45152 Federal Register / Vol. 62, No. 165 / Tuesday, August 26, 1997 / Rules and Regulations

were manufactured or repaired from August

1996 through July 1997; utilized in aircraft

that are certificated in any category.

Note 1: These Puritan-Bennett cone and

seal assemblies, part numbers 210543 and

210543–01, may be attached to the following

part number Puritan-Bennett sweep-on crew

oxygen masks:

114321–01, 114321–15, 114321–16, 114322–

01, 114322–02, 114322–03, 114322–05,

114323–01, 114622–01, 114622–02,

114623–01, 114623–02

Note 2: This AD applies to each aircraft

equipped with a cone and seal assembly that

is identified in the preceding applicability

provision, regardless of whether the aircraft

has been modified, altered, or repaired in the

area subject to the requirements of this AD.

For aircraft 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 (d) 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 within the next 7

days after the effective date of this AD, unless

already accomplished.

To prevent failure of the ultrasonic weld

on the cone and seal assembly of the oxygen

mask with consequent reduced oxygen flow

through the mask, which could result in the

crew not being able to obtain oxygen in an

emergency situation, accomplish the

following:

(a) Replace any cone and seal assembly

referenced in the Applicability section of this

AD with an FAA-approved assembly not

covered by this AD.

(b) As of the effective date of this AD, no

person may equip an aircraft with any

Puritan-Bennett cone and seal assembly, part

numbers 210543 and 210543–01, that were

manufactured or repaired between August

1996 and July 1997.

Note 3: Puritan-Bennett Service Bulletin

No. 3500–97–14, dated August 7, 1997,

specifies identification and replacement of

the part numbers 210543 and 210543–01

cone and seal assemblies.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas 67209. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(e) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to Puritan-Bennett

Aero Systems Co., 10800 Pflumm Road,

Lenexa, Kansas 66215; or may examine this

document at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

(f) This amendment (39–10113) becomes

effective on September 22, 1997.

Issued in Kansas City, Missouri, on August

19, 1997.

Terry L. Chasteen,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–22638 Filed 8–25–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–08; Amendment 39–

10106; AD 97–17–04]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D–200 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Pratt & Whitney JT8D–200

series turbofan engines, that currently

requires cleaning of front compressor

front hubs (fan hubs); initial and

repetitive eddy current (ECI) and

fluorescent penetrant inspections (FPI)

of tierod and counterweight holes for

cracks; removal of bushings; the

cleaning and ECI and FPI of bushed

holes for cracks; and, if necessary,

replacement with serviceable parts. In

addition, the current AD requires

reporting the findings of cracked fan

hubs. This amendment does not change

the current AD’s inspection procedures,

or the effectivity date that starts the

cycle count for the initial inspection

schedules. This AD does, however, add

an additional inspection schedule that

requires the initial inspection of certain

fan hubs with standard drilled holes

and coolant channel drilled (CCD) holes

to occur earlier than the existing AD

requires. Also, this AD requires

reporting the results of the initial fan

hub inspections. This amendment is

prompted by additional investigation

since publication of the current AD that

reveals that certain fan hubs with

standard drilled holes and CCD holes

may be more susceptible to cracking.

The actions specified by this AD are

intended to prevent fan hub failure due

to tierod, counterweight, or bushed hole

cracking, which could result in an

uncontained engine failure and damage

to the aircraft.

DATES: Effective September 30, 1997.

The incorporation by reference of

certain publications listed in the

regulations was previously approved by

the Director of the Federal Register as of

March 5, 1997 62 FR 4902, February 3,

1997).

ADDRESSES: The service information

referenced in this AD may be obtained

from Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone (860)

565–6600, fax (860) 565-4503. This

information may be examined at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Assistant Chief Counsel, 12 New

England Executive Park, Burlington, MA

01803–5299; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Christopher Spinney, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; telephone

(617) 238–7175, fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 97–02–11,

Amendment 39–9896 (62 FR 4902,

February 3, 1997), applicable to Pratt &

Whitney (PW) JT8D–200 series turbofan

engines, was published in the Federal

Register on February 24, 1997 (62 FR

8198), and a correction to a printing

error in a table was published on March

31, 1997 (62 FR 15225). That action

proposed to require cleaning, initial and

repetitive eddy current inspections (ECI)

and fluorescent penetrant inspections

(FPI) for cracks of tierod and

counterweight holes; removal of

bushings; the cleaning and initial and

repetitive ECI and FPI of bushed holes

for cracks; and, if necessary, replacing

with serviceable parts.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Three commenters state that the

March 5, 1997, date to begin counting

cycles is objectionable, as a retroactive

date is unenforceable. The FAA concurs

in part. The March 5, 1997, date is

supported by a safety risk analysis, but

basing the cyclic count on this date
Federal Register / Vol. 62, No. 165 / Tuesday, August 26, 1997 / Rules and Regulations 45153

would require immediate removal of

parts not in compliance at the effective

date of this AD. However, the FAA has

reviewed a new risk analysis that uses

the effective date of this AD to begin the

cyclic count for fan hubs added to Table

2 of this AD. This final rule has been

revised by changing the compliance

time to ‘‘315 cycles from the effective

date of this AD’’. This new date should

prevent any fan hubs from being out of

compliance at the date of final rule

publication. It does not, however,

extend the compliance time for those

fan hubs that were previously included

in AD 97–02–11 and are now listed in

Table 2 of this AD. Fan hubs previously

included in AD 97–02–11 must perform

initial inspections to the more

conservative compliance times.

One group of commenters object to

the monthly reporting requirements

required in the proposed rule, as these

requirements are burdensome and do

not contribute to safety. The FAA does

not concur. The reports received from

these inspections are used to validate

the assumptions used in the safety risk

analysis and are critical to the safety

assessment of the inspection program.

One commenter states that alternative

methods of compliance (AMOCs)

approved in the current AD should be

included in this superseded AD. The

FAA concurs and has added a statement

to this final rule that approves AMOCs

from AD 97–02–11 as acceptable for this

AD.

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 with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

There are approximately 2,624

engines of the affected design in the

worldwide fleet. The FAA estimates that

1,279 engines installed on aircraft of

U.S. registry will be affected by this AD,

that it will take 20 work hours per

engine for 360 engines to disassemble,

remove, inspect, and reassemble

engines, and 4 work hours per engine

for 919 engines to inspect at piece-part

exposure, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$862,560.

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

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

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air Transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–9896 (62 FR

4902, February 3, 1997) and by adding

a new airworthiness directive to read as

follows:

97–17–04 Pratt & Whitney: Amendment 39–

10106. Docket 97–ANE–08. Supersedes

AD 97–02–11, Amendment 39–9896.

Applicability: Pratt & Whitney JT8D–209,

–217, –217C, and –219 series turbofan

engines with front compressor front hub (fan

hub), Part Number (P/N) 5000501–01,

installed. These engines are installed on but

not limited to McDonnell Douglas MD–80

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 fan hub failure due to tierod,

counterweight, or bushed hole cracking,

which could result in an uncontained engine

failure and damage to the aircraft,

accomplish the following:

(a) Inspect fan hubs for cracks in

accordance with the Accomplishment

Instructions, Paragraph A, Part 1, and, if

applicable, Paragraph B, of PW ASB No.

A6272, dated September 24, 1996, as follows:

(1) For fan hubs identified by Serial

Numbers (S/Ns) in Table 2 of this AD, after

the fan hub has accumulated more than 4,000

cycles since new (CSN), as follows:

(i) Initially inspect within 315 cycles in

service (CIS) from the effective date of this

AD, or 4,315 CSN, whichever occurs later.

(ii) Thereafter, reinspect after accumulating

2,500 CIS since last inspection, but not to

exceed 10,000 CIS since last inspection.

(2) For fan hubs identified by S/Ns in

Appendix A of PW ASB No. A6272, dated

September 24, 1996, after the fan hub has

accumulated more than 4,000 CSN, as

follows:

(i) Select an initial inspection interval from

Table 1 of this AD, and inspect accordingly.

TABLE 1

Initial inspection Reinspection

1. Within 1,050 cycles in service (CIS) after the effective date of AD

97–02–11, March 5, 1997, or prior to accumulating 5,050 CSN,

whichever occurs later;

After accumulating 2,500 CIS since last inspection, but not to exceed

6,000 CIS since last inspection.

OR

2. Within 990 CIS after the effective date of AD 97–02–11, March 5,

1997, or prior to accumulating 4,990 CSN, whichever occurs later;

After accumulating 2,500 CIS since last inspection, but not to exceed

8,000 CIS since last inspection.
45154 Federal Register / Vol. 62, No. 165 / Tuesday, August 26, 1997 / Rules and Regulations

TABLE 1—Continued

Initial inspection Reinspection

OR

3. Within 965 CIS after the effective date of AD 97–02–11, March 5,

1997, or prior to accumulating 4,965 CSN, whichever occurs later.

