Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 15673 

2088: At the applicable time specified in 

Table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, do a 

detailed inspection for cracking of the 

tension tie at BS 760 or 780, and do all 

applicable corrective actions, in accordance 

with Part I of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, except as required by paragraph (j)(2) 

of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

inspection thereafter at the applicable time 

specified in Table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2088, Revision 4, dated 

January 11, 2013. Boeing Alert Service 

Bulletin 747–53A2088, Revision 4, dated 

January 11, 2013, notes that additional postmodification inspections are specified in 

Boeing Service Bulletin 747–53A2502; those 

post-modification inspections are required by 

AD 2006–01–07, Amendment 39–14446 (71 

FR 1947, January 12, 2006). 

(j) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, specifies a compliance time ‘‘after the 

Revision 4 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in this AD, if those actions 

were performed before the effective date of 

this AD using Boeing Alert Service Bulletin 

747–53A2088, Revision 3, dated September 

8, 1994, which is not incorporated by 

reference in this AD. 

(l) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(m) 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 (n)(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 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 84–19–01, 

Amendment 39–4913 (Docket No. 84–NM– 

10–AD; 49 FR 36365, September 17, 1984), 

are approved as AMOCs for the 

corresponding requirements of paragraph (g) 

(the retained detailed inspections) and 

paragraph (i) of this AD, but not as AMOCs 

for the high frequency eddy current 

inspections required by paragraph (g) of this 

AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: Nathan.P.Weigand@

faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (o)(3) and (o)(4) of 

this AD. 

(o) 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) Boeing Alert Service Bulletin 747– 

53A2088, Revision 4, dated January 11, 2013. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at 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. 

(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 Renton, Washington, on February 

26, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–06153 Filed 3–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0051; Directorate 

Identifier 2007–NE–37–AD; Amendment 39– 

17801; AD 2014–05–29] 

RIN 2120–AA64 

Airworthiness Directives; Continental 

Motors, Inc. Reciprocating Engines 

With Superior Air Parts, Inc. (SAP) 

Cylinder Assemblies Installed 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2009–16– 

03 for certain Continental Motors, Inc. 

(CMI) IO–520, TSIO–520, and IO–550 

series reciprocating engines, with 

certain SAP replacement parts 

manufacturer approval (PMA) 

investment cast cylinder assemblies 

installed. AD 2009–16–03 required 

initial and repetitive inspections and 

compression tests to detect cracks in 

those cylinders. This new AD requires 

that additional engines be added to the 

applicability. This AD was prompted by 

the need to add to the applicability all 

other engine models approved for the 

use of CMI 520 and 550 cylinder 

assemblies, such as the CMI 470 series 

engines when modified by 

supplemental type certificate (STC), 

with affected SAP investment cast 

cylinder assemblies installed. We are 

issuing this AD to prevent the 

separation of the cylinder head, damage 

to the engine, and damage to the 

airplane. 

DATES: This AD is effective April 25, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 25, 2014. 

ADDRESSES: For service information 

identified in this AD, contact 

Continental Motors, Inc., 2039 Broad 

St., Mobile, AL 36615; phone: 251–438– 

3411; Web site: http://

www.continentalmotors.aero/Support_

Materials/Publications/Service_

Bulletins/. You may view this service 

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15674 Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 

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–2007– 

0051; 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: 

Peter W. Hakala, Aerospace Engineer, 

Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, TX 76137; phone: 

817–222–5145; fax: 817–222–5785; 

email: peter.w.hakala@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–16–03, 

Amendment 39–15986 (74 FR 38896, 

August 5, 2009), (‘‘AD 2009–16–03’’). 

AD 2009–16–03 applied to the specified 

products. The NPRM published in the 

Federal Register on September 13, 2013 

(78 FR 56622). The NPRM proposed to 

continue to require initial and repetitive 

inspections and compression tests to 

detect cracks in certain replacement 

SAP PMA investment cast cylinder 

assemblies. The NPRM also proposed to 

require that additional engines be added 

to the applicability. We are issuing this 

AD to prevent the separation of the 

cylinder head, damage to the engine, 

and damage to the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Delete Requirement To 

Remove Cylinders After 12 Years 

SAP requested that we delete 

paragraph (i)(2), which requires the 

removal of cylinders after 12 years, 

stating that removal is not necessary if 

the required periodic 50-hour 

inspections show that the cylinders 

have no defects and are still airworthy. 

