[Federal Register Volume 61, Number 75 (Wednesday, April 17, 1996)]
[Rules and Regulations]
[Pages 16703-16704]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-9272]
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Rules and Regulations
Federal Register
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This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
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Federal Register / Vol. 61, No. 75 / Wednesday, April 17, 1996 /
Rules and Regulations
[[Page 16703]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-SW-14-AD; Amendment 39-9570; 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
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: 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.
DATES: Effective May 22, 1996. -
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 22, 1996.
ADDRESSES: The service information referenced in this AD 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; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
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: 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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]-
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
AD 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
[[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]
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