[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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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
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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.
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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