24 Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

223F and –243F airplanes, certificated in any 

category; manufacturer serial numbers 1004, 

1032, 1051, 1062, 1070, 1092, 1115, 1136, 

1148, 1164, 1175, 1180, 1320, 1332, 1344, 

1350, 1368, 1380, 1386, 1406, 1414, 1418, 

and 1428. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of 

missing fasteners in certain locations of the 

fuselage during production. We are issuing 

this AD to prevent cracking of the fuselage 

due to missing, damaged, or incorrectly 

installed fasteners, which could result in 

reduced structural integrity of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection 

Within 72 months since first flight of the 

airplane: Do a detailed inspection of all 

applicable fuselage zones for missing, 

damaged, or incorrectly installed fasteners, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraphs (g)(1) 

through (g)(4) of this AD. 

(1) Airbus Service Bulletin A330–53–3202, 

dated May 6, 2014. 

(2) Airbus Service Bulletin A330–53–3212, 

dated May 6, 2014. 

(3) Airbus Service Bulletin A330–53–3213, 

dated May 6, 2014. 

(4) Airbus Service Bulletin A330–53–3214, 

dated May 6, 2014. 

(h) Corrective Actions 

If any missing, damaged, or incorrectly 

installed fasteners are found during the 

detailed inspection required by paragraph (g) 

of this AD, before further flight, do a detailed 

inspection for discrepancies (deformation or 

cracking) of the adjacent fastener rows of the 

applicable fuselage zones, in accordance with 

the Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (g)(1) through (g)(4) of this AD. 

(1) If no discrepancy is found, before 

further flight, modify the affected fuselage 

zone, in accordance with the applicable 

service information specified in paragraphs 

(h)(1)(i) through (h)(1)(iv) of this AD. 

(i) Airbus Service Bulletin A330–53–3216, 

dated May 6, 2014. 

(ii) Airbus Service Bulletin A330–53–3217, 

dated May 6, 2014. 

(iii) Airbus Service Bulletin A330–53– 

3218, dated May 6, 2014. 

(iv) Airbus Service Bulletin A330–53– 

3219, dated May 6, 2014. 

(2) If any discrepancy is found, before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(i) Reporting Requirement 

Submit a report (including both positive 

and negative findings), using the applicable 

report sheet attached to the applicable 

service information specified in paragraphs 

(g)(1) through (g)(4) of this AD; of the 

inspection required by paragraph (g) of this 

AD. Submit the report to Airbus, Customer 

Services Directorate, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France, Attn: 

SDC32 Technical Data and Documentation 

Services; fax: (+33) 5 61 93 28 06; email: 

sb.reporting@airbus.com; at the applicable 

time specified in paragraph (i)(1) or (i)(2) of 

this AD. 

(1) For airplanes on which the inspection 

specified in paragraph (g) of this AD is 

accomplished on or after the effective date of 

this AD: Submit the report within 30 days 

after performing the inspection. 

(2) For airplanes on which the inspection 

specified in paragraph (g) of this AD is 

accomplished before the effective date of this 

AD: Submit the report within 30 days after 

the effective date of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(4) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0197, dated 

September 4, 2014, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2015–8136. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

December 21, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32906 Filed 12–31–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8135; Directorate 

Identifier 2015–NM–106–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules 25 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200, 

–300, and –400ER series airplanes. This 

proposed AD was prompted by multiple 

reports of un-commanded escape slide 

inflation. This proposed AD would 

require modifying the regulator valves 

of the forward entry door, forward 

service door, aft entry door, and aft 

service door, and as applicable, 

modifying the regulator valves of the 

mid entry door and mid service door. 

We are proposing this AD to prevent 

out-of-tolerance trigger mechanism 

components (sector and sear) in the 

regulator valves, which can produce 

insufficient trigger engagement and 

reduced pull force values, possibly 

leading to un-commanded deployment 

of the slide during normal airplane 

maintenance or operation, and could 

result in injury to passengers and crew, 

damage to equipment, and the slide 

becoming unusable in an emergency 

evacuation. 

DATES: We must receive comments on 

this proposed AD by February 18, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 98057–3356. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

8135. 

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– 

8135; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kimberly DeVoe, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6495; fax: 

425–917–6590; email: Kimberly.DeVoe@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–8135; Directorate Identifier 2015– 

NM–106–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received reports of two incidents 

of un-commanded escape slide 

inflation. In both cases, out-of-tolerance 

trigger mechanism components (sector 

and sear) were found in the regulator 

valves which produced insufficient 

trigger engagement and reduced pull 

force values. This condition, if not 

corrected, could result in possible uncommanded deployment of the slide 

during normal airplane maintenance or 

operation and could result in injury to 

passengers and crew, damage to 

equipment, and the slide becoming 

unusable in an emergency evacuation. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Service Bulletin 

767–25–0548, Revision 1, dated April 

23, 2015. The service information 

describes procedures for modifying the 

regulator valves of the forward entry 

door, forward service door, aft entry 

door, aft service door, mid entry door 

and mid service door. The modification 

includes replacing the existing trigger 

mechanism sector and sear of the 

regulator valve with new trigger 

mechanism sector and sear. This service 

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 NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information identified 

previously. For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8135. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) The 

steps labeled as RC, including substeps 

under an RC step and any figures 

identified in an RC step, must be done 

to comply with the AD, and an AMOC 


tkelley on DSK3SPTVN1PROD with PROPOSALS
26 Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules 

is required for any deviations to RC 

steps, including substeps and identified 

figures; and (2) steps not labeled as RC 

may be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an AMOC, provided the RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

Costs of Compliance 

We estimate that this proposed AD 

affects 302 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement of trigger mechanism components—forward and aft entry/service doors.15 work-hours × $85 per hour = $1,275 ........ $2,236 $3,511 $1,060,322 

Replacement of trigger mechanism components—mid entry/service doors.8 work-hours × $85 per hour = $680 ............. 1,118 1,798 542,996 

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 above, 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, 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

The Boeing Company: Docket No. FAA– 

2015–8135; Directorate Identifier 2015– 

NM–106–AD. 

(a) Comments Due Date 

We must receive comments by February 

18, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, and –400ER series 

airplanes, certificated in any category, as 

identified in Boeing Service Bulletin 767–25– 

0548, Revision 1, dated April 23, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/furnishings. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of un-commanded escape slide inflation. We 

are issuing this AD to prevent out-oftolerance trigger mechanism components 

(sector and sear) in the regulator valves, 

which can produce insufficient trigger 

engagement and reduced pull force values, 

possibly leading to un-commanded 

deployment of the slide during normal 

airplane maintenance or operation, and could 

result in injury to passengers and crew, 

damage to equipment, and the slide 

becoming unusable in an emergency 

evacuation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of the Trigger Mechanism 

Sector and Sear 

Within 42 months after the effective date 

of this AD, modify the regulator valves of the 

forward entry door, forward service door, aft 

entry door, and aft service door, and as 

applicable, modify the regulator valves of the 

mid entry door and mid service door, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

25–0548, Revision 1, dated April 23, 2015. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

modification required by paragraph (g) of this 

AD, if the modification was performed before 

the effective date of this AD using Boeing 

Service Bulletin 767–25–0548, dated 

November 5, 2014, which is not incorporated 

by reference in this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 (j)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 1 / Monday, January 4, 2016 / Proposed Rules 27 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

(1) For more information about this AD, 

contact Kimberly DeVoe, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 1601 

Lind Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6495; fax: 425–917–6590; 

email: Kimberly.DeVoe@faa.gov. 

(2) 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 98057– 

3356. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, WA, on December 21, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32903 Filed 12–31–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5193; Directorate 

Identifier 2015–NE–35–AD] 

RIN 2120–AA64 

Airworthiness Directives; Technify 

Motors GmbH Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Technify Motors GmbH (type certificate 

previously held by Thielert Aircraft 

Engines GmbH) TAE 125–02–99 and 

TAE 125–02–114 reciprocating engines. 

This proposed AD was prompted by 

reports of in-flight shutdowns (IFSDs) 

on TAE 125–02 engines. This proposed 

AD would require removal of affected 

fuel feed pumps. We are proposing this 

AD to prevent failure of the fuel feed 

pump, which could result in damage to 

the engine and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by March 4, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this proposed AD, contact Technify 

Motors GmbH, Platanenstrasse 14, D– 

09356 Sankt Egidien, Germany, phone: 

+49–37204–696–0; fax: +49–37204– 

696–2912; email: support@

continentaldiesel.de. 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://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5193; 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 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

in the ADDRESSES section. Comments 

will be available in the AD docket 

shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7770; fax: 781–238– 

7199; email: philip.haberlen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–5193; Directorate Identifier 

2015–NE–35–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2015– 

0189, dated September 21, 2015 

(referred to hereinafter as ‘‘the MCAI’’), 

to correct an unsafe condition for the 

specified products. The MCAI states: 

In-flight shut down occurrences have been 

reported on aeroplanes equipped with TAE 

125–02 engines. The initial results of the 

investigations showed that a defective fuel 

feed pump was the probable cause of the 

engine failure. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5193. 

Related Service Information 

Technify Motors GmbH has issued 

Operation & Maintenance Manual, CD– 

135/CD–155, OM–02–02, Issue 4, 

Revision No. 5, dated September 18, 

2015. The service information describes 

procedures for removing and replacing 

the fuel feed pump. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of Germany, and 

is approved for operation in the United 

States. Pursuant to our bilateral 

agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information provided by EASA and 

determined the unsafe condition exists 


tkelley on DSK3SPTVN1PROD with PROPOSALS