Document ID: FAA-2011-0561-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bell Helicopter Textron, Inc. Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP Helicopters
Posted Date: 2011-06-17T04:00Z

[Federal Register Volume 76, Number 117 (Friday, June 17, 2011)]
[Rules and Regulations]
[Pages 35334-35336]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-14247]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0561; Directorate Identifier 2010-SW-001-AD; 
Amendment 39-16715; AD 2011-12-08]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
205A, 205A-1, 205B, 212, 412, 412CF, and 412EP 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, Inc. (BHT) model helicopters 
with tail rotor (T[sol]R) blades with certain serial numbers installed. 
This action requires a one-time inspection of the T[sol]R blade for 
corrosion or pitting, and repairing or replacing the T[sol]R blade, if 
that condition is found during the inspection. This amendment is 
prompted by a report from the manufacturer that T[sol]R blades with 
certain serial numbers may have manufacturing anomalies in the spar 
area. These actions are intended to detect corrosion or pitting in the 
forward spar area of a T[sol]R blade to prevent a crack in the T[sol]R 
blade, loss of the T[sol]R blade, and subsequent loss of control of the 
helicopter.

DATES: Effective July 5, 2011.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 5, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before August 16, 2011.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, 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, 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 the 
AD, any comments, and other information on the Internet at http://www.regulations.gov, or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Operations office (telephone (800) 647-5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Michael 
Kohner, ASW-170, Aviation Safety Engineer, Rotorcraft Directorate, 
Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 
76137, telephone (817) 222-5447, fax (817) 222-5783.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the 
specified BHT model helicopters with an installed T[sol]R blade, part 
number 212-010-750 (all dash numbers), all serial numbers except those 
with a prefix of ``A'' and the number 17061 or larger. This action 
requires a one-time inspection of the T[sol]R blade for corrosion or 
pitting after sanding the paint from the spar area between blade 
stations 22.5 and 40.0, and repairing or replacing the T[sol]R blade if 
corrosion, pitting, or damage is discovered. This amendment is prompted 
by a report from the manufacturer that T[sol]R blades with certain 
serial numbers may have manufacturing anomalies in the spar area as a 
result of the chemical milling process. The anomalies may be identified 
as pits or corrosion on the spar. This corrosion or pitting condition 
in the forward spar of a T[sol]R blade, if not corrected, could lead to 
a crack in the T[sol]R blade, loss of the T[sol]R blade, and subsequent 
loss of control of the helicopter.
    We have reviewed the following BHT Alert Service Bulletins, all 
Revision A, and all dated December 8, 2009, which specify a one-time 
inspection of the T[sol]R blades for corrosion or pitting, and 
repairing or replacing the T[sol]R blade if corrosion, pitting, or 
other damage is discovered:
     Alert Service Bulletin (ASB) No. 205-09-102, for Model 
205A and 205A-1 helicopters;
     ASB No. 205B-09-54, for Model 205B helicopters;
     ASB No. 212-09-134, for Model 212 helicopters;
     ASB No. 412CF-09-38, for Model 412CF helicopters; and
     ASB No. 412-09-136, for Model 412 and 412EP helicopters.
    This unsafe condition is likely to exist or develop on other 
helicopters of these same type designs. Therefore, this AD is being 
issued to require inspecting the T[sol]R blades to detect corrosion or 
pitting in the forward spar area that could result in a crack, loss of 
a T[sol]R blade, and subsequent loss of control of the helicopter. 
Accomplish the actions by following specified portions of the ASBs 
described previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
structural integrity and controllability of the helicopter. Therefore, 
inspecting the T[sol]R blade for corrosion or pitting is required 
within 25 hours time-in-service (TIS) or 30 days, whichever occurs 
first. This is a very short compliance time, 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 263 helicopters. Removing, 
inspecting, refinishing, and re-installing the T[sol]R blade will take 
about 10 work hours at an average labor rate of $85 per work hour and 
an approximate labor cost of $850 per helicopter. Replacing the T[sol]R 
blade with an airworthy blade will take about 6 work hours at an 
average labor rate of $85 per work hour for an approximate labor cost 
of $510 per helicopter. Required parts will cost about $17,495 for each 
T[sol]R blade assembly. Based on these figures, we estimate the total 
cost impact of the AD on U.S. operators to be $277,565, assuming all 
affected helicopters are inspected and three T[sol]R blades are 
replaced.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an

[[Page 35335]]

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-2011-
0561; Directorate Identifier 2011-SW-001-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://www.regulations.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).

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, Incorporation by 
reference, 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 
(AD) to read as follows:

2011-12-08 Bell Helicopter Textron, Inc. (BHT): Amendment 39-16715. 
Docket No. FAA-2011-0561; Directorate Identifier 2010-SW-001-AD.

    Applicability: Model 205A, 205A-1, 205B, 212, 412, 412CF, and 
412EP helicopters with a tail rotor (T/R) blade, part number 212-
010-750 (all dash numbers), all serial numbers (S/Ns) except those 
S/Ns with a prefix of ``A'' and a number 17061 or larger, installed, 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect corrosion or pitting in the forward spar area of a T/R 
blade to prevent a crack in the T/R blade, loss of the T/R blade, 
and subsequent loss of control of the helicopter, do the following:
    (a) Within 25 hours time-in-service (TIS) or 30 days, whichever 
occurs first:
    (1) Remove the T/R hub and blade assembly from the helicopter 
and remove the T/R blade from the hub. Remove the paint from the 
spar area on both sides of the T/R blade by following the 
Accomplishment Instructions, paragraphs 3. through 5., of the 
following BHT Alert Service Bulletins, all Revision A, and all dated 
December 8, 2009: Alert Service Bulletin (ASB) No. 205-09-102 for 
the Model 205A and 205A-1 helicopters; ASB No. 205B-09-54 for the 
Model 205B helicopters; ASB No. 212-09-134 for the Model 212 
helicopters; ASB No. 412CF-09-38 for the Model 412CF helicopters; 
and ASB No. 412-09-136 for the Model 412 and 412EP helicopters.
    (2) Using a 3-power or higher magnifying glass, visually inspect 
both sides of the T/R blade for any corrosion or pitting in the spar 
inspection areas as depicted in Figure 1 of the ASB for your model 
helicopter.
    (b) Before further flight:
    (1) If you find any corrosion or pitting that is 0.003 inch deep 
or less, either replace the unairworthy T/R blade with an airworthy 
T/R blade or repair the T/R blade.

    Note: The maintenance and repair procedures along with the 
maximum repair damage limitations as referenced in paragraphs (b)(1) 
and (b)(3) of this AD are contained in the applicable maintenance 
manual and component repair and overhaul manuals.

    (2) If you find any corrosion or pitting that is greater than 
0.003 inch deep, replace the T/R blade with an airworthy T/R blade.
    (3) If any parent material is removed during the sanding 
operation required by paragraph (a)(1) of this AD, either replace 
the T/R blade with an airworthy T/R blade, or repair the T/R blade 
if the parent material removed is within the maximum repair damage 
limits.
    (4) If there is no corrosion or pitting and no damage greater 
than 0.003 inch deep, refinish the inspection areas and reinstall 
each T/R blade onto the T/R hub, install the T/R assembly on the 
helicopter and track and balance the T/R in accordance with the 
Accomplishment Instructions, paragraphs 8. through 10., of the ASB 
for your model helicopter.
    (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 Manager, Rotorcraft Certification Office, FAA, Attn: 
Michael Kohner, ASW-170, Aviation Safety Engineer, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5170, fax (817) 
222-5783, for information about previously approved alternative 
methods of compliance.
    (d) Joint Aircraft System/Component (JASC) Code 6410: Tail rotor 
blades.
    (e) Accomplish the instructions in this AD by following the 
specified portions of the following Bell Helicopter Textron, Inc. 
Alert Service Bulletin, as applicable to your model helicopter: No. 
205-09-102; No. 205B-09-54; No. 212-09-134; No. 412CF-09-38, or No. 
412-09-136. Each Alert Service Bulletin is Revision A, and each is 
dated December 8, 2009. The Director of the Federal Register 
approved this incorporation by reference in accordance with 5 U.S.C. 
552(a) and 1 CFR Part 51. Copies may be obtained 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. Copies may be inspected at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas or 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.
    (f) This amendment becomes effective on July 5, 2011.

[[Page 35336]]

    Issued in Fort Worth, Texas, on May 17, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-14247 Filed 6-16-11; 8:45 am]
BILLING CODE 4910-13-P