Airworthiness directives: Fairchild,

[Federal Register: September 23, 1999 (Volume 64, Number 184)]

[Proposed Rules]

[Page 51479-51481]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr23se99-24]

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).

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 filedin 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:

‹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.

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:

   ‹bullet› ``Limit the maximum indicated airspeed to maneuvering airspeed (Va) as shown in the appropriate airplane flight manual (AFM).''

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   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 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. 99-24767Filed9-22-99; 8:45 am]

   BILLING CODE 4910-13-U