Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations 49137

as required, in accordance with paragraph

(a)(3) of this AD. If the indicator window has

not turned completely black, install a new

indicator(s) in accordance with Section

2.A.(1) of the Accomplishment Instructions

of PW ASB No. 5944, Revision 3, dated

December 16, 1994, or Revision 2, dated June

8, 1992, prior to return to service, and

visually inspect the temperature indicator

within 65 hours TIS since installation.

Thereafter, inspect at intervals not to exceed

65 hours TIS since last inspection in

accordance with paragraphs (a)(2) and (a)(3)

of this AD.

(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, 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.

Note 2: Information concerning the

existence of approved alternative method of

compliance with this AD, if any, may be

obtained from the Engine 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 aircraft to

a location where the requirements of this AD

can be accomplished.

(f) The actions required by this AD shall be

done in accordance with the following PW

ASBs:

Document No. Pages Revision Date

5944 ................................................................................................................................. 1–35 3 December 16, 1994.

Total pages: 35.

5944 ................................................................................................................................. 1–44 2 June 8, 1992.

Total pages: 44.

This incorporation by reference of PW ASB

No. 5944, Revision 2, dated June 9, 1993, 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 January 31,

1995 (59 FR 61789, December 2, 1994).

Copies may be obtained from Pratt &

Whitney, Publication Department, Supervisor

Technical Publications Distribution,

M/S 132–30, 400 Main St., East Hartford, CT

06108; telephone (860) 565–7700, 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.

(g) This amendment becomes effective on

October 24, 1997.

Issued in Burlington, Massachusetts, on

September 10, 1997.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–24797 Filed 9–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–07; Amendment 39–

10135; AD 97–19–14]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D 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

series turbofan engines, that currently

requires inspections of low pressure

turbine (LPT) blade sets for blade

shroud crossnotch wear, and removal, if

necessary. In addition, the current AD

requires, as a terminating action to the

inspections, installation of improved

LPT containment hardware, and

installation of an improved No. 6

bearing scavenge pump bracket bushing.

This amendment keeps the compliance

actions of the current AD intact but

changes the compliance time for LPT

containment hardware installation from

the current calendar end-date to

December 31, 1998, for engines that

contain suspect 4th stage hubs

identified by serial number. This

amendment is prompted by a report of

a fourth stage hub manufacturing defect

that led to the failure of the hub and

subsequent release of LPT blades. The

actions specified by this AD are

intended to prevent damage to the

aircraft resulting from engine debris

following an LPT blade, shaft, or hub

failure.

DATES: Effective October 24, 1997.

The incorporation by reference of PW

Alert Service Bulletin No. A6131,

Revision 1, dated May 16, 1995; PW

Alert Service Bulletin No. A6131,

Revision 2, dated July 28, 1997; PW

Alert Service Bulletin No. A6274,

Original, dated November 7, 1996; and

PW Alert Service Bulletin No. A6274,

Revision 1, dated December 9, 1996, is

approved by the Director of the Federal

Register as of October 24, 1997.

The incorporation by reference of all

other publications listed in the

regulations was previously approved as

of November 14, 1994 (59 FR 51842,

October 13, 1994).

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

(781) 238–7175, fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 94–20–08,

Amendment 39–9036 (59 FR 51842,

October 15, 1994), applicable to Pratt &

Whitney (PW) JT8D–1, –1A, –1B, –7,

–7A, –7B, –9, –9A, –11, –15, –17, and

–17R series turbofan engines, was

published in the Federal Register on

April 1, 1997 (62 FR 15437). That action

proposed to require inspections of low

pressure turbine (LPT) blade sets for

blade shroud crossnotch wear, and

removal, if necessary. In addition, the

current AD requires, as a terminating

action to the inspections, installation of

improved LPT containment hardware,

and installation of an improved No. 6

bearing scavenge pump bracket bushing.

The proposal would have reduced the

compliance time for LPT containment

hardware installation from the current

calendar end-date to December 31, 1998.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due
49138 Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations

consideration has been given to the

comments received.

Eight commenters state that the more

stringent compliance times should only

be applicable to those engines that have

a suspect 4th stage LPT hub installed.

Otherwise, the proposed AD imposes an

undue burden to operators, since the

proposed AD does not specifically

address the threat of the 4th stage hub

suspect population. The commenters

offer several alternatives, such as

withdrawal of the NPRM, writing a

stand alone AD, changing the

compliance paragraph, and adding a

paragraph to NPRM Docket No. 96–

ANE–32. The FAA concurs with the

comments and is changing the

compliance paragraph accordingly. This

final rule contains a new compliance

schedule, which is intended to meet the

threat of an blade release due to the

failure of the 4th stage LPT hub. The

threat of a 4th hub failure has been

isolated to a suspect population of hubs

listed in PW Alert Service Bulletin No.

A6274, Revision 1, dated December 9,

1996.

Two commenters state that the third

stage turbine air sealing ring should not

have the more stringent compliance

times, as the third stage turbine air

sealing ring does not affect 4th stage

LPT containment, which is why the

compliance end-date is being moved up.

The FAA concurs. The third stage

turbine air sealing ring does not

contribute to the containment of 4th

stage LPT blades, therefore the FAA has

removed the more stringent compliance

times for the third stage turbine air

sealing ring in this final rule. The FAA

has also relaxed the compliance time for

the improved No. 6 bearing scavenge

pump bracket bushing, as this part also

does not contribute to the containment

of 4th stage LPT blades released due to

a 4th stage hub fracture.

One commenter states that the AD

cannot be complied with on schedule as

the replacement hardware is not

available. The FAA does not concur.

The manufacturer has advised the FAA

that there are no current or foreseen

shortages of hardware that will slow

down operators’ ability to comply with

the AD.

One commenter states that the

proposed rule should be withdrawn, as

the risk is within acceptable limits

without any further action and the

actions described in NPRM Docket No.

96–ANE–32 are adequate to prevent

future occurrences of uncontained

failures from this cause. The FAA does

not concur. While not yet published, the

actions proposed in NPRM Docket No.

96–ANE–32 would, if adopted,

minimize the threat of an uncontained

blade release due to a hub fracture. The

FAA has also evaluated the risk and

crack growth analysis data and field

experience for the 4th stage LPT hub

and the data supports the conclusion

that the failure mechanism is the loss of

a 4th stage LPT blade and that the hub

field management program must address

non-containment of the LPT blade as

well as the inspection of the LPT hub

for cracks. The FAA feels the added

measure of security offered by the

improved containment is warranted in

this case. However, the FAA agrees the

more aggressive containment schedule

should only apply to those hubs at

highest risk of failing and releasing a

blade as outlined in the compliance

section described in previous responses

to comments.

One commenter states that

accomplishment of the actions

described in PW ASB No. A6131,

Revision 1, dated May 16, 1995, should

be an acceptable alternative method of

compliance to the AD’s reference of the

Original version of the ASB. The FAA

concurs and has added reference to

Revision 1 to the compliance section of

this final rule.

One commenter states concern that

the same containment hardware will be

required for engines required to

accomplish the actions described in AD

94–20–09 covering ‘‘A’’ model engines.

The FAA does not concur. The suspect

hubs are not approved for installation

on ‘‘A’’ model engines; therefore, a

similar condition does not exist for the

‘‘A’’ models.

Three commenters support the rule as

proposed.

In addition, the FAA has reviewed

and approved the technical contents of

PW ASB No. A6274, Revision 1, dated

December 9, 1996, and Original, dated

November 7, 1996, that describe

procedures for repetitive inspections of

affected LPT hubs; and PW ASB No.

A6131, Revision 2, dated July 28, 1997,

that describes procedures for

installation of the improved No. 6

bearing scavenge pump bracket bushing.

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 the

changes to the AD would neither

increase the scope of the required

actions over the current AD, nor

increase the economic burden on

operators over the costs of complying

with the current AD. While the new AD

alters the compliance times, operators

should still be able to perform the

required actions at scheduled

maintenance. Therefore the FAA has

determined that this new AD will result

in no additional economic impact.

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 39–9036 (59 FR

51842, October 15, 1994) and by adding

a new airworthiness directive to read as

follows:

97–19–14 Pratt & Whitney: Amendment 39–

10135. Docket 97–ANE–07. Supersedes

AD 94–20–08, Amendment 39–9036.

Applicability: Pratt & Whitney (PW) JT8D–

1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15,

–17, and –17R turbofan engines, installed on

but not limited to Boeing 737 and 727 series

aircraft, and McDonnell Douglas DC–9 series

aircraft.
Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations 49139

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 (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 as indicated, unless

accomplished previously.

To prevent damage to the aircraft resulting

from engine debris following a low pressure

turbine (LPT) blade, shaft, or hub failure,

accomplish the following:

(a) For engines that do not contain fan

exhaust inner front duct segment assemblies

that are installed in accordance with PW

Alert Service Bulletin (ASB) No. 6039,

Revision 3, dated October 15, 1993, or earlier

revisions of PW ASB No. 6039, and either

PW honeycomb third stage outer airseal Part

Number (P/N) 801931, 802097, 797594, or

798279; or Pyromet Industries, Inc.,

honeycomb third stage outer airseal P/N

PI9336; or McClain International, Inc.,

honeycomb third stage outer airseal P/N

M2433; or a turbine case shield assembly

installed in accordance with PW ASB No.

6039, Revision 3, dated October 15, 1993, or

earlier revisions of PW ASB No. 6039; or a

third stage blade set that has third stage

turbine blades that were installed in

accordance with PW SB No. 5331, dated

October 27, 1982, accomplish the following:

(1) Conduct initial and repetitive

inspections on installed third and fourth

stage LPT blade sets, and remove and replace

with serviceable blade sets, as necessary, in

accordance with Part 1 of the

Accomplishment Instructions of PW ASB No.

A5913, Revision 6, dated October 15, 1993;

or PW ASB No. A5913, Revision 5, dated

August 10, 1992; or PW ASB No. A5913,

Revision 4, dated February 20, 1992, as

follows:

(i) Initially inspect the blade shroud

crossnotches of the third stage LPT blade set

when specified in paragraphs (a)(1)(i)(A) or

(a)(1)(i)(B) of this AD, whichever occurs later.

Engines that contain a third stage blade set

that have third stage turbine blades that were

installed per the requirements specified in

PW Service Bulletin (SB) No. 5331, dated

October 27, 1982, do not require the third

stage blade set inspection.

(A) Inspect within 6,000 cycles or 6,000

hours time in service, whichever occurs first,

since new, since the last blade shroud

crossnotch inspection specified in Section

72–53–12 of PW JT8D Engine Manual P/N

481672, or since last blade shroud crossnotch

repair that was accomplished per the

requirements specified in Section 72–53–12

of PW JT8D Engine Manual P/N 481672; or

(B) Inspect within 1,000 cycles or 1,000

hours time in service since November 14,

1994, whichever occurs first.

(ii) Initially inspect the blade shroud

crossnotches of the fourth stage LPT blade set

when specified in paragraph (a)(1)(ii)(A) or

(a)(1)(ii)(B) of this AD, whichever occurs

later. Engines that contain fan exhaust inner

front duct segment assemblies that were

installed per the requirements of PW ASB

No. 6039, Revision 3, dated October 15, 1993,

or earlier revisions of PW ASB No. 6039, do

not require the fourth stage blade set

inspection.

(A) Inspect within 6,000 cycles or 6,000

hours time in service, whichever occurs first,

since new, since the last blade shroud

crossnotch inspection specified in Section

72–53–13 of PW JT8D Engine Manual P/N

481672, or since last blade shroud crossnotch

repair that was accomplished per the

requirements specified in Section 72–53–13

of PW JT8D Engine Manual P/N 481672; or

(B) Inspect within 1,000 cycles or 1,000

hours time in service since November 14,

1994, whichever occurs first.

(iii) Thereafter, inspect the third and fourth

stage LPT blade sets in accordance with the

procedures and intervals specified in PW

ASB No. A5913, Revision 6, dated October

15, 1993;

(2) At the next shop visit after the effective

date of this AD, install the improved inner

front fan exhaust duct and associated

hardware in accordance with Part A of the

Accomplishment Instructions of PW ASB

A6110, Revision 1, dated October 15, 1993,

as follows:

(i) For engines that have a 4th stage LPT

hub installed with a serial number listed in

PW ASB A6274, Table A, dated November 7,

1996, or Revision 1, dated December 9, 1996,

install the improved inner front fan exhaust

duct before December 31, 1998, or 8,000

hours time in service since November 14,

1994, or 7,000 cycles in service since

November 14, 1994, whichever occurs first.

(ii) For engines that do not have a 4th stage

LPT hub installed with a serial number listed

in PW ASB A6274, Table A, dated November

7, 1996, or Revision 1, dated December 9,

1996, install the improved inner front fan

exhaust duct before December 31, 1999, or

8,000 hours time in service since November

14, 1994, or 7,000 cycles in service since

November 14, 1994, whichever occurs latest.

(3) At the next access to the third stage

turbine air sealing ring, install the improved

third stage turbine air sealing ring and

associated hardware in accordance with Part

B of the Accomplishment Instructions of PW

ASB A6110, Revision 1, dated October 15,

1993. The installation of the improved third

stage turbine air sealing ring must occur no

later than December 31, 1999, or 8,000 hours

time in service since November 14, 1994, or

7,000 cycles in service since November 14,

1994, whichever occurs latest.

Note 2: Third stage turbine outer air seal,

P/N M2533, is an acceptable alternative to

PW P/N 811962 for compliance with this

paragraph.

(4) At the next shop visit after the effective

date of this AD, install the improved No. 6

bearing scavenge pump bracket bushing in

accordance with the Accomplishment

Instructions of PW ASB No. A6131, dated

August 24, 1993, or Revision 1, dated May

16, 1995, or Revision 2, dated July 28, 1997.

The installation of the improved No. 6

bearing scavenge pump bracket bushing must

be accomplished no later than December 31,

1999, or 8,000 hours time in service since

November 14, 1994, or 7,000 cycles since

November 14, 1994, whichever occurs latest.

(5) Accomplishment of the installations

required by paragraphs (a)(2), (a)(3), and

(a)(4) of this AD constitutes terminating

action to the repetitive inspections required

by paragraph (a)(1) of this AD.

(b) For engines that do contain fan exhaust

inner front duct segment assemblies that are

installed in accordance with PW ASB No.

6039, Revision 3, dated October 15, 1993, or

earlier revisions of PW ASB No. 6039, and

either PW honeycomb third stage outer

airseal P/N 801931, 802097, 797594, or

798279; or Pyromet Industries, Inc.,

honeycomb third stage outer airseal P/N

PI9336; or McClain International, Inc.,

honeycomb third stage outer airseal P/N

M2433; or a turbine case shield assembly

installed in accordance with PW ASB No.

6039, Revision 3, dated October 15, 1993, or

earlier revisions of PW ASB No. 6039; or a

third stage blade set that has third stage

turbine blades that were installed in

accordance with PW SB No. 5331, dated

October 27, 1982, perform the installations

required by paragraphs (a)(2), (a)(3), and

(a)(4) of this AD, at the times specified in

those respective paragraphs.

(c) For the purpose of this AD, a shop visit

is defined as an engine removal, where

engine maintenance entails separation of

pairs of major mating engine flanges or the

removal of a disk, hub, or spool at a

maintenance facility that is capable of

compliance with the instructions of this AD,

regardless of other planned maintenance,

except for field maintenance type activities

performed at this maintenance facility in lieu

of performing them on-wing or at another

peripheral facility.

(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, 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.

Note 3: Information concerning the

existence of approved alternative method of

compliance with this AD, if any, may be

obtained from the Engine 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 aircraft to

a location where the requirements of this AD

can be accomplished.

(f) The actions required by this AD shall be

done in accordance with the following PW

service documents:
49140 Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations

Document No. Pages Revision Date

ASB No. A5913 ................................................................................................................. 1–12 6 .............. October 15, 1993.

Total pages: 12.

ASB No. A6110 ................................................................................................................. 1–59 1 .............. October 15, 1993.

Total pages: 59.

ASB No. A6131 ................................................................................................................. 1–13 Original .... August 24, 1993.

Total pages: 13.

ASB No. A6131 ................................................................................................................. 1–14 1 .............. May 16, 1995.

Total pages: 14.

ASB No. A6131 ................................................................................................................. 1–21 2 .............. July 28, 1997.

Total pages: 21.

ASB No. A6274 ................................................................................................................. 1, 2 1 .............. December 9, 1996.

3, 4 Original .... November 7, 1996.

5 1 .............. December 9, 1996.

6–22 Original .... November 7, 1996.

23 1 .............. December 9, 1996.

Total pages: 23.

ASB No. A6274 ................................................................................................................. 1–23 Original .... November 7, 1996.

Attachment NDIP–889 ....................................................................................................... 1–39 Original .... November 1, 1996.

Total pages: 62.

This incorporation by reference of PW ASB

No. A5913, Revision 6, dated October 15,

1993; and PW ASB No. A6110, Revision 1,

dated October 15, 1993; 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 November 14, 1994

(59 FR 51842, October 13, 1994). 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.

(g) This amendment becomes effective on

October 24, 1997.

Issued in Burlington, Massachusetts, on

September 10, 1997.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–24798 Filed 9–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 97

[Docket No. 29018; Amdt. No. 1821]

Standard Instrument Approach

Procedures; Miscellaneous

Amendments

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment establishes,

amends, suspends, or revokes Standard

Instrument Approach Procedures

(SIAPs) for operations at certain

airports. These regulatory actions are

needed because of changes occurring in

the National Airspace System, such as

the commissioning of new navigational

facilities, addition of new obstacles, or

changes in air traffic requirements.

These changes are designed to provide

safe and efficient use of the navigable

airspace and to promote safe flight

operations under instrument flight rules

at the affected airports.

DATES: An effective date for each SIAP

is specified in the amendatory

provisions.

Incorporation by reference—approved

by the Director of the Federal Register

on December 31, 1980, and reapproved

as of January 1, 1982.

ADDRESSES: Availability of matter

incorporated by reference in the

amendment is as follows:

For Examination

1. FAA Rules Docket, FAA Headquarters

Building, 800 Independence Avenue,

SW., Washington, DC 20591;

2. The FAA Regional Office of the

region in which affected airport is

located; or

3. The Flight Inspection Area Office

which originated the SIAP.

For Purchase

Individual SIAP copies may be

obtained from:

1. FAA Public Inquiry Center (APA–

200), FAA Headquarters Building, 800

Independence Avenue, SW.,

Washington, DC 20591; or

2. The FAA Regional Office of the

region in which the affected airport is

located.

By Subscription

Copies of all SIAPs, mailed once

every 2 weeks, are for sale by the

Superintendent of Documents, US

Government Printing Office,

Washington, DC 20402.

FOR FURTHER INFORMATION CONTACT: Paul

J. Best, Flight Procedures Standards

Branch (AFS–420), Technical Programs

Division, Flight Standards Service,

Federal Aviation Administration, 800

Independence Avenue, SW.,

Washington, DC 20591; telephone (202)

267–8277.

SUPPLEMENTARY INFORMATION: This

amendment to part 97 of the Federal

Aviation Regulations (14 CFR part 97)

establishes, amends, suspends, or

revokes Standard Instrument Approach

Procedures (SIAPs). The complete

regulatory description on each SIAP is

contained in the appropriate FAA Form

8260 and the National Flight Data

Center (FDC)/Permanent (P) Notices to

Airmen (NOTAM) which are

incorporated by reference in the

amendment under 5 U.S.C. 552(a), 1

CFR part 51, and § 97.20 of the Federal

Aviations Regulations (FAR). Materials

incorporated by reference are available

for examination or purchase as stated

above.

The large number of SIAPs, their

complex nature, and the need for a

special format make their verbatim

publication in the Federal Register

expensive and impractical. Further,

airmen do not use the regulatory text of

the SIAPs, but refer to their graphic

depiction of charts printed by

publishers of aeronautical materials.

Thus, the advantages of incorporation

by reference are realized and

publication of the complete description

of each SIAP contained in FAA form

documents is unnecessary. The

provisions of this amendment state the

affected CFR (and FAR) sections, with

the types and effective dates of the

SIAPs. This amendment also identifies

the airport, its location, the procedure

identification and the amendment

number.