26492 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 

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, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–32, dated 

September 8, 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–2015–0929. 

(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 April 13, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10947 Filed 5–7–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1275; Directorate 

Identifier 2014–NM–070–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) 2004–14– 

09, for certain Airbus Model A320–211, 

–212, and –231 airplanes. AD 2004–14– 

09 currently requires repetitive 

inspections for fatigue cracking of the 

lower surface panel on the wing center 

box, and repair if necessary; and 

modification of the lower surface panel 

on the wing center box, which 

constitutes terminating action for the 

repetitive inspections. Since we issued 

AD 2004–14–09, we have determined 

that, based on the average flight 

duration, the average weight of fuel at 

landing is higher than that defined for 

the analysis of the fatigue-related tasks; 

and that shot peening might have been 

improperly done on the chromic acid 

anodizing (CAA) protection, which 

would adversely affect fatigue crack 

protection. This proposed AD would 

reduce the compliance times for the 

repetitive inspections, and would 

require a repair for certain airplanes. We 

are proposing this AD to detect and 

correct fatigue cracking of the lower 

surface panel on the wing center box, 

which could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 2015. 

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, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

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

account.airworth-eas@airbus.com; 

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

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1275; 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–2015–1275; Directorate Identifier 

2014–NM–070–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 June 29, 2004, we issued AD 

2004–14–09, Amendment 39–13718 (69 

FR 41398, July 9, 2004). AD 2004–14– 

09 requires actions intended to address 

an unsafe condition on the products 

listed above. AD 2004–14–09 

superseded AD 98–22–05, Amendment 

39–10851 (63 FR 56542, October 22, 

1998). 

Since we issued AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, 

July 9, 2004), we have determined that, 

based on the average flight duration, the 

average weight of fuel at landing is 

higher than that defined for the analysis 

of the fatigue-related tasks; and that shot 

peening might have been improperly 

done on the CAA protection, which 

would adversely affect fatigue crack 

protection. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0065, dated March 14, 


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2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Model 

A320–211, –212, and –231 airplanes. 

The MCAI states: 

During center fuselage certification full 

scale test, damage was found in the center 

wing box (CWB) lower surface panel. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the CWB. 

To prevent such damage, Airbus developed 

mod 22418 which consists in shot-peening of 

the lower panel in the related area. Mod 

22418 has been embodied in production from 

aeroplane [manufacturer serial number] 

(MSN) 0359. For unmodified in-service 

aeroplanes, Airbus issued Service Bulletin 

(SB) A320–57–1082 to introduce repetitive 

High Frequency Eddy Current (HFEC) 

inspections on the external face of the center 

wing box lower panel between Frame (FR) 41 

and FR42 to detect damage. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD 2002–342 [http://

ad.easa.europa.eu/blob/20023420tb_

superseded.pdf/AD_F-2002-342_1] to require 

these inspections and, depending on 

findings, applicable corrective action(s). 

Airbus also issued SB A320–57–1043 as an 

optional terminating action for the repetitive 

inspections required by DGAC France AD 

2002–342. 

Since that [DGAC] AD was issued, the 

results of a survey, carried out on the A320 

fleet, highlighted some differences between 

the mission parameters, mainly on the weight 

of fuel at landing and on the average flight 

duration, which are higher than those 

defined for the analysis of the fatigue related 

tasks. 

These findings have led to an adjustment 

of the A320 reference fatigue mission. 

Consequently, the threshold and intervals of 

these repetitive inspections have been 

revised and a new threshold figure expressed 

in flight hours (FH) has been established. 

In addition, it has been identified that, on 

aeroplanes that have been modified in 

accordance with Airbus SB A320–57–1043 

(Airbus mod 22418) at Revision 05 or an 

earlier Revision, the shot peening may have 

been improperly done on the Chromic Acid 

Anodizing (CAA) protection, which has no 

fatigue benefit effect. Therefore, the 

inspections per Airbus SB A320–57–1082 are 

required again on these aeroplanes. 

Consequently, new shot-peening 

procedures with proper CAA protection 

removal instructions have been developed 

and their embodiment through Airbus SB 

A320–57–1043 Revision 06 cancels the 

repetitive inspections per Airbus SB A320– 

57–1082, as required by DGAC France AD 

2002–342. 

For the reasons described above, this new 

[EASA] AD retains the requirements of DGAC 

France AD 2002–342, which is superseded, 

but requires these actions to be accomplished 

within reduced thresholds and intervals. In 

addition, the optional terminating action 

provision (SB A320–57–1043) is amended by 

including reference to the SB at Revision 06. 

