60850 Federal Register / Vol. 65, No. 199 / Friday, October 13, 2000 / Rules and Regulations

(c) What problem does this AD address?

The actions specified by this AD are intended

to correct improper drive belt tension and

consequent engine crankshaft or connecting

rod bearing damage. Such damage could

result in loss of propulsion during critical

phases of flight.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance times Procedures

(1) Measure the drive belt tension. The difference should be a minimum of 6 millimeters

(mm) (0.236 inches (in)) and should not exceed 11 mm (0.433 in).

Within the next 25 hours time-in-service (TIS)

or 90 days after November 27, 2000, (the

effective date of this AD),whichever comes

first.

Follow the procedures in DG Flugzeugbau

Technical Note (TN) 873/16, dated October

25, 1999, and the Maintenance Manual for

DG–800B.

(2) If you find improper tension as specified in

this AD, accomplish the following:.

Before operating the sailplane.

(i) Lower the tension if it is too high. Check the

position of the propeller in relation to the engine compression point to assure it is within

limits, and adjust if necessary.

(ii) If you have to reduce the drive belt tension,

execute a ground test run. Check to assure

that the position of the propeller in relation to

the engine compression point has not

changed, and adjust as necessary. If this has

happened, the drive belt has slipped due to

too low tension.

(iii) Notify DG Flugzeugbau if tension problems

are still not resolved.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

Note 1: This AD applies to each sailplane

identified in paragraph (a) of this AD,

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 (e)

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Mike Kiesov, Aerospace

Engineer, FAA, Small Airplane Directorate,

901 Locust, Room 301, Kansas City, Missouri

64106; telephone: (816) 329–4144; facsimile:

(816) 329–4090.

(g) What if I need to fly the sailplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your sailplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

DG Flugzeugbau Technical Note (TN) 873/16,

dated October 25, 1999. The Director of the

Federal Register approved this incorporation

by reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from DG

Flugzeugbau, Postbox 41 20, D–76646

Bruchsal, Federal Republic of Germany;

telephone: +49 7257–890; facsimile: +49

7257–8922. You can look at copies at the

FAA, Central Region, Office of the Regional

Counsel, 901 Locust, Room 506, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC 20001.

Note 2: The subject of this AD is addressed

in German AD Number 1999–377, dated

December 2, 1999.

(i) When does this amendment become

effective? This amendment becomes effective

on November 27, 2000.

Issued in Kansas City, Missouri, on

September 28, 2000.

Michael Gallagher,

Manager, Small Airplane Directorate,,

Aircraft Certification Service.

[FR Doc. 00–25550 Filed 10–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–12–AD; Amendment

39–11924; AD 2000–20–13]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace HP137 Mk1, Jetstream

Series 200, and Jetstream Models 3101

and 3201 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain British Aerospace

HP137 Mk1, Jetstream series 200, and

Jetstream Models 3101 and 3201

airplanes. This AD requires you to

inspect the rudder quadrant support

structure for cracks and correct Dwasher installation; and also requires

you to replace any cracked component

and replace any incorrectly installed Dwashers. This AD is the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for the United

Kingdom. The actions specified by this

AD are intended to detect, correct, and

prevent further cracking in the rudder

quadrant structure caused by incorrectly

installed D-washers. Cracks in this

structure could result in loss of rudder

control with consequent airplane

control problems.

DATES: This AD becomes effective on

November 27, 2000.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of November 27, 2000.

ADDRESSES: You may get the service

information referenced in this AD from

British Aerospace Regional Aircraft,

Prestwick International Airport,

Ayrshire, KA9 2RW, Scotland;

telephone: (01292) 479888; facsimile:

(01292) 479703. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

12–AD, 901 Locust, Room 506, Kansas

Federal Register / Vol. 65, No. 199 / Friday, October 13, 2000 / Rules and Regulations 60851

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC

20001.

FOR FURTHER INFORMATION CONTACT: Mr.

S.M. Nagarajan, Aerospace Engineer,

FAA, Small Airplane Directorate, 901

Locust, Room 301, Kansas City,

Missouri 64106; telephone: (816) 329–

4145; facsimile: (816) 329–4090.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, recently notified

the FAA that an unsafe condition may

exist on certain British Aerospace

HP137 Mk1, Jetstream series 200, and

Jetstream Models 3101 and 3201

airplanes. The CAA reports two

incidents of cracks in the upper edge

member radii and bottom diaphragm

radii of the rudder quadrant support

structure.

Investigation of these incidents

revealed that the D-washers in the

rudder quadrant support structure were

installed incorrectly. These D-washers,

when installed correctly, are designed to

reinforce the bend radii of the affected

structure.

What are the consequences if the

condition is not corrected? Cracks in the

rudder quadrant support structure, if

not detected and corrected, could result

in loss of rudder control with

consequent airplane control problems.

Has FAA taken any action to this

point? We issued a proposal to amend

part 39 of the Federal Aviation

Regulations (14 CFR part 39) to include

an AD that would apply to certain

British Aerospace HP137 Mk1, Jetstream

series 200, and Jetstream Models 3101

and 3201 airplanes. This proposal was

published in the Federal Register as a

notice of proposed rulemaking (NPRM)

on August 10, 2000, (65 FR 48933). The

NPRM proposed to require you to

inspect the rudder quadrant support

structure for cracks and correct Dwasher installation; and would require

you to replace any cracked component

and replace any incorrectly installed Dwashers.

Was the public invited to comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. No comments were

received on the proposed rule or the

FAA’s determination of the cost to the

public.

The FAA’s Determination

What is FAA’s Final Determination on

this Issue? After careful review of all

available information related to the

subject presented above, we have

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. We determined

that these minor corrections:

• Will not change the meaning of the

AD; and

• Will not add any additional burden

upon the public than was already

proposed.

Compliance Time

What is the compliance time of this

AD? The compliance time of this AD

will be ‘‘within 90 calendar days after

the effective date of this AD.’’

Why is the compliance in calendar

time instead of hours time-in-service (TIS)?

The cracks in the rudder quadrant

support structure occur as a direct result

of airplane operation if the D-washers

are incorrectly installed. Because the Dwashers could have been incorrectly

installed in the field or at the factory,

the problem has the same chance of

occurring on an airplane with 50 hours

TIS as one with 5,000 hours TIS.

Therefore, we believe that 90 calendar

days will:

• Assure that the unsafe condition

does not go undetected for a long period

of time on the affected airplanes; and

• Will not inadvertently ground any

of the affected airplanes.

Cost Impact

How many airplanes does this AD

impact? We estimate that this AD affects

264 airplanes in the U.S. registry.

What is the cost impact of this AD on

owners/operators of the affected

airplanes? We estimate that it will take

approximately 1 workhour per airplane

to accomplish the inspection of the

rudder quadrant support structure and

the D-washers, at an average labor rate

of $60 an hour. Based on the figures

presented above, the total cost impact of

the inspection on U.S. operators is

estimated to be $15,840, or $60 per

airplane.

Costs for any necessary replacements

are as follows:

Action Number of workhours Parts cost Total cost

per airplane

Right upper edge member replacement ......................................................................... 8 workhours at $60 per

hour.

$514 $994

Lower diaphragm replacement ....................................................................................... 8 workhours at $60 per

hour.

760 1,240

D-washer replacement .................................................................................................... 4 workhours at $60 per

hour.

250 490

Regulatory Impact

Does this AD impact various entities?

The regulations adopted herein will not

have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

Does this AD involve a significant rule

or regulatory action? 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 copy of the final

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, Incorporation by Reference,

Safety.

Adoption of the Amendment

Accordingly, under 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:

60852 Federal Register / Vol. 65, No. 199 / Friday, October 13, 2000 / Rules and Regulations

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. FAA amends Section 39.13 by

adding a new AD to read as follows:

2000–20–13 British Aerospace:

Amendment 39–11924; Docket No.

2000–CE–12–AD.

(a) What airplanes are affected by this AD?

This AD affects Models HP137 Mk1,

Jetstream Series 200 airplanes, and Jetstream

Models 3101 and 3201 airplanes, all serial

numbers excluding 936 and 940, certificated

in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes on the U.S. Register must

comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to detect, correct, and prevent further

cracking in the rudder quadrant structure

caused by incorrectly installed D-washers.

Cracks in this structure could result in loss

of rudder control with consequent airplane

control problems.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance times Procedures

(1) Inspect the upper edge member radii and

bottom diaphragm radii adjacent to the rudder artificial feel assembly attachments at the

rudder quadrant support for cracks and inspect the D-washers to assure correct installation.

Within 90 calendar days after November 27,

2000 (the effective date of this AD).

Accomplish in accordance with the ‘‘ACCOMPLISHMENT INSTRUCTIONS: Part 1—Inspection’’ section of British Aerospace Mandatory Alert Service Bulletin 53–JA–990842,

Revision 1, dated February 21, 2000.

(2) If cracks are found in the area of the upper

edge member radii on the rudder quadrant

support structure, replace this component by

incorporating material Kit No. ‘53–JA–

990842PT2’.

Before further flight after the inspection where

the cracked part was detected.

Accomplish in accordance with the ‘‘ACCOMPLISHMENT INSTRUCTIONS: Part 2—Replacement of the right upper edge member

if cracks are found at Part 1’’ section of

British Aerospace Mandatory Alert Service

Bulletin 53–JA–990842, Revision 1, dated

February 21, 2000.

(3) If cracks are found in the area of the bottom

diaphragm on the rudder quadrant support

structure, replace this component by incorporating material Kit No. ‘53–JA–990842PT3’.

Before further flight after the inspection where

the cracked part was detected.

Accomplish in accordance with the ‘‘ACCOMPLISHMENT INSTRUCTIONS: Part 3—Replacement of the bottom diaphragm of the

rudder quadrant support structure’’ section

of British Aerospace Mandatory Alert Service Bulletin 53–JA–990842, Revision 1,

dated February 21, 2000.

(4) Remove any incorrectly installed D-washer

and replace with a new D-washer. This replacement is accomplished by incorporating

material Kit No. ‘53–JA–990842PT4’.

Before further flight after the inspection where

the incorrect installation was detected.

Accomplish in accordance with the ‘‘ACCOMPLISHMENT INSTRUCTIONS: Part 4—Removal and replacement of D-washers’’ section of British Aerospace Mandatory Alert

Service bulletin 53–JA–990842, Revision 1,

dated February 21, 2000.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate approves your alternative. Submit

your request through an FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 1: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (e)

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact S.M. Nagarajan,

Aerospace Engineer, FAA, Small Airplane

Directorate, 901 Locust, Room 301, Kansas

City, Missouri 64106; telephone: (816) 329–

4145; facsimile: (816) 329–4090.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

British Aerospace Mandatory Alert Service

Bulletin 53–JA–990842, Revision 1, dated

February 21, 2000. The Director of the

Federal Register approved this incorporation

by reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from British

Aerospace Regional Aircraft, Prestwick

International Airport, Ayrshire, KA9 2RW,

Scotland. You can look at copies at the FAA,

Central Region, Office of the Regional

Counsel, 901 Locust, Room 506, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW, suite

700, Washington, DC 20001.

(i) When does this amendment become

effective? This amendment becomes effective

on November 27, 2000.

Note 2: The subject of this AD is addressed

in British AD Number 006–12–99, not dated.

Issued in Kansas City, Missouri, on

September 28, 2000.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 00–25554 Filed 10–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF COMMERCE

Bureau of Export Administration

15 CFR Parts 734, 738, 740, 742, 743,

744, 748, and 774

[Docket No. 000204027–0266–02]

RIN 0694–AC14

Revisions to License Exception CTP

AGENCY: Bureau of Export

Administration, Commerce.

ACTION: Final rule.

SUMMARY: The Bureau of Export

Administration (BXA) is amending the