66302 Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules 

Engine model Engine manual part 

number (P/N) Part nomenclature 

Inspect per 

manual 

section 

Inspection/check 

All HPT Stage 1—2 Disks and Hubs ................. 72–51–00 Inspection/Check-03. 

All LPT Stage 3—6 Disks and Hubs .................. 72–52–00 Inspection/Check-03. 

7R4D/D1/E/E1 ............... 785058 and 785059 ..... All HPT Stage 1 Disk Web Cooling Holes ......... 72–51–06 Inspection/Check-02. 

* P/N 770407 and 770408 are customized versions of P/N 646028 engine manual. 

(2) For the purposes of these mandatory 

inspections, piece-part opportunity means: 

(i) The part is considered completely 

disassembled when done in accordance with 

the disassembly instructions in the 

manufacturer’s engine manual; and 

(ii) The part has accumulated more than 

100 cycles-in-service since the last piece-part 

opportunity inspection, provided that the 

part was not damaged or related to the cause 

for its removal from the engine.’’

Alternative Methods of Compliance 

(g) You must perform these mandatory 

inspections using the ALS of the Instructions 

for Continued Airworthiness and the 

applicable Engine Manual unless you receive 

approval to use an alternative method of 

compliance under paragraph (h) of this AD. 

Section 43.16 of the Federal Aviation 

Regulations (14 CFR 43.16) may not be used 

to approve alternative methods of 

compliance or adjustments to the times in 

which these inspections must be performed. 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Maintaining Records of the Mandatory 

Inspections 

(i) You have met the requirements of this 

AD when you change the manufacturer’s 

Instructions for Continued Airworthiness 

ALS specified in paragraph (f) of this AD, 

and, for air carriers operating under part 121 

of the Federal Aviation Regulations (14 CFR 

part 121), when you modify your continuous 

airworthiness maintenance plan to reflect 

those changes. You do not need to record 

each piece-part inspection as compliance to 

this AD but you must maintain records of 

those inspections according to the 

regulations governing your operation. For air 

carriers operating under part 121, you may 

use either the system established to comply 

with section 121.369 or an alternative 

accepted by your principal maintenance 

inspector if that alternative: 

(1) Includes a method for preserving and 

retrieving the records of the inspections 

resulting from this AD; and 

(2) Meets the requirements of section 

121.369(c); and 

(3) Maintains the records either 

indefinitely or until the work is repeated. 

(j) These record keeping requirements 

apply only to the records used to document 

the mandatory inspections required as a 

result of revising the ALS of the Instructions 

for Continued Airworthiness as specified in 

paragraph (f) of this AD, and do not alter or 

amend the record keeping requirements for 

any other AD or regulatory requirement. 

Issued in Burlington, Massachusetts, on 

October 27, 2005. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21804 Filed 11–1–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 92–ANE–34–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc., (Formerly 

AlliedSignal, Inc. and Textron 

Lycoming) ALF502L Series and 

ALF502R Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD), AD 95–04–11, for 

Honeywell International Inc., (formerly 

AlliedSignal, Inc. and Textron 

Lycoming) ALF502L series and 

ALF502R series turbofan engines. That 

AD currently establishes stress rupture 

retirement life limits for certain third 

stage turbine discs used in conjunction 

with certain third stage turbine nozzles. 

This proposed AD would bring 

requirements forward and unchanged, 

from the previous AD for ALF502R 

series turbofan engines. Also, this 

proposed AD would establish new 

reduced stress rupture retirement life 

limits for certain part numbers (P/Ns) of 

third stage turbine disc and shaft 

assemblies installed in ALF502L series 

turbofan engines. This proposed AD 

would also require removing those same 

parts from service using a drawdown 

schedule. This proposed AD results 

from a report of failure of a third stage 

turbine disc and shaft assembly, leading 

to turbine blade release and separation 

of the exhaust nozzle. We are proposing 

this AD to prevent total loss of engine 

power, in-flight engine shutdown, 

release of turbine blades, separation of 

the exhaust nozzle, and possible damage 

to the airplane. 

DATES: We must receive any comments 

on this proposed AD by January 3, 2006. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• By mail: Federal Aviation 

Administration (FAA), New England 

Region, Office of the Regional Counsel, 

Attention: Rules Docket No. 92–ANE–

34–AD, 12 New England Executive Park, 

Burlington, MA 01803–5299. 

• By fax: (781) 238–7055. 

• By e-mail: 9-aneadcomment@faa.gov. 

Contact Honeywell Engines, Systems 

& Services, Customer Support Center, 

M/S 26–06/2102–323, P.O. Box 29003, 

Phoenix, AZ 85038–9003; telephone 

(800) 601–3099, for the service 

information identified in this proposed 

AD. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. 

FOR FURTHER INFORMATION CONTACT: 

Robert Baitoo, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; telephone: (562) 627–5245, 

fax: (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 92–

ANE–34–AD’’ in the subject line of your 

comments. If you want us to 

acknowledge receipt of your mailed 

comments, send us a self-addressed, 

stamped postcard with the docket 

number written on it; we will datestamp your postcard and mail it back to 

you. We specifically invite comments 

on the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. If a person contacts us 

verbally, and that contact relates to a 

substantive part of this proposed AD, 

we will summarize the contact and 

place the summary in the docket. We 

will consider all comments received by 

Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules 66303 

the closing date and may amend the 

proposed AD in light of those 

comments. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See 

ADDRESSES for the location. 

Discussion 

On March 2, 1995, we issued AD 95–

04–11, Amendment 39–9163 (60 FR 

11621, April 3, 1995), applicable to 

ALF502L series and ALF502R series 

turbofan engines. That AD established 

stress rupture retirement life limits for 

certain third stage turbine discs used in 

conjunction with certain third stage 

turbine nozzles. That AD resulted from 

introduction of an improved design 

third stage turbine nozzle, and a new 

reduced stress rupture retirement life 

limit for certain third stage turbine discs 

on the ALF502L series engines. That 

condition, if not corrected, could result 

in total loss of engine power, in-flight 

engine shutdown, and possible damage 

to the airplane. 

Actions Since AD 95–04–11 Was Issued 

Since we issued that AD, we received 

a report of a third stage turbine disc and 

shaft assembly failure in an ALF502L–

2C engine. The rim of the disc ruptured 

during airplane climb, resulting in 

release of turbine blades and separation 

of the exhaust nozzle. Honeywell 

International Inc. has also cited several 

other separation incidents of third stage 

turbine blades, resulting in airplane and 

engine damage. The third stage turbine 

disc and shaft assemblies involved in 

these events were all of the Honeywell 

Pre SB No. ALF502L 72–232 

configuration. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Honeywell 

International Service Bulletin (SB) No. 

ALF502 72–0004, Revision 17, dated 

January 16, 2005. That SB establishes 

new reduced service life limits for third 

stage turbine disc and shaft assemblies 

installed in ALF502L series turbofan 

engines that have operated in the Pre SB 

No. ALF502L 72–232 configuration. 

That SB also describes procedures for 

calculating the remaining service life of 

certain third stage turbine disc and shaft 

assemblies that have operated in Pre 

and Post SB No. ALF502L 72–232 

configurations. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would require: 

• Bringing requirements forward and 

unchanged from AD 95–04–11 for 

ALF502R series turbofan engines; and 

• For ALF502L series turbofan 

engines, establishing new reduced 

service life limits for third stage turbine 

disc and shaft assemblies, P/N 2–143–

030–05; P/N 2–143–030–08; P/N 2–143–

030–14; P/N 2–143–030–R21; P/N 2–

143–030–22; and P/N 2–143–030–23, 

that have operated in the Honeywell Pre 

SB No. ALF502L 72–232 configuration; 

and 

• Removing those same parts from 

service using a drawdown schedule. 

• Limiting the special flight permits 

for this AD by allowing a onetime 

special flight if the disc life limit has 

been reached. 

The proposed AD would require that 

you calculate the remaining service life 

of certain third stage turbine disc and 

shaft assemblies using the service 

information described previously. 

Costs of Compliance 

There are about 180 Honeywell 

International, Inc. ALF502L, ALF502L–

2, ALF502L–2A, ALF502L–2C, 

ALF502L–3, and ALF502R series 

turbofan engines of the affected design 

in the worldwide fleet. We estimate the 

proposed AD would affect 170 engines 

installed on airplanes of U.S. registry. 

We also estimate that it would take 

about 14 work hours per engine to 

perform the proposed actions, and that 

the average labor rate is $65 per work 

hour. The prorated cost of a replacement 

third stage turbine disc and shaft 

assembly is estimated to be $40,000. 

Based on these figures, we estimate the 

total labor cost of the proposed AD on 

U.S. operators to be $6,954,700. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

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

3. Would not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this proposal and placed 

it in the AD Docket. You may get a copy 

of this summary by sending a request to 

us at the address listed under 

ADDRESSES. Include ‘‘AD Docket No. 92–

ANE–34–AD’’ in your request. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

proposes to amend 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. The FAA amends § 39.13 by 

removing Amendment 39–9163 (60 FR 

11621, April 3, 1995) and by adding a 

new airworthiness directive to read as 

follows: 

Honeywell International Inc. (formerly 

AlliedSignal, Inc. and Textron 

Lycoming): Docket No. 92–ANE–34–AD. 

66304 Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

January 3, 2006. 

Affected ADs 

(b) This AD supersedes AD 95–04–11, 

Amendment 39–9163. 

Applicability 

(c) This AD applies to Honeywell 

International Inc., (formerly AlliedSignal, 

Inc. and Textron Lycoming) ALF502L, 

ALF502L–2, ALF502L–2A, ALF502L–2C, and 

ALF502L–3 series turbofan engines with 

third stage turbine disc and shaft assemblies 

that have operated in the Honeywell Pre SB 

No. ALF502L 72–232 configuration. This AD 

also applies to ALF502R series engines. 

These engines are installed on, but not 

limited to, BAe Systems AVRO 146 and 

Bombardier (Canadair) CL600–1A11 series 

airplanes. 

Unsafe Condition 

(d) This AD results from a report of failure 

of a third stage turbine disc and shaft 

assembly, leading to turbine blade release 

and separation of the exhaust nozzle. We are 

issuing this AD to prevent total loss of engine 

power, in-flight engine shutdown, release of 

turbine blades, separation of the exhaust 

nozzle, and possible damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

ALF502L Series Turbofan Engines 

Determination of Third Stage Turbine Disc 

and Shaft Assembly Drawdown Schedule 

(f) For ALF502L series turbofan engines, 

determine if the third stage turbine disc and 

shaft assembly is currently operating in the 

Pre SB No. ALF502L 72–232 configuration as 

follows: 

(1) If third stage turbine nozzle assembly, 

part number (P/N) 2–141–120R56/–57 is 

installed, then Honeywell SB No. ALF502L 

72–232 has been complied with. Proceed to 

the drawdown schedule in paragraph (h) of 

this AD. 

(2) If any other third stage turbine nozzle 

assembly is installed, then the engine is in 

the Pre SB No. ALF502L 72–232 

configuration. Proceed to the drawdown 

schedule in paragraph (g) of this AD. 

Drawdown Schedule for Third Stage 

Turbine Disc and Shaft Assemblies That Are 

Operating in the Pre SB No. ALF502L 72–232 

Configuration 

(g) For ALF502L series turbofan engines, 

use the drawdown schedule described in the 

following Table 1, and replace with 

serviceable parts: 

TABLE 1.—DRAWDOWN SCHEDULE FOR THIRD STAGE TURBINE DISC AND SHAFT ASSEMBLIES IN PRE SB ALF502L 72–

232 CONFIGURATION

For third stage turbine disc and shaft assembly 

P/Ns 

If hours-in-service (HIS) on the effective date 

of this AD are Then remove 

2–143–030–05 .................................................... (1) 5,200 or more HIS ...................................... Within 50 additional HIS. 

2–143–030–08 .................................................... (2) 5,001 to 5,199 HIS ..................................... Before reaching 5,250 HIS. 

2–143–030–14 .................................................... (3) 2,551 to 5,000 HIS ..................................... Within 250 additional HIS. 

2–143–030R21 ................................................... (4) 2,550 or fewer HIS ..................................... Before reaching 2,800 HIS. 

2–143–030–22.

2–143–030–23.

Determination of Drawdown Schedule for 

Third Stage Turbine Disc and Shaft 

Assemblies That Have Operated in Pre and 

Post SB No. ALF502L 72–232 Configurations 

(h) For ALF502L series turbofan engines, 

with third stage turbine disc and shaft 

assemblies converted from Pre SB No. 

ALF502L 72–232 configuration to Post SB 

No. ALF502L 72–232 configuration, do the 

following: 

(1) Determine the total HIS accumulated on 

the third stage turbine disc and shaft 

assembly at time of installation of third stage 

turbine nozzle assembly, P/N 2–141–120–

R56/–57. 

(2) If the total is 2,800 HIS or more, use the 

drawdown schedule in Table 1 of this AD to 

remove the assembly from service. 

(3) If the total is fewer than 2,800 HIS, 

calculate the remaining service life using 

paragraphs 2.A. through 2.B.(4)(i) of the 

Accomplishment Instructions of Honeywell 

SB No. ALF502 72–0004, Revision 17, dated 

January 16, 2005. 

(i) For ALF502L series turbofan engines, 

use the drawdown schedule described in the 

following Table 2 to remove the assembly 

from service: 

TABLE 2.—DRAWDOWN SCHEDULE FOR THIRD STAGE TURBINE DISC AND SHAFT ASSEMBLIES OPERATED IN PRE AND

POST SB NO. ALF502L 72–232 CONFIGURATION

For third stage turbine disc and shaft assembly 

part numbers: If HIS on the effective date of this AD are: Then: 

(1) 2–143–030–05, 2–143–030–08,2–143–030–

14.

(i) 30,000 or more HIS ..................................... Remove within 50 additional HIS. 

(ii) 27,250 to 29,999 HIS ................................. Remove within 250 additional HIS. 

(iii) Fewer than 27, 250 HIS ............................ Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17, 

dated January 16, 2005. 

(2) 2–143–030R21, 2–143–030–23 ................... (i) 24,650 or more HIS ..................................... Remove within 50 additional HIS. 

(ii) 22,150 to 24,649 HIS ................................. Remove within 250 additional HIS. 

(iii) Fewer than 22,150 HIS .............................. Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17, 

dated January 16, 2005. 

(3) 2–143–030–22 .............................................. (i) 50,000 or more HIS ..................................... Remove within 50 additional HIS. 

(ii) 49,750 to 49,999 HIS ................................. Remove within 250 additional HIS. 

(iii) Fewer than 49,750 HIS .............................. Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17, 

dated January 16, 2005. 

Federal Register / Vol. 70, No. 211 / Wednesday, November 2, 2005 / Proposed Rules 66305 

ALF502R Series Turbofan Engines 

Requirements Brought Forward, and 

Unchanged From AD 95–04–11 

(j) For ALF502R series turbofan engines, 

remove from service and replace with a 

serviceable part third stage turbine disks, P/ 

Ns 2–143–030–05, 2–143–030–08, and 2–

143–030–14, as follows: 

(1) For disks that have been installed only 

with third stage turbine nozzles P/Ns 2–141–

130–52 or 2–141–120–53, remove from 

service as follows: 

(i) For disks that have accumulated 13,220 

or more hours time in service (TIS) since new 

on April 13, 1995 (the effective date of AD 

95–04–11), within the next 80 hours TIS after 

December 11, 1990, but not to exceed the 

existing cyclic life limit. 

(ii) For disks that have accumulated less 

than 13,220 hours TIS since new on April 13, 

1995, before accumulating more than 13,300 

hours TIS since new, but not to exceed the 

existing cyclic life limit. 

(iii) Thereafter, remove disks before 

accumulating more than 13,300 hours TIS 

since new, but not to exceed the existing 

cyclic life limit. 

(2) For disks that have been installed only 

with third stage turbine nozzles, P/Ns 2–141–

120–57 or 2–141–120–R56, remove from 

service as follows: 

(i) For disks that have accumulated 27,420 

or more hours TIS since new on April 13, 

1995, within 80 hours TIS after April 13, 

1995, but not to exceed the existing cyclic 

life limit. 

(ii) For disks that have accumulated less 

than 27,420 hours TIS since new on April 13, 

1995, before accumulating more than 27,500 

hours TIS since new, but not to exceed the 

existing cyclic life limit. 

(iii) Thereafter, remove disks before 

accumulating more than 27,500 hours TIS 

since new, but not to exceed the existing 

cyclic life limit. 

(3) For disks that have been installed with 

both third stage turbine nozzles, P/Ns 2–141–

120–52 or 2–141–120–120–53, and third 

stage turbine nozzles P/Ns 2–141–120–57 or 

2–141–120–R56, remove from service as 

follows: 

(i) Determine the prorated hourly life limit 

using the procedure defined in the 

Accomplishment Instructions, Section 2.B.(2) 

of Textron Lycoming SB No. ALF502 72–

0002, Revision 22, dated December 21, 1992. 

From this prorated hourly life limit, subtract 

80 hours TIS to determine the compliance 

threshold. 

(ii) For disks that have equaled or exceeded 

the compliance threshold on April 13, 1995, 

within the next 80 hours TIS, but not to 

exceed the existing cyclic life limit. 

(iii) For disks that have accumulated fewer 

than the compliance threshold on April 13, 

1995, before accumulating more than the 

calculated prorated hourly life limit. 

(iv) Thereafter, remove disks at or before 

accumulating the prorated hourly life limit, 

but not to exceed the existing cyclic life 

limit. 

Alternative Methods of Compliance 

(k) The Manager, Los Angeles Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Special Flight Permits 

(l) Under 14 CFR part 39.23, we are 

limiting the special flight permits for this AD 

by allowing a onetime special flight if the 

disc life limit has been reached. 

Related Information 

(m) Honeywell SB No. ALF/LF A72–1085, 

Revision 1, dated January 16, 2005, pertains 

to the subject of this AD. 

Issued in Burlington, Massachusetts, on 

October 27, 2005. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21802 Filed 11–1–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

User Input to the Aviation Weather 

Technology Transfer (AWTT) Board 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Proposed rule; notice of public 

meeting. 

SUMMARY: The FAA will hold an 

informal public meeting to seek aviation 

weather user input on convective 

weather products. Details: November 10, 

2005; Orlando Orange County 

Convention Center, 9800 International 

Drive, Room N210A, Orlando, Florida 

32819, 1 p.m. to 5 p.m. The objective of 

this meeting is to provide an 

opportunity for interested Government 

and commercial sector representatives 

who use Government-provided aviation 

weather information in operational 

decision-making to provide input on 

FAA’s plans for implementing new 

convective weather products. 

DATES: The meeting will be held at the 

Orlando Orange County Convention 

Center, 9800 International Drive, Room 

N210A, Orlando, Florida 32819; Times: 

1 p.m. to 5 p.m. on November 10, 2005. 

FOR FURTHER INFORMATION CONTACT: Debi 

Bacon, Air Traffic Administration, 800 

Independence Ave., SW., Washington, 

DC 20591; telephone number (202) 385–

7705; Fax: (202) 385–7701; e-mail: 

debi.bacon@faa.gov. 

SUPPLEMENTARY INFORMATION: 

History 

In 1999, the FAA established an 

Aviation Weather Technology Transfer 

(AWTT) Board to manage the orderly 

transfer of weather capabilities and 

products from research and 

development (R&D) into operations. The 

Director of the National Airspace (NAS) 

Weather Office, Operations Planning, 

Air Traffic Organization chairs the 

AWTT Board. The board is composed of 

stakeholders in the Air Traffic and 

Aviation Safety organizations in the 

Federal Aviation Administration and 

the Office of Climate, Water and 

Weather Services, the Office of Science 

and Technology, and the National 

Center for Environmental Predictions 

(NCEP) in the National Weather Service. 

The AWTT Board meets semiannually or as needed to determine the 

readiness of weather R&D products for 

experimental use or full operational use 

for meteorologists or for end users. The 

board makes the determination based on 

technical and operational readiness, 

cost and benefits, user needs and budget 

considerations. 

FAA has the sole responsibility and 

authority to make decisions intended to 

provide a safe, secure, and efficient U.S. 

national airspace system. However, it 

behooves FAA to not make decisions in 

a vacuum. Rather, FAA is seeking 

inputs from the user community before 

decisions are finalized. 

Industry users are invited to 

participate in one-day meetings about 

three times per year to give specific 

feedback to the Government. Meetings 

will be focused on a specific domain 

(e.g. terminal, enroute) or specific 

weather phenomena (e.g. turbulence, 

convection). Meetings will include a 

time for users to provide input on 

specific weather products and aviation 

weather road maps and to surface issues 

or concerns with those products. The 

industry review sessions will be 

announced in the Federal Register and 

open to all interested parties. 

This meeting is the industry session 

focused on convective weather 

products, roadmaps and research 

activities. 

Meeting Procedures 

(a) The meeting will be informal in 

nature and will be conducted by 

representatives of the FAA 

Headquarters. 

(b) The meeting will be open to all 

persons on a space-available basis. 

Every effort was made to provide a 

meeting site with sufficient seating 

capacity for the expected participation. 

There will be neither admission fee nor 

other charge to attend and participate. 

This meeting is being held in 

conjunction with the NBAA Convention 

2005. There is a charge to attend the 

NBAA convention; however, any person