65180 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and 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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2013–22–01 Bell Helicopter Textron 

Canada: Amendment 39–17633; Docket 

No. FAA–2013–0526; Directorate 

Identifier 2008–SW–14–AD. 

(a) Applicability 

This AD applies to Model 206L–4 and 407 

helicopters, with a freewheel aft bearing cap 

(cap), part number (P/N) 406–040–509–101, 

with a serial number with a prefix of ‘‘A-’’ 

and Nos. 1833 through 1912, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

certain caps being manufactured without a 

lubrication channel to allow oil flow into the 

aft bearing support assembly, which could 

result in failure of the freewheel unit and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective December 5, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 50 hours time-in-service (TIS): 

(1) Remove and disassemble each 

freewheel assembly. 

(2) Replace the sprag and retainer (item 7), 

the output shaft (item 10), and the aft seal 

(item 3), as depicted in Figure 2 of Bell Alert 

Service Bulletin (ASB) No. 206L–04–129 for 

the Model 206L–4 and ASB No. 407–04–66 

for the Model 407, both Revision A, and both 

dated December 1, 2004. 

(3) Visually inspect the remaining 

freewheel part details for a missing channel. 

(4) If the channel is missing, replace or 

rework the cap assembly by following the 

instructions depicted in Figure 3 of ASB 

206L–04–129 or ASB 407 04–66, as 

applicable for your model helicopter. Using 

a vibrating stylus, mark the letter ‘‘R’’ at the 

end of the serial number on the cap 

assembly. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Eric Haight, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Regulations and Policy Group, 

Fort Worth, Texas 76137, telephone (817) 

222–5110, email: eric.haight@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2004–17R1, dated February 11, 2005. 

You may view the TCCA AD at http://

www.regulations.gov in Docket No. FAA– 

2013–0526. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300: Main Rotor Drive System. 

(i) 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) Bell Alert Service Bulletin (ASB) No. 

206L–04–129, Revision A, dated December 1, 

2004. 

(ii) Bell ASB No. 407–04–66, Revision A, 

dated December 1, 2004. 

(3) For Bell service information identified 

in this AD, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, Texas 76101, 

telephone (817) 280–3391, fax (817) 280– 

6466. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on October 1, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–25310 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0401; Directorate 

Identifier 2012–SW–047–AD; Amendment 

39–17606; AD 2013–19–24] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc., Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2003–08– 

51 for MD Helicopters, Inc. (MDHI), 

Model 369A, 369D, 369E, 369H, 369HE, 

369HM, 369HS, 369F and 369FF 

helicopters with certain MDHI or 

Helicopter Technology Company (HTC) 

tail rotor blades installed. AD 2003–08– 

51 required reducing the retirement life 

of each tail rotor blade (blade), 

performing a one-time visual inspection 

of each blade’s pitch horn (pitch horn) 

for a crack or corrosion, and replacing 

any cracked blade or any blade that has 

exceeded its retirement life with an 


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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65181 

airworthy blade. AD 2003–08–51 also 

required reporting information to the 

FAA within 24 hours following the onetime inspection. Since we issued AD 

2003–08–51, an accident in England 

prompted an investigation that showed 

corrosion on the blade’s pitch horn that 

had not been detected under the paint. 

This new AD retains some of the 

requirements of AD 2003–08–51 and 

also requires paint removal for all pitch 

horn inspections, inspecting for pitting 

and the shot peen surface’s condition in 

addition to cracks and corrosion, and 

adds certain part-numbered blades to 

the applicability. These actions are 

intended to prevent a pitch horn from 

cracking, leading to vibration, loss of 

tail rotor pitch control, and subsequent 

loss of tail rotor and helicopter control. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact MD 

Helicopters, Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, AZ 85215– 

9734; telephone 1–800–388–3378; fax 

480–346–6813; email 

serviceengineering@mdhelicopters.com; 

Web site http://www.mdhelicopters.com 

or contact Helicopter Technology 

Company, 12923 South Spring Street, 

Los Angeles, CA 90061; telephone 310– 

523–2750; email gburdorf@

helicoptertech.com; Web site 

www.helicoptertech.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Fred 

Guerin, Aviation Safety Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 

3960 Paramount Blvd., Lakewood, 

California 90712; telephone (562) 627– 

5232; email fred.guerin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 13, 2013, at 78 FR 27867, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

removing AD No. 2003–08–51 (68 FR 

39449, July 2, 2003; corrected 68 FR 

47447, August 11, 2003) and by adding 

an AD that would apply to MDHI Model 

369A, 369D, 369E, 369H, 369HE, 

369HM, 369HS, 369F and 369FF 

helicopters with a tail rotor blade 

(blade) part number (P/N) 369D21640– 

501, 369D21640–503, 369D21641–501, 

369D21641–503, 369D21642–501, 

369D21642–503, 369D21643–501, or 

369D21643–503 installed, or with an 

HTC blade P/N 500P3100–101, 

500P3100–301, 500P3300–501, or 

500P3500–701 installed. AD No. 2003– 

08–51 required reducing the retirement 

life of the blade, performing a one-time 

visual inspection of each pitch horn for 

a crack or corrosion, and replacing any 

cracked blade or any blade that has 

exceeded its retirement life. AD No. 

2003–08–51 was prompted by two 

reports of cracked pitch horns that 

failed during flight. The cracks 

developed before the blades reached 

their retirement lives. 

Actions Since AD 2003–08–51 Was 

Issued 

Since we published AD No. 2003–08– 

51, investigation of an accident in 

England found corrosion on the pitch 

horn that was not detected under the 

paint. The corrosion compromised the 

shot peen surface, which caused 

premature fatigue failure. 

As a result, the NPRM (78 FR 27867, 

May 13, 2013) proposed to require 

establishing a retirement life for new 

applicable blades of 400 hours time-inservice (TIS), replacing within 10 hours 

TIS any installed blades with 390 to 700 

hours TIS, and replacing before further 

flight any blades with more than 700 

hours TIS. Within 60 days and 

thereafter at intervals not to exceed one 

year, the NPRM proposed to inspect all 

other blades with a 10X or higher power 

magnifying glass for a crack, pitting, 

corrosion, and the condition of the 

dimpled shot peen surface. If there is a 

crack, pitting, corrosion, or a 

nonconforming shot peen surface, the 

NPRM proposed to require replacement 

of the blade with an airworthy blade. 

The proposed requirements were 

intended to prevent a pitch horn from 

cracking and separating from the blade, 

leading to an unbalanced condition, 

vibration, loss of tail rotor pitch control, 

and loss of directional control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 27867, May 13, 2013). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

We reviewed MDHI Service Bulletins 

SB369D–210, SB369E–105, SB369F– 

091, and SB369H–252, all dated 

November 21, 2011, and HTC 

Mandatory Service Bulletin No. 3100–5, 

dated August 25, 2011 (service 

bulletins). The service bulletins specify 

removing the paint from the pitch horn, 

performing an inspection of the blade 

using a 10x magnifying glass and a 

bright light, repainting the pitch horn 

area, and repeating the inspection 

annually. The service bulletins state that 

no corrosion, pitting, or cracking is 

acceptable. The MDHI service bulletins 

adds that a lack, removal, or blending of 

the shot peen surface is unacceptable. 

Costs of Compliance 

We estimate that this AD will affect 

827 helicopters of U.S. Registry and that 

labor costs will average $85 a workhour. Based on these estimates, we 

expect the following costs: 

• The inspection will require 4.5 

work hours, and parts will cost $20 for 

a total cost of about $403 per helicopter 

and $333,281 for the U.S. fleet. 

• Replacing a tail rotor blade, if 

needed, would require 1 work hour. 

Parts would cost $15,951, for a total cost 

of $16,036 per helicopter. 

• The cost is negligible to revise the 

Airworthiness Limitations section of the 

maintenance manual to reflect a blade’s 

new retirement life. 

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 


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65182 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

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 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 Airworthiness Directive (AD) 

2003–08–51, Amendment 39–13215 (68 

FR 39449, August 11, 2003; correction 

68 FR 47447, August 11, 2003), and 

adding the following new (AD): 

2013–19–24 MD Helicopters, Inc.:

Amendment 39–17606; Docket No. 

