[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]


-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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