[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:

----------------------------------------------------------------------------------------------------------------
              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.                                                                                     
----------------------------------------------------------------------------------------------------------------


    (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