29932 Federal Register / Vol. 61, No. 115 / Thursday, June 13, 1996 / Rules and Regulations

is $60 per work hour. This AD adds no

additional requirements; the resetting of

engine timing for engines with the

improved cylinders is optional.

Therefore, there is no cost imposed by

the required actions. However, if the

timing was reset on all applicable

engines, based on these figures, the total

cost impact of the AD on U.S. operators

is estimated to be $2,820,000.

The regulations adopted herein will

not have substantial direct effects 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. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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, Incorporation by reference,

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

removing Amendment 39–2925 (42 FR

31770, June 23, 1977), and Amendment

39–3301 (43 FR 41374, September 18,

1978), and by adding a new

airworthiness directive, Amendment

39–9648, to read as follows:

96–12–06 Teledyne Continental Motors and

Rolls-Royce, plc.: Amendment 39–9648.

Docket 94–ANE–53. Supersedes AD 77–

13–03, Amendment 39–2925 and AD 78–

19–02, Amendment 39–3301.

Applicability: Teledyne Continental

Motors (TCM) Model O–200A and O–200B

and Rolls-Royce, plc. Model O–200A, O–

200B, and O–200C reciprocating engines.

These engines are installed on but not

limited to American Champion Models 7ECA

and 402; Cessna Model 150, 150A through

150M, A150K through A150M; Reims Models

F–150G through F–150M, FA–150K and FA–

150L; and Taylorcraft Model F19 aircraft.

Note: 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

use the authority provided in paragraph (g)

to request approval from the Federal Aviation

Administration (FAA). This approval may

address either no action, if the current

configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any engine from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent possible cylinder cracking with

subsequent loss of engine power, accomplish

the following:

(a) For engines that have one or more

cylinders with part numbers (P/N) lower than

641917, within the next 50 hours time in

service (TIS) after the effective date of this

AD, reset the engine timing to 24° (+1°, ¥1°)

Before Top Center (BTC) on both magnetos in

accordance with the magneto to engine

timing procedure for direct drive engines in

TCM Service Bulletin (SB) No. SB94–8, dated

September 14, 1994.

(b) For engines that have all four cylinders

with P/N 641917 or higher, the engine timing

may be reset to 28° (+1°, ¥1°) BTC on both

magnetos in accordance with the magneto

engine timing procedure for direct drive

engines in TCM SB No. SB94–8, dated

September 14, 1994.

(c) Subsequent installation of cylinders

must be of the P/N listed in paragraph (b) of

this AD to retain the 28° BTC timing.

Note: The P/N is stamped on the cylinder

barrel flange.

(d) This AD supersedes AD 77–13–03 and

AD 78–19–02.

(e) When paragraph (a) is accomplished,

restamp the engine data plate to indicate

magneto timing of 24° BTC.

(f) When paragraph (b) is accomplished,

restamp the engine data plate to indicate

magneto timing of 28° BTC.

(g) 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, Atlanta

Aircraft Certification Office. The request

should be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Atlanta Aircraft Certification Office.

Note: Information concerning the existence

of approved alternative method of

compliance with this AD, if any, may be

obtained from the Atlanta Aircraft

Certification Office.

(h) Special flight permits may be

issued in accordance with sections

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 accomplished.

(i) The actions required by this AD

shall be done in accordance with the

following service bulletin:

Document No. Pages Date

TCM SB No.

SB94–8.

1–6 September 14,

1994.

Total pages: 6.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Teledyne Continental Motors, P.O. Box

90, Mobile, AL 36601; telephone (334) 438–

3411. Copies may be inspected at the FAA,

New England Region, Office of the Assistant

Chief Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(j) This amendment becomes effective on

July 18, 1996.

Issued in Burlington, Massachusetts, on

May 29, 1996.

Robert E. Guyotte,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 96–14867 Filed 6–12–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–16; Amendment 39–

9647; AD 96–12–05]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal,

Inc. (Formerly Textron Lycoming)

LTS101 Series Turboshaft and LTP101

Series Turboprop Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to AlliedSignal, Inc.
Federal Register / Vol. 61, No. 115 / Thursday, June 13, 1996 / Rules and Regulations 29933

(formerly Textron Lycoming) LTS101

series turboshaft and LTP101 series

turboprop engines, that requires

identifying, removing, and replacing

certain defective power turbine rotors.

This amendment is prompted by reports

of workmanship deficiencies on certain

power turbine rotors that can reduce the

published life limit of the disk. The

actions specified by this AD are

intended to prevent power turbine rotor

failure, which could result in loss of

engine power.

DATES: Effective August 12, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 12,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from AlliedSignal Engines, 111 South

34th Street, Phoenix, AZ 85072;

telephone (602) 365–2493, fax (602)

365–2210. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Dave Keenan, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7139,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to AlliedSignal, Inc.

(formerly Textron Lycoming) LTS101

series turboshaft and LTP101 series

turboprop engines was published in the

Federal Register on October 16, 1995

(60 FR 53548). That action proposed to

require identifying, removing, and

replacing certain defective power

turbine rotors in accordance with

Textron Lycoming Service Bulletins

(SB’s) No. LT101–72–50–0144, dated

January 15, 1993, and No. LT101–72–

50–0145, dated November 27, 1991.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

There are approximately 645 engines

of the affected design in the worldwide

fleet. The FAA estimates that 430

engines installed on aircraft of U.S.

registry will be affected by this AD, that

it will take approximately 25 work

hours per engine to accomplish the

required actions, and that the average

labor rate is $60 per work hour. The

manufacturer has advised the FAA that

all required hardware will be provided

at no cost to the operators. Based on

these figures, the total cost impact of the

AD on U.S. operators is estimated to be

$645,000.

The regulations adopted herein will

not have substantial direct effects 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. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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, Incorporation by reference,

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.

§ 9.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–12–05 AlliedSignal, Inc.: Amendment 39–

9647. Docket 95–ANE–16.

Applicability: AlliedSignal, Inc. (formerly

Textron Lycoming) LTS101 series turboshaft

engines installed on, but not limited to, the

Eurocopter AS350 and SA366G1,

Messerschmitt-Bolkow-Blohm/Kawasaki

MBB–BK117 and the Bell Helicopter Textron

222 aircraft, and LTP101 series turboprop

engines, installed on but not limited to, the

Piaggio P166DL and Airtractor AT302

aircraft.

Note: 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

use the authority provided in paragraph (c)

to request approval from the Federal Aviation

Administration (FAA). This approval may

address either no action, if the current

configuration eliminates the unsafe

condition, or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any engine from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent power turbine rotor failure,

which could result in loss of engine power,

accomplish the following:

(a) For all LTS101 series turboshaft engines

except the LTS101–750B2 model, and all

LTP101 series turboprop engines, remove

and replace power turbine rotors identified

in Table 1 of Textron Lycoming Service

Bulletin (SB) No. LT101–72–50–0144, dated

January 15, 1993, in accordance with the

accomplishment procedures in Textron

Lycoming SB No. LT101–72–50–0144, dated

January 15, 1993, and the following schedule:

(1) For power turbine rotors with more

than 1,000 hours time since new (TSN) on

the effective date of this AD, remove and

replace within the next 50 hours time in

service (TIS), not to exceed 1,800 cycles since

new (CSN).

(2) For power turbine rotors with 1,000

hours TSN or less, but more than 800 hours

TSN on the effective date of this AD, remove

and replace within the next 100 hours TIS,

not to exceed 1,800 CSN.

(3) For power turbine rotors with 800 hours

TSN or less, but more than 400 hours TSN

on the effective date of this AD, remove and

replace within the next 150 hours TIS, not to

exceed 1,800 CSN.

(4) For power turbine rotors with 400 hours

TSN or less on the effective date of this AD,

remove and replace no later than 600 hours

TSN, not to exceed 1,800 CSN.
29934 Federal Register / Vol. 61, No. 115 / Thursday, June 13, 1996 / Rules and Regulations

(b) For all LTS101–750B2 model engines,

remove and replace power turbine rotors, in

accordance with the accomplishment

procedures of Textron Lycoming SB No.

LT101–72–50–0145 dated November 27,

1991, within the next 100 hours TIS after the

effective date of this AD, or 800 hours TSN

on the power turbine rotor, whichever occurs

first.

(c) 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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(d) Special flight permits may be issued in

accordance with sections 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 accomplished.

(e) The actions required by this AD shall

be done in accordance with the following

Textron Lycoming SB’s:

Document No. Pages Revision Date

LT101–72–50–0144 ............................................................................................................................................... 1–9 Original Jan. 15,

1993.

Total Pages: 9.

LT101–72–50–0145 ............................................................................................................................................... 1–3 Original Nov. 27,

1991.

Total Pages: 3.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from AlliedSignal Engines, 111 South 34th

Street, Phoenix, AZ 85072; telephone (602)

365–2493, fax (602) 365–2210. Copies may be

inspected at the FAA, New England Region,

Office of the Assistant Chief Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street NW., suite 700,

Washington, DC.

(f) This amendment becomes effective on

August 12, 1996.

Issued in Burlington, Massachusetts, on

May 29, 1996.

Robert E. Guyotte,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 96–14868 Filed 6–12–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 93–ANE–07; Amendment 39–

9649; AD 96–12–07]

RIN 2120–AA64

Airworthiness Directives; Teledyne

Continental Motors (formerly Bendix)

S–20, S–1200, D–2000, and D–3000

Series Magnetos

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Teledyne Continental

Motors (TCM) (formerly Bendix) S–20,

S–1200, D–2000, and D–3000 series

magnetos equipped with impulse

couplings, that currently requires

inspections for wear, and replacement,

if necessary, of the impulse coupling

assemblies. This amendment requires

replacement, if necessary, of worn

riveted impulse coupling assemblies

with serviceable riveted impulse

couplings or snap ring impulse

couplings. This amendment is prompted

by the availability of an improved

design for the impulse coupling

assembly. The actions specified by this

AD are intended to prevent magneto

failure and subsequent engine failure.

DATES: Effective July 18, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 18,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Teledyne Continental Motors, P.O.

Box 90, Mobile, AL 36601; telephone

(334) 438–3411. This information may

be examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA 01803–5299; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jerry

Robinette, Aerospace Engineer, Atlanta

Certification Office, FAA, Small

Airplane Directorate, Campus Building,

1701 Columbia Avenue, Suite 2–160,

College Park, GA, 30337–2748;

telephone (404) 305–7371, fax (404)

305–7348.

SUPPLEMENTARY INFORMATION: On

January 4, 1983, the Federal Aviation

Administration (FAA) issued

airworthiness directive (AD) 78–09–07

R3, Amendment 39–4538 (48 FR 1482,

January 13, 1983), to require inspections

for wear, and replacement, if necessary,

of the impulse coupling assemblies on

certain Teledyne Continental Motors

(TCM) (formerly Bendix) S–20, S–1200,

D–2000, and D–3000 series magnetos

equipped with impulse couplings. That

action was prompted by reports of

numerous magneto failures. That

condition, if not corrected, could result

in magneto failure and subsequent

engine failure.

A proposal to amend part 39 of the

Federal Aviation Regulations was

published as a notice of proposed

rulemaking (NPRM) in the Federal

Register on September 21, 1993 (58 FR

48987). That NPRM would have

retained the repetitive inspections for

wear required by the current AD, but

would have also required replacement,

if necessary, of the riveted impulse

coupling assembly with newly

designed, improved, snap ring impulse

coupling assemblies. In addition, the

proposed AD would have required

marking the magneto data plate to

indicate installation of a snap ring

impulse coupling assembly. Installation

of snap ring impulse coupling

assemblies would have constituted

terminating action to the inspection

requirements of this AD. That NPRM

was prompted by the manufacturer

redesigning the impulse coupling

assembly to include snap ring fastening

technology which strengthens the cam

axle and reduces wear. The snap ring

impulse coupling assembly was

believed not to have the failure mode of

the previous design.

Since the issuance of that NPRM, the

FAA received reports of snap ring

impulse coupling assemblies being

worn beyond limits. The FAA

determined that it was necessary to

reopen the proposal for public

comment, so a Supplemental NPRM was

published in the Federal Register on

November 17, 1994 (59 FR 59391). That

Supplemental NPRM proposed to retain

the 500 hour repetitive inspections for

wear required by the current AD, but

would require these inspections for