Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations 33045 

have been submitted in response to the 

prior opportunities for comment 

described above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for the Embraer S.A. 

Model EMB–550 airplane. 

Installation of Rechargeable Lithium 

Batteries 

In lieu of the requirements of 

§ 25.1353(b)(1) through (b)(4) at 

Amendment 25–123, all rechargeable 

lithium batteries and battery system 

installations on the Model EMB–550 

must be designed and installed as 

follows: 

(1) Safe cell temperatures and 

pressures must be maintained during 

any foreseeable charging or discharging 

condition and during any failure of the 

charging or battery monitoring system 

not shown to be extremely remote. The 

rechargeable lithium battery installation 

must preclude explosion in the event of 

those failures. 

(2) Design of the rechargeable lithium 

batteries must preclude the occurrence 

of self-sustaining, uncontrolled 

increases in temperature or pressure. 

(3) No explosive or toxic gases 

emitted by any rechargeable lithium 

battery in normal operation, or as the 

result of any failure of the battery 

charging system, monitoring system, or 

battery installation that is not shown to 

be extremely remote, may accumulate in 

hazardous quantities within the 

airplane. 

(4) Installations of rechargeable 

lithium batteries must meet the 

requirements of 14 CFR 25.863(a) 

through (d). 

(5) No corrosive fluids or gases that 

may escape from any rechargeable 

lithium battery may damage 

surrounding structure or any adjacent 

systems, equipment, or electrical wiring 

of the airplane in such a way as to cause 

a major or more severe failure condition, 

in accordance with § 25.1309(b) and 

applicable regulatory guidance. 

(6) Each rechargeable lithium battery 

installation must have provisions to 

prevent any hazardous effect on 

structure or essential systems caused by 

the maximum amount of heat the 

battery can generate during a short 

circuit of the battery or of its individual 

cells. 

(7) Rechargeable lithium battery 

installations must have a system to 

control the charging rate of the battery 

automatically, so as to prevent battery 

overheating or overcharging, and, 

(i) A battery temperature sensing and 

over-temperature warning system with a 

means for automatically disconnecting 

the battery from its charging source in 

the event of an over-temperature 

condition, or, 

(ii) A battery failure sensing and 

warning system with a means for 

automatically disconnecting the battery 

from its charging source in the event of 

battery failure. 

(8) Any rechargeable lithium battery 

installation, the function of which is 

required for safe operation of the 

airplane, must incorporate a monitoring 

and warning feature that will provide an 

indication to the appropriate flight 

crewmembers whenever the state-ofcharge of the batteries has fallen below 

levels considered acceptable for 

dispatch of the airplane. 

(9) The Instructions for Continued 

Airworthiness required by § 25.1529 

must contain maintenance requirements 

to assure that the battery is sufficiently 

charged at appropriate intervals 

specified by the battery manufacturer 

and the equipment manufacturer that 

contain the rechargeable lithium battery 

or rechargeable lithium battery system. 

This is required to ensure that lithium 

rechargeable batteries and lithium 

rechargeable battery systems will not 

degrade below specified ampere-hour 

levels sufficient to power the aircraft 

system, for intended applications. The 

Instructions for Continued 

Airworthiness must also contain 

procedures for the maintenance of 

batteries in spares storage to prevent the 

replacement of batteries with batteries 

that have experienced degraded charge 

retention ability or other damage due to 

prolonged storage at a low state of 

charge. Replacement batteries must be 

of the same manufacturer and part 

number as approved by the FAA. 

Precautions should be included in the 

Instructions for Continued 

Airworthiness maintenance instructions 

to prevent mishandling of the 

rechargeable lithium battery and 

rechargeable lithium battery systems 

that could result in short-circuit or other 

unintentional impact damage caused by 

dropping or other destructive means 

that could result in personal injury or 

property damage. 

Note 1: The electrical wiring 

interconnection systems (EWIS) maintenance 

and inspection tasks required by § 25.1729 

must ensure that EWIS components 

associated with the batteries and battery 

systems are sufficient to detect degradation of 

any EWIS component that is designed and 

installed to support compliance with special 

conditions 1 through 8. 

Note 2: The term ‘‘sufficiently charged’’ 

means that the battery will retain enough of 

a charge, expressed in ampere-hours, to 

ensure that the battery cells will not be 

damaged. A battery cell may be damaged by 

lowering the charge below a point where 

there is a reduction in the ability to charge 

and retain a full charge. This reduction 

would be greater than the reduction that may 

result from normal operational degradation. 

Note 3: These special conditions are not 

intended to replace § 25.1353(b) at 

Amendment 25–123 in the certification basis 

of the Embraer Model EMB–550. These 

special conditions apply only to rechargeable 

lithium batteries and rechargeable lithium 

battery systems and their installations. The 

requirements of § 25.1353(b) at Amendment 

25–123 remain in effect for batteries and 

battery installations on the Embraer Model 

EMB–550 that do not use rechargeable 

lithium batteries. 

