[Federal Register Volume 69, Number 192 (Tuesday, October 5, 2004)]
[Rules and Regulations]
[Pages 59541-59544]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-22265]



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Rules and Regulations
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Federal Register / Vol. 69, No. 192 / Tuesday, October 5, 2004 / 
Rules and Regulations

[[Page 59541]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-SW-04-AD; Amendment 39-13812; AD 2004-20-07]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

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

DATES: Effective November 9, 2004.

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: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on June 24, 2004 (69 FR 35273). That action proposed 
to require certain inspections of the yoke for a crack, fretting, or 
buffer deterioration and, if a crack is found, replacing the yoke with 
an airworthy yoke before further flight. If fretting or buffer 
deterioration are found, that action proposed further inspecting the 
hub assembly and repairing or replacing any unairworthy parts. Also, 
the AD proposed a torque inspection of the flapping bearing retaining 
nuts at specified intervals.
    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. The ASB's also 
specify 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 105 helicopters of U.S. 
registry. The FAA also estimates that this AD will:
    <bullet> 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;
    <bullet> 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;
    <bullet> Take 4 work hours to remove, inspect, and replace the yoke 
if required.
    <bullet> The average labor rate is $65 per work hour.
    <bullet> Required parts will cost about $32,675.
Based on these figures, we estimate the total cost impact of the AD on 
U.S. operators to be $3,499,125, assuming all yokes are replaced near 
the end of the first year.
    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

[[Page 59542]]

Adoption of the Amendment

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2004-20-07 Bell Helicopter Textron Canada: Amendment 39-13812. 
Docket No. 2004-SW-04-AD.

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

--------------------------------------------------------------------------------------------------------------------------------------------------------
                 Model                            Serial number (S/N)                  With main rotor hub (hub) assembly  part number 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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[GRAPHIC] [TIFF OMITTED] TR05OC04.005


    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

[[Page 59543]]

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.
[GRAPHIC] [TIFF OMITTED] TR05OC04.006


[[Page 59544]]


[GRAPHIC] [TIFF OMITTED] TR05OC04.007

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    (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.
    (d) This amendment becomes effective on November 9, 2004.

    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 September 24, 2004.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-22265 Filed 10-4-04; 8:45 am]
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