[Federal Register Volume 63, Number 81 (Tuesday, April 28, 1998)]
[Rules and Regulations]
[Pages 23203-23204]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11014]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-68-AD; Amendment 39-10493; AD 98-09-12]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Model 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) Model 1900D
airplanes (formerly known as Beech Aircraft Corporation Model 1900D
airplanes). This AD requires 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 use of the pilot/co-pilot intercom
system, VHF communication system, and public address system while in
flight prompted this action. The actions specified by this 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: Effective June 12, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 12, 1998.
ADDRESSES: Service information that applies to this AD may be obtained
from Raytheon Aircraft Company, P. O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043. This information may also be examined
at 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; or at the Office
of the Federal Register, 800 North Capitol Street, NW, suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Harvey Nero, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, Room 100, 1801 Airport Rd.,
Wichita, Kansas 67209; telephone: (316) 946-4137; facsimile: (316) 946-
4407.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to certain Raytheon
Model 1900D airplanes was published in the Federal Register as a notice
of proposed rulemaking (NPRM) on January 22, 1998 (63 FR 3278). The
NPRM proposed to 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.
Accomplishment of the proposed action as specified in the NPRM would be
in accordance with Raytheon Service Bulletin No. 2643, dated August,
1996.
The NPRM was the result of several reported incidents of lost
pilot/co-pilot intercom ability, VHF communication ability, and public
address system ability while in flight.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the following comment.
The commenter agrees with the proposed action, but states the
differences in frequency of flying time of the affected airplanes needs
to be taken into account when computing the compliance time. Some of
the airplanes may fly as much as 60 hours per week, while others may
only fly 3 hours per week. A compliance time of 1,000 hours after the
effective date of the AD could, in some cases, not require the operator
to comply with the AD for over 2 years. The commenter suggests that a
calendar compliance be added to the compliance time to assure that all
operators have accomplished the proposed action within a reasonable
amount of time.
The FAA partially concurs. Since the proposed action is the result
of moisture and corrosion, the electrical parts affected could corrode
regardless of whether the airplane is in service. The final rule will
reflect a change in the compliance time to assure that the affected
airplanes that have a low number of hours in service per year will be
in compliance within a reasonable amount of time. Based on this
comment, the compliance time will change from ``within the next 1,000
hours time-in-service (TIS) after the effective date'' to ``within the
next 1,000 hours TIS or within the next 180 days after the effective
date of this AD, whichever occurs first.''
[[Page 23204]]
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
a change to the compliance time and minor editorial corrections. The
FAA has determined that the change in compliance time and these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Cost Impact
The FAA estimates that 160 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 4 workhours per
airplane to accomplish this 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 this AD on U.S.
operators is estimated to be $97,600 or $610 per airplane.
Raytheon has informed the FAA that it has shipped approximately 127
A017 component PCB's to the owners/operators of the affected airplanes.
With this information in mind, the FAA will presume that 127 of the
airplanes already have replacement components installed; thereby
reducing the total cost impact of this AD on U.S. operators by $77,470,
from $97,600 to $20,130.
Regulatory Impact
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.
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, 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. 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:
98-09-12 Raytheon Aircraft Company (Type Certificate No. A24CE
formerly held by the Beech Aircraft Corporation): Amendment 39-
10493; 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) or within the next 180 days after the effective date of this
AD, whichever occurs first, 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 SB No. 2643, dated August, 1996.
(2) If corrosion is found, prior to further flight, either clean
or replace the component, as defined in and in accordance with the
Accomplishment Instructions in Raytheon 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 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 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 SB No. 2643, dated
August, 1996.
(d) Special flight permits may be issued in accordance with
sections 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
(ACO), 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 ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(f) The inspections, modifications, and replacements required by
this AD shall be done in accordance with Raytheon Aircraft Mandatory
Service Bulletin 1900D No. 2643, dated August, 1996. 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 Raytheon Aircraft Company, P. O. Box
85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA,
Central Region, Office of the Regional 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.
(g) This amendment becomes effective on June 12, 1998.
Issued in Kansas City, Missouri, on April 20, 1998.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-11014 Filed 4-27-98; 8:45 am]
BILLING CODE 4910-13-U
