[Federal Register Volume 59, Number 189 (Friday, September 30, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-23812]


[[Page Unknown]]

[Federal Register: September 30, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-CE-19-AD; Amendment 39-9033; AD 94-20-05]

 

Airworthiness Directives; Beech Aircraft Corporation 1900 Series 
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 
applies to certain Beech Aircraft Corporation (Beech) 1900 series 
airplanes. This action requires inspecting the hot battery bus fuse 
assembly for proper wiring, correcting the wiring if incorrect, and 
modifying the wiring to add a redundant power source for the hot 
battery bus. This action results from a report of the hot battery bus 
bar wrongly installed on the lower (load) side of the hot battery bus 
fuse assembly on one of the affected airplanes. Correct installation is 
the upper (power) side of the circuit. The actions specified by this AD 
are intended to protect from overloads to either circuit connected to 
the hot battery bus from overloads, which, if not protected, could 
result in loss of certain emergency equipment.

DATES: Effective October 14, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 14, 1994.
    Comments for inclusion in the Rules Docket must be received on or 
before December 12, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket 94-CE-19-AD, Room 1558, 601 E. 12th 
Street, Kansas City, Missouri 64106.
    Information that relates to this AD may be obtained from the Beech 
Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. This 
information may also be examined at the FAA at the address above; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Harvey E. Nero, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4137; 
facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION: The FAA has received a report that the hot 
battery bus bar was wrongly installed on the lower (load) side of the 
hot battery bus fuse assembly on a Beech 1900 series airplane. Correct 
installation is the upper (power) side of the circuit. With the 
reported configuration, a single five amp fuse supplies electrical 
power to all the systems connected to the bus instead of (under the 
correct wiring configuration) the hot battery bus supplying each 
essential load independently through a fuse for each load. In normal 
conditions, an airplane operator would not notice the miswired hot 
battery bus bar until the single fuse is blown. This condition, if not 
detected and corrected, could result in the loss of electrical power to 
all emergency equipment connected to the hot battery bus. This 
equipment includes the left and right engine fire extinguisher bottles, 
the left and right fire wall shutoff valves, the cockpit emergency 
lighting, and the engine fire extinguisher indicator lights.
    In addition, these airplanes currently are not equipped with a 
redundant power source for the emergency equipment receiving power from 
the hot battery bus. Under the present scenario, an internal battery 
problem could prevent the use of the emergency equipment because of no 
backup power sources for this equipment connected to the hot battery 
bus.
    Beech has issued Service Bulletin (SB) No. 2562, dated August 1994, 
which specifies procedures for (1) inspecting the hot battery bus fuse 
assembly for proper wiring and correcting the wiring if incorrect, and 
(2) modifying the wiring to add a redundant power source for the hot 
battery bus.
    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that AD action should be taken in order to protect either 
circuit connected to the hot battery bus from overloads, which, if not 
protected, could result in loss of certain emergency equipment.
    Since an unsafe condition has been identified that is likely to 
exist or develop in other Beech 1900 series airplanes of the same type 
design, this AD requires the inspection and modification specified in 
Beech SB No. 2562, dated August 1994.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for public 
prior 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 immediate flight safety and, thus, was not 
preceded by notice and opportunity to 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 should identify the Rules Docket number and be submitted 
in triplicate to the address specified above. 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.
    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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 94-CE-19-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation and that must be issued immediately to correct an unsafe 
condition in aircraft, and 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 (otherwise, an evaluation is 
not required). A copy of it, if filed, may be obtained from the Rules 
Docket.

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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

94-20-05 Beech Aircraft Corporation: Amendment 39-9033; Docket No. 
94-CE-19-AD.

    Applicability: The following model and serial number airplanes, 
certificated in any category: 

------------------------------------------------------------------------
               Model                             Serial Nos.            
------------------------------------------------------------------------
1900...............................  UA-2 and UA-3.                     
1900C..............................  UB-1 through UB-74 and UC-1 through
                                      UC-174.                           
1900D..............................  UE-1 through UE-87.                
C-12J (Military)...................  UD-1 through UD-6.                 
------------------------------------------------------------------------

    Compliance: Required within the next 50 hours time-in-service 
after the effective date of this AD, unless already accomplished.
    To protect either circuit connected to the hot battery bus from 
overloads, which, if not protected, could result in loss of certain 
emergency equipment, accomplish the following:
    (a) Visually inspect the hot battery bus fuse assembly to ensure 
that the hot battery bus bar is mounted on the row of terminals 
located on top of the hot battery bus fuse assembly in accordance 
with paragraphs 1 through 3 in the Accomplishment Instructions 
section of Beech Service Bulletin (SB) No. 2562, dated August 1994. 
If not mounted correctly, prior to further flight, reinstall the hot 
battery bus bar and reattach the wire harness in accordance with 
Beech SB No. 2562.
    (b) Modify the wiring to add a redundant power source for the 
hot battery bus by accomplishing paragraphs 1, 2, and 4 through 12 
of the Accomplishment Instructions section of Beech SB No. 2562, 
dated August 1994.
    (c) 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.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, Wichita Aircraft Certification Office 
(ACO), FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The 
request should be forwarded through an appropriate FAA Maintenance 
Inspector, who may add comments and send it to the Manager, Wichita 
ACO.

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

    (e) The inspection and modification required by this AD shall be 
done in accordance with the instructions to Beech Service Bulletin 
No. 2562, dated August 1994. 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 Beech 
Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 
Copies may be inspected at the FAA, Central Region, Office of the 
Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (f) This amendment (39-9033) becomes effective on October 14, 
1994.

    Issued in Kansas City, Missouri, on September 21, 1994.
Barry D. Clements,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 94-23812 Filed 9-29-94; 8:45 am]
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