Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 63307 

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 AD: 

2014–21–02 Pacific Aerospace Limited: 

Amendment 39–17994; Docket No. 

FAA–2014–0532; Directorate Identifier 

2014–CE–016–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective November 28, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pacific Aerospace 

Limited Models FU24–954 and FU24A–954 

airplanes, all serial numbers, certificated in 

any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted from mandatory 

continuing airworthiness information (MCAI) 

issued by the aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as cracking of 

the control column at the wiring access hole. 

We are issuing this AD to detect and correct 

cracking of the control column at the wiring 

access hole, which could cause control 

column failure and subsequent loss of 

control. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) through (f)(3) of 

this AD, following the accomplishment 

instructions in Pacific Aerospace Limited 

Mandatory Service Bulletin PACSB/FU/095, 

Issue 2, dated May 28, 2014. 

(1) Within the next 50 hours time-inservice (TIS) after November 28, 2014 (the 

effective date of this AD), inspect the control 

column part number (P/N) 08–45031/32 for 

cracks. 

(2) If any mechanical damage, deformation, 

or cracks are found, before further flight, 

replace the control column with an airworthy 

control column P/N 08–45031/32. 

(3) If no mechanical damage, deformation, 

or cracks are found after the inspection 

required in paragraph (f)(1) of this AD, at the 

next scheduled maintenance inspection or 

within the next 150 hours TIS, whichever 

occurs later, replace the control column with 

an airworthy P/N 08–45031/32. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI Civil Aviation Authority 

(CAA) AD DCA/FU24/183, dated May 29, 

2014, for related information. The MCAI can 

be found in the AD docket on the Internet at: 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0532-0002. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Pacific Aerospace Limited Mandatory 

Service Bulletin PACSB/FU/095, Issue 2, 

dated May 28, 2014. 

(ii) Reserved. 

(3) For Pacific Aerospace Limited service 

information identified in this AD, contact 

Pacific Aerospace Limited, Airport Road, 

Hamilton Private Bag 3027 Hamilton 3240, 

New Zealand; telephone: +64 7 843 6144; fax: 

+64 7 843 6134; email: pacific@

aerospace.co.nz; Internet: http://

www.aerospace.co.nz/. 

(4) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on 

October 9, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–24698 Filed 10–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28413; Directorate 

Identifier 2007–NE–25–AD; Amendment 39– 

17993; AD 2014–21–01] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directives (ADs) 90–26– 

01, 91–20–02, and 2009–05–02 for all 

General Electric Company (GE) CF6– 

80C2 and CF6–80E1 series turbofan 

engines. This AD retains the 

requirements of those ADs and requires 

removal of additional fuel manifold part 

numbers (P/Ns), additional repetitive 

inspections, replacement as required of 

certain fuel manifold P/Ns and tube 

(block) clamps, and replacement of loop 

clamps. This AD was prompted by a 

report of an under-cowl fire caused by 

a manifold high-pressure fuel leak, and 

several additional reports of fuel leaks. 

We are issuing this AD to prevent 

failure of the fuel manifold, which 

could lead to uncontrolled engine fire, 

engine damage, and damage to the 

airplane. 

DATES: This AD is effective November 

28, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 28, 2014. 

ADDRESSES: For service information 

identified in this AD, contact General 

Electric Company, GE Aviation, Room 

285, 1 Neumann Way, Cincinnati, OH 

45215; phone: (513) 552–3272; email: 

geae.aoc@ge.com. 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:// 


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63308 Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 

www.regulations.gov by searching for 

and locating Docket No. FAA–2007– 

28413; 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 Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Kasra Sharifi, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone (781) 238–7773; fax: (781) 238– 

7199; email: kasra.sharifi@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 90–26–01, 

Amendment 39–6810 (55 FR 49611, 

November 30, 1990), (‘‘AD 90–26–01’’), 

and AD 91–20–02, Amendment 39–8036 

(56 FR 55231, October 25, 1991), (‘‘AD 

91–20–02’’), and AD 2009–05–02, 

Amendment 39–15826 (74 FR 8161, 

February 24, 2009), (‘‘AD 2009–05–02’’). 

AD 90–26–01 and AD 91–20–02 applied 

to all GE CF6–80C2 series turbofan 

engines. AD 2009–05–02 applied to all 

GE CF6–80C2 and CF6–80E1 series 

turbofan engines. The NPRM published 

in the Federal Register on January 17, 

2014 (79 FR 3139). The NPRM was 

prompted by a report of an under-cowl 

fire caused by a manifold high-pressure 

fuel leak and several additional reports 

of fuel leaks. The NPRM proposed to 

retain the requirements of the 

superseded ADs: AD 90–26–01 and AD 

91–20–02 required removal of certain 

fuel manifold P/Ns; AD 2009–05–02 

required inspection of certain fuel 

manifold P/Ns and replacement of 

certain consumable components. The 

NPRM also proposed to require removal 

of additional fuel manifold P/Ns, 

performance of additional initial and 

repetitive inspections, replacement as 

required of certain fuel manifold P/Ns 

and tube (block) clamps, and 

replacement of loop clamps at each fuel 

manifold inspection opportunity. We 

are issuing this AD to prevent failure of 

the fuel manifold, which could lead to 

uncontrolled engine fire, engine 

damage, and damage to the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 3139, 

January 17, 2014) and the FAA’s 

response to each comment. 

Request To Replace Two Incorrect Part 

Numbers 

Several commenters requested that we 

replace two incorrect fuel manifold 

P/Ns with the correct P/Ns. 

We agree. We corrected the P/Ns in 

paragraph (c) of this AD from P/Ns 

1308M31G12 and 1308M32G12 to P/Ns 

1303M31G12 and 1303M32G12. 

Request To Change and Clarify 

Compliance Information 

Several commenters requested that we 

make changes to Table 1 to paragraph 

(e) in the NPRM (79 FR 3139, January 

17, 2014). Three commenters requested 

that we remove the compliance time of 

six months because this requirement is 

unjustified. Two commenters requested 

that we remove one row of information 

due to redundancy. One commenter 

requested that we reorder the rows to 

make the table easier to follow. 

We partially agree. We agree that the 

table is problematic. A six-month 

compliance time was meant to be a 

‘‘grace period’’ for products that might 

have already exceeded the threshold. 

But, including a ‘‘grace period’’ is 

unnecessary, since AD 2009–05–02, 

which we are superseding with this AD, 

mandates the same requirement. We 

removed the six-month compliance time 

period. 

We disagree with making the other 

changes as suggested, but did reword 

paragraph (e) to this AD to eliminate the 

tables and clarify the AD. 

Request To Change Definition of Shop 

Visit 

Several commenters requested that we 

change the definition of shop visit to 

exclude certain maintenance visits 

because the current definition forces the 

replacement of the fuel manifold at the 

majority of shop visits. 

We agree. We changed the definition 

of shop visit for the purposes of this AD 

to exclude shop visits for specified 

types of maintenance. 

Request To Allow Reinstallation of 

Certain P/N Fuel Manifolds During OnWing Maintenance 

Virgin Atlantic Airways, Delta Air 

Lines, AIRDO, and GE requested that we 

allow reinstallation of fuel manifolds, 

P/Ns 1303M31G12, 1303M32G12, 

2420M70G01, and 2420M71G01, during 

on-wing maintenance, and only 

mandate removal of these P/Ns during 

shop visits. The commenters state that 

modification of the fuel manifold 

configuration during on-wing 

maintenance is not practicable due to 

complexity, potential for maintenance 

error, and cost compared to replacement 

during shop visit. 

