[Federal Register Volume 65, Number 33 (Thursday, February 17, 2000)]
[Rules and Regulations]
[Pages 8037-8039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-3625]



[[Page 8037]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-59-AD; Amendment 39-11576; AD 2000-03-17]
RIN 2120-AA64


Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and 
SA227 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 97-23-
01, 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 or a certain 
Barber-Colman 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 AD 
retains the actions of AD 97-23-01, and adds these requirements on 
airplanes with different design pitch trim actuators installed. This AD 
is the result of the manufacturer developing different design pitch 
trim actuators and the Federal Aviation Administration (FAA) 
determining that these actuators should be subject to the actions of AD 
97-23-01. The actions specified by this AD are intended to detect 
excessive freeplay or rod slippage in the pitch trim actuator, which, 
if not detected and corrected, could result in pitch trim actuator 
failure and possible loss of control of the airplane.

DATES: Effective April 10, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 10, 2000.

ADDRESSES: 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 
Federal Aviation Administration (FAA), Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 99-CE-59-AD, 901 Locust, 
Room 506, 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:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Fairchild Aircraft 
SA226 and SA227 series airplanes that are equipped with a certain 
Simmonds-Precision pitch trim actuator or Barber-Colman pitch trim 
actuator was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on October 6, 1999 (64 FR 54242). The NPRM proposed 
to supersede AD 97-23-01, Amendment 39-10188 (62 FR 59277, November 3, 
1997). AD 97-23-01 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.

    In addition, AD 98-19-15 R1, Amendment 39-11507 (65 FR 1540, 
January 11, 2000), currently requires incorporating the following 
information into the applicable Airplane Flight Manual (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 (these pitch trim actuators are affected by AD 97-23-01):
     ``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 NPRM proposed to retain the requirements of AD 97-23-01, but 
would add these requirements on airplanes with the improved design 
pitch trim actuators installed.
    The NPRM was the result of the manufacturer developing different 
design pitch trim actuators and the Federal Aviation Administration 
(FAA) determining that these actuators should be subject to the actions 
of AD 97-23-01.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 508 airplanes in the U.S. registry will be 
affected by this AD. The only cost impact that this AD imposes upon the 
public over that already required by AD 97-23-01 is that incurred 
through the addition of the requirements on airplanes with the improved 
design pitch trim actuators installed. The costs of this AD on those 
airplanes that have these improved design pitch trim actuators 
incorporated will be less than that already required by AD 97-23-01 on 
airplanes with other pitch trim actuators installed.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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) 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 final evaluation prepared for this 
action is contained in the Rules Docket. A copy of it may be obtained 
by contacting the Rules Docket at the location provided under the 
caption ADDRESSES.

[[Page 8038]]

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 Airworthiness Directive 
(AD) 97-23-01, Amendment 39-10188 (62 FR 5922, November 3, 1997), and 
by adding a new AD to read as follows:

2000-03-17  Fairchild Aircraft, Inc.: Amendment 39-11576; Docket No. 
99-CE-59-AD, Supersedes AD 97-23-01, Amendment 39-10188; which 
superseded AD 93-15-02 R2, Amendment 39-9689; which revised AD 93-
15-02 R1, Amendment 39-9180; which revised AD 93-15-02, Amendment 
39-8648.

    Applicability: All SA226 and SA227 series airplanes (all models 
and serial numbers), 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 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 detect excessive freeplay or rod slippage in the pitch trim 
actuator, which, if not detected and corrected, could result in 
pitch trim actuator failure and possible 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, P/N DL5040M6, or P/N DL5040M8, 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 Revised: August 
3, 1999; or Fairchild Aircraft SA227 Series Service Letter CC7-SL-
028, Issued: August 12, 1999, as applicable.
     (ii) For airplanes equipped with Barber-Colman actuators, P/N 
27-19008-00-001, P/N 27-19008-002, P/N 27-19008-00-004, or P/N 27-
19008-005, conduct a functional inspection of the actuator in 
accordance with the INSTRUCTIONS section of Fairchild Aircraft SA226 
Series SL 226-SL-014, Revised: February 1, 1999, Fairchild Aircraft 
SA227 Series SL 227-SL-031, Revised: February 1, 1999, or Fairchild 
Aircraft SA227 Series SL CC7-SL-021, Revised: February 1, 1999, 
whichever is applicable.

    Note 3: The actions in this AD are the same as the actions in AD 
97-23-01, except for the actions added to the airplanes equipped 
with improved design pitch trim actuators.

    (2) Initial and repetitive replacements: Replace the pitch trim 
actuator with any of the pitch trim actuators presented in the Chart 
in paragraph (b) of this AD, as applicable, at the time specified in 
the Repetitive Replacement column of this chart. However, if certain 
freeplay limitations that are specified in the service letters are 
exceeded or if rod slippage is found, prior to further flight, 
replace the pitch trim actuator.
    (b) The following chart presents the pitch trim actuator that 
could be installed and 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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For all affected airplane models,  Upon accumulating 3,000    Every 250 hours TIS       Initially upon
 except for the Models SA227-CC     hours TIS on a Simmonds-   after the initial         accummulating 5,000
 and SA227-DC, with an original     Precision P/N DL5040M5     inspection until          hours TIS on the
 Simmonds-Precision actuator, P/N   actuator or within 50      accumulating 5,000        actuator or 500 hours
 DL5040M5, installed.               hours TIS after April      hours TIS on the          TIS after the initial
                                    17, 1995 (the effective    actuator or 500 hours     inspection, whichever
                                    date of AD 93-15-02 R1),   TIS after the last        occurs later, and
                                    whichever occurs later.    inspection required by    thereafter as indicated
                                                               AD93-15-02 R1.            below.
                                                               whichever occurs later.
For all affected airplane models,  Initially upon             Every 300 hours TIS       Upon accumulating 6,500
 except for the Models SA227-CC     accummulating 5,000        after the initial         hours TIS on the
 and SA227-DC, with a replacement   hours TIS on the new       inspection until          actuator.
 Simmonds-Precision actuator, PN/   actuator or within 50      accumulating 6,500
 DL5040M5, installed.               hours TIS after April      hours TIS on the
                                    17, 1995 (the effective    actuator.
                                    date of AD 93-15-02 R1),
                                    whichever occurs later.
For all affected airplane models,  Initially upon             Every 300 hours TIS       Upon accumulating 9,900
 except for the Models SA227-CC     accumulating 7,500 hours   after the initial         hours TIS on the
 and SA227-DC, with a replacement   TIS on the new or          inspection until          actuator.
 Simmonds-Precision actuator, P/N   modified actuator or       accumulating 9,900
 DL5040M6, installed. This part     within 50 hours TIS        hours TIS on the
 can be new, modified from a P/N    after April 17, 1995       actuator.
 DL5040M5 actuator, or overhauled   (the effective date of
 and zero-timed.                    AD 93-15-02 R1),
                                    whichever occurs later.
For all affected airplanes         Initially upon             Every 300 hours TIS       Upon accumulating 6,500
 models, except for the Models      accumulating 5,000 hours   after the initial         hours TIS on the
 SA227-CC and SA227-DC, with a      TIS on the overhauled      inspection until          actuator.
 replacement Simmonds-Precision     actuator or within 50      accumulating 6,500
 actuator, P/N DL5040M5,            hours TIS after April      hours TIS on the
 installed that was overhauled      17, 1995 (the effective    actuator.
 and zero-timed where both nut      date of AD 93-15-02 R1),
 assemblies, P/N AA56142, were      whichever occurs later.
 replaced with new assemblies
 during overhaul.

[[Page 8039]]

 
For all affected airplanes         Initially upon             Every 250 hours TIS       Upon accumulating 5,000
 models, except for the Models      accumulating 3,000 hours   after the initial         hours TIS on the
 SA227-CC and SA227-DC, with a      TIS on the overhauled      inspection until          actuator.
 replacement P/N DL5040M5           actuator or within 50      accumulating 5,000
 actuator installed that was        hours TIS after April      hours TIS on the
 overhauled and zero-timed where    17, 1995 (the effective    actuator.
 both nut assemblies, P/N           date of AD 93-15-02 R1),
 AA56142, were not replaced with    whichever occurs later.
 new assemblies during overhaul.
For all affected airplanes models  Upon accumulating 500      Every 300 hours TIS       None.
 with a newly fabricated or         hours total TIS on the     after the initial
 overhauled and zero-timed Barber-  newly fabricated or        inspection.
 Colman actuator, P/N 27-19008-     overhauled and zero-
 001-004 or P/N 27-19008-002-005.   timed actuator or within
                                    50 hours TIS after the
                                    effective date of AD 97-
                                    23-01, whichever occurs
                                    later.
For the Models SA227-CC and SA227- None.....................  None....................  Upon accumulating 1,500
 DC only, with a Simmonds-                                                               hours TIS on the
 Precision pitch trim actuator, P/                                                       actuator.
 N DL5040M5 or P/NDL5040M6,
 installed.
For all affected airplanes with a  Must be overhauled upon    Must be overhauled at     No replacement
 Barber-Colman P/N 27-19008-006     the accumulation of        intervals not to exceed   requirements.
 or 27-19008-007 actuator           2,000 hours TIS on the     2,000 hours EIS.
 installed.                         actuator.
For all affected airplanes with a  Upon accumulating 7,500    Every 600 hours TIS       Upon accumulating 9,900
 Simmonds-Precision pitch trim      hours TIS on the           after the initial         hours TIS on the
 actuator, PN DL5040M8, installed.  actuator of within the     inspection until          actuator.
                                    next 50 hours TIS after    accumulating, 9,900
                                    the effective date of      hours TIS.
                                    this AD, whichever
                                    occurs later.
----------------------------------------------------------------------------------------------------------------

    (c) Special flight permits may be issued in accordance with 
Secs. 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.
    (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 Airplane Certification Office.
    (2) Alternative methods of compliance that were approved in 
accordance with AD 97-23-01 are 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 Fort Worth Airplane Certification Office.

    (e)(1) The inspections required by this AD shall be done in 
accordance with the following:
    (i) Fairchild Aircraft SA226 Series SL 226-SL-005, Revised: 
August 3, 1999; or
    (ii) Fairchild Aircraft SA227 Series SL 227-SL-011; Revised: 
August 3, 1999; or
    (iii) Fairchild Aircraft SA227 Series SL CC7-SL-028, Issued: 
August 12, 1999; and
    (iv) Fairchild Aircraft SA 226 Series SL 226-SL-014, Revised: 
February 1, 1999; or
    (v) Fairchild Aircraft SA 227 Series SL 227-SL-031, Revised: 
February 1, 1999; or
    (vi) Fairchild Aircraft SA 227 Series SL CC7-SL-021, Revised: 
February 1, 1999.
    (2) This incorporation by reference was 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 Inc., P.O. Box 790490, San Antonio, Texas 78279-
0490. Copies may be inspected at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Room 301, Kansas City, Missouri, 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW, suite 700, Washington, DC.
    (f) This amendment supersedes 97-23-01, Amendment 39-10188; 
which superseded AD 93-15-02 R2, Amendment 39-9689; which revised AD 
93-15-02 R1, Amendment 39-9180; which revised AD 93-15-02, Amendment 
39-8648.
    (g) This amendment becomes effective on April 10, 2000.

    Issued in Kansas City, Missouri, on February 9, 2000.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-3625 Filed 2-16-00; 8:45 am]
BILLING CODE 4910-13-P