65128 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 

(h) Revision of Maintenance or Inspection 

Program 

Within 30 days after installing the bonding 

provisions and anti-spray cover specified in 

paragraph (g) of this AD: Revise the airplane 

maintenance or inspection program, as 

applicable, by incorporating fuel 

airworthiness limitation items and Critical 

Design Configuration Control Limitations 

(CDCCLs), using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. 

(i) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections), intervals, or 

CDCCLs may be used unless the actions, 

intervals, or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j)(1) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch; ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1137. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Fokker Services B.V.’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0099, dated 

April 30, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2015-0933-0003. 

(l) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on October 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26612 Filed 10–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3940; Directorate 

Identifier 2015–SW–065–AD; Amendment 

39–18300; AD 2015–19–51] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are publishing a new 

airworthiness directive (AD) for 

Sikorsky Aircraft Corporation Model S– 

76A, S–76B, S–76C, and S–76D 

helicopters, which was sent previously 

to all known U.S. owners and operators 

of these helicopters. This AD requires 

inspecting the main rotor (M/R) and tail 

rotor (T/R) pushrod assemblies and the 

jamnuts, and applying slippage marks 

across the pushrod tubes and jamnuts. 

This AD is prompted by an accident of 

a Sikorsky Aircraft Corporation Model 

S–76C helicopter. During preliminary 

investigation, a failed pushrod assembly 

was identified. These actions are 

intended to prevent loss of M/R or T/R 

flight control and subsequent loss of 

control of the helicopter. 

DATES: This AD becomes effective 

November 10, 2015 to all persons except 

those persons to whom it was made 

immediately effective by Emergency AD 

2015–19–51, issued on September 14, 

2015, which contains the requirements 

of this AD. 

We must receive comments on this 

AD by December 28, 2015. 

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–2015– 

3940; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the European Aviation 

Safety Agency (EASA) AD, 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 AD, contact Sikorsky Aircraft 

Corporation, Customer Service 

Engineering, 124 Quarry Road, 

Trumbull, CT 06611; telephone 1–800– 

Winged–S or 203–416–4299; email 

sikorskywcs@sikorsky.com. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: 

Blaine Williams, Aerospace Engineer, 

Boston Aircraft Certification Office, 

Engine & Propeller Directorate, 12 New 

England Executive Park, 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 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 65129 

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 

On September 14, 2015, we issued 

Emergency AD 2015–19–51 for Sikorsky 

Aircraft Corporation Model S–76A, S– 

76B, S–76C, and S–76D helicopters with 

M/R servo input control pushrod 

(pushrod) assembly part number (P/N) 

76400–00034–059 or T/R pushrod 

assembly P/N 76400–00014–071 

installed. Emergency AD 2015–19–51 

requires inspecting the M/R forward, aft, 

and lateral pushrod assemblies, the T/R 

pushrod assembly, and the jamnuts, and 

applying slippage marks across the 

pushrod tubes and jamnuts. Emergency 

AD 2015–19–51 was sent previously to 

all known U.S. owners and operators of 

these helicopters and was prompted by 

an accident of a Sikorsky Aircraft 

Corporation Model S–76C helicopter in 

which a failed pushrod assembly was 

identified during preliminary 

investigation. Separation of the pushrod 

tube and the control rod end with 

bearing was found. 

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 on other helicopters of these 

same type designs. 

Related Service Information 

Sikorsky issued Alert Service Bulletin 

No. 76–67–57, Basic Issue, dated 

September 10, 2015 (ASB), which 

specifies a one-time inspection of the 

M/R forward, aft, and lateral pushrod 

assemblies, the T/R pushrod assembly, 

and the jamnuts for proper installation, 

condition, and security. If a pushrod or 

jamnut does not meet criteria specified 

in the inspection, the ASB specifies 

replacing the assembly. The ASB also 

specifies applying two slippage marks 

across each M/R and T/R pushrod tube 

and jamnut. Further, the ASB references 

the applicable maintenance manual for 

a new recurring inspection of the 

slippage marks. 

AD Requirements 

This AD requires, within five hours 

time-in-service (TIS), inspecting each 

M/R and T/R pushrod assembly by 

inspecting the position of the control 

rod end in the pushrod tube. If the 

lockwire passes through the inspection 

hole, this AD requires replacing the 

pushrod assembly. If the lockwire does 

not pass through the inspection hole, 

this AD requires inspecting the jamnut 

to determine seating position against the 

pushrod and whether the jamnut can be 

turned with finger pressure. If the 

jamnut is not seated against the pushrod 

or is loose, this AD requires replacing 

the pushrod assembly. This AD also 

requires, both for those pushrod 

assemblies that are replaced and for 

those that pass the inspections, applying 

two slippage marks across each M/R and 

T/R pushrod tube and jamnut. 

Interim Action 

We consider this AD to be an interim 

action as the accident investigation is 

ongoing. If additional action is later 

identified, we might consider further 

rulemaking. 

Costs of Compliance 

We estimate that this AD affects 198 

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 workhour. It takes about 1 work-hour to 

inspect the pushrod assemblies and 

jamnut for a cost of $85 per helicopter 

and $16,830 for the U.S. fleet. It takes 

a minimal amount of time to apply the 

slippage marks for a negligible cost. 

Replacing a pushrod assembly takes 

about 1.5 work-hours for a labor cost of 

$128. Parts for an M/R pushrod 

assembly cost $2,411 for a total 

replacement cost of $2,539. Parts for a 

T/R pushrod assembly cost $1,905 for a 

total replacement cost of $2,033. 

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 found and continue to 

find that the risk to the flying public 

justifies waiving notice and comment 

prior to the adoption of this rule 

because the previously described unsafe 

condition can adversely affect the 

controllability of the helicopter and the 

initial required action must be 

accomplished within five hours TIS. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment before issuing this AD were 

impracticable and contrary to public 

interest and good cause existed to make 

the AD effective immediately by 

Emergency AD 2015–19–51, issued on 

September 14, 2015, to all known U.S. 

owners and operators of these 

helicopters. These conditions still exist 

and the AD is hereby published in the 

Federal Register as an amendment to 

section 39.13 of the Federal Aviation 

Regulations (14 CFR 39.13) to make it 

effective to all persons. 

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, 


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65130 Federal Register / Vol. 80, No. 206 / Monday, October 26, 2015 / Rules and Regulations 

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): 

2015–19–51 Sikorsky Aircraft 

Corporation: Amendment 39–18300; Docket 

No. FAA–2015–3940; Directorate Identifier 

2015–SW–065–AD. 

(a) Applicability 

This AD applies to Model S–76A, S–76B, 

S–76C, and S–76D helicopters with main 

rotor (M/R) servo input control pushrod 

(pushrod) assembly part number (P/N) 

76400–00034–059 or tail rotor (T/R) pushrod 

assembly P/N 76400–00014–071 installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

loose jamnut. This condition could result in 

failure of a pushrod assembly, loss of M/R or 

T/R flight control, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective November 10, 

2015 to all persons except those persons to 

whom it was made immediately effective by 

Emergency AD 2015–19–51, issued on 

September 14, 2015, which contains the 

requirements of this AD. 

(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 five hours time-in-service: 

(1) Inspect each pushrod end to determine 

whether a 0.020 inch diameter lockwire can 

pass through the inspection hole. 

(i) If the lockwire passes through the 

inspection hole, replace the pushrod 

assembly. 

(ii) If the lockwire does not pass through 

the inspection hole, inspect the jamnut to 

determine whether it is seated against the 

pushrod and whether it can be turned with 

finger pressure. If the jamnut is not seated 

against the pushrod or can be turned with 

finger pressure, replace the pushrod 

assembly. 

(2) Apply two slippage marks across each 

pushrod tube and jamnut as follows: 

(i) Clean the area where a slippage mark is 

to be applied. 

(ii) Apply two slippage marks across the 

pushrod tube and jamnut, parallel and on 

opposite sides of each other. Each slippage 

mark must extend at least 0.5 inch onto the 

pushrod tube and must not cover the 

inspection hole. Figures 2 and 4 of Sikorsky 

Alert Service Bulletin No. 76–67–57, Basic 

Issue, dated September 10, 2015, illustrate 

slippage marks across a pushrod tube and 

jamnut. 

(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, 12 New England 

Executive Park, 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) Additional Information 

Sikorsky Alert Service Bulletin No. 76–67– 

57, Basic Issue, dated September 10, 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 sikorskywcs@sikorsky.com. 

You may review a copy of the 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: 2700, Flight Control System. 

Issued in Fort Worth, Texas, on October 9, 

2015. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–26949 Filed 10–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4208; Directorate 

Identifier 2015–NM–152–AD; Amendment 

39–18303; AD 2015–21–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–19– 

03 for all The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes. AD 2015–19– 

03 required revising the maintenance or 

inspection program to include new 

airworthiness limitations. This AD 

continues to require a maintenance or 

inspection program revision, but with 

revised language. This AD was 

prompted by a determination that 

certain language in the airworthiness 

limitation was not accurate in AD 2015– 

19–03. We are issuing this AD to detect 

and correct latent failures of the fuel 

shutoff valve to the engine, which could 

result in the inability to shut off fuel to 

the engine and, in case of certain engine 

fires, an uncontrollable fire that could 

lead to wing failure. 

DATES: This AD is effective October 28, 

2015. 

We must receive any comments on 

this AD by December 10, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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–2015– 

4208; 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 street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6509; fax: 


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