The optional terminating action 

described in Airbus Service Bulletin 

A320–57–1043, Revision 06, dated 

December 5, 2013, is accomplishing 

shot peening in the radius of the milling 

step between stiffeners 13 and 14 near 

the fuel pump aperture. 

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– 

1275. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–57–1043, Revision 06, dated 

December 5, 2013. This service bulletin 

describes procedures for shot peening in 

the radius of the milling step between 

stiffeners 13 and 14 near the fuel pump 

aperture. 

Airbus has also issued Service 

Bulletin A320–57–1082, Revision 04, 

dated December 5, 2013. This service 

bulletin describes procedures for 

inspections for cracking of the lower 

surface panel on the wing center box. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 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 the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 46 airplanes of U.S. registry. 

The actions that are required by AD 

2004–14–09, Amendment 39–13718 (69 

FR 41398, July 9, 2004), and retained in 

this proposed AD take about 25 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that were required by AD 2004– 

14–09 is $2,125 per product. 

The new requirements of this 

proposed AD would add no additional 

economic burden. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

aircraft that might need these actions. 

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, 


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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) 

2004–14–09, Amendment 39–13718 (69 

FR 41398, July 9, 2004), and adding the 

following new AD: 

Airbus: Docket No. FAA–2014–1275; 

Directorate Identifier 2014–NM–070–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2015. 

(b) Affected ADs 

This AD replaces AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004). 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, and –231 airplanes, certificated in 

any category, all manufacturer serial 

numbers, except those on which Airbus 

Modification 22418 has been embodied in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that, based on the average flight duration, the 

average weight of fuel at landing is higher 

than that defined for the analysis of the 

fatigue-related tasks; and that shot peening 

might have been improperly done on the 

chromic acid anodizing (CAA) protection, 

which would adversely affect fatigue crack 

protection. We are issuing this AD to detect 

and correct fatigue cracking of the lower 

surface panel on the wing center box (WCB), 

which could result in reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections, With No 

Changes 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. Except as provided 

by paragraph (k) of this AD: Prior to the 

accumulation of 20,000 total flight cycles, or 

within 60 days after November 27, 1998 (the 

effective date of AD 98–22–05, Amendment 

39–10851 (63 FR 56542, October 22, 1998)), 

whichever occurs later, perform a high 

frequency eddy current (HFEC) inspection to 

detect fatigue cracking of the lower surface 

panel on the WCB, in accordance with 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997; or 

Revision 03, dated April 30, 2002. Repeat the 

HFEC inspection thereafter at intervals not to 

exceed 7,500 flight cycles until the actions 

required by paragraph (i) of this AD are 

accomplished. 

(h) Retained Repair, With No Changes 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. Except as provided 

by paragraph (j) of this AD, if any cracking 

is detected during any inspection required by 

paragraph (g) of this AD: Prior to further 

flight, repair in accordance with Airbus 

Service Bulletin A320–57–1082, Revision 01, 

dated December 10, 1997; or Revision 03, 

dated April 30, 2002. Accomplishment of the 

repair constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD for the repaired area only. 

(i) Retained Inspection/Modification/Repair, 

With Terminating Action 

This paragraph restates the requirements of 

paragraph (c) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with terminating action provided. 

Prior to the accumulation of 25,000 total 

flight cycles, or within 60 days after 

November 27, 1998 (the effective date of AD 

98–22–05, Amendment 39–10851 (63 FR 

56542, October 22, 1998)), whichever occurs 

later: Perform an HFEC inspection to detect 

fatigue cracking of the lower surface panel on 

the WCB, in accordance with Airbus Service 

Bulletin A320–57–1082, Revision 01, dated 

December 10, 1997; or Revision 03, dated 

April 30, 2002. Accomplishment of the initial 

inspection required by paragraph (p) of this 

AD constitutes terminating action for the 

inspection requirements of this paragraph. 

(1) If no cracking is detected: Prior to 

further flight, modify the lower surface panel 

on the WCB, in accordance with Airbus 

Service Bulletin A320–57–1043, Revision 02, 

dated May 14, 1997; or Revision 05, dated 

April 30, 2002. Accomplishment of the 

modification constitutes terminating action 

for the requirements of paragraph (g) of this 

AD. 

