[Federal Register Volume 61, Number 136 (Monday, July 15, 1996)]
[Rules and Regulations]
[Pages 36817-36820]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-17483]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-35-AD; Amendment 39-9689; AD 93-15-02 R2]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment revises Airworthiness Directive (AD) 93-15-02
R1, which 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
compliance times for the first inspection of an actuator that is
installed in accordance with AD 93-15-02 R1 was inadvertently
referenced incorrectly. This action retains the repetitive inspection
and replacement requirements of the current AD, corrects the above-
referenced compliance times, and adds an additional replacement
actuator option that will then require repetitive inspections and
replacements of that actuator. The actions specified by this AD are
intended to prevent the horizontal stabilizer from going nose-down or
jamming because of pitch trim actuator failure, which could result in
loss of control of the airplane.
DATES: Effective July 25, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director
[[Page 36818]]
of the Federal Register as of July 25, 1996.
Comments for inclusion in the Rules Docket must be received on or
before August 30, 1996.
ADDRESSES: Service information that applies to this AD may be obtained
from Field Support Engineering, Fairchild Aircraft, 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 FAA, Room
1558, 601 E. 12th Street, Kansas City, Missouri 64106.
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 This Action
On July 20, 1993, the FAA issued AD 93-15-02, Amendment 39-8648 (59
FR 40734, July 30, 1993), to require the following on Fairchild
Aircraft SA226 and SA227 series airplanes that are equipped with a
Simmonds-Precision pitch trim actuator, part number (P/N) DL5040M5:
--repetitively measuring the freeplay of the pitch trim actuator and
repetitively inspecting the actuator for rod slippage; and,
--if certain freeplay limitations are exceeded or rod slippage is
evident, replacing any actuator with a new actuator of the same part
number or with a part of improved design, P/N 27-19008-001 or P/N 27-
19008-002.
The requirements of the AD will no longer apply when an actuator of
improved design, P/N 27-19008-001 or P/N 27-19008-002, is installed. AD
93-15-02 specified accomplishment of the freeplay measurements and
inspections in accordance with the instructions in Fairchild Aircraft
SA226 Series Service Letter (SL) 226-SL-005, and Fairchild Aircraft
SA227 Series SL 227-SL-011, both Issued: April 8, 1993, Revised: April
28, 1993, as applicable; and specified accomplishment of the pitch trim
actuator replacement in accordance with the applicable maintenance
manual.
AD 93-15-02 was issued based on reports of two in-flight incidents
where the above-referenced pitch trim actuator failed on Fairchild
Aircraft SA226 and SA227 series airplanes. In one case, the horizontal
stabilizer went full-nose down, and in the other instance, the
horizontal stabilizer jammed. Fortunately, the pilots were able to
safely land in both of these instances. Upon removal and inspection of
each of these pitch trim actuators, fatigued barrel nuts were found and
the actuator usage time was well over 5,000 hours time-in-service
(TIS).
After AD 93-15-02 became effective, the FAA received a report of an
in-flight incident where the referenced actuator on one of the affected
airplanes failed. The airplane operator had accomplished the 5,000-hour
TIS initial inspection (with satisfactory results), but had not reached
the 6,500-hour TIS mandatory replacement threshold.
This prompted the FAA to revise AD 93-15-02 (to the R1 level,
Amendment 39-9180, 60 FR 15667, March 27, 1995) to require the same
repetitive inspections and actuator replacement as AD 93-15-02, but
changes the compliance times by (1) reducing the number of hours time-
in-service (TIS) before the initial inspection is required; and (2)
shortening both the time period between repetitive inspections and the
actuator replacement compliance time, unless the replacement actuator
is new or if the tube nut assemblies have been replaced during
overhaul. Fairchild Aircraft revised the applicable service bulletins
to reflect the inspection time changes. Accomplishment of the
inspections required by AD 93-15-02 R1 is in accordance with the
instructions in Fairchild Aircraft SA226 Series Service Letter (SL)
226-SL-005, and Fairchild Aircraft SA227 Series SL 227-SL-011, both
Issued: April 8, 1993, Revised: March 2, 1995, as applicable.
AD 93-15-02 R1 inadvertently referenced incorrect compliance times
for the first inspection for an actuator that is installed in
accordance with AD 93-15-02 R1. That AD specifies repetitively
inspecting the actuator at either 250 or 300-hour TIS intervals after
replacing the actuator. The intent was to initially inspect upon
accumulating 3,000, 5,000, or 7,500 hours TIS (depending on the type of
actuator replacement) after installing the actuator, and repetitively
inspecting every 250 or 300 hours TIS thereafter.
In addition, the FAA has become aware of an additional replacement
actuator that should be incorporated into the existing AD. This
replacement actuator is a modified P/N DL5040M5 actuator that is re-
identified as P/N DL5040M6. Installation of this actuator would then
require repetitive inspections and replacements.
After examining all available information related to the subject
discussed above, the FAA has determined that further AD action should
be taken to correct these compliance times of AD 93-15-02 R1 and to
prevent the horizontal stabilizer from going nose-down or jamming
because of pitch trim actuator failure, which could result in loss of
control of the airplane.
Fairchild Aircraft has revised (dated May 22, 1996) SA226 Series SL
226-SL-005 and SA227 Series 227-SL-011, to reflect the information
discussed above.
Explanation of the Provisions of the 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 Simmonds-
Precision pitch trim actuator, P/N DL5040M5 or P/N DL5040M6, this AD
requires the same repetitive inspections and actuator replacement as AD
93-15-02 R1, but revises the initial inspection compliance times after
installing the actuator as previously specified. This action
incorporates Simmonds-Precision pitch trim actuator, P/N DL5040M6, as a
replacement option that will then require repetitive inspections and
replacements. The P/N DL5040M6 actuator can consist of a new part or a
modified DL5040M5 actuator, both of which can be obtained from
Simmonds-Precision.
This action revises a previous action to correct an error in a
final rule by changing the compliance time for the initial inspection
after installing the actuator, and incorporates the additional
replacement option. This change in the compliance time reduces the
burden upon the public. The replacement option imposes the same burden
that is currently required. Since this action does not impose any
additional burden (financial or otherwise) upon the public than is
already required by AD 93-15-02 R1 or than was previously required by
AD 93-15-02, it is found that notice and prior public comment hereon
are unnecessary.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting immediate flight safety and, thus, was not
preceded by notice and opportunity to comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 will be considered,
and this rule may be amended in light of the comments received. Factual
information that supports the commenter's ideas and
[[Page 36819]]
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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
AD will be filed in the Rules Docket.
Regulatory Impact
The regulations adopted herein will 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 12612, it is determined that this final
rule does 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, 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 39-9180 (60 FR
15667, March 27, 1995), and by adding a new airworthiness directive to
read as follows:
93-15-02 R2 Fairchild Aircraft: Amendment 39-9689; Docket No. 93-CE-
35-AD. Revises AD 93-15-02 R1, Amendment 39-9180.
Applicability: All SA226 and SA227 series airplanes (all models
and serial numbers), certificated in any category, that are equipped
with a Simmonds-Precision pitch trim actuator, part number (P/N)
DL5040M5 or P/N DL5040M6.
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 prevent failure of the pitch trim actuator, which could
result in the horizontal stabilizer going nose-down or jamming,
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: 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, and
Fairchild Aircraft SA227 Series SL 227-SL-011, both Issued: April 8,
1993, Revised: May 22, 1996, as applicable.
(2) Initial and repetitive replacements: Replace the pitch trim
actuator with one of the following in accordance with the
instructions in the applicable maintenance manual at the times
specified in the Initial Inspection and Repetititive Inspection
columns of the chart in paragraph (b) of this AD and, replace the
pitch trim actuator prior to further flight if certain freeplay
limitations that are specified in the service letters are exceeded
or if rod slippage is found.
(i) A new Simmonds-Precision actuator, P/N DL5040M5 or DL5040M6.
(ii) A pitch trim actuator with an overhauled, zero-timed part
of the same design and part number.
(iii) A new actuator of improved design, P/N 27- 19008-001 or
27-19008-002. This replacement eliminates the repetitive inspection
and replacement requirements of this AD, and may be accomplished at
any time to eliminate the inspection requirement of this AD.
(b) The following chart presents 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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With an original Simmonds-Precision Upon accumulating 3,000 Every 250 hours TIS Initially upon
actuator, P/N DL5040M5, installed. hours TIS on a after initial accumulating 5,000
Simmonds-Precision P/N inspection until hours TIS on the
DL5040M5 actuator or accumulating 5,000 actuator or 500 hours
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.
With a replacement Simmonds-Precision Initially upon Every 300 hours TIS Upon accumulating 6,500
actuator, P/N DL5040M5, installed. accumulating 5,000 after the initial hours TIS on the
hours TIS on the new inspection until actuator.
actuator. accumulating 6,500
hours TIS on the
actuator.
With a replacement Simmonds-Precision Initially upon Every 300 hours TIS Upon accumulating 9,900
actuator, P/N DL5040M6, installed. accumulating 7,500 after the initial hours TIS on the
This part can be new, modified from hours TIS on the new inspection until actuator.
a P/N DL5040M5 actuator or or modified actuator. accumulating 9,900
overhauled and zero-timed. hours TIS on the
actuator..
[[Page 36820]]
With a replacement P/N DL5040M5 Initally upon Every 300 hours TIS Upon accumulating 6,500
actuator installed that was accumulating 5,000 after the initial hours TIS on the
overhauled and zero-timed where both hours TIS on the inspection until actuator.
nut assemblies, P/N AA56142, were overhauled actuator. accumulating 6,500
replaced with new assemblies during hours TIS on the
overhaul. actuator.
With a replacement P/N DL5040M5 Initally upon Every 250 hours TIS Upon accumulating 5,000
actuator installed that was accumulating 3,000 after the initial hours TIS on the
overhauled and zero-timed where both hours TIS on the inspection until actuator.
nut assemblies, P/N AA56142, were overhauled actuator. accumulating 5,000
not replaced with new assemblies hours TIS on the
during overhaul. actuator.
With a pitch trim actuator of No action necessary.... No action necessary.... No action necessary.
improved design installed, P/N 27-
19008-001 or 27-19008-002.
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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. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Fort Worth ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth ACO.
(e) The inspections and modification required by this AD shall
be done in accordance with Fairchild Aircraft SA226 Series Service
Letter 226-SL-005, and Fairchild Aircraft SA227 Series Service
Letter 227-SL-011, both Issued: April 8, 1993, Revised: May 22,
1996, as applicable. This incorporation by reference is 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, P.O. Box 790490, San Antonio, Texas
78279-0490. Copies may be inspected at the FAA, Central Region,
Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th
Street, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment (39-9689) revises AD 93-15-02 R1, Amendment
39-9180.
(g) This amendment (39-9689) becomes effective on July 25, 1996.
Issued in Kansas City, Missouri, on June 25, 1996.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-17483 Filed 7-12-96; 8:45 am]
BILLING CODE 4910-13-U
