Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 22939 

DEPARTMENT OF ENERGY 

10 CFR Parts 429 and 431 

[Docket No. EERE–2013–BT–TP–0055] 

RIN 1905–AD50 

Energy Conservation Program: Test 

Procedure for Pumps; Correction 

AGENCY: Office of Energy Efficiency and 

Renewable Energy, Department of 

Energy. 

ACTION: Notice of proposed rulemaking 

and public meeting; correction. 

SUMMARY: On April 1, 2015, the U.S. 

Department of Energy (DOE) published 

in the Federal Register a notice of 

proposed rulemaking and public 

meeting for Energy Conservation 

Program: Test Procedure for Pumps. 

This document corrects terms in four 

equations. 

DATES: April 24, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Ashley Armstrong, U.S. Department of 

Energy, Office of Energy Efficiency and 

Renewable Energy, Building 

Technologies Office, EE–5B, 1000 

Independence Avenue SW., 

Washington, DC 20585–0121. 

Telephone: (202) 586–6590. Email: 

ashley.armstrong@ee.doe.gov. 

Corrections 

In the Federal Register published on 

April 1, 2015, in FR Doc. 2015–06945, 

make the following corrections: 

1. On page 17604: Equation (6) is 

corrected by removing ‘‘13.46’’ and 

adding in its place ‘‘17.80’’. The 

corrected equation reads as follows: 

Appendix A to Subpart Y of Part 431— 

Uniform Test Method for the 

Measurement of Energy Consumption of 

Pumps. [Corrected] 

2. On page 17645: The equation in 

section II.B.1.1.1 is corrected by 

removing ‘‘13.46’’ and adding in its 

place ‘‘17.80’’. The corrected equation 

reads as follows: 

hpump,STD = ¥0.85 * In(Q100%)2 ¥ 0.38 * 

In(NS) * In(Q100%) ¥ 11.48 * In(NS)2

+ 17.80 * In(Q100%) + 179.80 * 

In(NS) ¥ (C ¥ 555.6) 

3. On page 17646: The equation in 

section III.D.1.2.1 is corrected by 

removing ‘‘MotorH’’ and adding in its 

place ‘‘MotorHP’’. The corrected 

equation reads as follows: 

4. On page 17648: The equation in 

section V.D.1.2.1 is corrected by 

removing ‘‘MotorHPMotorH’’ and 

adding in its place ‘‘MotorHP’’. The 

corrected equation reads as follows: 

Issued in Washington, DC, on April 20, 

2015. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2015–09566 Filed 4–23–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0831; Directorate 

Identifier 2014–NM–061–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 all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by a report of a 

rupture of a main landing gear (MLG) 

sliding tube axle. This proposed AD 

would require an inspection to identify 

the part number and serial number of 

the MLG sliding tubes installed on the 

airplane; and an inspection of the axle 

on certain MLG sliding tubes for burned 

areas, and replacement of the sliding 

tube if necessary. We are proposing this 

AD to detect and correct cracks in the 

axle and (partial) detachment of the axle 

and wheel from the sliding tube, which 

could result in failure of an MLG. 


tkelley on DSK3SPTVN1PROD with PROPOSALSEP24AP15.017</GPH> EP24AP15.001</GPH> EP24AP15.002</GPH>
22940 Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 

DATES: We must receive comments on 

this proposed AD by June 8, 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 Airbus 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. 

For Messier-Bugatti-Dowty service 

information identified in this proposed 

AD, contact Messier Services Americas, 

Customer Support Center, 45360 Severn 

Way, Sterling, VA 20166–8910; phone: 

703–450–8233; fax: 703–404–1621; 

Internet: https://techpubs.services/

messier-dowty.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– 

0831; 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–2015–0831; Directorate Identifier 

2014–NM–061–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 

Union, has issued EASA Airworthiness 

Directive 2014–0058, dated March 11, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A318, A319, A320, and A321 

series airplanes. The MCAI states: 

A main landing gear (MLG) sliding tube 

axle rupture occurred in service. 

