Federal Register / Vol. 62, No. 244 / Friday, December 19, 1997 / Proposed Rules 66565

Compliance: Required within the next 6

calendar months after the effective date of

this AD, unless already accomplished.

To prevent loss of aileron and flap control

caused by an inspection hole cover entering

the fuselage, which could result in loss of

control of the sailplane, accomplish the

following:

(a) Modify the inspection hole cover in the

fuselage area in accordance with the

Instructions: section of Alexander Schleicher

Technical Note No. 7, dated September 11,

1978.

Note 2: Alexander Schleicher Technical

Note No. 7 specifies taping the inspection

hole cover after the modification to reduce

noise and rattle and improve the

aerodynamics. Although this action does not

address the unsafe condition specified in this

AD, the FAA recommends taping the

inspection hole cover after accomplishing the

modification required by paragraph (a) of this

AD.

(b) 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.

(c) 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, FAA, 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(d) Questions or technical information

related to Alexander Schleicher Technical

Note No. 7, dated September 11, 1978,

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.

Note 4: The subject of this AD is addressed

in German AD No. 78–303, dated November

13, 1978.

Issued in Kansas City, Missouri, on

December 11, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–33141 Filed 12–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–74–AD]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal

Aerospace Bendix/King Model KSA

470 Autopilot Servo Actuators, Part

Numbers 065–0076–10 Through 065–

0076–15

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

AlliedSignal Aerospace Bendix/King

Model KSA 470 autopilot servo

actuators, part numbers 065–0076–10

through 065–0076–15, that are installed

on aircraft. The proposed AD would

require replacing the autopilot servo

actuator with a modified actuator. The

proposed AD is the result of two reports

of the affected autopilot servo actuators

containing loose roll pins within the

servo housing. Loose roll pins could fall

out, become lodged in the output shaft

clutch mechanism, and prevent this

mechanism from disengaging. The

actions specified by the proposed AD

are intended to prevent such an

occurrence, which could result in

increased effort by the pilot to control

the aircraft and possible loss of control

of the affected flight control axis.

DATES: Comments must be received on

or before February 19, 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–74–

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

AlliedSignal Aerospace, Commercial

Avionics Systems, 400 N. Rogers Road,

Olathe, Kansas 66062–1212. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Joel Ligon, Aerospace Engineer, Wichita

Aircraft Certification Office, FAA, 1801

Airport Road, Mid-Continent Airport,

Wichita, Kansas 67209; telephone (316)

946–4138; 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–74–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–74–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Discussion

AlliedSignal Aerospace recently

advised the FAA that an unsafe

condition may exist on certain Bendix/

King Model KSA 470 autopilot servo

actuators, part numbers 065–0076–10

through 065–0076–15, that are installed

on aircraft. AlliedSignal reports two

incidents where the roll pins within the

servo housing became loose on the

affected autopilot servo actuators. An

analysis of the design of the affected

servo actuators reveals that the roll pin

holes are larger than that recommended

by the roll pin specification.

Loose roll pins could fall out and

become lodged in the output shaft

clutch mechanism, which would

prevent this mechanism from

disengaging. This condition, if not
66566 Federal Register / Vol. 62, No. 244 / Friday, December 19, 1997 / Proposed Rules

corrected in a timely manner, could

result in increased effort by the pilot to

control the aircraft and possible loss of

control of the affected flight control

axis.

Relevant Service Information

AlliedSignal Aerospace has issued

Bendix/King Service Bulletin No. SB

KSA 470–3, dated May 1997. This

service bulletin references a factory

modification (Mod 3) that, when

incorporated, corrects the servo actuator

roll pin condition described above. This

service bulletin lists the following

aircraft that the affected AlliedSignal

Aerospace Bendix King Model KSA 470

actuators are installed in:

Aircraft Type FD/AP System KSA 470 Part

No. Location

Raytheon 400 series ................................................................. KFC 400 ................................. 065–0076–11 Yaw axis.

065–0076–15 Roll axis.

Raytheon 200 series ................................................................. KFC 400 ................................. 065–0076–11 Yaw axis.

Raytheon 300 series ................................................................. KFC 400 ................................. 065–0076–15 Yaw axis.

Raytheon 350 series ................................................................. KFC 400 ................................. 065–0076–15 Yaw axis.

Dassault Falcon 20 ................................................................... KFC 400 ................................ 065–0076–15 Pitch axis.

065–0076–15 Roll axis.

Fairchild C26A/C26B ................................................................. KFC400 .................................. 065–0076–11 Yaw axis.

Fairchild SA227–AC/AT/BC/CC/DC .......................................... KFC400 .................................. 065–0076–15 Roll axis.

Learjet 31A ................................................................................ KFC 3100 ............................... 065–0076–12 Pitch axis.

065–0076–14 Yaw axis.

065–0076–15 Roll axis.

Lockheed S–2 Tracker .............................................................. KFC 325 ................................. 065–0076–10 Special.

Piper 400LS and PA–42–1000 ................................................. KFC 400 ................................ 065–0076–15 Yaw axis.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

including the service information

previously referenced, the FAA has

determined that AD action should be

taken to prevent the servo actuator roll

pins from becoming loose; falling out;

becoming lodged in the output shaft

clutch mechanism; and preventing this

mechanism from disengaging, which

could result in increased effort by the

pilot to control the aircraft and possible

loss of control of the affected flight

control axis.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in AlliedSignal Aerospace

Bendix/King Model KSA 470 autopilot

servo actuators, part numbers 065–

0076–10 through 065–0076–15, that are

installed on aircraft, the FAA is

proposing an AD. The proposed AD

would require replacing the autopilot

servo actuator with an actuator

incorporating Mod 3. Accomplishment

of the proposed modifications would be

required in accordance with the

applicable maintenance manual.

