41262 Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations

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. 97–SW–19–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 that it 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.

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 to

read as follows:

97–16–02 Robinson Helicopter Company:

Amendment 39–10092. Docket No. 97–

SW–19–AD.

Applicability: Model R44 helicopters,

serial numbers 0001 through 0332,

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 (d) 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 as indicated, unless

accomplished previously.

To prevent failure of the sprag clutch to

lock in the driving direction, which would

result in loss of power to the main rotor

system and a subsequent forced landing; or

failure of the sprag clutch to unlock in the

overrunning direction, which, if combined

with engine failure, would result in an

inability to autorotate and a subsequent loss

of control of the helicopter, accomplish the

following:

(a) Within 25 hours time-in-service (TIS)

after the effective date of this AD, and

thereafter, at intervals not to exceed 100

hours TIS, inspect both up-limit switches,

part number (P/N) V3–1001, for proper

operation in accordance with the Compliance

Procedure in Robinson Helicopter Company

R44 Service Bulletin SB–21, dated April 18,

1997. If the motor runs when the springs are

depressed on one side, the switch on the

OPPOSITE side is not functioning properly.

(b) If the inspections required by paragraph

(a) of this AD indicate that either up-limit

switch does not function properly, replace

the up-limit switch with an airworthy uplimit switch in accordance with the

Compliance Procedure contained in

Robinson Helicopter Company R44 Service

Bulletin SB–21, dated April 18, 1997.

(c) Within 50 hours TIS after the effective

date of this AD, replace the clutch assembly,

P/N C018–1, with a clutch assembly, P/N

C018–2 or P/N C018–2A, in accordance with

the Compliance Procedure contained in

Robinson Helicopter Company R44 Service

Bulletin SB–23, dated May 30, 1997.

(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, Los

Angeles Aircraft Certification Office, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles 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 Los Angeles Aircraft

Certification Office.

(e) 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.

(f) The inspections and replacements, if

necessary, shall be done in accordance with

Robinson Helicopter Company R44 Service

Bulletin SB–21, dated April 18, 1997, and

Robinson Helicopter Company R–44 Service

Bulletin SB–23, dated May 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

Robinson Helicopter Company, 2901 Airport

Drive, Torrance, California 90505, telephone

(310) 539–0508, fax (310) 539–5198. Copies

may be inspected at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(g) This amendment becomes effective on

August 18, 1997.

Issued in Fort Worth, Texas, on July 22,

1997.

Mark R. Schilling,

Acting Manager, Rotercraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–20195 Filed 7–31–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–36; Amendment 39–

10091; AD 97–05–11 R1]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal

Inc. ALF502 and LF507 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to AlliedSignal Inc. ALF502

and LF507 series turbofan engines, that

currently requires initial and repetitive

inspections of the oil system chip

detectors and oil filter bypass valve, and

optional installation of an improved oil

filter bypass valve, to ensure the
Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations 41263

integrity of the reduction gear system

and overspeed protection system. This

amendment adds an initial inspection

threshold for the oil maintenance

requirements that was inadvertently

omitted from AD 97–05–11, and makes

editorial corrections. Paragraphs (b)

through (f) of AD 97–05–11 have been

rearranged in this AD to make these

corrections. This amendment is

prompted by the inadvertent omission

of the initial inspection threshold. The

actions specified by this AD are

intended to prevent No. 4 and 5 duplex

bearing failure, which can result in a

Stage 4 low pressure turbine (LPT) rotor

failure, an uncontained engine failure,

and damage to the aircraft.

DATES: Effective August 18, 1997.

The incorporation by reference of

certain publications listed in the

regulations was approved by the

Director of the Federal Register as of

April 16, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

September 30, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

96–ANE–36, 12 New England Executive

Park, Burlington, MA 01803–5299.

Comments may also be sent via the

Internet using the following address: ‘‘9-

ad-engineprop@faa.dot.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

AlliedSignal Aerospace, 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. This information may be

examined 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.

FOR FURTHER INFORMATION CONTACT:

Raymond Vakili, Aerospace Engineer,

Los Angeles Aircraft Certification

Office, FAA, Transport Airplane

Directorate, 3960 Paramount Blvd.,

Lakewood, CA 90712–4137; telephone

(562) 627–5262; fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: On July

17, 1987, the Federal Aviation

Administration (FAA) issued

airworthiness directive (AD) 87–06–52

R1, Amendment 39–5688 (52 FR 31979,

August 25, 1987), applicable to

AlliedSignal Inc. (formerly Avco

Lycoming Textron) ALF502R series

turbofan engines, to require initial and

repetitive inspections of the oil system

chip detectors and oil filter bypass

valve, and optional installation of an

improved oil filter bypass valve, to

ensure the integrity of the reduction

gear system and overspeed protection

system. The optional installation of the

improved oil filter bypass valve

provides terminating action for the

repetitive oil filter bypass valve spring

compression test also required by AD

87–06–52 R1. That action was prompted

by reports of power turbine (PT)

overspeed and uncontained PT blade

failure resulting from reduction gear

system decouple and inaccurate PT

overspeed signal generation. That

condition, if not corrected, could result

in No. 4 and 5 duplex bearing failure,

which can result in a Stage 4 low

pressure turbine (LPT) rotor failure, an

uncontained engine failure, and damage

to the aircraft.

Since the issuance of AD 87–06–52

R1, the FAA has received reports of four

additional failures of the Stage 4 low

pressure turbine (LPT) rotor on

AlliedSignal Inc. ALF502 series

turbofan engines. The LPT failures were

caused by failure of the No. 4 and 5

duplex bearing, causing bearing seizure

and LPT shaft separation between the

two bearings forward of the Stage 4 LPT

rotor. In one incident the Stage 4 LPT

shaft separation caused an uncontained

rotor failure.

On March 27, 1997, the FAA issued

AD 97–05–11, Amendment 39–9955 (62

FR 15378, April 1, 1997), to supersede

AD 87–06–52 R1 to require more

stringent oil system inspection

requirements, including inspection of

the full flow chip detector, oil filter

impending bypass button, oil acid

number, oil color, and oil quantity.

Since the issuance of AD 97–05–11,

the FAA has determined that the initial

inspection threshold for the oil

maintenance requirements were

inadvertently omitted. This amendment

adds the initial inspection threshold for

the oil maintenance requirements and

corrects the service bulletin numbers

referenced in the AD.

The FAA has reviewed and approved

the technical contents of AlliedSignal

Inc. Service Bulletins (SBs): No.

ALF502L 79–0171, Revision 1, dated

November 27, 1996; No. LF507–1F 79–

5, Revision 1, dated November 27, 1996;

No. LF507–1H 79–5, Revision 1, dated

November 27, 1996; and No. ALF502R

79–9, Revision 1, dated November 27,

1996. These SBs describe procedures for

oil system inspection. In addition, FAA

has reviewed and approved the

technical content of Textron Lycoming

SB No. ALF 502R–79–0162, Revision 2,

dated September 8, 1987, to ensure that

portions of the accomplishment

instructions paragraph of this SB

continues to provide the terminating

action for the oil filter bypass valve

compression spring test. Also, the FAA

has reviewed and approved the

technical contents of Avco Lycoming

Textron SB No. ALF 502R–72–0160,

Revision 2, dated May 26, 1987, and

Revision 1, dated March 23, 1987, that

describe procedures for chip detector

inspections. Finally, the FAA has

reviewed and approved the technical

contents of Avco Lycoming Textron SB

No. ALF 502R–79–0162, Revision 1,

dated May 26, 1987, and Original, dated

March 23, 1987, that describe

procedures of inspection of the oil filter

bypass valve.

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 97–05–

11 to add the initial inspection

threshold for the oil maintenance

requirements which was inadvertently

omitted from AD 97–05–11,

Amendment 39–9955, paragraphs (b)

through (e), and corrects the editorial

errors in paragraph (a)(1) and (c).

Paragraphs (b) through (f) are rearranged as a result of these corrections.

The actions are required to be

accomplished in accordance with the

SBs described previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

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

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.
41264 Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations

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 96–ANE–36.’’ 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 U.S.C. 106(g), 40113, 44701.