Investigation of the affected part showed that 

this failure was due to an abnormal grinding 

operation during overhaul by a certain 

maintenance and repair organisation located 

in Singapore. A population of MLG sliding 

tubes was subsequently identified whose 

axles may have been subject to this grinding 

operation, which may have resulted in areas 

of residual stress on the axles on the MLG 

sliding tubes. In addition, the MSN 

[manufacturer serial number] of the 

aeroplanes which are known to have had the 

affected parts installed have been identified. 

This condition, if not detected and 

corrected, could lead to cracks in the axle 

and (partial) detachment of axle and wheel 

from the sliding tube, possibly resulting in 

failure of a MLG with consequent damage to 

the aeroplane and injury to occupants. 

To address this potential unsafe condition, 

Messier-Bugatti-Dowty, the MLG gear 

manufacturer, issued Service Bulletin (SB) 

200–32–313 and SB 201–32–62 [both dated 

February 25, 2013], providing inspection 

instructions and criteria for removal from 

service of the affected MLG sliding tubes. 

For the reasons described above, this 

[EASA] AD requires a one-time Special 

Detailed Inspection (SDI) of the axle on the 

affected MLG sliding tubes and, depending 

on findings, replacement of the MLG sliding 

tube. 

The SDI includes a detailed visual 

inspection of the chromium plate for 

damage, and a Barkhausen noise 

inspection of the sliding tube axles for 

burned areas. 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–2015–0831. 

Related Service Information Under 1 

CFR part 51 

Airbus has issued Service Bulletin 

A320–32–1416, including Appendix 01, 

dated March 10, 2014 (for Model A319, 

A320, and A321 series airplanes). This 

service bulletin describes procedures for 

inspection of the MLG sliding tube 

axles, and replacement if necessary. 

Messier-Bugatti-Dowty has issued 

Service Bulletin 200–32–313, including 

Appendices A, B, and C, dated February 

25, 2013 (for Model A318, A319, and 

A320 series airplanes); and Service 

Bulletin 201–32–62, including 

Appendices A, B, and C, dated February 

25, 2013 (for Model A321 series 

airplanes). These service bulletins 

describe procedures for inspection of 

the MLG axles and brake flanges, and 

replacement if necessary. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

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. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 


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Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 22941 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The procedures and tests 

identified as RC (required for 

compliance) in any service information 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and tests that 

are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 3 airplanes of U.S. registry. 

We also estimate that it would take 

about 18 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 $4,590, or $1,530 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours, for a cost of $255 

per product. We have received no 

definitive data that would enable us to 

provide part cost estimates for the oncondition 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, 

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–2015–0831; 

Directorate Identifier 2014–NM–061–AD. 

(a) Comments Due Date 

We must receive comments by June 8, 

2015. 

(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, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 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 32, Landing gear. 

(e) Reason 

This AD was prompted by a report of a 

rupture of a main landing gear (MLG) sliding 

tube axle. We are issuing this AD to detect 

and correct cracks in the axle and (partial) 

detachment of the axle and wheel from the 

sliding tube, which could result in failure of 

an MLG. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) MLG Sliding Tube Part Number and 

Serial Number Identification 

Within 3 months after the effective date of 

this AD: Do an inspection to identify the part 

number and serial number of the MLG 

sliding tubes installed on the airplane. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number and serial number of the MLG 

sliding tubes can be conclusively determined 

from that review. 

(h) Identification of Airplanes Not Affected 

by the Requirements of Paragraph (i) of This 

AD 

An airplane with a manufacturer serial 

number (MSN) not listed in figure 1 to 

paragraph (h) of this AD is not affected by the 

requirements of paragraph (i) of this AD, 

provided it can be determined that no MLG 

sliding tube having a part number and serial 

number listed in table 1 to paragraphs (h), (i), 

(k)(1), (k)(2), (l)(1), and (l)(2) of this AD has 

been installed on that airplane since first 

flight of the airplane. 

FIGURE 1 TO PARAGRAPH (h) OF THIS AD 

Affected airplanes listed by MSN 

0179 0214 0296 0412 0558 0604 


tkelley on DSK3SPTVN1PROD with PROPOSALS
22942 Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 

FIGURE 1 TO PARAGRAPH (h) OF THIS AD—Continued 

0607 0668 0704 0720 0726 0731 

0754 0771 0799 0828 0841 0855 

0909 0914 0925 0939 0986 1028 

1030 1041 1070 1083 1093 1098 

1108 1148 1294 1356 2713 2831 

TABLE 1 TO PARAGRAPHS (h), (i), 

(k)(1), (k)(2), (l)(1), AND (l)(2) OF

THIS AD—AFFECTED MLG SLIDING

TUBES

Part No. Serial No. 

201160302 ............................ 78B. 

201160302 ............................ 1016B11. 

201160302 ............................ 1144B. 

201371302 ............................ B4493. 

201371302 ............................ B4513. 

201371302 ............................ SS4359. 

201371302 ............................ B4530. 

201371302 ............................ B4517. 

201371302 ............................ B4568. 

201371302 ............................ B4498. 

201371302 ............................ 4490B. 

201371302 ............................ B202–4598. 

201371302 ............................ B165–4623. 

201371302 ............................ B244–4766. 

201371302 ............................ B267–4794. 

201371302 ............................ B272–4813. 

201160302 ............................ 1108B. 

201371304 ............................ B041–4871. 

201371304 ............................ B045–4869. 

201371304 ............................ B001–4781. 

201371304 ............................ B051–4892. 

201371304 ............................ B110–1952. 

201371304 ............................ B054–4891. 

201371304 ............................ B063–4921. 

201371304 ............................ B071–4911. 

201371304 ............................ B071–4917. 

201371304 ............................ B080–1933. 

201371304 ............................ B117–5010. 

201371304 ............................ B120–4989. 

201371304 ............................ B132–2023. 

201371304 ............................ B114–1956. 

201371304 ............................ B208–2009. 

201371304 ............................ B133–1947. 

201371304 ............................ B154–5037. 

201371304 ............................ B89 4952. 

201371304 ............................ B129–1964. 

201371304 ............................ B227–2010. 

201371304 ............................ B170–5031. 

201371304 ............................ B182–5047. 

201371304 ............................ B239–2053. 

201371304 ............................ B1401–2856. 

201371304 ............................ B1813–3142. 

201371304 ............................ B116–5004. 

201522353 ............................ B011–149. 

201522350 ............................ B014–25. 

201522350 ............................ B019–56. 

201522350 ............................ B019–57. 

201522350 ............................ B021–69. 

201522350 ............................ B022–60. 

201522353 ............................ B03–111. 

201522353 ............................ B03–110. 

201522353 ............................ B112–317. 

201522353 ............................ B174–351. 

201522353 ............................ B179–392. 

201383350 ............................ 4377B. 

201383350 ............................ 4393B. 

201383350 ............................ B1831. 

201383350 ............................ B1832. 

201383350 ............................ SS4355B. 

201383350 ............................ SS4400B. 

(i) Inspections 

For each MLG sliding tube, identified as 

required by paragraph (g) of this AD, having 

a part number and serial number listed in 

table 1 to paragraphs (h), (i), (k)(1), (k)(2), 

(l)(1), and (l)(2) of this AD: Within 3 months 

after the effective date of this AD, inspect 

each affected MLG axle and brake flange by 

doing a detailed visual inspection of the 

chromium plate for damage, and a 

Barkhausen noise inspection of the sliding 

tube axles for burned areas, in accordance 

with the Accomplishment Instructions of 

Messier-Bugatti-Dowty Service Bulletin 200– 

32–313, including Appendices A, B, and C, 

dated February 25, 2013 (for Model A318, 

A319, and A320 series airplanes); or MessierBugatti-Dowty Service Bulletin 201–32–62, 

including Appendices A, B, and C, dated 

February 25, 2013 (for Model A321 series 

airplanes); or Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014 (for Model A319, A320, and 

A321 series airplanes). 

(j) Corrective Action 

If, during any inspection required by 

paragraph (i) of this AD, any damage is 

detected: Before further flight, replace the 

MLG sliding tube with a serviceable tube, in 

accordance with the Accomplishment 

Instructions of Messier-Bugatti-Dowty 

Service Bulletin 200–32–313, including 

Appendices A, B, and C, dated February 25, 

2013 (for Model A318, A319, and A320 series 

airplanes); or Messier-Bugatti-Dowty Service 

Bulletin 201–32–62, including Appendices 

A, B, and C, dated February 25, 2013 (for 

Model A321 series airplanes); or Airbus 

Service Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014 (for 

Model A319, A320, and A321 series 

airplanes). 

(k) Definition of Serviceable Sliding Tube 

For the purpose of this AD, a serviceable 

sliding tube is defined in paragraphs (k)(1) 

and (k)(2) of this AD. 

(1) A sliding tube having a part number 

and serial number not listed in table 1 to 

paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 

(l)(2) of this AD. 

(2) A sliding tube having a part number 

and serial number listed in table 1 to 

paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 

(l)(2) of this AD that has passed the 

inspections required by paragraph (i) of this 

AD. 

(l) Parts Installation Prohibitions 

(1) For airplanes that have an MLG sliding 

tube installed that has a part number and 

serial number listed in table 1 to paragraphs 

(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this 

AD: After an airplane is returned to service 

following accomplishment of the actions 

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

AD, no person may install on any airplane an 

MLG sliding tube having a part number and 

serial number listed in table 1 to paragraphs 

(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this 

AD. 

(2) For airplanes that, as of the effective 

date of this AD, do not have an MLG sliding 

tube installed that has a part number and 

serial number listed in table 1 to paragraphs 

(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this 

AD: No person may install on any airplane 

an MLG sliding tube having a part number 

and serial number listed in table 1 to 

paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 

(l)(2) of 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) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(3) 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 


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Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 22943 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided the MLG remains extended 

throughout the flight. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2014–0058, dated 

March 11, 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– 

2015–0831. 

(2) For Airbus 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. 

(3) For Messier-Bugatti-Dowty service 

information identified in this AD, contact 

Messier Services Americas, Customer 

Support Center, 45360 Severn Way, Sterling, 

VA 20166 8910; phone: 703–450–8233; fax: 

703–404–1621; Internet: https://

techpubs.services/messier-dowty.com. 

(4) 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 9, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–09288 Filed 4–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0926; Directorate 

Identifier 2014–NM–121–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) 97–07–14, 

for certain Airbus Model A320–111, 

–211, and –231 airplanes. AD 97–07–14 

currently requires modification of an 

area on the front spar of the wing center 

section by installing shims and new 

fasteners to reinforce pressure floor 

fittings. Since we issued AD 97–07–14, 

we have determined the need for 

repetitive inspections on airplanes on 

which the modification of the rib flange 

on the front spar of the wing center 

section has been done. This proposed 

AD would continue to require 

modifying the rib flange on the front 

spar of the wing center section by 

installing shims and new fasteners to 

reinforce pressure floor fittings; and 

would require repetitive high frequency 

eddy current inspections for cracking of 

the radius of the rib flanges and vertical 

stiffener at frame 36, a rototest 

inspection for cracking of the fastener 

holes of the rib flanges, repair if needed, 

and adding additional airplanes to the 

applicability. We are proposing this AD 

to prevent fatigue cracking on the rib 

flange area of the front spar of the wing 

center section, which can reduce the 

structural integrity of fuselage frame 36 

and the wing center section. 

DATES: We must receive comments on 

this proposed AD by June 8, 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– 

0926; 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–2015–0926; Directorate Identifier 

2014–NM–121–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 March 27, 1997, we issued AD 97– 

07–14, Amendment 39–9988 (62 FR 

16473, April 7, 1997). AD 97–07–14 

requires modification of an area on the 

front spar of the wing center section by 

installing shims and new fasteners to 

reinforce pressure floor fittings on 

certain Airbus Model A320–111, –211 

and –231 airplanes. 

Since we issued AD 97–07–14, 

Amendment 39–9988 (62 FR 16473, 

April 7, 1997), we have determined the 

need for repetitive inspections on 

airplanes on which Airbus Modification 

20976 (modification of the rib flange on 

the front spar of the wing center section) 

was done in production, or was done 

using Airbus Service Bulletin A320–57– 

1013, dated April 12, 1989; or Airbus 

Service Bulletin A320–57–1013, 

Revision 1, dated September 29, 1992. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 


tkelley on DSK3SPTVN1PROD with PROPOSALS