Airworthiness Directives; Sikorsky Aircraft Corporation, 12799-12802 [2016-05258]

Download as PDF Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations (i) Piper Aircraft, Inc. Service Bulletin No. 1273A, dated October 22, 2015. (ii) Reserved. (3) For Piper Aircraft, Inc. service information identified in this AD, contact Piper Aircraft, Inc. 2926 Piper Drive, Vero Beach, FL 32960; telephone: (415) 330–9500; email: sales@atp.com; and Internet: https:// www.piper.com/technical-publications/. (4) You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Kansas City, Missouri, on February 24, 2016. Robert P. Busto, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–04417 Filed 3–10–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–4280; Directorate Identifier 2016–SW–008–AD; Amendment 39–18429; AD 2016–05–11] RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S–92A helicopters. This AD requires certain inspections of the main rotor and tail rotor control pushrods (pushrods). This AD is prompted by a Sikorsky investigation that indicated that some pushrods may have incorrectly installed locking mechanisms. These AD actions are intended to detect an incorrectly installed locking mechanism, which if not corrected, could result in a loose jam nut, failure of the pushrod, loss of main rotor or tail rotor flight control, and consequent loss of helicopter control. asabaliauskas on DSK3SPTVN1PROD with RULES SUMMARY: This AD becomes effective March 28, 2016. DATES: VerDate Sep<11>2014 15:58 Mar 10, 2016 Jkt 238001 The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of March 28, 2016. We must receive comments on this AD by May 10, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • 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. • 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 4280; 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 1–800Winged-S or 203–416–4299; email sikorskywcs@sikorsky.com. 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 4280. FOR FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238–7161; email blaine.williams@ faa.gov. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 12799 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 propose to adopt a new AD for Sikorsky Model S–92A helicopters with certain main rotor or tail rotor control pushrods installed. After a review of a failed pushrod, Sikorsky investigated the airworthiness of pushrods installed on its helicopters. The investigation indicates that the pushrods installed on Model S–92A helicopters may have incorrect safety cable routing, incorrect jam nut torque, and/or incorrect locking device serrations and key engagement. This AD consequently requires inspecting the pushrods for safety cable routing, engagement of serrations of the locking device, engagement of keys on the locking device, thread engagement, and jam nut torque. This AD requires either repairing or replacing the pushrod assembly, depending on the inspection’s outcome. These AD actions are intended to detect and correct an incorrectly installed locking mechanism resulting in a loose jam nut, failure of the pushrods, loss of main rotor or tail rotor flight control, and consequent loss of helicopter control. 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 these same type designs. E:\FR\FM\11MRR1.SGM 11MRR1 12800 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations asabaliauskas on DSK3SPTVN1PROD with RULES Related Service Information Under 1 CFR Part 51 We reviewed Sikorsky S–92 Helicopter Alert Service Bulletin ASB 92–67–006, Revision A, dated February 19, 2016 (ASB), which specifies a onetime inspection of the pushrod assemblies for safety cable routing, engagement of serrations of the locking device, engagement of keys on the locking device, thread engagement, and torque of the jam nuts. The ASB also specifies documenting any noncompliant inspection results and, if any discrepancies are found during the inspection, removing, reworking, and reinstalling or replacing the pushrod. The ASB specifies performing a rig check as required. 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. AD Requirements This AD requires within 5 hours timein-service (TIS): • For each pushrod adjustable end, except for the upper deck quadrant pushrod, removing the safety cable and using finger pressure, inspecting each jam nut for movement. If a jam nut moves with finger pressure, removing the pushrod assembly from service. Æ Inspecting to determine whether a 0.02 inch diameter safety wire can pass through the inspection hole. If the safety wire passes through the inspection hole, repairing the pushrod, which is terminating action for that adjustable end. Æ Inspecting for correct engagement of serrations and keys of the locking device. If a locking device is not correctly engaged, repairing the locking device, which is terminating action for that adjustable end. Æ Torqueing each jam nut and installing the safety cable, making sure the right-hand threads have safety cable correctly routed, and the left-hand threads have safety cable correctly routed. • For the upper deck quadrant pushrod, this AD requires determining whether there is any gap between the jam nut, locking device, and the adjustable end. It also requires: Æ If there is a gap, gaining access to the pushrod, removing the safety cable and using finger pressure, inspecting the jam nut for movement. If the jam nut moves with finger pressure, removing the pushrod assembly from service. If the jam nut does not move, performing corrective actions. Æ If there is no gap, visually inspecting the adjustable end for correct VerDate Sep<11>2014 15:58 Mar 10, 2016 Jkt 238001 safety cable routing, correct engagement of serrations and keys of the locking device, and determining whether any thread is visible in the inspection hole. If the safety cable is routed incorrectly, if the locking device is not correctly engaged, or if there is no thread in the inspection hole, gaining access to the pushrod. Using finger pressure, inspecting the jam nut for movement. If the jam nut moves with finger pressure, removing the pushrod assembly from service. If the jam nut does not move with finger pressure, performing corrective actions. Differences Between This AD and the Service Information Sikorsky specifies compliance by May 16, 2016. We require compliance within 5 hours TIS. We also do not require you to contact Sikorsky or record information on the Pushrod Data Sheet. Costs of Compliance We estimate that this AD will affect 80 helicopters of U.S. Registry and labor costs average $85 per work-hour. Based on these estimates, we expect the following costs: • Inspecting all pushrod assemblies requires 2 work-hours for a labor cost of $170. No parts are needed for a total fleet cost of $13,600. • Replacing a pushrod requires 2 work-hours for a labor cost $170. Parts cost an average of $2,500 for a total cost of $2,670 per pushrod. • Repairing a pushrod requires an average 2 work-hours per helicopter for a labor cost of $170 and minimal part costs. 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 the required corrective actions must be accomplished within 5 hours TIS. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for prior public comment before issuing this AD are impracticable and contrary to the public interest and that good cause exists to make this AD 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, PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\11MRR1.SGM 11MRR1 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations § 39.13 Docket No. FAA–2016–4280; Directorate Identifier 2016–SW–008–AD. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2016–05–11 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39–18429; (a) Applicability 12801 input pushrod with a part number (P/N) listed in Table 1 to paragraph (a) of this AD, certificated in any category. This AD applies to Sikorsky Model S–92A helicopters, serial numbers 920006 through 920291, with a main rotor or tail rotor servo TABLE 1 TO PARAGRAPH (a) Name P/N Yaw Boost Input Pushrod ...................................................................................................................... Pitch Boost Input Pushrod ..................................................................................................................... Collective Boost Input Pushrod ............................................................................................................. Roll Boost Input Pushrod ....................................................................................................................... Yaw Boost Out Pushrod ........................................................................................................................ Roll Boost Out Pushrod ......................................................................................................................... Pitch Boost Out Pushrod ....................................................................................................................... Collective Boost Out Pushrod ............................................................................................................... Limiter Pushrod ...................................................................................................................................... Pitch to Roll Pushrod ............................................................................................................................. Left Hand Main Rotor Servo Pushrod ................................................................................................... Forward Main Rotor Servo Pushrod ...................................................................................................... Right Hand Main Rotor Servo Pushrod ................................................................................................. Upper Deck Quadrant Pushrod ............................................................................................................. Tail Rotor Servo Input Pushrod ............................................................................................................. 92400–04801–108 92400–04801–107 92400–04801–107 92400–04801–109 92400–04802–109 92400–04803–103 92400–04803–102 92400–04802–108 92400–04803–106 92400–04803–107 92400–04801–110 92400–04801–111 92400–04801–112 92400–04802–105 92400–04802–107 (b) Unsafe Condition This AD defines the unsafe condition as an incorrectly installed locking mechanism resulting in a loose jam nut. This condition, if not detected and corrected, could result in failure of the main rotor or tail rotor control pushrod, loss of main rotor or tail rotor flight control and consequent loss of helicopter control. (c) Effective Date This AD becomes effective March 28, 2016. (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. asabaliauskas on DSK3SPTVN1PROD with RULES (e) Required Actions Within 5 hours time-in-service: (1) For each control input pushrod (pushrod) adjustable end, except for the upper deck quadrant pushrod: (i) Remove the safety cable and using finger pressure, inspect each jam nut for movement. If a jam nut moves with finger pressure, remove the pushrod assembly from service. (ii) Inspect to determine whether a 0.02 inch diameter safety wire can pass through the inspection hole. If the safety wire passes through the inspection hole, repair the pushrod in accordance with the Accomplishment Instructions, paragraphs C.(2)(b) through C.(2)(l) of Sikorsky S–92 Helicopter Alert Service Bulletin ASB 92– 67–006, Revision A, dated February 19, 2016 (ASB), which is terminating action for that adjustable end. (iii) Where locking devices are used, inspect for correct engagement of serrations and keys of the locking device as shown in Figure 4 of the ASB. If a locking device is not correctly engaged, repair the locking device in accordance with the Accomplishment Instructions, paragraphs C.(3)(c) through VerDate Sep<11>2014 15:58 Mar 10, 2016 Jkt 238001 C.(3)(f) of the ASB, which is terminating action for that adjustable end. (iv) Torque each jam nut using the torque values listed in Table 1 to paragraph (a) of this AD. Install the safety cable, making sure the right-hand threads have safety cable routed as shown in Figure 2 of the ASB, and the left-hand threads have safety cable routed as shown in Figure 3 of the ASB. (2) For the upper deck quadrant pushrod, determine whether there is any gap between the jam nut, locking device, and adjustable end. (i) If there is a gap, gain access to the pushrod, remove the safety cable, and using finger pressure, inspect the jam nut for movement. If the jam nut moves with finger pressure, remove the pushrod assembly from service. If the jam nut does not move, perform the actions in paragraphs (e)(1)(ii) through (e)(1)(iv) of this AD. (ii) If there is no gap, visually inspect the adjustable end for correct safety cable routing as shown in Figure 2 of the ASB, correct engagement of serrations and keys of the locking device as shown in Figure 4 of the ASB, and to determine whether any thread is visible in the inspection hole. If the safety cable is routed incorrectly, if the locking device is not correctly engaged, or if there is no thread in the inspection hole, gain access to the pushrod. Using finger pressure, inspect the jam nut for movement. If the jam nut moves with finger pressure, remove the pushrod assembly from service. If the jam nut does not move with finger pressure, perform the actions in paragraphs (e)(1)(ii) through (e)(1)(iv) of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Blaine Williams, Aerospace Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 1200 District Avenue, PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Torque value 60–100 inch pounds. 