[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Proposed Rules]
[Pages 54242-54245]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26090]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-59-AD]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and
SA227 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede 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 Barbar-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. The proposed AD would retain the actions of AD 97-23-01, but
would add these requirements on airplanes with different design pitch
trim actuators installed. The proposed 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 the proposed 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: Comments must be received on or before December 6, 1999.
ADDRESSES: Submit comments in triplicate to the FAA, Central Region,
Office of the Regional Counsel, Attention: Rules Docket No. 99-CE-59-
AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
Comments may be inspected at this location between 8 a.m. and 4 p.m.,
Monday through Friday, holidays excepted.
Service information that applies to the proposed 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 also may be examined at the
Rules Docket at the address above.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 proposal will be filed in the Rules Docket.
[[Page 54243]]
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 99-CE-59-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 99-CE-59-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
AD 97-23-01, Amendment 39-10188 (62 FR 5922, November 3, 1997),
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.
The actions specified by AD 97-23-01 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.
In addition, AD 98-19-15, Amendment 39-10794 (63 FR 50983,
September 24, 1998), 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.''
Actions Since Issuance of AD 97-23-01
At the time the FAA issued AD 98-19-15, there was a design
alternative to the Barber-Colman pitch trim actuators for all of the
affected airplanes, except for the Models SA227-CC and SA227-DC
airplanes. Since that time, a design alternative for all affected
airplanes has been developed. These design alternatives are:
--Barber-Colman P/N 27-19008-006 or P/N 27-19008-007 pitch trim
actuators. Procedures to install these pitch trim actuators are
contained in Fairchild Service Bulletin 226-27-064, Fairchild Service
Bulletin 227-27-046, and Fairchild Service Bulletin CC7-27-015. All
airplane models are eligible for this installation and airplane models
vary by service bulletin;
--Simmonds-Precision P/N DL5040M5 or P/N DL5040M6 pitch trim
actuators. All airplane models are eligible for this installation.
Procedures to install these pitch trim actuators for the Models SA227-
CC and SA227-DC airplanes are contained in Fairchild Service Bulletin
CC7-27-014, and are contained in engineering data for all other models
(contact Fairchild); and
--Simmonds-Precision P/N DL5040M8 pitch trim actuators. Procedures
to install these pitch trim actuators are contained in Fairchild
Service Bulletin 227-27-045, Fairchild Service Bulletin 226-27-063, and
Fairchild Service Bulletin CC7-23-013. All airplane models are eligible
for this installation and airplane models vary by service bulletin.
These pitch trim actuators, when installed, would eliminate the
need for the requirements of AD 98-19-15.
However, there currently are no AD requirements that mandate
repetitive inspections and/or replacements or overhauls of these pitch
trim actuators similar to the pitch trim actuators affected by AD 97-
23-01. The FAA evaluated the design of these improved pitch trim
actuators and has determined that (1) a similar condition to that
specified in AD 97-23-01 exists for airplanes with these actuators
installed; and (2) the actuators should have inspections and/or
replacements or overhauls as follows:
--Barber-Colman P/N 27-19008-006 or P/N 27-19008-007 pitch trim
actuators: Overhaul at intervals not to exceed 2,000 hours time-in-
service (TIS);
--Simmonds-Precision P/N DL5040M5 or P/N DL5040M6 pitch trim
actuators: Replacement at intervals not to exceed 1,500 hours TIS; and
--Simmonds-Precision P/N DL5040M8 pitch trim actuators: Initial
inspection at 7,500 hours TIS after installation and thereafter at
intervals not to exceed 600 hours TIS. Repetitive replacement at
intervals not to exceed 9,900 hours TIS.
Relevant Service Information
Fairchild has revised SA226 Series Service Letter (SL) 226-SL-005
and Fairchild Aircraft SA227 Series SL 227-SL-011, both Revised: August
3, 1999; and issued SA227 Series SL CC7-SL-028, Issued: August 12,
1999, to also include the inspection procedures on the P/N DL5040M8
pitch trim actuators.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that:
--The improved design pitch trim actuators referenced above should
also have repetitive inspection and/or overhaul or replacement
requirements; and
--AD action should be taken 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.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild Aircraft SA226 and SA227 series
airplanes of the same type design that are equipped with a certain
Simmonds-Precision pitch trim actuator, the FAA is proposing an AD to
supersede AD 97-23-01. The proposed AD would retain the actions of AD
97-23-01, but would add these requirements on airplanes with the
improved design pitch trim actuators installed.
Cost Impact
The FAA estimates that 508 airplanes in the U.S. registry would be
affected by the proposed AD. The only cost impact that the proposed AD
imposes upon the public over that already required by AD 97-23-01 is
that incurred through the addition of the proposed requirements on
airplanes with the improved design pitch trim actuators installed. The
costs of the proposed AD on those airplanes that have these improved
design pitch trim actuators incorporated would be less than that
already required by AD 97-23-01 on airplanes with other pitch trim
actuators installed.
