2706 Federal Register / Vol. 61, No. 19 / Monday, January 29, 1996 / Rules and Regulations

specified in this AD can occur if the flap

settings are increased when conditions

for ICTS are present.

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 as proposed.

There are approximately 282 Model

240 series airplanes, including Model

T–29 (military) airplanes; Model 340

and 440 series airplanes; Model C–131

(military) airplanes, and those models

modified for turbo-propeller power; of

the affected design in the worldwide

fleet. The FAA estimates that 197

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 1 work hour per airplane

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the AD on U.S. operators

is estimated to be $11,820, or $60 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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, 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 the following new airworthiness

directive:

96–03–04 General Dynamics (Convair):

Amendment 39–9501. Docket 95–NM–

19–AD.

Applicability: All Model 240 series

airplanes, including Model T–29 (military)

airplanes; Model 340 and 440 series

airplanes; and Model C–131 (military)

airplanes; including those models modified

for turbo-propeller power (commonly

referred to as Model 580, 600, and 640 series

airplanes); certificated in any category.

Compliance: Required as indicated, unless

accomplished previously.

To ensure that the flight crew is advised of

the potential hazard associated with

increasing the flap settings when ice

contaminated tailplane stall (ICTS)

conditions are present, and the procedures

necessary to address it, accomplish the

following:

(a) Within 30 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) to include the following procedures,

which will limit the flap settings during

certain icing conditions and air temperatures.

This may be accomplished by inserting a

copy of this AD in the AFM.

‘‘FLAP LIMITATION IN ICING CONDITIONS

Flap selection is limited to a maximum of

30 degrees after icing conditions have been

encountered; or when icing conditions are

anticipated during approach and landing; or

when the outside air temperature is +5

degrees Celsius or below and any visible

moisture is present.’’

(b) 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, Los

Angeles Aircraft Certification Office (ACO),

FAA, Transport Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles ACO.

Note: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(c) 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 airplane to

a location where the requirements of this AD

can be accomplished.

(d) This amendment becomes effective on

February 28, 1996.

Issued in Renton, Washington, on January

23, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–1517 Filed 1–26–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–88–AD; Amendment 39–

9500; AD 95–24–10]

Airworthiness Directives; Michelin

Aircraft Tire Corporation Part Number

028–520–1 (22x5.75–12/10PR) Tires

Installed on the Main Landing Gear of

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting Airworthiness Directive (AD)

95–24–10, which was sent previously to

all known U.S. owners and operators of

airplanes with a Michelin Aircraft Tire

Corporation part number (P/N) 028–

520–1 (22x5.75–12/10PR) tire installed

on the main landing gear. This AD

requires replacing any of the affected

tires with an FAA-approved tire. Two

reports of failure (rupture) of the main

landing gear tire during landing

operations on Cessna Citation VII

airplanes prompted priority letter AD

95–24–10. The actions specified by this

AD are intended to prevent loss of

control of the airplane during landing

operations because of failure of a P/N

028–520–1 (22x5.75–12/10PR) tire.

DATES: Effective February 21, 1996, to

all persons except those to whom it was

made immediately effective by priority

letter AD 95–24–10, issued November

21, 1995, which contained the

requirements of this amendment.

Comments for inclusion in the Rules

Docket must be received on or before

April 30, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket 95–CE–88–AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Information that relates to this AD

may be examined at the Rules Docket at

the address above, or at the Office of the

Federal Register, 800 North Capitol

Street NW., 7th Floor, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ms.

Denise Bosonetto, Aerospace Engineer,
Federal Register / Vol. 61, No. 19 / Monday, January 29, 1996 / Rules and Regulations 2707

FAA, Atlanta Aircraft Certification

Office, Campus Building, 1701

Columbia Avenue, suite 2–160, College

Park, Georgia 30337–2748; telephone

(404) 305–7379; facsimile (404) 305–

7348.

SUPPLEMENTARY INFORMATION: The FAA

has received two reports of failure

(rupture) of the main landing gear tire

during landing operations on Cessna

Citation VII airplanes. Analysis of these

incidents revealed the following:

—The tires, P/N 028–520–1 (22x5.75–

12/10PR), were manufactured by the

Michelin Aircraft Tire Corporation

(FAA Manufacturing Approval: TSOC62c);

—The cause of the failure is attributed

to separations that developed in the

crown region of the tire with the

rubber component below the tread

reinforcing plies;

—The separations are attributed to low

adhesion caused by a misplaced

rubber compound; and

—A check of the company records

reveals that a total of 137 tires were

manufactured in this lot and the

remaining 135 tires could contain this

same low adhesion problem.

