[Federal Register Volume 59, Number 176 (Tuesday, September 13, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-22414]


[[Page Unknown]]

[Federal Register: September 13, 1994]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-SW-22-AD; Amendment 39-9023; AD 94-19-02]

 

Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
206A, 206A-1, 206B, 206B-1, 206L, 206L-1, and 206L-3 Series Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Bell Helicopter Textron, Inc. Model 206A, 206A-1, 
206B, 206B-1, 206L, 206L-1, and 206L-3 series helicopters. This action 
requires initial and repetitive inspections of the swashplate for 
cracks in the swashplate support assembly fillet radius area and 
replacement, if necessary. This amendment is prompted by reports of 
cracks found in the swashplate support assembly fillet radius area near 
the base. The actions specified in this AD are intended to prevent 
failure of the swashplate support assembly, loss of control of the main 
rotor system, and subsequent loss of control of the helicopter.

DATES: Effective on September 28, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 28, 1994.
    Comments for inclusion in the Rules Docket must be received on or 
before October 28, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 93-SW-22-AD, 2601 Meacham Boulevard, Room 663, Fort 
Worth, Texas 76137.
    The service information referenced in this AD may be obtained from 
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. 
This information may be examined at the FAA, Office of the Assistant 
Chief Counsel, 2601 Meacham Boulevard, 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. Richard Monschke, Aviation Safety 
Engineer, Rotorcraft Certification Office, FAA, Rotorcraft Directorate, 
ASW-170, Fort Worth, Texas 76193-0170, telephone (817) 222-5177, fax 
(817) 222-5959.

SUPPLEMENTARY INFORMATION: This amendment adopts a new airworthiness 
directive (AD) applicable to Bell Helicopter Textron, Inc. (BHTI) Model 
206A, 206A-1, 206B, 206B-1, 206L, 206L-1, and 206L-3 series 
helicopters, equipped with swashplate support assembly, part number (P/
N) 206-010-452-001, -005, or -109. BHTI has received three reports of 
swashplate support assemblies with cracks in the fillet radius area 
near the base. The cracks originated on the aft section of the 
swashplate support assembly. The total time-in-service (TIS) on each of 
the reported swashplate support assemblies exceeded 1,500 hours. The 
swashplate support assembly is a critical, non-rotating, rotor system 
component that supports the rotating swashplate. Through the swashplate 
support assembly and subsequently the swashplate, the pilot control 
movements that are necessary to maintain rotorcraft control are 
transferred to the main rotor system. Therefore, a crack in a 
swashplate support assembly creates an unsafe condition. This 
condition, if not corrected, could result in failure of the swashplate 
support assembly, loss of control of the main rotor system, and 
subsequent loss of control of the helicopter.
    The FAA has reviewed and approved Bell Helicopter Textron, Inc. 
Alert Service Bulletin No. 206-93-74, Revision B, and 206L-93-89, 
Revision B, both dated April 4, 1994, which describe procedures for an 
initial visual inspection for cracks within the next 25 hours TIS using 
a 10-power magnifying glass, and thereafter, repetitive visual 
inspections for cracks at intervals not to exceed 50 hours TIS from the 
last inspection. The inspections are for swashplate support assemblies 
that have more than 1,500 hours TIS. If a crack is suspected, the Alert 
Service Bulletins provide for a dye penetrant inspection. If a crack is 
found, the applicable Alert Service Bulletin specifies replacement of 
the swashplate support assembly with an airworthy swashplate support 
assembly prior to the next flight. Neither BHTI Alert Service Bulletin 
No. 206-93-74, Revision B, nor 206L-93-89, Revision B, both dated April 
4, 1994, shows the Model 206A-1 as being an affected model helicopter. 
However, this model helicopter uses the same swashplate support 
assembly as the Model 206A helicopter. Therefore, for purposes of this 
AD, Alert Service Bulletin No. 206-93-74, Revision B, dated April 4, 
1994, will also apply to the Model 206A-1 helicopter.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Bell Helicopter Textron, Inc. Model 206A, 
206A-1, 206B, 206B-1, 206L, 206L-1, and 206L-3 series helicopters of 
the same type design, this AD is being issued to prevent failure of the 
swashplate support assembly, loss of control of the main rotor system, 
and subsequent loss of control of the helicopter. For swashplate 
support assemblies that have 1,500 hours or more total TIS, this AD 
requires an initial visual inspection for cracks using a 10-power or 
higher magnifying glass within 25 hours TIS. Also, for swashplate 
support assemblies with less than 1,500 hours total TIS, this AD 
requires an initial visual inspection for cracks using a 10-power or 
higher magnifying glass prior to attaining 1,525 hours total TIS. 
Thereafter, repetitive inspections of the affected swashplate support 
assemblies are required at intervals not to exceed 50 hours TIS from 
the last inspection. If a crack is suspected, a dye penetrant 
inspection is required. Replacement of cracked swashplate support 
assemblies with airworthy swashplate support assemblies is required. 
Installation of an airworthy swashplate support assembly, P/N 206-010-
452-113, constitutes a terminating action for the requirements of this 
AD. The actions are required to be accomplished in accordance with the 
service bulletins described previously. Due to the criticalness of the 
swashplate support assembly and the short compliance times, this rule 
must be issued immediately to correct an unsafe condition in aircraft.
    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.

