[Federal Register Volume 67, Number 20 (Wednesday, January 30, 2002)]
[Rules and Regulations]
[Pages 4346-4348]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-1965]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-382-AD; Amendment 39-12617; AD 2002-01-23]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model Beech 400, 400A, and 
400T Series Airplanes; Model Beech MU-300-10 Airplanes; and Model 
Mitsubishi MU-300 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 certain Raytheon Model Beech 400, 400A, and 400T 
series airplanes; Model Beech MU-300-10 airplanes; and Model Mitsubishi 
MU-300 airplanes. This action requires repetitive inspections to detect 
cracking in the radius of the cutout of the aft flange of the left 
engine forward carry-through mount bracket, and replacement with a new 
bracket and fitting if necessary. This action is necessary to prevent 
failure of the engine mount and possible loss of the engine, and 
consequent loss of control of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective February 14, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 14, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before April 1, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-382-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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-382-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: David Ostrodka, Senior Aerospace 
Engineer, Wichita Aircraft Certification Office, 1801 Airport Road, 
Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 
946-4129; fax (316) 946-4407.

SUPPLEMENTARY INFORMATION: The FAA has been advised that certain engine 
mounts on affected airplanes have developed cracks. One operator 
discovered cracking during a routine inspection on the aft flange of 
the left engine forward carry-through mount bracket. Additional 
airplanes were subsequently inspected, and cracking was discovered in 
the same location on four airplanes. At the time of the crack findings, 
all of those airplanes had accumulated between 2,000 and 3,000 total 
flight hours, and all were equipped with thrust reversers. The cracks 
originate in the radius of the cutout of the aft flange of the engine 
mount brackets. The purpose of the cutout is to provide clearance for 
certain engine components. Because all of these airplanes were equipped 
with thrust reversers, it was initially determined that the condition 
would be found only on airplanes with thrust reversers. However, 
similar cracking was later discovered on a number of airplanes without 
thrust reversers. The cause of the cracking has not been determined. 
This condition, if not corrected, could result in failure of the engine 
mount and possible loss of the engine, and consequent loss of control 
of the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Raytheon Safety Communique No. 
189, Revision 1, dated January 2002, which describes procedures for a 
one-time visual inspection to detect evidence of cracking of the left 
engine forward carry-through mount bracket, and a subsequent one-time 
fluorescent penetrant inspection to detect cracking

[[Page 4347]]

in the same area. The communique recommends immediate replacement of 
any cracked bracket with a new bracket and fitting.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Raytheon Model Beech 400, 400A, and 400T 
series airplanes; Model Beech MU-300-10 airplanes; and Model Mitsubishi 
MU-300 airplanes of the same type design, this AD is being issued to 
prevent failure of the engine mount and possible loss of the engine, 
and consequent loss of control of the airplane. This AD requires 
repetitive inspections to detect cracking in the radius of the cutout 
of the aft flange of the left engine forward carry-through mount 
bracket, and replacement with a new bracket and fitting if necessary. 
The actions are required to be accomplished in accordance with the 
service information described previously, except as discussed below.

Requirements for Ferry Flight Permit

    The FAA has determined that a ferry flight permit, if granted, must 
include certain limitations for airplanes equipped with thrust 
reversers, due to the increased loads and vibration levels associated 
with thrust reverser operation.

Differences Between AD and Relevant Service Information

    The applicability of this AD and the manufacturer's Safety 
Communique No. 189 are identical with the exception of one serial 
number. For Beech MU-300-10 airplanes, the communique specifies serial 
numbers A1001SA through 1010SA inclusive. The type certification data 
sheet for this model specifies A1011SA as the last serial number. The 
FAA assumes serial number A1011SA may have been converted to a 
different model and reidentified and therefore has determined that it 
is necessary to include serial number A1011SA in the applicability of 
this AD to ensure the inclusion of all airplanes subject to the 
identified unsafe condition.
    In addition, Safety Communique No. 189 recommends inspection of the 
subject area via a one-time visual inspection within 25 flight hours 
(for airplanes with more than 1,500 total flight hours) and a one-time 
fluorescent penetrant inspection within 50 flight hours. However, in 
light of the potential severity of the unsafe condition and the 
uncertainty of the cause of the premature cracking, the FAA finds these 
recommendations inadequate to address the identified unsafe condition 
in a timely manner. The FAA has determined that a fluorescent penetrant 
inspection could detect cracking that a visual inspection might miss. 
Also, the FAA has determined that the initial inspection must be 
performed at the earlier of 14 days or 25 flight hours, and that the 
inspections must be repetitively performed, to timely detect cracking 
that could contribute to the unsafe condition.
    In developing appropriate actions and compliance times for this AD, 
the FAA considered not only the manufacturer's recommendations, but the 
availability of parts, the average utilization of the affected fleet, 
the time necessary to perform an inspection (2 work hours), and the 
degree of urgency associated with addressing the identified unsafe 
condition. In light of all of these factors, the FAA finds initial and 
repetitive fluorescent penetrant inspections to be warranted, in that 
they will provide more detailed data, allow operators to detect 
cracking before it becomes a hazard to the structure, and provide the 
necessary continued operational safety for the fleet.

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 2001-NM-382-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.

[[Page 4348]]

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:

2002-01-23  Raytheon Aircraft Company (Formerly Beech): Amendment 
39-12617. Docket 2001-NM-382-AD.

    Applicability: The following airplanes, certificated in any 
category:

                                             Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
                  Model                                               Serial Numbers
----------------------------------------------------------------------------------------------------------------
Beech 400 series airplanes..............  RJ-1 through RJ-65 inclusive.
Beech 400A series airplanes.............  RK-1 and subsequent.
Beech 400T series airplanes.............  TT-1 through TT-180 inclusive.
Beech 400T-1 airplanes..................  TX-1 through TX-11 inclusive.
Beech MU-300-10 airplanes...............  A1001SA through A1011SA inclusive.
Mitsubishi MU-300 airplanes.............  A003SA through A091SA inclusive.
----------------------------------------------------------------------------------------------------------------


    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the engine mount and possible loss of the 
engine, and consequent loss of control of the airplane, accomplish 
the following:

Repetitive Inspections

    (a) At the later of the times specified by paragraphs (a)(1) and 
(a)(2) of this AD: Perform a fluorescent penetrant inspection to 
detect cracking in the radius of the cutout of the aft flange of the 
left engine forward carry-through mount bracket, in accordance with 
Raytheon Safety Communique No. 189, Revision 1, dated January 2002. 
Repeat the inspection thereafter at least every 200 flight hours.
    (1) Inspect prior to the accumulation of 1,500 total flight 
hours; or
    (2) Inspect within 25 flight hours or 14 days after the 
effective date of this AD, whichever occurs first.

    Note 2: Accomplishment of a fluorescent penetrant inspection 
before the effective date of this AD in accordance with Raytheon 
Safety Communique No. 189, dated November 2001, is acceptable for 
compliance with the requirements for the initial inspection of 
paragraph (a) of this AD; however, accomplishment of only a visual 
inspection is not acceptable.

Corrective Action

    (b) If any cracking is detected during any inspection required 
by paragraph (a) of this AD: Prior to further flight, replace the 
cracked part with a new bracket and fitting in accordance with 
Raytheon Maintenance Manual, Chapter 54-40-00. The replacement parts 
are identified in Raytheon Safety Communique 189, dated November 
2001, or Revision 1, dated January 2002.

Alternative Methods of Compliance

    (c) 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, FAA.

    Note 3: 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

    (d) Special flight permits may be issued in accordance with 
Secs. 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, provided the 
limitations specified by paragraphs (d)(1) and (d)(2) of this AD are 
included in the special flight permit.
    (1) If any cracking is detected during any inspection required 
by paragraph (a) of this AD, but all cracks are less than one inch 
in length: Operation of the airplane is permitted to the nearest 
repair facility, provided the thrust reversers (if installed) are 
pinned or deactivated during operation.
    (2) If a crack of one inch or longer is detected during any 
inspection required by paragraph (a) of this AD: Operation of the 
airplane is permitted to the nearest repair facility provided a 
temporary repair is first accomplished in accordance with a method 
approved by the Manager, Wichita ACO.

Incorporation by Reference

    (e) Except as required by paragraph (b) of this AD: The actions 
must be done in accordance with Raytheon Safety Communique No. 189, 
Revision 1, dated January 2002. (Only page 1 of this document is 
dated; no other page contains this information.) 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

    (f) This amendment becomes effective on February 14, 2002.


    Issued in Renton, Washington, on January 18, 2002.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-1965 Filed 1-29-02; 8:45 am]
BILLING CODE 4910-13-P