79750 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 

TABLE 1 TO PARAGRAPH (I) OF THIS

AD—REPLACEMENT COMPLIANCE

TIMES—Continued 

Year of 

manufacture Compliance time 

2009 ............... Before exceeding 10 years 

since date of manufacture 

of the passenger chemical 

oxygen generator. 

(j) Definition of Serviceable 

For the purpose of this AD, a serviceable 

unit is a passenger chemical oxygen 

generator having P/N 117042–XX (XX 

represents any numerical value) with a 

manufacturing date not older than 10 years, 

or any other approved part number, provided 

that the generator has not exceeded the life 

limit established for that generator by the 

manufacturer. 

(k) Reporting 

At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD, submit 

a report of the findings (both positive and 

negative) of the inspection required by 

paragraph (g) of this AD, in accordance with 

paragraph 7, ‘‘Reporting,’’ of Airbus AOT 

A35W008–14, dated December 18, 2014. The 

report must include the information specified 

in Appendix 1 of Airbus AOT A35W008–14, 

dated December 18, 2014. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(l) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a passenger chemical 

oxygen generator, unless it is determined, 

prior to installation, that the oxygen 

generator is a serviceable unit (as defined in 

paragraph (j) of this AD). 

(m) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116 Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–2125; 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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0118, dated 

June 24, 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– 

2015–7528. 

(2) For Airbus service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EAW, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone: +33 5 61 93 36 96; fax: 

+33 5 61 93 44 51; email: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. For B/E service identified 

in this AD, contact B/E Aerospace Inc., 10800 

Pflumm Road, Lenexa, KS 66215; telephone: 

913–338–9800; fax: 913–469–8419; Internet 

http://beaerospace.com/home/globalsupport. 

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. 

Issued in Renton, Washington, on 

December 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32084 Filed 12–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0250; Directorate 

Identifier 2014–NM–216–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Airbus Model A318, A319, A320, 

and A321 series airplanes. The NPRM 

proposed to require replacing certain 

pitot probes on the captain, first officer, 

and standby sides with certain new 

pitot probes. The NPRM was prompted 

by reports of airspeed indication 

discrepancies while flying at high 

altitudes in inclement weather. This 

action revises the NPRM by reducing 

the proposed compliance time for 

replacing certain pitot probes based on 

a risk assessment due to additional 

reports of airspeed indication 

discrepancies while flying at high 

altitudes in inclement weather. We are 

proposing this supplemental NPRM 

(SNPRM) to prevent airspeed indication 

discrepancies during inclement 

weather, which, depending on the 

prevailing altitude, could lead to 

unknown accumulation of ice crystals 

and consequent reduced controllability 

of the airplane. Since these actions 

impose an additional burden over those 

proposed in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this SNPRM by January 22, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 79751 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0250; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0250; Directorate Identifier 

2014–NM–216–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

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 A318, A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on March 6, 2015 (80 FR 

12094) (‘‘the NPRM’’). The NPRM was 

prompted by reports of airspeed 

indication discrepancies while flying at 

high altitudes in inclement weather. 

The NPRM proposed to require 

replacing certain pitot probes on the 

captain, first officer, and standby sides 

with certain new pitot probes. 

Actions Since Previous NPRM (80 FR 

12094, March 6, 2015) Was Issued 

Since we issued the NPRM (80 FR 

12094, March 6, 2015), we have 

determined it is necessary to reduce the 

compliance time for replacing certain 

pitot probes based on a risk assessment 

due to additional reports of airspeed 

indication discrepancies while flying at 

high altitudes in inclement weather. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, issued EASA Airworthiness 

Directive 2015–0205, dated October 9, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. The MCAI states: 

Occurrences have been reported on A320 

family aeroplanes of airspeed indication 

discrepancies while flying at high altitudes 

in inclement weather conditions. 

Investigation results indicated that A320 

aeroplanes equipped with Thales Avionics 

Part Number (P/N) 50620–10 or P/N 

C16195AA pitot probes appear to have a 

greater susceptibility to adverse 

environmental conditions that aeroplanes 

equipped with certain other pitot probes. 

Prompted by earlier occurrences, DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France issued [DGAC] AD 2001-362 [http:// 

ad.easa.europa.eu/blob/easa_ad_2001_

362.pdf/AD_2001-362] [which corresponds to 

paragraph (f) of FAA AD 2004-03-33, 

Amendment 39-13477 (69 FR 9936, March 3, 

2004)] to require replacement of Thales 

(formerly known as Sextant) P/N 50620-10 

pitot probes with Thales P/N C16195AA 

probes. 

Since that [DGAC] AD was issued, Thales 

pitot probe P/N C15195BA was designed, 

which improved airspeed indication 

behavior in heavy rain conditions, but did 

not demonstrate the same level of robustness 

to withstand high-altitude ice crystals. Based 

on these findings, EASA have decided to 

implement replacement of the affected 

Thales [pitot] probes as a precautionary 

measure to improve the safety level of the 

affected aeroplanes. 

Consequently, EASA issued AD 2014–0237 

(later revised) [http://ad.easa.europa.eu/

blob/easa_ad_2014_0237.pdf/AD_2014- 

0237], retaining the requirements of DGAC 

France AD 2001–362, which was superseded, 

and cancelling two other DGAC ADs, to 

require replacement of Thales Avionics pitot 

probes P/N C16195AA and P/N C16195BA. 

Since EASA issued AD 2014–0237R1 

[http://ad.easa.europa.eu/ad/2014-0237R1] 

was issued, results of further analyses have 

determined that the compliance time (48 

months) of that AD has to be reduced in 

relation to the risk assessment. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0237R1, which is superseded, but 

reduces the compliance time. 

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– 

0250. 

Related Rulemaking 

On February 4, 2004, we issued AD 

2004–03–33, Amendment 39–13477 (69 

FR 9936, March 3, 2004), applicable to 

certain Airbus Model A300 B2 and B4 

series airplanes; Model A300 B4–600, 

A300 B4–600R, and A300 F4–600R 

series airplanes; Model A310 series 

Airplanes; Model A319, A320, and 

A321 series airplanes; Model A330–301, 

–321, –322, –341, and –342 airplanes; 

and Model A340 series airplanes. That 

AD requires, among other actions, 

replacement of certain pitot probes with 

certain new pitot probes. That AD was 

issued to prevent loss or fluctuation of 

indicated airspeed, which could result 

in misleading information being 

provided to the flightcrew. 

Accomplishing the replacement 

specified in paragraph (g) of this 

SNPRM would terminate the 

requirements of paragraph (f) of AD 

2004–03–33, for that airplane only. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information: 

• Service Bulletin A320–34–1170, 

Revision 30, dated June 18, 2015. 

• Service Bulletin A320–34–1456, 

Revision 01, dated May 15, 2012. 

• Service Bulletin A320–34–1463, 

Revision 01, dated May 15, 2012. 

The service information describes 

procedures for replacing certain Thales 

Avionics pitot probes on the captain, 

first officer, and standby sides. 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 of 

this SNPRM. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
79752 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 

Comments 

We gave the public the opportunity to 

participate in developing this SNPRM. 

We considered the comments received. 

American Airlines supports the 

proposed compliance time of 48 months 

for retrofit. 

Request To Refer To Revised Service 

Information 

United Airlines (UAL) and Virgin 

America asked that the NPRM be 

revised to refer to Airbus Service 

Bulletin A320–34–1170, Revision 29, 

dated February 16, 2015. (The NPRM 

(80 FR 12094, March 6, 2015) referred 

to Airbus Service Bulletin A320–34– 

1170, Revision 28, dated September 1, 

2014, as the appropriate source of 

service information for replacing the 

pitot probes.) UAL stated that Airbus 

Service Bulletin A320–34–1170, 

Revision 29, dated February 16, 2015, 

includes UAL effectivity, as well as all 

A320 family airplanes fitted with Thales 

Pitot Probes. Virgin America stated that 

Airbus Service Bulletin A320–34–1170, 

Revision 28, dated September 1, 2014, is 

available only to select operators who 

previously purchased the change; 

Airbus Service Bulletin A320–34–1170, 

Revision 29, dated February 16, 2015, is 

available to all operators with airplanes 

having Thales pitot probes installed. 

American Airlines (AAL) asked that we 

refer to Airbus Service Bulletin A320– 

34–1170, Revision 30, which is 

scheduled for release in the near future. 

