[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]



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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.

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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]
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