(2) Except as provided by paragraph (j) of 

this AD: If any cracking is detected, prior to 

further flight, repair in accordance with 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997, or 

Revision 03, dated April 30, 2002; and 

modify any uncracked area, in accordance 

with Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, or Revision 

05, dated April 30, 2002. Accomplishment of 

the repair of cracked area(s) and modification 

of uncracked area(s) constitutes terminating 

action for the requirements of paragraph (g) 

of this AD. 

(j) Retained Service Bulletin Exception, With 

No Changes 

This paragraph restates the requirements of 

paragraph (d) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. If any cracking is 

detected during any inspection required by 

paragraph (h) or (i)(2) of this AD, and the 

applicable service bulletin specifies to 

contact Airbus for an appropriate action: 

Prior to further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) (or its delegated 

agent). 

(k) Retained Provision for Certain Inspection 

Exception, With No Changes 

This paragraph restates the provision of 

paragraph (e) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. The actions required 

by paragraph (g) of this AD are not required 

to be accomplished if the requirements of 

paragraph (i) of this AD are accomplished at 

the time specified in paragraph (g) of this AD. 

(l) Retained Initial Inspection, With 

Terminating Action 

This paragraph restates the requirements of 

paragraph (f) of AD 2004–14–09, Amendment 

39–13718 (69 FR 41398, July 9, 2004), with 

terminating action provided. For airplanes on 

which neither the inspection required by 

paragraph (g) of this AD, nor the modification 

required by paragraph (i)(1) of this AD has 

been done before August 13, 2004 (the 

effective date of AD 2004–14–09): Perform an 

HFEC inspection to detect fatigue cracking of 

the lower surface panel on the WCB, in 

accordance with Airbus Service Bulletin 

A320–57–1082, Revision 01, dated December 

10, 1997; or Revision 03, dated April 30, 

2002; at the later of the times specified in 

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

Accomplishment of the inspection required 

by this paragraph terminates the 

requirements of paragraph (g) of this AD. 

Accomplishment of the initial inspection 

required by paragraph (p) of this AD 

terminates the inspection requirements of 

this paragraph. 

(1) Prior to the accumulation of 13,200 

total flight cycles or 39,700 total flight hours, 

whichever is first. 

(2) Prior to the accumulation of 20,000 

total flight cycles, or within 3,500 flight 

cycles after August 13, 2004 (the effective 

date of AD 2004–14–09, Amendment 39– 

13718 (69 FR 41398, July 9, 2004)), 

whichever is later. 

(m) Retained Repetitive Inspections, With 

No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. If no cracking is 

detected during the inspection required by 

paragraph (g) or (l) of this AD: Repeat the 

inspection required by paragraph (l) of this 

AD at the applicable time specified in 

paragraph (m)(1) or (m)(2) of this AD. 

Accomplishment of the modification 

required by paragraph (i)(1) of this AD 

terminates the requirements of this 

paragraph. 

(1) For airplanes on which the inspections 

required by paragraph (g) of this AD have 

been initiated before August 13, 2004 (the 

effective date of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004)): Do the next inspection within 5,700 

flight cycles after accomplishment of the last 

inspection, or within 1,800 flight cycles after 


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August 13, 2004, whichever is later. Repeat 

the inspection thereafter at intervals not to 

exceed 5,700 flight cycles. 

(2) For airplanes on which no inspection 

required by paragraph (g) of this AD has been 

done before August 13, 2004 (the effective 

date of AD 2004–14–09, Amendment 39– 

13718 (69 FR 41398, July 9, 2004)): Do the 

next inspection within 5,700 flight cycles 

after accomplishment of the inspection 

required by paragraph (l) of this AD. Repeat 

the inspection thereafter at intervals not to 

exceed 5,700 flight cycles. 

(n) Retained Repair/Modification, With No 

Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, July 9, 

2004), with no changes. If any cracking is 

detected during any inspection required by 

paragraph (l) or (m) of this AD, prior to 

further flight, repair in accordance with 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997, or 

Revision 03, dated April 30, 2002; and 

modify any uncracked area, in accordance 

with Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, or Revision 

05, dated April 30, 2002. Where Airbus 

Service Bulletin A320–57–1082 specifies to 

contact Airbus for an appropriate repair 

action: Prior to further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the DGAC 

(or its delegated agent). Accomplishment of 

the repair of cracked area(s) and modification 

of uncracked area(s) constitutes terminating 

action for the requirements of paragraphs (g) 

through (n) of this AD. 

(o) New Requirement of This AD: Repair of 

Certain Airplanes 

For airplanes on which the actions 

described in Airbus Service Bulletin A320– 

57–1043 have not been accomplished, and on 

which a repair has been accomplished, as 

described in Airbus Service Bulletin A320– 

57–1082, dated October 31, 1996; Revision 

01, dated December 10, 1997; Revision 02, 

dated July 26, 1999; or Revision 03, dated 

April 30, 2002: Within 30 days after the 

effective date of this AD, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA design organization approval (DOA). 

(p) New Requirement of This AD: Repetitive 

WCB Inspections 

At the applicable time specified in 

paragraphs (p)(1) and (p)(2) of this AD: Do an 

HFEC inspection for cracking of the lower 

surface panel on the WCB, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1082, 

Revision 04, dated December 5, 2013. Repeat 

the inspection of the lower surface panel on 

the WCB thereafter at intervals not to exceed 

7,200 flight cycles or 14,400 flight hours, 

whichever occurs first. Accomplishment of 

the initial inspection required by this 

paragraph terminates the inspections 

required by paragraphs (g), (i), and (l) of this 

AD. 

(1) For airplanes on which the actions 

described in Airbus Service Bulletin A320– 

57–1043 have not been done: At the later of 

the times specified in paragraphs (p)(1)(i) and 

(p)(1)(ii) of this AD. 

(i) Before the accumulation of 20,700 flight 

cycles or 41,400 flight hours, whichever 

occurs first since first flight of the airplane. 

(ii) Within 7,200 flight cycles or 14,400 

flight hours, whichever occurs first after 

doing the most recent inspection as specified 

in Airbus Service Bulletin A320–57–1082, 

dated October 31, 1996; Revision 01, dated 

December 10, 1997; Revision 02, dated July 

26, 1999; or Revision 03, dated April 30, 

2002. 

(2) For airplanes on which the actions 

specified in Airbus Service Bulletin A320– 

57–1043, dated February 16, 1993; Revision 

01, dated June 14, 1996; Revision 02, dated 

May 14, 1997; Revision 03, dated October 24, 

1997; Revision 04, dated March 15, 1999; or 

Revision 05, dated April 30, 2002; have been 

done: At the latest of the times specified in 

paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) 

of this AD. 

(i) Within 7,200 flight cycles or 14,400 

flight hours, whichever occurs first since 

doing the actions specified in Airbus Service 

Bulletin A320–57–1043. 

(ii) Within 3,750 flight cycles or 7,500 

flight hours, whichever occurs first after July 

31, 2012 (as described in Airbus Service 

Bulletin A320–57–1082, Revision 04, dated 

December 5, 2013). 

(iii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(q) New Requirement of This AD: Repair of 

WCB 

If any crack is found during any inspection 

required by paragraph (p) of this AD: Before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the EASA; or Airbus’s 

EASA DOA. 

(r) New Optional Terminating Action 

Modification of an airplane, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1043, 

Revision 06, dated December 5, 2013, 

constitutes terminating action for the actions 

required by paragraph (p) of this AD. 

(s) Credit for Previous Actions 

This paragraph provides credit for 

applicable actions required by paragraphs (g) 

through (n) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable Airbus Service 

Information provided in paragraphs (s)(1) 

through (s)(8) of this AD. 

(1) Airbus Service Bulletin A320–57–1043, 

dated February 16, 1993, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A320–57–1043, 

Revision 01, dated June 14, 1996, which is 

not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, which was 

incorporated by reference on November 27, 

1998 (63 FR 56542, October 22, 1998). 

(4) Airbus Service Bulletin A320–57–1043, 

Revision 03, dated October 24, 1997, which 

is not incorporated by reference in this AD. 

(5) Airbus Service Bulletin A320–57–1043, 

Revision 04, dated May 15, 1999, which is 

not incorporated by reference in this AD. 

(6) Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997, which 

was incorporated by reference on November 

27, 1998 (63 FR 56542, October 22, 1998). 

(7) Airbus Service Bulletin A320–57–1082, 

Revision 02, dated July 26, 1999, which is 

not incorporated by reference in this AD. 

(8) Airbus Service Bulletin A320–57–1082, 

Revision 03, dated April 30, 2002, which was 

incorporated by reference on August 13, 2004 

(69 FR 41398, July 9, 2004). 

(t) 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. 

(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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(u) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0065, dated 

March 14, 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– 

2014–1275. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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

You may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
26496 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 

Issued in Renton, Washington, on April 29, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–10949 Filed 5–7–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2014–0565; Airspace 

Docket No. 14–ACE–7] 

Proposed Revocation of Class D and E 

Airspace; Independence, KS 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM). 

SUMMARY: This supplemental notice of 

proposed rulemaking proposes to 

remove Class D airspace and Class E 

surface area airspace at Independence 

Municipal Airport, Independence, KS. 

In an NPRM published in the Federal 

Register September 25, 2014, the FAA 

proposed to remove Class D airspace at 

Independence Municipal Airport, 

Independence, KS. The FAA has 

reassessed the proposal to include the 

removal of the associated Class E 

surface area airspace. The closure of the 

airport’s air traffic control tower has 

necessitated the need for this proposal. 

DATES: Comments must be received on 

or before June 22, 2015. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. You must 

identify the docket number FAA–2014– 

0565/Airspace Docket No. 14–ACE–7, at 

the beginning of your comments. You 

may also submit comments through the 

Internet at http://www.regulations.gov. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office between 

9:00 a.m. and 5:00 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone 1–800– 

647–5527) is on the ground floor of the 

building at the above address. 

FAA Order 7400.9Y, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at http://www.faa.gov/air_traffic/ 

publications/. The Order is also 

available for inspection at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this proposed 

incorporation by reference material at 

NARA, call 202–741–6030, or go to 

http://www.archives.gov/federal_

register/code_of_federal-regulations/ibr_

locations.html. 

FAA Order 7400.9, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. For further information, 

you can contact the Airspace Policy and 

Regulations Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: 202–267–8783. 

FOR FURTHER INFORMATION CONTACT: Raul 

Garza, Jr., Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone: 817–321– 

7654. 

SUPPLEMENTARY INFORMATION: 

History 

On September 25, 2014, the FAA 

published a NPRM to remove Class D 

airspace at Independence Municipal 

Airport, Independence, KS, as the air 

traffic control tower has closed (79 FR 

57483). The comment period closed 

November 10, 2014. No comments were 

received. Subsequent to publication, the 

FAA reassessed the proposal to include 

the removal of the associated Class E 

surface area airspace at Independence 

Municipal Airport, Independence, KS. 

Also, the title section is amended to 

include Class E airspace. The FAA seeks 

comments on this SNPRM. 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers and be submitted in 

triplicate to the address listed above. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this notice must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2014–0565/Airspace 

Docket No. 14–ACE–7.’’ The postcard 

will be date/time stamped and returned 

to the commenter. 

Availability of SNPRMs 

An electronic copy of this document 

may be downloaded through the 

Internet at http://www.regulations.gov. 

Recently published rulemaking 

documents can also be accessed through 

the FAA’s Web page at http://

www.faa.gov/airports_airtraffic/air_

traffic/publications/airspace_

amendments/. 

You may review the public docket 

containing the proposal, any comments 

received and any final disposition in 

person in the Dockets Office (see 

ADDRESSES section for address and 

phone number) between 9:00 a.m. and 

5:00 p.m., Monday through Friday, 

except Federal holidays. An informal 

docket may also be examined during 

normal business hours at the office of 

the Central Service Center, 2601 

Meacham Blvd., Fort Worth, TX 76137. 

Persons interested in being placed on 

a mailing list for future NPRMs should 

contact the FAA’s Office of Rulemaking 

(202) 267–9677, to request a copy of 

Advisory Circular No. 11–2A, Notice of 

Proposed Rulemaking Distribution 

System, which describes the application 

procedure. 

Availability and Summary of 

Documents Proposed for Incorporation 

by Reference 

This document proposes to amend 

FAA Order 7400.9Y, Airspace 

Designations and Reporting Points, 

dated August 6, 2014, and effective 

September 15, 2014. FAA Order 

7400.9Y is publicly available as listed in 

the ADDRESSES section of this proposed 

rule. FAA Order 7400.9Y lists Class A, 

B, C, D, and E airspace areas, air traffic 

service routes, and reporting points. 

The Supplemental Proposal 

This supplemental proposal proposes 

to amend Title 14, Code of Federal 

Regulations (14 CFR), Part 71 by 

removing Class D airspace and the 

associated Class E surface area airspace 

at Independence Municipal Airport, 

Independence, KS. The closing of the 

airport’s air traffic control tower has 

made this action necessary. Also, the 

Title section is amended to read 

‘‘Proposed Revocation of Class D and E 

Airspace; Independence, KS’’. 

Class D and E airspace areas are 

published in Paragraph 5000 and 6002, 

respectively, of FAA Order 7400.9Y, 

dated August 6, 2014, and effective 

September 15, 2014, which is 

incorporated by reference in 14 CFR 

71.1. The Class D and E airspace 

designations listed in this document 

will be published subsequently in the 

Order. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS