[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47531-47534]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-18570]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0564; Directorate Identifier 2010-SW-013-AD; 
Amendment 39-17494; AD 2013-13-06]
RIN 2120-AA64


Airworthiness Directives; Various Restricted Category Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Arrow 
Falcon Exporters, Inc. (previously Utah State University); Firefly 
Aviation Helicopter Services (previously Erickson Air-Crane Co.); 
California Department of Forestry; Garlick Helicopters, Inc.; Global 
Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously 
Western International Aviation, Inc.); International Helicopters, Inc.; 
Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin 
Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. 
Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., 
Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; 
Southern Helicopter, Inc.; Southwest Florida Aviation International, 
Inc. (previously Jamie R. Hill and Southwest Florida Aviation); 
Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, 
Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West 
Coast Fabrication; and Williams Helicopter Corporation (previously 
Scott Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, 
UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation 
Model UH-

[[Page 47532]]

1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters. This AD requires 
creating a component history card or equivalent record for each main 
rotor grip (grip); determining and recording the total hours time-in-
service (TIS) for each grip; visually inspecting the upper and lower 
tangs of the grip for a crack; inspecting the grip buffer pads for 
delamination and if delamination is present, inspecting the grip 
surface for corrosion or other damage; inspecting the grip for a crack 
using ultrasonic (UT) and fluorescent penetrant inspection methods; and 
establishing a retirement life for certain grips. This AD was prompted 
by three in-flight failures of grips installed on Bell Helicopter 
Textron (Bell) Model 212 helicopters, which resulted from cracks 
originating in the lower main rotor blade bolt lug. The actions are 
intended to prevent failure of the grip, separation of a main rotor 
blade, and subsequent loss of control of the helicopter.

DATES: This AD is effective September 10, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of September 10, 
2013.

ADDRESSES: For service information identified in this AD, contact 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/. You may review a copy of the referenced service information at 
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.

Examining the AD Docket

    You may examine the AD docket 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 AD docket contains this AD, any incorporated-by-reference 
service information, the economic evaluation, any comments received, 
and other information. The street address for the Docket Operations 
Office (phone: 800-647-5527) is U.S. Department of Transportation, 
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5170; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On July 8, 2010, at 75 FR 39192, the Federal Register published our 
notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR 
part 39 to include an AD that would apply to Arrow Falcon Exporters, 
Inc. (previously Utah State University); Firefly Aviation Helicopter 
Services (previously Erickson Air-Crane Co.); California Department of 
Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, 
Inc.; Hagglund Helicopters, LLC (previously Western International 
Aviation, Inc.); International Helicopters, Inc.; Precision 
Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters 
(previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft 
(previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero 
Corporation, and Wilco Aviation); Smith Helicopters; Southern 
Helicopter, Inc.; Southwest Florida Aviation International, Inc. 
(previously Jamie R. Hill and Southwest Florida Aviation); Tamarack 
Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US 
Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast 
Fabrication; and Williams Helicopter Corporation (previously Scott 
Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-
1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation Model 
UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters with certain 
grips installed. The NPRM proposed to require creating a component 
history card or equivalent record for each grip; determining and 
recording the total hours TIS for each grip; visually inspecting the 
upper and lower tangs of the grip for a crack; inspecting the grip 
buffer pads for delamination and if delamination is present, inspecting 
the grip surface for corrosion or other damage; inspecting the grip for 
a crack using UT and fluorescent penetrant inspection methods; and 
establishing a retirement life for certain grips. The NPRM was prompted 
by reports of three in-flight failures of grips, P/N 204-011-121-009 
and 204-011-121-121, installed on Bell Model 212 helicopters. The 
failures resulted from cracks originating in the lower blade bolt lug. 
The cracking was attributed to subsurface fatigue, corrosion and 
mechanical damage. Grips with these same P/Ns are eligible for 
installation on certain restricted category helicopters. Grips, P/N 
204-044-121-005 and 204-044-121-113, are also affected if they were 
ever installed on a Model 205B or UH-1N helicopter. The proposed 
requirements were intended to prevent failure of the grip, separation 
of a main rotor blade, and subsequent loss of control of the 
helicopter.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (75 FR 39192, 
July 8, 2010).

FAA's Determination

    We have reviewed the relevant information and determined that an 
unsafe condition exists and is likely to exist or develop on other 
products of these same type designs and that air safety and the public 
interest require adopting the AD requirements as proposed except for we 
are incorporating the figure by reference instead of including it in 
our AD and other minor changes to meet current publication 
requirements. These changes are consistent with the intent of the 
proposals in the NPRM (75 FR 39192, July 8, 2010) and will not increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 20 helicopters of U.S. 
registry and that labor costs will average $85 per work-hour. Based on 
these estimates, we expect the following costs:
     Creating new component history cards or the equivalent 
will require two work-hours for a labor cost of $170 per helicopter, 
$3,400 for the U.S. fleet.
     Maintaining records will require five work-hours per year 
for a labor cost of $425.
     Conducting 24 visual inspections using a magnifying glass 
will require 12 work-hours per year for a labor cost of $1,020.
     \1/2\ of a buffer pad inspection: 1.5 hours per year for a 
labor cost of $128.
     \1/4\ of a fluorescent penetrant inspection: .5 work hour 
per year for a labor cost of $43.
     4 UT inspections: 4 work hours per year for a labor cost 
of $340.
     Removing and replacing a grip set will require 20 work 
hours per year. A set of grips will cost $37,590, for total cost of 
$39,290 per helicopter.

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

[[Page 47533]]

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.

Regulatory Findings

    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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) 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 and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2013-13-06 Various Restricted Category Helicopters: Amendment 39-
17494; Docket No. FAA-2010-0564; Directorate Identifier 2010-SW-013-
AD.

(a) Applicability

    This AD applies to Arrow Falcon Exporters, Inc. (previously Utah 
State University); Firefly Aviation Helicopter Services (previously 
Erickson Air-Crane Co.); California Department of Forestry; Garlick 
Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund 
Helicopters, LLC (previously Western International Aviation, Inc.); 
International Helicopters, Inc.; Precision Helicopters, LLC; 
Robinson Air Crane, Inc.; San Joaquin Helicopters (previously 
Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US 
Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, 
and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; 
Southwest Florida Aviation International, Inc. (previously Jamie R. 
Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. 
(previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. 
(previously UNC Helicopter, Inc.); West Coast Fabrication; and 
Williams Helicopter Corporation (previously Scott Paper Co.) Model 
HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and 
UH-1P Helicopters; and Southwest Florida Aviation Model UH-1B (SW204 
and SW204HP) and UH-1H (SW205) Helicopters with main rotor grip 
(grip) part number (P/N) 204-011-121-009, 204-011-121-121, or ASI-
4011-121-9, installed, or with grip P/N 204-011-121-005 or 204-011-
121-113, if the grip was ever installed on a Model 205B or a Model 
UH-1N helicopter, or P/N 204-011-121-117, installed, if the grip was 
ever installed on a Model 205B helicopter, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the lower 
main rotor blade bolt lug. This condition could result in failure of 
a grip, separation of a main rotor blade, and subsequent loss of 
control of the helicopter.

(c) Effective Date

    This AD becomes effective September 10, 2013.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    (1) Within 10 hours time-in-service (TIS), create a component 
history card or equivalent record and determine and record the total 
hours TIS for each grip. If the total hours TIS cannot be determined 
from the helicopter records, assume and record 50 hours TIS for each 
month for which the hours cannot be determined with the grip 
installed on any helicopter. Continue to count and record the hours 
TIS and begin to count and record the number of times the helicopter 
engine(s) are started (engine start/stop cycles).
    (2) Within 10 hours TIS, and then at intervals not to exceed 25 
hours TIS, without removing the main rotor blades:
    (i) Clean the exposed surfaces of the upper and lower tangs of 
each grip with denatured alcohol and wipe dry.
    (ii) Using a 10X or higher magnifying glass, visually inspect 
the exposed surfaces of the upper and lower tangs of each grip for a 
crack. Pay particular attention to the lower surface of each lower 
grip tang from the main rotor blade bolt-bushing flange to the 
leading and trailing edge of each grip tang as depicted in Figure 5-
7, Inspection of Main Rotor Hub Grip (1200 Hours), Revision 9, dated 
August 8, 2008, of Chapter 5, Inspections and Component Overhaul 
Schedule, Revision 11, dated April 30, 2010, of Bell Helicopter 
Textron, Inc. (BHTI), BHT-212-MM-1, Revision 13, dated September 16, 
2010.
    (iii) At the intervals shown in Table 1 to Paragraph (e) of this 
AD, ultrasonic (UT) inspect each grip for a crack in accordance with 
the BHTI Nondestructive Inspection Procedure, Log No. 00-340, 
Revision E, dated April 9, 2002. The UT inspection of the grip must 
be performed by a Nondestructive Testing (NDT) UT Level I Special, 
Level II, or Level III inspector who is qualified under the 
guidelines established by MIL-STD-410E, ATA Specification 105, AIA-
NAS-410, or an FAA-accepted equivalent for qualification standards 
of NDT Inspection/Evaluation Personnel.

                                            Table 1 to Paragraph (e)
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                                                                                Thereafter, at intervals not to
                                                                                exceed the following number of
                                                             Within 30 days,  hours TIS or the engine start/stop
                   UT inspect grip, P/N                      for a grip with    cycles, whichever occurs first:
                                                            the following or -----------------------------------
                                                             more hours TIS:                      Engine start/
                                                                                  Hours TIS        stop cycles
----------------------------------------------------------------------------------------------------------------
204-011-121-009 or ASI-4011-121-9.........................             4,000               400             1,600
204-011-121-121...........................................               500               150               600

[[Page 47534]]

 
204-011-121-005 or -113, if the grip was EVER installed on             4,000               400             1,600
 a Model 205B or Model UH-1N helicopter...................
204-011-121-117, if the grip was EVER installed on a Model               500               150               600
 205B helicopter..........................................
----------------------------------------------------------------------------------------------------------------

    (3) At intervals not to exceed 1,200 hours TIS or 24 months, 
whichever occurs first:
    (i) Remove each main rotor blade, and
    (ii) Inspect each grip buffer pad on the inner surfaces of each 
grip tang for delamination as depicted in Figure 5-7, Inspection of 
Main Rotor Hub Grip (1200 Hours), Revision 9, dated August 8, 2008, 
of Chapter 5, Inspections and Component Overhaul Schedule, Revision 
11, dated April 30, 2010, of Bell Helicopter Textron, Inc., BHT-212-
MM-1, Revision 13, dated September 16, 2010. If there is any 
delamination, remove the buffer pad and inspect the grip surface for 
corrosion or other damage.
    (4) Within 2,400 hours TIS or at the next overhaul of the main 
rotor hub, whichever occurs first, and then at intervals not to 
exceed 2,400 hours TIS:
    (i) Remove each main rotor blade.
    (ii) Remove each grip buffer pad (if installed) from the inner 
surfaces of each grip tang.
    (iii) Visually inspect the grip surfaces for corrosion or other 
damage.
    (iv) Fluorescent-penetrant inspect (FPI) the grip for a crack, 
paying particular attention to the upper and lower grip tangs. When 
inspecting a grip, P/N 204-011-121-005, 204-011-121-009, or 204-011-
121-113, or ASI-4011-121-9, pay particular attention to the leading 
and trailing edges of the grip barrel.
    (5) Before further flight:
    (i) Replace any cracked grip with an airworthy grip.
    (ii) Replace any grip with any corrosion or other damage with an 
airworthy grip, or repair the grip if the corrosion or other damage 
is within the maximum repair limitations.
    (iii) Remove any grip, P/N 204-011-121-009 or ASI-4011-121-9, 
that has been in service for 15,000 or more hours TIS.
    (iv) Remove any grip, P/N 204-011-121-121, that has been in 
service for 25,000 or more hours TIS.
    (6) Revise the Airworthiness Limitations section of the 
applicable maintenance manual or the Instructions for Continued 
Airworthiness (ICA) by establishing a new retirement life of 15,000 
hours TIS for grip, P/N 204-011-121-009 or ASI-4011-121-9, and 
25,000 hours TIS for grip, P/N 204-011-121-121, by marking pen and 
ink changes or inserting a copy of this AD into the maintenance 
manual or ICA.
    (7) Record a 15,000 hour TIS life limit for each grip, P/N 204-
011-121-009 or ASI-4011-121-9, and a 25,000 hour life limit for each 
grip, P/N 204-011-121-121, on the applicable component history card 
or equivalent record.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Michael Kohner, 
Aviation Safety Engineer, Rotorcraft Certification Office, 
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 
76137; telephone (817) 222-5170; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    BHTI Alert Service Bulletin (ASB) 212-94-92, Revision A, dated 
March 13, 1995; BHTI Operations Safety Notice (OSN) 204-85-6, OSN 
205-85-9, and OSN 212-85-13, all dated November 14, 1985 and co-
published as one document; BHTI ASB 205B-02-39, Revision B, dated 
November 22, 2002; and BHTI ASB 212-02-116, Revision A, dated 
October 30, 2002, which are not incorporated by reference, contain 
additional information about the subject of this AD.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6220, Main rotor 
head.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Bell Helicopter Textron, Inc. Nondestructive Inspection 
Procedure, Log No. 00-340, Revision E, dated April 9, 2002.
    (ii) Figure 5-7, Inspection of Main Rotor Hub Grip (1200 Hours), 
Revision 9, dated August 8, 2008, of Chapter 5, Inspections and 
Component Overhaul Schedule, Revision 11, dated April 30, 2010, of 
Bell Helicopter Textron, Inc., BHT-212-MM-1, Revision 13, dated 
September 16, 2010.
    (3) For BHTI service information identified in this AD, contact 
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/.
    (4) You may review a copy of this service information at the 
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas 76137.
    (5) You may also review a copy of this service 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/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on June 18, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-18570 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P