attachment bolt holes for cracks, and removing and replacing any blade in which a crack is found. \n\n\tInterested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule with only minor editorial changes that will neither increase the economic burden on any operator nor increase the scope of the AD. \n\n\tThe FAA estimates that 83helicopters of U.S. registry will be affected by this AD, that it will take approximately 2 work hours per helicopter for the initial inspection and 2 work hours per helicopter for each repetitive inspection and that the average labor rate is $60 per work hour. Required parts will cost approximately $40,000 per blade, if needed. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $49,960 for one inspection and one blade replacement for each helicopter per year. \n\n\tThe regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. \n\n\tFor the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the FAA, Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 97-SW-14-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. \n\nList of Subjects in 14 CFR Part 39 \n\tAir transportation, Aircraft, Aviation safety, Safety. \n\nAdoption of the Amendment \n\tAccordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: \n\nPART 39 - AIRWORTHINESS DIRECTIVES \n\t1. The authority citation for part 39 continues to read as follows: \n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n§ 39.13 (Amended) \n\t2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: