[Federal Register Volume 60, Number 58 (Monday, March 27, 1995)]
[Rules and Regulations]
[Pages 15667-15669]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-7113]
=======================================================================
-----------------------------------------------------------------------
NUCLEAR REGULATORY COMMISSION
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-35-AD; Amendment 39-9180; AD 93-15-02 R1]
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment revises Airworthiness Directive (AD) 93-15-02,
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 not met or rod slippage is evident; and eventually
replacing the actuator regardless of the inspection results. This
action maintains these requirements, but reduces the hours time-in-
service (TIS) before the initial inspection is required, and shortens
both the time period between repetitive inspections and the actuator
replacement compliance time (unless the replacement actuator is new or
if the nut tube assemblies have been replaced during overhaul). An in-
flight incident where the referenced actuator on one of the affected
airplanes failed after accomplishment of the 5,000-hour initial
inspection (with satisfactory results) prompted this action. 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 April 17, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 17, 1995.
Comments for inclusion in the Rules Docket must be received on or
before June 5, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 93-CE-35-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, 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) 222-5150; facsimile (817) 222-5959.
SUPPLEMENTARY INFORMATION: AD 93-15-02, Amendment 39-8648 (59 FR 40734,
July 30, 1993), currently requires 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 not met 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 27-19008-01 or 27-19008-02. The requirements of
the AD will no longer apply when an actuator of improved design is
installed. Accomplishment of the freeplay measurements and inspections
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: April 28,
1993, as applicable. Accomplishment of the pitch trim actuator
replacement is 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 TIS.
Since 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.
Fairchild Aircraft has revised SA226 Series SL 226-SL-005 and SA227
Series SL 227-SL-011 to reflect the revised compliance times and a
change to the inspection procedure. The revision date of this service
information is March 2, 1995.
After examining the circumstances and reviewing all available
information related to the incident described above, the FAA has
determined that AD 93-15-02 should be revised by (1) reducing the
number of hours 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.
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, this AD requires the same
repetitive inspections and actuator replacement as AD 93-15-02, but
revises the compliance times as previously specified. The inspections
will be accomplished 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.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for public
prior comment [[Page 15668]] 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 notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 93-CE-35-AD.'' The postcard will be date stamped and
returned to the commenter.
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 and that it is not considered to be significant under
Executive Order 12866. It is impracticable for the agency to follow the
procedures of Executive Order 12866 with respect to this rule since the
rule must be issued immediately to correct an unsafe condition in
aircraft. 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-8648 (59 FR
40734, July 30, 1993), and by adding a new airworthiness directive to
read as follows:
93-15-02 R1 Fairchild Aircraft: Amendment 39-9180; Docket No. 93-
CE-35-AD. Revises AD 93-15-02, Amendment 39-8648.
Applicability: All SA226 and SA227 series airplanes (all models
and serial numbers) that are equipped with a Simmonds-Precision
pitch trim actuator, part number (P/N) DL5040M5, 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 use the authority
provided in paragraph (d) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition, or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any aircraft from the applicability of this AD.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
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, 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) Upon accumulating 3,000 hours time-in-service (TIS) on a
Simmonds-Precision pitch trim actuator, P/N DL5040M5, or within the
next 50 hours TIS accumulated on this type pitch trim actuator after
the effective date of this AD, whichever occurs later, unless
already accomplished, and thereafter at intervals not to exceed 250
hours TIS until paragraph (b) is complied with, accomplish the
following:
Note 3: If hours TIS accumulated on the pitch trim actuator are
not maintained, then hours TIS accumulated on the airplane may be
substituted.
(1) Measure the freeplay 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: March 2, 1995, as applicable.
(2) If certain freeplay limitations specified in the service
letters are not met or rod slippage is evident, prior to further
flight, accomplish the replacement specified in either paragraph
(b)(1) or (b)(2) of this AD.
(b) Within 500 hours TIS after the inspection specified in
paragraph (a) of this AD or upon accumulating 5,000 hours TIS on a
Simmonds-Precision pitch trim actuator, P/N DL5040M5, whichever
occurs later, accomplish one of the following:
(1) Replace the pitch trim actuator with a new part of the same
design and part number in accordance with the instructions in the
applicable maintenance manual. Reinspect as specified in paragraph
(a) of this AD at intervals not to exceed 300 hours TIS, and replace
the actuator as specified in paragraph (b) of this AD at intervals
not to exceed 6,500 hours TIS.
(2) Replace the pitch trim actuator with an overhauled, zero-
timed part of the same design and part number. Accomplish this
replacement in accordance with the instructions in the applicable
maintenance manual, and reinspect and replace as specified below
(paragraphs (b)(2)(i) and (b)(2)(ii) of this AD):
(i) If both nut tube assemblies, P/N AA56142, were replaced with
new assemblies during overhaul, reinspect as specified in paragraph
(a) of this AD at intervals not to exceed 300 hours TIS, and
[[Page 15669]] replace the actuator as specified in paragraph (b) of
this AD at intervals not to exceed 6,500 hours TIS;
(ii) If both nut tube assemblies, P/N AA56142, were not replaced
with new assemblies during overhaul, reinspect as specified in
paragraph (a) of this AD at intervals not to exceed 250 hours TIS,
and replace the actuator as specified in paragraph (b) of this AD at
intervals not to exceed 5,000 hours TIS.
(3) Replace the pitch trim actuator with a new part of improved
design, P/N 27-19008-01 or 27-19008-02, in accordance with the
instructions in the applicable maintenance manual.
(i) This replacement eliminates the repetitive inspection
requirement of this AD.
(ii) This replacement may be accomplished at any time to
eliminate the inspection requirement of this AD.
(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 4: 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: March 2,
1995, 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 (39-9180) becomes effective on April 17,
1995.
Issued in Kansas City, Missouri, on March 17, 1995.
Dwight A. Young,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-7113 Filed 3-24-95; 8:45 am]
BILLING CODE 4910-13-U
