[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Proposed Rules]
[Pages 54242-54245]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26090]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-59-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to supersede 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 Barbar-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. The proposed AD would retain the actions of AD 97-23-01, but 
would add these requirements on airplanes with different design pitch 
trim actuators installed. The proposed 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 the proposed 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: Comments must be received on or before December 6, 1999.

ADDRESSES: Submit comments in triplicate to the FAA, Central Region, 
Office of the Regional Counsel, Attention: Rules Docket No. 99-CE-59-
AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. 
Comments may be inspected at this location between 8 a.m. and 4 p.m., 
Monday through Friday, holidays excepted.
    Service information that applies to the proposed 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 also may be examined at the 
Rules Docket at the address above.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 proposal will be filed in the Rules Docket.

[[Page 54243]]

    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. 99-CE-59-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Central Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 99-CE-59-AD, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106.

Discussion

    AD 97-23-01, Amendment 39-10188 (62 FR 5922, November 3, 1997), 
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.
    The actions specified by AD 97-23-01 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.
    In addition, AD 98-19-15, Amendment 39-10794 (63 FR 50983, 
September 24, 1998), 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.''

Actions Since Issuance of AD 97-23-01

    At the time the FAA issued AD 98-19-15, there was a design 
alternative to the Barber-Colman pitch trim actuators for all of the 
affected airplanes, except for the Models SA227-CC and SA227-DC 
airplanes. Since that time, a design alternative for all affected 
airplanes has been developed. These design alternatives are:
    --Barber-Colman P/N 27-19008-006 or P/N 27-19008-007 pitch trim 
actuators. Procedures to install these pitch trim actuators are 
contained in Fairchild Service Bulletin 226-27-064, Fairchild Service 
Bulletin 227-27-046, and Fairchild Service Bulletin CC7-27-015. All 
airplane models are eligible for this installation and airplane models 
vary by service bulletin;
    --Simmonds-Precision P/N DL5040M5 or P/N DL5040M6 pitch trim 
actuators. All airplane models are eligible for this installation. 
Procedures to install these pitch trim actuators for the Models SA227-
CC and SA227-DC airplanes are contained in Fairchild Service Bulletin 
CC7-27-014, and are contained in engineering data for all other models 
(contact Fairchild); and
    --Simmonds-Precision P/N DL5040M8 pitch trim actuators. Procedures 
to install these pitch trim actuators are contained in Fairchild 
Service Bulletin 227-27-045, Fairchild Service Bulletin 226-27-063, and 
Fairchild Service Bulletin CC7-23-013. All airplane models are eligible 
for this installation and airplane models vary by service bulletin.
    These pitch trim actuators, when installed, would eliminate the 
need for the requirements of AD 98-19-15.
    However, there currently are no AD requirements that mandate 
repetitive inspections and/or replacements or overhauls of these pitch 
trim actuators similar to the pitch trim actuators affected by AD 97-
23-01. The FAA evaluated the design of these improved pitch trim 
actuators and has determined that (1) a similar condition to that 
specified in AD 97-23-01 exists for airplanes with these actuators 
installed; and (2) the actuators should have inspections and/or 
replacements or overhauls as follows:
    --Barber-Colman P/N 27-19008-006 or P/N 27-19008-007 pitch trim 
actuators: Overhaul at intervals not to exceed 2,000 hours time-in-
service (TIS);
    --Simmonds-Precision P/N DL5040M5 or P/N DL5040M6 pitch trim 
actuators: Replacement at intervals not to exceed 1,500 hours TIS; and
    --Simmonds-Precision P/N DL5040M8 pitch trim actuators: Initial 
inspection at 7,500 hours TIS after installation and thereafter at 
intervals not to exceed 600 hours TIS. Repetitive replacement at 
intervals not to exceed 9,900 hours TIS.

Relevant Service Information

    Fairchild has revised SA226 Series Service Letter (SL) 226-SL-005 
and Fairchild Aircraft SA227 Series SL 227-SL-011, both Revised: August 
3, 1999; and issued SA227 Series SL CC7-SL-028, Issued: August 12, 
1999, to also include the inspection procedures on the P/N DL5040M8 
pitch trim actuators.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that:
    --The improved design pitch trim actuators referenced above should 
also have repetitive inspection and/or overhaul or replacement 
requirements; and
    --AD action should be taken 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.

Explanation of the Provisions of the Proposed 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 certain 
Simmonds-Precision pitch trim actuator, the FAA is proposing an AD to 
supersede AD 97-23-01. The proposed AD would retain the actions of AD 
97-23-01, but would add these requirements on airplanes with the 
improved design pitch trim actuators installed.

Cost Impact

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

Regulatory Impact

    The regulations proposed herein would 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

[[Page 54244]]

12612, it is determined that this proposal would 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 14 
CFR part 39 of the Federal Aviation Regulations 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:

Fairchild Aircraft, Inc.: 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 SL 
226-SL-014, 227-SL-031, or CC7-SL-021, Issued: October 3, 1997, 
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 and     hours TIS on a           after the initial        accumulating 5,000
 SA227-DC, with an original Simmonds-   Simmonds-Precision P/N   inspection until         hours TIS on the
 Precision actuator, P/N DL5040M5,      DL5040M5 actuator or     accumulating 5,000       actuator or 500 hours
 installed.                             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.
For all affected airplane models,      Initially upon           Every 300 hours TIS      Upon accumulating 6,500
 except for the Models SA227-CC and     accumulating 5,000       after the initial        hours TIS on the
 SA227-DC, with a replacement           hours TIS on the new     inspection until         actuator.
 Simmonds-Precision actuator, P/N       actuator or within 50    accumulating 6,500
 DL5040M5, installed.                   hours TIS after April    hours TIS on the
                                        17, 1995 (the            actuator.
                                        effective 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 and     accumulating 7,500       after the initial        hours TIS on the
 SA227-DC, with a replacement           hours TIS on the new     inspection until         actuator.
 Simmonds-Precision actuator, P/N       or modified actuator     accumulating 9,900
 DL5040M6, installed. This part can     or within 50 hours TIS   hours TIS on the
 be new, modified from a P/N DL5040M5   after April 17, 1995     actuator.
 actuator, or overhauled or             (the effective date of
 overhauled and zero-timed.             AD 93-15-02 R1),
                                        whichever occurs later.

[[Page 54245]]

 
For all affected airplane models,      Initially upon           Every 300 hours TIS      Upon accumulating 6,500
 except for the Models SA227-CC and     accumulating 5,000       after the initial        hours TIS on the
 SA227-DC, with a replacement           hours TIS on the over-   inspection until         actuator.
 Simmonds-Precision actuator, P/N       hauled actuator or       accumulating 6,500
 DL5040M5, installed that was           within 50 hours TIS      hours TIS on the
 overhauled and zero-timed where both   after April 17, 1995     actuator.
 nut assemblies, P/N AA56142, were      (the effective date of
 replaced with new assemblies during    AD 93-15-02 R1),
 overhaul.                              whichever occurs later.
For all affected airplane models,      Initially upon           Every 250 hours TIS      Upon accumulating 5,000
 except for the Models SA227-CC and     accumulating 3,000       after the initial        hours TIS on the
 SA227-DC, with a replacement P/N       hours TIS on the over-   inspection until         actuator.
 DL5040M5 actuator installed that was   hauled actuator or       accumulating 5,000
 overhauled and zero-timed where both   within 50 hours TIS      hours TIS on the
 nut assemblies, P/N AA56142, were      after April 17, 1995     actuator.
 not replaced with new assemblies       (the effective date of
 during overhaul.                       AD 93-15-02 R1),
                                        whichever occurs later.
For all affected airplanes models      Upon accumulating 500    Every 300 hours TIS      None.
 with a Barber-Colman pitch trim        hours total TIS on the   after the initial
 actuator installed, P/N 27-19008-001/  new or overhauled zero-  inspection.
 004 or 27-19008-002/-005, that is      timed pitch trim
 currently in-service with less than    actuator or within 50
 1,000 hours TIS since new or           hours TIS after the
 overhauled and zero-timed.             effective date of this
                                        AD, whichever occurs
                                        later.
For all affected airplane models with  Upon accumulating 500    Every 300 hours TIS      None.
 a newly fabricated and over-hauled     hours total TIS on the   after the initial
 and zero-timed Barber-Colman           actuator or within 50    inspection.
 actuator, P/N 27-19008-001/-004 or P/  hours TIS after the
 N 27-19008-02-005.                     effective date of this
                                        AD, whichever occurs
                                        later.
For the Models SA227-CC and SA227-DC   None...................  None...................  Upon accumulating 1,500
 only, with a Simmonds-Precision                                                          hours TIS on the
 pitch trim actuator, P/N DL5040M5 or                                                     actuator.
 P/N DL5040M6, installed.
For all affected airplanes with a      Must be overhauled upon  Must be overhauled at    No replacement
 Barber-Colman P/N 27-19008-006 or 27-  the accumulation of      intervals not to         requirements.
 19008-007 actuator installed.          2,000 hours TIS on the   exceed 2,000 hours TIS.
                                        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, P/N DL5040M8, installed.     actuator or within the   inspection until         actuator.
                                        next 50 hours TIS        accumulating 9,900
                                        after the effective      hours TIS.
                                        date of this AD,
                                        whichever occurs later.
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    (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.
    (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) Service information related to this AD 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.
    (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.

    Issued in Kansas City, Missouri, on September 30, 1999.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 99-26090 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-U