49982 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules 

Issued in Renton, Washington, on August 

9, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19925 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0695; Directorate 

Identifier 2011–NM–264–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Saab AB, Saab Aerosystems Model 340A 

(SAAB/SF340A) and SAAB 340B 

airplanes modified by Supplemental 

Type Certificate SA7971SW. This 

proposed AD was prompted by reports 

of smoke, a burning odor, and possible 

fire in the flight deck and cabin of the 

airplane, which was caused by brushes 

wearing beyond their limits, in the air 

conditioning motor. This proposed AD 

would require an inspection to 

determine if a certain air compressor 

motor is installed, an inspection to 

determine the age of a certain 

compressor hour meter since new or 

overhauled, and repetitive replacement 

of the brushes on affected air 

conditioning compressor motor units. 

As an option to the replacement, this 

proposed AD allows pulling the air 

conditioning circuit breaker and adding 

a placard. We are proposing this AD to 

detect and correct worn brushes 

contacting the commutator, which could 

result in a fire under the cabin floor 

with no means to detect or extinguish 

the fire. 

DATES: We must receive comments on 

this proposed AD by September 30, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Thiele, Aerospace Engineer, 

Special Certification Office, ASW–190, 

FAA, 2601 Meacham Boulevard, Fort 

Worth, TX 76137; phone: (817) 222– 

5229; fax: (817) 222–5785; email: 

gregory.thiele@faa.gov. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0695; Directorate Identifier 2011– 

NM–264–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received reports of smoke, a 

burning odor, and possible fire in the 

flight deck and cabin of the airplane, 

which was caused by brushes wearing 

beyond their limits, in the air 

conditioning motor. The rivets in the 

brush contacted the commutator, which 

caused sparks (the ignition source). The 

air conditioners (two units) are located 

under the floor, forward of the wing 

box. There is no fire detection or fire 

extinguishing equipment in the 

installed location. This condition (worn 

brushes contacting the commutator), if 

not corrected, could result in a fire 

under the cabin floor with no means to 

detect or extinguish the fire. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require an 

inspection to determine if a certain air 

compressor motor is installed, an 

inspection to determine the age of a 

certain compressor hour meter since 

new or overhauled, and repetitive 

replacement of the brushes on affected 

air conditioning compressor motor 

units. As an option to the replacement, 

this proposed AD allows pulling the air 

conditioning circuit breaker and adding 

a placard. This proposed AD also 

requires sending the inspection results 

to the FAA. 

This proposed AD contains detailed 

steps to address the unsafe condition 

rather than referring to service 

information. However, under the 

provisions of paragraph (p) of this 

proposed AD, operators may request 

approval of an alternative method of 

compliance (AMOC), if sufficient data 

are submitted to substantiate that the 

AMOC would provide an acceptable 

level of safety. 

Interim Action 

We consider this proposed AD 

interim action. The inspection reports 

that would be required by this proposed 

AD will enable us to obtain better 

insight into the nature, cause, and 

extent of the brush wear, and eventually 

to develop final action to address the 

unsafe condition. Once final action has 

been identified, we might consider 

further rulemaking. 

Costs of Compliance 

We estimate that this proposed AD 

affects 23 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

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Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules 49983 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection, drive motor assembly brush replacement; and parts return 

and report.

11 work-hours × $85 per 

hour = $935 per replacement cycle.

$252 per replacement 

cycle.

$1,187 per replacement 

cycle.

$27,301 per replacement 

cycle. 

Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to be 

approximately 5 minutes per response, 

including the time for reviewing 

instructions, completing and reviewing 

the collection of information. All 

responses to this collection of 

information are mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at: 800 

Independence Ave. SW., Washington, 

DC 20591, Attn: Information Collection 

Clearance Officer, AES–200. 

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 proposed 

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 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 this 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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA 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 adding 

the following new airworthiness 

directive (AD): 

Saab AB, Saab Aerosystems: Docket No. 

FAA–2013–0695; Directorate Identifier 

2011–NM–264–AD. 

(a) Comments Due Date 

We must receive comments by September 

30, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Saab AB, Saab 

Aerosystems Model 340A (SAAB/SF340A) 

and SAAB 340B airplanes, certificated in any 

category, that have been modified as 

specified in Supplemental Type Certificate 

SA7971SW (http://rgl.faa.gov/Regulatory_

and_Guidance_Library/rgstc.nsf/0/

CE3676EDFD53938785256CC

20058E501?Open

Document&Highlight=sa7971sw). 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 21, Air Conditioning. 

(e) Unsafe Condition 

This AD was prompted by reports of 

smoke, a burning odor, and possible fire in 

the flight deck and cabin of the airplane, 

which were caused by brushes wearing 

beyond their limits, in the air conditioning 

motor. We are issuing this AD to detect and 

correct worn brushes contacting the 

commutator, which could result in a fire 

under the cabin floor with no means to detect 

or extinguish the fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Part Number (P/N) Inspection 

Within 30 days or 10 flight hours after the 

effective date of this AD, whichever occurs 

first: Inspect the air conditioner (A/C) 

compressor motor to determine if P/N 

1134104–1 is installed. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number of the A/ 

C compressor motor can be conclusively 

determined from that review. 

(h) Inspection of Compressor Hour Meter 

and Maintenance Records 

If, during the inspection required by 

paragraph (g) of this AD, any A/C compressor 

motor is found having P/N 1134104–1: 

Within 30 days or 10 flight hours after the 

effective date of this AD, whichever occurs 

first, determine the hour reading on the A/ 

C compressor hour meter as specified in 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Inspect the number of hours on the A/ 

C compressor hour meter. 

(2) Check the airplane logbook for any 

entry for replacing the A/C compressor motor 

brushes with new brushes, or for replacing 

the compressor motor or compressor 

condenser module assembly (pallet) with a 

motor or assembly that has new brushes. 

(i) If the logbook contains an entry for 

replacement of parts as specified in 

paragraph (h)(2) of this AD, determine the 

number of hours on the A/C compressor 

motor brushes by comparing the number of 

hours on the compressor motor since 

replacement and use this number in lieu of 

the number determined in paragraph (h)(1) of 

this AD. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

49984 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules 

(ii) If, through the logbook check, the 

number of hours on the A/C compressor 

motor brushes cannot be positively 

determined as specified in paragraph (h)(2) of 

this AD, use the number of hours on the A/ 

C compressor hour meter determined in 

paragraph (h)(1) of this AD, or assume the 

brushes have over 500 hours time-in-service. 

(i) Replacement 

Except as provided by paragraph (k) of this 

AD: Using the hour reading on the A/C 

compressor hour meter determined in 

paragraph (h) of this AD, replace the A/C 

compressor motor brushes with new brushes 

at the later of the times specified in 

paragraphs (i)(1) and (i)(2) of this AD. 

Thereafter, repeat the replacement of the A/ 

C compressor motor brushes at intervals not 

to exceed every 500 hours time-in-service on 

the A/C compressor motor. Do the 

replacement in accordance with the actions 

specified in paragraph (j) of this AD. 

(1) Before or when the A/C compressor 

motor reaches a total of 500 hours time-inservice. Or, 

(2) Before further flight after the inspection 

required by paragraph (h) of this AD. 

(j) Motor Brush Replacement Instructions 

Do the actions specified in paragraphs (j)(1) 

through (j)(23) of this AD to replace the 

compressor motor brushes as required by 

paragraph (i) of this AD: 

(1) New brushes may be installed by first 

level maintenance personnel only under the 

conditions listed in paragraphs (j)(1)(i) 

through (j)(1)(iv) of this AD. If these 

conditions are not met, deactivate the A/C in 

accordance with paragraph (k)(1) of this AD 

until the conditions listed in paragraphs 

(j)(1)(i) through (j)(1)(iv) of this AD are met, 

or the entire compressor motor is replaced. 

(i) Motor was operating correctly prior to 

brush replacement. 

(ii) The motor is tested to verify proper 

operation and does not show any defects that 

would require motor replacement. 

(iii) Only approved vendor brushes are 

used (P/N 1251171). 

(iv) Brushes are installed, seated, and 

tested in accordance with paragraphs (j)(2) 

through (j)(23) of this AD. 

(2) Verify all electrical power is off to the 

system. 

(3) Remove all access panels and exhaust 

ducts to gain access to the drive motor. 

(4) Disconnect power leads from motor 

terminals (1/4–28). Tag the positive lead. 

(5) Remove condenser support bracket to 

provide access to brush cover fasteners and 

remove motor cuff shroud. 

(6) Loosen and unsnap brush cover 

assembly. Remove from the motor. 

(7) Verify all power is off, and that all 

panels, shrouds, brackets, and fairings are 

removed. 

(8) With a stiff wire hook or scribe, lift 

brush spring from holder and remove each 

worn brush set until all four sets are 

removed. 

(9) Remove brush shunt wire terminal 

screw. Continue this step until all four 

screws are removed. 

(10) With brushes removed and using shop 

air at 30–40 pounds per square inch gauge 

(psig) and nozzle, blow out as much carbon 

and/or copper dust as possible from the 

commutator, armature, and field windings. 

Purge from the commutator end of the motor. 

(11) Install each new brush set by lifting 

brush springs, sliding brush into holder (with 

brush leading edge in direction of motor 

rotation) and lightly releasing the brush 

spring on the brush. (See Figure 1 to 

paragraph (m)(2)(vii) of this AD). CAUTION: 

Do not allow brush spring to strike hard into 

place or damage to brush may result. 

(12) Verify that the brush seats flat on the 

commutator and that no binding in the 

holder is present. Align brush spring in 

center of brush groove. 

(13) Install terminal screw and lock washer 

on brush shunt lead and other leads and 

tighten. Repeat this step for other brush sets. 

Torque to 15–20 in.-lbs. CAUTION: Do not 

cross thread or over torque brush lead screws 

or thread damage may result. 

(14) Seat new brushes in accordance with 

paragraph (j)(15) of this AD. All new brushes 

must be seated to assure proper motor 

operation and/or performance. 

(15) Brush Seating Procedure: Cut a 7 inch 

long by 1.5 inch wide (±0.125 inch, both 

dimensions) strip of 400–500 grit sand paper 

and place, with rough side out, on 

commutator. Secure one end of the paper to 

the commutator with masking tape in a 

manner such that the taped end will lead in 

the direction of shaft rotation (counterclockwise looking at fan end). The other end 

will remain loose and overlap the taped end. 

Raise each brush momentarily while rotating 

the shaft until the taped end passes under 

each brush. After the sand paper is properly 

located tight against the commutator and 

encompasses all brush surface areas, 

carefully rotate the armature, by hand, in the 

normal direction of rotation until a full seat 

is obtained on each new brush. Three or four 

rotations is usually adequate. Excessive 

seating is not advised. Brush life may be 

reduced. 

(16) Remove sand paper and blow out all 

carbon dust from the commutator and brush 

area. CAUTION: Eye, nose and throat 

protection must be worn during this 

procedure. 

(17) Carefully lay brush shunt leads in 

position such as to prevent any shorting 

problems. Leads must be able to easily follow 

brush and spring movement as brush wear 

occurs. 

(18) Replace brush cover and attach motor 

power cables, if required. 

(19) Replace all bracketry and hardware 

removed to access motor. 

(20) Assure that brackets are properly 

installed, cooling fan does not interfere with 

shroud, motor drive belt aligned/tensioned, 

and belt cover is installed. 

(21) The motor should be tested to verify 

proper operation. Therefore, connect ground 

power source or verify aircraft power is on 

and turn system on. 

(22) Run system for a minimum of 15 

minutes to seat brushes and check motor 

operation. 

(23) Turn system and aircraft power off. 

System is ready for use. 

(k) Deactivation/Reactivation 

(1) In lieu of replacing the A/C compressor 

motor brushes as required by paragraphs (i) 

and (j) of this AD, before further flight, 

deactivate the A/C by doing the actions 

specified in paragraph (k)(1)(i) or (k)(1)(ii) of 

this AD, as applicable. 

(i) Single System: Pull the compressor 

control circuit breaker (cockpit right-hand 

10VU panel, ‘‘REAR AIR COND’’); install a 

placard by the A/C selection switch (copilot’s side panel) prohibiting use of the air 

conditioner; and document deactivation of 

the system in the airplane logbook referring 

to this AD as the reason for deactivation. 

(ii) Dual System: Pull the compressor 

control circuit breakers (cockpit right-hand 

10VU panel, ‘‘REAR AIR COND,’’ and 

cockpit left-hand 9VU panel, ‘‘FWD AIR 

COND’’); install a placard (or placards) by the 

A/C selection switches (co-pilot’s side panel) 

prohibiting use of the air conditioners; and 

document deactivation of the system in the 

airplane logbook referring to this AD as the 

reason for deactivation. 

(2) If an operator chooses to deactivate the 

system and then later chooses to return the 

airplane to service: Before returning the A/C 

system to service and removing the 

placard(s), do the inspection specified in 

paragarph (g) of this AD, and, as applicable, 

the inspection specified in paragraph (h) of 

this AD, and the replacements specified in 

paragraph (i) of this AD at the times specified 

in paragraph (i) of this AD. 

(l) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install an A/C compressor motor 

having P/N 1134104–1 on any airplane, 

unless the inspection specified in paragraph 

(h) of this AD has been done, and the 

replacements specified in paragraph (i) of 

this AD are done at the times specified in 

paragraph (i) of this AD. 

(m) Reporting Requirement 

Submit a report of the results of the 

determination of hours required by paragraph 

(h) of this AD to the Special Certification 

Office, ASW–190, Attn: Gregory Thiele, 

Aerospace Engineer, 2601 Meacham 

Boulevard, Fort Worth, TX 76137; or email 

to: 9-ASW-190-COS@faa.gov. The report 

must include the information specified in 

paragraphs (m)(1) through (m)(4) of this AD. 

(1) The model and serial number of the 

airplane. 

(2) The elapsed amount of flight hours 

since the last brush/motor replacement, if 

known. 

(3) The amount of hours on the hour meter 

of the A/C compressor motor. 

(4) The amount of wear on the brushes 

(including overall length and total calculated 

wear), calculated as specified in paragraphs 

(m)(4)(i) through (m)(4)(ix) of this AD. 

(i) Verify all electrical power is off to 

system. 

(ii) Remove all access panels and exhaust 

ducts to gain access to the drive motor. 

(iii) Disconnect power leads from motor 

terminals (1/4–28). Tag positive lead. 

(iv) Remove condenser support bracket to 

provide access to brush cover fasteners and 

remove motor cuff shroud. 

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Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules 49985 

(v) Loosen and unsnap brush cover 

assembly. Remove from motor. 

(vi) With wire hook or scribe, lift brush 

spring and remove brush. 

(vii) Measure each brush as shown in 

figure below and record values. 

(viii) Using the brush with the shortest 

measured length calculate the wear by 

subtracting the measured value from 1.000 

inch. 

(ix) Replace brushes in accordance with 

the instructions specified in paragraphs (j)(9) 

through (j)(23) of this AD. 

(n) Reporting Compliance Time 

Submit the report required by paragraph 

(m) of this AD at the applicable time 

specified in paragraph (m)(1) or (m)(2) of this 

AD. 

(1) If the determination of hours was done 

on or after the effective date of this AD: 

Submit the report within 30 days after the 

inspection. 

(2) If the determination of hours was done 

before the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

(o) Special Flight Permit 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

an appropriately rated repair station, 

provided that the A/C is deactivated as 

specified in paragraph (k)(1) of this AD on 

airplanes on which the A/C has been 

operated for 500 hours or more, and 

replacement brushes are not available. 

(p) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Special Certification 

Office, ASW–190, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the Special Certification 

Office, send it to the attention of the person 

identified in the Related Information section 

of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(q) Related Information 

For more information about this AD, 

contact Gregory Thiele, Aerospace Engineer, 

Special Certification Office, ASW–190, FAA, 

2601 Meacham Boulevard, Fort Worth, TX 

76137; phone: (817) 222–5229; fax: (817) 

222–5785; email: gregory.thiele@faa.gov. 

Issued in Renton, Washington, on August 

9, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19926 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0641; Airspace 

Docket No. 13–AGL–7] 

Proposed Establishment of Class E 

Airspace; Sisseton, SD 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class E airspace at Sisseton, 

SD. Controlled airspace is necessary to 

accommodate new Standard Instrument 

Approach Procedures (SIAP) at Sisseton 

Municipal Airport. The FAA is taking 

this action to enhance the safety and 

management of Instrument Flight Rules 

(IFR) operations for SIAPs at the airport. 

DATES: Comments must be received on 

or before September 30, 2013. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue SE., West Building, 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. You must 

identify the docket number FAA–2013– 

0641/Airspace Docket No. 13–AGL–7, at 

the beginning of your comments. You 

may also submit comments through the 

Internet at http://www.regulations.gov. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office between 

9:00 a.m. and 5:00 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone 1–800– 

647–5527), is on the ground floor of the 

building at the above address. 

FOR FURTHER INFORMATION CONTACT: 

Scott Enander, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone: 817–321– 

7716. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 


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