41260 Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations

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

removing amendment 39–8813 (59 FR

4575, February 1, 1994), and by adding

a new airworthiness directive (AD),

amendment 39–10095, to read as

follows:

97–16–04 SAAB Aircraft AB: Amendment

39–10095. Docket 96–NM–130–AD.

Supersedes AD 94–03–06, Amendment

39–8813.

Applicability: Model SAAB SF340A series

airplanes having serial numbers 004 through

159 inclusive; and Model SAAB 340B series

airplanes having serial numbers 160 through

345 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 request approval for an

alternative method of compliance in

accordance with paragraph (d) 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 incorrect wiring of the wire

harness installation to the fire extinguisher

cartridges in the engine nacelles, which

would result in the inability of the fire

extinguishers to jointly discharge agent into

a nacelle in the event of a fire, accomplish

the following:

(a) Within 25 days after February 16, 1994

(the effective date of AD 94–03–06,

amendment 39–8813), perform an inspection

to ensure proper connections of the wire

harness installation to the engine nacelle fire

extinguisher, in accordance with Saab

Service Bulletin SAAB 340–26–012, Revision

1, dated October 5, 1993, or Saab Service

Bulletin SAAB 340–26–015, Revision 1,

dated December 8, 1995. Prior to further

flight, correct any discrepancy found and

modify the wiring, in accordance with the

service bulletin. After the effective date of

this AD, perform this inspection and correct

any discrepancy found, in accordance with

Saab Service Bulletin SAAB 340–26–015,

Revision 1, dated December 8, 1995.

(b) Repeat the inspection specified in

paragraph (a) of this AD immediately

following any maintenance action during

which both electric connectors to either of

the fire extinguishers in the nacelle electrical

bays are disconnected.

(c) Prior to the accumulation of 4,000 hours

time-in-service after the effective date of this

AD, or at the next scheduled maintenance

inspection after the effective date of this AD,

whichever occurs earlier:

(1) Conduct an inspection to ensure proper

connection of the wire harness installation to

the fire extinguisher cartridges in both engine

nacelles, in accordance with Saab Service

Bulletin SAAB 340–26–015, Revision 1,

dated December 8, 1995. If any discrepancy

is detected, prior to further flight, correct this

discrepancy in accordance with the service

bulletin.

(2) After the inspection required by

paragraph (c)(1) of this AD has been

accomplished, measure the total length of the

wiring harness from the clamp to connector

9WB–P2/10WB–P2, in accordance with Saab

Service Bulletin SAAB 340–26–015, Revision

1, dated December 8, 1995. If the wiring

harness has been modified with a loop in

accordance with the requirements of

paragraph (a) of this AD, or in accordance

with Saab Service Bulletin SAAB 340–26–

012, Revision 1, dated October 5, 1993,

before measuring, remove the loop in the

wire harness in accordance with Saab Service

Bulletin SAAB 340–26–015, Revision 1,

dated December 8, 1995.

(i) If the total length is 7 inches (180mm)

or less, no further action is required by this

AD.

(ii) If the total length exceeds 7 inches

(180mm), modify this wiring in accordance

with Saab Service Bulletin SAAB 340–26–

015, Revision 1, dated December 8, 1995.

Accomplishment of this modification

constitutes terminating action for the

repetitive inspections required by paragraph

(b) of this AD, and no further action is

required by this AD.

Note 2: Accomplishment of this

modification in accordance with Saab

Service Bulletin SAAB 340–26–015, dated

November 23, 1995, prior to the effective date

of this AD, is considered acceptable for

compliance with the requirements of

paragraph (c)(2)(ii) of this AD.

(d) 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(e) 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.

(f) The actions shall be done in accordance

with Saab Service Bulletin SAAB 340–26–

012, Revision 1, dated October 5, 1993, and/

or Saab Service Bulletin SAAB 340–26–015,

Revision 1, dated December 8, 1995. The

incorporation by reference of Saab Service

Bulletin SAAB 340–26–012, Revision 1,

dated October 5, 1993, was approved

previously by the Director of the Federal

Register, in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51, as of February 16, 1994

(59 FR 4575, February 1, 1994). The

incorporation by reference of Saab Service

Bulletin SAAB 340–26–015, Revision 1,

dated December 8, 1995, is 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 SAAB Aircraft

AB, SAAB Aircraft Product Support, S–

581.88, Linko ̈ping, Sweden. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(g) This amendment becomes effective on

September 5, 1997.

Issued in Renton, Washington, on July 25,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–20128 Filed 7–31–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–19–AD; Amendment

39–10092; AD 97–16–02]

RIN 2120–AA64

Airworthiness Directives; Robinson

Helicopter Company Model R44

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Robinson Helicopter

Company (Robinson) Model R44

helicopters. This action requires

inspections of the belt tension actuator

switches (up-limit switches) for proper
Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations 41261

operation, and replacement if necessary;

and replacement of a certain partnumbered clutch assembly. This

amendment is prompted by six

occurrences of prematurely worn sprag

clutches. The actions specified in this

AD are intended to prevent failure of the

sprag clutch to lock in the driving

direction, which would result in loss of

power to the main rotor system and a

subsequent forced landing; or failure of

the sprag clutch to unlock in the

overrunning direction, which, if

combined with engine failure, would

result in an inability to autorotate and

a subsequent loss of control of the

helicopter.

DATES: Effective August 18, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 18,

1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 18,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

September 30, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 97–SW–19–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

The service information referenced in

this AD may be obtained from Robinson

Helicopter Company, 2901 Airport

Drive, Torrance, California 90505,

telephone (310) 539–0508, fax (310)

539–5198. This information may be

examined at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas

76137; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ms.

Elizabeth Bumann, Aerospace Engineer,

FAA, Los Angeles Aircraft Certification

Office, Propulsion Branch, 3960

Paramount Blvd., Lakewood, California

90712, telephone (562) 627–5265, fax

(562) 627–5210.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new Airworthiness

Directive (AD), which is applicable to

Robinson Model R44 helicopters and

requires, within 25 hours time-inservice (TIS) after the effective date of

this AD and thereafter at intervals not to

exceed 100 hours TIS, an inspection of

both up-limit switches, part number (P/

N) V3–1001, for proper operation, and

replacement of either switch, if

necessary. Additionally, this AD

requires, within 50 hours TIS after the

effective date of this AD, replacement of

the clutch assembly, P/N C018–1, with

clutch assembly, P/N C018–2 or P/N

C018–2A. This AD is prompted by six

occurrences of prematurely worn sprag

clutches. Five of those clutch

assemblies’ hours TIS ranged from 286.3

to 828.6 hours TIS. All of the clutch

assemblies were making noise during

the landings and/or shutdowns. One

clutch assembly would not allow the

main rotor to disengage from the engine

during a practice autorotation. Excessive

wear of the sprag crowns and chattering

of the sprag races causes erratic

operation of the clutch by preventing

the sprags from rolling into or releasing

from the locked position. A latent

failure of one up-limit switch can exist

undetected, eliminating the redundancy

of the system. A failure of both up-limit

switches while in the closed position

will result in over-tensioning of the

drive belts. The actions specified in this

AD are intended to prevent failure of the

sprag clutch to lock in the driving

direction, which would result in loss of

power to the main rotor system and a

subsequent forced landing; or failure of

the sprag clutch to unlock in the

overrunning direction, which, if

combined with engine failure, would

result in an inability to autorotate and

a subsequent loss of control of the

helicopter.

The FAA has reviewed Robinson

Helicopter Company R44 Service

Bulletin SB–21, dated April 18, 1997,

which describes procedures for

removing the aft engine cowling and

inspecting to verify that both up-limit

switches function properly. If either uplimit switch does not function properly,

the service bulletin refers the reader to

the replacement procedures in the

maintenance manual. The FAA has also

reviewed Robinson Helicopter Company

R44 Service Bulletin SB–23, dated May

30, 1997, which describes or refers to

the appropriate procedures for replacing

clutch assembly, P/N C018–1. The

compliance times of this AD differ from

those stated in the service bulletins.

Robinson Helicopter Company R44

Service Bulletin SB–21 describes a onetime inspection within the next 10

hours TIS, or by April 30, 1997,

whichever occurs first; this AD requires

an initial inspection within 25 hours

TIS after the effective date of this AD,

and thereafter, repetitive inspections at

intervals not to exceed 100 hours TIS.

Robinson Helicopter Company R44

Service Bulletin SB–23 describes

replacing the clutch assembly within

the next 100 hours TIS, or by September

30, 1997, whichever occurs first; this

AD requires replacing the clutch

assembly within 50 hours TIS after the

effective date of this AD, since the only

indication of excessive sprag clutch

wear is hard or rough engagement of the

clutch, which may be difficult for a pilot

to detect. The failure of the clutch

assembly to allow the main rotor system

to disengage from the engine in the

event of an engine failure creates a

significant unsafe condition in that this

condition would result in an inability to

autorotate.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Robinson Model R44

helicopters of the same type design, this

AD is being issued to prevent failure of

the sprag clutch to lock in the driving

direction, which will result in loss of

power to the main rotor and a

subsequent forced landing; or failure of

the sprag clutch to unlock in the

overrunning direction, which, if

combined with engine failure, could

result in catastrophic loss of the

helicopter since the main rotor cannot

be disengaged from the engine for

autorotation.

This AD requires both initial and

repetitive inspections of the up-limit

switches, P/N V3–1001, to determine

that they are functioning properly, and

replacement of either up-limit switch, if

necessary; and replacement of the

clutch assembly, P/N C018–1 with

clutch assembly, P/N C018–2 or P/N

C018–2A. The actions are required to be

accomplished in accordance with the

compliance procedures contained in the

service bulletins 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
41262 Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations

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 No. 97–SW–19–AD.’’ 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 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.

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 to

read as follows:

97–16–02 Robinson Helicopter Company:

Amendment 39–10092. Docket No. 97–

SW–19–AD.

Applicability: Model R44 helicopters,

serial numbers 0001 through 0332,

certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters 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 (d) 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 helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the sprag clutch to

lock in the driving direction, which would

result in loss of power to the main rotor

system and a subsequent forced landing; or

failure of the sprag clutch to unlock in the

overrunning direction, which, if combined

with engine failure, would result in an

inability to autorotate and a subsequent loss

of control of the helicopter, accomplish the

following:

(a) Within 25 hours time-in-service (TIS)

after the effective date of this AD, and

thereafter, at intervals not to exceed 100

hours TIS, inspect both up-limit switches,

part number (P/N) V3–1001, for proper

operation in accordance with the Compliance

Procedure in Robinson Helicopter Company

R44 Service Bulletin SB–21, dated April 18,

1997. If the motor runs when the springs are

depressed on one side, the switch on the

OPPOSITE side is not functioning properly.

(b) If the inspections required by paragraph

(a) of this AD indicate that either up-limit

switch does not function properly, replace

the up-limit switch with an airworthy uplimit switch in accordance with the

Compliance Procedure contained in

Robinson Helicopter Company R44 Service

Bulletin SB–21, dated April 18, 1997.

(c) Within 50 hours TIS after the effective

date of this AD, replace the clutch assembly,

P/N C018–1, with a clutch assembly, P/N

C018–2 or P/N C018–2A, in accordance with

the Compliance Procedure contained in

Robinson Helicopter Company R44 Service

Bulletin SB–23, dated May 30, 1997.

(d) 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, Los

Angeles Aircraft Certification Office, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(e) 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(f) The inspections and replacements, if

necessary, shall be done in accordance with

Robinson Helicopter Company R44 Service

Bulletin SB–21, dated April 18, 1997, and

Robinson Helicopter Company R–44 Service

Bulletin SB–23, dated May 30, 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

Robinson Helicopter Company, 2901 Airport

Drive, Torrance, California 90505, telephone

(310) 539–0508, fax (310) 539–5198. Copies

may be inspected at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(g) This amendment becomes effective on

August 18, 1997.

Issued in Fort Worth, Texas, on July 22,

1997.

Mark R. Schilling,

Acting Manager, Rotercraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–20195 Filed 7–31–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–36; Amendment 39–

10091; AD 97–05–11 R1]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal

Inc. ALF502 and LF507 Series

Turbofan 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. ALF502

and LF507 series turbofan engines, that

currently requires initial and repetitive

inspections of the oil system chip

detectors and oil filter bypass valve, and

optional installation of an improved oil

filter bypass valve, to ensure the