[Federal Register Volume 62, Number 212 (Monday, November 3, 1997)]
[Rules and Regulations]
[Pages 59277-59280]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-28880]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-90-AD; Amendment 39-10188; AD 97-23-01]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and
SA227 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 93-15-
02 R2, 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:
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 action retains the
repetitive inspections and replacement requirements, adds the
repetitive inspections after the installation of certain Barber-Coleman
pitch time actuators, and removes the terminating action. This action
is the result of failure of the no-backs on a Barber-Colman pitch time
actuator installed on a Fairchild Aircraft SA227 series airplane. The
actions specified by this AD are intended to prevent failure of the
pitch trim actuator, which could cause loss of control of the airplane.
DATES: Effective December 1, 1997.
The incorporation by reference of Fairchild Aircraft SA226 Series
Service Letter 226-SL-014, Fairchild Aircraft SA227 Series Service
Letter 227-SL-031, and Fairchild Aircraft SA227 Series Service Letter
CC7-SL-021, all Issued: October 3, 1997, is approved by the Director of
the Federal Register as of December 1, 1997.
The incorporation by reference of 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,
listed in the regulations was previously approved by the Director of
the Federal Register as of July 25, 1996 (61 FR 36817, July 15, 1996).
Comments for inclusion in the Rules Docket must be receive on or
before January 2, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket 97-CE-90-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
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 FAA,
Central Region, Office of the Regional Counsel, Attention: Rules Docket
97-CE-90-AD, Room 1558, 601 E. 12th Street, 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:
Discussion
Airworthiness Directive (AD) 93-15-02 R2, Amendment 39-9689 (61 FR
36817, July 25, 1996), 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.
Accomplishment of the inspections required by AD 93-15-02 R2 is in
accordance with Fairchild Aircraft SA226 Series Service Letter (SL)
226-SL-005, or Fairchild Aircraft SA227 Series SL 227-SL-011, both
Issued: April 8, 1993, Revised: May 22, 1996.
In addition, AD 93-15-02 R2, Amendment 39-9689 (61 FR 36817, July
15, 1996), eliminates the initial inspection and the repetitive
inspection if a Barber-Colman actuator (part number (P/N) 27-19008-001
or -002 is installed.
Actions Since Issuance of the Previous Rule
Since issuance of AD 93-15-02 R2, the FAA received an incident
report of a failure of a pitch trim actuator installed on a Fairchild
SA227 series airplane during a landing approach. The failure was
specifically of the no-backs
[[Page 59278]]
on a Barber-Colman pitch trim actuator (P/N 27-19008-002), which caused
the horizontal stabilizer to go full leading edge down, resulting in a
violent pitch-up of the airplane. According to the report, both pilots
had to use extreme force on the control column to recover from the
pitch-up and get the airplane safely on the ground.
Because of this incident, Fairchild re-examined the possible fail
rate of these pitch trim actuators. This examination shows that the no-
backs in the Barber-Coleman pitch trim actuators installed on the
Fairchild SA226 and SA227 series airplanes are subject to failure after
accumulating a certain amount of hours time-in-service (TIS). As a
result, Fairchild now recommends repetitive inspections of the Barber-
Colman pitch trim actuators (P/N 27-19008-001/-002).
Relevant Service Information
Fairchild has issued SA226 Series Service Letter (SL) 226-SL-014,
Fairchild Aircraft SA227 Series SL 227-SL-031, and Fairchild Aircraft
SA227 Series SL CC7-SL-021, all Issued: October 3, 1997, which specify
procedures for inspecting and testing all Fairchild SA226 and SA227
series airplanes equipped with a Barber-Colman pitch trim actuator P/N
27-19008-001 or -002.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, including the
referenced service information, the FAA has determined that AD action
should be taken in order to prevent failure of the pitch trim actuator,
which could cause loss of control of the airplane.
Explanation of the Provisions of This AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild SA226 and SA227 series airplanes of
the same type design, the FAA is issuing this AD to supersede AD 93-15-
02 R2. This AD retains the inspection requirements for airplanes
equipped with the Simmonds-Precision pitch trim actuators, and changes
the inspection requirements for airplanes equipped with Barber-Colman
pitch trim actuators to require repetitively inspecting the actuator.
This action eliminates the terminating action in AD 93-15-02 R2.
Inspecting the Barber-Colman actuator (P/N 27-19008-001 or -002) is
required in accordance with the instructions in Fairchild SL 226-SL-
014, SL 227-SL-031, or CC7-SL-021, all Issued: October 3, 1997,
whichever is applicable. Inspecting the Simmonds-Precision actuators
will continue to be accomplished in accordance with Fairchild Aircraft
SA226 Series SL 226-SL-005, or Fairchild Aircraft SA227 Series SL 227-
SL-011, both Issued: April 8, 1993, Revised: May 22, 1996.
Determination of the Effective Date of the AD
Since a situation exists (failure of the pitch-trim actuators) that
requires the immediate adoption of this regulation, it is found that
notice and opportunity for public prior comment hereon are
impracticable, and that good cause exists for making this amendment
effective in less than 30 days.
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 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.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 97-CE-90-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket (otherwise, an evaluation is
not required). A copy of it, if filed, may be obtained from the Rules
Docket.
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 AD 93-15-02 R2, Amendment
39-9689 (61 FR 36817, July 15, 1996), and by adding a new airworthiness
directive (AD) to read as follows:
97-23-01 Fairchild Aircraft, Inc.: Amendment 39-10188; Docket No.
97-CE-90-AD. Supersedes AD 93-15-01 R2, Amendment 39-9689.
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) or a Barber-Colman pitch trim actuator (P/
N 27-19008-001 or P/N 27-19008-002).
Note 1: This AD applies to each airplane identified in the
preceding applicability
[[Page 59279]]
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 cause
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 and P/N DL5040M6, 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 Issued: April 8, 1993, Revised: May 22,
1996, as applicable.
(ii) For airplanes equipped with Barber-Colman actuators, P/N
27-19008-001 or P/N 27-19008-002, 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, whichever is applicable.
Note 3: the actions in this AD are the same as the actions in AD
93-15-02 R2, except for the repetitive inspections added to the
Barber-Colman actuator, P/N 27-19008-001 or P/N 27-19008-002.
(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 time
specified in the Repetitive Replacement column of the chart in
paragraph (b) of this AD. However, if certain freeplay limitations
that are specified in the service letters are exceeded or if rod
slippage is found, replace the pitch trim actuator prior to further
flight.
(i) A new Simmonds-Precision actuator, P/N DL5040M5 or P/N
DL5040M6.
(ii) A pitch trim actuator with an overhauled, zero-timed part
of the same design and part number.
(iii) A Barber-Colman actuator, P/N 27-19008-001 or P/N 27-
19008-002.
(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, or within 50 accumulating 6,500
hours TIS after April hours TIS on the
17, 1995 (the actuator.
effective date of AD
93-15-02 R1),
whichever occurs later.
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. or within 50 hours TIS hours TIS on the
after April 17, 1995 actuator.
(the effective date of
AD 93-15-02 R1),
whichever occurs later.
With a replacement P/N DL5040M5 Initially 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 over- inspection until actuator.
nut assemblies, P/N AA56142, were hauled actuator, or accumulating 6,500
replaced with new assemblies during within 50 hours TIS hours TIS on the
overhaul. after April 17, 1995 actuator.
(the effective date of
AD 93-15-02 R1),
whichever occurs later.
With a replacement P/N DL5040M5 Initially 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 over- inspection until actuator.
nut assemblies, P/N AA56142, were hauled actuator, or accumulating 5,000
not replaced with new assemblies within 50 hours TIS hours TIS on the
during overhaul. after April 17, 1995 actuator.
(the effective date of
AD 93-15-02 R1),
whichever occurs later.
With a Barber-Colman pitch trim Upon accumulating 500 Every 300 hours TIS None.
actuator installed, P/N 27-19008-001 hours total TIS on the after the initial
or 27-19008-002, currently in- new or overhauled zero- inspection.
service with less than 1,000 hours timed pitch trim
TIS since new or overhauled, zero- actuator, or within 50
timed. hours TIS after the
effective date of this
AD, whichever occurs
later.
For newly fabricated and over-hauled, Upon accumulating 500 Every 300 hours TIS None.
zero-timed Barber-Colman actuator, P/ hours total TIS on the after the initial
N 27-19008-001 or P/N 27-19008-002 actuator, or within 50 inspection.
actuators. hours TIS after the
effective date of this
AD, whichever occurs
later.
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[[Page 59280]]
(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 Airplane Certification Office.
Alternative methods of compliance, approved in accordance with AD
93-15-02-R2, are not 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 Forth Worth Airplane Certification Office.
(e) The inspections required by this AD for Fairchild SA226 and
SA227 series airplanes equipped with Barber-Colman pitch trim
actuators shall be done in accordance with Fairchild Aircraft SA226
Series Service Letter 226-SL-014, Fairchild Aircraft SA227 Series
Service Letter 227-SL-031, or Fairchild Aircraft SA227 Series
Service Letter CC7-SL-021, all Issued: October 3, 1997, whichever is
applicable. This incorporation by reference is approved by the
Director of the Federal Register is accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. The inspections required by this AD on Fairchild
Aircraft SA226 and SA227 series airplanes equipped with Simmonds-
Precision pitch trim actuators shall be done in accordance with
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. This incorporation by reference was
previously approved by the Director of the Federal Register as of
July 25, 1996 (61 FR 36817, July 15, 1996). Copies of all of the
documents 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, or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment (39-10188) supersedes AD 93-15-02 R2,
Amendment 39-9689.
(g) This amendment (39-10188) becomes effective on December 1,
1997.
Issued in Kansas City, Missouri, on October 27, 1997.
Mary Ellen A. Schutt,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-28880 Filed 10-31-97; 8:45 am]
BILLING CODE 4910-13-M
