## 58354 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations

14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.

(h) Additional Information

(1) Airbus Helicopters Alert Service Bulletin No. ASB BO105–10–125, Revision 3, dated May 27, 2014, and Eurocopter Service Bulletin B0105–10–126, Revision 1, dated August 6, 2013, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–

3775; or at http:// www.airbushelicopters.com/techpub.You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, Texas 76177.

(2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD 2014–0230, dated October 21, 2014. You may
view the EASA AD on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2012–0503.

(i) Subject

Joint Aircraft Service Component (JASC)
Code: 6320 Main Gear Box.

Issued in Fort Worth, Texas, on September

17, 2015. James A. Grigg, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2015–24256 Filed 9–28–15; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–2207; Directorate Identifier 2015–CE–003–AD; Amendment**  **39–18272; AD 2015–19–10]**

**RIN 2120–AA64**



### Airworthiness Directives; M7 **Aerospace LLC Airplanes**

**AGENCY**

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding Airworthiness Directive (AD) 97–02–02 for certain Models SA26–AT, SA26–T, SA226–AT, SA226–T, SA226–T(B), SA226–TC, SA227–AC (C–26A), SA227–AT, SA227–BC (C–26A), SA227–CC, SA227–DC (C–26B), and SA227–TT airplanes. AD 97–02–02 required applying torque to the control column pitch bearing attaching nuts, inspecting the bearing assembly, inspecting the elevator control rod end bearing retainer/dust seals, and replacing or installing new parts as necessary. This new AD requires inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage and correct configuration, and replacing parts as necessary. This AD also requires a 10,000-hour time-in-service (TIS) repetitive replacement of the control column pivot bearing and elevator control rod bolt and requires replacement of the control column pivot bearing with the improved design by 35,000 hours TIS. This AD was prompted by loss of elevator control due to failure of the bolt attaching the
elevator control rod to the elevator walking beam under the cockpit floor. We are issuing this AD to correct the unsafe condition on these products.

**DATES** 

### : This AD is effective November 3,

2015.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 3, 2015.

**ADDRESSES** 

### : For service information identified in this AD, contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210) 804–7766;

Internet: http://www.elbitsystemsus.com; email: MetroTech@ M7Aerospace.com. 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. It is also available on the Internet

at http://www.regulations.gov by searching for Docket No. FAA–2015–

2207.
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–2015– 2207; 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**

### : Andrew McAnaul, Aerospace Engineer, FAA, ASW–143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 308–3365; fax: (210) 308–3370; email: andrew.mcanaul@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 97–02–02, Amendment 39–9886 (62 FR 2552, January 17, 1997), (‘‘AD 97–02–02’’). AD 97–02–02 applied to certain M7 Aerospace LLC Models SA26–AT, SA26–T, SA226–AT, SA226–T, SA226– T(B), SA226–TC, SA227–AC (C–26A), SA227–AT, SA227–BC (C–26A), SA227–CC, SA227–DC (C–26B), and SA227–TT airplanes. The NPRM published in the Federal Register on June 16, 2015 (80 FR 34326). The NPRM was prompted by an operator experiencing complete loss of elevator
control due to failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. A follow-on inspection of the operator’s fleet revealed a variety of
hardware installed. Some hardware matched the illustrated parts catalog (IPC), some matched the AD 97–02–02 configuration, and some matched neither of those configurations.

When AD 97–02–02 was issued, the
IPC was never revised to match the hardware configuration called out in AD
97–02–02 or in the service information
associated with that AD. Because of the
conflict between the AD and the IPC configurations, an airplane that was in compliance with the requirements of
AD 97–02–02 could have had an incorrect hardware configuration installed during routine maintenance after complying with the AD. The IPC has been updated and corrected by M7 Aerospace, LLC.

Also, since we issued AD 97–02–02, the manufacturer developed an improved design for the control column pivot bearing and support structure that terminates the repetitive torque check and replacement of control column pivot bearings.

