Federal Register / Vol. 79, No. 156 / Wednesday, August 13, 2014 / Proposed Rules 47395 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Bombardier, Inc.: Docket No. FAA–2014– 

0528; Directorate Identifier 2014–NM– 

060–AD. 

(a) Comments Due Date 

We must receive comments by September 

29, 2014. 

(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 4109 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 31, Main Landing Gear. 

(e) Reason 

This AD was prompted by a report that 

during production, an incorrect clevis was 

used, resulting in improper installation onto 

the alternate release cable of the main 

landing gear (MLG). We are issuing this AD 

to detect and correct improper installation of 

the clevis, which could cause loss of the 

alternate release system and prevent the MLG 

from extending and retracting, and could 

consequently affect the airplane’s continued 

safe flight and landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 2,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first: Do a general visual inspection of 

the emergency release clevis of the MLG to 

determine if an incorrect clevis has been 

installed, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–32–67, dated July 8, 

2009. If an incorrect clevis has been installed, 

before further flight, replace the clevis with 

a correct clevis and clevis pin, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–32–67, dated 

July 8, 2009. 

(h) 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 New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516 228–7300; fax 516– 

794–5531. Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–40, dated 

December 9, 2013, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–0528. 

(2) 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. 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. 

Issued in Renton, Washington, on August 

1, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19156 Filed 8–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0529; Directorate 

Identifier 2013–NM–260–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2011–13– 

11 and AD 2013–16–09, for all Airbus 

Model A318, A319, A320, and A321 

series airplanes. AD 2011–13–11 

currently requires an amendment of the 

airplane flight manual (AFM), repetitive 

checks of specific centralized fault 

display system (CFDS) messages, an 

inspection of the opening sequence of 

the main landing gear (MLG) door 

actuator for discrepancies if certain 

messages are found, and corrective 

actions if necessary. AD 2013–16–09 


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47396 Federal Register / Vol. 79, No. 156 / Wednesday, August 13, 2014 / Proposed Rules 

currently requires an inspection to 

determine airplane configuration and 

part numbers of the landing gear control 

interface unit and MLG door actuators; 

and, for affected airplanes, repetitive 

inspections of the opening sequence of 

the MLG door actuator, and replacement 

of the MLG door actuator if necessary; 

and provides optional terminating 

action for the repetitive inspections. 

Since we issued AD 2011–13–11 and 

AD 2013–16–09, we have determined 

that the interval of the MLG door 

opening sequence inspection must be 

reduced. This proposed AD would 

reduce the interval of the MLG door 

opening sequence inspection. This 

proposed AD would also require 

replacing or modifying certain MLG 

door actuators. We are proposing this 

AD to detect and correct deterioration of 

the damping ring and associated 

retaining ring of the MLG door actuator, 

which can sufficiently increase the 

friction inside the actuator to restrict 

opening of the MLG door by gravity, 

during operation of the landing gear 

alternate (free-fall) extension system. 

This condition could prevent the full 

extension and/or down-locking of the 

MLG, possibly resulting in MLG 

collapse during landing and consequent 

damage to the airplane and injury to 

occupants. 

DATES: We must receive comments on 

this proposed AD by September 29, 

2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus, Airworthiness Office—EIAS, 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. For 

General Electric service information 

identified in this AD contact GE 

Aviation, Customer Support Center, 1 

Neumann Way, Cincinnati, OH 45215; 

phone: 513–552–3272; email: 

cs.techpubs@ge.com; Internet: http://

www.geaviation.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. 

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– 

0529; 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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0529; Directorate Identifier 

2013–NM–260–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 16, 2011, we issued AD 

2011–13–11, Amendment 39–16734 (76 

FR 37241, June 27, 2011). AD 2011–13– 

11 required actions intended to address 

an unsafe condition on all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. The unsafe condition is the 

deterioration of the damping ring and 

associated retaining ring of the MLG 

door actuator, which can sufficiently 

increase the friction inside the actuator 

to restrict opening of the MLG door by 

gravity, during operation of the landing 

gear alternate (free-fall) extension 

system. This condition could prevent 

the full extension and/or down-locking 

of the MLG, possibly resulting in MLG 

collapse during landing and consequent 

damage to the airplane and injury to 

occupants. 

On July 26, 2013, we issued AD 2013– 

16–09, Amendment 39–17547 (78 FR 

48286, August 8, 2013). AD 2013–16–09 

required actions intended to detect and 

correct certain configuration of landing 

gear control interface unit and actuators, 

which could prevent the full extension 

or down-locking of the MLG, possibly 

resulting in MLG collapse during 

landing and consequent damage to the 

airplane and injury to occupants on all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. 

Since we issued AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241. 

June 27, 2011), and AD 2013–16–09, 

Amendment 39–17547 (78 FR 48286, 

August 8, 2013), we have determined 

that the interval of the MLG door 

opening sequence inspection must be 

reduced in order to detect and correct 

deterioration of the damping ring and 

associated retaining ring of the MLG 

door actuator, which can sufficiently 

increase the friction inside the actuator 

to restrict opening of the MLG door by 

gravity, during operation of the landing 

gear alternate (free-fall) extension 

system. This condition, if not detected 

and corrected, could prevent the full 

extension and/or down-locking of the 

MLG, possibly resulting in MLG 

collapse during landing and consequent 

damage to the airplane and injury to 

occupants. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0288, 

dated December 6, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Some operators reported slow operation of 

the main landing gear (MLG) door opening/ 

closing sequence, leading to the generation of 

ECAM warnings during the landing gear 

retraction or extension sequence. 

Investigations showed that the damping 

ring and associated retaining ring of the MLG 

door actuator deteriorate. The resultant 

debris increases the friction inside the 

actuator which can be sufficiently high to 

restrict opening of the MLG door by gravity, 

during operation of the landing gear alternate 

(free-fall) extension system. 


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This condition, if not corrected, could 

prevent the full extension and/or down 

locking of the MLG, possibly resulting in 

MLG collapse during landing or rollout and 

consequent damage to the aeroplane and 

injury to occupants. 

EASA AD 2006–0112R1 (http://

ad.easa.europa.eu/blob/easa_ad_2006_0112_

R1_superseded.pdf/AD_2006-0112R1_1) was 

issued to require repetitive inspections of the 

opening sequence of the MLG door in order 

to identify the defective actuators, and to 

introduce as an optional terminating action 

Airbus production Modification (MOD) 

38274 and associated Service Bulletin (SB) 

A320–32–1338, which incorporate an 

improved retaining ring, located on the 

piston rod’s extension end, and a new piston 

rod with machined shoulder to accommodate 

the thicker section of the modified retaining 

ring. 

After in-service introduction of the new 

MLG door actuator, Part Number (P/N) 

114122012 (Post MOD 38274—SB A320–32– 

1338), several operators reported failures of 

internal parts of the MLG door actuator. 

Investigations confirmed that these failures 

could result in slow extension of the actuator 

rod, delaying the MLG door operation, or 

possibly stopping just before the end of the 

stroke, preventing the door to reach the fully 

open position. 

EASA AD 2011–0069R1 (http://

ad.easa.europa.eu/blob/easa_ad_2011_0069_

R1_superseded.pdf/AD_2011-0069R1_1) 

(which corresponds to FAA AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011)), which supersedes EASA AD 

2006–0112R1 required an amendment of the 

applicable Airplane Flight Manual (AFM), 

repetitive checks of specific Centralized Fault 

Display System (CFDS) messages, repetitive 

inspections of the opening sequence of the 

MLG door actuator and, depending on 

findings, corrective action(s). 

Since that [EASA] AD was issued, Airbus 

introduced a reinforced MLG door actuator 

P/N 114122014 (MOD 153655). Airbus issued 

SB A320–32–1407 containing instructions for 

in-service replacement of the affected MLG 

door actuators, or modification of the 

actuators to the new standard. 

In addition, following a recent occurrence 

with a gear extension problem, the result of 

additional analyses by Airbus revealed that 

the CFDS expected specific messages may 

not be generated and as a result, repetitive 

checks of messages are not effective for 

aeroplanes fitted with landing gear control 

interface unit (LGCIU) interlink 

communication ARINC 429 (applied in 

production through Airbus MOD 39303, or in 

service through Airbus SB A320–32–1409), 

in combination with LGCIUs 80–178–02– 

88012 or 80–178–03–88013 in both positions 

and at least one MLG door actuator pre MOD 

153655 (SB A320–32–1407—SB 114122–32– 

105) installed. 

Prompted by these findings, EASA issued 

Emergency AD 2013–0132–E (http://

ad.easa.europa.eu/blob/easa_ad_2013_0132_

E_superseded.pdf/EAD_2013-0132-E_1) 

(which corresponds to FAA AD 2013–16–09, 

Amendment 39–17547 (78 FR 48286, August 

8, 2013)) to require identification of the 

affected aeroplanes to establish the 

configuration and, for those aeroplanes, 

repetitive inspections of the opening 

sequence of the MLG door actuator and, 

depending on findings, replacement of the 

MLG door actuator. That [EASA] AD also 

provided an optional terminating action by 

disconnection of the interlink for certain 

LGCIUs, or in-service modification of the 

aeroplane through Airbus SB A320–32–1407 

(equivalent to production MOD 153655). 

Since those [EASA] ADs were issues, 

analyses performed by Airbus have revealed 

that the MLG door opening sequence 

inspection interval must be reduced, and that 

the (previously optional) terminating action 

must be made mandatory. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0069R1 and [EASA] AD 2013– 

0132–E, which are superseded, but with 

reduced inspection intervals, and requires 

replacement or modification [including 

related investigative and corrective actions], 

as applicable, of the affected MLG door 

actuators as terminating action for the 

monitoring, repetitive checks and 

inspections. 

The related investigative actions 

include an inspection for damage 

(including nicks and burns) of the 

damping rings and an inspection for 

mechanical damage of the piston rod. 

Corrective actions include replacing or 

modifying parts. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov by 

searching for and locating it in Docket 

No. FAA–2014–0529. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–32–1390, Revision 02, dated 

October 23, 2013; and General Electric 

has issued Service Bulletin 114122–32– 

105, Revision 1, dated March 26, 2013. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Paragraph (17) of the MCAI 

incorrectly refers to paragraph (11) of 

the MCAI as requiring inspections; 

however, paragraph (11) of the MCAI 

specifies replacement actions. 

Paragraphs (j), (l), and (p) of this 

proposed AD refer to the inspections 

specified in paragraph (17) of the MCAI. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed 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. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

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 AD-mandated 

action. The Airworthy Product 


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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 

proposed AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 

approved by the FAA, EASA, or 

Airbus’s EASA 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 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Revisions to Notes in AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, 

June 27, 2011) 

We have removed Note 1 of AD 2011– 

13–11, Amendment 39–16734 (76 FR 

37241, June 27, 2011), and included that 

information in paragraph (g)(3) of this 

proposed AD. 

We have removed Note 2 of AD 2011– 

13–11, Amendment 39–16734 (76 FR 

37241, June 27, 2011), and included that 

information in paragraph (i) of this 

proposed AD. 

We have removed Note 3 of AD 2011– 

13–11, Amendment 39–16734 (76 FR 

37241, June 27, 2011), from this 

proposed AD. The note explained 

differences with the previous MCAI. 

Change to AD 2013–16–09, Amendment 

39–17547 (78 FR 48286, August 8, 2013) 

We have moved the information 

specified in paragraph (l) of AD 2013– 

16–09, Amendment 39–17547 (78 FR 

48286, August 8, 2013), into paragraphs 

(j) and (l) of this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

The actions that are required by AD 

2011–13–11, Amendment 39–16734 (76 

FR 37241, June 27, 2011), and retained 

in this proposed AD take about 7 workhours per product, per inspection cycle, 

at an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2011–13–11 is $595 per 

product. 

The actions that are required by AD 

2013–16–09, Amendment 39–17547 (78 

FR 48286, August 8, 2013), and retained 

in this proposed AD take about 3 workhours per product, per inspection cycle, 

at an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2013–16–09 is $255 per 

product. 

We also estimate that it would take 

about 10 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $17,140 for two 

actuators. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $15,309,490, or 

$17,990 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

■ a. Removing Airworthiness Directive 

(AD) 2011–13–11, Amendment 39– 

16734 (76 FR 37241, June 27, 2011); and 

AD 2013–16–09, Amendment 39–17547 

(78 FR 48286, August 8, 2013); and 

■ b. Adding the following new AD: 

Airbus: Docket No. FAA–2014–0529; 

Directorate Identifier 2013–NM–260–AD. 

(a) Comments Due Date 

We must receive comments by September 

29, 2014. 


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(b) Affected ADs 

This AD replaces AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011); and AD 2013–16–09, Amendment 

39–17547 (78 FR 48286, August 8, 2013). 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of 

this AD, all manufacturer serial numbers. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a determination 

that the inspection interval of the MLG door 

opening sequence must be reduced. We are 

issuing this AD to detect and correct 

deterioration of the damping ring and 

associated retaining ring of the MLG door 

actuator, which can sufficiently increase the 

friction inside the actuator to restrict opening 

of the MLG door by gravity, during operation 

of the landing gear alternate (free-fall) 

extension system. This condition could 

prevent the full extension and/or downlocking of the MLG, possibly resulting in 

MLG collapse during landing and consequent 

damage to the aeroplane and injury to 

occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections/

Replacement 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011), with a formatting change. At the 

time specified in paragraph (g)(1) or (g)(2) of 

this AD, as applicable: Do a general visual 

inspection of the operation of the MLG door 

opening sequence to determine if a defective 

actuator is installed by doing all the 

applicable actions, including replacing the 

door actuator, as applicable, specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1309, Revision 01, 

dated June 19, 2006. Do all applicable 

replacements before further flight. Repeat the 

inspection thereafter at intervals not to 

exceed 900 flight cycles. Accomplishing the 

actions before April 27, 2007 (the effective 

date of AD 2007–06–18, Amendment 39– 

14999 (72 FR 13681, March 23, 2007)), in 

accordance with Airbus Service Bulletin 

A320–32–1309, dated March 7, 2006, is 

acceptable for compliance with the 

corresponding requirements in this 

paragraph. Doing the inspection required by 

paragraph (l) of this AD terminates the 

requirements of this paragraph. 

(1) For airplanes on which a record of the 

total number of flight cycles on the MLG door 

actuator is available: Before the accumulation 

of 3,000 total flight cycles on the MLG door 

actuator, or within 800 flight cycles after 

April 27, 2007 (the effective date of AD 

2007–06–18, Amendment 39–16734 (76 FR 

37241, June 27, 2011)), whichever is later. 

(2) For airplanes on which a record of the 

total number of flight cycles on the MLG door 

actuator is not available: Within 800 flight 

cycles after April 27, 2007 (the effective date 

of AD 2007–06–18, Amendment 39–16734 

(76 FR 37241, June 27, 2011)). 

(3) For the purposes of this AD, a general 

visual inspection is: ‘‘A visual examination 

of an interior or exterior area, installation, or 

assembly to detect obvious damage, failure, 

or irregularity. This level of inspection is 

made from within touching distance unless 

otherwise specified. A mirror may be 

necessary to enhance visual access to all 

exposed surfaces in the inspection area. This 

level of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

(h) Retained Provision Regarding Reporting/ 

Parts Return 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011), with no changes. Although the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1309, Revision 01, 

dated June 19, 2006, specify submitting 

certain information to the manufacturer and 

sending defective actuators back to the 

component manufacturer for investigation, 

this AD does not include those requirements. 

(i) Retained Revision of the Airplane Flight 

Manual (AFM) 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–13–11, Amendment 

39–16734 (76 FR 37241, June 27, 2011), with 

formatting changes. Within 14 days after July 

12, 2011 (the effective date of AD 2011–13– 

11), revise the Emergency Procedure Section 

of the AFM to incorporate the information in 

figure 1 to paragraph (i) of this AD. This may 

be done by inserting a copy of this AD into 

the AFM. When a statement identical to that 

in figure 1 to paragraph (i) of this AD has 

been included in the Emergency Procedure 

Section of the general revisions of the AFM, 

the general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

FIGURE 1 TO PARAGRAPH (i) OF THIS AD—AFM REVISION

• If ECAM triggers the ‘‘L/G GEAR NOT DOWNLOCKED’’ warning apply the following procedure: 

Recycle landing gear. 

• If unsuccessful after 2 min: 

Extend landing gear by gravity. Refer to AGN–32 L/G GRAVITY EXTENSION. 

(j) Retained Repetitive Checks 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–13–11, Amendment 

39–16734 (76 FR 37241, June 27, 2011), with 

new optional actions. Within 14 days after 

July 12, 2011 (the effective date of AD 2011– 

13–11), or before the accumulation of 800 

total flight cycles, whichever occurs later, 

check the post flight report (PFR) for 

centralized fault display system (CFDS) 

messages triggered within the last 8 days, in 

accordance with paragraph 4.2.1 of Airbus 

All Operators Telex (AOT) A320–32A1390, 

dated February 10, 2011. Repeat the check 

thereafter at intervals not to exceed 8 days or 

5 flight cycles, whichever occurs later. If 

done in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA, 

the use of an alternative method to check the 

PFR for CFDS messages (e.g., AIRMAN) is 

acceptable in lieu of this check if the 

messages can be conclusively determined 

from that method. Repetitive inspections of 

the door opening sequence of the left-hand 

(LH) and right-hand (RH) doors of the MLG, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–32–1390, Revision 02, dated 

October 23, 2013, are an acceptable method 

of compliance for the actions required by this 

paragraph. Repetitive inspections of the door 

opening sequence of the LH and RH doors of 

the MLG of an airplane, as required by 

paragraph (p) of this AD, is an acceptable 

method to comply with the requirements of 

this paragraph. 

(k) Retained On-Condition Inspection 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011), with new service information. If, 

during any check required by paragraph (j) of 

this AD, a pair of specific CFDS messages 

specified in paragraph 4.2.1 of Airbus AOT 

A320–32A1390, dated February 10, 2011, has 

been triggered by both landing gear control 

and indication units (LGCIU) for the same 

flight, before further flight, inspect the door 

opening sequence of the affected doors of the 

MLG for discrepancies (i.e., if any condition 

specified in steps (a) through (d) of paragraph 

4.2.2 of Airbus AOT A320–32A1390, dated 

February 10, 2011, is not met; or if any door 

actuator fails any inspection check specified 

in Airbus Service Bulletin A320–32–1390, 


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Revision 02, dated October 23, 2013). Do the 

inspection in accordance with paragraph 

4.2.2 of Airbus AOT A320–32A1390, dated 

February 10, 2011; or Airbus Service Bulletin 

A320–32–1390, Revision 02, dated October 

23, 2013. As of the effective date of this AD, 

use only Airbus Service Bulletin A320–32– 

1390, Revision 02, dated October 23, 2013, 

for the actions required by this paragraph. 

(l) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–13–11, Amendment 

39–16734 (76 FR 37241, June 27, 2011), with 

new service information, new optional 

actions, and reduced compliance times. At 

the applicable time specified in paragraph 

(l)(1) or (l)(2) of this AD: Inspect the door 

opening sequence of the LH and RH doors of 

the MLG for discrepancies (i.e., if any 

condition specified in steps (a) through (d) of 

paragraph 4.2.2 of Airbus AOT A320– 

32A1390, dated February 10, 2011, is not 

met; or if any door actuator fails any 

inspection check specified in Airbus Service 

Bulletin A320–32–1390, Revision 02, dated 

October 23, 2013). Do the inspection in 

accordance with the instructions of 

paragraph 4.2.2 of Airbus AOT A320– 

32A1390, dated February 10, 2011; or Airbus 

Service Bulletin A320–32–1390, Revision 02, 

dated October 23, 2013. As of the effective 

date of this AD, use only Airbus Service 

Bulletin A320–32–1390, Revision 02, dated 

October 23, 2013. Repeat the inspection 

within 8 days or 5 flight cycles after the 

effective date of this AD, whichever occurs 

later, without exceeding 425 flight cycles 

since the most recent inspection; and 

thereafter repeat the inspection at intervals 

not to exceed 8 days or 5 flight cycles, 

whichever occurs later. In addition, 

whenever any airplane is not operated for a 

period longer than 8 days, do the inspection 

before further flight. Doing this inspection 

terminates the requirements of paragraph (g) 

of this AD. Repetitive inspections of the door 

opening sequence of the LH and RH doors of 

the MLG of an airplane, as required by 

paragraph (p) of this AD, is an acceptable 

method to comply with the requirements of 

this paragraph. 

(1) For airplanes on which an inspection 

required by paragraph (g) of this AD has been 

done as of July 12, 2011 (the effective date 

of AD 2011–13–11, Amendment 39–16734 

(76 FR 37241, June 27, 2011)): Within 800 

flight cycles after doing the most recent 

inspection required by paragraph (g) of this 

AD, or within 100 flight cycles after July 12, 

2011 (the effective date of AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011)), whichever occurs later. 

(2) For airplanes on which an inspection 

required by paragraph (g) of this AD has not 

been done as of July 12, 2011 (the effective 

date of AD 2011–13–11, Amendment 39– 

16734 (76 FR 37241, June 27, 2011)): Within 

800 flight cycles after July 12, 2011. 

(m) Retained Replacement 

This paragraph restates the requirements of 

paragraph (m) of AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011), with new service information. If 

any discrepancy (i.e., if any condition 

specified in steps (a) through (d) of paragraph 

4.2.2 of Airbus AOT A320–32A1390, dated 

February 10, 2011, is not met; or if any door 

actuator fails any inspection check specified 

in Airbus Service Bulletin A320–32–1390, 

Revision 02, dated October 23, 2013) is found 

during any inspection required by paragraph 

(k) or (l) of this AD, before further flight, 

replace the affected MLG door actuator with 

a new MLG door actuator, in accordance with 

the instructions of Airbus AOT A320– 

32A1390, dated February 10, 2011; or Airbus 

Service Bulletin A320–32–1390, Revision 02, 

dated October 23, 2013. As of the effective 

date of this AD, use only Airbus Service 

Bulletin A320–32–1390, Revision 02, dated 

October 23, 2013, to do the actions required 

by this paragraph. 

(n) Retained: No Terminating Action for 

Certain Requirements 

This paragraph restates the statement of 

paragraph (n) of AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011), with no changes. Replacement of 

the MLG door actuator as required by 

paragraph (m) of this AD is not a terminating 

action for the repetitive actions required by 

paragraphs (j) and (l) of this AD. 

(o) Retained Configuration and Part Number 

Determination 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–16–09, 

Amendment 39–17547 (78 FR 48286, August 

8, 2013), with no changes. At the later of the 

compliance times specified in paragraphs 

(o)(1) and (o)(2) of this AD: Do an inspection 

to determine the configuration (modification 

status) of the airplane and identify the part 

number of the LH and RH LGCIU and MLG 

door actuators. A review of the airplane 

delivery or maintenance records is acceptable 

for compliance with the requirements of this 

paragraph provided the airplane 

configuration and installed components can 

be conclusively determined from that review. 

(1) Prior to the accumulation of 800 total 

flight cycles since first flight of the airplane. 

(2) Within 14 days after August 23, 2013 

(the effective date of AD 2013–16–09, 

Amendment 39–17547 (78 FR 48286, August 

8, 2013)). 