FAA–2013–0401; Directorate Identifier 

2012–SW–047–AD. 

(a) Applicability 

This AD applies to MD Helicopters, Inc. 

(MDHI), Model 369A, 369D, 369E, 369H, 

369HE, 369HM, 369HS, 369F and 369FF 

helicopters with a tail rotor blade (blade) part 

number (P/N) 369D21640–501, 369D21640– 

503, 369D21641–501, 369D21641–503, 

369D21642–501, 369D21642–503, 

369D21643–501, or 369D21643–503 

installed, or with a Helicopter Technology 

Company blade P/N 500P3100–101, 

500P3100–301, 500P3300–501, or 500P3500– 

701 installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the tail rotor blade pitch horn (pitch horn) 

separating from the tail rotor blade, leading 

to an unbalanced condition, vibration, loss of 

tail rotor pitch control and loss of directional 

control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD No. 2003–08–51, 

Amendment 39–13215 (68 FR 39449, July 2, 

2003; correction 68 FR 47447, August 11, 

2003). 

(d) Effective Date 

This AD becomes effective December 5, 

2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Before further flight, for each applicable 

blade, revise the Airworthiness Limitations 

section of the maintenance manual to reflect 

that the blade has a retirement life of 400 

hours time-in-service (TIS). 

(2) For helicopters with an applicable 

blade installed that has 390 through 700 

hours TIS, within 10 hours TIS, replace the 

blade with an airworthy blade. 

(3) For all other applicable helicopters, 

within 60 days, and thereafter at intervals not 

to exceed one year, remove the paint from the 

blade pitch control arm in accordance with 

the Accomplishment Instructions, Section 

2.A.(1) through 2.A.(3), of MDHI Service 

Bulletins SB369D–210, SB369E–105, 

SB369F–091, and SB369H–252, all dated 

November 21, 2011, as applicable to your 

model helicopter. 

(i) Using a 10X or higher power magnifying 

glass, inspect all four sides and the pocket of 

the blade pitch control arm for a crack, 

pitting, or corrosion and for the condition of 

the dimpled shot peen surface by referring to 

Figure 1 of MDHI Service Bulletins SB369D– 

210, SB369E–105, SB369F–091, and 

SB369H–252, as applicable to your model 

helicopter, and by reviewing the rotorcraft 

maintenance records to determine whether 

rework was done in this area. 

(ii) If there is pitting, corrosion, a crack, 

blending or removal of any of the dimpled 

shot peen surface, or any indication that the 

shot peen has not been done, replace the 

blade with an airworthy blade. 

(iii) If there is no pitting, corrosion, cracks, 

or blending or removal of any of the dimpled 

shot peen surface, refinish the stripped pitch 

control arm in accordance with the 

Accomplishment Instructions, Section 

2.A.(6) through 2.A.(7), of MDHI Service 

Bulletins SB369D–210, SB369E–105, 

SB369F–091, and SB369H–252, as applicable 

to your model helicopter. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Fred Guerin, Aviation Safety Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 3960 

Paramount Blvd., Lakewood, California 

90712; telephone (562) 627–5232; email 

fred.guerin@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(3) AMOCs approved previously in 

accordance with AD No. 2003–08–51 (68 FR 

39449, July 2, 2003; correction 68 FR 47447, 

August 11, 2003) are approved as AMOCs for 

the corresponding requirements in this AD. 

(h) Additional Information 

MD Helicopters, Inc., maintenance 

manuals CSP–HMI2, TR12–001, CHP–H–4, 

and TR12–001, which are not incorporated 

by reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

MD Helicopters, Inc., Attn: Customer 

Support Division, 4555 E. McDowell Rd., 

Mail Stop M615, Mesa, AZ 85215–9734; 

telephone 1–800–388–3378; fax 480–346– 

6813; email serviceengineering@

mdhelicopters.com; Web site http://

www.mdhelicopters.com or contact 

Helicopter Technology Company, 12923 

South Spring Street, Los Angeles, CA 90061; 

telephone 310–523–2750; email gburdorf@

helicoptertech.com; Web site 

www.helicoptertech.com. You may review a 

copy of this information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail Rotor Blades. 

(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) MD Helicopters Service Bulletin 

SB369D–210, dated November 21, 2011. 

(ii) MD Helicopters Service Bulletin 

SB369E–105, dated November 21, 2011. 

(iii) MD Helicopters Service Bulletin 

SB369F–091, dated November 21, 2011. 


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(iv) MD Helicopters Service Bulletin 

SB369H–252, dated November 21, 2011. 

Note 1 to paragraph (j)(2): MD Helicopters 

Service Bulletins SB369D–210, SB369E–105, 

SB369F–091, and SB369H–252, all dated 

November 21, 2011, are co-published as one 

document. 

(3) For MD Helicopters service information 

identified in this AD, contact MD 

Helicopters, Inc., Attn: Customer Support 

Division, 4555 E. McDowell Rd., Mail Stop 

M615, Mesa, AZ 85215–9734; telephone 1– 

800–388–3378; fax 480–346–6813; email 

serviceengineering@mdhelicopters.com; Web 

site http://www.mdhelicopters.com. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may also 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 Fort Worth, Texas, on September 

18, 2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–24039 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0624; Directorate 

Identifier 2013–NM–071–AD; Amendment 

39–17632; AD 2013–21–08] 

RIN 2120–AA64 

Airworthiness Directives; ATR—GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

ATR—GIE Avions de Transport 

Re ́gional Model ATR72–101, –201, 

–102, –202, –211, –212, and –212A 

airplanes. This AD was prompted by 

reports of airplane incidents and 

accidents that have occurred because of 

low-level fuel tank situations and fuel 

starvation that resulted in engine 

flameouts. This AD requires installing a 

fuel quantity indicator (FQI) equipped 

with a locking adaptor on the electrical 

connector. We are issuing this AD to 

prevent an engine flame-out, which 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

December 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 5, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0624 or in 

person at the 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 ATR—GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre 

Nadot, 31712 Blagnac Cedex, France; 

telephone +33 (0) 5 62 21 62 21; fax +33 

(0) 5 62 21 67 18; email 

continued.airworthiness@atr.fr; Internet 

http://www.aerochain.com. You may 

review 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1137; 

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 the specified products. The 

NPRM published in the Federal 

Register on July 18, 2013 (78 FR 42898). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0047, 

dated March 4, 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: 

Large aeroplane incidents and accidents 

have occurred because of fuel tank low level 

situations, or because of fuel starvation, 

resulting in one or several engine(s) flameout. The results of the investigation into an 

ATR 72 accident in August 2005 have shown 

that overruling standard operational 

procedures and maintenance practices have 

led to this kind of occurrence. 

Consequently, additional actions to help 

avoid maintenance errors, like installation of 

a wrong gauge or wrong indicator, need to be 

taken. 

Although it is recognised that the fuel 

(indicating) system of the ATR 42/72 type 

design is compliant with the applicable 

requirements, the risk of other maintenance 

errors will be mitigated by making 

installation of an ATR 42 Fuel Quantity 

Indicator (FQI) on an ATR 72 aeroplane 

mechanically impossible through a specific 

design change on the ATR 72. 

For the reasons described above, this 

[EASA] AD requires modification of the ATR 

72 FQI by installing a locking adaptor on the 

electrical connector. You may obtain further 

information by examining the MCAI in the 

AD docket. 

We are issuing this AD to prevent an 

engine flame-out, which could result in 

reduced controllability of the airplane. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0624- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 42898, July 18, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this 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 (78 FR 

42898, July 18, 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 42898, 

July 18, 2013). 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects 25 products 

of U.S. registry. We also estimate that it 

takes 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts would 

cost about $3,882 per product. Where 

the service information lists required 

parts costs that are covered under 

warranty, we have assumed that there 

will be no charge for these parts. As we 

do not control warranty coverage for 

affected parties, some parties may incur 

costs higher than estimated here. Based 

on these figures, we estimate the cost of 


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