This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

74032 

Vol. 79, No. 240 

Monday, December 15, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0923; Directorate 

Identifier 2014–NM–176–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

the Boeing Company Model 737–700, 

–800, and –900ER series airplanes. This 

proposed AD was prompted by reports 

of troughs in the skin along the chemmill pocket edges of certain fuselage 

crown skin panel assemblies. This 

proposed AD would require repetitive 

inspections to detect cracking in the 

crown skin panel assembly. This 

proposed AD would also provide 

optional terminating action for the 

repetitive inspections. We are proposing 

this AD to detect and correct cracking 

from troughs in the chem-mill pocket 

edges, which could lead to rapid 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 29, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 

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– 

0923; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Haytham Alaidy, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6573; 

fax: 425–917–6590; email: 

haytham.alaidy@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0923; Directorate Identifier 2014– 

NM–176–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 because of 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 

Some section 43, 44, and 46 fuselage 

crown skin panel assemblies may 

contain troughs in the skin along the 

chem-mill pocket edges. The troughs are 

caused during production rework by the 

automated laser trace process for cutting 

maskant. The laser disrupted the bond 

surface and allowed the chemical 

milling solution to penetrate through, 

causing a 0.003- to 0.007-inch-deep 

trough in the skin. The discrepancy was 

discovered when an operator reported 

finding troughs around the perimeter of 

all chem-mill pockets on one crown 

skin panel assembly. If skin panel 

assemblies with troughs are not 

replaced, cracking can occur at the 

trough locations, which, if not repaired, 

could result in rapid decompression of 

the airplane. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 737–53– 

1334, dated August 4, 2014. For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0923. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 


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actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

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 actions specified in the 

service information described 

previously include steps that are labeled 

as RC (required for compliance) because 

these steps have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

As noted in the specified service 

information, steps labeled as RC must be 

done to comply with the proposed AD. 

However, steps that are not labeled as 

RC are recommended. Those steps that 

are not labeled as RC may be deviated 

from, done as part of other actions, or 

done using accepted methods different 

from those identified in the service 

information without obtaining approval 

of an alternative method of compliance 

(AMOC), provided the steps labeled as 

RC can be done and the airplane can be 

put back in a serviceable condition. Any 

substitutions or changes to steps labeled 

as RC will require approval of an 

AMOC. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Special Attention Service 

Bulletin 737–53–1334, dated August 4, 

2014, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1 airplane of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS: REQUIRED ACTIONS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Medium frequency eddy current Inspections.270 work-hours × $85 per hour = 

$22,950 per inspection cycle.

$0 $22,950 per inspection 

cycle.

22,950 per inspection 

cycle. 

ESTIMATED COSTS: OPTIONAL ACTIONS

Action Labor cost Parts cost Cost per 

product 

Terminating action (inspection for troughs) ................... 218 work-hours × $85 per hour = $18,530 ................... Unknown ..... $18,530 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
74034 Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules 

(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): 

The Boeing Company: Docket No. FAA– 

2014–0923; Directorate Identifier 2014– 

NM–176–AD. 

(a) Comments Due Date 

We must receive comments by January 29, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–700, –800, and –900ER 

series airplanes, certificated in any category, 

as identified in Boeing Special Attention 

Service Bulletin 737–53–1334, dated August 

4, 2014. 

(2) For airplanes identified as Group 7 in 

Boeing Special Attention Service Bulletin 

737–53–1334, dated August 4, 2014, no work 

is required by this AD. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

troughs in the skin along the chem-mill 

pocket edges of certain fuselage crown skin 

panel assemblies. We are issuing this AD to 

detect and correct troughs in the chem-mill 

pocket edges, which could lead to cracking 

at the trough locations, and consequent rapid 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

At the applicable time specified in 

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

Special Attention Service Bulletin 737–53– 

1334, dated August 4, 2014, except as 

required by paragraph (h) of this AD: Do 

external medium frequency eddy current 

inspections to detect cracking in higher- and 

lower-stress locations of the crown skin 

panel assembly, in accordance with Boeing 

Special Attention Service Bulletin 737–53– 

1334, dated August 4, 2014. Repeat the 

inspections thereafter at the applicable time 

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

Boeing Special Attention Service Bulletin 

737–53–1334, dated August 4, 2014. 

Accomplishment of the actions specified in 

paragraph (j) of this AD terminates the 

requirements of paragraph (g) of this AD. 

(h) Exception to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 737–53–1334, dated August 4, 2014, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(i) Crack Repair 

If any crack is found during any inspection 

required by paragraph (g) of this AD, repair 

before further flight using a method approved 

in accordance with the procedures specified 

in paragraph (j) of this AD. 

(j) Optional Terminating Action 

The actions specified in paragraph (g) of 

this AD may be terminated by 

accomplishment of a part mark inspection of 

the crown skin panel assembly in accordance 

with Part 5 of Work Package 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1334, dated August 4, 2014, and the 

applicable actions specified in paragraphs 

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

(1) If ‘‘Condition 5,’’ as defined in Boeing 

Special Attention Service Bulletin 737–53– 

1334, dated August 4, 2014, is found, 

corrective actions must be done before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(2) If ‘‘Condition 6’’, as defined in Boeing 

Special Attention Service Bulletin 737–53– 

1334, dated August 4, 2014, is found, the 

actions specified in paragraphs (j)(2)(i) and 

(j)(2)(ii) of this AD must be done at the 

applicable specified time. 

(i) A report of the findings, including the 

inspection results (discrepant part number of 

panel assembly), the airplane serial number, 

and the manufacturing order code as defined 

in Appendix C of Boeing Special Attention 

Service Bulletin 737–53–1334, dated August 

4, 2014, must be submitted to https://

www.myboeingfleet.com before further flight. 

(ii) An internal detailed inspection for 

troughs must be done before further flight in 

accordance with Boeing Special Attention 

Service Bulletin 737–53–1334, dated August 

4, 2014, and any skin panel assembly with 

a trough must be replaced before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(k) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(l) 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 (k)(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. 

(4) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 


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Federal Register / Vol. 79, No. 240 / Monday, December 15, 2014 / Proposed Rules 74035 

changes to steps labeled as RC require 

approval of an AMOC. 

(m) Related Information 

(1) For more information about this AD, 

contact Haytham Alaidy, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6573; fax: 425– 

917–6590; email: Haytham.alaidy@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 

December 3, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–29234 Filed 12–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0922; Directorate 

Identifier 2014–NM–156–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 and A320 series 

airplanes. This proposed AD was 

prompted by a report that fatigue 

cracking could appear at certain fastener 

locations in the longeron area below the 

emergency exit cut-outs. This proposed 

AD is intended to complete certain 

mandated programs intended to support 

the airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This proposed 

AD would require modification of eight 

fastener locations in the longeron area 

below the emergency exit cut-outs on 

the left-hand (LH) and right-hand (RH) 

sides. We are proposing this AD to 

detect and correct cracking at certain 

fastener locations in the longeron area 

below the emergency exit cut-outs, 

which could lead to failure of the 

fasteners and reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 29, 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 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– 

0922; 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–2014–0922; Directorate Identifier 

2014–NM–156–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 2014–0176, 

dated July 25, 2014 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on certain Model A319 and Model A320 

series airplanes. The MCAI states: 

During the A320 fatigue test campaign for 

Extended Service Goal (ESG), it was 

determined that fatigue damage could appear 

at certain fastener locations on the longeron 

[area] below the emergency exit cut-outs, on 

the left-hand (LH) and right-hand (RH) sides 

of the fuselage. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

Airbus developed a modification, which has 

been published through Airbus Service 

Bulletin (SB) A320–53–1265 for in-service 

application to allow aeroplanes to operate up 

to the new ESG limit. 

For the reasons described above, this 

[EASA] AD requires modification (cold 

working) of 8 fastener locations in the 

Longeron area (Stringer 20A) below the 

emergency exit cut-outs on the LH and RH 

sides. 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120-104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish an LOV of the engineering data 

that support the structural maintenance 

program under 14 CFR 26.21. This 

proposed AD is the result of an 

assessment of the previously established 

programs by DAH during the process of 

establishing the LOV for Airbus Model 

A319 and A320 series airplanes. The 


tkelley on DSK3SPTVN1PROD with PROPOSALS