[Federal Register Volume 70, Number 32 (Thursday, February 17, 2005)]
[Rules and Regulations]
[Pages 8021-8025]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-3049]



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  Federal Register / Vol. 70, No. 32 / Thursday, February 17, 2005 / 
Rules and Regulations  

[[Page 8021]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20107; Directorate Identifier 2005-SW-02-AD; 
Amendment 39-13981; AD 2005-04-09]
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; request for comments.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for the specified Bell Helicopter Textron Canada (BHTC) model 
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 
as the existing AD, but expands the applicability with the addition of 
two BHTC Model 430 helicopter serial numbers. This amendment is 
prompted by the manufacturer issuing revised service information that 
includes the additional two serial numbers. The actions specified by 
this AD are intended to detect a crack in the blade, and to prevent 
loss of a blade and subsequent loss of control of the helicopter.

DATES: Effective March 4, 2005.
    Comments for inclusion in the Rules Docket must be received on or 
before April 18, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: (202) 493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    You may get the service information identified in this AD from Bell 
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272. 
You may examine this information at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Examining the Docket:  You may examine the docket that contains the AD, 
any comments, and other information on the Internet at http://dms.dot.gov, or in person at the Docket Management System (DMS) Docket 
Offices between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The Docket Office (telephone (800) 647-5227) is 
located on the plaza level of the Department of Transportation Nassif 
Building at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after the DMS 
receives them.

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: On December 23, 2004, the FAA issued AD 
2004-26-11, Amendment 39-13923 (70 FR 7; January 3, 2005), to require 
certain checks and inspections of the blades. If a crack is found, that 
AD requires replacing the blade with an airworthy blade before further 
flight. That action was prompted by three reports of cracked blades 
that were found during scheduled inspections. That condition, if not 
corrected, could result in loss of a blade and subsequent loss of 
control of the helicopter.
    Since issuing that AD, the alert service bulletin (ASB) that is 
applicable to BHTC Model 430 helicopters has been revised by the 
manufacturer to include two additional helicopter serial numbers. 
Further, we discovered two typographical errors in the AD--the word 
``Canada'' is inadvertently omitted from the manufacturer's name in the 
Summary section, and in Note 1 of the AD, the number for the Model 430 
helicopter ASB is incorrectly stated as 430-04-32 instead of 430-04-
31--as well as some minor editorial errors, which have been corrected 
in this AD.
    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 ASB No. 222-04-100 for Model 222 and 222B 
helicopters; ASB No. 222U-04-71 for Model 222U helicopters; and ASB No. 
230-04-31 for Model 230 helicopters, all dated August 27, 2004; and, 
ASB No. 430-04-31, Revision A, dated November 29, 2004, for Model 430 
helicopters. The ASBs specify a visual inspection of the blade root end 
around the feather bearings for a crack, not later than at the next 
scheduled inspection, and thereafter at intervals not to exceed 3 
flight hours. Further, they describe a visual inspection for a crack, 
to include removing the blade from the helicopter, within 50 flight 
hours, and thereafter at intervals not to exceed 50 flight hours. 
Transport Canada classified these ASBs as mandatory and issued AD CF-
2004-21R1, dated December 9, 2004, to ensure the continued 
airworthiness of these helicopters in Canada. This AD differs from 
those ASBs in that it requires an initial visual check, which may be

[[Page 8022]]

