AD 2001-03-06

[Federal Register Volume 66, Number 32 (Thursday, February 15, 2001)]
[Rules and Regulations]
[Pages 10356-10359]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-3672]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-368-AD; Amendment 39-12110; AD 2001-03-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Raytheon (Beech) Model MU-300, MU-300-10, 400, and 400A 
series airplanes, that requires repetitive inspections of the bleed air 
supply tube assemblies for discrepancies; and replacement of the bleed 
air tube assembly with a new bleed air tube assembly, if necessary. In 
lieu of accomplishing the repetitive

[[Page 10357]]

inspections, this AD also provides for a revision of the Airworthiness 
Limitations to incorporate, among other things, certain inspections and 
compliance times to detect discrepancies of the subject area; and 
corrective action, if necessary. This amendment is prompted by reports 
of broken wire braiding in the bellows assembly of the bleed air supply 
tube assembly due to premature failure from loading. The actions 
specified by this AD are intended to prevent the bleed air supply tube 
assembly from disconnecting and contacting other pneumatic or 
electrical systems of the airplane or expelling high temperature air on 
surrounding systems and structure. Such a condition could reduce the 
functional capabilities of the airplane or the ability of the flight 
crew to cope with adverse operating conditions.

DATES: Effective March 22, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Manager, Service Engineering, 
Beechjet Premier Technical Support, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT: Paul C. DeVore, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas, 67209; telephone (316) 946-4142; fax (316) 
946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Raytheon (Beech) Model MU-300, 
MU-300-10, 400, and 400A series airplanes was published in the Federal 
Register on May 10, 2000 (65 FR 30031). That action proposed to require 
repetitive inspections of the bleed air supply tube assemblies for 
discrepancies; and replacement of the bleed air tube assembly with a 
new bleed air tube assembly, if necessary. That action also proposed to 
require that, in lieu of accomplishing the repetitive inspections, the 
Airworthiness Limitations Section (ALS) be revised to specify, among 
other things, certain inspections to detect discrepancies and 
compliance times for the subject area; and corrective action, if 
necessary.

Since the Issuance of the NPRM

    The FAA has reviewed and approved Raytheon Aircraft Beechjet 400/
400A Maintenance Manual, Airworthiness Limitations, Page 1, Section 4-
00-00, Revision B26, dated August 27, 1999. The FAA also has reviewed 
and approved Raytheon Aircraft Beechjet 400/400A Maintenance Manual, 
Time-Limited Inspections, Pages 3 and 6, Section 4-00-02, and Pages 4 
and 9, Section 4-00-04, Revision B26, dated August 27, 1999. The FAA 
has determined that Revision B26 contains no information that has been 
revised or added to since the issuance of Revision B23 regarding STARS 
Code 361031 (Bleed Air System). Since Revision B26 is the most current 
ALS revision, the FAA has cited Revision B26 in this final rule, as no 
required work has been added or changed from the requirements set forth 
in the proposed rule.
    The FAA has reviewed and approved Raytheon Aircraft Diamond 1/1A 
MU-300 Maintenance Requirement Manual, Revision 9, dated February 26, 
1999. The FAA has determined that Revision 9 contains no information 
that has been revised or added to since the issuance of Revision 8 
regarding the Bleed Air System. Since Revision 9 is the most current 
ALS revision, the FAA has cited Revision 9 in this final rule, as no 
required work has been added or changed from the requirements set forth 
in the proposed rule.

Clarification of Paragraph (a) of the Final Rule

    The FAA notes that the method of compliance in paragraph (a) of the 
proposal was inadvertently not included in the proposal. Therefore, the 
FAA has specified that those actions required by paragraph (a)(1) of 
this AD must be accomplished in accordance with the Airplane 
Maintainance Manual, Chapter 4, dated August 27, 1999. Paragraph (a)(1) 
of the final rule has been revised accordingly.

Comments to the NPRM

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request to Clarify the Compliance Time

    One commenter requests that the compliance time specified in 
paragraph (b) of the proposal be clarified to state that the actions 
must be accomplished within 200 hours time-in-service.
    The FAA concurs with the commenter that clarification is needed. 
Since paragraph (a) of the proposal clearly specifies a compliance time 
of 200 hours time-in-service, paragraph (b) of the the proposal has 
been redesignated as paragraph (a)(2) to clarify that the 200 hours 
time-in-service also applies to those requirements.

Request to Specify Incorporation of Airworthiness Limitations 
Section as Terminating Action

    One commenter requests that the proposal clearly specify that 
incorporation of the revisions of the ALS specified in the proposal be 
designated as a terminating action ``until such time as the operator 
elects to inspect the affected aircraft in accordance with paragraphs 
(a) or (d).''
    The FAA does not concur. Accomplishment of the requirements of 
paragraph (a)(2) of this AD (incorporation of the ALS revisions) is 
simply considered to be one way of complying with the requirements of 
paragraph (a) of this AD. Incorporation of the ALS revisions relieves 
the operator from continually updating compliance with the inspection 
requirements of this AD, but does not ``terminate'' the requirement to 
perform the inspections that are now enforceable as part of the ALS. No 
change is necessary to the final rule.

Request to Clarify the Requirements of Paragraph (b)

    The same commenter also requests that the proposal clarify that the 
ALS does not require any inspection until the aircraft accumulates 
1,000 hours time-in-service. The commenter further requests that the 
proposal clearly reference the current 20-hour ``inspection interval 
tolerance'' provided for in the ALS.
    The FAA acknowledges that the ALS does not require an inspection 
until the aircraft accumulates 1,000 hours time-in-service, and that 
the ALS provides for a 20-hour ``inspection interval tolerance.'' 
However, the requirements of paragraph (a)(2) of this AD merely require 
incorporating procedures specified in certain revisions of the ALS of 
the Instructions of Continued Airworthiness. The FAA does not consider 
it necessary to identify each of the procedures, provisions, or 
requirements that are included in those specific revisions of the ALS. 
Therefore, no change has been made to the final rule in this regard.

Conclusion

    After careful review of the available data, including the comments 
noted

[[Page 10358]]

above, the FAA has determined that air safety and the public interest 
require the adoption of the rule with the changes previously described. 
The FAA has determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Cost Impact

    There are approximately 530 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 452 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 1 work 
hour per airplane to accomplish either the inspection or the revision 
to the Airworthiness Limitations Section, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the AD on U.S. operators is estimated to be $27,120, or $60 per 
airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.
    Should an operator elect to accomplish the optional terminating 
action that would be provided by this AD action, it would take 
approximately 1 work hour to accomplish it, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of the 
optional terminating action would be $60 per airplane.

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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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, 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:

2001-03-06  Raytheon Aircraft Company (Formerly Beech): Amendment 
39-12110. Docket 98-NM-368-AD.

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

    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 the bleed air supply tube assembly from disconnecting 
and contacting other pneumatic or electrical systems of the airplane 
or expelling high temperature air on surrounding systems and 
structure, which could result in reduced functional capabilities of 
the airplane or the ability of the flight crew to cope with adverse 
operating conditions; accomplish the following:

Inspection

    (a) Within 200 hours time-in-service after the effective date of 
this AD, accomplish the actions specified in either paragraph (a)(1) 
or (a)(2) of this AD.
    (1) Perform a general visual inspection of the bleed air supply 
tube assemblies for broken wire braiding on the bellows assemblies 
or for ruptured or leaking bellow assemblies. The bleed air supply 
tube assemblies are located within the aft fuselage and connect to 
mating ducting in the pylon area on the right and left side of the 
airplane. Repeat the inspection thereafter at intervals not to 
exceed 400 hours time-in-service. If any broken wire is detected or 
if any bellow assembly is ruptured or leaking, prior to further 
flight, replace the bleed air tube assembly with a new bleed air 
tube assembly, in accordance with the Airplane Maintenance Manual, 
Revision B26 of Chapter 4, dated August 27, 1999.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (2) Revise the Airworthiness Limitations Sections of the 
Instructions for Continued Airworthiness by incorporating the 
procedures specified in Chapter 4, ``Airworthiness Limitations'' of 
Raytheon Aircraft Beechjet 400/400A Maintenance Manual, Revision 
B26, dated August 27, 1999, for Model MU-300-10, 400, and 400A 
series airplanes; or Section MR-11-00, ``Airworthiness Limitations'' 
of Raytheon Aircraft Diamond 1/1A MU-300 Maintenance Requirement 
Manual, Revision 9, dated February 26, 1999 (for Model MU-300 
airplanes); as applicable.
    (b) Except as provided in paragraph (c) of this AD: After the 
action specified in paragraph (a)(2) of this AD has been 
accomplished, no alternative inspections or inspection intervals may 
be approved for the part specified in paragraph (a)(2) of this AD.

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.

    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 
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.

Effective Date

    (e) This amendment becomes effective on March 22, 2001.


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    Issued in Renton, Washington, on February 7, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-3672 Filed 2-14-01; 8:45 am]
BILLING CODE 4910-13-U