[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.                                                                  
----------------------------------------------------------------------------------------------------------------


[[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