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 fuse 

on 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 


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

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 


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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: 

ESTIMATED 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 


jstallworth on DSK7TPTVN1PROD with RULES
21726 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

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. 


jstallworth on DSK7TPTVN1PROD with RULES