78808 Federal Register / Vol. 76, No. 244 / Tuesday, December 20, 2011 / Rules and Regulations 

FK23986. Replace the clips that hold the fuel 

tubes in place. Use paragraphs 3.A.(1) 

through 3.A.(3) (on-wing) of RR Nonmodification Alert Service Bulletin (ASB) 

RB.211–73–AD685, Revision 6, dated 

February 21, 2011 to do the inspection. 

Replace any fan case LP fuel tubes that fail 

inspection. 

(2) In-Shop Inspection and Clip Replacement 

Inspect the fan case LP fuel tubes, P/N 

FK22617, FK19213, and FK23986. Replace 

the clips that hold the fuel tubes in place 

with new or serviceable clips. Use 

paragraphs 3.B.(1) through 3.B.(3) (in-shop) 

of RR Non-modification ASB RB.211–73– 

AD685, Revision 6, dated February 21, 2011 

to do the inspection. Replace any fan case LP 

fuel tubes that fail inspection. 

(g) Repetitive Inspection and Clip 

Replacement 

Repeat the inspection required by 

paragraphs (f)(1) and (f)(2) of this AD and 

replace the clips at intervals not exceeding 

every 3,000 hours time-since-last-inspection. 

(h) Re-Installation Prohibition 

Do not re-install any clips replaced in 

accordance with paragraphs (f)(1) and (f)(2) 

of this AD. 

(i) Previous Inspection Credit 

If you previously performed the inspection 

required by Revision 3 of SB RB.211–73– 

D685, dated August 18, 2009, or Revision 4 

of SB RB.211–73–D685, dated January 20, 

2010, or Revision 5 of ASB RB.211–73– 

AD685, dated August 18, 2010, you met the 

initial inspection requirements of this AD. 

(j) Definition 

‘‘Last inspection’’ means the last 

inspection of the fan case LP fuel tubes, 

P/Ns FK22617, FK19213, and FK23986, for 

frettage between the securing clips and the 

tube outer surface. 

(k) FAA AD Differences 

None. 

(l) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2010–0188, dated 

September 20, 2010, and Rolls-Royce plc 

Alert Service Bulletin RB.211–73–AD685, 

Revision 6, dated February 21, 2011, for 

related information. Contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 31, 

Derby, England, DE248BJ; phone: 011–44– 

1332–242424; fax: 011–44–1332–245418; or 

email: http://www.rolls-royce.com/contact/

civil_team.jsp, for a copy of this service 

information. 

(2) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; email: alan.strom@faa.gov; phone: 

(781) 238–7143; fax: (781) 238–7199, for 

more information about this AD. 

(n) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified. 

(2) Rolls-Royce plc Alert Service Bulletin 

RB.211–73–AD685, Revision 6, dated 

February 21, 2011, approved for IBR January 

24, 2012. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–245418 or email: 

http://www.rolls-royce.com/contact/civil_

team.jsp. 

(4) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call (781) 238–7125. 

(5) 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 an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

December 12, 2011. 

Thomas A. Boudreau, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–32490 Filed 12–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0085; Directorate 

Identifier 2000–NE–19–AD; Amendment 39– 

16897; AD 2011–26–07] 

RIN 2120–AA64 

Airworthiness Directives; Teledyne 

Continental Motors (TCM) and RollsRoyce Motors Ltd. (R–RM) Series 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain TCM and R–RM series 

reciprocating engines. That AD 

currently requires replacement of 

certain magnetos if they fall within the 

specified serial number (S/N) range, 

inspection of the removed magneto to 

verify that the stop pin is still in place, 

and, if the stop pin is not in place, 

inspection of the engine gear train, 

crankcase, and accessory case. This new 

AD corrects the range of S/Ns affected, 

requires the same replacement and 

inspections, and adds R–RM C–125, C– 

145, O–300, IO–360, TSIO–360, and 

LTSIO–520–AE series reciprocating 

engines to the applicability. This AD 

was prompted by our awareness of an 

error in the previous AD applicability in 

the range of magneto S/Ns affected and 

of the need to include certain engines 

made by R–RM, under license of TCM. 

We are issuing this AD to prevent 

engine failure and loss of control of the 

airplane due to migration of the 

magneto impulse coupling stop pin out 

of the magneto frame and into the gear 

train of the engine. 

DATES: This AD is effective January 24, 

2012. 

ADDRESSES: For service information 

identified in this AD, contact Teledyne 

Continental Motors, Inc., PO Box 90, 

Mobile, AL 36601; phone: 251–438– 

3411, or go to http://tcmlink.com/ 

servicebulletins.cfm. You may review 

copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call (781) 238– 

7125. 

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 (phone: (800) 647–5527) 

is 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: 

Juanita Craft, Aerospace Engineer, 

Atlanta Certification Office, FAA, Small 

Airplane Directorate, 1701 Columbia 

Avenue, College Park, Georgia 30337; 

phone: (404) 474–5584; fax: (404) 474– 

5606; email: juanita.craft@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 76, No. 244 / Tuesday, December 20, 2011 / Rules and Regulations 78809 

part 39 to supersede AD 2002–13–04, 

amendment 39–12792 (67 FR 43230, 

June 27, 2002). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

June 28, 2011 (76 FR 37682). That 

NPRM proposed to continue to require 

replacement of certain magnetos if they 

fall within the specified S/N range, 

inspection of the removed magneto to 

verify that the stop pin is still in place, 

and, if the stop pin is not in place, 

inspection of the engine gear train, 

crankcase, and accessory case. That 

NPRM also proposed to correct the 

range of S/Ns affected and add R–RM C– 

125, C–145, O–300, IO–360, TSIO–360, 

and LTSIO–520–AE series reciprocating 

engines to the applicability. We are 

issuing this AD to prevent engine failure 

and loss of control of the airplane due 

to migration of the magneto impulse 

coupling stop pin out of the magneto 

frame and into the gear train of the 

engine. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to this comment. 

Question on Who the AD Is Written 

Against 

A commenter, not further identified, 

asked why the AD was issued against 

TCM and not ‘‘Slick.’’ 

We do not agree. We write ADs 

against either a product or an appliance. 

In the case of this AD, magnetos are part 

of the engine type certificate and, 

therefore, considered part of the product 

(the engine). We did not change the AD 

as a result of this comment. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 100 

R–RM C–125, C–145, O–300, IO–360, 

TSIO–360, and LTSIO–520–AE series 

reciprocating engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about 2 workhours per engine to perform the 

inspections, and that the average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the total cost 

of this AD to U.S. operators to be 

$17,000. Our cost estimate is exclusive 

of possible warranty coverage. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 

removing airworthiness directive (AD) 

2002–13–04, Amendment 39–12792 (67 

FR 43230, June 27, 2002), and adding 

the following new AD: 

2011–26–07 Teledyne Continental Motors 

(TCM) and Rolls-Royce Motors Ltd. (R– 

RM) Series Reciprocating Engines: 

Amendment 39–16897; Docket No. 

FAA–2011–0085; Directorate Identifier 

2000–NE–19–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 24, 2012. 

(b) Affected ADs 

This AD supersedes AD 2002–13–04, 

Amendment 39–12792 (67 FR 43230, June 

27, 2002). 

(c) Applicability 

This AD applies to TCM and R–RM C–125, 

C–145, O–300, IO–360, TSIO–360, and 

LTSIO–520–AE series reciprocating engines 

with Champion Aerospace (formerly Unison 

Industries) Slick Magnetos, models 6314, 

6324, and 6364, with magneto serial numbers 

(S/Ns) of 99110001 through 99129999, 

inclusive. 

(d) Unsafe Condition 

This AD was prompted by an error in the 

previous AD applicability in the range of 

magneto S/Ns affected, and by the need to 

include certain engines made by R–RM, 

under license of TCM. We are issuing this AD 

to prevent engine failure and loss of control 

of the airplane due to migration of the 

magneto impulse coupling stop pin out of the 

magneto frame and into the gear train of the 

engine. 

(e) Compliance 

Comply with this AD within 10 flight 

hours after the effective date of this AD, 

unless already done. 

(f) Replacement of Magneto 

Replace any magneto that has an S/N of 

99110001 through 99129999, inclusive, with 

a magneto that does not have a serial number 

in that range. If a magneto is not in this S/ 

N range, no further action is required by this 

AD. 

(g) Inspections 

Inspect each removed magneto to verify 

that the impulse coupling stop pin is present. 

If the pin is missing, do the following: 

(1) For C–125, C–145, O–300, IO–360, and 

TSIO–360 series engines, do the following: 

(i) Remove magnetos, alternator or 

generator, and starter adapter from the 

accessory case. 

(ii) Remove the accessory case from the 

crankcase and oil sump. 

(iii) Visually inspect the entire engine gear 

train for damaged or broken gears and gear 

teeth. 

(iv) Inspect visible portions of the engine 

crankcase and accessory case for damage due 

to the stop pin becoming lodged between the 

engine gear train and the crankcase or 

accessory case. 


pmangrum on DSK3VPTVN1PROD with RULES
78810 Federal Register / Vol. 76, No. 244 / Tuesday, December 20, 2011 / Rules and Regulations 

(v) If the accessory case is damaged, repair 

or replace the accessory case. 

(vi) If the engine crankcase is damaged, 

disassemble the engine, and repair or replace 

the crankcase. 

(vii) Inspect the oil pump drive gear teeth 

and inner cam gear teeth for damage. Replace 

any engine drive train component that has 

been damaged. 

(viii) Replace any damaged gear, and 

magnaflux the mating gears using the 

applicable engine overhaul manual. 

(2) For LTSIO–520–AE series engines, do 

the following: 

(i) Remove the starter adapter, fuel pump, 

vacuum pumps, accessory drive pads, and 

both magnetos. 

(ii) Visually inspect the entire engine gear 

train for damaged or broken gears and gear 

teeth. 

(iii) If any damage has occurred, remove 

the engine from the airplane, disassemble the 

engine, and inspect it for damage. If any 

damage is found, repair as necessary. 

(iv) Replace any damaged gear, and 

magnaflux the mating gears using the 

applicable engine overhaul manual. 

(v) Inspect the interior portions of the 

engine crankcase for damage due to the stop 

pin becoming lodged between the gear train 

and the crankcase. If the crankcase is 

damaged, repair or replace the crankcase. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install any Champion Aerospace (formerly 

Unison Industries) Slick magnetos, model 

6314, 6324, or 6364 that have an S/N of 

99110001 through 99129999, inclusive, on 

any engine. 

(i) Alternative Methods of Compliance 

The Manager, Atlanta Aircraft Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(j) Related Information 

(1) A cross-reference for part numbers (P/ 

Ns) for Champion Aerospace (formerly 

Unison Industries) Slick magneto model 6314 

(TCM P/N 653271), model 6324 (TCM P/N 

653292), and model 6364 (TCM P/N 649696) 

can be found in TCM Mandatory Service 

Bulletin MSB00–6D, dated November 19, 

2010. 

(2) For more information about this AD, 

contact Juanita Craft, Aerospace Engineer, 

Propulsion, Atlanta Aircraft Certification 

Office, FAA, Small Airplane Directorate; 

1701 Columbia Avenue, College Park, 

Georgia 30337; phone: (404) 474–5584; fax: 

(404) 474–5606; email: juanita.craft@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

December 8, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–32252 Filed 12–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30818; Amdt. No. 3457] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective December 

20, 2011. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

20, 2011. 

ADDRESSES: Availability of matter 

incorporated by reference in the 

amendment is as follows: 

For examination— 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; 

2. The FAA Regional Office of the 

region in which the affected airport is 

located; 

3. The National Flight Procedures 

Office, 6500 South MacArthur Blvd., 

Oklahoma City, OK 73169; or 

4. 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. 

Availability—All SIAPs are available 

online free of charge. Visit nfdc.faa.gov 

to register. Additionally, individual 

SIAP and Takeoff Minimums and ODP 

copies may be obtained from: 

1. FAA Public Inquiry Center (APA– 

200), FAA Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; or 

2. The FAA Regional Office of the 

region in which the affected airport is 

located. 

FOR FURTHER INFORMATION CONTACT: 

Richard A. Dunham III, Flight Procedure 

Standards Branch (AFS–420) Flight 

Technologies and Programs Division, 

Flight Standards Service, Federal 

Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd., Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082 Oklahoma City, OK 73125) 

telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This rule 

amends Title 14, Code of Federal 

Regulations, part 97 (14 CFR part 97) by 

amending the referenced SIAPs. The 

complete regulatory description of each 

SIAP is listed on the appropriate FAA 

Form 8260, as modified by the National 

Flight Data Center (FDC)/Permanent 

Notice to Airmen (P–NOTAM), and is 

incorporated by reference in the 

amendment under 5 U.S.C. 552(a), 1 

CFR part 51, and § 97.20 of Title 14 of 

the Code of Federal Regulations. 

The large number of SIAPs, their 

complex nature, and the need for a 

special format make their verbatim 

publication in the Federal Register 

expensive and impractical. Further, 

airmen do not use the regulatory text of 

the SIAPs, but refer to their graphic 

depiction on charts printed by 

publishers of aeronautical materials. 

Thus, the advantages of incorporation 

by reference are realized and 

publication of the complete description 

of each SIAP contained in FAA form 

documents is unnecessary. This 

amendment provides the affected CFR 

sections and specifies the types of SIAP 

and the corresponding effective dates. 

This amendment also identifies the 

airport and its location, the procedure 

and the amendment number. 

The Rule 

This amendment to 14 CFR part 97 is 

effective upon publication of each 

separate SIAP as amended in the 

transmittal. For safety and timeliness of 

change considerations, this amendment 

incorporates only specific changes 

contained for each SIAP as modified by 

FDC/P–NOTAMs. 

The SIAPs, as modified by FDC 

P–NOTAM, and contained in this 

amendment are based on the criteria 

contained in the U.S. Standard for 


pmangrum on DSK3VPTVN1PROD with RULES