90-22-06: Inspect Horizontal Stabilizer

90-22-06 AIRBUS INDUSTRIE: Amendment 39-6775. Docket No. 90-NM-12-AD. Applicability: All Model A300-B2, A300-B2K, and A300-B4 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the horizontal stabilizer, accomplish the following: A. Perform a visual inspection of the upper skin and spar web joining parts of the trimmable horizontal stabilizer (THS), in accordance with either the "preferred" or "alternative" method as described in Airbus Industrie Service Bulletin A300-55-0035, dated September 11, 1989, as follows: 1. For airplanes that have accumulated less than 11,000 landings, perform the initial inspection within 1,000 landings after the effective date of this AD, or prior to the accumulation of 11,400 landings, whichever occurs first. 2. For airplanes that have accumulated 11,000 or more landings, but less than 16,000 landings, perform the initial inspection within 400 landings after the effective date of this AD, or prior to the accumulation of 16,200 landings, whichever occurs first. 3. For airplanes that have accumulated 16,000 or more landings, perform the initial inspection within 200 landings after the effective date of this AD. B. If the "preferred inspection method" (THS support fitting removed), as specified in Airbus Industrie Service Bulletin A300-55-0035, dated September 11, 1989, is used to accomplish the inspection required by paragraph A. of this AD, proceed as follows: 1. If a crack indication is found in the top integral skin, accomplish the following: a. If the crack extends to the outer box top skin, repair prior to further flight in a manner approved by the Manager, Standardization Branch, ANM-113. Perform repetitive inspections at intervals approved by the Manager, Standardization Branch, ANM-113. b. If the crack does not extend to the outer box top skin, and there is no crackin the joining part, prior to further flight, accomplish either subparagraph (1) or (2), below: (1) Revise the FAA-approved Airplane Flight Manual (AFM) to impose the operational limits specified in the service bulletin for Vmo/Mmo and CCI, and install placards showing these limits in a prominent position in the cockpit until a permanent repair is made. Thereafter, repeat the inspection every 350 landings. Stop drill the ends of the crack and cold-expand the stop drill holes when the crack length is between the limits specified in the service bulletin; or (2) Repair in accordance with the service bulletin. After repair, conduct repetitive high frequency eddy current (HFEC) inspections of the visible area of the integral top skin and the reinforcing plate web finger areas at intervals not to exceed 7,500 landings. c. If the crack does not extend to the outer box top skin, and a crack is detected in the joining part, repair prior to further flight, in accordance withthe service bulletin. After repair, conduct repetitive HFEC inspections at intervals not to exceed 7,500 landings, in accordance with the service bulletin. 2. If no crack indication is found in the top integral skin, accomplish the following: a. If no crack indication is found in the joining part, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 6,000 landings. b. If a crack indication is found in the joining part, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113. After repair, conduct repetitive HFEC inspections at intervals not to exceed 7,500 landings, in accordance with the service bulletin. C. If the "alternative inspection method" (THS support fitting installed), as specified in Airbus Industrie Service Bulletin A300-55-0035, dated September 11, 1989, is used to accomplish the inspection required by paragraph A. of this AD, proceed as follows: 1. If a crack indication is found in the top integral skin, accomplish the following: a. If the crack extends to the outer box top skin, repair prior to further flight in a manner approved by the Manager, Standardization Branch, ANM-113. b. If the crack does not extend to the outer box top skin, remove the THS support fitting and inspect the joining part using an HFEC inspection technique, in accordance with the service bulletin. (1) If the joining part is cracked, repair prior to further flight, in accordance with the service bulletin. After repair, conduct repetitive HFEC inspections at intervals not to exceed 7,500 landings, in accordance with the service bulletin. (2) If the joining part is not cracked, prior to further flight, accomplish either subparagraph (a) or (b), below: (a) Revise the FAA-approved Airplane Flight Manual (AFM) to impose the operational limits specified in the service bulletin for Vmo/Mmo and CCI, and install placards showing these limits in a prominent position in the cockpit until permanent repair is made. Thereafter, repeat the inspection every 350 landings. Stop drill the ends of the crack and cold-expand the stop drill holes when the crack length is between the limits specified in the service bulletin; or (b) Repair in accordance with the service bulletin. After repair, conduct repetitive HFEC inspections at intervals not to exceed 7,500 landings, in accordance with the service bulletin. 2. If no crack indication is found in the top integral skin, repeat the inspection required by paragraph A. of this AD at intervals not to exceed 1,700 flights. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6775, AD 90-22-06) becomes effective on November 21, 1990.