55358 Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–45, dated 

December 23, 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–2015–3986. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(3), (p)(4), and (p)(5) of this 

AD. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier ModSum IS4Q2400028, 

Revision B, dated December 11, 2012. (This 

document has 33 pages; the first page of the 

modsum indicates that there are 32 pages.) 

(ii) Bombardier ModSum IS4Q2400029, 

Revision A, dated July 6, 2012. 

(iii) Bombardier ModSum IS4Q5450002, 

Revision B, dated June 22, 2012. 

(iv) Bombardier ModSum IS4Q5450003, 

Revision C, dated November 29, 2012. 

(v) Bombardier Service Bulletin 84–32– 

112, Revision C, dated April 2, 2015. 

(vi) Bombardier Service Bulletin 84–32– 

114, Revision B, dated February 3, 2015. 

(vii) Bombardier Service Bulletin 84–54– 

19, dated April 18, 2013. 

(viii) Bombardier Service Bulletin 84–54– 

20, Revision C, dated March 5, 2015. 

(ix) Bombardier Service Bulletin 84–54–21, 

dated May 9, 2013. 

(x) Goodrich Service Bulletin 46400–32– 

102 R2, Revision 2, dated February 17, 2015. 

(3) For Bombardier service information 

identified in this AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario M3K 

1Y5, Canada; telephone 416–375–4000; fax 

416–375–4539; email 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.com. 

(4) For Goodrich service information 

identified in this AD, contact Goodrich 

Corporation, Landing Gear, 1400 South 

Service Road, West Oakville, ON, Canada 

L6L 5Y7; phone: 905–825–1568; email: 

jean.breed@goodrich.com; Internet: http:// 

www.goodrich.com/TechPubs. 

(5) 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. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Renton, Washington, on August 

4, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–19480 Filed 8–18–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4226; Directorate 

Identifier 2015–NM–095–AD; Amendment 

39–18616; AD 2016–17–03] 

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) 2003–25– 

07 for certain Airbus Model A319 and 

A320 series airplanes, and AD 2005–13– 

39 for certain Airbus Model A321 series 

airplanes. AD 2003–25–07 required a 

revision to the airplane flight manual 

(AFM) and replacement of both elevator 

aileron computers (ELACs) having L80 

standards with new ELACs having L81 

standards. AD 2005–13–39 required a 

revision to the AFM, replacement of 

existing ELACs with ELACs having L83 

or L91 standards, as applicable; and a 

concurrent action. Since we issued AD 

2003–25–07 and AD 2005–13–39, we 

have determined that new ELAC 

standards must be incorporated. The 

ELAC standards have been upgraded to 

version L97+, which implements 

enhanced angle-of-attack (AOA) 

monitoring to better detect AOA 

blockage, including multiple AOA 

blockages. This AD requires replacing 

existing ELACs with new ELACs having 

L97+ standards or revising the software 

in an existing ELAC to the L97+ 

standards, as applicable, which 

terminates the requirements of AD 

2003–25–07 and AD 2005–13–39. This 

AD also expands the applicability to 

include all Airbus Model A318, A319, 

A320, and A321 series airplanes. We are 

issuing this AD to prevent inadvertent 

activation of the AOA protections. 

Inadvertent activation of the AOA 

protections could result in a continuous 

nose-down pitch rate that could result 

in reduced controllability of the 

airplane. 

DATES: This AD is effective September 

23, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 23, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 9, 2005 (70 FR 38580, July 

5, 2005). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 22, 2004 (68 FR 

70431, December 18, 2003). 

ADDRESSES: For 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. 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–2016– 

4226. 

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–2016– 

4226; 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 (telephone 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: 

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 2003–25–07, 

Amendment 39–13390 (68 FR 70431, 

December 18, 2003) (‘‘AD 2003–25– 

07’’); and AD 2005–13–39, Amendment 


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39–14176 (70 FR 38580, July 5, 2005) 

(‘‘AD 2005–13–39’’). 

AD 2003–25–07 applied to certain 

Airbus Model A319 and A320 series 

airplanes, and AD 2005–13–39 applied 

to certain Airbus Model A321 series 

airplanes. The NPRM published in the 

Federal Register on March 17, 2016 (81 

FR 14404). The NPRM was prompted by 

a determination that new ELAC 

standards must be incorporated. The 

ELAC standards have been upgraded to 

version L97+, which implements 

enhanced AOA monitoring to better 

detect AOA blockage, including 

multiple AOA blockages. 

The NPRM proposed to require 

replacing existing ELACs with new 

ELACs having L97+ standards or 

revising the software in an existing 

ELAC to the L97+ standards, as 

applicable, which would terminate the 

requirements of AD 2003–25–07 and AD 

2005–13–39. We are issuing this AD to 

prevent inadvertent activation of the 

AOA protections. Inadvertent activation 

of the AOA protections could result in 

a continuous nose-down pitch rate that 

could result in reduced controllability 

of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0088R1, including 

Appendix 01, dated June 2, 2015 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A318, 

A319, A320, and A321 series airplanes. 

The MCAI states: 

The latest elevator aileron computer 

(ELAC) standard, L97+, implements 

enhanced Angle of Attack (AOA) monitoring 

in order to better detect cases of AOA 

blockage, including multiple AOA blockage. 

Two ELAC L97+ versions are currently 

available, Part Number (P/N) 3945129109 

with data loading capability, and P/N 

3945128215 without the data loading 

capability. Three existing [EASA] ADs 

requiring installation of earlier ELAC 

(software) have been identified and taken 

into account for cancellation by this new 

[EASA] AD. 

For the reasons described above, EASA 

issued AD 2015–0088, cancelling DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France AD 95–203–072 (no requirements 

retained) [which corresponds to FAA AD 98– 

09–18, Amendment 39–10499 (63 FR 23374, 

April 29, 1998)], and partially retaining the 

requirements of DGAC France AD 2001–508 

[which corresponds to FAA AD 2003–25–07], 

and [DGAC France] AD F–2004–147 (EASA 

approval ref. 2004–8601) [which corresponds 

to FAA AD 2005–13–39], which were 

superseded, and to require replacement of all 

ELAC with ELAC L97+ standard. 

Since that [EASA] AD was issued, some 

errors were detected in Appendix 1 of the 

[EASA] AD, and one P/N ELAC was 

inadvertently omitted. This [EASA] AD 

revises EASA AD 2015–0088 to correct these 

errors and to add clarification to paragraph 

(7) [of the EASA AD]. 

The required actions include either 

replacing existing ELACs with new 

ELACs having L97+ standards 

uploaded, or revising the software in the 

existing ELACs to L97+ standards. This 

AD also expands the applicability to 

include all Airbus Model A318, A319, 

A320, and A321 series airplanes. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

4226. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supported the NPRM. 

Conclusion 

We reviewed the available data, 

including the comment 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 NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 

1 CFR Part 51 

Airbus has issued Service Bulletin 

A320–27–1243, including Appendix 01, 

dated March 17, 2015. This service 

information describes procedures for 

replacing the existing ELACs with new 

ELACs having L97+ standards, and 

modifying existing ELACs into units 

with L97+ standards. 

Airbus has also issued Service 

Bulletin A320–27–1244, dated March 5, 

2015. This service information describes 

procedures for modification of an 

airplane by replacing any existing ELAC 

unit with an ELAC 97+ unit having P/ 

N 3945128215. 

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 940 

airplanes of U.S. registry. 

The actions required by AD 2003–25– 

07 and retained in this AD take about 

1 work-hour per product, at an average 

labor rate of $85 per work-hour. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

2003–25–07 is $85 per product. 

The actions required by AD 2005–13– 

39 and retained in this AD take about 

1 work-hour per product, at an average 

labor rate of $85 per work-hour. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

2005–13–39 is $85 per product. 

We also estimate that it will take 

about 3 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 $7,230 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$7,035,900, or $7,485 per product. 

According to the parts manufacturer, 

some of the costs of this AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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; 


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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. 

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) 2003–25–07, Amendment 39– 

13390 (68 FR 70431, December 18, 

2003); and AD 2005–13–39, 

Amendment 39–14176 (70 FR 38580, 

July 5, 2005); and 

■ b. Adding the following new AD: 

2016–17–03 Airbus: Docket No. FAA–2016– 

4226; Directorate Identifier 2015–NM– 

095–AD. 

(a) Effective Date 

This AD is effective September 23, 2016. 

(b) Affected ADs 

This AD replaces the ADs identified in 

paragraphs (b)(1) and (b)(2) of this AD. 

(1) AD 2003–25–07, Amendment 39–13390 

(68 FR 70431, December 18, 2003) (‘‘AD 

2003–25–07’’). 

(2) AD 2005–13–39, Amendment 39–14176 

(70 FR 38580, July 5, 2005) (‘‘AD 2005–13– 

39’’). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(4) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

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

–114, –115, –131, –132, and –133 airplanes. 

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

–231, –232, and –233 airplanes. 

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

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that new elevator aileron computer (ELAC) 

standards must be incorporated. The ELAC 

standards have been upgraded to version 

L97+, which implements enhanced angle-ofattack (AOA) monitoring to better detect 

AOA blockage, including multiple AOA 

blockages. We are issuing this AD to prevent 

inadvertent activation of the AOA 

protections. Inadvertent activation of the 

AOA protections could result in a continuous 

nose-down pitch rate that could result in 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Replacement of ELAC L80 Units 

With L81 Units, With No Changes 

For Model A319 and A320 series airplanes, 

equipped with ELAC L80 standards having 

part numbers listed in Airbus Service 

Bulletin A320–27–1135, dated June 29, 2001: 

This paragraph restates the requirements of 

paragraph (b) of AD 2003–25–07, with no 

changes. Within 1 year after January 22, 2004 

(the effective date of AD 2003–25–07): 

Replace both ELACs having L80 standards 

with new ELACs having L81 standards, by 

doing all the actions per paragraphs A., B., 

C., and D. of the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1135, dated June 29, 2001. 

(h) Retained Installation of ELAC L83 or L91 

Software, With No Changes 

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

and –231 airplanes, except those with Airbus 

Modification 34043 installed in production: 

This paragraph restates the requirements of 

paragraph (g) of AD 2005–13–39, with no 

changes. Within 16 months after August 9, 

2005 (the effective date of AD 2005–13–39): 

Replace existing ELACs with ELACs having 

L83 standards, by accomplishing all of the 

actions specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1151, dated March 9, 2004, including 

Appendix 01, dated March 9, 2004; or with 

ELACs having L91 standards, by 

accomplishing all of the actions specified in 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1152, dated June 

4, 2004, including Appendix 01, dated June 

4, 2004; as applicable. 

(i) New Requirement of This AD: ELAC 

Replacement or Modification 

At the applicable times specified in table 

1 to paragraphs (i) and (m)(3)(ii) of this AD: 

Replace each ELAC unit with an ELAC L97+ 

unit having part number (P/N) 3945129100 

and software having P/N 3945129109, or 

modify existing ELAC units into ELAC L97+ 

units having P/N 3945129100 with L97+ 

operational software P/N 3945129109 loaded, 

as applicable, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1243, including 

Appendix 01, dated March 17, 2015. 

Accomplishing this replacement terminates 

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

of this AD. 

TABLE 1 TO PARAGRAPHS (i) AND (m)(3)(ii) OF THIS AD—COMPLIANCE TIMES

Airbus airplane models 

Compliance time 

(after the effective 

date of this AD) 

Model A318 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions 

(captain, first officer, and standby).

Within 5 months. 

Model A319 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions 

(captain, first officer, and standby).

Within 10 months. 

Model A320 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions 

(captain, first officer, and standby).

Within 10 months. 

Model A321 series airplanes with UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 0861ED2 installed in all 3 positions 

(captain, first officer, and standby).

Within 5 months. 

Model A318, A319, A320, and A321 series airplanes that do not have UTAS (formerly Goodrich) AOA P/N 0861ED or P/N 

0861ED2 installed in all 3 positions (captain, first officer, and standby).

Within 25 months. 

(j) Optional Method of Compliance 

Modification of an airplane by replacing 

any existing ELAC unit with an ELAC 97+ 

unit having P/N 3945128215, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–27–1244, 

dated March 5, 2015, is an acceptable method 

of compliance for the requirements of 

paragraph (i) of this AD, for only that 

modified airplane. Accomplishing this 

modification terminates the actions required 

by paragraphs (g) and (h) of this AD for that 

modified airplane. 

Note 1 to paragraph (j) of this AD: ELAC 

unit P/N 3945128215 is not data-loadable, 


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but it is fully interchangeable and mixable 

with data-loadable ELAC 97+ unit P/N 

3945129100 with software P/N 3945129109 

loaded. 

(k) Airplanes Excluded From Requirements 

of Paragraphs (g), (h), and (i), and From the 

Actions in Paragraph (j) of This AD 

Airplanes on which Airbus Modification 

156546 (installation of ELAC L97+ with 

software P/N 3945129109) was installed in 

production are excluded from the 

requirements of paragraphs (g), (h), and (i) of 

this AD, and from the actions specified in 

paragraph (j) of this AD, provided it can be 

determined that no ELAC having a part 

number identified in table 2 to paragraphs (k) 

and (m) of this AD has been installed on that 

airplane since the date of issuance of the 

original airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

TABLE 2 TO PARAGRAPHS (k) AND (m) OF THIS AD—PROHIBITED ELAC PART NUMBERS

Part No. Designation FIN 

3945122202 ............................................................................... ELAC A320–111 Type Def. ..................................................... 2 CE 1/2 

3945122203 ............................................................................... ELAC L50C .............................................................................. 2 CE 1/2 

3945122303 ............................................................................... ELAC L50C .............................................................................. 2 CE 1/2 

3945122304 ............................................................................... ELAC L60 ................................................................................. 2 CE 1/2 

3945122305 ............................................................................... ELAC L61B .............................................................................. 2 CE 1/2 

3945122306 ............................................................................... ELAC L61F ............................................................................... 2 CE 1/2 

3945122307 ............................................................................... ELAC L62C .............................................................................. 2 CE 1/2 

C12370AA01 .............................................................................. ELAC L68C .............................................................................. 2 CE 1/2 

3945122501 ............................................................................... ELAC L69 ................................................................................. 2 CE 1/2 

3945122502 ............................................................................... ELAC L69J ............................................................................... 2 CE 1/2 

3945122503 ............................................................................... ELAC L77 ................................................................................. 2 CE 1/2 

3945122504 ............................................................................... ELAC L78 ................................................................................. 2 CE 1/2 

3945122505 ............................................................................... ELAC A L80 ............................................................................. 2 CE 1/2 

3945123505 ............................................................................... ELAC A’ L80 ............................................................................ 2 CE 1/2 

3945128101 ............................................................................... ELAC B L80 ............................................................................. 2 CE 1/2 

3945122506 ............................................................................... ELAC A L81 ............................................................................. 2 CE 1/2 

3945123506 ............................................................................... ELAC A’ L81 ............................................................................ 2 CE 1/2 

3945128102 ............................................................................... ELAC B L81 ............................................................................. 2 CE 1/2 

3945122507 ............................................................................... ELAC A L82 ............................................................................. 2 CE 1/2 

3945123507 ............................................................................... ELAC A’ L82 ............................................................................ 2 CE 1/2 

3945128103 ............................................................................... ELAC B L82 ............................................................................. 2 CE 1/2 

3945122608 ............................................................................... ELAC A L83 ............................................................................. 2 CE 1/2 

3945123608 ............................................................................... ELAC A’ L83 ............................................................................ 2 CE 1/2 

3945122609 ............................................................................... ELAC A L84 ............................................................................. 2 CE 1/2 

3945123609 ............................................................................... ELAC A’ L84 ............................................................................ 2 CE 1/2 

3945128204 ............................................................................... ELAC B L90L ........................................................................... 2 CE 1/2 

3945128205 ............................................................................... ELAC B L90N ........................................................................... 2 CE 1/2 

3945128206 ............................................................................... ELAC B L91 ............................................................................. 2 CE 1/2 

3945129101 ............................................................................... ELAC B L91 data loadable ...................................................... 2 CE 1/2 SW1 

3945128207 ............................................................................... ELAC B L92 ............................................................................. 2 CE 1/2 

3945128208 ............................................................................... ELAC B L92L ........................................................................... 2 CE 1/2 

3945128209 ............................................................................... ELAC B L93 ............................................................................. 2 CE 1/2 

3945129103 ............................................................................... ELAC B L93 data loadable ...................................................... 2 CE 1/2 SW1 

3945128210 ............................................................................... ELAC B L94 ............................................................................. 2 CE 1/2 

3945129104 ............................................................................... ELAC B L94 data loadable ...................................................... 2 CE 1/2 SW1 

3945128212 ............................................................................... ELAC B L96 ............................................................................. 2 CE 1/2 

3945129106 ............................................................................... ELAC B L96 data loadable ...................................................... 2 CE 1/2 SW1 

3945129107 ............................................................................... ELAC B L96 H–A data loadable .............................................. 2 CE 1/2 SW1 

3945128214 ............................................................................... ELAC B L97 ............................................................................. 2 CE 1/2 

3945129108 ............................................................................... ELAC B L97 data loadable ...................................................... 2 CE 1/2 SW1 

(l) Later-Approved Parts 

Installation of an ELAC version (part 

number) approved after the effective date of 

this AD is an approved method of 

compliance with the requirements of 

paragraph (i) of this AD, and the actions 

specified in paragraph (j) of this AD, 

provided the requirements specified in 

paragraphs (l)(1) and (l)(2) of this AD are met. 

