| AD Number | 96-11-05 | Status | Superseded |
| Effective Date | June 28, 1996 | Issue Date | Not specified |
| Docket Number | 95-NM-85-AD | Amendment | 39-9630 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 [61 FR 26091 NO. 102 05/24/96] | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Airbus Industrie Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus |
| Model(s) | A300 Model B2-1A A300 Model B2-1C A300 Model B2-203 A300 Model B2K-3C A300 Model B4-103 A300 Model B4-203 A300 Model B4-2C A300 Model B4-600 Series A300 Model B4-600R Series A300 Model F4-600R Series A300B4-601 A300B4-603 A300B4-605R A300B4-620 A300B4-622R A300F4-605R A300F4-622R A310-203 A310-221 A310-222 A310-304 A310-322 A310-324 A310-325 A310 Model 325 |
| Superseded By | 2000-10-18 |
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes, that requires inspections to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, and repair, if necessary. This amendment is prompted by reports that fatigue cracking has been found on the lower spar of the pylon. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
Final rule.
96-11-05 AIRBUS INDUSTRIE: Amendment 39-9630. Docket 95-NM-85-AD.
Applicability: Model A300, A300-600, and A310 series airplanes; as listed in Airbus Industrie Service Bulletins A300-54-0073, A300-54-6014, and A310-54-2017, all Revision 1, all dated March 28, 1994; certificated in any category.
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 (k) 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 as indicated, unless accomplished previously.
To prevent reduced structural integrity of the lower spar, accomplish the following:
(a) For Model A300 series airplanes equipped with General Electric CF6-50C engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 10,900 total landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 6,700 landings.
(2) If any crack is found that is less than 35 mm, prior to further flight, stop- drill thecrack in accordance with the procedures specified in Section 51-41-10 of the Structural Repair Manual (SRM). Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 17,900 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (a)(2) of this AD thereafter at intervals not to exceed 15,000 landings.
(ii) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(b) For Model A300 series airplanes equipped with General Electric CF6-50C engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 30,300 landings since installation of the modification, or within 500 landings after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 21,300 landings.
(2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(c) For Model A300 series airplanes equipped with Pratt & Whitney JT9D-59A engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 8,600 total landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 5,700 landings.
(2) If any crack is found that is less than 35 mm, prior to further flight, stop- drill the crack in accordance with the procedures specified in Section 51-41-10 of the SRM. Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 14,200 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (c)(2) of this AD thereafter at intervals not to exceed 12,800 landings.
(ii) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(d) For Model A300 series airplanes equipped with Pratt & Whitney JT9D-59A engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-0080, Revision 1, dated January 16, 1995: Prior to the accumulation of 24,000 landings since installation of the modification, or within 500 landings after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 18,200 landings.
(2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(e) For Model A300-600 series airplanes equipped with General Electric CF6-80C2 engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 9,400 total landings, or within 500 landings after the effective date of this AD, whichever occurslater, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 6,100 landings.
(2) If any crack is found that is less than or equal to 35 mm, prior to further flight, stop-drill the crack in accordance with the procedures specified in Section 51-41-10 of the SRM. Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 15,600 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (e)(2) of this AD thereafter at intervals not to exceed 13,600 landings.
(ii) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(f) For Model A300-600 series airplanes equipped with General Electric CF6-80C2 engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 26,400 landings since installation of the modification, or within 500 landings after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 19,400 landings.
(2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(g) For Model A300-600 series airplanes equipped with Pratt & Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have not been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 5,700 total landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 4,400 landings.
(2) If any crack is found that is less than 35 mm, prior to further flight, stop- drill the crack in accordance with the procedures specified in Section 51-41-10 of the SRM. Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 10,100 landings after accomplishing the repair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (g)(2) of this AD thereafter at intervals not to exceed 10,000 landings.
(ii) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(h) For Model A300-600 series airplanes equipped with Pratt & Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have been modified in accordance with Airbus Industrie Service Bulletin A300-54-6020, dated February 22, 1994: Prior to the accumulation of 17,000 landings since installation of the modification, or within 500 landings after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the eddy current inspection thereafter at intervals not to exceed 14,500 landings.
(2) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, StandardizationBranch, ANM-113.
(i) For Model A310 series airplanes equipped with General Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney PW4000 engines: Prior to the accumulation of 36,700 total landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, in accordance with Airbus Industrie Service Bulletin A310-54-2017, Revision 1, dated March 28, 1994.
(1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 15,000 landings.
(2) If any crack is found that is less than 35 mm, prior to further flight, stop- drill the crack in accordance with the procedures specified in Section 51-41-10 of the SRM. Thereafter, prior to the accumulation of 250 landings after crack discovery, repair in accordance with the service bulletin. Prior to the accumulation of 40,000 landings after accomplishing therepair, perform an eddy current inspection to detect cracks at the stiffener ends, ribs 6 and 7, at the edge of the holes made during the repair and on the fasteners located at the edge of the doubler, in accordance with the service bulletin.
(i) If no crack is found, repeat the inspection required by paragraph (i)(2) of this AD thereafter at intervals not to exceed 33,000 landings.
(ii) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(3) If any crack is found that is greater than or equal to 35 mm, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113.
(j) For Model A310 series airplanes equipped with General Electric CF6-80C2, or Pratt & Whitney JT9D-7R4, or Pratt & Whitney PW4000 engines: Accomplishment of the modification specified in Airbus Industrie Service Bulletin A310-54-2023, dated October 15, 1993, constitutes terminating action for the inspections required by paragraph (i) of this AD.
(k) 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, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(l) 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.
(m) The actions shall be done in accordance with the following Airbus Industrie service bulletins, whichcontain the specified effective pages:
Service Bulletin
Referenced and Date
Revision Level
Page Number
Date
Shown on Page
Shown on Page
A300-54-0073,
Revision 1,
March 28, 1994
1, 5
2-4, 6-36
1
Original
March 28, 1994
October 15, 1993
A300-54-6014,
Revision 1,
March 28, 1994
1-4, 13
5-12, 14-44
1
Original
March 28, 1994
October 15, 1993
A310-54-2017,
Revision 1,
March 28, 1994
1, 5
2-4, 6-48
1
Original
March 28, 1994
October 15, 1993
A310-54-2023,
October 15, 1993
1-38
Original
October 15, 1993
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.
(n) This amendment becomes effective on June 28, 1996.
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes was published in the Federal Register on March 6, 1996 (61 FR 8892). That action proposed to require inspections to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, and repair, if necessary.
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.
Support for the Proposal
One commenter supports the proposed rule.
Request to Revise Compliance Threshold for Inspection
One commenter requests that the inspection threshold specified in paragraph (h) of the proposal be revised from 14,500 landings to 17,000 landings for consistency with the threshold provided in Airbus Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
The FAA concurs with the commenter's request. The FAA's intent is that the inspection threshold and repetitive inspection interval specified in paragraph (h) of this AD parallel the threshold and interval recommended in the Airbus service bulletin. The FAA has revised paragraph (h) of the final rule to specify an inspection threshold of 17,000 landings. The repetitive inspection interval of 14,500 landings, which was recommended in the Airbus service bulletin, remains unchanged in this final rule.
Correction of Service Bulletin Number
The FAA has revised the reference to a service bulletin number that appeared in paragraph (i) of the proposed AD as Airbus Industrie Service Bulletin A300-54-2017. The correct service bulletin number is A310-54-2017.
Conclusion
After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.
Cost Impact
The FAA estimates that 99 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $47,520, or $480 per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.
Should an operator of a Model A300 series airplane elect to accomplish the optional modification that is provided by this AD action, it will take approximately 100 work hours to accomplish, at an average labor rate of $60 per work hour. The cost of required parts will be approximately $1,500 per airplane. Based on these figures, the cost impact of the optional modification for Model A300 series airplanes is estimated to be $7,500 per airplane.
Should an operator of a Model A300-600 or A310 series airplane elect to accomplish the optional modification that is provided by this AD action, it will take approximately 110 work hours to accomplish, at an average labor rate of $60 per work hour. The cost of required parts will be approximately $1,500 per airplane. Based on these figures, the cost impact of the optional modification for Model A300-600 and A310 series airplanes is estimated to be $8,100 per airplane.
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 final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from 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.
39.13 - [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive:
The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Tim Backman, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1149.