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(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 versionL97+, 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 

### T IMES

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 

### T HIS 

### AD—P ROHIBITED 

### ELAC PART 

### N UMBERS

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


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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,