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 adding the following new AD:
2011-10-07 Airbus: Amendment 39-16688. Docket No. FAA-2010-1275; Directorate Identifier 2010-NM-091-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 15, 2011.
Affected ADs
(b) This AD affects AD 90-19-07, Amendment 39-6731 (55 FR 37455, September 12, 1990); and AD 91-06-18, Amendment 39-6940 (56 FR 10796, March 14, 1991).
Applicability
(c) This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all certified models, all serial numbers.
Subject(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France Airworthiness Directive (AD) 1992-106-132(B) * * * was issued to require a set of inspection- and modification tasks which addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25-571 requirements related to damage-tolerance and fatigue evaluation of structure.
* * * * *
The unsafe condition is reduced structural integrity of the wings.
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.
Restatement of Certain Requirements of AD 98-26-01, Amendment 39-10942 (63 FR 69179, December 16, 1998), With Reduced Compliance Times
Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks at Bolt Holes
(g) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification No. 05101 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2003 has been embodied in service before the accumulation of 9,400 total flight cycles and 18,800 total flight hours: At the times specified in paragraph (h) of this AD, perform a detailed visual inspection to detect cracks in the external surface of the wing lower skin around the landing access panel holes of the leading edge, in accordance with the Airbus Service Bulletin A310-57-2002, Revision 1, dated July 2, 1992; Airbus Service Bulletin A310-57- 2002, Revision 2, dated January 4, 1996; or Airbus Mandatory Service Bulletin A310-57-2002, Revision 03, dated November 28, 2006. If any discrepancy is found, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch,ANM-116, FAA, Transport Airplane Directorate, or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent) or EASA (or its delegated agent). Except as required by paragraph (n) of this AD, repeat the detailed inspection specified in this paragraph at the earlier of the times specified in paragraphs (g)(1) and (g)(2) of this AD; and thereafter at intervals not to exceed 2,300 flight cycles or 4,700 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2002, Revision 03, dated November 28, 2006. Accomplishment of Airbus Modification 05101 before the effective date of this AD terminates the repetitive inspection requirements of this paragraph; however, airplanes identified in paragraph (n) of this AD are applicable to the new inspections required by paragraph (n) of this AD. As of the effective date of this AD: Accomplishment of Airbus Modification 05101 before the accumulation of 9,400 total flight cycles and 18,800 total flight hours terminates the repetitive inspection requirements of this paragraph.
Note 1: Airbus Service Bulletin A310-57-2003, Revision 03, dated October 16, 2006, is
[[Page 27222]]
an additional source of guidance for accomplishing Airbus Modification 05101.
Note 2: As of the effective date of this AD, if Airbus Service Bulletin A310-57-2003 is done on or after the accumulation of 9,400 total flight cycles or on or after the accumulation of 18,800 total flight hours, the actions specified in paragraph (g) of this AD are still required.
(1) Within 3,000 flight cycles after doing the detailed inspection specified in paragraph (g) of this AD.
(2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within 2,300 flight cycles or 4,700 flight hours, whichever occurs first, after doing the detailed inspection required by paragraph (g) of this AD.
(ii) Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD.
(h) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification No. 05101 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2003 has been embodied in service before the accumulation of 9,400 total flight cycles and 18,800 total flight hours: At the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, do the detailed inspection required by paragraph (g) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999 (the effective date of AD 98-26-01, amendment 39-10942), whichever occurs later.
(2) At the later of the times specified in paragraph (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Prior to the accumulation of 9,400 total flight cycles or 18,800 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD.
Inspect Area around Overwing Refueling Aperture at Ribs 13-14
(i) For Model A310-203, A310-204, A310-222, A310-304, A310-322, A310-324, and A310-325 airplanes that are listed in Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996, and are identified as Configuration 1 in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007: Prior to the accumulation of 6,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later, perform an eddy current inspection to detect cracks in the holes around the overwing refueling aperture at ribs 13-14, in accordance with Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007. If any discrepancy is found, prior to further flight, perform follow-on corrective actions, as applicable, in accordance with Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007; except where the service bulletin specifies to contact Airbus for repair, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the DGAC (or its delegated agent) or EASA (or its delegated agent). Repeat the inspection specified in this paragraph at the earlier of the times specified in paragraphs (i)(1) and (i)(2) of this AD, and thereafter at intervals not to exceed 2,300 flight cycles or 4,600 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007. Accomplishment of Airbus Modification 05891H5128 terminates the repetitive inspections required bythis paragraph.
(1) Within 3,000 flight cycles after doing the last inspection required by paragraph (i) of this AD.
(2) At the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Within 2,300 flight cycles or 4,600 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (i) of this AD.
(ii) Within 380 flight cycles or 770 flight hours, whichever occurs first, after the effective date of this AD.
Note 3: Airbus Service Bulletin A310-57-2020, Revision 07, dated June 5, 2006, is an additional source of guidance for accomplishing Airbus Modification 05891H5128.
Upper Skin Forward of Front Spar--Inspection for Cracks
(j) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, except airplanes on which Airbus modification 05026 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2005 has beendone in service before the accumulation of 10,500 total flight cycles and 21,000 total flight hours: At the times specified in paragraph (k) of this AD, perform a detailed visual inspection to detect cracks around the bolts in the wing top skin upper surface of the front spar between rib 7 and rib 28, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996; or Airbus Mandatory Service Bulletin A310-57-2032, Revision 04, dated December 1, 2006. If any discrepancy is found, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or DGAC (or its delegated agent) or EASA (or its delegated agent). Except as required by paragraph (p) of this AD, repeat the detailed inspection specified in this paragraph at the earlier of the times specified in paragraphs (j)(1) and (j)(2) of this AD, and thereafter at intervals not to exceed 3,900 flight cycles or 7,900 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2032, Revision 04, dated December 1, 2006. Accomplishment of Airbus Modification 05026H0878 before the effective date of this AD terminates the repetitive inspection requirements of this paragraph; however, airplanes identified in paragraph (p) of this AD are applicable to the new inspections required by paragraph (p) of this AD. As of the effective date of this AD: Accomplishment of Airbus Modification 05026H0878 before the accumulation of 10,500 total flight cycles and 21,000 total flight hours terminates the repetitive inspection requirements of this paragraph.
(1) Within 4,500 flight cycles after doing the last inspection required by paragraph (j) of this AD.
(2) At the later of the times specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Within 3,900 flight cycles or 7,900 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (j) of this AD.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
Note 4: Airbus Service Bulletin A310-57-2005, Revision 03, dated October 2, 2006, is an additional source of guidance for accomplishing Airbus Modification 05026H0878.
Note 5: As of the effective date of this AD, if Airbus Service Bulletin A310-57-2005 is done on or after the accumulation of 10,500 total flight cycles or on or after the accumulation of 21,000 total flight hours, the actions specified in paragraph (j) of this AD are still required.
(k) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, except airplanes on which Airbus modification 05026 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2005 has been done in service before the accumulation of 10,500 total flight cycles and 21,000 total flight hours: At the earlier of the times specified in paragraphs (k)(1) and (k)(2) of this AD, do the detailed inspection required by paragraph (j) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later.
(2) At the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
(i) Prior to the accumulation of 10,500 total flight cycles or 21,000 total flight hours, whichever occurs first.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
Stringer Flanges at Rib 14 Wing Bottom Skin--Inspect for Cracks
(l) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification 04987 has been done in production: At the compliance time specified in paragraph (m) of this AD, perform a high frequency eddy current (HFEC) or X-ray inspection to detect cracking of the stringer runouts inboard and outboard of rib 14 at stringers 6, 7, 8, and 9, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57- 2038, Revision 2, dated January 4, 1996; or Airbus Mandatory
[[Page 27223]]
Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006. Do the next inspection at the earlier of the times specified in paragraph (l)(1) and (l)(2) of this AD, and repeat the inspection thereafter at intervals not to exceed the applicable times specified in table 1 of this AD. If any crack is detected, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or DGAC (or its delegated agent) or EASA (or its delegated agent). As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006.
(1) Within the applicable interval specified in paragraph 1.B.(5) of Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996.
(2) At the later of the times specified in paragraph (l)(2)(i) and (l)(2)(ii) of this AD.
(i) Within the applicable interval specified in table 1 of this AD after doing the most recent inspection specified in paragraph (l) of this AD.
(ii) Within 1,100 flight cycles or 2,300 flight hours, whichever occurs first, after the effective date of this AD.
Table 1--Repetitive Intervals, Depending on Inspection Type ------------------------------------------------------------------------
Repetitive interval (not to
Type of inspection exceed) ------------------------------------------------------------------------ X-Ray.................................. 7,200 flight cycles or 14,500
flight hours, whichever occurs
first. HFEC................................... 9,400 flight cycles or 18,800
flight hours, whichever occurs
first. ------------------------------------------------------------------------
(m) For Model A310-203 and A310-222 airplanes listed in Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification 04987 has been done in production: At the earlier of the times specified in paragraphs (m)(1) and (m)(2) of this AD, perform an inspection required by paragraph (l) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,500 flight cycles after January 20, 1999, whichever occurs later.
(2) At the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) Prior to the accumulation of 12,000 total flight cycles or 24,000 total flight hours, whichever occurs first.
(ii) Within 1,100 flight cycles or 2,300 flight hours after the effective date of this AD, whichever occurs first.
New Requirements of This AD
Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks at Bolt Holes--Additional Inspections for Certain Airplanes
(n) For Model A310-203 and A310-222 airplanes, on which Airbus Service Bulletin A310-57-2003 has been done in service on or after the accumulation of 9,400 total flight cycles or on or after the accumulation of 18,800 total flight hours: Do the inspection required by paragraph (g) of this AD at the later of the times specified in paragraphs (n)(1) and (n)(2) of this AD. Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 2,300 flight cycles or 4,700 flight hours, whichever occurs first.
(1) Within 2,300 flight cycles or 4,700 flight hours, whichever occurs first, after doing the most recent detailed inspection required by paragraph (g) of this AD.
(2) Within 1,500 flight cycles or 3,000 flight hours, after the effective date of this AD, whichever occurs first.
Inspect Area Around Overwing Refueling Aperture at Ribs 13-14 for Additional Airplanes
(o) For Model A310-203, A310-204, A310-222, A310-304, A310-322, A310-324, and A310-325 airplanes, except for airplanes identified in paragraph (i) of this AD on which Airbus Modification 05891H5128 has not been done: At the applicable compliance time specified in table 2 of this AD, do the applicable actions specified in paragraph (o)(1) or (o)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007. If any cracking is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007; except where this service bulletin specifies to contact Airbus for repair, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or EASA (or itsdelegated agent). Repeat the inspections thereafter at the applicable interval specified in table 2 of this AD. Certain compliance times specified in table 2 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours. For airplanes identified as Configuration 01 in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007, accomplishment of Airbus Modification 05891H5128 terminates the repetitive inspections required by this paragraph for Configuration 01 airplanes; thereafter do the applicable actions specified in paragraph (o)(2) of this AD at the times specified in table 2 of this AD.
Note 6: Airbus Service Bulletin A310-57-2020, Revision 07, dated June 5, 2006, is an additional source of guidance for accomplishing Airbus Modification 05891H5128.
(1) For Configuration 01 airplanes, as identified in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007: Do a rotating probe eddy current inspection for cracking in the holes around the overwing refueling aperture at ribs 13-14.
(2) For Configuration 02 through 06 airplanes, as identified in Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007: Do an external detailed inspection for cracking of the top skin at ribs 13-14, and an internal detailed inspection for cracking of string 7 and string 8 of the overwing refuel aperture.
Table 2--Compliance Times for Configuration 01 Through 06 Airplanes ----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Airplanes as Identified in Airbus Compliance time (whichever occurs later) Repetitive interval
Mandatory Service Bulletin A310-57- (not to exceed) 2006, revision 04, dated May 21, 2007 ---------------------------------------------------------------------------------------------------------------- Configuration 01 airplanes........... Prior to the Within 380 flight 2,300 flight cycles or
accumulation of 6,000 cycles or 770 flight 4,600 flight hours,
total flight cycles. hours, whichever whichever occurs
occurs first, after first.
the effective date of
this AD. Configuration 02 airplanes........... Within 30,900 flight Within 1,500 flight 11,300 flight cycles or
cycles or 61,900 cycles or 18 months, 22,600 flight hours,
flight hours, whichever occurs whichever occurs
whichever occurs first, after the first.
first, after effective date of this
accomplishing Airbus AD.
Service Bulletin A310-
57-2020. Configuration 03 airplanes........... Within 30,900 flight Within 1,500 flight 12,000 flight cycles or
cycles or 61,900 cycles or 18 months, 24,000 flight hours,
flight hours, whichever occurs whichever occurs
whichever occurs first, after the first.
first, after Airbus effective date of this
Modification AD.
05891H5128 is done or
Airbus Service
Bulletin A310-57-2020
is accomplished.
[[Page 27224]]
Configuration 04 and 05 short range Before the accumulation Within 1,500 flight 12,000 flight cycles or
airplanes. of 25,900 total flight cycles or 18 months, 33,600 flight hours,
cycles or 72,500 total whichever occurs whichever occurs
flight hours, first, after the first.
whichever occurs first. effective date of this
AD. Configuration 04 and 05 long range Before the accumulation Within 1,500 flight 9,400 flight cycles or
airplanes.of 18,800 total flight cycles or 18 months, 47,200 flight hours,
cycles or 94,200 total whichever occurs whichever occurs
flight hours, first, after the first.
whichever occurs first. effective date of this
AD. Configuration 06..................... Before the accumulation Within 1,500 flight 12,000 flight cycles or
of 30,900 total flight cycles or 18 months, 24,000 flight hours,
cycles or 61,900 total whichever occurs whichever occurs
flight hours, first, after the first.
whichever occurs first. effective date of this
AD. ----------------------------------------------------------------------------------------------------------------
Upper Skin Forward of Front Spar--Inspection for Cracks--Additional Inspections for Certain Airplanes
(p) For Model A310-203 and A310-222 airplanes on which Airbus Service Bulletin A310-57-2005 has been done in service on or after the accumulation of 10,500 total flight cycles or on or after 21,000 total flight hours: Do the inspection required by paragraph (j) of this AD at the later of the times specified in paragraphs (p)(1) and (p)(2) of this AD. Repeat the inspection specified in paragraph (j) of this AD thereafter at intervals not to exceed 3,900 flight cycles or 7,900 flight hours, whichever occurs first.
(1) Within 3,900 flight cycles or 7,900 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (j) of this AD.
(2) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
Inspection of Rear Spar at Selected Bolt Locations for Attachment of Main landing Gear Forward Pick-Up Fitting
(q) For Model A310-203, A310-204, A310-222, A310-304, A310-322, and A310-324 airplanes, except airplanes on which Airbus modification 07601 has been done in production: Do the applicable actions specified in paragraphs (q)(1), (q)(2), and (q)(3) of this AD. If any cracking is found during any inspection, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent).
Note 7: For Model A310-304, A310-322, and A310-324 airplanes on which Airbus modification 07601 has been done, guidance for post- modification inspections can be found in Structure Significant Item (SSI) 57.21.16 of the Maintenance Review Board Document (MRBD).
(1) For airplanes on which Airbus Modification 07925H1113 and Modification 11578H5436 have not been done: At the applicable time specified in table 3 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 3 of this AD until Airbus Modification 07925H1113 or 11578H5436 has been done. After doing Airbus Modification 07925H1113 or 11578H5436 do the applicable actions specified in paragraph (q)(2) or (q)(3) of this AD at the times specified in paragraph (q)(2) or (q)(3) of this AD, as applicable. Certain compliance times specified in table 3 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
Note 8: Airbus Service Bulletin A310-57-2049, Revision 6, dated November 26, 1997, is an additional source of guidance for accomplishing Airbus Modification 07925H1113. Airbus Service Bulletin A310-57-2074, Revision 03, dated July 3, 2006, is an additional source of guidance for accomplishing Airbus Modification 11578H5436.
Table 3--Compliance Times for Airplanes Pre-Mod 07925 and Pre-Mod 11578 ----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Airplanes Compliance time (whichever occurs later) Repetitive interval
(not to exceed) ---------------------------------------------------------------------------------------------------------------- Model A310-203, A310-204, and A310- Prior to the Within 750 flight 2,800 flight cycles or
222 airplanes. accumulation of 9,800 cycles or 1,500 flight 5,700 flight hours,
total flight cycles or hours, whichever whichever occurs
19,600 total flight occurs first, after first.
hours, whichever the effective date of
occurs first. this AD. Model A310-304, A310-322, and A310- Prior to the Within 750 flight 2,400 flight cyclesor
324 short range airplanes. accumulation of 7,100 cycles or 1,500 flight 6,900 flight hours,
total flight cycles or hours, whichever whichever occurs
20,100 total flight occurs first, after first.
hours, whichever the effective date of
occurs first. this AD. Model A310-304, A310-322, and A310- Prior to the Within 750 flight 1,900 flight cycles or
324 long range airplanes. accumulation of 5,700 cycles or 1,500 flight 9,800 flight hours,
total flight cycles or hours, whichever whichever occurs
28,600 total flight occurs first, after first.
hours, whichever the effective date of
occurs first. this AD. ----------------------------------------------------------------------------------------------------------------
(2) For airplanes on which Airbus Modification 07925H1113 has been done: At the applicable time specified in table 4 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 4 of this AD. Certain compliance times specified in table 4 of this AD are applicable to short range use, AFT equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
[[Page 27225]]
Table 4--Compliance Times for Airplanes Post-Mod 07925 ----------------------------------------------------------------------------------------------------------------
-- -- -- -- ----------------------------------------------------------------------------------------------------------------
AirplanesCompliance time (whichever occurs later) Repetitive interval
(not to exceed) ---------------------------------------------------------------------------------------------------------------- Model A310-203, A310-204, and A310- Prior to the Within 750 flight 9,400 flight cycles or
222 airplanes. accumulation of 14,700 cycles or 1,500 flight 18,900 flight hours,
total flight cycles or hours, whichever whichever occurs
29,400 total flight occurs first, after first.
hours, whichever the effective date of
occurs first. this AD. Model A310-304, A310-322, and A310- Prior to the Within 750 flight 5,000 flight cycles or
324 short range airplanes. accumulation of 11,900 cycles or 1,500 flight 14,000 flight hours,
total flight cycles or hours, whichever whichever occurs
33,500 total flight occurs first, afterfirst.
hours, whichever the effective date of
occurs first. this AD. Model A310-304, A310-322, and A310- Prior to the Within 750 flight 4,000 flight cycles or
324 long range airplanes. accumulation of 9,500 cycles or 1,500 flight 20,000 flight hours,
total flight cycles or hours, whichever whichever occurs
47,700 total flight occurs first, after first.
hours, whichever the effective date of
occurs first. this AD. ----------------------------------------------------------------------------------------------------------------
(3) For airplanes on which Airbus Modification 11578H5436 has been done: At the applicable time specified in table 5 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 5 of this AD. Certain compliance times specified in table 5 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
Table 5--Compliance Times for Airplanes Post-Mod 11578 ----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Airplanes Compliance time (whichever occurs later) Repetitive interval
(not to exceed) ---------------------------------------------------------------------------------------------------------------- Model A310-203, A310-204, and A310- Within 29,600 flight Within 750 flight 9,400 flight cycles or222 airplanes. cycles or 59,200 cycles or 1,500 flight 18,900 flight hours,
flight hours, hours, whichever whichever occurs
whichever occurs occurs first, after first.
first, after Airbus the effective date of
Modification this AD.
11578H5436 has been
done. Model A310-304, A310-322, and A310- Within 24,200 flight Within 750 flight 5,000 flight cycles or
324 short range airplanes. cycles or 67,900 cycles or 1,500 flight 14,000 flight hours,
flight hours, hours, whichever whichever occurs
whichever occurs occurs first, after first.
first, after Airbus the effective date of
Modification this AD.
11578H5436 has been
done. Model A310-304, A310-322, and A310- Within 19,300 flight Within 750 flight 4,000 flight cycles or
324 long range airplanes. cycles or96,800 cycles or 1,500 flight 20,000 flight hours,
flight hours, hours, whichever whichever occurs
whichever occurs occurs first, after first.
first, after Airbus the effective date of
Modification this AD.
11578H5436 has been
done. ----------------------------------------------------------------------------------------------------------------
Credit for Actions Accomplished in Accordance With Previous Service Information
(r) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2038, Revision 03, dated September 4, 1998, are acceptable for compliance with the corresponding actions specified in paragraph (l) of this AD.
(s) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999, are acceptable for compliance with the corresponding actions specified in paragraph (q) of this AD.
Terminating Action for Paragraph (a) of AD 90-19-07
(t) Accomplishing an inspection in accordance with Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, or Revision 03, dated September 4, 1998; or Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006; terminates the requirements of paragraph (a) of AD 90-19-07.
Note 9: Airbus Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996; and Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006; are referred to in paragraph (l) of this AD. Airbus Service Bulletin A310-57-2038, Revision 03, dated September 4, 1998, is referred to in paragraph (r) of this AD.
Terminating Action for AD 91-06-18
(u) Accomplishing an inspection in accordance with Airbus Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, as revised by Airbus Service Bulletin Change Notice 4A, dated October 16, 1996; Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999; or Airbus Mandatory Service Bulletin A310-57- 2046, Revision 08, dated December 1, 2006; terminates the requirements of AD 91-06-18.
Note 10: Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated December 1, 2006, is referred to in paragraph (q) of this AD. Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999, is referred to in paragraph (s) of this AD. Airbus Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, as revised by Airbus Service Bulletin Change Notice 4A, dated October 16, 1996, is referred to in paragraph (n) of AD 98-26-01.
