Federal Register / Vol. 62, No. 15 / Thursday, January 23, 1997 / Rules and Regulations 3449

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 (b) 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 improper grounding of the

housing of the lavatory pump and filter

assembly, which could result in an electrical

fire and/or injury to passengers and

crewmembers, accomplish the following:

(a) Within 6 months after the effective date

of this AD, install a bonding cable for the

housing of the lavatory pump and filter

assembly and the lavatory bowl in

accordance with Fokker Service Bulletin

SBF50–25–046, Revision 1, dated August 5,

1994 (for Model F27 Mark 050 series

airplanes); and Service Bulletin SBF100–25–

069, dated July 13, 1994, as revised by

Service Bulletin Change Notification (SBCN)

SBF100–25–069/01, dated February 15, 1995

(for Model F28 Mark 0100 series airplanes);

as applicable.

(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, 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(d) The installation shall be done in

accordance with Fokker Service Bulletin

SBF50–25–046, Revision 1, dated August 5,

1994; and Fokker Service Bulletin SBF100–

25–069, dated July 13, 1994, as revised by

Service Bulletin Change Notification (SBCN)

SBF100–25–069/01, dated February 15, 1995;

as applicable. Fokker Service Bulletin

SBF50–25–046, Revision 1, dated August 5,

1994, contains the following list of effective

pages:

Page No. Revision level shown on page Date shown on page

1 ........................................................................................... 1 .......................................................................................... August 5, 1994.

2–3 ....................................................................................... Original ................................................................................ August 1, 1994.

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 Fokker Services B.V.,

Technical Support Department, P.O.

Box 75047, 1117 ZN Schiphol Airport,

The Netherlands. 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.

(e) This amendment becomes effective

on February 27, 1997.

Issued in Renton, Washington, on January

8, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–882 Filed 1–22–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–243–AD; Amendment

39–9889; AD 97–02–05]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Jetstream Model

4101 airplanes, that currently requires,

among other things, replacing certain

yaw damper servos in the autopilot

system, or rendering the servo

inoperative. The actions specified by

that AD are intended to prevent

overheat failure of the Flight Control

Computer (FCC), which could result in

smoke in the flight deck that could

inhibit the ability of the flightcrew to

safely operate and land the airplane.

This new amendment requires

installation of circuit breakers on the

avionics relay panel, which, when

accomplished, constitutes terminating

action for the previous requirements of

the AD.

DATES: Effective February 27, 1997.

The incorporation by reference of

Jetstream Service Bulletin J41–22–006,

dated July 1, 1996, as listed in the

regulations, is approved by the Director

of the Federal Register as of February

27, 1997.

The incorporation by reference of

Jetstream Alert Service Bulletin J41–22–

005, dated July 1, 1996, as listed in the

regulations, was approved previously by

the Director of the Federal Register as of

October 1, 1996 (61 FR 48614,

September 16, 1996).

ADDRESSES: The service information

referenced in this AD may be obtained

from Jetstream Aircraft, Inc., P.O. Box

16029, Dulles International Airport,

Washington, DC 20041–6029. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 96–19–06,

amendment 39–9754 (61 FR 48614,

September 16, 1996), which is

applicable to certain Jetstream Model

4101 airplanes, was published in the

Federal Register on October 23, 1996

(61 FR 54967). The action proposed to

supersede AD 96–19–06 to continue to

require the actions currently specified

in that AD:

1. A one-time inspection of the

airplane records to determine:

—the serial number,

—the total number of hours time-inservice accumulated,

—the date of installation of the yaw

damper servo in the autopilot system;

and

—the date of installation of a particular

kit, if installed.

2. Removal and replacement of certain

yaw damper servos, or rendering the

yaw damper servo inoperative.

The action also proposed to add a

requirement to install circuit breakers

on the avionics relay panel. When

accomplished, this installation would

constitute terminating action for the

previous requirements of the AD.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No
3450 Federal Register / Vol. 62, No. 15 / Thursday, January 23, 1997 / Rules and Regulations

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 55 Jetstream

Model 4101 airplanes of U.S. registry

that will be affected by this AD.

The actions that are currently

required by AD 96–19–06 take

approximately 2 to 5 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

previously required actions on U.S.

operators is estimated to be between

$6,600 and $16,500, or between $120

and $300 per airplane.

The new action (installation of circuit

breakers) that is required by this new

AD will take approximately 3 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Required parts will be provided by the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of the installation requirement of this

AD on U.S. operators is estimated to be

$9,900, or $180 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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 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.

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 39–9754 (61 FR

48614, September 16, 1996), and by

adding a new airworthiness directive

(AD), amendment 39–9889, to read as

follows:

97–02–05 Jetstream Aircraft Limited:

Amendment 39–9889. Docket 96–NM–

243–AD. Supersedes AD 96–19–06,

Amendment 39–9754.

Applicability: Model 4101 airplanes having

serial numbers 41004 through 41092,

inclusive; on which Jetstream Service

Bulletin J41–22–006, dated July 1, 1996 (Kit

JK42867), has not been accomplished;

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, unless

accomplished previously.

To prevent overheat failure of the Flight

Control Computer (FCC), which could result

in smoke in the flight deck that could inhibit

the ability of the flightcrew to safely operate

and land the airplane, accomplish the

following:

(a) Within 14 days after October 1, 1996

(the effective date of AD 96–19–06), perform

a one-time inspection of the airplane records

to determine the serial number, the total

number of hours time-in-service

accumulated, and the date of installation of

the yaw damper servo in the autopilot

system; and to determine the date of

installation of Kit JK42716 (reference

Jetstream Service Bulletin J41–53–016 or J41–

22–007), if installed. Accomplish the

inspection in accordance with Part 1 of the

Accomplishment Instructions of Jetstream

Alert Service Bulletin J41–A22–005, dated

July 1, 1996. Thereafter, either remove and

replace the yaw damper servo and install Kit

JK42716 (if not installed previously), or

render the yaw damper servo inoperative, in

accordance with Part 2 or 3 of the alert

service bulletin, respectively, at the time

specified in paragraph (a)(1), (a)(2), or (a)(3)

of this AD, as applicable.

(1) If Kit JK42716 has not been installed:

Prior to the accumulation of 1,000 hours total

time-in-service on the yaw damper servo, or

within 30 days after October 1, 1996,

whichever occurs later.

(2) If Kit JK42716 has been installed and

the yaw damper servo was installed prior to

the installation of Kit JK42716: Prior to the

accumulation of 1,000 hours total time-inservice on the yaw damper servo, or within

30 days after October 1, 1996, whichever

occurs later.

(3) If Kit JK42716 has been installed and

the yaw damper servo was installed after the

installation of Kit JK42716: Prior to the

accumulation of 3,000 total hours time-inservice on the yaw damper servo, or within

30 days after October 1, 1996, whichever

occurs later.

(b) Within 90 days after the effective date

of this AD, install circuit breakers on the

avionics relay panel (Kit JK42867) in

accordance with Jetstream Service Bulletin

J41–22–006, dated July 1, 1996.

Accomplishment of this installation

constitutes terminating action for the

requirements of paragraph (a) 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,

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 actions shall be done in accordance

with Jetstream Alert Service Bulletin J41–

A22–005, dated July 1, 1996; and Jetstream

Service Bulletin J41–22–006, dated July 1,

1996. The incorporation by reference of

Jetstream Alert Service Bulletin J41–A22–

005, dated July 1, 1996, 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 October 1, 1996 (61
Federal Register / Vol. 62, No. 15 / Thursday, January 23, 1997 / Rules and Regulations 3451

FR 48614, September 16, 1996). The

incorporation by reference of Jetstream

Service Bulletin J41–22–006, dated July 1,

1996, 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 Jetstream Aircraft, Inc., P.O.

Box 16029, Dulles International Airport,

Washington, DC 20041–6029. 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

January 23, 1997.

Issued in Renton, Washington, on February

27, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–881 Filed 1–22–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–21–AD; Amendment 39–

9885; AD 97–02–01]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc. (Formerly Piper

Aircraft Corporation) Model PA–31T2

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to The New Piper Aircraft, Inc.

(Piper) Model PA–31T2 airplanes that

have a Parker Hannifin Wheel and Brake

Conversion Kit 199–111 installed in

accordance with Supplemental Type

Certificate (STC) SA599GL. This action

requires rerouting the landing gear

emergency extension line. This AD

results from three incidents of the brake

cylinder contacting the landing gear

emergency extension air line on both

wheel wells. The actions specified by

this AD are intended to prevent the

brake cylinder from chafing against the

landing gearemergency extension air

line when the gear is in the up and

locked position, which could result in

damage to the air line and subsequent

loss of emergency gear extension

capability.

DATES: Effective February 14, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

14, 1997.

ADDRESSES: Service information that

applies to this AD may be obtained from

the Parker Hannifin Corporation,

Aircraft Wheel & Brake, 1160 Center

Road, P.O. Box 158, Avon, Ohio 44011;

telephone (216) 937–6211; facsimile

(216) 937–5409. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket 95–

CE–21–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.

Nick Miller, Aerospace Engineer,

Chicago Aircraft Certification Office,

FAA, 2300 East Devon Avenue, Des

Plaines, Illinois 60018; telephone (847)

294–7837; facsimile (847) 294–7834.

SUPPLEMENTARY INFORMATION:

Events Leading to This Action

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to Piper Model PA–31T2

airplanes that have a Parker Hannifin

Wheel and Brake Conversion Kit 199–

111 installed in accordance with STC

SA599GL was published in the Federal

Register on June 13, 1996 (61 FR 29992).

The action proposed to require rerouting

the landing gear emergency extension

air line. Accomplishment of the

proposed action as specified in the

supplemental notice of proposed

rulemaking (NPRM) would be in

accordance with Parker Hannifin

Service Bulletin SB7034, Revision B,

dated December 19, 1995.

The supplemental NPRM results from

three incidents of the brake cylinder

contacting the landing gear emergency

extension air line on both wheels.

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.

Cost Impact

The FAA estimates that 62 Piper

Model PA31–T2 airplanes in the U.S.

registry could incorporate Parker

Hannifin Wheel and Brake Conversion

Kit 199–111 (in accordance with STC

SA599GL), that it will take

approximately 4 workhours per airplane

to accomplish the required action, and

that the average labor rate is

approximately $60 an hour. Parts cost

approximately $20 per airplane. Based

on these figures, the total cost impact of

the AD on U.S. operators could be as

much as $16,120 if all affected airplanes

had the referenced conversion kit

installed.

Parker Hannifin has informed the

FAA that it has distributed 31 kits

(shipped after March 28, 1994) to Piper

Model PA31T2 airplane owners/

operators. Kits shipped after March 28,

1994, included the replacement parts

referenced in Parker Hannifin SB7034,

Revision B, dated December 19, 1995.

Based on each of the 31 kits being

incorporated on an affected airplane, the

cost impact of this AD on U.S. owners

and operators is reduced 50 percent

from $16,120 to $8,060. The reduction

results from the difference between the

62 airplanes that are type certificated to

have a Parker Hannifin Wheel and Brake

Conversion Kit 199–111 incorporated

(in accordance with STC SA599GL) and

the 31 kits that have already been

distributed.

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.