[Federal Register Volume 64, Number 184 (Thursday, September 23, 1999)]
[Proposed Rules]
[Pages 51479-51481]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-24767]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-84-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 revise Airworthiness Directive (AD) 
98-19-15, which currently requires incorporating information into the 
Limitations Section of the airplane flight manual (AFM) that imposes a 
speed restriction and a minimum pilot requirement for Fairchild 
Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped 
with Barber-Colman pitch trim actuators, part number (P/N) 27-19008-
001/-004 or P/N 27-19008-002/-005. Since AD 98-19-15 became effective, 
improved design pitch trim actuators have been developed that, when 
installed, would eliminate the speed restriction and minimum pilot 
requirements of the current AD. The proposed AD would incorporate these 
installations as a method of complying with the current AD. The actions 
specified by the proposed AD are intended to lessen the possibility of 
airplane pitch up caused by mechanical failure of the pitch trim 
actuator, which could result in a pitch upset and structural failure of 
the airplane.

DATES: Comments must be received on or before November 24, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 98-CE-84-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 Fairchild Aircraft, Inc., P.O. Box 790490, San Antonio, Texas 
78279-0490; telephone: (800) 577-7273; facsimile: (210) 824-3869. This 
information also may be examined at the Rules Docket at the address 
above.

FOR FURTHER INFORMATION CONTACT: Mr. Werner G. Koch, Aerospace 
Engineer, FAA, Aircraft 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.
    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. 98-CE-84-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. 98-CE-84-AD, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106.

Discussion

    AD 98-19-15, Amendment 39-10794 (63 FR 50983, September 24, 1998), 
currently requires incorporating the following information into the 
applicable 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:

     ``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 following service information describes the AFM requirements:

--Fairchild Service Letter 226-SL-017, FAA Approved: August 26, 1998; 
Revised: September 2, 1998;
--Fairchild Service Letter 227-SL-033, FAA Approved: August 26, 1998;
--Revised: September 2, 1998; and
--Fairchild Service Letter CC7-SL-023, FAA Approved: August 26, 1998; 
Revised: September 2, 1998.

    AD 98-19-15 was the result of reports of two incidents of abrupt 
movement of the horizontal stabilizer to or near to the full airplane 
nose-up position. These two incidents involved mechanical failure of 
these Barber-Colman pitch trim actuators.
    The actions specified in AD 98-19-15 are intended to lessen the 
possibility of airplane pitch up caused by mechanical failure of the 
pitch trim actuator, which could result in a pitch upset and structural 
failure of the airplane.

Actions Since Issuance of Previous Rule

    At the time the FAA issued AD 98-19-15, there was a design 
alternative to

[[Page 51480]]

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 CC7-27-013. 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.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to this subject, including the above-referenced 
service information, the FAA has determined that:
--Accomplishing one of the installations referenced above should be 
considered as an alternative method of compliance with AD 98-19-15; and
--AD action should be taken to incorporate these options into the 
current AD and to lessen the possibility of airplane pitch up caused by 
mechanical failure of the pitch trim actuator, which could result in a 
pitch upset and structural failure 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 SA226 and SA227 airplanes of the 
same type design that have one of the affected pitch trim actuators 
installed, the FAA is proposing AD action to revise AD 98-19-15. The 
proposed AD would retain the requirements of the existing AD, and would 
provide the option of incorporating one of the replacements 
(installations) referenced earlier in this document as a method of 
accomplishing the AD.

Cost Impact

    The FAA estimates that 508 airplanes in the U.S. registry could 
have the affected pitch trim actuators installed and, therefore, could 
be affected by the AFM requirements of the proposed AD. Since an owner/
operator who holds at least a private pilot's certificate as authorized 
by sections 43.7 and 43.9 of the Federal Aviation Regulations (14 CFR 
43.7 and 43.9) may accomplish the proposed AFM insertions, the only 
cost impact upon the public would be the approximately 30 minutes it 
would take each owner/operator to incorporate the information into the 
AFM.
    The FAA has no way of determining the number of airplanes that have 
the design alternative pitch trim actuators installed, and would 
therefore not be affected by the proposed AD.

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 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 
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) 98-19-15, Amendment 39-10794, and adding a new AD to read as 
follows:

Fairchild Aircraft, Inc.: Docket No. 98-CE-84-AD; Revises AD 98-19-
15, Amendment 39-10794.

    Applicability: Models SA226-T, SA226-T(B), SA226-AT, SA226-TC, 
SA227-TT, SA227-AT, SA227-AC, SA227-BC, SA227-CC, and SA227-DC 
airplanes, all serial numbers, certificated in any category; that 
are equipped with Barber-Colman pitch trim actuators, part number 
(P/N) 27-19008-001/-004 or P/N 27-19008-002/-005.

    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 (e) 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 or made unnecessary by replacement of the P/N 
27-19008-001/-004 or P/N 27-19008-002/-005 Barber-Colman pitch trim 
actuator with a Simmonds-Precision actuator, P/N DL5040M5, P/N 
DL5040M6, or P/N DL5040M8; or a Barber-Colman actuator, P/N 27-
19008-006 or P/N 27-19008-007.
    To lessen the possibility of airplane pitch up caused by 
mechanical failure of the pitch trim actuator, which could result in 
a pitch upset and structural failure of the airplane, accomplish the 
following:
    (a) Prior to further flight after September 25, 1998 (the 
effective date of AD 98-19-15), revise the FAA-approved Airplane 
Flight Manual (AFM) by incorporating the following into the 
Limitations Section of the AFM. This may be accomplished by 
inserting a copy of this AD into the AFM:
     ``Limit the maximum indicated airspeed to maneuvering 
airspeed (Va) as shown in the appropriate airplane flight manual 
(AFM).''

[[Page 51481]]

and
     ``The minimum crew required is two pilots.''

    Note 2: Fairchild Service Letter 226-SL-017, Fairchild Service 
Letter 227-SL-033, and Fairchild Service Letter CC7-SL-023, all FAA 
Approved: August 26, 1998; Revised: September 2, 1998; address the 
subject matter of this AD.
    Note 3: The prior to further flight compliance time of paragraph 
(a) of this AD is being retained from AD 98-19-15. The only 
substantive difference between this AD and AD 98-19-15 is the 
addition of the alternative method of compliance referenced in 
paragraph (c) of this AD.

    (b) Incorporating the AFM revision, as specified in paragraph 
(a) of this AD, may be performed by the owner/operator holding at 
least a private pilot certificate as authorized by section 43.7 of 
the Federal Aviation Regulations (14 CFR 43.7), and must be entered 
into the aircraft records showing compliance with this AD in 
accordance with section 43.9 of the Federal Aviation Regulations (14 
CFR 43.9).

    Note 4: This AD does not affect AD 97-23-01, Amendment 39-10188 
(62 FR 5922, November 3, 1997). AD 97-23-01 still applies to all 
SA226 and SA227 series airplanes equipped with either Barber-Colman 
or Simmonds-Precision pitch trim actuators. AD 97-23-01 will be 
superseded to cover the improved design pitch trim actuators 
referenced in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. AD 
97-23-01 requires the following:

--repetitively measuring the freeplay of the pitch trim actuator and 
repetitively inspecting the actuator for rod slippage or ratcheting;
--immediately replacing any actuator if certain freeplay limitations 
are exceeded or rod slippage or ratcheting is evident; and
--eventually replacing the Simmonds-Precision actuators regardless 
of the inspection results.

    (c) As an alternative method of compliance to the requirements 
of this AD, replace each of the P/N 27-19008-001/-004 or P/N 27-
19008-002/-005 Barber-Colman pitch trim actuators with one of the 
following, or FAA-approved equivalent part number:
    (1) 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;
    (2) 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); or
    (3) 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 CC7-27-013. All airplane 
models are eligible for this installation and airplane models vary 
by service bulletin.
    (d) 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.
    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, Fort Worth 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 ACO.
    (2) Alternative methods of compliance approved in accordance 
with AD 98-19-15 are considered approved as alternative methods of 
compliance for this AD.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Fort Worth ACO.

    (f) All persons affected by this directive may obtain copies of 
the documents referred to herein upon request to Fairchild Aircraft, 
P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine these 
documents at the FAA, Central Region, Office of the Regional 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
    (g) This amendment revises AD 98-19-15, Amendment 39-10794.
    Issued in Kansas City, Missouri, on September 15, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-24767 Filed 9-22-99; 8:45 am]
BILLING CODE 4910-13-U