(1) The version (part number) must be 

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). 

(2) The installation must be done using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. 

(m) Parts Installation Limitation 

As of the applicable time specified in 

paragraph (m)(1) or (m)(2) of this AD, do not 

install on any airplane an ELAC unit having 

a part number identified in table 2 to 

paragraphs (k) and (m) of this AD, except as 

specified in paragraph (m)(3) of this AD. 

(1) For an airplane that, as of the effective 

date of this AD, has any ELAC unit installed 

having a part number identified in table 2 to 

paragraphs (k) and (m) of this AD: After 

modification of that airplane as required by 

paragraph (i) of this AD, or as specified in 

paragraph (j) of this AD. 

(2) For an airplane that, as of the effective 

date of this AD, does not have any ELAC unit 

installed having a part number identified in 

table 2 to paragraphs (k) and (m) of this AD: 

As of the effective date of this AD. 

(3) As of the effective date of this AD, a 

data-loadable ELAC B unit having a part 

number identified in table 2 to paragraphs (k) 

and (m) of this AD can be installed on an 

airplane provided that L97+ software P/N 

3945129109 is uploaded at the applicable 

time specified in paragraph (m)(3)(i) or 

(m)(3)(ii) of this AD. 

(i) For all airplanes except those identified 

in paragraph (m)(3)(ii) of this AD: Before 

further flight after the ELAC B unit 

installation. 

(ii) For airplanes that have not been 

modified as required by paragraph (i) of this 

AD: Within the applicable compliance time 


jstallworth on DSK7TPTVN1PROD with RULES
55362 Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations 

specified in table 1 to paragraphs (i) and 

(m)(3)(ii) of this AD. 

(n) 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. 

(ii) AMOCs approved previously for AD 

2003–25–07 are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(iii) AMOCs approved previously for AD 

2005–13–39 are approved as AMOCs for the 

corresponding provisions of paragraph (h) 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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

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

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. 

(o) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0088R1, 

including Appendix 01, dated June 2, 2015, 

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–2016–4226. 

(p) 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 September 23, 2016. 

(i) Airbus Service Bulletin A320–27–1243, 

including Appendix 01, dated March 17, 

2015. 

(ii) Airbus Service Bulletin A320–27–1244, 

dated March 5, 2015. 

(4) The following service information was 

approved for IBR on August 9, 2005 (70 FR 

38580, July 5, 2005). 

(i) Airbus Service Bulletin A320–27–1151, 

including Appendix 01, dated March 9, 2004. 

(ii) Airbus Service Bulletin A320–27–1152, 

including Appendix 01, dated June 4, 2004. 

(5) The following service information was 

approved for IBR on January 22, 2004 (68 FR 

70431, December 18, 2003). 

(i) Airbus Service Bulletin A320–27–1135, 

dated June 29, 2001. 

(ii) Reserved. 

(6) For 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. 

(7) 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. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on August 

8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–19486 Filed 8–18–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8463; Directorate 

Identifier 2014–NM–226–AD; Amendment 

39–18612; AD 2016–16–14] 

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) 2013–20– 

11, for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 

2013–20–11 required modifying the 

passenger emergency oxygen container 

assembly. This new AD expands the 

affected group of oxygen containers to 

include those labeled ‘‘DAe Systems.’’ 

This AD was prompted by a 

determination that the unsafe condition 

also affects oxygen containers labeled 

‘‘DAe Systems.’’ We are issuing this AD 

to prevent a high temperature oxygen 

generator and mask from falling down 

and possibly resulting in an ignition 

source in the passenger compartment, 

injury to passengers, and reduced 

availability of supplemental oxygen. 

DATES: This AD is effective September 

23, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 2, 2013 (78 FR 64162, 

October 28, 2013). 

ADDRESSES: 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.airwortheas@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– 

8463. 

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– 

8463; 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 (telephone 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 


jstallworth on DSK7TPTVN1PROD with RULES