Airworthiness directives › 96-08-04
AD 96-08-04 Airworthiness Directives; Eurocopter Deutschland GmbH (ECD) Model BO-105, BO-105A, BO-105C, BO-105S, and BO-105LS A-1 Helicopters
Models named: BO-105, BO-105A, BO-105C, BO-105S, BO- 105LS A-1. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model BO-105, BO-105A, BO-105C, BO-105S, and BO- 105LS A-1 helicopters with tandem hydraulic unit, part number (P/N) 105-45021, 105-45023, or 105-45028, having valve body manifolds D133-756, D133-756E, ZE1-126-I, ZE2-126, or ZE2-126-1, installed on either Hydraulic System 1 or Hydraulic System 2, certificated in any category. -Note 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 (b) to request approval from the FAA. This approval may address [[Page 16704]] 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. -
Compliance
Required as indicated, unless accomplished previously. - To detect switch-over system component wear, which could result in a sudden drop in the collective and a sudden loss of altitude, accomplish the following: - (a) Within 50 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 1 year, conduct a ground test of the tandem hydraulic system and an inspection of the switch-over system linkage for wear in accordance with section A, ``Inspections Required,'' of the Accomplishment Instructions of MBB- Helicopters Alert Service Bulletin ASB-BO 105-40-102, dated April 20, 1989. Based on the results of this ground test, accomplish the following as appropriate: - (1) If no switch-over reactions occur during the ground test, no further action is required. - (2) If any switch-over reaction occurs during the ground test, perform the additional inspections of the switch-over system and perform the required maintenance procedures in accordance with section B, ``Work Procedure,'' of the Accomplishment Instructions of MBB-Helicopters Alert Service Bulletin ASB-BO 105-40-102, dated April 20, 1989. - (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when 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. -(c) 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. - (d) The test, inspection, and parts replacement, if necessary shall be done in accordance with MBB-Helicopters Alert Service Bulletin ASB-BO 105-40-102, dated April 20, 1989. 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. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 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. - (e) This amendment becomes effective on May 22, 1996. Issued in Fort Worth, Texas, on April 2, 1996. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 96-9272 Filed 4-16-96; 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