AD 2000-20-19

[Federal Register Volume 65, Number 200 (Monday, October 16, 2000)]
[Rules and Regulations]
[Pages 61085-61087]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-26234]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-25-AD; Amendment 39-11931; AD 2000-20-19]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS-350B, BA, 
B1, B2, B3, C, D, and D1, and AS-355E, F, F1, F2 and N Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and 
AS-355E, F, F1, and F2 helicopters. That AD currently requires 
inspections of the main rotor head components, the main gearbox (MGB) 
suspension bars, and the ground resonance prevention system components. 
This amendment requires those same inspections, but would also apply to 
Model AS-350B3 and AS-355N helicopters. This amendment is prompted by 
the inadvertent omission of those model helicopters from the previous 
AD. The actions specified by this AD are intended to prevent ground 
resonance due to reduced structural stiffness, which could lead to 
failure of a main rotor head or MGB suspension component and subsequent 
loss of control of the helicopter.

DATES: Effective November 20, 2000.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of May 23, 2000 (65 FR 20721, April 18, 2000).

ADDRESSES: The service information referenced in this AD may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the 
Regional Counsel, Southwest Region, 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: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5490, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

[[Page 61086]]

Aviation Regulations (14 CFR part 39) by superseding AD 86-15-10 R2, 
Amendment 39-11681 (65 FR 20721), which applies to Eurocopter France 
Model AS-350B, BA, B1, B2, B3, C, D, and D1, and AS-355E, F, F1, F2 and 
N helicopters was published in the Federal Register on July 20, 2000 
(65 FR 44995). That action proposed to require an initial inspection 
within 10 hours time-in-service (TIS) and thereafter, repetitive 
inspections of the main rotor head components, the MGB suspension bars, 
and the ground resonance prevention system components at intervals not 
to exceed 500 hours TIS.
    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 586 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $480 per 
helicopter, or $281,280 for the entire fleet.
    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 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 removing Amendment 39-11681 (65 FR 
20721, April 18, 2000), Amendment 39-6515 (55 FR 5833, February 20, 
1990) and Amendment 39-5517 (52 FR 13233, April 22, 1987) and by adding 
a new airworthiness directive (AD), Amendment 39-11931, to read as 
follows:

2000-20-19  Eurocopter France: Amendment 39-11931. Docket No. 2000-
SW-25-AD. Supersedes AD 86-15-10 R2, Amendment 39-11681, Docket No. 
98-SW-82-AD; AD 86-15-10R1, Amendment 39-6515, Docket No. 86-ASW-22; 
and AD 86-15-10, Amendment 39-5517, Docket No. 86-ASW-22.

    Applicability: Model AS-350B, BA, B1, B2, B3, C, D, and D1, and 
AS-355E, F, F1, F2 and N helicopters, 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 (f) 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 ground resonance due to reduced structural stiffness, 
which could lead to failure of a main rotor head or main gearbox 
(MGB) suspension component and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Within 10 hours time-in-service (TIS):
    (1) For Model AS-350B, BA, B1, B2, B3, C, D, and D1 helicopters, 
inspect the main rotor head components, the MGB suspension bars 
(struts), and the landing gear ground resonance prevention 
components (aft spring blades and hydraulic shock absorbers) in 
accordance with paragraph CC.3 of Aerospatiale Service Bulletin (SB) 
No. 01.17a (not dated).
    (2) For Model AS-355E, F, F1, F2, and N helicopters, inspect the 
main rotor head components, the MGB suspension bars (struts), and 
the landing gear ground resonance prevention components (aft spring 
blades and hydraulic shock absorbers) in accordance with paragraph 
CC.3 of SB No. 01.14a (not dated).
    (b) Rework or replace damaged components in accordance with SB 
No. 01.17a or SB No. 01.14a, as applicable.
    (c) Repeat the inspections and rework required by paragraphs (a) 
and (b) of this AD at intervals not to exceed 500 hours TIS.
    (d) If the helicopter is subjected to a hard landing or to high 
surface winds when parked without effective tiedown straps 
installed, repeat the inspections required by paragraph (a) of this 
AD for the main rotor head star arms and the MGB suspension bars 
(struts) before further flight.
    (e) After a landing with abnormal self-sustained dynamic 
vibrations (ground resonance type vibrations), repeat all the 
inspections required by paragraph (a) of this AD.
    (f) 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.

    (g) 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.
    (h) The inspections shall be done in accordance with paragraph 
CC.3 of Aerospatiale Service Bulletin No. 01.17a (not dated) or No. 
01.14a (not dated), as applicable. The rework or replacement, if 
necessary, shall be done in accordance with Aerospatiale Service 
Bulletin No. 01.17a or No. 01.14a (neither is dated), as applicable. 
The incorporation by reference of those documents was previously 
approved by the Director of the Federal Register in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51 as of May 23, 2000 (65 FR 20721, 
April 18, 2000). Copies may be obtained from American Eurocopter 
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, 
telephone (972) 641-3460, fax (972) 641-3527. Copies may be 
inspected at the FAA, Office of the Regional Counsel, Southwest 
Region, 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.
    (i) This amendment becomes effective on November 20, 2000.


[[Page 61087]]


    Issued in Fort Worth, Texas, on September 29, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-26234 Filed 10-13-00; 8:45 am]
BILLING CODE 4910-13-U