[Federal Register Volume 65, Number 10 (Friday, January 14, 2000)]
[Rules and Regulations]
[Pages 2287-2289]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-877]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-318-AD; Amendment 39-11513; AD 2000-01-15]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F27 Mark 050 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Fokker Model F27 Mark 050 series airplanes. For
certain airplanes, this action requires modification of the electrical
power supply of the landing gear anti-skid unit. For certain airplanes,
this action also requires a revision to the Airplane Flight Manual
(AFM) to provide the flight crew with procedures for calculating the
accelerate-stop distance for certain conditions, and installation of a
new ground idle stop assembly and new placards on the top cover of the
pedestal, which terminates the requirements for the AFM revision. This
amendment is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified in this AD are intended to prevent interruption of the anti-
skid system function, or inadvertent selection of reverse thrust during
a rejected takeoff. Either of these conditions could result in reduced
controllability of the airplane.
DATES: Effective January 31, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 31, 2000.
Comments for inclusion in the Rules Docket must be received on or
before February 14, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-318-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the
Netherlands. This information may be examined 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.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The Rijksluchtvaartdienst (RLD), which is
the airworthiness authority for the Netherlands, notified the FAA that
an
[[Page 2288]]
unsafe condition may exist on certain Fokker Model F27 Mark 050 series
airplanes. The RLD advises that analysis of flight test data has
revealed that the braking performance may be less than expected in
certain conditions. During a rejected takeoff (RTO), a restrictor in
the pitch control unit (PCU) is activated if the power levers are moved
to the full reverse position. This restrictor limits the pitch rate of
change of the propeller blades, which affects the average drag and lift
characteristics of the airplane. Movement of the power levers to the
reverse position during an RTO, if not corrected, could result in
reduced controllability of the airplane.
The RLD also advises that, for airplanes equipped with Pratt &
Whitney Model PW127B engines, tests have shown that during an RTO the
propeller revolutions per minute (RPM) may temporarily exceed the trip
level of the generator control unit. This condition causes a loss of
generator power, and possible switching to an alternate bus power
source with consequent interruption of the anti-skid system function.
This condition, if not corrected, could result in reduced
controllability of the airplane.
Explanation of Relevant Service Information
Fokker has issued Service Bulletin SBF50-32-031, dated December 20,
1996, which describes procedures for modification of the electrical
power supply of the landing gear anti-skid unit. The modification
involves revising the EPC-1 panel 2 and panel 3, and EPC-2 direct
current panel, and adding wiring to the various assemblies.
Fokker also has issued Service Bulletin SBF50-76-016, dated
December 20, 1996, which describes procedures for installation of a new
ground idle stop assembly and new placards on the top cover of the
pedestal.
Accomplishment of the actions specified in the service bulletins
and the AFM revision described below is intended to adequately address
the identified unsafe condition. The RLD classified these service
bulletins and the AFM revision described below as mandatory and issued
Dutch airworthiness directives 1996-149 (A), and 1996-150 (A), both
dated December 31, 1996, in order to assure the continued airworthiness
of these airplanes in the Netherlands.
FAA's Conclusions
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 21.19) 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.
Explanation of Requirements of the Rule
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, this AD is being issued to prevent reduced
controllability of the airplane as a result of interruption of the
anti-skid system function, or inadvertent selection of reverse thrust
during an RTO. This AD requires accomplishment of the actions specified
in the service bulletins described previously. This AD also requires a
revision to the Limitations Section of the FAA-approved AFM to provide
the flight crew with procedures for calculating the accelerate-stop
distance for certain conditions.
Cost Impact
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this rule
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
Should an affected Fokker Model F27 Mark 050 series airplane
equipped with Pratt & Whitney Model PW127B engines be imported and
placed on the U.S. Register in the future, it would require
approximately 16 work hours to accomplish the required modification of
the electrical power supply of the landing gear anti-skid unit, at an
average labor rate of $60 per work hour. Required parts would cost
approximately $1,544 per airplane. Based on these figures, the cost
impact of this AD for those airplanes would be $2,504 per airplane.
Should an affected Fokker Model F27 Mark 050 series airplane, as
listed in Fokker Service Bulletin SBF50-76-016, dated December 20,
1996, be imported and placed on the U.S. Register in the future, it
would require approximately 1 work hour to accomplish the required AFM
revision, at an average labor rate of $60 per work hour. It also would
require approximately 1 work hour to accomplish the required
installation of a new ground idle stop assembly and new placards, at an
average labor rate of $60 per work hour. Required parts would cost
approximately $1,000 per airplane. Based on these figures, the cost
impact of this AD for these airplanes would be $1,120 per airplane.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, prior notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
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 under the caption
ADDRESSES. All communications received on or before the closing date
for comments will be considered, and this rule may be amended in light
of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 99-NM-318-AD.'' The postcard will be date stamped and
returned to the commenter.
[[Page 2289]]
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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
2000-01-15 Fokker Services B.V.: Amendment 39-11513. Docket 99-NM-
318-AD.
Applicability: All Model F27 Mark 050 series airplanes,
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 reduced controllability of the airplane as a result
of interruption of the anti-skid system function, or inadvertent
selection of reverse thrust during a rejected takeoff, accomplish
the following:
Modification for Certain Airplanes
(a) For Model F27 Mark 050 series airplanes equipped with Pratt
& Whitney Model PW127B engines: Within 12 months after the effective
date of this AD, modify the electrical power supply of the landing
gear anti-skid unit in accordance with Fokker Service Bulletin
SBF50-32-031, dated December 20, 1996.
Airplane Flight Manual Revision and Installation For Certain Airplanes
(b) For Model F27 Mark 050 series airplanes, as listed in Fokker
Service Bulletin SBF50-76-016, dated December 20, 1996: Accomplish
the actions specified in paragraphs (b)(1) and (b)(2) of this AD.
(1) Within 10 days after the effective date of this AD, revise
the Limitations Section of the FAA-approved Airplane Flight Manual
(AFM) to include the following statement. This may be accomplished
by inserting a copy of this AD in the AFM.
``Correct the `available accelerate-stop distance' as follows:
For dry runways, multiply the relevant figure by 0.9; For wet
runways, subtract 525 feet (160 meters) from the relevant figure;
and
For contaminated and slippery runways, subtract 1,181 feet (360
meters) from the relevant figure.
Additionally, the required accelerate-stop distance, as
calculated from the AFM for a given airplane weight and V1 or Vstop
must be increased in accordance with the same factors given for
available accelerate-stop distance, as shown above.''
(2) Within 12 months after the effective date of this AD,
install a new ground idle stop assembly and new placards on the top
cover of the pedestal, in accordance with Fokker Service Bulletin
SBF50-76-016, dated December 20, 1996. Following accomplishment of
these actions, the AFM revision required by paragraph (b)(1) of this
AD may be removed from the AFM.
Alternative Methods of Compliance
(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, International Branch, ANM-116, 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, International
Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(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.
Incorporation by Reference
(e) The actions required by paragraphs (a) and (b)(2) of this AD
shall be done in accordance with Fokker Service Bulletin SBF50-76-
016, dated December 20, 1996, and Fokker Service Bulletin SBF50-32-
031, dated December 20, 1996; as applicable. 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., P.O. Box 231, 2150 AE Nieuw-
Vennep, 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.
Note 3: The subject of this AD is addressed in Dutch
airworthiness directives 1996-149 (A), and 1996-150 (A), both dated
December 31, 1996.
(f) This amendment becomes effective on January 31, 2000.
Issued in Renton, Washington, on January 7, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-877 Filed 1-13-00; 8:45 am]
BILLING CODE 4910-13-U