# AD 96-21-05: Airworthiness Directives; Fairchild Aircraft SA226 and SA227 Series Airplanes - Type: Airworthiness directive - Effective: November 29, 1996 - Published: October 21, 1996, 61 FR 54538–54540 - Issued as: Final rule - Superseded by: Nothing supersedes this AD - Amendment: 39-9782 - Docket: 95-CE-40-AD - Official PDF: https://openairdocs.org/files/sha256/98/24/9824e353f5fd48bf03b9b23ffca974816dcd1c89b330f60e03a59e0ffae85a23 (from https://www.govinfo.gov/content/pkg/FR-1996-10-21/pdf/96-26705.pdf) - Federal Register: https://www.federalregister.gov/documents/1996/10/21/96-26705/airworthiness-directives-fairchild-aircraft-sa226-and-sa227-series-airplanes - Page: https://openairdocs.org/ad/96-21-05 ## Summary This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 and SA227 series airplanes that do not have a certain elevator torque tube installed. This action requires 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. Several reports of corrosion found in the elevator torque tube area on the affected airplanes prompted this action. 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. ## The airworthiness directive ### 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 adding a new airworthiness directive (AD) to read as follows: 96-21-05 Fairchild Aircraft: Amendment 39-9782; Docket No. 95-CE-40-AD. Applicability: The following airplane models and serial numbers, certificated in any category, that do not have a part number (P/N) 27-44026-007 elevator torque tube installed: ------------------------------------------------------------------------ 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. ------------------------------------------------------------------------ Note 1: This AD applies to each airplane identified in the preceding applicability revision, 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. 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) (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) (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 a P/N 27-44026-007 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) (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) (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. 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) (e) The drilling, inspection, and application required by this AD shall be done in accordance with Fairchild Aircraft Service Bulletin 226-27-050 or Fairchild Service Bulletin 227-27-028, both Issued: January 22, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from 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) (f) This amendment (39-9782) becomes effective on November 29, 1996. Issued in Kansas City, Missouri, on October 10, 1996. Marvin R. Nuss, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. ## Rule preamble ### Dates Effective November 29, 1996. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 29, 1996. ### Addresses Service information that applies to this AD may be obtained from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490; telephone (210) 824-9421. This information may also be examined at the Federal Aviation Administration (FAA), Central Region, Office of the Assistant Chief Counsel, Attention: Rules Docket 95-CE-40-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. ### Events Leading to 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 Aircraft SA226 and SA227 series airplanes was published in the Federal Register on September 19, 1995 (60 FR 48431). The action proposed to require 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. Accomplishment of the proposed inspection access hole drilling, the inspection, and the corrosion preventive compound application as specified in the notice of proposed rulemaking (NPRM) would be in accordance with either Fairchild Service Bulletin (SB) 226-27-050 or Fairchild SB 227-27-028, both Issued: January 22, 1990. Several reports of corrosion found in the elevator torque tube area on the affected airplanes prompted the proposal. Interested persons have been afforded an opportunity to participate in the making of this amendment. One comment was received in favor of the proposal and no comments were received regarding the FAA's determination of the cost to the public. Since issuing Fairchild SB 226-27-050, Fairchild Aircraft has designed an improved elevator torque tube, part number (P/N) 27-44026-007. The FAA has determined that airplane owners/operators of Fairchild Aircraft SA226 and SA227 series airplanes that have a P/N 27-44026-007 elevator torque tube installed should not have to accomplish the actions specified in the NPRM. ### 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 the exemption of those airplanes with a P/N 27-44026-007 elevator torque tube installed and minor editorial corrections. The FAA has determined that this exemption and the 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 This 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 390 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 $234,000. This figure is based on the assumption 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 assumption that no elevator torque tube would be found corroded and need to be replaced. The FAA has no way of determining how many owners/operators of the affected airplanes may have already complied with this AD. ### 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: ## Related documents - [Proposed rule 95-CE-40-AD](https://openairdocs.org/proposed/95-CE-40-AD): Notice of proposed rulemaking (NPRM), published Sep 19, 1995 Its text cites no advisory circulars or STCs. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.