AAL added that the effectivity in Airbus 

Service Bulletin A320–34–1170, 

Revision 28, dated September 1, 2014, is 

incomplete. 

We agree to refer to Airbus Service 

Bulletin A320–34–1170, Revision 30, 

dated June 18, 2015, for the pitot probe 

replacement. Airbus Service Bulletin 

A320–34–1170, Revision 30, dated June 

18, 2015, was issued to update the 

operator list and related information in 

the effectivity, and does not include 

additional work. We have changed 

paragraph (g) of this SNPRM to refer to 

Airbus Service Bulletin A320–34–1170, 

Revision 30, dated June 18, 2015. In 

addition, to give credit for using Airbus 

Service Bulletin A320–34–1170, 

Revision 28, dated September 1, 2014, 

and Airbus Service Bulletin A320–34– 

1170, Revision 29, dated February 16, 

2015, we added new paragraphs 

(i)(1)(xxv) and (i)(1)(xxvi) to this 

SNPRM. 

Request To Reduce the Compliance 

Time 

The Airline Pilots Association 

International (ALPA) asked that the 

compliance time for replacement of the 

pitot probes, as specified in paragraph 

(g) of the proposed AD (80 FR 12094, 

March 6, 2015), be reduced to 24 

months or less. ALPA stated that it 

recognizes the potential flight safety risk 

of operating an airplane with reduced 

controllability characteristics, which 

justifies reducing the compliance time. 

We agree with the request to reduce 

the compliance time for replacement of 

the pitot probes. As specified under 

‘‘Actions Since Previous NPRM was 

Issued,’’ we have reduced the proposed 

compliance time for replacing certain 

pitot probes based on a risk assessment 

due to additional reports of airspeed 

indication discrepancies while flying at 

high altitudes in inclement weather. 

EASA has issued Airworthiness 

Directive 2015–0205, dated October 9, 

2015, to reduce the compliance time for 

replacement of the pitot probes to 24 

months. We have changed the 

compliance time in paragraph (g) of this 

SNPRM accordingly. 

Request for Clarification 

AAL stated the use of a pitot probe 

which meets the current icing 

specification, as specified in the NPRM 

(80 FR 12094, March 6, 2015), should 

note that a new icing specification is 

forthcoming. In addition, the UTAS 

(formerly Goodrich) pitot probe having 

part number 0851HL is built to the 

current specification. AAL noted that 

the data available today shows that pitot 

probes on which the new icing 

requirement is met should be available 

for retrofit in 2016. 

We acknowledge the commenter’s 

statement about the NPRM proposing 

the use of a pitot probe that meets the 

current icing airworthiness 

requirements and not the new icing 

airworthiness requirements of 

Amendment 25–140 (79 FR 65508, 

November 4, 2014) to 14 CFR part 25. 

Since we are currently not aware of any 

pitot probes certified to the new icing 

airworthiness requirements, this 

SNPRM would mandate Goodrich pitot 

probes having part number 0851HL, 

which meet the icing airworthiness 

requirements in effect at the time of 

establishing the certification basis for 

Airbus Model A318, A319, A320, and 

A321 series airplanes. AAL may request 

approval for an alternative method of 

compliance for the installation of pitot 

probes that meet the new certification 

standards once the pitot probes are 

available for installation, under the 

provisions of paragraph (k)(1) of this 

proposed AD. 

AAL also asked the following related 

questions and we have provided a 

response to each comment: 

• What FAA activities are scheduled 

with suppliers to meet the expectations 

of the new icing requirement? FAA 

activities associated with the new icing 

requirements are related to new design 

modifications. At this time we are not 

mandating installation of pitot probes 

which meet the new icing certification 

standards. 

• Does the FAA anticipate issuing a 

new AD mandating a retrofit/forward fit 

to the new icing requirement? We do 

not plan to issue further rulemaking 

mandating a retrofit/forward fit to the 

new icing requirement at this time. 

• Would the FAA extend the 

compliance time if another pitot probe 

supplier demonstrates compliance to 

the new icing requirement? We would 

not extend the compliance time because 

this SNPRM does not require installing 

pitot probes that meet the new icing 

requirement; therefore, the compliance 

time for the installation is considered 

adequate to address the unsafe 

condition. 

