[Federal Register Volume 64, Number 184 (Thursday, September 23, 1999)]
[Proposed Rules]
[Pages 51479-51481]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-24767]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-84-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 revise Airworthiness Directive (AD)
98-19-15, which currently requires incorporating information into the
Limitations Section of the airplane flight manual (AFM) that imposes a
speed restriction and a minimum pilot requirement for Fairchild
Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped
with Barber-Colman pitch trim actuators, part number (P/N) 27-19008-
001/-004 or P/N 27-19008-002/-005. Since AD 98-19-15 became effective,
improved design pitch trim actuators have been developed that, when
installed, would eliminate the speed restriction and minimum pilot
requirements of the current AD. The proposed AD would incorporate these
installations as a method of complying with the current AD. The actions
specified by the proposed AD are intended to lessen the possibility of
airplane pitch up caused by mechanical failure of the pitch trim
actuator, which could result in a pitch upset and structural failure of
the airplane.
DATES: Comments must be received on or before November 24, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-84-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 Fairchild Aircraft, Inc., P.O. Box 790490, San Antonio, Texas
78279-0490; telephone: (800) 577-7273; facsimile: (210) 824-3869. This
information also may be examined at the Rules Docket at the address
above.
FOR FURTHER INFORMATION CONTACT: Mr. Werner G. Koch, Aerospace
Engineer, FAA, Aircraft 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.
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. 98-CE-84-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. 98-CE-84-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
AD 98-19-15, Amendment 39-10794 (63 FR 50983, September 24, 1998),
currently requires incorporating the following information into the
applicable 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:
``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 following service information describes the AFM requirements:
--Fairchild Service Letter 226-SL-017, FAA Approved: August 26, 1998;
Revised: September 2, 1998;
--Fairchild Service Letter 227-SL-033, FAA Approved: August 26, 1998;
--Revised: September 2, 1998; and
--Fairchild Service Letter CC7-SL-023, FAA Approved: August 26, 1998;
Revised: September 2, 1998.
AD 98-19-15 was the result of reports of two incidents of abrupt
movement of the horizontal stabilizer to or near to the full airplane
nose-up position. These two incidents involved mechanical failure of
these Barber-Colman pitch trim actuators.
The actions specified in AD 98-19-15 are intended to lessen the
possibility of airplane pitch up caused by mechanical failure of the
pitch trim actuator, which could result in a pitch upset and structural
failure of the airplane.
Actions Since Issuance of Previous Rule
At the time the FAA issued AD 98-19-15, there was a design
alternative to
[[Page 51480]]
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 CC7-27-013. 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.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to this subject, including the above-referenced
service information, the FAA has determined that:
--Accomplishing one of the installations referenced above should be
considered as an alternative method of compliance with AD 98-19-15; and
--AD action should be taken to incorporate these options into the
current AD and to lessen the possibility of airplane pitch up caused by
mechanical failure of the pitch trim actuator, which could result in a
pitch upset and structural failure 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 SA226 and SA227 airplanes of the
same type design that have one of the affected pitch trim actuators
installed, the FAA is proposing AD action to revise AD 98-19-15. The
proposed AD would retain the requirements of the existing AD, and would
provide the option of incorporating one of the replacements
(installations) referenced earlier in this document as a method of
accomplishing the AD.
Cost Impact
The FAA estimates that 508 airplanes in the U.S. registry could
have the affected pitch trim actuators installed and, therefore, could
be affected by the AFM requirements of the proposed AD. Since an owner/
operator who holds at least a private pilot's certificate as authorized
by sections 43.7 and 43.9 of the Federal Aviation Regulations (14 CFR
43.7 and 43.9) may accomplish the proposed AFM insertions, the only
cost impact upon the public would be the approximately 30 minutes it
would take each owner/operator to incorporate the information into the
AFM.
The FAA has no way of determining the number of airplanes that have
the design alternative pitch trim actuators installed, and would
therefore not be affected by the proposed AD.
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 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
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) 98-19-15, Amendment 39-10794, and adding a new AD to read as
follows:
Fairchild Aircraft, Inc.: Docket No. 98-CE-84-AD; Revises AD 98-19-
15, Amendment 39-10794.
Applicability: Models SA226-T, SA226-T(B), SA226-AT, SA226-TC,
SA227-TT, SA227-AT, SA227-AC, SA227-BC, SA227-CC, and SA227-DC
airplanes, all serial numbers, certificated in any category; that
are equipped with Barber-Colman pitch trim actuators, part number
(P/N) 27-19008-001/-004 or P/N 27-19008-002/-005.
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 (e) 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 or made unnecessary by replacement of the P/N
27-19008-001/-004 or P/N 27-19008-002/-005 Barber-Colman pitch trim
actuator with a Simmonds-Precision actuator, P/N DL5040M5, P/N
DL5040M6, or P/N DL5040M8; or a Barber-Colman actuator, P/N 27-
19008-006 or P/N 27-19008-007.
To lessen the possibility of airplane pitch up caused by
mechanical failure of the pitch trim actuator, which could result in
a pitch upset and structural failure of the airplane, accomplish the
following:
(a) Prior to further flight after September 25, 1998 (the
effective date of AD 98-19-15), revise the FAA-approved Airplane
Flight Manual (AFM) by incorporating the following into the
Limitations Section of the AFM. This may be accomplished by
inserting a copy of this AD into the AFM:
``Limit the maximum indicated airspeed to maneuvering
airspeed (Va) as shown in the appropriate airplane flight manual
(AFM).''
[[Page 51481]]
and
``The minimum crew required is two pilots.''
Note 2: Fairchild Service Letter 226-SL-017, Fairchild Service
Letter 227-SL-033, and Fairchild Service Letter CC7-SL-023, all FAA
Approved: August 26, 1998; Revised: September 2, 1998; address the
subject matter of this AD.
Note 3: The prior to further flight compliance time of paragraph
(a) of this AD is being retained from AD 98-19-15. The only
substantive difference between this AD and AD 98-19-15 is the
addition of the alternative method of compliance referenced in
paragraph (c) of this AD.
(b) Incorporating the AFM revision, as specified in paragraph
(a) of this AD, may be performed by the owner/operator holding at
least a private pilot certificate as authorized by section 43.7 of
the Federal Aviation Regulations (14 CFR 43.7), and must be entered
into the aircraft records showing compliance with this AD in
accordance with section 43.9 of the Federal Aviation Regulations (14
CFR 43.9).
Note 4: This AD does not affect AD 97-23-01, Amendment 39-10188
(62 FR 5922, November 3, 1997). AD 97-23-01 still applies to all
SA226 and SA227 series airplanes equipped with either Barber-Colman
or Simmonds-Precision pitch trim actuators. AD 97-23-01 will be
superseded to cover the improved design pitch trim actuators
referenced in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. AD
97-23-01 requires the following:
--repetitively measuring the freeplay of the pitch trim actuator and
repetitively inspecting the actuator for rod slippage or ratcheting;
--immediately replacing any actuator if certain freeplay limitations
are exceeded or rod slippage or ratcheting is evident; and
--eventually replacing the Simmonds-Precision actuators regardless
of the inspection results.
(c) As an alternative method of compliance to the requirements
of this AD, replace each of the P/N 27-19008-001/-004 or P/N 27-
19008-002/-005 Barber-Colman pitch trim actuators with one of the
following, or FAA-approved equivalent part number:
(1) 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;
(2) 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); or
(3) 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 CC7-27-013. All airplane
models are eligible for this installation and airplane models vary
by service bulletin.
(d) 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.
(e) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Fort Worth 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 ACO.
(2) Alternative methods of compliance approved in accordance
with AD 98-19-15 are considered approved as alternative methods of
compliance for this AD.
Note 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth ACO.
(f) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to Fairchild Aircraft,
P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine these
documents at the FAA, Central Region, Office of the Regional
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
(g) This amendment revises AD 98-19-15, Amendment 39-10794.
Issued in Kansas City, Missouri, on September 15, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-24767 Filed 9-22-99; 8:45 am]
BILLING CODE 4910-13-U
