Federal Register / Vol. 61, No. 126 / Friday, June 28, 1996 / Rules and Regulations 33647

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

There are approximately 41 Jetstream

Model 4101 airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 19 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 35 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will 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 $39,900, or $2,100 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. However, the FAA

has been advised that at least 5

airplanes of U.S. registry already have

been modified; therefore, the future cost

impact of this AD is reduced by at least

$10,500.

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:

96–13–10 Jetstream Aircraft Limited:

Amendment 39–9678. Docket 95–NM–

159–AD.

Applicability: Model 4101 airplanes;

having serial numbers 41004 through 41044,

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

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 use the authority

provided in paragraph (b) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition; or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue-related cracking in the

surround structure of the Type II emergency

exit, which could result in reduced structural

integrity of the fuselage pressure vessel,

accomplish the following:

(a) Prior to the accumulation of 7,200 total

landings, or within 1,400 landings after the

effective date of this AD, whichever occurs

later, modify the existing diaphragms on the

surround structure of the Type II emergency

exit in accordance with Jetstream Service

Bulletin J41–53–014, dated July 24, 1995; or

Revision 1, dated February 9, 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,

Standardization Branch, ANM–113, FAA,

Transport 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, 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.

(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 Jetstream Service Bulletin

J41–53–014, dated July 24, 1995; or Jetstream

Service Bulletin J41–53–014, Revision 1,

dated February 9, 1996, which contains the

following list of effective pages:

Page No.

Revision

level

shown on

page

Date shown on

page

1, 3 ............... 1 .............. Feb. 9, 1996.

2, 4–13 ......... Original .... July 24, 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 A.I.R. American Support, Inc., 13850

McLaren Road, Herndon, Virginia 22071.

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

August 2, 1996.

Issued in Renton, Washington, on June 17,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–15956 Filed 6–27–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–NM–129–AD; Amendment

39–9677; AD 96–13–09]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to all Jetstream Model 4101
33648 Federal Register / Vol. 61, No. 126 / Friday, June 28, 1996 / Rules and Regulations

airplanes. This action requires a review

of maintenance records to determine the

time-in-service (TIS) of the bearings in

the starter/generators of both engines.

This action also establishes a new TIS

limit for the bearings, and requires

replacement of the starter/generator unit

with a serviceable unit, if necessary.

This amendment is prompted by reports

of controlled in-flight engine shutdowns

resulting from failure of the bearings in

the starter/generator unit. The actions

specified in this AD are intended to

prevent such failure of the bearings of

the starter/generator, which could cause

severe vibrations and resultant in-flight

shutdown of one or both engines.

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.

Comments for inclusion in the Rules

Docket must be received on or before

August 27, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

129–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Jetstream

Aircraft, Inc., P. O. Box 16029, Dulles

International Airport, Washington, DC

20041–6029. This information may be

examined 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.

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: 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 all

Jetstream Model 4101 airplanes. The

CAA advises that it has received reports

of controlled in-flight engine

shutdowns. Investigation has revealed

that the bearings of the direct current

(DC) starter/generator failed, which

resulted in severe vibration. The bearing

failures that resulted in engine

shutdown occurred at 409, 433, and 470

hours time-in-service (TIS). These

conditions, if not corrected, could result

in an in-flight engine shutdown.

Explanation of Relevant Service

Information

Jetstream has issued Alert Service

Bulletin J41–A24–036, dated February

26, 1996, which describes procedures

for reviewing the airplane maintenance

records to determine the number of

hours TIS that the bearings of the DC

starter/generator have accumulated. The

alert service bulletin also describes

procedures to remove and replace the

starter/generator units with serviceable

units when the bearings have reached a

certain (reduced) TIS limit. Such

replacement of one of the starter/

generator units (per airplane) when the

bearings have reached a certain reduced

TIS limit, reduces the possibility of the

bearings failing in both of the starter/

generator units on any one airplane

during the same flight. The CAA

classified this service bulletin as

mandatory and issued United Kingdom

airworthiness directive 002–02–96,

dated March 1, 1996, in order to assure

the continued airworthiness of these

airplanes in the United Kingdom.

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 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 CAA has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAA,

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 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, this AD is being issued to

prevent in-flight engine shutdown of

both engines on the same flight due to

failure of the bearings of the starter/

generators of the engines and resultant

severe vibration. This AD requires a

review of maintenance records to

determine the TIS of the bearings in the

starter/generators of both engines. This

action also establishes a new TIS limit

for the bearings in one of the two

starter/generator units on each airplane,

and requires replacement of the unit

with a serviceable unit. The actions are

required to be accomplished in

accordance with the service bulletin

described previously.

Differences Between Service Bulletin

and AD

Operators should note that the

requirements of this AD differ from

certain TIS recommendations in the

referenced alert service bulletin.

Specifically, this AD establishes a new

limit of 300 hours TIS for the bearings

of one of the starter/generators of each

airplane, rather than specifying

replacement of the unit when 300 hours

‘‘remain’’ on the unit before scheduled

bearing replacement, as indicated in the

alert service bulletin. The FAA

considers that replacement of a unit

with 300 hours ‘‘remaining’’ on the unit

could permit a unit to operate

significantly longer than 300 hours TIS

if the TIS limit for the unit had

previously been extended. The FAA

finds that specifying a 300-hour TIS

limit for the bearings of one of the

starter/generator units per airplane will

ensure that, at no one time, will an

airplane be operating with both starter/

generator units having more than 300

hours TIS on the bearings. A review of

starter/generator unit failure reports and

consideration of probability of failure

requirements in the type certification

basis for Jetstream Model 4101 airplanes

support the establishment of a 300-hour

TIS limit for the bearings of one of the

starter/generator units on each airplane.

This limit will ensure an acceptable

level of safety, as related to continued

availability of power from both engines

on Jetstream Model 4101 airplanes.

Additionally, the manufacturer has

notified the FAA that the availability of

ample parts may be a problem should

the AD require both starter/generator

units to be replaced if their bearings

exceed the TIS limit. The FAA has

determined that limiting the bearings to

300 hours TIS on at least one of the

starter/generator units on the airplane

provides an adequate level of safety;

therefore, this AD establishes a 300-hour

TIS limit for the bearings of only one of

the two starter/generator units of the

airplane.

Interim Action

This is considered to be interim

action. The manufacturer has advised

that it currently is developing a

modification that will positively address

the unsafe condition addressed by this

AD. Once the modification is

developed, approved, and available, the

FAA may consider further rulemaking.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this
Federal Register / Vol. 61, No. 126 / Friday, June 28, 1996 / Rules and Regulations 33649

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 96–NM–129–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

96–13–09 Jetstream Aircraft Limited:

Amendment 39–9677. Docket 96–NM–

129–AD.

Applicability: All Model 4101 airplanes,

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 (c) 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 severe vibration of one or both

engines, which could cause in-flight engine

shutdown, accomplish the following:

(a) Within 7 days after the effective date of

this AD, review the airplane maintenance

records to determine the hours time-inservice (TIS) accumulated on the bearings in

the starter/generator units of both engines, in

accordance with Jetstream Alert Service

Bulletin J41–A24–036, dated February 26,

1996.

(1) If the bearings on both of the starter/

generator units have accumulated 300 or

more hours TIS: Prior to further flight,

replace at least one of the starter/generator

units with a unit having bearings with less

than 300 hours TIS, in accordance with the

alert service bulletin.

(2) If the bearings on one or both starter/

generator units have bearings with less than

300 hours TIS: Prior to the accumulation of

300 hours TIS on the bearings on both

starter/generator units, remove at least one of

the units and replace it with a unit having

bearings with less than 300 hours TIS, in

accordance with the alert service bulletin.

(b) As a continuing requirement thereafter:

Prior to the accumulation of 300 hours TIS

on the bearings on both of the starter/

generator units on the airplane, remove at

least one of the units and replace it with a

unit having bearings with less than 300 hours

TIS, in accordance with Jetstream Alert

Service Bulletin J41–A24–036, dated

February 26, 1996.

(c) 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 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.

(d) 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.

(e) The actions shall be done in accordance

with Jetstream Alert Service Bulletin J41–

A24–036, dated February 26, 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

Jetstream Aircraft, Inc., P.O. Box 16029,

Dulles International Airport, Washington, DC

20041–6029. 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.

(f) This amendment becomes effective on

July 15, 1996.
33650 Federal Register / Vol. 61, No. 126 / Friday, June 28, 1996 / Rules and Regulations

Issued in Renton, Washington, on June 17,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–15954 Filed 6–27–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–231–AD; Amendment

39–9681; AD 96–13–12]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires

replacement of a bus power control unit

(BPCU) and two generator control units

(GCU) with new improved units. This

amendment is prompted by results of

the manufacturer’s re-certification and

laboratory testing of a BPCU, which

revealed abnormal functions of the

BPCU and the GCU. The actions

specified by this AD are intended to

prevent such abnormal functions, which

could result in electrical short circuits

in the electrical power distribution

systems and a subsequent fire.

DATES: Effective August 2, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 2,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Dornier Luftfahrt GmbH, P.O. Box

1103, D–82230 Wessling, Germany. 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: Gary

Lium, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1112; 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 Dornier

Model 328–100 series airplanes was

published in the Federal Register on

April 4, 1996 (61 FR 15000). That action

proposed to require replacement of the

generator control units (GCU’s) 2PC and

12PC with new improved units having

part number 118–000–1. The AD also

will require replacement of the bus

power control unit (BPCU) 20PC with a

new improved unit having part number

106–000–3.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 12 Dornier

Model 328–100 series 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. The manufacturer

will provide required parts at no cost to

the operators. Based on these figures,

the cost impact of the AD on U.S.

operators is estimated to be $720, 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:

96–13–12 Dornier: Amendment 39–9681.

Docket 95–NM–231–AD.

Applicability: Model 328–100 series

airplanes having serial numbers 3005

through 3024 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 (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.

Compliance: Required as indicated, unless

accomplished previously.

To prevent abnormal functions of the bus

power control units and the generator control

units, which could result in electrical short

circuits in the electrical power distribution

systems and a subsequent fire, accomplish

the following:

(a) Within 3 months after the effective date

of this AD, perform the requirements of

paragraph (a)(1) and (a)(2) of this AD, in

accordance with Dornier Service Bulletin

SB–328–24–061, Revision 1, dated November

3, 1994.

(1) Remove the generator control units 2PC

and 12PC and replace them with new

improved units having part number 118–

000–1. And,