[Federal Register Volume 62, Number 92 (Tuesday, May 13, 1997)]
[Rules and Regulations]
[Pages 26223-26224]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-12517]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-65-AD; Amendment 39-10025; AD 97-10-13]
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 supersedes Airworthiness Directive (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. This AD retains the actions required by AD 96-
21-05, and adds certain Fairchild Model SA227-BC airplanes to the 
Applicability section of that AD. The actions specified by this 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: Effective July 8, 1997.
    The incorporation by reference of certain publications listed in 
the regulations was previously approved as of November 29, 1996 (61 FR 
54538, October 21, 1996).

ADDRESSES: Service information that applies to this AD may be obtained 
from Fairchild Aircraft, Inc., P.O. Box 790490, San Antonio, Texas 
78279-0490. This information may also be examined at 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; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

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:

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 certain Fairchild 
SA226 and SA227 series airplanes was published in the Federal Register 
as a notice of proposed rulemaking (NPRM) on January 29, 1997 (62 FR 
4203). The action proposed to supersede AD 96-21-05 with a new AD that 
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 
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 as specified in the NPRM would be in accordance with either 
Fairchild Aircraft Service Bulletin (SB) 226-27-050 or Fairchild 
Aircraft SB 227-27-028, both Issued: January 22, 1990.
    A Fairchild engineering order provides the instructions for 
reworking the elevator torque tube that, when incorporated, is 
identified as P/N 27-44026-SEO-1-03. Also, the P/N 27-44026-007 
elevator torque tube is not referenced in the service information. The 
FAA has determined that airplanes with this elevator torque tube 
installed are exempt from the actions of this AD, as well as those 
airplanes incorporating P/N 27-44026-005 or P/N 27-44026-SEO-1-03.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. One comment was received in support of 
the proposal 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 upon the public than was already proposed.

Compliance Time of the AD

    The compliance time for this 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 this 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 will be 
affected by this AD, that it will take approximately 10 workhours per 
airplane to accomplish the required action, and that the average labor 
rate is approximately $60 an hour. Based on these figures, the total 
cost impact of the 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 required 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 this AD for 390 
of the affected airplanes. The actions specified in this AD would 
affect only six additional airplanes over that already required by AD 
96-21-05. With this in mind, the cost impact of this AD over that 
already required by AD 96-21-05 would be $3,600.

[[Page 26224]]

Regulatory Impact

    The regulations adopted herein will 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 final 
rule does 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) 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, Incorporation by 
reference, 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) 96-21-05, Amendment 39-9782 (61 FR 54538, October 21, 1996), and 
by adding a new AD to read as follows:

97-10-13  Fairchild Aircraft, Inc.: Amendment 39-10025; 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 6 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 compliance with this AD, if any, may be 
obtained from the Fort Worth ACO.

    (e) The inspection access hole drilling, the inspection, and the 
corrosion preventive compound application required by this AD shall 
be done in accordance with Fairchild Aircraft SB 226-27-050 or 
Fairchild Aircraft SB 227-27-028, both Issued: January 22, 1990, as 
applicable. This incorporation by reference was previously approved 
by the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51, as of November 29, 1996 (61 FR 54538, 
October 21, 1996). Copies may be obtained Fairchild Aircraft, P.O. 
Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected 
at the FAA, Central Region, Office of the Assistant Chief Counsel, 
Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (f) This amendment (39-10025) supersedes AD 96-21-05, mendment 
39-9782.
    (g) This amendment (39-10025) becomes effective on July 8, 1997.

    Issued in Kansas City, Missouri, on May 7, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-12517 Filed 5-12-97; 8:45 am]
BILLING CODE 4910-13-U