1486 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0678; Directorate 

Identifier 2013–NM–207–AD; Amendment 

39–18367; AD 2016–01–08] 

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) 2013–13– 

04, for certain Airbus Model A318, 

A319, A320, and A321 series airplanes. 

AD 2013–13–04 required installing a 

power interruption protection circuit for 

the landing gear control interface unit 

(LGCIU). This new AD requires a new 

modification of any previously modified 

LGCIU. This new AD also requires 

revising the maintenance or inspection 

program to reduce a certain functional 

check interval. This new AD also adds 

airplanes to the applicability. This AD 

was prompted by a determination that 

additional work is necessary to 

adequately address the identified unsafe 

condition. We are issuing this AD to 

prevent untimely unlocking and/or 

retraction of the nose landing gear 

(NLG), which, while on the ground, 

could result in injury to ground 

personnel and damage to the airplane. 

DATES: This AD becomes effective 

February 17, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 17, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 14, 2013 (78 FR 

41286, July 10, 2013) . 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0678; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this final rule, contact Airbus, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

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

account.airworth-eas@airbus.com; 

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

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0678 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, 

July 10, 2013). AD 2013–13–04 applied 

to certain Airbus Model A318, A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on March 31, 2015 (80 FR 

17007). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0202, dated September 

5, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for Airbus Model 

A318–111, –112, –121, and –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, 

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

The MCAI states: 

After a push back from the gate, an A320 

aeroplane was preparing to initiate taxi, 

when an uncommanded nose landing gear 

(NLG) retraction occurred, causing the nose 

of the aeroplane to hit the ground. 

Investigations revealed that the retraction 

was caused by a combination of a power 

interruption to Landing Gear Control and 

Interface Units (LGCIU) and an internal 

hydraulic leak through the landing gear (LG) 

selector valve 40GA. 

Deeper investigations have revealed that 

LGCIU power interruption appears during 

engine start at each flight. Even though no 

incident has been reported in service, it has 

been determined that a non-compliance to 

the safety objective exists when combined 

with a dormant single failure of the selector 

valve seal leaking. 

This condition, if not corrected, could lead 

to further incidents of untimely unlocking 

and/or retraction of the NLG which, while on 

the ground, could result in injury to ground 

personnel and damage to the aeroplane. 

To address the possible hydraulic leak of 

the LG selector valve, EASA issued AD 2007– 

0065 [http://ad.easa.europa.eu/blob/easa_

ad_2007_0065.pdf/AD_2007-0065] currently 

at Revision 2. 

To address the risk of untimely unlocking 

and/or retraction of the NLG, EASA issued 

AD 2011–0202 [http://ad.easa.europa.eu/

blob/easa_ad_2011_0202.pdf/AD_2011-0202] 

to require installation of a power interruption 

protection circuit to the LGCIU and 

accomplishment of associated modifications. 

Since that [EASA] AD was issued, it has 

been discovered that additional work is 

necessary to adequately correct this unsafe 

condition and consequently, Airbus issued 

Service Bulletin (SB) A320–32–1346 to 

Revision 05. An update of the maintenance 

programme is required as well, following the 

required modification. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0202, which is superseded, and 

requires certain additional actions, as defined 

in the revised Airbus SB, as applicable to 

aeroplane model, and an update of the 

approved maintenance programme. 

The additional actions include a new 

modification of any previously modified 

LGCIU, and reducing a certain 

functional check interval. This AD also 

adds airplanes on which Airbus 

modification 37866 has been embodied 

in production to the applicability. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0678- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 17007, 

March 31, 2015) and the FAA’s response 

to the comment. 

Request To Include Revised Service 

Information 

United Airlines (UAL) stated that 

paragraphs (i) and (j) of the proposed 

AD (80 FR 17007, March 31, 2015) 

would be required to be done in 

accordance with the instructions of 

Airbus Service Bulletin A320–32–1346, 

Revision 05, dated January 13, 2012. 

UAL asked that we allow use of the 

latest revision available, Airbus Service 

Bulletin A320–32–1346, Revision 07, 

dated February 10, 2015, for 

accomplishing the modification. 

We agree with the commenter’s 

request. Airbus has issued Service 

Bulletin A320–32–1346, Revision 06, 

dated January 12, 2015, and Airbus 

Service Bulletin A320–32–1346, 

Revision 07, dated February 10, 2015. 


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These revisions state that no additional 

work is necessary on airplanes changed 

in accordance with Airbus Service 

Bulletin A320–32–1346, Revision 05, 

dated January 13, 2012, which was 

specified as the appropriate source of 

service information in the NPRM (80 FR 

17007, March 31, 2015). 

We have changed paragraphs (i) and 

(j) of this AD to specify accomplishing 

the modification in accordance with 

Airbus Service Bulletin A320–32–1346, 

Revision 07, dated February 10, 2015. 

We have also added a new paragraph 

(l)(2) to this AD (paragraph (l) of the 

proposed AD (80 FR 17007, March 31, 

2015) has been changed to paragraph 

(l)(1) in this AD) to give credit for 

actions done before the effective date of 

this AD using Airbus Service Bulletin 

A320–32–1346, Revision 05, dated 

January 13, 2012; or Airbus Service 

Bulletin A320–32–1346, Revision 06, 

dated January 12, 2015. 

Request To Include Terminating Action 

UAL stated that the NPRM (80 FR 

17007, March 31, 2015) does not 

include a terminating action. UAL asked 

that we create a new paragraph detailing 

all actions that will be terminated by 

accomplishing the modification of the 

LGCIU, as specified in Airbus Service 

Bulletin A320–32–1346, Revision 07, 

dated February 10, 2015. 

We do not agree with the request. 

Paragraph (i) of this AD specifies that 

the modification terminates the actions 

required by paragraphs (g) and (h) of 

this AD. Therefore, no change to this AD 

is necessary in this regard. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

17007, March 31, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 17007, 

March 31, 2015). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–32–1346, Revision 07, dated 

February 10, 2015, including 

Appendices 01 and 02, dated February 

10, 2015; and Task 32.30.00.17, 

‘‘Functional Check of LGCIU Power 

Supply Relays,’’ of Section C–32 of 

Section C, Systems and Powerplant, of 

the Airbus A318/A319/A320/A321 

Maintenance Review Board Report, 

Revision 18, dated March 2013. The 

service information describes 

procedures for installing a power 

interruption protection circuit for the 

LGCIU, and for a new modification of 

any previously modified LGCIU. 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 851 

airplanes of U.S. registry. 

The actions required by AD 2013–13– 

04, Amendment 39–17492 (78 FR 

41286, July 10, 2013), take about 48 

work-hours per product, at an average 

labor rate of $85 per work-hour. 

Required parts will cost about $8,220 

per product. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2013–13–04 is $12,300 

per product. 

We estimate that it takes about 46 

work-hours per product to comply with 

the new modification in this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $9,650 

per product. Based on these figures, we 

estimate the cost of the new 

modification on U.S. operators to be 

$11,539,560, or $13,560 per product. 

We estimate that it takes about 1 

work-hour per product to revise the 

maintenance or inspection program in 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of revising the 

maintenance program on U.S. operators 

to be $72,335, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0678; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2013–13–04, Amendment 39–17492 (78 

FR 41286, July 10, 2013), and adding the 

following new AD: 


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2016–01–08 Airbus: Amendment 39–18367. 

Docket No. FAA–2015–0678; Directorate 

Identifier 2013–NM–207–AD. 

(a) Effective Date 

This AD becomes effective February 17, 

2016. 

(b) Affected ADs 

This AD replaces AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013). 

(c) Applicability 

(1) This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–211, 

–212, –214, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

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

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a determination 

that additional work is necessary to 

adequately address the identified unsafe 

condition. We are issuing this AD to prevent 

untimely unlocking and/or retraction of the 

nose landing gear (NLG), which, while on the 

ground, could result in injury to ground 

personnel and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013) with no changes. For all airplanes 

except airplanes on which Airbus 

modification 37866 has been embodied in 

production: At the applicable compliance 

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

this AD: Install a power interruption 

protection circuit for the landing gear control 

interface unit (LGCIU), in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1346, Revision 04, 

including Appendices 01 and 02, dated April 

22, 2011 (for Model A318, A319, A320, and 

A321 series airplanes other than the Model 

A319CJ (corporate jet) airplanes); or Airbus 

Service Bulletin A320–32–1349, Revision 03, 

including Appendix 1, dated October 5, 2011 

(for Model A319CJ (corporate jet) airplanes). 

