AD 98-09-12

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.

Final rule

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 theAccomplishment 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.

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.

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 theU.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.

39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows: