AD 2000-19-04

[Federal Register Volume 65, Number 181 (Monday, September 18, 2000)]
[Rules and Regulations]
[Pages 56236-56239]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-23730]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-02-AD; Amendment 39-11905; AD 2000-19-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 
1900C, 1900C (C-12J), and 1900D airplanes. This AD requires 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. This AD is the result of 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 this 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. The actions are also intended to 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: Effective October 31, 2000.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
October 31, 2000.

ADDRESSES: You may get the service information referenced in this AD 
from the Raytheon Aircraft Company, P. O. Box 85, Wichita, Kansas 
67201-0085; telephone: (800) 625-7043 or (316) 676-4556. You may 
examine this information at FAA, Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-CE-02-AD, 901 Locust, Room 
506, Kansas City, Missouri 64106; or at the Office of the Federal 
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

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:

Discussion

    What caused this AD? 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 
Model 1900C (C-12J) airplanes are also susceptible to this condition.
    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:
    <bullet> 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
    <bullet> 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 is the potential impact if FAA took no action? If not 
corrected in a timely manner, the above-referenced conditions could 
result in the following:
    <bullet> 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
    <bullet> Fuel leaking through the wiring carry-through conduit and 
into the wing tip or wheel well area could lead to a fire or explosion.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include

[[Page 56237]]

an AD that would apply to certain Raytheon Beech Models 1900C, 1900C 
(C-12J), and 1900D airplanes. This proposal was published in the 
Federal Register as a notice of proposed rulemaking (NPRM) on March 22, 
2000 (65 FR 15278). The NPRM proposed to 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. Accomplishment of the proposed action as 
specified in the NPRM would be in accordance with Raytheon Mandatory 
Service Bulletin No. SB 28-3299, Issued: December, 1999.
    Was the public invited to comment? The FAA encouraged interested 
persons to participate in the making of this amendment. The following 
presents the comments received on the proposal and FAA's response to 
each comment:

Comment Issue No. 1: Provide Information on Allowable Fuel Quantity 
Wire Harness Chafing

    What is the commenter's concern? One commenter states that the NPRM 
does not clarify how much chafing damage is allowed before the fuel 
quantity harness must be replaced. The commenter requests that FAA 
include allowable limits, sketches, or definitions that dictate how 
much chafing is allowed on the fuel quantity harness.
    What is FAA's response to the concern? The intent of this AD action 
is to provide protection for the fuel quantity harness so that chafed 
or shorted wing fuel quantity harness wires do not occur on the 
affected airplanes. We believe that incorporating the actions of the 
proposed AD will provide the protection necessary on the fuel quantity 
harness. This NPRM does not propose replacement or repair of the fuel 
quantity harness. As with any aircraft part, the fuel quantity harness 
should be replaced if it has deteriorated to a point where it is not 
effective.
    We are not changing the AD as a result of this comment.

Comment Issue No. 2: FAA's Labor Cost Estimate Does Not Reflect the 
Work

    What is the commenters' concern? Two commenters do not believe that 
FAA's estimate of the number of workhours necessary to accomplish the 
actions proposed in the NPRM is correct. One commenter states that, 
based on discussions with other operators, the workhours should be 
increased from 10 to 12. Another commenter believes 20 workhours is 
appropriate and lists all the steps necessary to accomplish the 
proposed actions.
    What is FAA's response to the concern? The procedures necessary to 
accomplish the actions proposed in the NPRM are included in Raytheon 
Mandatory Service Bulletin No. SB 28-3299, Issued: December, 1999. We 
obtained the 10-workhour figure directly from this service bulletin. 
Raytheon has informed us that several owners/operators of the affected 
airplanes have already had the proposed actions accomplished and that 
on average the 10-hour estimate is correct. Some airplanes may require 
more time and some may require less. The exact time is dependent upon 
the experience of the mechanic, the availability of proper equipment, 
and the condition of the wire harness as stated in the ``Manpower'' 
section of the service bulletin.
    We are not changing the AD as a result of these comments.

Comment Issue No. 3: Cost Impact Does not Include Harness 
Replacement and Aircraft Down Time

    What is the commenter's concern? One commenter states that FAA 
failed to include the cost of replacing damaged fuel quantity harnesses 
and the revenues lost by taking the airplanes out of operation to 
accomplish the AD action.
    What is FAA's response to the concern? As we stated earlier, the 
intent of this AD action is to provide protection for the fuel quantity 
harness so that chafed or shorted wing fuel quantity harness wires do 
not occur on the affected airplanes. The cost impact of this AD 
addresses the cost of the actions to meet this intent. The FAA has no 
way of determining the number of fuel quantity harnesses that may need 
to be replaced. We also cannot estimate the revenue certain operators 
may lose while accomplishing the AD action. We did however structure 
the compliance time of the proposed AD to coincide with regularly 
scheduled maintenance activities.
    We are not changing the AD as a result of this comment.

Comment Issue No. 4: Compliance Time is too Short

    What is the commenter's concern? One commenter states that the 
compliance time of 3 months or 600 hours time-in-service (TIS), 
whichever occurs first, will require some operators to accomplish the 
AD action within 9 to 10 weeks. We infer that the commenter wants the 
compliance time extended.
    What is FAA's response to the concern? The FAA established the 
compliance time so that the accomplishment of the AD could coincide 
with regularly scheduled maintenance activities. Raytheon has informed 
us that many aircraft are already in compliance with the AD. For these 
reasons, we believe that the compliance time gives all airplane owners/
operators ample time to complete the AD action. As with any AD action, 
we will consider compliance time extensions provided they provide an 
acceptable level of safety and are submitted through the alternative 
method of compliance procedures specified in the AD.
    We are not changing the AD as a result of this comment.

Comment Issue No. 5: AD Is Not Justified

    What is the commenter's concern? One commenter states that its 
maintenance database does not contain information to support the 
actions proposed in the NPRM. This commenter also believes that placing 
sealer over the Wiggins fitting does not guarantee that the fitting 
will not leak. We infer that the commenter wants FAA to withdraw the 
NPRM.
    What is FAA's response to the concern? Raytheon provided FAA with 
several reports of chafed and shorted fuel quantity harness wires that 
were found during maintenance and refurbishment. Although the addition 
of sealer to the fitting cannot provide a guarantee that it will never 
leak (nothing will provide this guarantee), we have determined that the 
likelihood of leakage is greatly reduced.
    We are not changing the AD as a result of this comment.

The FAA's Determination

    What is FAA's final determination on this issue? We carefully 
reviewed all available information related to the subject presented 
above and determined that air safety and the public interest require 
the adoption of the rule as proposed except for minor editorial 
corrections. We determined that these minor corrections:
    <bullet> Will not change the meaning of the AD; and
    <bullet> Will not add any additional burden upon the public than 
was already proposed.

Compliance Time of This AD

    What is the compliance time of this AD? The compliance time of this 
AD is whichever of the following that occurs first:
    <bullet> Within the next 3 months after the effective date of this 
AD; or
    <bullet> Within the next 600 hours TIS after the effective date of 
this AD.

[[Page 56238]]

    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 addressed 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 AD impact? The FAA estimates that 303 
airplanes in the U.S. registry will be affected by this AD.
    What is the cost impact for the affected airplanes on the U.S. 
Register? We estimate that it will take approximately 10 workhours per 
airplane to accomplish the actions required by this AD, and that the 
average labor rate is approximately $60 an hour. There is no cost for 
parts to accomplish this AD. Based on these figures, we estimate the 
total cost impact of this AD on U.S. operators at $181,800, or $600 per 
airplane.

Regulatory Impact

    Does this AD impact various entities? 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.
    Does this AD involve a significant rule or regulatory action? 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 copy 
of the final evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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, under 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. FAA amends Section 39.13 by adding a new AD to read as follows:

2000-19-04  Raytheon Aircraft Company (Type Certificate No. A24CE 
formerly held by the Beech Aircraft Corporation): Amendment 39-
11905; Docket No. 2000-CE-02-AD.

    (a) What airplanes are affected by this AD? The following 
airplane models and serial numbers, certificated in any category:
    (1) Part I of this AD: Wing fuel quantity wiring harness 
attachment improvement.

------------------------------------------------------------------------
                 Model                             Serial nos.
------------------------------------------------------------------------
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 nos.
------------------------------------------------------------------------
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:

------------------------------------------------------------------------
           Action                Compliance time         Procedures
------------------------------------------------------------------------
(1) Part I--Install a spiral  Accomplish all        Accomplish these
 wrap around the wing fuel     actions within the    actions in
 quantity wiring harness;      next 3 calendar       accordance with
 and.                          months after          Raytheon Mandatory
                               October 31, 2000      Service Bulletin
                               (the effective date   No. SB 28-3299,
                               of this AD) or        Issued: December,
                               within the next 600   1999.
                               hours time-in-
                               service (TIS) after
                               October 31, 2000
                               (the effective date
                               of this AD),
                               whichever occurs
                               first.
(2) Part II--Apply an
 adhesive sealant to the
 Wiggins couplings on the
 internal fuel tank wiring
 carry-through conduit.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) 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.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 (e) 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.

    (f) 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.
    (g) 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

[[Page 56239]]

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.
    (h) Are any service bulletins incorporated into this AD by 
reference? You must accomplish the actions required by this AD in 
accordance with Raytheon Mandatory Service Bulletin No. SB 28-3299, 
Issued: December, 1999. The Director of the Federal Register 
approved this incorporation by reference under 5 U.S.C. 552(a) and 1 
CFR part 51. You can get copies from Raytheon Aircraft Corporation, 
P.O. Box 85, Wichita, Kansas 67201-0085. You can look at copies at 
FAA, Central Region, Office of the Regional Counsel, 901 Locust, 
Room 506, Kansas City, Missouri, or at the Office of the Federal 
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on October 31, 2000.

    Issued in Kansas City, Missouri, on September 8, 2000.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 00-23730 Filed 9-15-00; 8:45 am]
BILLING CODE 4910-13-P