[Federal Register Volume 64, Number 31 (Wednesday, February 17, 1999)]
[Rules and Regulations]
[Pages 7771-7773]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-3590]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 64, No. 31 / Wednesday, February 17, 1999 /
Rules and Regulations
[[Page 7771]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-27-AD; Amendment 39-11037; AD 99-04-13]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
214ST 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. (BHTI) Model 214ST
helicopters. This action requires a reduction of the never-exceed
velocity (Vne) limitation until an inspection of the tail rotor yoke
(yoke) assembly for fatigue damage and installation of a redesigned
yoke flapping stop are accomplished. Recurring periodic and special
inspections to detect occurrences of yoke overload are also required.
This amendment is prompted by reports of inflight failures of yokes
installed on civilian and military helicopters of similar type design.
The actions specified in this AD are intended to prevent fatigue
failure of the yoke that could result in loss of the tail rotor and
subsequent loss of control of the helicopter.
DATES: Effective March 4, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 4, 1999.
Comments for inclusion in the Rules Docket must be received on or
before April 19, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-27-AD, 2601 Meacham Blvd., 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,
telephone (817) 280-3391, fax (817) 280-6466. 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: Mr. Harry Edmiston, Aerospace
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5158,
fax (817) 222-5783.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD that is
applicable to BHTI Model 214ST helicopters. This action requires,
before further flight, reviewing the historical records for any
incidents that may have imposed greater than normal bending loads on
the tail rotor yoke, installing a placard on the instrument panel with
a reduced airspeed limitation, and inserting the limitation into the
Limitations section of the Rotorcraft Flight Manual (RFM). This action
also requires, within 180 days, replacing the yoke assembly with a
zero-hours TIS airworthy yoke assembly, or one that has passed an x-ray
diffraction inspection. A frangible tail rotor flapping stop/yield
indicator, P/N 214-011-809-109, must also be installed. Further, this
AD requires a repetitive 25 hours time-in-service (TIS) inspection to
detect tail rotor flapping stop damage due to a hard landing, sudden
stoppage, or miscellaneous power on/off incidents, and an inspection
after each incident in which damage due to a hard landing, sudden
stoppage, or miscellaneous power on/off incidents may have occurred.
This amendment is prompted by reports of inflight failures of yokes
installed on civilian and military helicopters of similar type design.
The actions specified in this AD are intended to prevent fatigue
failure of the yoke that could result in loss of the tail rotor and
subsequent loss of control of the helicopter.
The FAA has reviewed Bell Helicopter Textron, Inc. Alert Service
Bulletin No. 214ST-96-75, dated August 26, 1996, which specifies an
immediate, temporary reduction in the maximum airspeed, installing a
cockpit placard for this limitation, and incorporating a temporary RFM
supplement until the yoke historical records are researched for
previous damage history; until an x-ray diffraction inspection is
performed on the yoke to detect fatigue damage; and until a frangible
tail rotor flapping stop/yield indicator, P/N 214-011-809-109, is
installed. A repetitive 25 hour TIS inspection to detect damaging tail
rotor flapping stop contact due to a hard landing, sudden stoppage, or
miscellaneous power on/off incidents has been added.
Since an unsafe condition has been identified that is likely to
exist or develop on other BHTI Model 214ST helicopters of the same type
design, this AD is being issued to prevent fatigue failure of the yoke
due to external bending forces, which could result in failure of the
yoke, loss of control of the tail rotor, and subsequent loss of control
of the helicopter. The actions are required to be accomplished in
accordance with the service bulletin 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, the actions stated in the AD are required
prior to further flight, 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 14 helicopters will be affected by this
proposed AD, that it will take approximately 9 work hours to accomplish
the inspections and installations, and that the average labor rate is
$60 per work hour. Required parts will cost approximately $21,844 for
the yoke, and $936 for the flapping stop, per helicopter. Based on
these figures, the total cost impact of the AD on U.S. operators is
estimated to be $326,480 to replace the yoke and flapping stop in the
entire fleet.
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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 No. 98-SW-27-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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
AD 99-04-13 Bell Helicopter Textron, Inc.: Amendment 39-11037.
Docket No. 98-SW-27-AD.
Applicability: Model 214ST helicopters, serial numbers 28101 and
higher, 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 (e) 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 as indicated, unless accomplished
previously.
To prevent fatigue failure of the tail rotor yoke (yoke) that
could result in loss of the tail rotor and subsequent loss of
control of the helicopter, accomplish the following:
(a) Before further flight, review the historical records of the
yoke assembly, part number (P/N) 214-011-802-105 or 214-011-802-111,
for any recorded static or dynamic incidents that could have imposed
a bending load on the yoke, but did not require yoke assembly
replacement; for example, an incident in which a damaged tail rotor
blade was replaced due to a blade strike. If such a history exists,
replace the yoke assembly with an airworthy yoke assembly.
(b) Before further flight, unless paragraph (c) of this AD has
been accomplished previously:
(1) Install a Never Exceed Velocity (Vne) red line at 145 knots
indicated airspeed (KIAS) on the pilot and copilot airspeed
indicators using red tape or paint, and a slippage indicator on the
instrument case and glass.
(2) Install a placard made of material that is not easily
erased, disfigured, or obscured on the instrument panel in clear
view of the pilot and copilot: ``Observe temporary Maximum Never
Exceed (Vne) airspeed red line (marked at 145 knots indicated
airspeed (KIAS)). Basic Vne is 15 KIAS less than that determined by
the Air Data Computer (ADC) but never less than 70 KIAS.''
(3) Insert the Bell Helicopter Textron 214ST Temporary Revision
for Airspeed Restriction, dated August 16, 1996, which is attached
to Bell Helicopter Textron Alert Service Bulletin No. 214ST-96-75,
dated August 26, 1996 (ASB) into the Limitations section of the
Model 214ST Rotorcraft Flight Manual (RFM).
(c) Within 180 calendar days after the effective date of this
AD:
(1) Remove yoke assembly, P/N 214-011-802-105 or 214-011-802-
111, and replace it with an airworthy yoke assembly, P/N 214-011-
802-105 or 214-011-802-111, with zero hours time-in-service (TIS),
or an airworthy yoke (regardless of TIS) that has passed a one-time
x-ray diffraction inspection in accordance with the ASB.
(2) Install an airworthy tail rotor flapping stop, P/N 214-011-
809-109.
(3) After the requirements of paragraphs (c)(1) and (c)(2) of
this AD are accomplished, remove the 145 KIAS redline from the pilot
and copilot airspeed indicators, remove the Vne airspeed restriction
placard, and remove the Bell Helicopter Textron 214ST Temporary
Revision for Airspeed Restriction, dated August 16, 1996, from the
RFM.
(d) After accomplishing paragraph (c) of this AD, inspect the
yoke assembly and tail rotor flapping stop in accordance with Part
III, Recurring 25 Hour Inspection and Conditional Inspection
Requirement, of the ASB:
--at intervals not to exceed 25 hours TIS; and
--before further flight after each incident in which there could
have been imposed a bending load on the yoke as referenced in
paragraph (a).
(e) 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
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compliance with this AD, if any, may be obtained from the Rotorcraft
Certification Office.
(f) 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.
(g) The actions shall be done in accordance with Bell Helicopter
Textron Alert Service Bulletin No. 214ST-96-75, dated August 26,
1996. 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, telephone (817) 280-3391, fax
(817) 280-6466. 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.
(h) This amendment becomes effective on March 4, 1999.
Issued in Fort Worth, Texas, on February 5, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-3590 Filed 2-16-99; 8:45 am]
BILLING CODE 4910-13-U
