5028 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401 and –402 airplanes, 

certificated in any category, serial numbers 

4001 through 4454 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32; Main Landing Gear. 

(e) Reason 

This AD was prompted by reports of two 

in-service incidents where one side of the 

main landing gear (MLG) did not achieve 

down-lock. We are issuing this AD to detect 

and correct insufficiently greased stabilizer 

brace lock linkage of the MLG and overtorqued lock linkage attachment bolts, which 

could lead to the failure to extend and downlock the MLG, and could affect the safe 

landing of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 1,000 flight hours or 6 months after 

the effective date of this AD, whichever 

occurs first: Do a detailed inspection of the 

apex joints of the stabilizer brace lock link in 

the main landing gear (MLG) for clearance, in 

accordance with paragraph 3.B., 

‘‘Procedure,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–32–121, dated May 27, 2013. 

(1) If the clearance gap is 0.001 inches 

(0.025 millimeters) or greater, do the action 

in paragraph (h) of this AD at the time 

specified in paragraph (h) of this AD. 

(2) If the clearance gap is less than 0.001 

inches (0.025 millimeters), before further 

flight, rectify the clearance gap, in 

accordance with paragraph 3.B., 

‘‘Procedure,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–32–121, dated May 27, 2013; and do the 

action in paragraph (h) of this AD at the time 

specified in paragraph (h) of this AD. If the 

clearance gap cannot be rectified in 

accordance with Bombardier Service Bulletin 

84–32–121, dated May 27, 2013: Before 

further flight, repair using a method 

approved by the Manager, New York Aircraft 

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

or Transport Canada Civil Aviation (TCCA); 

or Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). After the repair is done, 

do the action in paragraph (h) of this AD at 

the time specified in paragraph (h) of this 

AD. 

Note 1 to paragraphs (g) and (h) of this AD: 

Completion of the actions in this AD does not 

affect the actions specified in the existing 

maintenance review board (MRB) task 

number 320001–201. 

(h) Lubrication 

Within 1,000 flight hours or 6 months after 

the effective date of this AD, whichever 

occurs first: Lubricate the apex joints of the 

stabilizer brace lock link in the MLG, in 

accordance with paragraph 3.B., 

‘‘Procedure,’’ of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–32–121, dated May 27, 2013. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (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, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–19, dated 

July 31, 2013, for related information. This 

MCAI may be found in the AD docket on the 

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

MCAI may be found in the AD docket on the 

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

searching for and locating it in Docket No. 

FAA–2014–0188. 

(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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 84–32–121, 

dated May 27, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, 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. 

(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 January 

14, 2015. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01180 Filed 1–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0173; Directorate 

Identifier 2013–NM–069–AD; Amendment 

39–18083; AD 2015–02–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–06– 

06 for all Airbus Model A310 and 

A300–600 series airplanes. AD 2009– 

06–06 required revising the 

Airworthiness Limitations Section of 

the Instructions for Continued 

Airworthiness to incorporate new 

limitations and maintenance tasks for 

aging systems maintenance. This new 

AD requires revising the maintenance or 

inspection program to incorporate new 

maintenance requirements and 

airworthiness limitations. This AD was 

prompted by a determination that more 

restrictive maintenance requirements 

and airworthiness limitations are 

necessary. We are issuing this AD to 

prevent reduced structural integrity and 

reduced control of these airplanes due 

to the failure of system components. 

DATES: This AD becomes effective 

March 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 28, 2009 (74 FR 

12228, March 24, 2009). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0173; or in 

person at the Docket Management 


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Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 5029 

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 to supersede AD 2009–06–06, 

Amendment 39–15842 (74 FR 12228, 

March 24, 2009). AD 2009–06–06 

applied to all Airbus Model A310 and 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes series 

airplanes. The NPRM published in the 

Federal Register on March 28, 2014 (79 

FR 17451). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0075, dated March 20, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for Airbus Model 

A310–203, –204, –221, –222, –304, 

–322, –324, and –325 airplanes; Model 

A300 B4–601, B4–603, B4–620, and B4– 

622 airplanes; Model A300 B4–605R 

and B4–622R airplanes; Model A300 

F4–605R and F4–622R airplanes; and 

Model A300 C4–605R Variant F 

airplanes. The MCAI states: 

The airworthiness limitations for Airbus 

aeroplanes are currently published in 

Airworthiness Limitations Section (ALS) 

documents. 

The mandatory instructions and 

airworthiness limitations applicable to the 

Aging Systems Maintenance (ASM) are 

specified in Airbus A310 or A300–600 ALS 

Part 4 documents, which are approved by the 

European Aviation Safety Agency (EASA). 

