Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 52267 

if those actions were performed before April 

23, 2008 (the effective date of AD 2008–06– 

18, Amendment 39–15430 (73 FR 14670, 

March 19, 2008)), using the applicable 

service information identified in paragraphs 

(i)(1)(i) through (i)(1)(iv) of this AD, which 

are not incorporated by reference by this AD. 

(i) Airbus Service Bulletin A300–57–0177, 

Revision 03, dated May 29, 2006. 

(ii) Airbus Service Bulletin A300–57–0177, 

Revision 04, dated January 5, 2007. 

(iii) Airbus Service Bulletin A300–57– 

6029, Revision 04, dated May 29, 2006. 

(iv) Airbus Service Bulletin A300–57– 

6029, Revision 05, dated October 23, 2006. 

(2) This paragraph provides credit for 

actions required by paragraph (g) or (h) of 

this AD, if those actions were performed 

before the effective date of this AD, using 

Airbus Service Bulletin A300–57–6029, 

Revision 07, dated June 6, 2011, which is not 

incorporated by reference by this AD. 

(j) 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. 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. AMOCs 

approved previously for AD 2008–06–18, 

Amendment 39–15430 (73 FR 14670, March 

19, 2008) are considered acceptable for this 

AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0203, dated October 1, 2012, 

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–2014–0618. 

(2) For service information identified in 

this AD, contact Airbus SAS Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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

You may view this 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 August 

23, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20917 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0589; Directorate 

Identifier 2014–NM–069–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 A318–111 and –112 

airplanes, Model A319, A320, and A321 

series airplanes. This proposed AD was 

prompted by reports of cracks on the 

forward corner fittings of engine pylon 

aft secondary structures. This proposed 

AD would require repetitive inspections 

of certain forward corner fittings of the 

pylon aft secondary structures, and 

corrective actions if necessary. This 

proposed AD also provides optional 

terminating action for the repetitive 

inspections. We are proposing this AD 

to detect and correct detachment of the 

lower fairing attachment and/or loss of 

the aft fixed fairing with the movable 

fairing from the airplane in flight, which 

could result in damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by October 20, 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– 

0589; 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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
52268 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 

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–2014–0589; Directorate Identifier 

2014–NM–069–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 2014–0064, 

dated March 14, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Model A318–111 and –112 

airplanes, Model A319 series airplanes, 

Model A320 series airplanes, and Model 

A321 series airplanes. The MCAI states: 

Several operators of A320 family 

aeroplanes have reported finding cracks on 

the forward corner fittings of engine pylon aft 

secondary structures, on the lateral face 

(lateral panel side). In some cases, these 

cracks had propagated onto the forward face 

(Rib 11 side). Investigation results have 

highlighted that these cracks are initiated by 

stress corrosion. 

This condition, if not detected and 

corrected, could lead to loss (i.e. detachment 

from the aeroplane) of the lower fairing 

attachment at Rib 10, and/or loss of the aft 

fixed fairing with the movable fairing, 

possibly resulting in * * * [damage to the 

airplane]. 

For the reasons described above, this 

[EASA] AD requires repetitive detailed 

inspections (DI) of the right hand (RH) Part 

Number (P/N) D54530014201 and left hand 

(LH) P/N D54530014200 corner fittings of 

engine pylon aft secondary structures (premod 38067 or pre-Airbus Service Bulletin 

(SB) A320–54–1019) to detect cracks or 

deformation in the splicing area with corner 

fitting between Ribs 11–12 and, depending 

on findings, replacement of the corner 

fittings. 

This [EASA] AD also recognizes that 

replacement of the corner fittings with 

improved parts (as per Airbus SB A320–54– 

1019) constitutes a terminating action for the 

repetitive DI required by this [EASA] AD. 

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– 

0589. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–54–1019, Revision 01, dated April 

10, 2008; and Service Bulletin A320– 

54–1022, Revision 02, dated July 12, 

2013. 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 these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

We also estimate that it would take 

about 30 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $2,170,050, or $2,550 per product. 