43 inch pounds. 350 inch pounds. 43 inch pounds. 40–46 inch pounds. 40–46 inch pounds. 40–46 inch pounds. 40–46 inch pounds. 40–46 inch pounds. 40–46 inch pounds. 350 inch pounds. 350 inch pounds. 350 inch pounds. 60–100 inch pounds. 40–46 inch pounds. Burlington, Massachusetts 01803; telephone (781) 238–7161; email blaine.williams@ 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: 6700, Rotorcraft Flight Control. (h) 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) Sikorsky S–92 Helicopter Alert Service Bulletin ASB 92–67–006, Revision A, dated February 19, 2016. (ii) Reserved. (3) For Sikorsky 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 sikorskywcs@sikorsky.com. (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 E:\FR\FM\11MRR1.SGM 11MRR1 12802 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on March 2, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–05258 Filed 3–10–16; 8:45 am] BILLING CODE 4910–13–P Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3658; Directorate Identifier 2014–SW–039–AD; Amendment 39–18427; AD 2016–05–09] RIN 2120–AA64 Airworthiness Directives; MD Helicopters, Inc. (MDHI) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain MDHI Model 369A (Army OH–6A), 369H, 369HE, 369HM, 369HS, 369D, 369E, 369F, 369FF, and 500N helicopters. This AD requires inspecting the auxiliary fuel pump (fuel pump) wire routing in the left-hand fuel cell and corrective action, if necessary. This AD also requires installing a warning decal on the left-hand fuel cell access cover. This AD was prompted by accidents resulting from incorrectly positioned fuel pump wiring within the fuel tank interfering with the operation of the fuel quantity sensor float, which caused an erroneous fuel quantity indication in the cockpit. The actions are intended to detect and correct routing of the fuel pump wiring to prevent interference with the fuel quantity sensor float, an erroneous fuel quantity indication in the cockpit, and subsequent fuel exhaustion and emergency landing. DATES: This AD is effective April 15, 2016. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of April 15, 2016. ADDRESSES: For service information identified in this final rule, contact MD Helicopters, Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, AZ 85215– 9734; telephone 1–800–388–3378; fax 480–346–6813; or at https:// www.mdhelicopters.com. You may asabaliauskas on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 15:58 Mar 10, 2016 review a copy of 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3658. Jkt 238001 You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3658; 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-byreference 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: Danny Nguyen, Aerospace Engineer, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone (562) 627– 5247; email danny.nguyen@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On September 2, 2015, at 80 FR 53030, 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 certain MDHI Model 369A (Army OH–6A), 369H, 369HE, 369HM, 369HS, 369D, 369E, 369F, 369FF, and 500N helicopters. The NPRM proposed to require inspecting the routing of the fuel pump wiring to determine whether the fuel pump wire is properly wrapped around the fuel inlet hose and correcting the routing of the wiring if it is not. The NPRM also proposed to require installing a decal regarding correct installation of the fuel pump wiring. The NPRM was prompted by two accidents and one incident that occurred on Model 369D helicopters resulting from an incorrectly positioned fuel pump wire within the fuel tank interfering with the operation of the fuel quantity sensor float, which caused an erroneous fuel quantity reading in the cockpit. Because the fuel pump is installed on all the affected model helicopters, we are including them in PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 the applicability. According to MDHI, because maintenance personnel caused the incorrect wire routing by failing to follow procedures for installing the fuel pump, it is also necessary to install a decal on the left-hand fuel cell access cover to refer maintenance personnel to the appropriate manual procedures. The proposed requirements were intended to detect and correct routing of the fuel pump wiring to prevent interference with the fuel quantity sensor float, an erroneous fuel quantity indication in the cockpit, and subsequent fuel exhaustion and emergency landing. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (80 FR 53030, September 2, 2015). 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 the same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Related Service Information Under 1 CFR Part 51 MD Helicopters issued one service bulletin on April 30, 2014, with five different numbers: SB369H–255, SB369E–111, SB500N–049, SB369D– 213, and SB369F–098. The service bulletin specifies a one-time inspection of the routing of the fuel pump wire in the left-hand fuel cell and corrective action, if necessary. The service bulletin also specifies installing a warning decal on the left-hand fuel cell access cover that refers personnel to the procedures for routing the fuel pump wire that is contained in the appropriate maintenance manual. The service bulletin states that recent field incidents have occurred where maintenance personnel have not followed the procedures for installation of the fuel pump. Also, the service bulletin states that an incorrectly installed fuel pump wire can interfere with the fuel quantity sensor float, which can result in erroneous fuel quantity indications. To prevent this situation, the service information states that the fuel pump wire must be wrapped around the fuel inlet hose as shown in the applicable maintenance manual. 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. E:\FR\FM\11MRR1.SGM 11MRR1

Agencies

[Federal Register Volume 81, Number 48 (Friday, March 11, 2016)]
[Rules and Regulations]
[Pages 12799-12802]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-05258]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4280; Directorate Identifier 2016-SW-008-AD; 
Amendment 39-18429; AD 2016-05-11]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This 
AD requires certain inspections of the main rotor and tail rotor 
control pushrods (pushrods). This AD is prompted by a Sikorsky 
investigation that indicated that some pushrods may have incorrectly 
installed locking mechanisms. These AD actions are intended to detect 
an incorrectly installed locking mechanism, which if not corrected, 
could result in a loose jam nut, failure of the pushrod, loss of main 
rotor or tail rotor flight control, and consequent loss of helicopter 
control.

DATES: This AD becomes effective March 28, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of March 28, 2016.
    We must receive comments on this AD by May 10, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     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.
     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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
4280; 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 sikorskywcs@sikorsky.com. 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 https://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-4280.

FOR FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer, 
Boston Aircraft Certification Office, Engine & Propeller Directorate, 
1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 
238-7161; email blaine.williams@faa.gov.

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 propose to adopt a new AD for Sikorsky Model S-92A helicopters 
with certain main rotor or tail rotor control pushrods installed. After 
a review of a failed pushrod, Sikorsky investigated the airworthiness 
of pushrods installed on its helicopters. The investigation indicates 
that the pushrods installed on Model S-92A helicopters may have 
incorrect safety cable routing, incorrect jam nut torque, and/or 
incorrect locking device serrations and key engagement. This AD 
consequently requires inspecting the pushrods for safety cable routing, 
engagement of serrations of the locking device, engagement of keys on 
the locking device, thread engagement, and jam nut torque. This AD 
requires either repairing or replacing the pushrod assembly, depending 
on the inspection's outcome. These AD actions are intended to detect 
and correct an incorrectly installed locking mechanism resulting in a 
loose jam nut, failure of the pushrods, loss of main rotor or tail 
rotor flight control, and consequent loss of helicopter control.

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 these same type 
designs.

[[Page 12800]]

Related Service Information Under 1 CFR Part 51

    We reviewed Sikorsky S-92 Helicopter Alert Service Bulletin ASB 92-
67-006, Revision A, dated February 19, 2016 (ASB), which specifies a 
one-time inspection of the pushrod assemblies for safety cable routing, 
engagement of serrations of the locking device, engagement of keys on 
the locking device, thread engagement, and torque of the jam nuts. The 
ASB also specifies documenting any non-compliant inspection results 
and, if any discrepancies are found during the inspection, removing, 
reworking, and reinstalling or replacing the pushrod. The ASB specifies 
performing a rig check as required.
    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.

AD Requirements

    This AD requires within 5 hours time-in-service (TIS):
     For each pushrod adjustable end, except for the upper deck 
quadrant pushrod, removing the safety cable and using finger pressure, 
inspecting each jam nut for movement. If a jam nut moves with finger 
pressure, removing the pushrod assembly from service.
    [cir] Inspecting to determine whether a 0.02 inch diameter safety 
wire can pass through the inspection hole. If the safety wire passes 
through the inspection hole, repairing the pushrod, which is 
terminating action for that adjustable end.
    [cir] Inspecting for correct engagement of serrations and keys of 
the locking device. If a locking device is not correctly engaged, 
repairing the locking device, which is terminating action for that 
adjustable end.
    [cir] Torqueing each jam nut and installing the safety cable, 
making sure the right-hand threads have safety cable correctly routed, 
and the left-hand threads have safety cable correctly routed.
     For the upper deck quadrant pushrod, this AD requires 
determining whether there is any gap between the jam nut, locking 
device, and the adjustable end. It also requires:
    [cir] If there is a gap, gaining access to the pushrod, removing 
the safety cable and using finger pressure, inspecting the jam nut for 
movement. If the jam nut moves with finger pressure, removing the 
pushrod assembly from service. If the jam nut does not move, performing 
corrective actions.
    [cir] If there is no gap, visually inspecting the adjustable end 
for correct safety cable routing, correct engagement of serrations and 
keys of the locking device, and determining whether any thread is 
visible in the inspection hole. If the safety cable is routed 
incorrectly, if the locking device is not correctly engaged, or if 
there is no thread in the inspection hole, gaining access to the 
pushrod. Using finger pressure, inspecting the jam nut for movement. If 
the jam nut moves with finger pressure, removing the pushrod assembly 
from service. If the jam nut does not move with finger pressure, 
performing corrective actions.

Differences Between This AD and the Service Information

    Sikorsky specifies compliance by May 16, 2016. We require 
compliance within 5 hours TIS. We also do not require you to contact 
Sikorsky or record information on the Pushrod Data Sheet.

Costs of Compliance

    We estimate that this AD will affect 80 helicopters of U.S. 
Registry and labor costs average $85 per work-hour. Based on these 
estimates, we expect the following costs:
     Inspecting all pushrod assemblies requires 2 work-hours 
for a labor cost of $170. No parts are needed for a total fleet cost of 
$13,600.
     Replacing a pushrod requires 2 work-hours for a labor cost 
$170. Parts cost an average of $2,500 for a total cost of $2,670 per 
pushrod.
     Repairing a pushrod requires an average 2 work-hours per 
helicopter for a labor cost of $170 and minimal part costs.

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 the required corrective 
actions must be accomplished within 5 hours TIS.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
prior public comment before issuing this AD are impracticable and 
contrary to the public interest and that good cause exists to make this 
AD 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.

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.

[[Page 12801]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-05-11 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39-
18429; Docket No. FAA-2016-4280; Directorate Identifier 2016-SW-008-
AD.

(a) Applicability

    This AD applies to Sikorsky Model S-92A helicopters, serial 
numbers 920006 through 920291, with a main rotor or tail rotor servo 
input pushrod with a part number (P/N) listed in Table 1 to 
paragraph (a) of this AD, certificated in any category.

                                            Table 1 to Paragraph (a)
----------------------------------------------------------------------------------------------------------------
                      Name                              P/N                         Torque value
----------------------------------------------------------------------------------------------------------------
Yaw Boost Input Pushrod........................    92400-04801-108  60-100 inch pounds.
Pitch Boost Input Pushrod......................    92400-04801-107  43 inch pounds.
Collective Boost Input Pushrod.................    92400-04801-107  350 inch pounds.
Roll Boost Input Pushrod.......................    92400-04801-109  43 inch pounds.
Yaw Boost Out Pushrod..........................    92400-04802-109  40-46 inch pounds.
Roll Boost Out Pushrod.........................    92400-04803-103  40-46 inch pounds.
Pitch Boost Out Pushrod........................    92400-04803-102  40-46 inch pounds.
Collective Boost Out Pushrod...................    92400-04802-108  40-46 inch pounds.
Limiter Pushrod................................    92400-04803-106  40-46 inch pounds.
Pitch to Roll Pushrod..........................    92400-04803-107  40-46 inch pounds.
Left Hand Main Rotor Servo Pushrod.............    92400-04801-110  350 inch pounds.
Forward Main Rotor Servo Pushrod...............    92400-04801-111  350 inch pounds.
Right Hand Main Rotor Servo Pushrod............    92400-04801-112  350 inch pounds.
Upper Deck Quadrant Pushrod....................    92400-04802-105  60-100 inch pounds.
Tail Rotor Servo Input Pushrod.................    92400-04802-107  40-46 inch pounds.
----------------------------------------------------------------------------------------------------------------

(b) Unsafe Condition

    This AD defines the unsafe condition as an incorrectly installed 
locking mechanism resulting in a loose jam nut. This condition, if 
not detected and corrected, could result in failure of the main 
rotor or tail rotor control pushrod, loss of main rotor or tail 
rotor flight control and consequent loss of helicopter control.

(c) Effective Date

    This AD becomes effective March 28, 2016.

 (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

    Within 5 hours time-in-service:
    (1) For each control input pushrod (pushrod) adjustable end, 
except for the upper deck quadrant pushrod:
    (i) Remove the safety cable and using finger pressure, inspect 
each jam nut for movement. If a jam nut moves with finger pressure, 
remove the pushrod assembly from service.
    (ii) Inspect to determine whether a 0.02 inch diameter safety 
wire can pass through the inspection hole. If the safety wire passes 
through the inspection hole, repair the pushrod in accordance with 
the Accomplishment Instructions, paragraphs C.(2)(b) through 
C.(2)(l) of Sikorsky S-92 Helicopter Alert Service Bulletin ASB 92-
67-006, Revision A, dated February 19, 2016 (ASB), which is 
terminating action for that adjustable end.
    (iii) Where locking devices are used, inspect for correct 
engagement of serrations and keys of the locking device as shown in 
Figure 4 of the ASB. If a locking device is not correctly engaged, 
repair the locking device in accordance with the Accomplishment 
Instructions, paragraphs C.(3)(c) through C.(3)(f) of the ASB, which 
is terminating action for that adjustable end.
    (iv) Torque each jam nut using the torque values listed in Table 
1 to paragraph (a) of this AD. Install the safety cable, making sure 
the right-hand threads have safety cable routed as shown in Figure 2 
of the ASB, and the left-hand threads have safety cable routed as 
shown in Figure 3 of the ASB.
    (2) For the upper deck quadrant pushrod, determine whether there 
is any gap between the jam nut, locking device, and adjustable end.
    (i) If there is a gap, gain access to the pushrod, remove the 
safety cable, and using finger pressure, inspect the jam nut for 
movement. If the jam nut moves with finger pressure, remove the 
pushrod assembly from service. If the jam nut does not move, perform 
the actions in paragraphs (e)(1)(ii) through (e)(1)(iv) of this AD.
    (ii) If there is no gap, visually inspect the adjustable end for 
correct safety cable routing as shown in Figure 2 of the ASB, 
correct engagement of serrations and keys of the locking device as 
shown in Figure 4 of the ASB, and to determine whether any thread is 
visible in the inspection hole. If the safety cable is routed 
incorrectly, if the locking device is not correctly engaged, or if 
there is no thread in the inspection hole, gain access to the 
pushrod. Using finger pressure, inspect the jam nut for movement. If 
the jam nut moves with finger pressure, remove the pushrod assembly 
from service. If the jam nut does not move with finger pressure, 
perform the actions in paragraphs (e)(1)(ii) through (e)(1)(iv) of 
this AD.

 (f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Boston Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Blaine Williams, 
Aerospace Engineer, Boston Aircraft Certification Office, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, 
Massachusetts 01803; telephone (781) 238-7161; email 
blaine.williams@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: 6700, Rotorcraft 
Flight Control.

 (h) 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) Sikorsky S-92 Helicopter Alert Service Bulletin ASB 92-67-
006, Revision A, dated February 19, 2016.
    (ii) Reserved.
    (3) For Sikorsky 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 sikorskywcs@sikorsky.com.
    (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

[[Page 12802]]

(202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on March 2, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-05258 Filed 3-10-16; 8:45 am]
 BILLING CODE 4910-13-P
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