AD Amdt-39-11507

[Federal Register Volume 65, Number 7 (Tuesday, January 11, 2000)]
[Rules and Regulations]
[Pages 1540-1542]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-537]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-84-AD; Amendment 39-11507; AD 98-19-15 R1]
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 revises 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, will 
eliminate the speed restriction and minimum pilot requirements of the 
current AD. This AD requires incorporating these installations as a 
method of complying with the current AD. The actions specified by this 
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.

DATE: Effective March 3, 2000.

ADDRESSES: Service information that applies to this 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 may also be examined at the Federal Aviation Administration 
(FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
Docket No. 98-CE-84-AD, 901 Locust, Room 506, Kansas City, Missouri 
64106.

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:

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 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 was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on September 23, 1999 (64 FR 
51479). The NPRM proposed to revise AD 98-19-15. 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:
    <bullet> ``Limit the maximum indicated airspeed to maneuvering 
airspeed (Va) as shown in the appropriate airplane flight manual 
(AFM).'' and
    <bullet> ``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.

    The NPRM proposed to retain the requirements of the existing AD, 
and would provide the option of incorporating one of the design 
alternatives developed since the issuance of AD 98-19-15. 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 and 
limitations 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 and 
limitations 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. One comment was received in favor of 
the NPRM and no comments were received on 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

[[Page 1541]]

upon the public than was already proposed.

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 this 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 AFM insertions, the only cost impact upon 
the public will be the approximately 30 minutes it will 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 will 
therefore not be affected by this AD.

Regulatory Impact

    These regulations 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, the FAA has 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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) 98-19-15, Amendment 39-10794, and adding a new AD to read as 
follows:

    98-19-15 R1 Fairchild Aircraft, Inc.: Amendment 39-11507; 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:
    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:
    <bullet> ``Limit the maximum indicated airspeed to maneuvering 
airspeed (Va) as shown in the appropriate airplane flight manual 
(AFM).''
      and
    <bullet> ``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 and limitations 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 and limitations 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

[[Page 1542]]

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, 901 Locust, Room 506, Kansas City, Missouri 64106.
    (g) This amendment becomes effective on March 3, 2000.

    Issued in Kansas City, Missouri, on January 4, 2000.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 00-537 Filed 1-10-00; 8:45 am]
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