[Federal Register Volume 63, Number 14 (Thursday, January 22, 1998)]
[Proposed Rules]
[Pages 3278-3280]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-1461]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-68-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Model 1900D
Airplane (Formerly Known as Beech Aircraft Corporation Model 1900D
Airplane)
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 Raytheon Aircraft Company (Raytheon) Models
1900D airplanes (formerly known as Beech Aircraft Corporation Models
1900D airplanes). The proposed action would require inspecting and
repairing the radio switching panel relay printed circuit board (PCB)
and the nose avionics wire harnesses, and replacing the existing A017
component PCB with a new A017 component PCB that has internal
overcurrent protection fuses. Several reported incidents of lost pilot/
co-pilot intercom ability, VHF communication ability, and public
address system ability while in flight prompted the proposed action.
The actions specified by the proposed AD are intended to prevent the
loss of the pilot and co-pilot intercom, VHF communications, and
passenger address system, which could result in loss of all
communication during critical phases of flight.
DATES: Comments must be received on or before March 14, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 97-CE-68-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106. Comments may be inspected at this location
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from Raytheon Aircraft Company, P. O. Box 85, Wichita, Kansas 67201-
0085; telephone (800) 625-7043. This information also may be examined
at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Harvey Nero, Aerospace Engineer,
Wichita Aircraft Certification Office, Room 100, 1801 Airport Rd.,
Wichita,
[[Page 3279]]
Kansas 67209; telephone (316) 946-4137; facsimile (316) 946-4407.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 proposal 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. 97-CE-68-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 97-CE-68-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The FAA has received several incident reports in which an in-flight
overcurrent condition occurred in the avionics/communications equipment
resulting in a loss of certain Raytheon Model 1900D airplanes' pilot
and co-pilot intercom, VHF communication, and passenger address
systems. Investigation of these incidents found that one of the
avionics wire harnesses had become chafed by rubbing against the PCB
rack in the forward avionics bay. Investigators also found overcurrent
conditions opening PCB traces in Collins CTL-22 communication control
heads.
These events are occurring because the manufacturer made a change
in the configuration design and installation of the avionics/
communication equipment and the wire harnesses on the Model 1900D
airplanes. The new configuration reduced the space between the
equipment and made the proper installation of the wire harnesses a more
critical issue. Also, the communication control heads are not
internally protected by fuses to prevent a short circuit on any of the
distribution circuits from affecting the entire communication system.
This design makes it possible for an electrical short in the radio
switching panel relay PCB's or in the avionics harnesses to create an
overcurrent condition in the CTL-22 communication control heads.
This condition could cause the pilot and co-pilot circuit breaker
to open, resulting in the pilot and co-pilot intercom system, VHF
communications, and the passenger address system not operating,
resulting in the loss of communication during critical phases of
flight.
Relevant Service Information
Raytheon has issued service bulletin (SB) No. 2643, dated August,
1996, which specifies procedures for:
inspecting the electrical connectors, the radio switching
panel, and this panel's relay PCB's for moisture and corrosion;
if moisture is found, cleaning and drying the components;
if corrosion is found, either cleaning or replacing the
component, depending on the severity;
if moisture or corrosion is found, locating and
eliminating the source;
inspecting the nose avionics wire harnesses for proper
installation, and if any wire harness is not installed properly,
securing it with cable ties; and
removing the A017 component PCB, part number (P/N) 101-
342536-1, and replacing it with a new A017 component PCB, P/N 101-
342536-5 (or an approved FAA-equivalent part number).
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above including the
referenced service information above, the FAA has determined that AD
action should be taken to prevent the loss of the pilot and co-pilot
intercom, VHF communications, and passenger address system during
critical flight, which could result in loss of all communication during
critical phases of flight.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Raytheon Model 1900D airplanes of the same
type design, the proposed AD would require: (1) Inspecting the radio
switching panel and nose avionics wire harnesses for moisture and
corrosion; (2) removing the corrosion; (3) locating and correcting the
source of the moisture that is causing the corrosion; (4) repairing or
replacing the corroded part; and, (5) replacing the A017 component PCB
with a new A017 component PCB that has internal overcurrent protection
fuses. Accomplishment of the proposed AD would be in accordance with
Raytheon Service Bulletin (SB) No. 2643, dated August, 1996.
Cost Impact
The FAA estimates that 160 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 4
workhours per airplane to accomplish the proposed action, and that the
average labor rate is approximately $60 an hour. Parts cost
approximately $370 per airplane. Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be $97,600
or $610 per airplane.
Raytheon has informed the FAA that they have shipped approximately
127 A017 component PCB's to the owners/operators of the affected
airplanes. With this information in mind, the FAA would presume that
127 of the airplanes have already accomplished the proposed action,
thereby reducing the total cost impact of the proposed AD on U.S.
operators by $77,470 from $97,600 to $20,130.
Regulatory Impact
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
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
[[Page 3280]]
economic impact, positive or negative, on a substantial number of small
entities under the criteria of the Regulatory Flexibility Act. A copy
of the draft regulatory evaluation prepared for this action has been
placed 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, Safety.
The Proposed Amendment
Accordingly, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Raytheon Aircraft Company: Docket No. 97-CE-68-AD.
Applicability: Model 1900D airplanes (serial numbers UE-1
through UE-160), 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 (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 the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required within the next 1,000 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished.
To prevent the loss of the pilot and co-pilot intercom, VHF
communications, and passenger address system, which could result in
loss of all communication during critical phases of flight,
accomplish the following:
(a) Inspect the electrical connectors, the radio switching panel
and its relay printed circuit boards (PCB's) for moisture and
corrosion in accordance with the Accomplishment Instructions in
Raytheon Service Bulletin (SB) No. 2643, dated August, 1996.
(1) If moisture is found, prior to further flight, clean and dry
the component in accordance with the Accomplishment Instructions in
Raytheon Service Bulletin (SB) No. 2643, dated August, 1996.
(2) If corrosion is found, prior to further flight, either clean
or replace the component, depending on the severity, in accordance
with the Accomplishment Instructions in Raytheon Service Bulletin
(SB) No. 2643, dated August, 1996.
(3) If moisture or corrosion is found, prior to further flight,
locate and eliminate the source (i.e., crack, hole, leak) in
accordance with the Accomplishment Instructions in Raytheon Service
Bulletin (SB) No. 2643, dated August, 1996.
(b) Inspect the nose avionics wire harnesses for proper
installation, and if any wire harness is not installed properly,
prior to further flight, secure it with cable ties in accordance
with the Accomplishment Instructions in Raytheon Service Bulletin
(SB) No. 2643, dated August, 1996.
(c) Remove the A017 component PCB, part number (P/N) 101-342536-
1, and replace the PCB with a new A017 component PCB (P/N 101-
342536-5 or an FAA-approved equivalent part number) in accordance
with the Accomplishment Instructions in Raytheon Service Bulletin
(SB) No. 2643, dated August, 1996.
(d) 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.
(e) 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, Room
100, 1801 Airport Rd., Wichita, Kansas 67209. The request shall be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, Wichita Aircraft
Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita Aircraft Certification Office.
(f) All persons affected by this directive may obtain copies of
the document referred to herein upon request to Raytheon Aircraft
Company, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine
this document at the FAA, Central Region, Office of the Regional
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
Issued in Kansas City, Missouri, on January 14, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-1461 Filed 1-21-98; 8:45 am]
BILLING CODE 4910-13-U