[Federal Register Volume 62, Number 97 (Tuesday, May 20, 1997)]
[Proposed Rules]
[Pages 27554-27556]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-13083]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-SW-28-AD]
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B,
47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1,
47J, 47J-2, 47J-2A, and 47K Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY:This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Bell Helicopter Textron, Inc.
(BHTI) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-
3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A,
47H-1, 47J, 47J-2, 47J-2A, and 47K helicopters. This proposal would
require installing a safety washer kit designed to preclude separation
of the stabilizer bar damper link (damper link) if the damper link rod
end bushing (bushing) loosens and exits the damper link rod end. This
proposal is prompted by two reported incidences in which the bushings
loosened and exited the damper link rod ends, allowing the damper link
to slide over the retention bolt and separate from the stabilizer bar
(in the first incident), and from the hydraulic damper (in the second
incident). The actions specified by the proposed AD are intended to
prevent failure of the stabilizer bar damper link assembly, which can
result in degraded control response and subsequent loss of control of
the helicopter.
DATES: Comments must be received by July 21,1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 96-SW-28-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137. Comments may be inspected at this location between 9:00
a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.
The service information referenced in the proposed rule 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 Blvd., Room 663, Fort Worth,
Texas.
FOR FURTHER INFORMATION CONTACT: Mr. Jurgen E. Priester, Aerospace
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5159,
fax (817) 222-5960.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact
[[Page 27555]]
concerned with the substance of this proposal will be filed in the
Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 96-SW-28-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Office of the Assistant Chief Counsel, Attention: Rules
Docket No. 96-SW-28-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
Discussion
This document proposes the adoption of a new AD that is applicable
to BHTI Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1,
47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5,
47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K helicopters. This proposal
would require installing a safety washer kit designed to preclude
separation of the damper link if the bushing loosens and exits the
damper link rod end. This proposal is prompted by two reported
incidences in which the bushings loosened and exited the damper link
rod ends, allowing the damper link to slide over the retention bolt and
separate from the stabilizer bar (in the first incident), and from the
hydraulic damper (in the second incident). In the first incident, an
inspection revealed that the rod end bearing had not been lubricated
for an extended period of time prior to failure. In the second
incident, a pilot safely landed the aircraft after reporting degraded
control response. A post-flight inspection revealed that one damper
link had separated from the hydraulic damper. A later inspection
indicated that the bushing had not been properly roll-staked by the
damper manufacturer. Therefore, one of the occurrences is attributed to
a quality control problem with the damper link manufacturer. This
condition, if not corrected, could result in failure of the stabilizer
bar damper link assembly, which can result in degraded control response
and subsequent loss of control of the helicopter.
The FAA has reviewed BHTI Alert Service Bulletin (ASB) No. 47-96-
22, dated August 16, 1996, which describes procedures for removing and
marking the stabilizer and damper link assemblies, installing a safety
washer kit, part number (P/N) CA-047-96-022-1, applying a corrosion
preventive compound, and reinstalling the stabilizer bar damper link
assemblies. The ASB states that these actions are to be accomplished at
the next 100-hour inspection, or no later than December 31, 1996. The
FAA has determined that the compliance time should be within the next
100 hours time-in-service (TIS) or no later than 120 calendar days
after the effective date of the AD, whichever occurs first.
Since an unsafe condition has been identified that is likely to
exist or develop on other BHTI Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-
2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-
4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K
helicopters of the same type design, the proposed AD would require,
within the next 100 hours TIS or within the next 120 calendar days
after the effective date of the proposed AD, whichever occurs first,
removing and marking the stabilizer and damper link assemblies,
installing a safety washer kit, P/N CA-047-96-022-1, applying a
corrosion preventive compound, and reinstalling the stabilizer and
damper link assemblies. The actions would be required to be
accomplished in accordance with the service bulletin described
previously.
The FAA estimates that 1,868 helicopters of U.S. registry would be
affected by this proposed AD, that it would take 1 work hour per
helicopter to accomplish the proposed actions, and that the average
labor rate is $60 per work hour. Required parts would cost
approximately $188 per helicopter. Based on these figures, the total
cost impact of the proposed AD on U.S. operators is estimated to be
$463,264.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) Is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 adding a new airworthiness directive
to read as follows:
Bell Helicopter Textron, Inc.: Docket No. 96-SW-28-AD.
Applicability: Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A,
47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-
4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K 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
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 use the authority
provided in paragraph (b) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required within the next 100 hours time-in-service
or within the next 120 calendar days after the effective date of
this AD, whichever occurs first, unless accomplished previously.
To prevent failure of the stabilizer bar damper link assembly,
which can result in degraded control response and subsequent loss of
control of the helicopter, accomplish the following:
(a) Remove the stabilizer bar damper link assemblies from the
helicopter, install a
[[Page 27556]]
safety washer kit, part number (P/N) CA-047-96-022-1, and reinstall
the stabilizer bar damper link assemblies onto the helicopter in
accordance with the Accomplishment Instructions contained in Bell
Helicopter Textron, Inc. Alert Service Bulletin No. 47-96-22, dated
August 16, 1996.
(b) 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, Rotorcraft Certification Office,
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, Rotorcraft Certification
Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Certification Office.
(c) 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.
Issued in Fort Worth, Texas, on May 9, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-13083 Filed 5-19-97; 8:45 am]
BILLING CODE 4910-13-U