FAA’s Determination and Requirements 

of This SNPRM 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Certain changes described above 

expand the scope of the proposed AD 

(80 FR 12094, March 6, 2015). As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The procedures and tests 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 79753 

identified as RC (required for 

compliance) in any service information 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1170, 

Revision 30, dated June 18, 2015, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and 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 alternative method of compliance 

(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 will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 953 airplanes of U.S. registry. 

We also estimate that it would take 

about 4 work-hours per product to 

comply with the new basic 

requirements of this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about 

$21,930 per product. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$21,223,310, or $22,270 per product. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus: Docket No. FAA–2015–0250; 

Directorate Identifier 2014–NM–216–AD. 

(a) Comments Due Date 

We must receive comments by January 22, 

2016. 

(b) Affected ADs 

This AD affects AD 2004–03–33, 

Amendment 39–13477 (69 FR 9936, March 3, 

2004). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

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

and –122 airplanes. 

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

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

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

–231, –232, and –233 airplanes. 

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

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 34, Navigation. 

(e) Reason 

This AD was prompted by reports of 

airspeed indication discrepancies while 

flying at high altitudes in inclement weather. 

We are issuing this AD to prevent airspeed 

indication discrepancies during inclement 

weather, which, depending on the prevailing 

altitude, could lead to unknown 

accumulation of ice crystals and consequent 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Certain Pitot Probes on 

the Captain, First Officer, and Standby Sides 

Within 24 months after the effective date 

of this AD: Replace any Thales pitot probe 

having part number (P/N) C16195AA or P/N 

C16195BA, with a Goodrich pitot probe 

having P/N 0851HL, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1170, Revision 30, 

dated June 18, 2015. Accomplishing the 

replacement in this paragraph terminates the 

requirements of paragraph (f) of AD 2004– 

03–33, Amendment 39–13477 (69 FR 9936, 

March 3, 2004), for that airplane only. 

(h) Optional Methods of Compliance for 

Replacement Required by Paragraph (g) of 

This AD 

(1) Replacement of the pitot probes in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

34–1456, Revision 01, dated May 15, 2012 

(pitot probes on the captain and standby 

sides); and Airbus Service Bulletin A320–34– 

1463, Revision 01, dated May 15, 2012 (pitot 

probes on the first officer side); is an 

acceptable method of compliance with the 

requirements of paragraph (g) of this AD. 

(2) Airplanes on which Airbus 

Modification 25578 was embodied in 

production, except for post-modification 

25578 airplanes on which Airbus 

Modification 155737 (installation of Thales 

pitot probes) was also embodied in 

production, are compliant with the 

requirements of paragraph (g) of this AD, 

provided it can be conclusively determined 

that no Thales pitot probe having P/N 

C16195AA, P/N C16195BA, or P/N 50620–10 

has been installed since the date of issuance 

of the original certificate of airworthiness or 

the date of issuance of the original export 

certificate of airworthiness. Post-modification 

25578 airplanes on which Airbus 

Modification 155737 (installation of Thales 

pitot probes) was also embodied in 

production must be in compliance with the 

requirements of paragraph (g) of this AD. 

(i) Credit for Previous Actions 

(1) 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 service 


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79754 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 

information identified in paragraph (i)(1)(i) 

through (i)(1)(xxvi) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(i) Airbus Service Bulletin A320–34–1170, 

Revision 04, dated May 24, 2000. 

(ii) Airbus Service Bulletin A320–34–1170, 

Revision 05, dated September 11, 2000. 

(iii) Airbus Service Bulletin A320–34– 

1170, Revision 06, dated October 18, 2001. 

(iv) Airbus Service Bulletin A320–34– 

1170, Revision 07, dated December 4, 2001. 

(v) Airbus Service Bulletin A320–34–1170, 

Revision 08, dated January 15, 2003. 

(vi) Airbus Service Bulletin A320–34– 

1170, Revision 09, dated February 17, 2003. 

(vii) Airbus Service Bulletin A320–34– 

1170, Revision 10, dated November 21, 2003. 

(viii) Airbus Service Bulletin A320–34– 

1170, Revision 11, dated August 18, 2004. 

(ix) Airbus Service Bulletin A320–34– 

1170, Revision 12, dated December 2, 2004. 

(x) Airbus Service Bulletin A320–34–1170, 

Revision 13, dated January 18, 2005. 

(xi) Airbus Service Bulletin A320–34– 

1170, Revision 14, dated April 21, 2005. 

(xii) Airbus Service Bulletin A320–34– 

1170, Revision 15, dated July 19, 2005. 

(xiii) Airbus Service Bulletin A320–34– 

1170, Revision 16, dated November 23, 2006. 

(xiv) Airbus Service Bulletin A320–34– 

1170, Revision 17, dated February 14, 2007. 

(xv) Airbus Service Bulletin A320–34– 

1170, Revision 18, dated October 9, 2009. 

(xvi) Airbus Service Bulletin A320–34– 

1170, Revision 19, dated November 9, 2009. 

(xvii) Airbus Service Bulletin A320–34– 

1170, Revision 20, dated December 1, 2010. 

(xviii) Airbus Service Bulletin A320–34– 

1170, Revision 21, dated March 24, 2011. 

(xix) Airbus Service Bulletin A320–34– 

1170, Revision 22, dated July 19, 2011. 

(xx) Airbus Service Bulletin A320–34– 

1170, Revision 23, dated February 3, 2012. 

(xxi) Airbus Service Bulletin A320–34– 

1170, Revision 24, dated April 12, 2012. 

(xxii) Airbus Service Bulletin A320–34– 

1170, Revision 25, dated September 4, 2012. 

(xxiii) Airbus Service Bulletin A320–34– 

1170, Revision 26, dated September 16, 2013. 

(xxiv) Airbus Service Bulletin A320–34– 

1170, Revision 27, dated March 18, 2014. 

(xxv) Airbus Service Bulletin A320–34– 

1170, Revision 28, dated September 1, 2014. 

(xxvi) Airbus Service Bulletin A320–34– 

1170, Revision 29, dated February 16, 2015. 

(2) This paragraph provides credit for the 

replacement of pitot probes on the captain 

and standby sides specified in paragraph 

(h)(1) of this AD, if the replacement was 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–34–1456, 

dated December 2, 2009, which is not 

incorporated by reference in this AD. 

(3) This paragraph provides credit for the 

replacement of pitot probes on the first 

officer side as specified in paragraph (h)(1) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–34–1463, 

dated March 9, 2010, which is not 

incorporated by reference in this AD. 

(j) Parts Installation Limitations 

(1) At the applicable time specified in 

paragraph (j)(1)(i) or (j)(1)(ii) of this AD: No 

person may install on any airplane a Thales 

pitot probe having P/N C16195AA or P/N 

C16195BA. 

(i) For airplanes with a Thales pitot probe 

having P/N C16195AA or P/N C16195BA 

installed: After accomplishing the 

replacement required by paragraph (g) of this 

AD. 

(ii) For airplanes without a Thales pitot 

probe having P/N C16195AA or P/N 

C16195BA installed: As of the effective date 

of this AD. 

(2) As of the effective date of this AD, no 

person may install on any airplane a Thales 

pitot probe having part number P/N 50620– 

10. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (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. 

(l) Related Information 

(1) Refer to EASA Airworthiness Directive 

2015–0205, dated October 9, 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–2015–0250. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

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. 

Issued in Renton, Washington, on 

November 25, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–30821 Filed 12–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7527; Directorate 

Identifier 2015–NM–094–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200, 

–200LR, –300, and –300ER series 

airplanes. This proposed AD was 

prompted by a report indicating that the 

manufacturer discovered locations 

where the control components and 

wiring of the left and right engine fuel 

spar valves do not have adequate 

physical separation to meet the 

redundant system separation 

requirements. This proposed AD would 

require modifying the wiring, and 

installing a new relay bracket and new 

location for the relay on the left and 

right engine fuel spar valves. This 

proposed AD would also require an 

inspection to identify the part number 

of the motor operated valve (MOV) 

actuators for the left and right engine 

fuel spar valves; replacement of 

specified MOV actuators with new MOV 

actuators; certain bonding resistance 

measurements; and applicable 

corrective actions. We are proposing 

this AD to prevent loss of control of 

both the left and right engine fuel spar 

valves during a single event, such as 


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