48024 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3152, Revision 3, 

dated December 22, 2011. Do all applicable 

corrective actions before further flight. 

(1) For airplanes pre-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD. 

(i) Prior to 24,400 total flight cycles or 

85,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(2) For airplanes pre-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Prior to 18,900 total flight cycles or 

122,900 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(3) For airplanes post-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(3)(i) or 

(g)(3)(ii) of this AD. 

(i) Prior to 16,400 total flight cycles or 

57,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(4) For airplanes post-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(4)(i) or 

(g)(4)(ii) of this AD. 

(i) Prior to 12,700 total flight cycles or 

82,700 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(h) Retained Modification 

This paragraph restates the requirements of 

paragraph (f)(2) of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008), with revised paragraph formatting. For 

Airbus Model A330–200 and A340–300 

series airplanes as identified in paragraph (c) 

of this AD, on which Modification 45012 has 

not been embodied in production: At the 

later of the compliance times specified in 

paragraphs (h)(1) and (h)(2) of this AD, 

modify the upper shell structure of the 

fuselage, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3157, or Airbus 

Service Bulletin A340–53–4163, both dated 

July 5, 2006, as applicable. 

(1) For the airplanes identified in 

paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. 

(i) For Model A330–200 series airplanes, 

prior to 6,600 total flight cycles. 

(ii) For Model A340–300 series airplanes, 

prior to 14,000 total flight cycles. 

(2) Within 90 days after August 21, 2008 

(the effective date of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008)). 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the service information 

specified in paragraph (i)(1), (i)(2), or (i)(3) of 

this AD. 

(1) Airbus Service Bulletin A330–53–3152, 

dated April 10, 2007, which was 

incorporated by reference in AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, 

July 17, 2008). 

(2) Airbus Service Bulletin A330–53–3152, 

Revision 1, dated May 5, 2009, which is not 

incorporated by reference in this AD. 

(3) Airbus Service Bulletin A330–53–3152, 

Revision 2, dated July 27, 2011, which is not 

incorporated by reference in this AD. 

(j) 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) 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0158, dated July 22, 2013, for 

related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0121-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (l)(5) and (l)(6) of this AD. 

(l) 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. 

(3) The following service information was 

approved for IBR on September 19, 2014. 

(i) Airbus Service Bulletin A330–53–3152, 

Revision 3, dated December 22, 2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 21, 2008 (73 FR 

40958, July 17, 2008). 

(i) Airbus Service Bulletin A330–53–3157, 

dated July 5, 2006. 

(ii) Airbus Service Bulletin A340–53–4163, 

dated July 5, 2006. 

(5) 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. 

(6) 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. 

(7) 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 July 23, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18461 Filed 8–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0468; Directorate 

Identifier 2012–NM–147–AD; Amendment 

39–17924; AD 2014–15–21] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2006–26– 

06 for certain The Boeing Company 

Model 777–200 and –300 series 

airplanes equipped with Rolls-Royce 

engines. AD 2006–26–06 required 

repetitive inspections to detect cracks of 

the outer V-blades of the thrust reverser, 

and corrective action if necessary. AD 


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Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 48025 

2006–26–06 also provided for an 

optional terminating action for the 

repetitive inspections. This new AD 

adds, for airplanes on which the 

optional terminating action is done, 

repetitive inspections for cracking in the 

outer V-blade fittings of the hinge beam 

and latch beam ends of each thrust 

reverser half, and replacement of an 

affected thrust reverser half if necessary. 

This new AD also adds airplanes to the 

applicability. This AD was prompted by 

reports of cracked outer V-blade fittings 

at the hinge beam end of Rolls-Royce 

engine thrust reversers, on airplanes on 

which the optional terminating action 

was done. We are issuing this AD to 

prevent separation of a thrust reverser 

from the airplane during normal reverse 

thrust or during a refused takeoff, which 

could result in unexpected thrust 

asymmetry and a possible runway 

excursion. 

DATES: This AD is effective September 

19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 11, 2007 (71 FR 

77586, December 27, 2006). 

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; 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: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6513; fax: 

425–917–6590; email: narinder.luthra@

faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006). AD 2006–26–06 

applied to Boeing Model 777–200 and 

–300 series airplanes, equipped with 

Rolls-Royce engines. The NPRM 

published in the Federal Register on 

July 3, 2013 (78 FR 40060). The NPRM 

proposed to continue to require 

repetitive inspections to detect cracks of 

the outer V-blades of the thrust reverser, 

and corrective action if necessary. The 

NPRM also proposed to continue to 

provide an optional terminating action 

for the repetitive inspections. The 

NPRM also proposed to require, for 

airplanes on which the optional 

terminating action is done, repetitive 

inspections for cracking in the outer Vblade fittings of the hinge beam and 

latch beam ends of each thrust reverser 

half, and replacement of an affected 

thrust reverser half if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 40060, 

July 3, 2013) and the FAA’s response to 

each comment. 

Requests To Incorporate Boeing Special 

Attention Service Bulletin 777–78–0091, 

Dated June 18, 2013 

Boeing, American Airlines (AAL), Air 

New Zealand, Delta Airlines, and 

Transaero requested that we allow the 

modifications and inspections defined 

in Boeing Special Attention Service 

Bulletin 777–78–0091, dated June 18, 

2013, as an alternative to the 

inspections specified in paragraph (j) of 

the NPRM (78 FR 40060, July 3, 2013). 

Boeing stated that Boeing Special 

Attention Service Bulletin 777–78– 

0091, dated June 18, 2013, has been 

approved as an alternative method of 

compliance (AMOC) with AD 2006–26– 

06, Amendment 39–14864 (71 FR 

77586, December 27, 2006), and is 

intended as an alternative to the 

inspections proposed by the NPRM. 

Boeing also requested that we provide 

credit for actions specified in paragraph 

(j) of the NPRM that were done before 

the effective date of the new AD in 

accordance with Boeing Special 

Attention Service Bulletin 777–78– 

0091, dated June 18, 2013. 

We disagree with the request. Boeing 

is considering revising Boeing Special 

Attention Service Bulletin 777–78– 

0091, dated June 18, 2013, to 

incorporate feedback on the 

Accomplishment Instructions of the 

service bulletin that resulted from 

validation of the service bulletin. The 

new revision might include 

improvements to the L-fitting 

modification to eliminate short edge 

margin, fastener changes to eliminate 

interference, and other changes to the 

installation sequence and other 

procedures. We will consider approving 

the revision of Boeing Special Attention 

Service Bulletin 777–78–0091 as an 

AMOC to the actions specified in 

paragraph (j) of this AD, once this 

service bulletin is approved and is 

released. We find that delaying this 

action would be inappropriate in light 

of the urgency of the identified unsafe 

condition. No change has been made to 

this final rule in this regard. 

Request To Reference Boeing Special 

Attention Service Bulletin 777–78–0064, 

Revision 2, Dated June 14, 2012 

Boeing requested that we add Boeing 

Special Attention Service Bulletin 777– 

78–0064, Revision 2, dated June 14, 

2012, as a reference to paragraph (g) of 

the NPRM (78 FR 40060, July 3, 2013). 

Boeing stated that Boeing Special 

Attention Service Bulletin 777–78– 

0064, Revision 2, dated June 14, 2012, 

reiterates the repetitive inspection 

intervals from Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 

1, dated November 30, 2006. 

We agree. The compliance times 

specified in Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 

1, dated November 30, 2006; and 

Revision 2, dated June 14, 2012; are the 

same, except that Revision 2 states that 

the compliance times are measured from 

the effective date of AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006), rather than the 

issue date of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 

1, dated November 30, 2006. We have 

revised paragraph (g) of this final rule to 

add Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated 

June 14, 2012, as a reference for 

accomplishing the actions. 

Request To Change Format of the 

NPRM (78 FR 40060, July 3, 2013) 

Air New Zealand requested that we 

change the format of the NPRM (78 FR 

40060, July 3, 2013) to clarify the 

requirements. The commenter requested 

that we list all repetitive inspection 


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requirements for all airplane 

configurations in one paragraph. The 

commenter stated that the format of the 

NPRM was confusing. 

We disagree with changing the format 

as it is consistent with the format used 

for most supersedure ADs. Paragraph (g) 

of this AD clearly identifies the affected 

airplanes that must continue to 

accomplish the retained repetitive 

inspections. Paragraph (j) of this AD 

clearly identifies the affected airplanes 

that must accomplish the new repetitive 

inspections. No change has been made 

to this final rule in this regard. 

Request To Consider AD 

Implementation Aviation Rulemaking 

Committee (AD ARC) 

Recommendations 

AAL requested that, in the spirit of 

the AD ARC to improve the AD process, 

we consider the guidance from the AD 

ARC when considering its comments to 

the proposed AD. AAL provided a 

general comment noting that certain 

service information referenced in the 

proposed AD is quite lengthy and 

contains extremely detailed data, while 

one of the referenced service documents 

is only 29 pages long. AAL does not 

consider the lengthy service information 

to be ‘‘AD-Friendly.’’ Further, AAL 

stated that the instructions in this 

service information does not 

differentiate between critical and noncritical tasks and figures (i.e., the service 

information does not incorporate the 

‘‘Required for Compliance’’ (RC) 

concept developed by the AD ARC). 

We agree that it is helpful when 

service information is presented in a 

way that meets ‘‘AD-Friendly’’ 

guidelines. The focus of AD-friendly 

service information is to ensure that the 

language (including compliance times 

and instructions) in the document is 

clear and legally enforceable and, 

therefore, easier for the FAA to adopt 

into an AD. However, this focus does 

not mean the service information will be 

brief. Many service bulletins are 

necessarily lengthy and complex due, in 

part, to multiple actions, multiple 

airplane groups/configurations, and 

multiple or complex compliance times. 

The RC concept is an additional 

improvement to service information. 

The concept was developed between the 

FAA and industry under the AD ARC to 

further enhance service bulletins and, in 

turn, the AD process. The RC concept is 

a new process for annotating which 

steps in the service information are 

‘‘required for compliance’’ with an AD. 

Differentiating these steps from other 

tasks in the service information is 

expected to improve an owner’s/

operator’s understanding of AD 

requirements and help provide 

consistent judgment in AD compliance. 

However, the RC concept does not 

necessarily result in less lengthy service 

information. Details might be necessary 

to provide clear understanding and 

accurate service instructions. 

In response to the AD ARC’s 

recommendations, the FAA released 

Advisory Circular (AC) 20–176, dated 

December 19, 2011 (http:// 

rgl.avs.faa.gov/Regulatory_and_

Guidance_Library/

rgAdvisoryCircular.nsf/0/

a78cc91a47b192278625796b0075f419/

$FILE/AC%2020-176.pdf); and Order 

8110.117, dated September 12, 2012 

(http://rgl.avs.faa.gov/Regulatory_and_

Guidance_Library/rgOrders.nsf/0/

984bb9eb07cdd86986257a7f0070744c/

$FILE/Order%208110.117.pdf); which 

discusses the RC concept. The FAA 

includes this concept in ADs when we 

receive service information containing 

RC steps. While some design approval 

holders have implemented the RC 

concept, the implementation is 

voluntary. The FAA does not intend to 

develop or revise AD requirements to 

incorporate the RC concept if it is not 

included in the service information. 

Request To Add More Detail for 

Compliance Requirements in AD 

AAL requested that rather than 

requiring compliance with the 

referenced service bulletins, the AD 

should focus compliance requirements 

on identifying detailed inspections by 

task name, identifying an optional 

configuration change by part numbers, 

and specifying the corrective action for 

crack findings. AAL stated that 

requiring compliance with the entirety 

of the referenced service bulletins 

would introduce an unnecessary and 

excessive burden on the operators, 

impede progress toward correcting the 

unsafe condition, and introduce 

unintended compliance risks not 

relevant to correcting the unsafe 

condition. 

We disagree with the request. As 

stated previously, the FAA does not 

intend to develop or revise AD 

requirements to incorporate the RC 

concept if it is not included in the 

service information. This final rule 

requires certain repetitive inspections 

and, as applicable, certain corrective 

actions and replacements, which are 

described in detail in the service 

information. No change has been made 

to this final rule in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments 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 

40060, July 3, 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 40060, 

July 3, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Interim Action 

We consider this AD interim action. 

The manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

Costs of Compliance 

We estimate that this AD affects 55 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Cost per product Cost on U.S. operators 

Inspections [retained actions from AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, December 27, 

2006)].

16 work-hours × $85 per 

hour = $1,360 per inspection cycle.

$1,360 per inspection cycle $74,800 per inspection 

cycle. 

Repetitive inspections outer V-blade [new action] 1 ....... 82 work-hours × $85 per 

hour = $6,970 per inspection cycle.

$6,970 per inspection cycle $383,350 per inspection 

cycle. 

1We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this AD. 


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Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 48027 

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 have 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 

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. 

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) 

2006–26–06, Amendment 39–14864 (71 

FR 77586, December 27, 2006), and 

adding the following new AD: 

2014–15–21 The Boeing Company: 

Amendment 39–17924; Docket No. 

FAA–2013–0468; Directorate Identifier 

2012–NM–147–AD. 

(a) Effective Date 

This AD is effective September 19, 2014. 

(b) Affected ADs 

This AD supersedes AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –300 series airplanes, 

certificated in any category, equipped with 

Rolls-Royce engines. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine exhaust. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracked outer V-blade fittings at the hinge 

beam end of Rolls-Royce engine thrust 

reversers, on airplanes on which the optional 

terminating action was done. We are issuing 

this AD to prevent separation of a thrust 

reverser from the airplane during normal 

reverse thrust or during a refused takeoff, 

which could result in unexpected thrust 

asymmetry and a possible runway excursion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections With 

New Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2006–26–06, Amendment 

39–14864 (71 FR 77586, December 27, 2006), 

with new service information. For Group 1, 

Configuration 1, airplanes, as identified in 

Boeing Special Attention Service Bulletin 

777–78–0064, Revision 2, dated June 14, 

2012: Do the detailed inspections to detect 

cracks in the outer V-blade of the thrust 

reversers. Do the inspections in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–78–0064, Revision 1, dated November 

30, 2006; or Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012. Do the inspections at the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 1, 

dated November 30, 2006; except where 

Boeing Special Attention Service Bulletin 

777–78–0064, Revision 1, dated November 

30, 2006, specifies an initial compliance time 

after the date on that service bulletin, this AD 

requires compliance within the specified 

time after January 11, 2007 (the effective date 

of AD 2006–26–06). Do applicable corrective 

actions before further flight, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–78–0064, Revision 1, dated November 

30, 2006; or Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012; or paragraph (m) of this AD. As of 

the effective date of this AD, use only Boeing 

Special Attention Service Bulletin 777–78– 

0064, Revision 2, dated June 14, 2012, to 

accomplish the actions required by this 

paragraph. 

(h) Retained Credit for Previous Actions 

This paragraph restates the credit 

provisions for the actions specified in 

paragraph (g) of AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006). For Group 1, 

Configuration 1, airplanes as identified in 

Boeing Special Attention Service Bulletin 

777–78–0064, Revision 2, dated June 14, 

2012. This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before 

January 11, 2007 (the effective date of AD 

2006–26–06), using Boeing Special Attention 

Service Bulletin 777–78–0064, dated August 

7, 2006. 

(i) Retained Optional Terminating Action 

With New Requirements and New Service 

Information 

This paragraph restates the optional 

terminating action specified in paragraph (i) 

of AD 2006–26–06, Amendment 39–14864 

(71 FR 77586, December 27, 2006), with new 

service information. Accomplishment of the 

actions specified in paragraph (i)(1) or (i)(2) 

of this AD terminates the requirements of 

paragraph (g) of this AD. For airplanes on 

which this terminating action has been 

accomplished, operators must do the 

inspection required by paragraph (j) of this 

AD. 

(1) Accomplishment of the applicable 

inspections and related investigative/

corrective actions before the effective date of 

this AD, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–78– 

0061, dated July 6, 2006; except, where 

Boeing Special Attention Service Bulletin 

777–78–0061, dated July 6, 2006, specifies to 

contact the manufacturer for appropriate 

action, repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(2) Accomplishment of the applicable 

modification, inspections, and related 

investigative/corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0061, Revision 1, 

dated August 28, 2007; except, where Boeing 

Special Attention Service Bulletin 777–78– 

0061, Revision 1, dated August 28, 2007, 

specifies to contact the manufacturer for 

appropriate action, repair before further flight 

using a method approved in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

(j) New Repetitive Inspections 

For airplanes in Group 1, Configuration 2, 

and Groups 2 and 3, as identified in Boeing 

Special Attention Service Bulletin 777–78– 


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48028 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

0064, Revision 2, dated June 14, 2012: At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 2, 

dated June 14, 2012, except as provided by 

paragraph (k) of this AD, do a detailed 

inspection for cracking of the outer V-blade 

fittings at the latch beam end and hinge beam 

end of each thrust reverser half, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 2, 

dated June 14, 2012. 

(1) If no cracking is found, repeat the 

inspections thereafter at the times specified 

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

Special Attention Service Bulletin 777–78– 

0064, Revision 2, dated June 14, 2012. 

(2) If any cracking is found, before further 

flight, replace the affected thrust reverser half 

with a serviceable thrust reverser half, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 2, 

dated June 14, 2012. Repeat the inspections 

thereafter at the times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Special 

Attention Service Bulletin 777–78–0064, 

Revision 2, dated June 14, 2012. 

(k) Service Information Exception 

Where Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012, specifies an initial compliance time 

‘‘after the date on Revision 2 of this service 

bulletin,’’ this AD requires compliance 

within the specified time after the effective 

date of this AD. 

(l) Reporting Not Required 

Although Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012, specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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, Seattle 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. 

(4) AMOCs approved previously in 

accordance with AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006), are not approved as 

AMOCs for this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6513; fax: 425–917–6590; 

email: narinder.luthra@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (o)(5) and (o)(6) of this AD. 

(o) 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. 

(3) The following service information was 

approved for IBR on September 19, 2014. 

(i) Boeing Special Attention Service 

Bulletin 777–78–0061, Revision 1, dated 

August 28, 2007. 

(ii) Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012. 

(4) The following service information was 

approved for IBR on January 11, 2007 (71 FR 

77586, December 27, 2006). 

(i) Boeing Special Attention Service 

Bulletin 777–78–0061, dated July 6, 2006. 

(ii) Reserved. 

(5) 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. 

(6) 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. 

(7) 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 July 23, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18313 Filed 8–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0219; Directorate 

Identifier 2014–NE–04–AD; Amendment 39– 

17939; AD 2014–16–15] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Turbomeca S.A. Makila 2A and Makila 

2A1 turboshaft engines. This AD 

requires initial and repetitive visual 

inspections, and replacement of the 

splines of the high-pressure (HP) fuel 

pump/metering valve and the module 

M01 drive gear, if necessary. This AD 

was prompted by the failure of two HP 

fuel pumps that resulted in engine inflight shutdowns. We are issuing this 

AD to prevent failure of the HP fuel 

pump, which could lead to an in-flight 

shutdown, damage to the engine, and 

forced landing or accident. 

DATES: This AD becomes effective 

September 19, 2014. 

ADDRESSES: For service information 

identified in this AD, contact 

Turbomeca, S.A., 40220 Tarnos, France; 

phone: 33 (0)5 59 74 40 00; telex: 570 

042; fax: 33 (0)5 59 74 45 15. 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–2014– 

0219; 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. 


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