(1) For airplanes that have embodied 

Airbus Modification 38947 specified in 

Airbus Service Bulletin A320–32–1348 

during production or in service: Within 72 

months after August 14, 2013 (the effective 

date of AD 2013–13–04, Amendment 39– 

17492 (78 FR 41286, July 10, 2013)). 

(2) For all airplanes other than those 

identified in paragraph (g)(1) of this AD: 

Within 60 months after August 14, 2013 (the 

effective date of AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013)). 

(h) Retained Re-Identification of 

Identification Plates With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013) with no changes. For airplanes on 

which the installation required by paragraph 

(g) of this AD has been done before August 

14, 2013 (the effective date of AD 2013–13– 

04) using Airbus Service Bulletin A320–32– 

1346, dated December 4, 2008 (for Model 

A318, A319, A320, and A321 series airplanes 

other than Model A319CJ (corporate jet) 

airplanes): Within the applicable times 

specified in paragraphs (g)(1) and (g)(2) of 

this AD, re-identify the identification plates, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1346, Revision 04, including Appendices 

01 and 02, dated April 22, 2011 (for Model 

A318, A319, A320, and A321 series airplanes 

other than Model A319CJ (corporate jet) 

airplanes). 

(i) New Modification 

For airplanes identified in paragraphs 

(i)(1), (i)(2), and (i)(3) of this AD except 

airplanes on which Airbus modification 

37866 has been embodied in production: 

Modify the LGCIU at the applicable time 

specified in paragraph (i)(1), (i)(2), or (i)(3) of 

this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1346, Revision 07, 

dated February 10, 2015, including 

Appendices 01 and 02, dated February 10, 

2015; or Airbus Service Bulletin A320–32– 

1349, Revision 03, including Appendix 1, 

dated October 5, 2011 (for Model A319CJ 

(corporate jet) airplanes), which was 

incorporated by reference on August 14, 2013 

(78 FR 41286, July 10, 2013). Accomplishing 

the modification in this paragraph terminates 

the actions required by paragraphs (g) and (h) 

of this AD. 

(1) For airplanes on which any landing 

gear (LG) selector valve having part number 

(P/N) 114079019 is installed and that have 

embodied Airbus Modification 38947 

specified in Airbus Service Bulletin A320– 

32–1348 during production or in service: 

Modify the LGCIU within 72 months after the 

effective date of this AD. 

(2) For airplanes on which any LG selector 

valve 40GA having a part number listed in 

paragraphs (i)(2)(i) through (i)(2)(xii) of this 

AD, provided the valve has the marking ‘‘DI’’ 

or ‘‘DI–BE’’ recorded on its amendment 

plates: Modify the LGCIU within 72 months 

after the effective date of this AD. 

(i) P/N 114079001. 

(ii) P/N 114079005. 

(iii) P/N 114079009. 

(iv) P/N 114079013. 

(v) P/N 114079001A. 

(vi) P/N 114079005A. 

(vii) P/N 114079009A. 

(viii) P/N 114079015. 

(ix) P/N 114079001AB. 

(x) P/N 114079005AB. 

(xi) P/N 114079009AB. 

(xii) P/N 114079017. 

(3) For all airplanes other than those 

identified in paragraphs (i)(1) and (i)(2) of 

this AD: Modify the LGCIU within 60 months 

after the effective date of this AD. 

(j) New Modification for Airplanes 

Previously Modified 

For airplanes that have been modified as of 

the effective date of this AD as specified in 

the applicable service information identified 

in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this 

AD, except airplanes on which Airbus 

modification 37866 has been embodied in 

production: Within 72 months after the 

effective date of this AD, do the additional 

modification of the LGCIU, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1346, 

Revision 07, dated February 10, 2015, 

including Appendices 01 and 02, dated 

February 10, 2015. 

(1) Airbus Service Bulletin A320–32–1346, 

Revision 01, dated October 27, 2009, which 

is not incorporated by reference in this AD. 

