[Federal Register Volume 69, Number 121 (Thursday, June 24, 2004)]
[Proposed Rules]
[Pages 35273-35277]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-14315]


 ========================================================================
 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. 69, No. 121 / Thursday, June 24, 2004 / 
Proposed Rules  

[[Page 35273]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-SW-04-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, 222U, and 230 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for the specified Bell Helicopter Textron Canada (BHTC) model 
helicopters. The AD would require certain inspections of the main rotor 
yoke (yoke) for a crack, fretting, or buffer deterioration. If a crack 
is found, the AD would require replacing the yoke with an airworthy 
yoke before further flight. If fretting or buffer deterioration are 
found, the AD would require further inspecting the main rotor hub 
assembly (hub assembly) and repairing or replacing any unairworthy 
parts. Also, the AD would require a torque inspection of the flapping 
bearing retaining nuts at specified intervals. This proposal is 
prompted by the discovery of a crack in a yoke. The actions specified 
by the proposed AD are intended to prevent failure of the yoke and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before August 23, 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-04-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: Charles Harrison, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5128, 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-04-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 BHTC Model 222, 222B, 
222U, and 230 helicopters. Transport Canada advises of a fatigue crack 
being found in a yoke in the area of the flapping bearing bushings.
    BHTC has issued Alert Service Bulletin (ASB) Nos. 222-03-97 for the 
Model 222 and 222B helicopters, 222U-03-68 for the Model 222U 
helicopters, and 230-03-28 for the Model 230 helicopters, all dated 
September 23, 2003. The ASB's specify a recurring visual inspection of 
the yoke for a crack, fretting, or buffer deterioration in the four (4) 
areas around the flapping bearing attachment bushings and verifying the 
torque of the main rotor flapping bearing retaining bolts/nuts. 
Transport Canada classified these service bulletins as mandatory and 
issued AD No. CF-2003-27, dated November 17, 2003, to ensure the 
continued airworthiness of these helicopters in Canada.
    These helicopter models are type certificated in Canada 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 these type designs 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:
     Initial and recurring visual inspections, using a 10X or 
higher magnifying glass, of the yoke for a crack, fretting, or buffer 
deterioration in the four areas around the flapping bearing attachment 
bushings. If a crack is found, before further flight, replace the yoke 
with an airworthy yoke. If fretting or buffer deterioration is found, 
the hub assembly must be further inspected.
     Initially and at specified intervals, assure that there is 
no movement while torquing the main rotor flapping bearing retaining 
nuts to 100 ft-lbs. While holding the bolt head, apply 100 foot-pounds 
(135Nm) of torque to the nut in the tightening direction. If 100 foot-
pounds (135Nm) of torque is reached without movement of the nut, before 
further flight, torque the bolt to 125 foot-pounds. If any nut moves 
before reaching 100 foot-pounds (135Nm) of torque, remove both flapping 
bearings from the hub assembly. Repair or replace any unairworthy part 
with an airworthy part.

[[Page 35274]]

    The FAA estimates that this proposed AD would affect 105 
helicopters of U.S. registry. The FAA also estimates that this proposed 
AD would:
     Take \1/2\ work hour to inspect the yoke every 25 hours 
time-in-service (TIS), assuming 8 inspections a year that would equal 4 
work hours per year;
     Take \1/2\ work hour to inspect the flapping bearing 
retaining bolts torque every 50 hours TIS, assuming 4 inspections a 
year that would equal 2 work hours per year;
     Take 4 work hours to remove, inspect, and replace the yoke 
if required.
     The average labor rate is $65 per work hour.
     Required parts would cost approximately $32,675.
     Based on these figures, we estimate the total cost impact 
of the proposed AD on U.S. operators to be $3,499,125, assuming all 
yokes are replaced near the end of the first year.
    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.


Sec.  39.13  [Amended]

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

Bell Helicopter Textron Canada: Docket No. 2004-SW-04-AD.

    Applicability: The following helicopter models, certificated in 
any category:

----------------------------------------------------------------------------------------------------------------
                                                 Serial number    With main rotor hub (hub) assembly part number
                    Model                            (S/N)                       (P/N), installed
----------------------------------------------------------------------------------------------------------------
(1) 222......................................       47006-47089  222-011-101-ALL or 222-012-101-ALL.
(2) 222B.....................................       47131-47156  222-011-101-ALL or 222-012-101-ALL.
(3) 222U.....................................       47501-47574  222-011-101-ALL or 222-012-101-ALL.
(4) 230......................................       23001-23038  222-012-101-ALL.
----------------------------------------------------------------------------------------------------------------

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the yoke and subsequent loss of control of 
the helicopter, accomplish the following:
    (a) Within 50 hours time-in-service (TIS) or by the next 
scheduled inspection for the hub assembly, whichever occurs first, 
and thereafter at intervals not to exceed 25 hours TIS, using a 10X 
or higher magnifying glass, visually inspect the main rotor yoke 
(yoke) for a crack, fretting or buffer deterioration in the four 
areas around the flapping bearing attachment bushings as shown in 
the following Figure 1 of this AD:
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[[Page 35275]]

[GRAPHIC] [TIFF OMITTED] TP24JN04.000


    Note 1: Bell Helicopter Textron Alert Service Bulletin (ASB) 
Nos. 222-03-97 for the Model 222 and 222B, 222U-03-68 for the Model 
222U, and 230-03-28 for the Model 230, all dated September 23, 2003, 
pertain to the subject of this AD.

    (1) If a crack is found, before further flight, replace the yoke 
with an airworthy yoke.
    (2) If fretting or buffer deterioration is found on the yoke in 
the areas shown in Figure 1 of this AD, before further flight, 
disassemble the hub assembly and further inspect the yoke with a 10X 
or higher magnifying glass in the four areas shown in Figures 2 and 
3 of this AD.
    (i) If a crack is found on any part, before further flight, 
replace the part with an airworthy part.
    (ii) If fretting or buffer deterioration is found on any part, 
before further flight, repair any unairworthy part or replace the 
part with an airworthy part.

[[Page 35276]]

[GRAPHIC] [TIFF OMITTED] TP24JN04.001


[[Page 35277]]


[GRAPHIC] [TIFF OMITTED] TP24JN04.002

BILLING CODE 4910-13-C
    (b) Within 50 hours TIS or by the next scheduled inspection for 
each hub assembly, whichever occurs first, and thereafter at 
intervals not to exceed 50 hours TIS, determine the torque of the 
four main rotor flapping bearing retaining bolts or nuts. While 
holding the bolt head, apply 100 foot-pounds (135Nm) of torque to 
the nut in the tightening direction.
    (1) If 100 foot-pounds (135Nm) of torque is reached without 
movement of the nut, before further flight, torque the nut to 125 
foot-pounds.
    (2) If any nut moves before reaching 100 foot-pounds (135Nm) of 
torque, before further flight, remove both flapping bearings from 
the hub assembly. Inspect the yoke, the bolt and nut, and the 
trunnion supports with a 10X or higher magnifying glass, for a 
crack, fretting, or buffer deterioration.
    (i) If a crack is found on any part, before further flight, 
replace the part with an airworthy part.
    (ii) If fretting or buffer deterioration is found on any part, 
before further flight, repair any unairworthy part or replace the 
part with an airworthy part.
    (c) 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 Safety Management Group, FAA, for information about 
previously approved alternative methods of compliance.

    Note 2: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2003-27, dated November 17, 2003.


    Issued in Fort Worth, Texas, on June 16, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-14315 Filed 6-23-04; 8:45 am]
BILLING CODE 4910-13-P