Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Proposed Rules 59157 

applicable time specified in paragraphs 

(k)(1), (k)(2), and (k)(3) of this AD. 

(1) For airplanes having accumulated less 

than 40,000 total flight hours since first flight 

of the airplane as of the effective date of this 

AD: Before the accumulation of 40,001 total 

flight hours. 

(2) For airplanes having accumulated 

40,000 total flight hours or more since first 

flight of the airplane as of the effective date 

of this AD, and on which Aging Systems 

Maintenance (ASM) Task 213115–04–1, or 

Maintenance Review Board Report (MRBR) 

Tasks 21.31.00/06 and 21.31.00/08, have 

been accomplished: Before the accumulation 

of 14,000 flight hours after the most recent 

accomplishment of ASM Tasks 213115–04–1, 

or MRBR Tasks 21.31.00/06 and 21.31.00/08, 

whichever occurs later. 

(3) For airplanes having accumulated 

40,000 total flight hours or more since first 

flight of the airplane as of the effective date 

of this AD, and on which ASM Task 213115– 

04–1, or MRBR Tasks 21.31.00/06 and 

21.31.00/08, have not been accomplished: 

Within 3 months after the effective date of 

this AD. 

(l) 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. 

(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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0072, dated 

March 20, 2013, 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– 

2014–0655. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 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 

September 20, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23375 Filed 9–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0653; Directorate 

Identifier 2014–NM–057–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. 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 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This proposed AD was 

prompted by reports of cracking on the 

skin panels and skin splice joints and 

angles at certain stringers at various 

locations between certain fuselage 

stations. This proposed AD would 

require revising the maintenance or 

inspection program, as applicable, to 

incorporate new or revised maintenance 

requirements and airworthiness 

limitations, and incorporating structural 

repairs and modifications to preclude 

widespread fatigue damage (WFD). We 

are proposing this AD to detect and 

correct WFD, which could adversely 

affect the structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 17, 

2014. 

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 service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.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–2014– 

0653; 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: Aziz 

Ahmed, Aerospace Engineer, Airframe 

and Mechanical Systems Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone: 516–228–7329; fax: 

516–794–5531; email: aziz.ahmed@

faa.gov. 

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–2014–0653; Directorate Identifier 

2014–NM–057–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://


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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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as widespread fatigue 

damage (WFD). As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–07, 

dated January 31, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B19 (Regional Jet Series 100 & 

440) airplanes. The MCAI states: 

Complete aeroplane fatigue testing on a 

CL–600–2B19 aeroplane by the aeroplane 

manufacturer revealed the onset of 

simultaneous cracking on the skin panels and 

skin splice joints and angles at stringers 

number 6 and 20 at various locations 

between fuselage stations (FS) 409.00 to FS 

589.00. 

Cracks at multiple locations may reduce 

the residual strength of the joint below the 

required levels if the cracks are not 

detectable under the existing maintenance 

program established at the time of 

certification. This multiple site damage 

(MSD) behavior, if not corrected, could lead 

to widespread fatigue damage (WFD) and 

adversely affect the structural integrity of the 

aeroplane and/or could result in rapid 

decompression of the aeroplane. 

A Temporary Revision (TR) has been made 

to the Maintenance Requirements Manual 

(MRM) to revise existing Airworthiness 

Limitations (AWL) tasks and introduce new 

inspection tasks for the detection of MSD. 

The aeroplane manufacturer is also 

developing a structural modification to 

preclude WFD from occurring in the fleet at 

these locations. 

This [Canadian] AD mandates the 

incorporation of the new and revised AWL 

tasks [into the maintenance program], and a 

structural modification to preclude WFD. 

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–2014– 

0653. 

Relevant Service Information 

Bombardier has issued the following 

AWL tasks to Part 2 Airworthiness 

Requirements, Revision 9, dated June 

10, 2013, of Appendix B, Airworthiness 

Limitations, of Bombardier CL–600– 

2B19, Maintenance Requirements 

Manual, CSP A–053: 

• AWL Task 53–41–109, 

‘‘Longitudinal Str. 6 splice at STR 6 and 

20’’; 

• AWL Task 53–41–110, 

‘‘Longitudinal Str. 6 splice butt strap at 

Str. 6, FS409.0 to FS617.0’’; 

• AWL Task 53–41–204, ‘‘Frame 

splice angles at STR 6 and 20’’; and 

• AWL Task 53–41–205, 

‘‘Longitudinal skin splice at STR 6 and 

20’’. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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 the same 

type design. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections). Compliance 

with these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by this proposed 

AD, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (j) of this proposed AD. The 

request should include a description of 

changes to the required actions that will 

ensure the continued damage tolerance 

of the affected structure. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

The TCCA AD specifies that, if there 

are findings from the airworthiness 

limitations section (ALS) inspection 

tasks, then corrective action must be 

accomplished in accordance with 

Bombardier. But this proposed AD does 

not include that requirement because 

operators of U.S.-registered airplanes are 

required by general airworthiness and 

operational regulations to use FAAacceptable methods when performing 

maintenance. We consider those 

methods to be adequate to address any 


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corrective action necessitated by the 

findings of ALS inspections required by 

this proposed AD. 

