[Federal Register Volume 67, Number 207 (Friday, October 25, 2002)]
[Proposed Rules]
[Pages 65524-65526]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-27169]



[[Page 65524]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 60

[Docket No. FAA-2002-12461; Notice No. 02-11]
RIN 2120-AH07


Flight Simulation Device Initial and Continuing Qualification and 
Use; Correction

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM); correction.

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SUMMARY: This document makes a correction to the proposed rule 
published in the Federal Register on September 25, 2002 (67 FR 60284), 
which proposes to establish flight simulation device qualification 
requirements in a new part. The FAA inadvertently omitted a table in 
the original NPRM.

DATES: Send your comments on or before December 24, 2002.

ADDRESSES: Address your comments to the Docket Management System, U.S. 
Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., 
Washington, DC 20590-0001. You must identify the docket number FAA-
2002-12461 at the beginning of your comments, and you should submit two 
copies of your comments. If you wish to receive confirmation that FAA 
received your comments, include a self-addressed, stamped postcard.
    You may also submit comments through the Internet to http://dms.dot.gov. You may review the public docket containing comments to 
these proposed regulations in person in the Dockets Office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Dockets Office is on the plaza level of the NASSIF Building at the 
Department of Transportation at the above address. Also, you may review 
public dockets on the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Edward Cook, National Simulator 
Program Staff (AFS-205), Flight Standards Service, Federal Aviation 
Administration, 1701 Columbia Avenue, College Park, GA 30337; telephone 
(404) 305-6100.

SUPPLEMENTARY INFORMATION: On September 25, 2002, the FAA published 
Notice No. 02-11, Flight Simulation Device Initial and Continuing 
Qualification and Use (67 FR 60284). The NPRM proposed to amend the 
regulations to establish flight simulation device qualification 
requirements for all certificate holders in a new part. The FAA 
inadvertently omitted a table entitled ``Table of Alternative Source 
Data FTD Levels 2, 3, and 5. Single Engine (Turbo-Propeller) 
Airplane.'' The table provides a range of performance that is typical 
for single engine, turbo-propeller powered airplanes for the indicated 
objective tests located in Attachment 2 of appendix B to part 60.

Correction

    In proposed rule FR Doc. 02-14785, published on September 25, 2002 
(67 FR 60284), make the following corrections:

PART 60--[CORRECTED]

Appendix B to part 60--[Corrected]
    1. On page 60403, in Attachment 2 to appendix B to part 60, 
immediately following Figure 6. Small, Multi-Engine (Reciprocating) 
Airplane, Rudder Pedal Position vs. Force, add the following table:
Attachment 2 to appendix B to part 60--Flight Training Device (FTD) 
Objective Tests
* * * * *

 Table of Alternative Source Data FTD Levels 2, 3, and 5. Single Engine
                       (Turbo-Propeller) Airplane
------------------------------------------------------------------------
                             QPS Requirement
-------------------------------------------------------------------------
    Applicable Test and Test Number        Authorized Performance Range
------------------------------------------------------------------------
2. Performance
----------------------------------------
    a. Takeoff.
----------------------------------------
    (1) Ground acceleration time; brake  20-30 Seconds.
     release to liftoff speed.
----------------------------------------
    b. Climb.
----------------------------------------
    (1) Normal climb with nominal gross  Climb airspeed = 95-115 knots.
     weight, at best rate-of-climb       Climb rate = 800-1800 fpm (4-9
     airspeed.                            m/sec).
----------------------------------------
    c. Ground Deceleration.
----------------------------------------
    (1) Deceleration time from 80 knots  20-35 Seconds.
     to zero; with a nominal gross
     weight; using wheel brakes on a
     dry runway.
----------------------------------------
    d. Engines.
----------------------------------------
    (1) Acceleration; idle to takeoff    4-8 Seconds.
     power.
----------------------------------------
    (2) Deceleration; takeoff power to   3-7 Seconds.
     idle.
----------------------------------------
3. Handling Qualities.
----------------------------------------
    a. Static Control Checks.
----------------------------------------
    (1)(b) Column position vs. force...  Plot of Column Position vs.
                                          Force must fall within the
                                          shaded areas shown in Figure 7
                                          of this appendix (Single
                                          Engine [Turbo-Propeller]
                                          Airplanes).
----------------------------------------

[[Page 65525]]

 
    (2)(b) Wheel position vs. force....  Plot of Wheel Position vs.
                                          Force must fall within the
                                          shaded areas shown in Figure 8
                                          of this appendix (Single
                                          Engine [Turbo-Propeller]
                                          Airplanes).
----------------------------------------
    (3)(b) Pedal position vs. force....  Plot of Rudder Pedal Position
                                          vs. Force must fall within the
                                          shaded areas shown in Figure 9
                                          of this appendix (Single
                                          Engine [Turbo-Propeller]
                                          Airplanes).
----------------------------------------
    (4) Nosewheel steering force.......  Plot of Rudder Pedal Position
                                          vs. Force must fall within the
                                          shaded areas shown in Figure 9
                                          of this appendix (Single
                                          Engine [Turbo-Propeller]
                                          Airplanes).
----------------------------------------
    (5) Rudder pedal steering            10-30 degrees of nosewheel
     calibration with full rudder pedal   angle, both sides of neutral.
     travel.
----------------------------------------
    (8) Brake pedal position vs. force;  50-100 lbs (22-44 daN) of
     at maximum pedal deflection.         force.
----------------------------------------
    b. Longitudinal.
----------------------------------------
    (1) Power change force.
        (a) Trim for straight and level  8 lbs (3.5 daN) of Push force
         flight at 80% of normal cruise   to 8 lbs (3.5 daN) of Pull
         airspeed with necessary power.   force.
         Reduce power to flight idle.
         Do not change trim or
         configuration. After
         stabilized, record column
         force necessary to maintain
         original airspeed; or
----------------------------------------
        (b) Trim for straight and level  12-22 lbs (5.3-9.7 daN) of
         flight at 80% of normal cruise   force (Push).
         airspeed with necessary power.
         Add power to maximum setting.
         Do not change trim or
         configuration. After
         stabilized, record column
         force necessary to maintain
         original airspeed.
----------------------------------------
    (2) Flap/slat change force.
        (a) Trim for straight and level  5-15 lbs (2.2-6.6 daN) of force
         flight with flaps fully          (Pull).
         retracted at a constant
         airspeed within the flaps-
         extended airspeed range. Do
         not adjust trim or power.
         Extend the flaps to 50% of
         full flap travel. After
         stabilized, record stick force
         necessary to maintain original
         airspeed; or
----------------------------------------
        (b) Trim for straight and level  5-15 lbs (2.2-6.6 daN) of force
         flight with flaps extended to    (Push).
         50% of full flap travel, at a
         constant airspeed within the
         flaps-extended airspeed range.
         Do not adjust trim or power.
         Retract the flaps to zero
         (fully retracted). After
         stabilized, record stick force
         necessary to maintain original
         airspeed.
----------------------------------------
    (3) Gear change force.
        (a) Trim for straight and level  2-12 lbs (0.88-5.3 daN) of
         flight with landing gear         force (Pull).
         retracted at a constant
         airspeed within the landing
         gear-extended airspeed range.
         Do not adjust trim or power.
         Extend the landing gear. After
         stabilized, record stick force
         necessary to maintain original
         airspeed; or
----------------------------------------
        (b) Trim for straight and level  2-12 lbs (0.88-5.3 daN) of
         flight with landing gear         force (Push).
         extended, at a constant
         airspeed within the landing
         gear-extended airspeed range.
         Do not adjust trim or power.
         Retract the landing gear.
         After stabilized, record stick
         force necessary to maintain
         original airspeed..
----------------------------------------
    (4) Gear and flap operating times.
        (a) Extend gear................  2-12 seconds.
----------------------------------------
        (b) Retract gear...............  2-12 seconds.
----------------------------------------
        (c) Extend flaps, zero to 50%    (c) 3-13 seconds.
         travel.
----------------------------------------
        (d) Retract flaps, 50% travel    (d) 3-13 seconds.
         to zero.
----------------------------------------
    (5) Longitudinal trim..............  Must be able to trim
                                          longitudinal stick force to
                                          ``zero'' in each of the
                                          following configurations: (a)
                                          cruise; (b) approach; and (c)
                                          landing.
----------------------------------------
    (7) Longitudinal static stability..  Must exhibit positive static
                                          stability.
----------------------------------------

[[Page 65526]]

 
    (8) Stall warning (actuation of
     stall warning device) with nominal
     gross weight; wings level; clean
     configuration, and a deceleration
     rate of approximately one (1) knot
     per second.
        (a) Landing configuration......  60-90 knots; +/- 5 degrees of
                                          bank.
----------------------------------------
        (b) Clean configuration........  Landing configuration speed, +
                                          10-20 percent.
----------------------------------------
    (9)(b) Phugoid dynamics............  Must have a phugoid with a
                                          period of 30-60 seconds; and
                                          may not reach \1/2\ or double
                                          amplitude in less than 2
                                          cycles.
----------------------------------------
    c. Lateral Directional.
----------------------------------------
    (1) Roll response.
        Roll rate must be measured       Must have a roll rate of 6-40
         through at least 30 degrees of   degrees/second.
         roll. Aileron control must be
         deflected 50 percent of
         maximum travel.
----------------------------------------
    (2) Response to roll controller
     step input.
        Trim for straight and level      Roll rate must decrease to not
         flight at nominal gross weight   more than 10 percent of the
         and approach airspeed. Roll      roll rate achieved, within 1-3
         into a 30 degree bank turn and   seconds of control release.
         stabilize. When ready, input a
         50 percent aileron control
         opposite to the direction of
         turn. When reaching zero bank
         angle, rapidly neutralize the
         aileron control and release.
         Record the response from at
         least 2 seconds prior to the
         initiation of control input
         opposite to the direction of
         turn until at least 20 seconds
         after neutralization of the
         controls.
----------------------------------------
    (3)(a) and (b) Spiral stability.
        Cruise configuration and normal  Initial bank angle (+/- 5
         cruise airspeed. Establish a     degrees) after 20 seconds.
         20-30 degree bank. When
         stabilized, neutralize the
         aileron control and release.
         Must be completed in both
         directions of turn.
----------------------------------------
    (4)(b) Rudder response.
        Use 50 percent of maximum        6-12 degrees/second yaw rate.
         rudder deflection. Applicable
         to approach or landing
         configuration.
----------------------------------------
    (5)(b) Dutch roll, yaw damper off.
        Applicable to cruise and         A period of 2-5 seconds; and \1/
         approach configurations.         2\-3 cycles.
----------------------------------------
    (6) Steady state sideslip.
        Use 50 percent rudder            2-10 degrees of bank; 4-10
         deflection; Applicable to        degrees of sideslip; and 2-10
         approach and landing             degrees of aileron.
         configurations.
----------------------------------------
4. Cockpit Instrument Response.
----------------------------------------
Instrument systems response to an        300 milliseconds or less.
 abrupt pilot controller input. One
 test is required in each axis (pitch,
 roll, and yaw).
------------------------------------------------------------------------

* * * * *

    Issued in Washington, DC, on October 18, 2002.
Donald P. Byrne,
Assistant Chief Counsel for Regulations.
[FR Doc. 02-27169 Filed 10-24-02; 8:45 am]
BILLING CODE 4910-13-P