Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 12413 

(3) For Airbus Model A310 series 

airplanes: Airbus Service Bulletin A310–53– 

2136, dated February 14, 2014. 

(j) Corrective Actions 

If, during any inspection required by 

paragraph (h) of this AD, any cracking is 

found, before further flight, replace the 

affected THS support strut(s) with 

serviceable struts and install clamps on each 

strut end, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraphs (g)(1) through (g)(3) of this AD. 

(k) Clarification 

Installation of reinforcing clamps as 

required by paragraph (i) of this AD, and the 

replacement of support struts and/or the 

installation of clamps as required by 

paragraph (j) of this AD, do not constitute 

terminating action for the repetitive 

inspections required by paragraph (h) of this 

AD. 

(l) Reporting 

At the applicable time specified in 

paragraphs (l)(1) and (l)(2) of this AD: After 

accomplishment of any inspection required 

by paragraph (g) of this AD, report all 

inspection results to Airbus, including no 

findings, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletins specified in 

paragraphs (g)(1) through (g)(3) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

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

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(n) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0164, dated 

July 11, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2015-0243-0002. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–53–0394, 

dated February 14, 2014. 

(ii) Airbus Service Bulletin A300–53–0395, 

dated February 14, 2014. 

(iii) Airbus Service Bulletin A300–53– 

6172, dated February 14, 2014. 

(iv) Airbus Service Bulletin A300–53– 

6174, dated February 14, 2014. 

(v) Airbus Service Bulletin A310–53–2136, 

dated February 14, 2014. 

(vi) Airbus Service Bulletin A310–53– 

2137, dated February 14, 2014. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

23, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04545 Filed 3–8–16; 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; Amendment 

39–18420; AD 2016–05–02] 

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) 2011–13– 

11 and AD 2013–16–09 for all Airbus 

Model A318, A319, A320, and A321 

series airplanes. AD 2011–13–11 

required 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 for 

discrepancies if certain messages are 

found, and corrective actions if 

necessary. AD 2013–16–09 required 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, and 

replacement of the MLG door actuator if 

necessary. AD 2013–16–09 also 

provided optional terminating action for 

the repetitive inspections. This new AD 

reduces the interval of the MLG door 

opening sequence inspection, requires 

replacing or modifying certain MLG 

door actuators, and also requires a 

flushing procedure to be performed 

when installing a new MLG door 

actuator. This AD was prompted by a 

determination that the interval of the 

MLG door opening sequence inspection 

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 


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12414 Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 

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: This AD becomes effective April 

13, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 13, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of August 23, 2013 (78 FR 

48286, August 8, 2013). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of July 12, 2011 (76 FR 

37241, June 27, 2011). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of April 27, 2007 (72 FR 

13681, March 23, 2007). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov/ 

#!docketDetail;D=FAA-2014-0529; 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 Airbus service information 

identified in this final rule, 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 Elec tric service information 

identified in this final rule, 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. It is also available 

on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0529. 

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: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede AD 

2011–13–11, Amendment 39–16734 (76 

FR 37241, June 27, 2011) (‘‘AD 2011– 

13–11’’); and AD 2013–16–09, 

Amendment 39–17547 (78 FR 48286, 

August 8, 2013) (‘‘AD 2013–16–09’’). AD 

2011–13–11 and AD 2013–16–09 

applied to all Airbus Model A318, 

A319, A320, and A321 series airplanes. 

The SNPRM published in the Federal 

Register on September 22, 2015 (80 FR 

57122). We preceded the SNPRM with 

a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on August 13, 2014 (79 FR 

47395; corrected August 27, 2014 (79 FR 

51117)) (‘‘the NPRM’’). The NPRM was 

prompted by a determination that the 

interval of the MLG door opening 

sequence inspection must be reduced. 

The NPRM proposed to continue to 

require an amendment of the AFM; 

repetitive checks of specific CFDS 

messages; an inspection of the opening 

sequence of the MLG door for 

discrepancies if certain messages are 

found, and corrective actions if 

necessary; 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, and replacement of the MLG door 

actuator if necessary; and optional 

terminating action for the repetitive 

inspections. The SNPRM proposed to 

require a flushing procedure to be 

performed when installing a new MLG 

door actuator. 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 down-locking of the 

MLG and consequent MLG collapse 

during landing and 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 

Union, has issued EASA Airworthiness 

Directive 2014–0221, dated September 

30, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. The MCAI states: 

Some operators reported slow operation of 

the main landing gear (MLG) door opening/ 

closing sequence, leading to the generation of 

[electronic centralized aircraft monitor] 

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 may 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 

(freefall) extension system. 

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. 

[An EASA AD] was issued [and later 

revised] to require repetitive inspections of 

the opening sequence of the MLG door in 

order to identify the affected actuators, and 

to introduce as an optional terminating 

action Airbus production Modification (mod) 

38274 and associated [Airbus] 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. 

[An EASA AD], which superseded 

EASA AD 2006–0112R1 [http:// 

ad.easa.europa.eu/blob/ 

easa_ad_2006_0112_R1_superseded.pdf/ 

AD_2006–0112R1_1], was issued [and later 

revised] to require 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 EASA AD 2011–0069R1 [http:// 

ad.easa.europa.eu/blob/ 

easa_ad_2011_0069_R1_superseded.pdf/ 

AD_2011-0069R1_1] 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 


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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 (pre-Airbus SB A320–32–1407—preGE 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] 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 Airbus production mod 

153655). 

Since those ADs (EASA AD 2011–0069R1 

and EASA AD 2013–0132–E) were issued, 

analyses performed by Airbus have revealed 

that the MLG door opening sequence 

inspection interval needed to be reduced, 

and that the (previously optional) 

terminating action needed to be made 

mandatory. 

Prompted by these findings, EASA issued 

AD 2013–0288 [http://ad.easa.europa.eu/ 

blob/easa_ad_2013_0288_superseded.pdf/ 

AD_2013-0288_1], retaining the requirements 

of EASA AD 2011–0069R1 and EASA AD 

2013–0132–E, which were superseded, but 

with reduced inspection intervals, and to 

require replacement or modification, as 

applicable, of the affected MLG door 

actuators as terminating action to the 

monitoring and repetitive checks and 

inspections. 

Following introduction of post-mod 

153655 MLG door actuators on in-service 

aeroplanes, it has been observed that, in case 

the removed pre-mod MLG door actuator has 

internal damage, contamination of the 

hydraulic system could have occurred. 

This condition, if not detected and 

corrected, could result in performance 

degradation (damping degradation) of the 

post-mod MLG door actuator. Testing 

performed with a new actuator tested in 

heavily contaminated hydraulic system did 

not show abnormal hydraulic restriction/ 

blockage. It is thus not requested to perform 

this ‘‘flushing procedure’’ on aircraft already 

retrofitted with std-14 actuators. 

In addition, since EASA AD 2013–0288 

was issued, the applicable AFM was revised 

and repetitive checks of specific CFDS 

messages are no longer considered to be 

required, due to the reduced intervals 

required by EASA AD 2013–0288. 

For the reasons described above, this 

[EASA] AD partially retains the requirements 

of EASA AD 2013–0288, which is 

superseded, introduces improved wording 

for clarification and requires, in addition to 

the revised operational (AFM) procedure, 

hydraulic flushing prior to any installation of 

a post-mod MLG door actuator. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov/ 

#!documentDetail;D=FAA-2014-0529- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received on 

the SNPRM. The Air Line Pilots 

Association International submitted two 

comments which supported the 

SNPRM. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletins 

A320–32–1390, Revision 03, dated July 

3, 2014; and A320–32–1407, Revision 

01, dated July 3, 2014. Airbus has also 

issued A318/A319/A320/A321 

Temporary Revision (TR) TR437, L/G— 

GEAR NOT DOWNLOCKED, Issue 1.0, 

dated May 23, 2014, to the Airbus A318/ 

A319/A320/A321 AFM. 

Airbus Service Bulletin A320–32– 

1390, Revision 03, dated July 3, 2014, 

describes procedures for inspecting the 

operation of the MLG door opening 

sequence to determine if an actuator is 

defective, flushing contamination from 

the landing gear extension and 

retraction system (LGERS), and 

replacing the door actuator if necessary. 

Airbus Service Bulletin A320–32– 

1407, Revision 01, dated July 3, 2014, 

describes procedures for flushing 

contamination from the LGERS and 

installing new MLG door actuators. 

Airbus A318/A319/A320/A321 TR 

TR437, L/G—GEAR NOT 

DOWNLOCKED, Issue 1.0, dated May 

23, 2014, to the AFM updates the 

procedure used for incomplete landing 

gear extension during approach. 

General Electric has issued Service 

Bulletin 114122–32–105, Revision 2, 

dated June 24, 2014, which describes 

procedures for conversion of a MLG 

door actuator and removal of unwanted 

material from the hydraulic fluid route. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 953 

airplanes of U.S. registry. 

The actions required by AD 2011–13– 

11, and retained in this AD, take about 

7 work-hours per product, per 

inspection cycle, 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 2011–13–11 is 

$595 per product, per inspection cycle. 

The actions required by AD 2013–16– 

09, and retained in this AD, take about 

3 work-hours per product, per 

inspection cycle, 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 2013–16–09 is 

$255 per product, per inspection cycle. 

We also estimate that it will take 

about 19 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $17,140 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$17,873,515, or $18,755 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 3 work-hours, for a cost of $255 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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. 


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12416 Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 

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-2014-0529; 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 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2011–13–11, Amendment 39– 

16734 (76 FR 37241, June 27, 2011) 

(‘‘AD 2011–13–11’’); and AD 2013–16– 

09, Amendment 39–17547 (78 FR 

48286, August 8, 2013) (‘‘AD 2013–16– 

09’’); and 

■ b. Adding the following new AD: 

2016–05–02 Airbus: Amendment 39–18420. 

Docket No. FAA–2014–0529; Directorate 

Identifier 2013–NM–260–AD. 

(a) Effective Date 

This AD becomes effective April 13, 2016. 

(b) Affected ADs 

This AD replaces AD 2011–13–11, 

Amendment 39–16734 (76 FR 37241, June 

27, 2011) (‘‘AD 2011–13–11’’); and AD 2013– 

16–09, Amendment 39–17547 (78 FR 48286, 

August 8, 2013) (‘‘AD 2013–16–09’’). 

(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 main 

landing gear (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 down-locking of the MLG, 

possibly resulting in MLG collapse during 

landing and consequent damage to the 

airplane and injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections/ 

Replacement, With a Formatting Change 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–13–11, 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. 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 39–14999 (72 FR 

13681, March 23, 2007)), 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 39–14999 

(72 FR 13681, March 23, 2007)). 

(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, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–13–11, 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), With Formatting Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–13–11, 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. Doing the actions 

required by paragraph (t) of this AD 

terminates the requirements of this 

paragraph. 

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 ABN–32 L/G GRAVITY EXTENSION. 


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Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 12417 

(j) Retained Repetitive Checks, With New 

Optional Actions and New Service 

Information 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–13–11, with new 

optional actions and new service 

information. 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 

Service Bulletin A320–32–1390, Revision 03, 

dated July 3, 2014, 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, With 

New Service Information and Revised 

Language for an Acronym 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–13–11, with new 

service information and revised langue for an 

acronym. 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 interface 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, Revision 03, 

dated July 3, 2014). Do the inspection in 

accordance with paragraph 4.2.2 of Airbus 

AOT A320–32A1390, dated February 10, 

2011; or the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1390, 

Revision 03, dated July 3, 2014. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–32–1390, Revision 03, 

dated July 3, 2014, for the actions required 

by this paragraph. 

(l) Retained Repetitive Inspections, With 

New Service Information, New Optional 

Actions, and Reduced Compliance Times 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–13–11, 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 the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1390, 

Revision 03, dated July 3, 2014). Do the 

inspection in accordance with the 

instructions of paragraph 4.2.2 of Airbus 

AOT A320–32A1390, dated February 10, 

2011; or the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1390, 

Revision 03, dated July 3, 2014. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–32–1390, Revision 03, 

dated July 3, 2014, for the actions required 

by this paragraph. 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): 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, 

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): Within 800 flight 

cycles after July 12, 2011. 

(m) Retained Replacement, With New 

Service Information 

This paragraph restates the requirements of 

paragraph (m) of AD 2011–13–11, 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 the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1390, Revision 03, 

dated July 3, 2014) 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 03, dated 

July 3, 2014. As of the effective date of this 

AD, use only Airbus Service Bulletin A320– 

32–1390, Revision 03, dated July 3, 2014, to 

do the actions required by this paragraph. 

(n) Retained Statement of No Terminating 

Action for Certain Requirements, With No 

Changes 

This paragraph restates the statement of 

paragraph (n) of AD 2011–13–11, 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, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–16–09, 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). 

