Federal Register / Vol. 74, No. 250 / Thursday, December 31, 2009 / Rules and Regulations 69249 

structure could result in failure of the outer 

flaps, and consequent reduced controllability 

of the airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) For airplanes equipped with 

P/N 35–A0736–0001 or –0002 outer flaps: 

Within 300 flight cycles after the effective 

date of this AD, do a borescopic inspection 

to detect cracking of the outer flaps fittings 

and longerons, in accordance with the 

Accomplishment Instructions of EADS– 

CASA Service Bulletin SB–235–57–20, 

Revision 2, dated March 30, 2007. 

(2) For airplanes equipped with P/N 35– 

15501–0001, –0002, –0003, or –0004 outer 

flaps: At the earlier of the times specified in 

paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, 

do a borescopic inspection to detect cracking 

of the outer flaps fittings; and within 300 

flight cycles after the effective date of this 

AD, do a borescopic inspection to detect 

cracking of the longerons. Do the inspections 

in accordance with the Accomplishment 

Instructions of EADS–CASA Service Bulletin 

SB–235–57–20, Revision 2, dated March 30, 

2007. 

(i) Within 600 flight cycles after the most 

recent inspection done in accordance with 

AD 99–07–13, or within 14 days after the 

effective date of this AD, whichever occurs 

later. 

(ii) Within 300 flight cycles after the 

effective date of this AD. 

(3) If, during any inspection required by 

paragraph (f)(1) or (f)(2) of this AD, no crack 

is detected, repeat the borescopic inspections 

of the outer flap fittings and longerons in 

accordance with the Accomplishment 

Instructions of EADS–CASA Service Bulletin 

SB–235–57–20, Revision 2, dated March 30, 

2007, thereafter at intervals not to exceed 300 

flight cycles or 6 months, whichever occurs 

first, until the replacement specified in 

paragraph (f)(4) or (f)(5) of this AD is 

accomplished. 

(4) If any crack is detected during any 

inspection required by paragraph (f)(1), (f)(2), 

or (f)(3) of this AD, prior to further flight, 

replace the outer flap with a new or 

retrofitted flap in accordance with the 

Accomplishment Instructions of EADS– 

CASA Service Bulletin SB–235–57–20, 

Revision 2, dated March 30, 2007. Such 

replacement constitutes terminating action 

for the repetitive borescopic inspection 

required by this AD for the replaced outer 

flap only. 

(5) For affected parts that have not been 

replaced in accordance with paragraph (f)(4) 

of this AD: At the later of the times specified 

in paragraphs (f)(5)(i) and (f)(5)(ii) of this AD, 

replace each outer flap with a new or 

retrofitted outer flap in accordance with the 

Accomplishment Instructions of EADS– 

CASA Service Bulletin SB–235–57–20, 

Revision 2, dated March 30, 2007. Replacing 

all outer flaps terminates the requirements of 

this AD. 

(i) Before the accumulation of 4,000 total 

flight cycles on the flap. 

(ii) Within 1,200 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(6) Actions done before the effective date 

of this AD in accordance with CASA Service 

Bulletin SB–235–57–20, dated December 23, 

1997; or EADS–CASA Service Bulletin 

SB–235–57–20, Revision 1, dated April 30, 

2004; are acceptable for compliance with the 

corresponding requirements of paragraph 

(f)(2) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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. 

Send information to ATTN: Shahram 

Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; fax (425) 

227–1149. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2008–0119, dated June 27, 2008; 

and EADS–CASA Service Bulletin SB–235– 

57–20, Revision 2, dated March 30, 2007; for 

related information. 

Material Incorporated by Reference 

(i) You must use EADS–CASA Service 

Bulletin SB–235–57–20, Revision 2, dated 

March 30, 2007, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EADS–CASA, Military 

Transport Aircraft Division (MTAD), 

Integrated Customer Services (ICS), 

Technical Services, Avenida de Arago ́n 404, 

28022 Madrid, Spain; telephone +34 91 585 

55 84; fax +34 91 585 55 05; e-mail 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

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/

code_of_federal_regulations/ibr_

locations.html. 

Issued in Renton, Washington, on 

December 16, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–30707 Filed 12–30–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0686; Directorate 

Identifier 2009–NM–044–AD; Amendment 

39–16155; AD 2009–26–16] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model MD–11 and 

MD–11F Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model MD–11 and MD–11F airplanes. 

This AD requires a one-time inspection 

to determine if wires touch the upper 

surface of the center upper auxiliary 

fuel tank and marking the location, if 

necessary; a one-time inspection of all 

wire bundles above the center upper 

auxiliary fuel tank for splices and 

damage; a one-time inspection for 

damage to the fuel vapor barrier seal 

and upper surface of the center upper 

auxiliary fuel tank; and corrective 

actions, if necessary. This AD also 

requires installation of nonmetallic 

barrier/shield sleeving, new clamps, 

new attaching hardware, and a new 

extruded channel. This AD results from 

fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 


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69250 Federal Register / Vol. 74, No. 250 / Thursday, December 31, 2009 / Rules and Regulations 

in fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD is effective February 4, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 4, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the 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: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5262; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain McDonnell Douglas Corporation 

Model MD–11 and MD–11F airplanes. 

That NPRM was published in the 

Federal Register on August 19, 2009 (74 

FR 41813). That NPRM proposed to 

require a one-time inspection to 

determine if wires touch the upper 

surface of the center upper auxiliary 

fuel tank and marking the location, if 

necessary; a one-time inspection of all 

wire bundles above the center upper 

auxiliary fuel tank for splices and 

damage; a one-time inspection for 

damage to the fuel vapor barrier seal 

and upper surface of the center upper 

auxiliary fuel tank; and corrective 

actions, if necessary. That NPRM also 

proposed to require installation of 

nonmetallic barrier/shield sleeving, new 

clamps, new attaching hardware, and a 

new extruded channel. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the two commenters. 

Request To Include Boeing Information 

Notice MD11–28–126 IN 02 in the Final 

Rule 

FedEx requests that Boeing 

Information Notice MD11–28–126 IN 

02, dated July 1, 2009, be incorporated 

into the final rule. FedEx states that 

without including the information 

notice, FedEx will not be able to comply 

with the AD unless an Alternative 

Method of Compliance (AMOC) is 

granted. We partially agree. Boeing 

issued Information Notice MD11–28– 

126 IN 02 to clarify the group 

applicability. The information notice is 

not approved by the FAA; therefore, we 

do not require the information notice for 

accomplishment of work and it is not 

incorporated into the requirements of 

this final rule. Note 1 has been added to 

this AD to explain that the information 

notice provides clarification of the 

airplane groups identified in the service 

bulletin. 

Request for Compliance Time Extension 

KLM requests that we extend the 

compliance time so that it will fall 

during regularly scheduled maintenance 

periods. KLM states that the 60-month 

compliance time specified in the NPRM 

does not take into consideration the 

impact on operators of accessing the 

area above the center upper auxiliary 

fuel tank, which is only opened during 

72-month intervals. KLM states the 

work-hours and costs specified in the 

NPRM are unrealistic because the 

inspection is not done in the 72-month 

period. 

We do not agree with the commenter’s 

request to extend the compliance time. 

We have determined that the 

compliance time, as proposed, 

represents the maximum interval of 

time allowable for the affected airplanes 

to continue to safely operate before the 

modification is done. Since 

maintenance schedules vary among 

operators, there would be no assurance 

that the airplane would be modified 

during that maximum interval. 

However, operators may request an 

AMOC in accordance with the 

procedures specified in paragraph (j) of 

this AD. We have not changed the AD 

in this regard. 

Explanation of Changes Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this AD affects 111 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection/Installation 1. 136 to 154 .... $80 $9,405 to $12,201 .... $20,285 to $24,521 .. 111 $2,251,635 to 

$2,721,831. 

1 Depending on airplane configuration. 

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. 


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Federal Register / Vol. 74, No. 250 / Thursday, December 31, 2009 / Rules and Regulations 69251 

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 

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), and 

(3) 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance 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 AD: 

2009–26–16 McDonnell Douglas 

Corporation: Amendment 39–16155. 

Docket No. FAA–2009–0686; Directorate 

Identifier 2009–NM–044–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective February 4, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Corporation Model MD–11 and MD–11F 

airplanes; certificated in any category; as 

identified in Boeing Service Bulletin MD11– 

28–126, Revision 1, dated June 18, 2009. 

Note 1: Boeing Information Notice MD11– 

28–126 IN 02, dated July 1, 2009, provides 

guidance that clarifies the airplane groups 

identified in Boeing Service Bulletin MD11– 

28–126, Revision 1, dated June 18, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to reduce the potential of ignition 

sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 60 months after the effective 

date of this AD: Do the actions specified in 

paragraphs (g)(1), (g)(2), (g)(3), (g)(4), and 

(g)(5) of this AD, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin MD11–28–126, Revision 1, 

dated June 18, 2009, except as required by 

paragraph (h) of this AD. Do all applicable 

corrective actions before further flight. 

(1) Do a general visual inspection to 

determine if wires touch the upper surface of 

the center upper auxiliary fuel tank, and 

mark the location, as applicable. 

(2) Do a detailed inspection for splices and 

damage of all wire bundles above the center 

upper auxiliary fuel tank. 

(3) Do a detailed inspection for damage 

(burn marks) on the upper surface of the 

center upper auxiliary fuel tank. 

(4) Do a detailed inspection for damage 

(burn marks) on the fuel vapor barrier seal. 

(5) Install nonmetallic barrier/shield 

sleeving, new clamps, new attaching 

hardware, and a new extruded channel. 

