This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

45709

Vol. 62, No. 168

Friday, August 29, 1997

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–228–AD; Amendment

39–10117; AD 97–18–07]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model BAe 125–800A Series Airplanes,

and Model Hawker 800 and Hawker

800XP Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon Model

BAe 125–800A series airplanes, and

Model Hawker 800 and 800XP series

airplanes, that requires modification of

the rudder. This amendment is

prompted by a report indicating that,

due to the existing design of the rudder,

overbias or overbalance of the rudder

occurs during single engine handling.

The actions specified by this AD are

intended to prevent overbias or

overbalance of the rudder, which could

result in reduced controllability of the

airplane.

DATES: Effective October 3, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of October 3,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Manager Service Engineering, Hawker

Customer Support Department, P.O. Box

85, Wichita, Kansas 67201–0085. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

Wichita Aircraft Certification Office,

Small Airplane Directorate, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Larry Engler, Aerospace Engineer,

Airframe Branch, ACE–118W, FAA,

Wichita Aircraft Certification Office,

Small Airplane Directorate, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4122; fax (316)

946–4407.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Raytheon Model

BAe 125–800A series airplanes, and

Model Hawker 800 and 800XP series

airplanes was published in the Federal

Register on April 24, 1997 (62 FR

19950). That action proposed to require

modification of the rudder.

No comments were submitted in

response to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of this rule as proposed.

Cost Impact

There are approximately 295 Beech

(Raytheon) Model BAe 125–800A series

airplanes, and Model Hawker 800 and

Hawker 800XP series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 190 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 8 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$300 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$148,200, or $780 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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 final evaluation has

been prepared for this action and it is

contained in the rules docket. A copy of

it may be obtained from 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 the following new airworthiness

directive:

97–18–07 Raytheon Aircraft Company

(Formerly Beech, Raytheon Corporate

Jets, British Aerospace, Hawker Siddley,

et al.): Amendment 39–10117. Docket

96–NM–228–AD.

Applicability: Model BAe 125–800A, and

Model Hawker 800 and Hawker 800XP series

airplanes; on which Raytheon Modification
45710 Federal Register / Vol. 62, No. 168 / Friday, August 29, 1997 / Rules and Regulations

25F017A&B (reference Raytheon Service

Bulletin SB.55–36–25F017A&B) has not been

installed; 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 (b) 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: Raytheon Model BAe 125–800B

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 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 prevent overbias or overbalance of the

rudder, which could result in reduced

controllability of the airplane, accomplish

the following:

(a) Within 100 hours time-in-service or

within 6 months after the effective date of

this AD, whichever occurs first, modify the

rudder in accordance with Raytheon Service

Bulletin SB.55–36–25F017A&B, dated April

15, 1996.

(b) 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, Wichita

Aircraft Certification Office (ACO), FAA,

Small 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, 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.

(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) The modification shall be done in

accordance with Raytheon Service Bulletin

SB.55–36–25F017A&B, dated April 15, 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, Manager

Service Engineering, Hawker Customer

Support Department, P.O. Box 85, Wichita,

Kansas 67201–0085. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita Aircraft

Certification Office, Small Airplane

Directorate, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., Suite 700, Washington,

DC.

(e) This amendment becomes effective on

October 3, 1997.

Issued in Renton, Washington, on August

25, 1997.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–23102 Filed 8–28–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–41–AD; Amendment

39–10119; AD 97–18–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Airbus Model A310

and A300–600 series airplanes, that

currently requires a revision to the

Airplane Flight Manual (AFM) that

warns the flight crew of certain

consequences associated with

overriding the autopilot when it is in

the pitch control axis. That AD also

requires modification of certain flight

control computers (FCC). That AD was

prompted by the results of an FAA

review of the requirements of an earlier

AD. This amendment requires a

modification to the autopilot that would

enable the flight crew to disconnect the

autopilot when direct force is applied to

the control column, regardless of its

mode and the altitude of the airplane;

accomplishment of that modification

terminates the current requirement to

revise the AFM. This amendment also

requires repetitive operational testing of

the modified autopilot to determine if

the disconnect function operates

properly, and repair, if necessary. The

actions specified by this AD are

intended to prevent an out-of-trim

condition between the trimmable

horizontal stabilizer and the elevator,

which could severely reduce

controllability of the airplane.

DATES: Effective October 3, 1997.

The incorporation by reference of

certain publications, as listed in the

regulations, is approved by the Director

of the Federal Register as of October 3,

1997.

The incorporation by reference of

certain other publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

May 23, 1996 (61 FR 16873, April 18,

1996).

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2589; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 96–08–07,

amendment 39–9573 (61 FR 16873,

April 18, 1996), which is applicable to

all Airbus Model A310 and A300–600

series airplanes, was published in the

Federal Register on April 9, 1997 (62 FR

17131). The action proposed to

supersede AD 96–08–07 to continue to

require a revision to the Limitations

Section of the AFM that warns the flight

crew of certain consequences associated

with overriding the autopilot when it is

in the pitch control axis, and

modification of certain FCC’s.

The action also proposed to require a

modification to the autopilot that would

enable the flight crew to manually

disconnect it, regardless of the autopilot

mode and the altitude of the airplane.

After this modification has been

accomplished, the action proposed to

require removal of the revision to the

AFM that is currently required by AD

96–08–07. In addition, the action

proposed to require repetitive

operational testing of the modified

autopilot to determine if the disconnect

function operates properly, and repair,

if necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due