Airworthiness Directives; Bell Helicopter Textron, Inc. Model 214B and 214B-1 Helicopters

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]

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