Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 63305 

for the remainder of the flight using the 

margins defined by § 25.629(b). 

(vi) Freedom from aeroelastic 

instability must also be shown up to V′ 

in Figure 3 above, for any probable 

system failure condition combined with 

any damage required or selected for 

investigation by § 25.571(b). 

(3) Consideration of certain failure 

conditions may be required by other 

sections of part 25 regardless of 

calculated system reliability. Where 

analysis shows the probability of these 

failure conditions to be less than 10¥9, 

criteria other than those specified in this 

paragraph may be used for structural 

substantiation to show continued safe 

flight and landing. 

c. Failure indications. For fuel system 

failure detection and indication, the 

following apply: 

(1) The fuel system must be checked 

for failure conditions, not extremely 

improbable, that degrade the structural 

capability below the level required by 

part 25 or significantly reduce the 

reliability of the remaining system. As 

far as reasonably practicable, the flight 

crew must be made aware of these 

failures before flight. Certain elements 

of the fuel system, such as mechanical 

and hydraulic components, may use 

special periodic inspections, and 

electronic components may use daily 

checks, in lieu of detection and 

indication systems to achieve the 

objective of this requirement. These 

identified inspections must be limited 

to components that are not readily 

detectable by normal detection and 

indication systems and where service 

history shows that inspections will 

provide an adequate level of safety. 

(2) The existence of any failure 

condition, not extremely improbable, 

during flight that could significantly 

affect the structural capability of the 

airplane and for which the associated 

reduction in airworthiness can be 

minimized by suitable flight limitations, 

requires a caution level alert for 

immediate flightcrew awareness and a 

warning level alert for immediate 

flightcrew awareness and corrective 

action. For example, a flightcrew alert 

during flight is required for failure 

conditions that result in a factor of 

safety between the airplane strength and 

the loads of subpart C below 1.25, or 

flutter margins below V′′, because it 

could significantly affect the structural 

capability of the airplane. 

d. Dispatch with known failure 

conditions. If the airplane is to be 

dispatched in a known fuel system 

failure condition that affects structural 

performance, or affects the reliability of 

the remaining system to maintain 

structural performance, then the 

provisions of these special conditions 

must be met, including the provisions of 

paragraph 2a for the dispatched 

condition, and paragraph 2b for 

subsequent failures. Expected 

operational limitations may be taken 

into account in establishing Pj as the 

probability of failure occurrence for 

determining the safety margin in Figure 

1. Flight limitations and expected 

operational limitations may be taken 

into account in establishing Qj as the 

combined probability of being in the 

dispatched failure condition and the 

subsequent failure condition for the 

safety margins in Figures 2 and 3. These 

limitations must be such that the 

probability of being in this combined 

failure state and then subsequently 

encountering limit load conditions is 

extremely improbable. No reduction in 

these safety margins is allowed if the 

subsequent system failure rate is greater 

than 10¥3 per hour. 

Issued in Renton, Washington, on October 

16, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–25242 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–2014–0532; Directorate 

Identifier 2014–CE–016–AD; Amendment 

39–17994; AD 2014–21–02] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 


wreier-aviles on DSK5TPTVN1PROD with RULESER23OC14.002</GPH>
63306 Federal Register / Vol. 79, No. 205 / Thursday, October 23, 2014 / Rules and Regulations 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Pacific 

Aerospace Limited Model FU24–954 

and FU24A–954 airplanes. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by an 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, which 

could lead to loss of control. We are 

issuing this AD to require actions to 

address the unsafe condition on these 

products. 

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 the AD 

as of November 28, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0532; or in person at 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 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/. You may view 

this referenced 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. 

FOR FURTHER INFORMATION CONTACT: 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to Pacific Aerospace Limited Model 

FU24–954 and FU24A–954 airplanes. 

The NPRM was published in the 

Federal Register on August 5, 2014 (79 

FR 45383). The NPRM proposed to 

correct an unsafe condition for the 

specified products and was based on 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country. 

The MCAI states: 

This AD requires an inspection of the 

control column for mechanical damage, 

deformation and cracks per the instructions 

in Pacific Aerospace Limited (PAL) 

Mandatory Service Bulletin (MSB) No. 

PACSB/FU/095 issue 2 dated 28 May 2014. 

For control columns found with mechanical 

damage or deformation the AD requires a 50 

hour repetitive NDT inspection until 

replacement. Control column replacement is 

required at the next maintenance inspection, 

or within the next 150 hours TIS, whichever 

is the later. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

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

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 45383, August 5, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

45383, August 5, 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 45383, 

August 5, 2014). 

Costs of Compliance 

We estimate that this AD will affect 1 

product of U.S. registry. We also 

estimate that it would take about .5 

work-hour per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of this AD on U.S. operators to 

be $42.50, or $42.50 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 8 work-hours and require parts 

costing $1,000, for a cost of $1,680 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify 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 by searching for 

and locating Docket No. FAA–2014– 

0532; 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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 


wreier-aviles on DSK5TPTVN1PROD with RULES
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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