[Federal Register Volume 65, Number 221 (Wednesday, November 15, 2000)]
[Proposed Rules]
[Pages 68953-68955]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-29211]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / 
Proposed Rules  

[[Page 68953]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-60-AD]


Airworthiness Directives; Bell Helicopter Textron, Inc., Model 
412 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Bell Helicopter Textron, Inc. (BHTI) Model 412 helicopters. 
The AD would require, within 25 hours time-in-service (TIS), reviewing 
the aircraft maintenance records and determining the number of landings 
for the high landing gear aft crosstube assembly (crosstube assembly); 
inspecting the crosstube assembly for damage; and replacing any 
unairworthy crosstube assembly. Additionally, the AD would require 
creating a component history card or equivalent record, and 
establishing a retirement life for each crosstube assembly. This AD 
would also require vibro-etching a part number (P/N) and serial number 
(S/N) on certain cross tube assemblies. This proposal is prompted by 
reported field failures of crosstube assemblies. The actions specified 
by the proposed AD are intended to detect damage that could lead to a 
fatigue crack in the crosstube assembly, failure of the crosstube 
assembly, and subsequent loss of control of the helicopter during 
landing.

DATES: Comments must be received on or before January 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-60-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]. 
Comments may be inspected at the Office of the Regional Counsel, 
between 9 a.m. and 3 p.m., Monday through Friday, except Federal 
holidays.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments will 
be considered before taking action on the proposed rule. The proposals 
contained in this action may be changed in light of the comments 
received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available in the Rules Docket for 
examination by interested persons. A report summarizing each FAA-public 
contact concerned with the substance of this proposal will be filed in 
the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this action must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2000-SW-60-AD.'' The postcard will be date 
stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-60-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    This document proposes adopting a new AD for BHTI Model 412 
helicopters. This proposal would require the following within 25 hours 
TIS:
     Reviewing the aircraft maintenance records and determining 
the number of landings for the crosstube assembly;
     Inspecting the crosstube assembly for damage and replacing 
any unairworthy crosstube assembly;
     Vibro-etching a P/N on certain crosstube assemblies;
     Vibro-etching a S/N on the crosstube assemblies;
     Creating a component history card or equivalent record for 
the crosstube assembly; and
     Revising the Airworthiness Limitations section of the 
maintenance manual by establishing a retirement life of 10,000 landings 
for crosstube assemblies, P/N 412-050-010-101 and 412-050-011-107 FM, 
and a retirement life of 20,000 landings for crosstube assemblies, P/N 
412-050-045-107.
    This proposal is prompted by reports of field failures of crosstube 
assemblies. Analysis of the failures indicates that a landing life 
limit must be assigned to the crosstube assembly. The actions specified 
by the proposed AD are intended to detect damage that could lead to a 
fatigue crack in the crosstube assembly, failure of the crosstube 
assembly, and subsequent loss of control of the helicopter during 
landing.
    The FAA has reviewed BHTI Service Bulletin No. 412-99-97, dated 
January 8, 1999 (ASB), which describes procedures for verifying that 
the affected crosstube assemblies meet inspection criteria, assigning a 
retirement life on the affected crosstube assemblies; vibro-etching a 
P/N on those crosstube assemblies not displaying a visible P/N; vibro-
etching a S/N on the affected crosstube assemblies, and providing 
information for calculating the number of landings.
    We have identified an unsafe condition that is likely to exist or 
develop on other BHTI Model 412 helicopters of the same type design. 
The proposed AD would require, within 25 hours TIS, for affected 
crosstube assemblies, reviewing the aircraft maintenance records and 
determining the number of landings for the crosstube assembly; 
inspecting the crosstube assembly; replacing any unairworthy crosstube 
assembly with an airworthy crosstube assembly; vibro-etching the 
S/N on the crosstube assembly; creating