Issued in Renton, Washington, on June 2, 

2014. 

Michael Kaszycki, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–13530 Filed 6–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1031; Directorate 

Identifier 2013–NM–155–AD; Amendment 

39–17854; AD 2014–11–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and Model A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. This AD was prompted by a 

non-connection of the constant speed 

motor/generator (CSM/G) during a final 

assembly operational test. This AD 

requires a detailed inspection of the 

connector wires for connector 1XE–A of 

the generator control unit (GCU)–CSM/ 


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33046 Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations 

G for discrepancies (evidence of arcing 

or overheating damage), and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct incorrect locking of 

contacts into connector 1XE–A of the 

GCU–CSM/G, which could result in a 

loss of contact continuity and lead to 

the CSM/G not operating, which, in 

conjunction with an emergency 

electrical configuration loss of the main 

electrical system or total engine 

flameout, could adversely affect the 

airplane’s safe flight. 

DATES: This AD becomes effective July 

15, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publications listed in this 

AD as of July 15, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1031; 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. 

For service information identified in 

this AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227 1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A330– 

200, A330–200 Freighter, and A330–300 

series airplanes; and Model A340–200, 

A340–300, A340–500, and A340–600 

series airplanes. The NPRM published 

in the Federal Register on December 26, 

2013 (78 FR 78294). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0175, 

dated August 2, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During Final Assembly Line tests on an 

A330 aeroplane, the Generator Control 

Unit—Constant Speed Motor/Generator 

(GCU–CSM/G) failed the operational test. 

Investigations revealed that it is due to 

incorrect locking of some contacts (pins) into 

the GCU–CSM/G connector 1XE–A. An 

inspection of other aeroplanes confirmed this 

production quality issue. Among the 26 pins 

used in GCU–CSM/G connector 1XE–A, 6 

pins have been identified as potentially 

affected by this issue. 

A badly locked contact could result in a 

loss of continuity [non-connection] and lead 

to the non-operation of the CSM/G. 

This condition, if not detected and 

corrected, and in conjunction with either an 

emergency electrical configuration loss of 

main electrical system or total engine flame 

out, could jeopardize the aeroplane’s safe 

flight. 

To address this condition, Airbus 

developed Alert Operator Transmission 

(AOT) A24L001–13, to provide instructions 

for a one-time inspection. 

For the reasons described above, this AD 

requires a one-time [detailed] inspection of 

the potentially affected connector wires of 

GCU–CSM/G connector 1XE–A and, 

depending on [the] finding, accomplishment 

of [a related investigative action] and 

applicable corrective actions. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1031- 

0002. 

Revised Service Information 

Since the NPRM (78 FR 78294, 

December 26, 2013) was published, we 

have received Airbus Alert Operators 

Transmission A24L001–13, Revision 01, 

dated March 6, 2014. We have 

determined that this service information 

does not add any additional actions to 

those proposed in the NPRM, therefore, 

we have revised paragraph (g) of this AD 

to refer to that service information. We 

have also added a new paragraph (h) to 

this AD to provide credit for actions 

performed before the effective date of 

this AD using Airbus Alert Operators 

Transmission A24L001–13, dated July 

25, 2013, and redesignated the 

subsequent paragraphs accordingly. 

Additionally, we have added paragraph 

(k), Material Incorporated by Reference, 

to the end of this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (78 FR 78294, 

December 26, 2013) and the FAA’s 

response to that comment. 

Request To Clarify What Prompted the 

NPRM (78 FR 78294, December 26, 

2013) 

Airbus requested clarification in the 

SUMMARY section and paragraph (e) of 

the NPRM (78 FR 78294, December 26, 

2013). Airbus stated that it was not 

‘‘failure of the generator control unitconstant speed motor/generator during a 

final assembly operational test’’ that 

caused the unsafe condition, but a nonconnection of the CSM/G during an 

operational test in the final assembly 

line. Investigations revealed an incorrect 

locking of some contacts into connector 

1XE–A of the GCU–CSM/G. 

We agree to revise the SUMMARY 

section and paragraph (e) of this final 

rule to state that this AD was prompted 

by a non-connection of the CSM/G 

during a final assembly operational test. 

Changes to This Final Rule 

Paragraphs (g)(1) and (g)(2) in the 

NPRM (78 FR 78294, December 26, 

2013) have been combined into 

paragraph (g) in this final rule. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

78294, December 26, 2013) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 78294, 

December 26, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 76 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $6,460, or $85 

per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 1 work-hour and require parts 

costing up to $17,314, for a cost of up 


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Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations 33047 

to $17,399 per product. We have no way 

of determining the number of aircraft 

that might need this action. 