We agree. The intent of this AD is to 

require removal of fuel manifolds, P/Ns 

1303M31G12, 1303M32G12, 

2420M70G01, and 2420M71G01, during 

shop visit, not during on-wing 

maintenance. We removed the 

installation prohibition statement that 

included these P/Ns. 

Request To Exclude Certain Engine 

Models From Applicability 

Lufthansa Cargo requested that we 

exclude from the applicability of this 

AD certain CF6–80C2 engine models. 

We disagree. All CF6–80C2 engine 

models are affected by the same unsafe 

condition. We did not change this AD. 

Request To Change the Focus of This 

AD, and To Retain and Supersede 

Different ADs 

KLM Royal Dutch Airlines (KLM) 

requested that we address pigtail 

cracking in this AD, instead of tube 

(block) clamp and loop clamp chafing, 

by retaining AD 2009–05–02, 

Amendment 39–15826 (74 FR 8161, 

February 24, 2009), AD 91–20–02, 

Amendment 39–8036 (56 FR 55231, 

October 25, 1991), and AD 90–26–01, 

Amendment 39–6810 (55 FR 49611, 

November 30, 1990), and by 

superseding AD 2007–11–20, 

Amendment 39–15077 (72 FR 30956, 

June 5, 2007). KLM states that the recent 

under-cowl fire event was related to 

pigtail cracking, which the FAA has not 

addressed, and not to tube (block) and 

loop clamp chafing. 

We disagree. Pigtail cracking, tube 

(block) clamp chafing, and loop clamp 

chafing can all be caused by resonant 

vibration within the engine operation 

range. This AD requires removal of fuel 

manifolds susceptible to resonant 

vibration, which addresses pigtail 

cracking, tube (block) clamp chafing, 

and loop clamp chafing leading to fuel 

manifold leaks. We did not change this 

AD. 

Request To Remove From Paragraph 

(e)(2) Reference to ‘‘Tube (Block) 

Clamp’’ 

KLM requested that we delete 

reference to the ‘‘Tube (Block) Clamp’’ 

from paragraph (e)(2) of this AD because 

instructions regarding inspection and 

replacement of the tube (block) clamp 

are not addressed in that paragraph. 


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Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 63309 

We partially agree. The reference to 

the ‘‘Tube (Block) Clamp’’ in paragraph 

(e)(2) is inaccurate. We restructured the 

compliance paragraphs. Paragraphs 

(e)(2)(ii) and (e)(2)(iii) of this AD now 

reference ‘‘Tube (Block) Clamp.’’ 

Request To Provide More Information 

Regarding the Unsafe Condition 

Lufthansa Technik AG and Deutsche 

Lufthansa AG requested that we provide 

additional details concerning the unsafe 

condition. 

We partially agree. Although the AD 

Discussion section provides sufficient 

information regarding the fuel manifold 

leaks, we included a reference to 

additional information in the Related 

Information paragraph of this AD. 

Request To Expand Compliance To 

Address Other Unsafe Conditions 

One commenter requested that we 

expand the compliance requirements of 

this AD to address other possible unsafe 

conditions in the designs of the 

accessory gearbox, spray shield, and 

fuel nozzle, and made reference to 

National Transportation Safety Board 

(NTSB) safety recommendations (SRs) 

A–13–022 and A–12–047. 

We disagree. Unsafe conditions in the 

engine caused by designs of the 

accessory gearbox and spray shield are 

not the subjects of this AD. Fire caused 

by fuel manifold leak is the subject of 

this AD. SRs A–13–022 and A–12–047 

do not address fire caused by fuel 

manifold leaks. We did not change this 

AD. 

Request To Allow Use of Future 

Revisions of Referenced Service 

Bulletins (SBs) 

Delta Air Lines requested that we 

allow use of future revisions of the SBs 

referenced in compliance paragraphs 

because this would eliminate the need 

to request an alternative method of 

compliance (AMOC) if the SBs are 

revised. 

