AD Amdt-39-11681

[Federal Register Volume 65, Number 75 (Tuesday, April 18, 2000)]
[Rules and Regulations]
[Pages 20721-20723]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-9109]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-82-AD; Amendment 39-11681; AD 86-15-10 R2]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS-350B, BA, 
B1, B2, 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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[[Page 20722]]

SUMMARY: This amendment revises an existing airworthiness directive 
(AD), applicable to Eurocopter France Model AS-350B, BA, B1, B2, C, D, 
and D1, and AS-355E, F, F1, F2 and N helicopters, that currently 
requires repetitive inspections of the main rotor head components, the 
main gearbox (MGB) suspension bars, and the ground resonance prevention 
system components at intervals not to exceed 400 hours time-in-service 
(TIS). This amendment requires the same inspections, but at intervals 
not to exceed 500 hours TIS. This amendment is prompted by reports of 
confusion and unnecessary costs associated with the difference in the 
current 400 hours TIS inspection interval and the current 
manufacturer's master service recommendation of 500 hours TIS 
inspection interval. The actions specified by this AD are intended to 
eliminate confusion and unnecessary costs and 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 May 23, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 23, 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, Aerospace 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 
Aviation Regulations (14 CFR part 39) by revising AD 86-15-10, 
Amendment 39-5517 (52 FR 13233, April 22, 1987) and AD 86-15-10 R1, 
Amendment 39-6515 (55 FR 5833, February 20, 1990), which is applicable 
to Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and AS-
355E, F, F1, F2 and N helicopters, was published in the Federal 
Register on January 20, 2000 (65 FR 3165). The action proposed to 
require 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 has determined that this regulation is relieving in nature 
and imposes no additional costs or regulatory burden on any person.
    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 39-5517 (52 FR 
13233, April 22, 1987) and Amendment 39-6515 (55 FR 5833, February 20, 
1990) and by adding a new airworthiness directive (AD), Amendment 39-
11681, to read as follows:

AD 86-15-10 R2  Eurocopter France: Amendment 39-11681. Docket No. 
98-SW-82-AD. Revises AD 86-15-10, Amendment 39-5517 and AD 86-15-10 
R1, Amendment 39-6515.

    Applicability: Model AS-350B, BA, B1, B2, C, D, and D1, and AS-
355E, F, F1, F2 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 
(MBG) 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, 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 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.

[[Page 20723]]

    (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 
before further flight.
    (e) In the event of a landing which exhibits abnormal self-
sustained dynamic vibrations (ground resonance type vibrations), 
repeat all the inspections contained in 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, FAA, Regulations Group, Rotorcraft 
Directorate. 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 and modification shall be done in accordance 
with Aerospatiale Service Bulletin No. 01.17a or No. 01.14a (neither 
is dated). 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, 
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 May 23, 2000.

    Issued in Fort Worth, Texas, on April 4, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-9109 Filed 4-17-00; 8:45 am]
BILLING CODE 4910-13-U