55604 Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0390; Directorate 

Identifier 2014–CE–013–AD; Amendment 

39–17969; AD 2014–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

airworthiness directive (AD) 2013–22– 

20 for Embraer S.A. Model EMB–505 

airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as cracks 

beyond acceptable limits in the carbon 

discs of the left hand (LH) and right 

hand (RH) brake assemblies. We are 

issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 22, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 22, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2014– 

0390; or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

For service information identified in 

this AD, contact EMBRAER S.A., 

Phenom Maintenance Support, Avenida 

Brigadeiro Faria Lima, 2170, Sa ̃o Jose ́

dos Campos—SP, CEP: 12227–901—PO 

Box: 36/2, Brasil; telephone: (+55 12) 

3927–1000; fax: (+55 12) 3927–6600, 

ext. 1448; email: phenom.reliability@

embraer.com.br; Internet: 

http://www.embraerexecutivejets.com/ 

en-US/customer-support/Pages/ServiceCenter-Network.aspx. You may view 

this referenced service information at 

the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090; email: jim.rutherford@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to Embraer S.A. Model EMB–505 

airplanes. The NPRM was published in 

the Federal Register on June 19, 2014 

(79 FR 35099), and proposed to 

supersede AD 2013–22–20, Amendment 

39–17652 (78 FR 67018, November 8, 

2013). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. The MCAI 

states that: 

This AD was prompted by reports that 

identified additional locations where 

inspections and corrective actions on the Left 

Hand (LH) and Right Hand (RH) brake 

assemblies are needed. We are issuing this 

AD to detect cracks beyond acceptable limit 

in the carbon discs of the brake assembly, 

which may result in reduced brake capability 

and loss of brake parts in the runway. 

Since this condition may occur in other 

airplanes of the same type and affects flight 

safety, a corrective action is required. Thus, 

sufficient reason exists to request compliance 

with this AD in the indicated time limit 

without prior notice. 

The MCAI requires an inspection to 

determine if the airplane has the 

affected part number brake assembly 

installed and an inspection for cracks of 

the affected brake assembly with repair 

or replacement as necessary. The MCAI 

can be found in the AD docket on the 

Internet at: http://www.regulations.gov/ 

#!documentDetail;D=FAA-0;2014-0390- 

0001. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

35099, June 19, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD will affect 

117 products of U.S. registry. We also 

estimate that it would take about 2 

work-hours per product to comply with 

Part 1 of the inspection and 3 workhours per product to comply with Part 

2 of the inspection requirements of this 

AD. The average labor rate is $85 per 

work-hour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $19,890, or $170 per 

product for Part 1 of the inspection, and 

$29,835, or $255 per product for Part 2 

of the inspection. 

In addition, we estimate that any 

necessary follow-on actions would take 

1.5 work-hours and require parts costing 

$2,405, for a cost of $2,532.50 per 

product per side for repair or 3 workhours and require parts costing $26,177, 

for a cost of $26,432 per product per 

side for replacement. 

We have no way of determining the 

number of products that may need these 

actions. 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Rules and Regulations 55605 

Executive Order 13132. This AD will 

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 AD: 

(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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0390; 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 the NPRM, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 

removing Amendment 39–17652 (78 FR 

67018; November 8, 2013) and adding 

the following new AD: 

2014–19–01 Embraer S.A.: Amendment 39– 

17969; Docket No. FAA–2014–0390; 

Directorate Identifier 2014–CE–013–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 22, 2014. 

(b) Affected ADs 

This AD supersedes AD 2013–22–20, 

Amendment 39–17652 (78 FR 67018, 

November 8, 2013). 

(c) Applicability 

This AD applies to Embraer S.A. Models 

EMB–505 airplanes, all serial numbers, that 

are: 

(1) Equipped with a part number (P/N) 

DAP00097–01 or P/N DAP00097–02 brake 

assembly; and 

(2) certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as cracks 

beyond acceptable limits in the carbon discs 

of the left hand (LH) and right hand (RH) 

brake assemblies. We are issuing this AD to 

detect and correct cracking of the stator 

pressure plate and possible loss of brake 

parts on the runway, which could result in 

reduced brake capability and a possible 

runway excursion. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) through (f)(14) of 

this AD, including all subparagraphs. 

(1) If the number of flight cycles is 

unknown, calculate the compliance times for 

flight cycles in this AD by multiplying the 

number of hours time-in-service (TIS) on the 

brake assembly by .71 to come up with the 

number of cycles. For the purposes of this 

AD, some examples are below: 

(i) 500 hours TIS equates to 355 flight 

cycles; and 

(ii) 12 hours equates to 9 flight cycles. 

(2) Do a general visual inspection (GVI) for 

cracks in the stator pressure plate on both the 

LH and RH brake assemblies following Part 

1 of the Accomplishment Instructions in 

Embraer Phenom Service Bulletin No. 505– 

32–0011, Revision 01, dated March 31, 2014. 

Use the compliance times in paragraphs 

(f)(2)(i) and (f)(2)(ii) of this AD: 

(i) For brake assemblies with 300 flight 

cycles or less since new or since the last 

overhaul: Before or upon accumulating 150 

flight cycles after October 22, 2014 (the 

effective date of this AD) or within the next 

30 flight cycles after October 22, 2014 (the 

effective date of this AD), whichever occurs 

later, and repetitively thereafter at intervals 

not to exceed 60 flight cycles or the next tire 

change, whichever occurs first. 

(ii) For brake assemblies with more than 

300 flight cycles since new or since the last 

overhaul: Within the next 10 flight cycles 

after October 22, 2014 (the effective date of 

this AD), and repetitively thereafter at 

intervals not to exceed 60 flight cycles or the 

next tire change, whichever occurs first. 

(3) If no cracks are found during any of the 

inspections required in paragraph (f)(2) of 

this AD, continue the repetitive inspection 

intervals required in paragraph (f)(2) of this 

AD, including all subparagraphs. 

(4) If any crack is found in the stator 

pressure plate during any of the inspections 

required in paragraph (f)(2) of this AD, before 

further flight, do a detailed inspection (DET) 

following Part 1 of the Accomplishment 

Instructions in Embraer Phenom Service 

Bulletin No. 505–32–0011, Revision 01, 

dated March 31, 2014. 

(5) If no cracks beyond the acceptable 

limits are found during the DET required in 

paragraph (f)(4) of this AD, continue the 

repetitive inspection intervals required in 

paragraph (f)(2) of this AD, including all 

subparagraphs. 

(6) If cracks that exceed the acceptable 

limits are found during the DET required in 

paragraph (f)(4) of this AD, before further 

flight, repair the brake assembly following 

Appendix 2 of Embraer Phenom Service 

Bulletin No. 505–32–0011, Revision 01, 

dated March 31, 2014; or replace the brake 

assembly with a brake assembly that has been 

inspected and found free of cracks that 

exceed the acceptable limits following the 

Accomplishment Instructions of Embraer 

Phenom Service Bulletin No. 505–32–0011, 

Revision 01, dated March 31, 2014. 

Note 1 to paragraph (f)(6) of this AD: 

Appendix 2 of Embraer Phenom Service 

Bulletin No. 505–32–0011, Revision 01, 

dated March 31, 2014, consists of Meggitt 

Aircraft Braking System Service Bulletin No. 

SB–32–1625, Revision A, dated October 17, 

2013. This service bulletin is incorporated as 

pages 27 through 40 of Embraer Phenom 

Service Bulletin No. 505–32–0011, Revision 

01, dated March 31, 2014. 

(7) At the next tire change or 30 days after 

October 22, 2014 (the effective date of this 

AD), whichever occurs later, do a DET for 

cracks on the external visible surface of the 

thrust stator, double stator, and rotors 

following Part 2 of the Accomplishment 

Instructions in Embraer Phenom Service 

Bulletin No. 505–32–0011, Revision 01, 

dated March 31, 2014. 

(8) If no crack is detected or if any crack 

within the acceptable limits shown in Figure 

4 Detail G of Embraer Phenom Service 

Bulletin No. 505–32–0011, Revision 01, 

dated March 31, 2014, is detected in the 

inspection required in paragraph (f)(7) of this 

AD, repeat the inspection required by 

paragraph (f)(7) of this AD at each tire change 

or at each maintenance action that requires 

wheel removal, whichever occurs first. 

(9) If any crack within the acceptable limits 

shown in Figure 4 Detail H of Embraer 

Phenom Service Bulletin No. 505–32–0011, 

Revision 01, dated March 31, 2014, is 

detected in the inspection required in 

paragraph (f)(7) of this AD, the affected brake 

assembly must be replaced within 40 flight 

cycles. 

(10) If any crack beyond the acceptable 

limits shown in Figure 4 Detail H of Embraer 

Phenom Service Bulletin No. 505–32–0011, 

Revision 01, dated March 31, 2014, is 

detected, the affected brake assembly must be 

replaced before the next flight. 

(11) After any repair or replacement of the 

brake assembly, the brake assembly P/N 

DAP00097–01 or P/N DAP00097–02 is 

subject to the inspections required in 


asabaliauskas on DSK5VPTVN1PROD with RULES
55606 Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Rules and Regulations 

paragraphs (f)(2) through (f)(10), including all 

subparagraphs as applicable, of this AD. 

(12) For the purposes of this AD, a GVI is 

a visual examination of an interior or exterior 

area, installation or assembly, to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance, unless otherwise 

specified. A mirror may be necessary to 

enhance visual access to all exposed surfaces 

in the inspection area. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or drop-light. It may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked. 

(13) For the purposes of this AD, a DET is 

an intensive examination of a specific item, 

installation or assembly, to detect damage, 

failure, or irregularity. Available lighting is 

normally supplemented with a direct source 

of good lighting at an intensity deemed 

appropriate. Inspection aids such as mirrors, 

magnifying lenses, etc., may be necessary. 

Surface cleaning and elaborate access 

procedures may be required. 

(14) As of November 8, 2013 (the effective 

the date of AD 2013–22–20) and to October 

22, 2014 (the effective date of this AD), do 

not install on any airplane a brake assembly 

P/N DAP00097–01 or P/N DAP00097–02 

unless it is inspected per the requirements of 

AD 2013–22–20 and continues to be crack 

free or the cracks do not exceed the allowable 

limits; and as of October 22, 2014 (the 

effective date of this AD), do not install on 

any airplane a brake assembly P/N 

DAP00097–01 or P/N DAP00097–02 unless it 

is inspected per the requirements of this AD 

and continues to be crack free or the cracks 

do not exceed the allowable limits. 

(g) Credit for Actions Done Following 

Previous Service Information 

This AD provides credit for the inspections 

required in paragraphs (f)(2) and (f)(6) of this 

AD, if those actions were performed before 

October 22, 2014 (the effective date of this 

AD), using Embraer Alert Service Bulletin 

(ASB) 505–32–A011, original issue, dated 

September 13, 2013; Embraer Alert Service 

Bulletin (ASB) 505–32–A011, Revision 01, 

dated November 01, 2013; Embraer Alert 

Service Bulletin (ASB) 505–32–A011, 

Revision 02, dated December 19, 2013; or 

Embraer Phenom Service Bulletin No. 505– 

32–0011, original issue, dated February 11, 

2014. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(i) Related Information 

Refer to MCAI Ageˆncia Nacional De 

Aviac ̧a ̃o Civil (ANAC) AD No.: 2014–04–01, 

dated April 16, 2014, for related information. 

The MCAI can be found in the AD docket on 

the Internet at: http://www.regulations.gov/ 

#!documentDetail;D=FAA-2014-0390-0001. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Embraer Phenom Service Bulletin No. 

505–32–0011, Revision 01, dated March 31, 

2014. 

(ii) Reserved. 

(3) For Embraer S.A. service information 

identified in this AD, contact EMBRAER 

S.A., Phenom Maintenance Support, Avenida 

Brigadeiro Faria Lima, 2170, Sa ̃o Jose ́ dos 

Campos—SP, CEP: 12227–901—PO Box: 36/ 

2, Brasil; telephone: (+55 12) 3927–1000; fax: 

(+55 12) 3927–6600, ext. 1448; email: 

phenom.reliability@embraer.com.br; Internet: 

http://www.embraerexecutivejets.com/en-US/ 

customer-support/Pages/Service-CenterNetwork.aspx. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on 

September 8, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–21913 Filed 9–16–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 73 

[Docket No. FAA–2014–0703; Airspace 

Docket No. 13–ASO–22] 

RIN 2120–AA66 

Amendment of Restricted Areas 

R–2901A, B, G, H, J, K, L and N; Avon 

Park, FL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action makes minor 

adjustments to the latitude/longitude 

positions of two points in the 

descriptions of restricted areas R– 

2901A, B, G, H, J, K, L and N at the 

Avon Park Air Force Range, FL. The 

corrections are the result of more 

accurate digital plotting of the points. 

DATES: Effective date 0901 UTC, 

November 13, 2014. 

FOR FURTHER INFORMATION CONTACT: Paul 

Gallant, Airspace Policy and 

Regulations Group, Office of Airspace 

Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

Background 

A review of the descriptions of 

restricted areas R–2901A, B, G, H, J, K, 

L and N at the Avon Park Air Force 

Range, FL, identified the need to update 

two points common to the boundaries of 

several of the restricted areas. The 

changes are needed to fix slight 

mismatches in the descriptions of 

common boundaries between the areas. 

Because the differences are minor, they 

are not apparent on Sectional 

Aeronautical Charts, but with the 

transition to more precise digital 

charting databases, the mismatches 

require resolution. 


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