41098 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

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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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41099 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (78 FR 70003, November 22, 

2013) about these proposed changes. 

However, a comment was provided for 

another NPRM, Directorate Identifier 

2012–NM–101–AD (78 FR 78285, 

December 26, 2013). The commenter 

stated the following: ‘‘The proposed 

wording, being specific to repairs, 

eliminates the interpretation that Airbus 

messages are acceptable for approving 

minor deviations (corrective actions) 

needed during accomplishment of an 

AD mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this AD to obtain 

corrective actions from a manufacturer, 

the action must be accomplished using 

a method approved by the FAA, the 

European Aviation Safety Agency 

(EASA), or Airbus’s EASA DOA. Where 

necessary throughout this AD, we also 

replaced any reference to approvals of 

corrective actions with a reference to the 

Contacting the Manufacturer paragraph. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

discussed previously, Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), pointed out 

that in many cases the foreign 

manufacturer’s service bulletin and the 

foreign authority’s MCAI might have 

been issued some time before the FAA 

AD. Therefore, the DOA might have 

provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. We also 

have decided not to include a generic 

reference to either the ‘‘delegated agent’’ 

or ‘‘DAH with State of Design Authority 

design organization approval,’’ but 

instead we have provided the specific 

delegation approval granted by the State 

of Design Authority for the DAH in the 

Contacting the Manufacturer paragraph 

of this AD. 

Conclusion 

We reviewed the relevant data 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 

70003, November 22, 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 70003, 

November 22, 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 156 

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 $85 per test, or 

$13,260 per test for U.S.-registered 

airplanes. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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 


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41100 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

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-2013-0973; 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): 

2014–13–17 Airbus: Amendment 39–17893. 

Docket No. FAA–2013–0973; Directorate 

Identifier 2013–NM–139–AD. 

(a) Effective Date 

This AD becomes effective August 19, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1), (c)(2), (c)(3), 

(c)(4), (c)(5), and (c)(6) of this AD; certificated 

in any category; all serial numbers. 

(1) Model A300 B2–1A, B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Model A300 B4–601, B4–603, B4–620, 

and B4–622 airplanes. 

(3) Model A300 B4–605R and B4–622R 

airplanes. 

(4) Model A300 F4–605R and F4–622R 

airplanes. 

(5) Model A300 C4–605R Variant F 

airplanes. 

(6) Model A310–203, –204, –221, –222, 

–304, –322, –324, and –325 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by reports of 

failures of the right inner tank fuel pump. 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. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Functional Tests of Circuit 

Breakers 

(1) Within 6 months or 500 flight hours 

after the effective date of this AD, whichever 

occurs first: Do a functional test of the circuit 

breakers for the fuel pump power supply, as 

identified in paragraphs (g)(1)(i), (g)(1)(ii), 

and (g)(1)(iii) of this AD, as applicable, in 

accordance with Airbus Alert Operators 

Transmission A28W002–13, dated July 23, 

2013. Repeat the functional test thereafter at 

intervals not to exceed 6 months or 500 flight 

hours, whichever occurs first. 

(i) For Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, and B2–203 airplanes: Inner and 

outer pump, No. 1 and No. 2 left-hand (LH) 

side and right-hand (RH) side. 

(ii) For Airbus Model A300 B4–2C, B4– 

103, B4–203, B4–601, B4–603, B4–620, and 

B4–622 airplanes; and A310–203, –204, –221, 

and –222 airplanes: 

(A) Inner and outer pump, No. 1 and No. 

2, LH and RH; and 

(B) Center pump, LH and RH. 

(iii) For Airbus Model A300 B4–605R, B4– 

622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes; and Model A310–304, 

–322, –324, and –325 airplanes: 

(A) Inner and outer pump, No. 1 and No. 

2, LH and RH; 

(B) Center pump, LH and RH; and 

(C) Trim tank pump No. 1 and No. 2. 

(2) If, during any functional test required 

by paragraph (g)(1) of this AD, any circuit 

breaker fails any functional test, or any 

circuit breaker is found to be stuck closed, 

before further flight, replace the affected 

circuit breaker with a serviceable part, in 

accordance with Airbus Alert Operators 

Transmission A28W002–13, dated July 23, 

2013. 

(3) The replacement of one or more circuit 

breakers as required by paragraph (g)(2) of 

this AD does not terminate the repetitive 

functional tests required by paragraph (g)(1) 

of this AD. 

(h) 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: 

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. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0163, dated July 24, 2013, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov/#!document

Detail;D=FAA-2013-0973-0002. 

(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 this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

A28W002–13, dated July 23, 2013. 

(ii) Reserved. 

(3) 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. 


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41101 

(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 June 25, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–15800 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–2013–0867; Directorate 

Identifier 2013–NM–115–AD; Amendment 

39–17853; AD 2014–11–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200, 

–200LR, –300, and –300ER series 

airplanes. This AD was prompted by 

reports of severe corrosion on bonding 

jumpers installed on the flight control 

surfaces. This AD requires repetitive 

bonding jumper inspections for 

corrosion, sealant disbond, and 

insufficient sealant coverage; and 

corrective actions if necessary. This AD 

also specifies an optional inspection for 

corrosion damage of the bonding 

brackets, and corrective actions if 

necessary, which would terminate the 

repetitive inspections. For certain 

airplanes, this AD requires installing 

certain bonding jumpers, and replacing 

single-tabbed brackets with two-tabbed 

brackets. We are issuing this AD to 

detect and correct corrosion on bonding 

jumpers installed on the flight control 

surfaces, which, in the event of a 

lightning strike, could damage the 

actuator control electronics (ACEs) and 

result in the loss of the ability to 

command individual flight control 

surfaces or cause uncommanded motion 

of individual flight control surfaces. 

DATES: This AD is effective August 19, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2014. 

ADDRESSES: For 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. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0867; 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 address for the 

Docket Office (phone: 800–647–5527) is 

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 FURTHER INFORMATION CONTACT: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, Seattle Aircraft Certification 

Office, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6482; fax: 425–917–6590; email: 

Georgios.Roussos@faa.gov. 

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 The Boeing Company 

Model 777–200, –200LR, –300, and 

–300ER series airplanes. The NPRM 

published in the Federal Register on 

October 25, 2013 (78 FR 63903). The 

NPRM was prompted by reports of 

severe corrosion on bonding jumpers 

installed on the flight control surfaces. 

The NPRM proposed to require 

repetitive bonding jumper inspections 

for corrosion, sealant disbond, and 

insufficient sealant coverage; and 

corrective actions if necessary. The 

NPRM also specified an optional 

inspection for corrosion damage of the 

bonding brackets, and corrective actions 

if necessary, which would terminate the 

repetitive inspections. For certain 

airplanes, the NPRM proposed installing 

certain bonding jumpers, and replacing 

single-tabbed brackets with two-tabbed 

brackets. We are issuing this AD to 

detect and correct corrosion on bonding 

jumpers installed on the flight control 

surfaces, which, in the event of a 

lightning strike, could damage the ACEs 

and result in the loss of the ability to 

command individual flight control 

surfaces or cause uncommanded motion 

of individual flight control surfaces. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 63903, 

October 25, 2013) and the FAA’s 

response to each comment. 

Request To Base Compliance Time on 

AD Issue Date 

American Airlines (AAL) requested 

that paragraph (f) of the proposed AD 

(78 FR 63903, October 25, 2013) be 

revised to allow operators to comply 

with Boeing Service Bulletin 777– 

27A0078, Revision 1, dated April 1, 

2013, within 36 months after the AD 

effective date. AAL stated that Boeing 

Alert Service Bulletin 777–27A0078, 

dated September 10, 2009, was issued 

with a compliance time of 36 months 

from the original release of the service 

bulletin. AAL explained that after 

Boeing Alert Service Bulletin 777– 

27A0078, dated September 10, 2009, 

was released, Boeing accomplished a 

service bulletin validation on another 

operator’s airplane and found many 

discrepancies and errors with the work 

instructions and parts required, 

resulting in Revision 1 of Boeing Service 

Bulletin 777–27A0078, dated April 1, 

2013. AAL stated that due to the issues 

still existing in the work instructions for 

Boeing Alert Service Bulletin 777– 

27A0078, dated September 10, 2009, 

and a long lead time on the part kits, 

operators will be unable to accomplish 

Boeing Service Bulletin 777–27A0078, 

Revision 1, dated April 1, 2013, by the 

compliance time given without severe 

disruption of schedules. 

We agree with the commenter’s 

request. We agree that the compliance 

time should be based on the effective 

date of this final rule and not on the 

original issue date of Boeing Service 

Bulletin 777–27A0078, Revision 1, 

dated April 1, 2013. We had already 

included this information in the 

proposed AD (78 FR 63903, October 25, 

2013), paragraph (j)(1) of this AD, as 


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