[[Page 68954]]

a component history card or equivalent record; and establishing a 
retirement life. The AD would also require, on certain crosstube 
assemblies, vibro-etching a P/N.
    The FAA estimates that 138 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 5 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $6,044 for crosstube assembly, P/N 412-050-010-101, and 
$11,415 for crosstube assembly, P/N 412-050-045-107. BHTI states in the 
ASB that customers with affected crosstube assemblies are eligible for 
a special rebate credit ranging from 25 percent of the replacement cost 
to 100 percent depending on the age of the crosstube assembly. Based on 
these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $875,472 to replace all crosstube 
assemblies with crosstube assembly, P/N 412-050-010-101, or $1,616,670 
to replace all crosstube assemblies with crosstube assembly, 
P/N 412-050-045-107. The total costs would be $41,400 for labor if all 
of the crosstube assemblies were replaced with 100 percent parts 
credit.
    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Bell Helicopter TEXTRON, Inc.: Docket No. 2000-SW-60-AD.

    Applicability: Model 412 helicopters with high landing gear aft 
crosstube assembly (crosstube assembly), part number (P/N) 412-050-
010-101, 412-050-011-107 FM, or 412-050-045-107, 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 (e) 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.

    Note 2: Bell Helicopter Textron, Inc. Alert Service Bulletin 
412-99-97, dated January 8, 1999, pertains to the subject of this 
AD.

    To prevent a fatigue crack in the crosstube assembly, failure of 
the crosstube assembly, and subsequent loss of control of the 
helicopter during landing, accomplish the following:
    (a) Within 25 hours time-in-service (TIS) and thereafter before 
installing a replacement crosstube assembly:
    (1) Review the aircraft maintenance records and determine the 
number of landings for the crosstube assembly. Operators who do not 
have landing records may determine the number of landings by 
multiplying the hours TIS of the crosstube assembly by a factor of 
4. If the number of hours TIS of the crosstube assembly is unknown, 
within 30 days, remove the crosstube assembly from service and 
replace it with an airworthy crosstube assembly.
    (2) Inspect the crosstube assembly for damage. If damage exceeds 
the maximum allowable damage limits and repair criteria, as 
specified in the applicable maintenance manual, before further 
flight, replace it with an airworthy crosstube assembly.
    (3) Vibro-etch the P/N on the crosstube assembly adjacent to the 
skid tube saddle in accordance with Figure 1 for any crosstube 
assembly not displaying a visible P/N. Identify the crosstube 
assembly as P/N 412-050-011-107 FM.
    (4) Vibro-etch a serial number (S/N) on the crosstube assembly 
below the P/N in accordance with Figure 1. The S/N must be unique 
for each crosstube assembly.

[[Page 68955]]

[GRAPHIC] [TIFF OMITTED] TP15NO00.000

    (5) Create a component history card or equivalent record for 
each crosstube assembly and enter the P/N, S/N, and the accumulated 
number of landings derived in accordance with paragraph (1).
    (6) Begin tracking the number of landings for each crosstube 
assembly on the component history card or equivalent record.
    (b) For a crosstube assembly, P/N 412-050-010-101 or 412-050-
011-107 FM, on or before accumulating 10,000 landings or within 25 
hours TIS after the effective date of this AD, whichever occurs 
later, replace the crosstube assembly with an airworthy crosstube 
assembly.
    (c) For a crosstube assembly, P/N 412-050-045-107, on or before 
accumulating 20,000 landings or within 25 hours TIS after the 
effective date of this AD, whichever occurs later, replace the 
crosstube assembly with an airworthy crosstube assembly.
    (d) This AD revises the Airworthiness Limitations section of the 
Maintenance Manual by establishing a life limit of 10,000 landings 
for the crosstube assembly, P/N 412-050-010-101 and 412-050-011-107 
FM, and 20,000 landings for the crosstube assembly, P/N 412-050-045-
107.
    (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 3: 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 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.

    Issued in Fort Worth, Texas, on November 8, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-29211 Filed 11-14-00; 8:45 am]
BILLING CODE 4910-13-P