59160 Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Proposed Rules 

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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Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Proposed Rules 59161 

actions include measuring the diameter 

of a hole of a fastener and a rotating 

probe inspection. Corrective actions 

include repairs. 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–2014–0652. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–53–1267, Revision 01, dated 

October 2, 2013; and Service Bulletin 

A320–53–1272, Revision 02, dated May 

19, 2014. 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 25 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $420 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $2,165,795, or 

$2,545 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): 

Airbus: Docket No. FAA–2014–0652; 

Directorate Identifier 2014–NM–076–AD. 

(a) Comments Due Date 

We must receive comments by November 

17, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category, all 

manufacturer serial numbers, except those on 

which Airbus Modification 160055 or Airbus 

Modification 160056 has been embodied in 

production. 

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

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

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

–231, –232, and –233 airplanes. 

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

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This 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. We are issuing 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

(1) Within the compliance time specified 

in paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), 

(g)(1)(iv), and (g)(1)(v) of this AD, as 

applicable, modify the potable water service 

panel, including doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1272, Revision 02, dated May 19, 2014, 

except where Airbus Service Bulletin A320– 

53–1272, Revision 02, dated May 19, 2014, 

specifies to contact Airbus, repair before 

further flight 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). Do all applicable related 

investigative and corrective actions within 

the compliance time identified in paragraphs 

(g)(1)(i), (g)(1)(ii), (g)(1)(iii), (g)(1)(iv), and 

(g)(1)(v) of this AD. 

(i) For Model A319 airplanes premodification 160001: Within 48,500 flight 

cycles or 97,000 flight hours, whichever 

occurs first since the airplane’s first flight. 

(ii) For Model A319 airplanes postmodification 160001: Within 46,000 flight 

cycles or 92,000 flight hours, whichever 

occurs first since the airplane’s first flight. 

(iii) For Model A320 airplanes premodification 160001: Within 54,200 flight 

cycles or 108,400 flight hours, whichever 

occurs first since the airplane’s first flight. 

(iv) For Model A320 airplanes postmodification 160001: Within 36,000 flight 

cycles or 72,000 flight hours, whichever 

occurs first since the airplane’s first flight. 

(v) For Model A321 airplanes: Within 

60,000 flight cycles or 120,000 flight hours, 

whichever occurs first since the airplane’s 

first flight. 

(2) Within the compliance time specified 

in paragraphs (g)(2)(i), (g)(2)(ii), (g)(2)(iii), 

(g)(2)(iv), (g)(2)(v), and (g)(2(vi) of this AD, as 

applicable, modify the waste water service 

panel, including doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
59162 Federal Register / Vol. 79, No. 190 / Wednesday, October 1, 2014 / Proposed Rules 

53–1267, Revision 01, dated October 2, 2013, 

except where Airbus Service Bulletin A320– 

53–1267, Revision 01, dated October 2, 2013, 

specifies to contact Airbus, repair before 

further flight using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

EASA; or Airbus’s EASA DOA. Do all 

applicable related investigative and 

corrective actions within the compliance 

time identified in paragraphs (g)(2)(i), 

(g)(2)(ii), (g)(2)(iii), (g)(2)(iv), and (g)(2)(v) of 

this AD. 

(i) For Airbus A319 airplanes premodification 160001: Within 44,400 flight 

cycles or 88,800 flight hours, whichever 

occurs first since the airplane’s first flight. 

(ii) For Airbus A319 airplanes postmodification 160001: Within 43,600 flight 

cycles or 87,200 flight hours, whichever 

occurs first since the airplane’s first flight. 

(iii) For Airbus A320 airplanes premodification 160001, within the compliance 

times identified in paragraph (g)(2)(iii)(A) or 

(g)(2)(iii)(B) of this AD, whichever occurs 

later: 

(A) Within 46,400 flight cycles or 92,800 

flight hours, whichever occurs first since the 

airplane’s first flight. 

