Federal Register / Vol. 62, No. 41 / Monday, March 3, 1997 / Rules and Regulations 9361

(d) Accomplishment of the actions

specified in paragraphs (d)(1) and (d)(2) of

this AD in accordance with Boeing Service

Bulletin 727–54A0010, Revision 4, dated

January 30, 1997, constitutes terminating

action for the requirements of paragraphs (a)

and (b) of this AD.

(1) Perform a HFEC inspection to detect

cracks of the fastener holes in the forward

support fitting of the number 1 and number

3 engines, and, if possible, modify the

fastener holes, in accordance with Part II—

Fastener Hole Modification of the

Accomplishment Instructions of the service

bulletin.

(i) If the modification (i.e., a fastener

installed in a hole with no cracks) was

accomplished at all eight holes, no further

action is required by paragraph (d)(1) of this

AD.

(ii) If the modification was not

accomplished at all eight holes because of the

continued detection of cracking, prior to

further flight, repair the forward support

fitting in accordance with a method approved

by the Manager, Seattle ACO.

(2) Prior to the accumulation of 3,000 flight

cycles or 24 months, whichever occurs first,

following accomplishment of paragraph

(d)(1) of this AD, perform a HFEC inspection

to detect corrosion or cracks of the modified

forward support fitting of the number 1 and

number 3 engines, in accordance with Part

III—Post-Modification Inspections of the

Accomplishment Instructions of the service

bulletin.

(i) If no crack or corrosion is detected, prior

to further flight, install the fasteners wet with

a sealant in accordance with the service

bulletin. Repeat the HFEC inspection

required by paragraph (d)(2) of this AD

thereafter at intervals not to exceed 3,000

flight cycles or 24 months, whichever occurs

first.

(ii) If any crack or corrosion is detected,

prior to further flight, repair the forward

support fitting in accordance with a method

approved by the Manager, Seattle ACO.

(e) 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, Seattle

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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(f) 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.

(g) The inspections and modifications shall

be done in accordance with Boeing Service

Bulletin 727–54A0010, Revision 4, dated

January 30, 1997. 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 Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle, Washington

98124–2207. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite700, Washington,

DC.

(h) This amendment becomes effective on

March 18, 1997.

Issued in Renton, Washington, on February

21, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–4947 Filed 2–28–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–SW–17–AD; Amendment

39–9950; AD 97–05–06]

RIN 2120–AA64

Airworthiness Directives; Schweizer

Aircraft Corporation and Hughes

Helicopters, Inc. Model 269A, 269A–1,

269B, and TH–55A Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Schweizer Aircraft

Corporation and Hughes Helicopters,

Inc. Model 269A, 269A–1, 269A–2, and

269B helicopters, that currently requires

initial and repetitive inspections of the

main rotor thrust bearing (bearing) for

bearing rotational roughness, corrosion,

inadequate lubrication, physical

damage, or excessive zinc chromate

paste or moisture. This amendment

requires the same initial and repetitive

inspections required by the existing AD,

but would extend the retirement life for

certain bearings, and would remove the

Model 269A–2 helicopter from, and add

the Model TH–55A helicopters to the

applicability of this AD. This

amendment is prompted by an FAA

analysis of service information issued

by the manufacturer that extends the

retirement life for certain bearings. The

actions specified by this AD are

intended to prevent failure of the

bearing, loss of the main rotor, and

subsequent loss of control of the

helicopter.

DATES: Effective April 7, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 7,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Schweizer Aircraft Corporation,

P.O. Box 147, Elmira, New York 14902.

This information may be examined at

the FAA, Office of the Assistant Chief

Counsel, Room 663, 2601 Meacham

Blvd., Fort Worth, Texas; or at the Office

of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Ray O’Neill, Aerospace Engineer,

Airframe and Propulsion Branch, New

York Aircraft Certification Office, FAA,

New England Region, 10 5th Street,

Valley Stream, New York 11581,

telephone (516) 256–7505, fax (516)

568–2716.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 68–21–05,

Amendment 39–672 (33 FR 15543,

October 19, 1968), which is applicable

to Model 269A helicopters, serial

numbers (S/N) 0011 through 0979

(except Model TH–55A helicopters),

Model 269A–1 helicopters, S/N 0001

through 0041, Model 269A–2 helicopter,

S/N 0001, and Model 269B, S/N 0001

through 0370, as revised by Amendment

39–1055 (35 FR 12532, August 6, 1970),

was published in the Federal Register

on June 17, 1996 (61 FR 30548). That

action proposed to require the same

initial and repetitive inspections

required by the existing AD (inspections

of the main rotor thrust bearing

(bearing) for bearing rotational

roughness, corrosion, inadequate

lubrication, physical damage, or

excessive zinc chromate paste or

moisture), but would extend the

retirement life for certain bearings, and

would remove the Model 269A–2

helicopter from, and add the Model TH–

55A helicopters to the applicability of

this AD.

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, except for editorial

changes and changes to paragraph (a)

that more specifically state the actions

that are required for those bearings

having less than 300 hours time-inservice. The FAA has determined that

these changes will neither increase the

economic burden on any operator nor

expand the scope of the AD.

The FAA estimates that 500

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 8 work hours per

helicopter to accomplish the required
9362 Federal Register / Vol. 62, No. 41 / Monday, March 3, 1997 / Rules and Regulations

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $1,890 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $1,185,000.

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. App. 106(g), 40113,

and 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Amendment 39–1055 (35 FR

12532, August 6, 1970), and

Amendment 39–672 (33 FR 15543,

October 19, 1968) and by adding a new

airworthiness directive (AD),

Amendment 39–9950, to read as

follows:

AD 97–05–06 SCHWEIZER AIRCRAFT

CORPORATION AND HUGHES

HELICOPTERS, INC.: Amendment 39–

9950. Docket No. 94–SW–17–AD.

Supersedes AD 68–21–05, Amendment

39–1055 and Amendment 39–672.

Applicability: Model 269A helicopters,

serial numbers (S/N) 0011 through 1109,

Model 269A–1 helicopters, S/N 0001 through

0041, Model 269B, S/N 0001 through 0444,

and Model TH–55A, with main rotor thrust

bearing, part number (P/N) 269A5050–50,

–51, or –73, installed, certificated in any

category.

Note 1: This AD applies to each helicopter

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

helicopters 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 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 helicopter

from the applicability of this AD.

Compliance: Required within 25 hours

time-in-service (TIS) after the effective date

of this AD, unless accomplished previously.

To prevent failure of the main rotor thrust

bearing (bearing), loss of the main rotor, and

subsequent loss of control of the helicopter,

accomplish the following:

(a) From available helicopter records,

determine the TIS of the appropriate bearing,

part number (P/N) 269A5050–50, P/N

269A5050–51, or P/N 269A5050–73.

(1) If the TIS on the bearing, P/N

269A5050–50 or –51, equals or exceeds 300

hours TIS, replace the bearing with an

airworthy bearing before further flight.

(2) If the TIS on the bearing, P/N

269A5050–50 or –51, equals or exceeds 275

hours TIS, and is less than 300 hours TIS,

replace the bearing with an airworthy bearing

within the next 25 hours TIS.

(3) If the TIS on the bearing, P/N

269A5050–50 or –51, is less than 275 hours

TIS, replace the bearing with an airworthy

bearing on or before 300 hours TIS.

(b) Inspect bearing, P/N 269A5050–50 or

–51, for rotational roughness, corrosion,

inadequate lubrication, physical damage,

moisture or inadequate drainage due to

build-up of zinc chromate paste in

accordance with Step II, paragraph b of

Schweizer Service Notice (SSN) No. N–59,

dated October 9, 1968.

(1) If bearing rotational roughness,

corrosion, inadequate lubrication, physical

damage, moisture or inadequate drainage due

to build-up of zinc chromate paste is found,

replace the bearing with an airworthy

bearing.

(2) If no bearing rotational roughness,

corrosion, lack of lubrication, physical

damage, moisture or inadequate drainage due

to build-up of zinc chromate paste is found,

thereafter, inspect the bearing in accordance

with this paragraph upon attaining an

additional 150 hours TIS.

(3) For replacement bearings, inspect in

accordance with this paragraph upon

attaining 150 hours TIS, unless the bearing

reaches its 300 hour TIS retirement life limit

prior to this inspection.

(c) For bearing, P/N 269A5050–73:

(1) Inspect the bearing for corrosion, rust,

freedom of rotation, looseness, binding,

nicks, burrs, cracks and lubrication.

Thereafter, inspect the bearing at intervals

not to exceed 600 hours TIS.

(2) As necessary, repack the bearing cavity

in accordance with Schweizer Aircraft

Corporation CKP–C–41 ‘‘Installation

Instructions For 269 Series Helicopters, SA–

269K–057–1 Main Rotor Thrust Bearing Kit,’’

dated June 9, 1994.

(d) This AD establishes a retirement life of

300 hours TIS for bearings, P/Ns 269A5050–

50 and –51 and a retirement life of 3,000

hours TIS for bearing, P/N 2695050–73.

However, bearings, P/Ns 269A5050–50 and

–51, with at least 275 hours TIS but less than

300 hours TIS, need not be retired until or

before the accumulation of an additional 25

hours TIS.

(e) Inspect the thrust bearing nut (nut), P/

N 269A1306–5, for corrosion and physical

damage and determine whether the nut has

been modified in accordance with Step III of

SSN No. N–59, dated October 9, 1968.

(1) If corrosion or physical damage is

found, replace the nut with an airworthy nut

that has been modified in accordance with

Step III of SSN No. N–59, dated October 9,

1968.

(2) If the nut has not been modified,

modify the nut in accordance with Step III

of SSN No. N–59, dated October 9, 1968.

(f) Inspect the interior of the main rotor

mast (mast) for corrosion, physical damage,

foreign materials, moisture or inadequate

drainage due to a buildup of zinc chromate

paste and determine whether the mast has

been modified in accordance with Step II of

SSN No. N–59, dated October 9, 1968 to

install a drain hole.

(1) If corrosion or physical damage is

found, replace the mast with an airworthy

mast that has been modified in accordance

with Step III of SSN No. N–59, dated October

9, 1968.

(2) If the interior of the mast has foreign

materials, moisture or inadequate drainage

due to a buildup of zinc chromate paste,

clean the area with a suitable solvent in

accordance with Step II of SSN No. N–59,

dated October 9, 1968.

(3) If the mast has not been modified,

modify the mast in accordance with Step III

of SSN No. N–59, dated October 9, 1968.

(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, New York

Aircraft Certification Office. Operators shall

submit their requests through an FAA

Principal Maintenance Inspector, who may

concur or comment and then send it to the
Federal Register / Vol. 62, No. 41 / Monday, March 3, 1997 / Rules and Regulations 9363

Manager, New York Aircraft Certification

Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(i) The inspections, modifications, and

replacements shall be done in accordance

with Schweizer Service Notice No. N–59,

dated October 9, 1968 and Schweizer Aircraft

Corporation CKP–C–41 ‘‘Installation

Instructions For 269 Series Helicopters, SA–

269K–057–1 Main Rotor Thrust Bearing Kit,’’

dated June 9, 1994. 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 Schweizer Aircraft

Corporation, P.O. Box 147, Elmira, New York

14902. Copies may be inspected at the FAA,

Office of the Assistant Chief Counsel, Room

663, 2601 Meacham Blvd., Fort Worth, Texas;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(j) This amendment becomes effective on

April 7, 1997.

Issued in Fort Worth, Texas, on February

20, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–4951 Filed 2–28–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Docket No. 96–ACE–23]

Amendment to Class E Airspace, York,

NE

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This rule amend the Class E

airspace area at York Municipal Airport,

York, Nebraska. The effect of this rule

is to provide additional controlled

airspace for aircraft executing Standard

Instrument Approach Procedures (SIAP)

at the York Municipal Airport.

