Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations 48141 

the P14 and P15 electrical terminal panels 

using the borescope may be done. 

(h) Where Boeing Alert Service Bulletins 

747–53A2732 and 747–53A2753, both dated 

August 28, 2008, recommend an initial 

inspection threshold relative to the date on 

Boeing Alert Service Bulletins 747–53A2732 

and 747–53A2753, both dated August 28, 

2008; this AD requires the initial inspection 

threshold relative to the effective date of this 

AD. 

(i) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletins 747–53A2732 and 

747–53A2753, both dated August 28, 2008, 

specify to contact Boeing for appropriate 

action: Before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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. Send information to ATTN: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle ACO, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6437; fax (425) 

917–6590. Or, e-mail information to 9–ANM– 

Seattle-ACO–AMOC–Requests@faa.gov. 

(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 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who 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. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 747–53A2732 dated August 28, 

2008; or Boeing Alert Service Bulletin 747– 

53A2753, dated August 28, 2008; as 

applicable; 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, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1, fax 206–766– 

5680; e-mail me.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 

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

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 1, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21922 Filed 9–21–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0367; Directorate 

Identifier 2009–NE–10–AD; Amendment 39– 

16023; AD 2009–19–06] 

RIN 2120–AA64 

Airworthiness Directives; Teledyne 

Continental Motors O–470, IO–470, 

TSIO–470, IO–520, TSIO–520, IO–550, 

and IOF–550 Series Reciprocating 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Teledyne Continental Motors (TCM) O– 

470, IO–470, TSIO–470, IO–520, TSIO– 

520, IO–550, and IOF–550 series 

reciprocating engines with TCM EQ3 

cylinders installed. This AD requires 

initial and repetitive visual inspections 

of TCM EQ3 cylinders for cracks. This 

AD also requires removal of all EQ3 

cylinders as terminating action to the 

repetitive visual inspections. This AD 

results from reports of 35 EQ3 cylinders 

found cracked. We are issuing this AD 

to prevent loss of engine power due to 

cracks in the cylinder head, possible 

engine failure, and fire in the engine 

compartment. 

DATES: This AD becomes effective 

October 7, 2009. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of October 7, 2009. 

We must receive any comments on 

this AD by November 23, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Docket Management 

Facility, 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 FURTHER INFORMATION CONTACT: 

Anthony Holton, Engineer, Propulsion, 

Atlanta Aircraft Certification Office, 

FAA, Small Airplane Directorate, 1701 

Columbia Avenue, College Park, Georgia 

30337; e-mail anthony.holton@faa.gov; 

telephone: (404) 474–5567; fax: (404) 

474–5606. 

Contact Teledyne Continental Motors, 

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

telephone (251) 438–3411, or go to: 

http://tcmlink.com/servicebulletins.cfm, 

for the service information in this AD. 

SUPPLEMENTARY INFORMATION: In 

February 2009, we were made aware by 

TCM of reports of 35 EQ3 cylinders 

found with cracks during inspection. 

Cracked cylinders occurred on engines 

with times ranging from about 430 to 

1,300 hours of operation. TCM 

investigated the cause and discovered 

that their EQ3 configuration cylinder 

head casting tool used in the cylinder 

manufacturing process created an area 

of reduced wall thickness. This reduced 

wall thickness can result in a crack in 

the area between the upper spark plug 

bore and the fuel injector/primer nozzle 

bore during operation. TCM shipped 

engines with EQ3 cylinders and shipped 

individual EQ3 cylinders from 

November 1, 2007, through January 30, 

2009. Also, TCM produced a group of 

about 300 EQ3 cylinders in August and 

September of 2006. This condition, if 

not corrected, could result in loss of 

engine power due to cracks in the 

cylinder head, possible engine failure, 

and fire in the engine compartment. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of TCM Mandatory 

Service Bulletin (MSB) No. MSB09–1B, 

dated July 14, 2009. That MSB describes 

procedures for initial and repetitive 

visual inspections of EQ3 cylinders for 

cracks, and requires replacing those 

cylinders no later than December 31, 

2009. 


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48142 Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations 

Differences Between This AD and the 

Service Information 

TCM MSB No. MSB09–1B, dated July 

14, 2009, requires that the EQ3 

cylinders be identified and initially 

inspected within the next 20 flight 

hours, but no later than April 30, 2009. 

However, this AD requires the EQ3 

cylinders be identified and initially 

inspected within 20 flight hours after 

the effective date of this AD. The MSB 

also requires that all EQ3 cylinders be 

removed from service no later than 

December 31, 2009. This AD requires 

that the cylinders be removed from 

service within 1,300 hours total time of 

operation. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other TCM O–470, IO–470, TSIO– 

470, IO–520, TSIO–520, IO–550, and 

IOF–550 series reciprocating engines 

with EQ3 cylinders installed. For that 

reason, we are issuing this AD to 

prevent loss of engine power due to 

cracks in the cylinder head, possible 

engine failure, and fire in the engine 

compartment. This AD requires initial 

and repetitive visual inspections of all 

EQ3 cylinders for cracks within 20 flight 

hours of the effective date of this AD. 

This AD also requires replacement of all 

EQ3 cylinders within 1,300 hours total 

time of operation after the effective date 

of this AD. You must use the service 

information described previously to 

perform the actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2009–0367; Directorate Identifier 

2009–NE–10–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

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 AD. Using the 

search function of the Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 the 

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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration amends part 39 

of the Federal Aviation Regulations (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: 

2009–19–06 Teledyne Continental Motors: 

Amendment 39–16023. Docket No. 

FAA–2009–0367; Directorate Identifier 

2009–NE–10–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 7, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Teledyne 

Continental Motors (TCM) O–470, IO–470, 

TSIO–470, IO–520, TSIO–520, IO–550, and 

IOF–550 reciprocating engine models listed 

in Table 1 of this AD that have one or more 

affected TCM cylinders installed. To identify 

the affected cylinders, cross reference the 

engine models in Table 1 of this AD with the 

engine serial numbers found in Tables 1, 1A, 

2, and 2A of TCM Mandatory Service 

Bulletin (MSB) No. MSB09–1B, dated July 

14, 2009. Use the tables found in MSB No. 

MSB09–1B, dated July 14, 2009, to also 

identify spare EQ3 cylinders by cylinder part 

number and cylinder serial number that may 

have been installed on these engines. 


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Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations 48143 

TABLE 1—ENGINE MODELS AFFECTED

O–470–G, K, L, R, S, M, U 

IO–470–C, D, E, F, H, L, M, N, S, U, V, VO 

TSIO–470–B, C, D 

IO–520–A, B, BA, BB, C, CB, D, E, F, J, K, 

L, M, MB 

TSIO–520–AF, B, BB, C, CE, D, DB, E, EB, 

G, H, J, JB, K, KB, L, LB, M, N, NB, P, R, 

T, UB, VB, WB 

IO–550–A, B, C, D, E, F, L 

IOF–550–B, C, D, E, F, L 

(d) These engines are installed on, but not 

limited to, Alexandria Aircraft LLC (formerly 

Bellanca) model 300 Super Viking; Beech 

Bonanza 33, 35 and 36 series, Beech Baron 

56 and 58 series, Cessna 180, 182, 188, 205, 

206, 207, 210, 303, 310, 320, 402, and 414 

model series; Aero Commander 200 and 500; 

certain Rockwell (formerly Meyers) 

Windecker Eagle 200, and Navion airplanes. 

Unsafe Condition 

(e) This AD results from reports of 35 EQ3 

cylinders found cracked. We are issuing this 

AD to prevent loss of engine power due to 

cracks in the cylinder head, possible engine 

failure, and fire in the engine compartment. 

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. 