In addition, we estimate the optional 

terminating modification would take 

about 60 work-hours and require parts 

costing about $932 per product, for a 

cost of $6,032 per product. 

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. 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2014–0589; 

Directorate Identifier 2014–NM–069–AD. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 52269 

(a) Comments Due Date 

We must receive comments by October 20, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, 

except for airplanes on which Airbus 

Modification 33844, or Modification 33847, 

as applicable, has been embodied in 

production. 

(1) Airbus Model A318–111 and –112 

airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Reason 

This AD was prompted by reports of cracks 

on the forward corner fittings of engine pylon 

aft secondary structures. We are issuing this 

AD to detect and correct detachment of the 

lower fairing attachment and/or loss of the aft 

fixed fairing with the movable fairing from 

the airplane in flight, which could result in 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the latest of the times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Do a detailed inspection for cracking of 

forward corner fittings having part number 

(P/N) D54530014201 (right-hand (RH)) and 

P/N D54530014200 (left-hand (LH)) of the 

pylon aft secondary structures, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–54–1022, 

Revision 02, dated July 12, 2013, except as 

provided by paragraph (j) of this AD. Repeat 

the inspection thereafter at intervals not to 

exceed 15,000 flight cycles or 22,500 flight 

hours, whichever occurs first. 

Accomplishment of the actions required by 

paragraph (i) of this AD terminates the 

actions required by this paragraph. 

(1) Within 15,000 flight cycles or 22,500 

flight hours, whichever occurs first since first 

flight of the airplane. 

(2) Within 5,000 flight cycles or 7,500 

flight hours after the effective date of this AD, 

without exceeding 40,750 flight cycles or 

60,750 flight hours, whichever occurs first 

since first flight of the airplane. 

(3) Within 750 flight cycles or 750 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(h) Related Investigative and Corrective 

Actions 

If any crack is found on the corner fittings 

of a pylon during any inspection required by 

paragraph (g) of this AD: Before further flight, 

do a detailed inspection for cracking of the 

lower and medium spars, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–54–1022, Revision 02, 

dated July 12, 2013. 

(1) If any damage is found: Before further 

flight, repair 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). 

(2) If no damage is found: Within 5,000 

flight cycles or 7,500 flight hours, whichever 

occurs first after the detailed inspection 

specified in paragraph (h) of this AD, modify 

the airplane, in accordance with the 

Accomplishment Instructions of Service 

Bulletin A320–54–1019, Revision 01, dated 

April 10, 2008. 

(i) Optional Terminating Action 

Modification of an airplane by installation 

of corner fittings having P/N 

D0041092120000 RH and P/N 

D0041092120100 LH on both pylons, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

54–1019, Revision 01, dated April 10, 2008, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(j) Parts Installation Exception 

Airplanes on which Airbus Modification 

38067 (installation of new corner fittings) has 

been embodied in production, and airplanes 

already modified in service as described in 

Airbus Service Bulletin A320–54–1019, are 

not affected by the requirements of paragraph 

(g) of this AD, provided that no corner 

fittings having P/N D54530014201 RH or 

P/N D54530014200 LH have been installed 

since first flight of the airplane, or since 

modification, as applicable. 

(k) Parts Installation Prohibition 

(1) As of the effective date of this AD, for 

airplanes on which Airbus Modification 

38067 has been embodied in production on 

both pylons, and for airplanes previously 

modified in service as described in Airbus 

Service Bulletin A320–54–1019: Do not 

install any corner fittings having P/N 

D54530014201 RH or P/N D54530014200 LH. 

(2) After modification as required by 

paragraph (h) of this AD, or after optional 

modification as specified in paragraph (i) of 

this AD, as applicable: Do not install any 

corner fittings having P/N D54530014201 RH 

or P/N D54530014200 LH. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–54–1022, dated July 7, 2009; 

or Airbus Service Bulletin A320–54–1022, 

Revision 01, dated September 29, 2011; 

which are not incorporated by reference in 

this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0064, 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– 

2014–0589. 

(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. 

Issued in Renton, Washington, on August 

22, 2014. 

Kevin Hull, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20937 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 


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