Federal Register / Vol. 61, No. 108 / Tuesday, June 4, 1996 / Rules and Regulations 28031

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–11–16 Fokker: Amendment 39–9640.

Docket 95–NM–172–AD.

Applicability: Model F28 Mark 0100

airplanes, serial numbers 11244 through

11277 inclusive, 11279, 11281 through 11287

inclusive, and 11289 through 11400

inclusive, 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 (g) 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 as indicated, unless

accomplished previously.

To prevent over-pressurization and/or

damage to the wing collector tanks, which

could result in reduced structural integrity of

the wings, accomplish the following:

(a) Within 45 days after the effective date

of this AD, perform a one-time measurement

during refueling to determine the pressure in

each collector tank in accordance with Part

1 of the Accomplishment Instructions of

Fokker Service Bulletin SBF100–57–030,

dated December 17, 1994.

Note 2: Pressure Limits Categories are

defined in Table 2 of Fokker Service Bulletin

SBF100–57–030, dated December 17, 1994.

(b) For Pressure Limits Category 1: Within

2 years after the effective date of this AD,

modify the four affected top-hat stringers

(2.32, 2.33, 2.34, and 2.35) in each outer wing

tank area by removing the restriction blocks,

in accordance with the Accomplishment

Instructions of Fokker Service Bulletin

SBF100–57–029, Revision 1, dated March 23,

1995.

(c) For Pressure Limits Categories 2

through 5: Except as provided by paragraph

(d) of this AD, prior to the number of

accumulated total flight cycles or within the

time specified in Table 1 of Fokker Service

Bulletin SBF100–57–030, dated December

17, 1994, whichever occurs earlier,

accomplish the requirements of paragraphs

(c)(1) and (c)(2) of this AD.

(1) Perform the Non-Destructive Test (NDT)

inspections specified in Part 2 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–57–030, dated

December 17, 1994, to detect cracking or

deformations of the collector tank ribs on

each wing at wing stations 1825, 2230, and

2635. These inspections are to be performed

in accordance with Fokker Service Bulletin

SBF100–57–030, dated December 17, 1994.

(2) Modify the four affected top-hat

stringers (2.32, 2.33, 2.34, and 2.35) in each

outer wing tank area by removing the

restriction blocks, in accordance with the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–57–029, Revision 1,

dated March 23, 1995.

(d) For Pressure Limits Category 6, and for

airplanes having pressure limits within the

limits specified in Categories 3 through 5 and

that have exceeded the number of

accumulated total flight cycles specified in

Table 1: Within 100 flight cycles, accomplish

the requirements of paragraphs (d)(1) and

(d)(2) of this AD.

(1) Perform the NDT inspections in

accordance with the procedures of Part 2 of

the Accomplishment Instructions of Fokker

Service Bulletin SBF100–57–030, dated

December 17, 1994. The fueling pressure

must not exceed 25 pounds per square inch

(PSI) during refueling.

(2) Modify the four affected top-hat

stringers (2.32, 2.33, 2.34, and 2.35) in each

outer wing tank area by removing the

restriction blocks, in accordance with the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–57–029, Revision 1,

dated March 23, 1995.

(e) For Pressure Limits Category 7: Prior to

further flight following the measurement

required by paragraph (a) of this AD,

accomplish the requirements of paragraphs

(e)(1) and (e)(2) of this AD.

(1) Perform the NDT inspections in

accordance with the procedures of Part 2 of

the Accomplishment Instructions of Fokker

Service Bulletin SBF100–57–030, dated

December 17, 1994.

(2) Modify the four affected top-hat

stringers (2.32, 2.33, 2.34, and 2.35) in each

outer wing tank area by removing the

restriction blocks, in accordance with the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–57–029, Revision 1,

dated March 23, 1995.

(f) If any cracking or deformation is

detected during any inspection required by

this AD, prior to further flight, repair in

accordance with a method approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate.

(g) 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 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.

(h) 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.

(i) The measurement and inspections shall

be done in accordance with Fokker Service

Bulletin SBF100–57–030, dated December

17, 1994. The modification shall be done in

accordance with Fokker Service Bulletin

SBF100–57–029, Revision 1, dated March 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 Fokker Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

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.

