AD Amdt-39-9682
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Fokker | F28 0100 0070 | Airworthiness Directives; Fokker Model F28 Mark 0100 and 0070 Series Airplanes |
Unsafe Condition
Excessive brake wear beyond specified limits could lead to loss of brake effectiveness during a high energy rejected takeoff (RTO).
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Incorporate new maximum brake wear limits for additional brake units into the FAA-approved maintenance program. Remove the requirement to revise the Airplane Flight Manual (AFM) for RTO procedures.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Fokker Model F28 Mark 0100 and 0070 series airplanes with additional brake unit part numbers requiring new wear limits.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
This amendment supersedes 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 amendment requires the incorporation of new maximum brake wear limits for additional brake units into the FAA-approved maintenance program. This action also deletes the previous requirement for the AFM revision. This amendment is prompted by the determination of the maximum allowable brake wear limits for additional brake unit part numbers. The actions specified by the AD are intended to prevent the loss of brake effectiveness during a high energy RTO.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 61, Number 125 (Thursday, June 27, 1996)]
[Rules and Regulations]
[Pages 33305-33308]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 96-16242]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-224-AD; Amendment 39-9682; AD 96-13-13]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F28 Mark 0100 and 0070
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes 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 amendment requires the
incorporation of new maximum brake wear limits for additional brake
units into the FAA-approved maintenance program. This action also
deletes the previous requirement for the AFM revision. This amendment
is prompted by the determination of the maximum allowable brake wear
limits for additional brake unit part numbers. The actions specified by
the AD are intended to prevent the loss of brake effectiveness during a
high energy RTO.
EFFECTIVE DATE: August 1, 1996.
ADDRESSES: Information pertaining to this rulemaking action may be
examined at the Federal Aviation Administration (FAA), Transport
Airplane Directorate, Rules Docket, 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 94-06-06,
amendment 39-8854 (59 FR 11713, March 14, 1994), which is applicable to
certain Fokker Model F28 Mark 0100 series airplanes, was published in
the Federal Register on February 12, 1996 (61 FR 5331). The action
proposed to require the incorporation of new maximum brake wear limits
for additional brake units into the FAA-approved maintenance program.
The action also proposed to delete a previous requirement for a
revision to the Airplane Flight Manual (AFM) that pertained to
reporting certain rejected takeoff conditions to maintenance.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Request To Extend Compliance Time
One commenter requests that the proposed compliance time of 180
days for incorporating the maximum brake wear pin limits into the
maintenance program be extended to 360 days. This commenter, a U.S.
operator, requests this extension in order to ensure that the new
information provided in the AD can be inserted in its fleet's required
manuals during a normal revision cycle. This would avoid the costs and
time associated with having to issue a temporary partial revision and/
or supplement.
The FAA does not concur. In developing an appropriate compliance
time for this action, the FAA considered not only the degree of urgency
associated with addressing the subject unsafe condition, but the
practical aspect of incorporating and implementing the required
maintenance program change within a reasonable
[[Page 33306]]
period of time for the majority of affected operators. Additionally,
the FAA has issued numerous other AD's, applicable to transport
category airplanes, with requirements and compliance times similar to
this one [for example, reference AD 94-09-03, amendment 39-8891 (59 FR
18713, April 20, 1994), pertaining to British Aerospace Model BAe 146
series airplanes; AD 94-11-07, amendment 39-8923 (59 FR 28475, June 2,
1994), pertaining to British Aerospace Model BAC 1-11 series airplanes;
and AD 94-26-05, amendment 39-9101, (60 FR 3, January 3, 1995),
pertaining to Airbus Model A300, A310, and A320 series airplanes]. The
180-day compliance time specified in each of the previously issued AD's
apparently has posed no problem in implementation for operators that
are subject to those AD's. The FAA considers that the brake wear limits
should be followed as soon as this information can reasonably be
incorporated into an affected operator's maintenance program. Since the
issuance of temporary manual revisions is a common practice among
operators, the FAA cannot find that the incorporation of information
required by this AD within the 180-day time period would be an undue
burden on any operator.
Request To Clarify Service Information
This same commenter requests clarification as to the appropriate
manual that should be used to determine the limits for refurbished
brakes. The commenter points out an apparent discrepancy in the
proposed AD between Note 5 in proposed paragraph (a)(l) and Table 4:
Both reference the Aircraft Braking Systems (ABS) Component Maintenance
Manual with Illustrated Parts List, but one specifies the document
number as ``AP-652,'' while the other specifies ``AP-625.''
The FAA notes this typographical error. The correct document number
is AP-652, which was shown correctly in Note 5 of the proposal. The FAA
has revised Table 4 of the final rule to indicate this correct document
number.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
There are approximately 124 Model F28 Mark 0100 and 0070 series
airplanes of U.S. registry and 5 U.S. operators that will be affected
by this 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 required by this AD action will 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 new 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 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, 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.
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), amendment 39-9682, to read as follows:
96-13-13 Fokker: Amendment 39-9682. 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, -8, 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
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 (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
[[Page 33307]]
program and comply with these measurements thereafter.
Table 1.--Brake Manufacturer: Aircraft Braking Systems Corporation (ABS)
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Maximum settings--non refurbished brakes
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Brake P/N- Maximum wear pin measurement- (inch/ Alternate wear measurement (inch/
mm) mm)
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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)
----------------------------------------------------------------------------------------------------------------
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
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Maximum settings--refurbished brakes
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Brake P/N Maximum wear-pin measurement- (inch/ Alternate wear measurement (inch/
mm) mm)
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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)
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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 part number (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 equipped with brakes having
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
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Maximum settings--non-refurbished brakes (original equipment manufacturer)
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Brake unit part No.- Measure in accordance with aircraft braking
Maximum wear pin measurement- Alternate brake wear systems (ABS) component maintenance manual with
measurement illustrated parts list (CMM w/IPL) number
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5008132-2......................... 1.85'' (47 mm) 4.00'' (101.6 mm) CMM w/IPL AP-652 (32-43-77)
5008132-3......................... 1.85'' (47 mm) 4.00'' (101.6 mm) CMM w/IPL AP-652 (32-43-77)
5008132-4......................... 2.10'' (53.3 mm) 4.25'' (107.9 mm) CMM w/IPL AP-652 (32-43-77)
5008132-5......................... 2.10'' (53.3 mm) 4.25'' (107.9 mm) CMM w/IPL AP-652 (32-43-77)
5008132-6......................... 2.10'' (53.3 mm) 4.25'' (107.9 mm) CMM w/IPL AP-652 (32-43-77)
5008132-7......................... 2.10'' (53.3 mm) 4.25'' (107.9 mm) CMM w/IPL AP-652 (32-43-77)
5008132-8......................... 2.20'' (55.9 mm) 4.35'' (110.5 mm) CMM w/IPL AP-652 (32-43-77)
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[[Page 33308]]
Table 4
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Maximum settings--refurbished brakes (R11-3 on brake housing)
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Brake unit part number Measure in accordance with aircraft braking
Maximum wear pin measurement Alternate brake wear systems (ABS) component maintenance manual with
measurement illustrated parts list (CMM w/IPL) number
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5008132-2......................... 1.85'' (47 mm) 4.00'' (101.6 mm) CMM w/IPL AP-652(32-43-77)
5008132-3-........................ 1.85'' (47 mm) 4.00'' (101.6 mm) CMM w/IPL AP-652 (32-43-77)
5008132-4-........................ 2.20'' (55.9 mm) 4.35'' (110.5 mm) CMM w/IPL AP-652 (32-43-77)
5008132-5-........................ 2.20'' (55.9 mm) 4.35'' (110.5 mm)- CMM w/IPL AP-652 (32-43-77)
5008132-6-........................ 2.20'' (55.9 mm) 4.35'' (110.5 mm)- CMM w/IPL AP-652 (32-43-77)
5008132-7-........................ 2.20'' (55.9 mm) 4.35'' (110.5 mm)- CMM w/IPL AP-652 (32-43-77)
5008132-8-........................ 2.20'' (55.9 mm) 4.35'' (110.5 mm)- CMM w/IPL AP-652 (32-43-77)
--------------------------------------------------------------------------------------------------------------------------------------------------------
(2) For Model F28 Mark 0100 and 0070 series airplanes equipped a
brake unit having 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) Component
Maintenance Manual (CMM) with Illustrated Parts List (IPL) AP-747
(32-43-65).
(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.
(e) This amendment becomes effective on August 1, 1996.
Issued in Renton, Washington, on June 19, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service. -
[FR Doc. 96-16242 Filed 6-26-96; 8:45 am]
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