Airworthiness directives › 99-08-06
AD 99-08-06 Airworthiness Directives; Eurocopter France Model SA. 3160, SA. 316B, SA. 316C, and SA. 319B Helicopters
Models named: SE. 3160, SA. 316B, SA. 316C, SA. 319B. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model SE. 3160, SA. 316B, SA. 316C, and SA. 319B helicopters, with main rotor blade, part numbers (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, and 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 (e) 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.
Compliance
Required as indicated, unless accomplished previously. To detect bonding separation, corrosion, or cracks in the area of a main rotor blade (blade) root reinforcement strip, which could result in failure of the blade and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, and afterwards at intervals not to exceed 100 hours time-in-service or 6 calendar months, whichever occurs first, inspect the spar skin and blade root reinforcement strip area for a bonding separation, corrosion, or a crack in accordance with paragraphs 2.A and 2.B of the Accomplishment Instructions in Eurocopter SA 316/319 Service Bulletin No. 05.92. Revision No. 1, dated September 28, 1998 (SB), except operators are not required to contact Eurocopter if an anamoly is found. (b) For the hatched areas (1.5 x 50mm and 10 x 100mm) on the upper and lower surfaces of each blade, if bonding separation is found, replace the blade with an airworthy blade prior to further flight (refer to Figure 1 of the SB). (c) Bonding separation in the non-hatched area (10 x 100mm) of the upper and lower surfaces of each blade is permissible and must be inspected using the tapping method at intervals not to exceed 25 hours time-in-service to monitor possible propagation. When the bonding separation reaches the hatched area, the blade must be replaced with an airworthy blade (refer to Figure 1 of the SB). (d) 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). (e) 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, 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, Standards Staff. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standards Staff. (f) Special flight permits will not be issued. (g) Accomplish the inspections in accordance with Eurocopter SA 316/319 Service Bulletin No. 05.92 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. (h) This amendment becomes effective on April 22, 1999. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 98-285-057(A), dated July 15, 1998, and AD 98-285-057(A)R1, dated December 16, 1998. Issued in Fort Worth, Texas, on March 30, 1999. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 99-8409 Filed 4-6-99; 8:45 am] BILLING CODE 4910-13-U
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1