Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58351 

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: 

2015–19–11 PIAGGIO AERO INDUSTRIES 

S.p.A: Amendment 39–18273; Docket 

No. FAA–2015–2466; Directorate 

Identifier 2015–CE–018–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective November 3, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to PIAGGIO AERO 

INDUSTRIES S.p.A P–180 Model P–180 

airplanes, serial numbers (S/N) 1004 through 

1033, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 53: Fuselage. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated 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 the need to 

restore the safe fatigue life of the bulkhead 

structure. We are issuing this AD to correct 

the safe fatigue life of the airplane. 

(f) Actions and Compliance 

(1) Unless already done, do the actions in 

paragraphs (f)(2) through (f)(4) of this AD at 

whichever of the following compliance times 

occurs later: 

(i) Within 1,500 hours time-in-service (TIS) 

after November 3, 2015 (the effective date of 

this AD), but not to exceed 6,000 hours total 

hours TIS on the airplane; or 

(ii) Within 200 hours TIS after November 

3, 2015 (the effective date of this AD) or 6 

months after November 3, 2015 (the effective 

date of this AD), whichever occurs first. 

(2) Inspect (visually or using a standard 

endoscope) the forward pressurized bulkhead 

to verify presence of bulkhead reinforcement 

following Part A1 of the Accomplishment 

Instructions of PIAGGIO AERO INDUSTRIES 

S.p.A. Service Bulletin 80–0081, Revision 

No. 3, dated: January 20, 2015. 

(i) If the inspection results indicate that the 

reinforcements are properly installed, 

ascertain (visually or by means of standard 

endoscope equipment) that there are no 

cracks or defects. If cracks or defects are 

identified, before further flight, contact 

Piaggio Aero Industries at the address 

specified in paragraph (i)(3) of this AD for an 

FAA-approved repair scheme, approved 

specifically for this AD, and incorporate that 

repair. 

(ii) If the inspection results indicate that 

the reinforcements are not installed, reinforce 

the forward pressurized bulkhead following 

Part A2 of the Accomplishment Instructions 

of PIAGGIO AERO INDUSTRIES S.p.A. 

Service Bulletin 80–0081, Revision No. 3, 

dated: January 20, 2015. 

(3) Modify the forward pressurized 

bulkhead following Part C of the 

Accomplishment Instructions of PIAGGIO 

AERO INDUSTRIES S.p.A. Service Bulletin 

80–0081, Revision No. 3, dated: January 20, 

2015. 

(4) This AD allows credit for the actions 

required in paragraphs (f)(2)(ii) and (f)(3) of 

this AD if done before November 3, 2015 (the 

effective date of this AD) following the 

instructions of PIAGGIO AERO INDUSTRIES 

S.p.A. Service Bulletin 80–0081, Original 

Issue, dated: April 28, 1997; PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 80– 

0081, Revision No. 1, dated: May 11, 2010; 

or PIAGGIO AERO INDUSTRIES S.p.A. 

Service Bulletin 80–0081, Revision No. 2, 

dated: July 19, 2010. 

(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: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090; email: mike.kiesov@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 European Aviation Safety 

Agency (EASA) AD No.: 2015–0071, dated 

April 30, 2015; PIAGGIO AERO INDUSTRIES 

S.p.A. Service Bulletin 80–0081, Original 

Issue, dated: April 28, 1997; PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 80– 

0081, Revision No. 1, dated: May 11, 2010; 

and PIAGGIO AERO INDUSTRIES S.p.A. 

Service Bulletin 80–0081, Revision No. 2, 

dated: July 19, 2010, for related information. 

The MCAI can be found in the AD docket on 

the Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2015-2466-0002. 

(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) PIAGGIO AERO INDUSTRIES S.p.A. 

Service Bulletin 80–0081, Revision No. 3, 

dated: January 20, 2015. 

(ii) Reserved. 

(3) For PIAGGIO AEROSPACE service 

information identified in this AD, contact 

PIAGGIO AERO INDUSTRIES S.p.A, 

Airworthiness Office, Viale Generale 

Disegna, 1—17038 Villanova d’Albenga, 

Savona, Italy; telephone: +39 010 6481800; 

fax: +39 010 6481374; email: 

technicalsupport@piaggioaerospace.it; 

Internet: www.piaggioaerospace.it/en/

customer-support#care. 

(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. In 

addition, you can access this service 

information on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–2466. 

(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. 2015–24257 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–2012–0503; Directorate 

Identifier 2011–SW–032–AD Amendment 

39–18276; AD 2015–19–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(formerly Eurocopter Deutschland 

GmbH) (Airbus Helicopters) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model BO–105A, BO–105C, 


asabaliauskas on DSK5VPTVN1PROD with RULES
58352 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 

and BO–105S helicopters. This AD 

requires inspections to detect oil 

contamination in the main gearbox 

(MGB). This AD was prompted by initial 

findings from an accident investigation 

of a Model BO–105 helicopter, which 

indicated deterioration of the MGB 

caused by a contaminated oil supply. 

The actions of this AD are intended to 

detect oil contamination in the MGB, 

which could result in MGB 

deterioration, MGB failure, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective November 3, 

2015. 

ADDRESSES: 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. 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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–2012– 

0503; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed 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 the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 

6N–321, Fort Worth, Texas 76177. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the EASA AD, 

the economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy., Fort Worth, Texas 76177; 

telephone (817) 222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 11, 2012, at 77 FR 27659, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

add an AD that would apply to 

Eurocopter Deutschland GmbH (now 

Airbus Helicopters) Model BO–105A, 

BO–105C, and BO–105S helicopters. 

The NPRM proposed to require 

inspecting the MGB oil filter and MGB 

magnetic plug and, if the MGB oil filter 

or magnetic plug contained metallic 

fuzz, cleaning the magnetic plug, 

flushing the main transmission, 

changing the oil, and performing a 

ground run. If there was a chip in the 

MGB oil filter or MGB magnetic plug, 

the NPRM proposed replacing the main 

transmission with an airworthy main 

transmission and cleaning the oil cooler 

and oil lines. The NPRM proposed 

repeating the MGB magnetic plug 

inspection every 10 hours time-inservice (TIS) and repeating the MGB oil 

filter inspection every 100 hours TIS. 

The NPRM was prompted by AD No. 

2011–0091, dated May 18, 2011, issued 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for Model BO105 A, BO105 C, BO105 D, 

and BO105S helicopters. EASA AD No. 

2011–0091 requires an inspection of the 

MGB magnetic plug every 10 flight 

hours and an inspection of the Mann oil 

filter every 100 flight hours. 

Actions Since NPRM Was Issued 

Since we issued the NPRM, EASA 

superseded AD No. 2011–0091 and 

issued AD No. 2014–0230, dated 

October 21, 2014, to provide different 

inspection intervals if an improved 

Purolator oil filter is installed. After 

reviewing the EASA AD, we have 

determined that the actions should 

address installation of a Purolator oil 

filter and that the AD should only apply 

if a certain part-numbered Mann or 

Purolator oil filter is installed. The AD 

also increases the inspection interval if 

a Purolator oil filter is installed. 

Comments 

We gave the public the opportunity to 

comment on the NPRM. The following 

presents the one comment received on 

the NPRM and the FAA’s response to 

the comment. 

Request 

The commenter, Timberland Logging, 

requested that the wording be clarified 

so that the AD would require an 

inspection of the magnetic plug only 

and not the chip detector. The 

commenter noted that the term 

‘‘magnetic plug/chip detector’’ in the 

NPRM implies that the 10-hour 

inspection applies to both the magnetic 

plug and the chip detector. The 

commenter stated that the chip detector 

will activate a warning light on the 

pilot’s caution panel with any 

accumulation of fuzz or chips. 

We agree that the wording ‘‘magnetic 

plug/chip detector’’ is confusing; 

therefore, we have revised the wording 

to remove ‘‘chip detector’’ and only 

refer to the ‘‘magnetic plug.’’ 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed except for the changes 

previously described. These changes are 

consistent with the intent of the 

proposals in the NPRM, and will not 

increase the economic burden on any 

operator nor increase the scope of this 

AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to Model 

BO105D helicopters; this AD does not 

because this model is not type 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58353 

certificated in the U.S. The EASA AD 

allows for a grace period between 

checking the magnetic plug by +10 

hours TIS. This AD does not allow the 

grace period. 

