[Federal Register Volume 64, Number 229 (Tuesday, November 30, 1999)]
[Rules and Regulations]
[Pages 66762-66763]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30797]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-41-AD; Amendment 39-11443; AD 99-24-18]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to Eurocopter France Model AS-350B, B1, B2, B3, BA, 
and D, and AS-355E, F, F1, F2, and N helicopters, that requires 
inspecting certain versions of the tail rotor spider plate bearing 
(bearing) for the proper rotational torque, axial play, and any 
brinelling of the bearing. This amendment has the same inspection 
requirements as the current AD. Also, this AD expands the applicability 
to include additional part numbers (P/N's) and reduces the initial and 
recurring inspection compliance times. This amendment is prompted by 
additional reports of deterioration of the bearing. The actions 
specified by this AD are intended to prevent seizure of the bearing, 
loss of tail rotor control, and subsequent loss of control of the 
helicopter.

DATES: Effective December 15, 1999. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of December 15, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before January 31, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-41-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    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 
76137; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: On April 14, 1999, the FAA issued AD 99-09-
06, Amendment 39-11139 (64 FR 19881, April 23, 1999), to require 
inspecting the bearing for the proper rotational torque, axial play, 
and any brinelling of the bearing. That action was prompted by service 
difficulty reports citing the need to prematurely replace bearings due 
to wear and by two in-flight incidents of increased tail rotor 
vibration levels due to bearing wear. That condition, if not corrected, 
could result in seizure of the bearing, loss of tail rotor control, and 
subsequent loss of control of the helicopter.
    Since the issuance of that AD, the FAA has received additional 
reports of deterioration of the bearing affected by AD 99-09-06 and 
other bearings not covered by AD 99-09-06. Therefore, this AD expands 
the applicability to include additional bearing P/N's and to reduce the 
initial and recurring inspection compliance times.
    Eurocopter France has issued Service Bulletin (SB) 05.00.29, 
Revision 2, applicable to Model AS-350 series helicopters, and SB 
05.00.30, Revision 2, applicable to Model AS-355 series helicopters, 
both dated September 29, 1999. These SB's specify a check of the 
bearing for rotational torque. The Direction Generale De L'Aviation 
Civile (DGAC), the airworthiness authority for France, classified these 
SB's as mandatory and issued AD's 1999-085-076(A)R2 and 1999-084-
057(A)R2, both dated October 20, 1999, to ensure the continued 
airworthiness of these helicopters in France.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Eurocopter France Model AS-350B, B1, B2, B3, 
BA, and D, and AS-355E, F, F1, F2, and N helicopters of the same type 
design, this AD supersedes AD 99-09-06 (64 FR 19881, April 23, 1999). 
This AD has the same requirements as the current AD. This AD also 
expands the applicability to include additional P/N's 350A33-2004-00, -
01 and -02, and 350A33-2009-00 and -01, installed, and excludes a 
bearing which has MOD 076551 incorporated. This AD also revises the 
initial and recurring inspection compliance times. The actions are 
required to be accomplished in accordance with the SB's described 
previously. The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. Therefore, including additional P/
N's in the applicability, requiring an initial inspection within 10 
hours time-in-service (TIS) to measure the bearing rotational torque, 
and inspecting the bearing for axial play or brinelling at intervals 
not to exceed 50 hours TIS or 6 months, whichever occurs first, are 
required and this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that 507 helicopters will be affected by this AD, 
that it will take approximately 1 work hour to accomplish the 
inspection, and 4 work hours to replace a bearing, if required, and 
that the average labor rate is $60 per work hour. Required parts will 
cost approximately $60 per helicopter. Based on these figures, the 
total cost impact of the AD on U.S. operators is estimated to be 
$182,520 to inspect all affected helicopters and to replace one bearing 
in each helicopter in the fleet.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and

[[Page 66763]]

suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 99-SW-41-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not impose substantial direct 
compliance costs on states or local governments or 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 13132, the FAA has not consulted with 
States or local authorities prior to the publication of this rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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 39-11139 (64 FR 
19881, April 23, 1999), and by adding a new airworthiness directive 
(AD), Amendment 39-11443, to read as follows:

AD 99-24-18  Eurocopter France: Amendment 39-11443. Docket No. 99-
SW-41-AD. Supersedes AD 99-09-06, Amendment 39-11139, Docket No. 98-
SW-44-AD.

    Applicability: AS-350B, B1, B2, B3, BA, and D, and AS-355E, F, 
F1, F2, and N helicopters, with tail rotor spider assembly, part 
number (P/N) 350A33-2004-00, -01, -02, -03, -05, or 350A33-2009-00 
or -01, installed, and which do not incorporate MOD 076551, 
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 seizure of the tail rotor spider plate bearing 
(bearing), loss of tail rotor control, and subsequent loss of 
control of the helicopter, accomplish the following in accordance 
with the specified paragraphs of Eurocopter Service Bulletin (SB) 
05.00.29, Revision 2, applicable to Model AS-350 helicopters, or SB 
05.00.30, Revision 2, applicable to Model AS 355 helicopters, both 
dated September 29, 1999, as applicable.
    (a) Within 10 hours time-in-service (TIS), measure the 
rotational torque of the bearing using the operational procedure in 
paragraph 2.B.1) of the Accomplishment Instructions in the 
applicable SB. If the rotational load is equal to or greater than 
300 grams, replace the pitch change spider plate assembly with an 
airworthy pitch change spider plate assembly before further flight.
    (b) At intervals not to exceed 50 hours TIS or at intervals not 
to exceed 6 months, whichever occurs first, measure the axial play 
and inspect for rotational binding or brinelling of the bearing 
using the operational procedure in paragraph 2.B.2) of the 
Accomplishment Instructions in the applicable SB.
    (c) If the bearing fails to meet the airworthiness criteria 
stated in paragraph 2.B.3)b) of the Accomplishment Instructions in 
the applicable SB, replace the pitch change spider plate assembly 
with an airworthy pitch change spider plate assembly before further 
flight.
    (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, Rotorcraft Directorate.

    (e) 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.
    (f) The inspections and replacements, if necessary, shall be 
done in accordance with paragraph 2.B of Eurocopter SB 05.00.29, 
Revision 2, applicable to Model AS-350 helicopters, or Eurocopter SB 
05.00.30, Revision 2, applicable to Model AS 355 helicopters, both 
dated September 29, 1999, as applicable. 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, Rules Docket No. 99-SW-41-AD, 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.
    (g) This amendment becomes effective on December 15, 1999.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 1999-084-057(A)R2 and AD 
1999-085-076(A)R2, both dated October 20, 1999.

    Issued in Fort Worth, Texas, on November 19, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-30797 Filed 11-29-99; 8:45 am]
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