41886 Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules 

By order of the Board of Directors. 

Dated at Washington, DC, this 21st day of 

June, 2016. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2016–15096 Filed 6–27–16; 8:45 am] 

BILLING CODE 6714–01–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: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Airbus Model A318 and A319 

series airplanes, A320–211, –212, –214, 

–231, –232, and –233 airplanes, and 

A321 series airplanes. The NPRM 

proposed to require an inspection to 

identify the part number and serial 

number of the main landing gear (MLG) 

sliding tubes installed on the airplane; 

and inspection of affected chromium 

plates for damage; an inspection of 

affected sliding tube axles for damage; 

and replacement of the sliding tube if 

necessary. The NPRM was prompted by 

a report of a rupture of a MLG sliding 

tube axle. This action revises the NPRM 

by removing certain service information 

that does not adequately address the 

identified unsafe condition and revising 

the compliance method. We are 

proposing this supplemental NPRM 

(SNPRM) 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. 

Since these actions impose an 

additional burden over those proposed 

in the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this SNPRM by August 12, 2016. 

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 SNPRM, 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– 

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 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 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus Model A318 and 

A319 series airplanes, A320–211, –212, 

–214, –231, –232, and –233 airplanes, 

and A321 series airplanes. The NPRM 

published in the Federal Register on 

April 24, 2015 (80 FR 22939) (‘‘the 

NPRM’’). The NPRM was prompted by 

a report of a rupture of a MLG sliding 

tube axle. The NPRM proposed to 

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 damage, and 

replacement of the sliding tube if 

necessary. 

Actions Since Previous NPRM Was 

Issued 

Since we issued the NPRM, we have 

determined that Messier-Bugatti-Dowty 

Service Bulletin 200–32–313, dated 

February 25, 2013, including 

Appendices A, B, and C, dated February 

25, 2013; and Service Bulletin 201–32– 

62, including Appendices A, B, and C, 

dated February 25, 2013; do not 

adequately address the identified unsafe 

condition because this service 

information does not include all 

Required for Compliance steps required 

in Airbus Service Bulletin A320–32– 

1416, including Appendix 01, dated 

March 10, 2014. Therefore, this SNPRM 

proposes revising the service 

information specified for accomplishing 

the proposed actions. 

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 and A319 series airplanes, 

A320–211, –212, –214, –231, –232, and 

–233 airplanes, 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 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules 41887 

this failure was due to an abnormal grinding 

operation during overhaul by a certain 

maintenance and repair organization 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 

damage. 

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, dated March 10, 2014, 

including Appendix 01, dated March 

10, 2014. This service information 

describes procedures for inspecting 

MLG axles and brake flanges by doing 

a detailed visual inspection of the 

chromium plates for damage, and a 

Barkhausen noise inspection of the 

sliding tube axles for damage, and 

replacement of affected parts if 

necessary. 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. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comments 

received. 

Request To Revise Parts Installation 

Limitation 

American Airlines requested that we 

revise paragraphs (l)(1) and (l)(2) of the 

proposed AD (in the NPRM) to allow 

installation of serviceable MLG sliding 

tubes that have passed the inspection 

required by paragraph (i) of the 

proposed AD (in the NPRM). American 

Airlines stated that it believes that this 

is the intent of the MCAI. 

We agree with the commenter’s 

request and have revised paragraphs 

(l)(1) and (l)(2) of this proposed AD 

accordingly. 

Additional Changes to This SNPRM 

We have removed Messier-BugattiDowty Service Bulletin 200–32–313, 

including Appendices A, B, and C, 

dated February 25, 2013; and Service 

Bulletin 201–32–62, including 

Appendices A, B, and C, dated February 

25, 2013; as sources of service 

information in this SNPRM. We have 

specified Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014, as the appropriate 

source of service information for 

accomplishing the proposed actions. 

FAA’s Determination and Requirements 

of This SNPRM 

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. 

Certain changes described above 

expand the scope of the NPRM. As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

Differences Between This SNPRM and 

the MCAI or Service Information 

The effectivity in Airbus Service 

Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014, 

does not include Model A318 series 

airplanes. This SNPRM specifies using 

the procedures specified for Model 

A319 series airplanes in Airbus Service 

Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014, for 

accomplishing the proposed actions on 

Model A318 series airplanes. 

Costs of Compliance 

We estimate that this SNPRM 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 SNPRM. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of this 

SNPRM on U.S. operators to be $4,590, 

or $1,530 per product. 

In addition, we estimate that any 

necessary on-condition 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 

SNPRM. 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. 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
41888 Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules 

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 August 12, 

2016. 

(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 

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 

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

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

THIS AD—AFFECTED MLG SLIDING

TUBES—Continued 

Part No. Serial No. 

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 

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

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

THIS AD—AFFECTED MLG SLIDING

TUBES—Continued 

Part No. Serial No. 

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 

affected MLG axles and brake flanges by 

doing a detailed visual inspection of the 

chromium plates for damage, and a 

Barkhausen noise inspection of the sliding 

tube axles for damage, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1416, including 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 124 / Tuesday, June 28, 2016 / Proposed Rules 41889 

Appendix 01, dated March 10, 2014. For 

Model A318 series airplanes, use the 

procedures specified for Model A319 series 

airplanes in Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014. 

(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 Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014. For Model A318 series 

airplanes, use the procedures specified for 

Model A319 series airplanes in Airbus 

Service Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014. 

(k) Definition of Serviceable Sliding Tube 

For the purpose of this AD, a serviceable 

sliding tube is defined as a sliding tube that 

meets the criterion in either paragraph (k)(1) 

or (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 unless that sliding tube has passed the 

inspection required by paragraph (i) 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 unless that sliding tube has 

passed the inspection required by paragraph 

(i) 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 

an airworthy 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 

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) 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/

#!documentDetail;D=FAA-2015-0831-0003. 

(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 June 16, 

2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–14969 Filed 6–27–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–7418; Directorate 

Identifier 2015–NM–163–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. 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 

Bombardier, Inc. Model CL–600–2A12 

(CL–601 Variant), and CL–600–2B16 

(CL–601–3A, CL–601–3R, and CL–604 

Variants) airplanes. This proposed AD 

was prompted by a report that a 

potential chafing condition exists 

between the negative-G fuel feed drain 

line of the auxiliary power unit (APU) 

and its surrounding structure and 

components. This proposed AD would 

require, for certain airplanes, a detailed 

inspection for chafing conditions of the 

negative-G fuel feed drain line of the 

APU, and corrective actions if 

necessary. For certain other airplanes, 

this proposed AD would require 

replacement of the APU negative-G fuel 

feed tube assembly and the drain line. 

We are proposing this AD to prevent a 

chafing condition in the negative-G fuel 

feed drain line, which can result in fuel 

leaking from the drain line. Leakage of 

the negative-G fuel feed drain line is a 

dormant failure. This condition, in 

combination with a nearby hot surface 

or other potential ignition source, could 

result in an uncontrolled fire in the aft 

equipment bay. 

DATES: We must receive comments on 

this proposed AD by August 12, 2016. 

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– 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS