Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 51815 

device, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–71–1028, dated March 

23, 2001. 

(2) For Configuration 02 airplanes 

identified in Airbus Service Bulletin A320– 

71–1028, dated March 23, 2001: Install a new 

hold-open device, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–71–1028, dated March 

23, 2001. 

(h) New Modifications 

Within 36 months after the effective date 

of this AD, do the actions required by 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1069, dated December 18, 2015. 

(1) Modify the left-hand and right-hand 

FCDs on engines 1 and 2. 

(2) Install a placard on the box located at 

the bottom of the 120 VU panel or at the 

bottom of the coat stowage, as applicable. 

(3) Re-identify both engine FCDs with the 

new part numbers (P/Ns), as specified in 

table 1 to paragraph (h) of this AD and table 

2 to paragraph (h) of this AD, as applicable. 

TABLE 1 TO PARAGRAPH (h) OF THIS

AD—LEFT-SIDE DOOR

Old part No. New part No. 

740–4000–501 ................ 740–4000–9501 

740–4000–503 ................ 740–4000–9503 

745–4000–501 ................ 745–4000–513 

745–4000–503 ................ 745–4000–515 

745–4000–505 ................ 745–4000–517 

TABLE 2 TO PARAGRAPH (h) OF THIS

AD—RIGHT-SIDE DOOR

Old part No. New part No. 

740–4000–502 ................ 740–4000–9502 

740–4000–504 ................ 740–4000–9504 

740–4000–506 ................ 740–4000–9506 

740–4000–508 ................ 740–4000–9508 

745–4000–502 ................ 745–4000–9502 

745–4000–504 ................ 745–4000–9504 

745–4000–506 ................ 745–4000–9506 

745–4000–508 ................ 745–4000–514 

745–4000–510 ................ 745–4000–516 

745–4000–512 ................ 745–4000–518 

(i) New Alternative Compliance 

(1) Replacing an engine FCD having a part 

number listed as ‘‘Old Part Number’’ in table 

1 to paragraph (h) of this AD or table 2 to 

paragraph (h) of this AD, as applicable, with 

a FCD having the corresponding part number 

listed as ‘‘New Part Number’’ in table 1 to 

paragraph (h) of this AD or table 2 to 

paragraph (h) of this AD, as applicable, is an 

acceptable method of compliance with the 

requirements of paragraphs (h)(1) and (h)(3) 

of this AD for that engine FCD only. 

(2) An airplane on which Airbus 

Modification 157516 has been embodied in 

production is compliant with the 

requirements of paragraph (h)(1) and (h)(3) of 

this AD, provided no engine FCD, having a 

part number identified as ‘‘Old Part Number’’ 

in table 1 to paragraph (h) of this AD or table 

2 to paragraph (h) of this AD, as applicable, 

is installed on that airplane. 

(3) An airplane on which Airbus 

Modification 157718 has been embodied in 

production is compliant with the 

requirements of paragraph (h)(2) of this AD. 

(j) New Parts Installation Limitations 

(1) For an airplane with an engine FCD 

installed having a part number identified as 

‘‘Old Part Number’’ in table 1 to paragraph 

(h) of this AD or table 2 to paragraph (h) of 

this AD, as applicable: After modification of 

that airplane as required by paragraph (h) of 

this AD, do not install an engine FCD, having 

a part number identified as ‘‘Old Part 

Number’’ in table 1 to paragraph (h) of this 

AD or table 2 to paragraph (h) of this AD, as 

applicable. 

(2) For an airplane that does not have an 

engine FCD installed having a part number 

identified as ‘‘Old Part Number’’ in table 1 

to paragraph (h) of this AD or table 2 to 

paragraph (h) of this AD, as applicable: On 

or after the effective date of this AD, do not 

install an engine FCD, having a part number 

identified as ‘‘Old Part Number’’ in table 1 

to paragraph (h) of this AD or table 2 to 

paragraph (h) of this AD, as applicable. 

