48138 Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations 

TABLE 2—INSPECTION COMPLIANCE SCHEDULE

If on the effective date of this AD, the propeller blade: Then inspect the propeller blade: 

(1) Has more than 2,400 operating hours TSN, time-since-last inspection (TSLI), or time-since-overhaul (TSO) and has been inspected 

using AD 2008–08–01 or McCauley Propellers ASB No. ASB255, 

dated January 8, 2007 within the past 2,400 operating hours.

Upon reaching 2,500 operating hours TSLI. See TSLI definition paragraph (p) of this AD. 

(2) Has more than 2,400 operating hours TSN, TSLI, or TSO and has 

not been inspected using AD 2008–08–01 or McCauley Propellers 

ASB No. ASB255, dated January 8, 2007 within the past 2,400 operating hours.

Within the next 100 operating hours time-in-service. 

(3) Has 2,400 or fewer operating hours TSN, TSLI, or TSO ................... Upon reaching 2,500 operating hours TSN, TSLI, or TSO. 

Propellers Failing Blade Inspection 

(l) Remove from service all of the propeller 

blades, and the propeller hub, if one or more 

propeller blades are found cracked on a 

propeller assembly. Propeller blades and the 

propeller hub of a propeller assembly that 

has had one or more cracked propeller blades 

are prohibited from installation in any 

configuration on any airframe. 

(m) Remove from service all propeller 

blades that exhibit a blade shank ‘‘step 

condition’’ of 0.005-inch or greater. Blades 

removed from service are prohibited from 

installation in any configuration on any 

airframe. 

Removal of C–5963 Split Retainers From 

Service 

(n) Remove from service all C–5963 split 

retainers at the time of blade inspection 

specified in paragraph (k) of this AD. C–5963 

split retainers removed from service are 

prohibited from installation in any 

configuration on any airframe. 

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

not install propeller assemblies with C–5963 

split retainers on any airframe. 

Definition 

(p) For the purpose of this AD, TSLI refers 

only to inspections performed using AD 

2008–08–01 or McCauley ASB No. ASB255, 

dated January 8, 2007. 

Reporting Requirements 

(q) Within 10 calendar days of the 

inspection, use the Reporting Form in 

McCauley ASB No. ASB255A, to report all 

inspection findings to the FAA, Wichita 

Aircraft Certification Office, 1801 Airport 

Road, Room 100, Wichita, KS 67209, 

Attention: Jeff Janusz; telephone (316) 946– 

4148; fax (316) 946–4107; e-mail: 

jeff.janusz@faa.gov. 

(r) Include any photographs, and any other 

information related to the means of detection 

of the crack, and the history of the propeller 

and blades. 

(s) The Office of Management and Budget 

(OMB) has approved the reporting 

requirements and assigned OMB control 

number 2120–0056. 

Alternative Methods of Compliance 

(t) The Manager, Wichita 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 

(u) Under 39.23, we are limiting the 

availability of special flight permits for this 

AD. Special flight permits are available only 

if: 

(1) The operator has not seen signs of 

external oil leakage from the hub; 

(2) The operator has not observed abnormal 

propeller vibration or abnormal engine 

vibration; 

(3) The operator has not observed any other 

abnormal operation from the propeller; 

(4) The operator has not made earlier 

reports of abnormal propeller vibration, 

abnormal engine vibration, or other abnormal 

propeller operations that have not been 

addressed. 

Related Information 

(v) Contact Jeff Janusz, Aerospace Engineer, 

Wichita Aircraft Certification Office, FAA, 

Small Airplane Directorate, 1801 Airport 

Road, Room 100, Wichita, KS 67209; e-mail: 

jeff.janusz@faa.gov; telephone: (316) 946– 

4148; fax: (316) 946–4107, for more 

information about this AD. 

Material Incorporated by Reference 

(w) You must use McCauley Propellers 

Alert Service Bulletin No. ASB255A, dated 

October 6, 2008 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 McCauley Propeller Systems, 

5800 E. Pawnee, Wichita, KS 67218, 

telephone (800) 621–7767 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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 3, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–21919 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–2009–0136; Directorate 

Identifier 2008–NM–171–AD; Amendment 

39–16022; AD 2009–19–05] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747 airplanes. This AD 

requires repetitive inspections for 

cracking of the fuselage frames in 

section 41, and corrective actions if 

necessary. This AD results from reports 

of cracking in fuselage frames made of 

2024 aluminum alloy that were installed 

during previous modification of the 

frames in section 41 and during 

production. We are issuing this AD to 

detect and correct frame cracks, which 

could result in cracking of the adjacent 

fuselage skin and consequent rapid 

decompression of the airplane. 

DATES: This AD is 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 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. 

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 


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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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

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 Boeing Model 747 airplanes. 

That NPRM was published in the 

Federal Register on February 23, 2009 

(74 FR 8034). That NPRM proposed to 

require repetitive inspections for 

cracking of the fuselage frames in 

section 41, and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Requests To Delay or Withdraw NPRM 

Japan Airlines (JAL) asks that we 

delay issuing the AD until Boeing 

revises the referenced service 

information. JAL states that Boeing Alert 

Service Bulletin 747–53A2753, dated 

August 28, 2008, does not include 

access and restoration information for 

the frame structure inspection. JAL adds 

that without this information operators 

are caused an undue burden such as 

engineering costs and validation. JAL 

notes that it asked Boeing to develop 

access and restoration procedures and 

Boeing agreed to revise the service 

information to include those 

procedures. 

We do not agree to delay issuing the 

AD to wait for revised service 

information, nor has Boeing informed us 

of its intent to issue revised service 

information to include the procedures 

discussed by the commenter. We have 

determined that although Boeing Alert 

Service Bulletin 747–53A2753, dated 

August 28, 2008, does not include 

access information for the frame 

inspection, the majority of operators 

have their own acceptable access and 

closing procedures. Although this AD 

does not mandate a particular method of 

doing the access and closing 

procedures, operators can obtain those 

procedures directly from Boeing if 

necessary. We have not changed the AD 

in this regard. 

Northwest Airlines (NWA) would like 

the NPRM to be withdrawn. NWA states 

that, in view of the reported damage 

findings and service information 

specified in the preamble of the NPRM, 

there is no justification to support 

issuing an NPRM which covers a much 

broader area than where the crack 

damage was found. NWA states that the 

inspection for cracking of certain critical 

regions of the body section 41 structure 

is also addressed in the supplemental 

structural inspection document (SSID) 

inspection program. NWA notes that the 

SSID inspection program is mandated in 

previously issued rulemaking and 

should be used to determine if 

mandated inspections of the entire body 

section 41 structure are necessary. NWA 

adds that additional justification is 

needed to support mandating those 

inspections. 

Although we understand NWA’s 

concern, we do not agree to withdraw 

the NPRM. We have received several 

reports of significant cracking of certain 

fuselage frames in section 41; the 

cracked frames were found when the 

airplanes had accumulated relatively 

low flight cycles. As the fuselage frames 

on the airplanes affected by this AD are 

of similar type design, we have 

determined that all fuselage frames in 

section 41 are susceptible to the same 

unsafe condition. 

We are aware that the Boeing Model 

747 SSID inspection program, as 

mandated by AD 2004–07–22 R1, 

amendment 39–15326 (73 FR 1052, 

January 7, 2008), requires repetitive 

inspections of the fuselage frames in 

section 41. However, analysis by the 

manufacturer shows that a repetitive 

inspection interval significantly reduced 

from the interval specified in the SSID 

inspection program is required to ensure 

safety. Rather than revising AD 2004– 

07–22 R1, which is complex and 

includes numerous inspections, we 

have determined that this new AD is 

appropriate and must be issued without 

further delay. 

Request To Correct Paragraph 

Identifiers 

Boeing requests a correction to the 

paragraph identifiers specified in 

paragraph (g) of this AD—i.e., to specify 

paragraphs (h) and (i) instead of 

paragraphs (g) and (h). 

We agree with the Boeing comment. 

The paragraph identifiers were 

incorrectly identified in the NPRM; 

therefore, we have changed those 

identifiers in paragraph (g) of this AD 

accordingly. 

Change to AD Preamble 

The Costs of Compliance paragraph 

has been revised to note that for certain 

airplanes, it may be necessary to 

accomplish more than one Part of 

Boeing Alert Service Bulletin 747– 

53A2732, dated August 28, 2008, 

depending on airplane configuration. 

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 change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 165 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. For 

airplanes on which Boeing Alert Service 

Bulletin 747–53A2732, dated August 28, 

2008, must be done, accomplishment of 

more than one Part of the alert service 

bulletin may be required, depending on 

airplane configuration. 

TABLE—ESTIMATED COSTS

Inspection Work 

hours 

Average 

labor rate 

per hour 

Cost per product 

Number 

of U.Sregistered 

airplanes 

Fleet cost 

Boeing Alert Service Bulletin 747– 

53A2732, Part 1.

50 $80 Up to $4,000, per inspection cycle 94 Up to $376,000, per inspection 

cycle. 


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48140 Federal Register / Vol. 74, No. 182 / Tuesday, September 22, 2009 / Rules and Regulations 

TABLE—ESTIMATED COSTS—Continued 

Inspection Work 

hours 

Average 

labor rate 

per hour 

Cost per product 

Number 

of U.Sregistered 

airplanes 

Fleet cost 

Boeing Alert Service Bulletin 747– 

53A2732, Part 2.

650 80 Up to $52,000, per inspection 

cycle.

94 Up to $4,888,000, per inspection 

cycle. 

Boeing Alert Service Bulletin 747– 

53A2732, Part 3.

6 80 $480, per inspection cycle ............ 94 Up to $45,120, per inspection 

cycle. 

Boeing Alert Service Bulletin 747– 

53A2732, Part 4.

51 80 Up to $4,080, per inspection cycle 94 Up to $383,520, per inspection 

cycle. 

Boeing Alert Service Bulletin 747– 

53A2732, Part 5.

11 80 Up to $880, per inspection cycle .. 94 Up to $82,720, per inspection 

cycle. 

Boeing Alert Service Bulletin 747– 

53A2732, Part 6.

52 80 Up to $4,160, per inspection cycle 94 Up to $391,040, per inspection 

cycle. 

Boeing Alert Service Bulletin 747– 

53A2732, Part 7.

13 80 Up to $1,040, per inspection cycle 94 Up to $97,760, per inspection 

cycle. 

Boeing Alert Service Bulletin 747– 

53A2732, Part 8.

54 80 Up to $4,320, per inspection cycle 94 Up to $406,080, per inspection 

cycle. 

Boeing Alert Service Bulletin 747– 

53A2753.

244 80 Up to $19,520, per inspection 

cycle.

71 Up to $1,385,920, per inspection 

cycle. 

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 

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: 

2009–19–05 Boeing: Amendment 39–16022. 

Docket No. FAA–2009–0136; Directorate 

Identifier 2008–NM–171–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective October 27, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 747 

airplanes, certificated in any category, as 

specified in paragraph (c)(1) or (c)(2) of this 

AD, as applicable. 

(1) Boeing Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP series airplanes, 

as identified in Boeing Alert Service Bulletin 

747–53A2732, dated August 28, 2008. 

(2) Boeing Model 747–400, 747–400D, and 

747–400F series airplanes, as identified in 

Boeing Alert Service Bulletin 747–53A2753, 

dated August 28, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of cracking 

in fuselage frames made of 2024 aluminum 

alloy that were installed during previous 

modification of the frames in section 41 and 

during production. We are issuing this AD to 

detect and correct frame cracks, which could 

result in cracking of the adjacent fuselage 

skin and consequent rapid decompression of 

the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections and Corrective 

Actions 

(g) At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2732 

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

as applicable, do the detailed inspection for 

cracking of the fuselage frames in section 41, 

and do all applicable corrective actions, by 

accomplishing all the actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2732 or 747– 

53A2753, both dated August 28, 2008, as 

applicable; except as provided by paragraphs 

(h) and (i) of this AD. Repeat the inspection 

at intervals not to exceed those specified in 

paragraph 1.E. of Boeing Alert Service 

Bulletin 747–53A2732 or 747–53A2753, both 

dated August 28, 2008, as applicable. If any 

crack is found, do all corrective actions 

before further flight. 

Note 1: As specified in Boeing Alert 

Service Bulletins 747–53A2732 and 747– 

53A2753, both dated August 28, 2008, an 

optional special detailed inspection behind 


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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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