Related Service Information 

Airbus Helicopters issued Alert 

Service Bulletin (ASB) No. ASB B0105– 

10–125, Revision 3, dated May 27, 2014 

(ASB BO105–10–125), to specify 

repetitive inspections of the magnetic 

plug and oil filter with different 

inspection intervals based upon what 

type of oil filter is installed. Eurocopter 

(now Airbus Helicopters) Service 

Bulletin B0105–10–126, Revision 1, 

dated August 6, 2013 (ASB B0105–10– 

126), introduces an improved oil filter, 

Purolator part number (P/N) 1740001– 

13. Eurocopter states that Mann oil filter 

P/N 6140063321 will not be available in 

the future and will be replaced by a new 

oil filter provided by Purolator. 

Installation of the Purolator oil filter 

increases the inspection interval of the 

magnetic plug from 10 flight hours to 50 

flight hours and increases the inspection 

interval of the oil filter from 100 flight 

hours to 600 flight hours. 

Costs of Compliance 

We estimate that this AD will affect 

68 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. Labor costs are estimated 

at $85 per work hour. We estimate 2 

work hours to inspect the oil filter and 

chip detector at an estimated $170 per 

helicopter and $11,560 for the fleet per 

inspection cycle. We estimate 40 hours 

to replace a transmission with a 

required parts cost of $225,000 for a 

total cost of $228,400. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

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 to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 airworthiness 

directive (AD): 

2015–19–14 Airbus Helicopters 

Deutschland GmbH (AHD) (formerly 

Eurocopter Deutschland GmbH) 

Helicopters: Amendment 39–18276; 

Docket No. FAA–2012–0503; Directorate 

Identifier 2011–SW–032–AD. 

(a) Applicability 

This AD applies to Model BO–105A, BO– 

105C, and BO–105S helicopters with a Mann 

oil filter part number (P/N) 6140063321 or a 

Purolator oil filter P/N 1740001–13, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

deterioration of the main gearbox (MGB) 

caused by oil contamination. This condition 

could result in MGB failure and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective November 3, 

2015. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 100 hours time-in-service (TIS) 

or at the next MGB magnetic plug or chip 

detector inspection, whichever occurs first, 

and thereafter at intervals not to exceed 100 

hours TIS if a Mann oil filter is installed or 

600 hours TIS if a Purolator oil filter is 

installed, clean and inspect the MGB oil filter 

for chips and the MGB magnetic plug for fine 

particles (metallic fuzz) or chips. A ‘‘chip’’ is 

a solid piece of metal but not metallic fuzz. 

(i) If there are no chips on the MGB oil 

filter or on the magnetic plug, and the 

metallic fuzz covers less than 25% of the 

magnetic plug, clean the magnetic plug. 

(ii) If there are no chips on the MBG oil 

filter or on the magnetic plug, but the 

metallic fuzz covers 25% or more of the 

magnetic plug, flush the main transmission, 

change the oil, perform a ground run for 15 

minutes at the flight-idle power setting, and 

then re-inspect the MGB oil filter and 

magnetic plug for a chip and the quantity of 

metallic fuzz on the metallic plug. 

(iii) If there is a chip on the MGB oil filter 

or on the magnetic plug, or, after complying 

with paragraph (e)(1)(ii) of this AD, metallic 

fuzz covers 25% or more of the magnetic 

plug, replace the main transmission with an 

airworthy main transmission and clean the 

oil cooler and oil lines. 

(2) At intervals not to exceed 10 hours TIS 

if a Mann oil filter is installed and 50 hours 

TIS if a Purolator oil filter, inspect the 

magnetic plug for a chip or metallic fuzz in 

accordance with the requirements of 

paragraph (e)(1) of this AD. 

(3) If a Purolator oil filter has been 

installed on a helicopter, do not install a 

Mann oil filter on that helicopter. 

(f) Special Flight Permit 

A special flight permit will be permitted 

for up to 10 hours TIS for the purpose of 

operating the aircraft to a maintenance 

facility only. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 10101 Hillwood Pkwy., Fort Worth, 

Texas 76177; telephone (817) 222–5110; 

email 9-ASW-FTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 


asabaliauskas on DSK5VPTVN1PROD with RULES
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