40672 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 

TABLE 1 TO PARAGRAPHS (g) AND (h) 

OF THIS AD—PARTS TO BE INSPECTED/INSTALLED

Affected part No. 

Acceptable 

replacement 

part No. 

Area 

F5347126620600 ... F5347126620000 ... Cabin. 

F5347126621000 ... F5347126620400 ... Cabin. 

F5377004320300 ... F5377004320351 ... Cabin. 

F5347170420400 ... F5347170420400 ... Cargo. 

F5347170420600 ... F5347170420600 ... Cargo. 

G5367131300000 ... G5367131300000 .. Cargo. 

G5367173700000 ... G5367173700000 .. Cargo. 

G5367173800000 ... G5367173800000 .. Cargo. 

(h) Replacement 

If during the inspection required by 

paragraph (g) of this AD, any affected part 

having a part number specified in table 1 to 

paragraphs (g) and (h) of this AD is found to 

have a measured value greater than that 

specified in Figure A–GFAAA, Sheet 02, 

‘‘Inspection Flowchart,’’ of the applicable 

service information identified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, except as 

provided by paragraph (i) of this AD: Within 

6 years after the effective date of this AD, but 

not exceeding 12 years since the date of 

issuance of the original certificate of 

airworthiness or the date of issuance of the 

original export certificate of airworthiness, 

replace the affected part with an acceptable 

replacement part having a part number 

specified in table 1 to paragraphs (g) and (h) 

of this AD, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

(i) Exception to Certain Service Information 

Where Figure A–GFAAA, Sheet 02, 

‘‘Inspection Flowchart,’’ of the service 

information identified in paragraphs (g)(2) 

and (g)(3) of this AD specifies to ‘‘do the 

conductivity (s) measurement with 60kHz 

(refer to Appendix 01) s480 = lllMS/m,’’ 

the correct conductivity measurement is 

‘‘s60 = lllMS/m.’’ 

(j) Additional Inspection for Certain 

Airplanes 

For Model A330 airplanes on which the 

inspection and replacement, as applicable, 

specified in paragraphs (g) and (h) of this AD 

were done before the effective date of this 

AD, in accordance with Airbus Service 

Bulletin A330–53–3261, dated June 23, 2015: 

Within 6 years after the effective date of this 

AD, but not exceeding 12 years since the date 

of issuance of the original certificate of 

airworthiness or the date of issuance of the 

original export certificate of airworthiness, 

do a one-time eddy current conductivity 

measurement of structural parts having part 

number (P/N) G5367131300000, P/N 

G5367173700000, and P/N G5367173800000, 

located in fuselage section 15, in accordance 

with the ‘‘Additional Work’’ section of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3261, Revision 01, 

including Appendixes 01, 02, and 03, dated 

November 10, 2016. 

(k) Replacement 

If during the inspection required by 

paragraph (j) of this AD, any affected part 

having a part number specified in paragraph 

(j) of this AD is found to have a measured 

value greater than that specified in Figure A– 

GFAAA, Sheet 02, ‘‘Inspection Flowchart,’’ 

of Airbus Service Bulletin A330–53–3261, 

Revision 01, including Appendixes 01, 02, 

and 03, dated November 10, 2016: Within 6 

years after the effective date of this AD, but 

not exceeding 12 years since the date of 

issuance of the original certificate of 

airworthiness or the date of issuance of the 

original export certificate of airworthiness, 

replace the affected part with an acceptable 

replacement part having a part number 

specified in table 1 to paragraphs (g) and (h) 

of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3261, Revision 01, 

including Appendixes 01, 02, and 03, dated 

November 10, 2016. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 International 

Section, send it to the attention of the person 

identified in paragraph (m)(2) of this AD. 

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. 

(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 Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized 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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2017–0021, dated 

February 8, 2017, 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–2016–7264. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; telephone 

425–227–1138; fax 425–227–1149. 

(n) 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 A330–53–3261, 

Revision 01, including Appendixes 01, 02, 

and 03, dated November 10, 2016. 

(ii) Airbus Service Bulletin A330–53–3262, 

including Appendixes 01 and 02, dated June 

23, 2015. 

(iii) Airbus Service Bulletin A340–53– 

5072, including Appendixes 01 and 02, dated 

June 23, 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 Standards Branch, 

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 August 

9, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17536 Filed 8–25–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0337; Product 

Identifier 2017–NM–006–AD; Amendment 

39–19006; AD 2017–17–16] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


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Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40673 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767 

airplanes. This AD was prompted by a 

report of cracking of the vertical 

stiffener in the nose wheel well. This 

AD requires repetitive inspections of the 

nose wheel well bulkhead stiffener for 

any cracking, and corrective actions if 

necessary. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 2, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; Internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 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–2017– 

0337. 

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–2017– 

0337; 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 final rule, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

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

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO 

Branch, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6447; 

fax: 425–917–6590; email: 

wayne.lockett@faa.gov. 

