Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 13084-13087 [E8-3989]

Download as PDF 13084 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations Boeing 757 MPD Document D622N001, Section 9, Revision January 2007, into the MPD Document to incorporate AWL No. 28– AWL–23, No. 28–AWL–24, and No. 28– AWL–25. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (j) You must use the service information listed in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or 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: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Service information Revision Boeing 737–600/700/700C/700IGW/800/900 Maintenance Planning Data Document D626A001–CMR, Section 9. Boeing 757 Maintenance Planning Data Document D622N001, Section 9 ............................ Boeing Alert Service Bulletin 737–28A1207 ............................................................................ Boeing Alert Service Bulletin 757–28A0088 ............................................................................ November 2006 R1 ................ November 2006. January 2007 ......................... Original ................................... Original ................................... January 2007. February 15, 2007. January 25, 2007. Issued in Renton, Washington, on February 28, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–4486 Filed 3–11–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25658; Directorate Identifier 2006–NM–054–AD; Amendment 39–15406; AD 2008–05–12] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. jlentini on PROD1PC65 with RULES AGENCY: SUMMARY: The FAA is superseding an existing AD that applies to certain Airbus Model A318, A319, A320, and A321 airplanes. That AD currently requires repetitive detailed inspections of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and corrective actions if necessary. This new AD adds airplanes that were recently added to the type certificate data sheet and changes the inspection type. This AD results from reports of wear damage to the inboard flap trunnions after incorporation of the terminating modification. We are issuing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss VerDate Aug<31>2005 17:40 Mar 11, 2008 Jkt 214001 of flap surface control and consequently result in the flap detaching from the airplane. A detached flap could result in damage to the tail of the airplane. DATES: This AD becomes effective April 16, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of April 16, 2008. On March 24, 2006 (71 FR 8439, February 17, 2006), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320–57–1133, excluding Appendix 01, dated July 28, 2005. On January 8, 2001 (65 FR 75603, December 4, 2000), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. ADDRESSES: For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Date 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. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Discussion The FAA issued a second supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2006–04–06, amendment 39–14487 (71 FR 8439, February 17, 2006). The existing AD applies to certain Airbus Model A318, A319, A320, and A321 airplanes. That second supplemental NPRM was published in the Federal Register on August 16, 2007 (72 FR 45982). That second supplemental NPRM proposed to supersede an existing AD that currently requires repetitive detailed inspections of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and corrective actions if necessary. That second supplemental NPRM proposed to add airplanes that were recently added to the type certificate data sheet and change the inspection type. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Include Revised Service Information Airbus asks that Airbus Service Bulletin A320–57–1133, Revision 03, dated July 3, 2007, be incorporated into E:\FR\FM\12MRR1.SGM 12MRR1 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations second supplemental NPRM, certain requirements were removed based on a previous recommendation from Airbus. Regarding that recommendation, Airbus notes that Model A321–211 and –231 airplanes that are pre-modification 26495, and on which Airbus Service Bulletin A320–27–1117, Revision 04, dated November 6, 2001, was not applied, should have dedicated procedures included in the AD. Airbus states that the inspections specified in Airbus Service Bulletin A320–27–1108, Revision 04, dated November 22, 1999, provide those procedures. We agree with Airbus, although there are no U.S. operators of Model A321– 211 and –231 airplanes that are specified in the effectivity that are premodification 26495. In the unlikely event that an operator has an airplane configuration that is pre-modification 26495, or on which Airbus Service Bulletin A320–27–1117 was applied, we the AD. (We referred to Revision 02, dated December 12, 2006, of that service bulletin as the appropriate source of service information for accomplishing certain actions specified in the second supplemental NPRM.) We agree with Airbus and have changed the applicable paragraphs in this AD to refer to Revision 03 of Airbus Service Bulletin A320–57–1133 for accomplishing certain actions, as no additional work is required by this revision. We have also changed paragraph (k) of this AD to give credit to operators who have accomplished the actions in accordance with Airbus Service Bulletin A320–57–1133, Revision 02, dated December 12, 2006, before the effective date of this AD. Request To Include Inspections Removed From Second Supplemental NPRM Under the ‘‘Request to Remove Certain Requirements’’ section of the 13085 have determined that the alternative inspections specified in Airbus Service Bulletin A320–27–1108, Revision 04, can be used, as the inspections provide an acceptable level of safety. We have added a new paragraph (p) to this AD to include the alternate inspections. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. These changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Average labor rate per hour Work hours Modification in AD 2006–04–06. Detailed inspection in AD 2006–04–06. General visual inspection (new action). Cost per airplane $1,120 ........................... 768 $860,160. $160, per inspection cycle. $80, per inspection cycle. 768 $122,880, per inspection cycle. $60,320, per inspection cycle. 14 $80 2 80 The manufacturer states that it will supply required parts to operators at no cost. None ............................. 1 80 None ............................. for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Authority for This Rulemaking jlentini on PROD1PC65 with RULES Currently, there are no affected Model A321–211 and –231 airplanes on the U.S. Register. However, if an affected airplane is imported and placed on the U.S. Register in the future, the required inspection would take about 1 work hour, at an average labor rate of $80 per work hour. Based on these figures, we estimate the cost of this AD to be $80 per airplane, per inspection cycle. We have 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 that this AD: (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 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 VerDate Aug<31>2005 17:40 Mar 11, 2008 Jkt 214001 Number of U.S.registered airplanes Parts Regulatory Findings PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 754 Fleet cost (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 AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\12MRR1.SGM 12MRR1 13086 § 39.13 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14487 (71 FR 8439, February 17, 2006) and adding the following new airworthiness directive (AD): I 2008–05–12 Airbus: Amendment 39–15406. Docket No. FAA–2006–25658; Directorate Identifier 2006–NM–054–AD. Effective Date (a) This AD becomes effective April 16, 2008. Affected ADs (b) This AD supersedes AD 2006–04–06. Applicability (c) This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A318–111, –112, –121, and –122 airplanes on which Airbus Modification 26495 has been incorporated in production. (2) All Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. Unsafe Condition (d) This AD results from reports of wear damage to the inboard flap trunnions after incorporation of the terminating modification. We are issuing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss of flap surface control and consequently result in the flap detaching from the airplane. A detached flap could result in damage to the tail of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. jlentini on PROD1PC65 with RULES Restatement of Requirements of AD 2006– 04–06 17:40 Mar 11, 2008 Jkt 214001 Detailed Inspections (g) For Model A318–111 and –112 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111 airplanes; Model A320– 211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, and –131 airplanes: At the latest of the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, do a detailed inspection of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and do any corrective actions, as applicable, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320– 57–1133, dated July 28, 2005; Revision 01, dated August 7, 2006; or Revision 03, dated July 3, 2007, except as provided by paragraph (n) of this AD. As of the effective date of this AD, only Revision 03 may be used. Any corrective actions must be done at the compliance times specified in Figures 5 and 6, as applicable, of the service bulletin; except as provided by paragraphs (k), (l), and (m) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,000 flight hours until the inspection required by paragraph (h) of this AD is done. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ (1) Before accumulating 4,000 total flight hours on the inboard flap trunnion since new. (2) Within 4,000 flight hours after accomplishing paragraph (f) of this AD. (3) Within 600 flight hours after March 24, 2006 (the effective date of AD 2006–04–06). New Requirements of This AD Modification (f) For Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, and –131 airplanes; except those on which Airbus Modification 26495 has been accomplished in production: Within 18 months after January 8, 2001 (the effective date of AD 2000–24–02, amendment 39–12009), modify the sliding panel driving mechanism of the flap drive trunnions, in accordance with Airbus Service Bulletin A320–27–1117, Revision 02, dated January 18, 2000; or Revision 04, dated November 6, 2001. As of the effective date of this AD, only Revision 04 may be used. Note 1: Accomplishment of the modification required by paragraph (f) of this AD before January 8, 2001, in accordance with Airbus Service Bulletin A320–27–1117, dated July 31, 1997; or Revision 01, dated VerDate Aug<31>2005 June 25, 1999; is acceptable for compliance with that paragraph. General Visual Inspections (h) For all airplanes: At the time specified in paragraph (h)(1) or (h)(2) of this AD, as applicable, do a general visual inspection of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and do all applicable corrective actions by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320– 57–1133, Revision 03, dated July 3, 2007; except as provided by paragraphs (i) and (o) of this AD. All corrective actions must be done at the compliance times specified in Figures 5 and 6, as applicable, of the service bulletin; except as provided by paragraphs (l), (m), and (n) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,000 flight hours. Accomplishing the general visual inspection required by this paragraph terminates the detailed inspection requirement of paragraph (g) of this AD. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Note 3: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (1) For airplanes on which the detailed inspection required by paragraph (g) of this AD has been done before the effective date of this AD: Inspect before accumulating 4,000 total flight hours on the inboard flap trunnion since new, or within 4,000 flight hours after accomplishing the most recent inspection required by paragraph (g) of this AD, whichever occurs later. (2) For airplanes other than those identified in paragraph (h)(1) of this AD: Inspect at the latest of the applicable times specified in paragraphs (h)(2)(i), (h)(2)(ii), and (h)(2)(iii) of this AD. (i) Before accumulating 4,000 total flight hours on the inboard flap trunnion since new. (ii) Within 4,000 flight hours after accomplishing paragraph (f) of this AD. (iii) Within 600 flight hours after the effective date of this AD. (i) Where Airbus Service Bulletin A320– 57–1133, Revision 03, dated July 3, 2007, specifies to contact the manufacturer for instructions on how to repair certain conditions: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its ´ ´ delegated agent), or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). Actions Done Using Previous Issues of Service Information (j) Accomplishing the modification required by paragraph (f) of this AD before the effective date of this AD, in accordance with Airbus Service Bulletin A320–27–1117, Revision 03, dated August 24, 2001, is acceptable for compliance with the requirements of that paragraph. (k) Accomplishing the inspections and corrective actions required by paragraphs (g) and (h) of this AD before the effective date of this AD, in accordance with Airbus Service Bulletin A320–57–1133, dated July 28, 2005; Revision 01, dated August 7, 2006; or Revision 02, dated December 12, 2006; is acceptable for compliance with the requirements of that paragraph. Compliance Times (l) Where Airbus Service Bulletin A320– 57–1133, Revision 03, dated July 3, 2007, specifies replacing the sliding panel at the next opportunity if damaged, replace it within 600 flight hours after the inspection required by paragraph (g) or (h) of this AD, as applicable. E:\FR\FM\12MRR1.SGM 12MRR1 13087 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations (m) If any damage to the trunnion is found during any inspection required by paragraph (g) or (h) of this AD, before further flight, do the corrective actions specified in Airbus Service Bulletin A320–57–1133, Revision 03, dated July 3, 2007. Grace Period Assessment (n) Where Airbus Service Bulletin A320– 57–1133, Revision 03, dated July 3, 2007, specifies contacting the manufacturer for a grace period assessment after replacing the trunnion or flap, contact the Manager, International Branch, ANM–116; or the ´ ´ Direction Generale de l’Aviation Civile (or its delegated agent) for the grace period assessment. No Reporting Requirement (o) Although Airbus Service Bulletin A320–57–1133, Revision 03, dated July 3, 2007, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternate Inspections (p) For Model A321–211 and –231 airplanes that have not been modified in accordance with Airbus Modification 26495, or on which the actions specified in Airbus Service Bulletin A320–27–1117, Revision 04, dated November 6, 2001, have not been done as of the effective date of this AD: Do the inspections specified in Airbus Service Bulletin A320–27–1108, Revision 04, dated November 22, 1999; at the applicable time specified in paragraph 1.E., ‘‘Compliance’’ of the service bulletin; except, where the service bulletin specifies a compliance time after the date of French airworthiness directive 96– 271–092(B), this AD requires compliance within the specified compliance time after the effective date of this AD. Do all applicable corrective actions before further flight. Do the actions in accordance with the Accomplishment Instructions of the service bulletin. Alternative Methods of Compliance (AMOCs) (q)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) AMOCs approved previously in accordance with AD 2006–04–06, amendment 39–14487, are approved as AMOCs for the corresponding provisions of this AD. (3) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (r) French airworthiness directive F–2005– 139, dated August 3, 2005, also addresses the subject of this AD. Material Incorporated by Reference (s) You must use the service information contained in Table 1 of this AD to do the actions required by this AD, unless the AD specifies otherwise. TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin No. Revision Date A320–27–1117 .................................................................................................................................. A320–27–1117 .................................................................................................................................. A320–57–1133, excluding Appendix 01 ........................................................................................... A320–57–1133 .................................................................................................................................. A320–57–1133, excluding Appendix 01 ........................................................................................... 02 ................................. 04 ................................. Original ......................... 01 ................................. 03 ................................. January 18, 2000. November 6, 2001. July 28, 2005. August 7, 2006. July 3, 2007. (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 2.—NEW MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin No. Revision jlentini on PROD1PC65 with RULES A320–27–1117 .................................................................................................................................................... A320–57–1133 .................................................................................................................................................... A320–57–1133, excluding Appendix 01 ............................................................................................................. (2) On March 24, 2006 (71 FR 8439, February 17, 2006), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320–57–1133, excluding Appendix 01, dated July 28, 2005. (3) On January 8, 2001 (65 FR 75603, December 4, 2000), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320–27–1117, Revision 02, dated January 18, 2000. (4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, VerDate Aug<31>2005 17:40 Mar 11, 2008 Jkt 214001 04 01 03 Date November 6, 2001. August 7, 2006. July 3, 2007. or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html. DEPARTMENT OF TRANSPORTATION Issued in Renton, Washington, on February 25, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–3989 Filed 3–11–08; 8:45 am] Federal Aviation Administration BILLING CODE 4910–13–P PO 00000 14 CFR Part 39 [Docket No. FAA–2007–27611; Directorate Identifier 2007–CE–024–AD; Amendment 39–15408; AD 2008–05–14] RIN 2120–AA64 Airworthiness Directives; Sierra Hotel Aero, Inc. Models Navion (L–17A), Navion A (L–17B), (L–17C), Navion B, Navion D, Navion E, Navion F, Navion G, and Navion H Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\12MRR1.SGM 12MRR1

Agencies

[Federal Register Volume 73, Number 49 (Wednesday, March 12, 2008)]
[Rules and Regulations]
[Pages 13084-13087]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-3989]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25658; Directorate Identifier 2006-NM-054-AD;
Amendment 39-15406; AD 2008-05-12]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A318, A319, A320, and A321
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing AD that applies to certain
Airbus Model A318, A319, A320, and A321 airplanes. That AD currently
requires repetitive detailed inspections of the inboard flap trunnions
for any wear marks and of the sliding panels for any cracking at the
long edges, and corrective actions if necessary. This new AD adds
airplanes that were recently added to the type certificate data sheet
and changes the inspection type. This AD results from reports of wear
damage to the inboard flap trunnions after incorporation of the
terminating modification. We are issuing this AD to detect and correct
wear of the inboard flap trunnions, which could lead to loss of flap
surface control and consequently result in the flap detaching from the
airplane. A detached flap could result in damage to the tail of the
airplane.

DATES: This AD becomes effective April 16, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 16,
2008.
On March 24, 2006 (71 FR 8439, February 17, 2006), the Director of
the Federal Register approved the incorporation by reference of Airbus
Service Bulletin A320-57-1133, excluding Appendix 01, dated July 28,
2005.
On January 8, 2001 (65 FR 75603, December 4, 2000), the Director of
the Federal Register approved the incorporation by reference of certain
other publications listed in the AD.

ADDRESSES: For service information identified in this AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA issued a second supplemental notice of proposed rulemaking
(NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD
2006-04-06, amendment 39-14487 (71 FR 8439, February 17, 2006). The
existing AD applies to certain Airbus Model A318, A319, A320, and A321
airplanes. That second supplemental NPRM was published in the Federal
Register on August 16, 2007 (72 FR 45982). That second supplemental
NPRM proposed to supersede an existing AD that currently requires
repetitive detailed inspections of the inboard flap trunnions for any
wear marks and of the sliding panels for any cracking at the long
edges, and corrective actions if necessary. That second supplemental
NPRM proposed to add airplanes that were recently added to the type
certificate data sheet and change the inspection type.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.

Request To Include Revised Service Information

Airbus asks that Airbus Service Bulletin A320-57-1133, Revision 03,
dated July 3, 2007, be incorporated into

[[Page 13085]]

the AD. (We referred to Revision 02, dated December 12, 2006, of that
service bulletin as the appropriate source of service information for
accomplishing certain actions specified in the second supplemental
NPRM.)
We agree with Airbus and have changed the applicable paragraphs in
this AD to refer to Revision 03 of Airbus Service Bulletin A320-57-1133
for accomplishing certain actions, as no additional work is required by
this revision. We have also changed paragraph (k) of this AD to give
credit to operators who have accomplished the actions in accordance
with Airbus Service Bulletin A320-57-1133, Revision 02, dated December
12, 2006, before the effective date of this AD.

Request To Include Inspections Removed From Second Supplemental NPRM

Under the ``Request to Remove Certain Requirements'' section of the
second supplemental NPRM, certain requirements were removed based on a
previous recommendation from Airbus. Regarding that recommendation,
Airbus notes that Model A321-211 and -231 airplanes that are pre-
modification 26495, and on which Airbus Service Bulletin A320-27-1117,
Revision 04, dated November 6, 2001, was not applied, should have
dedicated procedures included in the AD. Airbus states that the
inspections specified in Airbus Service Bulletin A320-27-1108, Revision
04, dated November 22, 1999, provide those procedures.
We agree with Airbus, although there are no U.S. operators of Model
A321-211 and -231 airplanes that are specified in the effectivity that
are pre-modification 26495. In the unlikely event that an operator has
an airplane configuration that is pre-modification 26495, or on which
Airbus Service Bulletin A320-27-1117 was applied, we have determined
that the alternative inspections specified in Airbus Service Bulletin
A320-27-1108, Revision 04, can be used, as the inspections provide an
acceptable level of safety. We have added a new paragraph (p) to this
AD to include the alternate inspections.

Conclusion

We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
These changes will neither increase the economic burden on any operator
nor increase the scope of the AD.

Costs of Compliance

The following table provides the estimated costs for U.S. operators
to comply with this AD.

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average Number of
Work labor U.S.-
Action hours rate per Parts Cost per airplane registered Fleet cost
hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification in AD 2006-04-06......... 14 $80 The manufacturer states $1,120.................. 768 $860,160.
that it will supply
required parts to
operators at no cost.
Detailed inspection in AD 2006-04-06.. 2 80 None..................... $160, per inspection 768 $122,880, per inspection
cycle. cycle.
General visual inspection (new action) 1 80 None..................... $80, per inspection 754 $60,320, per inspection
cycle. cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Currently, there are no affected Model A321-211 and -231 airplanes
on the U.S. Register. However, if an affected airplane is imported and
placed on the U.S. Register in the future, the required inspection
would take about 1 work hour, at an average labor rate of $80 per work
hour. Based on these figures, we estimate the cost of this AD to be $80
per airplane, per inspection cycle.

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 it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have 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 that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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.

[[Page 13086]]

Sec. 39.13 [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14487 (71 FR 8439, February 17, 2006) and adding
the following new airworthiness directive (AD):

2008-05-12 Airbus: Amendment 39-15406. Docket No. FAA-2006-25658;
Directorate Identifier 2006-NM-054-AD.

Effective Date

(a) This AD becomes effective April 16, 2008.

Affected ADs

(b) This AD supersedes AD 2006-04-06.

Applicability

(c) This AD applies to the airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes on
which Airbus Modification 26495 has been incorporated in production.
(2) All Airbus Model A319-111, -112, -113, -114, -115, -131, -
132, and -133 airplanes; Model A320-111 airplanes; Model A320-211, -
212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112,
-131, -211, -212, -213, -231, and -232 airplanes.

Unsafe Condition

(d) This AD results from reports of wear damage to the inboard
flap trunnions after incorporation of the terminating modification.
We are issuing this AD to detect and correct wear of the inboard
flap trunnions, which could lead to loss of flap surface control and
consequently result in the flap detaching from the airplane. A
detached flap could result in damage to the tail of the airplane.

Compliance

(e) 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 Requirements of AD 2006-04-06

Modification

(f) For Model A319-111, -112, -113, -114, -115, -131, -132, and
-133 airplanes; Model A320-111 airplanes; Model A320-211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, and -
131 airplanes; except those on which Airbus Modification 26495 has
been accomplished in production: Within 18 months after January 8,
2001 (the effective date of AD 2000-24-02, amendment 39-12009),
modify the sliding panel driving mechanism of the flap drive
trunnions, in accordance with Airbus Service Bulletin A320-27-1117,
Revision 02, dated January 18, 2000; or Revision 04, dated November
6, 2001. As of the effective date of this AD, only Revision 04 may
be used.

Note 1: Accomplishment of the modification required by paragraph
(f) of this AD before January 8, 2001, in accordance with Airbus
Service Bulletin A320-27-1117, dated July 31, 1997; or Revision 01,
dated June 25, 1999; is acceptable for compliance with that
paragraph.

Detailed Inspections

(g) For Model A318-111 and -112 airplanes; Model A319-111, -112,
-113, -114, -115, -131, -132, and -133 airplanes; Model A320-111
airplanes; Model A320-211, -212, -214, -231, -232, and -233
airplanes; and Model A321-111, -112, and -131 airplanes: At the
latest of the applicable times specified in paragraphs (g)(1),
(g)(2), and (g)(3) of this AD, do a detailed inspection of the
inboard flap trunnions for any wear marks and of the sliding panels
for any cracking at the long edges, and do any corrective actions,
as applicable, by accomplishing all of the applicable actions
specified in the Accomplishment Instructions of Airbus Service
Bulletin A320-57-1133, dated July 28, 2005; Revision 01, dated
August 7, 2006; or Revision 03, dated July 3, 2007, except as
provided by paragraph (n) of this AD. As of the effective date of
this AD, only Revision 03 may be used. Any corrective actions must
be done at the compliance times specified in Figures 5 and 6, as
applicable, of the service bulletin; except as provided by
paragraphs (k), (l), and (m) of this AD. Repeat the inspection
thereafter at intervals not to exceed 4,000 flight hours until the
inspection required by paragraph (h) of this AD is done.

Note 2: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''

(1) Before accumulating 4,000 total flight hours on the inboard
flap trunnion since new.
(2) Within 4,000 flight hours after accomplishing paragraph (f)
of this AD.
(3) Within 600 flight hours after March 24, 2006 (the effective
date of AD 2006-04-06).

New Requirements of This AD

General Visual Inspections

(h) For all airplanes: At the time specified in paragraph (h)(1)
or (h)(2) of this AD, as applicable, do a general visual inspection
of the inboard flap trunnions for any wear marks and of the sliding
panels for any cracking at the long edges, and do all applicable
corrective actions by accomplishing all of the applicable actions
specified in the Accomplishment Instructions of Airbus Service
Bulletin A320-57-1133, Revision 03, dated July 3, 2007; except as
provided by paragraphs (i) and (o) of this AD. All corrective
actions must be done at the compliance times specified in Figures 5
and 6, as applicable, of the service bulletin; except as provided by
paragraphs (l), (m), and (n) of this AD. Repeat the inspection
thereafter at intervals not to exceed 4,000 flight hours.
Accomplishing the general visual inspection required by this
paragraph terminates the detailed inspection requirement of
paragraph (g) of this AD.

Note 3: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''

(1) For airplanes on which the detailed inspection required by
paragraph (g) of this AD has been done before the effective date of
this AD: Inspect before accumulating 4,000 total flight hours on the
inboard flap trunnion since new, or within 4,000 flight hours after
accomplishing the most recent inspection required by paragraph (g)
of this AD, whichever occurs later.
(2) For airplanes other than those identified in paragraph
(h)(1) of this AD: Inspect at the latest of the applicable times
specified in paragraphs (h)(2)(i), (h)(2)(ii), and (h)(2)(iii) of
this AD.
(i) Before accumulating 4,000 total flight hours on the inboard
flap trunnion since new.
(ii) Within 4,000 flight hours after accomplishing paragraph (f)
of this AD.
(iii) Within 600 flight hours after the effective date of this
AD.
(i) Where Airbus Service Bulletin A320-57-1133, Revision 03,
dated July 3, 2007, specifies to contact the manufacturer for
instructions on how to repair certain conditions: Before further
flight, repair using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or its delegated agent), or
the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or
its delegated agent).

