63134 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 

(g) Wire Separation Measurement, Related 

Investigative Actions, and Corrective 

Actions 

Within 24 months after the effective date 

of this AD: Measure the separation between 

the electro-mechanical actuator wire 

W801182 of the left wing, spoiler 4, and the 

support bracket of the flap variable camber 

trim unit, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

B787–81205–SB270024–00, Issue 001, dated 

September 24, 2014. Do all applicable related 

investigative and corrective actions before 

further flight. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (i)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Related Information 

(1) For more information about this AD, 

contact Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6479; fax: 425–917–6590; email: 

sean.schauer@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 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. 

Issued in Renton, Washington, on October 

6, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26221 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3990; Directorate 

Identifier 2014–NM–255–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A320–214, –232, and 

–233 airplanes; and Airbus Model 

A321–211 and –231 airplanes. This 

proposed AD was prompted by reports 

of incorrect installation of jiffy joint 

connectors on cables connected to 

certain passenger service units (PSU), 

which could cause the passenger oxygen 

container to malfunction if the 

connector becomes disengaged during 

flight due to vibration. This proposed 

AD would require identification of the 

affected PSUs, and depending on 

findings, doing applicable related 

investigative and corrective actions. We 

are proposing this AD to prevent failure 

of the door of the passenger oxygen 

container to open in the event of 

airplane decompression, resulting in 

lack of oxygen supply and consequent 

injury to occupants. 

DATES: We must receive comments on 

this proposed AD by December 3, 2015. 

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 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 Airbus Operations GMBH service 

information identified in this proposed 

AD, contact Airbus Operations GMBH, 

Cabin Electronics, Lueneburger Schanze 

30, 21614 Buxtehude, Germany; 

telephone +49 40 7437 46 32; telefax 

+49 40 7437 16 80; email 

ruediger.jansen@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– 

3990; 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–2015–3990; Directorate Identifier 

2014–NM–255–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63135 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0256, dated November 

26, 2014, (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A320–214, –232, and –233 

airplanes; and Airbus Model A321–211 

and –231 airplanes. The MCAI states: 

A quality issue was reported regarding 

incorrect installation of jiffy joint connectors 

on cables connected to certain Passenger 

Service Units (PSU), which may lead to a 

malfunction of the passenger oxygen 

container in case of connector disengagement 

during flight due to vibrations. All the 

aeroplanes that had a potentially affected 

PSU installed were identified. Most of those 

aeroplanes were corrected during a specific 

quality inspection on the final assembly line 

prior to customer delivery. Unfortunately, a 

limited number of aeroplanes were delivered 

before the quality inspection was 

implemented. 

This condition, if not detected and 

corrected, could lead to failure of the door of 

the passenger oxygen container and open in 

case of aeroplane decompression, possibly 

resulting in lack of oxygen supply and 

consequent injury to occupants. 

For the reasons described above, this 

[EASA] AD requires identification of the 

affected PSU and, depending on the findings, 

* * * related investigative and corrective 

actions. 

Related investigative actions include a 

detailed inspection to determine if the 

jiffy joint connector works properly. 

Corrective actions include rework or 

replacement of the jiffy joint connectors. 

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– 

3990. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A320–25– 

1B20, dated October 9, 2014. This 

service information describes 

procedures for inspecting for affected 

PSU part numbers and serial numbers, 

and depending on findings, doing 

applicable related investigative and 

corrective actions. Related investigative 

actions include a detailed inspection to 

determine if the jiffy joint connector 

works properly. Corrective actions 

include rework or replacement of the 

jiffy joint connectors. 

• Airbus Operations GmbH Vendor 

Service Bulletin Z315H–25–004, dated 

September 26, 2014. This service 

information describes procedures for 

inspecting for the connection of the jiffy 

joint connectors, and depending on 

findings, doing rework or replacement 

of the jiffy joint connectors. 

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 NPRM. 

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. 

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 

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 A320–25–1B20, dated 

October 9, 2014, 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 a serviceable 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 7 airplanes of U.S. registry. 

We also estimate that it would take 

about 5 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost $0 per product. Based 

on these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $2,975, or $425 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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
63136 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 

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–2015–3990; 

Directorate Identifier 2014–NM–255–AD. 

(a) Comments Due Date 

We must receive comments by December 3, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

214, –232, and –233 airplanes; and Airbus 

Model A321–211 and –231 airplanes, 

certificated in any category, having 

manufacturer serial numbers (MSNs) 5583, 

5598, 5602, 5604, 5608, 5610, 5613 through 

5622 inclusive, 5624 through 5627 inclusive, 

5629 through 5632 inclusive, 5634 through 

5636 inclusive, 5638, 5640 through 5644 

inclusive, 5646 through 5649 inclusive, 5651 

through 5653 inclusive, 5655, 5657 through 

5661 inclusive, 5663, 5665, 5667, 5670, 5672, 

5673, and 5675. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of 

incorrect installation of jiffy joint connectors 

on cables connected to certain passenger 

service units (PSU), which could cause the 

passenger oxygen container to malfunction if 

the connector becomes disengaged during 

flight due to vibration. We are issuing this 

AD to prevent failure of the door of the 

passenger oxygen container to open in the 

event of airplane decompression, resulting in 

lack of oxygen supply and consequent injury 

to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Related Investigative and 

Corrective Actions 

Within 7,500 flight hours or 26 months 

after the effective date of this AD, whichever 

occurs first, do an inspection to identify the 

part number and serial number of each PSU 

and if an affected part number or serial 

number is found, do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

25–1B20, dated October 9, 2014. Do all 

applicable related investigative and 

corrective actions within 7,500 flight hours 

or 26 months after the effective date of this 

AD, whichever occurs first. An affected PSU 

part number or serial number is one listed in 

Appendix 1 of Airbus Operations GmbH 

Vendor Service Bulletin Z315H–25–004, 

dated September 26, 2014. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number and 

serial number of the PSU can be conclusively 

determined from that review. 

(h) Clarification of Vendor Service 

Information 

Appendix 1 of Airbus Operations GmbH 

Vendor Service Bulletin Z315H–25–004, 

dated September 26, 2014, identifies 

Attachment 1 as the list of affected PSU part 

numbers and serial numbers. Also, the ‘‘List 

of Attachments’’ in Appendix 1, specifies 

Attachment 1 as Table 4, however 

‘‘Attachment 1’’ and ‘‘Table 4’’ do not appear 

on any of the pages of the list of affected PSU 

part numbers and serial numbers, nor does a 

date. Furthermore, the pagination of the list 

of affected PSU part numbers and serial 

numbers is independent of the pagination of 

Airbus Operations GmbH Vendor Service 

Bulletin Z315H–25–004, dated September 26, 

2014. 

(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: 

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 

a serviceable condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0256, dated 

November 26, 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–2015–3990. 

(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.airworth-eas@

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

For Airbus Operations GMBH service 

information identified in this AD, contact 

Airbus Operations GMBH, Cabin Electronics, 

Lueneburger Schanze 30, 21614 Buxtehude, 

Germany; telephone +49 40 7437 46 32; 

telefax +49 40 7437 16 80; email 

ruediger.jansen@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 October 

6, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26223 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3989; Directorate 

Identifier 2014–NM–250–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


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