Federal Register / Vol. 62, No. 198 / Tuesday, October 14, 1997 / Proposed Rules 53269

(1) Required annual Distributions

under §§ 107.1540(a)(1), and any

Distributions under §§ 107.1550 and

107.1560, must be made no later than

the second Payment Date following the

end of your fiscal year;

(2) Required Distributions under

§ 107.1540(b) must be made no later

than the first Payment Date following

the end of the applicable fiscal quarter;

(3) Optional Distributions under

§ 107.1540(a)(2) and § 107.1570 may be

made on any date.

(b) Conditions for making

distribution. All Distributions under this

§ 107.1575 are subject to the following

conditions:

(1) You must obtain SBA’s written

approval before the distribution date;

(2) You must use the distribution date

as the ending date of the period for

which you compute your Earmarked

Profits, Prioritized Payments,

Adjustments, Charges, Profit

Participation, Retained Earnings

Available for Distributions, liquidity

ratio, Capital Impairment, and any other

applicable computations required under

§§ 107.1500 through 107.1570;

(3) If your Distribution includes an

amount which SBA will apply as a

redemption of Participating Securities,

the effective date of such redemption,

for all purposes including future

computations of Prioritized Payments,

will be the next Payment Date following

the distribution date.

40. In § 107.1580, the introductory

text of paragraph (a) is proposed to be

revised to read as follows:

§ 107.1580 Special rules for In-Kind

Distributions by Licensees.

(a) In-Kind distributions. A

Distribution under §§ 107.1540,

107.1560 or 107.1570 may consist of

securities (an ‘‘In-Kind Distribution’’).

Such a Distribution must satisfy the

conditions in this paragraph (a).

* * * * *

41. Section 107.1590 is proposed to be

amended by removing paragraph (c),

redesignating paragraph (d) as

paragraph (c), and revising paragraph

(a)(1) to read as follows:

§ 107.1590 Special rules for companies

licensed on or before March 31, 1993.

* * * * *

(a) Election to exclude pre-existing

portfolio. * * *

(1) The proceeds of your first issuance

of Participating Securities are not used

to refinance outstanding Debentures (see

§ 107.1585(a)). SBA will consider

payment or prepayment of any

outstanding Debenture to be a

refinancing unless you demonstrate to

SBA’s satisfaction that you can pay the

Debenture principal without relying on

the proceeds of the Participating

Securities.

* * * * *

42. In § 107.1600, the first sentence of

paragraph (a) and paragraph (b) are

proposed to be revised to read as

follows:

§ 107.1600 SBA authority to issue and

guarantee Trust Certificates.

(a) Authorization. Sections 319 (a)

and (b) of the Act authorize SBA or its

CRA to issue TCs, and SBA to guarantee

the timely payment of the principal and

interest thereon. * * *

(b) Periodic exercise of authority. SBA

will issue guarantees of Debentures and

Participating Securities under section

303 and of TCs under section 319 of the

Act at three month intervals, or at

shorter intervals, taking into account the

amount and number of such guarantees

or TCs.

* * * * *

43. Section 107.1720 is proposed to be

added to subpart I to read as follows:

§ 107.1720 Characteristics of SBA’s

guarantee.

If SBA agrees to guarantee a

Licensee’s Debentures or Participating

Securities, such guarantee will be

unconditional, irrespective of the

validity, regularity or enforceability of

the Debentures or Participating

Securities or any other circumstances

which might constitute a legal or

equitable discharge or defense of a

guarantor. Pursuant to its guarantee,

SBA will make timely payments of

principal and interest on the Debentures

or the Redemption Price of and

Prioritized Payments on the

Participating Securities.

44. In § 107.1820, paragraph (e)(9) is

proposed to be revised to read as

follows:

§ 107.1820 Conditions affecting issuers of

Preferred Securities and/or Participating

Securities.