performed by a pilot, within 3 hours time-in-service (TIS) rather than 
a visual inspection not later than at the next scheduled inspection and 
every 3 flight hours maximum thereafter as stated in the ASBs.
    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 previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type design. Therefore, this 
AD supersedes AD 2004-26-11 to require the following:
     Within 3 hours TIS, and thereafter at intervals not to 
exceed 3 hours TIS, clean and visually check both sides of each blade 
for a crack in the area around the tail rotor feathering bearing. An 
owner/operator (pilot) may perform this check. Pilots may perform the 
checks required by paragraph (a) of this AD 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).
     Within 50 hours TIS, and thereafter at intervals not to 
exceed 50 hours TIS, clean and inspect both sides of each blade for a 
crack using a 10X or higher magnifying glass.
     If a crack is found in the blade paint during a visual 
check or inspection, further inspect the blade as follows, before 
further flight:
     Remove the blade. Remove the paint to the bare metal in 
the area of the suspected crack by using plastic metal blasting (PMB) 
or a nylon web abrasive pad and abrading the blade surface in a span-
wise direction only.
     Using a 10X or higher power magnifying glass, inspect the 
blade for a crack.
     If a crack is found, replace the blade with an airworthy 
blade before further flight.
     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), per Fed. Std. 595, and reinstall the blade.
    This AD is an interim action, pending release of additional service 
information from the manufacturer concerning instructions for 
inspecting and reworking the affected blades. We expect that service 
information to eliminate the recurring inspections required by this AD.
    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, 
checking the blade for a crack within 3 hours TIS, and thereafter at 
intervals not to exceed 3 hours TIS, is required, 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.
    We estimate that this AD will affect 156 helicopters and will 
require:
     0.25 work hour for a pilot check, and 2 work hours for a 
maintenance inspection, at an average labor rate of $65 per work hour; 
and
     Parts, which will cost an estimated $13,410 per 
helicopter.
    Based on these figures, the estimated total cost impact of the AD 
on U.S. operators is $2,842,320 per year, assuming each helicopter will 
require 200 pilot checks, 12 maintenance inspections, and one blade 
replacement per year.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send or deliver your comments to 
an address listed under ADDRESSES. Include ``Docket No. FAA-2005-20107; 
Directorate Identifier 2005-SW-02-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of our docket 
web site, you can find and read the comments to any of our dockets, 
including the name of the individual who sent the comment. You may 
review the DOT's complete Privacy Act Statement in the Federal Register 
published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

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 DMS 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.

[[Page 8023]]

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 39-13923 (70 FR 7, 
January 3, 2005), and by adding a new airworthiness directive (AD), 
Amendment 39-13981, to read as follows:

2005-04-09 Bell Helicopter Textron Canada: Amendment 39-13981. 
Docket No. FAA-2005-20107; Directorate Identifier 2005-SW-02-AD. 
Supersedes AD 2004-26-11, Amendment 39-13923, Docket No. FAA-2004-
19969, Directorate Identifier 2004-SW-43-AD.

    Applicability: The following helicopter models, identified by 
serial number, with one of the following part numbered tail rotor 
blades installed, certificated in any category.

----------------------------------------------------------------------------------------------------------------
               Model                     Serial No.                  Tail rotor blade (blade) part no.
----------------------------------------------------------------------------------------------------------------
222...............................  47006 through 47089.  222-016-001-123, -127, -131, and -135.
222B..............................  47131 through 47156.  222-016-001-123, -127, -131, and -135.
222U..............................  47501 through 47574.  222-016-001-123, and -131.
230...............................  23001 through 23038.  222-016-001-123, and -131.
430...............................  49001 through 49107.  222-016-001-123, and -131.
----------------------------------------------------------------------------------------------------------------

    Compliance: Required as indicated.
    To detect a crack in the 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), 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).

BILLING CODE 4910-13-P

[[Page 8024]]

[GRAPHIC] [TIFF OMITTED] TR17FE05.002

BILLING CODE 4910-13-C

    Note 1: Bell Helicopter Textron Alert Service Bulletin (ASB) No. 
222-04-100, No. 222U-04-71, and No. 230-04-31, all dated August 27, 
2004, and ASB No. 430-04-31, Revision A, dated November 29, 2004, 
pertain to the subject of this AD.

    (b) If the visual check required by paragraph (a) 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 metal blasting (PMB) or 
a nylon web abrasive pad. Abrade the blade surface in a span-wise 
direction only.

    Note 2: PMB may cause damage to helicopter parts if untrained 
personnel perform the paint removal. BHT-ALL-SPM, chapter 3, 
paragraph 3-24, pertains to the subject of this AD.

    (3) Using a 10X or higher power magnifying glass, inspect the 
blade for a crack.

[[Page 8025]]

    (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), per Fed. Std. 595. Reinstall 
the blade.

    Note 3: BHT-ALL-SPM, chapter 4, pertains to painting the blade.

    (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, FAA, for information about 
previously approved alternative methods of compliance.
    (e) Special flight permits may be issued by following 14 CFR 
21.197 and 21.199 to operate the helicopter to a location where the 
requirements of this AD can be accomplished provided you do not find 
a crack in the blade paint during a check or inspection.
    (f) This amendment becomes effective March 4, 2005.

    Note 4: The subject of this AD is addressed in Transport Canada 
(Canada) Airworthiness Directive CF-2004-21R1, dated December 9, 
2004.


    Issued in Fort Worth, Texas, on February 10, 2005.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-3049 Filed 2-16-05; 8:45 am]
BILLING CODE 4910-13-P