[Federal Register Volume 75, Number 112 (Friday, June 11, 2010)]
[Rules and Regulations]
[Pages 33159-33162]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-11071]



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Federal Register / Vol. 75, No. 112 / Friday, June 11, 2010 / Rules 
and Regulations

[[Page 33159]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0071; Directorate Identifier 2006-SW-27-AD; 
Amendment 39-16291; AD 2010-10-12]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, 222U, 230, and 430 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for the specified Bell Helicopter Textron Canada (BHTC) 
helicopters, that currently requires certain checks and inspections of 
the tail rotor blades. If a crack is found, the existing AD requires 
replacing the tail rotor blade (blade) with an airworthy blade before 
further flight. This amendment requires the same checks and inspections 
of the blades until they are required to be replaced and removes 
certain serial numbered and specifically coded blades from the 
applicability of the AD. This amendment is prompted by the approved 
rework of certain blades and two newly redesigned blades, which, if 
installed, constitute terminating action for the inspection 
requirements. The actions specified by this AD are intended to detect a 
crack in a blade, and to prevent loss of a blade and subsequent loss of 
control of the helicopter.

DATES: Effective July 16, 2010.

ADDRESSES: You may get the service information identified in this AD 
from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101, 
telephone (817) 280-3391, fax (817) 280-6466, or at http://www.bellcustomer.com/files/.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://www.regulations.gov, or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Sharon 
Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, 
Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 
76137, telephone (817) 222-5122, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On February 10, 2005, we issued AD 2005-04-
09, Amendment 39-13981 (70 FR 8021, February 17, 2005), that superseded 
AD 2004-26-11, Amendment 39-13923 (70 FR 7, January 3, 2005), to 
require certain checks and inspections of the blades. Both AD 2004-26-
11 and 2005-04-09 also require replacing any cracked blade before 
further flight. AD 2004-26-11 was prompted by reports of cracked blades 
and required certain checks, inspections, and replacements, if 
necessary. AD 2005-04-09 required the same checks and inspections as AD 
2004-26-11 but also added two serial numbers to the applicability and 
corrected some typographical errors.
    Since issuing AD 2005-04-09, the manufacturer has introduced a 
rework procedure for the affected blades and two newly redesigned 
blades, which, if installed, constitute terminating action for the 
inspection requirements. Therefore, a proposal to amend 14 CFR part 39 
by superseding AD 2005-04-09 for the specified BHTC model helicopters 
was published as a Notice of proposed rulemaking (NPRM) in the Federal 
Register on July 28, 2008 (73 FR 43648, July 28, 2008). That NPRM 
proposed the same checks, inspections, and replacements of the blades. 
The NPRM also proposed to remove certain serial numbered and 
specifically coded blades from the applicability of the AD. The NPRM 
was prompted by the approved rework of certain blades and two newly 
redesigned blades, which, if installed, constitutes terminating action 
for the inspection requirements.
    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on the specified BHTC model 
helicopters. Transport Canada advises of the discovery of cracked 
blades during scheduled inspections on three occasions. Two cracks 
originated from the outboard feathering bearing bore underneath the 
flanged sleeves. The third crack started from the inboard feathering 
bearing bore. Investigation found that the cracks originated from 
either a machining burr or a corrosion site in the bearing bore 
underneath the flanged sleeves.
    BHTC has issued Alert Service Bulletin (ASB) No. 222-04-100, 
Revision B, for Model 222 and 222B helicopters; ASB No. 222U-04-71, 
Revision B, for Model 222U helicopters; ASB No. 230-04-31, Revision B, 
for Model 230 helicopters; and ASB No. 430-04-31, Revision C, for Model 
430 helicopters, all dated March 31, 2008. The ASBs specify a visual 
inspection of the blade root end around the feathering bearings for a 
crack, not later than at the next scheduled inspection, and thereafter 
at every 3 flight hours maximum. Further, they describe a visual 
inspection for a crack, to include removing the blade from the 
helicopter if a crack is found in the paint, within the next 50 flight 
hours, and thereafter at every 50 flight hours. In addition, the ASBs 
state that, on or before December 31, 2008, each blade should be 
reworked by Rotor Blades, Inc., or exchanged if the blade has less than 
4,000 hours TIS or if the blade has 4,000 or more hours TIS, the blade 
should continue to be repetitively inspected or a replacement blade 
should be ordered. Transport Canada classified these service bulletins 
as mandatory and issued AD CF-2004-21R3, dated April 23, 2008, to 
ensure the continued airworthiness of these helicopters in Canada.
    This AD differs from the ASB in that it requires, on or before 90 
days after the effective date of the AD, replacing all affected blades 
with airworthy blades that are not subject to the inspection 
requirements, without differentiating between blades based on hours 
TIS. Additionally, this AD does not require operators to send their 
blades to Rotor Blades, Inc. for rework.
    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

[[Page 33160]]

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. However, we have inserted the Joint 
Aircraft System/Component Code into this AD for informational purposes. 
We have determined that this change will neither increase the economic 
burden on any operator nor increase the scope of this AD.
    We estimate that this AD will affect 156 helicopters of U.S. 
registry, and the required actions will take:
    <bullet> About 0.25 work hour for a pilot check, and 2 work hours 
for a maintenance inspection, at an average labor rate of $80 per work 
hour, and
    <bullet> About 6 work hours to remove and replace the blade. 
Required parts will cost about $13,410 per blade, assuming one blade 
per helicopter is replaced each year. Based on these figures, we 
estimate the cost of this AD on U.S. operators is $3,090,360, assuming 
each helicopter requires 200 pilot checks and 12 maintenance 
inspections prior to replacing a blade on or before the compliance date 
for all affected helicopters.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the AD docket to examine the economic evaluation.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

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 removing Amendment 39-13981 (70 FR 8021, 
February 17, 2005), and by adding a new airworthiness directive (AD), 
Amendment 39-16291, to read as follows:

2010-10-12 Bell Helicopter Textron Canada: Amendment 39-16291. 
Docket No. FAA-2008-0071; Directorate Identifier 2006-SW-27-AD. 
Supersedes AD 2005-04-09, Amendment 39-13981, Docket No. FAA-2005-
20107.

    Applicability: The following helicopter models, with a listed 
helicopter serial number (S/N) and a listed part-numbered tail rotor 
blade (blade) installed, that does not have an excepted S/N or code, 
certificated in any category.

----------------------------------------------------------------------------------------------------------------
            Helicopter model                     Helicopter S/N                   Blade Part No. (P/N)
----------------------------------------------------------------------------------------------------------------
222.....................................  47006 through 47089........  222-016-001-123, -123M, -127, [dash]127M,
                                                                        -131, -135, -139M, -141M, except those P/
                                                                        Ns with S/Ns listed in Exceptions 1 and
                                                                        2 or the ``R'' code described in
                                                                        Exception 3.
222B....................................  47131 through 47156........  222-016-001-123, -123M, -127, [dash]127M,
                                                                        -131, -135, -139M, -141M, except those P/
                                                                        Ns with S/Ns listed in Exceptions 1 and
                                                                        2 or the ``R'' code described in
                                                                        Exception 3.
222U....................................  47501 through 47574........  222-016-001-123, -123M, -131, -139M,
                                                                        except those P/Ns with a S/N listed in
                                                                        Exception 2 or the ``R'' code described
                                                                        in Exception 3.
230.....................................  23001 through 23038........  222-016-001-123, -123M, -131, -139M,
                                                                        except those P/Ns with a S/N listed in
                                                                        Exception 2 or the ``R'' code described
                                                                        in Exception 3.
430.....................................  49001 through 49107........  222-016-001-123, -123M, -131, -139M,
                                                                        except those P/Ns with a S/N listed in
                                                                        Exception 2 or the ``R'' code described
                                                                        in Exception 3.
----------------------------------------------------------------------------------------------------------------

    Exception 1: Blade, P/N 222-016-001-135 or -141M, S/N A-1502, A-
1503, A-1504, A-1505, A-1507, A-1508, A-1509, A-1510, A-1556, A-1557, 
A-1558, A-1560, A-1561, A-1574, A-1635, A-1636, A-1828, A-1829, and S/
Ns with a prefix of ``A'' and a number greater than 1829 have the 
intent of this proposal accomplished prior to delivery and no further 
action is required by this AD.
    Exception 2: Blade, P/N 222-016-001-131 and -139M, S/N A-2049, A-
2055, A-2060, A-2070, A-2071, A-2085, and S/Ns with a prefix of ``A'' 
and a number greater than 2085 have the intent of this proposal 
accomplished prior to delivery and no further action is required by 
this AD.
    Exception 3: Blades identified with an ``R'' code in the square 
block below the P/N field of the Data Plate have already been modified 
and no further actions are required by this AD.


[[Page 33161]]


    Note 1: New blades, P/N 222-016-001-139 and -141, with no letter 
on the Data Plate after the P/N, are not subject to the requirements 
of this AD.

    Compliance: Required as indicated.
    To detect a crack in a blade, and to prevent loss of the blade and 
subsequent loss of control of the helicopter, accomplish the following:
    (a) Within 3 hours time-in-service (TIS), unless accomplished 
previously, and thereafter at intervals not to exceed 3 hours TIS, 
clean and visually check both sides of each blade for a crack in the 
paint in the areas shown in Figure 1 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 43.11 and 
91.417(a)(2)(v).
[GRAPHIC] [TIFF OMITTED] TR11JN10.002


    Note 2: Bell Helicopter Textron Alert Service Bulletin (ASB) No. 
222-04-100, Revision B, for Model 222 and 222B helicopters; ASB No. 
222U-04-71, Revision B, for Model 222U helicopters; ASB No. 230-04-
31, Revision B, for Model 230 helicopters; and ASB No. 430-04-31, 
Revision C, for Model 430 helicopters, all dated March 31, 2008, 
contain guidance on the subject of this AD.

    (b) If the visual check required by paragraph (a) of this AD 
reveals a crack in the paint, before further flight, remove the blade 
and follow the requirements in paragraphs (c)(2) through (c)(3)(ii) of 
this AD.
    (c) Within the next 50 hours TIS, unless accomplished previously, 
and thereafter at intervals not to exceed 50 hours TIS, clean the blade 
by wiping down both surfaces of each blade in the inspection area 
depicted in Figure 1 of this AD using aliphatic naphtha (C-305) or 
detergent (C-318) or an equivalent. Using a 10X or higher power 
magnifying glass, visually inspect both sides of the blade in the areas 
depicted in Figure 1 of this AD.
    (1) If a crack is found, even if only in the paint, before further 
flight, remove the blade from the helicopter and proceed with the 
following:
    (2) Remove the paint on the blade down to the bare metal in the 
area of the suspected crack by using plastic media blasting (PMB) or a 
nylon web abrasive pad. Abrade the blade surface in a span-wise 
direction only.

    Note 3: PMB may cause damage to helicopter parts if untrained 
personnel perform the paint removal. BHT-ALL-SPM, chapter 3, 
paragraph 3-24, contains guidance on the subject of this AD.

    (3) Using a 10X or higher power magnifying glass, inspect the blade 
for a crack.
    (i) If a crack is found, replace the blade with an airworthy blade 
before further flight.
    (ii) If no crack is found in the blade surface, refinish the blade 
by applying one coat of epoxy polyamide primer, MIL-P-23377 or MIL-P-
85582, so that the primer overlaps the existing coats just beyond the 
abraded area. Let the area dry for 30 minutes to 1 hour. Then, apply 
one sealer coat of polyurethane, MILC85285 TYI CL2, color number 27925 
(semi-gloss white). Reinstall the blade.

    Note 4: BHT-ALL-SPM, chapter 4, contains guidance on painting 
the blade.

    (d) On or before 90 days after the effective date of this AD, 
replace any affected serial-numbered blade with an airworthy blade that 
has a S/N that is not subject to, or has been excepted from, the 
requirements of this AD. Installing an airworthy blade that is not 
subject to the requirements of this AD, or has been excepted from the 
requirements of this AD, including those blades with an ``R'' code in 
the square block below the part number field of the Data Plate, 
constitute a terminating action for the requirements of this AD.
    (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 Manager, Safety Management Group, FAA, ATTN: Sharon Miles, 
Aviation Safety Engineer,

[[Page 33162]]

FAA, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5122, fax (817) 
222-5961, for information about previously approved alternative methods 
of compliance.
    (f) The Joint Aircraft System/Component (JASC) Code is 6410: Tail 
Rotor Blades.
    (g) This amendment becomes effective on July 16, 2010.

    Note 5: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2004-21R3, dated April 23, 2008.


    Issued in Fort Worth, Texas, on April 28, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-11071 Filed 6-10-10; 8:45 am]
BILLING CODE 4910-13-P