We disagree. We are authorized to 

mandate use of procedures in SBs that 

are published and which we have 

reviewed. Since future revisions of SBs 

are not yet published, we are not 

authorized to mandate their use in 

advance. We did not change this AD. 

Request To Address Repetitive 

Inspections of Fuel Manifolds Repaired 

With PTFE-Coated Para-Aramid Tape 

Japan Airlines requested that we 

allow repetitive inspections of fuel 

manifolds that have PTFE-coated paraaramid tape at the tube (block) clamp 

locations. The NPRM (79 FR 3139, 

January 17, 2014) addressed initial 

inspections, but did not address 

repetitive inspections of fuel manifolds 

repaired with PTFE-coated para-aramid 

tape. 

We agree. We changed the references 

to SBs in this AD to more recent 

versions that allow repetitive 

inspections of fuel manifolds that have 

PTFE-coated para-aramid tape at the 

tube (block) clamp locations. 

Request To Require the Use of GE 

Method To Replace Fuel Manifolds 

Boeing Commercial Airplanes and 

another commenter requested that we 

require that manifolds be replaced using 

the method stated in the GE SBs. To 

substantiate the request, the second 

commenter referred to NTSB SR A–13– 

028. 

We disagree. The regulations require 

that operators use acceptable methods, 

techniques, and practices to replace the 

fuel manifolds. The GE SBs contain one 

acceptable method to replace the fuel 

manifolds, but not the only acceptable 

method of doing so. We did not change 

this AD. 

Request To Clarify Certain Preamble 

and Compliance Paragraphs 

GE requested that we clarify, in the 

‘‘Proposed AD Requirements’’ 

paragraph, the additional P/Ns of fuel 

manifolds to be inspected and replaced. 

GE also requested that we make clear, in 

the ‘‘Summary’’ paragraph, that on-wing 

replacement of tube (block) clamps and 

fuel manifolds is based on inspection 

results. GE also requested that we use 

alternative wording in paragraph (e) and 

Table 2 to paragraph (e) of this AD. 

We partially agree. We agree that we 

needed to clarify the P/Ns to be 

removed before further flight, and those 

to be inspected until removed. We 

changed this AD to clearly identify both 

groups. We also agree that paragraph (e) 

of this AD required clarification. We 

reworded paragraph (e) of this AD to 

clearly identify the requirements to 

correct the unsafe condition. 

Request To Allow Installation of 

Certain Prohibited P/Ns 

Asiana Airlines, EVA Airways, Thai 

Airways, AIRDO, and Japan Airlines 

requested that for fuel manifold, P/Ns 

1303M31G12, 1303M32G12, 

2420M70G01, and 2420M71G01, we 

reduce the inspection interval or require 

non-destructive inspection at shop visits 

rather than require removal and prohibit 

installation. The operators state that 

their records do not indicate that these 

parts cause leaks or experience wear 

that would cause their replacement, and 

they expressed concerns that the 

reliability of the replacement fuel 

manifolds is lower than that of the 

prohibited fuel manifolds. 

We disagree. A reduced inspection 

interval does not prevent pigtail 

cracking between shop visits. Our data 

does not justify a reduced inspection 

interval to prevent fuel leak events, or 

indicate that the new fuel manifold 

design has lower reliability. We did not 

change this AD. 

Request To Allow Use of Certain P/Ns 

for Drained Engine Configurations 

Lufthansa Technik AG requested that 

we allow the use of fuel manifold, P/Ns 

2420M70G01, 2420M71G01, 

1303M31G12, and 1303M32G12, as 

replacement parts for drained (pre SB 

73–0253) engine configurations. The 

commenter states that GE’s service 

information allows use of fuel manifold, 

P/Ns 1303M31G12 and 1303M32G12, 

on engines with drain system installed, 

and this AD does not prohibit 

installation of fuel manifold, P/Ns 

1303M31G10 and 1303M32G10. 

We disagree. We have no data 

showing that drainless fuel manifolds 

installed in engines with a drain system 

are more reliable than when installed in 

engines with a drainless system. We did 

not change this AD. 

Request To Remove Certain Fuel 

Manifolds From Applicability 

Lufthansa Cargo requested that we 

remove from the applicability of this AD 

drainless fuel manifolds to which PTFEcoated para-aramid tape was applied 

and the loop and tube (block) clamps 

were inspected. 

We disagree. We received several 

reports of fuel leaks and a report of 

under-cowl fire. The inspections alone 

required by this AD do not address 

pigtail cracking leading to fuel leaks, 

and therefore do not provide an 

acceptable level of safety. We did not 

change this AD. 

Request To Remove the Word 

‘‘Uncontrolled’’ From the Description of 

Fire 

Boeing Commercial Airplanes 

requested that we remove from the 

preamble the word ‘‘uncontrolled’’ from 

the description of fire caused by a fuel 

manifold leak because an uncontrolled 

fire in this scenario could only occur 

with a significant failure of the engine 

nacelle fire protection system. 

We disagree. The data upon which we 

relied, including the Continued 

Airworthiness Assessment 

Methodologies (CAAM) database for 

transport category airplanes, includes 

data showing flammable fluid leaks 

leading to uncontrolled fires. We did 

not change this AD. 


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63310 Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 

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 editorial changes to improve clarity. 

We have determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 3139, 

January 17, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 3139, 

January 17, 2014). 

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 would affect 

1,126 engines installed on airplanes of 

U.S. registry. We also estimate that 

required parts cost about $34,894 per 

engine. We also estimate that it will take 

about 6 hours to accomplish the actions 

required by this AD. The average labor 

rate is $85 per hour. Based on these 

figures, we estimate the total cost of this 

AD to U.S. operators to be $39,864,904. 

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 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. 

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: 

■ a. Removing airworthiness directive 

(AD) 90–26–01, Amendment 39–6810 

(55 FR 49611, November 30, 1990); AD 

91–20–02, Amendment 39–8036 (56 FR 

55231, October 25, 1991); and AD 2009– 

05–02, Amendment 39–15826 (74 FR 

8161, February 24, 2009); and 

■ b. Adding the following new AD: 

2014–21–01 General Electric Company: 

Amendment 39–17993; Docket No. 

FAA–2007–28413; Directorate Identifier 

2007–NE–25–AD. 

(a) Effective Date 

This AD is effective November 28, 2014. 

(b) Affected ADs 

This AD supersedes AD 90–26–01, 

Amendment 39–6810 (55 FR 49611, 

November 30, 1990); AD 91–20–02, 

Amendment 39–8036 (56 FR 55231, October 

25, 1991); and AD 2009–05–02, Amendment 

39–15826, (74 FR 8161, February 24, 2009). 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) CF6–80C2 and CF6–80E1 

series turbofan engines with fuel manifold, 

part number (P/N) 1303M31G04, 

1303M32G04, 1303M31G06, 1303M32G06, 

1303M31G07, 1303M32G07, 1303M31G08, 

1303M32G08, 1303M31G12, 1303M32G12, 

2420M70G01, or 2420M71G01, installed. 

(d) Unsafe Condition 

This AD was prompted by a report of an 

under-cowl fire caused by a fuel manifold 

high-pressure fuel leak, and several 

additional reports of fuel leaks. We are 

issuing this AD to prevent failure of the fuel 

manifold, which could lead to uncontrolled 

engine fire, engine damage, and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Fuel Manifold Removal. 

(i) After the effective date of this AD, do 

not return to service any CF6–80C2 or CF6– 

80E1 series engine with fuel manifold P/N 

1303M31G04, 1303M32G04, 1303M31G06, 

1303M32G06, 1303M31G07, 1303M32G07, 

1303M31G08, or 1303M32G08, installed. 

(ii) At the next engine shop visit after the 

effective date of this AD, remove from service 

fuel manifold P/Ns 1303M31G12, 

1303M32G12, 2420M70G01, and 

2420M71G01. 

(2) Fuel Manifold, Loop Clamp, and Tube 

(Block) Clamp Initial and Repetitive 

Inspection and Replacement. 

(i) For CF6–80C2 and CF680E1 series 

engines, with fuel manifold, P/N 

1303M31G12, 1303M32G12, 2420M70G01, or 

2420M71G01 installed, inspect the fuel 

manifold and replace if required by 

inspection results, and replace the loop 

clamps as follows: 

(A) For CF6–80C2 series engines, use 

paragraphs 3.A, 3.C, and 3.D of GE CF6–80C2 

Service Bulletin (SB) No. S/B 73–0326 R04, 

Revision 4, dated December 23, 2009, to do 

the inspection and replacements. 

(B) For CF6–80E1 series engines, use 

paragraphs 3.A, 3.B, and 3.C of GE CF6–80E1 

SB No. S/B 73–0061 R04, Revision 4, dated 

December 23, 2009, to do the inspection and 

replacements. 

(C) Compliance time for fuel manifold 

inspection and loop clamp replacement: 

(1) If the engine is a first-run engine, 

inspect the fuel manifold and replace the 

loop clamps within 7,500 flight hours (FH) 

time-since-new (TSN). 

(2) If the engine’s fuel manifold was ever 

inspected and new loop clamps were 

previously installed, inspect the fuel 

manifold and replace the loop clamps within 

7,500 FH time-since-last-inspection (TSLI). 

(3) If the engine’s fuel manifold was not 

inspected, new loop clamps were not 

installed, or it is unknown when the loop 

clamps were installed, inspect the fuel 

manifold and replace the loop clamps within 

1,750 FH time-since-last-shop-visit or within 

4 months after the effective date of this AD, 

whichever occurs later. 

(ii) For CF6–80C2 and CF6–80E1 series 

engines, with fuel manifold, P/N 

1303M31G12, 1303M32G12, 2420M70G01, or 

2420M71G01, with tube (block) clamp, P/N 

1153M26G15, installed, inspect fuel 

manifold and tube (block) clamps, and 

replace if required by inspection results, as 

follows: 

(A) For CF6–80C2 series engines, use 

paragraphs 3.A.(1) through 3.A.(8) and 3.C.(1) 

through 3.C.(2) of GE CF6–80C2 SB No. S/B 

73–0414, Revision 1, dated May 29, 2014, to 

do the inspection. 

(B) For CF6–80E1 series engines, use 

paragraphs 3.A.(1) through 3.A.(6) and 3.C.(1) 


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Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 63311 

through 3.C.(2) of GE CF6–80E1 SB No. S/B 

73–0121, Revision 1, dated May 29, 2014, to 

do the inspection. 

(C) Compliance time for fuel manifold and 

tube (block) clamp inspection: 

(1) If the engine is a first-run engine, 

inspect the fuel manifold and tube (block) 

clamps within 7,500 FH TSN or within 3 

months after the effective date of this AD, 

whichever occurs later. 

(2) If the engine was previously inspected 

using either of GE CF6–80C2 SB No. S/B 73– 

0414, Revision 1, dated May 29, 2014, or GE 

CF6–80E1 SB No. S/B 73–0121, Revision 1, 

dated May 29, 2014, or earlier versions, then 

inspect the fuel manifold and tube (block) 

clamps within 7,500 FH TSLI or within 3 

months after the effective date of this AD, 

whichever occurs later. 

(3) If the engine is not a first-run engine 

and was not previously inspected using GE 

CF6–80C2 SB No. S/B 73–0414, Revision 1, 

dated May 29, 2014, or GE CF6–80E1 SB No. 

S/B 73–0121, Revision 1, dated May 29, 

2014, or earlier versions, then inspect the 

fuel manifold and tube (block) clamps within 

7,500 FH TSN or within 3 months after the 

effective date of this AD, whichever occurs 

later. 

