[Federal Register Volume 60, Number 212 (Thursday, November 2, 1995)]
[Proposed Rules]
[Pages 55680-55681]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-27202]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-SW-14-AD]


Airworthiness Directives; Eurocopter Deutschland GmbH (ECD) Model 
BO-105, BO-105A, BO-105C, BO-105S, BO-105LS A-1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to Eurocopter Deutschland GmbH (ECD) 
(Eurocopter) Model BO-105, BO-105A, BO-105C, BO-105S, BO-105LS A-1 
helicopters. This proposal would require a ground test and inspection 
of the tandem hydraulic switch-over system (switch-over system) for 
component wear and parts replacement, if necessary. This proposal 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 the proposed 
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.

DATES: Comments must be received by January 2, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 95-SW-14-AD, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137. Comments may be inspected at this location between 9:00 
a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005. This information may be examined at the FAA, 
Office of the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Mr. Robert McCallister, Aerospace 
Engineer, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5121, fax 
(817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 95-SW-14-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Assistant Chief Counsel, Attention: Rules 
Docket No. 95-SW-14-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

Discussion

    The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority 
for the Federal Republic of Germany, has notified the FAA that an 
unsafe condition may exist on Eurocopter Deutschland GmbH (ECD) 
(Eurocopter) Model BO-105 series helicopters. The LBA advises that 
excessive wear on tandem hydraulic units may exist on certain 
Eurocopter Model BO-105 series helicopters. Wear of more than 0.5mm in 
the switch-over components may prevent normal switching from Hydraulic 
System 1 to Hydraulic System 2.
    Eurocopter has issued MBB-Helicopters Alert Service Bulletin ASB-BO 
105-40-102, dated April 20, 1989, applicable to all BO-105 series 
helicopters with tandem hydraulic units, part numbers 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 Hydraulic System 1 or 
Hydraulic System 2. This service bulletin specifies procedures for a 
ground test of the tandem hydraulic switch-over system to determine 
whether excessive wear exists. The LBA classified this service bulletin 
as mandatory and issued AD 89-123/2 MBB, dated October 25, 1989, in 
order to assure the continued airworthiness of these helicopters in 
Germany.
    This helicopter model is manufactured in Germany and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the LBA has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
LBA, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are certificated for 
operation in the United States.
    There has been a recent occurrence in the United States that may 
have been attributable to this out-of-tolerance condition. Since an 
unsafe condition has been identified that is likely to exist or develop 
on other Eurocopter Model BO-105, BO-105A, BO-105C, BO-105S, BO-105LS 
A-1 helicopters of the same type design registered in the United 
States, the proposed AD would require that a ground test be conducted 
of the tandem hydraulic switch-over system to detect component wear and 
require parts replacement if necessary. The actions would be required 
to be accomplished in accordance with the service bulletin described 
previously.
    The FAA estimates that 165 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 5 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts, if needed, 
would cost approximately $750. Based on these figures, the total cost 
impact of the proposed AD on U.S. operators is estimated to be 
$173,250.
    The regulations proposed herein would not have substantial direct 
effects on the States, on the relationship between the national 
government and 

[[Page 55681]]
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 proposal would not 
have sufficient federalism implications to warrant the preparation of a 
Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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), 40101, 40113, 44701.


Sec. 39.13  [Amended] -

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Eurocopter Deutschland GmbH (ECD): 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 units, part numbers (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 
Secs. 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.

    Issued in Fort Worth, Texas, on October 26, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-27202 Filed 11-1-95; 8:45 am]
BILLING CODE 4910-13-U