48828 Federal Register / Vol. 78, No. 155 / Monday, August 12, 2013 / Proposed Rules 

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– 

2013–0672; Directorate Identifier 2013– 

NM–058–AD. 

(a) Comments Due Date 

We must receive comments by September 

26, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

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

series airplanes; certificated in any category; 

as identified in Boeing Service Bulletin 767– 

28–0105, dated January 12, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by reports 

indicating that a standard access door was 

located where an impact-resistant access 

door was required, and stencils were missing 

from some impact-resistant access doors. We 

are issuing this AD to prevent foreign object 

penetration of the fuel tank, which could 

cause a fuel leak near an ignition source (e.g., 

hot brakes or engine nozzle), consequently 

leading to a fuel-fed fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Within 72 months after the effective date 

of this AD, do the actions specified in 

paragraphs (g)(1) and (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28–0105, dated January 12, 2012. 

(1) Do either a general visual inspection or 

ultrasonic non-destructive test of the left- and 

right-hand wing fuel tank access doors to 

determine whether impact-resistant access 

doors are installed in the correct locations. If 

any standard access door is found, before 

further flight, replace with an impactresistant access door, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–28–0105, dated January 

12, 2012. 

(2) Do a general visual inspection of the 

left- and right-hand wing fuel tank impactresistant access doors to verify stencils and 

index markers are applied. If a stencil or 

index marker is missing, before further flight, 

apply stencil or index marker, as applicable, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

28–0105, dated January 12, 2012. 

(h) Maintenance Program Revision 

Within 60 days after the effective date of 

this AD, revise the maintenance program to 

incorporate critical design configuration 

control limitation (CDCCL) Task 57–AWL– 

01, ‘‘Impact-Resistant Fuel Tank Access 

Door,’’ of Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs) of Boeing 

767 Maintenance Planning Data Document 

D622T001–9, Revision October 2012. 

(i) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9–ANMSeattle-ACO–AMOC-Requests@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 method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Suzanne Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6438; fax: 425–917–6590; 

email: suzanne.lucier@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 review copies of the referenced 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 August 

2, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19458 Filed 8–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0002; Directorate 

Identifier 2011–NE–42–AD] 

RIN 2120–AA64 

Airworthiness Directives; Continental 

Motors, Inc. Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


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Federal Register / Vol. 78, No. 155 / Monday, August 12, 2013 / Proposed Rules 48829 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airmotive Engineering Corp. 

replacement parts manufacturer 

approval (PMA) cylinder assemblies 

marketed by Engine Components 

International Division (ECi), used on the 

Continental Motors, Inc. (CMI) models 

520 and 550 reciprocating engines, and 

all other engine models approved for the 

use of CMI models 520 and 550 cylinder 

assemblies such as the CMI model 470 

when modified by supplemental type 

certificate (STC). This proposed AD was 

prompted by failure reports of multiple 

cylinder head-to-barrel separations and 

cracked and leaking aluminum cylinder 

heads. This proposed AD would require 

initial and repetitive inspections, 

replacement of cracked cylinders, and 

replacement of cylinder assemblies at 

reduced times-in-service. This proposed 

AD would also prohibit the installation 

of affected cylinder assemblies into any 

engine. We are proposing this AD to 

prevent cylinder head cracks, engine 

failure, and loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 11, 2013. 

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 certain service information 

identified in this proposed AD, contact 

Continental Motors, Inc., PO Box 90, 

Mobile, AL 36601; phone: 251–438– 

3411, Internet: http://tcmlink.com/ 

servicebulletins.cfm. For certain other 

service information identified in this 

proposed AD, contact Engine 

Components International Division, 

9503 Middlex Drive, San Antonio, TX 

78217; phone 210–820–8101; Internet: 

http//www.eci.aero/pages/ 

tech_svcpubs.aspx. 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; 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: 

Jurgen E. Priester, Aerospace Engineer, 

Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, TX 76137; phone: 

817–222–5159; fax: 817–222–5785; 

email: jurgen.e.priester@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– 

2012–0002; Directorate Identifier 2011– 

NE–42–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 multiple failure reports 

of Airmotive Engineering Corp. PMA 

cylinder assemblies, part number (P/N) 

AEC631397, ECi Class 71 and Class 76, 

installed on certain CMI models IO–520, 

TSIO–520, IO–550, and IOF–550 

reciprocating engines and other engines 

approved for the use of CMI models 520 

and 550 cylinder assemblies such as the 

CMI model 470 when modified by STC. 

ECi part numbering includes four 

Classes of P/N AEC631397 cylinder 

assemblies based upon their intended 

use. Only Classes 71 and 76 are affected; 

Classes 68 and 70 are not affected. The 

Class number appears in the ECi P/N 

cylinder marking immediately following 

AEC631397. These markings are found 

on the bottom flange of the cylinder. We 

identified two independent failure 

modes resulting in the cylinder head 

separations; however, the exact root 

cause of each failure mode could not be 

definitively identified. One failure mode 

is cracking that initiates in the internal 

dome radius of the cylinder head and 

the second is cracking at the cylinder 

head-to-barrel threads. The affected 

cylinder assemblies are separated into 

two manufacturing groups that would 

require the actions in this proposed AD. 

Those two groups are defined by serial 

number (S/N) ranges. One group 

consists of cylinder assemblies with S/ 

N 1 through S/N 33696. The second 

group consists of cylinder assemblies 

with S/N 33697 through S/N 61176. The 

unsafe condition, if not corrected, could 

result in cylinder head cracks, engine 

failure, and loss of the airplane. 

Airmotive Engineering Corp. held a 

meeting, which we attended, on 

December 11, 2012, to discuss certain 

active PMA projects. Also on their 

agenda was a briefing to us on their 

meeting with the National 

Transportation Safety Board (NTSB) 

regarding the subject of this proposed 

AD. Although that briefing was not 

intentioned by us, because it occurred, 

we are placing a summary and a copy 

of what they provided for our 

consideration, into the AD docket for 

public review. 

Airmotive Engineering Corp. held 

another meeting, with us and the NTSB 

in attendance, on February 14, 2013. 

The purpose of the meeting was to 

further discuss the causes of their 

cylinder failures and what they have 

done to address these failures. We are 

placing all of the information from this 

meeting in the AD docket for public 

review. 

Knowing the likely impact that 

compliance with the AD will have upon 

the owners and operators, a detailed 

review was performed to consider all 

aspects of the information provided by 

Airmotive Engineering Corp. After 

considering all factors, which included, 

for example, the efforts of two Chief 

Scientific and Technical Advisors, data 

from the FAA/Airmotive Engineering 

Corp. meetings, and the application of 

the FAA Policy Statement on Risk 

Assessment 08/07/13for Reciprocating 

Engine Airworthiness Directives (PS– 

ANE100–1999–00006), we concluded 

that proceeding with this proposed AD 

to correct the unsafe condition was 

appropriate. 

Relevant Service Information 

We reviewed Continental Motors, Inc. 

Service Bulletin (SB) No. SB96–12, 

dated September 10, 1996. Part 1 

Section C of the SB describes 

procedures for leak checking cylinder 

assemblies. We also reviewed ECi 

Service Instruction No. 99–8–1, 


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48830 Federal Register / Vol. 78, No. 155 / Monday, August 12, 2013 / Proposed Rules 

Revision 9, dated February 23, 2009, 

Sections 4.3, 4.4, 6.1, and 6.2, which 

provide information on cylinder 

identification and part numbering. 

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 divides ECi 

cylinder assemblies, P/N AEC631397, 

Class 71 and Class 76, into two groups; 

Group A cylinder assemblies and Group 

B cylinder assemblies. Group A cylinder 

assemblies are those cylinder assemblies 

with S/N 1 through S/N 33696. Group 

B cylinder assemblies are those cylinder 

assemblies with S/N 33697 through S/ 

N 61176. This proposed AD would 

require removing Group A cylinder 

assemblies from service within 25 

operating hours if, on the effective date 

of the AD, the cylinder operating hours 

are fewer than 500 hours, or more than 

1,000 hours. This proposed AD would 

also require removing Group B cylinder 

assemblies from service within 25 

operating hours if, on the effective date 

of the AD, the cylinder operating hours 

are 1,000 or more. 

This proposed AD would also require 

repetitive visual inspections, 

compression tests, and leak checks for 

cracks, for Group A cylinder assemblies 

with between 500 and 1,000 operating 

hours, and for Group B cylinder 

assemblies with fewer than 1,000 

operating hours, until they are removed 

from service. 

Finally, this proposed AD would also 

prohibit installing affected ECi cylinder 

assemblies onto any engine and would 

require reporting to the FAA all 

removed cylinder assemblies. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 6,000 Continental 

Motors, Inc. models IO–520, TSIO–520, 

IO–550, and IOF–550 reciprocating 

engines and all other engine models 

approved for the use of CMI models 520 

and 550 cylinder assemblies (such as 

the CMI model 470 when modified by 

STC), installed on airplanes of U.S. 

registry. We also estimate that each 

affected ECi cylinder will be inspected 

on average four times in the first year. 

We also estimate that about six hours 

per engine would be required to perform 

the visual inspection, compression test, 

and leak check. The average labor rate 

is $85 per hour. Finally, we estimate 

that about 18 hours would be required 

to replace all six cylinder assemblies 

during scheduled overhaul 

maintenance, and that a replacement 

cylinder assembly would cost about 

$1,700. Based on these figures, we 

estimate the total cost of this proposed 

AD to U.S. operators to change all ECi 

cylinders to be $82,620,000. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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 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. 

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): 

Continental Motors, Inc. (formerly Teledyne 

Continental Motors, Inc., formerly 

Continental): Docket No. FAA–2012– 

0002; Directorate Identifier 2011–NE– 

42–AD. 

(a) Comments Due Date 

We must receive comments by October 11, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following 

Continental Motors, Inc. (CMI) models 520 

and 550 reciprocating engines, and all other 

engine models approved for the use of CMI 

models 520 and 550 cylinder assemblies such 

as the CMI model 470 when modified by 

supplemental type certificate (STC), with 

Airmotive Engineering Corp. replacement 

parts manufacturer approval (PMA) cylinder 

assemblies, marketed by Engine Components 

International Division (hereinafter referred to 

as ECi), part number (P/N) AEC631397, with 

ECi Class 71 or Class 76, serial number (S/ 

N) 1 through S/N 33696, or S/N 33697 

through S/N 61176, installed on, but not 

limited to: 

(1) IO–520–A, –B, –BA, –BB, –C, –CB, –D, 

–E, –F, –J, –K, –L, –M, –MB, –N, –NB, and 

LIO–520–P. 

(2) TSIO–520–A, –AE, –AF, –B, –BB, –BE, 

–C, –CE, –D, –DB, –E, –EB, –G, –H, –J, –JB, 

–K, –KB, –L, –LB, –M, –N, –NB, –P, –R, –T, 

–U, –UB, –VB, –WB, and LTSIO–520–AE. 

(3) IO–550–A, –B, –C, –D, –E, –F, and –L. 

(4) IOF–550–B, –C, –D, –E, –F, and –L. 

(5) Other engines using CMI models 520 

and 550 cylinder assemblies, such as the CMI 

model 470 when modified by STC. 

(d) Unsafe Condition 

This AD was prompted by reports of 

multiple cylinder head-to-barrel separations 

and cracked and leaking aluminum cylinder 

heads. We are issuing this AD to prevent 

cylinder head cracks, engine failure, and loss 

of the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Review the engine maintenance records 

to determine if any affected cylinders were 


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Federal Register / Vol. 78, No. 155 / Monday, August 12, 2013 / Proposed Rules 48831 

installed at the time of engine overhaul or 

during any other maintenance event, or were 

installed when the engine was modified and 

are currently installed. 

(2) If you do not have any of the affected 

ECi cylinders installed on your engine, no 

further action is required. 

(f) Cylinder Identification and Serial 

Number Location 

(1) Check the cylinder assembly P/N and 

Class number. The ECi cylinder assembly, P/ 

N AEC631397, Class 71 or Class 76, is 

stamped on the bottom flange of the cylinder 

barrel. Guidance on the P/N and Class 

number description and location can be 

found in ECi Service Instruction No. 99-8-1, 

Revision 9, dated February 23, 2009. 

(2) For ECi cylinder assemblies, P/N 

AEC631397, manufactured through 2008, 

find the cylinder assembly S/N stamped on 

the intake port boss two inches down from 

the top edge of the head. 

(3) For ECi cylinder assemblies, P/N 

AEC631397, manufactured on or after 

January 1, 2009, find the cylinder assembly 

S/N stamped just below the top edge of the 

head on the exhaust port side. 

(4) If you cannot see the cylinder assembly 

P/N when the cylinder assembly is installed 

on the engine, an alternative method of 

identification may be used as follows: 

(i) Remove the cylinder rocker box cover. 

(ii) Find the letters ECi, cast into the 

cylinder head between the valve stems. 

(iii) Check the cylinder head casting P/N. 

Affected cylinder assemblies have the 

cylinder head casting P/N, AEC65385, cast 

into the cylinder head between the valve 

stems. 

(iv) Find the cylinder assembly S/N as 

specified in paragraph (f)(2) or (f)(3) of this 

AD as applicable. 

(g) Removal From Service 

(1) For those Group A cylinder assemblies, 

P/N AEC631397, ECi Class 71 or 76, S/N 1 

through S/N 33696, with fewer than 500 

operating hours time-in-service (TIS) or with 

more than 1,000 operating hours TIS on the 

effective date of this AD, remove the cylinder 

assemblies from service within the next 25 

operating hours TIS. 

(2) For those Group B cylinder assemblies, 

P/N AEC631397, ECi Class 71 or 76, S/N 

33697 through S/N 61176, with more than 

1,000 operating hours TIS on the effective 

date of this AD, remove the cylinder 

assemblies from service within the next 25 

operating hours TIS. 

(h) Inspection of Group A Cylinder 

Assemblies With Between 500 and 1,000 

Operating Hours TIS and Group B Cylinder 

Assemblies With Fewer Than 1,000 

Operating Hours TIS 

(1) Within the next 10 operating hours TIS 

after the effective date of this AD, visually 

inspect, compression test, and leak check the 

Group A cylinder assemblies with between 

500 and 1,000 operating hours TIS, and 

Group B cylinder assemblies with fewer than 

1,000 operating hours TIS. Use paragraphs 

(h)(2) through (h)(5) of this AD to do the 

inspection, test, and leak check. 

(2) Visually inspect the exterior of each 

cylinder head and barrel interface around the 

perimeter of the cylinder as follows: 

(i) Before any engine cleaning, with good 

lighting, look for signs of white or black 

combustion products between cooling fins, 

especially on the exhaust valve side of the 

cylinder assembly. 

(ii) Remove the cylinder from service if you 

find any indication of a crack or black 

combustion products on the side of a 

cylinder. 

(iii) The presence of oil or a normal dirty 

appearance may not indicate a head crack. 

(3) Perform a standard differential 

compression test to the cylinder assembly. If 

the cylinder assembly has a pressure reading 

of less than 55/80 pounds per square inch 

gauge pressure, on the differential pressure 

test gauges, remove the cylinder assembly 

from service. 

(4) Use Part 1 Section C ‘‘Leak Check’’ of 

Teledyne Continental Motors Service 

Bulletin (SB) No. SB96–12, dated September 

10, 1996, to perform the leak checks required 

by this AD. 

(5) Remove from service any cylinder 

assembly found cracked and/or leaking. 

(6) Repeat paragraphs (h)(2) though (h)(5) 

of this AD within every 50 operating hours 

TIS since last inspection. Remove from 

service any cylinder assembly before 

accumulating 1,000 operating hours TIS. 

(i) Installation Prohibitions 

After the effective date of this AD: 

(1) Do not repair, or reinstall onto any 

engine, any cylinder assembly removed per 

this AD. 

(2) Do not install any ECi cylinder 

assemblies, P/N AEC631397, ECi Class 71 or 

76, with the S/Ns listed in paragraph (c) of 

this AD, onto any engine. 

(3) Do not install any engine having one or 

more ECi cylinder assemblies, P/N 

AEC631397, ECi Class 71 or 76, with the S/ 

Ns listed in paragraph (c) of this AD, into any 

aircraft. 

(4) Do not return to service any aircraft that 

has an engine with an ECi cylinder assembly 

subject to this AD, if the cylinder assembly 

has 1,000 or more operating hours TIS. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Special Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(k) Reporting Requirements 

Report to the FAA all cylinder assemblies 

that you removed per this AD. Send your 

report to the Special Certification Office, 

FAA, Rotorcraft Directorate, Attn: Jurgen E. 

Priester, Aerospace Engineer, 2601 Meacham 

Blvd., Fort Worth, TX 76137; phone: 817– 

222–5159; fax: 817–222–5785; email: 9-ASW190-COS@faa.gov. Include the following 

information: 

(1) Aircraft model. 

