AD 2012-26-06

[Federal Register Volume 78, Number 48 (Tuesday, March 12, 2013)]
[Rules and Regulations]
[Pages 15599-15602]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-05503]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD; 
Amendment 39-17301; AD 2012-26-06]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-
64F Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 15600]]


ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for 
Sikorsky Aircraft Corporation-manufactured Model S-64F helicopters, now 
under the Erickson Air-Crane Incorporated (Erickson) Model S-64F type 
certificate. This AD supersedes an existing AD which requires 
inspections, rework, and replacement, if necessary, of the main gearbox 
(MGB) second stage lower planetary plate (plate). Since we issued that 
AD, the manufacturer has conducted a configuration review and analysis, 
and a review of the service history of certain components. The actions 
of this AD are intended to establish life limits for certain 
components, remove various parts from service, and require consistency 
in the part numbers of certain four bladed tail rotor (T/R) assemblies 
to prevent fatigue cracking, failure from static overload, and 
subsequent loss of control of the helicopter.

DATES: This AD is effective April 16, 2013.

ADDRESSES: For service information identified in this AD, contact 
Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance 
Officer, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR 
97502, telephone (541) 664-5544, fax (541) 664-2312, email address 
<a href="/cdn-cgi/l/email-protection#bad9dfc8d3d9d1c9d5d4fadfc8d3d9d1c9d5d4dbd3c8d9c8dbd4df94d9d5d7"><span class="__cf_email__" data-cfemail="264543544f454d5549486643544f454d554948474f5445544748430845494b">[email&#160;protected]</span></a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 
Fort Worth, Texas 76137, telephone (817) 222-5170, email <a href="/cdn-cgi/l/email-protection#0f38226e797c226e7c78223e383f4f696e6e21686079"><span class="__cf_email__" data-cfemail="94a3b9f5e2e7b9f5e7e3b9a5a3a4d4f2f5f5baf3fbe2">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    On June 29, 2012, at 77 FR 38744, 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 Sikorsky Aircraft 
Corporation-manufactured Model S-64F helicopters, now under the 
Erickson Air-Crane Incorporated Model S-64F type certificate. That NPRM 
proposed to supersede existing AD 97-10-15 (62 FR 28321, May 23, 1997), 
to require reducing or establishing the life limits for certain flight-
critical components, removing other parts with service difficulties 
from service, and require that T/R blade assembly, P/N 65160-00001-048, 
be installed only as a set of four and not be installed with another 
part-numbered blade. The proposed requirements were intended to prevent 
a fatigue crack in a flight critical component, which could result in 
component failure from static overload 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 (77 FR 38744, 
June 29, 2012).

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 
helicopters of the same type design and that air safety and the public 
interest require adopting the AD requirements as proposed except for 
minor editorial changes to meet current publication requirements. These 
minor editorial changes are consistent with the intent of the proposals 
in the NPRM (77 FR 38744, June 29, 2012) and will not increase the 
economic burden on any operator nor increase the scope of the AD.

Related Service Information

    Erickson Service Bulletin No. 64F General-1, Rev. 17, contains the 
Airworthiness Limitations Schedule for the Model S-64F helicopter and 
lists the parts and assemblies with their specified retirement lives.

Costs of Compliance

    We estimate that this AD will affect 7 helicopters of U.S. Registry 
and estimate, at an average labor rate of $85 per hour, the following 
costs for removing from service the parts listed in Table 2 of this AD:
    <bullet> Reviewing helicopter records to determine if an affected 
part is installed will require approximately 2 work-hours, for a cost 
per helicopter of $170 and a fleet cost of $1,190.
    <bullet> Replacing the rotary rudder spindle assembly will require 
10 work-hours and a parts cost of $2,787, for a cost per helicopter of 
$3,637 and a fleet cost of $25,459.
    <bullet> Replacing the plate will require 40 work-hours and a parts 
cost of $43,750, for a cost per helicopter of $47,150 and a fleet cost 
of $330,050.
    <bullet> Replacing the main servo bracket assembly will require 2 
work-hours and a parts cost of $5,223, for a cost per helicopter of 
$5,393 and a fleet cost of $37,751.
    <bullet> Replacing the primary servo link assembly of the M/R 
tandem servo will require 10 work-hours and a parts cost of $14,533, 
for a cost per helicopter of $15,383 and a fleet cost of $107,681.
    <bullet> Replacing the T/R shoulder bolt will require 10 work-hours 
and a parts cost of $571, for a cost per helicopter of $1,421 and a 
fleet cost of $9,947.
    <bullet> Replacing the T/R Blade Assembly will require 8 work-hours 
and a parts cost of $125,765 for a cost per helicopter of $126,445 and 
a fleet cost of $885,115.
    <bullet> The total cost to replace the parts that are required to 
be removed from service is estimated to be $199,599 per helicopter and 
a fleet cost of $1,397,193.

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.

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.

[[Page 15601]]

    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 removing Amendment 39-10028 (62 FR 
28321, May 23, 1997) and adding the following new airworthiness 
directive (AD):

2012-26-06 ERICKSON AIR-CRANE INCORPORATED: Amendment 39-17301; 
Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD.

(a) Applicability

    This AD applies to Sikorsky Aircraft Corporation-manufactured 
Model S-64F helicopters, now under the Erickson Air-Crane 
Incorporated Model S-64F type certificate, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a fatigue crack in a 
flight critical component. This condition could result in component 
failure from static overload and subsequent loss of control of the 
helicopter.

(c) Other Affected ADs

    This AD supersedes AD 97-10-15, Amendment 39-10028 (62 FR 28321, 
May 23, 1997).

(d) Effective Date

    This AD becomes effective April 16, 2013.

(e) 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.

(f) Required Actions

    (1) Before further flight:
    (i) Remove from service any part with a number of hours time-in-
service (TIS) equal to or greater than the part's retirement life as 
stated in Table 1 to Paragraph (f) of this AD.

                         Table 1 to Paragraph (f)--Parts With New or Revised Life Limits
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                    Part name                        Part No. (P/N)                  Retirement life
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Main Rotor (M/R) Blade Assembly.................        6415-20601-045  13,280 hours TIS.
Main Transmission Support Beam Assembly, LH.....        6420-62363-045  9,300 hours TIS.
Main Transmission Support Beam Assembly, RH.....        6420-62363-046  9,300 hours TIS.
Left Splice Fitting (Transition Fitting),               6420-66341-101  8,300 hours TIS.
 Rotary, Rudder Boom.
Right Splice Fitting (Transition Fitting),              6420-66341-102  8,300 hours TIS.
 Rotary, Rudder Boom.
M/R Drive Shaft.................................        6435-20536-101  2,200 hours TIS.
Pressure Plate Assembly, Rotary Wing Head.......       65101-11016-042  8,800 hours TIS.
Horn and Liner Assembly.........................       65102-11047-041  1,140 hours TIS.
Lower Hub Plate Assembly........................       65103-11009-041  15,500 hours TIS.
Horizontal Hinge Pin, Rotary Wing Head..........       65103-11020-103  5,100 hours TIS.
Damper Bracket Assembly, Rotary Wing Head.......       65103-11032-043  20,000 hours TIS.
Hub Subassembly, Rotary Wing....................       65103-11310-043  21,600 hours TIS.
Shaft Assembly, Pitch Control Tail Gearbox......       65358-07035-043  9,400 hours TIS.
Rod End Assembly, Primary Servo Assembly........       65652-11212-041  20,800 hours TIS.
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    Note 1 to Table 1 to Paragraph (f) of this AD:  The list of 
parts in Table 1 to Paragraph (f) of this AD contains only a portion 
of the life-limited parts for this model helicopter and is not an 
all-inclusive list.

    (ii) Revise the retirement life of each part as shown in Table 1 
to Paragraph (f) of this AD by making pen and ink changes or by 
inserting a copy of this AD into the Airworthiness Limitations 
section of the maintenance manual.
    (iii) Record on the component history card or equivalent record 
the retirement life for each part as shown in Table 1 to Paragraph 
(f) of this AD.
    (2) Before further flight, remove from service any part with a 
P/N listed in Table 2 to Paragraph (f) of this AD, regardless of the 
part's TIS. The P/Ns listed in Table 2 to Paragraph (f) of this AD 
are not eligible for installation on any helicopter.

                           Table 2 to Paragraph (f)--Parts To Be Removed From Service
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                    Part name                                                   P/N
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Spindle Assembly, Rotary Rudder.................  6410-30302-041.
Main Gearbox Second Stage Lower Planetary Plate.  6435-20516-101 or 6435-20516-102.
Bracket Assembly, Main Servo....................  6435-20527-041 or 6435-20527-042.
Primary Servo Link, Tandem Servo, M/R...........  6465-62161-042.
Shoulder Bolt, Tail Rotor (T/R).................  65111-07001-102.
T/R Blade Assembly..............................  65161-00001-041.
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[[Page 15602]]

     (3) Before further flight, if a T/R blade assembly, P/N 65160-
00001-048, is installed, remove any of the other three T/R blade 
assemblies that have a different P/N and replace it with a T/R blade 
assembly, P/N 65160-00001-048. The T/R blade assembly, P/N 65160-
00001-048, must be installed in sets of four only.

(g) 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, FAA, Rotorcraft Directorate, Rotorcraft 
Certification Office, Fort Worth, Texas 76137, telephone (817) 222-
5170, email <a href="/cdn-cgi/l/email-protection#2d1a004c5b5e004c5e5a001c1a1d6d4b4c4c034a425b"><span class="__cf_email__" data-cfemail="a1968cc0d7d28cc0d2d68c909691e1c7c0c08fc6ced7">[email&#160;protected]</span></a>.
    (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.

(h) Additional Information

    Erickson Service Bulletin No. 64F General-1, Revision 17, dated 
August 17, 2010, which is not incorporated by reference, contains 
additional information about the subject of this AD. For service 
information identified in this AD, contact Erickson Air-Crane 
Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow 
Springs Rd, P.O. Box 3247, Central Point, OR 97502, telephone (541) 
664-5544, fax (541) 664-2312, email address 
<a href="/cdn-cgi/l/email-protection#b3d0d6c1dad0d8c0dcddf3d6c1dad0d8c0dcddd2dac1d0c1d2ddd69dd0dcde"><span class="__cf_email__" data-cfemail="2c4f495e454f475f43426c495e454f475f43424d455e4f5e4d4249024f4341">[email&#160;protected]</span></a>. You may review a copy of this 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6300: Main Rotor 
Drive System and 6400: Tail Rotor System.

    Issued in Fort Worth, Texas, on March 1, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-05503 Filed 3-11-13; 8:45 am]
BILLING CODE 4910-13-P