EASA AD 2007–0092 [http://

ad.easa.europa.eu/blob/easa_ad_2007_

0092.pdf/AD_2007-0092, which corresponds 

to FAA AD 2009–06–06, Amendment 39– 

15842 (74 FR 12228, March 24, 2009)] was 

issued to require compliance to the 

requirements as specified in these 

documents. 

The revision 02 of Airbus A310 and Airbus 

A300–600 ALS Part 4 documents introduces 

more restrictive maintenance requirements 

and/or airworthiness limitations. Failure to 

comply with the instructions of ALS Part 4 

could result in an unsafe condition. 

For the reasons described above, this new 

AD retains the requirements of EASA AD 

2007–0092, which is superseded, and 

requires the implementation of the new or 

more restrictive maintenance requirements 

and/or airworthiness limitations as specified 

in Airbus A310 ALS Part 4, Revision 02, or 

Airbus A300–600 ALS Part 4, Revision 02, as 

applicable to aeroplane type/model. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0173- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (74 FR 12228, 

March 24, 2009), and the FAA’s 

response to the comment. 

Request To Include Variation to Service 

Information 

FedEx asked that Airbus A300–600 

Variation 0CVLG120001/C0S, dated 

August 24, 2012, to Airbus A300–600 

ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated April 

18, 2012, be included with the service 

information referenced for 

accomplishing the actions specified in 

the NPRM (74 FR 12228, March 24, 

2009). FedEx stated that this variation 

provides additional trimmable 

horizontal stabilizer actuator (THSA) 

part numbers and is approved by EASA. 

We agree with the commenter’s 

request. The referenced variation added 

some dash numbers that were not 

previously listed in the Airworthiness 

Limitation Items (ALI), but all airplanes 

affected by the NPRM (74 FR 12228, 

March 24, 2009) have this basic part 

number. We have revised paragraph (j) 

of this AD to refer to Airbus A300–600 

Variation 0CVLG120001/C0S, dated 

August 24, 2012, to Airbus A300–600 

ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated April 

18, 2012. 

‘‘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 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 


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5030 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

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, 

considered the comment received, 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 

17451, March 28, 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 17451, 

March 28, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information 

Airbus has issued A310 

Airworthiness Limitations Section 

(ALS) Part 4—Ageing Systems 

Maintenance, Revision 02, dated 

November 30, 2012; and A300–600 ALS 

Part 4—Ageing Systems Maintenance, 

Revision 02, dated April 18, 2012. The 

service information describes 

procedures for revising the maintenance 

or inspection program to incorporate 

new maintenance requirements and 

airworthiness limitations. You can find 

this information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0173. 

Costs of Compliance 

We estimate that this AD affects 156 

airplanes of U.S. registry. 

The ALS revision required by AD 

2009–06–06, Amendment 39–15842 (74 

FR 12228, March 24, 2009), and retained 

in this AD takes about 1 work-hour per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that 

were required by AD 2009–06–06 is $85 

per product. 

We also estimate that it takes about 1 

work-hour per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$13,260, or $85 per product. 

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-2014-0173; 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 

removing Airworthiness Directive (AD) 

2009–06–06, Amendment 39–15842 (74 

FR 12228, March 24, 2009), and adding 

the following new AD: 

2015–02–16 Airbus: Amendment 39–18083. 

Docket No. FAA–2014–0173; Directorate 

Identifier 2013–NM–069–AD. 

(a) Effective Date 

This AD becomes effective March 6, 2015. 

(b) Affected ADs 

This AD replaces AD 2009–06–06, 

Amendment 39–15842 (74 FR 12228, March 

24, 2009). 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes; Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes; Model A300 

B4–605R and B4–622R airplanes; Model 

A300 F4–605R and F4–622R airplanes, and 

Model A300 C4–605R Variant F airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls; Code 32, 

Landing Gear. 

(e) Reason 

This AD was prompted by a determination 

that more restrictive maintenance 

requirements and airworthiness limitations 

are necessary. We are issuing this AD to 

prevent reduced structural integrity and 

reduced control of these airplanes due to the 

failure of system components. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


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Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 5031 

