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

[Federal Register Volume 66, Number 30 (Tuesday, February 13, 2001)]
[Rules and Regulations]
[Pages 9908-9909]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-3179]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-56-AD; Amendment 39-12104; AD 2001-03-03]
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) for 
Bell Helicopter Textron, Inc. (BHTI) Model 214B and 214B-1 helicopters. 
This action requires, within 10 hours time-in-service (TIS), 
determining the hours TIS for certain main rotor outboard strap fitting 
assemblies and creating appropriate records. This action also requires, 
if any main rotor outboard strap fitting assembly (strap fitting) is 
determined to have 2,500 or more hours TIS or the hours TIS cannot be 
determined, replacing the strap fitting with an airworthy strap fitting 
before further flight. This action also establishes a 2,500-hour 
retirement life for the strap fitting and revises the Airworthiness 
Limitations section accordingly. This amendment is prompted by fatigue 
testing that indicates a fatigue crack may occur in the strap fitting 
with resulting failure. The actions specified in this AD are intended 
to prevent failure of a strap fitting, separation of a main rotor 
blade, and subsequent loss of control of the helicopter.

DATES: Effective February 28, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before April 16, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-56-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected].

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5447, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for BHTI 
Model 214B and 214B-1 helicopters. This action requires, within 10 
hours TIS, determining the hours TIS for each strap fitting, P/N 214-
010-185-107, and creating a component history card or equivalent record 
for each strap fitting. This action also requires that if a strap 
fitting has 2,500 or more hours TIS or if the hours TIS cannot be 
determined, replacing the strap fitting with an airworthy strap fitting 
before further flight. This strap fitting is structurally identical to 
strap fitting, P/N 214-010-189-103, which currently has a retirement 
life of 2,500 hours. The strap fitting has been sold for spares since 
approximately 1982. This amendment is prompted by fatigue testing which 
indicates that a fatigue crack may occur in the strap fitting leading 
to failure of the strap fitting if it is allowed to remain in service 
in excess of 2,500 hours. The actions specified in this AD are intended 
to prevent a failure of a strap fitting, separation of a main rotor 
blade, and subsequent loss of control of the helicopter.
    The FAA has reviewed BHTI Alert Service Bulletin 214-00-62, dated 
June 2, 2000, which describes procedures for establishing a 2,500-hour 
airworthiness life pending formal revision of the 214B series 
Maintenance Manual and provides information to determine continued 
serviceability for strap fitting, P/N 214-010-185-107.
    We have identified an unsafe condition that is likely to exist or 
develop on other BHTI Model 214B and 214B-1 helicopters of the same 
type design. Therefore, this AD is being issued to require the 
following for each strap fitting, P/N 214-010-185-107:
    <bullet> Within 10 hours TIS, by referring to the helicopter 
maintenance records, create a component history card or equivalent 
record for each strap fitting and record the hours TIS and serial 
number.
    <bullet> If the hours TIS cannot be determined, replace the strap 
fitting with an airworthy strap fitting before further flight.
    <bullet> If the strap fitting has accumulated 2,500 or more hours 
TIS, replace it with an airworthy strap fitting before further flight.
    <bullet> Continue to record the subsequent hours TIS.
    <bullet> Revise the Airworthiness Limitations section of the 
maintenance manual by establishing a retirement life of 2,500 hours TIS 
for the strap fitting.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability and structural integrity of the helicopter. Therefore, 
replacing any strap fitting, 
P/N 214-010-185-107, that has 2,500 or more hours TIS or a strap 
fitting for which the hours TIS cannot be determined is required within 
10 hours TIS, 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 11 helicopters will be affected by this 
proposed AD, that it will take approximately 14 work hours to replace 
each of the 2 strap fittings, 2 work hours to create a new component 
history card, and 10 work hours annually to maintain the records, and 
that the average labor rate is $60 per

[[Page 9909]]

work hour. Required parts will cost approximately $4807 per helicopter. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $79,277 the first year assuming all strap 
fittings will be replaced.

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 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 mailed 
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. 2000-SW-56-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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, 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:

2001-03-03  Bell Helicopter Textron, Inc.: Amendment 39-12104. 
Docket No. 2000-SW-56-AD.

    Applicability: Model 214B and 214B-1 helicopters, with a main 
rotor outboard strap fitting assembly (strap fitting), part number 
(P/N) 214-010-185-107, installed, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Within 10 hours time-in-service (TIS), unless 
accomplished previously.
    To prevent failure of a strap fitting, separation of a main 
rotor blade, and subsequent loss of control of the helicopter, 
accomplish the following:

    Note 2: Bell Helicopter Textron Alert Service Bulletin 214-00-62 
dated June 2, 2000, pertains to the subject of this AD.

    (a) By referring to the helicopter maintenance records, create a 
component history card or equivalent record for each strap fitting, 
and record the hours TIS and serial number.
    (1) If the hours TIS cannot be determined, replace the strap 
fitting with an airworthy strap fitting before further flight.
    (2) If the strap fitting has accumulated 2,500 or more hours 
TIS, replace it with an airworthy strap fitting before further 
flight.
    (b) After accomplishing paragraph (a) of this AD, continue to 
record the subsequent hours TIS.
    (c) This AD revises the Airworthiness Limitations section of the 
maintenance manual by establishing a life limit of 2,500 hours TIS 
for the strap fitting, 
P/N 214-010-185-107.
    (d) 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (e) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (f) This amendment becomes effective on February 28, 2001.


    Issued in Fort Worth, Texas, on February 1, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate,, Aircraft Certification 
Service.
[FR Doc. 01-3179 Filed 2-12-01; 8:45 am]
BILLING CODE 4910-13-U

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