§39.13 [Amended]

2. Section 39.13 is amended by

removing Amendment 39–9955 (62 FR

15378, April 1, 1997) and by adding a

new airworthiness directive,

Amendment 39–10091, to read as

follows:

97–05–11 R1 AlliedSignal Inc.: Amendment

39–10091. Docket 96–ANE–36. Revises

AD 97–05–11, Amendment 39–9955.

Applicability: AlliedSignal Inc. and

Textron Lycoming Model ALF502 and LF507

series turbofan engines, installed on but not

limited to British Aerospace BAe146–100A,

BAe146–200A, BAe146–300A, AVRO 146–

RJ70A, AVRO 146–RJ85A, AVRO 146-

RJ100A, and Canadair Model CL–600–1A11

series aircraft.

Note 1: 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 (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 as indicated, unless

accomplished previously.

To prevent No. 4 and 5 duplex bearing

failure, which can result in a Stage 4 low

pressure turbine (LPT) rotor failure, an

uncontained engine failure, and damage to

the aircraft, accomplish the following:

(a) For ALF502R series engines equipped

with oil filter bypass valve, part number (P/

N) 2–303–432–01, accomplish the following:

(1) Inspect the engine oil filter bypass valve

for leakage within the next 25 engine hours

or 25 flights in service, whichever occurs

first, from the effective date of this AD, in

accordance with Avco Lycoming Textron

Service Bulletin (SB) No. ALF 502R–79–

0162, Original, dated March 23, 1987, or

Revision 1, dated May 26, 1987. Prior to

further flight, remove from service oil filters

exhibiting any leakage and replace with

serviceable parts.

(2) Thereafter, inspect the oil filter bypass

valve for any leakage in accordance with

Avco Lycoming Textron SB No. ALF 502R–

79–0162, Original, dated March 23, 1987, or

Revision 1, dated May 26, 1987, at intervals

not to exceed 50 engine hours or 50 flights

in service since last inspection, whichever

occurs first, and at the same time accomplish

the following:

(i) Visually inspect the following engine

chip detectors for metal contamination:

(A) For engines with a full flow chip

detector installed, inspect the full flow chip

detector.

(B) For engines without a full flow chip

detector installed, inspect the chip detectors

located in the accessory gearbox, Number 2

bearing scavenge line, and Number 4/5

bearing scavenge line.

(ii) For engines with engine chip detectors

exhibiting Condition 3, or Condition 2, or

Condition 1 where the oil filter bypass

indicator is extended, prior to further flight,

remove oil filter bypass valves exhibiting any

leakage and replace with a serviceable part.

Note 2: Chip detector conditions are

described in Avco Lycoming Textron SB No.

ALF502R–72–0160, Revision 1, dated March

23, 1987, Figures 1, 2 and 3.

(3) At the next engine shop visit, or within

2,500 engine hours after the effective date of

this AD, whichever occurs first, conduct the

oil filter bypass valve spring compression

force check, in accordance with Avco

Lycoming Textron SB No. ALF 502R–79–

0162, Original, dated March 23, 1987. Oil

filter bypass valves which do not comply

with the spring compression force limits

contained in Avco Lycoming Textron SB No.

ALF 502R–79–0162, Original, dated March

23, 1987, must be removed and replaced with

oil filter bypass valve, P/N 2–303–432–02.

Replacement of oil filter bypass valve, P/N 2–

303–432–01, with the improved oil filter

bypass valve, P/N 2–303–432–02, constitutes

terminating action for the inspection

requirements of paragraphs (a)(1) and (a)(2)

of this AD.

(4) For the purpose of this AD, an engine

shop visit is defined as engine maintenance

that entails any of the following:

(i) Separation of a major engine flange

(lettered or numbered) other than flanges

mating with major sections of the nacelle

reverser. Separation of flanges purely for

purposes of shipment, without subsequent

internal maintenance, is not a ‘‘shop visit.’’

(ii) Removal of a disk, hub, or spool.

(iii) Removal of the fuel nozzles.

(b) For ALF502R, ALF502L, LF507–1F, and

LF507–1H series engines, equipped with the

No. 4 and 5 duplex bearing assembly

numbers 2–141–930–01, 2–141–930–02, or

2–141–930–03, perform the repetitive oil

system maintenance and inspections in

accordance with the intervals and procedures

described in the Accomplishment

Instructions paragraphs of the applicable

AlliedSignal Inc. SBs referenced in

paragraphs (b)(1), (b)(2), (b)(3), and (b)(4) of

this AD, within the next 25 engine hours or

25 flights in service, whichever occurs first,

from the effective date of this AD.

(1) For ALF502R series engines, in

accordance with AlliedSignal Inc. SB No.

ALF502R 79–9, Revision 1, dated November

27, 1996.

(2) For ALF502L series engines, in

accordance with AlliedSignal Inc. SB No.

ALF502L 79–0171, Revision 1, dated

November 27, 1996.

(3) For LF507–1F series engines, in

accordance with AlliedSignal Inc. SB No.

LF507–1F–79–5, Revision 1, dated November

27, 1996.
Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations 41265

(4) For LF507–1H series engines, in

accordance with AlliedSignal SB No. LF507–

1H–79–5, Revision 1, dated November 27,

1996.

(c) An alternative method of compliance or

adjustment of the initial compliance time

that provides an acceptable level of safety

may be used if approved by the Manager, Los

Angeles Aircraft Certification Office.

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 Aircraft

Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

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

accomplishment instructions paragraphs of

the following documents:

Document No. Pages Revision Date

Avco Lycoming Textron SB No. ALF 502R–72-0160 ................................................................ 1–7 2 May 26, 1987.

Total Pages: 7.

Avco Lycoming Textron SB No. ALF 502R–72-0160 ................................................................ 1–7 1 March 23, 1987.

Total Pages: 7.

Avco Lycoming Textron SB No. ALF 502R–79-0162 ................................................................ 1–5 2 September 8, 1987.

Total Pages: 5.

Avco Lycoming Textron SB No. ALF 502R–79-0162 ................................................................ 1–4 1 May 26, 1987.

Total Pages: 4.

Avco Lycoming Textron SB No. ALF 502R–79-0162 ................................................................ 1–6 Original March 23, 1987.

Total Pages: 6.

AlliedSignal Inc. SB No. ALF502R 79–9 1 1 November 27, 1996.

2 Original June 29, 1995.

3–7 1 November 27, 1996.

8 Original June 29, 1995.

9–12 1 November 27, 1996.

13,14 Original June 29, 1995.

Total Pages: 14.

AlliedSignal Inc. SB No. LF507–1F 79–5 .................................................................................. 1 1 November 27, 1996.

2 Original June 29, 1995.

3–7 1 November 27, 1996.

8 Original June 29, 1995.

9–12 1 November 27, 1996.

13,14 Original June 29, 1995.

Total Pages: 14.

AlliedSignal Inc. SB No. LF507–1H 79–5 .................................................................................. 1 1 November 27, 1996.

2 Original June 29, 1995.

3–7 1 November 27, 1996.

8 Original June 29, 1995.

9–12 1 November 27, 1996.

13,14 Original June 29, 1995.

Total Pages: 14.

AlliedSignal Inc. SB ALF502L 79–0171 ..................................................................................... 1 1 November 27, 1996.

2 Original November 3, 1995.

3–7 1 November 27, 1996.

8 Original November 3, 1995.

9–12 1 November 27, 1996.

13,14 Original November 3, 1995.

Total Pages: 14

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

Aerospace, 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 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 18, 1997.

Issued in Burlington, Massachusetts, on

July 23, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–20192 Filed 7–31–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 94–ASW–8]

RIN 2120–AA66

Alteration of Jet Route

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This rule extends Jet Route

231 (J–231) from the St. Johns, AZ, Very

High Frequency Omnidirectional Range/

Tactical Air Navigation (VORTAC) west

to the Twentynine Palms, CA, VORTAC.

This action enhances air safety,

simplifies routings, and reduces

controller workload.

DATE: Effective 0901 UTC, November 6,

1997.

FOR FURTHER INFORMATION CONTACT:

Steve Brown, Airspace and Rules

Division, ATA–400, Office of Air Traffic

Airspace Management, Federal Aviation

Administration, 800 Independence

Avenue, SW., Washington, DC 20591;

telephone: (202) 267–8783.