[Federal Register: January 6, 2003 (Volume 68, Number 3)]
[Rules and Regulations]
[Page 483-485]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06ja03-10]
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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]
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