[Federal Register Volume 70, Number 1 (Monday, January 3, 2005)]
[Rules and Regulations]
[Pages 7-10]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-28628]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19969; Directorate Identifier 2004-SW-43-AD; 
Amendment 39-13923; AD 2004-26-11]
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.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Bell Helicopter Textron (BHTC) model helicopters. This 
action requires certain checks and inspections of the tail rotor 
blades. If a crack is found, before further flight, this AD requires 
replacing the tail rotor blade (blade) with an airworthy blade. This 
amendment is prompted by three reports of cracked blades found during 
scheduled inspections. The actions specified in this AD are intended to 
detect a crack in the blade and prevent loss of a blade and subsequent 
loss of control of the helicopter.

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

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 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 certain checks 
and inspections of the blades. If a crack is found, before further 
flight, this AD requires replacing the blade with an airworthy blade. 
This amendment is prompted by three reports of cracked blades found 
during scheduled inspections. This condition, if not detected, could 
result in loss of a blade and subsequent loss of control of the 
helicopter.
    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 for 
Model 222 and 222B helicopters, No. 222U-04-71 for Model 222U 
helicopters, No. 230-04-31 for Model 230 helicopters, and No. 430-04-31 
for Model 430 helicopters, all dated August 27, 2004. The ASBs specify 
a repetitive visual inspection every 3 hours time-in-service (TIS) and 
a 50-hour inspection of the blade root end around the feathering 
bearings for a crack. Transport Canada classified these ASBs as 
mandatory and issued AD CF-2004-21, dated October 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. Therefore, this AD is being 
issued to prevent loss of a blade and subsequent loss of control of the 
helicopter. This AD requires the following:
     Within 3 hours time-in-service (TIS), and at specified 
intervals, 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 the check for cracked blades. 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).
     Within 50 hours TIS and at specified intervals, clean and 
inspect both sides of each blade for a crack using a 10X or higher 
magnifying glass.
     If a crack is found even in the paint during a visual 
check or during a 50-hour TIS inspection, before further flight, a 
further inspection of the blade for a crack is required as follows:
     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, before further flight, replace the 
blade with an airworthy blade.
     If no crack is found in the blade surface, refinish the 
blade by applying one coat of MIL-P-23377 or MIL-P-85582 Epoxy 
Polyamide Primer so that the primer overlaps the existing coats

[[Page 8]]

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.
    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 within 3 hours TIS and 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 require:
     \1/4\ hour for a pilot check, assuming 200 a year; and 2 
hours for a maintenance inspection, assuming 12 a year at an average 
labor rate of $65 per work hour;
     Parts cost at about $13,410 per helicopter, assuming one 
blade replacement a year. Based on these figures, the estimated total 
cost impact of the AD on U.S. operators is $2,842,320 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 your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-19969; 
Directorate Identifier 2004-SW-43-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.

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:

AD 2004-26-11 Bell Helicopter Textron Canada: Amendment 39-13923. 
Docket No. FAA-2004-19969; Directorate Identifier 2004-SW-43-AD.

    Applicability: The following helicopter models, identified by 
serial number and with the following part number (P/N) tail rotor 
blade (blade), installed, certificated in any category.

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             Model                   Serial No.                                Blade P/N
----------------------------------------------------------------------------------------------------------------
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 49105.  222-016-001-123, and -131.
----------------------------------------------------------------------------------------------------------------

    Compliance: Required as indicated.
    To detect a crack in the blade and 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 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 sections 43.11 and 91.417(a)(2)(v).
BILLING CODE 4910-13-P

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[GRAPHIC] [TIFF OMITTED] TR03JA05.011

BILLING CODE 4910-13-C
    Note 1: Bell Helicopter Textron Alert Service Bulletins 222-04-
100, 222U-04-71, 230-04-31, and 430-04-32, all dated August 27, 
2004, pertain to the subject of this AD.
    (b) If a crack is found in the paint while complying with 
paragraph (a) of this AD, before further flight, inspect the blade 
by removing the blade and by abrading the area and following the 
other requirements in paragraph (c) of this AD.
    (c) Within the next 50 hours TIS, unless accomplished 
previously, and 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 naptha (C-305) 
or detergent (C-318) or equivalents. 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 even a crack is found in the paint, before further 
flight, remove the blade.
    (2) 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. Abrade the blade surface in a span-wise direction 
only.
    Note 2: PMB may cause damage to helicopter parts if performed by 
untrained personnel. 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.
    (i) If a crack is found, before further flight, replace the 
blade with an airworthy blade.
    (ii) If no crack is found in the blade surface, refinish the 
blade by applying one coat of MIL-P-23377 or MIL-P-85582 Epoxy 
Polyamide Primer so that the primer overlaps

[[Page 10]]

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.
    (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 paint during a check or inspection.
    (f) This amendment becomes effective January 18, 2005.
    Note 4: The subject of this AD is addressed in Transport Canada 
(Canada) Airworthiness Directive CF-2004-21, dated October 28, 2004.

    Issued in Fort Worth, Texas, on December 23, 2004.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-28628 Filed 12-30-04; 8:45 am]
BILLING CODE 4910-13-P