Airworthiness Directives; Eurocopter Deutschland GMBH Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 Helicopters

[Federal Register Volume 65, Number 167 (Monday, August 28, 2000)]
[Rules and Regulations]
[Pages 52010-52012]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-21871]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-66-AD; Amendment 39-11882; AD 2000-17-08]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Deutschland GMBH Model BO-
105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 
CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) that applies to Eurocopter Deutschland

[[Page 52011]]

GMBH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-
4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 
helicopters. That AD requires creating a component log card or 
equivalent record and determining the calendar age and number of 
flights on each tension-torsion (TT) strap. That AD also requires 
inspecting and removing, as necessary, certain unairworthy TT straps. 
This amendment establishes a life limit for certain main rotor TT 
straps. This amendment is prompted by a need to establish a life limit 
for certain TT straps because of an accident in which a main rotor 
blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to 
fatigue failure of a TT strap. The same part-numbered TT strap is used 
on the ECD Model BO-105 helicopters. The actions specified by this AD 
are intended to prevent fatigue failure of the TT strap, loss of a 
blade, and subsequent loss of control of the helicopter.

EFFECTIVE DATE: October 2, 2000.

FOR FURTHER INFORMATION CONTACT: Charles Harrison, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5128, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-19-22, which 
applies to ECD Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 
CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-
1 helicopters, was published in the Federal Register on April 24, 2000 
(65 FR 21673). That action proposed to require establishing a life 
limit for the TT straps of 120 months or 40,000 flights, whichever 
occurs first.
    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.
    The FAA estimates that 200 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 16 work hours per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$10,400 per helicopter. Based on these figures, the total cost impact 
of this AD on U.S. operators is estimated to be $2,272,200.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 removing Amendment 39-11357 (64 FR 
54770, October 8, 1999), and by adding a new airworthiness directive 
(AD), Amendment 39-11882, to read as follows:

2000-17-08  Eurocopter Deutschland GMBH: Amendment 39-11882. Docket 
No. 99-SW-66-AD. Supersedes AD 99-19-22, Amendment 39-11357, Docket 
No. 99-SW-52-AD.

    Applicability: Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, 
BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and 
BO-105LS A-1 helicopters, with part number (P/N) 2604067 (Bendix) or 
J17322-1 (Lord) rotor tension-torsion (TT) strap, installed, 
certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue failure of a TT strap, loss of a main rotor 
blade (blade), and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Before further flight,
    (1) Create a component log card or equivalent record for each TT 
strap.
    (2) Review the history of the helicopter and each TT strap. 
Determine the age since initial installation on any helicopter (age) 
and the number of flights on each TT strap. Enter both the age and 
the number of flights for each TT strap on the component log card or 
equivalent record. When the number of flights is unknown, multiply 
the number of hours time-in-service (TIS) by 5 to determine the 
number of flights. If a TT strap has been previously used at any 
time on Model BO-105LS A-3 ``SUPER LIFTER'', BO-105 CB-5, BO-105 
CBS-5, BO-105 DBS-5, or any MBB-BK 117 series helicopter, multiply 
the number of flights accumulated on those other models by a factor 
of 1.6 and then add that result to the number of flights accumulated 
on the helicopters affected by this AD.
    (3) Remove any TT strap from service if the total hours TIS or 
number of flights and age cannot be determined.
    (b) On or before January 1, 2001, remove any TT strap that has 
been in service 120 months since initial installation on any 
helicopter or accumulated 40,000 flights (a flight is a takeoff and 
a landing), on any helicopter. Replace the TT strap with an 
airworthy TT strap.
    (c) This AD revises the Airworthiness Limitations Section of the 
maintenance manual by establishing a life limit for the TT strap, P/
N 2604067 and J17322-1, of 120 months or 40,000 flights, whichever 
occurs first.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Regulations Group, 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, Regulations Group.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR

[[Page 52012]]

21.197 and 21.199) to operate the helicopter to a location where the 
requirements of this AD can be accomplished.
    (f) This amendment becomes effective on October 2, 2000.

    Note 3: The subject of this AD is addressed in the Luftfahrt 
Bundesamt (Federal Republic of Germany) AD 1999-300/3, dated August 
31, 1999.


    Issued in Fort Worth, Texas, on August 21, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-21871 Filed 8-25-00; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:36:53.028950+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

eeaa4acfbb4584eec837b5112996ccee7c389bcdec7dab7f7a624dc86bb353d4

Text SHA-256

2d86fc04f8d2332371c3b42ce375c7f4df0c8c2ca4c899f82cc9cc8dc56b2f10