21070 Federal Register / Vol. 61, No. 91 / Thursday, May 9, 1996 / Rules and Regulations

(b) Replacement of the lower gate hinge of

the forward galley service door with an

improved hinge, in accordance with Boeing

Alert Service Bulletin 737–52A1124, dated

January 11, 1996, constitutes terminating

action for the requirements of this AD.

(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, Seattle

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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 inspection and replacement shall

be done in accordance with Boeing Alert

Service Bulletin 737–52A1124, dated January

11, 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. 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

May 24, 1996.

Issued in Renton, Washington, on May 1,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–11407 Filed 5–8–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–12; Amendment 39–

9609; AD 96–10–04]

Airworthiness Directives; AlliedSignal,

Inc. LTS101–600 Series Turboshaft

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to AlliedSignal, Inc. LTS101–

600 series turboshaft engines, that

requires installation of an improved

design fuel control. This amendment is

prompted by reports of fuel control

bearings failing prior to the

recommended overhaul period. The

actions specified by this AD are

intended to prevent a fuel control

failure, which could result in an

uncommanded increase or decrease in

engine power.

DATES: Effective June 13, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 13,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from AlliedSignal Engines, 111 South

34th Street, Phoenix, AZ 85072;

telephone (602) 365–2493, fax (602)

365–2210. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

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:

Dave Keenan, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7139,

fax (617) 238–7199.

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 AlliedSignal, Inc.

Models LTS101–600A–2/A–3 turboshaft

engines was published in the Federal

Register on August 21, 1995 (60 FR

43413). That action proposed to require

the installation of an improved fuel

control in accordance with AlliedSignal

Engines Service Bulletin (SB) No.

LTS101A–73–20–0166, Revision 1,

dated November 21, 1994.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter, the manufacturer,

states that since the issuance of the

NPRM, AlliedSignal, Inc. has revised

AlliedSignal Engines SB No. LTS101A–

73–20–0166 to recommend the

installation of a screened pneumatic

fitting on the main fuel control (MFC).

The FAA concurs in part. Both revisions

of the SB address the incorporation of

fuel control drive (Meldin) bearings in

the MFC in the same manner, which is

the primary focus of this AD. The FAA

has determined that installation of a

screened pneumatic fitting is not

necessary to prevent a MFC failure due

to lack of bearing lubrication. Therefore,

this final rule references both

AlliedSignal Engines SB No. LTS101A–

73–20–0166, Revision 1, dated

November 21, 1994, and Revision 2,

dated August 1, 1995, but does not

require installation of a screened

pneumatic fitting.

The manufacturer also states that due

to the time required to publish the

NPRM and receive comments, the AD

will not be published prior to

compliance end-date specified in the

NPRM. The FAA concurs and has

extended the compliance end-date in

this final rule to September 1, 1996.

In addition, the FAA is considering

future rulemaking to address other

aircraft installations of the AlliedSignal,

Inc. LT101 series engines.

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

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

The FAA estimates that 216 engines

installed on aircraft of U.S. registry will

be affected by this AD, that it will take

approximately 2.5 work hours per

engine to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $1,000 per

engine. Based on these figures, the total

cost impact of the AD on U.S. operators

is estimated to be $248,400.

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.
Federal Register / Vol. 61, No. 91 / Thursday, May 9, 1996 / Rules and Regulations 21071

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–10–04 AlliedSignal, Inc.: Amendment 39–

9609. Docket 95–ANE–12.

Applicability: AlliedSignal, Inc. Models

LTS101–600A–2 and A–3 turboshaft engines,

installed on but not limited to Eurocopter

AS350 series aircraft.

Note: This airworthiness directive (AD)

applies to each engine 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 engines 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)

to request approval from the Federal Aviation

Administration (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 engine from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent a fuel control failure, which

could result in an uncommanded increase or

decrease in available engine power,

accomplish the following:

(a) At the next replacement of an affected

fuel control, prior to accumulating 300 hours

time in service (TIS) after the effective date

of this AD, or September 1, 1996, whichever

occurs first, accomplish the following in

accordance with AlliedSignal Engines

Service Bulletin (SB) No. LTS101A–73–20–

0166, Revision 1, dated November 21, 1994,

or Revision 2, dated August 1, 1995:

(1) For AlliedSignal, Inc. Model LTS101–

600A–2 engines, install an improved fuel

control, P/N 4–301–098–04 with ‘‘B’’ or ‘‘BF’’

stamped on the data plate after the dash

number of the AlliedSignal Aerospace

Equipment Division (formerly AlliedSignal

Controls and Accessories/Bendix) part

number, or P/N 4–301–098–15. These

improved fuel controls incorporate fuel

control drive (Meldin) bearings.

(2) For AlliedSignal, Inc. Model LTS101–

600A–3 engines, install an improved fuel

control, P/N 4–301–288–02 with ‘‘B’’ or ‘‘BF’’

stamped on the data plate after the dash

number of the AlliedSignal Aerospace

Equipment Division (formerly AlliedSignal

Controls and Accessories/Bendix)

P/N, or P/N 4–301–288–04. These improved

fuel controls incorporate fuel control drive

(Meldin) bearings.

(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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(d) The actions required by this AD shall

be done in accordance with the following

AlliedSignal Engines SB’s:

Document

No. Pages Revision Date

LTS101A–

73–20–

0166.

1–3 1 November

21, 1994.

Total Pages:

3.

LTS101A–

73–20–

0166.

1–6 2 August 1,

1995.

Total Pages:

6.

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 AlliedSignal Engines, 111 South 34th

Street, Phoenix, AZ 85072; telephone (602)

365–2493, fax (602) 365–2210. Copies may be

inspected at the FAA, New England Region,

Office of the Assistant Chief 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.

(e) This amendment becomes effective on

June 13, 1996.

Issued in Burlington, Massachusetts, on

April 24, 1996.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 96–11258 Filed 5–8–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–ANE–03; Amendment 39–

9583; AD 69–09–03 R3]

Airworthiness Directives; Sensenich

Propeller Manufacturing Company Inc.

Models M76EMM, M76EMMS, 76EM8,

and 76EM8S() Metal Propellers

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to Sensenich Propeller

Manufacturing Company Inc. Models

M76EMM, M76EMMS, 76EM8, and

76EM8S() metal propellers, that

currently restricts operators from

continuously operating the propeller at

engine speeds from 2,150 to 2,350

revolutions per minute (RPM) and

specifies propeller inspection and

rework or replacement. This

amendment eliminates the requirement

to add tachometer markings on aircraft

with certain additional Textron

Lycoming O–360 series reciprocating

engines with solid crankshafts installed,

and updates the referenced Sensenich

Propeller Company Inc. service bulletin

to the latest revision. Reworking of all

affected propeller models remains a

requirement of the AD, regardless of

engine installation. This amendment is

prompted by inquiries concerning

tachometer red arc restrictions on

certain Textron Lycoming O–360 series

reciprocating engines with solid

crankshafts. The actions specified by

this AD are intended to prevent

propeller blade tip fatigue failure, which

can result in loss of control of the

aircraft.

DATES: Effective June 13, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 13,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Sensenich Propeller

Manufacturing Company Inc., 519

Airport Road, Lititz, PA 17543;

telephone (717) 569–0435, fax (717)

560–3725. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., 7th Floor, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Raymond J. O’Neill, Aerospace