AD 99-07-08 Airworthiness Directives; Eurocopter France Model SA. 315B Helicopters

Models named: SA. 315B. Read the applicability below — it usually turns on serial or part numbers too.

Model SA. 315B helicopters, with main rotor blades, part number (P/N) 3160S11-10000--all part numbers, 3160S11- 30000--all part numbers, 3160S11-35000--all part numbers, 3160S11- 40000--all part numbers, 3160S11-45000--all part numbers, 3160S11- 50000--all part numbers, or 3160S11-55000--all part numbers, installed, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise 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 request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To detect bonding separation, corrosion, or a crack in the area of the main rotor blade (blade) root reinforcement strip, which could result in failure of the blade and loss of control of the helicopter, accomplish the following: (a) Before further flight, and thereafter at intervals not to exceed 100 hours time-in-service (TIS) or 6 months, whichever occurs first, inspect each blade spar skin and blade root reinforcement strip area for bonding separation, corrosion, or a crack in accordance with paragraphs 2.A. and 2.B. of the Accomplishment Instructions in Eurocopter SA 315 Service Bulletin No. 05.34, Revision No. 1, dated September 28, 1998 (SB), except that notification to Eurocopter La Courneuve, Department E/SRPT, is not required. (1) For the hatched areas (15 x 50mm and 100 x 10mm) on the upper and lower surfaces, if bonding separation is found, replace the blade with an airworthy blade prior to further flight (refer to Figure 1 of the SB). (2) Bonding separation in the non-hatched area (100 x 10mm) of the upper and lower surfaces is permissible but must be inspected using a tapping method at intervals not to exceed 25 hours TIS in order to monitor any propagation. If bonding separation reaches the hatched area, the blade must be replaced with an airworthy blade before further flight. (b) Before further flight, and thereafter at intervals not to exceed 100 hours TIS or 6 months, whichever occurs first, visually inspect for a crack or corrosion on the upper and lower skin in the 100 x 100mm blade root area. If a crack or corrosion is detected, replace the blade with an airworthy blade prior to further flight (refer to Figure 1 of the SB). (c) An 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 an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (d) Special flight permits will not be issued. (e) The inspections shall be done in accordance with Eurocopter SA 315 Service Bulletin No. 05.34, Revision No. 1, dated September 28, 1998. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on April 13, 1999. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 98-277-040(A), dated July 15, 1998, and AD 98-277-040(A)R1, dated December 16, 1998. Issued in Fort Worth, Texas, on March 18, 1999. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 99-7384 Filed 3-26-99; 8:45 am] BILLING CODE 4910-13-U