(p) Retained MLG Door Opening Sequence 

Repetitive Inspections, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–16–09, 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 figure 2 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. 

FIGURE 2 TO PARAGRAPH (p) OF THIS

AD—AFFECTED PART NUMBERS

Component name Part No. 

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

80–178–03–88013 

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

114122007 

114122009 

114122010 

114122011 

114122012 


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12418 Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 

(q) Retained MLG Door Opening Sequence 

Corrective Action, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2013–16–09, 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, With New Service 

Information 

This paragraph restates the requirements of 

paragraph (j) of AD 2013–16–09, with new 

service information. 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; or Airbus Service Bulletin A320– 

32–1407, Revision 01, dated July 3, 2014. As 

of the effective date of this AD, use only 

Airbus Service Bulletin A320–32–1407, 

Revision 01, dated July 3, 2014, for the 

actions required by this paragraph. 

(s) Retained Repetitive Inspection Exception, 

With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2013–16–09, 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 as described in Airbus 

Service Bulletin A320–32–1407), 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 Revision of the AFM 

Within 14 days after the effective date of 

this AD, revise the Emergency Procedure 

Section of the AFM to incorporate Airbus 

A318/A319/A320/A321 Temporary Revision 

(TR) TR437, L/G—GEAR NOT 

DOWNLOCKED, Issue 1.0, dated May 23, 

2014. When this TR has been included in 

general revisions of the AFM, the general 

revisions may be inserted in the AFM, 

provided the relevant information in the 

general revision is identical to that in this 

TR, and the copy of this TR may be removed 

from the AFM. Doing the action required by 

this paragraph terminates the actions 

required by paragraph (i) of this AD. 

(u) 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 114122014, and flush 

the affected hydraulic system, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1407, 

Revision 01, dated July 3, 2014; 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 2, dated 

June 24, 2014; except where General Electric 

Service Bulletin 114122–32–105, Revision 2, 

dated June 24, 2014, 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). 

(v) 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 figure 3 to 

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

114122012, with a MLG door actuator having 

P/N 114122014, and flush the affected 

hydraulic system, in accordance with 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1407, Revision 01, 

dated July 3, 2014; 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 2, dated 

June 24, 2014; except where General Electric 

Service Bulletin 114122–32–105, Revision 2, 

dated June 24, 2014, 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 EASA; or 

Airbus’s EASA DOA. 

FIGURE 3 TO PARAGRAPH (v) OF THIS

AD—AFFECTED PART NUMBERS

Component name Part No. 

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

114122007 

114122009 

114122010 

114122011 

114122012 

(w) New Terminating Action 

Modification of an airplane as required by 

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

applicable, constitutes terminating action for 

all repetitive actions (PFR monitoring checks 

and inspections) required by this AD for that 

airplane. 

(x) 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 03, dated 

July 3, 2014; does 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, Revision 01, 

dated July 3, 2014. 

(y) New Exception to AD Requirements 

(1) An airplane 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 as specified in Airbus 

Service Bulletin A320–32–1407, dated May 

14, 2013; Airbus Service Bulletin A320–32– 

1407, Revision 01, dated July 3, 2014; 

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; or General 

Electric Service Bulletin 114122–32–105, 

Revision 2, dated June 24, 2014); is not 

affected by the requirements of paragraphs (j) 

through (v) of this AD, provided that no MLG 

door actuator with a part number in figure 3 

to paragraph (v) of this AD has been installed 

on that airplane since first flight, or since 

modification, as applicable. 

(2) An airplane in the configuration 

specified in paragraph (y)(1) of this AD, and 

with flight warning computers having P/N 

350E053021212 (H2F7) installed (Airbus 

Modification 153741 applied in production, 

or modified in service as specified in Airbus 

Service Bulletin A320–31–1414), is not 

affected by the requirement of paragraph (t) 

of this AD and, following modification, 

Airbus A318/A319/A320/A321 TR TR437, L/ 

G GEAR NOT DOWNLOCKED, Issue 1.0, 

dated May 23, 2014 (if inserted), may be 

removed from the AFM of that airplane. 

(z) New Parts Installation Prohibitions 

(1) Except as specified in paragraph (z)(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 figure 

3 to paragraph (v) of this AD. 

(2) For an airplane subject to the 

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

AD, as applicable, do not install a MLG door 

actuator having a part number listed in figure 

3 to paragraph (v) of this AD after 

modification of the airplane. 

(3) Except as specified in paragraph (z)(4) 

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

do not install on any airplane a flight 

warning computer (FWC) having a part 

number listed in figure 4 to paragraph (z) of 

this AD. 

(4) For an airplane subject to the 

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

AD, as applicable, do not install a FWC 

having a part number listed in figure 4 to 

paragraph (z) of this AD after modification of 

the airplane. 

FIGURE 4 TO PARAGRAPH (z) OF THIS

AD—AFFECTED PART NUMBERS

Component 

name Part No. 

Flight warning 

computer.

350E016187171 (C5) 

350E017238484 (H1D1) 

350E017248685 (H1D2) 


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FIGURE 4 TO PARAGRAPH (z) OF THIS

AD—AFFECTED PART NUMBERS— 

Continued 

Component 

name Part No. 

350E017251414 (H1E1) 

350E017271616 (H1E2) 

350E018291818 (H1E3CJ) 

350E018301919 (H1E3P) 

350E018312020 (H1E3Q) 

350E053020202 (H2E2) 

350E053020303 (H2E3) 

350E053020404 (H2E4) 

350E053020606 (H2F2) 

350E053020707 (H2F3) 

350E053021010 (H2F3P) 

350E053020808 (H2F4) 

350E053020909 (H2F5) 

350E053021111 (H2F6) 

(aa) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before April 

27, 2007 (the effective date of AD 2007–06– 

18), using Airbus Service Bulletin A320–32– 

1309, dated March 7, 2006. This service 

information is not incorporated by reference 

in this AD. 

(2) 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 Service Bulletin A320–32–1390, 

Revision 01, dated September 21, 2011; or 

Airbus Service Bulletin A320–32–1390, 

Revision 02, dated October 23, 2013. This 

service information is not incorporated by 

reference in this AD. 

(3) This paragraph provides credit for 

actions required by paragraphs (u) and (v) 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; or General 

Electric Service Bulletin 114122–32–105, 

Revision 1, dated March 26, 2013. This 

service information is not incorporated by 

reference in this AD. 

(bb) 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) Required for Compliance (RC): If any 

Airbus service information contains 

procedures or tests that are identified as RC, 

those procedures and tests must be done to 

comply with this AD; any procedures or tests 

that are not identified as RC are 

recommended. Those procedures and tests 

that are not identified as RC may be deviated 

from using accepted methods in accordance 

with the operator’s maintenance or 

inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(3) Contacting the Manufacturer: As of the 

effective date of this AD, 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(4) Previously Approved AMOCs: AMOCs 

approved previously for AD 2011–13–11 and 

AD 2013–16–09 are approved as AMOCs for 

the corresponding provisions of this AD. 

(cc) 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. 

(dd) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0221, dated 

September 30, 2014, 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) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (ee)(7), (ee)(8), and (ee)(9) of this 

AD. 

(ee) 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 April 13, 2016. 

(i) Airbus A318/A319/A320/A321 

Temporary Revision TR437, L/G—GEAR 

NOT DOWNLOCKED, Issue 1.0, dated May 

23, 2014, to the Airbus A318/A319/A320/ 

A321 Airplane Flight Manual. 

(ii) Airbus Service Bulletin A320–32–1390, 

Revision 03, dated July 3, 2014. 

(iii) Airbus Service Bulletin A320–32– 

1407, Revision 01, dated July 3, 2014. 

(iv) General Electric Service Bulletin 

114122–32–105, Revision 2, dated June 24, 

2014. 

(4) The following service information was 

approved for IBR on August 23, 2013 (78 FR 

48286, August 8, 2013). 

(i) Airbus Alert Operators Transmission 

A32N001–13, dated June 24, 2013. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on July 12, 2011 (76 FR 

37241, June 27, 2011). 

(i) Airbus All Operators Telex A320– 

32A1390, dated February 10, 2011. 

(ii) Reserved. 

(6) The following service information was 

approved for IBR on April 27, 2007 (72 FR 

13681, March 23, 2007). 

(i) Airbus Service Bulletin A320–32–1309, 

Revision 01, dated June 19, 2006. 

(ii) Reserved. 

(7) 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(8) 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. 

(9) 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. 

(10) 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 February 

18, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04577 Filed 3–8–16; 8:45 am] 

BILLING CODE 4910–13–P 


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