Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3061 

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): 

Fokker Services B.V.: Docket No. FAA– 

2015–8466; Directorate Identifier 2015– 

NM–045–AD. 

(a) Comments Due Date 

We must receive comments by March 7, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, 

certificated in any category, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by the need for 

more restrictive fuel airworthiness 

limitations. We are issuing this AD to reduce 

the potential of ignition sources inside fuel 

tanks, which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance Program Revision 

(1) Within 12 months after the effective 

date of this AD, revise the maintenance or 

inspection program, as applicable, to 

incorporate the fuel airworthiness limitation 

items (ALIs) and critical design configuration 

control limitations (CDCCLs) specified in 

Fokker Services B.V. Engineering Report SE– 

672, Fokker 70/100 Fuel ALI’s and CDCCL’s, 

Issue 5, released December 11, 2014. 

(2) The initial compliance times and 

repetitive intervals for the actions are at the 

applicable times specified within Fokker 

Services B.V. Engineering Report SE–672, 

Fokker 70/100 Fuel ALI’s and CDCCL’s, Issue 

5, released December 11, 2014. If any 

discrepancy is found, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency; or Fokker B.V. Service’s 

EASA Design Organization Approval (DOA). 

Repair any discrepancy before further flight. 

(h) No Alternative Inspections, Inspection 

Intervals, or CDCCLs 

After accomplishment of the actions 

specified in paragraph (g) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (i)(1) 

of this AD. 

(i) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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 Fokker Services B.V.’s EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(j) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2015–0032, dated February 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– 

2015–8466. 

(2) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.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 January 

5, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00633 Filed 1–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8463; Directorate 

Identifier 2014–NM–226–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–20– 

11, for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 


tkelley on DSK3SPTVN1PROD with PROPOSALS
3062 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

2013–20–11 currently requires 

modifying the passenger emergency 

oxygen container assembly. Since we 

issued AD 2013–20–11, we have 

determined that the unsafe condition 

also affects oxygen containers labeled 

‘‘DAe Systems.’’ This proposed AD 

would expand the affected group of 

oxygen containers to include those 

labeled ‘‘DAe Systems.’’ We are 

proposing this AD to prevent a high 

temperature oxygen generator and mask 

from falling down and possibly 

resulting in an ignition source in the 

passenger compartment, injury to 

passengers, and reduced availability of 

supplemental oxygen. 

DATES: We must receive comments on 

this proposed AD by March 7, 2016. 

ADDRESSES: You may send comments 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 Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus 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. 

For B/E Aerospace service 

information identified in this proposed 

AD, contact Dieter Heins, Customer 

Support Manager, Oxygen & PSU 

Systems, B/E Aerospace Systems, GmbH 

Revalstr. 1, D–23560 Lu ̈ beck; telephone: 

+49 (0)451 4093 2976; fax: +49 (0)451 

4093 4488; email: dieter_heins@

beaerospace-systems.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– 

8463; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

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–2015–8463; Directorate Identifier 

2014–NM–226–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 

On September 17, 2013, we issued AD 

2013–20–11, Amendment 39–17617 (78 

FR 64162, October 28, 2013). AD 2013– 

20–11 requires modifying the passenger 

emergency oxygen container assembly 

on all Model A318, A319, A320, and 

A321 series airplanes. 

Since we issued AD 2013–20–11, 

Amendment 39–17617 (78 FR 64162, 

October 28, 2013), we have determined 

that the unsafe condition also affects 

oxygen containers labeled ‘‘DAe 

Systems.’’ 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2014–0207, 

dated September 16, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition. 

The MCAI states: 

It was determined that oxygen generators, 

installed on a specific batch of Type 1 (22 

min) passenger emergency oxygen container 

assemblies, may become detached by extreme 

pulling of the mask tube at the end of oxygen 

supply. Investigations revealed that such 

detachment can be caused by the increase in 

temperature towards the end of the generator 

operation, which may weaken the plastic 

housing in the attachment area of the bracket. 

This condition, if not corrected, could 

make the rivets slip through the plastic 

housing, causing a ‘hot’ oxygen generator and 

mask to fall down, possibly resulting in 

injury to passengers. 

To address this potential unsafe condition, 

EASA issued AD 2012–0055 (later revised) 

[http://ad.easa.europa.eu/blob/easa_ad_

2012_0055_R1_superseded.pdf/AD_2012- 

0055R1_1] [which corresponds to FAA AD 

2013–20–11, Amendment 39–17617 (78 FR 

64162, October 28, 2013)] to require 

modification of the affected oxygen container 

assemblies. That [EASA] AD also prohibited 

installation of unmodified containers on any 

aeroplane as replacement parts. 

Since that [EASA] AD was issued, it was 

found that the affected containers have not 

only been marked with company name B/E 

Aerospace, as was specified, but also, for a 

brief period, with the former company name 

DAe Systems. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0055R1, which is superseded, and 

expands the affected group of containers to 

include those that have the name ‘‘DAe 

Systems’’ on the identification plate. 

This [EASA] AD also clearly separates the 

serial number (s/n) groups of containers into 

those manufactured by B/E Aerospace and 

those manufactured by DAe Systems, for 

which additional compliance time is 

provided. 

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– 

8463. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. This service 

information describes procedures for 

installation of a reinforcement plate in 

the oxygen container assembly. 

• Airbus Service Bulletin A320–35– 

1049, dated June 15, 2011. 

• Airbus Service Bulletin A320–35– 

1053, dated June 15, 2011. 

• Airbus Service Bulletin A320–35– 

1054, dated June 15, 2011. 

• Airbus Service Bulletin A320–35– 

1055, dated June 15, 2011. 

• Airbus Service Bulletin A320–35– 

1056, dated June 15, 2011. 

• Airbus Service Bulletin A320–35– 

1057, dated June 15, 2011. 

• Airbus Service Bulletin A320–35– 

1058, dated June 15, 2011. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 


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Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3063 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination and Requirements 

of This Proposed AD 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 airplanes of U.S. registry. 

The actions required by AD 2013–20– 

11, Amendment 39–17617 (78 FR 

64162, October 28, 2013), and retained 

in this proposed AD take about 2 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that are required by AD 2013– 

20–11 is $170 per product. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $680, or $170 per product. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 

removing Airworthiness Directive (AD) 

2013–20–11, Amendment 39–17617 (78 

FR 64162, October 28, 2013), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–8463; 

Directorate Identifier 2014–NM–226–AD. 

(a) Comments Due Date 

We must receive comments by March 7, 

2016. 

(b) Affected ADs 

This AD replaces AD 2013–20–11, 

Amendment 39–17617 (78 FR 64162, October 

28, 2013). 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, specified in 

paragraphs (c)(1) through (c)(4) of this AD, 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 35, Oxygen. 

(e) Reason 

This AD was prompted by a determination 

that oxygen generators installed on a certain 

batch of passenger emergency oxygen 

container assemblies might become detached 

by extreme pulling of the mask tube at the 

end of the oxygen supply causing a high 

temperature oxygen generator and mask to 

fall down. This AD was also prompted by a 

determination that the unsafe condition 

affects oxygen containers labeled ‘‘DAe 

Systems.’’ We are issuing this AD to prevent 

a high temperature oxygen generator and 

mask from falling down and possibly 

resulting in an ignition source in the 

passenger compartment, injury to passengers, 

and reduced availability of supplemental 

oxygen. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Oxygen Container Assembly 

Modification, With Service Information 

Referenced in a New Paragraph 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–20–11, 

Amendment 39–17617 (78 FR 64162, October 

28, 2013), with service information 

referenced in a new paragraph. Except as 

specified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD, within 5,000 flight cycles, 

or 7,500 flight hours, or 24 months, 

whichever occurs first, after December 2, 

2013 (the effective date of AD 2013–20–11): 

Modify each type 1 (22 minute) passenger 

emergency oxygen container assembly 

installed on an airplane, having a part 

number (P/N) listed in paragraph (g)(1)(i) of 

this AD and a serial number (S/N) listed in 

paragraph (g)(1)(ii) of this AD, in accordance 

with the Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraphs (k)(1) through (k)(7) 

of this AD. 

