Federal Register / Vol. 63, No. 118 / Friday, June 19, 1998 /Rules and Regulations 33537

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 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, 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 a new airworthiness directive

(AD) to read as follows:

98–13–07 Industrie Aeronautiche E

Meccaniche: Amendment 39–10595;

Docket No. 98–CE–21–AD.

Applicability: Model Piaggio P–180

airplanes, serial numbers 1002, 1004, 1006

through 1017, 1019, and 1021 through 1030,

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 in the

body of this AD, unless already

accomplished.

To prevent water leakage from the lavatory

water duct system, which could collect in the

fuselage, freeze in cold weather conditions,

and cause the rudder control system to jam,

accomplish the following:

(a) Within the next 3 calendar months after

the effective date of this AD, accomplish a

leakage check of all lavatory water tube/hose

connections in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Piaggio Service Bulletin

(Mandatory) No. SB–80–0096, dated January

31, 1997. If leakage is found, prior to further

flight, correct the installation of these

connections in accordance with the abovereferenced service bulletin.

Note 2: Although not required by this AD,

the FAA recommends an inspection of the

rudder cables for corrosion if any evidence of

water is found on the cables.

(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 times that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, 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 Piaggio Service Bulletin

(Mandatory) No. SB–80–0096, dated January

31, 1997, should be directed to I.A.M.

Rinaldo Piaggio S.p.A., Via Cibrario, 4 16154

Genoa, Italy. 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.

(e) The inspection and correction required

by this AD shall be done in accordance with

Piaggio Service Bulletin (Mandatory) No. SB–

80–0096, dated January 31, 1997. 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 I.A.M.

Rinaldo Piaggio S.p.A., Via Cibrario, 4 16154

Genoa, Italy. Copies may be inspected at the

FAA, Central Region, Office of the Regional

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

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

Note 4: The subject of this AD is addressed

in Italian AD 97–022, dated March 2, 1997.

(f) This amendment becomes effective on

August 1, 1998.

Issued in Kansas City, Missouri, on June 8,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–15886 Filed 6–18–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–13–AD; Amendment 39–

10594; AD 98–13–06]

RIN 2120–AA64

Airworthiness Directives; Glaser-Dirks

Flugzeugbau GmbH Model DG–400

Gliders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Glaser-Dirks

Flugzeugbau GmbH (Glaser-Dirks)

Model DG–400 gliders. This AD requires

replacing the bungees that secure the

left engine restraining cable and the

bowden cable of the rear engine door.

This AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for Germany. The actions

specified by this AD are intended to

prevent the engine from locking in flight

and not extending because of the left

restraining cable or bowden cable of the

rear door making contact with the

engine, which could result in loss of

glider power and potential loss of

control.

DATES: Effective August 2, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 2,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

DG Flugzeugbau GmbH, Postfach 4120,

D–76625 Bruchsal 4, Germany;

telephone: +49 7257–89–0; facsimile:

+49 7257–8922. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–13–

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

Kansas City, Missouri 64106; or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Mike Kiesov, Aerospace Engineer, Small
33538 Federal Register / Vol. 63, No. 118 / Friday, June 19, 1998 /Rules and Regulations

Airplane Directorate, Aircraft

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone: (816) 426–6934;

facsimile: (816) 426–2169.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to certain Glaser-Dirks Model DG–

400 gliders was published in the

Federal Register as a notice of proposed

rulemaking (NPRM) on March 19, 1998

(63 FR 13376). The NPRM proposed to

require replacing the bungees that

secure the left engine restraining cable

and the bowden cable of the rear engine

door. Accomplishment of the proposed

action as specified in the NPRM would

be in accordance with Glaser-Dirks

Technical Note No. 826/15, dated

October 1, 1985.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Germany.

Interested persons have been 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

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

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 of This AD

Although the left engine restraining

cable or bowden cable of the rear engine

door would only contact the engine and

block the engine extension during flight,

this unsafe condition is not a result of

the number of times the glider is

operated. The chance of this situation

occurring is the same for a glider with

10 hours time-in-service (TIS) as it is for

a glider with 500 hours TIS. For this

reason, the FAA has determined that a

compliance based on calendar time

should be utilized in this AD in order

to assure that the unsafe condition is

addressed on all gliders in a reasonable

time period.

Cost Impact

The FAA estimates that 27 gliders in

the U.S. registry will be affected by this

AD, that it will take approximately 3

workhours per glider to accomplish this

action, and that the average labor rate is

approximately $60 an hour. Parts cost

approximately $20 per glider. Based on

these figures, the total cost impact of

this AD on U.S. operators is estimated

to be $5,400, or $200 per glider.

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 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, 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 a new airworthiness directive

(AD) to read as follows:

98–13–06 Glaser-Dirks Flugzeugbau

GMBH: Amendment 39–10594; Docket

No. 98–CE–13–AD.

Applicability: Model DG–400 gliders, serial

numbers 4–1 through 4–140, 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 the next 3

calendar months after the effective date of

this AD, unless already accomplished.

To prevent the engine from locking in

flight and not extending because of the left

restraining cable or bowden cable of the rear

door catching on the engine, which could

result in loss of glider power and potential

loss of control, accomplish the following:

(a) Replace the bungees that secure the left

engine restraining cable and the bowden

cable of the rear engine door in accordance

with the Installation plan included with

Glaser-Dirks Technical Note No. 826/15,

dated October 1, 1985.

(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 2: 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 Glaser-Dirks Technical Note No.

826/15, dated October 1, 1985, should be

directed to DG Flugzeugbau GmbH, Postfach

4120, D–76625 Bruchsal 4, 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.

(e) The replacements required by this AD

shall be done in accordance with Glaser-
Federal Register / Vol. 63, No. 118 / Friday, June 19, 1998 /Rules and Regulations 33539

Dirks Technical Note No. 826/15, dated

October 1, 1985. 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 DG Flugzeugbau GmbH,

Postfach 4120, D–76625 Bruchsal 4,

Germany. Copies may be inspected at the

FAA, Central Region, Office of the Regional

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

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

Note 3: The subject of this AD is addressed

in German AD 85–223, dated November 7,

1985.

(f) This amendment becomes effective on

August 2, 1998.

Issued in Kansas City, Missouri, on June 8,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–15893 Filed 6–18–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–38–AD; Amendment

39–10610; AD 97–21–07 R1]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal

Inc. (Formerly Textron Lycoming)

Model T5313B, T5317A, and T53

(Military) Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to AlliedSignal Inc. (formerly

Textron Lycoming) Model T5313B,

T5317A, and T53 series military

turboshaft engines approved for

installation on aircraft certified in

accordance with Section 21.25 of the

Federal Aviation Regulations (FAR),

that currently requires a one-time visual

inspection of accessory drive carrier

assemblies for affected serial numbers

(S/Ns) designating a defective assembly,

and if the S/N is applicable,

replacement with a serviceable

assembly. This amendment adds

military helicopter models and removes

one civilian helicopter model to the

sentence in the Applicability paragraph

of the AD that provides guidance as to

the helicopter models with the affected

engines. This amendment is prompted

by the need to revise the Applicability

paragraph. The actions specified by this

AD are intended to prevent accessory

drive carrier assembly failure, which

could result in an N2 overspeed and an

uncontained engine failure.

DATES: Effective July 6, 1998.

The incorporation by reference of

AlliedSignal Inc. Alert Service Bulletin

(ASB) No. T5313B/17A–A0092,

Revision 1, dated July 1, 1997, ASB No.

T53–L–13B–A0092, dated June 4, 1997,

and ASB No. T53–L–703–A0092, dated

June 4, 1997, as listed in the regulations,

was approved previously by the Director

of the Federal Register as of November

3, 1997 (62 FR 53935, October 17, 1997).

Comments for inclusion in the Rules

Docket must be received on or before

August 18, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–ANE–

38–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

The service information referenced in

this AD may be obtained from

AlliedSignal Aerospace, Attn: Data

Distribution, M/S 64–3/2101–201, P.O.

Box 29003, Phoenix, AZ 85038–9003;

telephone (602) 365–2493, fax (602)

365–5577. This information may be

examined at the FAA, New England

Region, Office of the Regional Counsel,

12 New England Executive Park,

Burlington, MA; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: Ray

Vakili, Aerospace Engineer, Los Angeles

Aircraft Certification Office, FAA,

Transport Airplane Directorate, 3960

Paramount Blvd., Lakewood, CA 90712–

4137; telephone (562) 627–5262, fax

(562) 627–5210.

SUPPLEMENTARY INFORMATION: On

October 8, 1997, the Federal Aviation

Administration (FAA) issued AD 97–

21–07, Amendment 39–10160 (62 FR

53935, October 17, 1997), applicable to

AlliedSignal Inc. (formerly Textron

Lycoming) Model T5313B, T5317A, and

T53 series military turboshaft engines

approved for installation on aircraft

certified in accordance with Section

21.25 of the Federal Aviation

Regulations (FAR), to require a one-time

visual inspection of accessory drive

carrier assemblies for affected serial

numbers (S/Ns) designating a

potentially defective assembly, and if

the S/N is applicable, replacement with

a serviceable assembly. That action was

prompted by a report of an N2

overspeed condition on an AlliedSignal

Inc. Model T5317A–1 turboshaft engine.

That condition, if not corrected, could

result in accessory drive carrier

assembly failure, which could result in

an N2 overspeed and an uncontained

engine failure.

Since the issuance of that AD, the

FAA has been informed that the military

helicopter models that incorporate this

engine installation had been omitted

from the sentence in the Applicability

paragraph of the AD that provides

guidance as to the helicopter models

with the affected engines, and that a

civilian helicopter model, the Kaman

Aircraft Corp. K–1200 series helicopter,

should be removed from the list. The

military helicopter models, certified in

accordance with Section 21.25 of the

FAR, are: the UH–1A through E; UH–

1G, H, L, M; AH–1F, Q, G, S; HH–1H,

K; TH–1L; OV–1C, D; and HH–43. This

revised AD makes these changes to the

Applicability paragraph. All mandatory

actions required by the AD remain the

same.

The FAA has reviewed and approved

the technical contents of AlliedSignal

Inc. Alert Service Bulletin (ASB) No.

T5313B/17A–A0092, Revision 1, dated

July 1, 1997; ASB No. T53–L–13B–

A0092, dated June 4, 1997; and ASB No.

T53–L–703–A0092, dated June 4, 1997.

These ASBs describe procedures for

performing a one-time visual inspection

of accessory drive carrier assemblies for

affected S/Ns designating a defective

assembly, and if the S/N is applicable,

replacement with a serviceable

assembly.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of this same

type design, this AD revises AD 97–21–

07 to add military helicopter models

and remove one civilian helicopter

model from the sentence in the

Applicability paragraph of the AD that

provides guidance as to the helicopter

models with the affected engines. The

actions are required to be accomplished

in accordance with the ASBs described

previously.

Since a situation exists that allows the

immediate adoption of this regulation, it

is found that notice and opportunity for

prior public comment hereon are

unnecessary, 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