The manufacturer also issued new
service information that adds the 10,000-hour TIS repetitive replacement of the control column pivot bearing that
is in the airworthiness limitations section (ALS) of the airplane maintenance manual (AMM) and (if this revision is mandated) requires the replacement of the pivot bearing with the improved design by 35,000 hours TIS that is in the supplemental inspections document (SID). Issuance of


## 58355 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations

the new service information, the revised IPC, and this AD will eliminate the conflicts between AD 97–02–02, the service information, the IPC, the ALS,
and the SID.

The NPRM (80 FR 34326, June 16, 2015) proposed to require inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage and correct configuration, and replacing parts as necessary. The NPRM also proposed to require a 10,000-hour TIS repetitive replacement of the control column pivot bearing and elevator control rod bolt and require replacement of the control column pivot bearing with the improved design by 35,000 hours TIS. Replacing the original control column pivot bearing with the improved design terminates the requirement to repetitively replace the original control column pivot bearing every 10,000 hours. We are issuing this AD to correct the unsafe condition on these products.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 34326, June 16, 2015) 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 this 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 (80 FR 34326, June 16, 2015) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 34326, June 16, 2015).

Relevant Service Information Under 1

CFR 51

We reviewed M7 Aerospace SA26
Series Service Bulletin No. 26–27–30– 046 R2, dated December 5, 2014;
Fairchild Aircraft SA26 Series Service Bulletin No. 26–27–30–047, dated June 16, 1997; M7 Aerospace SA226 Series Service Bulletin No. 226–27–060 R2, dated December 5, 2014; Fairchild Aerospace SA226 Series Service Bulletin No. 226–27–061, dated June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227–27–041 R2, dated December 5, 2014; Fairchild
Aircraft SA227 Series Service Bulletin No. 227–27–042, dated June 16, 1997; M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7–27–010 R2, dated December 5, 2014; and Fairchild Aircraft SA227 Series Commuter Category Service Bulletin No. CC7–27–011, dated June 16, 1997. The service information describes procedures for inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage, and replacing parts as necessary. The service information also adds a repetitive replacement of the control column pivot bearings at 10,000 hours TIS and requires replacement of the control column pivot bearing with the improved design within 35,000
hours TIS. This information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the

**ADDRESSES** 

### section of this AD.

Costs of Compliance

We estimate that this AD affects 360 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

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

Inspection of torque on the control column

pivot bearing. 2 work-hours × $85 per hour = $170 ............ Not applicable $170 $61,200

Control column pivot bearing replacement .... 8 work-hours × $85 per hour = $680 ............ $300 ................ 980 352,800 New designed control column pivot bearing

replacement. 20 work-hours × $85 per hour = $1,700 ....... $2,450 ............. 4,150 1,494,000

Elevator rod end bolt replacement ................. 4 work-hours × $85 per hour = $340 ............ $10 .................. 350 126,000



### 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.


## 58356 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 97–02–02, Amendment 39–9886 (62 FR 2552, January 17, 1997), and adding the following new AD:

2015–19–10 M7 Aerospace: Amendment 39–18272; Docket No. FAA–2015–2207;
Directorate Identifier 2015–CE–003–AD.

(a) Effective Date

This AD is effective November 3, 2015.

(b) Affected ADs

This AD supersedes AD 97–02–02, Amendment 39–9886 (62 FR 2552, January 17, 1997).

(c) Applicability

This AD applies to M7 Aerospace LLC Models SA26–AT, SA26–T, SA226–AT, SA226–T, SA226–T(B), SA226–TC, SA227– AC (C–26A), SA227–AT, SA227–BC (C–26A), SA227–CC, SA227–DC (C–26B), SA227–TT, all serial numbers, certificated in any category.

(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

AD 97–02–02 (62 FR 2552, January 17, 1997) (‘‘AD 97–02–02’’) resulted from reports of Fairchild SA227 series airplanes losing pitch control in-flight. This supersedure was prompted by an operator experiencing complete loss of elevator control because of failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. We are issuing this AD to prevent loss of pitch control, which if not corrected, could result in loss of airplane
control.

(f) Compliance

Comply with this AD within the compliance times specified, unless already done. Models SA227–CC and SA227–DC, serial numbers 892, 893, and 895 and up, have the revised (modified) configuration. Since those airplanes are already in compliance, they do not have to do the actions in paragraphs (h) or (i) of this AD, including all subparagraphs. Those airplanes must still do the actions required in paragraph (j) of this AD, including all subparagraphs.

(g) Credit for Actions Accomplished in
Accordance With Previous Service
Information

This AD allows credit for the control column pivot bearing torque check and initial replacement required in paragraph (i)(2) of this AD and the elevator rod bolt inspection and initial replacement required in paragraphs (j)(1) and (j)(3)(i) of this AD, if done before November 3, 2015 (the effective date of this AD), following the procedures specified in the Accomplishment Instructions of the applicable service information listed in paragraphs (g)(1) through (g)(4) of this AD: (1) M7 Aerospace SA227 Commuter Category Service Bulletin No. CC7–27–010, original issue or revision 1.

(2) M7 Aerospace SA227 Series Service Bulletin No. 227–27–041, original issue or

revision 1.

(3) M7 Aerospace SA226 Series Service Bulletin No. 226–27–060, original issue or

revision 1.

(4) M7 Aerospace SA26 Series Service Bulletin No. 26–27–30–046, original issue or

revision 1.

(h) Control Column Pivot Bearing Revised (Modified) Configuration

(1) On or before the airplane accumulates a total of 35,000 hours time-in-service (TIS) or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later, you must revise (modify) the control column pivot bearing configuration with the improved design. Use the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the actions for paragraph (i) of this AD, including all subparagraphs, but you must still complete the required actions in paragraph (j) of this AD, including all subparagraphs.

(i) Fairchild Aircraft SA26 Series Service Bulletin No. 26–27–30–047, dated June 16,

1997;

(ii) Fairchild Aircraft SA226 Series Service Bulletin No. 226–27–061, dated June 16,

1997;

(iii) Fairchild Aircraft SA227 Series Service Bulletin No. 227–27–042, dated June

16, 1997; or

(iv) Fairchild Aircraft SA227 Series Commuter Category No. CC7–27–011, dated June 16, 1997.

(2) You may at any time before 35,000 hours TIS revise (modify) the control column pivot bearing configuration with the improved design to terminate the repetitive replacement of the original control column pivot bearing using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. This action terminates the requirements of paragraph (i) of this AD, including all subparagraphs, but you must still complete the required actions in paragraph (j) of this AD, including all subparagraphs.

(i) Torque Check or Replacement of the Control Column Pivot Bearing

(1) Use the service information, as applicable, listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to do a control column pivot bearing torque check or replacement at the applicable compliance times in paragraph (i)(2) or (i)(3) of this AD, including all subparagraphs:

(i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26–27–30–046 R2, dated December 5, 2014;

(ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226–27–060 R2, dated December 5, 2014;

(iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227–27–041 R2, dated December 5, 2014; or (iv) M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7–27–010 R2, December 5, 2014.

(2) For airplanes where the control column pivot bearing has been torque checked or replaced within the last 10,000 hours TIS before November 3, 2015 (the effective date of this AD) using the applicable service information listed in paragraph (g)(1) through (g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, do one of the following actions:

(i) Within the next 10,000 hours TIS after the last control column pivot bearing replacement or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later, and repetitively thereafter every 10,000 hours TIS, replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or

(ii) Within the next 10,000 hours TIS after the last control column pivot bearing replacement or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later, revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. No other actions are required for paragraph (i) of this AD, including all subparagraphs, but you must still complete the actions in paragraph (j) of this AD, including all subparagraphs.

(3) For airplanes where the control column pivot bearing has not been torque checked or replaced within the last 10,000 hours TIS before November 3, 2015 (the effective date of this AD) using the applicable service information listed in paragraphs (g)(1) through (g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, within the next 200 hours TIS after November 3, 2015 (the effective date of this AD), torque check the control column pivot bearing following paragraph 2.A. of the service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD.

(4) If nut movement occurs during the torque check required in paragraph (i)(3) of this AD, do one of the following actions:

(i) Before further flight and repetitively thereafter at intervals not to exceed every 10,000 hours TIS, replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or

(ii) Before further flight, revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. No other actions are required for paragraph (i) of this AD, including all


## 58357 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations

subparagraphs, but you must still complete the actions in paragraph (j) of this AD, including all subparagraphs.

(5) If no nut movement occurs during the torque check required in paragraph (i)(3) of this AD, do one of the following actions:

(i) Within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or

(ii) Within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing.

(j) Inspect the Elevator Control Rod Ends
and Hardware

(1) Within the next 200 hours TIS after November 3, 2015 (the effective date of this AD), inspect the elevator control rod ends and hardware for wear, creasing, or other damage and verify the elevator rod bolt and
attachment hardware for correct configuration following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this

AD.

(2) If any damage is found during the inspection required in paragraph (j)(1) of this
AD or the elevator rod bolt and attachment
hardware does not match the correct configuration, before further flight, replace the elevator rod bolt, rod ends, and associated hardware following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this

AD.

(3) Replace the elevator rod end bolt and associated hardware following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD at whichever of the following compliance times applies and repetitively thereafter at intervals not to exceed 10,000 hours TIS:

(i) For airplanes where the elevator rod bolt has been replaced: Within the next 10,000
hours TIS after the last elevator rod bolt replacement or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later; or

(ii) For airplanes where the elevator rod bolt has never been replaced: Within the next 200 hours TIS after November 3, 2015 (the effective date of this AD).

(k) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Fort Worth Airplane Certification Office, 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 paragraph (l)(1) of this AD.

(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.

(l) Related Information

(1) For more information about this AD, contact Andrew McAnaul, Aerospace Engineer, FAA, ASW–143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 308– 3365; fax: (210) 308–3370; email: andrew.mcanaul@faa.gov.

(m) 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) M7 Aerospace LLC SA26 Series Service Bulletin No. 26–27–30–046 R2, dated December 5, 2014.

(ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226–27–060 R2, dated December 5, 2014.

(iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227–27–041 R2, dated December 5, 2014.

(iv) M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7–27–010 R2, December 5, 2014.

(v) Fairchild Aircraft SA26 Series Service Bulletin No. 26–27–30–047, dated June 16,

1997.

(vi) Fairchild Aircraft SA226 Series Service Bulletin No. 226–27–061, dated June 16,

1997.

(vii) Fairchild Aircraft SA227 Series Service Bulletin No. 227–27–042, dated June

16, 1997.

(viii) Fairchild Aircraft SA227 Series Commuter Category No. CC7–27–011, dated June 16, 1997.

(3) For service information identified in this AD, contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210)
804–7766; Internet: http://www.elbitsystemsus.com; email: MetroTech@ M7Aerospace.com.

(4) You may view this service information at 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 September 17, 2015.
Melvin Johnson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–24249 Filed 9–28–15; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0773; Directorate Identifier 2014–NM–068–AD; Amendment**  **39–18271; AD 2015–19–09]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY**

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787–8 airplanes. This AD was prompted by reports of a potential latent failure of the fuel shutoff valve actuator circuitry, which was not identified during actuator development. This AD requires replacing certain engine and auxiliary power unit (APU) fuel shutoff valve actuators with new actuators, and also requires revising the maintenance or inspection program to include a new
airworthiness limitation into the
Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA). We are issuing this
AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire
that could lead to structural failure.

**DATES** 

### : This AD is effective November 3,

2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 3, 2015.

**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