[Federal Register Volume 61, Number 29 (Monday, February 12, 1996)]
[Proposed Rules]
[Pages 5331-5334]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-3000]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-224-AD]


Airworthiness Directives; Fokker Model F28 Mark 0100 and 0070 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Fokker Model F28 
Mark 0100 series airplanes, that currently requires certain maximum 
brake wear limits to be incorporated into the FAA-approved maintenance 
inspection program. That AD also currently requires that the Airplane 
Flight Manual (AFM) be revised to include certain procedures concerning 
operations in the event of a rejected takeoff (RTO). This action would 
add a requirement for the incorporation of new maximum brake wear 
limits for additional brake units into the FAA-approved maintenance 
program. This action would also delete the current requirement for the 
AFM revision. This proposal is prompted by the determination of the 
maximum allowable brake wear limits for additional brake unit part 
numbers. The actions specified by the proposed AD are intended to 
prevent the loss of brake effectiveness during a high energy RTO.

DATES: Comments must be received by March 25, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-224-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.
    This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Ruth Harder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-1721; 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 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-224-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-224-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On March 7, 1994, the FAA issued AD 94-06-06, amendment 39-8854 (59 
FR 11713, March 14, 1994), applicable to certain Fokker Model F28 Mark 
0100 series airplanes, to require that certain maximum brake wear 
limits be incorporated into the FAA-approved maintenance program. That 
AD also requires that the Airplane Flight Manual (AFM) be revised to 
include certain procedures concerning operations in the event of a 
rejected takeoff (RTO). That action was prompted by an accident in 
which a transport category airplane executed an RTO and was unable to 
stop on the runway due to worn brakes; and the subsequent review of 
allowable brake wear limits for all transport category airplanes. The 
requirements of that AD are intended to prevent the loss of brake 
effectiveness during a high energy RTO.

Actions Since AD 94-06-06 Was Issued

    Since the issuance of that AD, additional brake unit part numbers, 
that were not addressed in the existing rule, have been evaluated and 
the maximum allowable brake wear limits for these brake units have been 
determined in accordance with a methodology approved by the FAA. The 
FAA has determined that both Model F28 Mark 0100 and F28 Mark 0070 
series airplanes equipped with these brake units are currently 
subjected to the same unsafe condition addressed in the existing AD, 
and that the newly identified maximum brake wear limits must be applied 
to these brake configurations in order to ensure their braking 
effectiveness.
    In addition, the FAA has reviewed the results of 100% worn brake 
RTO testing on the subject brake units as installed on Model F28 Mark 
0100 and 0070 series airplanes. Based on the successful results of 
these laboratory tests, the FAA finds that the main landing gear 
sliding member on these airplanes will not overheat beyond approved 
limits after an RTO. Therefore, the FAA has determined that the AFM 
revision currently required by paragraphs (b) and (c) of AD 94-06-06 is 
no longer necessary.
    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. The FAA has 
determined that AD action is necessary for products of this type design 
that are certificated for operation in the United States.

[[Page 5332]]


Explanation of Proposed New Requirements

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes that are of the same type design, 
that are equipped with the subject brake configurations, and that are 
registered in the United States, the proposed AD would supersede AD 94-
06-06. It would continue to require that maximum brake wear limits for 
certain brake units be incorporated into the FAA-approved maintenance 
program. The proposed AD would require that new maximum brake wear 
limits and alternate wear measurements (AWM*) for additional brake 
units be incorporated into the FAA-approved maintenance program.

    (*An AWM is a measurement of the brake stack that determines 
stack wear. This measurement is used for any brake assembly without 
a wear indicator pin, or any brake assembly having a damaged wear 
indicator pin. The brake wear can be determined by measuring the 
distance from the back of the pressure plate subassembly to the 
inboard face of the brake housing at the wear indicator location.)

Cost Impact

    There are approximately 124 Model F28 Mark 0100 and 0070 series 
airplanes of U.S. registry and 5 U.S. operators that would be affected 
by this proposed AD. The actions that are currently required by AD 94-
06-06 take approximately 20 work hours per operator to accomplish, at 
an average labor rate of $60 per work hour. Based on these figures, the 
cost impact on U.S. operators of the actions currently required is 
estimated to be $6,000, or $1,200 per operator.
    The new actions that are proposed in this AD action would take 
approximately 20 work hours per operator to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact on U.S. operators of the proposed requirements of this AD is 
estimated to be $6,000, or $1,200 per operator.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or 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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8854 (59 FR 
11713, March 14, 1994), and by adding a new airworthiness directive 
(AD), to read as follows:

Fokker: Docket 95-NM-224-AD. Supersedes AD 94-06-06, Amendment 39-
8854.

    Applicability: Model F28 Mark 0100 and F28 Mark 0070 series 
airplanes, equipped with Aircraft Braking Systems Corp. brakes 
having part number (P/N) 5008132-2, -3, -4, -5, -6, -7, or 5011809; 
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 loss of brake effectiveness during a high energy 
rejected take off (RTO), accomplish the following:

    Note 2: An alternate wear measurement (AWM) is a measurement of 
the brake stack that determines stack wear. This measurement is used 
for any brake assembly without a wear indicator pin, or any brake 
assembly having a damaged wear indicator pin. The brake wear can be 
determined by measuring the distance from the back of the pressure 
plate subassembly to the inboard face of the brake housing at the 
wear indicator location.

    (a) For Model F28 Mark 0100 series airplanes: Within 180 days 
after April 13, 1994 (the effective date of AD 94-06-06, amendment 
39-8854), accomplish the requirements of paragraphs (a)(1) and 
(a)(2) of this AD:
    (1) Incorporate the maximum brake wear limits specified in the 
following tables into the FAA-approved maintenance inspection 
program and comply with these measurements thereafter.

                             Brake Manufacturer Aircraft Braking Systems Corp. (ABS)                            
                               Table 1.--Maximum Settings--Non Refurbished Brakes                               
----------------------------------------------------------------------------------------------------------------
                                                                               Alternate wear measurement (inch/
             Brake P/N                Maximum wear pin measurement (inch/mm)                  mm)               
----------------------------------------------------------------------------------------------------------------
5008132-2..........................  1.85'' (47 mm)..........................  4.00'' (101.6 mm)                
5008132-3..........................  1.85'' (47 mm)..........................  4.00'' (101.6 mm)                
5008132-4..........................  2.10'' (53.3 mm)........................  4.25'' (107.9 mm)                
5008132-5..........................  2.10'' (53.3 mm)........................  4.25'' (107.9 mm)                
5008132-6..........................  2.10'' (53.3 mm)........................  4.25'' (107.9 mm)                
5008132-7..........................  2.10'' (53.3 mm)........................  4.25'' (107.9 mm)                
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[[Page 5333]]

    Note 3: Measuring instructions for non refurbished brakes can be 
found in the ABS Component Maintenance Manual with Illustrated Parts 
List AP-652 (Fokker Manual No. 32-43-77) or in ABS Service Bulletin 
Fo100-32-35. ABS Service Bulletin Fo100-32-35 does not contain 
measurement information relative to brake P/N's 5008132-2 and -3.

                                 Table 2.--Maximum Settings--Refurbished Brakes                                 
----------------------------------------------------------------------------------------------------------------
                                                                               Alternate wear measurement (inch/
             Brake P/N                Maximum wear pin measurement (inch/mm)                  mm)               
----------------------------------------------------------------------------------------------------------------
5008132-2..........................  1.85'' (47 mm)..........................  4.00'' (101.6 mm)                
5008132-3..........................  1.85'' (47 mm)..........................  4.00'' (101.6 mm)                
5008132-4..........................  2.20'' (55.9 mm)........................  4.35'' (110.5 mm)                
5008132-5..........................  2.20'' (55.9 mm)........................  4.35'' (110.5 mm)                
5008132-6..........................  2.20'' (55.9 mm)........................  4.35'' (110.5 mm)                
5008132-7..........................  2.20'' (55.9 mm)........................  4.35'' (110.5 mm)                
----------------------------------------------------------------------------------------------------------------

    Note 4: Refurbished brakes will have ``R11-3'' etched on the 
brake housing adjacent to the shuttle valve.
    Note 5: Measuring instructions for refurbished brakes can be 
found in the ABS Component Maintenance Manual with Illustrated Parts 
List AP-652 (Fokker Manual No. 32-43-77) or in ABS Service Bulletin 
Fo100-32-38.

    (2) For brakes on which a heat stack kit having an ``R'' after 
the P/N (i.e., 5010322-2R, also called short stacks) have been 
installed: Operators must use the maximum wear pin length which is 
based on the measured wear of the thinnest disk in the stack and is 
specified on the Airworthiness Tag that accompanies each heat stack 
kit (i.e., for airplanes having brakes with short stacks installed, 
do not use either the standard maximum wear pin measurements or the 
alternate brake wear measurements specified in either Table 1 or 
Table 2 of this AD to determine brake wear.)
    (b) Within 180 days after the effective date of this AD, 
incorporate the maximum brake wear pin limits specified in 
paragraphs (b)(1) and (b)(2) of this AD, as applicable, into the 
FAA-approved maintenance program and comply with these measurements 
thereafter. If any brake has measured wear beyond the maximum wear 
limits specified in those paragraphs, prior to further flight, 
replace it with a brake that is within the wear limits specified in 
the applicable paragraph.
    (1) For Model F28 Mark 0100 and 0070 series airplanes:

              Table 3.--Maximum Settings--Non-Refurbished Brakes (Original Equipment Manufacturer)              
----------------------------------------------------------------------------------------------------------------
                                                                                          Measure in accordance 
                                                                                          with aircraft braking 
                                        Maximum wear pin        Alternate brake wear     systems (ABS) component
      Brake unit part number              measurement                measurement         maintenance manual with
                                                                                         illustrated parts list 
                                                                                                 number         
----------------------------------------------------------------------------------------------------------------
5008132-2........................  1.85'' (47 mm)...........  4.00'' (101.6 mm).......  AP-652(32-43-77) CMM w/ 
                                                                                         IPL                    
5008132-3........................  1.85'' (47 mm)...........  4.00'' (101.6 mm).......  AP-652(32-43-77) CMM w/ 
                                                                                         IPL                    
5008132-4........................  2.10'' (53.3 mm).........  4.25'' (107.9 mm).......  AP-652(32-43-77) CMM w/ 
                                                                                         IPL                    
5008132-5........................  2.10'' (53.3 mm).........  4.25'' (107.9 mm).......  AP-652(32-43-77) CMM w/ 
                                                                                         IPL                    
5008132-6........................  2.10'' (53.3 mm).........  4.25'' (107.9 mm).......  AP-652(32-43-77) CMM w/ 
                                                                                         IPL                    
5008132-7........................  2.10'' (53.3 mm).........  4.25'' (107.9 mm).......  AP-652(32-43-77) CMM w/ 
                                                                                         IPL                    
5008132-8........................  2.20'' (55.9 mm).........  4.35'' (110.5 mm).......  AP-652(32-43-77) CMM w/ 
                                                                                         IPL                    
----------------------------------------------------------------------------------------------------------------


                     Table 4.--Maximum Settings--Refurbished Brakes (R11-3 on Brake Housing)                    
----------------------------------------------------------------------------------------------------------------
                                                                                          Measure in accordance 
                                                                                          with aircraft braking 
      Brake unit part number            Maximum wear pin        Alternate brake wear     systems (ABS) Component
                                          measurement                measurement         maintenance manual with
                                                                                         illustrated parts list 
----------------------------------------------------------------------------------------------------------------
5008132-2........................  1.85'' (47 mm)...........  4.00'' (101.6mm)........  AP-625 (32-43-77) CMM w/
                                                                                         IPL                    
5008132-3........................  1.85'' (47 mm)...........  4.00'' (101.6mm)........  AP-625 (32-43-77) CMM w/
                                                                                         IPL                    
5008132-4........................  2.20'' (55.9 mm).........  4.35'' (110.5mm)........  AP-625 (32-43-77) CMM w/
                                                                                         IPL                    
5008132-5........................  2.20'' (55.9 mm).........  4.35'' (110.5mm)........  AP-625 (32-43-77) CMM w/
                                                                                         IPL                    
5008132-6........................  2.20'' (55.9 mm).........  4.35'' (110.5mm)........  AP-625 (32-43-77) CMM w/
                                                                                         IPL                    
5008132-7........................  2.20'' (55.9 mm).........  4.35'' (110.5mm)........  AP-625 (32-43-77) CMM w/
                                                                                         IPL                    
5008132-8........................  2.20'' (55.9 mm).........  4.35'' (110.5 mm).......  AP-625 (32-43-77) CMM w/
                                                                                         IPL                    
----------------------------------------------------------------------------------------------------------------

    (2) For Model F28 Mark 0100 and 0070 series airplanes having a 
brake unit with P/N 5011809, A5011809, or B5011809: The maximum wear 
pin measurement is 2.50'' (63.5 mm), with an alternate brake wear 
measurement of 4.35'' (110.5 mm). The measurement shall be done in 
accordance with Aircraft Braking Systems (ABS) AP-747 (32-43-65) 
Component Maintenance Manual (CMM) with Illustrated Parts List 
(IPL).
    (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 6: 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.

 
[[Page 5334]]

    Issued in Renton, Washington, on February 6, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-3000 Filed 2-9-96; 8:45 am]
BILLING CODE 4910-13-U