Federal Register / Vol. 67, No. 90 / Thursday, May 9, 2002 / Rules and Regulations 31113

Document No. Pages Revision Date

3–12 ......... Original ............. July 22, 1999.

Total pages 12

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 Honeywell International, Inc., Attn:

Data Distribution, M/S 64–3/2101–201, P.O.

Box 29003, Phoenix, AZ 85038–9003;

telephone: (602) 365–2493; fax: (602) 365–

5577. Copies may be inspected, by

appointment, at the FAA, New England

Region, Office of the Regional 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.

Effective Date

(h) This amendment becomes effective on

June 13, 2002.

Issued in Burlington, Massachusetts, on

April 29, 2002.

Diane S. Romanosky,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 02–11216 Filed 5–8–02; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–08–AD; Amendment

39–12741; AD 2002–09–08]

RIN 2120–AA64

Airworthiness Directives; Hartzell

Propeller, Inc. Compact Series

Propellers

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

that is applicable to Hartzell models

( )HC-( )( )Y( )-( )( )( ) compact series,

constant speed or feathering propellers

with Hartzell manufactured ‘‘Y’’ shank

blades. That AD currently requires

initial and repetitive blade inspections;

rework of all ‘‘Y’’ shank blades

including cold rolling of the blade

shank retention radius; blade

replacement and modification of pitch

change mechanisms for certain

propeller models; and changing the

airplane operating limitations with

specific models of propellers installed.

This amendment requires initial blade

inspections, with no repetitive

inspections; rework of all ‘‘Y’’ shank

blades including cold rolling of the

blade shank retention radius, blade

replacement and modification of pitch

change mechanisms for certain

propeller models; and changing the

airplane operating limitations with

specific models of propellers installed.

This amendment is prompted by FAA

reviews of propeller service histories

since the issuance of AD 77–12–06R2.

The actions specified by this AD are

intended to prevent failure of the

propeller blade from fatigue cracks in

the blade shank radius, which can result

in damage to the airplane and loss of

airplane control.

DATES: Effective date June 13, 2002. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of June 13, 2002.

ADDRESSES: The service information

referenced in this AD may be obtained

from Hartzell Propeller Inc., One

Propeller Place, Piqua, Ohio 45356–

2634, telephone (937) 778–4200; fax

(937) 778–4391. This information 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; or at

the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Tomaso DiPaolo, Aerospace Engineer,

Chicago Aircraft Certification Office,

FAA, Small Airplane Directorate, 2300

E. Devon Ave., Des Plaines, IL 60018;

telephone (847) 294–7031; fax (847)

294–7834.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 77–12–06R2,

Amendment 39–3097 (42 FR 63165,

December 15, 1977), which is applicable

to Hartzell models ( )HC-( )( )Y( )-

( )( )( ) compact series, constant speed

or feathering propellers with Hartzell

manufactured ‘‘Y’’ shank blades was

published in the Federal Register on

November 20, 2001 (66 FR 58077). That

action proposed to require initial blade

inspections, with no repetitive

inspections; rework of all ‘‘Y’’ shank

blades including cold rolling of the

blade shank retention radius, blade

replacement and modification of pitch

change mechanisms for certain

propeller models; and changing the

airplane operating limitations with

specific models of propellers installed.

Comments

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.

Economic Analysis

At the time the existing AD was

issued, there were about 55,000

propellers of the affected design in the

worldwide fleet. The FAA estimated

that there were 35,750 propellers

installed on airplanes of U.S. registry.

The FAA expects that all of the affected

propellers should have already been

inspected to comply with the existing

AD’s requirements to inspect, and

rework or replace the blades. If these

actions have not already been done,

then the total cost to comply with this

AD is estimated to be $700 per

propeller.

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.

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 the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 by contacting the

Rules Docket at the location provided

under the caption ADDRESSES.

31114 Federal Register / Vol. 67, No. 90 / Thursday, May 9, 2002 / Rules and Regulations

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 39–2922 (42 FR

31152, June 20, 1977), Amendment 39–

3018 (42 FR 42191, August 22, 1977),

and Amendment 39–3097 (42 FR 63165,

December 15, 1977) and by adding a

new airworthiness directive,

Amendment 39–12741, to read as

follows:

2002–09–08 Hartzell Propellers, Inc.:

Amendment 39–12741. Docket No.

2000–NE–08–AD. Supersedes AD 77–

12–06R2, Amendment 39–3097.

Applicability

This airworthiness directive (AD) is

applicable to Hartzell Propellers, Inc. Models

( )HC-( )( )Y( )-( )( )( ) compact series constant

speed or feathering propellers with Hartzell

manufactured ‘‘Y’’ shank blades. These

propellers are used on but not limited to the

following airplanes:

Aermacchi S.pA. (formerly Siai-Marchetti) S–

208

Aero Commander 200B and 200D

Aerostar 600

Beech 24, 35, 36, 45, 55, 56TC, 58, 60, and

95

Bellanca 14 and 17 series

Cessna 182 and 188

Embraer EMB–200A

Maule M5

Mooney M20 and M22

Pilatus Britten Norman, or Britten Norman

BN–2, BN–2A, and BN–2A–6

Piper PA–23, PA–24, PA–28, PA–30, PA–31,

PA–32, PA–34, PA–36, and PA–39

Pitts S–1T and S–2A

Rockwell 112, 114, 200, 500, and 685 series

Note 1: This AD applies to each propeller

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

propellers 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 (e) 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 as

indicated, unless already done. Propeller

maintenance records showing compliance

with AD 77–12–06R2 is an indication that

compliance was previously done.

To prevent failure of the propeller blade

from fatigue cracks in the blade shank radius,

which can result in damage to the airplane

and loss of airplane control, do the following:

(a) Propellers are considered in compliance

with the one-time inspection and rework

requirements only, of this AD if:

(1) All blades are serial number D47534

and above, or

(2) All blades are identified with the letters

‘‘PR’’ or ‘‘R’’ or ‘‘SP–P’’ ink-stamped on the

camber side, or the letters ‘‘SP’’, ‘‘RD’’ or

‘‘SP–P’’ metal-stamped on the blade butt.

Models ( )HC-( )( )Y( ) Compact Series ‘‘Y’’

Shank Propellers

(b) If propellers models ( )HC-( )( )Y( ) have

not been inspected and reworked in

accordance with AD 77–12–06R2, then before

further flight, do a one-time action to remove,

inspect, rework or replace blades if necessary

in accordance with Hartzell Service Bulletin

(SB) No.118A, dated February 15, 1977.

Note 2: One requirement in SB No. 118A

is the cold rolling of the propeller blade

shank. This is a critical requirement in the

prevention of cracks in the blade. Propeller

repair shops must obtain and maintain

proper certification to perform the cold

rolling procedure. For a current list of

propeller overhaul facilities approved to

perform the blade shank cold rolling

procedure, contact Hartzell Product Support,

telephone: (937) 778–4200. Not all propeller

repair facilities have the equipment to

properly perform a cold roll of the blade

shanks. In addition, any rework in the blade

shank area will also necessitate the cold

rolling of the blade shank area, apart from the

one-time cold rolling requirement of this AD.

Instrument Panel Modifications

(c) If airplanes with propeller models

( )HC–C2YK-( )( )( ) / ( )( )7666A-( ), installed

on (undampered) 200 horsepower Lycoming

IO–360 series engines, have not been

modified in accordance with AD 77–12–

06R2, then modify the airplane instrument

panel according to the following

subparagraphs before further flight. Airplanes

include, but are not limited to, Mooney M20E

and M20F (normal category), Piper PA–28R–

200 (normal category), and Pitts S–1T and S–

2A (acrobatic category).

(1) For normal category airplanes, before

further flight, remove the present vibration

placard and affix a new placard near the

engine tachometer that states:

‘‘Avoid continuous operation:

Between 2000 and 2350 rpm.’’

(2) For utility and acrobatic category

airplanes, before further flight, remove the

present vibration placard and affix a new

placard near the engine tachometer that

states:

‘‘Avoid continuous operation:

Between 2000 and 2350 rpm.

Above 2600 rpm in acrobatic flight.’’

(3) For normal category airplanes, re-mark

the engine tachometer face or bezel with a

red arc for the restricted engine speed range,

between 2000 and 2350 rpm.

(4) For acrobatic and utility airplanes, remark the engine tachometer face or bezel

with a red arc for each restricted engine

speed range, i.e., between 2000 and 2350 rpm

and between 2600 and 2700 rpm (red line).

Models ( )HC–C2YK-( )( )( ) / ( )( )8475( )-

( ) or ( )( )8477( )-( ) Propellers

(d) If propeller models ( )HC–C2YK-( )( )

( ) / ( )( )8475( )-( ) or ( )( )8477( )-( ) have

not been inspected and reworked in

accordance with AD 74–15–02, then do the

following maintenance before further flight.

(1) Remove propeller from airplane.

(2) Modify pitch change mechanism, and

replace blades with equivalent model blades

prefixed with letter ‘‘F’’ in accordance with

Hartzell Service Letter No. 69, dated

November 30, 1971 and Hartzell SB No.

101D, dated December 19, 1974.

(3) Inspect and repair or replace, if

necessary, in accordance with Hartzell SB

No. 118A, dated February 15, 1977.

Alternative Methods of Compliance

(e) Alternative methods of compliance to

Hartzell Service Bulletin No. 118A are

Hartzell Service Bulletin No.’s 118B, 118C,

118D, and Hartzell Manual 133C. Alternative

method of compliance to Hartzell SB No.

101D is Hartzell Manual 133C. No

adjustment in the compliance time is

allowed. Any requests for an alternative

method of compliance that provides an

acceptable level of safety may be used if

approved by the Manager, Chicago Aircraft

Certification Office (ACO). Operators must

submit their request through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Chicago ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Manager,

Chicago ACO.

Special Flight Permits

(f) 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 airplane to a

location where the requirements of this AD

can be done.

Documents That Have Been Incorporated By

Reference

(g) The inspections must be done in

accordance with the following Hartzell

Propeller, Inc. service bulletins (SB’s) and

service letter (SL):

Federal Register / Vol. 67, No. 90 / Thursday, May 9, 2002 / Rules and Regulations 31115

Document No. Pages Revision Date

SB No. 101D Total pages: 2. ............................................................................................. All ............ D ....................... December 19, 1974.

SB No. 118A Total pages: 16 ............................................................................................ All ............ A ....................... February 15, 1977.

SL No. 69 Total pages: 2 ................................................................................................... All ............ 1 ....................... November 30, 1971.

These incorporations by reference were

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 Hartzell Propeller, Inc., One Propeller

Place, Piqua, Ohio 45356–2634; telephone

(937) 778–4200; fax (937) 778–4391. Copies

may be inspected, by appointment, at the

FAA, New England Region, Office of the

Regional 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.

Effective Date

(h) This amendment becomes effective on

June 13, 2002.

Issued in Burlington, Massachusetts, on

April 24, 2002.

Marc J. Bouthillier,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 02–11251 Filed 5–8–02; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–CE–13–AD; Amendment

39–12745; AD 2002–09–12]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Beech Model C90

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Raytheon Aircraft

Company (Raytheon) Beech Model C90

airplanes. This AD requires you to

inspect the left-hand (LH) and righthand (RH) nacelle and spar assembly for

the existence of rivets, and requires you

to install rivets if they do not exist or

are the wrong size or type. This AD is

the result of Raytheon identifying

several instances where rivets were

either missing or were the wrong size or

type on these airplanes. The actions

specified by this AD are intended to

correct the installation of rivets in the

LH and RH nacelle and spar assembly.

These rivets must be present and have

the correct dimension in order to

prevent reduced structural integrity,

which could result in structural failure

and possible loss of control of the

airplane.

DATES: This AD becomes effective on

June 21, 2002.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of June 21, 2002.

ADDRESSES: You may get the service

information referenced in this AD from

Raytheon Aircraft Company, P.O. Box

85, Wichita, Kansas 67201–0085;

telephone: (800) 429–5372 or (316) 676–

3140. You may view this information at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 2001–CE–13–AD, 901

Locust, Room 506, Kansas City,

Missouri 64106; or at the Office of the

Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Steve Potter, Aerospace Engineer, FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone: (316) 946–4124; facsimile:

(316) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

Raytheon has identified several

instances of rivets not being installed

and/or the wrong size or type installed

during the manufacturing process on the

nacelles and spar assembly of the Model

C90A airplanes. This conclusion is the

result of a quality control problem.

At least 20 airplanes have been found

with this condition. The number and

location of the missing rivets and

incorrectly installed rivets may vary

from airplane to airplane.

What Is the Potential Impact if FAA

Took No Action?

This condition, if not detected and

corrected, could result in reduced

structural integrity. This could lead to

critical structural failure with

consequent loss of airplane control.

Has FAA Taken Any Action to This

Point?

We issued a proposal to amend part

39 of the Federal Aviation Regulations

(14 CFR part 39) to include an AD that

would apply to certain Raytheon Beech

Model C90 airplanes. This proposal was

published in the Federal Register as a

notice of proposed rulemaking (NPRM)

on November 26, 2001 (66 FR 58983).

The NPRM proposed to require you to

inspect the left-hand (LH) and righthand (RH) nacelle and spar assembly for

the existence of rivets and would

require you to install rivets if they do

not exist or are the wrong size or type.

Was the Public Invited To Comment?

The FAA encouraged interested

persons to participate in the making of

this amendment. We did not receive any

comments on the proposed rule or on

our determination of the cost to the

public.

FAA’s Determination

What Is FAA’s Final Determination on

This Issue?

After careful review of all available

information related to the subject

presented above, we have determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections. We have determined that

these minor corrections:

—Provide the intent that was proposed

in the NPRM for correcting the unsafe

condition; and

—Do not add any additional burden

upon the public than was already

proposed in the NPRM.

Cost Impact

How Many Airplanes Does This AD

Impact?

We estimate that this AD affects 381

airplanes in the U.S. registry.

What Is the Cost Impact of This AD on

Owners/Operators of the Affected

Airplanes?

We estimate the following costs to

accomplish the inspection: