[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