(2) Airbus Service Bulletin A320–32–1346, 

Revision 02, dated November 4, 2009, which 

is not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A320–32–1346, 

Revision 03, dated January 7, 2010, which is 

not incorporated by reference in this AD. 

(4) Airbus Service Bulletin A320–32–1346, 

including Appendices 01 and 02, Revision 

04, dated April 22, 2011, which is 

incorporated by reference in AD 2013–13–04, 

Amendment 39–17492 (78 FR 41286, July 10, 

2013). 

(k) New Maintenance or Inspection Program 

Revision 

Before further flight after accomplishing 

the actions specified in paragraph (i) or (j) of 

this AD or within 7 days after the effective 

date of this AD, whichever occurs later: 

Revise the maintenance or inspection 

program, as applicable, to incorporate Task 

32.30.00.17, ‘‘Functional Check of LGCIU 

Power Supply Relays,’’ of Section C–32 of 

Section C, Systems and Powerplant, of the 

Airbus A318/A319/A320/A321 Maintenance 

Review Board Report, Revision 18, dated 

March 2013. The initial compliance time is 

within 4,000 flight hours after accomplishing 

the additional modification of the LGCIU. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for A319 

Corporate Jet airplanes for the modification 

required by paragraph (g) of this AD if that 

modification was performed before the 

effective date of this AD using the following 

applicable service information. This service 

information is not incorporated by reference 

in this AD. 

(i) Airbus Service Bulletin A320–32–1349, 

dated December 4, 2008; 

(ii) Airbus Service Bulletin A320–32–1349, 

Revision 01, dated August 31, 2009; 

(iii) Airbus Service Bulletin A320–32– 

1349, Revision 02, dated June 16, 2010. 

(2) This paragraph provides credit for the 

modification required by paragraphs (i) and 

(j) of this AD, as applicable, if that 

modification was performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–32–1346, Revision 05, dated 

January 13, 2012; or Airbus Service Bulletin 

A320–32–1346, Revision 06, dated January 

12, 2015. This service information is not 

incorporated by reference in this AD. 


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(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: 

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. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2013–13–04, Amendment 39–17492 (78 FR 

41286, July 10, 2013) are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0202, dated 

September 5, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0678-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

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

(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. 

(3) The following service information was 

approved for IBR on February 17, 2016. 

(i) Airbus Service Bulletin A320–32–1346, 

Revision 07, dated February 10, 2015, 

including Appendices 01 and 02, dated 

February 10, 2015. 

(ii) Task 32.30.00.17, ‘‘Functional Check of 

LGCIU Power Supply Relays,’’ of Section C– 

32 of Section C, Systems and Powerplant, of 

the Airbus A318/A319/A320/A321 

Maintenance Review Board Report, Revision 

18, dated March 2013. 

(4) The following service information was 

approved for IBR on August 14, 2013 (78 FR 

41286, July 10, 2013). 

(i) Airbus Service Bulletin A320–32–1346, 

Revision 04, including Appendices 01 and 

02, dated April 22, 2011. 

(ii) Airbus Service Bulletin A320–32–1349, 

Revision 03, including Appendix 1, dated 

October 5, 2011. 

(5) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(6) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on 

December 31, 2015. 

Philip Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00014 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1984; Directorate 

Identifier 2015–NM–022–AD; Amendment 

39–18363; AD 2016–01–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2005–01– 

09, which applied to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. AD 2005–01–09 required a 

one-time detailed inspection for 

discrepancies of the frame web and 

inner chords on the forward edge frame 

of the number 5 main entry door cutout, 

and corrective action if necessary. This 

new AD adds repetitive high frequency 

eddy current (HFEC) inspections for 

cracking of the frame inner chords 

(forward and aft), and corrective action 

if necessary. This AD was prompted by 

additional cracking found in the same 

area after completion of the one-time 

detailed inspection. We are issuing this 

AD to detect and correct discrepancies 

of the frame web and inner chords, 

which could result in cracking, 

subsequent severing of the frame, and 

consequent rapid depressurization of 

the airplane. 

DATES: This AD is effective February 17, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 17, 2016. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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–2015– 

1984. 

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–2015– 

1984; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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