## 21722 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations

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 adding the following new airworthiness directive (AD):
2016–07–25 The Boeing Company: Amendment 39–18470; Docket No. FAA–2015–2959; Directorate Identifier 2015–NM–008–AD.
(a) Effective Date

This AD is effective May 18, 2016.

(b) Affected ADs

None.
(c) Applicability

This AD applies to The Boeing Company Model 787–8 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin B787–81205–SB290015–00, Issue 002, dated November 25, 2014.
(d) Subject

Air Transport Association (ATA) of America Code 29, Hydraulic Power.

(e) Unsafe Condition

This AD was prompted by reports indicating that the ram air turbine (RAT) assembly may fail to operate if deployed at low airspeeds. We are issuing this AD to prevent failure of the RAT assembly to operate at low air speeds. The volume fuseon the RAT assembly may be activated inflight before the RAT is deployed. This may lead to improper pump hydraulic pressure offloading when the RAT is needed. Failure of the RAT to operate in an all engine out event would result in loss of control of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Replacement

Within 36 months after the effective date of this AD, replace the RAT pump and control module assembly or the RAT assembly, including an installation test and applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205– SB290015–00, Issue 002, dated November 25, 2014. Do all applicable corrective actions before further flight.

(h) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin B787–81205–SB290015–00, Issue 001, dated September 4, 2014, which is not incorporated by reference in this AD.
(i) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.

(2) 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD.

(4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply.

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.
(j) Related Information

(1) For more information about this AD, contact Sean J. Schauer, Aerospace Engineer, Systems and Equipment Branch, ANM 130S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6479; fax: 425–917–6590; email: sean.schauer@faa.gov.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD.
(k) 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 the AD specifies otherwise.

(i) Boeing Alert Service Bulletin B787– 81205–SB290015–00, Issue 002, dated November 25, 2014.

(ii) Reserved. (3) For Boeing 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.

(4) You may view this service information at FAA, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on March 26, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–07839 Filed 4–12–16; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–4810; Directorate Identifier 2015–NM–090–AD; Amendment**  **39–18475; AD 2016–07–30]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY**

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY**

### : We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200, –200 Freighter, and –300 series airplanes, and all Airbus Model A340–200, –300, –500, and –600 series airplanes. This AD was prompted by a report of blockage of Angle of Attack (AOA) probes during climb, leading to activation of the Alpha Protection (Alpha Prot) while the Mach number increased. This activation could cause a continuous nose-down pitch rate that cannot be stopped with backward sidestick input, even in the full backward position. For certain airplanes, this AD requires replacing certain AOA sensors (probes) with


## 21723 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations

certain new AOA sensors. For certain other airplanes, this AD also requires inspections and functional heat testing of certain AOA sensors for discrepancies, and replacement if necessary. We are issuing this AD to prevent erroneous AOA information and Alpha Prot activation due to blocked AOA probes, which could result in a continuous nose-down command and loss of control of the airplane.

**DATES** 

### : This AD becomes effective May 18, 2016.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 18, 2016.

**ADDRESSES** 

### : For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@ 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–2015–4810. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-4810; 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 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 FURTHER INFORMATION CONTACT**

### : Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and all Airbus Model A340– 200, –300, –500, and –600 series airplanes. The NPRM published in the Federal Register on November 12, 2015 (80 FR 69899) (‘‘the NPRM’’).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0134, dated July 8, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330– 200, –200 Freighter, and –300 series airplanes; and all Model A340–200, –300, –500, and –600 series airplanes. The MCAI states:

An occurrence was reported where an Airbus A321 aeroplane encountered a blockage of two Angle of Attack (AOA) probes during climb, leading to activation of the Alpha Protection (Alpha Prot) while the Mach number increased. The flight crew managed to regain full control and the flight landed uneventfully. It was determined that the affected AOA probes are also fitted on A330 and A340 aeroplanes.

When Alpha Prot is activated due to blocked AOA probes, the flight control laws order a continuous nose down pitch rate that, in a worst case scenario, cannot be stopped with backward sidestick inputs, even in the full backward position. If the Mach number increases during a nose down order, the AOA value of the Alpha Prot will continue to decrease. As a result, the flight control laws will continue to order a nose down pitch rate, even if the speed is above minimum selectable speed, known as VLS.

This condition, if not corrected, could result in loss of control of the aeroplane.

Investigation results indicated that aeroplanes equipped with certain UTC Aerospace (UTAS, formerly known as Goodrich) AOA sensors, or equipped with certain SEXTANT/THOMSON AOA sensors, appear to have a greater susceptibility to adverse environmental conditions than aeroplanes equipped with the latest Thales AOA sensor, Part Number (P/N) C16291AB, which was designed to improve AOA indication behaviour in heavy rain conditions.

Having determined that replacement of these AOA sensors is necessary to achieve and maintain the required safety level of the aeroplane, EASA issued [an AD ***], to require modification of the aeroplanes by replacement of the affected P/N sensors, and, after modification, prohibits (re-) installation of those P/N AOA sensors. That [EASA] AD also required repetitive detailed visual inspections (DET) and functional heating tests of certain Thales AOA sensors and provided an optional terminating action for those inspections.

Since EASA AD 2015–0089 was issued, based on further analysis results, Airbus issued Operators Information Transmission (OIT) Ref. 999.0017/15 Revision 1, instructing operators to speed up the removal from service of UTAS P/N 0861ED2 AOA

sensors.

For the reasons described above, this [EASA] AD retains the requirements of EASA [AD ***], which is superseded, but reduces the compliance times for aeroplanes with UTAS P/N 0861ED2 AOA sensors installed.



### 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–2015–
4810.

Actions Since the NPRM Was Issued

Since we issued the NPRM Airbus has issued the following service information:

• Service Bulletin A330–34–3215, Revision 03, dated July 23, 2015.

• Service Bulletin A340–34–4215, Revision 03, dated July 27, 2015.

• Service Bulletin A340–34–5062, Revision 02, dated July 24, 2015. Explanation of Certain Changes to the NPRM

We have revised paragraph (j) of this AD to refer to this revised service information.

We have also added a new paragraph (l) to this AD, and reidentified subsequent paragraphs, to give credit for doing the actions using the following service information:

• Airbus Service Bulletin A330–34– 3215, Revision 02, dated March 29,
2010.

• Airbus Service Bulletin A340–34– 4215, Revision 02, dated March 29,
2010.

• Airbus Service Bulletin A340–34– 5062, Revision 01, dated March 29,
2010.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA’s
response. Request To Reduce Certain Compliance Times

Airbus asked that we reduce the compliance time from 22 months to 12 months for P/N 0861ED removal, and from 7 months to 3 months for P/N 0861ED2 removal.

We do not agree with the request, as no supporting data was provided by the commenter. We contacted Airbus to determine if there was a justification for reducing the compliance times specified in the proposed AD. We noted that reducing the compliance times would necessitate (under the provisions of the Administrative Procedure Act) reissuing the notice, reopening the period for public comment, considering additional


## 21724 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations

comments subsequently received, and eventually issuing a final rule. Airbus stated it concurs with keeping the compliance times specified in the proposed AD. We have determined that further delay of this final rule is not appropriate. However, if additional data are presented that would justify a shorter compliance time, we may consider further rulemaking on this issue.

In developing an appropriate compliance time, we considered the safety implications, parts availability, and normal maintenance schedules for timely accomplishment of replacing the AOA sensors, as well as the compliance times required by the EASA AD. In consideration of these factors, we have determined that the compliance time, as proposed, represents an appropriate time in which the AOA sensors can be replaced in a timely manner within the fleet, while still maintaining an adequate level of safety. Most ADs, including this one, permit operators to accomplish the requirements of an AD at a time earlier than the specified compliance time; therefore, an operator may choose to replace the AOA sensors earlier. We have not changed this final rule in this regard.

Conclusion

We reviewed the relevant data, considered the comment received, 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 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 the following service information:

• Service Bulletin A330–34–3215, Revision 03, dated July 23, 2015.

• Service Bulletin A330–34–3228, dated October 7, 2009.

• Service Bulletin A330–34–3315, dated March 26, 2015.

• Service Bulletin A340–34–4215, Revision 03, dated July 27, 2015. • Service Bulletin A340–34–4234, dated October 7, 2009.

• Service Bulletin A340–34–4294, dated March 26, 2015.

• Service Bulletin A340–34–5062, Revision 02, dated July 24, 2015.

• Service Bulletin A340–34–5070, dated October 9, 2009.

• Service Bulletin A340–34–5105, dated March 26, 2015.

The service information describes procedures for replacing certain pitot probes with certain new pitot probes. The service information also describes procedures for inspections and functional heat testing of certain pitot probes, and replacement if necessary. 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 55 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Replacement ................................... 5 work-hours × $85 per hour = $425. $0 $425 ............................................... $23,375

Inspection/test ................................. 3 work-hours × $85 per hour = $255. 0 255 per inspection/test cycle ......... 14,025



### We have received no definitive data that will enable us to provide a cost estimate for the on-condition actions specified in this AD. 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. 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 adding the following new airworthiness directive (AD):

2016–07–30 Airbus: Amendment 39–18475. Docket No. FAA–2015–4810; Directorate Identifier 2015–NM–090–AD.
(a) Effective Date

This AD becomes effective May 18, 2016.


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(b) Affected ADs

None.
(c) Applicability

This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD, all manufacturer serial numbers.

(1) Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes.

(2) Airbus Model A340–211, –212, –213, –311, –312, –313, –541, and –642 airplanes.
(d) Subject

Air Transport Association (ATA) of America Code 34, Navigation.

(e) Reason

This AD was prompted by a report of blockage of two Angle of Attack (AOA) probes during climb, leading to activation of the Alpha Protection (Alpha Prot) while the Mach number increased. This activation could cause a continuous nose-down pitch rate that cannot be stopped with backward sidestick input, even in the full backward position. We are issuing this AD to prevent erroneous AOA information and Alpha Prot activation due to blocked AOA probes, which could result in a continuous nose-down command and consequent loss of control of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Replacement of Certain UTC Aerospace (UTAS) AOA Sensors

For airplanes on which any UTAS AOA sensor having part number (P/N) 0861ED or P/N 0861ED2 is installed: At the applicable time specified in paragraph (h) of this AD, replace all Captain and First Officer AOA sensors (probes) having P/N 0861ED or 0861ED2 with AOA sensors having Thales P/ N C16291AB, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.

(1) Airbus Service Bulletin A330–34–3315, dated March 26, 2015 (for Model A330 airplanes).

(2) Airbus Service Bulletin A340–34–4294, dated March 26, 2015 (for Model A340–200 and –300 airplanes).

(3) Airbus Service Bulletin A340–34–5105, dated March 26, 2015 (for Model A340–500 and –600 airplanes).
(h) Compliance Times for the Requirements of Paragraph (g) of This AD

Do the actions required by paragraph (g) of this AD at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD.

(1) For airplanes with AOA sensors having P/N 0861ED: Within 22 months after the effective date of this AD.

(2) For airplanes with AOA sensors having P/N 0861ED2: Within 7 months after the effective date of this AD. (i) Replacement of Certain SEXTANT/ THOMSON AOA Sensors

For airplanes on which any SEXTANT/ THOMSON AOA sensor having P/N 45150320 is installed: Within 22 months after the effective date of this AD, replace all SEXTANT/THOMSON AOA sensors (probes) having P/N 45150320 with AOA sensors having Thales P/N C16291AB, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(1) or (i)(2) of this AD.

(1) Airbus Service Bulletin A330–34–3228, dated October 7, 2009 (for Model A330 airplanes).

(2) Airbus Service Bulletin A340–34–4234, dated October 7, 2009 (for Model A340–200 and –300 airplanes).
(j) Repetitive Inspections/Tests of Certain Thales AOA Sensors

For airplanes on which one or more Thales AOA sensor having P/N C16291AA is installed: Before the accumulation of 17,000 total flight hours on the AOA sensor since first installation on an airplane, or within 6 months after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 3,800 flight hours; do a detailed inspection of the three AOA sensors at FINs 3FP1, 3FP2, and 3FP3 for discrepancies ( e.g., the vane of the sensor does not deice properly), and a functional heating test of each AOA sensor having P/N C16291AA, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD.

(1) Airbus Service Bulletin A330–34–3215, Revision 03, dated July 23, 2015 (for Model A330 airplanes).

(2) Airbus Service Bulletin A340–34–4215, Revision 03, dated July 27, 2015 (for Model A340–200 and –300 airplanes).

(3) Airbus Service Bulletin A340–34–5062, Revision 02, dated July 24, 2015 (for Model A340–500 and –600 airplanes).

(k) Corrective Actions

If any discrepancy is found during any inspection required by paragraph (j) of this AD, or if any test is failed during the heating test required by paragraph (j) of this AD: Before further flight, replace all affected AOA sensors with sensors identified in paragraph (k)(1) or (k)(2) of this AD, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD.

(1) Replace with AOA sensors having Thales P/N C16291AA, on which the inspection and test required by paragraph (j) of this AD were passed.

(2) Replace with AOA sensors having Thales P/N C16291AB.

(l) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, which are not incorporated by reference in this AD.

