52174 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 

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 above, I 

certify this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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 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): 

2014–17–08 Pratt & Whitney Canada Corp.: 

Amendment 39–17961; Docket No. 

FAA–2013–0766; Directorate Identifier 

2013–NE–26–AD. 

(a) Effective Date 

This AD becomes effective October 8, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

Canada Corp. (P&WC) PT6A–114 and PT6A– 

114A turboprop engines. 

(d) Unsafe Condition 

This AD was prompted by several 

incidents of compressor turbine (CT) blade 

failure, causing power loss, and engine 

failure. We are issuing this AD to prevent 

failure of CT blades, which could lead to 

damage to the engine and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For engines that have CT blades 

installed other than P&WC single crystal CT 

blades, part numbers (P/Ns) 3072791–01 or 

3072791–02, perform the following actions: 

(i) Within 150 operating hours after the 

effective date of this AD, perform a borescope 

inspection (BSI) of CT blades for engines 

with 500 or more hours time-since-new that 

have not been previously inspected or timesince-last-inspection (TSLI). 

(ii) Thereafter, repeat the inspection in 

paragraph (e)(1)(i) of this AD within 500 

flight hours TSLI. 

(iii) During the next hot section inspection 

(HSI) after the effective date of this AD, and 

each HSI thereafter, replace the complete set 

of CT blades with any of the following: 

(A) New CT blades; 

(B) CT blades that have passed a two-blade 

metallurgical examination in accordance 

with paragraph 3.B., Accomplishment 

Instructions, of P&WC Service Bulletin (SB) 

No. PT6A–72–1669, Revision 9, dated June 

28, 2013; or 

(C) P&WC single crystal CT blades, P/Ns 

3072791–01 or 3072791–02. 

(2) Reserved. 

(f) Mandatory Terminating Action 

Within 36 months after the effective date 

of this AD, replace the complete set of CT 

blades with P&WC single crystal CT blades, 

P/Ns 3072791–01 or 3072791–02. 

(g) Credit for Previous Action 

If you performed a metallurgical 

examination of single crystal CT blades 

before the effective date of this AD in 

accordance with P&WC SB No. PT6A–72– 

1669, Revision 8, dated January 17, 2013, or 

earlier versions, all of which are not 

incorporated by reference, you have met the 

initial inspection requirements of paragraph 

(e)(1)(i) of this AD. However, you must still 

comply with the repetitive BSI requirement 

of paragraph (e)(1)(ii) of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7154; fax: 781–238–7199; 

email: robert.c.morlath@faa.gov. 

(2) Refer to Transport Canada Civil 

Aviation AD CF–2013–21R1, dated 

November 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-2013-0766-0008. 

(j) 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) Pratt & Whitney Canada Service Bulletin 

No. PT6A–72–1669, Revision 9, dated June 

28, 2013. 

(ii) Reserved. 

(3) For P&WC service information 

identified in this AD, contact Pratt & Whitney 

Canada Corp., 1000 Marie-Victorin, 

Longueuil, Quebec, Canada, J4G 1A1; phone: 

800–268–8000; fax: 450–647–2888; Internet: 

www.pwc.ca. 

(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 

August18, 2014. 

Richard P. Warren, 

Acting Assistant Directorate Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–20453 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0137; Directorate 

Identifier 2013–NM–135–AD; Amendment 

39–17960; AD 2014–17–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 52175 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 series airplanes; 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes; Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes); and Model A310 series 

airplanes. This AD was prompted by 

reports of rupture of the uplock springs 

of the nose landing gear (NLG) and main 

landing gear (MLG) doors and legs. This 

AD requires repetitive inspections of the 

uplock springs of the NLG and MLG 

doors and legs for broken and damaged 

springs, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct improper free fall 

extension of the MLG or NLG, which 

could lead to possible loss of control of 

the airplane on the ground, and 

consequent damage to the airplane and 

injury to occupants. 

DATES: This AD becomes effective 

October 8, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 8, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0137; 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 Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

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 Airbus Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, and F4–600R series airplanes; 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. The NPRM 

published in the Federal Register on 

March 7, 2014 (79 FR 13003). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0150, 

dated July 16, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, and F4–600R series airplanes; 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. The MCAI states: 

Some cases of Nose Landing Gear (NLG) and 

Main Landing Gear (MLG) Door and Leg 

Uplock spring ruptures on A300, A310 or 

A300–600 aeroplanes have been reported in 

service. 

Springs within the uplock are used to 

either lock the gear or the door in the up 

position, or to participate in emergency 

mechanical unlocking. 

The springs are positioned in pairs, and in 

case of rupture of one spring the other one 

remains to fulfill the function, whereas the 

rupture of both springs will disable the 

locking function or the emergency unlocking 

function. 

This condition, if not detected and 

corrected, could prevent proper free fall 

extension of the MLG or NLG, possibly 

leading to loss of control of the aeroplane on 

the ground, consequently resulting in damage 

to the aeroplane and injury to occupants. 

