Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Series Airplanes

[Federal Register Volume 68, Number 3 (Monday, January 6, 2003)]
[Rules and Regulations]
[Pages 483-485]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-16]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-290-AD; Amendment 39-13004; AD 2002-26-16]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Fokker Model F.28 Mark 0070 and 0100 series 
airplanes, that requires measurement of the over-center force of the 
thrust reverser operating levers, a functional test of the secondary 
lock solenoid of the thrust reversers, and corrective actions if 
necessary. The actions specified by this AD are intended to detect and 
correct an insufficient over-center force in the corresponding thrust 
reverser operating lever, and incorrect setting of the thrust reverser 
selector switch (S9), which could result in uncommanded deployment of 
the thrust reversers during flight and consequent reduced 
controllability of the airplane. This AD is intended to address the 
identified unsafe condition.

DATES: Effective February 10, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 10, 2003.

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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Fokker Model F.28 Mark 0070 
and 0100 series airplanes was published in the Federal Register on 
April 5, 2002 (67 FR 16333). That action proposed to require 
measurement of the over-center force of the thrust reverser operating 
levers; a functional test to verify proper energizing of the secondary 
lock solenoid of the thrust reversers; and corrective actions, if 
necessary.

Explanation of Relevant Service Information

    In the proposed AD, the FAA identified Fokker Service Bulletin 
SBF100-76-015, dated January 15, 2001, as the appropriate source of 
service information for the proposed requirements. Since the proposed 
AD was issued, Fokker issued Service Bulletin Change Notification 
(SBCN) SBF100-76-015/01, dated May 1, 2001, and Manual Change 
Notification--Maintenance Documentation (MCNM) F100-060, Revision 1, 
dated March 19, 2001. The revised MCNM provides wording that is 
consistent with the existing maintenance manual wording to clarify the 
procedures; the procedures otherwise remain unchanged. The SBCN advises 
that the MCNM changes have been incorporated into the service bulletin.

[[Page 484]]

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposed AD

    One commenter fully supports the proposed AD.

Request To Cite Revised Service Documents

    The manufacturer requests that the proposed AD be revised to cite 
the most recent versions of the relevant service documents.
    Based on a review of the document revisions, the FAA concurs with 
the request. Paragraphs (a) and (b) of this AD have been revised 
accordingly.

Request To Clarify Certain Requirements

    The manufacturer requests that paragraph (b) of the proposed AD be 
revised for several reasons. First, the proposed language suggests that 
the functional test is intended to verify proper energizing of the 
secondary lock solenoid, whereas the solenoids are not supposed to 
energize during the test. Second, the reference to movement of the 
``thrust reverser operating lever'' in paragraphs (b)(1), (b)(2), 
(b)(2)(i), and (b)(2)(ii) of the proposed AD suggests that the thrust 
reverser operating levers are operated during the functional test. The 
manufacturer advises that the thrust levers, not the thrust reverser 
operating levers, are operated during the functional test. Third, the 
manufacturer suggests that paragraph (b)(2) of the proposed AD, which 
would require operators to repeat the functional test ``one more 
time,'' could be misinterpreted. The service bulletin provides 
instructions to perform the functional test at least five times before, 
and (if necessary) after, a rigging check of the thrust lever 
switchbox. The functional test involves ``slamming'' the thrust levers 
with the thrust reverser operating levers in the stowed position. The 
commenter suggests a reader could infer that a single ``slam'' is 
sufficient.
    The FAA agrees with the requests for the reasons provided by the 
commenter and has made the following changes in this final rule: First, 
the phrase ``to verify proper energizing'' has been removed from the 
summary and paragraphs (b) and (b)(2) of this AD. Second, the phrase 
``movement of thrust reverser operating levers'' has been changed to 
``movement of the thrust levers'' in paragraphs (b)(1), (b)(2), 
(b)(2)(i), and (b)(2)(ii). Third, the phrase ``one more time'' has been 
removed from paragraph (b)(2).

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

    The FAA estimates that 139 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the cost impact of 
the AD on U.S. operators is estimated to be $16,680, or $120 per 
airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD, 
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 adding the following new 
airworthiness directive:

2002-26-16 Fokker Services B.V.: Amendment 39-13004. Docket 2001-NM-
290-AD.

    Applicability: All Model F.28 Mark 0070 and 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 detect and correct an insufficient over-center force in the 
corresponding thrust reverser operating lever, and incorrect setting 
of the thrust reverser selector switch (S9), which could result in 
uncommanded deployment of the thrust reversers during flight and 
consequent reduced controllability of the airplane, accomplish the 
following:

Over-Center Force Measurement and Readjustment

    (a) Within 6 months after the effective date of this AD, measure 
the over-center force of the left- and right-hand thrust reverser 
operating levers, per paragraph 2.A. of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-76-015, dated January 
15, 2001, including Service Bulletin Change Notification (SBCN) 
SBF100-76-015/01, dated May 1, 2001, and Manual Change 
Notification--Maintenance Document

[[Page 485]]

(MCNM) F100-060, Revision 1, dated March 19, 2001.
    (1) If the over-center force is equal to or higher than 4.5 
pounds, but not higher than 5.5 pounds, no further action is 
required by this paragraph.
    (2) If the over-center force is less than 4.5 pounds or higher 
than 5.5 pounds, before further flight, readjust the over-center 
force and accomplish the corrective actions (including measuring and 
readjusting the minimum stop of the reverse-thrust lever and over-
center force of the thrust reverser), per the service bulletin.

Functional Test and Corrective Actions

    (b) Within 6 months after the effective date of this AD, perform 
a functional test of the secondary lock solenoid of the left- and 
right-hand thrust levers, per paragraph 2.B. of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-76-015, dated January 
15, 2001, including SBCN SBF100-76-015/01, dated May 1, 2001, and 
MCNM F100-060, Revision 1, dated March 19, 2001.
    (1) If the secondary lock solenoid does NOT (momentarily or 
continuously) energize with movement of the thrust levers as 
described in paragraph 2.B.(9) of the service bulletin, no further 
action is required by this paragraph.
    (2) If the secondary lock solenoid (momentarily or continuously) 
energizes with movement of the thrust levers as described in 
paragraph 2.B.(9) of the service bulletin, before further flight, 
perform a rigging check of the thrust reverser switchbox and repeat 
the functional test of the secondary lock solenoid, per paragraph 
2.B.(9) of the service bulletin.
    (i) If the solenoid does NOT (momentarily or continuously) 
energize with movement of the thrust levers as described in 
paragraph 2.B.(9) of the service bulletin, no further action is 
required by this paragraph.
    (ii) If the secondary lock solenoid still (momentarily or 
continuously) energizes with movement of the thrust levers as 
described in paragraph 2.B.(9) of the service bulletin, before 
further flight, replace the thrust reverser switchbox with a new or 
serviceable switchbox, per the service bulletin.

Credit for Accomplishment per Prior Version of Service Information

    (c) Accomplishment, before the effective date of this AD, of the 
actions specified in paragraphs (a) and (b) of this AD in accordance 
with Fokker Service Bulletin SBF100-76-015, dated January 15, 2001, 
including MCNM F100-060, dated January 1, 2001, is acceptable for 
compliance with the requirements of this AD.

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 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

    (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) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Fokker Service Bulletin SBF100-76-015, dated 
January 15, 2001, including Service Bulletin Change Notification 
SBF100-76-015/01, dated May 1, 2001, and Manual Change Notification 
MCNM F100-060, Revision 1, dated March 19, 2001. 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 directive 2001-040, dated March 30, 2001.

Effective Date

    (g) This amendment becomes effective on February 10, 2003.

    Issued in Renton, Washington, on December 26, 2002.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-16 Filed 1-3-03; 8:45 am]
BILLING CODE 4910-13-P

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