Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Rules and Regulations 54893 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 30 days after the effective date of 

this AD: Incorporate tasks for performing a 

general visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components into the airplane 

maintenance or inspection program, as 

applicable, in accordance with a method 

approved by the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA. 

Note 1 to paragraph (g) of this AD: For 

Model DHC–8–100 series airplanes, the 

instructions provided in de Havilland Dash 

8 Maintenance Task Cards 531X1 and 631X1, 

‘‘General visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components,’’ in Section 8, 

‘‘Electrical Wiring Interconnection System 

Inspection Program,’’ of the Bombardier (de 

Havilland) Dash 8 Series 100 Maintenance 

Review Board Report of the Bombardier (de 

Havilland) Dash 8 Series 100 Maintenance 

Program Manual PSM 1–8–7, Revision 25, 

dated February 20, 2012, provides guidance 

for revising the maintenance program to 

include general visual inspections of the 

wiring and associated EWIS components. 

This service information is not incorporated 

by reference in this AD. 

Note 2 to paragraph (g) of this AD: For 

Model DHC–8–200 series airplanes, the 

instructions provided in de Havilland Dash 

8 Maintenance Task Cards 531X1 and 631X1, 

‘‘General visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components,’’ in Section 8, 

‘‘Electrical Wiring Interconnection System 

Inspection Program,’’ of the Bombardier (de 

Havilland) Dash 8 Series 200 Maintenance 

Review Board Report of the Bombardier (de 

Havilland) Dash 8 Series 200 Maintenance 

Program Manual PSM 1–82–7, Revision 16, 

dated February 20, 2012, provides guidance 

for revising the maintenance program to 

include general visual inspections of the 

wiring and associated EWIS components. 

This service information is not incorporated 

by reference in this AD. 

Note 3 to paragraph (g) of this AD: For 

Model DHC–8–300 series airplanes, the 

instructions provided in de Havilland Dash 

8 Maintenance Task Cards 531X1 and 631X1, 

‘‘General visual inspection of the wiring and 

associated electrical wiring interconnection 

system (EWIS) components,’’ in Section 8, 

‘‘Electrical Wiring Interconnection System 

Inspection Program,’’ of the Bombardier (de 

Havilland) Dash 8 Series 300 Maintenance 

Review Board Report of the Bombardier (de 

Havilland) Dash 8 Series 300 Bombardier 

Maintenance Program Manual PSM 1–83–7, 

Revision 25, dated February 20, 2012, 

provides guidance for revising the 

maintenance program to include general 

visual inspections of the wiring and 

associated EWIS components. This service 

information is not incorporated by reference 

in this AD. 

(h) Initial Task Compliance Time 

The initial compliance time for the tasks 

incorporated into the maintenance or 

inspection program, as applicable, specified 

in paragraph (g) of this AD, is at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. 

(1) For airplanes with 45,000 total flight 

hours or more as of the effective date of this 

AD: Within 1,000 flight hours after the 

effective date of this AD. 

(2) For airplanes with less than 45,000 total 

flight hours as of the effective date of this 

AD: Within 6,000 flight hours after the 

effective date of this AD, but not to exceed 

46,000 total flight hours. 

(i) No Alternative Actions or Intervals 

After accomplishing the revisions required 

by paragraph (g) of this AD, no alternative 

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

used, unless the actions and intervals 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, New York ACO, 

ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–25, dated 

August 28, 2012, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2013–0298. 

(2) For service information identified in 

this AD that is not incorporated by reference, 

contact Bombardier, Inc., Q-Series Technical 

Help Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone 416– 

375–4000; fax 416–375–4539; email 

thd.qseries@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. 

(l) Material Incorporated by Reference 

None 

Issued in Renton, Washington, on July 12, 

2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–21770 Filed 9–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0216; Directorate 

Identifier 2013–SW–045–AD; Amendment 

39–17964; AD 2014–07–04R1] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising 

airworthiness directive (AD) 2014–07– 

04 that published in the Federal 

Register to correct certain errors. AD 

2014–07–04 applied to certain Sikorsky 

Model S–92A helicopters. The range of 

serial numbers in the Applicability 

section and a reference to the service 

information in the Required Actions 

section of the regulatory text are 

incorrect. This document corrects those 

errors. In all other respects, the original 

document remains the same. 

DATES: This final rule is effective 

September 30, 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 (79 FR 21385, April 

16, 2014). 

We must receive comments on this 

AD by November 14, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov; 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 


rmajette on DSK2TPTVN1PROD with RULES2
54894 Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Rules and Regulations 

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: 

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 

AD 2014–07–04, Amendment 39– 

17818 (79 FR 21385, April 16, 2014), 

applied to certain Sikorsky Model S– 

92A helicopters and required, in part, 

repetitively inspecting each clamp for 

correct installation. Due to 

typographical errors when the AD was 

published, an incorrect serial number 

and an incorrect reference to the service 

information appeared in the text of the 

rule. 

Specifically, AD 2014–07–04 

included the following under paragraph 

(a) in the Applicability section: ‘‘This 

AD applies to Model S–92A helicopters, 

serial numbers 92006 through 920084, 

certificated in any category.’’ As 

published, the reference to serial 

number ‘‘92006’’ is incorrect and should 

be serial number ‘‘920006.’’ 

AD 2014–07–04 also included the 

following under paragraph (e)(2) in the 

Required Actions section: ‘‘(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, 

paragraphs 3.A.(4) through 3.A.(17) of 

the ASB.’’ As published, the reference to 

‘‘Figures 1 through 14’’ is incorrect 

because there are only 13 figures in the 

service information. 

The FAA has determined that it is 

appropriate to take action to revise AD 

2014–07–04 to correct the serial 

numbers and figure reference. This 

revision ensures that this AD only 

applies to those aircraft subject to the 

unsafe condition and that it is possible 

for operators to comply with the AD by 

referencing the correct portions of the 

service information. 

No other part of the preamble or 

regulatory information has been 

changed. The final rule is being 

reprinted in its entirety for the 

convenience of affected operators. 

Impact of the Correction 

Since this action reduces the number 

of helicopters to which the AD is 

applicable and corrects an obvious error 

in referencing the service information, it 

has no adverse economic impact and 

imposes no additional burden on any 

person. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

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) 

2014–07–04, Amendment 39–17818 (79 

FR 21385, April 16, 2014), and by 

adding the following new AD: 

2014–07–04R1 Sikorsky Aircraft 

Corporation: Amendment 39–17964; 

Docket No. FAA–2014–0216; Directorate 

Identifier 2013–SW–045–AD. 

(a) Applicability 

This AD applies to Model S–92A 

helicopters, serial numbers 920006 through 

920084, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

incorrectly installed clamp that does not 

provide adequate clearance to prevent 

chafing between the high voltage electrical 

lines and the hydraulic hoses. This condition 

could result in a fire in an area of the 

helicopter without extinguishing capability 

and subsequent loss of control of the 

helicopter. 

(c) Affected ADs 

This AD revises AD 2014–07–04, 

Amendment 39–17818 (79 FR 21385, April 

16, 2014). 

(d) Effective Date 

This AD becomes effective September 30, 

2014. 

(e) 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. 

(f) 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 13 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 

(f)(1) and (f)(2) of this AD. 

(g) 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 


rmajette on DSK2TPTVN1PROD with RULES2
Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Rules and Regulations 54895 

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 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. 

(3) The following service information was 

approved for IBR on May 1, 2014 (79 FR 

21385, April 16, 2014). 

(i) Sikorsky Aircraft Corporation Alert 

Service Bulletin No. 92–20–001, dated 

October 27, 2005. 

(ii) Reserved. 

(4) 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. 

(5) 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. 

(6) 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 August 21, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–21880 Filed 9–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0929; Directorate 

Identifier 2013–CE–031–AD; Amendment 

39–17968; AD 2013–22–14 R1] 

RIN 2120–AA64 

Airworthiness Directives; DG 

Flugzeugbau GmbH Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an 

airworthiness directive (AD) 2013–22– 

14 for any DG Flugzeugbau GmbH 

Model DG–1000T glider equipped with 

a Solo Kleinmotoren Model 2350 C 

engine. This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as engine shaft 

failure and consequent propeller 

detachment. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective October 20, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 20, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0929; 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 20590. 

For service information identified in 

this AD, contact Solo Kleinmotoren 

GmbH, Postfach 60 01 52, D 71050 

Sindelfingen, Germany; telephone: +49 

07031–301–0; fax: +49 07031–301–136; 

email: aircraft@solo-germany.com; 

Internet: http://aircraft.solo-online. 

com/. 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. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090; email: jim.rutherford@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to DG Flugzeugbau GmbH Model DG– 

1000T airplanes. The NPRM was 

published in the Federal Register on 

June 27, 2014 (79 FR 36440), and 

proposed to revise AD 2013–22–14, 

Amendment 39–17646 (78 FR 65869, 

November 4, 2013) (‘‘AD 2013–22–14’’). 

Since we issued AD 2013–22–14, the 

manufacturer of the Solo Kleinmotoren 

Model 2350 C engine has developed an 

engine modification to restore engine 

operation. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2013– 

0217R1, dated May 5, 2014 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

An occurrence of Solo 2350 C engine shaft 

failure and consequent propeller detachment 

was reported. The preliminary investigation 

revealed that the failed shaft was earlier 

modified in accordance with an approved 

method. 

This condition, if not corrected, could lead 

to additional cases of release of the propeller 

from the engine, possibly resulting in damage 

to the sailplane, or injury to persons on the 

ground. 

To address this potential unsafe condition, 

EASA issued Emergency AD 2013–0217–E to 

prohibit operation of the engine. 

Since that AD was issued, Solo 

Kleinmotoren GmbH developed a 

modification consisting of installing an 

improved eccenter axle—pulley assembly, 

allowing to resume operation of the engine. 

For the reason described above, this AD is 

revised to incorporate the optional 

modification, cancelling the operational 

restriction. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0929- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 36440, June 27, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the 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 (79 FR 

36440, June 27, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 36440, 

June 27, 2014). 

Costs of Compliance 

We estimate that this AD will affect 2 

products of U.S. registry. We also 

estimate that it will take about .5 workhour per product to comply with the 

retained requirement of placing a copy 

of AD 2013–22–14 into the Limitations 

section of the aircraft flight manual, 


rmajette on DSK2TPTVN1PROD with RULES2