29276 Federal Register / Vol. 61, No. 112 / Monday, June 10, 1996 / Rules and Regulations

N 001A561A0000205 is installed on the

right-hand side of the cockpit: Within

24 hours after receipt of this AD, revise

the Limitations Section of the FAAapproved Airplane Flight Manual

(AFM) to include the following

statement. This may be accomplished by

inserting a copy of this AD in the AFM.

‘‘Flight above 10,000 feet mean sea level

(MSL) is prohibited.’’

(b) For all airplanes: Within 45 days after

receipt of this AD, replace any windshield

having P/N 001A561A0000204 (left-hand

side), or P/N 001A61A0000205 (right-hand

side); with a new windshield having P/N

001A561A0000200 (left-hand side), or P/N

001A561A0000201 (right-hand side); in

accordance with Dornier Service Bulletin

SB–328–56–165, dated April 19, 1996.

Following this replacement, the AFM

limitation required by paragraph (a) of this

AD may be removed.

(c) For all airplanes: Within 24 hours

(clock hours, not flight hours) following any

incident of shattering or cracking of either

front windshield, submit a report containing

the serial number of the airplane and the part

number of the affected windshield to: Connie

Beane, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate, 1601

Lind Avenue SW., Renton, Washington

98055–4056; fax (206) 227–1149. This

reporting requirement is applicable to

findings on all windshields, including the

replacement windshields required by

paragraph (b) of this AD. Information

collection requirements contained in this

regulation have been approved by the Office

of Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB control number 2120–0056.

(d) As of the date of receipt of this AD, no

person shall install a windshield having P/

N 001A561A0000204 (left-hand side), or P/N

001A561A0000205 (right-hand side), on any

airplane.

(e) 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 Maintenance Inspector,

who may add comments and then send it to

the Manager, Standardization Branch, ANM–

113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(f) 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.

(g) The replacement shall be done in

accordance with Dornier Service Bulletin

SB–328–56–165, dated April 19, 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 Dornier

Luftfahrt GmbH, P.O. Box 1103, D–82230

Wessling, Germany. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(h) This amendment becomes effective on

June 17, 1996, to all persons except those

persons to whom it was made immediately

effective by emergency AD 96–11–15, issued

May 24, 1996, which contained the

requirements of this amendment.

Issued in Renton, Washington, on May 31,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14227 Filed 6–7–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–122–AD; Amendment

39–9659; AD 96–12–16]

RIN 2120–AA64

Airworthiness Directives; Beech

(Raytheon) Model BAe 125 Series 800A

and Model Hawker 800 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Beech (Raytheon)

Model BAe 125 series 800A and Model

Hawker 800 airplanes, that requires

modification of the airframe structure in

the lower area of the fuselage aft of the

wing rear spar. For certain airplanes,

this amendment also requires a

functional test to determine if a

particular bolt fouls the flap control

system. This amendment is prompted

by reports of restricted control of the

aileron due to water accumulation that

froze in the area around an aileron

pulley located in the lower area of the

fuselage aft of the wing rear spar. The

actions specified by this AD are

intended to prevent such water

accumulation, which could freeze and

result in restricted control of the

ailerons; subsequently, this could

reduce the pilot’s ability to initiate roll

control during critical phases of flight.

DATES: Effective July 15, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 15,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Co., Manger

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 Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1149.

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 certain Beech

(Raytheon) Model BAe 125 series 800A

and Model Hawker 800 airplanes was

published in the Federal Register on

February 9, 1996 (61 FR 4943). That

action proposed to require modification

of the airframe structure in the lower

area of the fuselage aft of the wing rear

spar. For certain airplanes, that action

also proposed to require a functional

test to determine if a bolt fouls the flap

control system.

No Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Editorial Changes Made to the Final

Rule

The FAA has revised the final rule to

correctly designate the affected airplane

models as ‘‘Beech (Raytheon) Model

BAe 125 series 800A and Model Hawker

800 airplanes.’’

Additionally, a new ‘‘Note 2’’ has

been added to the final rule to clarify

that airworthiness authorities of

countries in which Beech (Raytheon)

Model BAe 125 series 800B airplanes

are approved for operation should

consider adopting corrective action that

is similar to that required by this AD.

Those airplane models are not

certificated for operation in the United

States, but are similar in design to the

affected airplanes and, thus, may be

subjected to the same unsafe condition

addressed by this AD.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will
Federal Register / Vol. 61, No. 112 / Monday, June 10, 1996 / Rules and Regulations 29277

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 163 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 25

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts be supplied by the

manufacturer at no cost to the operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $244,500, or $1,500 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:

96–12–16 Beech Aircraft Corporation.

(Formerly deHavilland; Hawker

Siddeley; British Aerospace, plc;

Raytheon Corporate Jets, Inc.):

Amendment 39–9659. Docket 95–NM–

122–AD.

Applicability: Model BAe 125 series 800A

airplanes (including military variants C–29A

and U–125); and Model Hawker 800

airplanes, excluding airplanes having

constructor’s numbers 258079 and 258213;

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 (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.

Note 2: Beech (Raytheon) Model BAe 125

series 800B 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 operations in the

United States. Airworthiness authorities of

countries in which the Model BAe 125 series

800B 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 restricted control of the

ailerons, which could reduce the pilot’s

ability to initiate roll control during critical

phases of flight, accomplish the following:

(a) For all airplanes, except Model BAe 125

series 800A airplane having constructor’s

number 258186: Within 6 months after the

effective date of this AD, modify (including

functional test) the airframe structure in the

lower area of the fuselage aft of the wing rear

spar, in accordance with Hawker Service

Bulletin SB.53–82–3566G, Revision 3,

December 14, 1995.

(b) For airplanes identified in paragraph (a)

of this AD on which Hawker Modification

253566G has been installed prior to the

effective date of this AD, in accordance with

Hawker Service Bulletin SB.53–82–3566G,

dated March 1, 1995, Revision 1, dated

March 14, 1995, or Revision 2, dated May 3,

1995: Within 30 days after the effective date

of this AD, perform a functional test to

determine if a bolt fouls the flap control

system, in accordance with paragraph

2.A.(18) of the Accomplishment Instructions

of Hawker Service Bulletin SB.53–82–3566G,

Revision 3, dated December 14, 1995. If any

foul is detected, prior to further flight, repair

in accordance with a method approved by

the Manager, Standardization Branch, ANM–

113, Transport Airplane Directorate, FAA.

(c) For Model BAe 125 series 800A

airplane having constructor’s number

258186: Within 6 months after the effective

date of this AD, modify the airframe structure

in the lower area of the fuselage aft of the

wing rear spar, in accordance with Hawker

Service Bulletin SB.53–85–3566D, dated

March 10, 1995, or Revision 1, dated May 23,

1995.

(d) 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.

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(e) 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.

(f) For certain airplanes, the modification

and functional test shall be done in

accordance with Hawker Service Bulletin

SB.53–82–3566G, Revision 3, dated

December 14, 1995. For certain other

airplanes, the modification and functional

test shall be done in accordance with Hawker

Service Bulletin SB.53–85–3566D, dated

March 10, 1995, or Hawker Service Bulletin

SB.53–85–3566D, Revision 1, dated May 23,

1995. 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 Co., Manger 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 Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(g) This amendment becomes effective on

July 15, 1996.

Issued in Renton, Washington, on May 31,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14229 Filed 6–7–96; 8:45 am]

BILLING CODE 4910–13–U