(a) APPLICABILITY
This AD applies to Model S-70, S-70A, and S-70C helicopters,
certificated in any category, with the following parts installed:
(1) Spindle and liner assembly, part number (P/N) 38023-10374-041;
(2) Main Rotor Hub, P/N 70070-10046-055 and -056;
(3) Main Rotor Spindle nut, P/N 70102-08105-102;
(4) Main Rotor Control Horn, P/N 70102-08111-047;
(5) Main Rotor Hub, P/N 70103-08112-041 and -047;
(6) Rotating Swashplate, P/N 70104-08001-044 and -045;
(7) Main Rotor Shaft Extension, P/N 70351-08186-043;
(8) Main Rotor Gear Box Housing, P/N 70351-38110-043, -044, and -045;
(9) Main Rotor Shaft, P/N 70351-38131-042;
(10) Output Bevel Gear and Shaft, P/N 70358-06620-101 and -102;
(11) Left Tie Rod Assembly, P/N 70400-08115-043, -045, -046, and -047;
(12) Forward Bellcrank Support Assembly, P/N 70400-08162-042;
(13) Lateral Servo Bellcrank, P/N 70400-08166-041; or
(14) Tail Rotor Servo Assembly, P/N 70410-06520-044 through -046.
(b) UNSAFE CONDITION
This AD defines the unsafe condition as a critical part remaining in
service beyond its life limit due to previously being installed on a
different helicopter model with higher usage and flight loads. This
condition could result in fatigue failure of a critical part and
subsequent loss of control of the helicopter.
(c) EFFECTIVE DATE
This AD becomes effective February 25, 2014.
(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 25 hours time-in-service (TIS):
(i) Insert into the airworthiness limitation section of the maintenance
manual or instructions for continued airworthiness the component life
prorating formula in Section 1.1.3, Component Life Prorating, pages 1
-25 and 1-26, of Sikorsky Technical Manual TM 1-70-23AW-2, Change 3,
dated April 15, 2012.
(ii) Using the service life limits in Table 1 to Paragraph (e) of this AD,
apply the component life prorating formula and calculate the new life
limit for each specified part. If the number of hours of a part is
unknown, that part cannot be installed on a Sikorsky Model S-70, S
-70A, or S-70C helicopter. Do not calculate a new life limit for the
part where the Model SH-60 life limit is higher than the life limit
on Models S-70, S-70A, and S-70C.
TABLE 1 TO PARAGRAPH (E)
__________________________________________________________________________
S-70,
S-70A,
S-70C UH-60M SH-60B/F
PART SERVICE SERVICE SERVICE
P/N DESCRIPTION LIFE LIFE LIFE
__________________________________________________________________________
38023-10374-041 Spindle and Liner 8,000 6,400 10,000
Assembly
70070-10046-055 Main Rotor Hub 5,100 3,100 ¹N/A
and -056
70102-08105-102 Main Rotor 8,000 6,400 10,000
Spindle Nut
70102-08111-047 Main Rotor 20,000/1,300² 10,000 ¹N/A
Control Horn 2,500²
70103-08112-041 Main Rotor Hub 5,100 3,100 ¹N/A
and -047
70104-08001-044-045 Rotating 11,000 4,600 9,600
Swashplate
70351-08186-043 Main Rotor Shaft 14,000 4,900 16,000
Extension
70351-38110-043, Main Rotor Gear 11,000 4,000 9,000
-044, and -045 Box Housing
70351-38131-042 Main Rotor Shaft 17,000 5,200 19,000
70358-06620-101 Output Bevel Gear 5,000 1,800 ¹N/A
and -102 and Shaft
70400-08115-043, Left Tie Rod 14,000 4,600 6,300
-045, -046, and Assembly
-047
70400-08162-042 Forward Bellcrank 14,000/2,500³ 5,600 7,600
Support Assembly
70400-08166-041 Lateral Servo 20,000 11,000 14,000
Bellcrank
70410-06520-044 Tail Rotor Servo 15,000 11,000 ¹N/A
through -046 Assembly
__________________________________________________________________________
¹There is no service life limit listed because the parts on Model SH-60B/F
have a different P/N than the parts on Models S-70, S-70A, and S-70C.
²For serial number (S/N) 32479930 through 324791859, with CAGE code
60078, the life limit is 1,300 hours TIS. For S/N A241-07543 through A241
-07594, A241-07706 through A241-07755, A241-07768 through A241-07771,
A241-07800 through A241-07831, R241-00101 through R241-00355, R241-00701
through R241-00966, and R241-01001 through R241-01166, the life limit is
2,500 hours TIS.
³For S/N A-367-00001 through A367-00035, with CAGE code 78286, the life
limit is 2,500 hours TIS.
(iii) Record the newly-established life limit of each part on the part's
component log card or equivalent record.
(2) After establishing the new life limit, replace each part that has
reached or exceeded its new life limit with an airworthy part before
further flight.
(3) Do not install the following parts on a Model S-70, S-70A, or S-70C
helicopter if they have been previously installed on a Model UH-60M
helicopter:
(i) Bolt, self retaining, P/N 70103-08801-102;
(ii) Bifilar, P/N 70107-08400-046;
(iii) Aft Bellcrank, P/N 70400-08102-045;
(iv) Aft Walking Beam Assembly, P/N 70400-08104-048; or
(v) Close Tolerance Bolt, P/N 70400-26802-102 and -103.
(f) ALTERNATIVE METHODS OF COMPLIANCE (AMOC)
(1) The Manager, Boston Aircraft Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to: Michael Davison, Flight Test
Engineer, Boston Aircraft Certification Office, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, Massachusetts
01803; telephone (781) 238-7156; email michael.davison@faa.gov.
(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) SUBJECT
Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor Hub,
6230 Main Rotor Mast/Swashplate, 6320 Main Rotor Gearbox, 6310
Engine/Transmission Coupling, 6510 Tail Rotor Drive Shaft.
(h) 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) Pages 1-25 and 1-26, Section 1.1.3, Component Life Prorating, of
Sikorsky Technical Manual TM 1-70-23AW-2, Change 3, dated April 15,
2012.
(ii) Reserved.
(3) For Sikorsky service information identified in this AD, contact
Sikorsky Aircraft Corporation, Customer Service Engineering, 124
Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-
4299; email sikorskywcs@sikorsky.com.
(4) You may view this service information at FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137. For information on the availability of this material at
the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated by
reference 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 December 5, 2013. Kim Smith, Directorate
Manager, Rotorcraft Directorate, Aircraft Certification Service.
FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer,
Boston Aircraft Certification Office, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, Massachusetts 01803; telephone
(781) 238-7156; email michael.davison@faa.gov.
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AGENCY: Federal Aviation Administration
(FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new airworthiness directive (AD) for
Sikorsky Model S-70, S-70A, and S-70C helicopters. This AD establishes
a new life limit based on a prorated formula for certain identified
components (parts) installed on Model S-70, S-70A, and S-70C
helicopters after being previously installed on certain military model
helicopters. This AD was prompted by the discovery that certain parts
have been interchanged between military helicopter models with
different life limits and the possibility that these same parts can be
interchanged with civilian models with different life limits. The
actions are intended to establish a pro-rated in service life limit for
each identified part to prevent fatigue failure of a part and
subsequent loss of control of the helicopter.
DATES: This AD is effective February 25, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of February 25,
2014.
ADDRESSES: For service information identified in this AD, contact
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry
Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299;
email sikorskywcs@sikorsky.com. 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, 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 Davison, Flight Test Engineer,
Boston Aircraft Certification Office, Engine & Propeller Directorate,
12 New England Executive Park, Burlington, Massachusetts 01803;
telephone (781) 238-7156; email michael.davison@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 23, 2013, at 78 FR 44045, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Sikorsky Model S-70, S-
70A, and S-70C helicopters. The NPRM proposed inserting the component
life prorating formula into the airworthiness limitation section of the
maintenance manual or instructions for continued airworthiness,
calculating the new life limit for each part by applying the formula,
and establishing life limits for certain parts without applying the
formula. Furthermore, the NPRM proposed updating the component log or
equivalent record with the new in-service life limit and replacing each
part that has reached or exceeded its new life limit with an airworthy
part. Lastly, the NPRM proposed prohibiting installation of any
applicable part on a Model S-70, S-70A, or S-70C helicopter if the
number of hours is unknown or if certain parts have been previously
installed on a Model UH-60M helicopter. The NPRM was prompted by the
discovery that certain parts with identical part numbers but different
life limits have been interchanged between military helicopter models
and the possibility that these same parts can be interchanged with
civilian models with different life limits.
The proposed requirements were intended to establish a pro-rated in
service life limit for each identified part to prevent fatigue failure
of a part 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 (78 FR 44045,
July 23, 2013).
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.
Costs of Compliance
We estimate that this AD affects 9 helicopters of U.S. Registry.
We estimate that the cost to insert pages into the aircraft's
airworthiness limitation section is negligible.
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.
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.
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
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]
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
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