EFFECTIVE DATE: 0901 UTC March 27,

1997.

FOR FURTHER INFORMATION CONTACT:

Kathy Randolph, Air Traffic Division,

Operations Branch, ACE–530C, Federal

Aviation Administration, 601 East 12th

Street, Kansas City, Missouri 64106;

telephone: (816) 426–3408.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with a

request for comments in the Federal

Register on January 6, 1997 (62 FR 607).

The FAA uses the direct final

rulemaking procedure for a noncontroversial rule where the FAA

believes that there will be no adverse

public comment. This direct final rule

advised the public that no adverse

comments were anticipated, and that

unless a written adverse comment, or a

written notice of intent to submit such

an adverse comment, was received

within the comment period, the

regulation would become effective on

March 27, 1997. No adverse comments

were received, and thus this notice

confirms that this final rule will become

effective on that date.

Issued in Kansas City, MO, on February 13,

1997.

Herman J. Lyons, Jr.,

Manager, Air Traffic Division, Central Region.

[FR Doc. 97–5054 Filed 2–28–97; 8:45 am]

BILLING CODE 4910–13–M

14 CFR Part 71

[Airspace Docket No. 97–ASO–3]

Amendment to Class E Airspace;

Mayport NS Mayport, FL

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment modifies the

Class E4 airspace description at Mayport

NS Mayport, FL, to reflect the part time

status of the Class E4 airspace. The

control tower is not open continuously

at Mayport NAS. Therefore, a reference

to effective days and times in the

airspace description is necessary to

reflect the part time status of the

airspace. The effective days and times

will be continuously published in the

Airport/Facility Directory.

EFFECTIVE DATE: 0901 UTC, May 22,

1997.

FOR FURTHER INFORMATION CONTACT:

Benny L. McGlamery, Operations

Branch, Air Traffic Division, Federal

Aviation Administration, P.O. Box

20636, Atlanta, Georgia 30320;

telephone (404) 305–5570.

SUPPLEMENTARY INFORMATION:

History

The control tower at Mayport NAS,

FL, is not open continuously. The Class

D airspace description for Mayport NS

Mayport, FL, reflects the part time status

of the Class D airspace. Since the Class

E4 airspace is an extension to the Class

D airspace, the status of the class E4

airspace is the same as the Class D

airspace. Therefore, a reference to days

and times must be added to the Class E4

airspace description to reflect its status

as part time. The effective days and

times will be continuously published in

the Airport/Facility Directory. This

action will have a positive impact on

the users of the airspace in the vicinity

of Mayport NAS by accurately reflecting

the part time status of the airspace. This

rule will become effective on the date

specified in the DATES section. Since

this action makes a technical

amendment to the Class E4 airspace,

which has a positive impact on users of

the airspace in the vicinity of the

airport, notice and public procedure

under 5 U.S.C. 553(b) are unnecessary.

The Rule

This amendment to Part 71 of the

Federal Aviation Regulations (14 CFR

part 71) modifies the Class E4 airspace

description at Mayport NS Mayport, FL,

to reflect the part time status of the

Class E4 airspace. The effective days

and times will be continuously

published in the Airport/Facility

Directory.

The FAA has determined that this

regulation only involves an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. It, therefore, (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)

does not warrant preparation of a

regulatory evaluation as the anticipated

impact is so minimal. Since this is a

routine matter that will only affect air

traffic procedures and air navigation, it

is certified that this rule will not have

a significant economic impact on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

Federal Aviation Administration

amends 14 CFR Part 71 as follows:

PART 71—[AMENDED]

1. The authority citation for 14 CFR

Part 71 continues to read as follows:

Authority: 49 U.S.C. 106(g); 40103, 40113,

40120; EO 10854, 24 FR 9565, 3 CFR, 1959–

1963 Comp., p. 389; 14 CFR 11.69.

§ 71.1 [Amended]

2. The incorporation by reference in

14 CFR 71.1 of Federal Aviation