FAA AD Differences
Note 11: This AD differs from the MCAI and/or service information as follows:
Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (j) of this AD requires that you repair the crack(s) before further flight.
Other FAA AD Provisions
(v) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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
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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 principal inspector or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. TheAMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 98-26-01, are approved as AMOCs for the corresponding provisions of 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
(w) Refer to MCAI EASA Airworthiness Directive 2007-0242, dated September 4, 2007, and the Airbus service bulletins listed in table 6 of this AD for related information.
Table 6--Related Service Information ----------------------------------------------------------------------------------------------------------------
Service Bulletin RevisionDate ---------------------------------------------------------------------------------------------------------------- Airbus Mandatory Service Bulletin A310- 03.......................... November 28, 2006.
57-2002. Airbus Mandatory Service Bulletin A310- 04.......................... May 21, 2007.
57-2006. Airbus Mandatory Service Bulletin A310- 04.......................... December 1, 2006.
57-2032. Airbus Mandatory Service Bulletin A310- 04.......................... October 19, 2006.
57-2038. Airbus Mandatory Service Bulletin A310- 08.......................... December 1, 2006.
57-2046. Airbus Service Bulletin A310-57-2038.... 2........................... January 4, 1996. Airbus Service Bulletin A310-57-2038.... 03.......................... September 4, 1998 Airbus Service Bulletin A310-57-2046.... 4........................... October 16, 1996. Airbus Service Bulletin A310-57-2046.... 07.......................... April 2, 1999. Airbus ServiceBulletin A310-57-2046, Original.................... October 16, 1996.
Change Notice 4A. ----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(x) You must use the service bulletins contained in table 7 of this AD to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating actions specified by this AD, you must use the service information contained in table 7 of this AD to perform those actions unless the AD specifies otherwise.
Table 7--All Material Incorporated by Reference ----------------------------------------------------------------------------------------------------------------
Required/optional
Service Bulletin Revision Date action ---------------------------------------------------------------------------------------------------------------- Airbus Mandatory Service Bulletin 03...................... November 28, 2006...... Required.
A310-57-2002. Airbus Mandatory Service Bulletin 04...................... May 21, 2007........... Required.
A310-57-2006. Airbus Mandatory Service Bulletin 04...................... December 1, 2006....... Required.
A310-57-2032. Airbus Mandatory Service Bulletin 04...................... October 19, 2006....... Required and optional.
A310-57-2038. Airbus Mandatory Service Bulletin 08...................... December 1, 2006....... Required and optional.
A310-57-2046. Airbus Service Bulletin A310-57-2038 2....................... January 4, 1996........ Optional. Airbus Service Bulletin A310-57-2038 03...................... September 4, 1998...... Optional. Airbus Service Bulletin A310-57-2046 4....................... October 16, 1996....... Optional. Airbus Service Bulletin A310-57-2046 07...................... April 2, 1999.......... Optional. Airbus Service Bulletin A310-57- Original................ October 16, 1996....... Optional.
2046, Change Notice 4A. ----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the incorporation by reference of the service information contained in table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 8--New Material Incorporated by Reference ----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision Date ---------------------------------------------------------------------------------------------------------------- Airbus Mandatory Service Bulletin A310-57-2002. 03 November 28, 2006. Airbus Mandatory Service Bulletin A310-57-2006. 04 May 21, 2007. Airbus Mandatory Service Bulletin A310-57-2032. 04 December 1, 2006. Airbus Mandatory Service Bulletin A310-57-2038. 04 October 19, 2006. Airbus Mandatory Service Bulletin A310-57-2046. 08 December 1, 2006. Airbus Service Bulletin A310-57-2038........... 03 September 4, 1998. Airbus Service Bulletin A310-57-2046........... 07 April 2, 1999. ----------------------------------------------------------------------------------------------------------------
(2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in table 9 of this AD on January 20, 1999 (63 FR 69179, December 16, 1998).
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Table 9--Material Previously Incorporated by Reference ----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision Date ---------------------------------------------------------------------------------------------------------------- Airbus Service Bulletin A310-57-2038.... 2........................... January 4, 1996. Airbus Service Bulletin A310-57-2046.... 4........................... October 16, 1996. Airbus Service Bulletin A310-57-2046, Original.................... October 16, 1996.
Change Notice 4A. ----------------------------------------------------------------------------------------------------------------
(3) For service information identified in this AD, contact Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; 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.
(4) 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.
(5) 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.