[Federal Register Volume 65, Number 33 (Thursday, February 17, 2000)]
[Rules and Regulations]
[Pages 8037-8039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-3625]
[[Page 8037]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-59-AD; Amendment 39-11576; AD 2000-03-17]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and
SA227 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 97-23-
01, which currently requires the following on Fairchild Aircraft, Inc.
(Fairchild Aircraft) SA226 and SA227 series airplanes that are equipped
with a certain Simmonds-Precision pitch trim actuator or a certain
Barber-Colman pitch trim actuator: repetitively measuring the freeplay
of the pitch trim actuator and repetitively inspecting the actuator for
rod slippage; immediately replacing any actuator if certain freeplay
limitations are exceeded or rod slippage is evident; and eventually
replacing the actuator regardless of the inspection results. This AD
retains the actions of AD 97-23-01, and adds these requirements on
airplanes with different design pitch trim actuators installed. This AD
is the result of the manufacturer developing different design pitch
trim actuators and the Federal Aviation Administration (FAA)
determining that these actuators should be subject to the actions of AD
97-23-01. The actions specified by this AD are intended to detect
excessive freeplay or rod slippage in the pitch trim actuator, which,
if not detected and corrected, could result in pitch trim actuator
failure and possible loss of control of the airplane.
DATES: Effective April 10, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 10, 2000.
ADDRESSES: Service information that applies to this AD may be obtained
from Field Support Engineering, Fairchild Aircraft, Inc., P.O. Box
790490, San Antonio, Texas 78279-0490; telephone: (210) 824-9421;
facsimile: (210) 820-8609. This information may also be examined at the
Federal Aviation Administration (FAA), Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 99-CE-59-AD, 901 Locust,
Room 506, Kansas City, Missouri 64106; or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Werner Koch, Aerospace Engineer,
FAA, Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150; telephone: (817) 222-5133; facsimile: (817) 222-5960.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to Fairchild Aircraft
SA226 and SA227 series airplanes that are equipped with a certain
Simmonds-Precision pitch trim actuator or Barber-Colman pitch trim
actuator was published in the Federal Register as a notice of proposed
rulemaking (NPRM) on October 6, 1999 (64 FR 54242). The NPRM proposed
to supersede AD 97-23-01, Amendment 39-10188 (62 FR 59277, November 3,
1997). AD 97-23-01 currently requires the following on Fairchild
Aircraft SA226 and SA227 series airplanes that are equipped with a
certain Simmonds-Precision pitch trim actuator:
--repetitively measuring the freeplay of the pitch trim actuator and
repetitively inspecting the actuator for rod slippage;
--immediately replacing any actuator if certain freeplay limitations
are exceeded or rod slippage is evident; and
--eventually replacing the actuator regardless of the inspection
results.
In addition, AD 98-19-15 R1, Amendment 39-11507 (65 FR 1540,
January 11, 2000), currently requires incorporating the following
information into the applicable Airplane Flight Manual (AFM) on
Fairchild SA226 and SA227 airplanes that are equipped with Barber-
Colman pitch trim actuators, P/N 27-19008-001/-004 or P/N 27-19008-002/
-005 (these pitch trim actuators are affected by AD 97-23-01):
``Limit the maximum indicated airspeed to maneuvering
airspeed (Va) as shown in the appropriate airplane flight manual
(AFM).''
and
``The minimum crew required is two pilots.''
The NPRM proposed to retain the requirements of AD 97-23-01, but
would add these requirements on airplanes with the improved design
pitch trim actuators installed.
The NPRM was the result of the manufacturer developing different
design pitch trim actuators and the Federal Aviation Administration
(FAA) determining that these actuators should be subject to the actions
of AD 97-23-01.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Cost Impact
The FAA estimates that 508 airplanes in the U.S. registry will be
affected by this AD. The only cost impact that this AD imposes upon the
public over that already required by AD 97-23-01 is that incurred
through the addition of the requirements on airplanes with the improved
design pitch trim actuators installed. The costs of this AD on those
airplanes that have these improved design pitch trim actuators
incorporated will be less than that already required by AD 97-23-01 on
airplanes with other pitch trim actuators installed.
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 copy of the final evaluation prepared for this
action is contained in the Rules Docket. A copy of it may be obtained
by contacting the Rules Docket at the location provided under the
caption ADDRESSES.
[[Page 8038]]
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 Airworthiness Directive
(AD) 97-23-01, Amendment 39-10188 (62 FR 5922, November 3, 1997), and
by adding a new AD to read as follows:
2000-03-17 Fairchild Aircraft, Inc.: Amendment 39-11576; Docket No.
99-CE-59-AD, Supersedes AD 97-23-01, Amendment 39-10188; which
superseded AD 93-15-02 R2, Amendment 39-9689; which revised AD 93-
15-02 R1, Amendment 39-9180; which revised AD 93-15-02, Amendment
39-8648.
Applicability: All SA226 and SA227 series airplanes (all models
and serial numbers), 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 in the body of this AD, unless
already accomplished.
To detect excessive freeplay or rod slippage in the pitch trim
actuator, which, if not detected and corrected, could result in
pitch trim actuator failure and possible loss of control of the
airplane, accomplish the following:
Note 2: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1
paragraph they immediately follow.
(a) Accomplish the following at the times specified in the chart
in paragraph (b) of this AD:
(1) Initial and repetitive inspections:
(i) For airplanes equipped with a Simmonds-Precision actuator,
P/N DL5040M5, P/N DL5040M6, or P/N DL5040M8, measure the freeplay
(inspection) of the pitch trim actuator and inspect the actuator for
rod slippage in accordance with the INSTRUCTIONS section of
Fairchild Aircraft SA226 Series Service Letter (SL) 226-SL-005, or
Fairchild Aircraft SA227 Series SL 227-SL-011, both Revised: August
3, 1999; or Fairchild Aircraft SA227 Series Service Letter CC7-SL-
028, Issued: August 12, 1999, as applicable.
(ii) For airplanes equipped with Barber-Colman actuators, P/N
27-19008-00-001, P/N 27-19008-002, P/N 27-19008-00-004, or P/N 27-
19008-005, conduct a functional inspection of the actuator in
accordance with the INSTRUCTIONS section of Fairchild Aircraft SA226
Series SL 226-SL-014, Revised: February 1, 1999, Fairchild Aircraft
SA227 Series SL 227-SL-031, Revised: February 1, 1999, or Fairchild
Aircraft SA227 Series SL CC7-SL-021, Revised: February 1, 1999,
whichever is applicable.
Note 3: The actions in this AD are the same as the actions in AD
97-23-01, except for the actions added to the airplanes equipped
with improved design pitch trim actuators.
(2) Initial and repetitive replacements: Replace the pitch trim
actuator with any of the pitch trim actuators presented in the Chart
in paragraph (b) of this AD, as applicable, at the time specified in
the Repetitive Replacement column of this chart. However, if certain
freeplay limitations that are specified in the service letters are
exceeded or if rod slippage is found, prior to further flight,
replace the pitch trim actuator.
(b) The following chart presents the pitch trim actuator that
could be installed and the initial and repetitive inspection and
replacement compliance times of this AD:
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Condition Initial inspection Repetitive inspection Repetitive replacement
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For all affected airplane models, Upon accumulating 3,000 Every 250 hours TIS Initially upon
except for the Models SA227-CC hours TIS on a Simmonds- after the initial accummulating 5,000
and SA227-DC, with an original Precision P/N DL5040M5 inspection until hours TIS on the
Simmonds-Precision actuator, P/N actuator or within 50 accumulating 5,000 actuator or 500 hours
DL5040M5, installed. hours TIS after April hours TIS on the TIS after the initial
17, 1995 (the effective actuator or 500 hours inspection, whichever
date of AD 93-15-02 R1), TIS after the last occurs later, and
whichever occurs later. inspection required by thereafter as indicated
AD93-15-02 R1. below.
whichever occurs later.
For all affected airplane models, Initially upon Every 300 hours TIS Upon accumulating 6,500
except for the Models SA227-CC accummulating 5,000 after the initial hours TIS on the
and SA227-DC, with a replacement hours TIS on the new inspection until actuator.
Simmonds-Precision actuator, PN/ actuator or within 50 accumulating 6,500
DL5040M5, installed. hours TIS after April hours TIS on the
17, 1995 (the effective actuator.
date of AD 93-15-02 R1),
whichever occurs later.
For all affected airplane models, Initially upon Every 300 hours TIS Upon accumulating 9,900
except for the Models SA227-CC accumulating 7,500 hours after the initial hours TIS on the
and SA227-DC, with a replacement TIS on the new or inspection until actuator.
Simmonds-Precision actuator, P/N modified actuator or accumulating 9,900
DL5040M6, installed. This part within 50 hours TIS hours TIS on the
can be new, modified from a P/N after April 17, 1995 actuator.
DL5040M5 actuator, or overhauled (the effective date of
and zero-timed. AD 93-15-02 R1),
whichever occurs later.
For all affected airplanes Initially upon Every 300 hours TIS Upon accumulating 6,500
models, except for the Models accumulating 5,000 hours after the initial hours TIS on the
SA227-CC and SA227-DC, with a TIS on the overhauled inspection until actuator.
replacement Simmonds-Precision actuator or within 50 accumulating 6,500
actuator, P/N DL5040M5, hours TIS after April hours TIS on the
installed that was overhauled 17, 1995 (the effective actuator.
and zero-timed where both nut date of AD 93-15-02 R1),
assemblies, P/N AA56142, were whichever occurs later.
replaced with new assemblies
during overhaul.
[[Page 8039]]
For all affected airplanes Initially upon Every 250 hours TIS Upon accumulating 5,000
models, except for the Models accumulating 3,000 hours after the initial hours TIS on the
SA227-CC and SA227-DC, with a TIS on the overhauled inspection until actuator.
replacement P/N DL5040M5 actuator or within 50 accumulating 5,000
actuator installed that was hours TIS after April hours TIS on the
overhauled and zero-timed where 17, 1995 (the effective actuator.
both nut assemblies, P/N date of AD 93-15-02 R1),
AA56142, were not replaced with whichever occurs later.
new assemblies during overhaul.
For all affected airplanes models Upon accumulating 500 Every 300 hours TIS None.
with a newly fabricated or hours total TIS on the after the initial
overhauled and zero-timed Barber- newly fabricated or inspection.
Colman actuator, P/N 27-19008- overhauled and zero-
001-004 or P/N 27-19008-002-005. timed actuator or within
50 hours TIS after the
effective date of AD 97-
23-01, whichever occurs
later.
For the Models SA227-CC and SA227- None..................... None.................... Upon accumulating 1,500
DC only, with a Simmonds- hours TIS on the
Precision pitch trim actuator, P/ actuator.
N DL5040M5 or P/NDL5040M6,
installed.
For all affected airplanes with a Must be overhauled upon Must be overhauled at No replacement
Barber-Colman P/N 27-19008-006 the accumulation of intervals not to exceed requirements.
or 27-19008-007 actuator 2,000 hours TIS on the 2,000 hours EIS.
installed. actuator.
For all affected airplanes with a Upon accumulating 7,500 Every 600 hours TIS Upon accumulating 9,900
Simmonds-Precision pitch trim hours TIS on the after the initial hours TIS on the
actuator, PN DL5040M8, installed. actuator of within the inspection until actuator.
next 50 hours TIS after accumulating, 9,900
the effective date of hours TIS.
this AD, whichever
occurs later.
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(c) Special flight permits may be issued in accordance with
Secs. 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.
(d) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Airplane
Certification Office (ACO), FAA, 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150.
(1) The request shall be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Fort Worth Airplane Certification Office.
(2) Alternative methods of compliance that were approved in
accordance with AD 97-23-01 are considered to be approved as
alternative methods of compliance with this AD.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth Airplane Certification Office.
(e)(1) The inspections required by this AD shall be done in
accordance with the following:
(i) Fairchild Aircraft SA226 Series SL 226-SL-005, Revised:
August 3, 1999; or
(ii) Fairchild Aircraft SA227 Series SL 227-SL-011; Revised:
August 3, 1999; or
(iii) Fairchild Aircraft SA227 Series SL CC7-SL-028, Issued:
August 12, 1999; and
(iv) Fairchild Aircraft SA 226 Series SL 226-SL-014, Revised:
February 1, 1999; or
(v) Fairchild Aircraft SA 227 Series SL 227-SL-031, Revised:
February 1, 1999; or
(vi) Fairchild Aircraft SA 227 Series SL CC7-SL-021, Revised:
February 1, 1999.
(2) 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 Field Support Engineering,
Fairchild Aircraft Inc., P.O. Box 790490, San Antonio, Texas 78279-
0490. Copies may be inspected at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 301, Kansas City, Missouri,
or at the Office of the Federal Register, 800 North Capitol Street,
NW, suite 700, Washington, DC.
(f) This amendment supersedes 97-23-01, Amendment 39-10188;
which superseded AD 93-15-02 R2, Amendment 39-9689; which revised AD
93-15-02 R1, Amendment 39-9180; which revised AD 93-15-02, Amendment
39-8648.
(g) This amendment becomes effective on April 10, 2000.
Issued in Kansas City, Missouri, on February 9, 2000.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-3625 Filed 2-16-00; 8:45 am]
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