(1) An oxygen container that has a part 

number listed in paragraph (g)(1)(i) of this 

AD and a serial number as listed in 

paragraph (g)(1)(ii) of this AD, and that has 

been modified using the instructions of B/E 

Aerospace Service Bulletin 1XC22–0100–35– 

006, is compliant with the modification 

requirement of paragraph (g) of this AD. 

(i) Oxygen container part numbers listed in 

paragraphs (g)(1)(i)(A) through (g)(1)(i)(D) of 

this AD, where xxxxx stands for an 

alphanumerical value. 

(A) 13C22Lxxxxx0100. 

(B) 13C22Rxxxxx0100. 

(C) 14C22Lxxxxx0100. 


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(D) 14C22Rxxxxx0100. 

(ii) Oxygen container serial numbers listed 

in paragraphs (g)(1)(ii)(A) through 

(g)(1)(ii)(H) of this AD. 

(A) ARBC–0182 to ARBC–9999, inclusive. 

(B) ARBD–0000 to ARBD–9999, inclusive. 

(C) ARBE–0000 to ARBE–9999, inclusive. 

(D) BEBF–0000 to BEBF–9999, inclusive. 

(E) BEBH–0000 to BEBH–9999, inclusive. 

(F) BEBK–0000 to BEBK–9999, inclusive. 

(G) BEBL–0000 to BEBL–9999, inclusive. 

(H) BEBM–0000 to BEBM–0454, inclusive. 

(2) Airplanes on which Airbus 

Modification 150704 has not been embodied 

in production are excluded from the 

requirements of paragraph (g) of this AD, 

unless an oxygen container with a part 

number listed in paragraph (g)(1)(i) of this 

AD and a serial number listed in paragraph 

(g)(1)(ii) of this AD is installed. 

(3) Airplanes on which Airbus 

Modification 150704 has been embodied in 

production and that are not listed by model 

and manufacturer serial number in the 

applicable Airbus service information 

specified in paragraphs (k)(1) through (k)(7) 

of this AD; are excluded from the 

requirements of paragraph (g) of this AD, 

unless an oxygen container with a part 

number listed in paragraph (g)(1)(i) of this 

AD and a serial number listed in paragraph 

(g)(1)(ii) of this AD is installed. 

Note 1 to paragraph (g) of this AD: The 

oxygen container assemblies listed in 

paragraph (g)(1)(i) of this AD and paragraph 

(g)(1)(ii) of this AD are B/E Aerospace 

products with the mark ‘‘B/E AEROSPACE’’ 

on the identification plate. 

(h) Retained Parts Installation Limitation, 

With Service Information Referenced in a 

New Paragraph 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–20–11, 

Amendment 39–17617 (78 FR 64162, October 

28, 2013), with service information 

referenced in a new paragraph. As of 

December 2, 2013 (the effective date of AD 

2013–20–11), no person may install, on any 

airplane, an oxygen container with a part 

number listed in paragraph (g)(1)(i) of this 

AD, and serial number listed in paragraph 

(g)(1)(ii) of this AD, unless the oxygen 

container has been modified according to the 

applicable Airbus service information 

specified in paragraphs (k)(1) through (k)(7) 

of this AD. 

(i) New Requirement of This AD: 

Modification of Additional Oxygen 

Containers 

At the applicable times specified in 

paragraphs (i)(1) and (i)(2) of this AD: Modify 

each type 1 (22 minute) passenger emergency 

oxygen container assembly installed on an 

airplane, having a part number and a serial 

number listed in paragraph (j) of this AD, in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraphs (k)(1) 

through (k)(7) of this AD; except as specified 

in paragraph (l) of this AD. 

(1) For units with ‘‘B/E AEROSPACE’’ on 

the identification plate and having a part 

number and a serial number listed in 

paragraph (j)(1) of this AD: Within 5,000 

flight cycles, or 7,500 flight hours, or 24 

months, whichever occurs first after the 

effective date of this AD. 

(2) For units with ‘‘DAe Systems’’ on the 

identification plate and having a part number 

and a serial number listed in paragraph (j)(2) 

of this AD: Within 2,500 flight cycles, or 

3,750 flight hours, or 12 months, whichever 

occurs first after the effective date of this AD. 

(j) New Part Numbers and Serial Numbers 

for the Parts Affected by Paragraph (i) of 

This AD 

Affected parts for the actions required by 

paragraph (i) of this AD are identified in 

paragraphs (j)(1) and (j)(2) of this AD. 

(1) For oxygen containers with ‘‘B/E 

AEROSPACE’’ on the identification plate: 

Units having a part number identified in 

paragraphs (j)(1)(i) through (j)(1)(iv) of this 

AD, where part number ‘‘xxxxx’’ stands for 

any alphanumerical value, and a serial 

number of BEBM–0455 to BEBM–9999, 

inclusive. 

(i) 13C22Lxxxxx0100. 

(ii) 13C22Rxxxxx0100. 

(iii) 14C22Lxxxxx0100. 

(iv) 14C22Rxxxxx0100. 

(2) For oxygen containers with ‘‘DAe 

Systems’’ on the identification plate: Units 

having a part number identified in 

paragraphs (j)(1)(i) through (j)(1)(iv) of this 

AD, where part number ‘‘xxxxx’’ stands for 

any alphanumerical value, and a serial 

number identified in paragraphs (j)(2)(i) 

through (j)(2)(iv) of this AD. 

(i) ARBC–0000 to ARBC–9999 inclusive. 

(ii) ARBD–0000 to ARBD–9999 inclusive. 

(iii) ARBE–0000 to BEBE–9999 inclusive. 

(iv) BEBE–0000 to BEBE–9999 inclusive. 

(k) New Service Information Paragraph for 

the Requirements of Paragraphs (g), (h), (i), 

and (m) of This AD 

Accomplish the requirements specified in 

paragraphs (g), (h), (i), and (m) of this AD in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information identified in paragraphs (k)(1) 

through (k)(7) of this AD. 

(1) Airbus Service Bulletin A320–35–1049, 

dated June 15, 2011. 

(2) Airbus Service Bulletin A320–35–1053, 

dated June 15, 2011. 

(3) Airbus Service Bulletin A320–35–1054, 

dated June 15, 2011. 

(4) Airbus Service Bulletin A320–35–1055, 

dated June 15, 2011. 

(5) Airbus Service Bulletin A320–35–1056, 

dated June 15, 2011. 

(6) Airbus Service Bulletin A320–35–1057, 

dated June 15, 2011. 

(7) Airbus Service Bulletin A320–35–1058, 

dated June 15, 2011. 

(l) New Exceptions to the Requirements of 

Paragraph (i) of This AD 

(1) An oxygen container that has a part 

number and a serial number listed in 

paragraph (j) of this AD, and that has been 

modified as specified in B/E Aerospace 

Service Bulletin 1XC22–0100–35–006, is 

compliant with the modification requirement 

of paragraph (i) of this AD. 

(2) Airplanes on which Airbus 

Modification 150704 has not been embodied 

in production are excluded from the 

requirements of paragraph (i) of this AD, 

unless an oxygen container with a part 

number and a serial number listed in 

paragraph (j) of this AD is installed. 

(3) Airplanes on which Airbus 

Modification 150704 has been embodied in 

production and that are not listed by model 

and manufacturer serial number in the 

Airbus service information specified in 

paragraphs (k)(1) through (k)(7) of this AD, as 

applicable, are excluded from the 

requirements of paragraph (i) of this AD, 

unless an oxygen container with a part and 

a serial number listed in paragraph (j) of this 

AD is installed. 

(4) Airplanes on which the design of the 

passenger oxygen container is not Design A, 

as defined in figure 1 to paragraph (l)(4) of 

this AD, are excluded from the requirements 

of paragraph (i) of this AD for that passenger 

oxygen container. 

Note 2 to paragraph (l)(4) of this AD: For 

‘‘Design A,’’ the placard on the passenger 

oxygen container test button is as described 

in ‘‘Picture A’’ in figure 1 to paragraph (l)(4) 

of this AD. The mask configuration (‘‘ZZ’’ in 

‘‘Picture A’’) is a number, and the test button 

is as shown in ‘‘Picture B.’’ 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3065 

(m) New Requirement of This AD: Parts 

Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, an 

oxygen container with a part number and a 

serial number listed in paragraph (j) of this 

AD, unless the oxygen container has been 

modified in accordance with the 

Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraphs (k)(1) through (k)(7) 

of this AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: (425) 227–1405; fax: (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

2013–20–11, Amendment 39–17617 (78 FR 

64162, October 28, 2013), are approved as 

AMOCs for the corresponding provisions of 

paragraphs (g) and (h) of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the 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. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 


tkelley on DSK3SPTVN1PROD with PROPOSALSEP20JA16.001</GPH>
3066 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

2014–0207, dated September 16, 2014, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2015–8463. 

(2) For Airbus 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.airwortheas@airbus.com; Internet http://

www.airbus.com. 

(3) For B/E Aerospace service information 

identified in this AD, contact Dieter Heins, 

Customer Support Manager, Oxygen & PSU 

Systems, B/E Aerospace Systems, GmbH 

Revalstr. 1, D–23560 Lu ̈ beck; telephone: +49 

(0)451 4093 2976; fax: +49 (0)451 4093 4488; 

email: dieter_heins@beaerospacesystems.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. 

Issued in Renton, Washington, on January 

5, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00697 Filed 1–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8468; Directorate 

Identifier 2014–NM–208–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2007–21– 

14 R1, for all Airbus Model A310 series 

airplanes. AD 2007–21–14 R1 currently 

requires revising the Airworthiness 

Limitations Section of the Instructions 

for Continued Airworthiness to 

incorporate new limitations for fuel tank 

systems. Since we issued AD 2007–21– 

14R1, we have determined that more 

restrictive maintenance requirements 

and/or airworthiness limitations are 

necessary. This proposed AD would 

require revising the maintenance 

program or inspection program to 

incorporate revised fuel maintenance 

and inspection tasks. We are proposing 

this AD to prevent the potential of 

ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors caused by latent failures, 

alterations, repairs, or maintenance 

actions, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by March 7, 2016. 

ADDRESSES: You may send comments 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 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 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.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– 

8468; 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 Operations 

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: 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. 

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–2015–8468; Directorate Identifier 

2014–NM–208–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 

On October 19, 2009, we issued AD 

2007–21–14 R1, Amendment 39–16061 

(74 FR 55123, October 27, 2009). AD 

2007–21–14 R1 requires actions 

intended to address an unsafe condition 

on all Airbus Model A310 series 

airplanes. AD 2007–21–14 R1 revised 

AD 2007–21–14, Amendment 39–15232, 

(72 FR 58499, October 16, 2007). 

Since we issued AD 2007–21–14R1, 

Amendment 39–16061 (74 FR 55123, 

October 27, 2009), we have determined 

more restrictive maintenance 

requirements and airworthiness 

limitations are necessary. 

The European Aviation Safety 

Agency, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0193, dated October 15, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition all Airbus Model 

A310 series airplanes. The MCAI states: 

Prompted by an accident . . ., the Federal 

Aviation Administration (FAA) published 

Special Federal Aviation Regulation (SFAR) 

88, [http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgFAR.nsf/0/EEFB3F94451

DC06286256C93004F5E07?OpenDocument&

Highlight=sfar 88], and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. In response to these 

regulations, Airbus conducted a design 

review to develop Fuel Airworthiness 

Limitations (FAL) for Airbus on A310 

aeroplanes. 

The FAL were specified in Airbus A310 

FAL document ref. 95A.1930/05 at issue 02 

and in the A310 Airworthiness Limitations 

Section (ALS) variation to FAL document 

issue 02, ref. 0BVLG110006/C0S issue 01, for 

A310 aeroplanes. 

EASA issued [EASA] AD 2006–0202 

(http://ad.easa.europa.eu/ad/2006-0202) to 


tkelley on DSK3SPTVN1PROD with PROPOSALS