16390 Federal Register / Vol. 60, No. 61 / Thursday, March 30, 1995 / Proposed Rules

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 draft

regulatory 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Boeing: Docket 94–NM–177–AD.

Applicability: Model 727 and Model 737

series airplanes; equipped with J.C. Carter

Company fuel valve actuators, as listed in J.C.

Carter Company Service Bulletin 61163–28–

08, dated December 2, 1994, 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 use the authority

provided in paragraph (b) 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 airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent improper functioning of certain

actuators, which could result in a fuel

imbalance due to the inability of the

flightcrew to crossfeed fuel, or which could

prevent the pilot from shutting off the fuel to

the engine following an engine failure and/

or fire, accomplish the following:

(a) Within 24 months after the effective

date of this AD, replace the actuator having

part number (P/N) 40574–2 (Model EM487–

2, serial numbers 0001 through 1443

inclusive; and Model EM487–3, serial

numbers 0001 through 2711 inclusive), on

the fuel system crossfeed valve and the

engine shutoff valves with a new actuator

having P/N 40574–4, in accordance with the

Accomplishment Instructions of J.C. Carter

Company Service Bulletin 61163–28–08,

dated December 2, 1994.

(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, 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.

(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.

Issued in Renton, Washington, on March

24, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–7779 Filed 3–29–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–116–AD]

Airworthiness Directives; Fokker

Model F28 Mk 0100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Fokker Model F28 Mk 0100

series airplanes. This proposal would

require the installation of modified

Passenger Service Unit (PSU) panel

lenses. This proposal would also require

a one-time post-installation inspection

to detect corrosion or deterioration of

the PSU connectors, and correction of

discrepancies, and application of

sealant. This proposal is prompted by

reports that ‘‘No Smoking’’ and ‘‘Fasten

Seat Belt’’ signs installed in certain

overhead PSU’s are not readable from

passengers’ and flight attendants’ seats.

This proposal is also prompted by

reports of smoke in the passenger cabin

caused by overheating of the PSU

connectors. The actions specified by the

proposed AD are intended to ensure that

warning signs are readable to passengers

and flight attendants, and to eliminate a

potential fire hazard.

DATES: Comments must be received by

May 8, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 94–NM–

116–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Fokker Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia

22314. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Mark Quam, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2145; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,
Federal Register / Vol. 60, No. 61 / Thursday, March 30, 1995 / Proposed Rules 16391

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal 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–NM–116–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

94–NM–116–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Rijksluchtvaartdienst (RLD),

which is the airworthiness authority for

the Netherlands, recently notified the

FAA that an unsafe condition may exist

on certain Fokker Model F28 Mk 0100

series airplanes. The RLD advises that

the ‘‘No Smoking’’ and ‘‘Fasten Seat

Belt’’ signs installed in certain overhead

Passenger Service Units (PSU) on these

airplanes may not be readable to each

seated passenger under all probable

conditions of cabin illumination.

Additionally, these ‘‘No Smoking’’ or

‘‘Fasten Seat Belt’’ signs are not visible

at all from the flight attendants’ seats in

the aft cabin. The ability to clearly see

these signs under all conditions of

illumination in the cabin is necessary in

order to ensure that passengers and

flight attendants are notified when

smoking is not permitted on an aircraft,

and when seat belts must be fastened. If

the ‘‘No Smoking’’ signs are not

readable or visible, passengers and flight

attendants may not be aware of

situations when smoking on the

airplane could present a fire hazard. If

the ‘‘Fasten Seat Belts’’ signs are not

readable or visible, passengers and flight

attendants may not be aware of

situations when it is necessary that they

be properly restrained in their seats to

prevent injury during turbulent or other

flight conditions.

Additionally, the RLD advises that

there have been two reports of smoke in

the passenger aft compartment coming

from a PSU. Investigation revealed that,

in each case, the cause of the smoke was

water ingress (condensation from the air

duct) in the electrical connectors of the

PSU. Water ingression in PSU

connectors can result in corrosion of the

contacts. Because there is a 115V

(alternating) current present, the

temperature inside the connector can

rise subsequently and cause the

connector to melt. This condition, if not

corrected, can result in failure of the

warning signs at the PSU to illuminate

and could pose a fire hazard.

Fokker has issued Service Bulletin

SBF100–25–061, dated March 8, 1994

(as corrected by Fokker Service Bulletin

Change Notification SBF100–25–061/02,

dated June 20, 1994), which describes

procedures for installing modified PSU

panel lenses. (This Fokker service

bulletin refers to Grimes Aerospace

Service Bulletins 10–1178–33–0036 and

10–1178–33–0039, Revision 1, dated

October 31, 1993, for additional

installation instructions.) Certain of the

modified lenses are configured so that

the readability of the warning signs from

the passengers’ seats is improved. Other

modified lenses incorporate a tilted

legend (prisma lens) that makes

readability possible from the aft cabin

flight attendants’ seats. The RLD

classified this service bulletin as

mandatory and issued Netherlands

airworthiness directive BLA 94–078(A),

dated May 11, 1994, in order to assure

the continued airworthiness of these

airplanes in the Netherlands.

Fokker also has issued Service

Bulletin SB100–25–068, dated March

31, 1994, which describes procedures

for conducting a one-time inspection to

detect corrosion or deterioration of the

PSU connectors, correction of

discrepancies identified, and

application of sealant. Fokker

recommends that this inspection be

performed after the modified PSU panel

lenses are installed in accordance with

Service Bulletin SBF100–25–061. The

RLD has classified this service bulletin

as ‘‘Recommended.’’

This airplane model is manufactured

in the Netherlands and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the RLD has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RLD,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

the installation of modified PSU panel

lenses. This action would be required to

be accomplished in accordance with the

Fokker Service Bulletin SBF100–25–

061, described previously.

Additionally, this proposed AD

would require a one-time postinstallation inspection to detect

corrosion or deterioration of the PSU

connectors, correction of discrepancies

identified, and application of sealant.

These actions would be required to be

accomplished in accordance with

Fokker Service Bulletin SB100–25–068.

The proposed AD would be

applicable only to Model F28 Mk 0100

series airplanes having serial numbers

11244 through 11437, inclusive.

Beginning at serial number 11438, the

modified PSU panel lenses were

installed during production.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been included in this notice to clarify

this requirement.

The FAA estimates that 83 airplanes

of U.S. registry would be affected by this

proposed AD.

The proposed installation of the

modified PSU’s would take

approximately 2 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $248 per airplane. Based

on these figures, the total cost impact of

the proposed installation action on U.S.

operators is estimated to be $30,544, or

$368 per airplane.

The proposed one-time inspection of

the PSU connectors would take

approximately 5 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the total cost impact of

the proposed inspection action on U.S.

operators is estimated to be $24,900, or

$300 per airplane.

Based on the figures discussed above,

the total cost impact of the proposed AD

is estimated to be $55,444, or $668 per

airplane. This total cost impact figure is
16392 Federal Register / Vol. 60, No. 61 / Thursday, March 30, 1995 / Proposed Rules

based on assumptions that no operator

has yet accomplished any of the

proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 draft

regulatory 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Fokker: Docket 94–NM–116–AD.

Applicability: Model F28 Mk 0100 series

airplanes having serial numbers 11244

through 11437, inclusive; and equipped with

Grimes Aerospace Passenger Service Units

having part number (P/N) 10–1178–( )

through P/N 10–1571–( ), 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

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 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 airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To ensure that warning signs are readable

to passengers and flight attendants, and to

eliminate a potential fire hazard, accomplish

the following:

(a) Within 9 months after the effective date

of this AD, install modified Passenger Service

Unit (PSU) panel lenses in accordance with

Fokker Service Bulletin SBF100–25–061,

dated March 8, 1994 (as corrected by Fokker

Service Bulletin Change Notification

SBF100–25–061/02, dated June 20, 1994).

(b) Prior to further flight after

accomplishing the installation required by

paragraph (a) of this AD, perform a one-time

post-installation inspection to detect

corrosion and/or deterioration of the PSU

connector, in accordance with Fokker Service

Bulletin SBF100–25–068, dated March 31,

1994. Prior to further flight, correct any

discrepancies detected and apply sealant in

accordance with the service bulletin.

(c) As of the effective date of this AD, no

person shall install on any airplane a Grimes

Aerospace Passenger Service Unit having

part number (P/N) 10–1178–( ) through P/N

10–1571–( ), inclusive.

(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 Aircraft 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.

(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.

Issued in Renton, Washington, on March

24, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–7780 Filed 3–29–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–06–AD]

Airworthiness Directives; Boeing

Model 747 SP, SR, –100, –200, and

–300 Series Airplanes Equipped With

Pratt & Whitney Model JT9D Series

Engines (Excluding Model JT9D–70

Engines)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Boeing Model 747 SP, SR, –100,

–200, and –300 series airplanes. This

proposal would require repetitive

operational tests of the reversible

gearbox pneumatic drive unit (PDU) or

the reversing air motor PDU to ensure

that the unit can restrain the thrust

reverser sleeve, and correction of any

discrepancy found. This proposal is

prompted by the results of an

investigation, which revealed that, in

the event of thrust reverser deployment

during high-speed climb or during

cruise, these airplanes could experience

control problems. The actions specified

by the proposed AD are intended to

ensure the integrity of the fail safe

features of the thrust reverser system by

preventing possible failure modes in the

thrust reverser control system that can

result in inadvertent deployment of a

thrust reverser during flight.

DATES: Comments must be received by

May 24, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

06–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport