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.govby 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 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58355 

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: 

ESTIMATED 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. 


asabaliauskas on DSK5VPTVN1PROD with RULES
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 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58357 

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 


asabaliauskas on DSK5VPTVN1PROD with RULES