Regulatory Impact
The regulations proposed herein would 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
[[Page 54244]]
12612, it is determined that this proposal would 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) if promulgated,
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 draft regulatory evaluation
prepared for this action has been placed in the Rules Docket. A copy of
it may be obtained by contacting the Rules Docket at the location
provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations 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:
Fairchild Aircraft, Inc.: 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 SL
226-SL-014, 227-SL-031, or CC7-SL-021, Issued: October 3, 1997,
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 and hours TIS on a after the initial accumulating 5,000
SA227-DC, with an original Simmonds- Simmonds-Precision P/N inspection until hours TIS on the
Precision actuator, P/N DL5040M5, DL5040M5 actuator or accumulating 5,000 actuator or 500 hours
installed. within 50 hours TIS hours TIS on the TIS after the initial
after April 17, 1995 actuator or 500 hours inspection, whichever
(the effective date of TIS after the last occurs later, and
AD 93-15-02 R1), inspection required by thereafter as
whichever occurs later. AD 93-15-02 R1, indicated 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 and accumulating 5,000 after the initial hours TIS on the
SA227-DC, with a replacement hours TIS on the new inspection until actuator.
Simmonds-Precision actuator, P/N actuator or within 50 accumulating 6,500
DL5040M5, installed. hours TIS after April hours TIS on the
17, 1995 (the actuator.
effective 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 and accumulating 7,500 after the initial hours TIS on the
SA227-DC, with a replacement hours TIS on the new inspection until actuator.
Simmonds-Precision actuator, P/N or modified actuator accumulating 9,900
DL5040M6, installed. This part can or within 50 hours TIS hours TIS on the
be new, modified from a P/N DL5040M5 after April 17, 1995 actuator.
actuator, or overhauled or (the effective date of
overhauled and zero-timed. AD 93-15-02 R1),
whichever occurs later.
[[Page 54245]]
For all affected airplane models, Initially upon Every 300 hours TIS Upon accumulating 6,500
except for the Models SA227-CC and accumulating 5,000 after the initial hours TIS on the
SA227-DC, with a replacement hours TIS on the over- inspection until actuator.
Simmonds-Precision actuator, P/N hauled actuator or accumulating 6,500
DL5040M5, installed that was within 50 hours TIS hours TIS on the
overhauled and zero-timed where both after April 17, 1995 actuator.
nut assemblies, P/N AA56142, were (the effective date of
replaced with new assemblies during AD 93-15-02 R1),
overhaul. whichever occurs later.
For all affected airplane models, Initially upon Every 250 hours TIS Upon accumulating 5,000
except for the Models SA227-CC and accumulating 3,000 after the initial hours TIS on the
SA227-DC, with a replacement P/N hours TIS on the over- inspection until actuator.
DL5040M5 actuator installed that was hauled actuator or accumulating 5,000
overhauled and zero-timed where both within 50 hours TIS hours TIS on the
nut assemblies, P/N AA56142, were after April 17, 1995 actuator.
not replaced with new assemblies (the effective date of
during overhaul. AD 93-15-02 R1),
whichever occurs later.
For all affected airplanes models Upon accumulating 500 Every 300 hours TIS None.
with a Barber-Colman pitch trim hours total TIS on the after the initial
actuator installed, P/N 27-19008-001/ new or overhauled zero- inspection.
004 or 27-19008-002/-005, that is timed pitch trim
currently in-service with less than actuator or within 50
1,000 hours TIS since new or hours TIS after the
overhauled and zero-timed. effective date of this
AD, whichever occurs
later.
For all affected airplane models with Upon accumulating 500 Every 300 hours TIS None.
a newly fabricated and over-hauled hours total TIS on the after the initial
and zero-timed Barber-Colman actuator or within 50 inspection.
actuator, P/N 27-19008-001/-004 or P/ hours TIS after the
N 27-19008-02-005. effective date of this
AD, whichever occurs
later.
For the Models SA227-CC and SA227-DC None................... None................... Upon accumulating 1,500
only, with a Simmonds-Precision hours TIS on the
pitch trim actuator, P/N DL5040M5 or actuator.
P/N DL5040M6, installed.
For all affected airplanes with a Must be overhauled upon Must be overhauled at No replacement
Barber-Colman P/N 27-19008-006 or 27- the accumulation of intervals not to requirements.
19008-007 actuator installed. 2,000 hours TIS on the exceed 2,000 hours TIS.
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, P/N DL5040M8, installed. actuator or within the inspection until actuator.
next 50 hours TIS accumulating 9,900
after the effective hours TIS.
date of this AD,
whichever occurs later.
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(c) 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.
(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) Service information related to this AD 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, Room 1558, 601 E.
12th Street, Kansas City, Missouri.
(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.
Issued in Kansas City, Missouri, on September 30, 1999.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 99-26090 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-U