AD 98-16-05

This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, and repair, if necessary. This amendment also requires inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, this amendment provides for optional terminating action for certain inspections. This amendment is prompted by reports indicating that corrosion was found behind the scuff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. The actions specified by this AD are intended to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings.

Final rule.

98-16-05 AIRBUS INDUSTRIE: Amendment 39-10680. Docket 96-NM-42-AD.

Applicability: All Model A300-600 series airplanes, 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 (i) 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 detect and correct corrosion behind the scuff plates at exit and cargo doors, and fatigue cracking in certain fastener holes located in adjacent structure, which could result in reduced structural integrity of the door surroundings, accomplish the following:

(a) Perform an initial inspection of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A300-53-6011, Revision 3, dated February 4, 1991; at the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD. If any crack or corrosion is found during this inspection, prior to further flight, repair in accordance with the service bulletin. Accomplishment of this inspection is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed.

(1) For airplanes on which Modification 5382S6526 (for forward doors) and Modification 5382D4741 (for all other doors) have been accomplishedprior to delivery of the airplane: Perform the initial inspection within 9 years since date of manufacture, or within 1 year after the effective date of this AD, whichever occurs later.

(2) For airplanes on which Modification 5382S6526 (for forward doors) and Modification 5382D4741 (for all other doors) have not been accomplished; and on which the procedures described in Airbus Service Information Letter (SIL) A300-53-033, Revision 2 (for all doors), dated November 23, 1984, have been accomplished: Perform the initial inspection within 5 years after accomplishment of the procedures described in the SIL, or within 1 year after the effective date of this AD, whichever occurs later.

(3) For airplanes on which Modification 5382S6526 (for forward doors), Modification 5382D4741 (for all other doors), and the procedures described in Airbus SIL A300-53-033, Revision 2, dated November 23, 1984, have not been accomplished: Perform the initial inspection within 4 years since date of manufacture, or within 1 year after the effective date of this AD, whichever occurs later.

(b) Perform repetitive inspections of the areas behind the scuff plates below the passenger/crew doors and bulk cargo door to detect cracks and corrosion, in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991; at the applicable times specified in paragraphs (b)(1) and (b)(2) of this AD. Accomplishment of these inspections is not required for the mid and aft passenger/crew doors if a steel doubler that covers the entire inspection area is installed.

(1) For the forward and mid passenger/crew doors, the bulk cargo door, and the aft passenger/crew doors, except the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler: Perform the first inspection within 5 years after accomplishing the inspection required by paragraph (a) of this AD; and repeat the inspection thereafter at intervals not to exceed 5 years.

(2) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors: Perform the first inspection within 5 years or 6,000 landings after accomplishing the inspection required by paragraph (a) of this AD, whichever occurs first; and repeat the inspection thereafter at intervals not to exceed 5 years or 6,000 landings, whichever occurs first.

(c) If any crack is found during any inspection required by paragraph (b) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991. Thereafter, perform the repetitive inspections required by paragraph (b) of this AD at the applicable times specified in paragraphs (b)(1) and (b)(2) of this AD.

(d) If corrosion is found during any inspection required by paragraph (b) of this AD, prior to further flight, repair in accordance with Airbus Service Bulletin A300-53-6022, dated February 4, 1991. Thereafter, perform the repetitive inspections required by paragraph (b) of this AD at the applicable times specified in paragraphs (d)(1) or (d)(2) of this AD.

(1) For the upper and lower edges of the fail-safe ring and the upper edges of the corner doubler of the aft passenger/crew doors, and for the mid passenger/crew door: Inspect at intervals not to exceed 5 years or 5,000 landings, whichever occurs first.

(2) For the forward passenger/crew doors and bulk cargo doors: Inspect at intervals not to exceed 5 years.

(e) Perform an inspection to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the left- and right-hand forward, mid, and aft passenger/crew door structures, in accordance with Airbus Service Bulletin A300-53-6018, Revision 1, dated April 29, 1992, and at the applicable time specified in paragraph (e)(1), (e)(2), (e)(3), or (e)(4) of this AD.

(1) For the upper corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within2,000 landings after the effective date of this AD, whichever occurs later.

(2) For the lower corners of the forward doors: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after the effective date of this AD, whichever occurs later.

(3) For the upper and lower corners of the mid doors: Inspect prior to the accumulation of 20,000 total landings, or within 2,000 landings after the effective date of this AD, whichever occurs later.

(4) For the upper and lower corners of the aft doors, and for the parts underneath the corners of the upper door frames: Inspect prior to the accumulation of 20,000 total landings, or within 4,000 landings after the effective date of this AD, whichever occurs later.

(f) Repeat the inspections required by paragraph (e) of this AD at the applicable times specified in paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(5).

(1) For the upper corners of the forward doors: Inspect at intervals not to exceed6,000 landings.

(2) For the lower corners of the forward doors: Inspect at intervals not to exceed 10,000 landings.

(3) For the upper and lower corners of the mid and aft doors on which an inspection required by paragraph (e) of this AD was accomplished using a Roto test technique: Inspect at intervals not to exceed 8,000 landings.

(4) For the upper and lower corners of the mid and aft doors on which an inspection required by paragraph (e) of this AD was accomplished using an X-ray technique: Inspect at intervals not to exceed 3,500 landings.

(5) For the areas around the fasteners in the vicinity of stringer 12 on the upper door frames of the aft doors on which an inspection required by paragraph (e) of this AD was accomplished using a visual technique: Inspect at intervals not to exceed 6,900 landings.

(g) If any crack is found during any inspection required by paragraph (e) or (f) of this AD: Prior to further flight, accomplish the requirement of paragraph (g)(1) or (g)(2) of this AD, as applicable.

(1) If any crack is found, and the crack can be eliminated using the method specified in Airbus Service Bulletin A300-53-6018, Revision 1, dated April 29, 1992: Prior to further flight, repair the crack in accordance with that service bulletin.

(2) If any crack is found, and the crack cannot be eliminated using the method specified in Airbus Service Bulletin A300-53-6018, Revision 1, dated April 29, 1992: Prior to further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.

(h) Modification of the passenger/crew door frames in accordance with Airbus Service Bulletin A300-53-6002, Revision 3, dated February 22, 1992, constitutes terminating action for the repetitive inspections required by paragraph (f) of this AD.

(i) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety maybe used if approved by the Manager, International Branch, ANM-116. 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.

(j) 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.

(k) Except as provided by paragraph (g)(2) of this AD, the actions shall be done in accordance with the following Airbus service bulletins, which contain the specified list of effective pages:

Service Bulletin
Referenced and Date
Page Number
Shown on Page
Revision Level
Shown on Page
Date
Shown on Page
A300-53-6022, February 4, 1991
1-15
Original
February 4, 1991
A300-53-6002,
Revision 3,
February 22, 1992
1-2, 56, 67-68

3-26, 31-55, 57-66

27-30
3

1

2
February 22, 1992

February 4, 1991

May 6, 1991
A300-53-6011,
Revision 3,
February 4, 1991
1-17
3
February 4, 1991
A300-53-6018,
Revision 1,
April 29, 1992
1, 3-4, 9-14, 17, 24,
31-34, 36, 50

2, 5-8, 15-16, 18-23,
25-30, 35, 37-49, 51-65
1

Original
April 29, 1992

February 4, 1991

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 91-132- 124(B), dated June 26, 1991, as amended by a Correction, dated August 21, 1991.

(l) This amendment becomes effective on September 4, 1998.

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 all Airbus Model A300-600 series airplanes was published in the Federal Register on January 29, 1997 (62 FR 4211). That action proposed to require inspections of the lower door surrounding structure to detect cracks and corrosion, and repair, if necessary. That action also proposed to require inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, that action proposed to provide for optional terminating action for certain inspections.

Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.

Clarification of Terminology
One commenter expresses no objection to the proposed rule, but requests that certain terminology in the proposed AD be changed for the sake of clarity. The commenter states that the title is not complete, since it refers only to inspections of the lower door structure, while inspection of the upper door corners is also required. The FAA concurs. The FAA infers that the commenter is referring to the Summary section of the proposed AD, which states that "this proposal would require inspections of the lower door surrounding structure." However, in all other sections of the proposed AD, the area to be inspected is described as "the areas behind the scuff plates below the passenger/crew doors and bulk cargo door," in accordance with procedures described in Airbus Service Bulletin A300-53-6011, Revision 3, dated February 4, 1991. To avoid confusion regarding the area to be inspected for cracks and corrosion, the Summary section of the final rule has been changed to correspond to the terminology used elsewhere throughout the AD.

The same commenter requests that paragraphs (b) and (d) of the proposed AD be changed to refer to the "fail-safe ring and corner strap," rather than the existing terminology of "fail-safe ring and corner doubler." The commenter states that the term "corner strap" is used in Airbus Service Bulletin A300-53-6022, dated February 4, 1991, and in other maintenance documents, rather than "corner doubler." The FAA does not concur. The FAA has verified that the referenced service bulletin uses the term "corner doubler" to identify the affected part. Therefore, the usage of this terminology has been retained in the final rule.

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 change described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact
The FAA estimates that 35 airplanes of U.S. registry will be affected by this AD, that it will take approximately 700 work hours per airplane to accomplish the required inspections (including access and close-up), and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the required AD on U.S. operators is estimated to be $1,470,000, or $42,000 per airplane.

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 elect to accomplish the optional terminating action that is provided by this AD action, it will take approximately 147 work hours to accomplish it, at an average labor rate of $60 per work hour. The cost of required parts will be approximately $5,581 per airplane. Based on these figures, the cost impact of the optional terminating action will be $14,401 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 U.S.C. 106(g), 40113, 44701.
39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive: