Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 56355 

TABLE 1.—SERVICE INFORMATION

Inspect in accordance with either— 

The Accomplishment Instructions of Boeing Service Bulletin 737–53– 

1117, Revision 1, dated April 6, 1989— Figure 17 of the special attention service bulletin— 

A detailed inspection for cracks in the fuselage lower skin in the area 

of the electronics bay cooling duct cutout.

An eddy current inspection for cracks of the exhaust port duct cutout 

edge and the 6 fastener locations; 

An eddy current and open-hole probe inspection for cracks of the satellite holes; and 

A general visual inspection for corrosion of the area under the repair. 

Corrective Actions 

(j) If any crack at the equipment cooling 

duct cutout is found that is less than 3 inches 

in length during the inspection required by 

paragraph (i) of this AD: Before further flight, 

stop-drill the crack or cracks and install an 

external repair doubler in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1117, Revision 1, 

dated April 6, 1989; or repair in accordance 

with Part III of the special attention service 

bulletin. If the special attention service 

bulletin specifies to contact Boeing for 

appropriate Action: Before further flight, 

repair using a method approved in 

accordance with paragraph (m) of this AD. 

Accomplishment of the repair terminates the 

repetitive inspection requirements of 

paragraph (g) of this AD for the repaired area. 

(k) If any corrosion is found, or if any crack 

is found that is 3 inches in length or greater 

during the inspection required by paragraph 

(i) of this AD: Before further flight, repair 

using a method approved in accordance with 

paragraph (m) of this AD. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Optional Terminating Action 

(l) Installing preventive modification 

doublers in accordance with the special 

attention service bulletin, including the 

additional eddy current inspection with the 

fasteners removed (with no crack finding), 

terminates the repetitive inspection 

requirements of paragraph (g) of this AD. 

Where Figure 2 of the special attention 

service bulletin specifies to ‘‘eddy current 

countersink inspect and open hole probe 

inspect the 16 satellite holes,’’ and the 

airplane has an external repair doubler 

installed in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1117, Revision 1, 

dated April 6, 1989; that inspection is not 

required by this AD. If any crack is found 

during the eddy current inspection specified 

by this paragraph: Before further flight, 

discontinue the preventive modification and 

do the applicable actions in paragraph (h) of 

this AD. 

Alternative Methods of Compliance 

(m)(1) In accordance with 14 CFR 39.19, 

the Manager, Seattle Aircraft Certification 

Office (ACO), is authorized to approve 

alternative methods of compliance (AMOCs) 

for this AD. 

(2) 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 

Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make those 

findings. 

(3) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Material Incorporated by Reference 

(n) You must use Boeing Service Bulletin 

737–53–1117, Revision 1, dated April 6, 

1989; and Boeing Special Attention Service 

Bulletin 737–53–1230, dated June 13, 2002; 

as applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of these documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207, 

for a copy of this service information. You 

may review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the 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 15, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–18911 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20850; Directorate 

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

14297; AD 2005–20–04] 

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 adopting a new 

airworthiness directive (AD) for 

Teledyne Continental Motors (TCM) 

GTSIO–520 series reciprocating engines. 

This AD requires initial and repetitive 

visual inspections of the starter adapter 

assembly and crankshaft gear. This AD 

also requires unscheduled visual 

inspections of the starter adapter 

assembly and crankshaft gear due to a 

rough-running engine. This AD also 

requires replacement of the starter 

adapter shaft gear needle bearing with a 

certain bushing. Also, this AD requires 

installation of a certain TCM service kit 

at the next engine overhaul, or at the 

next starter adapter replacement, 

whichever occurs first. This AD results 

from six service difficulty reports and 

one fatal accident report received 

related to failed starter adapter 

assemblies. 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. 

DATES: This AD becomes effective 

November 1, 2005. The Director of the 

56356 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of November 1, 2005. 

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. For the Teledyne 

Continental Motors Web site: Go to 

http://www.TCMLINK.com. 

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 airworthiness directive (AD). 

The proposed AD applies to TCM 

GTSIO–520 series reciprocating engines. 

We published the proposed AD in the 

Federal Register on January 13, 2005 

(70 FR 2333). That action proposed to 

require: 

• Before further flight, adding a 

placard to the instrument panel within 

view of the pilot that states, in 1⁄4 inchhigh or higher characters, ‘‘In 

accordance with AD (number to be 

provided), the pilot must report a roughrunning engine that cannot be cleared 

by adjustment of the engine controls; 

particularly the fuel mixture setting, to 

maintenance personnel, immediately 

after landing.’’ 

• Initial and repetitive visual 

inspections of the starter adapter 

assembly and crankshaft gear, and 

replacement of components as 

necessary. 

• Unscheduled visual inspections of 

the starter adapter assembly and 

crankshaft gear due to a rough-running 

engine, and replacement of components 

as necessary. 

• Replacement of the starter adapter 

shaft gear needle bearing, P/N 537721 

with bushing, P/N 654472. 

• Installation of TCM service kit, P/N 

EQ6642R, at next engine overhaul, or at 

next starter adapter replacement, 

whichever occurs first. 

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 Offices 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 comments received. 

Request To Delete Requirement for a 

Placard 

Two commenters request that we 

delete the requirement for a placard in 

the cockpit. The placard would state 

that the pilot must report a roughrunning engine that cannot be cleared 

by adjustment of the engine controls; 

particularly the fuel mixture setting, to 

maintenance personnel, immediately 

after landing. The commenters state that 

the placard provides no useful in-flight 

information. One of the commenters 

states that there is no chance that the 

commenter would depart with a rough 

running engine. We agree that the 

placard provides no useful in-flight 

information. Therefore, we have 

removed the placard requirement from 

the AD. 

Parts Costs in the NPRM Are 

Underestimated 

One commenter states that the parts 

costs in the NPRM are underestimated 

and are actually much higher. We 

disagree. However, we found that TCM 

agreed to reduce the prices for these 

parts. The price for the TCM service kit, 

P/N EQ6642R is reduced from $2,477 to 

$1,858, and the price for the bushing is 

reduced from $105 to $53. 

Revised Mandatory Service Bulletin 

The proposed AD referenced TCM 

Mandatory Service Bulletin (MSB) No. 

MSB94–4E, dated January 24, 2005. 

Since we issued the NPRM, TCM 

revised that bulletin. This AD references 

the revised SB, TCM MSB No. MSB94– 

4F, dated July 5, 2005. 

Conclusion 

We 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 determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

About 5,300 TCM GTSIO–520 series 

reciprocating engines of the affected 

design are in the worldwide fleet. We 

estimate that 4,240 engines installed on 

airplanes of U.S. registry will be affected 

by this AD. We also estimate that it will 

take about one work hour per engine to 

perform one of the inspections, and 

about one work hour per engine to 

perform the bushing installation. We 

also estimate that it will take about six 

work hours per engine to install TCM 

service kit, P/N EQ6642R. The average 

labor rate is $65 per work hour. We 

estimate that about 25% (1,060) of the 

engines will require an unscheduled 

(rough-running engine) inspection, that 

each engine has eight 100-hour 

inspections per year, and two 400-hour 

inspections per year. We also estimate 

that about 50% (2,120) of the engines 

will require the bushing installed and 

TCM service kit, P/N EQ6642R 

installed. Required bushings will cost 

about $53 per engine and required 

service kits will cost about $1,858 per 

engine. Based on these figures, we 

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

operators to be $7,840,820. 

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: 

Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 56357 

(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 adding 

the following new airworthiness 

directive: 

2005–20–04 Teledyne Continental Motors: 

Amendment 39–14297. Docket No. 

FAA–2005–20850; Directorate Identifier 

2005–NE–05—AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 1, 2005. 

Affected ADs 

(b) None. 

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 six service 

difficulty reports and one fatal accident 

report received related to failed starter 

adapter assemblies. 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 bushing, P/N 654472, before 

reassembling components. Use the bushing 

installation procedure specified in Part 4 of 

TCM Mandatory Service Bulletin (MSB) No. 

MSB94–4F, dated July 5, 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. MSB94–4F, dated 

July 5, 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 a 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, at the next 100-hour or 

annual inspection, whichever occurs first, do 

the following: 

(1) Perform the inspection procedures 

specified in Part 2 of TCM MSB No. MSB94–

4F, dated July 5, 2005, and replace 

components as necessary. 

(2) Thereafter, at each 100-hour inspection, 

(plus or minus 10 hours), and annual 

inspection, perform repetitive inspections 

and component replacements as specified in 

paragraph (h)(1) of this AD. 

Starter Adapters With 400 Hours or More 

Time-In-Service (TIS) or Unknown TIS 

(i) 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. MSB94–4F, dated July 5, 

2005, and replace components as necessary. 

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

(plus or minus 10 hours), perform repetitive 

inspections and component replacements 

specified in Part 3 of TCM MSB No. MSB94–

4F, dated July 5, 2005, and replace 

components as necessary. 

Starter Adapters With Fewer Than 400 

Hours TIS 

(j) 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), perform the 

inspection procedures specified in Part 3 of 

TCM MSB No. MSB94–4F, dated July 5, 

2005, and replace components as necessary. 

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

(plus or minus 10 hours), perform repetitive 

inspections and component replacements, as 

specified in Part 3 of TCM MSB No. MSB94–

4F, dated July 5, 2005, and replace 

components as necessary. 

Installation of TCM Service Kit, EQ6642R 

(k) 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 EQ6642R. 

Use the service kit installation procedures 

specified in Part 5 of TCM MSB No. MSB94–

4F, dated July 5, 2005. 

(2) Continue performing the inspections 

and component replacements specified in 

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

Prohibition of Special Flight Permits for 

Rough-Running Engines 

(l) Special flight permits are prohibited for 

rough-running engines described in 

paragraph (g)(2) of 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. 

Related Information 

(n) European Aviation Safety Agency AD 

2004–0006, dated December 15, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(o) You must use Teledyne Continental 

Motors Mandatory Service Bulletin No. 

MSB94–4F, dated July 5, 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 Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, Room 

PL–401, Washington, DC 20590–0001, on the 

Internet at http://dms.dot.gov, 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 20, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–19149 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–P