[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]
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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.
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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