We disagree. The 12-year calendar 

requirement is due to the increased risk 

of environmental corrosion, a 

corresponding increase in potential for 

metal fatigue cracks, and the subsequent 

separation of the cylinder assemblies. 

The type certificate holder recommends 

removal and replacement of the 

cylinders no later than 12 years from 

date placed in service. We did not 

change this AD. 

Request To Delete From Applicability 

the Additional Engines Identified by 

This Supersedure AD, and To Cancel 

This AD 

SAP requested that we delete from the 

applicability of this AD the Continental 

Motors, Inc. model CMI 470 series 

engines that are added to the 

applicability of this supersedure AD, 

and that we cancel this supersedure AD. 

SAP is not aware of any problems with 

the investment cast SAP cylinders 

installed on CMI model 470 series 

engines modified by STC to install SAP 

520 cylinder assemblies. 

We disagree. We are not aware of data 

that would indicate that the failure 

mode of SAP 520 cylinder assemblies 

identified in this AD would not also 

exist in the comparatively small 

population of CMI model 470 series 

engines modified by STC. We did not 

change this AD. 

Request To Allow Reinstallation of 

Removed Cylinders 

SAP requested that we change 

paragraph (j) to allow reinstallation of 

cylinders that have been removed for 

maintenance because the removal and 

reinstallation of a cylinder does not 

impact cylinder head fatigue. 

We disagree. The purpose of this AD 

is to correct an unsafe condition by 

removing from service SAP investment 

cast cylinder assemblies. We did not 

change this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 6,000 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 5 hours to replace a cylinder, 

and 15 hours per engine to inspect the 

cylinders. The average labor rate is $85 

per hour. Required parts will cost about 

$1,200 per cylinder. We anticipate that 

4,000 cylinders will require 

replacement. Based on these figures, we 

estimate the total cost of this AD to U.S. 

operators to be $14,150,000. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

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Federal Register / Vol. 79, No. 55 / Friday, March 21, 2014 / Rules and Regulations 15675 

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 

removing airworthiness directive (AD) 

2009–16–03, Amendment 39–15986 (74 

FR 38896, August 5, 2009), and adding 

the following new AD: 

2014–05–29 Continental Motors, Inc. 

(formerly Teledyne Continental Motors, 

Continental): Amendment 39–17801; 

Docket No. FAA–2007–0051; Directorate 

Identifier 2007–NE–37–AD. 

(a) Effective Date 

This AD is effective April 25, 2014. 

(b) Affected ADs 

This AD supersedes AD 2009–16–03, 

Amendment 39–15986 (74 FR 38896, August 

5, 2009). 

(c) Applicability 

This AD applies to: 

(1) Continental Motors, Inc. (CMI) IO–520, 

TSIO–520, and IO–550 series reciprocating 

engines with replacement Superior Air Parts, 

Inc. (SAP) parts manufacturer approval 

(PMA) investment cast cylinder assemblies, 

part numbers (P/Ns) SA52000–A1, SA52000– 

A20P, SA52000–A21P, SA52000–A22P, 

SA52000–A23P, SA55000–A1, or SA55000– 

A20P, installed. 

(2) All other engine models approved for 

the use of CMI 520 and 550 cylinder 

assemblies such as the CMI 470 series 

engines when modified by Supplemental 

Type Certificate (STC), with SAP investment 

cast cylinder assemblies, P/Ns SA52000–A1, 

SA52000–A20P, SA52000–A21P, SA52000– 

A22P, SA52000–A23P, SA55000–A1, or 

SA55000–A20P, installed. 

(3) This AD applies to all serial numbers 

for the P/Ns listed in paragraphs (c)(1) and 

(c)(2) of this AD. 

(4) If no SAP replacement cylinders were 

installed during engine maintenance since 

the CMI engines were new, then this AD does 

not apply. 

(d) Unsafe Condition 

This AD was prompted by the need to add 

to the applicability all other engine models 

approved for the use of CMI 520 and 550 

cylinder assemblies such as the CMI 470 

series engines when modified by STC, with 

affected SAP investment cast cylinder 

assemblies installed. We are issuing this AD 

to prevent the separation of the cylinder 

head, damage to the engine, and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Identification of SAP Cylinder Assemblies 

Seeing the SAP cylinder assembly P/Ns 

referenced in paragraphs (c)(1) and (c)(2) of 

this AD may be difficult because the 

assembly P/Ns are stamped on the bottom 

cylinder flange. Therefore, you may review 

the engine maintenance records instead of 

the steps listed in paragraphs (f)(1) and (f)(2) 

of this AD, to see if the engine records 

identify the P/Ns of the cylinders installed. 