Identification and Initial Visual Inspection 

(g) Within 20 flight hours after the effective 

date of this AD, identify EQ3 cylinders using 

Step 1 of TCM MSB No. MSB09–1B, dated 

July 14, 2009. 

(1) Within 20 flight hours after the effective 

date of this AD, for EQ3 cylinders with 400 

or more hours total time of operation on the 

effective date of this AD, perform an initial 

visual inspection of the cylinder for cracks 

using Step 2, paragraph B, of TCM MSB No. 

MSB09–1B, dated July 14, 2009. 

(2) For EQ3 cylinders with fewer than 400 

hours total time of operation on the effective 

date of this AD, perform an initial visual 

inspection of the cylinder for cracks before 

reaching 400 hours total time of operation, 

using Step 2, paragraph B, of TCM MSB No. 

MSB09–1B, dated July 14, 2009. 

(3) Remove from service before flight, any 

cylinders found cracked. 

Repetitive Visual Inspections 

(h) Repeat the visual inspections required 

by this AD every 50 hours of operation. Use 

Step 2, paragraph B, of TCM MSB No. 

MSB09–1B, dated July 14, 2009, to perform 

the inspection. 

(i) Remove from service before flight, any 

cylinders found cracked. 

Removal of All EQ3 Cylinders From Service 

(j) Within 1,300 hours total time of 

operation after the effective date of this AD, 

remove all EQ3 cylinders from service. 

EQ3 Cylinder Installation Prohibition 

(k) After the effective date of this AD, do 

not install any EQ3 cylinder onto any engine, 

or any EQ3 cylinder-equipped engine, onto 

any aircraft. 

Previous Credit 

(l) Initial visual inspections done before 

the effective date of this AD per TCM MSB 

No. MSB09–1A, dated March 11, 2009, 

comply with the initial inspection 

requirements specified in this AD. 

Alternative Methods of Compliance 

(m) The Manager, Atlanta Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Special Flight Permits 

(n) Under 14 CFR 39.23, we are limiting 

the special flight permits for this AD to 

engines that have no evidence of fuel or 

combustion staining in the cylinder crack 

location, and for a total special flight time of 

5 hours. 

Related Information 

(o) Contact Anthony Holton, Engineer, 

Propulsion, Atlanta Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

1701 Columbia Avenue, College Park, 

Georgia 30337; e-mail 

anthony.holton@faa.gov; telephone: (404) 

474–5567; fax: (404) 474–5606, for more 

information about this AD. 

Material Incorporated by Reference 

(p) You must use Teledyne Continental 

Motors Mandatory Service Bulletin No. 

MSB09–1B, dated July 14, 2009, to perform 

the actions required by this AD. The Director 

of the Federal Register approved the 

incorporation by reference of this service 

bulletin in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Contact Teledyne 

Continental Motors, Inc., PO Box 90, Mobile, 

AL 36601; telephone (251) 438–3411, or go 

to: http://tcmlink.com/servicebulletins.cfm, 

for a copy of this service information. You 

may review copies at the FAA, New England 

Region, 12 New England Executive Park, 

Burlington, MA; or 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/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

September 8, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–22287 Filed 9–21–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0292; Directorate 

Identifier 2008–NM–011–AD; Amendment 

39–16011; AD 2009–18–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300, A310, and A300–600 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A300 and A310 series airplanes. That 

AD currently requires replacement of 

the nose landing gear drag strut upper 

attachment pin. This new AD requires 

revising the Airworthiness Limitations 

section (ALS) of the Instructions for 

Continued Airworthiness (ICA) to 

require additional life limits and/or 

replacements for certain main landing 

gear and nose landing gear components, 

and also expands the applicability. This 

AD results from revisions to the ALS of 

the ICA to include new or more 

restrictive life limits and/or 

replacements. We are issuing this AD to 

ensure the continued structural integrity 

of these airplanes. 

DATES: This AD becomes effective 

October 27, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 27, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

SAS—EAW (Airworthiness Office), 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; 

Internet http://www.airbus.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 


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