[Federal Register Volume 66, Number 70 (Wednesday, April 11, 2001)]
[Rules and Regulations]
[Pages 18721-18723]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-8614]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-290-AD; Amendment 39-12172; AD 2001-07-07]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0070 and Mark 
0100 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 all Fokker Model F.28 Mark 0070 and Mark 0100 
series airplanes, that currently requires revising the Airplane Flight 
Manual (AFM) to provide the flightcrew with instructions not to arm the 
liftdumper system prior to commanding the landing gear to extend. For 
Model F.28 Mark 0100 series airplanes, the existing AD also requires 
modification of the grounds of the shielding of the wheelspeed sensor 
wiring of the main landing gear (MLG) and installation of new 
electrical grounds for the wheelspeed sensor channel of the anti-skid 
control box of the MLG. This amendment removes the previous revision of 
the AFM and requires a new limitation and a new warning. This amendment 
is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by this AD are intended to prevent inadvertent deployment of 
the liftdumpers during approach for landing or reduced brake pressure 
during low speed taxiing, and consequent reduced controllability and 
performance of the airplane.

DATES: Effective May 16, 2001.
    The incorporation by reference of certain publications, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as of November 2, 1999 (64 FR 52219, September 28, 
1999).

[[Page 18722]]


ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-20-07, 
amendment 39-11337 (64 FR 52219, September 28, 1999), which is 
applicable to all Fokker Model F.28 Mark 0070 and Mark 0100 series 
airplanes, was published in the Federal Register on January 16, 2001 
(66 FR 3518). The action proposed to continue to require modification 
of the grounds of the shielding of the wheelspeed sensor wiring of the 
main landing gear (MLG) and installation of new electrical grounds for 
the wheelspeed sensor channel of the anti-skid control box of the MLG. 
The action also proposed to remove the previously required revision of 
the Airplane Flight Manual (AFM) and would require a new limitation and 
a new warning.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 123 airplanes of U.S. registry that will be 
affected by this AD.
    The modifications that are currently required by AD 99-20-07 take 
approximately 33 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts cost approximately $755 
to $1,236 per airplane. Based on these figures, the cost impact of the 
currently required actions on U.S. operators is estimated to be between 
$336,405 and $395,568, or between $2,735 and $3,216 per airplane.
    The revision to the AFM required in this AD will take approximately 
1 work hour per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of the AFM 
revision required by this AD on U.S. operators is estimated to be 
$7,380, or $60 per airplane.
    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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 removing amendment 39-11337 (64 FR 
52219, September 28, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-12172, to read as follows:

2001-07-07 Fokker Services B.V.: Amendment 39-12172. Docket 2000-NM-
290-AD. Supersedes AD 99-20-07, Amendment 39-11337.

    Applicability: All Model F.28 Mark 0070 and Mark 0100 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 (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 inadvertent deployment of the liftdumper systems 
during the approach for landing or reduced brake pressure during low 
speed taxiing, and consequent reduced controllability and 
performance of the airplane, accomplish the following:

Restatement of Certain Requirements of AD 99-20-07

Corrective Actions

    (a) For Model F.28 Mark 0100 series airplanes having serial 
numbers as listed in Fokker Service Bulletin SBF100-32-067, Revision 
1, dated July 6, 1998: Within 6 months after November 2, 1999 (the 
effective date of AD 99-20-07, amendment 39-11337), modify the 
grounds of the shielding of the wheelspeed sensor wiring of the main 
landing gear (MLG), in accordance with Part 1, 2, 3, or 4 of the 
Accomplishment Instructions of the service bulletin, as applicable.

    Note 2: Modifications accomplished prior to November 2, 1999, in 
accordance with Fokker Service Bulletin SBF100-32-067, dated March 
12, 1993, are considered acceptable for compliance with the 
requirements of paragraph (a) of this AD.

    (b) For Model F.28 Mark 0100 series airplanes having serial 
numbers as listed in Fokker Service Bulletin SBF100-32-037, Revision 
2, dated December 4, 1998: Within 12 months after November 2, 1999, 
install

[[Page 18723]]

new electrical grounds for the wheelspeed sensor channel of the 
anti-skid control box of the MLG, in accordance with Part 1, 2, or 3 
of the Accomplishment Instructions of the service bulletin, as 
applicable.

    Note 3: Installations accomplished prior to November 2, 1999, in 
accordance with Fokker Service Bulletin SBF100-32-037, dated 
November 12, 1990, or Revision 1, dated November 16, 1998, are 
considered acceptable for compliance with the requirements of 
paragraph (b) of this AD.

New Actions Required by This AD:

Revision of the Airplane Flight Manual

    (c) Within 10 days after the effective date of this AD, revise 
the Limitations and Normal Procedures sections of the FAA-approved 
Airplane Flight Manual (AFM), in accordance with paragraphs (c)(1), 
(c)(2), (c)(3) and (c)(4) of this AD. This may be accomplished by 
inserting a copy of this AD into the appropriate sections of the 
AFM.
    (1) Remove the following information from the Limitations 
section:

``LIFTDUMPER SYSTEM

DO NOT ARM THE LIFTDUMPER SYSTEM BEFORE LANDING GEAR DOWN 
SELECTION.''

    (2) Add the following information to the Limitations section in 
the Miscellaneous Limitations sub-section:

``FLIGHT CONTROLS

NORMAL OPERATION OF LIFTDUMPERS: DO NOT ARM THE LIFTDUMPER SYSTEM 
BEFORE LANDING GEAR IS DOWN AND LOCKED.''

    (3) Remove the following information from Section 5--Normal 
Procedures, sub-section Approach and Landing, after the subject 
Approach:

``BEFORE LANDING

WARNING: DO NOT ARM THE LIFTDUMPER SYSTEM BEFORE LANDING GEAR DOWN 
SELECTION. Selecting Landing Gear DOWN after arming the liftdumper 
system may result in inadvertent deployment of the liftdumpers, 
because the liftdumper arming test may be partially ineffective.''

    (4) Add the following information to Section 5--Normal 
Procedures, sub-section Approach and Landing, after the subject 
Approach:

``BEFORE LANDING

WARNING: DO NOT ARM THE LIFTDUMPER SYSTEM BEFORE LANDING GEAR IS 
DOWN AND LOCKED.''

Alternative Methods of Compliance

    (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, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. 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 4: 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

    (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.

Incorporation by Reference

    (f) Except for the AFM revisions required by paragraph (c) of 
this AD, the actions shall be done in accordance with Fokker Service 
Bulletin SBF100-32-067, Revision 1, dated July 6, 1998; and Fokker 
Service Bulletin SBF100-32-037, Revision 2, dated December 4, 1998; 
as applicable. This incorporation by reference was approved 
previously by the Director of the Federal Register as of November 2, 
1999 (64 FR 52219, September 28, 1999). 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 5: The subject of this AD is addressed in Dutch 
airworthiness directive 1998-042/2, dated February 29, 2000.

Effective Date

    (g) This amendment becomes effective on May 16, 2001.

    Issued in Renton, Washington, on April 2, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-8614 Filed 4-10-01; 8:45 am]
BILLING CODE 4910-13-U