(2) Continental Motors, Inc. engine model 

number. 

(3) ECi cylinder assembly S/N. 

(4) Cylinder assembly total operating 

hours. 

(5) Installation date of ECi cylinder 

assembly. 

(6) Airplane utilization average per year 

(flight hours per year). 

(7) Number of flight hours since last 

mandatory inspection required by this AD. 

(8) Reason for cylinder removal, i.e., 

leaking head with cracks or other indications 

found, failed compression test, valves or 

rings leaking, or a head separation. 

(9) How the defect was found, i.e., visual 

inspection, leak check, compression test, etc. 

(10) Source of leak(s). 

(11) Location of crack(s). Locate by 

counting the number of cooling fins up from 

the head/barrel interface. 

(12) Length of crack(s). 

(13) Location of separation. Locate by 

counting the number of cooling fins up from 

the head/barrel interface. 

(14) Your contact information (optional). 

(l) Paperwork Reduction Act Burden 

Statement 

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. 

(m) Related Information 

(1) For more information about this AD, 

contact Jurgen E. Priester, Aerospace 

Engineer, Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham Blvd., 

Fort Worth, TX 76193; phone: 817–222–5159; 

fax: 817–222–5785; email: 

jurgen.e.priester@faa.gov. 

(2) For ECi Service Instruction No. 99–8– 

1, Revision 9, dated February 23, 2009, 

which is not incorporated by reference in this 

AD, contact Engine Components 

International Division, 9503 Middlex Drive, 

San Antonio, TX 78217; phone 210–820– 

8101; Internet: http//www.eci.aero/pages/ 

tech_svcpubs.aspx. 

(3) For other service information 

referenced in this AD, contact Continental 

Motors, Inc., PO Box 90, Mobile, AL 36601; 

phone: 251–438–3411, Internet: http:// 

tcmlink.com/servicebulletins.cfm. 

(4) 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. 


ehiers on DSK2VPTVN1PROD with PROPOSALS-1
48832 Federal Register / Vol. 78, No. 155 / Monday, August 12, 2013 / Proposed Rules 

Issued in Burlington, Massachusetts, on 

August 5, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19414 Filed 8–9–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0674; Directorate 

Identifier 2012–NM–217–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This proposed 

AD was prompted by a design review, 

which revealed that no controlled 

bonding provisions are present on a 

number of critical locations inside the 

fuel tank or connected to the fuel tank 

wall. This proposed AD would require 

installing additional bonding provisions 

in the fuel tank, and revising the 

airplane maintenance program by 

incorporating fuel airworthiness 

limitation items and critical design 

configuration control limitations. We 

are proposing this AD to prevent an 

ignition source in the fuel tank vapor 

space, which could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by September 26, 

2013. 

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. 

• 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.com. You may 

review copies of the referenced 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. 

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 proposed AD, the MCAI, 

the regulatory 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 FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–1137; fax 425–227–1149. 

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–2013–0674; Directorate Identifier 

2012–NM–217–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 we receive 

about 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 

Airworthiness Directive 2012–0242, 

dated November 12, 2012 (referred to 

after this the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Prompted by an accident * * *, the FAA 

published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. 

The design review conducted by Fokker 

Services on the Fokker 70 and Fokker 100 in 

response to these regulations revealed that no 

controlled bonding provisions are present on 

a number of critical locations, inside the fuel 

tank or connected to the fuel tank wall. 

This condition, if not corrected, may create 

an ignition source in the fuel tank vapour 

space, possibly resulting in a fuel tank 

explosion and consequent loss of the 

aeroplane. 

For the reasons described above, this [EASA] 

AD requires the installation of additional 

bonding provisions and, subsequently, the 

implementation of the associated Fuel 

Airworthiness Limitation Items (ALI) and 

Critical Design Configuration Control 

Limitations (CDCCL[s]) [and revising the 

maintenance program to incorporate the ALIs 

and CDCCLs]. 

You may obtain further information by 

examining the MCAI in the AD docket. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 (66 FR 

23086, May 7, 2001) requires certain 

type design (i.e., type certificate (TC) 

and supplemental type certificate (STC)) 

holders to substantiate that their fuel 

tank systems can prevent ignition 

sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 


ehiers on DSK2VPTVN1PROD with PROPOSALS-1