This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

21385 

Vol. 79, No. 73 

Wednesday, April 16, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0216; Directorate 

Identifier 2013–SW–045–AD; Amendment 

39–17818; AD 2014–07–04] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Model S–92A helicopters. This 

AD requires, initially and each time the 

clamps are removed, inspecting for 

chafing between the electrical wires and 

the hydraulic lines and, if there is 

chafing between the wires or lines, 

before further flight, replacing the 

unairworthy wires or lines with 

airworthy wires or lines. Also, this AD 

requires inspecting each clamp for 

correct installation, and if a clamp is 

incorrectly installed or missing, before 

further flight, correctly installing the 

clamps. This AD is prompted by chafing 

between high voltage electrical wiring 

and hydraulic lines that led to two fires 

in the top deck of the helicopter, which 

does not have fire detection nor 

extinguishing capability. The actions 

specified by this AD are intended to 

detect any chafing between the 

electrical wires and the hydraulic lines 

that could result in a fire and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective May 

1, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of May 1, 2014. 

We must receive comments on this 

AD by June 16, 2014. 

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 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 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, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Caspar Wang, Aviation Safety Engineer, 

Boston Aircraft Certification Office, 

Engine & Propeller Directorate, FAA, 12 

New England Executive Park, 

Burlington, Massachusetts 01803; 

telephone (781) 238–7799; email 

caspar.wang@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 are adopting a new AD for 

Sikorsky Model S–92A helicopters. This 

AD requires, initially and each time the 

clamps are removed, inspecting for 

chafing between the electrical wires and 

the hydraulic lines and, if there is 

chafing between the wires and lines, 

before further flight, replacing the 

unairworthy wires or lines with 

airworthy wires or lines. Also, this AD 

requires inspecting each clamp for 

correct installation, and if a clamp is 

incorrectly installed or missing, before 

further flight, correctly installing the 

clamps. 

This AD is prompted by chafing 

between high voltage electrical wires 

and hydraulic lines that led to two fires 

in the top deck of the helicopter, which 

does not have fire detection nor 

extinguishing capability. The chafing 

occurred because of improper clamp 

installation after maintenance was 

performed in the top deck. A redesign 

eliminated the need for clamping in 

newer Model S–92A helicopters. 

However, because of the high volume of 

maintenance performed in the area 

where the fire occurred immediately 

following maintenance involving 


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21386 Federal Register / Vol. 79, No. 73 / Wednesday, April 16, 2014 / Rules and Regulations 

removing and installing the clamps, 

more detailed instructions are necessary 

for correct installation of the clamps in 

the older model helicopters. The actions 

specified by this AD are intended to 

detect any chafing between the 

electrical wires and the hydraulic lines 

that could result in a fire and 

subsequent loss of control of the 

helicopter. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other helicopters of the same 

type design. 

Related Service Information 

Sikorsky has issued Alert Service 

Bulletin No. 92–20–001, dated October 

27, 2005 (ASB) to specify a one-time 

installation of clamps to provide 

additional clearance between the 

electrical harnesses on the upper deck 

and the hydraulic lines. 

AD Requirements 

This AD requires: 

• Within 5 hours time-in-service 

(TIS), inspecting the electrical wires and 

the hydraulic lines in the affected area 

for evidence of chafing. If there is 

chafing between electrical wires and the 

hydraulic lines, this AD requires, before 

further flight, replacing unairworthy 

wires or lines with airworthy wires or 

lines. 

• Within 5 hours TIS, inspecting each 

clamp for correct installation. If clamps 

are incorrectly installed or missing, 

before further flight, install clamps by 

following the Accomplishment 

Instructions of the ASB. 

• After each maintenance that 

requires removing clamps, this AD 

requires repeating the previous 

inspections. 

Differences Between This AD and the 

Service Information 

The service information specifies a 

one-time installation of the clamps 

between the electrical harnesses on the 

upper deck and the hydraulic lines 

within 30 days. This AD requires, 

within 5 hours TIS, inspecting each 

clamp for correct installation, and 

within 5 hours TIS and after each 

maintenance that requires removing 

clamps, inspecting the electrical wires 

and the hydraulic lines for chafing. This 

AD applies to S/N 920006 through 

920084, and the service bulletin applies 

to S/N 920006 through 920022. 

Interim Action 

We consider this AD interim action. 

