Federal Register / Vol. 60, No. 78 / Monday, April 24, 1995 / Rules and Regulations 20017

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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new AD to read as follows:

95–08–13 B. Grob Flugzeugbau:

Amendment 39–9202; Docket No. 94–

CE–30–AD.

Applicability: Model G109B gliders, serial

numbers 6200 through 6445, 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 use the authority

provided in paragraph (c) 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 glider from the

applicability of this AD.

Compliance: Required within the next 25

hours time-in-service after the effective date

of this AD or within the next 6 calendar

months after the effective date of this AD,

whichever occurs first, unless already

accomplished.

To prevent failure of the elevator inner

hinges because of delamination or corrosion,

which, if not detected and corrected, could

lead to loss of control of the glider,

accomplish the following:

(a) Replace the elevator inner hinges (2)

with hinges of improved design, part number

109B–3550, in accordance with Grob Repair

Instructions No. 817–25 for Service Bulletin

TM 817–25, dated November 9, 1987.

Note 2: The service instructions of this AD

call for ‘‘the execution of the instructions to

be certified in the log-book by an authorized

inspector class 3.’’ This type of inspector is

not applicable in the United States and the

person accomplishing the AD is as outlined

in part 43 of the Federal Aviation Regulations

(14 CFR part 43). This is not a change over

normal AD procedures.

(b) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate gliders 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

should 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) The replacement required by this AD

shall be done in accordance with Grob Repair

Instructions No. 817–25 for Service Bulletin

TM 817–25, dated November 9, 1987. 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 B. Grob

Flugzeugbau, D–8939 Mattsies, Germany.

Copies may be inspected at the FAA, Central

Region, Office of the Assistant Chief 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.

(e) This amendment (39–9202) becomes

effective on June 2, 1995.

Issued in Kansas City, Missouri, on April

11, 1995.

Dwight A. Young,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–9342 Filed 4–21–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–ANE–58; Amendment 39–

9203; AD 95–08–14]

Airworthiness Directives; AlliedSignal,

Inc. (Formerly Textron Lycoming)

LTS101 Series Turboshaft Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to AlliedSignal, Inc.

(formerly Textron Lycoming) LTS101

series turboshaft engines. This action

requires a one-time replacement of

magnetic speed pickups in the engine

electronic overspeed protection system,

or inspection, and replacement, if

necessary, of pickups with incorrect

polarity. This amendment is prompted

by reports of a manufacturing error that

resulted in improper sensor polarity of

magnetic speed pickups. The actions

specified in this AD are intended to

prevent the engine electronic overspeed

protection system from failing to

function as designed, which can result

in the inability to arrest an uncontrolled

power turbine (PT) rotor overspeed and

damage to the aircraft.

DATES: Effective May 9, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

June 23, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

94–ANE–58, 12 New England Executive

Park, Burlington, MA 01803–5299.

The service information referenced in

this AD may be obtained from

AlliedSignal Engines, 550 Main Street,

Stratford, CT 06497; telephone (203)

385–1470, fax (203) 385–2256. This

information may be examined 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.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7148,

fax (617) 238–7199.
20018 Federal Register / Vol. 60, No. 78 / Monday, April 24, 1995 / Rules and Regulations

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

has received reports of a manufacturing

error that resulted in improper sensor

polarity of magnetic speed pickups on

certain AlliedSignal, Inc. (formerly

Textron Lycoming) Models LTS101–

650B1, –750B1, –650C3/3A, and –750C1

turboshaft engines. These engines

incorporate an engine electronic

overspeed protection system installed in

production or retrofitted in accordance

with Textron Lycoming Service Bulletin

(SB) No. LTS101B–73–10–0127,

Revision 2, dated August 14, 1992, or

previous revisions; or SB No. LTS101C–

73–10–0129, Revision 3, dated August

14, 1992, or previous revisions. The

engine electronic overspeed protection

system utilizes signals from two

magnetic pickups to sense and arrest

power turbine (PT) rotor overspeed. The

improper sensor polarity induced by the

manufacturing error can result in a

malfunctioning engine electronic

overspeed protection system although

the system self-test indicates normal

operation. This condition, if not

corrected, could result in the engine

electronic overspeed protection system

failing to function as designed, which

can result in the inability to arrest an

uncontrolled PT rotor overspeed and

damage to the aircraft.

The FAA has reviewed and approved

the technical contents of AlliedSignal

Engines SB No. LTS101–73–10–0169,

dated December 12, 1994, that describes

procedures for a one-time replacement

of magnetic speed pickups in the engine

electronic overspeed protection system,

or inspection, and replacement, if

necessary, of pickups with incorrect

polarity.

Since an unsafe condition has been

identified that is likely to exist or

develop on other AlliedSignal, Inc.

LTS101 series engines of the same type

design, this airworthiness directive (AD)

is being issued to prevent the engine

electronic overspeed protection system

from failing to function as designed.

This AD requires a one-time

replacement of magnetic speed pickups

in the engine electronic overspeed

protection system, or inspection, and

replacement, if necessary, of pickups

with incorrect polarity. The actions are

required to be accomplished in

accordance with the service bulletin

described previously.

Since a situation exists that requires

the immediate adoption of this

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 should 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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 94–ANE–58.’’ The

postcard will be date stamped and

returned to the commenter.

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 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–08–14 AlliedSignal, Inc.: Amendment

39–9203. Docket 94–ANE–58.

