Airworthiness Directives; Sikorsky Aircraft Corporation

[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)]
[Rules and Regulations]
[Pages 34838-34841]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15222]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0664; Directorate Identifier 2016-SW-073-AD; 
Amendment 39-18947; AD 2017-14-03]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for 
Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This 
AD requires an inspection and reduces the retirement lives of certain 
landing gear components. This AD is prompted by a revised analysis of 
the fatigue life of the landing gear. The actions of this AD are 
intended to prevent an unsafe condition on these products.

DATES: This AD becomes effective August 11, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of August 11, 
2017.
    We must receive comments on this AD by September 25, 2017.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
    <bullet> Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0664; 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 (telephone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.
    For service information identified in this final rule, contact 
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry 
Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-416-4299; 
email: [email protected]. You may review the 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0664.

FOR FURTHER INFORMATION CONTACT: Dorie Resnik, Aviation Safety 
Engineer, Boston Aircraft Certification Office, Engine & Propeller 
Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; 
telephone (781) 238-7693; email [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    We are adopting a new AD for Sikorsky Model S-92A helicopters. This 
AD is prompted by Sikorsky's updated fatigue analysis of the nose and 
main landing gear as part of a supplier transition project. The updated 
fatigue

[[Page 34839]]

analysis revealed that certain components--main landing gear (MLG) 
wheel axle part number (P/N) 2392-2334-001, MLG and nose landing gear 
(NLG) threaded hinge pin P/N 2392-2311-003, NLG cylinder P/N 2392-4006-
005, NLG hinge pin P/N 2392-4312-003, and landing gear actuator rod end 
P/N 2392-0876-901--require a reduced service life. Sikorsky updated the 
airworthiness limitations schedule accordingly and developed a 
recurring visual and ultrasonic inspection of NLG airframe fitting 
assembly P/N 92209-01101-041 once it has accumulated 31,600 landing 
cycles.
    Accordingly, this AD requires inspecting and reducing the life 
limits of these landing gear components. The actions specified by this 
AD are intended to detect and prevent cracks or failure of any landing 
gear component, which could result in damage and loss of control of the 
helicopter.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of this same type design.

Related Service Information Under 1 CFR Part 51

    We reviewed Ultrasonic Inspection Technique No. UT 5077, Revision 
0, dated July 25, 2014 (UT 5077). UT 5077 contains the inspection 
method, equipment and materials, calibration, and inspection procedure 
for performing an ultrasonic inspection of nose gear actuator fitting 
P/N 92209-01101-101.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Other Related Service Information

    We also reviewed Sikorsky S-92 Helicopter Alert Service Bulletin 
92-32-004, Basic Issue, dated January 30, 2015 (ASB). The ASB describes 
procedures for conducting a visual inspection of the NLG airframe 
fitting assembly and an ultrasonic inspection by following the 
procedures in UT 5077.

AD Requirements

    This AD requires removing the following components from service:
    <bullet> Any MLG wheel axle P/N 2392-2334-001 that has 22,300 or 
more landing cycles.
    <bullet> Any MLG or NLG threaded hinge pin P/N 2392-2311-003 that 
has 26,100 or more landing cycles.
    <bullet> Any NLG cylinder P/N 2392-4006-005 that has 26,300 or more 
landing cycles.
    <bullet> Any NLG hinge pin P/N 2392-4312-003 that has 26,700 or 
more landing cycles.
    <bullet> Any landing gear actuator rod end P/N 2392-0876-901 that 
has 41,700 or more landing cycles.
    For helicopters that have 31,600 or more landing cycles and an NLG 
airframe fitting assembly P/N 92209-01101-041 installed, this AD also 
requires:
    <bullet> Using a 10X or higher power magnifying glass, inspecting 
each bushing and all visible surfaces of mating lug fittings adjacent 
to each bushing for fretting, corrosion, wear, and scratches.
    <bullet> Replacing the NLG airframe fitting assembly before further 
flight if there is fretting, corrosion, wear, or a scratch more than 
0.0005 inch deep.
    <bullet> Ultrasonic inspecting the NLG actuator fitting and 
replacing the NLG actuator fitting before further flight if there are 
any anomalies.

Differences Between This AD and the Service Information

    The ASB requires a repetitive inspection of the NLG airframe 
fitting assemblies P/N 92209-01101-041 every 1,986 landing cycles; this 
AD does not.

Interim Action

    We consider this AD to be an interim action. We are currently 
considering requiring a repetitive inspection of the NLG airframe 
fitting assemblies P/N 92209-01101-041 that would occur every 1,986 
landing cycles. However, the planned compliance time for the 
inspections would allow enough time to provide notice and opportunity 
for prior public comment on the merits of the repetitive inspections.

Costs of Compliance

    We estimate that this AD will affect 80 helicopters of U.S. 
Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD. At an average labor rate of $85 per hour:
    <bullet> Replacing a wheel axle P/N 2392-2334-001 will require 2 
work-hours and required parts cost $22,000, for a cost per helicopter 
of $22,170.
    <bullet> Replacing a MLG or NLG threaded hinge pin P/N 2392-2311-
003 will require 1 work-hour and required parts cost $3,800, for a cost 
per helicopter of $3,885.
    <bullet> Replacing a NLG cylinder P/N 2392-4006-005 will require 1 
work-hour and required parts cost $27,200, for a cost per helicopter of 
$27,285.
    <bullet> Replacing a NLG hinge pin P/N 2392-4312-003 will require 1 
work-hour and required parts cost $4,400, for a cost per helicopter of 
$4,485.
    <bullet> Replacing a landing gear actuator rod end P/N 2392-0876-
901 will require 1 work-hour and required parts cost $900, for a cost 
per helicopter of $985.
    <bullet> Inspecting the NLG airframe fitting assembly P/N 92209-
01101-041 will require 8 work-hours, and required parts cost is 
minimal, for a cost of $680 per helicopter and $54,400 for the U.S. 
fleet.
    <bullet> If required, replacing a NLG actuator fitting P/N 92209-
01101-101 would require 70 work-hours, and required parts cost $10,000, 
for a cost per helicopter of $15,950.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because replacing the landing gear 
components affected by the life-limit reductions required by this AD 
must be accomplished before further flight.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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.

[[Page 34840]]

Regulatory Findings

    We 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, 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):

2017-14-03 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39-
18947; Docket No. FAA-2017-0664; Directorate Identifier 2016-SW-073-
AD.

(a) Applicability

    This AD applies to Sikorsky Model S-92A helicopters, 
certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as fatigue failure of the 
landing gear. This condition could result in failure of the landing 
gear and subsequent damage to and loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective August 11, 2017.

(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) Before further flight, remove from service any part that has 
accumulated the number of landing cycles listed in Table 1 to 
paragraph (e)(1) of this AD. Thereafter, remove from service any 
part before accumulating the number of landing cycles listed in 
Table 1 to paragraph (e)(1) of this AD. For purposes of this AD, a 
landing cycle is counted anytime the helicopter lifts off into the 
air and then lands again regardless of the duration of the landing 
and regardless of whether the engine is shut down. If the number of 
landing cycles in unknown, multiply the number of hours time-in-
service by 4.5 to determine the number of landing cycles.

                                     Table 1 to Paragraph (e)(1) of This AD
----------------------------------------------------------------------------------------------------------------
                   Part name                        Part number                      Life limit
----------------------------------------------------------------------------------------------------------------
Main landing gear (MLG) wheel axle.............      2392-2334-001  22,300 landing cycles.
MLG or nose landing gear (NLG) threaded hinge        2392-2311-003  26,100 landing cycles.
 pin.
NLG cylinder...................................      2392-4006-005  26,300 landing cycles.
NLG hinge pin..................................      2392-4312-003  26,700 landing cycles.
Landing gear actuator rod end..................      2392-0876-901  41,700 landing cycles.
----------------------------------------------------------------------------------------------------------------

    (2) For helicopters with 31,600 or more landing cycles and an 
NLG airframe fitting assembly P/N 92209-01101-041 installed, before 
further flight:
    (i) Using a 10X or higher power magnifying glass, inspect each 
bushing (P/N 92209-01101-102 and P/N 92209-01101-103) and all 
visible surfaces of mating lug fittings adjacent to each bushing for 
fretting, corrosion, wear, and scratches. If there is fretting, 
corrosion, wear, or a scratch more than 0.0005 inch deep, replace 
the NLG airframe fitting assembly before further flight.
    (ii) Ultrasonic inspect each NLG actuator fitting P/N 92209-
01101-101 in accordance with Sikorsky Ultrasonic Inspection 
Technique No. UT 5077, Revision 0, dated July 25, 2014 (UT 5077), 
except you are not required to report to or contact Sikorsky. If 
there are any anomalies or suspect indications, replace the NLG 
actuator fitting before further flight.

    Note 1 to paragraph (e)(2)(ii) of this AD: A copy of UT 5077 is 
attached to Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-
004, Basic Issue, dated January 30, 2015.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Boston Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Dorie Resnik, 
Aviation Safety Engineer, Boston Aircraft Certification Office, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, 
Massachusetts 01803; telephone (781) 238-7693; 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

    Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic 
Issue, dated January 30, 2015, which is not incorporated by 
reference, contains additional information about the subject of this 
AD. 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: 
[email protected]. You may review this service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 3200 Main Landing 
Gear and 3220 Nose Landing Gear.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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) Ultrasonic Inspection Technique No. UT 5077, Revision 0, 
dated July 25, 2014.

    Note 2 to paragraph (i)(2)(i): Ultrasonic Inspection Technique 
No. UT 5077, Revision 0, dated July 25, 2014, is an attachment to 
Sikorsky S-92 Helicopter Alert Service Bulletin 92-32-004, Basic 
Issue, dated

[[Page 34841]]

January 30, 2015, which is not incorporated by reference.

    (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: [email protected].
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. 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 June 27, 2017.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2017-15222 Filed 7-26-17; 8:45 am]
BILLING CODE 4910-13-P

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