(p) Retained MLG Door Opening Sequence 

Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–16–09, 

Amendment 39–17547 (78 FR 48286, August 

8, 2013), with no changes. If, during the 

determination and identification required by 

paragraph (o) of this AD, the configuration of 

the airplane is determined to be post-Airbus 

modification 39303 or post-Airbus Service 

Bulletin A320–32–1409 (Interlink 

Communication ARINC 429 installed), and 

both an LGCIU and a MLG door actuator are 

installed with a part number listed in table 

1 to paragraph (p) of this AD: Except as 

provided by paragraph (s) of this AD, at the 

later of the compliance times specified in 

paragraphs (o)(1) and (o)(2) of this AD, and 

thereafter at intervals not to exceed 8 days or 

5 flight cycles, whichever occurs later, do an 

inspection of the door opening sequence of 

the LH and RH MLG doors, in accordance 

with the instructions of Airbus Alert 

Operators Transmission (AOT) A32N001–13, 

dated June 24, 2013. 

TABLE 1 TO PARAGRAPH (p) OF THIS

AD 

Component name Part number 

LGCIU (LH and RH) ....... 80–178–02–88012 

LGCIU (LH and RH) ....... 80–178–03–88013 

MLG door actuator ......... 114122006 

MLG door actuator ......... 114122007 

MLG door actuator ......... 114122009 

MLG door actuator ......... 114122010 

MLG door actuator ......... 114122011 

MLG door actuator ......... 114122012 

(q) Retained MLG Door Opening Sequence 

Corrective Action 

This paragraph restates the requirements of 

paragraph (i) of AD 2013–16–09, Amendment 

39–17547 (78 FR 48286, August 8, 2013), 

with no changes. If a slow door operation or 

restricted extension is found during any 

inspection required by paragraph (p) of this 

AD: Before further flight, replace the affected 

MLG door actuator with a new or serviceable 

actuator, in accordance with the instructions 

of Airbus AOT A32N001–13, dated June 24, 

2013. 

(r) Retained Terminating Action Limitation 

for Certain Actions 

This paragraph restates the requirements of 

paragraph (j) of AD 2013–16–09, Amendment 

39–17547 (78 FR 48286, August 8, 2013), 

with no changes. Replacement of a MLG door 

actuator, as required by paragraph (q) of this 

AD, does not constitute terminating action 

for the repetitive inspections required by 

paragraph (p) of this AD, unless MLG door 

actuators having P/N 114122014 are installed 

on both LH and RH sides, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1407, dated May 

14, 2013. 

(s) Retained Repetitive Inspection Exception 

This paragraph restates the requirements of 

paragraph (k) of AD 2013–16–09, 

Amendment 39–17547 (78 FR 48286, August 

8, 2013), with no changes. Airplanes on 

which the LGCIU interlink is disconnected 

(Airbus modification 155522 applied in 

production, or modified in-service in 

accordance with the instructions of Airbus 

AOT A32N001–13, dated June 24, 2013), or 

on which MLG door actuators having P/N 

114122014 are installed on both LH and RH 

sides (Airbus modification 153655 applied in 

production, or modified in-service in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1407, dated May 14, 2013), are not 

required to do the actions required by 

paragraph (p) of this AD, provided that the 

airplane is not modified to a configuration as 

defined in paragraph (p) of this AD. 

(t) New Replacement of MLG Door Actuator 

having P/N 114122012 

Within 12 months after the effective date 

of this AD: Replace each MLG door actuator 

having P/N 114122012 with a MLG door 

actuator having P/N 14122014, in accordance 

with the Accomplishment Instructions of 


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Airbus Service Bulletin A320–32–1407, 

dated May, 14 2013; or modify each actuator, 

including doing all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of General Electric Service 

Bulletin 114122–32–105, Revision 1, dated 

March 26, 2013; except where General 

Electric Service Bulletin114122–32–105, 

Revision 1, dated March 26, 2013, specifies 

to contact the manufacturer, before further 

flight, repair 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 DOAauthorized signature. 

