Document ID: FAA-2009-0484-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Bell Helicopter Textron, Inc. Model 47, 47B, 47B3, 47D, 47D1, 47E, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K Helicopters
Posted Date: 2009-06-12T04:00Z

[Federal Register: June 12, 2009 (Volume 74, Number 112)]
[Rules and Regulations]               
[Page 27915-27917]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12jn09-6]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0484; Directorate Identifier 2008-SW-44-AD; 
Amendment 39-15924; AD 2009-12-01]
RIN 2120-AA64

 
Airworthiness Directives; Bell Helicopter Textron, Inc. Model 47, 
47B, 47B3, 47D, 47D1, 47E, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 
47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 
47J, 47J-2, 47J-2A, and 47K 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. (Bell) helicopters. This 
action requires visually inspecting each main rotor blade box beam clip 
(clip) for correct installation. This amendment is prompted by a report 
of a main rotor blade with an incorrectly installed clip. The actions 
specified in this AD are intended to prevent a main rotor blade spar 
crack as a result of an incorrectly installed clip, loss of a main 
rotor blade, and subsequent loss of control of the helicopter.

DATES: Effective June 29, 2009.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 29, 2009.
    Comments for inclusion in the Rules Docket must be received on or 
before August 11, 2009.

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: Michael Kohner, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5170, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the 
specified Bell helicopters. This action requires visually inspecting 
each clip for correct installation. This amendment is prompted by a 
report of a main rotor blade with an incorrectly installed clip. This 
condition, if not corrected, could result in a main rotor blade spar 
crack, loss of a main rotor blade, and subsequent loss of control of 
the helicopter.
    We have reviewed Bell Alert Service Bulletin No. 47-08-25, dated 
May 26, 2008 (ASB), which describes procedures for visually inspecting 
each clip on the affected main rotor blade for correct installation. 
The ASB specifies that a clip incorrectly installed may cause a main 
rotor blade spar crack.
    This unsafe condition is likely to exist or develop on other 
helicopters of these same type designs. Therefore, this AD is being 
issued to prevent a main rotor blade spar crack as a result of an 
incorrectly installed clip, loss of a main rotor blade, and subsequent 
loss of control of the helicopter. This AD requires visually inspecting 
the entire length of each clip on an affected main rotor blade by 
following specified portions of the ASB 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, visually inspecting 
each main rotor blade for an incorrectly installed clip within 10 hours 
time-in-service and replacing any main rotor blade that has an 
incorrectly installed clip with an airworthy main rotor blade before 
further flight is a very short time period, 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 1,130 helicopters. It will 
require a minimal amount of time to locate the 7 affected blades. The 
visual inspection for an incorrectly installed clip will take about 5 
work hours at an average labor rate of $80 per work hour. Required 
parts will cost about $42,640. Based on these figures, we estimate the 
total cost impact of the AD on U.S. operators to be $45,440 ($2,800 for 
labor costs and $42,640 in parts costs) assuming only one blade will 
need to be replaced in the helicopter fleet.

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-2009-0484;

[[Page 27916]]

Directorate Identifier 2008-44-SW-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

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 adding a new airworthiness directive to 
read as follows:

2009-12-01 Bell Helicopter Textron, Inc.: Amendment 39-15924. Docket 
No. FAA-2009-15924; Directorate Identifier 2008-SW-44-AD.

    Applicability: Model 47, 47B, 47B3, 47D, 47D1, 47E, 47G, 47G-2, 
47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-
4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K 
helicopters with a main rotor blade, installed, with a part number 
(P/N) and serial number (S/N), listed as follows, certificated in 
any category:

------------------------------------------------------------------------
        Main rotor blade, P/N                    With a S/N of
------------------------------------------------------------------------
047-110-250-021.....................  A-303, A-304, A-312, or A-316.
047-110-250-023.....................  A-298, A-301, or A-305.
------------------------------------------------------------------------

    Compliance: Required as indicated, unless done previously.
    To prevent a main rotor blade spar crack as a result of an 
incorrectly installed main rotor blade box beam clip (clip), loss of 
a main rotor blade, and subsequent loss of control of the 
helicopter, do the following:
    (a) Within 10 hours time-in-service (TIS), visually inspect the 
entire length of each upper and lower clip of each main rotor blade 
from the main rotor blade tip to the root by following Part II of 
the Accomplishment Instructions, paragraphs 1. through 8., of Bell 
Helicopter Textron, Inc. Alert Service Bulletin No. 47-08-25, dated 
May 26, 2008 (ASB) and referring to the depictions in Figures 1 and 
2 of the ASB and Figure 1 of this AD for correct installation.

    Note: Figure 3 of the ASB depicts a clip installed incorrectly.

[[Page 27917]]

[GRAPHIC] [TIFF OMITTED] TR12JN09.000

    (b) Before further flight, if you find a main rotor blade with 
an incorrectly installed clip, replace that unairworthy main rotor 
blade with an airworthy main rotor blade that has a clip that is 
installed correctly.
    (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, Aviation Safety Engineer, Rotorcraft Directorate, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5170, fax (817) 
222-5783.
    (d) Special flight permits may be issued under 14 CFR 21.197 and 
21.199 to operate the helicopter to a location where the 
requirements of this AD can be done provided the onetime ferry 
flight does not exceed 5 hours TIS.
    (e) The visual inspection shall be done by following the 
specified portions of Bell Helicopter Textron, Inc., Alert Service 
Bulletin No. 47-08-25, dated May 26, 2008. 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 June 29, 2009.

    Issued in Fort Worth, Texas, on May 19, 2009.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E9-13563 Filed 6-11-09; 8:45 am]

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