Actions Done Using Previous Issues of Service Information

(j) Accomplishing the modification required by paragraph (f) of
this AD before the effective date of this AD, in accordance with
Airbus Service Bulletin A320-27-1117, Revision 03, dated August 24,
2001, is acceptable for compliance with the requirements of that
paragraph.
(k) Accomplishing the inspections and corrective actions
required by paragraphs (g) and (h) of this AD before the effective
date of this AD, in accordance with Airbus Service Bulletin A320-57-
1133, dated July 28, 2005; Revision 01, dated August 7, 2006; or
Revision 02, dated December 12, 2006; is acceptable for compliance
with the requirements of that paragraph.

Compliance Times

(l) Where Airbus Service Bulletin A320-57-1133, Revision 03,
dated July 3, 2007, specifies replacing the sliding panel at the
next opportunity if damaged, replace it within 600 flight hours
after the inspection required by paragraph (g) or (h) of this AD, as
applicable.

[[Page 13087]]

(m) If any damage to the trunnion is found during any inspection
required by paragraph (g) or (h) of this AD, before further flight,
do the corrective actions specified in Airbus Service Bulletin A320-
57-1133, Revision 03, dated July 3, 2007.

Grace Period Assessment

(n) Where Airbus Service Bulletin A320-57-1133, Revision 03,
dated July 3, 2007, specifies contacting the manufacturer for a
grace period assessment after replacing the trunnion or flap,
contact the Manager, International Branch, ANM-116; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated agent)
for the grace period assessment.

No Reporting Requirement

(o) Although Airbus Service Bulletin A320-57-1133, Revision 03,
dated July 3, 2007, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.

Alternate Inspections

(p) For Model A321-211 and -231 airplanes that have not been
modified in accordance with Airbus Modification 26495, or on which
the actions specified in Airbus Service Bulletin A320-27-1117,
Revision 04, dated November 6, 2001, have not been done as of the
effective date of this AD: Do the inspections specified in Airbus
Service Bulletin A320-27-1108, Revision 04, dated November 22, 1999;
at the applicable time specified in paragraph 1.E., ``Compliance''
of the service bulletin; except, where the service bulletin
specifies a compliance time after the date of French airworthiness
directive 96-271-092(B), this AD requires compliance within the
specified compliance time after the effective date of this AD. Do
all applicable corrective actions before further flight. Do the
actions in accordance with the Accomplishment Instructions of the
service bulletin.

Alternative Methods of Compliance (AMOCs)

(q)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) AMOCs approved previously in accordance with AD 2006-04-06,
amendment 39-14487, are approved as AMOCs for the corresponding
provisions of this AD.
(3) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.

Related Information

(r) French airworthiness directive F-2005-139, dated August 3,
2005, also addresses the subject of this AD.

Material Incorporated by Reference

(s) You must use the service information contained in Table 1 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.

Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
Airbus Service Bulletin No. Revision Date
------------------------------------------------------------------------
A320-27-1117................. 02............. January 18, 2000.
A320-27-1117................. 04............. November 6, 2001.
A320-57-1133, excluding Original....... July 28, 2005.
Appendix 01.
A320-57-1133................. 01............. August 7, 2006.
A320-57-1133, excluding 03............. July 3, 2007.
Appendix 01.
------------------------------------------------------------------------

(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part
51.

Table 2.--New Material Incorporated by Reference
------------------------------------------------------------------------
Airbus Service Bulletin No. Revision Date
------------------------------------------------------------------------
A320-27-1117................... 04 November 6, 2001.
A320-57-1133................... 01 August 7, 2006.
A320-57-1133, excluding 03 July 3, 2007.
Appendix 01.
------------------------------------------------------------------------

(2) On March 24, 2006 (71 FR 8439, February 17, 2006), the
Director of the Federal Register approved the incorporation by
reference of Airbus Service Bulletin A320-57-1133, excluding
Appendix 01, dated July 28, 2005.
(3) On January 8, 2001 (65 FR 75603, December 4, 2000), the
Director of the Federal Register approved the incorporation by
reference of Airbus Service Bulletin A320-27-1117, Revision 02,
dated January 18, 2000.
(4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; or 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:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in Renton, Washington, on February 25, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-3989 Filed 3-11-08; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.