Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41095 

(1) All Model 707–100 long body, –200, 

–100B long body, and –100B short body 

series airplanes; and Model 707–300, –300B, 

–300C, and –400 series airplanes. 

(2) All Model 720 and 720B series 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

scribe-line-related fatigue cracks on Model 

727 airplanes, which are similar in design to 

the Model 707 airplanes, and Model 720 and 

720B series airplanes. We are issuing this AD 

to detect and correct scribe lines, which can 

develop into fatigue cracks in the skin and 

cause rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Scribe Line Inspection 

(1) Except as specified in paragraphs (j)(1) 

and (j)(2) of this AD, at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing 707 Alert Service Bulletin A3539, 

dated April 26, 2013: Do a detailed 

inspection of the fuselage skin for scribe 

lines, in accordance with the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013. If no scribe line is found: Before further 

flight, do surface finish restoration, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3539, dated April 26, 2013. 

(2) The inspection exceptions described in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, apply to paragraph (g)(1) of this AD. 

(h) Related Investigative and Corrective 

Actions 

If any scribe line is found during any 

inspection required by paragraph (g)(1) of 

this AD: At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, except as specified in paragraphs (j)(1) 

and (j)(2) of this AD, do all applicable related 

investigative and corrective actions, by doing 

all applicable actions specified in the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, except as specified in paragraph (j)(3) 

of this AD. 

(i) Surface Finish Restoration 

After completing any actions required by 

paragraph (h) of this AD: Before further 

flight, do surface finish restoration, in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3539, dated April 26, 2013. 

(j) Exceptions to Paragraphs (g) and (h) of 

this AD 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing 707 Alert Service Bulletin A3539, 

dated April 26, 2013, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where the Condition column of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3539, dated April 26, 

2013, refers to total flight cycles ‘‘as of the 

original issue date of this service bulletin,’’ 

this AD applies to the airplanes with the 

specified total flight cycles as of the effective 

date of this AD. 

(3) Where Boeing 707 Alert Service 

Bulletin A3539, dated April 26, 2013, 

specifies to contact Boeing for additional 

inspections or repair instructions: Before 

further flight, repair the scribe line or 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCREQUESTS@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

For more information about this AD, 

contact Chandraduth Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Boulevard, 

Suite 100, Lakewood, CA 90712–4137, 

phone: 562–627–5239; fax: 562–627–5210; 

email: chandraduth.ramdoss@faa.gov. 

(m) 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) Boeing 707 Alert Service Bulletin 

A3539, dated April 26, 2013. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at 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 June 24, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–15507 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0440; Directorate 

Identifier 2013–SW–075–AD; Amendment 

39–17885; AD 2014–13–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH (Type 

Certificate Previously Held by 

Eurocopter Deutschland GmbH 

Helicopters) (AHD) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for AHD 

Model EC135P1, P2, P2+, T1, T2, and 

T2+ helicopters. This AD requires 

repetitive visual inspections of the ring 

frame X9227 for a crack and, if there is 

a crack, replacing the ring frame before 

further flight. This AD is prompted by 

a fatigue crack in the ring frame. These 

actions are intended to detect a crack in 

the ring frame and prevent loss of the 

tail rotor and subsequent loss of control 

of the helicopter. 

DATES: This AD becomes effective July 

30, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 30, 2014. 

We must receive comments on this 

AD by September 15, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 


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41096 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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, the European 

Aviation Safety Agency (EASA) AD, the 

economic evaluation, any incorporated 

by reference service information, any 

comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this AD, contact Airbus Helicopters, 

Inc., 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641– 

0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

We are adopting a new AD for AHD 

Model EC135P1, P2, P2+, T1, T2, and 

T2+ helicopters with certain mounting 

ring frames installed. This AD requires 

repetitive visual inspections of the ring 

frame X9227 for a crack and, if there is 

a crack, replacing the ring frame with an 

airworthy part before further flight. 

These actions are intended to detect a 

crack in the ring frame and prevent loss 

of tail rotor and subsequent loss of 

control of the helicopter. 

This AD was prompted by AD No. 

2013–0289–E, dated December 6, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for AHD Model EC135P1, 

EC135P2, EC135P2+, EC135T1, 

EC135T2, EC135T2+, EC635P2+, 

EC635T1, and EC635T2+ helicopters 

equipped with mounting ring frame 

X9227, part number (P/N) 

L535H2120301, P/N L535H2120303, or 

P/N L535H2120304 without frame 

reinforcement. EASA advises that ring 

frames X9227 with frame reinforcement 

P/N L535H2100201 are not affected by 

its AD. EASA advises that the fuselage 

tail boom structure of the EC135/EC635 

type design is connected to the tail rotor 

‘‘fenestron’’ housing by means of a ring 

frame attached by two rivet rows each. 

EASA states that during a recent post 

flight check, the pilot detected a crack 

that ran along three rivets across the 

ring frame. According to EASA, this 

condition if not corrected would 

gradually reduce the structural integrity 

of the tail boom fenestron attachment, 

potentially resulting in detachment of 

the fenestron and loss of the helicopter. 

To address this condition, EASA AD 

No. 2013–0289–E requires repetitive 

visual inspections of the ring frame 

X9227. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Eurocopter issued Safety Information 

Notice No. 2636–S–53, dated October 

10, 2013, alerting operators that during 

a post-flight check a pilot discovered a 

crack at the rear ring frame between the 

rear structure tube and the fenestron 

box. The Notice reminds operators to 

conduct the dedicated visual ring frame 

check according to the flight manual’s 

pre-flight check so any cracked ring 

frames will be immediately discovered. 

Eurocopter also issued Alert Service 

Bulletin ASB EC 135–53A–029, 

Revision 0, dated November 19, 2013 

(ASB). The ASB specifies, every 50 

flight hours, visually inspecting ring 

frame X9227 for a crack in addition to 

the visual pre-flight check of the ring 

frame. The ASB states that a crack 

within the ring frame and between the 

rivet heads is not permissible, and if 

detected in this area, AHD must be 

contacted before further flight. 

AD Requirements 

This AD requires, on or before 

reaching 100 hours TIS, or within 50 

hours TIS for helicopters with more 

than 100 hours TIS, and thereafter at 

intervals not to exceed 50 hours TIS, 

using a 10X or higher power magnifying 

glass and a light, visually inspecting the 

ring frame X9227 for a crack between 

the rivets. If a crack is found, this AD 

requires, before further flight, replacing 

the ring frame X9227 with an airworthy 

part. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to EC635P2+, 

EC635T1, and EC635T2+ helicopters, 

and this AD does not because those 

helicopters are non-FAA type 

certificated. The EASA AD requires 

contacting the manufacturer if a crack is 

found in the ring frame. This AD 

requires replacing the ring frame if a 

crack is found. 

Costs of Compliance 

We estimate that this AD will affect 

275 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. Labor costs are estimated 

at $85 per work hour. We estimate 0.2 


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41097 

work hour to do the inspection for a 

total estimated cost of $17 per 

helicopter and $4,675 for the U.S. fleet 

per inspection cycle. Replacing a ring 

frame will require 5 work hours and 

$18,500 for parts for a total cost of 

$18,925 per helicopter. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments before adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment before adopting this rule 

because the required corrective actions 

in a structural critical area must be done 

within 50 hours TIS, a very short time 

period based on the average flight-hour 

utilization rate for air ambulance and 

law enforcement operations of these 

helicopters. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

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, 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): 

2014–13–09 Airbus Helicopters 

Deutschland GmbH (Type Certificate 

Previously Held by Eurocopter 

Deutschland GmbH): Amendment 39– 

17885; Docket No. FAA–2014–0440; 

Directorate Identifier 2013–SW–075–AD. 

(a) Applicability 

This AD applies to Model EC135P1, P2, 

P2+, T1, T2, and T2+ helicopters with 

mounting ring frame X9227, part number 

(P/N) L535H2120301, P/N L535H2120303, or 

P/N L535H2120304, installed, except those 

with frame reinforcement P/N L535H2100201 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

fatigue crack in a ring frame. This condition 

could result in loss of a tail rotor and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective July 30, 2014. 

(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 

(1) On or before 100 hours time-in-service 

(TIS), or within 50 hours TIS for helicopters 

with more than 100 hours TIS, and thereafter 

at intervals not to exceed 50 hours TIS, using 

a 10X or higher power magnifying glass and 

a light, visually inspect the ring frame X9227 

for a crack between the rivets as shown in 

Figure 2 of Eurocopter Alert Service Bulletin 

ASB EC135–53A–029, Revision 0, dated 

November 19, 2013. Paint cracks are 

permissible. 

(2) If there is a crack, before further flight, 

replace the ring frame X9227 with an 

airworthy part. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@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. 

(h) Additional Information 

(1) Eurocopter Safety Information Notice 

No. 2636–S–53, Revision 0, dated October 10, 

2013, which is not incorporated by reference, 

contains additional information about the 

subject of this AD. You may review a copy 

of the service information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2013–0289–E, dated December 6, 2013. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2014–0440. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302 Tail Rotor. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Eurocopter Alert Service Bulletin ASB 

EC135–53A–029, Revision 0, dated 

November 19, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus Helicopters, Inc., 

2701 N. Forum Drive, Grand Prairie, TX 


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75052; telephone (972) 641–0000 or (800) 

232–0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

(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 June 25, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15527 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0973; Directorate 

Identifier 2013–NM–139–AD; Amendment 

39–17893; AD 2014–13–17] 

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 all 

Airbus Model A300 series airplanes; 

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); and Model 

A310 series airplanes. This AD was 

prompted by reports of failures of the 

right inner tank fuel pump. This AD 

requires repetitive functional tests of the 

circuit breakers for the fuel pump power 

supply, and replacement of certain 

circuit breakers. We are issuing this AD 

to detect and correct failure of the 

circuit breakers for the fuel pump power 

supply, which could result in a fuel 

pump overheating, leading to a fuel tank 

explosion. 

DATES: This AD becomes effective 

August 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 19, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0973; 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—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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 all Airbus Model A300 series 

airplanes; 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); and Model 

A310 series airplanes. The NPRM 

published in the Federal Register on 

November 22, 2013 (78 FR 70003). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0163, 

dated July 24, 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: 

Two successive failures have been reported 

of a Right Hand #1 inner tank fuel pump, Part 

Number 2052Cxx series (with placeholder 

‘‘xx’’ indicating numerals). The fix consisted 

in the replacement of the pump, the 

associated circuit breaker and the AC 

[alternating current] bus load relay. 

Investigations determined that, in case of 

loss of one phase on the pump supply and 

the associated circuit breaker failing to trip, 

the fuel pump thermal fuses may not operate 

as quickly as expected. 

This condition, if not detected and 

corrected, would result in an overheat 

condition of the fuel pump in excess of 

200 °C and could lead to a fuel tank 

explosion. 

To address this potential unsafe condition, 

Airbus issued Alert Operator Transmission 

(AOT) A28W002–13 providing instructions 

for a functional test of circuit breakers and 

corrective action. 

For the reasons described above, as a 

temporary measure until further notice, this 

[EASA] AD mandates functional tests of the 

affected fuel pump power supply circuit 

breakers, and, depending on findings, 

replacement of circuit breakers. 

This [EASA] AD will be followed by 

further [EASA] AD action. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0973- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 70003, November 22, 2013) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (78 FR 70003, November 

22, 2013), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 


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