(k) New Method of Compliance 

Installation on an engine of a right-hand 

and left-hand engine FCD having a part 

number approved after the effective date of 

this AD is a method of compliance with the 

requirements of paragraphs (g), (h)(1), and 

(h)(3) of this AD for that engine only, 

provided the part number is approved, and 

the installation is accomplished, in 

accordance with 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). 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (k) of this AD, 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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0053, dated 

March 14, 2016, 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– 

2016–8185. 

(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 July 26, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18492 Filed 8–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3143; Directorate 

Identifier 2015–NM–047–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(Embraer) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

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51816 Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Empresa Brasileira de 

Aeronautica S.A. (Embraer) Model 

EMB–135 airplanes and Model EMB– 

145, –145ER, –145MR, –145LR, 

–145MP, and –145EP airplanes. The 

NPRM proposed to require a detailed 

inspection for chafing on the electrical 

harness of each electrical fuel pump in 

the fuel tanks, replacement of the 

affected electrical fuel pump with a new 

or serviceable pump if necessary, and 

installation of clamps on the fuel pump 

electrical harnesses. The NPRM was 

prompted by a report of chafing found 

between the fuel pump electrical 

harness and the fuel pump tubing 

during scheduled maintenance. This 

action revises the NPRM by expanding 

the proposed applicability and revising 

the compliance time for the detailed 

inspection. We are proposing this 

supplemental NPRM (SNPRM) to detect 

and correct chafing of the fuel pump 

harnesses with other parts inside the 

fuel tank, which could present a 

potential ignition source that could 

result in a fire or fuel tank explosion. 

Since certain 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 September 19, 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 Empresa Brasileira 

de Aeronautica S.A. (Embraer), 

Technical Publications Section (PC 

060), Av. Brigadeiro Faria Lima, 2170— 

Putim—12227–901 Sa ̃o Jose dos 

Campos—SP—Brasil; telephone +55 12 

3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.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– 

3143; 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1175; 

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–2015–3143; Directorate Identifier 

2015–NM–047–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 certain Empresa Brasileira de 

Aeronautica S.A. (Embraer) Model 

EMB–135 airplanes and Model EMB– 

145, –145ER, –145MR, –145LR, 

–145MP, and –145EP airplanes. The 

NPRM published in the Federal 

Register on August 21, 2015 (80 FR 

50812) (‘‘the NPRM’’). 

Actions Since Previous NPRM was 

Issued 

Since we issued the NPRM, we have 

determined that certain airplanes were 

inadvertently omitted from the 

applicability, and the compliance time 

for the detailed inspection required by 

paragraph (h)(1) of this AD must be 

revised to ‘‘within 5,000 flight hours or 

24 months after the effective date of this 

AD, whichever occurs first.’’ 

The Ageˆncia Nacional de Aviac ̧a ̃o 

Civil (ANAC), which is the aviation 

authority for Brazil, has issued Brazilian 

Airworthiness Directive 2015–03–01, 

effective March 23, 2015 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on certain Empresa Brasileira de 

Aeronautica S.A. (Embraer) Model 

EMB–135 airplanes and Model EMB– 

145, –145ER, –145MR, –145LR, 

–145MP, and –145EP airplanes. The 

MCAI states: 

Chafing between the fuel pump electrical 

harness and fuel pump tubing was detected 

during scheduled maintenance. We are 

issuing this [Brazilian] AD to protect the fuel 

pump harnesses against chafing with other 

parts inside the fuel tank, which could 

present a potential ignition source that could 

result in a fire or fuel tank explosion. 

The required actions include a 

detailed inspection for chafing on the 

electrical harness of each electrical fuel 

pump in the fuel tanks, replacement of 

the affected electrical fuel pump with a 

new or serviceable pump if necessary, 

and installation of clamps on the fuel 

pump electrical harnesses. 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– 

3143. 

Related Service Information Under 1 

CFR Part 51 

Embraer has issued Service Bulletin 

145–28–0030, Revision 01, dated 

October 22, 2010; and Service Bulletin 

145LEG–28–0032, Revision 01, dated 

November 20, 2012. The service 

information describes procedures for a 

detailed inspection for chafing on the 

electrical harness of each electrical fuel 

pump in the fuel tanks, replacement of 

the affected electrical fuel pump with a 

new or serviceable pump if necessary, 

and installation of clamps on the fuel 

pump electrical harnesses. 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. 

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Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 51817 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comments 

received. 

Request To Clarify Airplane 

Applicability 

ExpressJet Airlines stated that the 

airplane effectivity in Embraer Service 

Bulletin 145–28–0030, Revision 01, 

dated October 22, 2010, included Model 

EMB–145XR airplanes. ExpressJet 

Airlines stated that Model EMB–145XR 

airplanes are not included in paragraph 

(c), ‘‘Applicability,’’ of the proposed AD 

(in the NPRM) and asked if this is the 

intent of the NPRM or if the Model 

EMB–145XR airplanes should be 

included. 

We agree with the commenter to 

clarify the applicability of this SNPRM. 

Although ANAC unintentionally 

omitted Model EMB–145XR airplanes 

from the applicability of its AD, the 

serial numbers corresponding to Model 

EMB–145XR airplanes are identified in 

the Embraer Service Bulletin 145–28– 

0030, Revision 01, dated October 22, 

2010. We have added Model EMB– 

145XR airplanes to the applicability of 

this SNPRM. We have coordinated this 

issue with ANAC. 

Request To Extend the Compliance 

Time 

ExpressJet requested that we revise 

the compliance time for the detailed 

inspection in the proposed AD (in the 

NPRM) to ‘‘within 5,000 flight hours or 

24 months after the effective date of this 

AD, whichever occurs first,’’ instead of 

‘‘within 2,500 flight hours or 24 months 

after the effective date of this AD, 

whichever occurs first.’’ ExpressJet 

stated that this would allow the majority 

of the airplanes to be inspected during 

a C-check interval, which would be the 

most effective time to accomplish the 

task as the fuel tanks have to be drained 

and vented for the inspection to be 

performed. ExpressJet commented that 

these limits also line up with the 

current recommendations in the service 

information. 

We agree with the commenter for the 

reasons stated previously. Data from 

Embraer confirms that increasing the 

flight hours another 2,500 flight hours is 

acceptable. We have changed this 

SNPRM accordingly. 

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. 

Costs of Compliance 

We estimate that this SNPRM affects 

731 airplanes of U.S. registry. 

We estimate that it would take about 

11 work-hours per product to comply 

with the new basic requirements of this 

SNPRM. The average labor rate is $85 

per work-hour. Required parts would 

cost about $0 per product. Based on 

these figures, we estimate the cost of 

this SNPRM on U.S. operators to be 

$683,485, or $935 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours and would require 

parts costing $11,242, for a cost of 

$11,752 per product. We have no way 

of determining the number of aircraft 

that might need this action. 

According to the manufacturer, some 

of the costs of this SNPRM 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Empresa Brasileira de Aeronautica S.A. 

(Embraer): Docket No. FAA–2015–3143; 

Directorate Identifier 2015–NM–047–AD. 

(a) Comments Due Date 

We must receive comments by September 

19, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes specified 

in paragraphs (c)(1) and (c)(2) of this AD. 

(1) Empresa Brasileira de Aeronautica S.A. 

(Embraer) Model EMB–135ER, –135KE, 

–135KL, and –135LR airplanes; and Model 

EMB–145, –145ER, –145MR, –145LR, 

–145MP, –145EP, and –145XR airplanes, 

certificated in any category, as identified in 

Embraer Service Bulletin 145–28–0030, 

Revision 01, dated October 22, 2010. 

(2) Empresa Brasileira de Aeronautica S.A. 

(Embraer) Model EMB–135BJ airplanes, 

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51818 Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 

certificated in any category, as identified in 

Embraer Service Bulletin 145LEG–28–0032, 

Revision 01, dated November 20, 2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a report of 

chafing found between the fuel pump 

electrical harness and the fuel pump tubing 

during scheduled maintenance. We are 

issuing this AD to detect and correct chafing 

of the fuel pump harnesses with other parts 

inside the fuel tank, which could present a 

potential ignition source that could result in 

a fire or fuel tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection and Corrective 

Action 

Do the actions specified in paragraphs 

(g)(1) and (g)(2) of this AD at the applicable 

times specified in paragraph (h)(1) or (h)(2) 

of this AD. 

(1) Do a detailed inspection for chafing on 

the electrical harness of each electrical fuel 

pump in the fuel tanks, in accordance with 

the Accomplishment Instructions of Embraer 

Service Bulletin 145–28–0030, Revision 01, 

dated October 22, 2010 (for Model EMB– 

135ER, –135KE, –135KL, and –135LR 

airplanes; and Model EMB–145, –145ER, 

–145MR, –145LR, –145MP, –145EP, and 

–145XR airplanes); or Embraer Service 

Bulletin 145LEG–28–0032, Revision 01, 

dated November 20, 2012 (for Model EMB– 

135BJ airplanes). If any chafing is found, 

before further flight, replace the affected 

electrical fuel pump with a new or 

serviceable pump having the same part 

number, in accordance with the 

Accomplishment Instructions of Embraer 

Service Bulletin 145–28–0030, Revision 01, 

dated October 22, 2010; or Embraer Service 

Bulletin 145LEG–28–0032, Revision 01, 

dated November 20, 2012; as applicable. 

(2) Install clamps on the fuel pump 

electrical harnesses, in accordance with the 

Accomplishment Instructions of Embraer 

Service Bulletin 145–28–0030, Revision 01, 

dated October 22, 2010 (for Model EMB– 

135ER, –135KE, –135KL, and –135LR 

airplanes; and Model EMB–145, –145ER, 

–145MR, –145LR, –145MP, –145EP, and 

–145XR airplanes); or Embraer Service 

Bulletin 145LEG–28–0032, Revision 01, 

dated November 20, 2012 (for Model EMB– 

135BJ airplanes). 

(h) Compliance Times 

(1) For Model EMB–135ER, –135KE, 

–135KL, and –135LR airplanes; and Model 

EMB–145, –145ER, –145MR, –145LR, 

–145MP, –145EP, and –145XR airplanes: Do 

the actions specified in paragraph (g) of this 

AD within 5,000 flight hours or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For Model EMB–135BJ airplanes: Do 

the actions specified in paragraph (g) of this 

AD within 4,800 flight hours or 48 months 

after the effective date of this AD, whichever 

occurs first. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Embraer Service 

Bulletin 145–28–0030, dated September 1, 

2010 (for Model EMB–135ER, –135KE, 

–135KL, and –135LR airplanes; and Model 

EMB–145, –145ER, –145MR, –145LR, 

–145MP, –145EP, and –145XR airplanes); or 

Embraer Service Bulletin 145LEG–28–0032, 

dated September 15, 2011 (for Model EMB– 

135BJ airplanes), as applicable. This service 

information is not incorporated by reference 

in 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1175; 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 Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC); or ANAC’s authorized Designee. If 

approved by the ANAC Designee, the 

approval must include the Designee’s 

authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Brazilian 

Airworthiness Directive 2015–03–01, 

effective March 23, 2015, for related 

information. This MCAI may be found in the 

AD docket on the Internet by searching for 

and locating Docket No. FAA–2015–3143. 

(2) For service information identified in 

this AD, contact Empresa Brasileira de 

Aeronautica S.A. (Embraer), Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—Brasil; telephone +55 

12 3927–5852 or +55 12 3309–0732; fax +55 

12 3927–7546; email distrib@embraer.com.br; 

Internet http://www.flyembraer.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 July 25, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18500 Filed 8–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–8184; Directorate 

Identifier 2016–NM–036–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 A300 series airplanes; 

and Airbus Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). This 

proposed AD was prompted by reports 

of cracks in certain pins in the main 

landing gear (MLG). This proposed AD 

would require repetitive detailed visual 

inspections of the pins for cracks, and 

replacing the MLG leg if necessary. We 

are proposing this AD to detect and 

correct cracking of certain pins in the 

MLG, which could result in a MLG 

collapse, and consequent damage to the 

airplane and injury to the airplane 

occupants. 

DATES: We must receive comments on 

this proposed AD by September 19, 

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: Deliver to Mail 

address above between 9 a.m. and 5 

mstockstill on DSK3G9T082PROD with PROPOSALS