43230 Federal Register / Vol. 67, No. 124 / Thursday, June 27, 2002 / Rules and Regulations 

Register on March 8, 2002 (67 FR 

10606). Information in the Mandatory 

Inspections Requirements Table is 

incorrect in two places. In all other 

respects, the original document remains 

the same.

EFFECTIVE DATE: April 12, 2002.

FOR FURTHER INFORMATION CONTACT:

Barbara Caufield, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299; telephone (781) 238–7146; 

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A final 

rule airworthiness directive FR DOC. 

02–5527, applicable to General Electric 

Company (GE) CF34–3A1 and –3B1 

series turbofan engines, was published 

in the Federal Register on March 8, 

2002 (67 FR 10606). The following 

correction is needed:

§ 39.13 [Corrected]

On page 10608, in AD 2002–05–02, in 

Table 804 Mandatory Inspection 

Requirements, in the Part nomenclature 

column, fourth line, ‘‘HPT Rotor Outer 

Torque Coupling (all)’’ is corrected to 

read ‘‘HPT Rotor Outer Torque 

Coupling’’ and in the eleventh line, 

‘‘Stage 3–8 Compressor Rotor Spool 

(all)’’, in the Mandatory inspection 

column for that line, ‘‘All Areas (FPI)’’

is corrected to read ‘‘All Non-coated 

Areas (FPI)’’.

Issued in Burlington, MA, on June 17, 

2002. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service.

[FR Doc. 02–16175 Filed 6–26–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NE–19–AD; Amendment 

39–12792; AD 2002–13–04] 

RIN 2120–AA64 

Airworthiness Directives; Teledyne 

Continental Motors

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule, request for 

comments. 

SUMMARY: This amendment supersedes 

emergency airworthiness directive (AD) 

2000–11–51 that was sent previously to 

all known U.S. owners and operators of 

Teledyne Continental Motors (TCM) O–

300, IO–360, TSIO–360, and LTSIO–

520–AE series reciprocating engines. 

That action required within 10 flight 

hours after receipt of that AD, 

replacement of certain magnetos if they 

fall within the specified serial number 

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. This amendment requires the 

same replacement and inspections and 

adds TCM C–125 and C145 series 

reciprocating engines to the 

applicability, which were inadvertently 

omitted from the emergency AD. This 

amendment is prompted by reports of 

engine failures on certain TCM 

reciprocating engines. The actions 

specified by this AD are intended 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: Effective July 12, 2002. 

Comments for inclusion in the Rules 

Docket must be received on or before 

August 26, 2002.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), New England 

Region, Office of the Regional Counsel, 

Attention: Rules Docket No. 2000–NE–

19–AD, 12 New England Executive Park, 

Burlington, MA 01803–5299. Comments 

may be inspected at this location, by 

appointment, between 8:00 a.m. and 

4:30 p.m., Monday through Friday, 

except Federal holidays. Comments may 

also be sent via the Internet using the 

following address: ‘‘9-aneadcomment@faa.gov’’. Comments sent 

via the Internet must contain the docket 

number in the subject line. The service 

information referenced in this AD may 

be obtained from Teledyne Continental 

Motors, PO Box 90, Mobile, AL 36601; 

telephone (888) 200–7565. Information 

regarding this action may be examined 

at the FAA, New England Region, Office 

of the Regional Counsel, 12 New 

England Executive Park, Burlington, 

MA.

FOR FURTHER INFORMATION CONTACT:

Michael Downs, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, 2300 East Devon Avenue, Des 

Plaines, IL 60018; telephone (847) 294–

7870, fax (847) 294–7834.

SUPPLEMENTARY INFORMATION: On June 7, 

2000, the Federal Aviation 

Administration (FAA) issued 

Emergency airworthiness directive (AD) 

2000–11–51, applicable to TCM O–300, 

IO–360, TSIO–360, and LTSIO–520–AE 

series reciprocating engines, which 

requires, within 10 flight hours after the 

receipt of that AD, replacement of the 

magneto if it falls within the specified 

serial number range, an inspection of 

the removed magneto to verify that the 

stop pin is still in place, and, if the stop 

pin is not in place, an inspection of the 

engine gear train. That action was 

prompted by reports of engine failures 

on certain TCM reciprocating engines. 

This amendment requires the same 

replacement and inspections and adds 

TCM C–125 and C145 series 

reciprocating engines to the 

applicability, which were inadvertently 

omitted from the emergency AD. This 

condition, if not corrected, could result 

in engine failure and subsequent loss of 

control of the airplane. 

FAA’s Determination of an Unsafe 

Condition and Required Actions 

Since the unsafe condition described 

is likely to exist or develop on other 

engines of the same type design, this AD 

is being issued 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. This requires: 

• Replacement of the magneto within 

10 flight hours after the effective date, 

of this AD, if it falls within the specified 

serial number range, and 

• 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. 

Immediate Adoption of This AD 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately on June 7, 2000 to 

all known U.S. owners and operators of 

Teledyne Continental Motors (TCM) O–

300, IO–360, TSIO–360, and LTSIO–

520–AE series reciprocating engines. 

TCM C–125 and C145 series 

reciprocating engines are added to the 

applicability, which were inadvertently 

omitted from the emergency AD. These 

conditions still exist, and the AD is 

hereby superseded in the Federal 

Register as an amendment to Section 

39.13 of part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to make it 

effective to all persons. 

Comments Invited 

Although this action is in the form of 

a final rule that involves requirements 

affecting flight safety and, thus, was not 

preceded by notice and an opportunity 

for public comment, comments are 

invited on this rule. Interested persons

Federal Register / Vol. 67, No. 124 / Thursday, June 27, 2002 / Rules and Regulations 43231

are invited to comment on this rule by 

submitting such written data, views, or 

arguments as they may desire. 

Communications should identify the 

Rules Docket number and be submitted 

in triplicate to the address specified 

under the caption ADDRESSES. All 

communications received on or before 

the closing date for comments will be 

considered, and this rule may be 

amended in light of the comments 

received. Factual information that 

supports the commenter’s ideas and 

suggestions is extremely helpful in 

evaluating the effectiveness of the AD 

action and determining whether 

additional rulemaking action would be 

needed. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the rule that might suggest a need to 

modify the rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report that 

summarizes each FAA-public contact 

concerned with the substance of this AD 

will be filed in the Rules Docket.

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this notice 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2000–NE–19–AD.’’ The 

postcard will be date stamped and 

returned to the commenter. 

Regulatory Analysis 

This final rule does not have 

federalism implications, as defined in 

Executive Order 13132, because it 

would 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. 

Accordingly, the FAA has not consulted 

with state authorities prior to 

publication of this final rule. 

The FAA has determined that this 

regulation is an emergency regulation 

that must be issued immediately to 

correct an unsafe condition in aircraft, 

and is not a ‘‘significant regulatory 

action’’ under Executive Order 12866. It 

has been determined further that this 

action involves an emergency regulation 

under DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979). If it is determined that this 

emergency regulation otherwise would 

be significant under DOT Regulatory 

Policies and Procedures, a final 

regulatory evaluation will be prepared 

and placed in the Rules Docket. A copy 

of it, if filed, may be obtained from the 

Rules Docket at the location provided 

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

Adoption of the Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) as follows:

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by 

adding a new airworthiness directive, 

Amendment 39–12792, to read as 

follows:

2002–13–04 Teledyne Continental Motors:

Amendment 39–12792. Docket No. 

2000–NE–19–AD. 

Applicability 

This airworthiness directive (AD) is 

applicable to Teledyne Continental Motors 

(TCM) C–125, C145, O–300, IO–360, TSIO–

360, and LTSIO–520-AE series reciprocating 

engines with Unison Industries (Slick) 

Magnetos, models 6314, 6324, and 6364, with 

magneto serial numbers of 99110001 through 

9912999 inclusive. These engines are used 

on, but not limited to Cessna 170, 170A, 

170B, 172, 172A through 172H, 172XP, 336, 

337, and T303, Beagle B242–C, Cirrus SR20 

and SR22, Globe Swift GC–1A and GC–1B, 

Maule M4, Piper PA–28R–201T and PA–34, 

and Reims (Cessna) FA172, F337, and FR172.

Note 1: The magneto serial number (SN) 

can be found in logbooks or other 

maintenance records. If the magneto was 

installed, or if the engine was assembled 

new, rebuilt, or overhauled before October 

31, 1999, it is likely that a suspect magneto 

is not installed on the engine.

Note 2: This airworthiness directive (AD) 

applies to each engine identified in the 

preceding applicability provision, regardless 

of whether it has been modified, altered, or 

repaired in the area subject to the 

requirements of this AD. For engines that 

have been modified, altered, or repaired so 

that the performance of the requirements of 

this AD is affected, the owner/operator must 

request approval for an alternative method of 

compliance in accordance with paragraph (d) 

of this AD. The request should include an 

assessment of the effect of the modification, 

alteration, or repair on the unsafe condition 

addressed by this AD; and, if the unsafe 

condition has not been eliminated, the 

request should include specific proposed 

actions to address it.

Compliance 

Compliance with this AD is required 

within 10 flight hours after the effective date 

of this AD, unless already done. 

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, do the following: 

Replacement of Magneto 

(a) Replace any magneto that has a SN of 

99110001 through 99129999, inclusive, with 

a magneto that does not have a serial number 

in that range. 

Inspections 

(b) 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, C145, 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. 

(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. 

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

not install any Unison Industries magnetos, 

model 6314, 6324, or 6364 that have a SN of 

99110001 through 99129999 inclusive, on 

any engine.

Note 3: A cross-reference for part numbers 

(P/N’s) for Unison magneto model 6314 

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

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

43232 Federal Register / Vol. 67, No. 124 / Thursday, June 27, 2002 / Rules and Regulations 

can be found in TCM Mandatory Service 

Bulletin 00–6A, dated June 8, 2000.

Alternative Methods of Compliance 

(d) An alternative method of compliance or 

adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Chicago 

Aircraft Certification Office (CHIACO). 

Operators must submit their requests through 

an appropriate FAA Principal Maintenance 

Inspector, who may add comments and then 

send it to the Manager, CHIACO.

Note 4: Information concerning the 

existence of approved alternative methods of 

compliance with this airworthiness directive, 

if any, may be obtained from the CHIACO.

Special Flight Permits 

(e) Special flight permits may be issued in 

accordance with §§ 21.197 and 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199) to operate the aircraft to a 

location where the requirements of this AD 

can be done. 

Effective Date 

(f) This amendment becomes effective July 

12, 2002.

Issued in Burlington, Massachusetts, on 

June 17, 2002. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service.

[FR Doc. 02–16174 Filed 6–26–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 98–ANE–38–AD; Amendment 

39–12790; AD 2002–13–03] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International (CFMI) CFM56–2, –2A, 

–2B, –3, –3B, –3C, –5, –5B, –5C, and 

–7B Series Turbofan Engines

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

that is applicable to certain CFM 

International (CFMI) CFM56 series 

turbofan engines. That AD currently 

requires revisions to the Airworthiness 

Limitations Section of applicable Engine 

Shop Manuals (ESM’s) to include 

required enhanced inspection of 

selected critical life-limited parts at 

each piece-part exposure. This 

amendment requires revisions to the 

Airworthiness Limitations Section of 

the applicable manufacturer’s manuals 

and air carrier’s approved continuous 

airworthiness maintenance program to 

incorporate additional inspections of 

selected critical life-limited parts at 

each piece-part exposure. This 

amendment is prompted by an FAA 

study of in-service events involving 

uncontained failures of critical rotating 

parts. The actions specified by this AD 

are intended to prevent critical lifelimited rotating engine part failure, 

which could result in an uncontained 

engine failure and damage to the 

airplane.

DATES: Effective date August 1, 2002.

ADDRESSES: Information regarding this 

action may be examined, by 

appointment, at the Federal Aviation 

Administration (FAA), New England 

Region, Office of the Regional Counsel, 

12 New England Executive Park, 

Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Diane Cook, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7133, fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2000–12–01, 

Amendment 39–11779 (65 FR 37031, 

June 13, 2000), which is applicable to 

certain CFMI CFM56 series turbofan 

engines, was published in the Federal 

Register on October 5, 2001, (66 FR 

50910). That action proposed to modify 

the airworthiness limitations section of 

the manufacturer’s manual and an air 

carrier’s approved continuous 

airworthiness maintenance program to 

incorporate additional inspection 

requirements. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Typographical Errors 

Four commenters requested 

typographical errors be corrected in the 

Mandatory Inspections Table as follows:

• For HPT Disk, change Engine 

Manual Section from 75–72–02 to 75–

52–02. 

• For HPC Rear (CDP) Air Seal, 

change Engine Manual Section from 72–

52–03 to 72–31–08. 

• For LPT Stub Shaft, change Engine 

Models from All to -2, -2A, -2B, -3, -3B, 

and -3C. 

• For LPT Stub Shaft, change Engine 

Manual Section from 72–52–03 to 72–

55–02. 

• For LPT Shaft, change Inspection 

from FPI to MPI. 

The FAA agrees and has corrected 

these typographical errors in the final 

rule. 

Concern for Lead Time 

One commenter is concerned that for 

operators to put procedures and tooling 

in place in time to comply with the AD, 

the manufacturer should release the 

Engine Manual time limit and 

procedural changes by Temporary 

Revision before the issuance of the AD, 

or, revise the AD compliance time to 

state compliance to be within 30 days 

after the issuance of the Engine Manual 

revision (or Temporary Revision). 

The FAA understands the 

commenter’s concern. The FAA is aware 

that the manufacturer has not yet issued 

Temporary Revisions to the Engine 

Manual time limits section. However, 

the existing AD and this final rule allow 

the manufacturer up to 30 days after the 

effective date of the AD to issue the 

necessary revisions to the time limits 

section. Therefore, no action is 

necessary to address the commenter’s 

observation. 

Question on Model Effectivity 

One commenter asks why the 

proposed rule does not affect the 

various models of the CFM56–5A 

engine. The FAA understands that the 

commenter is referring to the CFM56–5–

A engine in the proposed rule and in the 

final rule that is an engine subset 

covered under the -5 series. The -5 

series is listed in the Applicability 

section, and therefore, the CFM56–5–A 

engine is included in the applicability 

of this AD. 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Economic Analysis 

The FAA estimates that 5,100 CFM56 

engines installed on airplanes of US 

registry would be affected by this AD 

and that there are approximately 2,300 

piece part annual inspections that 

would be required. It would take 

approximately 2,775 work hours to do 

these inspections. The average labor rate 

is $60 per work hour. The total 

estimated annual cost of the new 

inspections on US operators is expected 

to be approximately $166,500.