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 
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 Number 93-SW-22-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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.
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

AD 94-07-11  Bell Helicopter Textron, Inc. (BHTI): Amendment 39-
8869. Docket Number 93-SW-22-AD.

    Applicability: Model 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 
and 206L-3 series helicopters, equipped with swashplate support 
assembly, part number (P/N) 206-010-452-001, -005, or -109, 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously. To prevent failure of the swashplate support assembly, 
loss of control of the main rotor system, and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) For swashplate support assemblies with 1,500 hours or more 
total time-in-service (TIS), within the next 25 hours TIS, and 
thereafter at intervals not to exceed 50 hours TIS from the last 
inspection, visually inspect the swashplate support assembly in the 
fillet radius area for cracks using a 10-power or higher magnifying 
glass in accordance with the Accomplishment Instructions of the 
applicable BHTI Alert Service Bulletin (ASB) No. 206-93-74, Revision 
B, or 206L-93-89, Revision B, both dated April 4, 1994.
    (b) For swashplate support assemblies with less than 1,500 hours 
TIS, prior to attaining 1,525 hours total TIS, and thereafter at 
intervals not to exceed 50 hours TIS from the last inspection, 
visually inspect the swashplate support assemblies in the fillet 
radius area for cracks using a 10-power or higher magnifying glass 
in accordance with the Accomplishment Instructions of the applicable 
ASB, dated April 4, 1994.
    (c) ASB No. 206-93-74, Revision B, dated April 4, 1994, is 
applicable to BHTI Model 206A-1 helicopters in addition to the Model 
206A, 206B and 206B-1 helicopters.
    (d) If a crack is suspected, perform a dye penetrant inspection 
in accordance with the Accomplishment Instructions of the applicable 
ASB, dated April 4, 1994, before further flight.
    (e) Replace any cracked swashplate support assembly with an 
airworthy assembly before further flight.
    (f) Installation of a swashplate support assembly, P/N 206-010-
452-113, constitutes a terminating action for the requirements of 
this AD.

    Note: The swashplate support assembly, P/N 206-010-452-113, has 
a life limit of 4,800 hours TIS.

    (g) 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 Certification Office, 
FAA, 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, Rotorcraft Certification 
Office.

    Note: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (h) 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.
    (i) The inspections and replacement, if necessary, shall be done 
in accordance with BHTI ASB No. 206-93-74, Revision B, or 206L-93-
89, Revision B, both dated April 4, 1994. 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort 
Worth, Texas 76101. Copies may be inspected at the FAA, Office of 
the Assistant Chief Counsel, 2601 Meacham Boulevard, Room 663, Fort 
Worth, Texas; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (j) This amendment becomes effective on September 28, 1994.

    Issued in Fort Worth, Texas, on September 6, 1994.
James D. Erickson,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 94-22414 Filed 9-12-94; 8:45 am]
BILLING CODE 4910-13-P