After accumulating 2,500 CIS since last inspection, but not to exceed

10,000 CIS since last inspection.

TABLE 2.—HUBS WITH TRAVELER NOTATIONS

Non CCD Non CCD Non CCD Non CCD CCD Hub CCD Hub CCD Hub

M67663 M67802 P66880 S25545 P66747 R33099 S25292

M67671 M67812 P66885 S25558 P66756 R33107 S25299

M67675 M67826 R32732 S25564 P66800 R33113 S25301

M67681 M67829 R32733 S25598 P66814 R33124 S25302

M67685 M67830 R32735 S25618 P66819 R33131 S25308

M67686 M67831 R32740 S25621 P66831 R33132 S25312

M67687 M67832 R32741 S25637 R32767 R33133 S25316

M67697 M67834 R32810 S25640 R32787 R33136 S25323

M67700 M67843 R32849 T50693 R32792 R33152 S25334

M67706 M67849 R32850 T50752 R32795 R33157 S25335

M67710 M67858 S25222 T50785 R32796 R33163 S25337

M67712 M67866 S25464 T50791 R32800 R33165 S25344

M67713 M67868 S25481 T50792 R32807 R33168 S25369

M67714 M67869 S25483 T50819 R32856 R33171 S25377

M67715 M67872 S25484 T50823 R32860 R33173 S25378

M67716 M67888 S25486 T50827 R32870 R33180 S25381

M67717 N71771 S25488 T50874 R32883 R33181 S25394

M67722 N71804 S25489 T50875 R32905 R33189 S25399

M67723 N71806 S25490 T51058 R32926 R33194 S25402

M67725 N71810 S25491 T51104 R32930 R33198 S25406

M67726 N71811 S25492 R32952 R33201 S25411

M67730 N71875 S25494 R32964 R33202 S25413

M67731 N71876 S25495 R32966 R33207 S25414

M67746 N71921 S25497 R32971 S25193 S25415

M67751 N71965 S25498 R32976 S25195 S25418

M67753 N72062 S25499 R32981 S25207 S25419

M67764 N72126 S25500 R32990 S25208 S25421

M67765 N72152 S25501 R32994 S25221 S25422

M67784 N72162 S25502 R33000 S25229 S25430

M67791 N72207 S25505 R33004 S25238 S25437

M67792 N72216 S25506 R33040 S25246 S25439

M67793 N72219 S25507 R33055 S25248 S25449

M67794 N72242 S25508 R33059 S25250 R33186

M67795 P66693 S25509 R33077 S25256 S25528

M67796 P66695 S25514 R33080 S25262

M67797 P66696 S25529 R33082 S25268

M67798 P66698 S25532 R33086 S25278

M67799 P66699 S25541 R33087 S25287

M67800 P66737 S25543 R33089 S25288

M67801 P66753 S25544 R33090

(ii) Thereafter, reinspect at intervals that

correspond to the selected inspection

interval.

(3) If a fan hub is identified in both Table

2 of this AD and Appendix A of PW ASB No.

A6272, dated September 24, 1996, inspect in

accordance with paragraph (a)(1) or (a)(2) of

this AD, whichever occurs first.

(4) For fan hubs with S/Ns not listed in

Table 2 of this AD or in Appendix A of PW

ASB No. A6272, dated September 24, 1996,

after the fan hub has accumulated more than

4,000 CSN, inspect the next time the fan hub

is in the shop at piece-part level, but not to

exceed 10,000 CIS after March 5, 1997.

(5) Prior to further flight, remove from

service fan hubs found cracked or that exceed

the bushed hole acceptance criteria described

in PW ASB No. A6272, dated September 24,

1996.

(b) Report the number of completed

inspections on a monthly basis and report

findings of cracked fan hubs in accordance

with Accomplishment Instructions,

Paragraph F, of Attachment 1 to PW ASB No.

A6272, dated September 24, 1996, within 48

hours after inspection to Robert Guyotte,

Manager, Engine Certification Branch, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–5299;

telephone (617) 238–7142, fax (617) 238–

7199; Internet: Robert.Guyotte@faa.dot.gov.

Reporting requirements have been approved

by the Office of Management and Budget and

assigned OMB control number 2120–0056.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Engine

Certification Office. Operators shall forward

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Alternative methods of compliance approved

for AD 97–02–11 are also considered

approved for this AD.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Engine Certification Office.

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the aircraft to

a location where the requirements of this AD

can be accomplished.
Federal Register / Vol. 62, No. 165 / Tuesday, August 26, 1997 / Rules and Regulations 45155

(e) The actions required by this AD shall

be done in accordance with the following PW

ASB:

Document

No. Pages Date

A6272 ........... 1–21 Original.September

24, 1996.

NDIP–892 ..... 1–30 A ....... September

15, 1996.

Attachment I AI–1–AI–4 A September

15, 1996.

Total Pages: 55.

This incorporation by reference was

previously approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51 as of March 5, 1997

(62 FR 4902, February 3, 1997). Copies may

be obtained from Pratt & Whitney, 400 Main

St., East Hartford, CT 06108; telephone (860)

565–6600, fax (860) 565–4503. 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

September 30, 1997.

Issued in Burlington, Massachusetts, on

August 12, 1997.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–22307 Filed 8–25–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–ASW–03]

Revision of Class E Airspace; Carlisle,

AR

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This action confirms the

effective date of a direct final rule which

revises the Class E airspace at Carlisle,

AR. The development of a Global

Positioning System (GPS) Standard

Instrument Approach Procedure (SIAP)

to Runway (RWY) 09 at Carlisle

Municipal Airport and a Nondirectional

Radio Beacon (NDB) SIAP to RWY 18 at

Stuttgart Municipal Airport has made

this rule necessary. The direct final rule

is intended to provide adequate Class E

airspace for aircraft operating under

Instrument Flight Rules (IFR) and

executing the GPS SIAP at Carlisle

Municipal Airport and the NDB SIAP at

Stuttgart Municipal Airport, and both

airports are identified within Carlisle,

AR, Class E airspace.

EFFECTIVE DATE: The direct final rule

published at 62 FR 28339 is effective

0901 UTC, September 11, 1997.

FOR FURTHER INFORMATION CONTACT:

Donald J. Day, Airspace Branch, Air

Traffic Division, Southwest Region,

Federal Aviation Administration, Fort

Worth, TX 76193–0520, telephone: (817)

222–5593.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with a

request for comments in the Federal

Register on May 23, 1997 (62 FR 28339).

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, were received

within the comment period, the

regulation would become effective on

September 11, 1997. No adverse

comments were received, and thus this

action confirms that the direct final rule

will be effective on that date.

Issued in Fort Worth, TX, on August 5,

1997.

Albert L. Viselli,

Acting Manager, Air Traffic Division,

Southwest Region.

[FR Doc. 97–22503 Filed 8–25–97; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–ASW–05]

Revision of Class E Airspace; Alice, TX

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This action confirms the

effective date of a direct final rule which

revokes the Class E surface airspace at

Alice, TX. Communication capability

with aircraft operating within the

surface area no longer exists; therefore,

Class E surface airspace designated to

provide controlled airspace for terminal

instrument operations is no longer

required. The direct final rule is

intended to revoke Class E surface

airspace for aircraft operating under

Instrument Flight Rules (IFR) for

terminal operations at Alice

International Airport, Alice, TX.

EFFECTIVE DATE: The direct final rule

published at 62 FR 28340 is effective

0901 UTC, September 11, 1997.

FOR FURTHER INFORMATION CONTACT:

Donald J. Day, Airspace Branch, Air

Traffic Division, Southwest Region,

Federal Aviation Administration, Fort

Worth, TX 76193–0520, telephone: (817)

222–5593.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with a

request for comments in the Federal

Register on May 23, 1997 (62 FR 28340).

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, were received

within the comment period, the

regulation would become effective on

September 11, 1997. No adverse

comments were received, and thus this

action confirms that the direct final rule

will be effective on that date.

Issued in Fort Worth, TX, on August 5,

1997.

Albert L. Viselli,

Acting Manager, Air Traffic Division,

Southwest Region.

[FR Doc. 97–22504 Filed 8–25–97; 8:45 am]

BILLING CODE 4910–19–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–ASW–06]

Revision of Class E Airspace; Ponca

City, OK

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This action confirms the

effective date of a direct final rule which

revises the Class E surface airspace at

Ponca City, OK. Communication

capability and weather observations

exist continuously for terminal

instrument operations at Ponca City

Municipal Airport. Therefore, Class E

surface airspace should be continuous

rather than designated as part-time Class

E surface airspace. The direct final rule

is intended to revise Class E surface

airspace to provide controlled airspace

for continuous terminal instrument

operations at Ponca City Municipal

Airport, Ponca City, OK.