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 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 71303 

Model DH 83 airplanes. The NPRM 

published in the Federal Register on 

September 15, 2014 (79 FR 54919). The 

NPRM was prompted by reports of 

structural failure of the attachment of 

the wing to the fuselage that resulted 

from failed lateral fuselage tie rods. The 

NPRM proposed to require inspecting 

the aircraft maintenance records to 

determine the date of installation or the 

date of last replacement of the lateral 

fuselage tie rods. The NPRM also 

proposed to require 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 54919, September 15, 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 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 (79 FR 

54919, September 15, 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 54919, 

September 15, 2014). 

Costs of Compliance 

We estimate that this AD will affect 

69 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 

Inspect the aircraft maintenance records to determine the date of installation or date of last replacement of the lateral fuselage tie rods and attaching 

nuts.

1 work-hour × $85 per 

hour = $85.

Not applicable .................. $85 $5,865 

We estimate the following costs to the 

necessary replacements. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Replace lateral fuselage tie rods and attaching nuts ... 30 work-hours × $85 per hour = $2,550 ...................... $825 $3,375 

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, 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): 

2014–24–01 Harry E. Williams, Cliff 

Robertson, and de Havilland Airplanes: 

Amendment 39–18034; Docket No. 

FAA–2014–0701; Directorate Identifier 

2014–CE–025–AD. 

(a) Effective Date 

This AD is effective January 6, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Harry E. Williams and 

Cliff Robertson de Havilland Model DH 82A 

airplanes, all serial numbers, and de 

Havilland Model DH 83 airplanes, all serial 

numbers, certificated in any category. 

mstockstill on DSK4VPTVN1PROD with RULES

71304 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 5341, Fuselage, Wing Attach Fittings. 

(e) Unsafe Condition 

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. We are issuing this 

AD to correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraphs (g) 

through (h) of this AD, unless already done. 

(g) Determine Date of Installation or Date of 

Last Replacement of the Lateral Fuselage Tie 

Rods and Attaching Nuts 

Within the next 30 days after January 6, 

2015 (the effective date of this AD), review 

the aircraft records to determine the date of 

installation or date of last replacement of the 

lateral fuselage tie rods and attaching nuts. 

(h) Replace the Lateral Fuselage Tie Rod and 

Attaching Nuts 

Initially replace the lateral fuselage tie rod 

and attaching nuts at whichever of the 

compliance times specified in paragraph 

(h)(1) or paragraph (h)(2) of this AD that 

applies. Repetitively thereafter replace the 

lateral fuselage tie rod and attaching nuts 

every 2,000 hours TIS or 18 years, whichever 

occurs first. Do the replacement following the 

procedures in paragraph 2.C. of the 

Accomplishment Instructions and the table 

on Figure 1 in British Aerospace Military 

Aircraft and Aerostructures BAe Aircraft 

Bulletin for De Havilland Moth Aircraft, 

Document Type and Ref No Technical News 

Sheet CT (Moth) No 29, Issue 3, dated March 

1, 1999. 

(1) If the date of lateral fuselage tie rod 

installation or date of last replacement is 

known: Do the initial replacement at 

whichever of the following compliance times 

in paragraph (h)(1)(i) or paragraph (h)(1)(ii) of 

this AD that occurs later: 

(i) Upon accumulating 2,000 hours TIS on 

the lateral fuselage tie rod or upon reaching 

18 years from the last lateral fuselage tie rod 

replacement, whichever occurs first; or 

(ii) Within the next 6 months after January 

6, 2015 (the effective date of this AD) or 

within the next 100 hours TIS January 6, 

2015 (after the effective date of this AD), 

whichever occurs first. 

(2) If the date of lateral fuselage tie rod 

installation or date of last replacement is not 

known: Do the initial replacement within the 

next 6 months after January 6, 2015 (the 

effective date of this AD) or within the next 

100 hours TIS after January 6, 2015 (the 

effective date of this AD), whichever occurs 

first. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager of the Fort Worth 

Airplane Certification Office (ACO), the 

Manager of the Los Angeles Aircraft 

Certification Office (ACO), and the Manager 

of the Standards Office, FAA, have the 

authority to approve AMOCs for their 

respective products covered by 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 applicable FAA office, 

send it to the attention of the person 

identified in paragraphs (j)(1), (j)(2), or (j)(3), 

as applicable. 

(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. 

(j) Related Information 

(1) For more information about this AD for 

airplanes covered under Type Certificate 

Data Sheet (TCDS) A5PC (Model de 

Havilland DH 82A airplanes built in 

Australia), contact Andrew McAnaul, 

Aerospace Engineer, FAA, Fort Worth ACO, 

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. 

(2) For more information about this AD for 

airplanes covered under TCDS A8EU (Model 

de Havilland DH 82A airplanes built in the 

United Kingdom), contact Fred Guerin, 

Aerospace Engineer, FAA, Los Angeles ACO, 

3960 Paramount Blvd., Suite 100, Lakewood, 

California 90712; phone (562) 627–5232; fax: 

(562) 627–5210; email: fred.guerin@faa.gov. 

(3) For more information about this AD for 

airplanes covered under TCDS 2–439 (Model 

de Havilland DH 83 airplanes built in the 

United Kingdom), contact Karl Schletzbaum, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329– 

4123; fax: (816) 329–4090; email: 

karl.schletzbaum@faa.gov. 

(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) British Aerospace Military Aircraft and 

Aerostructures BAe Aircraft Bulletin for De 

Havilland Moth Aircraft, Document Type and 

Ref No Technical News Sheet CT (Moth) No 

29, Issue 3, dated March 1, 1999. 

(ii) Reserved. 

(3) For British Aerospace Military Aircraft 

and Aerostructures service information 

identified in this AD, contact: 

(i) For de Havilland DH 82A airplanes: 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. 

(ii) For de Havilland DH 83 airplanes: Air 

Stratus Ltd., Oaksey Park Airfield, Oaksey, 

Malmesbury, Wiltshite, United Kingdom SN 

16 9SD; telephone: +44 (0) 1666 575111; no 

known Internet address. 

(4) You may view this service information 

at 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 

November 18, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–27789 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–2014–0776; Directorate 

Identifier 2013–NM–240–AD; Amendment 

39–18033; AD 2014–23–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–20– 

06 for all Airbus Model A340–211, 

–212, –213, –311, –312, –313, –541, and 

–642 airplanes. AD 2013–20–06 

required revising the maintenance 

program to incorporate certain 

maintenance requirements and 

airworthiness limitations. This new AD 

requires revising the maintenance or 

inspection program to incorporate 

certain other maintenance requirements 

and airworthiness limitations. This AD 

was prompted by a determination that 

existing maintenance requirements are 

not adequate to address the aging effects 

of aircraft systems. We are issuing this 

AD to address the aging effects of 

aircraft systems. Such aging effects 

could change the characteristics of 

systems’ life-limited components 

leading to an increased potential for 

failure, which, in isolation or in 

combination with one or more other 

specific failures or events, could result 

in failure of certain life limited parts, 

which could reduce the structural 

integrity or the controllability of the 

airplane. 

mstockstill on DSK4VPTVN1PROD with RULES