Applicability: AlliedSignal, Inc. (formerly

Textron Lycoming) Models LTS101–650B1,

–750B1, –650C3/3A, and –750C1 turboshaft

engines incorporating engine electronic

overspeed protection system installed in

production prior to the effective date of this

airworthiness directive (AD), or retrofitted in

accordance with Textron Lycoming Service

Bulletin (SB) No. LTS101B–73–10–0127,

Revision 2, dated August 14, 1992, or

previous revisions; or SB No. LTS101C–73–

10–0129, Revision 3, dated August 14, 1992,

or previous revisions. These engines are

installed on but not limited to

Messerschmitt-Bolkow-Blohm BK117 series

and Bell Helicopter Textron 222 series

helicopters.

Note: This 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 (c) 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
Federal Register / Vol. 60, No. 78 / Monday, April 24, 1995 / Rules and Regulations 20019

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 the engine electronic overspeed

protection system from failing to function as

designed, which can result in the inability to

arrest an uncontrolled power turbine (PT)

rotor overspeed and damage to the aircraft,

accomplish the following:

(a) Within 150 hours time in service after

the effective date of this AD, accomplish

either paragraph (a)(1) or paragraph (a)(2) of

this AD.

(1) Replace magnetic speed pickups, P/N

4–301–356–01, in the engine electronic

overspeed protection system, with a

serviceable part in accordance with Allied

Signal Engines SB No. LTS101–73–10–0169,

dated December 12, 1994.

(2) Inspect magnetic speed pickups, P/N 4–

301–356–01, in the engine electronic

overspeed protection system, for polarity in

accordance with AlliedSignal Engines SB No.

LTS101–73–10–0169, dated December 12,

1994, and prior to further flight, remove

magnetic speed pickups with incorrect

polarity, and replace with a serviceable part,

in accordance with AlliedSignal Engines SB

No. LTS101–73–10–0169, dated December

12, 1994.

(b) Prior to installation, inspect all

uninstalled magnetic speed pickups, P/N 4–

301–356–01, for polarity, and replace

pickups with incorrect polarity with a

serviceable part, in accordance with

AlliedSignal Engines SB No. LTS101–73–10–

0169, dated December 12, 1994.

(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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

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.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(e) The inspection, and replacement, of the

magnetic speed pickups shall be done in

accordance with the following AlliedSignal

Engines service document:

Document No. Pages Date

SB No. LTS101–

73–10–0169.

1–3 Dec. 12, 1994.

Total pages: 3

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, 550 Main Street,

Stratford, CT 06497; telephone (203) 385–

1470, fax (203) 385–2256. 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.

(f) This amendment becomes effective on

May 9, 1995.

Issued in Burlington, Massachusetts, on

April 11, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–9472 Filed 4–19–95; 2:14 pm]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–ANE–04; Amendment 39–

9204; AD 95–08–15]

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Pratt & Whitney (PW) JT8D

series turbofan engines. This action

requires a one-time borescope

inspection of certain combustion

chamber outer cases (CCOC) installed

only on McDonnell Douglas DC–9 series

and Boeing 737 series aircraft, and an

ultrasonic inspection of all affected

CCOC’s at every accessibility. This

amendment is prompted by reports of

two CCOC ruptures in service and of

two CCOC’s discovered during

maintenance with intergranular cracks.

The actions specified in this AD are

intended to prevent CCOC rupture,

which can result in an uncontained

engine failure and damage to the

aircraft.

DATES: Effective May 9, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

June 23, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–ANE–04, 12 New England Executive

Park, Burlington, MA 01803–5299.

The service information referenced in

this AD may be obtained from Pratt &

Whitney, 400 Main St, East Hartford, CT

06108. This information may be

examined 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.

FOR FURTHER INFORMATION CONTACT:

Mark A. Rumizen, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7137,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

has received reports of two uncontained

engine failures on Pratt & Whitney (PW)

JT8D series turbofan engines.

Investigation revealed that the engine

failures were due to combustion

chamber outer case (CCOC) ruptures

that exhibited intergranular cracking.

The CCOC ruptures resulted from the

low cycle fatigue (LCF) propagation of

the intergranular crack. In addition,

intergranular cracking on two other

CCOC’s was discovered during in-shop

maintenance. The FAA has determined

that intergranular cracks may develop

from an initiation site on the case

during assembly of the CCOC to the

high pressure turbine (HPT) case, or

during engine operation in which an

impact load is imposed on the CCOC.

During subsequent engine operation, the

crack can then propagate to failure due

to normal LCF loads. Analysis of

operating experience relative to CCOC

ruptures indicated that only engines

installed on McDonnell Douglas DC–9

series and Boeing 737 series aircraft

have a significant risk of CCOC rupture,

whereas engines installed on other

aircraft have been statistically proven to

have less risk of CCOC rupture.

Therefore, the FAA has determined that

a borescope inspection of CCOC’s

installed only on McDonnell Douglas

DC–9 series and Boeing 737 series

aircraft is required to meet safety of

flight criteria. However, the FAA has

determined that an ultrasonic

inspection of all affected CCOC’s during

in-shop maintenance is also required,

regardless of intended aircraft

installation, to meet safety of flight

criteria. This condition, if not corrected,

could result in CCOC rupture, which

can result in an uncontained engine

failure and damage to the aircraft.

The FAA has reviewed and approved

the technical contents of PW Alert

Service Bulletin (ASB) No. A6202, dated

February 20, 1995, that describes

procedures for a one-time borescope

inspection of certain CCOC’s installed