21980 Federal Register / Vol. 61, No. 93 / Monday, May 13, 1996 / Proposed Rules

The actions would be required to be

accomplished in accordance with the

service bulletin described previously.

The FAA estimates that 23 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour per airplane

to accomplish the proposed actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the proposed AD on U.S.

operators is estimated to be $1,380, or

$60 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

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 proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the 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 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, 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Beech Aircraft Company (Formerly

DeHavilland; Hawker Siddeley; British

Aerospace, PLC; Raytheon Corporate

Jets, Inc.): Docket 95–NM–165–AD.

Applicability: Model BAe 125–800A and

–1000A, and Model Hawker 800 and 1000

series airplanes; on which Modification

257676A has not been accomplished

(reference Hawker Service Bulletin SB.30–

61–7676A or Aerospace Systems and

Technology Service Bulletin S.B.30–25);

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (c) 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.

Note 2: Beech (Raytheon) Model BAe 125–

800B and BAe 125–1000B series airplanes are

similar in design to the airplanes that are

subject to the requirements of this AD and,

therefore, also may be subject to the unsafe

condition addressed by this AD. However, as

of the effective date of this AD, those models

are not type certificated for operation in the

United States. Airworthiness authorities of

countries in which the Model BAe 125–800B

and BAe 125–1000B series airplanes are

approved for operation should consider

adopting corrective action, applicable to

those models, that is similar to the corrective

action required by this AD.

Compliance: Required as indicated, unless

accomplished previously.

To ensure that silver plate wiring is

removed from the TKS metering pump and

a possible fire hazard eliminated, accomplish

the following:

(a) Within 3 months after the effective date

of this AD, modify the TKS pump in

accordance with Hawker Service Bulletin

SB.30–61–7676A, dated February 15, 1995.

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

person shall install on any airplane a TKS

metering pump, having part number

XA9511E003–3 or XA9511E009, unless it has

been modified in accordance with the

requirements of paragraph (a) of this AD.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

Issued in Renton, Washington, on May 3,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–11825 Filed 5–10–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–CE–39–AD]

RIN 2120—AA64

Airworthiness Directives; H.B.

Flugtechnik GmbH 23/2400 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 H.B.

Flugtechnik GmbH (Flugtechnik) 23/

2400 sailplanes. The proposed action

would require inspecting the rudder

bearing support bracket for cracks,

replacing the bracket if cracked, and

modifying the bracket with a third bolt

if no cracks are found. Cracks found in

the rudder bearing support brackets

during routine inspections prompted

the proposed action. The actions

specified by the proposed AD are

intended to prevent cracks in the rudder

bearing support bracket, which could

cause loss of control of the rudder and

possible loss of control of the sailplane.

DATES: Comments must be received on

or before July 15, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 95–CE–39–

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 H.B.

Flugtechnik GmbH, attn: Dr. Adolf

Scharf STR, 42 P.F. 74, A–4053, Haid,

Austria. This information also may be

examined at the Rules Docket at the

address below. Send comments on the
Federal Register / Vol. 61, No. 93 / Monday, May 13, 1996 / Proposed Rules 21981

proposal in triplicate to the Federal

Aviation Administration (FAA), Central

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–CE–39–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.

FOR FURTHER INFORMATION CONTACT: Mr.

Herman C. Belderok, 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

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. 95–CE–39–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

Assistant Chief Counsel, Attention:

Rules Docket No. 95–CE–39–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Discussion

The Austro Control GmbH (ACG),

which is the airworthiness authority for

Austria, notified the FAA that an unsafe

condition may exist on certain

Flugtechnik HB 23/2400 sailplanes. The

ACG reports that, upon routine

inspections of certain Flugtechnik HB

23/2400 sailplanes, cracks are appearing

in the rudder bearing support bracket.

This condition, if not detected and

corrected, could result in loss of control

of the rudder and possible loss of

control of the sailplane.

Flugtechnik has issued service

bulletin (SB) HB 23/19/91, dated

October 5, 1991, which specifies

procedures for inspecting the rudder

bearing support bracket for cracks,

replacing the bracket if cracks are found

and modifying the bracket with a third

bolt if no cracks are found.

The ACG classified this service

bulletin as mandatory and issued AD

No. 68, dated October 28, 1991, in order

to assure the continued airworthiness of

these sailplanes in Austria.

This sailplane model is manufactured

in Austria and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the ACG has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the ACG,

reviewed all available information

including the service information

referenced above, and determined that

AD action is necessary for products of

this type design that are certificated for

operation in the United States.

Since an unsafe condition has been

identified that is likely to exist or

develop in other certain Flugtechnik 23/

2400 sailplanes of the same type design

registered in the United States, the

proposed AD would require inspecting

the rudder bearing support bracket for

cracks, and replacing the bracket with a

new bracket with 3 bolt holes, or

modifying the bracket by making a third

hole and installing a new bolt.

Accomplishment of the proposed

installation would be in accordance

with Flugtechnik SB HB 23/19/91, dated

October 5, 1991.

The FAA estimates that one sailplane

in the U.S. registry would be affected by

the proposed AD, that it would take

approximately 1 workhour per sailplane

to accomplish the proposed action, and

that the average labor rate is

approximately $60 an hour. Parts cost

approximately $5 per sailplane. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $65. The FAA has no

way of determining whether the one

sailplane owner/operator has replaced

or modified the rudder bearing support

bracket and this figure takes into

account that the affected sailplane

operator has not accomplished the

proposed action.

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 USC 106(g), 40113, 44701.

§ 39.13 [AMENDED]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

H.B. Flugtechnik: Docket No. 95–CE–39–AD.

Applicability: Model 23/2400 Sailplanes

(serial numbers 23001 through 23048),

certificated in any category.

Note 1: This AD applies to each sailplane

identified in the preceding applicability
21982 Federal Register / Vol. 61, No. 93 / Monday, May 13, 1996 / Proposed Rules

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

sailplanes 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 (c) 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 50

hours time-in- service (TIS) after the effective

date of this AD, unless already accomplished.

To prevent the rudder bearing support

bracket from cracking, which could cause

loss of rudder control and possible loss of the

sailplane, accomplish the following:

(a) Inspect (one time) the rudder bearing

support bracket with a 10x magnifying glass

for any visible cracks in accordance with the

Actions section of Flugtechnik service

bulletin (SB) HB–23/19/91, dated October 5,

1991.

(1) If cracks are found, prior to further

flight, replace the rudder bearing support

bracket with a new support bracket that has

3 bolt holes in accordance with the Actions

section of Flugtechnik SB HB–23/19/91,

dated October 5, 1991.

(2) If no cracks are found, modify the

rudder bearing support bracket by installing

a third bolt (part number M6x30) or replace

the bracket with a new bracket that has 3 bolt

holes in accordance with the Actions section

of Flugtechnik SB HB–23/19/91, dated

October 5, 1991.

(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, Aircraft Certification Service,

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane Directorate

Aircraft Certification Office.

(d) All persons affected by this directive

may obtain copies of this document referred

to herein upon request to H.B. Flugtechnik

GmbH, attn: Dr. Adolf Scharf STR, 42 P.F. 74,

A–4053, Haid, Austria; or may examine this

document at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Issued in Kansas City, Missouri, on May 6,

1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–11880 Filed 5–10–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–63–AD]

RIN 2120–AA64

Airworthiness Directives; Gates Learjet

Model 35 and 36 Series Airplanes

Modified by Raisbeck STC SA766NW

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Gates Learjet Model 35 and 36

series airplanes that have been modified

in accordance with Raisbeck

Supplemental Type Certificate (STC)

SA766NW. This proposal would require

a reduction of the maximum operating

limit speed on the affected airplanes to

prevent encountering certain potentially

hazardous conditions. This proposal is

prompted by reports of incidents of

aileron buffet or buzz experienced

during high speed cruise. The actions

specified by the proposed AD are

intended to prevent aileron buffet or

buzz conditions, which can result in the

deterioration of the aircraft lateral

control system characteristics to an

unacceptable level.

DATES: Comments must be received by

June 24, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

63–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

Information concerning the subject of

this rulemaking action may be obtained

from Jet Air Corporation, P.O. Box 245,

Bellevue, Washington 98009.

Information concerning this rulemaking

action may be examined at the FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Stan

Wood, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington;

telephone (206) 227–2772; fax (206)

227–1181.

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 shall

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

summarizing 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 Number 96–NM–63–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, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

96–NM–63–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On July 23, 1985, the FAA issued AD

85–16–04, amendment 39–5110 (50 FR

30803, July 30, 1985), which is

applicable to certain Gates Learjet

Model 35 and 36 series airplanes that

have been modified in accordance with

Raisbeck Supplemental Type Certificate

(STC) SA766NW. That AD requires the

accomplishment of one of two optional

actions, both of which are intended to

prevent the airplane from encountering

the potentially hazardous condition of

aileron buffet or buzz:

1. One optional action requires

operators to reduce permanently the

maximum operating Mach limit (MMO)

of these airplanes from .83 to .80. This

action includes resetting the Mach