The P/N 028–520–1 (22x5.75–12/

10PR) tires are predominantly installed

on Cessna Model 650 (Citation III, VI,

and VII) airplanes; however, they could

be installed on other airplanes.

After reviewing and examining all

available information to the incidents

received above, the FAA has determined

that (1) the remaining 135 tires

manufactured in the lot that could have

a possible low adhesion problem should

be removed from service; and (2) AD

action should be taken to prevent loss

of control of the airplane during landing

operations because of failure of a

Michelin Aircraft Tire Corporation P/N

028–520–1 (22x5.75–12/10PR) tire.

Since an unsafe condition has been

identified that is likely to exist or

develop in other airplanes that are

equipped with at least one Michelin

Aircraft Tire Corporation P/N 028–520–

1 (22x5.75–12/10PR) tire (serial

numbers as referenced in the actual AD)

installed on the main landing gear, the

FAA issued priority letter AD 95–24–10

to require replacing any of the affected

tires with an FAA-approved tire.

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 by individual

letters issued on November 21, 1995, to

all known U.S. operators of airplanes

with a Michelin Aircraft Tire

Corporation P/N 028–520–1 (22x5.75–

12/10PR) tires installed on the main

landing gear. These conditions still

exist, and the AD is hereby published in

the Federal Register as an amendment

to section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it

effective as to all persons.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting immediate flight safety and,

thus, was not preceded by notice and

opportunity to comment, comments are

invited on this rule. Interested persons

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

above. 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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 95–CE–88–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

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, 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

95–24–10 Michelin Aircraft Corporation:

Amendment 39–9500; Docket No. 95–

CE–88–AD.

Applicability: Part number (P/N) 028–520–

1 (22x5.75–12/10PR) tires with the following

serial numbers that are installed on the main

landing gear of, but not limited to, Cessna

Model 650 (Citation III, VI, and VII) airplanes

that are certificated in any category:

Serial Nos.

4279N00339 4279N00340 4279N00341

4279N00342 4279N00343 4279N00597

4279N00598 4279N00599 4279N00600

4279N00601 4280N00075 4280N00199

4280N00200 4280N00201 4280N00203

4280N00204 4280N00205 4280N00206

4280N00360 4280N00361 4282N00352

4283N00099 4283N00100 4283N00101

4283N00102 4283N00200 4283N00201

4283N00202 4283N00453 4283N00454

4283N00455 4283N00456 4284N00612

4284N00613 4284N00614 4284N00615

4284N00616 4285N00100 4285N00101

4285N00102 4285N00103 4285N00104

4285N00105 4285N00106 4285N00107

4285N00108 4285N00347 4285N00348

4285N00349 4285N00353 4285N00354

4285N00355 4285N00356 4285N00608

4285N00609 4286N00103 4286N00104
2708 Federal Register / Vol. 61, No. 19 / Monday, January 29, 1996 / Rules and Regulations

4286N00105 4286N00106 4286N00442

4286N00443 4286N00444 4286N00445

4286N00446 4286N00447 4286N00448

4286N00449 4286N00450 4286N00600

4286N00601 4286N00602 4286N00603

4286N00604 4286N00605 4286N00606

4286N00608 4286N00609 4287N00088

4287N00089 4287N00090 4287N00091

4287N00092 4287N00093 4287N00094

4287N00095 4287N00096 4287N00097

4287N00357 4287N00358 4287N00359

4287N00360 4287N00361 4287N00362

4287N00363 4287N00364 4288N00118

4288N00119 4288N00120 4288N00121

4288N00302 4288N00303 4288N00304

4288N00305 4288N00306 4288N00307

4290N00111 4290N00113 4290N00114

4290N00115 4290N00116 4290N00117

4290N00355 4290N00356 4290N00606

4290N00607 4290N00608 4290N00609

4290N00610 4290N00611 4290N00612

4291N00082 4291N00083 4291N00084

4291N00085 4291N00086 4291N00087

4291N00088 4291N00089 4291N00091

4291N00273 4291N00274 4291N00275

4291N00276 4291N00277 4291N00278

4291N00620 4291N00621

Note 1: This AD applies to each tire

identified in the preceding applicability

provision that is installed on an airplane,

regardless of whether it has been modified,

altered, or repaired in the area subject to the

requirements of this AD. For airplanes 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 (c)

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: Required prior to further

flight after the effective date of this AD (see

NOTE 2), except to those operators receiving

this action by priority letter issued November

21, 1995, which made these actions effective

immediately upon receipt.

