Airworthiness directives › 99-09-06
AD 99-09-06 Airworthiness Directives; Eurocopter France Model AS-350B, B1, B2, B3, BA, and D Helicopters, and Model AS 355E, F, F1, F2 and N Helicopters
Models named: AS-350B, B1, B2, B3, BA, D, AS 355E, F, F1, F2. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Eurocopter France Model AS-350B, B1, B2, B3, BA, and D helicopters, and Model AS 355E, F, F1, F2 and N helicopters, with tail rotor spider assembly, part number 350A332004-03 or 350A332004-05, 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 (d) 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 prevent seizure of the tail rotor spider plate bearing (bearing), loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following in accordance with the specified paragraphs of Eurocopter Service Bulletin (SB) 05.00.29, applicable to Model AS-350 helicopters, or SB 05.00.30, applicable to Model AS 355 helicopters, both dated February 8, 1999, as applicable: (a) Within 50 hours time-in-service, measure the rotational torque of the bearing using the operational procedure in paragraph 2.B.1 of the Accomplishment Instructions in the applicable SB. If the rotational load is equal to or greater than 300 grams, replace the pitch change spider plate assembly with an airworthy pitch change spider plate assembly before further flight. (b) At intervals not to exceed 100 hours time-in-service, measure the axial play, and inspect for rotational binding or brinelling of the bearing using the operational procedure in paragraph 2.B.2 of the Accomplishment Instructions in the applicable SB. (c) If the bearing fails to meet the airworthiness criteria stated in paragraph 2.B.3(b) of the Accomplishment Instructions in the applicable SB, replace the pitch change spider plate assembly with an airworthy pitch change spider plate assembly before further flight. (d) 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. (e) Special 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. (f) The measurements and replacements, if necessary, shall be done in accordance with Eurocopter Mandatory SB 05.00.29, applicable to Model AS-350 helicopters, or Eurocopter Mandatory SB 05.00.30, applicable to Model AS 355 helicopters, both dated February 8, 1999, as applicable. 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, (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 98-SW-44-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 10, 1999. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 1999-084-057(A) and AD 1999-085-076(A), both dated February 24, 1999. Issued in Fort Worth, Texas, on April 14, 1999. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 99-10053 Filed 4-22-99; 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