71300 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(6) You may view this service information 

at 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. 

(7) 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 Renton, Washington, on 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27362 Filed 12–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0776; Directorate 

Identifier 2009–NE–32–AD; Amendment 39– 

18007; AD 2010–17–11R2] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Constant Speed Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising airworthiness 

directive (AD) 2010–17–11R1, which 

applies to all Dowty Propellers R408/6– 

123–F/17 model propellers. AD 2010– 

17–11R1 required initial application of 

sealant between the bus bar assembly 

and the backplate assembly of certain 

line-replaceable units (LRUs) and 

repetitive re-applications of sealant on 

all R408/6–123–F/17 model propellers. 

AD 2010–17–11R1 also provided an 

optional terminating action to the 

repetitive re-application of sealant. This 

AD increases the interval allowed 

between the required re-application of 

sealant, and specifies an additional 

acceptable sealant. This AD was 

prompted by failure of the propeller deice bus bar due to friction or contact 

between the bus bar and the backplate 

assembly, consequent intermittent short 

circuit, and possible double generator 

failure. We are issuing this AD to 

prevent an in-flight double generator 

failure, which could result in reduced 

control of the airplane. 

DATES: This AD is effective January 6, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 6, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Dowty 

Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL2 

9QN, UK; phone: 44 0 1452 716000; fax: 

44 0 1452 716001. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

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

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–2009– 

0776; 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 mandatory 

continuing airworthiness information, 

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: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax 781–238–7170; email: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2010–17–11R1, 

Amendment 39–17481 (78 FR 41283, 

July 10, 2013), (‘‘AD 2010–17–11R1’’). 

AD 2010–17–11R1 applied to the 

specified products. The NPRM 

published in the Federal Register on 

March 19, 2014 (79 FR 15269). The 

NPRM proposed to require increasing 

the interval allowed between the 

required re-application of sealant and 

specified an additional acceptable 

sealant. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request Correction to the Applicability 

and Compliance Paragraphs 

Horizon Air requested a correction in 

the Applicability and Compliance 

paragraphs for possible typographical 

errors between AD 2010–17–11R1 and 

the NPRM (79 FR 15269, March 19, 

2014). Horizon Air stated that the 

Applicability has changed from ‘‘. . . 

serial number (S/N) below DAP0327’’ in 

AD 2010–17–11R1 to ‘‘. . . S/N below 

DAP0927’’ in the proposed rule. With 

no discussion about the increased 

number of affected propellers, Horizon 

Air believes that typographical errors 

exist in the Applicability and 

Compliance sections. 

We do not agree. AD 2010–17–11R1 

required initial sealant application to all 

Dowty Propellers R408/6–123–F/17 

model propellers with a hub, actuator, 

and backplate assembly LRU S/Ns 

below DAP0347, not DAP0327 as 

quoted above. AD 2010–17–11R1 also 

required repetitive re-application of 

sealant for all LRU S/Ns below 

DAP0927. We did not change this AD. 

Request Change to Optional 

Terminating Action 

Horizon Air requested that all 

revisions to Dowty Propellers Service 

Bulletin (SB) No. D8400–61–94 be 

included in the Optional Terminating 

Action paragraph. The implied reason 

for this request was to support 

terminating action throughout the range 

of qualified SBs. 

We partially agree. We agree that 

Dowty Propellers SB No. D8400–61–94, 

Revision 6, dated December 12, 2013 

and earlier revisions provide adequate 

corrective actions to address the unsafe 

condition. We changed the Optional 

Terminating Action paragraph to 

include Dowty Propellers SB No. 

D8400–61–94, Revision 6, dated 

December 12, 2013 and earlier revisions. 

We do not agree that unknown future 

SB versions should be included in this 

AD. The content of future SB revisions 

is speculation. We did not change this 

AD to include all revisions of the SB. 

Request for Alternative Method of 

Compliance 

Horizon Air requested that we allow 

the use of 3M 4200 sealant as an 

equivalent replacement for the 3M 5300 

sealant. 

We agree. We approved 3M 4200 as 

an acceptable sealant in response to the 

Horizon Air comment to AD 2010–17– 

11R1 when that AD was at the NPRM 

stage; see 78 FR 41283, July 10, 2013. 

3M 4200 sealant is also one of three 

sealants identified in Dowty Propellers 

Alert Service Bulletin (ASB) No. D8400– 

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Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 71301 

61–A66, Revision 8, dated October 31, 

2013. That Dowty ASB is incorporated 

by reference to this AD and is 

authorized for use when performing 

paragraph (g) of this AD. We did not 

change this AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 104 

propellers installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 2 hours per propeller to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts cost 

about $20 per propeller. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $19,760. 

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 

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 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 part 39 of the Federal 

Aviation Regulations (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) 

2010–17–11R1, Amendment 39–17481 

(78 FR 41283, July 10, 2013), and adding 

the following new AD: 

2010–17–11R2 Dowty Propellers Constant 

Speed Propellers: Amendment 39– 

18007; Docket No. FAA–2009–0776; 

Directorate Identifier 2009–NE–32–AD. 

(a) Effective Date 

This AD is effective January 6, 2015. 

(b) Affected ADs 

This AD revises AD 2010–17–11R1, 

Amendment 39–17481 (78 FR 41283, July 10, 

2013). 

(c) Applicability 

This AD applies to Dowty Propellers R408/ 

6–123–F/17 model propellers with a hub, 

actuator, and backplate assembly linereplaceable unit (LRU) serial number (S/N) 

below DAP0927. 

(d) Unsafe Condition 

This AD was prompted by failure of the 

propeller de-ice bus bar due to friction or 

contact between the bus bar and the 

backplate assembly, consequent intermittent 

short circuit, and possible double generator 

failure. We are issuing this AD to prevent an 

in-flight double generator failure, which 

could result in reduced control of the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For R408/6–123–F/17 model propellers 

with a hub, actuator, and backplate assembly 

LRU S/N below DAP0347, do the following 

initial sealant application within 5,000 flighthours (FHs) after September 27, 2010, or 

within 100 FHs after the effective date of this 

AD, whichever occurs later: 

(i) Apply a sealant specified in Dowty 

Propellers Alert Service Bulletin (ASB) No. 

D8400–61–A66, Revision 8, dated October 

31, 2013 between the bus bar assemblies and 

the backplate assembly. 

(ii) Use paragraph 3.A. or 3.B. of the 

Accomplishment Instructions of Dowty 

Propellers ASB No. D8400–61–A66, Revision 

8, dated October 31, 2013, to apply the 

sealant. 

(2) Thereafter, for R408/6–123–F/17 model 

propellers, with a hub, actuator, and 

backplate assembly LRU S/N below 

DAP0927, re-apply sealant as specified in 

paragraphs (e)(1)(i) and (e)(1)(ii) of this AD 

within every additional 10,500 FHs. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any Dowty Propellers R408/6–123–F/ 

17 model propeller unless 3M 5300 or 3M 

4200 sealant was applied between the bus bar 

assembly and the backplate assembly as 

required by this AD, or unless the optional 

terminating action as specified in paragraph 

(g) of this AD was performed. 

(g) Optional Terminating Action 

As optional terminating action to the 

sealant application required by paragraph (e) 

of this AD, replace the bus bar assembly with 

a slip ring de-icer harness. Use paragraph 

3.A. of the Accomplishment Instructions of 

Dowty Propellers Service Bulletin (SB) No. 

D8400–61–94, Revision 6, dated December 

12, 2013, to do the replacement. 

(h) Credit for Previous Actions 

(1) Sealant applications performed before 

the effective date of this AD using Dowty 

Propellers SB No. D8400–61–66, dated 

February 9, 2007; Revision 1, dated May 4, 

2007; ASB No. D8400–61–A66, Revision 2, 

dated August 19, 2009; Revision 3, dated 

November 10, 2009; Revision 4, dated 

January 19, 2010; Revision 5, dated June 16, 

2010; Revision 6, dated August 17, 2011; or 

Revision 7, dated December 1, 2011, satisfy 

the initial sealant application required by 

paragraph (e) of this AD. 

(2) Replacement of the busbar assembly 

with a slip ring de-icer harness before the 

effective date of this AD using Dowty 

Propellers SB No. D8400–61–94, Revision 2, 

dated August 29, 2012; Revision 3, dated 

October 23, 2012; Revision 4, dated June 12, 

2013; or Revision 5, dated September 2, 2013, 

satisfies the optional terminating action 

specified in paragraph (g) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Boston Aircraft Certification 

Office, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) For more information about this AD, 

contact Michael Schwetz, Aerospace 

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71302 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

Engineer, Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

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

7170; email: michael.schwetz@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2009–0114R2, (Correction: 

December 16, 2013), dated December 13, 

2013, for more information. You may 

examine the MCAI in the AD docket on the 

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

#!documentDetail;D=FAA-2009-0776-0014. 

(3) Dowty Propellers SB No. D8400–61–66, 

dated February 9, 2007; Revision 1, dated 

May 4, 2007; ASB No. D8400–61–A66, 

Revision 2, dated August 19, 2009; Revision 

3, dated November 10, 2009; Revision 4, 

dated January 19, 2010; Revision 5, dated 

June 16, 2010; Revision 6, dated August 17, 

2011; or Revision 7, dated December 1, 2011, 

which are not incorporated by reference in 

this AD, can be obtained from Dowty 

Propellers, using the contact information in 

paragraph (k)(3) of this AD. 

(4) Dowty Propellers SB No. D8400–61–94, 

Revision 2, dated August 29, 2012; Revision 

3, dated October 23, 2012; Revision 4, dated 

June 12, 2013; or Revision 5, dated 

September 2, 2013, which are not 

incorporated by reference in this AD, can be 

obtained from Dowty Propellers, using the 

contact information in paragraph (k)(3) of 

this AD. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

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

(k) 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. D8400–61–A66, Revision 8, dated 

October 31, 2013. 

(ii) Dowty Propellers Service Bulletin No. 

D8400–61–94, Revision 6, dated December 

12, 2013. 

(3) For Dowty Propellers service 

information identified in this AD, contact 

Dowty Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL2 9QN, 

UK; phone: 44–0–1452–716000; fax: 44–0– 

1452–716001. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 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 

November 3, 2014. 

Kim Smith, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–28325 Filed 12–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0701; Directorate 

Identifier 2014–CE–025–AD; Amendment 

39–18034; AD 2014–24–01] 

RIN 2120–AA64 

Airworthiness Directives; Various de 

Havilland Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Harry E. Williams de Havilland Model 

DH 82A airplanes, all Cliff Robertson de 

Havilland Model DH 82A airplanes, and 

all de Havilland Model DH 83 airplanes. 

This AD was prompted by reports of 

structural failure of the attachment of 

the wing to the fuselage that resulted 

from failed lateral fuselage tie rods. This 

AD requires inspecting the aircraft 

maintenance records to determine the 

date of installation or the date of last 

replacement of the lateral fuselage tie 

rods. This AD also requires repetitively 

replacing all lateral fuselage tie rods and 

attaching nuts at a specified life limit 

interval. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective January 6, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 6, 2015. 

ADDRESSES: For service information 

identified in this AD, for de Havilland 

DH 82A airplanes, contact de Havilland 

Support Ltd., Building 213, Duxford 

Airfield, Cambridge, United Kingdom 

CB22 4QR, telephone: +44 (0) 1223 

830090; fax: +44 (0) 1223 830085; email: 

info@dhsupport.com; Internet: http://

www.dhsupport.com/moth.php. 

For service information identified in 

this AD, for de Havilland DH 83 

airplanes, contact Air Stratus Ltd., 

Oaksey Park Airfield, Oaksey, 

Malmesbury, Wiltshite, United 

Kingdom SN 16 9SD; telephone: +44 (0) 

1666 575111; no known Internet 

address. 

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. 

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–2014– 

0701; 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: For 

airplanes covered under Type 

Certificate Data Sheet (TCDS) A5PC 

(Model de Havilland DH 82A airplanes 

built in Australia): Andrew McAnaul, 

Aerospace Engineer, FAA, Fort Worth 

Airplane Certification Office, ASW–150 

(c/o San Antonio MIDO), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; phone: (210) 308–3365; 

fax: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. 

For airplanes covered under TCDS 

A8EU (Model de Havilland DH 82A 

airplanes built in the United Kingdom): 

Fred Guerin, Aerospace Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Blvd., Suite 

100, Lakewood, California 90712; phone 

(562) 627–5232; fax: (562) 627–5210; 

email: fred.guerin@faa.gov. 

For airplanes covered under TCDS 2– 

439 (Model de Havilland DH 83 

airplanes built in the United Kingdom): 

Karl Schletzbaum, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; phone: (816) 329–4123; 

fax: (816) 329–4090; email: 

karl.schletzbaum@faa.gov. 

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 all Harry E. Williams de 

Havilland Model DH 82A airplanes, all 

Cliff Robertson de Havilland Model DH 

82A airplanes, and all de Havilland 

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