10918 Federal Register / Vol. 72, No. 47 / Monday, March 12, 2007 / Rules and Regulations 

Issued in Kansas City, Missouri, on March 

5, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 07–1106 Filed 3–9–07; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20850; Directorate 

Identifier 2005–NE–05–AD; Amendment 39–

14976; AD 2007–05–15] 

RIN 2120–AA64 

Airworthiness Directives; Teledyne 

Continental Motors GTSIO–520 Series 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Teledyne Continental Motors (TCM) 

GTSIO–520 series reciprocating engines. 

That AD currently requires initial and 

repetitive visual inspections of the 

starter adapter assembly and crankshaft 

gear and unscheduled visual 

inspections of the starter adapter 

assembly and crankshaft gear due to a 

rough-running engine. That AD also 

requires replacement of the starter 

adapter shaft gear needle bearing with a 

certain bushing and installation of a 

certain TCM service kit at the next 

engine overhaul, or at the next starter 

adapter replacement, whichever occurs 

first. This AD requires performing the 

inspection ordered in paragraph (h) of 

this AD every 100 hours time-in-service 

(TIS), or annually. This proposed AD 

results from an error discovered in AD 

2005–20–04. We are issuing this AD to 

failure of the starter adapter assembly 

and or crankshaft gear, resulting in 

failure of the engine and possible forced 

landing. 

DATES: This AD becomes effective April 

16, 2007. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of April 16, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

Teledyne Continental Motors, Inc., PO 

Box 90, Mobile, AL 36601; telephone 

(251) 438–3411. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Jerry 

Robinette, Senior Engineer, Propulsion, 

Atlanta Aircraft Certification Office, 

FAA, Small Airplane Directorate, One 

Crown Center, 1895 Phoenix Blvd., 

Suite 450, Atlanta, GA 30349; 

telephone: (770) 703–6096, 

fax: (770) 703–6097. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to TCM GTSIO–520 series 

reciprocating engines. We published the 

proposed AD in the Federal Register on 

October 26, 2006, (71 FR 62570). That 

action proposed to require performing 

the inspection ordered in paragraph (h) 

of AD 2005–20–04 every 100 hours 

time-in-service (TIS), or annually to 

correct an error that required the 

inspection at every 100-hour inspection. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility Docket Office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Office (telephone (800) 647–5227) is 

located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment[s] received. 

Remove the Requirement for a Placard 

Two commenters propose dropping 

the placard from the requirements of the 

proposed AD. The commenters do not 

believe the placard is necessary. We 

agree. It appears the commenters are 

basing their comment on the original 

notice of proposed rulemaking (NPRM) 

that we issued on April 6, 2005, not the 

current NPRM. We received comments 

to the original NPRM similar to these 

comments and removed the requirement 

to add a placard before we issued AD 

2005–20–05. We didn’t change this AD. 

Request to Change the Required 

Inspection 

The same two commenters request we 

mandate a more detailed inspection for 

the components. The commenters state 

that a visual inspection might not be 

sufficient. We don’t agree. The 

commenters didn’t specify any 

additional inspections. We consider a 

visual inspection the best method to 

detect abnormal surface wear. We don’t 

have any requirement for 

nondestructive testing because we have 

no indication of subsurface 

deterioration. We didn’t change the AD. 

Request To Perform Additional 

Economic Assessment 

One commenter asks us to perform 

additional economic assessment. The 

commenter states we didn’t consider the 

economic effects on other small entities. 

We don’t agree. We used our current 

procedures to consider the economic 

effects of this action. We didn’t change 

the AD. 

Editorial Changes To Improve Clarity 

and Correct an Omission 

We changed paragraph (f) of this AD 

from ‘‘If, during an inspection * * * 

crankcase, replace it with a serviceable 

bushing before reassembling 

components’’ to ‘‘(f) If, during an 

inspection required by paragraph (g), 

(h), (i), or (j) of this AD, you find needle 

bearing, part number (P/N) 537721, 

installed in the crankcase, replace it 

with a serviceable bushing, P/N 654472 

or equivalent FAA approved bearing, 

before reassembling components’’ to 

clarify the intent of that requirement. 

We also added paragraph (h)(3) to 

make the compliance times in that 

requirement consistent with paragraph 

(i)(3). 

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 

4,240 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about one work-hour per 

engine to perform the inspection, about 

one work-hour per engine to perform 

the proposed bushing installation and 

about six work-hours per engine to 

install the TCM service kit. The average 

labor rate is $80 per work-hour. We 

estimate that about 25 percent of the 

engines will require an unscheduled 

(rough-running engine) inspection and 

about half of the engines will require the 

bushing and TCM service kit. Required 

bushings would cost about $16 per 

engine and service kits about $800 per 

engine. Based on these figures, we 


hsrobinson on PROD1PC76 with RULES
Federal Register / Vol. 72, No. 47 / Monday, March 12, 2007 / Rules and Regulations 10919 

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

operators to be $6,393,432. 

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); 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 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

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 

removing Amendment 39–14297 (70 FR 

56355, September 27, 2005) and by 

adding a new airworthiness directive, 

Amendment 39–14976, to read as 

follows: 

2007–05–15 Teledyne Continental Motors: 

Amendment 39–14976. Docket No. 

FAA–2005–20850; Directorate Identifier 

2005–NE–05–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 16, 2007. 

Affected ADs 

(b) This AD supersedes AD 2005–20–04, 

Amendment 39–14297. 

Applicability 

(c) This AD applies to Teledyne 

Continental Motors (TCM) GTSIO–520 series 

reciprocating engines. These engines are 

installed on, but not limited to, Twin 

Commander (formerly Aero Commander) 

model 685, Cessna model 404, 411 series, 

and 421 series, British Aerospace, Aircraft 

Group, Scottish Division model B.206 series 

2 and Aeronautica Macchi model AM–3 

airplanes. 

Unsafe Condition 

(d) This AD results from an error 

discovered in AD 2005–20–04. We are 

issuing this AD to prevent failure of the 

starter adapter assembly and or crankshaft 

gear, resulting in failure of the engine and 

possible forced landing. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Starter Adapter Shaft Gear Needle Bearing 

Replacement 

(f) If, during an inspection required by 

paragraph (g), (h), (i), or (j) of this AD, you 

find needle bearing, part number (P/N) 

537721, installed in the crankcase, replace it 

with a serviceable bushing, P/N 654472 or 

equivalent FAA approved bearing, before 

reassembling components. Use the bushing 

installation procedure specified in Part 4 of 

TCM Mandatory Service Bulletin (MSB) No. 

MSB94–4G, dated October 31, 2005. 

Unscheduled Inspections for Rough-Running 

Engines 

(g) For any engine that experiences rough 

running conditions regardless of time-inservice (TIS), do the following: 

(1) Before further flight, perform the 

inspection procedures specified in Part 1 and 

Part 3 of TCM MSB No. MSB94–4G, dated 

October 31, 2005, and replace components as 

necessary. 

(2) An engine is considered rough-running 

if there is a sudden increase in the perceived 

vibration levels that cannot be cleared by 

adjustment of the engine controls; 

particularly the fuel mixture setting. 

Information on rough running engines can be 

found in the aircraft manufacturer’s Airplane 

Flight Manual, Pilot’s Operating Handbook, 

or Aircraft Owners Manual. 

100-Hour and Annual Inspections 

(h) For any engine that has been inspected 

using paragraph (h) of AD 2005–20–04 and 

the 100-hour inspection procedures or 100 

hour TIS intervals or annual inspection 

procedures, continue the inspections as 

follows: 

(1) Perform the inspection procedures 

specified in Part 2 of TCM MSB No. MSB94–

4G, dated October 31, 2005 and replace 

components as necessary at each 100 hour 

TIS interval (plus or minus 10 hours TIS) or 

annual inspection, whichever occurs first. 

(2) Thereafter, at each 100 hour TIS 

interval (plus or minus 10 hours TIS) perform 

repetitive inspections and component 

replacements as specified in paragraph (h)(1) 

of this AD. 

(3) If the inspection is performed at more 

than 100 hour intervals, subtract the 

additional hours from the next scheduled 100 

hour inspection. 

(i) For any engine that has not been 

inspected using paragraph (h) of AD 2005–

20–04, within 25 hours TIS or at the annual 

inspection, whichever occurs first, do the 

following: 

(1) Perform the inspection procedures 

specified in Part 2 of TCM MSB No. MSB94–

4G, dated October 31, 2005 and replace 

components as necessary. 

(2) Thereafter, at each 100-hour TIS 

interval (plus or minus 10 hours TIS) perform 

repetitive inspections and component 

replacements as specified in paragraph (i)(1) 

of this AD. 

(3) If the inspection is performed at more 

than 100 hour intervals, subtract the 

additional hours from the next scheduled 100 

hour inspection. 

Starter Adapters With 400 Hours or More 

Time-In-Service (TIS) or Unknown TIS 

(j) For any starter adapter with 400 hours 

or more TIS or unknown TIS on the effective 

date of this AD, do the following: 

(1) Within 25 hours TIS, perform the 

inspection procedures specified in Part 3 of 

TCM MSB No. MSB94–4G, dated October 31, 

2005, and replace components as necessary. 

(2) Thereafter, at 400-hour TIS intervals, 

(plus or minus 10 hours TIS), perform 

repetitive inspections and component 

replacements specified in Part 3 of TCM MSB 

No. MSB94–4G, dated October 31, 2005, and 

replace components as necessary. 

Starter Adapters With Fewer Than 400 

Hours TIS 

(k) For any starter adapter with fewer than 

400 hours TIS on the effective date of this 

AD, do the following: 

(1) Upon accumulation of 400 hours TIS, 

(plus or minus 10 hours TIS), perform the 

inspection procedures specified in Part 3 of 

TCM MSB No. MSB94–4G, dated October 31, 

2005, and replace components as necessary. 


hsrobinson on PROD1PC76 with RULES
10920 Federal Register / Vol. 72, No. 47 / Monday, March 12, 2007 / Rules and Regulations 

(2) Thereafter, at 400-hour TIS intervals, 

(plus or minus 10 hours TIS), perform 

repetitive inspections and component 

replacements, as specified in Part 3 of TCM 

MSB No. MSB94–4G, dated October 31, 2005, 

and replace components as necessary. 

Installation of TCM Service Kit, EQ6642 or 

EQ6642R 

(l) At the next engine overhaul or starter 

adapter replacement after the effective date of 

this AD, whichever occurs first, do the 

following: 

(1) Install TCM service kit, P/N EQ6642 

(new) or EQ6642R (rebuilt). Use the service 

kit installation procedures specified in Part 5 

of TCM MSB No. MSB94–4G, dated October 

31, 2005. 

(2) Continue performing the inspections 

and component replacements specified in 

paragraphs (g), (h), (i), (j) and (k) of this AD. 

Prohibition of Special Flight Permits for 

Rough-Running Engines 

(m) Special flight permits are prohibited 

for rough-running engines described in 

paragraph (g)(2) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n) The Manager, Atlanta Aircraft 

Certification Office, FAA, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(o) None. 

Material Incorporated by Reference 

(p) You must use TCM MSB No. MSB94–

4G, dated October 31, 2005, 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 for a 

copy of this service information. For the 

Teledyne Continental Motors Web site: Go to 

http://www.TCMLINK.com. You may review 

copies at the FAA, New England Region, 

Office of the Regional Counsel, 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 

February 26, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–3832 Filed 3–9–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24846; Directorate 

Identifier 2006–NE–21–AD; Amendment 39–

14981; AD 2007–05–20] 

RIN 2120–AA64 

Airworthiness Directives; Microturbo 

Saphir 20 Models 095 Auxiliary Power 

Units (APU) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

It has been reported that with the existing 

configuration, a certain failure could cause 

overspeed of the gas generator rotor resulting 

in uncontained burst of the turbine liberating 

high-energy fragments. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

16, 2007. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in this AD as of April 16, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Tracy Murphy, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate; 

12 New England Executive Park, 

Burlington, MA 01803; telephone 781–

238–7172; fax 781–238–7170. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on December 18, 2006 (71 FR 

75684). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states that: 

It has been reported that with the existing 

configuration, a certain failure could cause 

overspeed of the gas generator rotor resulting 

in uncontained burst of the turbine liberating 

high-energy fragments. The occurrence that 

the high-energy fragments would be 

uncontained is considered a potentially 

dangerous situation which requires 

imperative corrective action. The purpose of 

the modification, which has been made 

mandatory, is to limit gas generator speed 

during an acceleration towards overspeed by 

installation of a modified Electronic Control 

Unit (ECU) and Drain Valve. In addition, the 

modification also renders the exhaust gas 

temperature (EGT) control function 

compliant with the certificated 

specifications. In operation, if EGT exceeds 

the certificated limit value, turbine blade 

shedding could occur. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 


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