Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 / Proposed Rules 31375

light support and seal assemblies and

that none of the owners/operators of the

affected airplanes have replaced the

landing light support and seal

assemblies with parts of improved

design.

Piper has informed the FAA that parts

have been distributed to equip

approximately 7,021 airplanes.

Assuming that these distributed parts

are incorporated on the affected

airplanes, the cost of this AD will be

reduced by $1,825,460 from $2,626,000

to $800,540.

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 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) 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 has been placed 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 Airworthiness Directive (AD)

96–10–01, Amendment 39–39-9606, and

adding a new AD to read as follows:

The New Piper Aircraft Inc.: Docket No. 95–

CE–51–AD; Revises AD 96–10–01,

Amendment 39–9606.

Applicability: The following airplane

models and serial numbers, certificated in

any category:

Models Serial numbers

PA–28–140 ................ 28–20000 through

28–7725290.

PA–28–150, PA–28–

160, and PA–28–

180.

28–1 through 28–

1760.

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 within the next 100

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished.

Note 2: Early compliance is encouraged.

To prevent the landing light seal from

lodging in the carburetor, which could result

in rough engine operation or possible engine

failure and possible loss of control of the

airplane, accomplish the following:

(a) Replace the landing light support and

seal assembly in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Piper Service Bulletin No. 975,

dated November 2, 1994.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Atlanta Aircraft

Certification Office, One Crown Center, 1895

Phoenix Blvd., Suite 450, Atlanta, Georgia

30349.

(1) The request shall be forwarded through

an appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Atlanta Aircraft Certification

Office.

(2) Alternative methods of compliance

approved in accordance with AD 96–10–01,

are considered approved as alternative

methods of compliance for this AD.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta Aircraft

Certification Office.

(d) All persons affected by this directive

may obtain copies of the document referred

to herein upon request to The New Piper

Aircraft, Inc., Attn: Customer Service, 2926

Piper Dr., Vero Beach, Florida, 32960; or may

examine this document at the FAA, Central

Region, Office of the Regional Counsel, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

(e) This amendment revises AD 96–10–01,

Amendment 39–9606.

Issued in Kansas City, Missouri, on June 1,

1998.

Ronald K. Rathgeber,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–15200 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–12–AD]

RIN 2120–AA64

Airworthiness Directives; Glaser-Dirks

Flugzeugbau GmbH Model DG–400

Gliders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain GlaserDirks Flugzeugbau GmbH (Glaser-Dirks)

Model DG–400 gliders. The proposed

action would require inspecting the

powerplant mount and the propeller

mount for any loose parts. If parts are

loose, the proposed AD would require

immediately modifying the starter

motor, retrofitting the holder for the

starter motor, and checking the engine

ignition timing. If parts are not found

loose, the proposed AD would require

modifying the starter motor, retrofitting

the holder for the starter motor, and

checking the engine ignition timing at a

later time. The proposed AD is the

result of mandatory continuing

airworthiness information (MCAI)

issued by the airworthiness authority for

Germany. The actions specified by the

proposed AD are intended to prevent

damage to the engine caused by

vibration, which could result in loss of

engine power during critical phases of

flight.

DATES: Comments must be received on

or before July 17, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,
31376 Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 / Proposed Rules

Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–12–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from DG

Flugzeugbau GmbH, Im Schollengarten

19–20, 7520 Bruchsal 4, Germany;

telephone: +49 7257–89–0; facsimile:

+49 7257–8922. This information also

may be examined at the Rules Docket at

the address above.

FOR FURTHER INFORMATION CONTACT:

Mike Kiesov, Aerospace Engineer, FAA,

Small Airplane Directorate, Aircraft

Certification Service, 1201 Walnut, suite

900, Kansas City, Missouri 64106;

telephone: (816) 426–6934; facsimile:

(816) 426–2169.

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

should 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 that

summarizes 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 No. 98–CE–12–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, Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 98–CE–12–AD, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

Discussion

The Luftfahrt-Bundesamt (LBA),

which is the airworthiness authority for

Germany, recently notified the FAA that

an unsafe condition may exist on certain

Glaser-Dirks Model DG–400 gliders. The

LBA reports that several of these gliders

have lost engine power during flight.

Further investigation revealed that the

powerplant propeller mount was not

secure on some engines. This problem

related back to the engine manufacturer

not drilling the rear mount holes deep

enough on the propeller mount to hold

it securely during engine vibration.

These conditions, if not corrected,

could result in the propeller mount and

powerplant mount coming loose during

critical phases of flight.

Relevant Service Information

DG Flugzeugbau has issued Technical

Note Nr. 826/22 dated January 10, 1990,

which specifies procedures for

inspecting for loose parts on the

powerplant and propeller mount and

inserting revised pages into the

maintenance manual. If any part is

found loose, the service information

specifies procedures for modifying the

starter motor, retrofitting the holder of

the starter motor, and checking the

engine timing.

The LBA classified this service

bulletin as mandatory and issued

German AD 90–43, dated February 26,

1990, in order to assure the continued

airworthiness of these gliders in

Germany.

The FAA’s Determination

This glider model is manufactured in

Germany 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 LBA has kept the FAA informed of

the situation described above.

The FAA has examined the findings

of the LBA; reviewed all available

information, including the service

information referenced above; and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Glaser-Dirks Model

DG–400 gliders of the same type design

registered in the United States, the FAA

is proposing AD action.

The proposed AD would require

inspecting the powerplant mount and

the propeller mount for loose parts. If

any parts are loose, the proposed AD

would require modifying the starter

motor, retrofitting the holder for the

starter motor, checking the engine

ignition timing, and adjusting the timing

if necessary.

Accomplishment of the proposed

action would be in accordance with DG

Flugzeugbau Technical Note Nr. 826/22,

dated January 10, 1990.

Differences Between the Service

Information and the Proposed AD

The manufacturer’s service

information specifies procedures for

inspecting the powerplant mount for a

secure, tight condition prior to every

flight. This service information also

specifies inserting revised pages to the

maintenance manual.

The proposed AD would not require

an inspection prior to each flight, and

would not require inserting revised

pages to the maintenance manual. The

FAA will insert a ‘‘NOTE’’ into the body

of the proposed AD, recommending

inserting the revised pages into the

maintenance manual.

Cost Impact

The FAA estimates that 35 gliders in

the U.S. registry would be affected by

the proposed AD, that it would take

approximately 4 workhours per airplane

to accomplish the proposed action, and

that the average labor rate is

approximately $60 an hour. Parts cost

approximately $150 per airplane. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $13,650, or $390 per

glider.

Proposed Compliance Time

The compliance time of the proposed

AD is in calendar time instead of hours

time-in-service (TIS). The average

monthly usage of the affected glider

ranges throughout the fleet. For

example, one owner may operate the

glider 25 hours TIS in one week, while

another operator may operate the glider

25 hours TIS in one year. In order to

ensure that all of the owners/operators

of the affected glider have inspected the

powerplant and propeller mounts for

loose parts within a reasonable amount

of time, the FAA is proposing a calendar

compliance time.

Regulatory Impact

The regulations proposed herein

would not have substantial direct effects

on the States, on the relationship
Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 / Proposed Rules 31377

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 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) 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 has been placed 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

adding a new airworthiness directive

(AD) to read as follows:

Glaser-Dirks Flugzeugbau GMBH: Docket

No. 98–CE–12–AD. Applicability: Model

DG–400 gliders, serial numbers 4–1

through 4–249, certificated in any

category.

Note 1: This AD applies to each glider

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

gliders 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 within 1 calendar

month after the effective date of this AD,

unless already accomplished.

To prevent damage to the engine caused by

vibration, which could result in loss of

engine power during critical phases of flight,

accomplish the following:

(a) Inspect the powerplant (engine) mount

and propeller mount for any loose parts in

accordance with paragraph 1 in the

Instructions section of Glaser-Dirks Technical

Note (TN) Nr. 826/22, dated January 10,

1990.

(1) If any part of the powerplant mount or

propeller mount is found loose, prior to

further flight, accomplish paragraphs 2

through 4 in the Instructions section of

Glaser-Dirks TN Nr. 826/22, dated January

10, 1990. The engine ignition timing

procedures shall be accomplished in

accordance with the appropriate Bombardier

ROTAX maintenance manual for ROTAX

engine type 505, which is referenced in

Working Instruction No. 3, Instruction 4 of

the Glaser-Dirks TN Nr. 826/22.

(2) If no part of the powerplant mount or

propeller mount is loose upon the inspection

required in paragraph (a) of this AD,

accomplish paragraphs 2 through 4 in the

Instructions section of Glaser-Dirks TN Nr.

826/22, dated January 10, 1990, within the

next 3 calendar months after the date of the

initial inspection.

Note 2: It is recommended that the manual

pages referenced in the Instructions section

of Glaser-Dirks TN Nr. 826/22 be inserted

into the maintenance manual.

(b) 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 glider to a

location where the requirements of this AD

can be accomplished.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(d) Questions or technical information

related to DG Flugzeugbau Technical Note

No. 826/22, dated January 10, 1990, should

be directed to DG Flugzeugbau GmbH, P.O.

Box 4120, 76625 Bruchsal, Germany;

telephone: +49 7257–89–0; facsimile: +49

7257–8922. This service information may be

examined at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

Note 4: The subject of this AD is addressed

in German AD 90–43 Glaser-Dirks, dated

February 26, 1990.

Issued in Kansas City, Missouri, on June 1,

1998.

Ronald K. Rathgeber,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–15197 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–116–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model CL–600–2B19 (Regional Jet

Series 100 and 200) 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 certain

Bombardier Model CL–600–2B19

(Regional Jet Series 100 and 200)

airplanes, that currently requires

repetitive inspections to detect

discrepancies of the shock strut end

caps and attachment pins of the main

landing gear (MLG), and replacement of

discrepant parts with new parts. It also

requires a check for and replacement of

certain pins that currently may be

installed on some airplanes. This action

would add a requirement for the

installation of new, improved MLG

shock strut upper and lower attachment

pins, which would constitute

terminating action for the repetitive

inspections. This action also would

reduce the applicability of the existing

AD by removing certain airplanes. This

proposal is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to prevent failure of

attachment pins and the attachment pin

end caps, which could result in failure

of the MLG.

DATES: Comments must be received by

July 9, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

116–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00