Cost Impact

The FAA estimates that 500 of the

affected servo actuators could be

installed on aircraft in the U.S. registry.

The proposed replacement would take

approximately 2 workhours per airplane

to accomplish, at an average labor rate

of approximately $60 an hour. Servo

actuators with Mod 3 incorporated cost

$2,350. Based on these figures, the total

cost impact of the proposed AD on U.S.

operators is estimated to be $1,235,000,

or $2,470 per aircraft. These figures are

based on the presumption that no

owner/operator of the affected aircraft

has accomplished the proposed

replacement.

AlliedSignal has informed the FAA

that costs of the required labor and

modification of the servo actuators on

affected aircraft may be recovered under

an AlliedSignal conditional warranty

program. Information regarding

warranty claims associated with this

action can be obtained directly from

AlliedSignal at the address included in

the ADDRESSES section of the proposed

AD.

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

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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

Alliedsignal Aerospace: Docket No. 97–

CE–74–AD.

Applicability: Bendix/King Model KSA 470

Autopilot Servo Actuators; part numbers

065–0076–10 through 065–0076–15; serial

numbers 0001 through 3081; that are

installed on, but not limited to, the following

aircraft, certificated in any category:

Note 1: This subject is addressed in

AlliedSignal Bendix/King Service Bulletin

No. SB KSA 470–3, dated May 1997. This

service bulletin references serial number

3082. Regardless of this reference, serial

number 3082 is not affected by this AD.
Federal Register / Vol. 62, No. 244 / Friday, December 19, 1997 / Proposed Rules 66567

Aircraft type FD/AP system KSA 470 Part

No. Location

Raytheon 400 Series ............................................ KFC 400 .............................................................. 065–0076–11 Yaw axis.

065–0076–15 Roll axis.

Raytheon 200 Series ............................................ KFC 400 .............................................................. 065–0076–11 Yaw axis.

Raytheon 300 Series ............................................ KFC 400 .............................................................. 065–0076–15 Yaw axis.

Raytheon 350 Series ............................................ KFC 400 .............................................................. 065–0076–15 Yaw axis.

Dassault Falcon 20 ............................................... KFC 400 .............................................................. 065–0076–15 Pitch axis.

065–0076–15 Roll axis.

Fairchild C26A/C26B ............................................ KFC 400 .............................................................. 065–0076–11 Yaw axis.

Fairchild SA227–AC/AT/BC/CC/DC ...................... KFC 400 .............................................................. 065–0076–15 Roll axis.

Learjet 31A ............................................................ KFC 3100 ............................................................ 065–0076–12 Pitch axis.

065–0076–14 Yaw axis.

065–0076–15 Roll axis.

Lockheed S–2 Tracker .......................................... KFC 325 .............................................................. 065–0076–10 Special.

Piper 400LS and PA–42–1000 ............................. KFC 400 .............................................................. 065–0076–15 Yaw axis.

Note 2: This AD applies to each aircraft

identified in the preceding applicability

provision that incorporates one of the

affected actuators, regardless of whether it

has been modified, altered, or repaired in the

area subject to the requirements of this AD.

For aircraft 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 (d) 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 100

hours time-in-service after the effective date

of this AD, unless already accomplished.

To prevent the servo actuator roll pins

from becoming loose; falling out; becoming

lodged in the output shaft clutch mechanism;

and preventing this mechanism from

disengaging, which could result in increased

effort by the pilot to control the aircraft and

possible loss of control of the affected flight

control axis, accomplish the following:

(a) Replace the autopilot servo actuator

with an actuator that incorporates Mod 3 in

accordance with the applicable maintenance

manual. This modification changes the size

of the servo actuator roll pin holes to assure

that the pins do not become loose and fall

out.

(b) As of the effective date of this AD, no

person may install, on aircraft, one of the

affected servo actuators that does not

incorporate Mod 3.

(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 airplane 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, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Room 100, Mid-Continent Airport,

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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(e) All persons affected by this directive

may obtain copies of the documents referred

to herein upon request to AlliedSignal

Aerospace, Technical Publications,

Department 65–70, P.O. Box 52170, Phoenix,

Arizona 85072–2170; or may examine these

documents 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

December 10, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–33146 Filed 12–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–109–AD]

RIN 2120–AA64

Airworthiness Directives; Alexander

Schleicher Segelflugzeugbau Model

ASK–21 Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Alexander Schleicher Segelflugzeugbau

(Alexander Schleicher) Model ASK–21

sailplanes that do not have a certain

automatic elevator connection installed.

The proposed AD would require drilling

a drainage hole in the elevator pushrod,

inspecting the elevator pushrod for

corrosion damage, and replacing any

elevator pushrod if a certain amount of

corrosion damage is found. The

proposed AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for Germany. The actions

specified by the proposed AD are

intended to prevent failure of the

elevator pushrod caused by corrosion

damage, which could result in loss of

control of the sailplane.

DATES: Comments must be received on

or before January 19, 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–

109–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

Alexander Schleicher Segelflugzeugbau,

6416 Poppenhausen, Wasserkuppe,

Federal Republic of Germany. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

J. Mike Kiesov, Project Officer,

Sailplanes/Gliders, Small Airplane

Directorate, Aircraft Certification

Service, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106; telephone

(816) 426–6932; facsimile (816) 426–

2169.

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