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

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 P j 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 Q j 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.


### 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.


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

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://