If the records do not identify the P/Ns of the 

cylinders installed, do the following: 

(1) Remove the valve cover from the 

cylinder assembly. 

(2) Look at the top of the cylinder head for 

the casting markings ‘‘AMCAST’’ or ‘‘CP’’ 

(note that the cylinder head casting part 

number, P/N SAC 52001 ‘‘I’’ or P/N SAC 

55001 ‘‘I’’, will also be visible). If a cylinder 

head has these markings, do the steps 

required by paragraphs (g) through (j) of this 

AD. 

(g) Initial Inspection of SAP Cylinder 

Assemblies 

For engines and cylinders listed in 

paragraphs (c)(1) and (c)(2) of this AD, with 

cylinders over 750 flight hours (FH) time-inservice (TIS) on the effective date of this AD, 

do the following initial inspection within 25 

FH TIS. 

(1) Inspect each cylinder head around the 

exhaust valve side for visual cracks or any 

signs of black combustion leakage. 

(2) Replace any cracked or leaking 

cylinders before further flight. 

(3) Perform a standard cylinder 

compression test. Guidance on standard 

cylinder compression tests can be found in 

Teledyne Continental Aircraft Engine Service 

Bulletin SB03–3, Differential Pressure Test 

and Borescope Inspection Procedures for 

Cylinders, dated March 28, 2003. 

(i) If the cylinder pressure gauge reads 

below 60 pounds per square inch, determine 

if the unacceptable pressure is due to a 

cracked cylinder. 

(ii) To check the cylinder, apply a 2- 

percent soapy water solution to the side of 

the leaking cylinder. 

(iii) If you see air bubbles, indicating air 

leakage, on the side of the cylinder head, or 

near the head-to-cylinder interface, replace 

the cylinder assembly before further flight. 

(h) Repetitive Inspections of SAP Cylinder 

Assemblies 

Thereafter, repeat the cylinder visual 

inspections and compression tests specified 

in paragraphs (g)(1) through (g)(3)(iii) of this 

AD, within every 50 FH time-since-last 

inspection until the cylinder reaches the TIS 

as listed in paragraph (i) of this AD. 

(i) Replacing SAP Cylinder Assemblies 

For installed cylinders, replace the affected 

SAP cylinders at the earliest of the following: 

(1) When the cylinder reaches the 

operating hours TIS between overhaul limits 

specified in Table 1, ‘‘Engine Time Between 

Overhaul’’, in Continental Motors Aircraft 

Engine Service Information Letter SIL98–9C, 

Revision C, dated July 17, 2013; or 

(2) When the cylinder reaches 12 calendar 

years-since-installation. 

(j) Prohibition Against Installing Certain 

P/Ns of SAP Cylinder Assemblies 

After the effective date of this AD, do not 

install or reinstall after any removal, any SAP 

investment cast cylinder assembly, P/Ns 

SA52000–A1, SA52000–A20P, SA52000– 

A21P, SA52000–A22P, SA52000–A23P, 

SA55000–A1, or SA55000–A20P, in any 

engine. 

(k) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Special Certification Office, 

may approve AMOCs to this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(l) Special Flight Permits 

Under 14 CFR Part 39.23, we will not 

approve special flight permits for this AD for 

engines that have failed the visual inspection 

or the 50-hour periodic cylinder assembly 

compression test required by this AD. 

(m) Related Information 

For more information about this AD, 

contact Peter W. Hakala, Aerospace Engineer, 

Special Certification Office, FAA, Rotorcraft 

Directorate, 2601 Meacham Blvd., Fort 

Worth, TX 76137; phone: 817–222–5145; fax: 

817–222–5785; email: peter.w.hakala@

faa.gov. 

(n) 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) Continental Motors Aircraft Engine 

Service Information Letter SIL98–9C, 

Revision C, dated July 17, 2013. 

(ii) Reserved. 

(3) For Continental Motors, Inc. service 

information identified in this AD, contact 

Continental Motors, Inc., 2039 Broad St., 

Mobile, AL 36615; phone: 251–438–3411; 

Web site: http:// 

www.continentalmotors.aero/Support_

Materials/Publications/Service_Bulletins. 

(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. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

March 4, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–06198 Filed 3–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

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