
[Federal Register: February 4, 2010 (Volume 75, Number 23)]
[Rules and Regulations]               
[Page 5681-5683]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04fe10-2]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0065; Directorate Identifier 2009-SW-01-AD; 
Amendment 39-16186; AD 2010-03-03]
RIN 2120-AA64

 
Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
205B and 212 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 
Bell Helicopter Textron, Inc. (Bell) Model 205B and 212 helicopters 
with certain main rotor (M/R) blade assemblies installed. This action 
requires inspecting the M/R blades paying particular attention to an 
area near the blade root for an edge void, corrosion, or a crack. This 
amendment is prompted by two reports of fatigue cracks on M/R blades 
installed on Model 212 helicopters. Both model helicopters use the same 
part-numbered M/R blades. The actions specified in this AD are intended 
to detect an edge void, corrosion, or a crack on a M/R blade, which 
could lead to loss of the M/R blade and subsequent loss of control of 
the helicopter.

DATES: Effective February 19, 2010.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 19, 2010.
    Comments for inclusion in the Rules Docket must be received on or 
before April 5, 2010.

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) 222-5170, fax (817) 222-5783.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for certain 
serial-numbered Bell Model 205B and 212 helicopters with a M/R blade, 
part number (P/N) 212-015-501-005, -111, -113, -115, -117, -119, or -
121, installed. The AD requires, within 25

[[Page 5682]]

hours time-in-service (TIS), and thereafter at intervals not to exceed 
100 hours TIS, washing the upper and lower surfaces of each M/R blade 
and visually inspecting the grip plates and doublers in the area 
between blade stations 24.5 and 40.0 for an edge void, corrosion, or a 
crack, using a 3x power or higher magnifying glass. It also requires 
visually inspecting the remaining surfaces of each M/R blade in the 
area between blade stations 24.5 and 40.0 for any corrosion or a crack 
using a 3x power or higher magnifying glass. If a crack is found in the 
paint finish, removing the paint and re-inspecting the M/R blade is 
required before further flight. If a crack is found in the M/R blade, 
replacing it with an airworthy M/R blade is required before further 
flight. If an edge void or any corrosion is found in the M/R blade, 
replacing it with an airworthy M/R blade, or repairing it if the damage 
is within the maximum repair damage limits, is required before further 
flight. This amendment is prompted by two reports of fatigue cracks on 
M/R blades installed on Model 212 helicopters. The cracks were located 
in the lower doublers and skin, and the box beam at the M/R blade 
attachment bolt hole, and in the lower grip plate at blade station (BS) 
36. The M/R blades had accumulated 1,026 and 2,559 hours TIS. The cause 
of the cracks has been attributed to inadequate adhesive bonding during 
manufacture in the area between the grip plate and mating doubler 
surface. A crack first appears in the grip plate, which can be detected 
visually with the M/R blade installed on the helicopter. The actions 
specified in this AD are intended to detect an edge void, corrosion, or 
a crack on a M/R blade, which could lead to loss of the M/R blade and 
subsequent loss of control of the helicopter.
    We have reviewed Bell Helicopter Alert Service Bulletin (ASB) No. 
205B-08-51 and ASB No. 212-08-130, both Revision A, dated January 13, 
2009, applicable to Model 205B and Model 212 helicopters, respectively, 
which describe procedures for initial and repetitive inspections of 
certain part-numbered M/R blades on certain serial-numbered helicopters 
for signs of an edge void, corrosion, or a crack, including a hair-line 
crack in the M/R blade paint finish.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to detect an edge void, corrosion, or a crack on a M/R blade, which 
could lead to loss of the M/R blade and subsequent loss of control of 
the helicopter. Accomplish the actions by following specified portions 
of the applicable 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, the AD must be issued 
immediately to require the following actions within 25 hours TIS, and 
thereafter at intervals not to exceed 100 hours TIS:
     Washing the upper and lower M/R blade surfaces using a 
solution of cleaning compound (C-318) and water;
     Using a 3x or higher magnifying glass, visually inspecting 
the upper and lower grip plates and doublers of the M/R blade between 
blade station (BS) 24.5 to 40, and the whole width of the chord, for an 
edge void, any corrosion, or a crack;
     Using a 3x power or higher magnifying glass, visually 
inspecting the remaining upper and lower surfaces of the M/R blade 
between BS 24.5 and 40.0, and the whole width of the chord, for any 
corrosion or a crack;
     Applying a light coat of preservative oil (C-125) to all 
surfaces of the M/R blade;
     Removing paint from areas in which a crack is discovered 
in the M/R blade paint finish by sanding with 180-220 grit paper to 
determine if a crack exists in the M/R blade;
     Replacing any M/R blade that has a crack in any part of 
the M/R blade other than the paint finish with an airworthy M/R blade;
     Replacing any M/R blade that has any corrosion or an edge 
void with an airworthy M/R blade, or repairing the M/R blade if the 
damage is within the maximum repair damage limits. The maximum repair 
damage limitations are contained in the applicable Component and Repair 
Overhaul Manual; and
     Replacing any M/R blade that has any parent material 
removed during the sanding operation to remove paint from areas in 
which a paint crack is discovered, or repairing the M/R blade if the 
amount of parent removed material is within the maximum repair damage 
limits.
    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 87 helicopters of U.S. 
registry, and washing and visually inspecting each M/R blade will take 
approximately 1 work hour per helicopter at an average labor rate of 
$80 per work hour. If an edge void, corrosion, or a crack is 
discovered, replacing the M/R blade with an airworthy blade will take 
approximately 6 work hours. Required parts will cost approximately 
$97,500 for a replacement M/R blade. Based on these figures, we 
estimate the total cost impact of the AD on U.S. operators to be 
$139,740, assuming that 6 inspections per year are conducted on each 
helicopter, and that one M/R blade will need to be replaced.

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-2010-0065; Directorate 
Identifier 2009-SW-01-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.

[[Page 5683]]

    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:

2010-03-03 Bell Helicopter Textron, Inc.: Amendment 39-16186. Docket 
No. FAA-2010-0065; Directorate Identifier 2009-SW-01-AD.

    Applicability: Serial-numbered Model 205B and Model 212 
helicopters, with the specified part-numbered main rotor (M/R) blade 
that is listed in Table 1 of this AD installed, certificated in any 
category.

                                                     Table 1
----------------------------------------------------------------------------------------------------------------
  Helicopter model and serial
           No. (S/N)                                              M/R blade P/N
----------------------------------------------------------------------------------------------------------------
Model 205B: S/N 30066, 30166,   P/N 212-015-501-005, -111, -113, -115, -117, -119, or -121.
 30188, or 30297.
Model 212: S/N 30502 through    P/N 212-015-501-005, -111, -113, -115, -117, -119, or - 121.
 30603, 30611 through 30999,
 31101 through 31311, 32101
 through 32262, or 35001
 through 35103.
----------------------------------------------------------------------------------------------------------------

     Compliance: Required as indicated.
    To detect an edge void, corrosion, or a crack on a M/R blade, 
which could lead to loss of the M/R blade and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Within 25 hours time-in-service (TIS), unless accomplished 
previously, and thereafter at intervals not to exceed 100 hours TIS:
    (1) Wash the upper and lower surfaces of the M/R blade with a 
solution of cleaning compound (C-318) and water. Rinse thoroughly 
and wipe dry.
    (2) Using a 3x power or higher magnifying glass, on each 
affected M/R blade, in an area from blade stations 24.5 to 40, 
including the entire width of the M/R blade chord, as depicted in 
Figure 1 in Bell Helicopter Alert Service Bulletin No. 205B-08-51 
for the Model 205B helicopters, or No. 212-08-130 for the Model 212 
helicopters, both Revision A, dated January 13, 2009 (ASBs), as 
applicable:
    (i) Visually inspect the upper and lower grip plates and 
doublers of the M/R blade in the specified area for an edge void, 
corrosion, or a crack.
    (ii) Visually inspect the remaining upper and lower surfaces of 
the M/R blade in the specified area for any corrosion or a crack.

    Note 1: The inspections required by paragraphs (a)(2)(i) and 
(a)(2)(ii) of this AD can be accomplished with the M/R blade 
installed on the helicopter.


    Note 2: Crack indications on an actual M/R blade are shown in 
Figure 2 of both ASBs.

    (3) Apply a light coat of preservative oil (C-125) to all 
surfaces of the M/R blade in the specified area.
    (b) Before further flight:
    (1) If any corrosion or an edge void is found, replace the M/R 
blade with an airworthy M/R blade, or repair the M/R blade if the 
damage is within the maximum repair damage limits.
    (2) If a crack is found in the M/R blade paint finish, remove 
the paint in the affected area by lightly sanding with 180-220 grit 
paper in a span wise direction to determine if the grip plate, 
doubler, or skin is cracked. Do not remove any parent material of 
the M/R blade during the sanding operation. Refinish the sanded 
area.
    (3) If a crack is found in any part of the M/R blade other than 
the paint finish, replace the M/R blade with an airworthy M/R blade.
    (4) If any parent material is removed during the sanding 
operation required by paragraph (b)(2) of this AD, replace the M/R 
blade with an airworthy M/R blade, or repair the M/R blade if the 
amount of parent material removed is within the maximum repair 
damage limits.

    Note 3: The maximum repair damage limitations specified in 
paragraphs (b)(1) through (b)(4) of this AD are contained in the 
applicable Component and Repair Overhaul Manual.

    (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, ATTN: Michael 
Kohner, Aviation Safety Engineer, FAA, Rotorcraft Directorate, 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) The inspections and replacements, if necessary, shall be 
done in accordance with the specified portions of Bell Helicopter 
Alert Service Bulletin No. 205B-08-51 for Model 205B helicopters, or 
No. 212-08-130 for Model 212 helicopters, both Revision A, dated 
January 13, 2009, as applicable. 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.

Joint Aircraft System/Component (JASC) Code

    (e) JASC Code 6210: Main Rotor Blades.
    (f) This amendment becomes effective on February 19, 2010.

    Issued in Fort Worth, Texas, on December 21, 2009.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-1720 Filed 2-3-10; 8:45 am]
BILLING CODE 4910-13-P

