12796 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD affects 4 

propellers installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 5 hours per propeller to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts cost 

about $322 per propeller. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be $2,988. 

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 above, I 

certify this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–05–04 Dowty Propellers: Amendment 

39–18422; Docket No. FAA–2015–3661; 

Directorate Identifier 2015–NE–24–AD. 

(a) Effective Date 

This AD becomes effective April 15, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dowty Propellers R352/ 

6–123–F/1, R352/6–123–F/2, and R410/6– 

123–F/35 model propellers, part numbers (P/ 

Ns) 660715001, 660715004, and 660715005 

with hub P/Ns 660715201, 660715255, 

660720217, 660720241, 660720252, 

660720260, and 660720288, installed. 

(d) Reason 

This AD was prompted by reports of dowel 

hole cracks in the face of the rear hub half. 

We are issuing this AD to prevent loss of 

structural integrity of the propeller hub, 

which could result in damage to the 

propeller and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) At the next removal of the propeller 

from the airplane, after the effective date of 

this AD, install liners into the hub location 

dowel holes and identify the hub P/N. 

(2) Use Dowty Propellers Alert Service 

Bulletin (ASB) No. F50–61–A165, Revision 2, 

dated July 28, 2015 to install the liners and 

identify the hub. 

(f) Credit for Previous Actions 

You may take credit for the actions 

required by paragraph (e) of this AD if you 

performed those actions before the effective 

date of this AD using Dowty Propellers ASB 

No. F50–61–A165, Revision 1, dated May 12, 

2015; or initial issue, dated November 19, 

2012. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Boston Aircraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

(h) Related Information 

(1) For more information about this AD, 

contact Michael Schwetz, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, 1200 District Avenue, Burlington, MA 

01803; phone: 781–238–7761; fax: 781–238– 

7898; email: michael.schwetz@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0158, dated July 30, 

2015, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2015–3661. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Dowty Propellers Alert Service Bulletin 

No. F50–61–A165, Revision 2, dated July 28, 

2015. 

(ii) Reserved. 

(3) For Dowty Propellers service 

information identified in this AD, contact 

Dowty Propellers, 114 Powers Court, 

Sterling, VA 20166; phone: 703–421–4434; 

fax: 703–450–0087; email: technicalsupport@

dowty.com; Internet: http://dowty.com/

services/repair-and-overhaul. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

February 24, 2016. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–05460 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–2015–7205; Directorate 

Identifier 2015–CE–025–AD; Amendment 

39–18419; AD 2016–05–01] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations 12797 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 96–12–12, 

which applies to certain Piper Aircraft, 

Inc. Models PA–31, PA–31–300, PA– 

31–325, and PA–31–350 airplanes. AD 

96–12–12 requires a one-time inspection 

of the bulkhead assembly at fuselage 

station (FS) 317.75 for cracks and the 

installation of one of two reinforcement 

kits determined by whether cracks were 

found during the inspection. This new 

AD requires repetitive inspections of the 

bulkhead assembly at FS 317.75 for 

cracks, repair of cracks as necessary, 

and the installation of a reinforcement 

modification. This AD was prompted by 

cracks found in the FS 317.75 upper 

bulkhead. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective April 15, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 15, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Piper Aircraft, Inc. 2926 Piper Drive, 

Vero Beach, FL 32960; telephone: (415) 

330–9500; email: sales@atp.com; and 

Internet: http://www.piper.com/

technical-publications/. 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

7205. 

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–2015– 

7205; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta Aircraft 

Certification Office (ACO), 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: (404) 474–5551; fax: (404) 

474–5606; email: gregory.noles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 96–12–12, 

Amendment 39–9654 (61 FR 28732, 

June 6, 1996) (‘‘AD 96–12–12’’). AD 96– 

12–12 applied to certain Piper Aircraft, 

Inc. Models PA–31, PA–31–300, PA– 

31–325, and PA–31–350 airplanes. The 

NPRM published in the Federal 

Register on December 9, 2015 (80 FR 

76398). The NPRM was prompted by 

cracks found in the fuselage station (FS) 

317.75 upper bulkhead, which could 

cause structural failure of the vertical 

fin forward spar and lead to loss of 

control. The NPRM proposed to require 

repetitive inspections of the bulkhead 

assembly at FS 317.75 for cracks, repair 

of cracks as necessary, and the 

installation of a reinforcement 

modification to prevent cracks from 

developing. We are issuing this AD to 

correct the unsafe condition on these 

products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (80 FR 76398, 

December 9, 2015) and the FAA’s 

response to the comment. 

Request 

Erin Talbott of Hageland Aviation 

Service commented that the estimated 

labor of 8 work-hours to install the 

reinforcement modification was 

incorrect. The commenter’s company 

installed the modification on 3 of their 

airplanes, and the correct estimated 

work-hours for installation of the 

reinforcement modification was 32 

work-hours. 

We infer from the comment that the 

commenter requests we change the 

number of work-hours to more 

accurately state the estimated labor cost. 

The FAA agrees with this comment, 

and we have revised the estimated Cost 

of Compliance section to reflect this 

change. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

76398, December 9, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 76398, 

December 9, 2015). 

Related Service Information Under 

1 CFR Part 51 

We reviewed Piper Aircraft, Inc. 

Service Bulletin No. 1273A, dated 

October 22, 2015. The service bulletin 

describes procedures for inspecting the 

bulkhead assembly at FS 317.75, 

repairing any cracks found, and 

installation of a reinforcement 

modification to prevent cracks from 

developing. 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 of this final rule. 

Costs of Compliance 

We estimate that this AD affects 977 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of the bulkhead assembly ....... 2 work-hours × $85 per hour = $170 ....... Not applicable ........... $170 $166,090 

Repair/reinforcement of bulkhead assembly.32 work-hours × $85 per hour = $2,720 .. 500 ............................ 3,220 3,145,940 


asabaliauskas on DSK3SPTVN1PROD with RULES
12798 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations 

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 have 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 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, 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

96–12–12, Amendment 39–9654 (61 FR 

28732, June 6, 1996), and adding the 

following new AD: 

2016–05–01 Piper Aircraft, Inc.: 

Amendment 39–18419; Docket No. 

FAA–2015–7205; Directorate Identifier 

2015–CE–025–AD. 

(a) Effective Date 

This AD is effective April 15, 2016. 

(b) Affected ADs 

This AD replaces 96–12–12, Amendment 

39–9654 (61 FR 28732, June 6, 1996) (‘‘AD 

96–12–12’’). 

(c) Applicability 

This AD applies to the following Piper 

Aircraft, Inc. airplanes listed in paragraphs 

(c)(1) and (c)(2) of this AD, certificated in any 

category: 

(1) Models PA–31, PA–31–300, and PA– 

31–325: Serial numbers 31–2 through 31–900 

and 31–7300901 through 31–8312019; and 

(2) Model PA–31–350: Serial numbers 31– 

5001 through 31–5004 and 31–7305005 

through 31–8553002. 

Note 1 to paragraph (c)(1) of this AD: The 

Model PA–31 may also be identified as a PA– 

31–310, even though the PA–31–310 is not a 

model recognized by the Federal Aviation 

Administration (FAA) on the type certificate 

data sheet. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by bulkhead cracks 

found on airplanes that had complied with 

AD 96–12–12 and on additional airplanes not 

affected by AD 96–12–12. We are issuing this 

AD to prevent structural failure of the 

vertical fin forward spar caused by cracks in 

the fuselage station (FS) at 317.75 upper 

bulkhead, which could lead to loss of 

control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection/Repair 

(1) Before or upon accumulating 2,000 

hours time-in-service (TIS) or within the next 

100 hours TIS after April 15, 2016 (the 

effective date of this AD), whichever occurs 

later, and repetitively thereafter at intervals 

not to exceed 100 hours TIS, inspect the 

bulkhead assembly at FS 317.75 for cracks 

following Part I of the Instructions in Piper 

Aircraft, Inc. Service Bulletin No. 1273A, 

dated October 22, 2015. 

(2) If any cracks are found during the 

inspection required in paragraph (g)(1) of this 

AD, before further flight, repair the cracks 

and install the reinforcement modification 

following Part I of the Instructions in Piper 

Aircraft, Inc. Service Bulletin No. 1273A, 

dated October 22, 2015. This repair/

modification terminates the requirements for 

the repetitive inspections required in 

paragraph (g)(1) of this AD. 

(3) You may do the modification required 

in paragraph (h) of this AD to terminate the 

repetitive inspections required in paragraph 

(g)(1) of this AD. 

(h) Modification 

Unless already done as a repair for cracks 

found in the inspection required in 

paragraph (g)(1) of this AD, before or upon 

accumulating 2,500 hours TIS or within the 

next 500 hours after April 15, 2016 (the 

effective date of this AD), whichever occurs 

later, install the reinforcement modification 

following Part II of the Instructions in Piper 

Aircraft, Inc. Service Bulletin No. 1273A, 

dated October 22, 2015. This modification 

terminates the repetitive inspections required 

in paragraph (g)(1) of this AD. 

(i) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

This AD allows credit for the inspection 

required in paragraph (g)(1) of this AD and 

the repair required in paragraph (g)(2) of this 

AD, if done before April 15, 2016 (the 

effective date of this AD), following Part I of 

the Instructions in Piper Aircraft, Inc. Service 

Bulletin No. 1273, dated June 4, 2015. This 

AD also allows credit for the modification 

required in paragraph (h) of this AD, if done 

before April 15, 2016 (the effective date of 

this AD), following Part II of the Instructions 

in Piper Aircraft, Inc. Service Bulletin No. 

1273, dated June 4, 2015. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in Related 

Information, paragraph (j)(1) of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(k) Related Information 

For more information about this AD, 

contact Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta ACO, 1701 Columbia 

Avenue, College Park, Georgia 30337; phone: 

(404) 474–5551; fax: (404) 474–5606; email: 

gregory.noles@faa.gov. 

(l) 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. 


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Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Rules and Regulations 12799 

(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: http://

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: http://

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 

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 

http://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 http://

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 http://

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. 


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