[Federal Register Volume 71, Number 89 (Tuesday, May 9, 2006)]
[Proposed Rules]
[Pages 26877-26879]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-7014]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24694; Directorate Identifier 2006-NM-018-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon (Beech) Model 400 and 400A 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Raytheon (Beech) Model 400 and 400A series airplanes. This 
proposed AD would require, among other actions, reviewing the airplane 
logbook to determine whether certain generator control unit (GCU) 
installation kits are installed, and replacing any incorrect GCU. This 
proposed AD results from reports of over-voltage conditions of the 
direct current (DC) starter generator. We are proposing this AD to 
prevent such over-voltage conditions due to the incompatibility between 
certain GCUs, which could result in the loss of normal electrical 
power, damage to some electrical components, or blown fuses during 
flight, and consequent unrecoverable loss of some or all essential 
equipment.

DATES: We must receive comments on this proposed AD by June 23, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Raytheon Aircraft Company, Department 62, P.O. Box 85, 
Wichita, Kansas 67201-0085, for the service information identified in 
this proposed AD.

FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer, 
Electrical Systems and Avionics, ACE-119W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4139; fax (316) 
946-4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24694; Directorate Identifier 2006-NM-018-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal

[[Page 26878]]

information you provide. We will also post a report summarizing each 
substantive verbal contact with FAA personnel concerning this proposed 
AD. Using the search function of that Web site, anyone can find and 
read the comments in any of our dockets, including the name of the 
individual who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You may review DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    We have received reports of over-voltage conditions of the direct 
current (DC) starter generator. In one case, over-voltage conditions 
resulted in complete loss of the DC electrical power during flight and 
loss of the primary flight display. The cause is the incompatibility 
between a Goodrich (formerly Lucas Aerospace) DC starter generator and 
a Shinko generator control unit (GCU). This condition, if not 
corrected, could result in loss of normal electrical power, damage to 
some electrical components, or blown fuses during flight, which could 
result in the unrecoverable loss of some or all essential equipment.

Relevant Service Information

    We have reviewed Raytheon Service Bulletin SB 24-3713, dated 
November 2005. The service bulletin describes procedures for reviewing 
the airplane logbook to determine whether a certain GCU installation 
kit (Lucas Aerospace/Goodrich) is installed and replacing any incorrect 
Shinko GCU with a new Lucas Aerospace/Goodrich GCU. For certain 
findings, the service bulletin also describes the following procedures, 
as applicable:
     Inspecting to determine the part number (P/N) of both 
GCUs;
     Inspecting to determine the P/N of both current sense 
transformers on the lower inboard quadrant of the left-hand and right-
hand engine inlets;
     Replacing any incorrect GCU with a certain new GCU; and
     Replacing any incorrect current sense transformer with a 
certain new transformer.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously except as discussed under ``Difference 
Between the Proposed AD and the Service Bulletin.''

Difference Between the Proposed AD and the Service Bulletin

    Operators should note that the applicability of this proposed AD 
differs from the Effectivity of Raytheon Service Bulletin SB 24-3713. 
In addition to airplanes on which Kit No. 128-3004-1 P has been 
incorporated, this proposed AD also affects airplanes on which Kit No. 
128-3004-3 P has been incorporated. We have determined that those 
airplanes also are subject to the identified unsafe condition.
    We have coordinated this difference with the airplane manufacturer.

Costs of Compliance

    There are about 43 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 40 airplanes of 
U.S. registry. The proposed inspection would take about 1 work hour per 
airplane, at an average labor rate of $80 per work hour. Based on these 
figures, the estimated cost of the proposed AD for U.S. operators is 
$3,200, or $80 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory 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 FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Raytheon Aircraft Company (Formerly Beech): Docket No. FAA-2006-
24694; Directorate Identifier 2006-NM-018-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by June 23, 
2006.

[[Page 26879]]

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in Table 1 of 
this AD, certificated in any category.

                                             Table 1.--Applicability
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        Raytheon (Beech) model--                   Serials--                           On which--
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(1) 400 series airplanes................  RJ-1 through RJ-65           Kit part number (P/N) 128-3004-1 P or 128-
                                           inclusive.                   3004-3 P has been incorporated (Lucas
                                                                        Aerospace/Goodrich Direct Current (DC)
                                                                        Starter Generator).
(2) 400A series airplanes...............  RK-1 through RK-23           Kit P/N 128-3004-1 P or 128-3004-3 P has
                                           inclusive.                   been incorporated (Lucas Aerospace/
                                                                        Goodrich DC Starter Generator).
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Unsafe Condition

    (d) This AD results from reports of over-voltage conditions of 
the DC starter generator. We are issuing this AD to prevent over-
voltage conditions of the DC starter generator due to the 
incompatibility between certain GCUs, which could result in the loss 
of normal electrical power, damage to some electrical components, or 
blown fuses during flight, and consequent unrecoverable loss of some 
or all essential equipment.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Raytheon Service Bulletin SB 24-3713, 
dated November 2005.

Review of Logbook

    (g) Within 200 flight hours or 6 months after the effective date 
of this AD, whichever occurs first, review the airplane logbook to 
determine whether GCU installation kit, P/N 128-3001-1 P or 128-
3001-3 P, is installed, in accordance with the service bulletin.

Installation Kit Not Found Installed: Replacement of Shinko GCU

    (h) If no GCU installation kit, P/N 128-3001-1 P or 128-3001-3 
P, is found installed or if the kit P/N cannot be conclusively 
determined during the review required by paragraph (g) of this AD, 
within 200 flight hours or 6 months after the effective date of this 
AD, whichever occurs first, replace the Shinko GCUs with new Lucas 
Aerospace/Goodrich GCUs (installation kit P/N 128-3001-1 P or 128-
3001-3 P), in accordance with the service bulletin.

Installation Kit Found Installed: Inspections of GCUs and Current Sense 
Transformers and Replacement of Transformers as Applicable

    (i) If any GCU installation kit, P/N 128-3001-1 P or 128-3001-3 
P is found installed during the review required by paragraph (g) of 
this AD: Within 200 flight hours or 6 months after the effective 
date of this AD, whichever occurs first, inspect to determine the P/
N of both GCUs, in accordance with the service bulletin; and at the 
times specified in Table 2, do the applicable action(s) in that 
table.

                       Table 2.--Inspection and Replacement of Current Sense Transformers
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                                       Then, within 200 flight
                                       hours or 6 months after
                 If--                   the effective date of             If--                    Then--
                                          this AD, whichever
                                             occurs first
----------------------------------------------------------------------------------------------------------------
(1) Both GCUs have P/N 45AS88801-19    Inspect to determine     Both current sense       No further action is
 or -25.                                the P/N of both          transformers have P/N    required by this AD.
                                        current sense            45AS88801-21.           Within 200 flight hours
                                        transformers on the     Either current sense      or 6 months after the
                                        lower inboard quadrant   transformer is not       effective date of this
                                        of the left-hand and     identified with P/N      AD, whichever occurs
                                        right-hand engine        45AS88801-21.            first, replace the
                                        inlets, in accordance                             current sense
                                        with the service                                  transformer with a new
                                        bulletin.                                         transformer, P/N
                                                                                          45AS88801-21, in
                                                                                          accordance with the
                                                                                          service bulletin.
(2) Either GCU does not have P/N       Replace the GCU with a   Both current sense       No further action is
 45AS88801-19 or -25.                   new GCU, P/N 45AS88801-  transformers have P/N    required by this AD.
                                        19 or -25, and inspect   45AS88801-21.           Within 200 flight hours
                                        to determine the P/N    Either current sense      or 6 months after the
                                        of both current sense    transformer is not       effective date of this
                                        transformers on the      identified with P/N      AD, whichever occurs
                                        lower inboard quadrant   45AS88801-21.            first, replace the
                                        of the left-hand and                              current sense
                                        right-hand engine                                 transformer with a new
                                        inlets; in accordance                             transformer, P/N
                                        with the service                                  45AS88801-21, in
                                        bulletin.                                         accordance with the
                                                                                          service bulletin.
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Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on April 28, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-7014 Filed 5-8-06; 8:45 am]
BILLING CODE 4910-13-P