[Federal Register Volume 62, Number 19 (Wednesday, January 29, 1997)]
[Proposed Rules]
[Pages 4203-4205]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-2103]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-65-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 AD 96-21-05, which 
currently requires the following on certain Fairchild Aircraft, Inc. 
(Fairchild) SA226 and SA227 series airplanes that do not have a certain 
elevator torque tube installed: drilling inspection access holes in the 
elevator torque tube arm, inspecting the elevator torque tube for 
corrosion, replacing any corroded elevator torque tube, and applying a 
corrosion preventive compound. AD 96-21-05 resulted from several 
reports of corrosion found in the elevator torque tube area on the 
affected airplanes. The proposed AD would retain the actions required 
by AD 96-21-05, and would add certain Fairchild Model SA227-BC 
airplanes to the Applicability section of that AD. The actions 
specified by the proposed AD are intended to prevent failure of the 
flight control system caused by a corroded elevator torque tube, which 
could result in loss of control of the airplane.

DATES: Comments must be received on or before April 1, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 96-CE-65-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 (210) 824-9421. This information also may be 
examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Hung Viet Nguyen, Aerospace 
Engineer, FAA, Airplane Certification Office, 2601 Meacham Boulevard, 
Fort Worth, Texas 76193-0150; telephone (817) 222-5155; 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. 96-CE-65-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 Assistant Chief Counsel, 
Attention: Rules Docket No. 96-CE-65-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Events Leading to the Proposed AD

    AD 96-21-05, Amendment 39-9782 (61 FR 54538, October 21, 1996), 
currently requires the following on certain Fairchild Aircraft SA226 
and SA227 series airplanes that do not have a part number (P/N) 27-
44026-007 elevator torque tube installed:
     Drilling inspection access holes in the elevator torque 
tube arm;
     Inspecting the elevator torque tube for corrosion and 
replacing any corroded elevator torque tube; and
     Applying a corrosion preventive compound.
    Accomplishment of the inspection access hole drilling, the 
inspection, and the corrosion preventive compound application is in 
accordance with either Fairchild Aircraft Service Bulletin (SB) 226-27-
050 or Fairchild Aircraft SB 227-27-028, both issued: January 22, 1990.
    AD 96-21-05 resulted from several reports of corrosion found in the 
elevator torque tube area on the affected airplanes.
    The FAA has since determined that the requirements of AD 96-21-05 
should also apply to certain Fairchild Model SA227-BC airplanes. In 
addition, Fairchild has issued an engineering order that provides 
instructions for reworking the elevator torque tube. When reworked, the 
elevator torque tube is identified as P/N 27-44026-SEO-1-03.
    The FAA has also determined that airplane owners/operators should 
not have to accomplish the actions of AD 96-21-05 if the affected 
airplane incorporates an elevator torque tube with either P/N 27-44026-
005, P/N 27-44026-007, or P/N 27-44026-SEO-1-03.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that AD action should be taken to prevent failure of the 
flight control system caused by a corroded elevator torque tube, which 
could result in 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 SA226 and SA227 series airplanes of 
the same type design, the FAA is proposing an AD that would supersede 
AD 96-21-05. The proposed AD would (1) retain the requirements of 
drilling inspection access holes in the elevator torque tube arm, 
inspecting the elevator torque tube for corrosion and replacing any 
corroded elevator torque tube, and applying a corrosion preventive 
compound; (2) add certain Fairchild

[[Page 4204]]

Model SA227-BC airplanes to the Applicability section of the AD; and 
(3) exempt from the AD those airplanes incorporating an elevator torque 
tube with either P/N 27-44026-005, P/N 27-44026-007, or P/N 27-44026-
SEO-1-03. Accomplishment of the proposed inspection access hole 
drilling, the inspection, and the corrosion preventive compound 
application would still be in accordance with either Fairchild Aircraft 
SB 226-27-050 or Fairchild Aircraft SB 227-27-028, both Issued: January 
22, 1990.

Compliance Time of the Proposed AD

    The compliance time for the proposed AD is presented in calendar 
time instead of hours time-in-service (TIS). The FAA has determined 
that a calendar time for compliance would be the most desirable method 
because the unsafe condition described by the proposed AD is caused by 
corrosion. Corrosion can occur on airplanes regardless of whether the 
airplane is in service or on the ground.

Cost Impact

    The FAA estimates that 396 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 10 
workhours per airplane to accomplish the proposed action, and that the 
average labor rate is approximately $60 an hour. Based on these 
figures, the total cost impact of the proposed AD on U.S. operators is 
estimated to be $237,600. This figure is based on the presumption that 
no owner/operator of the affected airplanes has accomplished the 
proposed inspection access hole drilling, inspection, or corrosion 
preventive compound application. It also is based on the presumption 
that no elevator torque tube would be found corroded and need to be 
replaced.
    AD 96-21-05 currently requires the same actions as is proposed for 
390 of the affected airplanes. The actions specified in this proposed 
AD would affect only six additional airplanes over that already 
required by AD 96-21-05. With this in mind, the cost impact of the 
proposed AD over that already required by AD 96-21-05 would be $3,600.

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 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) 96-21-05, Amendment 39-9782, and by adding a new AD to read as 
follows:

Fairchild Aircraft, Inc.: Docket No. 96-CE-65-AD; Supersedes AD 96-
21-05, Amendment 39-9782.

    Applicability: The following airplane models and serial numbers, 
certificated in any category, that do not incorporate an elevator 
torque tube with either part number (P/N) 27-44026-005, P/N 27-
44026-007, or P/N 27-44026-SEO-1-03:

------------------------------------------------------------------------
               Model                             Serial Nos.            
------------------------------------------------------------------------
SA226-T............................  T201 through T275 and T277 through 
                                      T291.                             
SA226-T(B).........................  T(B)276 and T(B)292 through        
                                      T(B)417.                          
SA226-AT...........................  AT001 through AT074.               
SA226-TC...........................  TC201 through TC419.               
SA227-TT...........................  TT421 through TT541.               
SA227-AT...........................  AT423 through AT695.               
SA227-AC...........................  AC406, AC415, AC416, and AC420     
                                      through AC772.                    
SA227-BC...........................  BC762, BC764, BC766, BC770, BC771, 
                                      and BC772.                        
------------------------------------------------------------------------

    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 within the next six calendar months after 
the effective date of this AD, unless already accomplished 
(compliance with AD 96-21-05).
    To prevent failure of the flight control system caused by a 
corroded elevator torque tube, which could result in loss of control 
of the airplane, accomplish the following:
    (a) Drill two .5-inch diameter holes in the inboard side of the 
elevator torque tube arm in accordance with the ACCOMPLISHMENT 
INSTRUCTIONS section of, and as specified in Figure 1 of, Fairchild 
Aircraft Service Bulletin (SB) 226-27-050 or Fairchild Aircraft SB 
227-27-028, both Issued: January 22, 1990, as applicable.
    (b) Inspect the elevator torque tube in accordance with the 
ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft SB 226-27-
050 or Fairchild Aircraft SB 227-27-028, both Issued: January 22, 
1990, as applicable.
    (1) If corrosion is found inside the elevator torque tube, prior 
to further flight after the inspection required by paragraph (b) of 
this AD, replace the corroded elevator torque tube with either a P/N 
27-44026-005, P/N 27-44026-007, or P/N 27-44026-SEO-1-03 elevator 
torque tube in accordance with the applicable maintenance manual.
    (2) If corrosion is not found inside the elevator torque tube, 
prior to further flight after the inspection required by paragraph 
(b) of this AD, apply a corrosion preventive compound in accordance 
with the ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Aircraft 
SB 226-27-050 or Fairchild Aircraft SB 227-27-028, both Issued: 
January 22, 1990, as applicable.
    (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 
compliance time 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. 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. Alternative methods of compliance approved in accordance with 
AD 96-21-05 (superseded by this AD) are considered approved for this 
AD.

    Note 2: Information concerning the existence of approved 
alternative methods of

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compliance with this AD, if any, may be obtained from the Fort Worth 
ACO.

    (e) All persons affected by this directive may obtain copies of 
the service bulletins referred to herein upon request to Fairchild 
Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490; or may 
examine these service bulletins at the FAA, Central Region, Office 
of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    (f) This amendment supersedes AD 96-21-05, Amendment 39-9782.

    Issued in Kansas City, Missouri, on January 21, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-2103 Filed 1-28-97; 8:45 am]
BILLING CODE 4910-13-P