AD 98-20-36 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes

Models named: A300 B2, B4 series, A300-600 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model A300 B2 and B4 series airplanes, certificated in any category, excluding Model A300-600 series airplanes. 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 (j) 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.

Required as indicated, unless accomplished previously. To prevent fatigue-related cracking, which could result in reduced structural integrity of the fuselage, wing, and vertical stabilizer, accomplish the following: (a) For airplanes with serial numbers listed in Airbus Service Bulletin A300-53-127, Revision 4, dated May 10, 1984: Perform a visual inspection to detect cracks in the upper fuselage skin at frame 58 between stringer 5 left and stringer 5 right, in accordance with the Accomplishment Instructions of the service bulletin, and in accordance with the times specified in this paragraph. (1) Perform the initial inspection at the later of the times specified in paragraph (a)(1)(i) or (a)(1)(ii) of this AD. (i) Prior to the accumulation of 18,000 total landings or 18,000 total flight hours, whichever occurs earlier; or [[Page 52581]] (ii) Within one year after September 26, 1986 (the effective date of AD 86-19-02, amendment 39-5396). (2) If no crack is detected, repeat this inspection thereafter at intervals not to exceed 3,000 flight hours. (3) If any crack is detected, prior to further flight, repair it in accordance with Figure 2, ``Inspection and Repair Alternative Chart,'' of the service bulletin. (4) Installation of Airbus Modification 2147 (reference Airbus Service Bulletin A300-53-110, Revision 10, dated April 7, 1986) or Airbus Modification 2526/1693 (reference Airbus Service Bulletin A300-53-128, Revision 5, dated May 10, 1984) constitutes terminating action for the repetitive inspection requirements of paragraph (a)(2) of this AD. (b) For airplanes with serial numbers listed in Airbus Service Bulletin A300-53-101, Revision 7, dated May 10, 1984: Perform a radiographic and ultrasonic inspection to detect cracks in the circumferential fuselage splice plates and stringer couplings, in accordance with the Accomplishment Instructions of the service bulletin, and in accordance with the times specified in this paragraph. (1) Perform the initial inspections at the applicable time specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD: (i) For airplanes on which the actions specified in Airbus Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have been accomplished previously: Inspect prior to the accumulation of 20,000 landings since accomplishment of those actions, or within one year after September 26, 1986, whichever occurs later. (ii) For airplanes on which the actions specified in Airbus Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have not been accomplished: Inspect prior to the accumulation of 18,000 total landings, or within one year after September 26, 1986, whichever occurs later. (2) If no crack is detected, repeat the inspections thereafter at intervals not to exceed 3,000 landings. (3) If any crack is detected, prior to further flight, repair it in accordance with Figures 1 and 2 of the service bulletin. (4) Installation of Airbus Modification 3760 (reference Airbus Service Bulletin A300-53-170, Revision 1, dated April 26, 1982, or Revision 2, dated February 2, 1988) constitutes terminating action for the repetitive inspection requirements of paragraph (b)(2) of this AD. (c) For airplanes with serial numbers listed in Airbus Service Bulletin A300-53-143, Revision 3, dated May 10, 1984: Perform a visual inspection to detect cracks in frame 57A between stringers 15 and 16 (left- and right-hand), and the stringer 5 connection angle at frame 65 (left- and right-hand), in accordance with the Accomplishment Instructions of the service bulletin, and in accordance with the times specified in this paragraph. (1) Perform the initial inspection at the later of the times specified in paragraph (c)(1)(i) or (c)(1)(ii) of this AD: (i) Prior to the accumulation of 20,000 total landings; or (ii) Within one year after September 26, 1986. (2) If no crack is detected, repeat this inspection thereafter at intervals not to exceed 3,000 landings. (3) If any crack is detected, prior to further flight, repair it in accordance with the service bulletin. (4) Installation of Airbus Modification 2643 (reference Airbus Service Bulletin A300-53-132, Revision 4, dated May 10, 1984) constitutes terminating action for the repetitive inspection requirement of paragraph (c)(2) of this AD. (d) For airplanes having serial number 002 through 156 inclusive, on which Airbus Modification 2611 has not been installed: Perform a visual inspection, and liquid penetrant test if applicable, to detect cracks in the web plate and support fitting between frames 30A and 32 at stringer 18, and between stringers 22 and 23 (left- and right-hand), in accordance with Airbus Service Bulletin A300-53-182, Revision 3, dated March 16, 1994, and in accordance with the times specified in this paragraph. (1) Perform the initial inspection at the later of the times specified in paragraph (d)(1)(i) or (d)(1)(ii) of this AD: (i) Prior to the accumulation of 30,000 total landings; or (ii) Within 1,500 landings after the effective date of this AD. (2) If no crack is detected, repeat the inspection at the applicable intervals specified in paragraph (d)(2)(i) or (d)(2)(ii) of this AD. (i) If, at the time of the most recent inspection, the airplane has accumulated fewer than 36,000 total landings, repeat the inspection thereafter at intervals not to exceed 3,000 landings. (ii) If, at the time of the most recent inspection, the airplane has accumulated 36,000 or more total landings, repeat the inspection thereafter at intervals not to exceed 2,000 landings. (3) If any crack is detected in the web plate between frames 30A and 32 at stringer 18, prior to further flight, replace the web plate and support fitting at stringer 18 (left- and right-hand) with a new web plate and support fitting, in accordance with the service bulletin. Accomplishment of this replacement constitutes terminating action for the repetitive inspection requirements for stringer 18 as required by paragraph (d)(2) of this AD. (4) If any crack is detected in the web plate between frame 30A and 32 between stringers 22 and 23, prior to further flight, replace the web plate and support fitting between stringers 22 and 23 (left- and right-hand) with a new web plate and support fitting, in accordance with Airbus Service Bulletin A300-53-182, Revision 3, dated March 16, 1994. Accomplishment of this replacement constitutes terminating action for the repetitive inspection requirements for the subject area between stringers 22 and 23 as required by paragraph (d)(2) of this AD. (5) Terminating action for the repetitive inspection requirements of paragraph (d)(2) of this AD is as follows: (i) Installation of Airbus Modification 1691 (reference Airbus Service Bulletin A300-53-063, Revision 4, dated October 22, 1991) between stringers 22 and 23 constitutes terminating action for the repetitive inspection requirements of paragraph (d)(2) of this AD for that area only. (ii) Replacement of the web plates and support fittings at the level of stringer 18 (left- and right-hand) with a new web plate and support fitting, in accordance with Airbus Service Bulletin A300-53- 182, Revision 3, dated March 16, 1994, constitutes terminating action for the repetitive inspection requirements of paragraph (d)(2) of this AD for that stringer only. (iii) Accomplishment of the actions specified in both paragraph (d)(5)(i) and paragraph (d)(5)(ii) of this AD constitutes terminating action for all repetitive inspection requirements required by paragraph (d)(2) of this AD. (e) For airplanes with serial numbers listed in Airbus Service Bulletin A300-53-112, Revision 2, dated July 20, 1981: Perform a visual inspection to detect cracks of the skin from frame 28 to frame 31 between stringers 29 and 31 (left- and right-hand), in accordance with the Accomplishment Instructions of the service bulletin, and in accordance with the times specified in this paragraph. (1) Perform the initial inspection at the later of the times specified in paragraph (e)(1)(i) or (e)(1)(ii) of this AD: (i) Prior to the accumulation of 24,000 total landings; or (ii) Within one year after September 26, 1986. (2) If no crack is detected, repeat the inspection at the applicable intervals specified in paragraph (e)(2)(i) or (e)(2)(ii) of this AD: (i) If, at the time of the most recent inspection, the airplane has accumulated fewer than 36,000 total landings, repeat the inspection thereafter at intervals not to exceed 6,000 landings. (ii) If, at the time of the most recent inspection, the airplane has accumulated 36,000 or more total landings, repeat the inspection thereafter at intervals not to exceed 3,000 landings. (3) If any crack is found, prior to further flight, install Airbus Modification 1358 in accordance with Airbus Service Bulletin A300-53-027, Revision 4, dated January 30, 1981. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of paragraph (e)(2) of this AD. (4) Installation of Airbus Modification 1358 (reference Airbus Service Bulletin A300-53-027, Revision 4, dated January 30, 1981) constitutes terminating action for the repetitive inspection requirements of paragraph (e)(2) of this AD. (f) For airplanes with serial numbers listed in Airbus Service Bulletin A300-53-100, Revision 1, dated May 10, 1984: Perform an internal and external visual inspection to detect cracks of the longitudinal joint at stringer 51 (left- and right-hand) between frames 72 and 80, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-100, Revision 1, dated May 10, 1984, or Revision 2, dated July 11, 1995, and in accordance with the times specified in this paragraph. [[Page 52582]] (1) Perform the initial inspection at the later of the times specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD: (i) Prior to the accumulation of 12,000 total landings or 15,000 total flight hours, whichever occurs earlier; or (ii) Within one year after September 26, 1986. (2) If no crack is found, repeat the internal inspection thereafter at intervals not to exceed 1,500 flight hours, and repeat the external inspection thereafter at intervals not to exceed 12,000 flight hours. (3) If any crack is detected, prior to further flight, repair it in accordance with the service bulletin. (4) Installation of Airbus Modification 1421 (reference Airbus Service Bulletin A300-53-033, Revision 3, dated May 10, 1984) constitutes terminating action for the repetitive inspection requirements of paragraph (f)(2) of this AD. (g) For airplanes with serial numbers listed in Airbus Service Bulletin A300-55-026, Revision 3, dated May 10, 1984: Perform a visual inspection of the 6 vertical stabilizer attachment fittings for cracks, which initiate from the rivet holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-55- 026, Revision 3, dated May 10, 1984, or Revision 4, dated February 16, 1988, and in accordance with the times specified in this paragraph. (1) Perform the initial inspection at the later of the times specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD: (i) Prior to the accumulation of 20,000 total landings or 20,000 total flight hours, whichever occurs earlier; or (ii) Within one year after September 26, 1986, whichever occurs earlier. (2) If no crack is detected, repeat the inspection thereafter at intervals not to exceed 1,500 landings. (3) If any crack is detected, prior to further flight, repair it in accordance with the service bulletin. (4) Installation of Airbus Modification 3172 (reference Airbus Service Bulletin A300-55-024, Revision 4, dated May 25, 1984) constitutes terminating action for the repetitive inspection requirements of paragraph (g)(2) of this AD. (h) For airplanes with serial numbers listed in Airbus Service Bulletin A300-57-109, Revision 1, dated July 10, 1982: Perform a visual inspection to detect cracks in the landing angle attached to the outboard side of the wing leading edge at nose rib 8 (left- and right-hand), in accordance with the Accomplishment Instructions of the service bulletin, and in accordance with the times specified in this paragraph. (1) Perform the initial inspection at the later of the times specified in paragraph (h)(1)(i) or (h)(1)(ii): (i) Prior to the accumulation of 15,000 total landings; or (ii) Within one year after September 26, 1986. (2) If no crack is detected, repeat the inspection thereafter at intervals not to exceed 3,000 landings. (3) If any crack is detected, within the next 1,000 landings following crack detection, install Airbus Modification 1307 in accordance with Airbus Service Bulletin A300-57-026, Revision 3, dated October 21, 1982, or Revision 4, dated December 12, 1985. (4) Installation of Airbus Modification 1307 (reference Airbus Service Bulletin A300-57-026, Revision 3, dated October 21, 1982, or Revision 4, dated December 12, 1985) constitutes terminating action for the repetitive inspection requirements of paragraph (h)(2) of this AD. (i) 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. (j) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (k) The actions shall be done in accordance with the following Airbus service bulletins, as applicable, which contain the specified list of effective pages: -------------------------------------------------------------------------------------------------------------------------------------------------------- Service bulletin referenced and date Page No. Revision level shown on page Date shown on page -------------------------------------------------------------------------------------------------------------------------------------------------------- A300-53-127, Revision 4, May 10, 1-5, 11, 12............................. 4...................................... May 10, 1984. 1984. 6-10, 13................................ Original............................... April 17, 1980. A300-53-101, Revision 7, May 10, 1, 2.................................... 7...................................... May 10, 1984. 1984. 3, 7.................................... 5...................................... September 10, 1982. 4-6, 8, 9............................... 4...................................... June 15, 1981. A300-53-143, Revision 3, May 10, 1, 2, 5, 8.............................. 3...................................... May 10, 1984. 1984. 3, 4, 6, 7, 9........................... Original............................... September 28, 1981. A300-53-182, Revision 3, March 16, 1-20.................................... 3...................................... March 16, 1994. 1994. A300-53-112, Revision 2, July 20, 1....................................... 2...................................... July 20, 1981. 1981. 2, 3.................................... Original............................... December 28, 1979. A300-53-027, Revision 4, January 1, 15................................... 4...................................... January 30, 1981. 30, 1981. 2....................................... 3...................................... October 23, 1979. 3-14.................................... Original............................... March 14, 1976. A300-53-100, Revision 1, May 10, 1-4..................................... 1...................................... May 10, 1984. 1984. 5-9..................................... Original............................... September 14, 1979. A300-53-100, Revision 2, July 11, 1, 4.................................... 2...................................... July 11, 1995. 1995. 2, 3.................................... 1...................................... May 10, 1984. 5-9..................................... Original............................... September 14, 1979. A300-55-026, Revision 3, May 10, 1, 7.................................... 3...................................... May 10, 1984. 1984. 2-6, 8, 9............................... 2...................................... October 10, 1981. A300-55-026, Revision 4, February 1-5..................................... 4...................................... February 16, 1988. 16, 1988. 6, 8, 9................................. 2...................................... October 10, 1981. 7....................................... 3...................................... May 10, 1984. A300-57-109, Revision 1, July 10, 1-4..................................... 1...................................... July 10, 1982. 1982. A300-57-026, Revision 3, October 1, 2.................................... 3...................................... October 21, 1982. 21, 1982. 3, 5-17................................. Original............................... August 2, 1976. 4....................................... 1...................................... December 2, 1976. A300-57-026, Revision 4, December 1....................................... 4...................................... December 12, 1985. 12, 1985. 2....................................... 3...................................... October 21, 1982. 3, 5-17................................. Original............................... August 2, 1976. 4....................................... 1...................................... December 2, 1976. -------------------------------------------------------------------------------------------------------------------------------------------------------- [[Page 52583]] 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 3: The subject of this AD is addressed in French airworthiness directive 83-102-053(B)R2, dated March 2, 1994. (l) This amendment becomes effective on November 5, 1998. Issued in Renton, Washington, on September 22, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-25953 Filed 9-30-98; 8:45 am] BILLING CODE 4910-13-P