AD 95-19-07

2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:

Applicability: Models SA226-T, SA226-AT, SA226-TC, SA226-T(B), SA227-AC, SA227-AT, SA227-BC, SA227-TT, SA227-CC, and SA227-DC airplanes (all serial numbers), certificated in any category, that are equipped with one or more of the following:

1. Main landing gear part number (P/N) OAS5453-*(dash numbers 1 through 19) with either a P/N 5453005-1, 5453005-3, or 5453005-5 yoke installed; or

2. Nose landing gear P/N OAS5451-*(dash numbers 1 through 17) with a P/N 5451005-1 yoke installed.

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 (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 initially as follows and thereafter as indicated in the body of this AD:

1. Within the next 75 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished; and

2. Upon the installation of one of the affected main landing gear or nose landing gear assemblies or yokes.

To prevent main landing gear or nose landing gear failure caused by stress corrosion cracks of the yoke, which, if not detected and corrected, could result in loss of control of the airplane during landing operations, accomplish the following:

Note 2: The paragraph structure of this AD is as follows:

Level 1: (a), (b), (c), etc. Level 2: (1), (2), (3), etc. Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are designations of the Level 1 paragraph they immediately follow.

(a) Inspect, using ultrasonic methods, the left-hand and right-hand main landing gear and the nose landing gear yoke for stress corrosion cracking in accordance with one of the following, as applicable:

(1) The ACCOMPLISHMENT INSTRUCTIONS section of Fairchild Service Bulletin (SB) 226-32-065, Issued: August 16, 1995.

(2) The ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB 227-32-039, Issued: August 16, 1995.

(3) The ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB CC7-32-007, Issued: August 16, 1995.

(b) Reinspect or replace the right-hand or left-hand main landing gear or nose landing gear yoke as follows based on the results of any required inspection:

(1) If no cracks are found or a crack is found that is less than .25 inch, accomplish the following:

(i) Prior to further flight after the inspection required by paragraph (a) of this AD, clean the main landing gears and nose landing gear yoke and piston in accordance with Figure 2 of the service bulletins referenced in paragraphs (a)(1), (a)(2), and (a)(3) of this AD;

(ii) Prior to further flight after the inspection required by paragraph (a) of this AD, apply a small bead of Products Research and Chemical Corporation PR-1422 or PR-1435 sealant to the main landing gears and nose landing gear yoke as shown in Figure 2 of the service bulletins referenced in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, and as described in the SA226/227 Series Service Repair Manual, Chapter 51-30-03, Standard Practices--Sealing; and

(iii) Reinspect at intervals not to exceed 2,000 hours TIS provided no cracks are found that are .25 inch or more in length.

(2) If a crack is found with a length of .25 inch or more but not more than .50 inch, reinspect at intervals not to exceed 1,000 hours TIS provided the crack is no longer than .50 inch.

(3) If a crack is found with a length more than .50 inch but not more than .75 inch, reinspect at intervals not to exceed 500 hours TIS provided the crack is no longer than .75 inch.

(4) If a crack is found with a length more than .75 inch but not more than 1 inch, reinspect at intervals not to exceed 200 hours TIS provided the crack is no longer than 1 inch.

(5) If a crack is found with a length more than 1 inch but not more than 1.5 inches, accomplish the following:

(i) Within 100 hours TIS after the inspection required by paragraph (a) of this AD, replace the cracked part with a new part in accordance with the applicable maintenance manual. This may be accomplished by replacing the cracked yoke, the total gear assembly, or the yoke/cylinder combination;

(ii) Prior to further flight after replacing the cracked part, clean the main landing gears and nose landing gear yoke and piston in accordance with figure 2 of the service bulletins referenced in paragraphs (a)(1), (a)(2), and (a)(3) of this AD;

(iii) Prior to further flight after replacing the cracked part, apply a small bead of Products Research and Chemical Corporation PR-1422 or PR-1435 sealant to the main landing gears and nose landing gear yoke as shown in Figure 2 of the service bulletins referenced in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, and as described in the SA226/227 Series Service Repair Manual, Chapter 51-30-03, Standard Practices--Sealing; and

(iv) Repeat the inspections specified in paragraphs (a) and (b) of this AD and replace the part as required.

(6) If a crack is found with a length more than 1.5 inches, accomplish the following:

(i) Prior to further flight after the inspection required by paragraph (a) of this AD, replace the cracked part with a new part in accordance with the applicable maintenance manual. This may be accomplished by replacing the cracked yoke, the total gear assembly, or the yoke/cylinder combination;

(ii) Prior to further flight after replacing the cracked part, clean the main landing gears and nose landing gear yoke and piston in accordance with figure 2 of the service bulletins referenced in paragraphs (a)(1), (a)(2), and (a)(3) of this AD;

(iii) Prior to further flight after replacing the cracked part, apply a small bead of Products Research and Chemical Corporation PR-1422 or PR-1435 sealant to the main landing gears and nose landing gear yoke as shown in Figure 2 of the service bulletins referenced in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, and as described in the SA226/227 Series Service Repair Manual, Chapter 51-30-03, Standard Practices--Sealing; and

(iv) Repeat the inspections specified in paragraphs (a) and (b) of this AD and replace the part as required.

(7) If multiple cracks are found, add the total length of the cracks and use the criteria presented in paragraphs (b)(1) through (b)(6) of this AD, including all subparagraph designations, to establish repetitive inspection intervals or replacement times.

(c) The MLG and NLG yokes affected by this AD are manufactured by Ozone Industries, Inc. Replacing these yokes with approved parts manufactured by Fairchild Aircraft eliminates the repetitive inspection requirements of this AD.

(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, 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth ACO.

(f) The inspections required by this AD shall be done in accordance with Fairchild Aircraft Service Bulletin 226-32-065, Issued: August 16, 1995, Fairchild Aircraft Service Bulletin 227-32-039, Issued: August 16, 1995, or Fairchild Aircraft Service Bulletin CC7-32-007, Issued: August 16, 1995, as applicable. 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., 7th Floor, suite 700, Washington, DC.

(g) This amendment (39-9369) becomes effective on September 28, 1995.

Issued in Kansas City, Missouri, on September 6, 1995. Gerald W. Pierce, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.