The design approval holder is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

Costs of Compliance 

We estimate that this AD will affect 

20 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. Labor costs are estimated 

at $85 per work hour. An initial 

inspection of the clamps will take .5 

work hour. Inspecting and reclamping 

will take 2 work hours at a parts cost of 

$25 per helicopter. Inspecting and 

replacing the electrical wires will take 2 

work hours at a parts cost of $7,500 per 

helicopter. Inspecting and replacing the 

hydraulic lines will take 3 work hours 

at a parts cost of $500 per helicopter. 

Based on these estimates, the total cost 

per helicopter is $8,663, and the total 

cost of compliance for the U.S. fleet is 

$173,250, assuming the clamps, 

electrical wires, and hydraulic lines are 

replaced. 

According to Sikorsky’s service 

information, the costs of this AD may be 

covered under warranty thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage by Sikorsky. Accordingly, we 

have included all costs in our cost 

estimate. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments before 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 before adopting this rule 

because the required corrective actions 

must be done within 5 hours TIS, a very 

short time period based on the average 

flight-hour utilization rate of these 

helicopters. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

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. 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 73 / Wednesday, April 16, 2014 / Rules and Regulations 21387 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2014–07–04 Sikorsky Aircraft Corporation: 

Amendment 39–17818; Docket No. 

FAA–2014–0216; Directorate Identifier 

2013–SW–045–AD. 

(a) Applicability 

This AD applies to Model S–92A 

helicopters, serial numbers 92006 through 

920084, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

installation that does not provide adequate 

clearance to prevent chafing between the 

high voltage electrical wires and hydraulic 

lines. This condition could result in fire and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective May 1, 2014. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 5 hours time-in-service, inspect 

the electrical wires and the hydraulic lines in 

the upper deck of the helicopter for chafing 

between electrical wires and hydraulic lines. 

If there is chafing between electrical wires 

and hydraulic lines, before further flight, 

replace the unairworthy wires or lines with 

airworthy wires or lines. 

(2) Within 5 hours TIS, inspect each clamp 

for correct installation as shown in Figures 1 

through 14 of Sikorsky Aircraft Corporation 

Alert Service Bulletin No. 92–20–001, dated 

October 27, 2005 (ASB). If clamps are 

incorrectly installed or missing, before 

further flight, install clamps by following the 

Accomplishment Instructions, paragraph 

3.A.(4) through 3.A.(17) of the ASB. 

(3) After each maintenance that requires 

removing clamps, comply with paragraphs 

(e)(1) and (e)(2) 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: 

Caspar Wang, Aviation Safety Engineer, 

Boston Aircraft Certification Office, Engine & 

Propeller Directorate, FAA, 12 New England 

Executive Park, Burlington, Massachusetts 

01803; telephone (781) 238–7799; email 

caspar.wang@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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2910 Main Hydraulic System. 

(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) Sikorsky Aircraft Corporation Alert 

Service Bulletin No. 92–20–001, dated 

October 27, 2005. 

(ii) Reserved. 

(3) For Sikorsky Aircraft Corporation 

service information identified in this AD, 

contact Customer Service Engineering, 124 

Quarry Road, Trumbull, CT 06611; telephone 

1–800–Winged–S or 203–416–4299; email 

sikorskywcs@sikorsky.com. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

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

Issued in Fort Worth, Texas, on March 28, 

2014. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–07672 Filed 4–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1069; Directorate 

Identifier 2013–NM–197–AD; Amendment 

39–17827; AD 2014–08–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes, and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. This AD was prompted by a 

determination that for certain slat 

system failure cases, the resulting slat 

skew could lead to failure of the slat 

system. This AD requires replacing 

certain locking plates with certain antimigration assemblies on certain left and 

right wing slats. We are issuing this AD 

to prevent failure of the eccentric pins 

at the slat track attachment, and slat 

panels consequently disconnecting from 

the wing, leading to the loss of the 

airplane. 

DATES: This AD becomes effective May 

21, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 21, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1069; or in 

person at the Docket 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. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone (516) 228–7318; 

fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

CL–600–2C10 (Regional Jet Series 700, 

701, & 702) airplanes, Model CL–600– 

2D15 (Regional Jet Series 705) airplanes, 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes, and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. The NPRM published in the 

Federal Register on January 2, 2014 (79 

FR 70). 


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