(B) Within 2,300 flight cycles or 4,600 

flight hours, whichever occurs first since last 

accomplishment of Airworthiness Limitation 

Section (ALS) Part 2 Task No. 534126–01–3 

without exceeding 48,000 flight cycles or 

96,000 flight hours, whichever occurs first 

since the airplane’s first flight. 

(iv) For Airbus A320 airplanes postmodification 160001: Within 39,200 flight 

cycles or 78,400 flight hours, whichever 

occurs first since the airplane’s first flight. 

(v) For Airbus A321 airplanes premodification 160021: Within 51,600 flight 

cycles or 103,200 flight hours, whichever 

occurs first since the airplane’s first flight. 

(vi) For Airbus A321 airplanes postmodification 160021: Within 51,200 flight 

cycles or 102,400 flight hours, whichever 

occurs first since the airplane’s first flight. 

(h) Corrective Action 

For Airbus A320 airplanes having premodification 160001, that have exceeded 

46,400 flight cycles or 92,800 flight hours, 

whichever occurred first since the airplane’s 

first flight: If any crack is found during 

accomplishment of ALS Part 2 Task 534126– 

01–3 done, before further flight, repair using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. 

(i) Terminating Action for ALS Task 

(1) Modification of an airplane as required 

by paragraph (g)(1) of this AD, terminates the 

requirement for the ALS Part 2 Task for that 

airplane as identified in paragraphs (i)(1)(i), 

(i)(1)(ii), (i)(1)(iii), (i)(1)(iv), (i)(1)(v), and 

(i)(1)(vi) of this AD, as applicable. 

(i) For Airbus A319 airplanes premodification 160001: ALS Part 2 Task No. 

534125–01–2. 

(ii) For Airbus A319 airplanes postmodification 160001: ALS Part 2 Task No. 

534125–01–5. 

(iii) For Airbus A320 airplanes premodification 160001: ALS Part 2 Task No. 

534125–01–3. 

(iv) For Airbus A320 airplanes postmodification 160001: ALS Part 2 Task No. 

534125–01–6. 

(v) For Airbus A321 airplanes premodification 160021: ALS Part 2 Task No. 

534125–01–4. 

(vi) For Airbus A321 airplanes postmodification 160021: ALS Part 2 Task No. 

534125–01–7. 

(2) Modification of an airplane as required 

by paragraphs (g)(2) and (g)(3) of this AD, 

terminates the requirement for the ALS Part 

2 task for that airplane as identified in 

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

(i)(2)(iv), (i)(2)(v), and (i)(2)(vi) of this AD, as 

applicable. 

(i) For Airbus A319 airplanes premodification 160001: ALS Part 2 Task No. 

534126–01–2. 

(ii) For Airbus A319 airplanes postmodification 160001: ALS Part 2 Task No. 

534126–01–5. 

(iii) For Airbus A320 airplanes premodification 160001: ALS Part 2 Task No. 

534126–01–3. 

(iv) For Airbus A320 airplanes postmodification 160001: ALS Part 2 Task No. 

534126–01–6. 

(v) For Airbus A321 airplanes premodification 160021: ALS Part 2 Task No. 

534126–01–4. 

(vi) For Airbus A321 airplanes postmodification 160021: ALS Part 2 Task No. 

534126–01–7. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1272, dated 

January 10, 2013; and Airbus Service Bulletin 

A320–53–1272, Revision 01, dated August 6, 

2013; which are not incorporated by 

reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (g)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1267, dated June 

24, 2013, which is not incorporated by 

reference in this AD. 

(k) 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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0081, dated 

March 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– 

2014–0652. 

(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 

September 20, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23366 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–2014–0651; Directorate 

Identifier 2014–NM–043–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2013–22– 

19, which applies to all Gulfstream 

Aerospace Corporation Model GV and 

GV–SP airplanes. AD 2013–22–19 

currently requires inspecting to 

determine if fuel boost pumps having a 

certain part number are installed, 


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