[Federal Register Volume 69, Number 230 (Wednesday, December 1, 2004)]
[Rules and Regulations]
[Pages 69810-69814]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-26425]



[[Page 69810]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-SW-12-AD; Amendment 39-13884; AD 2004-24-08]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
206A, B, L, L-1, L-3, and L-4 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Bell Helicopter Textron Canada (BHTC) model helicopters. 
This action requires an initial inspection and, at specified intervals, 
certain repetitive checks and inspections of the tail rotor blade 
(blade) for a deformation, a crack, and a bent or deformed tail rotor 
weight (weight). Also, this action requires, before further flight, 
replacing each blade with an airworthy blade if a deformation, a crack, 
or a bent or deformed weight is found. This amendment is prompted by 
three reports of skin cracks originating near the blade trailing edge 
balance weight. This condition, if not detected, could result in blade 
failure and subsequent loss of control of the helicopter.

DATES: Effective December 16, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before January 31, 2005.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2004-SW-12-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#a89185c9dbdf85c9cccbc7c5c5cdc6dcdbe8cec9c986cfc7de"><span class="__cf_email__" data-cfemail="dfe6f2beaca8f2bebbbcb0b2b2bab1abac9fb9bebef1b8b0a9">[email protected]</span></a>.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the 
specified BHTC model helicopters. This action requires an initial 
inspection and certain repetitive checks and inspections of the blade, 
at specified intervals, for a deformation, a crack, and a bent or 
deformed weight. Also, this action requires, before further flight, 
replacing each blade with an airworthy blade if a deformation, a crack, 
or a bent or deformed weight is found. This amendment is prompted by 
three reports of skin cracks originating near the blade trailing edge 
balance weight. In two reports, a loss of the weight and a strip of 
material along the trailing edge led to an imbalance and fracture of 
three of the four tail rotor gearbox attachment bolts. In one of these 
incidents the gearbox shifted resulting in failure of the drive shaft 
and loss of yaw control. This condition, if not detected, could result 
in blade failure and subsequent loss of control of the helicopter.
    BHTC has issued Alert Service Bulletin No. 206-04-100 for Model 
206A and B and No. 206L-04-127 for Model 206L series helicopters, both 
Revision B, both dated May 28, 2004. These service bulletins specify 
checking and inspecting the blades for a deformation, a crack, and a 
bent or deformed weight and a one-time inspection by Rotor Blades Inc. 
in Louisiana, USA, and if the blades pass the one-time inspection, 
adding a ``V'' at the end of the serial number. The service bulletins 
also specify replacing any blade with a deformation, a crack, or bent 
or deformed weight.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on these helicopter models. 
Transport Canada advises of three reports of skin cracks originating 
near the blade trailing edge balance weight. Two of the occurrences 
caused a loss of the weight and a strip of material along the trailing 
edge leading to an imbalance, which caused the fracture of three of the 
four tail rotor gearbox attachments. One of these occurrences resulted 
in the gearbox shifting that caused failure of the drive shaft and 
resulting loss of yaw control. Transport Canada classified the alert 
service bulletins as mandatory and issued AD No. CF-2004-05R1, dated 
June 28, 2004, to ensure the continued airworthiness of these 
helicopters in Canada.
    These helicopter models are manufactured in Canada and are 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 these type 
designs that are certificated for operation in the United States.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type designs registered in the United States. 
Therefore, the FAA is issuing this AD to detect a blade with a 
deformation, a crack, or a bent or deformed weight and to prevent blade 
failure and subsequent loss of control of the helicopter. This AD 
requires the following for the specified BHTC helicopters with certain 
blade part numbers and serial numbers:
    <bullet> Before further flight, unless accomplished previously, and 
before installing any blade with an affected part number and serial 
number, cleaning the blade. Then, using a 10X or higher magnifying 
glass, inspecting both sides of each blade for a deformation, a crack, 
and a bent or deformed weight.
    <bullet> Thereafter, cleaning both sides of each blade and using a 
10X or higher magnifying glass, inspecting for a deformation, a crack, 
and a bent or deformed weight as follows:
    [cir] At intervals not to exceed 12 hours time-in-service (TIS), or
    [cir] At intervals not to exceed 24 hours TIS and checking both 
sides of each blade for a deformation, a crack, and a bent or deformed 
weight at intervals not to exceed 3 hours TIS between inspections. An 
owner/operator (pilot) may perform the 3-hour TIS check for deformed or 
cracked blades and for bent or deformed weights. Pilots may perform 
these checks because they require no tools, can be done by observation, 
and can be done equally well by a pilot or a mechanic. However, the 
pilot must enter compliance with these requirements into the helicopter 
maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v).
    <bullet> Before further flight, replacing each blade with an 
airworthy blade if you find a deformation, a crack, or a bent or 
deformed weight.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability and structural integrity of the helicopter. Therefore, 
inspecting the blade, for a deformation, a crack, and a bent or 
deformed weight is required before further flight and at short 
specified time intervals, 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 this AD will:
    <bullet> Affect 2194 helicopters.

[[Page 69811]]

    <bullet> Take about \1/4\ work hour for a blade check or inspection 
and 3 work hours to replace one blade at an average labor rate of $65 
per work hour.
    <bullet> Required parts will cost about $5,848 per helicopter. (The 
service bulletin states that warranty credit will be given based on 
hour usage on the blade with remaining life hours and other 
restrictions.) Based on these figures, the total estimated cost impact 
of the AD on U.S. operators is $21,315,807, assuming 226 checks or 
inspections and replacing one blade on each helicopter in the fleet.

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 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. 2004-SW-12-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 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 
economic 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

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:

2004-24-08 Bell Helicopter Textron Canada: Amendment 39-13884. 
Docket No. 2004-SW-12-AD.

    Applicability: Model 206A, B, L, L-1, L-3, and L-4 helicopters, 
with a tail rotor blade (blade) with the following part number (P/N) 
and serial number (S/N) installed, certificated in any category.

----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
 Model 206A & B; Blade, P/N 206-016-    Model 206A, B, L, L-1, L-3, & L-4, Blade, P/N 206-016-201-131, S/N with
 201-133, S/N with prefix ``CS'' and                       prefix ``CS'' and no ``V'' suffix
           no ``V'' suffix
-------------------------------------
1381 through 1442                     7000 through 7018                     10174 through 10218.
1492 through 1517                     7020 through 7043                     10220.
1520 through 1542                     7045 through 7050                     10232.
1550                                  7052 through 7132                     10235.
1556                                  7134 through 7246                     10237 through 10241.
1560                                  7248 through 7270                     10244.
1562                                  7272 through 7277                     10245.
1564 through 1567                     7279 through 7339                     10248.
1569 through 1606                     7342 through 7368                     10250 through 10264.
1609                                  7784                                  10266 through 10268.
1611                                  7786                                  10270 through 10274.
1612                                  7788                                  10276 through 10278.
1614 through 1631                     7790 through 7796                     10280 through 10282.
1633 through 1675                     7798 through 7819                     10284 through 10292.
1677                                  7821 through 7833                     10296.
1678                                  7835 through 7839                     10300 through 10330.
1680 through 1682                     7841 through 8001                     10332.
1684 through 1787                     8003 through 8026                     10333.
1789 through 1803                     8029 through 8061                     10335 through 10347.
1810 through 1812                     8064 through 8117                     10349.
1814                                  8119                                  10351 through 10359.
1816                                  8121 through 8139                     10363 through 10365.


[[Page 69812]]


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----------------------------------------------------------------------------------------------------------------
 Model 206A & B; Blade, P/N 206-016-    Model 206A, B, L, L-1, L-3, & L-4, Blade, P/N 206-016-201-131, S/N with
 201-133, S/N with prefix ``CS'' and                       prefix ``CS'' and no ``V'' suffix
           no ``V'' suffix
-------------------------------------
1820                                  8142 through 8176                     10367.
1823 through 1831                     8178 through 8262                     10373.
1834 through 1836                     8264 through 8294                     10374.
1838                                  8298 through 8368                     10377 through 10385.
1840 through 1844                     8370 through 8375                     10387 through 10408.
1846                                  8378 through 8416                     10410.
1848 through 1882                     8419                                  10414 through 10417.
1884 through 1887                     8421                                  10419 through 10427.
1889 through 1893                     8425 through 8428                     10430.
1896 through 1898                     8430 through 8438                     10432.
1900                                  8440                                  10437.
1904                                  8441                                  10438.
1909 through 1912                     8443                                  10442 through 10445.
1915                                  8445 through 8447                     10458 through 10466.
1916                                  8449 through 8606                     10469.
1919 through 1921                     8608 through 8622                     10470.
1924                                  8624 through 8626                     10474.
1928 through 1931                     8628 through 8632                     10476 through 10478.
1933                                  8635 through 8653                     10480 through 10487.
1934 through 1939                     8655 through 8686                     10489 through 10491.
1943                                  8690                                  10493 through 10495.
1945                                  8692 through 8700                     10497 through 10503.
1947                                  8703 through 8715                     10505 through 10588.
1948                                  8717 through 8722                     10591 through 10606.
1952 through 1957                     8724 through 8742                     10608 through 10610.
1960                                  8745 through 8828                     10612 through 10620.
1962 through 1965                     8830 through 8835                     10623.
                                      8838 through 8840                     10624.
                                      8842 through 8881                     10631 through 10655.
                                      8883 through 9032                     10657 through 10669.
                                      9034 through 9139                     10672.
                                      9141 through 9198                     10673.
                                      9200                                  10676 through 10678.
                                      9202 through 9302                     10680 through 10683.
                                      9304 through 9339                     10685.
                                      9341 through 9371                     10687.
                                      9373 through 9411                     10689 through 10702.
                                      9413                                  10707.
                                      9415 through 9417                     10712.
                                      9419 through 9496                     10715.
                                      9498 through 9585                     10730.
                                      9587 through 9594                     10732 through 10734.
                                      9596 through 9618                     10736.
                                      9621 through 9629                     10738.
                                      9632 through 9642                     10739.
                                      9645 through 9651                     10746.
                                      9653 through 9673                     10750.
                                      9675 through 9707                     10756.
                                      9709 through 9724                     10760.
                                      9727 through 9731                     10761.
                                      9733 through 9735                     10765.
                                      9737 through 9739                     10770.
                                      9741 through 9748                     10774 through 10776.
                                      9751 through 9785                     10778.
                                      9787                                  10781.
                                      9788                                  10783 through 10785.
                                      9790 through 9792                     10792.
                                      9795 through 9847                     10794.
                                      9849 through 9928                     10798.
                                      9930 through 9937                     10799.
                                      9940 through 9942                     10806 through 10808.
                                      9944 through 9952                     10811.
                                      9955 through 9972                     10814 through 10822.
                                      9974 through 9989                     10824.
                                      9991 through 9995                     10825.
                                      9997 through 10004                    10829.
                                      10006 through 10009                   10831.
                                      10011                                 10917.