Costs of Compliance 

We estimate that This proposed AD 

affects 526 airplanes of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. We have received no 

definitive data that would enable us to 

provide cost estimates for the repairs 

and modifications specified in 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 

$44,710, or $85 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): 

Bombardier, Inc.: Docket No. FAA–2014– 

0653; Directorate Identifier 2014–NM–057– 

AD. 

(a) Comments Due Date 

We must receive comments by November 

17, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, certificated in any category, serial 

numbers 7003 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic Inspections. 

(e) Reason 

This AD was prompted by reports of 

cracking on the skin panels and skin splice 

joints and angles at certain stringers at 

various locations between certain fuselage 

stations. We are issuing this AD to detect and 

correct widespread fatigue damage, which 

could adversely affect the structural integrity 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 60 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating the airworthiness limitations 

(AWL) tasks specified in paragraphs (g)(1) 

through (g)(4) of this AD, of Part 2 

Airworthiness Requirements, Revision 9, 

dated June 10, 2013, of Appendix B, 

Airworthiness Limitations, of Bombardier 

CL–600–2B19, Maintenance Requirements 

Manual, CSP A–053. The initial compliance 

times for the tasks start from the applicable 

threshold times specified in Part 2 

Airworthiness Requirements, Revision 9, 

dated June 10, 2013, of Appendix B, 

Airworthiness Limitations, of Bombardier 

CL–600–2B19, Maintenance Requirements 

Manual, CSP A–053; except that, for 

airplanes that have accumulated more than 

38,000 total flight cycles as of the effective 

date of this AD, the initial compliance time 

for the AWL tasks is before the accumulation 

of 2,000 flight cycles after the effective date 

of this AD. 

(1) AWL Task 53–41–109, ‘‘Longitudinal 

Str. 6 splice at STR 6 and 20.’’ 

(2) AWL Task 53–41–110, ‘‘Longitudinal 

Str. 6 splice butt strap at Str. 6, FS409.0 to 

FS617.0.’’ 

(3) AWL Task 53–41–204, ‘‘Frame splice 

angles at STR 6 and 20.’’ 

(4) AWL Task 53–41–205, ‘‘Longitudinal 

skin splice at STR 6 and 20.’’ 

(h) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

(i) Repairs and Modifications 

Before the accumulation of 60,000 total 

flight cycles: Install repairs and 

modifications to preclude widespread fatigue 

damage at locations specified in paragraphs 

(g)(1) through (g)(4) of this AD, using a 

method approved by the Manager, New York 

ACO, ANE–170, FAA; or Transport Canada 

Civil Aviation (TCCA); or Bombardier, Inc.’s 

TCCA Design Approval Organization (DAO). 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 


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the approval must include the DAOauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–07, dated 

January 31, 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–2014–0653. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http:// 

www.bombardier.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 

September 20, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23376 Filed 9–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0652; Directorate 

Identifier 2014–NM–076–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 A319 series airplanes; 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model 

A321 series airplanes. This proposed 

AD was prompted by reports of cracks 

that could be initiated at the waste 

water service panel area and the potable 

water service panel area. This proposed 

AD would require modification of the 

potable water service panel and waste 

water service panel, including doing 

applicable related investigative and 

corrective actions. We are proposing 

this AD to prevent any cracking at the 

waste water service panel area and the 

potable water service panel area, which 

could affect the structural integrity of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by November 17, 

2014. 

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 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–2014– 

0652; 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–2014–0652; Directorate Identifier 

2014–NM–076–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 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0081, 

dated March 31, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A319; Model 

A320–211, –212, –214, –231, –232, and 

–233; and Model A321 series airplanes. 

The MCAI states: 

During the full scale fatigue test on A320– 

200, it has been noticed that, due to fatigue, 

cracks could be initiated at the waste water 

service panel area and the potable water 

service panel area. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

Prompted by these findings, ALS 

[airworthiness limitations section] Part 2 

tasks have been introduced for the affected 

A320 family aeroplanes. Since those actions 

were taken, Airbus developed production 

mod 160055 and mod 160056 to embody 

reinforcements (cold working on certain rivet 

rows) of the potable water and waste water 

service panels, and published associated 

Airbus Service Bulletin (SB) A320–53–1272 

(retrofit mod 153074) and SB A320–53–1267 

(retrofit mod 153073) for in-service 

embodiment. 

Following complementary Design Office 

studies, it appears that the Sharklet 

installations on certain aeroplanes have a 

significant impact on the aeroplane structure 

(particularly, A319 and A320 post-mod 

160001, and A321 post-mod 160021), leading 

to different compliance times, depending on 

aeroplane configuration. 

For the reasons described above, this 

[EASA] AD requires reinforcement of the 

potable water and waste water service panels. 

Accomplishment of these modifications 

cancels the need for the related ALS Part 2 

Tasks. 

The modification includes doing 

applicable related investigative and 

corrective actions. Related investigative 


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