AD 96-08-04

This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model BO-105, BO-105A, BO-105C, BO-105S, and BO-105LS A-1 helicopters, that requires a ground test and inspection of the tandem hydraulic switch-over system (switch-over system) for component wear and parts replacement, if necessary. This amendment is prompted by incidents involving Model BO-105 series helicopters in which, during the switch-over from Hydraulic System 1 to Hydraulic System 2, a 3-inch drop in the collective occurred, caused by component wear in the switch-over system. The actions specified by this AD are intended to detect switch-over system component wear, which could result in a sudden drop in the collective and a sudden loss of altitude.

Final rule

96-08-04 EUROCOPTER DEUTSCHLAND GmbH (ECD): Amendment 39-9570. Docket No. 95-SW-14-AD.

Applicability: 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 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.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to Eurocopter Model BO-105, BO-105A, BO-105C, BO-105S, and BO-105LS A-1 helicopters was published in the Federal Register on November 2, 1995 (60 FR 55680). That action proposed to require a ground test and inspection of the tandem hydraulic switch-over system (switch-over system) for component wear and parts replacement, if necessary.

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed, except for editorial changes. The FAA has determined that these changes will neither increase the cost to any operator nor increase the scope of this AD.

The FAA estimates that 165 helicopters of U.S. registry will be affected by this AD, that it will take approximately 5 work hours per helicopter to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts, if needed, will cost approximately $750. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $173,250.

The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40113, 44701.

39.13 - [Amended]
2. Section39.13 is amended by adding a new airworthiness directive to read as follows: