AD 94-07-10 R1 ACTIVE

This amendment revises AD 94-07-10, which currently requires the following on Fairchild Aircraft SA226 and SA227 series airplanes: repetitively inspecting (visually) the wing skin for cracks; dye penetrant inspecting the rib straps if the wing skin is found cracked; and, if any crack is found in the rib straps, repairing the rib straps and modifying the wing skin. That AD references an incorrect dye penetrant inspection when the wing skin is found cracked. This action maintains the requirements of AD 94-07-10, but incorporates reference to the correct dye penetrant inspection for when the wing skin is found cracked. The actions specified by this AD are intended to prevent failure of the wing skin at the top aft outboard corner of the battery box, which could result in structural damage to the wing.

Final rule.

94-07-10 R1 FAIRCHILD AIRCRAFT: Amendment 39-9516; Docket No. 93-CE-21-AD. Revises AD 94-07-10, Amendment 39-8868.

Applicability: The following model and serial number airplanes, certificated in any category:

Model
Serial Numbers
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 AT631, and AT695
SA227-AC
AC406, AC415, AC416, and AC420 through AC789
SA227-BC
BC420 through BC789
SA227-CC
CC784, and CC790 through CC822
SA227-DC
DC784, and DC790 through DC822

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 initially upon the accumulation of 2,500 hours time-in-service (TIS) or within the next 100 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished (compliance with AD 94-07-10), and thereafter as indicated in the body of the AD.

To prevent failure of the wing skin at the top aft outboard corner of the battery box, which could result in structural damage to the wing, 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.
Level3:
(i), (ii), (iii), etc.

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

(a) Visually inspect the right and left upper wing skin by the top aft outboard corner of the battery box for cracks in accordance with Figure 1 and the ACCOMPLISHMENT INSTRUCTIONS, A. Inspection, section of whichever of the following is applicable:

(1) Fairchild Service Bulletin (SB) 226-57-018, Issued: January 28, 1993, Revised: June 3, 1993 (pages 4 through 11 and 13 through 15), Revised: July 1, 1993 (page 12) and Revised: October 25, 1993 (pages 1 through 3);

(2) Fairchild SB 227-57-005, Issued: December 21, 1992, Revised: June 3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July 1, 1993 (pages 1 and 12); or

(3) Fairchild Aircraft SB CC7-57-002, Issued: January 28, 1993, Revised: June 3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July 1, 1993 (pages 1 and 12).

(b) If cracks are not found duringthe visual inspection required by paragraph (a) of this AD, within 500 hours TIS after this initial visual inspection, accomplish one of the following:

(1) Reinspect the right and left upper wing skin by the top aft outboard corner of the battery box for cracks in accordance with Figure 1 and the ACCOMPLISHMENT INSTRUCTIONS, A. Inspection, section of the applicable service information presented in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, and reinspect thereafter at intervals not to exceed 500 hours TIS; or

(2) Modify the upper wing skin in accordance with the ACCOMPLISHMENT INSTRUCTIONS, B. Removal and C. Installation, section of the service information referenced in paragraphs (a)(1), (a)(2), or (a)(3) of this AD, as applicable. Accomplishing this modification terminates the repetitive visual inspections that are specified in paragraph (b)(1) of this AD, and the modification may be accomplished at any time to eliminate this repetitive inspection requirement.

(c) If cracks are found during the inspection required by paragraph (a) of this AD, prior to further flight, dye penetrant inspect the 27-31130 straps in the wheel wells as specified in the ACCOMPLISHMENT INSTRUCTIONS, A. Inspection section, paragraph (1)(b), of the service information referenced in paragraphs (a)(1), (a)(2), or (a)(3) of this AD, as applicable.

(1) If cracks are found in either of the 27-31130 straps during the inspection required by paragraph (c) of this AD, prior to further flight, accomplish the following:

(i) Repair the 27-31130 strap in accordance with a scheme obtained from the manufacturer through the Fort Worth Airplane Certification Office (ACO) at the address specified in paragraph (e) of this AD; and

(ii) Modify the upper wing skin in accordance with the ACCOMPLISHMENT INSTRUCTIONS, B. Removal and C. Installation, section of the service information referenced in paragraphs (a)(1), (a)(2), or (a)(3) of this AD, as applicable.

(2) If no cracks are found in either of the 27-31130 straps, within 150 hours TIS after the initial dye penetrant inspection required by paragraph (c) of this AD, accomplish one of the following:

(i) Reinspect (dye penetrant) the 27-31130 straps in the wheel well for cracks as specified in the ACCOMPLISHMENT INSTRUCTIONS, A. Inspection section, paragraph (1)(b), of the service information referenced in paragraphs (a)(1), (a)(2), or (a)(3) of this AD, as applicable. Continue to reinspect at intervals not to exceed 150 hours TIS provided no cracks are found, and repair and modify as specified in paragraphs (c)(1) and (c)(2) of this AD if any cracks are found.

(ii) Modify the upper wing skin in accordance with the ACCOMPLISHMENT INSTRUCTIONS, B. Removal and C. Installation, section of the service information referenced in paragraphs (a)(1), (a)(2), or (a)(3) of this AD, as applicable. Accomplishing this modification terminates the repetitive dye penetrant inspections that are specifiedin paragraph (c)(2)(i) of this AD, and the modification may be accomplished at any time to eliminate this repetitive inspection requirement.

NOTE 3: Certain Limited Approved Repair (LAR) and Approved Repair Procedure (ARP) documents issued by Fairchild Aircraft specify procedures for accomplishing the same modification referenced in paragraphs (b)(2), (c)(1)(ii), and (c)(2)(ii) of this AD. Check with the Fort Worth ACO at the address presented in paragraph (e) of this AD to find out which LAR's and ARP's are considered "unless already accomplished" as they relate to 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 initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Fort Worth ACO, FAA, 2601 Meacham Boulevard, Fort Worth, Texas 76137-0150. 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 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth ACO.

(f) Alternative methods of compliance approved in accordance with AD 94-07-10 (revised by this action) are considered approved as alternative methods of compliance with this AD.

(g) The inspections, possible repair, and optional modification required by this AD shall be done in accordance with Fairchild Service Bulletin 226-57-018, Issued: January 28, 1993, Revised: June 3, 1993 (pages 4 through 11 and 13 through 15), Revised: July 1, 1993 (page 12) and Revised: October 25, 1993 (pages 1 through 3); Fairchild Service Bulletin 227-57-005, Issued: December 21, 1992, Revised: June3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July 1, 1993 (pages 1 and 12); or Fairchild Aircraft Service Bulletin CC7-57-002, Issued: January 28, 1993, Revised: June 3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July 1, 1993 (pages 1 and 12), 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. 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.

(h) This amendment (39-9516) revises AD 94-07-10, Amendment 39-8868.

(i) This amendment becomes effective on March 25, 1996.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to Fairchild Aircraft SA226 and SA227 series airplanes was published in the Federal Register on June 23, 1995 (60 FR 32628). The action proposed to revise AD 94-07-10 to retain the requirement of repetitively inspecting the wing skin for cracks, and would maintain the dye penetrant inspection requirement but require it in accordance with the correct portion of the ACCOMPLISHMENT INSTRUCTIONS section of the applicable service bulletin. This action also proposed to maintain the option of modifying the wing skin as terminating action for the repetitive inspections. Accomplishment of the proposed actions would be in accordance with one of the following, as applicable:

- Fairchild Service Bulletin (SB) 226-57-018, Issued: January 28, 1993, Revised: June 3, 1993 (pages 4 through 11 and 13 through 15), Revised: July 1, 1993 (page 12) and Revised: October 25, 1993 (pages 1 through 3);

- Fairchild SB 227-57-005, Issued: December 21, 1992, Revised: June 3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July 1, 1993 (pages 1 and 12); or

- Fairchild Aircraft SB CC7-57-002, Issued: January 28, 1993, Revised: June 3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July 1, 1993 (pages 1 and 12).

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.

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 additionalburden upon the public than was already proposed.

The FAA estimates that 776 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 1 workhour per airplane to accomplish the required visual inspection of the upper wing skin on both wings, 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 $46,560. This figure does not include the cost of any dye penetrant inspections of the rib strap that will be required if the wing skin is found cracked, and it does not include the cost of the repetitive inspections or the optional modification. Incorporating the optional modification terminates the need for the repetitive inspection requirement. The figure above is based upon the assumption that no affected airplane owner/operator has accomplished this inspection-terminating modification.

In addition, the actions required by this AD impose the samecost impact upon U.S. operators as is already required by AD 94-07-10.

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 iscontained 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 USC 106(g), 40113, 44701.

Section 39.13 - [AMENDED]
2. Section 39.13, is amended by removing Airworthiness Directive (AD) 94-07-10, Amendment 39-8868 (59 FR 15329; April 1, 1994), and by adding a new AD to read as follows:

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 93-CE-21-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.

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.