(iii) Thereafter, inspect fuel manifold, P/Ns 

1303M31G12, 1303M32G12, 2420M70G01, 

and 2420M71G01, and tube (block) clamps, 

replace if required by inspection results, and 

replace the loop clamps within every 7,500 

FH TSLI, using paragraphs (e)(2)(i)(A), 

(e)(2)(i)(B), (e)(2)(ii)(A), and (e)(2)(ii)(B) of 

this AD, as applicable. 

(f) Definition 

(1) For the purposes of this AD, an engine 

shop visit is the induction of an engine into 

the shop where the separation of a major 

engine flange occurs, except that induction 

into the shop for any of the reasons in 

paragraphs (f)(i) through (f)(iv) of this AD is 

not an engine shop visit: 

(i) Induction of an engine into a shop 

solely for removal of the compressor top or 

bottom case for airfoil maintenance, or for 

variable stator vane bushing replacement; 

(ii) Induction of an engine into a shop 

solely for replacement of the turbine rear 

frame; 

(iii) Induction of an engine into a shop 

solely for replacement of the accessory 

gearbox or transfer gearbox, or both; or 

(iv) Induction of an engine into a shop 

solely for core vibration trim balance 

procedure that requires separation of a major 

engine flange. 

(2) For the purposes of this AD, a first-run 

engine is an engine that has not had a shop 

visit since entering service. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Engine Certification 

Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

(2) Previously approved AMOCs for AD 

2009–05–02 (74 FR 8161, February 24, 2009) 

remain approved for the corresponding 

requirements of paragraphs (e)(1) and (e)(2) 

of this AD. 

(h) Related Information 

(1) For more information about this AD, 

contact Kasra Sharifi, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. 01803; 

phone (781) 238–7773; fax: (781) 238–7199; 

email: kasra.sharifi@faa.gov. 

(2) For additional details of the under cowl 

fire that prompted this AD, refer to National 

Transportation Safety Board (NTSB) safety 

recommendation (SR) A–13–028. The NTSB 

SR is available on the Internet at http://

www.ntsb.gov/doclib/recletters/2013/A-13- 

028.pdf. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) General Electric Company (GE) CF6– 

80C2 Service Bulletin (SB) No. 73–0326 R04, 

Revision 4, dated December 23, 2009. 

(ii) GE CF6–80C2 SB No. S/B 73–0414, 

Revision 1, dated May 29, 2014. 

(iii) GE CF6–80E1 SB No. 73–0061 R04, 

Revision 4, dated December 23, 2009. 

(iv) GE CF6–80E1 SB No. S/B 73–0121, 

Revision 1, dated May 29, 2014. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: (513) 552– 

3272; email: geae.aoc@ge.com. 

(4) 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. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

October 7, 2014. 

Kim Smith, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–24697 Filed 10–22–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0345; Directorate 

Identifier 2013–NM–230–AD; Amendment 

39–17998; AD 2014–21–06] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company; Beech Aircraft Corporation) 

Model 400, 400A, 400T, and MU–300 

airplanes. This AD was prompted by a 

report of a failure of the Acme nut 

threads in a pitch trim actuator (PTA). 

This AD requires an inspection to 

determine if PTAs having a certain 

serial number and part number are 

installed, and replacement if they are 

installed. This AD also requires 

repetitive replacements of PTAs with 

new PTAs or certain overhauled PTAs. 

We are issuing this AD to prevent 

failure of the Acme nut threads in the 

PTA, which could lead to loss of control 

of pitch trim and reduced controllability 

of the airplane. 

DATES: This AD is effective November 

28, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 28, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Beechcraft 

Corporation, TMDC, P.O. Box 85, 

Wichita, KS 67201–0085; telephone 

316–676–8238; fax 316–671–2540; email 

tmdc@beechcraft.com; Internet http://

pubs.beechcraft.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–2014– 


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