(1) Airbus Service Bulletin A330–34–3215, Revision 02, dated March 29, 2010. (2) Airbus Service Bulletin A340–34–4215, Revision 02, dated March 29, 2010.

(3) Airbus Service Bulletin A340–34–5062, Revision 01, dated March 29, 2010.
(m) Airplanes Excluded From Certain Requirements

(1) The actions specified in paragraphs (g), (i), (j), and (k) of this AD are not required, provided that the conditions specified in paragraphs (m)(1)(i), (m)(1)(ii), and (m)(1)(iii) of this AD are met.

(i) Airbus Modification 58555 (installation of Thales P/N C16291AB AOA sensors) has been embodied in production.

(ii) Airbus Modification 46921 (installation of UTAS AOA sensors) has not been embodied in production.

(iii) No AOA sensor having SEXTANT/ THOMSON P/N 45150320 or UTAS P/N 0861ED or P/N 0861ED2 has been installed on the airplane since date of issuance of the original airworthiness certificate or date of issuance of the original export certificate of airworthiness.

(2) The actions specified in paragraphs (g) and (i) of this AD are not required, provided that all conditions specified in paragraphs (m)(2)(i), (m)(2)(ii), and (m)(2)(iii) of this AD
are met.

(i) Only AOA sensors with part numbers approved after the effective date of this AD have been installed.

(ii) The AOA sensor part number is approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA).

(iii) The installation is accomplished in accordance with airplane modification instructions approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the EASA; or Airbus’s EASA DOA.
(n) Optional Terminating Modification

Replacement of all Thales AOA sensors having P/N C16291AA with Thales AOA sensors having P/N C16291AB, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (n)(1), (n)(2), or (n)(3) of this AD, terminates the repetitive inspections and functional heating tests required by paragraph (j) of this AD.

(1) Airbus Service Bulletin A330–34–3228, dated October 7, 2009 (for Model A330 airplanes).

(2) Airbus Service Bulletin A340–34–4234, dated October 7, 2009 (for Model A340–200 and –300 airplanes).

(3) Airbus Service Bulletin A340–34–5070, dated October 9, 2009 (for Model A340–500 and –600 airplanes).

(o) Parts Installation Prohibitions

(1) For airplanes on which only Thales P/ N C16291AB AOA sensors are installed as of the effective date of this AD: No person may install, on any airplane, a Thales AOA sensor having P/N C16291AA as of the effective date of this AD.

(2) For airplanes on which the modification specified in paragraph (n) of this AD has been done: No person may install, on any airplane, a Thales AOA sensor


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having P/N C16291AA after accomplishing the specified modification.

(3) For airplanes on which Thales P/N C16291AA or P/N C16291AB AOA sensors are installed as of the effective date of this AD: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, as of the effective date of this AD.

(4) For airplanes on which the replacement required by paragraph (i) of this AD has been done: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing the replacement.

(5) For airplanes on which the replacement required by paragraph (g) of this AD has been done: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing the replacement, except that a UTAS AOA sensor having P/N 0861ED may be installed in the standby position of that airplane.
(p) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the 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.
(q) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0134, dated July 8, 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–

2015–4810.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD.
(r) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

(i) Airbus Service Bulletin A330–34–3215, Revision 03, dated July 23, 2015.

(ii) Airbus Service Bulletin A330–34–3228, dated October 7, 2009.

(iii) Airbus Service Bulletin A330–34– 3315, dated March 26, 2015.

(iv) Airbus Service Bulletin A340–34– 4215, Revision 03, dated July 27, 2015.

(v) Airbus Service Bulletin A340–34–4234, dated October 7, 2009.

(vi) Airbus Service Bulletin A340–34– 4294, dated March 26, 2015.

(vii) Airbus Service Bulletin A340–34– 5062, Revision 02, dated July 24, 2015.

(viii) Airbus Service Bulletin A340–34– 5070, dated October 9, 2009.

(ix) Airbus Service Bulletin A340–34– 5105, dated March 26, 2015.

(3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com.

(4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on March 26, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–08267 Filed 4–12–16; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–2464; Directorate Identifier 2014–NM–195–AD; Amendment**  **39–18476; AD 2016–07–31]**

**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) 2013–22– 11 for certain The Boeing Company Model 747–400 and –400D series airplanes. AD 2013–22–11 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013–22–11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013–22–11. This AD adds additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracks could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.

**DATES** 

### : This AD is effective May 18,
2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 18, 2016.

**ADDRESSES** 

### : For service information identified in this final rule, 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–
2464.