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 

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 that 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/ 

#!docketDetail;D=FAA-2013-1031; 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 

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. 

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 adding 

the following new airworthiness 

directive (AD): 

2014–11–04 Airbus: Amendment 39–17854. 

Docket No. FAA–2013–1031; Directorate 

Identifier 2013–NM–155–AD. 

(a) Effective Date 

This AD becomes effective July 15, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, –343 airplanes; and A340–211, –212, 

–213, –311, –312, –313, –541, and –642 

airplanes; certificated in any category; 

manufacturer serial numbers (MSNs) 1 

through 1391 inclusive, except MSNs 0925 

and 1382. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by a nonconnection of the constant speed motor/ 

generator (CSM/G) during a final assembly 

operational test. We are issuing this AD to 

detect and correct incorrect locking of 

contacts into connector 1XE–A of the 

generator control unit (GCU)–CSM/G, which 

could result in a loss of contact continuity 

and lead to the CSM/G not operating, which, 

in conjunction with an emergency electrical 

configuration loss of the main electrical 

system or total engine flameout, could 

adversely affect the airplane’s safe flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

Within 1,000 flight hours after the effective 

date of this AD: Do a detailed inspection for 

discrepancies (proper engagement and 

evidence of arcing or overheating) of the 

affected connector wires of connector 1XE– 

A of the GCU–CSM/G, in accordance with 

Airbus Alert Operators Transmission 

A24L001–13, Revision 01, dated March 6, 

2014. If any discrepancy is detected during 

the inspection, before further flight, do all 

applicable related investigative and 

corrective actions, in accordance with Airbus 

Alert Operators Transmission A24L001–13, 

Revision 01, dated March 6, 2014. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Alert 

Operators Transmission A24L001–13, dated 

July 25, 2013, which is not incorporated by 

reference in this AD. 

(i) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the Design Approval 

Holder with a State of Design Authority’s 

design organization approval, as applicable). 

You are required to ensure the product is 

airworthy before it is returned to service. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0175, dated August 2, 2013, 

for related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov/ 

#!documentDetail;D=FAA-2013-1031-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (k)(3) and (k)(4) of this AD. 

(k) 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. 


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33048 Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

A24L001–13, Revision 01, dated March 6, 

2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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. 

(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 Renton, Washington, on May 16, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–12444 Filed 6–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1088; Directorate 

Identifier 2008–NE–15–AD; Amendment 39– 

17831; AD 2008–21–07R1] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising airworthiness 

directive (AD) 2008–21–07 for certain 

Dowty Propellers model R408/6–123–F/ 

17 propellers. AD 2008–21–07 required 

initial and repetitive inspections of the 

blade bonded metallic leading edge (L/ 

E) guards for correct bonding until they 

accumulate more than 1,200 flight hours 

(FH) time-in-service. This AD requires 

the same inspection and replacement 

requirements of AD 2008–21–07. This 

AD also provides an optional 

terminating action to those 

requirements. This AD was prompted by 

updated service bulletins that identify 

terminating action to the requirements 

of AD 2008–21–07. We are issuing this 

AD to prevent the loss of the bonded 

metallic L/E guard of the propeller, 

which could result in damage to the 

propeller or to the airplane, or injury to 

personnel. 

DATES: This AD is effective July 15, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 15, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 31, 2008 (73 FR 

61346, October 16, 2008). 

ADDRESSES: For service information 

identified in this AD, contact Dowty 

Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL2 

9QN, UK; phone: 44 (0) 1452 716000; 

fax: 44 (0) 1452 716001. You may view 

this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

MA. For information on the availability 

of this material at the FAA, call 781– 

238–7125. 

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–2008– 

1088; 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 AD, the mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document 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 FURTHER INFORMATION CONTACT: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax: 781–238–7170; email: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2008–21–07, 

Amendment 39–15691 (73 FR 61346, 

October 16, 2008), (‘‘AD 2008–21–07’’). 

AD 2008–21–07 applied to the specified 

products. The NPRM published in the 

Federal Register on December 26, 2013 

(78 FR 78290). The NPRM proposed to 

continue to require the inspection and 

replacement requirements of AD 2008– 

21–07 and provide an optional 

terminating action to those 

requirements. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 78290, December 26, 2013). Since we 

issued the NPRM we received 

information that propeller blade, part 

number (P/N) 697071278–18, has not 

been implemented and that no parts 

were manufactured using this P/N. We 

removed propeller blade, P/N 

697071278–18, from this AD. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 174 

propellers installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 4 hours per propeller to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts cost 

about $352 per propeller. Based on 

these figures, we estimate the cost of 

this AD to U.S. operators is $120,408. 

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 

This AD will not have federalism 

implications under Executive Order 


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