(j) This amendment becomes effective on

July 9, 1996.

Issued in Renton, Washington, on May 23,

1996.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–13608 Filed 6–3–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–180–AD; Amendment

39–9641; AD 96–11–17]

RIN 2120–AA64

Airworthiness Directives; Beech

(Raytheon) Model BAe 125 Series

1000A and Model Hawker 1000

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 1000A and Model

Hawker 1000 airplanes, that requires a

one-time inspection for adequate

clearances between, and damage to, the

flap cables and turnbuckles, airbrakes

cables and turnbuckles, and all other

flight control cables and turnbuckles at

keel subframe 15A; and various followon actions, if necessary. This

amendment is prompted by reports of

chafing due to insufficient clearance

between the flaps turnbuckle and the

subframe, and between the airbrakes

cable and the subframe. The actions

specified by this AD are intended to

prevent such chafing, which could

result in damage to the flaps turnbuckle

and the airbrakes cable, and subsequent

fraying or seizing of the flight control

cables. These conditions, if not

corrected, could result in restriction or

loss of the flight controls.

DATES: Effective July 9, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 9, 1996.

ADDRESSES: The service information

referenced in this AD may be obtained
28032 Federal Register / Vol. 61, No. 108 / Tuesday, June 4, 1996 / Rules and Regulations

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 Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Tim Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; 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 1000A

and Model Hawker 1000 airplanes was

published in the Federal Register on

March 12, 1996 (61 FR 9959). That

action proposed to require a one-time

visual inspection for adequate

clearances between, and/or damage to,

the flap cables and turnbuckles,

airbrakes cables and turnbuckles, and

all other flight control cables and

turnbuckles at keel subframe 15A (leftand right-hand side); and various

follow-on actions, if necessary.

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.

Changes 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 1000A and Model

Hawker 1000 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 and BAe

125 series 1000B airplanes are approved

for operation should consider adopting

corrective action that is similar to that

required by this AD, since those

airplanes are similar in design to the

affected airplanes.

Conclusion

After careful review of the available

data, including the comments noted

above, 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

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 25 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $1,500, or $60 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:

96–11–17 Beech Aircraft Corporation

(Formerly DeHavilland; Hawker

Siddeley; British Aerospace, PLC;

Raytheon Corporate Jets, Inc.):

Amendment 39–9641. Docket 95–NM–

180–AD.

Applicability: Model BAe 125 series 1000A

and Model Hawker 1000 airplanes, as listed

in Hawker Service Bulletin SB.27–168, dated

July 17, 1995; 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 (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: Beech (Raytheon) Model BAe 125

series 800B and BAe 125 series 1000B

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 series 800B and BAe 125 series

1000B 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 restriction or loss of the flight

controls due to insufficient clearance and

resultant chafing and damage to the flaps

cable and/or turnbuckle and the airbrakes

cable, accomplish the following:

(a) Within 6 months after the effective date

of this AD: Perform a one-time detailed

visual inspection for adequate working

clearances and for damage of the flap,

airbrakes, and other flight control cables and

turnbuckles with the structure at keel

subframe 15A (left- and right-hand sides)

specified in Hawker Service Bulletin SB.27–

168, dated July 17, 1995. Perform the

inspection in accordance with that service

bulletin. The detailed visual inspection for

working clearances shall be conducted for

each affected flight control through its full

range of travel.
Federal Register / Vol. 61, No. 108 / Tuesday, June 4, 1996 / Rules and Regulations 28033

(1) If all clearances are within the limits

specified in the service bulletin, and no

damage is found: No further action is

required by this AD.

(2) If the clearance for the flaps controls is

outside the limits specified in the service

bulletin: Prior to further flight, accomplish

Modification SB 27–168–253705B in

accordance with the service bulletin.

(3) If the clearance for the airbrakes

controls is outside the limits specified in the

service bulletin: Prior to further flight, repair

in accordance with the service bulletin.

(4) If any cable is found to be damaged, and

the damage exceeds the limits defined in

Chapter 20–10–31 of the Airplane

Maintenance Manual: Prior to further flight,

replace the damaged cable with a new cable

in accordance with the service bulletin.

(5) If any turnbuckle, keel subframe, or

polythene strip is found to be damaged: Prior

to further flight, repair in accordance with a

method approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate.

(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,

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 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.

(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 actions shall be done in accordance

with Hawker Service Bulletin SB.27–168,

dated July 17, 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 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 Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(e) This amendment becomes effective on

July 9, 1996.

Issued in Renton, Washington, on May 23,

1996.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–13610 Filed 6–3–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 95–ASW–24]

Revision of Class E Airspace; Mena,

AR

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action revises the Class

E airspace extending upward from 700

feet above ground level (AGL) at Mena,

AR. The development of a Global

Positioning System (GPS) Standard

Instrument Approach Procedure (SIAP)

to Runway (RWY) 17 at Mena

Intermountain Municipal Airport has

made this action necessary. This action

is intended to provide adequate Class E

airspace to contain instrument flight

rule (IFR) operations for aircraft

executing the GPS SIAP to RWY 17 at

Mena Intermountain Municipal Airport,

Mena, AR.

EFFECTIVE DATE: 0901 u.t.c., August 15

1996.

FOR FURTHER INFORMATION CONTACT:

Chuck Frankenfield, Operations Branch,

Air Traffic Division, Southwest Region,

Federal Aviation Administration, Fort

Worth, TX 76193–0530, telephone 817–

222–5591.

SUPPLEMENTARY INFORMATION:

History

On January 24, 1996, a proposal to

amend part 71 of the Federal Aviation

Regulations (14 CFR part 71) to revise

the Class E airspace at Mena, AR, was

published in the Federal Register (61

FR 1871). A GPS SIAP to RWY 17

developed for Mena Intermountain

Municipal Airport, Mena, AR, requires

the revision of the Class E airspace at

this airport. The proposal was to revise

the controlled airspace extending

upward from 700 feet AGL to contain

IFR operations in controlled airspace

during portions of the terminal

operation and while transitioning

between the enroute and terminal

environments.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments to the proposal were

received. The rule is adopted as

proposed.

The coordinates for this airspace

docket are based on North American

Datum 83. Class E airspace designations

for airspace areas extending upward

from 700 feet or more AGL are

published in Paragraph 6005 of FAA

Order 7400.9C dated August 17, 1995,

and effective September 16, 1995, which

is incorporated by reference in 14 CFR

71.1 The Class E airspace designation

listed in this document will be

published subsequently in the Order.

The Rule

This amendment to part 71 of the

Federal Aviation Regulations (14 CFR

part 71) amends the Class E airspace

located at Mena Intermountain

Municipal Airport, Mena, AR, to

provide controlled airspace extending

upward from 700 feet AGL for aircraft

executing the GPS SIAP to RWY 17.

The FAA has determined that this

regulation only involves an established

body of technical regulations that need

frequent and routine amendments to

keep them operationally current. It,

therefore—(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) does not warrant

preparation of a regulatory evaluation as

the anticipated impact is so minimal.

Since this is a routine matter that will

only affect air traffic procedures and air

navigation, it is certified that this rule

will not have a significant economic

impact on a substantial number of small

entities under the criteria of the

Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

Federal Aviation Administration

amends 14 CFR part 71 as follows:

PART 71—[AMENDED]

1. The authority citation for 14 CFR

part 71 continues to read as follows:

Authority: 49 U.S.C. 40103, 40113, 40120;

E.O. 10854; 24 FR 9565, 3 CFR, 1959–1963

Comp., p. 389; 49 U.S.C. 106(g); 14 CFR

11.69.

§ 71.1 [Amended]

2. The incorporation by reference in

14 CFR 71.1 of the Federal Aviation

Administration Order 7400.9C, Airspace

Designations and Reporting Points,

dated August 17, 1995, and effective

September 16, 1995, is amended as

follows:

Paragraph 6005: Class E Airspace areas

extending upward from 700 feet or more

above the surface of the earth.

* * * * *

ASW AR E5 Mena, AR [Revised]

Mena Intermountain Municipal Airport, AR

(Lat. 34°32′55′′ N., long. 94°12′29′′ W.)

Mena RBN