4944 Federal Register / Vol. 62, No. 22 / Monday, February 3, 1997 / Proposed Rules

Restatement of Requirements of AD 94–24–

02

(b) Within 7 days after December 14, 1994

(the effective date of AD 94–24–02,

amendment 39–9075), accomplish the

requirements of paragraph (b)(1) and (b)(2) of

this AD:

(1) Until the requirements of paragraph

(c)(2) of this AD are accomplished, remove

the elevator dampers in accordance with

Canadair Regional Jet Alert Service Bulletin

S.B. A601R–27–041, dated October 28, 1994.

(2) Revise the Limitations Section of the

FAA-approved AFM to include the

following, which advises the flight crew of

daily checks to verify proper operation of the

elevator control system. Revision of the AFM

may be accomplished by inserting a copy of

this AD or AFM Revision 32, dated March 30,

1995, in the AFM.

Note 3: The daily check described in the

AFM Temporary Revision (TR)RJ/40, dated

October 28, 1994, meets the requirements of

this paragraph. Therefore, inserting a copy of

TR RJ/40 into the AFM in lieu of this AD is

considered an acceptable means of

compliance with this paragraph.

‘‘Elevator, Before Engine Start (First Flight of Day)

(1) Elevator ................................................. Check ...... Travel range (to approximately 1/2 travel) using each hydraulic system in turn,

with the other hydraulic systems depressurized.’’

New Requirements of this AD

(c) Within 12 months after the effective

date of this AD, perform the requirements of

paragraphs (c)(1) and (c)(2) of this AD, as

applicable, in accordance with Canadair

Regional Jet Service Bulletin S.B. 601R–27–

040, Revision ‘B,’ dated September 11, 1995.

(1) For airplanes having serial numbers

7003 through 7049, inclusive: Perform the

inspections specified in paragraphs (c)(1)(i),

(c)(1)(ii), and (c)(1)(iii) of this AD in

accordance with Section 2.B., Part A, of the

service bulletin.

(i) Remove the shear pins and shear links

of the flutter dampers and perform a visual

inspection to detect any deformation or

discrepancy of the flutter damper hinge

fitting and lug of the horizontal stabilizer.

Prior to further flight, replace any deformed

or discrepant part with a serviceable part in

accordance with the service bulletin.

(ii) Perform a visual inspection to detect

any deformation or discrepancy of the

elevator hinge/damper fitting and shear pin

lugs. Prior to further flight, replace any

discrepant part with a serviceable part in

accordance with the service bulletin.

(iii) Perform a fluorescent penetrant

inspection and a dimensional inspection to

detect any deformation or discrepancy of the

shear pin lugs. If any deformation or

discrepancy is found on the lugs, prior to

further flight, replace the elevator with a new

or serviceable elevator in accordance with

the service bulletin.

(2) For airplanes having serial numbers

7003 through 7054, inclusive: Install new

shear pins [part number (P/N) 601R24063–

953] and new elevator flutter dampers (P/N

601R75142–7) in accordance with Section

2.B., Part B, of the service bulletin:

(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, New York

Aircraft Certification Office (ACO), FAA,

Engine and Propeller Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(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 January

27, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–2519 Filed 1–31–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–29–AD]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F28 Mark 0070 and 0100 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to certain Fokker

Model F28 Mark 0070 and 0100 series

airplanes, that would have required a

one-time operational test of the pitot

heating system, and repair or

replacement of failed elements. That

action also proposed to require the

replacement of the pitot heating system

with a new improved system. This new

action would revise the proposal by

adding a requirement to install power

supply wiring with increased gauge

thickness and a circuit breaker with an

increased amperage rating. This action

also would add additional airplanes to

the applicability of the rule. The actions

specified by this proposed AD are

intended to prevent icing of the No. 1

pitot tube, which could result in failure

of the No. 1 Air Data Computer, or

output of erroneous airspeed data to all

on-side subsidiary systems, including

the Automatic Flight Control and

Augmentation System.

DATES: Comments must be received by

February 24, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

29–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 Services B.V., Technical Support

Department, P. O. Box 75047, 1117 ZN

Schiphol Airport, The Netherlands. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT: Tim

Dulin, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2141; fax (206) 227–1149.

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,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact
Federal Register / Vol. 62, No. 22 / Monday, February 3, 1997 / Proposed Rules 4945

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 95–NM–29–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.

95–NM–29–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to certain

Fokker Model F28 Mark 0100 and 0070

series airplanes, was published as a

supplemental notice of proposed

rulemaking (NPRM) in the Federal

Register on February 12, 1996 (61 FR

5329). That supplemental NPRM

proposed to require a one-time

operational test of the pitot heating

system, and repair or replacement of

failed elements. That supplemental

NPRM also proposed to require the

replacement of the No. 1 pitot heating

system powered by direct current (DC)

with a new improved pitot heating

system powered by alternating current

(AC). That supplemental NPRM was

prompted by reports indicating that the

captains airspeed indicator and the No.

1 Air Data Computer (ADC #1) failed on

Model F28 Mark 0100 series airplanes

due to icing of the No. 1 pitot tube, even

though both DC-powered heating

elements were operating normally. Icing

of the No. 1 pitot heat system, if not

corrected, could result in failure of the

ADC #1, or lead to output of erroneous

data to all on-side subsidiary systems,

including the Automatic Flight Control

and Augmentation System (AFCAS).

Actions Since Issuance of Previous

Proposal

Since the issuance of that

supplemental NPRM, the

Rijksluchtvaartdienst (RLD), which is

the airworthiness authority for the

Netherlands, and Fokker have notified

the FAA that during emergency power

conditions (battery power only), the

new AC-powered (853BR) pitot tube

described in Fokker Service Bulletin

SBF100–30–017 may not de-ice

sufficiently due to a low DC battery

voltage input to the No. 1 pitot tube

inverter. The low voltage is due to

insufficient thickness of the wire gauge

of the power supply wiring.

Additionally, during emergency power

conditions, the inverter draws more

current to maintain the specified power

to the pitot tube, which could trip the

No. 1 pitot heating circuit breaker.

In light of this information, the

actions proposed in the previous

proposal would be inadequate to

prevent icing of the No. 1 pitot tube, and

the same unsafe condition would

continue to exist.

New Service Information

In light of the above, Fokker has

issued Service Bulletin SBF100–30–019,

dated June 20, 1996, which supersedes

Fokker Service Bulletin SBF100–30–017

(which was referenced in the previous

supplemental NPRM). This new service

bulletin describes procedures for:

1. Replacement of the captains pitot

heating system with type 853BR pitot

heating system,

2. Installation of a new power supply

wiring with increased gauge thickness

of AWG 12, and

3. Installation of a new No. 1 pitot

tube circuit breaker with an increased

amperage rating to 20 Amps.

Accomplishment of these actions will

ensure that the No. 1 pitot tubes have

adequate de-icing capability.

Fokker also has issued Service

Bulletin SBF100–30–020, dated June 20,

1996, which describes procedures for

installation of new power supply wiring

with increased gauge thickness of AWG

12, and a new No. 1 pitot tube circuit

breaker with an increased amperage

rating of 20 Amps, for those airplanes

on which type 853BR pitot heating

system has previously been installed in

accordance with Fokker Service Bulletin

SBF100–30–017.

The RLD classified these service

bulletins as mandatory and issued

Netherlands airworthiness directive

BLA 1994–114/4 (A), dated July 31,

1996, in order to assure the continued

airworthiness of these airplanes in the

Netherlands.

FAA’s Conclusions

The FAA has examined the findings

of the RLD and reviewed the new

service information. The FAA finds that

the proposed actions in the previously

issued supplemental NPRM may not

prevent freezing of the No. 1 pitot tube

during emergency power conditions.

Therefore, to ensure the safety of the

fleet, the FAA finds that, in addition to

the previously proposed actions, other

actions are necessary.

Explanation of Requirements of

Proposed AD

This new action proposes to continue

to require operational tests of the No. 1

pitot heating system and replacement of

the pitot heating system with a new

improved system. This new action

would add a requirement to install a

new power supply wiring with

increased gauge thickness, and a circuit

breaker with an increased amperage

rating. These new proposed

requirements would affect airplanes on

which the new improved pitot heating

system has been installed previously (in

accordance with Fokker Service Bulletin

SBF100–30–017). In addition, this new

proposal would add additional

airplanes to the applicability of the rule.

These actions would be required to be

accomplished in accordance with the

applicable service bulletins described

previously.

Operators should note that the

operational test of the No. 1 pitot

heating system, as proposed previously,

continues to be required in this

supplemental NPRM. The service

information describing that operational

test (referenced as Fokker Service

Bulletin SBF100–30–015, Revision 2,

dated January 25, 1995, in the previous

proposal) has been superseded by a later

service bulletin (Fokker Service Bulletin

SBF100–30–017, dated August 23, 1995,

which was superseded by Fokker

Service Bulletin SFB100–30–019); but

the procedures for accomplishing the

operational test were not included in

the superseding service bulletins.

However, the FAA has determined that

accomplishment of this operational test

is necessary in accordance with Fokker

Service Bulletin SBF100–30–015 to

determine if any pitot tube heating

element is inoperative, and to ensure

that any failed element is repaired or

replaced.

Conclusion

Since these changes expand the scope

of the originally proposed rule, the FAA

has determined that it is necessary to

reopen the comment period to provide

additional opportunity for public

comment.

Cost Impact

There are approximately 285 Fokker

Model F28 Mark 0100 and 0070 series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

129 airplanes of U.S. registry would be

affected by this proposed AD.

The proposed operational check

would take approximately 1 work hour

per airplane to accomplish, at an

average labor rate of $60 per work hour.
4946 Federal Register / Vol. 62, No. 22 / Monday, February 3, 1997 / Proposed Rules

Based on these figures, the cost impact

for the proposed operational check on

U.S. operators is estimated to be $7,740,

or $60 per airplane.

The proposed replacement of the pitot

heating system would take

approximately 36 work hours per

airplane, at an average labor rate of $60

per work hour. Required parts would

cost approximately $16,000 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators is estimated to be $18,160 per

airplane.

For airplanes on which replacement

of the pitot heating system has been

accomplished previously, the proposed

installation of the power supply

electrical wiring and circuit breaker

would take approximately 12 work

hours per airplane at an average labor

rate of $60 per work hour. Required

parts would cost approximately $350

per airplane. Based on these figures, the

cost impact is estimated to be $1,070 per

airplane.

The cost impact figures discussed

above are 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.

Regulatory Impact

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Fokker: Docket 95–NM–29–AD.

Applicability: Model F28 Mark 0070 and

0100 series airplanes, certificated in any

category, and having the following serial

numbers: 11244 through 11495, inclusive;

11497 through 11507, inclusive; 11509;

11511 through 11517, inclusive; 11519

through 11523, inclusive; 11527 through

11529, inclusive; 11532; 11536 through

11541, inclusive; 11543; 11545; 11547;

11549; 11551; 11553 through 11565,

inclusive; 11567; 11570; 11573; and 11574.

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 icing of the No. 1 pitot tube,

which could result in failure of the No. 1 Air

Data Computer (ADC #1) or output of

erroneous airspeed data to all on-side

subsidiary systems, including the Automatic

Flight Control and Augmentation System

(AFCAS), accomplish the following:

(a) For airplanes that have type 853JB pitot

tubes installed: Within 30 days after the

effective date of this AD, perform an

operational test of the No. 1 pitot heating

system in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–30–015, Revision 2,

dated January 25, 1995.

(1) If the pitot heating system passes the

operational test, accomplish the requirements

of either paragraph (b)(1) or (b)(2) of this AD,

as applicable, at the times specified.

(2) If any pitot tube heating element is

found to be inoperative, prior to further

flight, repair or replace the failed element

with a serviceable element, in accordance

with the Fokker 100 Aircraft Maintenance

Manual (AMM).

(b) For airplanes on which Fokker Service

Bulletin SBF100–30–017, dated August 23,

1995, has not been accomplished: At the

applicable time specified in either paragraph

(b)(1) or (b)(2) of this AD, replace the type

853JB or type 853KK No. 1 pitot tube, with

a type 853BR pitot tube; and install the

inverter, current sensor, wiring, and circuit

breaker; in accordance with Fokker Service

Bulletin SBF100–30–019, dated June 20,

1996.

(1) For airplanes with the flight warning

system (FWS) speed comparator not activated

and with a type 853JB No. 1 pitot tube

installed: Accomplish the replacement

within 9 months after the effective date of

this AD.

(2) For airplanes with the FWS speed

comparator activated or with a type 853KK

No. 1 pitot tube installed: Accomplish the

replacement within 18 months after the

effective date of this AD.

(c) For airplanes on which Fokker Service

Bulletin SBF100–30–017, dated August 23,

1995, has been accomplished, either in

service or factory-incorporated: Within 18

months after the effective date of the AD,

replace the No. 1 pitot heating circuit breaker

and modify the power supply electrical

wiring, in accordance with Fokker Service

Bulletin SBF100–30–020, dated June 20,

1996.

(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, 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.

(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 January

27, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–2520 Filed 1–31– 97; 8:45 am]

BILLING CODE 4910–13–P