* * * * *

(e) Restricted Operations

Conditions. * * *

(9) Failure to meet investment

requirements. You fail to make the

amount of Equity Capital Investments

required for Participating Securities

(§ 107.1500(b)(4)), if applicable to you;

or you fail to maintain as of the end of

each fiscal year the investment ratios or

amounts required for Leverage in excess

of 300 percent of Leverageable Capital

(§ 107.1160 (c)) or Preferred Securities

in excess of 100 percent of Leverageable

Capital (§ 107.1160(d)), if applicable to

you. In determining whether you have

met the maintenance requirements in

§ 107.1160(c) or (d), SBA will disregard

any prepayment, sale, or disposition of

Venture Capital Financings, any

increase in Leverageable Capital, and

any receipt of additional Leverage,

within 120 days prior to the end of your

fiscal year.

* * * * *

45. In § 107.1830, paragraph (a) is

revised to read as follows:

§ 107.1830 Licensee’s Capital

Impairment—definition and general

requirements.

(a) Applicability of this section. This

§ 107.1830 applies to Leverage issued on

or after April 25, 1994. For Leverage

issued before April 25, 1994, you must

comply with paragraphs (e) and (f) of

this section and the Capital Impairment

regulations in this part in effect when

you issued your Leverage. For all

Leverage issued, you must also comply

with any contractual provisions to

which you have agreed.

* * * * *

Dated: September 25, 1997.

Aida Alvarez,

Administrator.

[FR Doc. 97–26720 Filed 10–10–97; 8:45 am]

BILLING CODE 8025–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–77–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to all Airbus

Model A310 series airplanes, that

currently requires measurement of the

force required to move the interior

control handle of the emergency exit

doors, and various follow-on corrective

actions, if necessary. This action would

add repetitive functional tests to

measure the force necessary to move the

interior control handle of the emergency

exit doors; and adjusting an emergency

exit door or replacing the bearing of the

door lifting mechanism, if necessary.

This proposal is prompted by reports of

seizure of a bearing and increased door

handle forces that were outside the

limits of the required hand forces due to
53270 Federal Register / Vol. 62, No. 198 / Tuesday, October 14, 1997 / Proposed Rules

seizure of two teflon line bearings on

the lifting shaft. The actions specified

by the proposed AD are intended to

prevent impeding passenger evacuation

during an emergency due to difficulty in

lifting the interior control handle that is

used to open the emergency exit door.

DATES: Comments must be received by

November 10, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

77–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.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

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:

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 97–NM–77–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.

97–NM–77–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On April 5, 1995, the FAA issued AD

95–08–07, amendment 39–9196 (60 FR

19155, April 17, 1995), applicable to all

Airbus Model A310 series airplanes, to

require measurement of the force

required to move the interior control

handle of the emergency exit doors, and

various follow-on corrective actions, if

necessary. That action was prompted by

a report that, during routine

maintenance, excessive force was

required to lift the interior control

handle of the emergency exit door. The

requirements of that AD are intended to

prevent impeding passenger evacuation

during an emergency due to difficulty in

lifting the interior control handle that is

used to open the emergency exit door.

Actions Since Issuance of Previous Rule

Since issuance of AD 95–08–07, the

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, advises that,

during the inspection required by that

AD, the seizure of one bearing was

found on an affected airplane. The

DGAC also advises that, following

accomplishment of the inspection

required by that AD, increased door

handle forces that were outside the

limits of the required hand forces were

required to lift the interior control

handle of the emergency exit doors. The

cause of the excessive force was

attributed to the seizure of two teflon

line bearings on the lifting shaft. This

condition, if not corrected, could

impede passenger evacuation during an

emergency due to difficulty in lifting the

interior control handle that is used to

open the emergency exit door.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A310–52–2060, dated July 22, 1996,

which describes procedures for

performing repetitive functional tests to

measure the force necessary to move the

interior control handle of the emergency

exit doors; and adjusting an exit door or

replacing the bearings of the door lifting

mechanism, if necessary. The DGAC

classified this service bulletin as

mandatory and issued French

airworthiness directive 96–239–205(B),

dated October 23, 1996, in order to

assure the continued airworthiness of

these airplanes in France.

FAA’s Conclusions

This airplane model is manufactured

in France 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 DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, reviewed all available

information, and determined that AD

action is necessary for products of this

type design that are certificated for

operation in the United States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would

supersede AD 95–08–07 to continue to

require measurement of the force

required to move the interior control

handle of the emergency exit doors, and

various follow-on corrective actions, if

necessary. The proposed AD also would

require repetitive functional tests to

measure the force necessary to move the

interior control handle of the emergency

exit doors; and adjusting an exit door or

replacing the bearings of the door lifting

mechanism, if necessary. The actions

would be required to be accomplished

in accordance with the service bulletin

described previously; except that any

discrepancy of the mechanism inside

the emergency exit door would be

required to be repaired in accordance

with a method approved by the FAA.

Differences Between the Proposal and

the Relevant French AD

This proposed rule would differ from

the parallel French airworthiness

directive 96–239–205(B), in that it

would exclude from the applicability

those airplanes that have been modified

in accordance with Supplemental Type

Certificate (STC) ST0001NY. This STC,

which was issued by the FAA,

converted airplanes from a passenger to

a cargo-carrying configuration. Thus, the

emergency exit doors of these airplanes

are no longer available for use.

Therefore, the FAA has determined that

Airbus Model A310 series airplanes that

have been modified in accordance with
Federal Register / Vol. 62, No. 198 / Tuesday, October 14, 1997 / Proposed Rules 53271

the identified STC are not subject to the

addressed unsafe condition.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Cost Impact

There are approximately 6 Airbus

Model A310 series airplanes of U.S.

registry that would be affected by this

proposed AD.

The actions that are currently

required by AD 95–08–07 take

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the currently

required actions on U.S. operators is

estimated to be $360, or $60 per

airplane.

The new actions that are proposed in

this AD action would take

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the proposed

requirements of this AD on U.S.

operators is estimated to be $360, or $60

per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or proposed 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 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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–9196 (60 FR

19155, April 17, 1995), and by adding

a new airworthiness directive (AD), to

read as follows:

Airbus Industrie: Docket 97–NM–77–AD.

Supersedes AD 95–08–07, Amendment

39–9196.

Applicability: All Model A310 series

airplanes, except those airplanes that have

been modified in accordance with

Supplemental Type Certificate (STC)

ST0001NY; 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 (f) 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 impeding passenger evacuation

during an emergency due to difficulty in

lifting the interior control handle that is used

to open the emergency exit door, accomplish

the following:

Restatement of Requirements of AD 95–08–

07, Amendment 39–9196

(a) Within 60 days after May 2, 1995 (the

effective date of AD 95–08–07), measure the

amount of force required to move the interior

control handle of the emergency exit doors,

in accordance with Airbus All Operators

Telex (AOT) 52–08, Revision 1, dated

December 1, 1994.

(b) If the force required to move the interior

control handle of the door is equal to or does

not exceed 20 daN (45 foot-pounds), no

further action is required by this paragraph

for that door.

(c) If the force required to move the interior

control handle of the door exceeds 20 daN

(45 foot-pounds), prior to further flight,

perform a full functional test of the

emergency exit doors to measure the amount

of force required to open the doors, in

accordance with the AOT.

(1) If the force required to open the door

does not exceed 20 daN (45 foot-pounds), no

further action is required by this paragraph

for that door.

(2) If the force required to open the door

exceeds 20 daN (45 foot-pounds), prior to

further flight, perform a visual inspection to

detect discrepancies of the mechanism inside

the door, in accordance with the AOT.

(i) If no discrepancy is found, prior to

further flight, replace seized bearings with

new or serviceable bearings, in accordance

with AOT.

(ii) If any discrepancy is found, prior to

further flight, repair the discrepancy in

accordance with a method approved by the

Manager, Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate.

(d) Within 10 days after accomplishing the

inspection required by paragraph (a) of this

AD, submit a report of the findings of

discrepancies to Airbus Industrie,

Engineering Services, Attention: Mr. R.

Filaquier, AI/SE E121, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

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.

New Requirements of This AD

(e) Within 3 months after the effective date

of this AD, perform a functional test to

measure the force necessary to move the

interior control handle of the emergency exit

doors, in accordance with Airbus Service

Bulletin A310–52–2060, dated July 22, 1996.

(1) If the emergency exit door opens and

the force required to move the interior

control hand is less than or equal to the

limits specified in the service bulletin, repeat

the test thereafter at intervals not to exceed

3 months.

(2) If the emergency exit door does not

open or the force required to move the

interior handle is greater than the limits

specified in the service bulletin, prior to

further flight, perform an inspection to detect

discrepancies of the mechanisms inside the

door, in accordance with the service bulletin.

(i) If no discrepancy is detected, prior to

further flight, replace the bearings with new

bearings, in accordance with the service

bulletin. Repeat the test thereafter at intervals

not to exceed 3 months.

(ii) If any discrepancy is detected, prior to

further flight, adjust the emergency exit doors

in accordance with the service bulletin.

Repeat the test thereafter at intervals not to

exceed 3 months.

(f) 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,
53272 Federal Register / Vol. 62, No. 198 / Tuesday, October 14, 1997 / Proposed Rules

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.

(g) 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 October

7, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27090 Filed 10–10–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–127–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model 4101

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

revise an existing airworthiness

directive (AD), applicable to certain

British Aerospace (Jetstream) Model

4101 airplanes, that currently requires

an inspection to determine the thickness

of the intercostal that attaches the third

crew member seat to the floor structure

in the flight compartment, and

replacement, if necessary. That AD was

prompted by a report from the

manufacturer indicating that

intercostals have been installed that are

not of sufficient thickness (and

consequent strength) to support the

third crew member seat during

emergency landing dynamic conditions.

The actions specified by that AD are

intended to prevent the failure of this

intercostal during an emergency

landing, which could consequently

result in injury to the flight crew. This

action would revise the applicability of

the existing AD by removing several

airplanes.

DATES: Comments must be received by

November 10, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

127–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.

The service information referenced in

the proposed rule may be obtained from

AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia

20171. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

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

(425) 227–2148; fax (425) 227–1149.

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 97–NM–127–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.

97–NM–127–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On May 12, 1997, the FAA issued AD

97–11–02, amendment 39–10031 (62 FR

28795, May 28, 1997), applicable to

certain British Aerospace (Jetstream)

Model 4101 airplanes, to require a onetime inspection to determine the

thickness of the intercostal that attaches

the third crew member seat to the floor

structure in the flight compartment to

determine the thickness of this part, and

replacement with a new intercostal of

the correct thickness, if necessary. That

action was prompted by a report from

the manufacturer indicating that

intercostals have been installed that are

not of sufficient thickness (and

consequent strength) to support the

third crew member seat during

emergency landing dynamic conditions.

The requirements of that AD are

intended to prevent the failure of this

intercostal during an emergency

landing, which could consequently

result in injury to the flight crew.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

manufacturer has issued Alert Service

Bulletin J41–A53–030, Revision 1, dated

August 8, 1996, and Revision 2, dated

February 14, 1997. The inspection and

replacement procedures described in

these revisions are identical to those

described in the original version of the

service bulletin (which was referenced

in AD 97–11–02). The only change

effected by Revisions 1 and 2 is to

remove airplanes having constructors

numbers 41044, 41068, 41069, and

41070 from the effectivity listing of the

alert service bulletin, since these

airplanes are not subject to the

addressed unsafe condition. The Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom, classified these alert service

bulletins as mandatory.

The FAA has been advised that

Jetstream Aircraft Limited has revised

its corporate name to British Aerospace

Regional Aircraft.

FAA’s Conclusions

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the CAA has kept the FAA informed of

the situation described above. The FAA