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99-09-16 EUROCOPTER FRANCE: Amendment 39-11150. Docket No. 98-SW-54-AD. Supersedes AD 97-24-04, Amendment 39-10211, Docket No. 97-SW-22-AD.
Applicability: Model SE 3130, SE 313B, SA 3180, SA 318B, and SA 318C helicopters with main rotor blades, part number (P/N) 3130S11-10000-all part numbers, 3130S11-20000-all part numbers, or 3130S11-30000-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 repairon 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.
Compliance: Required as indicated, unless accomplished previously.
To prevent failure of a main rotor blade (blade) in flight and subsequent 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 calendar months, whichever occurs first, inspect each blade spar skin and blade root reinforcement strip area for bonding separations, cracks, or corrosion in accordance with paragraphs 2.A. and 2.B. of the Accomplishment Instructions of Eurocopter Service Bulletin No. 05.91 Revision No. 1, dated September 28, 1998 (SB). Notification to Eurocopter La Courneuve, Department E/SRPT is not required.
(1) For the hatched areas (15 x 95mm and 8 x 95mm) on the upper and lower surfaces of each blade, ifbonding separation is found, replace the blade with an airworthy blade prior to further flight (see Figure 1 of the SB).
(2) Bonding separation in the non-hatched area (8 x 95mm) of the upper and lower surfaces of each blade is permissible but must be inspected using the tapping method at intervals not to exceed 25 hours TIS in order to monitor possible propagation. If the bonding separation reaches the hatched area, the blade must be replaced with an airworthy blade before further flight (see Figure 1 of the SB).
(b) Before further flight, and thereafter at intervals not to exceed 100 hours TIS or 6 calendar months, whichever occurs first, visually inspect for bonding separation, a crack, or corrosion on the upper and lower skin in the 100 x 95mm blade root area (see Figure 1 of the SB). If a bonding separation in the hatched area, a crack, or corrosion is detected, replace the blade with an airworthy blade prior to further flight.
(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, FAA, Rotorcraft Directorate. 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 inspection and replacement, if necessary, shall be done in accordance with the Accomplishment Instructions of Eurocopter Service Bulletin No. 05.91 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 American 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.
NOTE 3: The subject of this AD is addressed in Direction Generale de L'Aviation Civile (France) AD 97-135-055(A) R1, dated July 15, 1998 and AD 97-135-055(A)R2, dated December 16, 1998.
(f) This amendment becomes effective on May 13, 1999. FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aerospace Engineer, Rotorcraft Standards Staff, 2601 Meacham Blvd. Fort Worth, Texas 76137, telephone (817) 222-5116, fax (817) 222-5961.