(g) Retained Revision of Airworthiness 

Limitation Section (ALS) To Incorporate 

Limitations and Maintenance Tasks for 

Aging Systems Maintenance 

This paragraph restates the requirements of 

paragraph (n) of AD 2009–06–06, 

Amendment 39–15842 (74 FR 12228, March 

24, 2009). Within 3 months after April 28, 

2009 (the effective date of AD 2009–06–06), 

revise the ALS of the Instructions for 

Continued Airworthiness (ICA) to 

incorporate Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006 (for Model A310 series 

airplanes); or Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 01, 

dated December 21, 2006 (for Model A300– 

600 series airplanes). For all tasks identified 

in Airbus A310 ALS Part 4—Ageing Systems 

Maintenance, Revision 01, dated December 

21, 2006; and Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 01, 

dated December 21, 2006; do the tasks at the 

later of the times specified in paragraphs 

(g)(1) and (g)(2) of this AD, as applicable, 

except as provided by paragraph (h) of this 

AD. The repetitive inspections must be 

accomplished thereafter at the interval 

specified in Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006; or Airbus A300–600 ALS 

Part 4—Ageing Systems Maintenance, 

Revision 01, dated December 21, 2006; as 

applicable. 

(1) At the initial compliance times 

(thresholds) specified in Airbus A310 ALS 

Part 4—Ageing Systems Maintenance, 

Revision 01, dated December 21, 2006; or 

Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006; as applicable; with the 

compliance times starting from the later of 

the times specified in paragraphs (g)(1)(i) and 

(g)(1)(ii) of this AD. 

(i) Since first flight of the airplane. 

(ii) Since the applicable part was new or 

refurbished if the part’s life (in flight hours, 

flight cycles, landings, or calendar time, as 

applicable) can be conclusively determined. 

(2) Within 3 months after doing the 

revision of the ALS of the ICA required by 

paragraph (h) of this AD. 

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

additional guidance on the trimmable 

horizontal stabilizer actuators (THSA) life 

limits, refer to Airbus Operators Information 

Telex (OIT) SE 999.0074/05/BB, dated 

August 3, 2005. 

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

additional guidance on the THSA life limits 

and calculation method for unknown history 

of parts, refer to Airbus OIT SE 999.0008/07/ 

LB, dated January 16, 2007; and Airbus 

Service Information Letter 05–008, Revision 

01, dated February 21, 2007. 

(h) Retained Revision of ALS To Incorporate 

Certain Other Limitations and Maintenance 

Tasks for Aging Systems Maintenance 

This paragraph restates the requirements of 

paragraph (o) of AD 2009–06–06, 

Amendment 39–15842 (74 FR 12228, March 

24, 2009), with revised affected airplane 

language. For airplanes on which any life 

limitation/maintenance task has been 

complied with in accordance with the 

requirements of paragraph (f), (g), (k), (l), or 

(m) of AD 2009–06–06: The last 

accomplishment of each limitation/task must 

be retained as a starting point for the 

accomplishment of each corresponding 

limitation/task interval now introduced 

Airbus A310 ALS Part 4—Ageing Systems 

Maintenance, Revision 01, dated December 

21, 2006; and Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 01, 

dated December 21, 2006; as applicable. 

(i) Retained No Alternative Inspections/

Limitations 

This paragraph restates the requirements of 

paragraph (p) of AD 2009–06–06, 

Amendment 39–15842 (74 FR 12228, March 

24, 2009). Except as provided by paragraph 

(l) of this AD: After accomplishing the 

actions specified in paragraphs (g) and (h) of 

this AD, no alternative inspection, inspection 

intervals, or limitations may be used, except 

as required by paragraph (j) of this AD. 

(j) New Requirements of This AD: 

Maintenance/Inspection Program Revision 

Within 3 months after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, to 

incorporate Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

November 30, 2012 (for Model A310 series 

airplanes); or Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 02, 

dated April 18, 2012, and Airbus A300–600 

Variation 0CVLG120001/C0S, dated August 

24, 2012, to Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 02, 

dated April 18, 2012 (for Model A300–600 

series airplanes). For all limitation/

replacement/inspection tasks identified in 

Airbus A310 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated November 

30, 2012; or Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 02, 

dated April 18, 2012, and Airbus A300–600 

Variation 0CVLG120001/C0S, dated August 

24, 2012, to Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 02, 

dated April 18, 2012; the initial compliance 

times for the tasks are at the later of the times 

specified in paragraphs (j)(1) and (j)(2) of this 

AD, as applicable. Doing any limitation/

replacement/inspection task required by this 

paragraph terminates the corresponding task 

required by paragraph (g) of this AD. 

(1) At the initial compliance times 

(thresholds) specified in Airbus A310 ALS 

Part 4—Ageing Systems Maintenance, 

Revision 02, dated November 30, 2012; or 

Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

April 18, 2012, and Airbus A300–600 

Variation 0CVLG120001/C0S, dated August 

24, 2012, to Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 02, 

dated April 18, 2012; as applicable; with the 

compliance times starting from the later of 

the times specified in paragraphs (j)(1)(i) and 

(j)(1)(ii) of this AD. 

(i) Since first flight of the airplane. 

(ii) Since the applicable part was new or 

refurbished if the part’s life (in flight hours, 

flight cycles, landings, or calendar time, as 

applicable) can be conclusively determined. 

(2) Within 3 months after the effective date 

of this AD. 

(k) New Limitation: No Alternative Actions 

or Intervals 

After accomplishment of the revision 

required by paragraph (j) of this AD, no 

alternative actions (e.g., inspections) or 

intervals, may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (l)(1) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: As of the 

effective date of this AD, 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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0075, dated 

March 20, 2013, for related information. You 

may examine the MCAI in the AD docket on 

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

#!documentDetail;D=FAA-2014-0173-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (n)(5) and (n)(6) of this AD. 

(n) 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. 

(3) The following service information was 

approved for IBR on March 6, 2015. 

(i) Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

April 18, 2012. 


rljohnson on DSK4SPTVN1PROD with RULES
5032 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

(ii) Airbus A300–600 Variation 

0CVLG120001/C0S, dated August 24, 2012, 

to Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

April 18, 2012. 

(iii) Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

November 30, 2012. 

(4) The following service information was 

approved for IBR on April 28, 2009 (74 FR 

12228, March 24, 2009). 

(i) Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006. 

(ii) Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006. 

(5) 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. 

(6) 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. 

(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 January 

13, 2015. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01182 Filed 1–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0525; Directorate 

Identifier 2013–NM–235–AD; Amendment 

39–18078; AD 2015–02–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–300, A340–200, 

and A340–300 series airplanes. This AD 

was prompted by a report of substantial 

inner skin disbonding damage found on 

a rudder. This AD requires performing 

an inspection for damage of certain 

rudders, and repair if necessary. We are 

issuing this AD to detect and correct 

damage of the rudder, which could 

result in reduced structural integrity of 

the rudder. 

DATES: This AD becomes effective 

March 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 6, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov/#!docketDetail;

D=FAA-2014-0525; 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—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

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 certain Airbus Model A330– 

300, A340–200, and A340–300 series 

airplanes. The NPRM published in the 

Federal Register on August 13, 2014 (79 

FR 47387). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0270R1, dated 

November 27, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for Airbus Model A330–300, A340–200, 

and A340–300 series airplanes. The 

MCAI states: 

One A310 operator found substantial inner 

skin disbonding damage on a rudder. The 

results of the subsequent investigation 

revealed that the most probable cause of this 

damage was a blunt impact with no visible 

damage from outside during the rudder 

handling. Such type of damage might grow 

with pressure variation during ground-airground cycles, and tests performed with 

other rudders showed a rapid propagation of 

damage during artificial pressure cycling. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder. 

For the affected A310 and A300–600 

aeroplanes, EASA issued AD 2013–0039 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0039.pdf/AD_2013-0039], to address 

and correct this potential unsafe condition. 

As potentially affected rudders can also be 

installed on A330 and A340 aeroplanes, 

Airbus issued Alert Operator Transmission 

(AOT) A55L001–12 [dated December 20, 

2012], pending Aircraft Maintenance Manual 

(AMM) 27–21–41 PB401 revision, to provide 

operators with updated rudder handling 

procedures. 

EASA issued AD 2013–0270 [http://

ad.easa.europa.eu/blob/easa_ad_2013_

0270.pdf/AD_2013-0270], to require 

identification of affected rudders P/N [part 

number] A55471500XXX (where XXX stands 

for any numerical value), a one-time 

ultrasonic test (UT) inspection of each 

affected rudder to detect signs of disbonding 

and, depending on findings, accomplishment 

of applicable corrective action(s). 

After [EASA] AD 2013–0270 was issued, 

operators commented that the batch of 

rudders to be inspected was not correctly 

defined. 

For the reason described above, [EASA] AD 

2013–0270 is revised to clarify that no action 

is required for rudders previously inspected 

in accordance with Airbus Service Bulletin 

(ASB) A330–55–3038 or SB A340–55–4034 

[which are required by FAA AD 2009–10–11, 

Amendment 39–15907 (74 FR 23622, May 20, 

2009)], as applicable to aeroplane model, 

provided the rudder has never been removed 

and/or installed on an aeroplane since this 

inspection. 

Required actions include an elasticity 

of laminate checker inspection of the 

rudder side panel to detect external and 

internal disbonding, and a woodpecker 

or tap test inspection to detect external 

disbonding, and repair if necessary. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0525- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 47387, 

August 13, 2014) and the FAA’s 

response. 

Request To Correct Certain Document 

Numbers 

Lufthansa Technik (Lufthansa) asked 

that we correct certain document 


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