[Federal Register Volume 66, Number 235 (Thursday, December 6, 2001)]
[Rules and Regulations]
[Pages 63307-63310]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-30083]



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  Federal Register / Vol. 66, No. 235 / Thursday, December 6, 2001 / 
Rules and Regulations  

[[Page 63307]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-347-AD; Amendment 39-12528; AD 2001-24-11]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model Beech 400, 400A, and 
400T Series Airplanes, Model Mitsubishi MU-300 Airplanes, and Model 
Beech MU-300-10 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to all Raytheon Model Beech 400, 400A, and 400T series 
airplanes, Model Mitsubishi MU-300 airplanes, and Model Beech MU-300-10 
airplanes. This action requires revising the Emergency Procedures 
Section of the Airplane Flight Manual to ensure the flightcrew is 
advised of in-flight procedures in the event of loss of airspeed 
indication. Such loss of airspeed indication and the resulting adverse 
effects on certain connecting systems could result in reduced 
controllability of the airplane.

DATES: Effective December 11, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 11, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before February 4, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-347-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-347-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, Kansas 
67201-0085. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Bennett Sorensen, Aerospace Engineer, 
Flight Test Branch, ACE-117W, FAA, Wichita Aircraft Certification 
Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, 
Kansas 67209; telephone (316) 946-4165; fax (316) 946-4407.

SUPPLEMENTARY INFORMATION: The FAA has received several reports of loss 
of the pilot's and/or the co-pilot's Indicated Airspeed (IAS) display 
on certain Raytheon Model Beech 400A series airplanes. Such loss of IAS 
display may lead to loss of the altitude displays and up to 10 degrees 
of pitch error in the pilot's and/or co-pilot's attitude display. Loss 
of the Indicated Airspeed (IAS) display can also adversely affect the 
display for altitude and attitude (Attitude/Heading/Reference System 
(AHRS)), and can result in uncommanded autopilot or yaw damper 
disengagement. The reported incidents occurred between 38,000 and 
41,000 feet of altitude while the airplanes were in cruise or during 
initial descent. In the reported incidents, the altitude indication 
returned to normal at an undetermined point in the descent, and the 
airplanes landed without further incident. Investigation of those 
reports indicates that the cause of the loss of airspeed indication 
display may be due to water freezing in the pitot systems.
    Loss of airspeed indication and the resulting adverse effects on 
certain connecting systems could result in reduced controllability of 
the airplane.

Similar Models

    The pitot systems installation on Raytheon Model Beech 400, and 
400T series airplanes, Model Mitsubishi MU-300 airplanes, and Model 
Beech MU-300-10 airplanes are identical to those installed on the 
affected Model Beech 400A series airplanes. Therefore, all of these 
models may be subject to the same unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved the following Raytheon Temporary 
Changes to the FAA-approved Airplane Flight Manual:
     Beechjet 400T Temporary Change, P/N 132-590002-5TC3, dated 
November 12, 2001;
     Beechjet 400T Temporary Change, P/N 134-590002-1TC3, dated 
November 12, 2001;
     Beechjet 400A Temporary Change, P/N 128-590001-91TC5, 
dated November 12, 2001;
     Beechjet 400A Temporary Change, P/N 128-590001-95TC5, 
dated November 12, 2001;
     Beechjet 400A Temporary Change, P/N 128-590001-107TC5, 
dated November 12, 2001;
     Beechjet 400A Temporary Change, P/N 128-590001-109TC5, 
dated November 12, 2001;
     Beechjet 400A Temporary Change, P/N 128-590001-167TC7, 
dated November 12, 2001;
     Beechjet 400A Temporary Change, P/N 128-590001-169TC3, 
dated November 12, 2001;
     Beechjet 400 Temporary Change, P/N 128-590001-13BTC1, 
dated November 12, 2001;
     Beechjet 400 Temporary Change P/N 128-590001-13BTC2, dated 
November 12, 2001;
     MU-300 Diamond I Temporary Change, P/N MR-0460TC1, dated 
November 12, 2001;
     MU-300 Diamond IA Temporary Change, P/N MR-0873TC1, dated 
November 12, 2001.

[[Page 63308]]

    The documents specified above describe certain in-flight procedures 
in the event of loss of airspeed indication for the various models 
specified.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to ensure the flightcrew is advised of in-flight 
procedures in the event of loss of airspeed indication. Such loss of 
airspeed indication and the resulting adverse effects of certain 
connecting systems could result in reduced controllability of the 
airplane. This AD requires accomplishment of the actions specified in 
the Temporary AFM's described previously, or insertion of this AD into 
the Airplane Flight Manual (AFM).

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the AD is 
being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-347-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2001-24-11  Raytheon Aircraft Company (Formerly Beech): Amendment 
39-12528. Docket 2001-NM-347-AD.

    Applicability: All Model Beech 400, 400A, and 400T series 
airplanes, Model Mitsubishi MU-300 airplanes, and Model Beech MU-
300-10 airplanes; certificated in any category.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced controllability of the airplane due to loss 
of airspeed indication by ensuring that the flightcrew is advised of 
in-flight procedures in the event of loss of airspeed indication, 
accomplish the following:
    (a) Within five days after the effective date of this AD, revise 
the Emergency Procedures Section of the FAA-approved Airplane Flight 
Manual (AFM), as applicable, by inserting a copy of Raytheon 
Beechjet 400T Temporary Change, P/N 132-590002-5TC3, dated November 
12, 2001; Beechjet 400T Temporary Change, P/N 134-590002-1TC3, dated 
November 12, 2001; Beechjet 400A Temporary Change, P/N 128-590001-
91TC5, dated November 12, 2001; Beechjet 400A Temporary Change, P/N 
128-590001-95TC5, dated November 12, 2001; Beechjet 400A Temporary 
Change, P/N 128-590001-107TC5, dated November 12, 2001; Beechjet 
400A Temporary Change, P/N 128-590001-109TC5, dated November 12, 
2001; Beechjet 400A Temporary Change, P/N 128-590001-167TC7, dated 
November 12, 2001; Beechjet 400A Temporary Change, P/N 128-590001-
169TC3, dated November 12, 2001; Beechjet 400 Temporary Change, P/N 
128-590001-13BTC1, dated November 12, 2001; Beechjet 400 Temporary 
Change P/N 128-590001-13BTC2, dated November 12, 2001; MU-300 
Diamond I Temporary Change, P/N MR-0460TC1, dated November 12, 2001; 
or MU-300 Diamond IA Temporary Change, P/N MR-0873TC1, dated 
November 12, 2001; as applicable, into the AFM or by inserting a 
copy of this AD into the AFM to include the following procedures:

``Emergency Procedures (400 & MU-300)

Loss of Airspeed

    Note: If the pilot's and/or copilot's airspeed(s) are noted to 
be decreasing toward zero, refer to the AOA indicator for airspeed 
control and land at the nearest suitable airport.

1. Autopilot--Disconnect
2. Airspeed--Slow to and Maintain 0.2 AOA
3. Thrust--As Required

[[Page 63309]]

4. Speed Brakes--As Required (Slow to 0.25 AOA with speed brakes 
extended)

    Note: An AOA of 0.2 (0.25 with speed brakes extended) will yield 
an airspeed of about 210 knots. Use pitch attitude as the primary 
reference. Make small changes in pitch and wait for the AOA to 
stabilize.

When Ready for Descent

5. Seat Belts/Shoulder Harnesses--Fastened
6. Cabin Sign--As Required
7. Recognition Light--As Required
8. Anti/De-Ice Systems--As Required

Caution

    If icing conditions are anticipated during the descent and 
approach, turn ice protection systems ON as early as possible prior 
to penetrating clouds. Maintain wing anti/deice operation light ON 
(approximately 70% N2) during descent to assure proper wing anti-ice 
operation.
9. Cabin Pressure Control--Set Field Elevation + 500 Feet
10. Windshield Defog--As Required
11. Altimeters--Set

When Ready for Approach

12. Airspeed--Slow to and Maintain 0.3 AOA

    Note: Maintain 0.3 AOA throughout the configuration change to 
Flaps 10 deg. Gear Down. This will yield an airspeed of about 180 
knots.

13. Fuel Management--Check
14. N1, Landing Distance--Confirm
15. Cabin Sign--Safety
16. Windshield Anti-Ice--Low
17. Hydraulic/Nitrogen Pressure--Check
18. Engine Sync--Off
19. Flaps 10 deg.

Before Landing

20. AOA Index--Preset 1.3 V/Vs
21. Landing Gear--Down
22. Airspeed--Slow to 0.4 AOA
23. Recognition Light--Off
24. Landing Lights--As Required
25. Ignitions--On
26. Flaps--30 deg.
27. Approach Airspeed (VREF)--Slow to and Maintain 0.57 AOA

    Note: This will yield a normal approach speed of VREF (0.57 AOA) 
and normal landing distances.

Balked Landing

28. Thrust--Takeoff N1
29. Pitch Attitude--10 deg.

When Positive Climb Has Been Established

30. Flaps--10 deg.
31. Landing Gear--Up
32. Airspeed--Accelerate to 0.3 AOA
33. Flaps--Up
34. Airspeed--Accelerate and Maintain 0.2 AOA
35. Landing Lights--Ret/off

Emergency Procedures (400A & RJ-61)

Loss of Airspeed

    Note: If the pilot's, or copilot's and standby, or all three 
airspeed(s) are noted to be decreasing toward zero, refer to the 
standby attitude indicator, standby altimeter, standby heading and 
the AOA indicator for aircraft control and land at the nearest 
suitable airport. On PFD equipped airplanes, the pilot's and 
copilots altimeters, attitude displays and heading displays may be 
unreliable and the autopilot may disconnect. This may be accompanied 
by amber boxed A/S, ALT, ATT and/or HDG comparator flags. The 
comparator flags may be followed by red FAIL flags and removal of 
airspeed and altitude tapes and attitude/heading displays.

1. Autopilot--Disconnect
2. Airspeed--Slow to and Maintain 0.2 AOA
3. Thrust--As Required
4. Speed Brakes--As Required (Slow to 0.25 AOA with speed brakes 
extended)

    Note: An AOA of 0.2 (0.25 speed brakes extended) will yield an 
airspeed of about 210 knots. Use pitch attitude as primary 
reference. Make small changes in pitch attitude and wait for AOA to 
stabilize.

When Ready for Descent

5. Seat Belts/Shoulder Harnesses--Fastened
6. Cabin Sign--As Required
7. Recognition Light--As Required
8. Anti/De-Ice Systems--As Required

Caution

    If icing conditions are anticipated during the descent and 
approach, turn ice protection systems ON as early as possible prior 
to penetrating clouds. Maintain wing anti/deice operation light ON 
(approximately 70% N2) during descent to assure proper wing anti-ice 
operation.
9. Cabin Pressure Control--Set Field Elevation + 500 Feet
10. Windshield Defog--As Required
11. Altimeters--Set

When Ready for Approach

12. Airspeed--Slow to and Maintain 0.3 AOA

    Note: Maintain 0.3 AOA throughout the configuration change to 
Flaps 10 deg., Gear Down. This will yield an airspeed of about 180 
knots.

13. Fuel Management--Check
14. N1, Landing Distance--Confirm
15. Cabin Sign--Safety
16. Windshield Anti-Ice--Low
17. Hydraulic/Nitrogen Pressure--Check
18. Engine Sync--Off
19. Flaps--10 deg.

Before Landing

20. AOA Index--Preset 1.3 V/Vs
21. Landing Gear--Down
22. Airspeed--Slow to 0.4 AOA
23. Recognition Light--Off
24. Landing Lights--As Required
25. Ignitions--On
26. Flaps--30 deg.
27. Approach Airspeed (VREF) Slow to and Maintain 0.57 AOA

    Note: This will yield a normal approach speed of VREF (0.57 AOA) 
and normal landing distances.

28. Yaw Damp--Off

Balked Landing

29. Thrust--Takeoff N1
30. Pitch Attitude 10 deg.

When Positive Climb Has Been Established

31. Flaps--10 deg.
32. Landing Gear--Up
33. Yaw Damp--On
34. Airspeed--Accelerate to 0.3 AOA
35. Flaps--Up
36. Airspeed--Accelerate and Maintain 0.2 AOA
37. Landing Lights--Ret/off

Emergency Procedures 400T(T-1A)

Loss of Airspeed

    Note: If the pilot's, or copilot's and standby, or all three 
airspeed(s) are noted to be decreasing toward zero, refer to the 
standby attitude indicator, standby altimeter, standby heading and 
the AOA indicator for aircraft control and land at the nearest 
suitable airport. The pilot's and copilots altimeter's, attitude 
displays and heading displays may be unreliable and the autopilot 
may disconnect. This may be accompanied by amber boxed A/S, ALT, ATT 
and/or HDG comparator flags. The comparator flags may be followed by 
red FAIL flags on the airspeed, altitude, attitude and heading 
displays.

1. Autopilot--Disconnect
2. Airspeed--Slow to and Maintain 0.2 AOA
3. Thrust--As Required
4. Speed Brakes--As Required (Slow to 0.25 AOA with speed brakes 
extended)

    Note: An AOA of 0.2 (0.25 speed brakes extended) will yield an 
airspeed of about 210 knots. Use pitch attitude as primary 
reference. Make small changes in pitch attitude and wait for AOA to 
stabilize.

When Ready for Descent

5. Seat Belts/Shoulder Harnesses--Fastened
6. Cabin Sign--AS Required
7. Anti/De-Ice Systems--As Required

Caution

    If icing conditions are anticipated during the descent and 
approach, turn ice protection systems ON as early as possible prior 
to penetrating clouds. Maintain wing anti/deice operation light ON 
(approximately 70% N2) during descent to assure proper wing anti-ice 
operation.
8. Cabin Pressure Control--Set Field Elevation + 500 Feet
9. Windshield Defog--As Required
10. Altimeters--Set

When Ready for Approach

11. Airspeed--Slow to and Maintain 0.3 AOA

    Note: Maintain 0.3 AOA throughout the configuration change to 
Flaps 10 deg., Gear Down. This will yield an airspeed of about 180 
knots.

12. Fuel Management--Check
13. N1, Landing Distance--Confirm
14. Cabin Sign--Safety
15. Windshield Anti-Ice--Low
16. Hydraulic/Nitrogen Pressure--Check
17. Engine Sync--Off
18. Flaps--10 deg.
19. GPWS TAC and FLP ORIDE--Off

Before Landing

20. AOA Index--Preset 1.3 V/Vs
21. Landing Gear--Down

[[Page 63310]]

22. Airspeed--Slow to 0.4 AOA
23. Landing Lights--As Required
24. Ignitions--On
25. Flaps--Set for Landing
26. Approach Airspeed (VREF)--Slow to and Maintain 0.57 AOA

    Note: This will yield an approach speed of VREF (0.57 AOA) and 
normal landing distances.

27. Yaw Damp--Off

Caution

    If icing conditions are encountered during flight, the maximum 
landing flap is 10 deg. unless one of the following are met.
    The icing conditions are encountered for less than 10 minutes, 
and the RAM Air Temperature (RAT) during the encounter was warmer 
than -8 deg.C.
    A RAT of +10 deg.C, or warmer, is observed during the descent, 
approach or landing.
    If either of the above two conditions are met, Flaps 30 deg. may 
be used for landing.

Balked Landing

28. Thrust--Takeoff N1
29. Pitch Attitude--10 deg.

When Positive Climb Has Been Established

30. Flaps--10 deg.
31. Landing Gear--Up
32. Yaw Damp--On
33. Airspeed--Accelerate to 0.3 AOA
34. Flaps--Up
35. Airspeed--Accelerate and Maintain 0.2 AOA
36. Landing Lights--Ret/off

Emergency Procedures 400T(TX)

Loss of Airspeed

    Note: If the pilot's, or copilot's and standby, or all three 
airspeed(s) are noted to be decreasing toward zero, refer to the 
standby attitude indicator, standby altimeter, standby heading and 
the AOA indicator for aircraft control and land at the nearest 
suitable airport. The pilot's and copilots altimeter's, attitude 
displays and heading displays may be unreliable and the autopilot 
may disconnect. This may be accompanied by amber boxed A/S, ALT, ATT 
and/or HDG comparator flags. The comparator flags may be followed by 
red FAIL flags on the airspeed, altitude, attitude and heading 
displays.

1. Autopilot--Disconnect
2. Airspeed--Slow to and Maintain 0.2 AOA
3. Thrust--As Required
4. Speed Brakes--As Required (Slow to 0.25 AOA with speed brakes 
extended)

    Note: An AOA of 0.2 (0.25 speed brakes extended) will yield an 
airspeed of about 210 knots. Use pitch attitude as primary 
reference. Make small changes in pitch attitude and wait for AOA to 
stabilize.

When Ready for Descent

5. Seat Belts/Shoulder Harnesses--Fastened
6. Cabin Sign--As Required
7. Anti/DeIce Systems--As Required

Caution

    If icing conditions are anticipated during the descent and 
approach, turn ice protection systems ON as early as possible prior 
to penetrating clouds. Maintain wing anti/deice operation light ON 
(approximately 70% N2) during descent to assure proper wing anti-ice 
operation.
8. Cabin Pressure Control--Set Field Elevation + 500 Feet
9. Windshield Defog--As Required
10. Altimeters--Set

When Ready for Approach

11. Airspeed--Slow to and Maintain 0.3 AOA

    Note: Maintain 0.3 AOA throughout the configuration change to 
Flaps--10 deg., Gear Down. This will yield an airspeed of about 180 
knots.

12. Fuel Management--Check
13. N1, Landing Distance--Confirm
14. Cabin Sign--Safety
15. Windshield Anti-Ice--Low
16. Hydraulic/Nitrogen Pressure--Check
17. Engine Sync--Off
18. Flaps--10 deg.

Before Landing

19. AOA Index--Preset 1.3 V/Vs
20. Landing Gear--Down
21. Airspeed--Slow to 0.4 AOA
22. Landing Lights--As Required
23. Ignitions--On
24. Flaps--30 deg.
25. Approach Airspeed (VREF)--Slow to and Maintain 0.57 AOA

    Note: This will yield a normal approach speed of VREF (0.57 AOA) 
and normal landing distances.

26. Yaw Damp--Off

Balked Landing

26. Thrust--Takeoff N1
27. Pitch Attitude 10 deg.

When Positive Climb Has Been Established

29. Flaps 10 deg.
30. Landing Gear--Up
31. Yaw Damp--On
32. Airspeed--Accelerate to 0.3 AOA
33. Flaps-- 0 deg.
34. Airspeed--Accelerate and Maintain 0.2 AOA
35. Landing Lights--Ret/off''

    Note 1: When a previously specified Temporary AFM revision has 
been incorporated into the general revisions of the AFM, the general 
revision may be inserted in the AFM, provided the information 
contained in the general revision is identical to that specified in 
the specified Temporary AFM revision.

Alternative Methods of Compliance

    (b) 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, Wichita Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Wichita ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (d) Except as provided by paragraph (a) of this AD, the AFM 
revision shall be done in accordance with Raytheon Beechjet 400T 
Temporary Change, P/N 132-590002-5TC3, dated November 12, 2001; 
Beechjet 400T Temporary Change, P/N 134-590002-1TC3, dated November 
12, 2001; Beechjet 400A Temporary Change, P/N 128-590001-91TC5, 
dated November 12, 2001; Beechjet 400A Temporary Change, P/N 128-
590001-95TC5, dated November 12, 2001; Beechjet 400A Temporary 
Change, P/N 128-590001-107TC5, dated November 12, 2001; Beechjet 
400A Temporary Change, P/N 128-590001-109TC5, dated November 12, 
2001; Beechjet 400A Temporary Change, P/N 128-590001-167TC7, dated 
November 12, 2001; Beechjet 400A Temporary Change, P/N 128-590001-
169TC3, dated November 12, 2001; Beechjet 400 Temporary Change, P/N 
128-590001-13BTC1, dated November 12, 2001; Beechjet 400 Temporary 
Change P/N 128-590001-13BTC2, dated November 12, 2001; MU-300 
Diamond I Temporary Change, P/N MR-0460TC1, dated November 12, 2001; 
or MU-300 Diamond IA Temporary Change, P/N MR-0873TC1, dated 
November 12, 2001; as applicable. This incorporation by reference 
was approved by the Director of the Federal Register in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from 
Raytheon Aircraft Company, Department 62, P.O. Box 85, Wichita, 
Kansas 67201-0085. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on December 11, 2001.


    Issued in Renton, Washington, on November 26, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-30083 Filed 12-5-01; 8:45 am]
BILLING CODE 4910-13-U