Federal Register / Vol. 63, No. 81 /Tuesday, April 28, 1998 /Rules and Regulations 23203

Alexander Schleicher Technical Note No. 20,

dated October 16, 1987.

(b) If there is any displacement of the

plastic S-shaped rudder pedal tube, prior to

further flight, correct the placement in

accordance with the Actions sections 1.1, 1.2,

and 1.3 of Alexander Schleicher Technical

Note No. 20, dated October 16, 1987.

(c) 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 sailplane

to a location where the requirements of this

AD can be accomplished.

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, Aircraft Certification Service,

1201 Walnut, suite 900, Kansas City,

Missouri 64106. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(e) Questions or technical information

related to Alexander Schleicher Technical

Note No. 20, dated October 16, 1987, should

be directed to Alexander Schleicher,

Segelflugzeugbau, 6416 Poppenhausen,

Wasserkuppe, Federal Republic of Germany;

telephone: 49.6658.890 or 49.6658.8920;

facsimile: 49.6658.8923 or 49.6658.8940.

This service information may be examined at

the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

(f) The inspection and correction required

by this AD shall be done in accordance with

Alexander Schleicher Technical Note No. 20,

dated October 16, 1987. 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 Alexander Schleicher,

Segelflugzeugbau, 6416 Poppenhausen,

Wasserkuppe, Federal Republic of Germany.

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.

Note 3: The subject of this AD is addressed

in German AD No. 88–2 Schleicher, dated

January 18, 1988.

(g) This amendment becomes effective on

June 14, 1998.

Issued in Kansas City, Missouri, on April

17, 1998.

James A. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–11006 Filed 4–27–98; 8:45 am]

BILLING CODE 4910–13–U

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.

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-inservice (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.’’
23204 Federal Register / Vol. 63, No. 81 /Tuesday, April 28, 1998 /Rules and Regulations

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.

§ 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