[Federal Register Volume 65, Number 178 (Wednesday, September 13, 2000)]
[Rules and Regulations]
[Pages 55175-55177]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-23208]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-29-AD; Amendment 39-11894; AD 2000-18-09]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
412, 412EP, and 412CF 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 412, 412EP, and 412CF 
helicopters. This AD requires inspecting the upper left-hand cap angle 
(cap angle) and adjacent structure for a crack and, before further 
flight, replacing any cracked cap angle and repairing any crack in the 
adjacent structure. This AD is prompted by a report of a fatigue crack 
in a tailboom attachment cap angle. The actions specified in this AD 
are intended to prevent failure of a cap angle, loss of the tailboom, 
and subsequent loss of control of the helicopter.

DATES: Effective September 28, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before November 13, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-29-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 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for BHTI 
Model 412, 412EP, and 412CF helicopters. This AD requires inspecting 
and replacing any cracked cap angle, part number (P/N) 212-030-191-001, 
and repairing any cracked adjacent structure.
    This AD is prompted by a report of a fatigue crack in a tailboom 
attachment cap angle. This condition, if not corrected, could result in 
loss of the tailboom and subsequent loss of control of the helicopter.
    The FAA has reviewed BHTI Alert Service Bulletin No. 412-00-100, 
and the temporary revision to the Maintenance Manual, BHT-412-MM, both 
dated March 24, 2000, which specify inspecting the cap angle and 
adjacent structure for a crack and contacting BHTI if a crack is found.
    We have identified an unsafe condition that is likely to exist or 
develop on other BHTI Model 412, 412EP, and 412CF helicopters of these 
same type designs. This AD is being issued to prevent failure of a cap 
angle, loss of the tailboom, and subsequent loss of control of the 
helicopter. This AD requires, within 25 hours time-in-service (TIS) and 
thereafter at intervals not to exceed 100 hours TIS, inspecting the cap 
angle, P/N 212-030-191-001, for a crack. Before further flight, if a 
crack is found, this AD requires replacing any cracked cap angle with 
an airworthy cap angle and repairing any cracked adjacent structure. 
This AD also requires reporting any crack to the Manager, Rotorcraft 
Certification Office.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability or structural integrity of the helicopter. Therefore, 
inspecting the cap angle, P/N 212-030-191-001, for a crack is required 
within 25 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 149 helicopters will be affected by this AD, 
that it will take approximately \1/2\ work hour to inspect a cap angle 
and approximately 15 work hours to replace and repair each part, and 
that the average labor rate is $60 per work hour. Required parts will 
cost approximately $279 per helicopter. Based on these figures, the 
total cost impact of the AD on U.S. operators is estimated to be 
$180,141 assuming all cap angles are 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, 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 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-29-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

[[Page 55176]]

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:

2000-18-09--Bell Helicopter Textron, Inc.: Amendment 39-11894. 
Docket No. 2000-SW-29-AD.

    Applicability: Model 412, 412EP, and 412CF helicopters with 
upper left-hand cap angle (cap angle), part number (P/N) 212-030-
191-001, 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 (b) 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: Required as indicated, unless accomplished 
previously.
    To prevent failure of a cap angle, loss of the tailboom, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 25 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 100 hours TIS, inspect the cap angle and 
adjacent structure for a crack in the area shown in figure 1. Use a 
10-power or higher magnifying glass.

    Note 2: Bell Helicopter Textron, Inc. Alert Service Bulletin 
412-00-100, dated March 24, 2000, pertains to the subject of this 
AD.

    (1) If a crack is found in the cap angle, replace it with an 
airworthy cap angle before further flight.
    (2) Repair any crack found in the adjacent structure before 
further flight.
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    (3) Report any crack found to the Manager of the Rotorcraft 
Certification Office within 10 days of the inspection. Reporting 
requirements have been approved by the Office of Management and 
Budget and assigned OMB control number 2120-0056.
    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be

[[Page 55177]]

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.

    (c) 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.
    (d) This amendment becomes effective on September 28, 2000.


Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-23208 Filed 9-12-00; 8:45 am]
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