AD 2011-17-05

We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

* * * [C]racks * * * in sections 13 to 18 of the fuselage between
rivets of longitudinal lap joints between frames 18 and 80 which could affect the structural integrity of the fuselage if not corrected.
* * * * *

We are issuing this AD to require actions to correct the unsafe condition on these products.

Final rule.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0 2. The FAA amends Sec. 39.13 by removing Amendment 39-6448 (55 FR 261, January 4, 1990) and adding the following new AD:

2011-17-05 Airbus: Amendment 39-16769. Docket No. FAA-2011-0389; Directorate Identifier 2007-NM-189-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective November 16, 2011.

Affected ADs

(b) This AD supersedes AD 90-01-10, Amendment 39-6448 (55 FR 261, January 4, 1990).

Applicability

(c) This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; certificated in any category; serial numbers 0003 through 0156 inclusive.

Subject

(d) Air Transport Association (ATA) of America Code 53: Fuselage.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:
This Airworthiness Directive (AD) is issued in order to prevent cracks development in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames 18 and 80 which could affect the structural integrity of the fuselage if not corrected.
This new AD:

--Retains the requirements of DGAC AD 1989-061-092(B)R4 [which corresponds to FAA AD 90-10-10 (55 FR 261, January 4, 1990)], which is cancelled; --Takes into account a new inspection program as detailed in AIRBUS Service Bulletins (SB) A300-53-0211 Revision 7, which will allow A300 aircraft to reach the Limit of Validity (LOV).

This AD has been republished to correctly refer to SB A300-53- 0211 in Note 2 of the Compliance section.
The inspection program consists of repetitive detailed inspections for disbonding and cracking of the fuselage inner doubler; eddy current and ultrasonic inspections of the fuselage longitudinal lap joints for cracking; and repair if necessary (i.e., repairing any cracking or disbonding, or contacting Airbus for repair instructions and doing the repair).

Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Repetitive Inspections of ``Special Areas'' and Repair or Modification if Necessary

(g) For airplanes on which an eddy current inspection of the ``special'' areas of the longitudinal lap joints has not been done as of the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300-53-0211: Prior to the accumulation of 24,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later; do an eddy current inspection for cracking of the ``special'' areas of the longitudinal lap joints, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 1 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ``Special'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

[[Page 63179]]

Table 1--Repetitive Intervals for Inspecting Special Areas of the Longitudinal Lap Joints ----------------------------------------------------------------------------------------------------------------
Inspect special area--
For airplanes-- Repeat at intervals not to exceed-- ---------------------------------------------------------------------------------------------------------------- All................................. STGR5 LH and RH (FR54 3,600 flight cycles.
through FR58). All................................. STGR22 LH and RH 2,700 flight cycles.
(FR26 through FR40). All................................. STGR22 RH (FR58 3,000 flight cycles.
through FR65). All................................. STGR31 LH/RH (FR26 3,000 flight cycles.
through FR39). MSN 0003............................ STGR31 LH/RH (FR54 3,600 flight cycles.
through FR58). ----------------------------------------------------------------------------------------------------------------

(h) For airplanes on which an eddy current inspection of the ``special'' areas of the longitudinal lap joints has been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211; except for airplanes on which a repair or modification of the ``special'' areas has been done in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: Do the next inspection of the ``special'' areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 2 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07,dated December 1, 2006, and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ``Special'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
(1) Within 6,000 flight cycles after doing the last inspection of the ``special'' areas of the longitudinal lap joints, in accordance with Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
(2) Within the applicable intervals specified in Table 2 of this AD, or within 60 days after the effective date of this AD, whichever occurs later.

Table 2--Repetitive Intervals for Inspecting Special Areas of the Longitudinal Lap Joints ----------------------------------------------------------------------------------------------------------------
Inspect special area--
For airplanes-- Repeat at intervals not to exceed-- ---------------------------------------------------------------------------------------------------------------- All................................. STGR5 LH and RH (FR54 3,600 flight cycles.
through FR58). All................................. STGR22 LH and RH 2,700 flight cycles.
(FR26 through FR40). All................................. STGR22 RH (FR58 3,000 flight cycles.
through FR65). All................................. STGR31 LH/RH (FR26 3,000 flight cycles.
through FR39). MSN 0003............................ STGR31 LH/RH (FR54 3,600 flight cycles.
through FR58). ----------------------------------------------------------------------------------------------------------------

Repetitive Inspections of ``Standard Areas'' and Repair or Modification if Necessary

(i) For airplanes on which an eddy current inspection of the ``standard'' areas of the longitudinal lap joints has not been done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: At the applicable time specified in Tables 3 and 4 of this AD, do an eddy current inspection for cracking of the longitudinal lap joints in the ``standard'' areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Repeat the inspection thereafter at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the applicable area specified in Tables 3 and 4 of this AD. ``Standard'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

Table 3--Initial Compliance Times and Repetitive Intervals for Inspecting Standard Areas of the Longitudinal Lap
Joints ----------------------------------------------------------------------------------------------------------------
Before the
For airplanes-- accumulation Inspect Repeat at intervals not to exceed--
of-- standard area-- ---------------------------------------------------------------------------------------------------------------- All........................... 32,000 total STGR5, 13, 22 3,600 flight cycles.
flight cycles. LH and RH,
STGR31 LH
(FR18 through
FR26). All........................... 32,000 total STGR27 RH, 8,000 flight cycles.
flight cycles. STGR39 RH
(FR18 through
FR20A, FR25A,
FR26). All........................... 32,000 total STGR43 LH, 5,700 flight cycles.
flight cycles. STGR46 RH,
STGR51 LH
(FR19 through
FR26). All...........................32,000 total STGR5 LH/RH 3,000 flight cycles.
flight cycles. (FR26 through
FR40); STGR11
LH/RH (FR27
through FR32);
STGR13 LH/RH
(FR 26 through
FR28, FR31
through FR40);
STGR27 LH/RH
(FR 27 through
FR32); STGR43
LH/RH (FR 26
through FR39);
STGR49 RH
(FR26 through
FR39). All........................... 32,000 total STGR47 LH (FR26 5,700 flight cycles.
flight cycles. through FR39). All........................... 32,000 total STGR5, 13, 22 5,000 flight cycles.
flight cycles. LH/RH (FR40
through FR54).

[[Page 63180]]

All except MSN 0003........... 32,000 total STGR13, 44, 52 3,600 flight cycles.
flight cycles. LH/RH (FR54
through FR58);
STGR22 LH/RH
(FR54, FR55);
STGR31 LH/RH
(FR54 through
FR58). ----------------------------------------------------------------------------------------------------------------

(j) For airplanes on which an eddy current inspection of the ``standard'' areas of the longitudinal lap joints has been done as of the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211; except for airplanes on which a repair or modification of the ``standard areas'' has been done in accordance with Airbus Mandatory Service Bulletin A300-53-0211: Do the next inspection of the ``standard'' areas of the longitudinal lap joints at the earlier of the times specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. Thereafter, if no cracking is found, repeat the inspection at the applicable intervals specified in Tables 3 and 4 of this AD. If any crack is found during any inspection required by this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006, and do the applicable inspection of the repaired or modified area in accordance with paragraph (k) of this AD. ``Standard'' areas of the longitudinal lap joints are defined in Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

Table 4--Initial Compliance Times and Repetitive Intervals for Inspecting Additional Standard Areas of the
Longitudinal Lap Joints ----------------------------------------------------------------------------------------------------------------
Before the
For airplanes-- accumulation Inspect Repeat at intervals not to exceed--
of-- standard area-- ---------------------------------------------------------------------------------------------------------------- Pre-Mod 1398.................. 32,000 total STGR5, 13 LH/RH 2,700 flight cycles.
flight cycles. 22 LH (FR58
through FR65);
STGR31 LH
(FR58 throughFR72); STGR31
RH (FR65
through FR72). All........................... 32,000 total STGR27 RH, 8,000 flight cycles.
flight cycles. STGR39 RH
(FR58, FR59A,
FR63A through
FR65). Post-Mod 1398................. 32,000 total STGR5, 13 LH/RH 3,000 flight cycles.
flight cycles. 22 LH (FR58
through FR65);
STGR31 LH
(FR58 through
FR72); STGR 31
RH (FR65
through FR72). Pre-Mod 1398.................. 32,000 total STGR5, 13, 22 2,300 flight cycles.
flight cycles. LH/RH (FR65
through FR72). Post-Mod 1398................. 32,000 total STGR5, 13, 22 3,000 flight cycles.
flight cycles. LH/RH (FR65
through FR72). All........................... 32,000 total STGR44 LH (FR58 3,000 flight cycles.
flight cycles. through FR72);
STGR52 LH/RH
(FR58 through
FR65); STGR47
RH (FR58
through FR72);
STGR57 LH
(FR65 through
FR72). All........................... 24,000 total STGR22 RH (FR583,000 flight cycles.
flight cycles. through FR65). All........................... 32,000 total STGR6 LH/RH 3,000 flight cycles.
flight cycles. (FR72 through
FR80); STGR24
LH/RH (FR76
through FR80). All........................... 32,000 total STRG17 LH/RH 5,700 flight cycles.
flight cycles. (FR76 through
FR80); STGR29
LH/RH (FR72
through FR76);
STGR35 LH/RH
(FR72 through
FR80). All........................... 27,000 total STGR51 LH/RH 5,700 flight cycles.
flight cycles. (FR72 through
FR80). ----------------------------------------------------------------------------------------------------------------

(1) Within the applicable time in paragraph (j)(1)(i) or (j)(1)(ii) of this AD after doing the last inspection of the ``standard'' areas of the longitudinal lap joints in accordance with Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
(i) For longitudinal lap jointswith bonded doublers: 6,000 flight cycles.
(ii) For longitudinal lap joints without bonded doublers: 8,000 flight cycles.
(2) Within the applicable time specified in Tables 3 or 4 of this AD, or within 60 days after the effective date of this AD, whichever occurs later.

Post-Repair or Modification Inspections and Repair or Modification if Necessary

(k) For airplanes on which a repair or modification has been done in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211: At the applicable initial inspection time specified in Table 5 of this AD, do an eddy current inspection for cracking of the repaired or modified areas, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006. If no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 5 of this AD. If any crack is found during any inspection requiredby this paragraph, repair or modify before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.

[[Page 63181]]

Table 5--Post-Repair or Modification Compliance Time ---------------------------------------------------------------------------------------------------------------- Repair or retrofit solution/area-- as identified in Airbus Mandatory Initial inspection after Follow-up inspections at intervals not to exceed--
Service Bulletin A300-53-0211-- repair or retrofit--

---------------------------------------------------------------------------------------------------------------- Repair 1: (Without cut out) also Skin/doubler thickness
applicable to the solution with
removed inner doubler.
< 1 inch: 10,000 1,000 flight cycles.
flight cycles after
repair.
>= 1 inch and < 2,000 flight cycles.
2 inch: 30,000 flight
cycles after repair.
>= 2 inch: 6,400 flight cycles.
60,000 flight cycles
after repair. Repair 4 (With cut out).......... Within 32,000 flight 5,000 flight cycles.
cycles after repair. Repair 4A (With cut out)......... Within 24,000 flight 5,300 flight cycles.
cycles after repair. Repair 7 (MSN 0095 at STGR52 LH Within 37,000 flight 12,000 flight cycles.
in Section 16). cycles after repair. Repair 9 (MSN 0073 and 0095 Within 36,000 flight 5,000 flight cycles.
STGR44 LH/RH in Sections 16 and cycles after repair.
17). Repair 10 (Post-repair Within 20,000 flight 11,000 flight cycles.
inspections in Figure 13). cycles after repair. Repair 2 (With cut out).......... Within 24,000 flight 5,300 flight cycles.
cycles after repair. Repair 3 (Without cut out)....... Within 24,000 flight 5,300 flight cycles.
cycles after repair. Retrofit 1 (Retrofit lap joint).. Within32,000 flight 5,000 flight cycles.
cycles after retrofit. Retrofit 2 Retrofit lower shell Within 32,000 flight 3,000 flight cycles.
(4 panel solution) STGR43 LH cycles after retrofit.
(FR26 through FR39), STGR43 RH
(FR26 through FR38), and STGR49
RH (FR26 through FR38). Retrofit 2 Retrofit lower shell Within 32,000 flight 5,700 flight cycles.
(4 panel solution) STGR46 RH cycles after retrofit.
(FR19 through FR26), and STGR47
LH (FR26 through FR39), and
STGR51 LH (FR19 through FR26). Retrofit 3 Retrofit lower shell Within 32,000 flight 3,000 flight cycles.
(3 panel solution) STGR43 LH cycles after retrofit.
(FR26 through FR39), and STGR43
RH (FR26 through FR38). Retrofit 3 Retrofit lower shell Within 32,000 flight 5,700 flight cycles.
(3 panel solution) STGR46 RH cycles after retrofit.
(FR19 through FR26), and STGR51
LH (FR19 through FR26), and
STGR54 LH (FR26 through FR39).Retrofit 3A (STGR43 LH/RH between Within 32,000 flight 5,000 flight cycles.
FR37 and FR39 in Section 14). cycles after retrofit. Retrofit 4 (Retrofit lap joint Within 42,000 flight 5,000 flight cycles.
without cut out). cycles after retrofit. Retrofit 5 (Retrofit lap joint).. Within 42,000 flight 5,000 flight cycles.
cycles after retrofit. Retrofit 6 (Retrofit lap joint).. Within 34,000 flight 12,000 flight cycles.
cycles after retrofit. Retrofit 7 (Retrofit lap joint).. Within 47,600 flight 5,400 flight cycles.
cycles after retrofit. ----------------------------------------------------------------------------------------------------------------

Fuselage Inner Doubler Inspections and Repair if Necessary

(l) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have not been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 15 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at the applicable intervals specified in Table 6 of this AD.

Table 6--Repetitive Intervals for Inspections for Disbonding and
Cracking ------------------------------------------------------------------------
Inspect at intervals not toexceed--
For area-- ------------------------------------------------------------------------ Sections 13 and 14 as specified in Within 7 years or 12,000 flight
Airbus Service Bulletin cycles after doing the inspection,
A300[dash]53[dash]229, Revision 5, whichever occurs first.
dated April 8, 1997. Sections 15 through 18 as specified Within 8.5 years or 12,000 flight
in Airbus Service Bulletin cycles after doing the inspection,
A300[dash]53[dash]229, Revision 5, whichever occurs first.
dated April 8, 1997. ------------------------------------------------------------------------

(1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22.
(2) If no cracking is found and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(m) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229; except for airplanes on which a repair of that area has been done in accordance with Airbus Service

[[Page 63182]]

Bulletin A300-53-229: At the applicable time specified in Table 6 of thisAD, or within 60 days after the effective date of this AD, whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection at the applicable intervals specified in Table 6 of this AD.
(1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22.
(2) If no cracking is found and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5,dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(n) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have not been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 12 years since new, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking is found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first.
(1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area.
(2) If no cracking is found and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(o) For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking have been done as of the effective date of this AD in accordance with Airbus Service Bulletin A300-53-229; except airplanes on which a repair of that area has been done in accordance with Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first; or within 60 days after the effective date of this AD; whichever occurs later, do a detailed inspection of the fuselage bonded inner doubles of the longitudinal lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-hand for disbonding and cracking in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and corrosion are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first.
(1) If no cracking is found and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area.
(2) If no cracking is found and ``major'' disbonding, as defined inAirbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997.
(p) Although Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997; and Airbus Mandatory Service Bulletin A300-53- 0211, Revision 07, dated December 1, 2006; specify to submit certain information to the manufacturer, this AD does not include that requirement.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows:
(1) Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, this AD requires that you repair the crack(s) before further flight.
(2) The MCAI or service information does not include enforceable compliance times for certain actions; however, this AD requires that those actions be done at the enforceable times specified in this AD.
(3) Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (p) of this AD specifies that such submittal is not required.

Other FAA AD Provisions

(q) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

Related Information

(r) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007-0091, dated April 10, 2007, corrected June 23, 2008; Airbus Service BulletinA300-53-229, Revision 5, dated April 8, 1997; and Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; for related information.

Material Incorporated by Reference

(s) You must use Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, including Appendix A300SB/53-229, dated April 10, 1989; and Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. Only pages 1, 2, 5, 11, and 12, of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, show revision level 5 and issue date April 8, 1997; pages 3, 4-10, and 13-17 show revision level 4 and issue date March 30, 1994, and pages 1-17 of Appendix A300SB/53- 229 show issue date April 10, 1989.
(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) Forservice information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France;

[[Page 63183]]

telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com; Internet http://www.airbus.com.
(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.
(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on May 10, 2011 (76 FR 26962), and proposed to supersede AD 90-01-10, Amendment 39-6448 (55 FR 261, January 4, 1990). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

This Airworthiness Directive (AD) is issued in order to prevent cracks development in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames 18 and 80 which could affect the structural integrity of the fuselage if not corrected.
This new AD:

--Retains the requirements of DGAC AD 1989-061-092(B)R4 [which corresponds to FAA AD 90-01-10 (55 FR 261, January 4, 1990)], which is cancelled; --Takes into account a new inspection program as detailed in AIRBUS Service Bulletins (SB) A300-53-0211 Revision 7, which will allow A300 aircraft to reach the Limit of Validity (LOV).

This AD has been republished to correctly refer to SB A300-53- 0211 in Note 2 of the Compliance section.

The inspection program consists of repetitive detailed inspections for disbonding and cracking of the fuselage inner doubler; eddy current and ultrasonic inspections of the fuselage longitudinal lap joints for cracking; and repair if necessary (i.e., repairing any cracking or disbonding, or contacting Airbus for repair instructions and doing the repair). You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (76 FR 26962, May 10, 2011) or on the determination of the cost to the public.

Clarification of Service Bulletin References

Paragraphs (h)(1) and (j)(1) of the NPRM (76 FR 26962, May 10, 2011) refer to Airbus Mandatory Service Bulletin A300-53-0211 as the service information for airplanes on which an inspection of the longitudinal lap joints has been done. For clarity, we have revised the paragraphs to refer to the latest service bulletin revision and, therefore, we have revised paragraphs (h)(1) and (j)(1) of this AD to refer to Airbus Mandatory Service Bulletin A300-53-0211, Revision 07, dated December 1, 2006.
Paragraphs (l)(1), (1)(2), (m)(1), (m)(2), (n)(1), (n)(2), (o)(1), and (o)(2) of the NPRM (76 FR 26962, May 10, 2011) refer to Airbus Service Bulletin A300-53-229 for the definition of ``major'' and ``minor'' disbonding. For clarity, we have revised the paragraphs to refer to the latest service bulletin revision and, therefore, we have revised paragraphs (l)(1), (1)(2), (m)(1), (m)(2), (n)(1), (n)(2), (o)(1), and (o)(2) of this AD to refer to Airbus Service Bulletin A300- 53-229, Revision 5, dated April 8, 1997.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.

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Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.
We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.

Costs of Compliance

We estimate that this AD will affect about 5 products of U.S. registry.
We estimate that it will take about3,735 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the AD on U.S. operators to be $1,587,375, or $317,475 per product.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because itaddresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect 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.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order 12866;
2. Is not a ``significant rule'' under the 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.
We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the ADdocket.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM (76 FR 26962, May 10, 2011), the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.