To prevent loss of control of the airplane

during landing operations because of P/N

028–520–1 (22x5.75–12/10PR) tire failure,

accomplish the following:

(a) Replace any of the P/N 028–520–1

(22x5.75–12/10PR) tires identified in the

Applicability section of this AD with an

FAA-approved tire.

(b) 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 airplane to

a location where the requirements of this AD

can be accomplished.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Atlanta Aircraft

Certification Office (ACO), Campus Building,

1701 Columbia Avenue, suite 2–160, College

Park, Georgia 30337–2748. The request shall

be forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(d) Information that applies to this AD may

be examined at the FAA, Central Region,

Office of the Assistant Chief Counsel, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

(e) This amendment (39–9500) becomes

effective on February 21, 1996, to all persons

except those persons to whom it was made

immediately effective by priority letter AD

95–24–10, issued November 21, 1995, which

contained the requirements of this

amendment.

Issued in Kansas City, Missouri, on January

23, 1996.

John R. Colomy,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–1573 Filed 1–26–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 92–ANE–32; Amendment 39–

9490; AD 94–05–05 R1]

Airworthiness Directives; Teledyne

Continental Motors Models C75, C85,

C90, C125, C145, O–200, O–300, and

GO–300 Series and Rolls-Royce, plc

C90, O–200 and O–300 Series

Reciprocating Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to Teledyne Continental

Motors (TCM) Models C75, C85, C90,

C125, C145, O–200, O–300, and GO–300

series reciprocating engines, that

currently requires inspection of the

cylinder rocker shaft bosses for cracks,

and inspection of the cylinder rocker

shaft for looseness and replacement, if

necessary, with a serviceable part. This

amendment clarifies that the inspection

must be accomplished at the next

cylinder removal from the engine or

engine overhaul, whichever occurs first,

and adds certain Rolls-Royce, plc

engines to the AD’s applicability. This

amendment is prompted by the need to

clarify when the inspection must be

performed. The actions specified by this

AD are intended to prevent engine

power loss and engine failure.

DATES: Effective February 13, 1996.

Comments for inclusion in the Rules

Docket must be received on or before

March 29, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

92–ANE–32, 12 New England Executive

Park, Burlington, MA 01803–5299.

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

February 18, 1994, the Federal Aviation

Administration (FAA) issued AD 94–

05–05, Amendment 39–8843 (59 FR

10057, March 3, 1994), applicable to

Teledyne Continental Motors (TCM)

Models C75, C85, C90, C125, C145, O–

200, O–300, and GO–300 series

reciprocating engines, to require

inspection of the cylinder rocker shaft

bosses for cracks, and inspection of the

cylinder rocker shaft for looseness and

replacement, if necessary, with a

serviceable part. That action was

prompted by reports of cracked or

improperly repaired cylinder rocker

shaft bosses. That condition, if not

corrected, could result in engine power

loss and engine failure.

Since the issuance of that AD, the

FAA has received reports indicating

confusion among operators as to when

the inspection must be performed. The

FAA has learned that an operator

removed a cylinder from an affected

engine but did not do the inspection

specified by AD 94–05–05, claiming that

the inspection need only be

accomplished when a cylinder is

removed for an overhaul, but not for a

repair. That is not the intent of the

current wording of the AD. The FAA

has therefore revised the compliance

requirement in this AD to state that the

inspection must be performed at the

next cylinder removal from the engine,

or engine overhaul, whichever occurs

first.

In addition, the Civil Aviation

Authorities of the United Kingdom and

Denmark notified the FAA that the AD

should apply also to Rolls-Royce, plc

C90, O–200 and O–300 series

reciprocating engines, as they were

produced by Rolls-Royce, plc under a

licensing agreement with TCM. Some

time after production ceased, continuing

airworthiness responsibility reverted to

TCM. The FAA has therefore added

these Rolls-Royce, plc engines to the

AD’s applicability.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD revises AD 94–05–

05 to clarify that the inspection must be