[Federal Register Volume 65, Number 56 (Wednesday, March 22, 2000)]
[Proposed Rules]
[Pages 15278-15280]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-7091]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-02-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Beech Models 
1900C, 1900C (C-12J), and 1900D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain Raytheon Aircraft Company (Raytheon) 
Beech Models 1900C, 1900C (C-12J), and 1900D airplanes. The proposed AD 
would require you to install a spiral wrap around the wing fuel 
quantity wiring harness and apply an adhesive sealant to the Wiggins 
couplings on the internal fuel tank wiring carry-through conduit. The 
proposed AD results from reports of chafed or shorted wing fuel 
quantity harness wires on the affected airplanes. These occurrences 
were found during regular maintenance inspections. The actions 
specified by the proposed AD are intended to:
--prevent chafing between the wing fuel quantity wiring harness and the 
internal wing harness supports at each wing rib location, which could 
cause the fuel quantity indication to become unreliable. This could 
leave the flight crew without an indication of the amount of fuel the 
airplane has during flight; and
--prevent fuel from leaking through the wiring carry-through conduit 
and into the wing tip or wheel well area, which could lead to a fire or 
explosion.

DATES: The Federal Aviation Administration (FAA) must receive any 
comments on this rule on or before May 19, 2000.

ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office 
of the Regional Counsel, Attention: Rules Docket No. 2000-CE-02-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106.

[[Page 15279]]

    You may get the service information referenced in the proposed AD 
from the Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. You may examine this 
information at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Jeff Pretz, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4153; 
facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites comments on the proposed rule. You may submit 
whatever written data, views, or arguments you choose. You need to 
include the rule's docket number and submit your comments in triplicate 
to the address specified under the caption ADDRESSES. We will consider 
all comments received on or before the closing date specified above, 
before taking action on the proposed rule. We may change the proposals 
contained in this notice in light of the comments received.
    The FAA is re-examining the writing style we currently use in 
regulatory documents, in response to the Presidential memorandum of 
June 1, 1998. That memorandum requires federal agencies to communicate 
more clearly with the public. We are interested in your comments on 
whether the style of this document is clearer, and any other 
suggestions you might have to improve the clarity of FAA communications 
that affect you. You can get more information about the Presidential 
memorandum and the plain language initiative at http://www.plainlanguage.gov.
    The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule that 
might necessitate a need to modify the proposed rule. You may examine 
all comments we receive before and after the closing date for comments 
in the Rules Docket. We will file a report in the Rules Docket that 
summarizes each FAA contact with the public that concerns the 
substantive parts of this proposal.
    If you want us to acknowledge the receipt of your comments, you 
must include a self-addressed, stamped postcard. On the postcard, write 
``Comments to Docket No. 2000-CE-02-AD.'' We will date stamp and mail 
the postcard back to you.

Availability of NPRMs

    You may obtain a copy of this NPRM by submitting a written request 
to FAA, Central Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2000-CE-02-AD, 901 Locust, Room 506, Kansas City, 
Missouri 64106.

Discussion

    What events have caused the proposed rule? Several operators of 
Raytheon Beech Models 1900C and 1900D airplanes have reported chafing 
of the wing fuel quantity wiring harness against the wing fuel quantity 
wiring harness supports (located at the wing wiring harness lighting 
hole mounts). The condition is also conducive to the Model 1900C (C-
12J) airplanes.
    The lightning hole mounts at each wing rib support the wing fuel 
quantity wiring harness. The following could occur and cause the above-
referenced condition:

--Vibration and fuel movement cause the insulation on the wiring 
harness to chafe on the tie straps used to secure the harness to the 
lightning hole mounts; and
--Exposed conductors of the wiring harness could then contact each 
other and result in an incorrect fuel quantity indication or the 
indicator reading zero.

    In addition to the above condition on the Raytheon Beech Models 
1900C, 1900C (C-12J), and 1900D airplanes, the O-rings in Wiggins 
couplings that join the electrical conduit internal to the wing fuel 
tanks could leak and allow fuel to enter the conduit. This could result 
in a fire or explosion.
    What are the consequences if the conditions are not corrected? If 
not corrected in a timely manner, the above-referenced conditions could 
result in the following:

--Chafing between the wing fuel quantity wiring harness and the 
internal wing harness supports at each wing rib location could cause 
the fuel quantity indication to become unreliable. This could leave the 
flight crew without an indication of the amount of fuel in the airplane 
during flight; and
--Fuel leaking through the wiring carry-through conduit and into the 
wing tip or wheel well area could lead to a fire or explosion.

Relevant Service Information

    Is there service information that applies to this subject? Yes. 
Raytheon has issued Mandatory Service Bulletin No. SB 28-3299, Issued: 
December, 1999.
    What are the provisions of this service bulletin? The service 
bulletin includes procedures for:

--Installing a spiral wrap around the wing fuel quantity wiring 
harness; and
--Applying an adhesive sealant to the Wiggins couplings on the internal 
fuel tank wiring carry-through conduit.

The FAA's Determination and an Explanation of the Provisions of the 
Proposed AD

    What has the FAA decided? After examining the circumstances and 
reviewing all available information related to the incidents described 
above, including the relevant service information, FAA has determined 
that:

--An unsafe condition is likely to exist or develop in other Raytheon 
Beech Models 1900C, 1900C (C-12J), and 1900D airplanes of the same type 
design;
--The actions of the above-referenced service bulletin should be 
accomplished on the affected airplanes; and
--AD action should be taken to prevent the above-referenced conditions 
from occurring.

    What would the proposed AD require? The proposed AD would require 
you to:
--Install a spiral wrap around the wing fuel quantity wiring harness; 
and
--Apply an adhesive sealant to the Wiggins couplings on the internal 
fuel tank wiring carry-through conduit.

Compliance Time of This Proposed AD

    What is the compliance time of this proposed AD? The compliance 
time in the proposed AD is whichever of the following that occurs 
first:

--Within the next 3 months after the effective date of this AD; or
--Within the next 600 hours time-in-service (TIS) after the effective 
date of this AD.

    Why is the compliance time in both calendar time and hours TIS? 
Chafing damage is a direct result of airplane usage; however, the fuel 
leakage problem could result regardless of whether the airplane is 
utilized. Therefore, to assure that both problems are address in a 
timely manner without inadvertently grounding any of the affected 
airplanes, we are utilizing a compliance based upon both hours TIS and 
calendar time.

Cost Impact

    How many airplanes does this proposed AD impact? The FAA estimates 
that 303 airplanes in the U.S. registry would be affected by the 
proposed AD.

[[Page 15280]]

    What is the cost impact of the affected airplanes on the U.S. 
Register? We estimate that it would take approximately 10 workhours per 
airplane to accomplish the proposed actions, and that the average labor 
rate is approximately $60 an hour. There is no cost for parts to 
accomplish the proposed actions.
    Based on these figures, we estimate the total cost impact of the 
proposed AD on U.S. operators to be $181,800, or $600 per airplane.

Regulatory Impact

    These proposed regulations would 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, FAA 
determines that this proposed rule would 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) if promulgated, 
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. The FAA has placed a copy of the draft 
regulatory evaluation prepared for this action in the Rules Docket. You 
may contact the Rules Docket (at the location provided under the 
caption ADDRESSES) to get a copy of this evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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. FAA amends Section 39.13 by adding a new airworthiness directive 
(AD) to read as follows:

Raytheon Aircraft Company (Type Certificate No. A24CE formerly held 
by the Beech Aircraft Corporation):  Docket No. 2000-CE-02-AD.
    (a) What airplanes are affected by this AD? This AD affects the 
following airplanes, certificated in any category:
    (1) Part I of this AD: Wing fuel quantity wiring harness 
attachment improvement.

------------------------------------------------------------------------
                Model                              Serial No.
------------------------------------------------------------------------
1900C................................  UC-1 through UC-174.
1900C (C-12J)........................  UD-1 through UD-6.
1900D................................  UE-1 through UE-331.
------------------------------------------------------------------------

    (2) Part II of this AD: Wiggins coupling adhesive sealing.

------------------------------------------------------------------------
                Model                              Serial No.
------------------------------------------------------------------------
1900C................................  UC-1 through UC-174.
1900C (C-12J)........................  UD-1 through UD-6.
1900D................................  UE-1 through UE-354.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes on the U.S. Register must comply with 
this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent the following:
    (1) Part I of this AD: chafing between the wing fuel quantity 
wiring harness and the internal wing harness supports at each wing 
rib location, which could cause the fuel quantity indication to 
become unreliable. This could leave the flight crew without an 
indication of the amount of fuel the airplane has during flight; and
    (2) Part II of this AD: fuel from leaking through the wiring 
carry-through conduit and into the wing tip or wheel well area, 
which could lead to a fire or explosion.
    (d) What must I do to address this problem? To address this 
problem, you must accomplish the following actions:
    (1) Part I of this AD: Install a spiral wrap around the wing 
fuel quantity wiring harness; and
    (2) Part II of this AD: Apply an adhesive sealant to the Wiggins 
couplings on the internal fuel tank wiring carry-through conduit.
    (e) What is the compliance time of all actions of this AD? You 
must accomplish all actions of this AD at whichever of the following 
times that occurs first:
    (1) Within the next 3 calendar months after the effective date 
of this AD; or
    (2) Within the next 600 hours time-in-service (TIS) after the 
effective date of this AD.
    (f) What procedures must I use to accomplish the actions 
required in this AD? You must use the procedures in Raytheon 
Mandatory Service Bulletin No. SB 28-3299, Issued: December, 1999, 
to accomplish the actions of this AD.
    (g) Can I comply with this AD in any other way? Yes.
    (1) You may use an alternative method of compliance or adjust 
the compliance time if:
    (i) Your alternative method of compliance provides an equivalent 
level of safety; and
    (ii) The Manager, Wichita Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Wichita ACO.
    (2) 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 (g)(1) 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 you have not eliminated the unsafe 
condition, specific actions you propose to address it.
    (h) Where can I get information about any already-approved 
alternative methods of compliance? Contact Jeff Pretz, Aerospace 
Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4153; facsimile: (316) 946-4407.
    (i) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (j) Who should I contact if I have questions regarding the 
service information? Questions or technical information related to 
Raytheon Mandatory Service Bulletin No. SB 28-3299, Issued: 
December, 1999, should be directed to Raytheon Aircraft Corporation, 
P.O. Box 85, Wichita, Kansas 67201-0085. This service information 
may be examined at the FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

    Issued in Kansas City, Missouri, on March 14, 2000.
Carolanne L. Cabrini,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-7091 Filed 3-21-00; 8:45 am]
BILLING CODE 4910-13-U