[[Page 69813]]


----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
 Model 206A & B; Blade, P/N 206-016-    Model 206A, B, L, L-1, L-3, & L-4, Blade, P/N 206-016-201-131, S/N with
 201-133, S/N with prefix ``CS'' and                       prefix ``CS'' and no ``V'' suffix
           no ``V'' suffix
-------------------------------------
                                      10013 through 10018                   10923.
                                      10021 through 10030                   10931.
                                      10034                                 10936.
                                      10036 through 10057                   10937.
                                      10061 through 10082                   10940.
                                      10090 through 10092                   10943.
                                      10094 through 10100                   10945.
                                      10116                                 10947.
                                      10119                                 10948.
                                      10121                                 10964.
                                      10123 through 10134                   10965.
                                      10136 through 10140                   10973.
                                      10142 through 10144                   10982.
                                      10146 through 10172                   10985.
                                      ....................................  10986.
----------------------------------------------------------------------------------------------------------------

    Compliance: Required as indicated.
    To prevent blade failure and subsequent loss of control of the 
helicopter, do the following:
    (a) Before further flight, unless accomplished previously, and 
before installing any blade with a P/N and S/N listed in the 
applicability section of this AD, clean the blade. Using a 10X or 
higher magnifying glass, inspect both sides of each blade for a 
deformation, a crack, and a bent or deformed weight in the area shown 
in Figure 1 of this AD.

    Note 1: Paint irregularities on the blade may indicate a crack.

    [GRAPHIC] [TIFF OMITTED] TR01DE04.000
    

[[Page 69814]]


    (b) After doing paragraph (a) of this AD, at the following 
intervals, clean both sides of each blade and do either paragraph (1) 
or (2) as follows:
    (1) At intervals not to exceed 12 hours time-in-service (TIS), 
using a 10X or higher magnifying glass, inspect both sides of each 
blade for a deformation, a crack, and a bent or deformed weight in the 
area shown in Figure 1 of this AD, or
    (2) Inspect and check both sides of each blade for a deformation, a 
crack, and a bent or deformed weight in the area shown in Figure 1 of 
this AD as follows:
    (i) Using a 10X or higher magnifying glass, inspect at intervals 
not to exceed 24 hours TIS, and
    (ii) Check at intervals not to exceed 3 hours TIS between the 
inspections required by paragraph (b)(2)(i) of this AD. An owner/
operator (pilot), holding at least a private pilot certificate, may 
perform this visual check and must enter compliance with this paragraph 
into the helicopter maintenance records by following 14 CFR sections 
43.11 and 91.417(a)(2)(v).
    (c) Before further flight, replace any blade that has a 
deformation, a crack, or a bent or deformed weight with an airworthy 
blade.

    Note 2: Bell Helicopter Textron Alert Service Bulletin No. 206-
04-100 for Model 206A and B and No. 206L-04-127 for Model 206L 
series, both Revision B, both dated May 28, 2004, pertain to the 
subject of this AD.

    (d) 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, Rotorcraft Directorate, FAA, for 
information about previously approved alternative methods of 
compliance.
    (e) This amendment becomes effective on December 16, 2004.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-2004-05R1, dated June 28, 2004.


    Issued in Fort Worth, Texas, on November 22, 2004.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-26425 Filed 11-30-04; 8:45 am]
BILLING CODE 4910-13-P


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