For the reason described above, this 

[EASA] AD requires [repetitive] detailed 

visual inspection[s] of the NLG and MLG 

Door and Leg Uplock springs [for broken and 

damaged springs] and, depending of findings, 

their replacement. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0137- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 13003, March 7, 2014) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

We have become aware that some 

operators have misunderstood or 

misinterpreted the Airworthy Product 

paragraph to allow the owner/operator 

to use messages provided by the 

manufacturer as approval of deviations 

during the accomplishment of an ADmandated action. The Airworthy 

Product paragraph does not approve 

messages or other information provided 

by the manufacturer for deviations to 

the requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 


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52176 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

13003, March 7, 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 13003, 

March 7, 2014). 

We also 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 156 

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 

Repetitive inspections ... 1 work-hour × $85 per hour = $85 per inspection.$0 $85 per inspection ....... $13,260 per inspection. 

In addition, we estimate that any 

necessary replacement would take about 

9 work-hours for a cost of $765 per 

product. The cost of parts is minimal. 

We have no way of determining the 

number of aircraft that might need this 

action. 

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 above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0137; 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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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): 

2014–17–07 Airbus: Amendment 39–17960. 

Docket No. FAA–2014–0137; Directorate 

Identifier 2013–NM–135–AD. 

(a) Effective Date 

This AD becomes effective October 8, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1), (c)(2), (c)(3), 

(c)(4), (c)(5), and (c)(6) of this AD; certificated 

in any category; all serial numbers. 

(1) Model A300 B2–1A, B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Model A300 B4–601, B4–603, B4–620, 

and B4–622 airplanes. 

(3) Model A300 B4–605R and B4–622R 

airplanes. 

(4) Model A300 F4–605R and F4–622R 

airplanes. 

(5) Model A300 C4–605R Variant F 

airplanes. 

(6) Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports of 

rupture of the uplock springs of the nose 

landing gear (NLG) and main landing gear 

(MLG) doors and legs. We are issuing this AD 

to detect and correct improper free fall 

extension of the MLG or NLG, which could 

lead to possible loss of control of the airplane 

on the ground, and consequent damage to the 

airplane and injury to occupants. 


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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 52177 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Within 18 months after the effective date 

of this AD: Perform a detailed inspection of 

the uplock springs of the MLG and NLG legs 

and doors for broken and damaged springs, 

in accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (g)(1), 

(g)(2), or (g)(3) of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 18 months. 

(1) Airbus Service Bulletin A300–32–0465, 

Revision 01, dated April 25, 2013 (for Model 

A300 series airplanes). 

(2) Airbus Service Bulletin A300–32–6111, 

Revision 01, dated April 25, 2013 (for Model 

A300–600 series airplanes). 

(3) Airbus Service Bulletin A310–32–2147, 

Revision 01, dated April 25, 2013 (for Model 

A310 series airplanes). 

(h) Corrective Actions 

The corrective actions required by 

paragraphs (h)(1), (h)(2), and (h)(3) of this AD 

do not constitute terminating actions for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(1) If, during any inspection required by 

paragraph (g) of this AD, one spring on the 

MLG or NLG door uplock is found broken or 

damaged, within 2 months after the 

inspection, replace the affected MLG or NLG 

door uplock, as applicable, with a serviceable 

part, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

(2) If, during any inspection required by 

paragraph (g) of this AD, one spring on the 

MLG or NLG leg uplock is found broken or 

damaged, repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed 50 flight cycles. 

Replacement of any affected leg uplock, as 

required by paragraph (h)(2)(i) or (h)(2)(ii) of 

this AD, as applicable, constitutes 

terminating action for the repetitive 

inspections required by paragraph (h)(2) of 

this AD. 

(i) If, during any inspection required by 

paragraph (h)(2) of this AD, the second free 

fall spring on the MLG or NLG leg uplock is 

found broken or damaged, before further 

flight, replace the affected MLG or NLG leg 

uplock, as applicable, with a serviceable part, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. 

(ii) Within 1,000 flight cycles after doing 

the inspection required by paragraph (g) of 

this AD during which the spring has been 

found broken, replace the affected MLG or 

NLG leg uplock, as applicable, with a 

serviceable part, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

(3) If, during any inspection required by 

paragraph (g) of this AD, two free fall springs 

on the same MLG or NLG leg uplock are 

found broken or damaged, before further 

flight, replace the affected MLG or NLG leg 

uplock, as applicable, with a serviceable part, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

applicable actions required by paragraphs (g) 

and (h) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable service information 

identified in paragraph (i)(1), (i)(2), or (i)(3) 

of this AD. 

(1) Airbus Service Bulletin A300–32–0465, 

dated July 20, 2012, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A300–32–6111, 

dated July 20, 2012, which is not 

incorporated by reference in this AD. 

(3) Airbus Service Bulletin A310–32–2147, 

dated July 20, 2012, which is not 

incorporated by reference in 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0150, dated 

July 16, 2013, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0137-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–32–0465, 

Revision 01, dated April 25, 2013. 

(ii) Airbus Service Bulletin A300–32–6111, 

Revision 01, dated April 25, 2013. 

(iii) Airbus Service Bulletin A310–32– 

2147, Revision 01, dated April 25, 2013. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this 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. 

(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 Renton, Washington, on August 

15, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20259 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0617; Directorate 

Identifier 2014–CE–019–AD; Amendment 

39–17962; AD 2014–17–09 

RIN 2120–AA64 

Airworthiness Directives; Various de 

Havilland Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

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 requires inspecting the aircraft 

maintenance records and/or the 

installed lateral fuselage tie rods and 


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