[Federal Register Volume 69, Number 149 (Wednesday, August 4, 2004)]
[Proposed Rules]
[Pages 47041-47043]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-17795]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-SW-07-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
407 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 Canada (Bell) Model 407 helicopters. 
This proposal would require creating a component history card or 
equivalent record for each crosstube assembly,

[[Page 47042]]

converting accumulated run-on landings to an accumulated Retirement 
Index Number (RIN) count, and establishing a maximum accumulated RIN 
for certain crosstube assemblies. This proposal is prompted by fatigue 
testing, analysis, and evaluation by the manufacturer that determined 
that run-on landings impose a high stress on landing gear or crosstubes 
and may cause cracking in the area above the skid tube saddle. The 
actions specified by this proposed AD are intended to prevent fatigue 
failure in a crosstube assembly due to excessive stress during run-on 
landings and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before October 4, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2004-SW-07-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: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

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 document 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, both before and after the closing 
date for comments, 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 proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2004-SW-07-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on Bell Model 407 
helicopters. Transport Canada advises that run-on landings impose high 
stress on landing gear crosstubes, and to prevent possible crosstube 
failure, the manufacturer has introduced the life limitation of 5,000 
RIN. Further evaluation has confirmed the possibility that an extensive 
training environment with run-on landings may impose high stress on 
crosstubes. The same condition may result from repetitive landings with 
forward travel with rotorcraft weight on the skids.
    Bell has issued Alert Service Bulletin No. 407-03-59, dated October 
15, 2003, which specifies assigning a RIN count to forward and aft 
crosstube assemblies on Model 407 helicopters. Transport Canada 
classified this alert service bulletin as mandatory and issued AD No. 
CF-2004-03, dated February 11, 2004, to ensure the continued 
airworthiness of these helicopters in Canada.
    This helicopter model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of Transport Canada reviewed all available information, and 
determined that AD action is necessary for products of this type design 
that are certificated for operation in the United States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type design registered in the 
United States. Therefore, the proposed AD would require, before further 
flight, creating a component history card or equivalent record for each 
crosstube assembly, converting accumulated run-on landings to an 
accumulated RIN count, and establishing a retirement life of 5,000 
accumulated RIN for the affected crosstube assemblies.
    The FAA estimates that 319 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4 work 
hours per helicopter to replace the forward and aft crosstube 
assemblies, and that the average labor rate is $65 per work hour. 
Required parts would cost approximately $6,670 per helicopter for both 
forward and aft low gear crosstube assemblies or $8,450 per helicopter 
for both forward and aft high gear crosstube assemblies. Based on these 
figures, the total cost impact of the proposed AD on U.S. operators is 
estimated to be $2,210,670 to replace the low gear crosstube assemblies 
on the entire fleet or $2,778,490 to replace the high-gear crosstube 
assemblies on the entire fleet and assuming the costs associated with 
creating and updating the historical component card are negligible.
    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 
economic 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.

[[Page 47043]]

Sec.  39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Bell Helicopter Textron Canada (Bell): Docket No. 2004-SW-07-AD.
    Applicability: Model 407 helicopters, with landing gear 
crosstube assemblies, part number (P/N) 407-050-101-101 and -103; P/
N 407-050-102-101 and -103; P/N 407-050-201-101 and -103; P/N 407-
050-202-101 and -103; P/N 407-704-007-119; P/N 407-722-101; P/N 407-
723-104; P/N 407-724-101; or P/N 407-725-104, installed, 
certificated in any category.

    Note 1: This AD applicability includes both Bell crosstube 
assemblies and Bell's approved production and spare alternate 
crosstube assemblies from Aeronautical Accessories Incorporated 
(AAI).

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue failure of the crosstube assembly and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Before further flight, create a component history card or 
equivalent record for each crosstube assembly.
    (b) Before further flight, determine and record the accumulated 
Retirement Index Number (RIN) for each crosstube assembly as 
follows:
    (1) For each crosstube assembly, record one (1) RIN for every 
run-on landing.
    (2) For any crosstube assembly with an unknown number of run-on 
landings, assume and record ten (10) RINs for each 100 hours TIS 
since the crosstube assembly was installed (for example, 5,000 hours 
of time-in-service equals 500 RIN).
    (c) Replace any crosstube assembly on or before reaching 5,000 
RIN.

    Note 2: Bell Helicopter Textron Alert Service Bulletin No. 407-
03-59, dated October 15, 2003, pertains to the subject of this AD.

    (d) This AD revises the Airworthiness Limitations section of the 
maintenance manual by establishing a retirement life of 5,000 RIN 
for the affected crosstube assemblies.
    (e) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Regulations and Policy Group, Rotorcraft Directorate, 
FAA, for information about previously approved alternative methods 
of compliance.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-2004-03, dated February 11, 2004.


    Issued in Fort Worth, Texas, on July 28, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-17795 Filed 8-3-04; 8:45 am]
BILLING CODE 4910-13-P