(h) If damage (burn marks) is found on the 

upper surface of the center upper auxiliary 

fuel tank during any inspection required by 

paragraph (g)(3) of this AD, and Boeing 

Service Bulletin MD11–28–126, Revision 1, 

dated June 18, 2009, specifies to contact The 

Boeing Company for repair instructions: 

Before further flight, repair the auxiliary fuel 

tank using a method approved in accordance 

with the procedures specified in paragraph 

(j)(3) of this AD. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(i) Actions accomplished before the 

effective date of this AD according to Boeing 

Service Bulletin MD11–28–126, dated March 

3, 2009, are considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Los Angeles 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. Send information to ATTN: 

Samuel Lee, Aerospace Engineer, Propulsion 

Branch, ANM–140L, FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; telephone (562) 627–5262; fax (562) 

627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair of 

the center upper auxiliary tank required by 

this AD, if it is approved by a Structures 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Los Angeles 

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. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

MD11–28–126, Revision 1, dated June 18, 

2009, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

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 


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69252 Federal Register / Vol. 74, No. 250 / Thursday, December 31, 2009 / Rules and Regulations 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

December 16, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–30709 Filed 12–30–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0052; Directorate 

Identifier 2008–NE–01–AD; Amendment 39– 

16151; AD 2009–26–12] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Components, Inc. (ECi) Reciprocating 

Engine Cylinder Assemblies 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Lycoming Engines (formerly Textron 

Lycoming) models 320, 360, and 540 

series, ‘‘Parallel Valve’’ reciprocating 

engines, with certain Engine 

Components, Inc. (ECi) cylinder 

assemblies, part number (P/N) 

AEL65102 series ‘‘Titan,’’ installed. 

That AD currently requires initial and 

repetitive visual inspections and 

compression tests to detect cracks at the 

head-to-barrel interface, replacement of 

cylinder assemblies found cracked, and 

replacement of certain cylinder 

assemblies at new, reduced times-inservice. This AD requires the same 

actions, but for an expanded population 

of cylinder assemblies. This AD results 

from reports of 10 additional cylinder 

head separations since issuing AD 

2008–19–05, on cylinder serial numbers 

not listed in that AD. We are issuing this 

AD to prevent loss of engine power due 

to cracks at the head-to-barrel interface 

and possible engine failure caused by 

separation of a cylinder head, which 

could result in loss of control of the 

aircraft. 

DATES: This AD becomes effective 

February 4, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Peter W. Hakala, Aerospace Engineer, 

Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, TX 76193; e-mail: 

peter.w.hakala@faa.gov; telephone (817) 

222–5145; fax (817) 222–5785. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 by 

superseding AD 2008–19–05, 

Amendment 39–15672 (73 FR 53105, 

September 15, 2008), with a proposed 

AD. The proposed AD applies to 

Lycoming Engines (formerly Textron 

Lycoming) models 320, 360, and 540 

series, ‘‘Parallel Valve’’ reciprocating 

engines, with certain Engine 

Components, Inc. (ECi) cylinder 

assemblies, part number (P/N) 

AEL65102 series ‘‘Titan,’’ installed. We 

published the proposed AD in the 

Federal Register on July 30, 2009 (74 FR 

37955). That action proposed to require 

initial and repetitive visual inspections 

and compression tests to detect cracks at 

the head-to-barrel interface, replacement 

of cylinder assemblies found cracked, 

and replacement of certain cylinder 

assemblies at new, reduced times-inservice, and for an expanded population 

of cylinder assemblies. 

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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Two commenters state that proposed 

AD paragraphs (m) and (n) are confusing 

and contradictory. Paragraph (m) allows 

repair or replacement of cylinders with 

leakage provided that the cylinder is not 

cracked, but paragraph (n) prohibits 

removed cylinders from being reinstalled. 

We agree. We changed paragraph (m) 

to state ‘‘For Group ‘A’ cylinder 

assemblies only, repair or replace the 

engine cylinder assembly before further 

flight if the cause of the low gauge 

reading in paragraph (k) of this AD is 

from leaking intake or exhaust valves, or 

from leaking piston rings.’’ We also 

changed paragraph (n) to state, ‘‘After 

the effective date of this AD, do not 

install any Group ‘B’ ECi cylinder 

assembly, P/N AEL65102, onto any 

engine and do not attempt to repair or 

reuse Group ‘B’ cylinder assemblies.’’ 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 18,000 ECi cylinder assemblies 

installed in aircraft of U.S. registry. The 

visual inspection and compression tests 

will take about 4 work-hours for each 

engine. An individual cylinder 

replacement will require $1,100 for 

parts and 6 work-hours. Lycoming 

engines with a set of 4 ECi cylinders 

will require 12 work-hours for the 

cylinder replacement. Lycoming engines 

with a set of 6 ECi cylinders will require 

16 work-hours for the cylinder 

replacement. We estimate 18 percent of 

the affected population of cylinders will 

be replaced. We estimate the total cost 

of the AD to U.S. operators to be 

$10,172,000. Our estimate is exclusive 

of any 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. 


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