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 certain The Boeing Company 

Model 767 airplanes. The NPRM 

published in the Federal Register on 

May 16, 2017 (82 FR 22443). The NPRM 

was prompted by a report of cracking of 

the vertical stiffener in the nose wheel 

well. The NPRM proposed to require 

repetitive inspections of the nose wheel 

well bulkhead stiffener for any cracking, 

and corrective actions if necessary. We 

are issuing this AD to detect and correct 

such cracking, which could adversely 

affect the structural integrity of the 

airplane and possibly lead to cabin 

depressurization or a nose landing gear 

collapse. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. United 

Airlines and The Boeing Company 

supported the NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST01920SE does not 

affect the actions specified in the 

NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD (82 FR 22443, May 16, 

2017) as paragraph (c)(1) and added 

paragraph (c)(2) to this AD to state that 

installation of STC ST01920SE does not 

affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST01920SE 

is installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the change 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. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 767–53A0275, dated January 5, 

2017. The service information describes 

procedures for a detailed inspection and 

a medium frequency eddy current 

inspection of the nose wheel well 

bulkhead stiffener for any cracking, and 

corrective actions 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 144 

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 

Inspection ...................... 10 work-hour × $85 per hour = $850 per inspection cycle.$0 $850 per inspection 

cycle.

$122,400 per inspection 

cycle. 

We estimate the following costs to do 

certain repairs that would be required 

based on the results of the inspection. 

We have no way of determining the 

number of aircraft that might need this 

repair: 


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40674 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair .............................................. 18 work-hour × $85 per hour = $1,530 ..................................................... $0 $1,530 

We have received no definitive data 

that would enable us to provide cost 

estimates for other repairs 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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes to the Director of the System 

Oversight Division. 

Regulatory Findings 

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 

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): 

2017–17–16 The Boeing Company: 

Amendment 39–19006; Docket No. 

FAA–2017–0337; Product Identifier 

2017–NM–006–AD. 

(a) Effective Date 

This AD is effective October 2, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 767–53A0275, dated January 

5, 2017. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE does not affect 

the ability to accomplish the actions required 

by this AD. Therefore, for airplanes on which 

STC ST01920SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53; Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracking in the vertical stiffener in the nose 

wheel well. We are issuing this AD to detect 

and correct such cracking, which could 

adversely affect the structural integrity of the 

airplane and possibly lead to cabin 

depressurization or a nose landing gear 

collapse. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 767–53A0275, dated 

January 5, 2017, except as specified in 

paragraph (h)(1) of this AD: Do a detailed 

inspection and a medium frequency eddy 

current inspection of the nose wheel well 

bulkhead stiffener for any cracking, and do 

all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0275, dated January 5, 2017; except 

as specified in paragraph (h)(2) of this AD. 

Do all corrective actions before further flight. 

Repeat the inspections thereafter at the times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 767–53A0275, 

dated January 5, 2017. 

(h) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

767–53A0275, dated January 5, 2017, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) If any cracking is found and Boeing 

Alert Service Bulletin 767–53A0275, dated 

January 5, 2017, specifies to contact Boeing 

for appropriate action and specifies that 

action as ‘‘RC’’ (Required for Compliance): 

Before further flight repair using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO Branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (j) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 


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Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40675 

(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 

Branch, 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) Except as required by paragraph (h)(2) 

of this AD: For service information that 

contains steps that are labeled as 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. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. 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 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO Branch, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6447; fax: 425–917– 

6590; email: wayne.lockett@faa.gov. 

(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 767– 

53A0275, dated January 5, 2017. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: 

Contractual & Data Services (C&DS), 2600 

Westminster Blvd., MC 110–SK57, Seal 

Beach, CA 90740–5600; telephone 562–797– 

1717; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

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 August 

11, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–17591 Filed 8–25–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9518; Product 

Identifier 2015–NM–091–AD; Amendment 

39–18989; AD 2017–16–12] 

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) 2013–19– 

09 and AD 2014–25–51, which applied 

to all Airbus Model A318, A319, A320, 

and A321 series airplanes. AD 2013–19– 

09 required replacing Angle of Attack 

(AOA) sensor conic plates with AOA 

sensor flat plates. AD 2014–25–51 

required revising the airplane flight 

manual (AFM) to advise the flightcrew 

of emergency procedures for abnormal 

Alpha Protection (Alpha Prot). This new 

AD requires replacing certain AOA 

sensors; and doing a detailed inspection 

and a functional heating test for 

discrepancies on certain AOA sensors, 

and replacing the affected AOA sensors. 

This AD was prompted by a report 

indicating that a Model A321 airplane 

encountered a blockage of two AOA 

probes during climb, leading to 

activation of the Alpha Prot while the 

Mach number increased. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective October 2, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 2, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 6, 2013 (78 FR 

60667, October 2, 2013). 

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 

Standards Branch, 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– 

9518. 

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– 

9518; 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 Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–19–09, 

Amendment 39–17591 (78 FR 60667, 

October 2, 2013) (‘‘AD 2013–19–09’’), 

and AD 2014–25–51, Amendment 39– 

18067 (80 FR 3153, January 22, 2015) 

(‘‘AD 2014–25–51’’). AD 2013–19–09 

and AD 2014–25–51 applied to all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. The NPRM 

published in the Federal Register on 

December 28, 2016 (81 FR 95531). The 

NPRM was prompted by a report 

indicating that an Airbus Model A321 

airplane encountered a blockage of two 

AOA probes during climb, leading to 

activation of the Alpha Prot while the 

Mach number increased. The NPRM 

proposed to continue to require 

replacing AOA sensor conic plates with 

AOA sensor flat plates and revising the 

AFM to advise the flight crew of 

emergency procedures for abnormal 

Alpha Prot. The NPRM also proposed to 


asabaliauskas on DSKBBXCHB2PROD with RULES