(u) New Replacement of Certain Other MLG 

Door Actuators 

Within 24 months after the effective date 

of this AD: Replace each MLG door actuator 

having a part number listed in table 1 to 

paragraph (p) of this AD, except P/N 

114122012, with a MLG door actuator having 

P/N 14122014, in accordance with 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1407, dated May 

14, 2013; or modify each actuator, including 

doing all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of General 

Electric Service Bulletin 114122–32–105, 

Revision 1, dated March 26, 2013; except 

where General Electric Service Bulletin 

114122–32–105, Revision 1, dated March 26, 

2013, specifies to contact the manufacturer, 

before further flight, repair 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 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(v) New Terminating Action 

Modification of an airplane as required by 

paragraphs (t) and (u) of this AD, as 

applicable, constitutes terminating action for 

all repetitive actions (PFR monitoring checks 

and inspections) required by this AD for that 

airplane. 

(w) New Conditional Terminating Action 

Replacement of a MLG door actuator as 

required by paragraphs (m) and (q) of this 

AD; or corrective actions as specified in 

Airbus AOT A320–32A1390, dated February 

10, 2011; or replacement of a MLG door 

actuator as specified in Airbus Service 

Bulletin A320–32–1390, Revision 1, dated 

September 21, 2011; do not constitute 

terminating action for the repetitive 

inspections required by paragraphs (j), (l), 

and (p) of this AD, unless MLG door 

actuators having P/N 114122014 are installed 

on both LH and RH sides, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1407, dated May 

14, 2013. 

(x) New Exception to AD Requirements 

An airplane on which MLG door actuators 

having P/N 114122014 are installed on both 

LH and RH sides (Airbus MOD 153655 

applied in production, or modified in service 

as specified in Airbus Service Bulletin A320– 

32–1407, dated May, 14 2013; General 

Electric Service Bulletin 114122–32–105, 

dated January 17, 2013; or General Electric 

Service Bulletin 114122–32–105, Revision 1, 

dated March 26, 2013; is not affected by the 

requirements of paragraphs (j) through (u) of 

this AD, provided that no MLG door actuator 

with a part number in table 1 to paragraph 

(p) of this AD has been installed on that 

airplane since first flight, or since 

modification, as applicable. 

(y) New Parts Installation Prohibitions 

(1) Except as specified in paragraph (y)(2) 

of this AD, as of the effective date of this AD, 

do not install on any airplane a MLG door 

actuator, having a part number listed in table 

1 to paragraph (p) of this AD. 

(2) For an airplane subject to the 

requirements of paragraphs (t) and (u) of this 

AD, as applicable, do not install a MLG door 

actuator having a part number listed in table 

1 to paragraph (p) of this AD after 

modification of the airplane. 

(z) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (k), (l), and 

(m) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Mandatory Service Bulletin 

A320–32–1390, Revision 01, dated 

September 21, 2011, which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraphs (t) and (u) of 

this AD, if those actions were performed 

before the effective date of this AD using 

General Electric Service Bulletin 114122–32– 

105, dated January 17, 2013, which is not 

incorporated by reference in this AD. 

(aa) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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: Except as 

specified in paragraph (j) of this AD for the 

use of an alternative method to check the 

PFR for CFDS messages, 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. 

(3) Previously Approved AMOCs: AMOCs 

approved previously for the ADs identified in 

paragraphs (aa)(3)(i) and (aa)(3)(ii) of this AD, 

are approved as AMOCs for the 

corresponding provisions of this AD. 

(i) AD 2011–13–11, Amendment 39–16734 

(76 FR 37241, June 27, 2011). 

(ii) AD 2013–16–09, Amendment 39–17547 

(78 FR 48286, August 8, 2013). 

(bb) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided the MLG remains extended and 

locked, and that no MLG recycle is done. 

(cc) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0288, dated 

December 6, 2013, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–0529. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 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. 

(3) For General Electric service information 

identified in this AD, contact GE Aviation, 

Customer Support Center, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: cs.techpubs@ge.com; Internet: http://

www.geaviation.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. 

Issued in Renton, Washington, on August 

1, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19157 Filed 8–12–14; 8:45 am] 

BILLING CODE 4910–13–P 


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