[Federal Register Volume 64, Number 16 (Tuesday, January 26, 1999)]
[Rules and Regulations]
[Pages 3821-3823]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-1350]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-28-AD; Amendment 39-11009; AD 99-02-17]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
214B and 214B-1 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 214B and
214B-1 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 February 10, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 10, 1999.
Comments for inclusion in the Rules Docket must be received on or
before March 29, 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-28-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.
[[Page 3822]]
FOR FURTHER INFORMATION CONTACT: 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 214B and 214B-1 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 time-in-service (TIS) airworthy yoke assembly, or one that
has passed an x-ray diffraction inspection. A frangible tail rotor
flapping stop/yield indicator, part number (P/N) 214-011-809-109, must
also be installed. Further, this AD requires a repetitive 25 hours 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. 214-96-57, 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 214B and 214B-1 helicopters of the
same type designs, this AD is being issued to prevent fatigue failure
of the yoke that could result in 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 10 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 $233,200 to replace the yoke and flapping stop in the
entire 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
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-28-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.
[[Page 3823]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
AD 99-02-17 Bell Helicopter Textron, Inc.: Amendment 39-11009.
Docket No. 98-SW-28-AD.
Applicability: Model 214B and 214B-1 helicopters, serial numbers
28001 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 replacing the yoke
assembly; 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 130 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 with the following words:
``Observe temporary Maximum Never Exceed (Vne) airspeed red line
(marked at 130 knots indicated airspeed (KIAS)). Vne is the greater
of 10 KIAS less than the value presented on the airspeed limits
placard or 68 KIAS for each ambient condition.''
(3) Insert the applicable Bell Helicopter Textron 214B or 214B-1
Temporary Revision for Airspeed Restriction, dated August 16, 1996,
which is attached to Bell Helicopter Textron, Inc. Alert Service
Bulletin No. 214-96-57, dated August 26, 1996 (ASB), into the
Limitations section of the applicable Model 214B or 214B-1
Rotorcraft Flight Manual (RFM).
(c) Within 180 calendar days after the effective date of this
AD:
(1) Remove the yoke assembly, P/N 214-011-802-105 or 214-011-
802-111, and replace it with an airworthy yoke assembly 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 130 KIAS redline from the pilot
and copilot airspeed indicators, remove the Vne airspeed restriction
placard, and remove the Bell Helicopter Textron 214B or 214B-1
Temporary Revision for Airspeed Restriction, dated August 16, 1996,
from the RFM.
(d) After accomplishing paragraph (c) of this AD, thereafter,
inspect the yoke assembly and tail rotor flapping stop at intervals
not to exceed 25 hours TIS in accordance with Part III, Recurring 25
Hour Special Inspection and Conditional Inspection Requirement, of
the ASB.
(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 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 recurring 25 hours TIS inspection shall be done in
accordance with Bell Helicopter Textron, Inc. Alert Service Bulletin
No. 214-96-57, 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 February 10, 1999.
Issued in Fort Worth, Texas, on January 13, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-1350 Filed 1-25-99; 8:45 am]
BILLING CODE 4910-13-U
